US Pat. No. 10,794,329

EXHAUST PLUME COOLING USING PERIODIC INTERRUPTION OF EXHAUST GAS FLOW TO FORM AMBIENT AIR ENTRAINING VORTICES

Lockheed Martin Corporati...

1. An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces, the device comprising:an injector supportable in a position adjacent an exhaust nozzle of an engine and aimed into an exhaust plume zone that is occupied by an exhaust plume when the engine is running, the injector being aimed upstream relative to the flow of the exhaust plume; and
a flow generator that is connected to and in fluid communication with the injector and generates and periodically transmits fluid flow through the injector into the exhaust plume zone at a rate and duty cycle that forms exhaust gas pulses that form vortical structures that entrain currents of ambient air.

US Pat. No. 10,794,328

THRUST REVERSER WITH BLOCKER DOOR FOLDING LINKAGE

Rohr, Inc., Chula Vista,...

1. An assembly for an aircraft propulsion system, comprising:a fixed structure;
a translating structure configured to move between a stowed position and a deployed position;
a blocker door pivotally attached to the translating structure at a first pivot joint; and
a folding linkage linking the blocker door to the fixed structure, the folding linkage comprising a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position;
wherein the second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.

US Pat. No. 10,794,327

SYSTEMS AND METHODS FOR THRUST REVERSER WITH TEMPERATURE AND FLUID MANAGEMENT

HONEYWELL INTERNATIONAL I...

1. A thrust reverser system for a gas turbine engine, comprising:a transcowl movable between a first, stowed position, a second, deployed position and a partially deployed position between the first, stowed position and the second, deployed position by at least one actuator, and in the partially deployed position the transcowl defines at least one opening;
a temperature sensor that observes a temperature associated with the thrust reverser system and generates temperature sensor signals based on the temperature observation;
at least one resistance sensor that observes a displacement of the transcowl and generates resistance sensor signals based on the displacement observation; and
a controller, having a processor, that:
outputs one or more control signals to the at least one actuator to move the transcowl to the partially deployed position;
receives and processes the temperature sensor signals to determine whether a temperature associated with the transcowl exceeds a temperature threshold;
based on the determination that the temperature is below the temperature threshold, outputs one or more control signals to the at least one actuator to move the transcowl from the partially deployed position to the first, stowed position;
receives and processes the resistance sensor signals from the at least one resistance sensor to determine whether the transcowl has encountered resistance; and
based on the determination that the transcowl has encountered resistance, outputs one or more control signals to the at least one actuator to stop a movement of the transcowl and outputs the one or more control signals to move the transcowl to the partially deployed position.

US Pat. No. 10,794,326

BLOCKER DOOR ASSEMBLY HAVING A THERMOPLASTIC BLOCKER DOOR FOR USE IN A TURBINE ENGINE

The Boeing Company, Chic...

1. A blocker door assembly for use in a gas turbine engine, said blocker door assembly comprising:a facesheet, wherein said facesheet comprises a plurality of openings to facilitate noise attenuation; and
a body portion coupled to said facesheet, wherein said body portion comprises a backsheet integrally formed with a honeycomb core, said body portion further comprises a plurality of mounting structures integrally formed with said backsheet and said honeycomb core, wherein said backsheet, said honeycomb core, and said mounting structures are co-molded from a thermoplastic material.

US Pat. No. 10,794,325

HEAT ENGINE WITH A DYNAMICALLY CONTROLLABLE HYDRAULIC OUTLET

1. A heat engine with a dynamically controlled outlet, driven by a high-pressure pump and a gas turbine comprising:a pressure vessel having an inner space,
a lid,
a movable partition,
a gas working space,
a liquid working space, and
a recuperator,
characterized in that:
a sealing is disposed between the pressure vessel and the lid, wherein in the inner space of the pressure vessel, the partition is movably attached to a folded membrane which is further attached to the lid,
wherein the partition divides the inner space of the pressure vessel into the gas working space and the liquid working space, wherein the gas working space occupies a larger area thereof, the gas working space being surrounded by a folded permeable membrane in the area of the first partition, and further, shaped parts are arranged within the pressure vessel, which define an external gas channel,
wherein the external gas working channel is led between a shell of the pressure vessel and the shaped parts,
a circumferential gas channel is located between the shaped parts and the folded membrane and further between a first permeable membrane and the partition,
wherein the gas working space is filled with a micro structure made of a solid material with porosity higher than 99% of its volume, and is surrounded by a second permeable membrane to which a recuperator is connected,
a heating exchanger being positioned within the recuperator and connected to an inlet and outlet of a heat transfer medium, wherein the recuperator is further surrounded by the shaped parts, and is separated from the gas working space by the second permeable membrane, the external gas channel is fed into space of the recuperator on the opposite side of its connection to the gas working space,
wherein the external gas channel is connected to a pneumatic actuator chamber, into which is further fed an inner gas channel, connected to the circumferential gas channel.

US Pat. No. 10,794,324

SPACER

UCHIYAMA MANUFACTURING CO...

1. A spacer formed of a resin molded body and used by being inserted into a coolant water flow path through an opening of the coolant water flow path, the coolant water flow path being formed around a plurality of cylinder bores formed adjacent to each other in a cylinder block of an internal combustion engine, comprising:a spacer body formed in a cylindrical shape to surround the plurality of cylinder bores; and
a protruding remaining portion remaining after removal of a portion necessary in molding and unnecessary after the molding, wherein
the spacer body comprises:
a stemming portion being formed on an inner peripheral portion of the spacer body, extending to intersect a flow direction of coolant water in the coolant water flow path and having an uppermost surface in an axial direction of the spacer body; and
at an upper end of the spacer body positioned on a side close to the opening, a flange portion protruding from an inner peripheral wall of the spacer body toward a bore wall of the cylinder bores and extending over the uppermost surface of the stemming portion, the remaining portion is formed at an uppermost surface of the flange portion in the axial direction, and
the remaining portion and the stemming portion are arranged in this order from upper to lower in the axial direction.

US Pat. No. 10,794,323

CONTROL SYSTEM FOR COMPRESSION-IGNITION ENGINE

Mazda Motor Corporation, ...

1. A control system for a compression-ignition engine including a cylinder, an intake passage, an exhaust passage, an intake port communicating the intake passage to the cylinder, an intake valve configured to open and close the intake port, an exhaust port communicating the exhaust passage to the cylinder, an exhaust valve configured to open and close the exhaust port, an injector configured to inject fuel into the cylinder, and a spark plug configured to ignite a mixture gas containing the fuel injected by the injector and air, the engine executing partial compression-ignition combustion in which the mixture gas is spark-ignited with the spark plug to be partially combusted by spark ignition (SI) combustion and the remaining mixture gas self-ignites to be combusted by compression ignition (CI) combustion, comprising:an intake phase-variable mechanism configured to simultaneously change an open timing and a close timing of the intake valve; and
a controller including a processor configured to control parts of the engine, including the intake phase-variable mechanism and the spark plug, wherein
the controller controls the intake phase-variable mechanism to form a gas-fuel ratio (G/F) lean environment in which burnt gas remains inside the cylinder and an air-fuel ratio that is a ratio of air to fuel inside the cylinder is near a stoichiometric air-fuel ratio, and controls the spark plug to spark-ignite the mixture gas so as to combust by the partial compression-ignition combustion at a given timing, and
the controller controls the intake phase-variable mechanism to retard, as an engine speed increases at a constant engine load, the close timing of the intake valve on a retarding side of a bottom dead center of intake stroke and the open timing of the intake valve on an advancing side of a top dead center of exhaust stroke, so that a rate of change in the open timing of the intake valve with respect to the engine speed in a high engine speed range is greater than that in a low engine speed range.

US Pat. No. 10,794,322

METHOD AND DEVICE FOR OPERATING AN INTERNAL COMBUSTION ENGINE

VITESCO TECHNOLOGIES GMBH...

1. A method for operating an internal combustion engine having at least two cylinders, the method comprising:determining a respective torque output of each of the at least two cylinders resulting from a respective injection of fuel into the respective cylinder;
determining a difference in the respective torque output;
comparing the difference in the respective torque output with a predetermined threshold value for the torque output;
determining a respective injection mass of the respective injection into the respective cylinder;
determining a difference in the respective injection masses;
comparing the difference in the injection masses with a predetermined threshold value for the injection mass;
if the determined differences in each case exceed the associated threshold value, determining whether the respective torque outputs correspond to the associated injection mass; and
if the respective torque outputs lie outside a predetermined tolerance range for a respective corresponding injection mass, changing an injection time in at least one of the at least two cylinders;
determining a second defect if, after a predetermined time interval, the further determined difference is not less than the predetermined threshold value for the torque output, wherein the second defect comprises at least one defect selected from the group consisting of: a defect in exhaust gas recirculation and a defect in compression.

US Pat. No. 10,794,321

ESTIMATION DEVICE AND CONTROL DEVICE FOR COMBUSTION SYSTEM

DENSO CORPORATION, Kariy...

1. A combustion system, comprising:an internal combustion engine including at least one fuel injector;
at least one sensor configured to detect a combustion characteristic value or a fuel characteristic value; and
a controller coupled to the sensor and the at least one fuel injector, the controller including a processor and a memory storing program instructions that when executed by the processor, cause the processor to:
estimate, based on the combustion characteristic value or the fuel characteristic value detected by at least the one sensor, a mixing ratio of various components contained in the fuel used for combustion in the internal combustion engine;
estimate, based on the mixing ratio, a main combustion region corresponding to a combustion region of the fuel for a main combustion produced by injecting the fuel into a combustion chamber of the internal combustion engine during a main injection;
estimate, based on the mixing ratio, an after combustion region corresponding to an injection region of the fuel for an after combustion produced by injecting the fuel into the combustion chamber during an after injection, the main injection and the after injection being defined as being performed during a same combustion cycle, the after injection being performed after the main injection; and
control at least an injection pressure of the at least one fuel injector based on a comparison between the estimated main combustion region and the estimated after combustion region.

US Pat. No. 10,794,320

METHODS AND SYSTEM FOR REDUCING PARTICULATE MATTER PRODUCED BY AN ENGINE

Ford Global Technologies,...

1. An engine fueling method, comprising:injecting fuel to a cylinder of an engine via a controller, a port fuel injector, and a direct fuel injector, the injection of fuel based on whether the engine is operated before a vehicle with the engine is delivered to a customer, an amount of fuel injected via the port fuel injector increased relative to an amount of fuel injected via the direct fuel injector prior to delivery of the vehicle to the customer as compared to after delivery of the vehicle to the customer during similar engine operating conditions.

US Pat. No. 10,794,319

METHOD FOR CALIBRATING A FUEL PUMP FOR AN INTERNAL COMBUSTION ENGINE

Vitesco Technologies GmbH...

1. A method for operating an internal combustion engine, in which fuel is supplied to the internal combustion engine, comprising the steps of:providing a rotating pump having a pressure side, the rotating pump having a rotational speed and a pump current;
providing a demand variable;
providing a calibration valve in fluid communication with the pressure side of the rotating pump;
providing a determination specification having a characteristic map;
providing a trigger pressure which actuates the calibration valve;
providing a predefined set of fixed values representing a plurality of rotational speeds of the rotating pump;
providing a plurality of calibration values obtained during the calibration;
changing the operating mode of the internal combustion engine to an overrun mode of operation;
performing a calibration including detecting and maintaining the rotational speed of the rotating pump, and detecting the pump current upon actuation of the calibration valve at the trigger pressure, such that the rotational speed of the rotating pump and the pump current of the rotating pump are part of the determination specification; and
controlling the rotational speed of the fuel pump and the pump current for feeding the fuel pump based on the demand variable and the determination specification;
changing the rotational speed of the rotating pump during the calibration, such that that rotational speed of the rotating pump corresponds to one of the predefined set of fixed values;
changing the rotational speed of the rotating pump during the calibration, such that that the rotational speed of the rotating pump corresponds to one of the predefined set of fixed values that has not already been determined in an earlier calibration measurement;
changing the operation of the internal combustion engine as a result of a change in the demand variable such that the internal combustion engine is no longer in the overrun mode of operation;
ending the calibration as a result of the internal combustion engine is no longer being in the overrun mode of operation;
determining to what extent the calibration has progressed;
assigning a weight to the plurality of calibration values.

US Pat. No. 10,794,318

METHOD AND APPARATUS FOR OPERATING AN EC-FUEL PUMP

VOLKSWAGEN AG, Wolfsburg...

1. A method for operating an electronically commutated fuel pump under control of an upstream fuel pump electronics unit of a motor vehicle to avoid a speed irregularity indicative of a malfunction of the fuel pump resulting from lack of synchronicity of a rotor of the fuel pump occurring when a ratio of consumed and fed power falls below a threshold value, wherein pulse-width modulation is used to control rotational frequency of a magnetic rotary field generated in a drive of the fuel pump, wherein the rotational frequency is controlled separately from a strength of the magnetic rotary field, which defines maximum mechanical power available at the fuel pump drive, the fuel pump being operated at a predefined speed corresponding to stable operation of the fuel pump, the method comprising:monitoring an operating speed of the fuel pump to determine a speed deviation from the predefined speed, wherein the speed deviation indicates the speed irregularity indicative of the malfunction of the fuel pump resulting from lack of synchronicity of the rotor of the fuel pump, wherein the speed deviation is determined by examination of the synchronicity between the magnetic rotary field and the rotor of the fuel pump using the magnetic rotary field generated by stator coils in the pump drive; and
in response to the determination that the speed deviation from the predefined speed exceeds a predefined value, implementing an increase of the operating speed of the upstream fuel pump using a pump electronics unit to re-establish stable operation of the fuel pump resulting from rotor synchronicity,
wherein the control of the increase of the operating speed is performed by the upstream fuel pump electronics unit in one step by a predefined speed jump or is performed at predefined speed steps, the speed being increased until stable operation of the fuel pump is re-achieved as determined based on the speed deviation determined based on the examination of the synchronicity between the magnetic rotary field and the rotor of the fuel pump using the magnetic rotary field generated by stator coils in the pump drive,
wherein the upstream fuel pump electronics unit controls the electronically commutated fuel pump based on the detection of the speed irregularity indicative of a malfunction of the fuel pump resulting from lack of synchronicity of a rotor of the fuel pump to cause recovery of the rotor by the rotary field, maintain the higher operating speed for a specified period of time such that the operation of the electronically commutated fuel pump under control of the upstream fuel pump electronics unit of the motor vehicle avoids the speed irregularity indicative of the malfunction of the fuel pump resulting from lack of synchronicity of the rotor of the fuel pump occurring when the ratio of consumed and fed power falls below the threshold value to reduce a risk of loss of synchronicity, and
wherein the method further comprises the upstream fuel pump electronics unit controlling the electronically commutated fuel pump to lower the operating speed of the electronically commutated fuel pump again after a predefined time once an operating speed value for stable operation has been reached.

US Pat. No. 10,794,317

CONTROL DEVICE FOR COMPRESSION-IGNITION ENGINE

Mazda Motor Corporation, ...

1. A control device for a compression-ignition engine in which partial compression-ignition combustion including spark ignition (SI) combustion performed by combusting a portion of a mixture gas inside a cylinder by spark-ignition followed by compression ignition (CI) combustion performed by causing the remaining mixture gas inside the cylinder to self-ignite is executed at least within a part of an operating range of the engine, comprising:a detector configured to detect a given parameter that changes as combustion progresses inside the cylinder;
an A/F (air-fuel ratio) controller configured to change an air-fuel ratio of air to fuel introduced into the cylinder; and
a combustion controller configured to determine combustion stability based on the detected parameter of the detector and control the A/F controller to reduce the air-fuel ratio when it is confirmed that during the partial compression-ignition combustion the combustion stability is low, wherein
the combustion controller identifies based on the detected parameter of the detector, a given mass combustion timing at which a given mass ratio of part of fuel supplied to the cylinder in one combustion cycle combusts, and determines the combustion stability based on the identified given mass combustion timing.

US Pat. No. 10,794,316

CONTROL SYSTEM FOR COMPRESSION IGNITION ENGINE

Mazda Motor Corporation, ...

1. A control system for a compression ignition engine, comprising:a combustion chamber of the engine defined by a cylinder, a piston configured to reciprocate inside the cylinder, and a cylinder head closing one end of the cylinder;
a throttle valve configured to adjust an amount of air filled up in the combustion chamber;
an injector attached to the cylinder head and configured to inject fuel to be supplied into the combustion chamber;
an ignition plug disposed so as to be oriented in the combustion chamber and configured to ignite mixture gas inside the combustion chamber;
a swirl control valve configured to generate a swirl flow inside the combustion chamber;
a sensor configured to measure a parameter related to an operation of the engine; and
a controller having a circuitry connected with the throttle valve, the injector, the ignition plug, the swirl control valve, and the sensor, configured to perform a calculation in response to a measurement signal from the sensor and output signals to the throttle valve, the injector, the ignition plug, and the swirl control valve,
wherein the controller is configured to execute a first mode module to operate the engine in a first mode, a second mode module to operate the engine in a second mode, and a changing module to change the mode from the first mode to the second mode in response to a change demand,
wherein the first mode module outputs the signals to the injector and the throttle valve so that a fuel amount becomes an amount according to a load of the engine and an air-fuel ratio of the mixture gas becomes a first air-fuel ratio, and outputs an ignition signal to the ignition plug so that a part of the mixture gas starts combustion accompanied by flame propagation due to a forcible ignition of the ignition plug, and remaining unburnt mixture gas then combusts by self-ignition,
wherein the second mode module outputs the signals to the injector and the throttle valve so that the fuel amount becomes the amount according to the load of the engine and the air-fuel ratio of the mixture gas becomes a second air-fuel ratio higher than the first air-fuel ratio, and outputs the ignition signal to the ignition plug so that a part of the mixture gas starts combustion accompanied by flame propagation due to a forcible ignition of the ignition plug, and remaining unburnt mixture gas then combusts by self-ignition,
wherein the changing module outputs the signals to the throttle valve and the injector in response to the change demand so that the air-fuel ratio of the mixture gas becomes a stoichiometric air-fuel ratio or a substantially stoichiometric air-fuel ratio, and outputs the signal to the swirl control valve so that the swirl flow becomes stronger than before the change demand, and
wherein when the swirl flow is determined to be reached a given strength, the changing module causes the second mode module to start the second mode.

US Pat. No. 10,794,315

METHOD FOR DIAGNOSING THE OPERATION OF A MOTOR VEHICLE DIESEL ENGINE INJECTOR

Continental Automotive Fr...

1. A method for diagnosing the operation of at least one injector of a diesel engine of a motor vehicle, said injector being controlled by at least one control law on the basis of at least one operating parameter of the injector, the method comprisingmeasuring a value of said operating parameter during use of said injector, and
determining an efficiency value of the injector on the basis of the measured value of the parameter and of a predetermined reference curve representing the efficiency of the parameter in its interval of operating values,
the injector being controlled by a plurality of control laws on the basis of at least one operating parameter of the injector, the at least one operating parameter of the injector being different for each of the control laws,
determining an efficiency value of each control law on the basis of the measured value of said at least one parameter of the respective control law and of a predetermined reference curve representing the efficiency of said parameter in its interval of operating values, and wherein the efficiency value of the injector is determined on the basis of the efficiency value of each of the control laws.

US Pat. No. 10,794,314

UNEQUAL INTERVAL COMBUSTION ENGINE MISFIRE DETERMINATION DEVICE AND VEHICLE

DENSO CORPORATION, Kariy...

1. An unequal interval combustion engine misfire determination device that determines a misfire in an unequal interval combustion engine including a plurality of cylinders in which combustion occurs at unequal intervals and a crankshaft, the determination being performed based on a crank angle signal indicating a rotation angle of the crankshaft, the unequal interval combustion engine misfire determination device comprising:an unequal interval combustion fluctuation canceled value acquisition unit that acquires an unequal interval combustion fluctuation canceled value in which a fluctuation component attributable to an unequal interval combustion is canceled, for every 720 crank angle degrees based on the crank angle signal while the unequal interval combustion engine is in operation, the unequal interval combustion fluctuation canceled value being a rotation speed in a section of 720×m crank angle degrees including a predetermined determination angle position, where m is a natural number;
an unequal interval combustion fluctuation manifested value calculation unit that calculates an unequal interval combustion fluctuation manifested value in which the fluctuation component attributable to the unequal interval combustion is manifested based on the crank angle signal while the unequal interval combustion engine is in operation, the calculation being performed by removing, from a rotation speed at the determination angle position, the unequal interval combustion fluctuation canceled value acquired by the unequal interval combustion fluctuation canceled value acquisition unit and being a rotation speed in a section of 720×m crank angle degrees including the determination angle position; and
a specific cylinder misfire determination unit that determines a misfire in a specific cylinder among the plurality of cylinders included in the unequal interval combustion engine, based on the unequal interval combustion fluctuation manifested value calculated by the unequal interval combustion fluctuation manifested value calculation unit while the unequal interval combustion engine is in operation, and a predetermined reference value pre-stored in the engine misfire determination device.

US Pat. No. 10,794,313

INTEGRATED IGNITION AND ELECTRONIC AUTO-CHOKE MODULE FOR AN INTERNAL COMBUSTION ENGINE

Kohler Co.

1. An electronic system for controlling a choke valve of an internal combustion engine, the electronic system comprising:a first temperature sensor configured to measure a first temperature indicative of an engine temperature;
a second temperature sensor configured to measure a second temperature indicative of an ambient air temperature;
an actuator operably coupled to the choke valve to adjust position of the choke valve to adjust a fuel-to-air ratio of a fuel mixture to be combusted in the internal combustion engine; and
a controller operably coupled to the actuator, the first temperature sensor, and the second temperature sensor, the controller configured to:
determine a starting position for the choke valve based on the first temperature;
operate the actuator to move the choke valve from an initial position to the starting position during a first choke opening stage;
determine a first ramp having a first characteristic that is dependent on the first and second temperatures; and
operate the actuator to move the choke valve toward a fully-open position during a second choke opening stage in accordance with the first ramp.

US Pat. No. 10,794,312

SYSTEMS AND METHODS FOR CONTROLLING FUEL VAPOR CANISTER PURGING OPERATIONS

Ford Global Technologies,...

1. A method comprising:reactivating one or more cylinders of an engine and duty cycling a canister vent valve positioned in a vent line that couples a fuel vapor storage canister to atmosphere while the fuel vapor storage canister positioned in an evaporative emissions control system of a vehicle is being purged of stored fuel vapors in response to an indication that purging of stored fuel vapors is compromised as a result of fuel vaporization stemming from a fuel tank positioned in a fuel system coupled to the evaporative emissions system.

US Pat. No. 10,794,311

METHOD FOR ADJUSTING A FUEL/AIR RATIO OF AN INTERNAL COMBUSTION ENGINE

Robert Bosch GmbH, Stutt...

1. A method for adjusting a fuel/air ratio of an internal combustion engine (10) which has an exhaust gas system (14) with a single catalyst having a catalyst volume (26) which is capable of storing an exhaust gas component, the method comprising:determining a first actual fill level of the exhaust gas component for a first catalyst partial volume (26.1) of the catalyst volume (26) from operating parameters of the internal combustion engine (10) and the exhaust gas system (14) with a calculation model, wherein the first catalyst partial volume (26.1) extends in a direction of an exhaust gas flow across a front region of the catalyst volume (26);
determining a second actual fill level of the exhaust gas component for a second catalyst partial volume (26.2) with the calculation model, wherein the second catalyst partial volume (26.2) extends downstream of the first catalyst partial volume (26.1) across a rear region of the catalyst volume (26);
adjusting the fuel/air ratio based on a deviation of the second actual fill level from a second setpoint value; and
adjusting the fuel/air ratio based on a deviation of the first actual fill level from a first setpoint value after adjusting the fuel/air ratio based on the deviation of the second actual fill level from the second setpoint value.

US Pat. No. 10,794,310

ENGINE CONTROL SYSTEM AND METHOD

HITACHI AUTOMOTIVE SYSTEM...

1. A system comprising:an engine including a piston mounted for reciprocating within a cylinder including a combustion chamber, the combustion chamber including an intake valve associated with an intake passage, an exhaust valve associated with an exhaust passage for receiving an exhaust gas from the combustion chamber, and a fuel injector positioned to inject fuel into air received into the combustion chamber through the intake passage for combustion in the combustion chamber;
one or more sensors for sensing one or more parameters of the engine;
one or more processors in communication with the one or more sensors;
one or more computer-readable media storing instructions which, when executed by the one or more processors, program the one or more processors to perform operations comprising:
receiving sensor data from the one or more sensors;
based on the sensor data, accessing a data structure for determining a homogeneity index indicative of a homogeneity of an air-fuel mixture within the combustion chamber at least during a transient engine operating condition, the data structure including one or more homogeneity index distributions having been determined in advance using a computer simulation of the engine;
determining an estimated amount of NOx in the exhaust gas due at least to the transient engine operating condition based at least on inputting the homogeneity index into a machine learning model trained to output an indication of the estimated amount of NOx in the exhaust gas based at least on the homogeneity index; and
controlling an engine component based at least partially on the estimated amount of NOx in the exhaust gas.

US Pat. No. 10,794,309

METHODS AND SYSTEMS FOR A PARTICULATE FILTER

Ford Global Technologies,...

1. A method comprising:manufacturing a particulate filter;
applying a hydrocarbon-containing composition onto at least a portion of the particulate filter;
arranging the particulate filter in an exhaust passage of a vehicle; and
adjusting engine operating parameters during a first combustion of an engine of the vehicle to incompletely oxidize the hydrocarbon-containing composition
wherein the incomplete oxidation includes an air/fuel ratio of greater than or equal to stoichiometric.

US Pat. No. 10,794,308

APPARATUS AND METHOD FOR CONTROLLING DEACTIVATION OF CYLINDERS IN ENGINE

Hyundai Motor Company, S...

1. An apparatus for controlling deactivation of cylinders in an engine, the apparatus comprising:a sensor configured to measure pressure inside an intake manifold of the engine;
an oil control valve (OCV) configured to deactivate the cylinders in the engine; and
a controller configured to control the OCV to deactivate a predetermined cylinder among the cylinders in the engine, based on the pressure inside the intake manifold,
wherein the controller is configured to:
set a plurality of reference ranges and a number of cylinders to be deactivated for each reference range of the plurality of reference ranges; and
determine a number of cylinders to be deactivated, based on a reference range in which the pressure inside the intake manifold is included,
wherein the controller is configured to determine an order in which all the cylinders in the engine are deactivated, to prevent the predetermined cylinder from being continually deactivated, and
wherein the controller is configured to periodically modify the order in which all the cylinders in the engine are deactivated.

US Pat. No. 10,794,307

CYLINDER DEACTIVATION FOR CATALYST DRYING

Cummins Inc., Columbus, ...

1. An engine control system, comprising:a sensor configured to measure a first unburned hydrocarbon mass quantity of unburned hydrocarbons accumulated on an exhaust after-treatment component; and
a controller operably coupled to the sensor, the controller configured to:
generate an exhaust condition signal based on a determined condition in the exhaust after-treatment component, the determined condition comprising the first unburned hydrocarbon mass quantity of unburned hydrocarbons measured by the sensor and an exhaust gas humidity level, the exhaust after-treatment component coupled to a first bank of cylinders of an engine,
cause transmission of a first bank control signal to cause the first bank of cylinders of the engine to deactivate at least in part based on: a) the exhaust gas humidity level, and b) in response to a determination based on the exhaust condition signal that the first unburned hydrocarbon mass quantity is above a pre-determined hydrocarbon mass quantity threshold, such that the deactivating of the first bank of cylinders causes evaporation of the unburned hydrocarbons accumulated on the exhaust after-treatment component; and
estimate an amount of hydrocarbons that have been purged from the exhaust after-treatment component based at least on an air flow rate and an air temperature through the deactivated first bank of cylinders.

US Pat. No. 10,794,306

EXHAUST TEMPERATURE MAINTENANCE USING A PARASITIC LOAD

Caterpillar Inc., Peoria...

1. A method for operating a machine, comprising:determining, by a controller, an exhaust temperature of an engine operatively connected to:
a parasitic load, and
one of a continuously variable transmission (CVT) or a hybrid transmission,
the parasitic load being operatively connected to an implement of the machine;
determining, by the controller, a target increase to the exhaust temperature of the engine based on the exhaust temperature of the engine failing to satisfy an exhaust temperature threshold;
determining, by the controller, a target increase to a torque output of the engine based on the target increase to the exhaust temperature of the engine,
the target increase to the torque output of the engine corresponding to a target implement power; and
causing, by the controller and based on the target increase to the torque output, a parasitic torque of the engine to be increased by increasing a stroke rate of the parasitic load,
the parasitic torque being increased without increasing a stroke rate of the engine.

US Pat. No. 10,794,305

VALVE DUTY DIFFERENTIATED EXHAUST GAS RECIRCULATION CONTROL METHOD AND EXHAUST GAS RECIRCULATION SYSTEM

Hyundai Motor Company, S...

1. An exhaust gas recirculation (EGR) system, comprising:a controller for implementing a valve duty differentiated control,
wherein the valve duty differentiated control:
detects an operation region to which acceleration is applied, a mixer region to which a ratio of an air-fuel is applied, and an external factor region to which a cooling water temperature, an air-lean environment condition, and a gear stage are applied as a valve control condition, respectively;
determining whether or not an EGR valve duty and the minimum EGR valve duty are applied; and
calculates an EGR valve duty, which is set by a target air amount to an intake air amount, by a minimum EGR valve duty depending upon the valve control condition and applying the calculated EGR valve duty for an EGR valve when the calculated minimum EGR valve duty is greater than the EGR valve duty.

US Pat. No. 10,794,304

METHOD AND SYSTEMS FOR EGR CONTROL

TRANSPORTATION IP HOLDING...

1. A method, comprising:with a controller, during a first mode of operation, estimating a first fresh intake air flow rate to an engine based on a volumetric efficiency estimation, the engine having an intake manifold to receive fresh intake air and an exhaust gas recirculation (EGR) system to supply EGR to the intake manifold, flow of EGR through the EGR system controlled by one or more exhaust valves; and
with the controller, during a second mode of operation, estimating a second fresh intake air flow rate to the engine based on a combination of a transient flow estimation and a steady state flow estimation, where the steady state flow estimation is selected from among a plurality of different steady state flow estimations, and the plurality of different steady state flow estimations differ in at least one or more inputs used to calculate each respective steady state flow estimation.

US Pat. No. 10,794,303

METHOD AND DEVICE FOR CONTROLLING A TURBOCHARGER

1. A method, comprising:determining a control reserve of an engine control of an internal combustion engine, wherein the engine control has a control range, a portion of the control range is used during normal operation of the internal combustion engine, and the control reserve comprises a remaining portion of the control range that is not intended to be used during normal operation of the internal combustion engine, wherein the control reserve decreases as a first portion of the control reserve is used to compensate for degradation of the internal combustion engine and a second portion of the control reserve is used to compensate for degradation of an air filter; and
adjusting a maximum permitted differential pressure of the air filter in an intake tract of the internal combustion engine as a function of the decreased control reserve.

US Pat. No. 10,794,302

METHODS OF KNOCK CONTROL

1. A method, comprising:controlling one or more parameters of each combustion chamber of a plurality of combustion chambers of an internal combustion engine to reduce knock, wherein the one or more parameters are controlled differently for the plurality of combustion chambers depending on a level of input from one or more knock sensors, wherein the one or more parameters comprise at least closure times of a plurality of intake valves associated with the plurality of combustion chambers, wherein controlling comprises:
identifying a knock condition associated with a combustion chamber of the plurality of combustion chambers based on the level of input from the one or more knock sensors; and
adjusting a closure time of an intake valve of the plurality of intake valves associated with the combustion chambers to reduce the knock condition, wherein the closure time is adjusted to be earlier when the intake valve controls an intake of air without a cooled exhaust gas, or the closure time is adjusted to be later when the intake valve controls an intake of the air with the cooled exhaust gas.

US Pat. No. 10,794,301

FUEL SUPPLY SYSTEM, INTERNAL COMBUSTION ENGINE SYSTEM, AND METHOD FOR SUPPLYING AN INTERNAL COMBUSTION ENGINE WITH AN LPG FUEL

Ford Global Technologies,...

1. A fuel supply system for an internal combustion engine, comprising:an LPG tank for storing an LPG fuel;
a direct injection unit, including a direct injection fuel distributor and direct injection valves supplied with fuel via said distributor, wherein the direct injection valves each have a closure part that rises outward from a valve seat to open the respective direct injection valve;
a booster pump coupled between the LPG tank and the direct injection fuel distributor, a discharge side of the booster pump directly coupled to the direct injection fuel distributor by at least one line;
a fuel tank for storing gasoline;
a port injection unit for injecting the gasoline into inlet ducts of the internal combustion engine;
a fuel switching valve having a switching state in which the LPG fuel is fed both to the direct injection unit and to the port injection unit; and
a pressure reducer inserted between the fuel switching valve and the port injection unit, and wherein the fuel switching valve and the pressure reducer are arranged on a suction side of the booster pump.

US Pat. No. 10,794,300

SYSTEM AND METHOD FOR VARIABLE COMPRESSION RATIO ENGINE

Ford Global Technologies,...

1. A method for an engine, comprising:maintaining a position of a control shaft for varying a compression ratio of an engine via braking force from a brake;
adjusting the braking force prior to and during actuation of the control shaft based on operating conditions; and
actuating the control shaft responsive to an upcoming transmission shift, a transmission shift schedule adjusted based on the braking force.

US Pat. No. 10,794,299

VARIABLE EXHAUST VALVE ASSEMBLY FOR VEHICLE

Hyundai Motor Company, S...

1. A variable exhaust valve assembly for a vehicle, comprising:an exhaust housing through which exhaust gas flows;
a power transmission device disposed apart from the exhaust housing and configured to transmit rotational power;
a shaft configured to receive the rotational power from the power transmission device, extending through and across the exhaust housing, and coupled with a valve provided inside the exhaust housing so as to open and close the exhaust housing according to a rotational position thereof; and
a heat shielding unit mounted on the shaft between the power transmission device and the exhaust housing and configured to block heat transfer so as to reduce heat transfer between the power transmission device and the exhaust housing,
wherein the exhaust housing is provided with a through hole through which the shaft passes,
wherein the heat shielding unit has a cover unit formed to cover a peripheral portion of the through hole in the exhaust housing in a state of being mounted on the shaft,
wherein the power transmission device is provided with a rotary shaft configured to transmit rotational power,
wherein the heat shielding unit is provided with a connection portion that extends from the cover unit and is coupled to the rotary shaft, and the connection portion is provided with a mounting groove, which is recessed such that the shaft is inserted thereinto,
wherein the connection portion of the heat shielding unit is provided with a first opening hole,
wherein the shaft is provided with a second opening hole that corresponds to the first opening hole in a state where the shaft is inserted into the mounting groove in the connection portion, and
wherein a fastening pin is inserted into the first opening hole and the second opening hole such that the heat shielding unit and the shaft are connected to each other.

US Pat. No. 10,794,298

ENGINE

KUBOTA Corporation, Osak...

1. An engine comprising:an exhaust manifold;
an exhaust lead-out path led out from a manifold exit of the exhaust manifold;
a catalyst case provided on the exhaust lead-out path; and
a catalyst housed in the catalyst case,
wherein, when a front-back direction is defined to be a direction in which a crankshaft is extended, the exhaust manifold and the catalyst case are both extended in the front-back direction and disposed side by side in a direction orthogonal to the front-back direction,the engine further comprising an exhaust throttle device provided on an exhaust downstream side of the catalyst;a main water path in which an engine body is water-cooled; and
a bypass water path bifurcated from the main water path,
wherein the bypass water path is connected with the exhaust throttle device,
the engine further comprising:
an EGR cooler; and
a pair of bypass water paths individually bifurcated from the main water path in which the engine body is water-cooled,
wherein the pair of bypass water paths are individually connected with the exhaust throttle device and the EGR cooler, respectively.

US Pat. No. 10,794,297

METHOD FOR OPERATING A GAS TURBINE INSTALLATION AND A GAS TURBINE INSTALLATION FOR CARRYING OUT THE METHOD

Siemens Aktiengsellschaft...

1. A method for operating a gas turbine installation at a compressor input temperature (Ti-ist) and an almost constant turbine input temperature (TiTiso), the method comprising:detecting the compressor input temperature (Ti-ist) is equal to or above a threshold temperature;
compensating for an increase of a calculated exhaust gas temperature (ATK) when the compressor input temperature (Ti-ist) is equal to or above the threshold temperature by effecting a reduced mass flow (m) of a flow medium which flows through a compressor of the gas turbine installation, by
measuring the compressor input temperature (Ti-ist);
comparing the compressor input temperature (Ti-ist) with a desired compressor input temperature (Ti-sol),
determining a difference between the compressor input temperature (Ti-ist) and the desired compressor input temperature (Ti-soll),
effecting the reduced mass flow of the flow medium in response to the difference by adjusting at least one guide vane of the compressor to a more closed position; and
wherein predetermined and stored value pairs (W1, W2, Wx) correlate a respective guide vane position (S) and a respective fuel quantity (n) for various compressor input temperatures (Ti-ist) equal to or above the threshold temperature, and wherein the adjustment moves the at least one guide vane to the respective guide vane position (S) associated with the compressor input temperature (Ti-ist).

US Pat. No. 10,794,296

GAS TURBINE COMBUSTOR AND METHOD OF OPERATING THE SAME

Mitsubishi Hitachi Power ...

1. A method of operating a gas turbine combustor which includes a pilot burner and a main burner arranged around an outer circumference of the pilot burner, the pilot burner being configured to be capable of performing an oil burning operation and a gas burning operation, and the main burner being configured to be capable of performing at least the gas burning operation,wherein upon switching of a combustion by the pilot burner from the oil burning operation to the gas burning operation, a gas fuel is supplied to the main burner to start the gas burning operation, and subsequent to starting the gas burning operation in the main burner the gas fuel is supplied to the pilot burner to start the gas burning operation in the pilot burner.

US Pat. No. 10,794,295

ENGINE BLEED SYSTEM WITH MULTI-TAP BLEED ARRAY

HAMILTON SUNSTRAND CORPOR...

4. An engine bleed control system for an aircraft, the engine bleed control system comprising:a gas turbine engine comprising a compressor section;
a multi-tap bleed array comprising a plurality of engine bleed taps distributed axially between a plurality of stages of the compressor section, wherein each stage of the plurality of stages comprises a rotor blade and stator vane pair, the plurality of engine bleed taps comprises at least four bleed taps, and the plurality of engine bleed taps is located before a ninth stage of the plurality of stages of the compressor section;
a plurality of valves configured to extract bleed air from each of the plurality of engine bleed taps;
a controller comprising a processor and memory programmed with a plurality of instructions to selectively open and close each of the plurality of valves based on a bleed air demand and control delivery of the bleed air to an aircraft use; and
a pneumatic bleed of the compressor section located downstream at a higher temperature point than the plurality of engine bleed taps, wherein the pneumatic bleed provides anti-icing to at least a nacelle inlet of the gas turbine engine responsive to execution of the plurality of instructions by the processor of the controller.

US Pat. No. 10,794,294

EFFICIENT JET

ROLLS-ROYCE plc, London ...

1. A gas turbine engine for an aircraft comprising:an engine core comprising a turbine system comprising one or more turbines, a compressor system comprising one or more compressors, and a core shaft connecting the turbine system to the compressor system, wherein a compressor exit pressure is defined as an average pressure of airflow at the exit of the highest pressure compressor of the compressor system at cruise conditions, the engine core further comprising an annular splitter at which flow is divided between a core flow that flows through the engine core, and a bypass flow that flows along a bypass duct, wherein stagnation streamlines around the circumference of the engine, stagnating on a leading edge of the annular splitter, form a streamsurface forming a radially outer boundary of a streamtube that contains all of the core flow;
a fan located upstream of the engine core, the fan comprising a plurality of fan blades extending from a hub, each fan blade having a leading edge and a trailing edge, each fan blade having a radially inner portion lying within the streamtube that contains the core flow, and wherein a fan root entry pressure is defined as an average pressure of airflow across the leading edge of the radially inner portion of each fan blade at cruise conditions; and
a nacelle surrounding the engine core, the nacelle defining the bypass duct and a bypass exhaust nozzle, wherein:
a compression stage number is defined as a number of compression stages provided by the fan and the compressor system combined, and wherein the compression stage number is 13 or 14;
an overall pressure ratio, OPR, is defined as the compressor exit pressure divided by the fan root entry pressure,
a bypass jet velocity (vjet) is defined as the jet velocity of air flow exiting the bypass exhaust nozzle at cruise conditions, and
a jet velocity to OPR ratio defined as:

is in a range between 4.7 m/s and 7.7 m/s; andan annular fan face is defined at a leading edge of the fan, anda quasi-non-dimensional mass flow rate Q is defined as:

where:
W is mass flow rate through the fan in Kg/s;
T0 is average stagnation temperature of the air at the fan face in Kelvin;
P0 is average stagnation pressure of the air at the fan face in Pa;
Afan is an area of the fan face in m2;
wherein at cruise conditions, Q has a value in the range between
0.031 Kgs?1N?1K1/2 and 0.036 Kgs?1N?1K1/2.

US Pat. No. 10,794,293

TURBINE SECTION OF HIGH BYPASS TURBOFAN

RAYTHEON TECHNOLOGIES COR...

1. A turbofan engine comprising:a fan including a fan rotor and a circumferential array of fan blades;
a compressor in fluid communication with the fan, the compressor including a four-stage second compressor section and a nine-stage first compressor section, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area;
a fan duct including a fan duct annulus area outboard of the second compressor section inlet, wherein the ratio of the fan duct annulus area to the second compressor section inlet annulus area defines a bypass area ratio between 8.0 and 20.0;
a combustor in fluid communication with the compressor;
a shaft assembly having a first portion and a second portion;
a turbine in fluid communication with the combustor, the turbine having a two-stage first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, the second turbine section being a four-stage turbine section, the second turbine section including blades and vanes, and a second turbine airfoil count defined as the numerical count of all of the blades and vanes in the second turbine section; and
a planetary gearbox coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine section to turn faster than the fan, the gearbox having a speed reduction ratio between 2:1 and 13:1 determined by the ratio of diameters within the gearbox, and wherein the planetary gearbox is intermediate the second compressor section and the second portion of the shaft assembly such that the fan rotor and the second compressor section are rotatable at a common speed;
wherein a ratio of the second turbine airfoil count to the bypass area ratio is less than 150, and
wherein the second turbine section further includes a maximum gas path radius and the fan blades include a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.55.

US Pat. No. 10,794,292

GEARED TURBOFAN GAS TURBINE ENGINE ARCHITECTURE

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine comprising:a fan including a plurality of fan blades rotatable about an axis, and a low fan pressure ration across the plurality of fan blades alone of less than 1.45;
a compressor section;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor, the turbine section including a fan drive turbine and a second turbine, wherein the second turbine is disposed forward of the fan drive turbine and the fan drive turbine includes a plurality of turbine rotors with a ratio between the number of fan blades and the number of fan drive turbine rotors is between 2.5 and 8.5; and
a speed change system configured to be driven by the fan drive turbine to rotate the fan about the axis at a different speed than the fan drive turbine;
wherein the fan drive turbine has a first exit area and rotates at a first speed, the second turbine section has a second exit area and rotates at a second speed, which is faster than the first speed, said first and second speeds being redline speeds, a first performance quantity is defined as the product of the first speed squared and the first area, a second performance quantity is defined as the product of the second speed squared and the second area, and a performance ratio of the first performance quantity to the second performance quantity is greater than 0.5, and the performance ration is less than or equal to 1.5.

US Pat. No. 10,794,291

GEARED TURBOFAN ARCHITECTURE FOR REGIONAL JET AIRCRAFT

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine comprising:a fan situated at an inlet of a bypass passage, the fan is a single-stage fan, the fan having fewer than 26 fan blades and an outer housing surrounding the fan to define the bypass passage;
a geared architecture;
a core engine configured to drive the fan, the core engine including:
a low pressure compressor section driven by a low pressure turbine section, wherein the low pressure turbine section drives the fan through the geared architecture; and
a high pressure compressor section driven by a high pressure turbine section;
wherein the gas turbine engine has a bypass ratio greater than 10, the fan has a fan diameter, Dfan, the high pressure compressor section has a compressor diameter, Dcomp, and the fan diameter Dfan and the compressor diameter Dcomp have an interdependence represented by a scalable ratio Dfan/Dcomp that is greater than 4.5; and
wherein the low pressure compressor section includes no more than three stages, the low pressure turbine section includes four stages, the high pressure turbine section includes two stages, and the high pressure compressor section includes eight stages.

US Pat. No. 10,794,290

INTERCOOLED COOLED COOLING INTEGRATED AIR CYCLE MACHINE

Raytheon Technologies Cor...

1. An intercooled cooling system for a gas turbine engine, the intercooled cooling system comprising:a plurality of cooling stages,
wherein a first cooling stage of the plurality of cooling stages is fluidly coupled to a bleed port of a compressor of the gas turbine engine to receive bleed air to produce a cool bleed air;
a cooling pump fluidly coupled to the first cooling stage to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air,
wherein a second cooling stage of the plurality of cooling stages is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air;
a delivery valve downstream of said second cooling stage, said delivery valve selectively delivering said intercooled cooling air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the bleed air, air from said mixing chamber being delivered to cool a turbine section on the gas turbine engine and said delivery valve also selectively supplying said intercooled cooling air to a use on an aircraft associated with the gas turbine engine without passing into said mixing chamber.

US Pat. No. 10,794,289

MODULATED TURBINE COMPONENT COOLING

General Electric Company,...

1. An airfoil for a gas turbine engine, the airfoil comprising: a body having a pressure side and a suction side, the body extending along a radial direction from an inner segment to an outer segment, the body defining a cavity for receipt of a flow of cooling fluid;a flow modulation insert positioned within the cavity, the flow modulation insert defining a first plurality of apertures permitting the cooling fluid to flow therethrough;
an attachment element that varies in position between a first position and a second position along the radial direction, the attachment element disposed outside the body radially outward from the outer segment; and
a cavity insert positioned within the cavity, wherein the flow modulation insert is surrounds the cavity insert, and wherein a space is defined between the flow modulation insert and the cavity insert,
wherein the flow modulation insert is coupled to the attachment element such that a location of the first plurality of apertures of the flow modulation insert is variable to modulate the flow of cooling fluid to the body.

US Pat. No. 10,794,288

COOLED COOLING AIR SYSTEM FOR A TURBOFAN ENGINE

Raytheon Technologies Cor...

1. A gas turbine engine comprising:a fan bypass duct defined between a fan nacelle and core cowl of an engine core;
the engine core including a cooled cooling air system configured to receive cooling air from a primary flowpath bleed within the engine core and configured to provide cooled cooling air to at least one component within the engine core, the cooled cooling air system further including a cold air modulator having a first position, a second position, and at least one intermediate position between the first and second positions;
the cooled cooling air system including an air-air heat exchanger; and
a controller controllably connected to the cold air modulator and configured to control a position of said cold air modulator based on at least one of an engine power and a combination of engine rotor speed and ambient temperatureengine operating condition.

US Pat. No. 10,794,287

MODULAR GAS TURBINE SYSTEM

NUOVO PIGNONE TECNOLOGIE ...

1. A modular gas turbine system, comprising:a base plate;
mounted on the base plate, a gas turbine engine having a rotation axis, a first air compressor section and a second air compressor section;
at least one rotating load, mechanically coupled to the gas turbine engine and mounted on the base plate;
a supporting frame extending above the base plate;
an air intercooler fluidly coupled to the first air compressor section and second air compressor section, the air intercooler configured and arranged to cool partly compressed air from the first air compressor section in heat exchange relationship with a heat removal fluid;
wherein a plurality of secondary coolers are arranged on the supporting frame above the base plate at a level above at least one of the gas turbine engine and the load, and are in fluid exchange relationship with the intercooler, the heat removal fluid being in heat exchange relationship with a cooling medium in the secondary coolers.

US Pat. No. 10,794,286

METHOD AND SYSTEM FOR MODULATED TURBINE COOLING AS A FUNCTION OF ENGINE HEALTH

General Electric Company,...

1. A modulated turbine cooling (MTC) control system comprising a processor in communication with a memory, wherein said processor is programmed to:determine a first cooling flow requirement of an engine component for each of a plurality of operating conditions comprising one or more flight conditions, wherein the flight conditions includes at least a takeoff condition, a climb condition, a cruise condition, and a descent condition;
channel the first cooling flow requirement to the engine component during each respective operating condition of the plurality of operating conditions;
assess a health of the engine component;
determine a second cooling flow requirement based on the first cooling flow requirement, the assessed health of the engine component, and the flight condition; and
supply the second cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.

US Pat. No. 10,794,285

GAS TURBINE AIR INJECTION SYSTEM CONTROL AND METHOD OF OPERATION

PowerPHASE LLC, Jupiter,...

1. A method of preheating an air injection system for a gas turbine engine comprising:operating the gas turbine engine;
opening all valves within the air injection system to at least a partially opened position;
directing a flow of compressed air from a compressor discharge region of the gas turbine engine to flow through a pipe of a piping portion and the valves of the air injection system;
discharging the flow of compressed air to an atmosphere through a silencer;
determining that a desired operating temperature for the pipe of the air injection system has been established; and,
terminating the flow of compressed air from the compressor discharge region of the gas turbine engine in response to the pipe desired operating temperature determination.

US Pat. No. 10,794,284

SEAL PLATE WITH FLUID BYPASS CONTROL

RAYTHEON TECHNOLOGIES COR...

1. A manifold assembly comprising:a first manifold including a plurality of exterior surfaces including a manifold top surface;
a first manifold channel and a second manifold channel, each extending between the manifold top surface and another of the plurality of exterior manifold surfaces;
the first manifold channel and the second manifold channel having a respective first channel opening and second channel opening in the manifold top surface;
a seal plate having a seal plate top surface and a seal plate bottom surface spaced from the seal plate top surface in a first direction, the first direction being an axial direction that defines a seal plate thickness;
the seal plate bottom surface disposed against the manifold top surface;
a first seal plate aperture and a second seal plate aperture extending through the seal plate in the axial direction;
the first seal plate aperture and the second seal plate aperture respectively aligned with the first channel opening and the second channel opening;
a seal plate channel extending in a second direction connecting the first seal plate aperture and the second seal plate aperture, wherein the second direction is perpendicular to the first direction;
the seal plate channel defining a fluid circuit between the first manifold channel and the second manifold channel; and
the seal plate channel narrowing in a third direction, whereby the seal plate channel is configured to control a flow characteristic of the fluid circuit, and wherein the third direction is perpendicular to the first direction and the second direction.

US Pat. No. 10,794,283

DAMPER CHECK VALVE

United Technologies Corpo...

1. A gas turbine engine comprising:a fan;
a compressor downstream of the fan;
a combustor downstream of the fan;
a turbine downstream of the fan;
a bypass duct downstream of the fan and radially outward of the compressor; and
a bearing compartment assembly comprising:
a fluid pump;
a compartment;
a fluid line extending between the fluid pump and the compartment; and
a damper check valve located in the fluid line, the damper check valve being
a unitary, monolithic component that is configured to restrict a reverse flow from the compartment to the fluid pump substantially more than the damper check valve restricts a standard flow from the fluid pump to the compartment, wherein the damper check valve comprises:
an inlet portion with a straight inner shape comprising a length and a diameter along the length, wherein the length is between one to five times the diameter of the straight inner shape;
a converging portion downstream of the inlet portion;
a diverging portion downstream of the converging portion, and a constriction between the converging portion and the diverging portion; wherein
the diverging portion comprises:
a full-width portion in contact with an interior of the fluid line; and
a reentrant protrusion downstream of the full-width portion that is spaced apart from the interior of the fluid line;
wherein the reentrant protrusion comprises:
 a protrusion length measured from a downstream end of the full-width portion to an exit diameter of the reentrant protrusion, and wherein the protrusion length is less than the length of the inlet portion.

US Pat. No. 10,794,282

INLET TURBINE FOR HIGH-MACH ENGINES

Rolls-Royce North America...

1. A high-mach engine comprisinga gas turbine core including a compressor, a combustor, and a turbine, and
an inlet assembly at an inlet of the high-mach engine and configured to selectively cool a portion of air that enters the gas turbine core when the high-mach engine is travelling at a speed greater than a predetermined speed coupled to the gas turbine core; the inlet assembly defining an inlet turbine passageway and an inlet bypass passageway coaxial with the inlet turbine passageway, wherein the inlet assembly includes an inlet turbine extending into the inlet turbine passageway and configured to be driven by the portion of air moving through the inlet turbine passageway thereby removing heat from the portion of air, a generator coupled to the inlet turbine to apply a load on the inlet turbine, the generator mechanically independent of the turbine of the gas turbine core, and a core-flow director translatable along a central engine axis from (i) an open position arranged to allow the portion of air from the inlet bypass passageway to move through the inlet bypass passageway and enter the gas turbine core without interacting with the inlet turbine to (ii) a closed position arranged to block the portion of air from moving through the inlet bypass passageway into the gas turbine core, forcing the portion of air moving toward the gas turbine core to move through the inlet turbine passageway and interact with the inlet turbine so that the portion of air entering the gas turbine core is cooled before interacting with components of the gas turbine core; and
wherein the inlet assembly comprises an opening that is arranged to allow at least a sub-portion of the portion of air to enter the inlet turbine passageway when the core flow director is in either of the open and closed positions.

US Pat. No. 10,794,281

GAS TURBINE ENGINE HAVING INSTRUMENTED AIRFLOW PATH COMPONENTS

General Electric Company,...

1. A gas turbine engine for an aircraft comprising:an outer casing located downstream of a fan defining an annular inlet, the outer casing encasing a compressor section, a combustion section, and a turbine section in series flow, the compressor section, the combustion section, and the turbine section defining an engine airflow path for the gas turbine engine, and the annular inlet providing a first pathway for a first portion of air to enter the engine airflow path;
a variable core inlet device located downstream of the annular inlet and upstream of the compressor section, the variable core inlet device defining a secondary airflow passage for a second portion of air to enter the engine airflow path;
one or more members extending at least partially into the engine airflow path of the compressor section of the gas turbine engine, the one or more members comprising one or more variable guide vanes located downstream of the annular inlet; and
one or more pressure sensor devices at least partially integrated into the one or more members extending at least partially into the engine airflow path, the one or more pressure sensor devices configured to obtain one or more measurements for determining a distortion condition for the gas turbine engine, the one or more pressure sensor devices configured to obtain the one or more measurements across two or more surfaces of a member of the one or more members;
wherein the one or more pressure sensor devices comprise one or more transducers; and
wherein the variable core inlet device is configured to open or close in response to the distortion condition.

US Pat. No. 10,794,280

AIR INTAKE FOR GAS TURBINE ENGINE

1. A gas turbine engine having an aircraft intake duct for an annular engine compressor inlet of the gas turbine engine, the annular engine compressor inlet having a compressor reference axis that is coaxial with a centerline of the engine and a reference plane extending from such compressor reference axis, the reference plane dividing the compressor inlet into a first side and an opposite second side, the aircraft intake duct comprising:an oblong air intake inlet located on the first side of the reference plane;
a top wall and a bottom wall extending downstream from such air intake inlet and being slanted towards one another to define a contracting central intake channel of the aircraft intake duct; and
two side walls extending downstream from such aft intake inlet and being slanted away from one another to define two distal intake channels of the aircraft intake duct, the two distal intake channels being located on each side of the central intake channel.

US Pat. No. 10,794,279

COMPRESSED AIR ENERGY STORAGE POWER GENERATION DEVICE

Kobe Steel, Ltd., Hyogo ...

1. A compressed air energy storage power generation device capable of accumulating renewable energy in a form of compressed air, generating power by using the compressed air as necessary, and supplying power to a consumer facility, comprising:a power demand receiving unit which receives a power demand value of the consumer facility;
a cold heat demand receiving unit which receives a cold heat demand value of the consumer facility;
an electric motor driven by power generated by use of the renewable energy;
a compressor driven by the electric motor;
a pressure accumulation unit which accumulates the compressed air compressed by the compressor;
an expander driven by the compressed air supplied from the pressure accumulation unit;
a power generator driven by the expander;
a power adjustment unit which adjusts the amount of power generated by the power generator;
a first heat exchanger which cools a first heat medium by exchanging heat between the first heat medium and cold air exhausted from the expander;
a first heat medium storage unit which stores as cold heat the first heat medium cooled in the first heat exchanger;
a cold heat adjustment unit which adjusts the supply amount of the cold heat from the first heat medium storage unit to the consumer facility; and
a control device which controls the power adjustment unit and the cold heat adjustment unit so as to supply the consumer facility with the power and the cold heat according to the power demand value received by the power demand receiving unit and the cold heat demand value received by the cold heat demand receiving unit.

US Pat. No. 10,794,278

COMPRESSED AIR STORAGE POWER GENERATION DEVICE

Kobe Steel, Ltd., Hyogo ...

1. A compressed air energy storage power generation device comprising:an electric motor to be driven by electric power generated by renewable energy;
a compressor configured to be driven by the electric motor and to compress air;
a pressure accumulator configured to store compressed air compressed by the compressor;
an expander to be driven by the compressed air to be supplied from the pressure accumulator;
a generator mechanically connected to the expander;
a first heat exchanger configured to perform heat exchange between the compressed air to be supplied from the compressor to the pressure accumulator and a first heating medium to cool the compressed air and to heat the first heating medium;
a first heat storage configured to store the first heating medium heated by the first heat exchanger;
a second heat exchanger configured to perform heat exchange between the compressed air to be supplied from the pressure accumulator to the expander and the first heating medium to be supplied from the first heat storage to heat the compressed air and to cool the first heating medium;
a third heat exchanger configured to perform heat exchange between air exhausted from the expander and a second heating medium to heat the air and to cool the second heating medium; and
a fourth heat exchanger configured to perform heat exchange between the second heating medium cooled by the third heat exchanger and at least one of lubricating oil to be supplied to the compressor and the first heating medium to be supplied to the first heat exchanger to heat the second heating medium and to cool the lubricating oil and/or the first heating medium.

US Pat. No. 10,794,277

THERMAL STORAGE SYSTEM CHARGING

Aestus Energy Storage, LL...

1. An energy storage system, comprising:a turbo train drive in mechanical communication with a compressor and an expander;
a hot heat sink in thermal communication between an output of the compressor and an input of the expander;
a reservoir in thermal communication between an output of the expander and an input of the compressor;
a first bottoming cycle positioned between an output of the hot heat sink and the input of the expander; and
a second bottoming cycle positioned between an output of the reservoir and the input of the compressor,
wherein the compressor and the expander, via the turbo train drive, are operable between a charging function for charging the hot heat sink and a discharging function for discharging the hot heat sink.

US Pat. No. 10,794,276

ENERGY STORAGE VIA THERMAL RESERVOIRS AND AIR TURBINES

KARL BROTZMANN CONSULTING...

1. A process to store energy through conversion into thermal energy and subsequent power generation by means of:a gas turbine set with compressor, gas turbine and power generator,
with at least a first and a second low-temperature reservoirs, and
a high-temperature reservoir with bulk material as the heat storage medium;
wherein the process comprising:
electric energy is stored in the form of high-temperature heat, at a temperature higher than a gas turbine outlet temperature in a high-temperature reservoir, that during a power generation phase a compressed gas from the compressor is heated in the at least the first and the second low-temperature reservoirs to a temperature near the gas turbine outlet temperature and then heated in the high-temperature reservoir with stored heat from the gas turbine outlet temperature which is temperature of the gas at an inlet of the high temperature reservoir to a temperature level of at least a gas turbine inlet temperature of the gas and that a ratio between a bed height in flow direction and a mean particle diameter of the bulk material in the high-temperature reservoir is at least 10, and
at end of a discharge phase, before the gas turbine comes to a standstill, a first pair of valves or second pair of valves, are closed in such a manner that the high-temperature reservoir, the at least the first and the second low-temperature reservoirs and the gas turbine are remaining near operating pressure.

US Pat. No. 10,794,275

MULTI-CIRCUIT BUFFER SYSTEM FOR A GAS TURBINE ENGINE

RAYTHEON TECHNOLOGIES COR...

1. A gas turbine engine, comprising:a shaft;
a first bearing structure and a second bearing structure that support said shaft, wherein each of said first bearing structure and said second bearing structure includes a bearing compartment that contains a lubricant and a seal that contains said lubricant within said bearing compartment; and
a buffer system that pressurizes said seals to prevent said lubricant from escaping said bearing compartments, said buffer system including a first circuit that supplies a first buffer supply air to said first bearing structure, a second circuit that supplies a second buffer supply air to said second bearing structure, and a controller programmed with logic for selecting between at least two bleed air supplies to communicate said first buffer supply air and said second buffer supply air;
wherein said at least two bleed air supplies includes first, second, third and fourth bleed air supplies, and wherein said controller is programmed to select either said first bleed air supply or said second bleed air supply as the first buffer supply air, and is programmed to select either said third bleed air supply or said fourth bleed air supply as the second buffer supply air;
wherein: said first circuit includes a first valve coupled to said first and said second bleed air supplies, and said controller is programmed to switch said first valve between said first and said second bleed air supplies; and said second circuit includes a second valve coupled to said third and said fourth bleed air supplies, and said controller is programmed to switch said second valve between said third and said fourth bleed air supplies.

US Pat. No. 10,794,274

GAS TURBINE FACILITY WITH SUPERCRITICAL FLUID “CO2” RECIRCULATION

8 RIVERS CAPITAL, LLC, D...

1. A gas turbine facility, comprising:a combustor combusting fuel and oxidant;
a turbine rotated by combustion gas exhausted from the combustor;
a heat exchanger cooling the combustion gas exhausted from the turbine;
a water vapor remover removing water vapor from the combustion gas which passed through the heat exchanger to regenerate dry working gas therefrom;
a compressor compressing the dry working gas until it becomes supercritical fluid;
a combustor introduction pipe guiding a part of the supercritical fluid exhausted from the compressor to the combustor via the heat exchanger;a pump configured to pressurize the dry working gas;an exhaust pipe branched from the combustor introduction pipe on an upstream side of the heat exchanger to exhaust a part of the dry working gas flowing through the combustor introduction pipe to the outside; and
a bypass pipe introducing a remaining part of the supercritical fluid exhausted from the compressor into a pipe coupling extending from an outlet of the turbine to an inlet of the heat exchanger.

US Pat. No. 10,794,273

ADVANCED DISTRIBUTED ENGINE ARCHITECTURE-DESIGN ALTERNATIVE

Raytheon Technologies Cor...

1. A gas turbine engine, comprising:a first compressor and a first turbine for driving the first compressor;
a core section including a second compressor and a second turbine for driving the second compressor;
a third turbine arranged fluidly downstream of the first turbine and the second turbine and configured to drive a power take-off; and
a first duct system arranged fluidly between the first compressor and the core section, the first duct system arranged to reverse fluid flow before entry into the core section, wherein the first compressor is configured to receive a working fluid flowing in an axially aft direction, the second compressor is configured to receive the working fluid flowing in an axially forward direction opposite the axially aft direction, and the first compressor is directly joined to the first duct system;
a combustor; and
a centrifugal compressor arranged fluidly between the second compressor and the combustor, wherein the combustor is a reverse flow combustor.

US Pat. No. 10,794,272

AXIAL AND CENTRIFUGAL COMPRESSOR

General Electric Company,...

1. A turbine engine comprising:a compressor section comprising a compressor, the compressor comprising an axial compressor stage, a variable outlet guide vane, and a centrifugal compressor stage, the variable outlet guide vane positioned between the axial compressor stage and the centrifugal compressor stage;
a bleed assembly comprising a bleed airflow duct in airflow communication with the compressor and a bleed valve operable with the bleed airflow duct, the bleed valve comprising a bleed valve actuator; and
a linkage assembly coupling the bleed valve actuator with the variable outlet guide vane such that that variable outlet guide vane is moveable with the bleed valve.

US Pat. No. 10,794,271

ALTITUDE AUGMENTATION SYSTEM

Rolls-Royce North America...

1. An augmented thrust system, wherein a prime power engine of an aircraft is configured to provide a first thrust for the aircraft, the augmented thrust system comprising:a tank of compressed gas; and
a turbine and/or a nozzle configured to generate a second thrust by a flow of the compressed gas released from the tank and exhausted from the turbine and/or the nozzle in a direction opposite the second thrust,
the augmented thrust system configured to supplement the first thrust with the second thrust, and
wherein the augmented thrust system is configured to supplement the first thrust with the second thrust to exceed a maximum sustained climb of the aircraft.

US Pat. No. 10,794,270

CONNECTING ROD FOR AN INTERNAL COMBUSTION ENGINE WITH VARIABLE COMPRESSION

ECO Holding 1 GmbH, Mark...

1. A connecting rod for an internal combustion engine with variable compression, the connecting rod comprising:an eccentrical element adjustment arrangement configured to adjust an effective connecting rod length,
wherein the eccentrical element adjustment arrangement includes an eccentrical element that cooperates with an eccentrical element lever and supports rods that engage the eccentrical element lever, and
wherein the eccentrical element lever is integrally configured in one piece as a stamped and bent component or fabricated by a massive cold forming method,
wherein the eccentrical element lever includes joint receivers that are engageable by ball joints of the support rods,
wherein the joint receivers are configured as an embossing in the eccentrical element lever,
wherein a connecting rod bearing eye and the eccentrical element include first portions with first face contours,
wherein the eccentrical element lever envelops the eccentrical element exclusively in the first portions of the eccentrical element
wherein the first portions of the eccentrical element are arranged on both axial sides of the eccentrical element with respect to an eccentrical element rotation axis and extend over half or less of a circumference of the eccentrical element.

US Pat. No. 10,794,269

TURBOCHARGER UNIT

VOLVO TRUCK CORPORATION, ...

18. A turbocharger unit comprising:a bearing housing having at least one through hole for fastening the turbocharger unit to a cylinder block of an internal combustion engine via an engine structure, the engine structure having
at least one through hole for fastening the turbocharger unit to the cylinder block via the engine structure such that the engine structure is positioned in between the turbocharger unit and the cylinder block; and
at least one fluid channel extending in a bent manner from a first surface of the engine structure to a second surface of the engine structure,
wherein the first surface is configured to bear on the cylinder block, and the second surface is configured to bear on the turbocharger unit, wherein the at least one through hole is configured for receiving a fastener insertable through an opening of the turbocharger unit, such that the fastener is further engaging with an aligned bore of the cylinder block, wherein the engine structure is configured for releasably connecting to the turbocharger unit, and wherein at least one of a fluid inlet and a fluid outlet comprises a dam,
wherein at least one through hole extends to a back side of the bearing housing facing at least one of the engine structure and the cylinder block, and wherein the bearing housing comprises a depression at least partly surrounding one through hole.

US Pat. No. 10,794,268

POWERING A SUPERCHARGER FOR A HYBRID ELECTRIC POWERTRAIN

FORD GLOBAL TECHNOLOGIES,...

1. A hybrid vehicle comprising:an engine configured to rotate driven wheels of the vehicle;
a motor on a common shaft with the engine and configured to also rotate the driven wheels, wherein the common shaft is powered by at least one of the engine and motor;
a supercharger configured to provide forced induction to the engine;
a mechanical connection configured to transfer torque from the common shaft to the supercharger, wherein the supercharger is a single torque load on the mechanical connection;
a first clutch between the engine and motor;
a second clutch between the motor and supercharger.

US Pat. No. 10,794,267

SYSTEM FOR CORRECTING TURBO LAG

Hyundai Motor Company, S...

1. A system for correcting turbo lag of a diesel engine vehicle equipped with a turbo charger and a vacuum pump, the system comprising:a chamber comprising a top wall and a bottom wall connected by side walls, the chamber having an interior space formed by the top wall, the bottom wall, and the side walls, the chamber to be supplied with an air/oil mixture discharged from the vacuum pump, to separate the air/oil mixture into air and oil and to store the air and the oil within the interior space of the chamber, wherein the chamber includes a first valve for spraying the air and a second valve for discharging the oil and wherein the bottom wall is inclined downward from the side walls to a specific point on the bottom wall such that the oil separated by the chamber can collect at the specific point;
an accelerator pedal sensor configured to sense a depression extent of an accelerator pedal of the vehicle;
a first pressure sensor configured to sense pressure of the air compressed in the chamber; and
a controller configured to control the first valve in accordance with the depression extent of the accelerator pedal sensed by the accelerator pedal sensor.

US Pat. No. 10,794,266

SYSTEM FOR COOLING ENGINE INTAKE FLOW

AI ALPINE US BIDCO INC, ...

1. A system comprising:an air source;
an internal combustion engine;
a first turbocharger including a first turbine and a first compressor;
a second turbocharger including a second turbine and a second compressor; and
a third turbocharger including a third turbine and a third compressor, the third turbine configured to receive compressed air from the second compressor, wherein the third compressor is fluidly coupled to the air source, the third compressor is fluidly coupled upstream of at least one of the first compressor or the second compressor, the first compressor is fluidly coupled upstream of the second compressor, the second compressor configured to receive compressed air from the first compressor, the second compressor is fluidly coupled upstream of the third turbine, and the third turbine is fluidly coupled upstream of the internal combustion engine;
wherein when the compressed air discharged from the second compressor is at a nominal operation point with a maximum expansion ratio of the third turbine, the compressed air discharged from the second compressor is at a pressure higher than a required pressure in an intake manifold.

US Pat. No. 10,794,265

VENTING TANK AND AUTOMOTIVE VEHICLE COMPRISING SUCH A TANK

ILLINOIS TOOL WORKS INC.,...

1. A venting tank (1) for a cooling system of an automotive vehicle, the venting tank (1) comprising:a main wall (3), which defines an inner venting volume (V) of the venting tank, the main wall comprising a bottom (5) and a cover (7) opposite one another,
an intake (45, 47, 49, 51, 53) for a heat transfer fluid to be vented within the inner venting volume,
a discharge (55, 57) for discharging the vented heat transfer fluid from the inner venting volume, and
a heat transfer fluid duct (19), which crosses through the cover (7) and the bottom (5) and comprises an inner segment (29) extending within the inner venting volume (V) from the cover (7) to the bottom (5);
and whereof an inner volume (V29) of the inner segment is separated from the inner venting volume;
wherein the intake provides a first fluid path from the inner segment to the inner venting volume (V);
wherein the discharge provides a second fluid path from the inner venting volume to the heat transfer fluid duct (19), wherein the second fluid path is separate from the first fluid path; and
wherein the inner segment is configured to form a bypass inside the venting tank so that only a fraction of the heat transfer fluid is conducted into the inner venting volume of the venting tank to be degassed, and a bypass fraction of the heat transfer fluid passes through the bypass without being degassed.

US Pat. No. 10,794,264

COOLANT TANK

TOYOTA JIDOSHA KABUSHIKI ...

1. A coolant tank comprising:a tank main body configured to store a coolant discharged from a processing machine;
a vortex flow generator that creates a vortex flow of the coolant in the tank main body; and
a float configured to float on a liquid surface of the coolant stored in the tank main body and move on the liquid surface due to the vortex flow of the coolant to collide with an inner peripheral wall surface of the tank main body.

US Pat. No. 10,794,263

THERMOSTAT FOR ENGINE COOLING SYSTEM

Hyundai Motor Company, S...

1. A thermostat for an engine cooling system, comprising:a housing comprising a radiator-side flowing-in inlet for receiving coolant flowing from a radiator, a bypass-side flowing-in inlet for receiving the coolant bypassed from an engine, and a coolant flowing-out outlet for discharging the coolant to the engine;
a wax chamber disposed in the housing; and
a main valve provided in the housing, wherein the main valve is configured to be open for allowing the coolant received through the radiator-side flowing-in inlet to the coolant flowing-out outlet, and further configured to be closed for blocking the coolant from the radiator-side flowing-in inlet from flowing to the coolant flowing-out outlet, wherein the main valve is configured to be opened and closed by a change of the volume of wax contained the wax chamber,
wherein the main valve is configured to move in a first direction to be opened for allowing the coolant received through the radiator-side flowing-in inlet to flow out through the coolant flowing-out outlet, and the coolant from the radiator-side flowing-in inlet is configured to press the main valve in a second direction which is opposite to the first direction.

US Pat. No. 10,794,262

INTEGRATED FLOW RATE CONTROL VALVE ASSEMBLY AND ENGINE COOLING SYSTEM INCLUDING THE SAME

Hyundai Motor Company, S...

1. An integrated flow rate control valve assembly connected to an engine of a vehicle, comprising;a housing;
a plurality of valve rooms formed in the housing and separated by partition walls; and
a plurality of rotary valves, each of which is provided in a corresponding one of the plurality of valve rooms,
wherein each of the plurality of valve rooms is not in fluid communication with the other valve rooms.

US Pat. No. 10,794,261

COOLING MODULE

DENSO CORPORATION, Kariy...

1. A cooling module applied to a vehicle having a blower arranged on a front side in a vehicle traveling direction with respect to a driving engine in a front engine compartment, comprising:a duct having a first opening portion and a second opening portion so as to form an air flow between the first opening portion and the second opening portion, wherein the first opening portion opens to the front side in the vehicle traveling direction with respect to the driving engine in the front engine compartment and the second opening portion opens to an object to be cooled in the front engine compartment other than the driving engine,
wherein in the duct the air flow blown out from the blower after being sucked into the blower from the driving engine side rather than the blower is pushed into the first opening portion and the pushed air flow is blown out from the second opening portion to the object to be cooled.

US Pat. No. 10,794,260

COOLANT PUMP FOR VEHICLE, COOLING SYSTEM PROVIDED WITH THE SAME AND CONTROL METHOD FOR THE SAME

Hyundai Motor Company, S...

1. A coolant pump for a vehicle, the coolant pump comprising:an impeller mounted at a first side of a shaft and configured for pumping a coolant;
a pulley mounted at a second side of the shaft and configured for receiving a torque to rotate the shaft;
a pump housing enclosing the impeller and including an outlet for the coolant to flow out therethrough;
an inflow portion including a first inlet and a second inlet configured for receiving coolant;
a slider slidably mounted on the shaft and slidable along a longitudinal direction of the shaft, the slider including:
a first closing portion selectively opening the outlet to fluidically-connect the first inlet to the outlet; and
a second closing portion selectively opening the second inlet to fluidically-connect the second inlet to the outlet; and
a driver configured for moving the slider.

US Pat. No. 10,794,259

METHOD AND APPARATUS FOR COOLING THE IMPULSE MECHANISM OF A VIBRATORY DEVICE

Astec Industries, Inc., ...

1. An impulse mechanism for a vibratory device comprising:(a) an eccentrically weighted shaft having an eccentrically weighted drive shaft that is supported by bearings and that is adapted to be rotated to create vibratory forces;
(b) a fan component that is mounted on the eccentrically weighted shaft, said fan component having a plurality of fan blades spaced around its periphery that curve radially around a portion of the shaft when the fan component is mounted on the shaft, wherein the fan component is combined with a drive sheave component to form a unitary structure comprising a combination drive sheave and fan having a motor side;
(c) a drive belt that is operatively attached to the sheave component of the combination drive sheave and fan;
(d) a wheel case having a wheel case side cover that encloses the bearings supporting the eccentrically weighted drive shaft, wherein the fan component of the combination drive sheave and fan is adapted to direct air across an outer surface of the wheel case side cover as the eccentrically weighted drive shaft is rotated:
(e) a guard that is mounted to the outside of the wheel case and that is adapted to enclose the combination drive sheave and fan and is adapted to channel air moved by the fan blades of the combination drive sheave and fan across a lower portion of the wheel case side cover and then upwardly across the wheel case side cover and to accelerate the air moved by the fan blades of the combination drive sheave and fan to improve the convection heat transfer from the surface of the wheel case, the guard comprising:
an enclosure that is adapted to protect the combination drive sheave and fan from impact by materials being processed by the vibratory device;
a guard side cover for the enclosure that is generally parallel to the wheel case side cover, said guard side cover having an opening that allows outside air to be drawn into the guard by the rotation of the combination drive sheave and fan;
a closed end of the enclosure spaced away from the combination drive sheave and fan;
a top wall for the enclosure which is provided with a plurality of air outlets; and
curved ducting that wraps around the motor side of the combination drive sheave and fan and slopes downwardly from the top of combination drive sheave and fan towards the closed end of the enclosure, which curved ducting has a plurality of upper air outlets near an end of the guard away from combination drive sheave and fan so that air is drawn into the guard by rotation of the combination drive sheave and fan and directed to flow across the outer surface of the lower portion of the side cover of the wheel case and then upwardly across the side cover through the upper outlets in the curved ducting and through the air outlets in the top wall of the enclosure after passing across the upper portion of the side cover for the wheel case.

US Pat. No. 10,794,258

EXHAUST PIPE STRUCTURE FOR IN-LINE FOUR-CYLINDER INTERNAL COMBUSTION ENGINE

HONDA MOTOR CO., LTD., T...

1. An exhaust pipe structure for an in-line four-cylinder internal combustion engine, comprising:an in-line four-cylinder internal combustion engine;
four exhaust pipes connected with respective exhaust ports in respective cylinders of the internal combustion engine; and
a converging exhaust pipe connected with a converging portion at which downstream ends of all the exhaust pipes converge, wherein
the exhaust pipes are each configured as a dual pipe including an outer pipe and an inner pipe disposed inside the outer pipe, and
at the converging portion, the four exhaust pipes are arrayed linearly in parallel with each other, and the outer pipes of adjacent ones of the exhaust pipes are directly welded with each other at the downstream ends.

US Pat. No. 10,794,257

AUTONOMOUS AUXILIARY DEF SUPPLY SYSTEM WITH PURGE CONTROL

Multiquip Inc., Cypress,...

1. An autonomous auxiliary diesel exhaust fluid (DEF) supply system for supplying DEF to an onboard DEF tank in a diesel engine, comprising:an auxiliary DEF tank;
an auxiliary DEF supply line configured for fluid communication between the auxiliary DEF tank and the onboard DEF tank;
a pump configured to force DEF through the auxiliary DEF supply line; and
a controller electrically coupled to the pump;
wherein the controller is configured to command the pump responsive to DEF level signals received from an engine control module of the diesel engine;
wherein the controller is configured to execute a routine encoded in software for calculating onboard DEF tank volume; and
wherein the routine executed by the controller comprises:
receiving a low DEF level signal from the engine control module that indicates a low level of DEF in the onboard DEF tank;
running the pump for a single fill cycle selected to deliver to the onboard DEF tank a volume of DEF that is less than a total volume of the onboard DEF tank;
receiving an actual DEF level signal from the engine control module that indicates a higher level of DEF in the onboard DEF tank; and
calculating the total volume of the onboard DEF tank based on the low level of DEF, the delivered volume of DEF, and the higher level of DEF.

US Pat. No. 10,794,256

CONTROL OF AFTERTREATMENT OF AN INTERNAL COMBUSTION ENGINE

JAGUAR LAND ROVER LIMITED...

1. An apparatus for controlling an aftertreatment system of an internal combustion engine, the apparatus comprising an electronic processor having an electrical input and an electronic memory device electrically coupled to the electronic processor and having instructions stored therein, the electrical processor being configured to:receive a first signal from a first temperature sensor, the first signal being indicative of a first temperature of exhaust gases outputted from an internal combustion engine at a first location upstream of a first exhaust system component configured to provide a passage for exhaust gases;
receive a second signal from a flow rate sensor, the second signal being indicative of a flow rate of the exhaust gases outputted from the engine;
calculate an approximated value at least from the first signal and the second signal, the approximated value being indicative of a second temperature of exhaust gases at a location downstream of the first exhaust system component;
provide an output signal to control the aftertreatment system, based on the calculated approximated value;
access the memory device and execute the instructions stored therein such that it is operable to receive the first and second signals and calculate the approximated value indicative of the second temperature;
receive a third signal indicative of a third temperature of exhaust gases downstream of a further exhaust system component, the further exhaust system component being arranged downstream of the first exhaust system component; and
calculate a correction of the approximated value based at least in part on the third signal.

US Pat. No. 10,794,255

APPARATUS FOR UTILIZING WASTE HEAT OF AN INTERNAL COMBUSTION ENGINE

GF CASTING SOLUTIONS AG, ...

1. An apparatus for utilizing waste heat of an internal combustion engine, the apparatus comprising:an exhaust gas manifold;
a cooling element, the cooling element being a casting that is separate from the exhaust gas manifold, the casting having at least one cooling passage in an interior thereof configured to provide for throughflow of a fluid; and
a thermoelectric element configured to generate an electric voltage as a result of a temperature difference between a side of the thermoelectric element facing away from the exhaust gas manifold and an opposite side of the thermoelectric element facing the exhaust gas manifold,
wherein the thermoelectric element is arranged on the exhaust gas manifold, and
wherein the cooling element is arranged on the side of the thermoelectric element en facing away from the exhaust gas manifold.

US Pat. No. 10,794,254

UREA INJECTION CONTROL METHOD IN EXHAUST AFTERTREATMENT SYSTEM

HYUNDAI MOTOR COMPANY, S...

1. A urea injection control method in an exhaust after-treatment system having a selective catalytic reduction (SCR) catalyst, a filter located upstream of the SCR catalyst, a dosing module injecting urea to the SCR catalyst, and a dosing control unit controlling the dosing module, the method comprising:performing an ammonia slip prevention logic that adjusts a urea injection amount based on a predetermined temperature during a predetermined period of time from an end point of filter regeneration to a thermal equilibrium point when a temperature of the SCR catalyst is higher than or equal to a predetermined threshold temperature at the end point of the filter regeneration; and
adjusting the urea injection amount based on an ammonia storage amount map when the temperature of the SCR catalyst is lower than or equal to the predetermined threshold temperature at the end point of the filter regeneration,
wherein:
the thermal equilibrium point is a point at which a temperature of the filter is close or equal to an exhaust gas temperature,
the filter is a diesel particulate filter with SCR coating (SDPF),
the ammonia storage amount map includes map data, in which an ammonia storage amount is defined based on an inlet temperature of the SDPF, an inlet temperature of the SCR catalyst, a model temperature of the SDPF, a model temperature of the SCR catalyst, and a representative model temperature,
the model temperature of the SDPF is a substrate temperature of the SDPF which is calculated based on the inlet temperature of the SDPF,
the model temperature of the SCR catalyst is a substrate temperature of the SCR catalyst which is calculated based on the inlet temperature of the SCR catalyst, and
the representative model temperature is calculated by applying a correction value to an average value of the model temperature of the SDPF and the model temperature of the SCR catalyst.

US Pat. No. 10,794,253

ENGINE AND COOLANT SYSTEM CONTROL SYSTEMS AND METHODS

GM GLOBAL TECHNOLOGY OPER...

1. A coolant control system of a vehicle comprising:a coolant pump that pumps coolant to a second radiator that is different than a first radiator that receives coolant from an engine of the vehicle;
a diesel exhaust fluid (DEF) injector that injects a DEF into an exhaust system of the vehicle and that receives coolant output from the second radiator;
a fuel heat exchanger that receives fuel flowing from a fuel rail to a fuel tank of the vehicle, that receives coolant output from the DEF injector, and that transfers heat between coolant flowing through the fuel heat exchanger and fuel flowing through the fuel heat exchanger, wherein the coolant pump receives coolant output from the fuel heat exchanger; and
an engine control module (ECM) configured to:
determine a temperature of the DEF injector;
determine a vaporized condition of the coolant based on the DEF injector temperature; and
control the coolant pump based on the determined vaporized condition of the coolant.

US Pat. No. 10,794,252

DIRECT SPRAY EXHAUST MIXER SYSTEM

Faurecia Emissions Contro...

1. A mixer for a vehicle exhaust system comprising:an outer housing defining an exhaust gas flow path, wherein the outer housing includes an inlet opening and an outlet opening; and
a distribution pipe configured to deliver a reduction fluid directly into the exhaust gas flow path, wherein the distribution pipe has an inlet end associated with the inlet opening and an outlet end associated with the outlet opening, and wherein the distribution pipe comprises a fluid flow path that is coiled about a center of the exhaust gas flow path.

US Pat. No. 10,794,251

FUEL APPORTIONMENT STRATEGY FOR IN-CYLINDER DOSING

Caterpillar Inc., Peoria...

1. An engine comprising:a plurality of combustion chambers each having a piston reciprocally movable therein to perform a combustion cycle;
an aftertreatment device disposed in an exhaust system communicating with the plurality of combustion chambers;
a plurality of injectors disposed one each in the plurality of combustion chambers to introduce a total regeneration quantity of dosing fuel for regenerating the aftertreatment device;
a controller communicating with the plurality of injectors and configured to calculate a temporal dosing window occurring after an exhaust valve of a combustion chamber opens during the combustion cycle to limit combustion of the dosing fuel and to apportion the total regeneration quantity of dosing fuel into a first plurality of dosing shots; the controller further configured to calculate a per cylinder quantity of dosing fuel based on the total regeneration quantity of dosing fuel and a total number of the plurality of combustion chambers, the controller further configured to compare the first plurality of dosing shots to the temporal dosing window and dosing the first plurality of dosing shots if the comparison determines the first plurality of dosing shots fits the temporal dosing window; the controller further adjusts a number of the first plurality of dosing shots to calculate a second plurality of dosing shots based on the comparison by reducing one shot from the first plurality of dosing shots if the first plurality of dosing shots does not fit the temporal dosing window, and the controller further reapportions the per cylinder quantity among the second plurality of dosing shots.

US Pat. No. 10,794,250

ELECTROCHEMICAL REACTOR AND INTERNAL COMBUSTION ENGINE PROVIDED WITH ELECTROCHEMICAL REACTOR

TOYOTA JIDOSHA KABUSHIKI ...

1. An electrochemical reactor comprising:a proton conductive solid electrolyte layer;
an anode layer arranged on a surface of the solid electrolyte layer, the anode layer configured to hold water molecules;
a cathode layer arranged on a surface of the solid electrolyte layer; and
a controller controlling a current flowing through the anode layer and the cathode layer,
wherein the controller is configured to determine an amount of the water molecules held within the anode, and based on the amount of the water molecules held by the anode layer, the controller is configured to reduce the current flowing through the anode layer and the cathode layer, when the water molecules held in the anode layer become smaller in amount.

US Pat. No. 10,794,249

EXHAUST GAS PURIFICATION APPARATUS FOR INTERNAL COMBUSTION ENGINE AND CONTROL APPARATUS FOR INTERNAL COMBUSTION ENGINE

TOYOTA JIDOSHA KABUSHIKI ...

1. An exhaust gas purification apparatus for an internal combustion engine comprising:a particulate filter arranged in an exhaust passage of the internal combustion engine, and configured to support a catalyst having an oxidizing capacity and an oxygen storage capacity; and
a controller comprising at least one processor configured to
estimate the oxygen storage capacity of the catalyst,
obtain, as a correlation between a reference value of an intramural PM deposition amount, which is an amount of deposition of particulate matter in an interior of a partition wall of the particulate filter, and the oxygen storage capacity of the catalyst, a change over time of the oxygen storage capacity of the catalyst according to a change of a filter PM deposition amount, which is an amount of deposition of particulate matter in the particulate filter, in a period of time from a point in time at which the filter PM deposition amount is substantially zero to a point in time at which the oxygen storage capacity of the catalyst, which becomes larger according to an increase of the filter PM deposition amount, reaches a maximum value, and
estimate a current value of the intramural PM deposition amount based on a current value of the oxygen storage capacity of the catalyst and the correlation, after the correlation is obtained.

US Pat. No. 10,794,248

EXHAUST GAS PURIFYING APPARATUS OF VEHICLE

Hyundai Motor Company, S...

1. An exhaust gas purifying apparatus for a vehicle comprising:a turbocharger having a turbine which rotates by exhaust gas flowing from an engine into an inlet of the turbine;
a filter connected to an outlet of the turbine at an inlet of the filter and allowing the exhaust gas passing through the turbine to flow into the filter; and
a gasket disposed between the outlet of the turbine and the inlet of the filter to maintain airtightness between the turbine and the filter,
wherein a portion of the gasket is exposed toward the turbine or toward the filter.

US Pat. No. 10,794,247

CONTROLLER AND CONTROL METHOD FOR INTERNAL COMBUSTION ENGINE

TOYOTA JIDOSHA KABUSHIKI ...

1. A controller for an internal combustion engine, the controller being configured to control an internal combustion engine that is mounted on a vehicle and includes a filter configured to trap particulate matter in exhaust gas discharged from a plurality of cylinders and fuel injection valves provided for the respective cylinders, the controller comprising a processor being configured to execute:when an execution request for a regeneration process of the filter is made, a dither control process of operating the fuel injection valves such that:
at least one of the cylinders is a lean combustion cylinder in which an air-fuel ratio is leaner than a stoichiometric air-fuel ratio, and
at least another one of the cylinders is a rich combustion cylinder in which an air-fuel ratio is richer than the stoichiometric air-fuel ratio; and
a deposition amount calculating process of calculating a deposition amount, which is an amount of particulate matter trapped by the filter, such that,
as compared to a case in which a target value of an average value of an exhaust air-fuel ratio in a predetermined period by the dither control process is a first air-fuel ratio, a decrease amount per unit time of the deposition amount is calculated to be a greater value in a case in which the target value is a second air-fuel ratio, which is leaner than the first air-fuel ratio.

US Pat. No. 10,794,246

HEAT-EXCHANGE AND NOISE-REDUCTION PANEL FOR A PROPULSION ASSEMBLY

SAFRAN AIRCRAFT ENGINES, ...

1. A heat-exchange and noise-reduction panel for a propulsion assembly, the panel comprising:a perforated plate comprising a plurality of through-openings;
a cellular structure comprising structural walls which are longitudinally oriented and which are covered directly by said perforated plate, wherein each of said structural walls extends substantially perpendicularly to the perforated plate, wherein each of said structural walls comprises a first end and a second end opposed to said first end, wherein the first end is thickened and flared in a cross section,
said cellular structure further comprising cavities which are located between said structural walls, and which define Helmholtz resonators,
said plurality of through-openings forming necks of said resonators; and
fluid circulation channels formed at least in part directly into a thickness of the first end of said structural walls, on a same side as said perforated plate.

US Pat. No. 10,794,245

DEVICE FOR THE VENTILATION OF A CRANKCASE OF AN INTERNAL COMBUSTION ENGINE

Bayerische Motoren Werke ...

1. An internal combustion engine, comprising:an engine block having a crankcase, at least one cylinder and a crankcase ventilation line;
a cylinder head arranged on the engine block over the at least one cylinder and connected to at least one intake line;
a compressor arranged to compress air in the at least one intake line;
a regulating valve in the crankcase ventilation line inside one or both of the engine block and the cylinder head, the regulating valve having a crankcase ventilation line inlet configured to receive crankcase vapors from the crankcase, a first regulating valve outlet separate from the crankcase ventilation line inlet from which a branching point extends, separate from the crankcase ventilation line inlet, to at least one first connection point on the intake line downstream of the compressor, and a second regulating valve outlet separate from the crankcase ventilation line inlet from which a separate line branch branches to at least one second connection point upstream of the compressor; and
a non-return valve arranged in the line branch between the regulating valve and the at least one second connection point to prevent flow from the at least one second connection point to the branching point,
wherein
the crankcase is fluidly connected to the at least one intake line via the crankcase ventilation line, and
the crankcase ventilation line is arranged substantially entirely inside one or both of the engine block and the cylinder head.

US Pat. No. 10,794,244

METHOD AND SYSTEM FOR CRANKCASE VENTILATION MONITOR

Ford Global Technologies,...

1. An engine method, comprising:following each of a first set of qualifying pedal transients of a drive cycle, updating a minimum and maximum value of crankcase pressure;following each of a second set of qualifying pedal transients of the drive cycle, learning a pressure difference between a last updated minimum and maximum value of crankcase pressure; andindicating degradation in crankcase ventilation based on an average pressure difference over the second set.

US Pat. No. 10,794,243

LUBRICATION STRUCTURE OF INTERNAL COMBUSTION ENGINE

SUZUKI MOTOR CORPORATION,...

1. A lubrication structure of an internal combustion engine, comprising: a crank chamber having a crankshaft provided therein; a transmission chamber arranged adjacently at the rear of the crank chamber and having a transmission mechanism provided therein; an oil chamber configured to communicate with a bottom part of the transmission chamber; a feed pump configured to supply oil in the oil chamber to a lubrication target part; and a scavenging pump configured to suck the oil accumulated in the crank chamber and to discharge the oil to the transmission chamber, wherein the feed pump and the scavenging pump are arranged coaxially in a width direction of the internal combustion engine, in which a rotary shaft of the crankshaft extends, wherein at least a part of the scavenging pump is arranged at a position higher than a lower end of the crank chamber, and wherein a rear end of the scavenging pump is arranged at the same position as a rear end of the crank chamber or in front of the rear end of the crank chamber in a front and rear direction, wherein the lubrication structure further comprises a first oil passage extending from the oil chamber toward an oil strainer, and a second oil passage extending from the oil strainer toward the feed pump, wherein the first oil passage and the second oil passage extend in the width direction, passing through a position adjacent to the scavenging pump, and wherein a part of the oil strainer overlaps with the scavenging pump, as seen from a side in the width direction, the lubrication structure of the internal combustion engine further comprising a crankcase in which the crank chamber and the transmission chamber are formed, wherein the scavenging pump is provided at one side of the crankcase and the oil strainer is provided at another side of the crankcase such that the part of the oil strainer overlaps with the scavenging pump, as seen from the side in the width direction.

US Pat. No. 10,794,242

DEVICE FOR CONTROLLING AT LEAST ONE VALVE IN AN INTERNAL COMBUSTION ENGINE

VOLVO TRUCK CORPORATION, ...

1. A gas valve actuation device for an internal combustion engine, the gas valve actuation device comprising:a first actuation means for actuating two gas valves in a first lift even;
a second actuation means for selectively actuating a first gas valve of the two gas valves in a second lift event;
a fluid circuit configured to control the actuating of the first gas valve during the second lift event,
wherein the fluid circuit comprises a first fluid circuit valve controlled by the first actuation means such that the first fluid circuit valve is closed only during the first lift event, for creating conditions for achieving an exact positioning of the second actuation means in an engaged state of the second actuation means.

US Pat. No. 10,794,241

REDUCED-WEIGHT VALUE SPRING COLLAR

Dr. Ing. h.c. F. Porsche ...

1. A valve spring collar for supporting spring forces of closing springs that act on gas exchange valves in a valve actuation means of internal combustion engines, comprising:a tubular wall having opposite top and bottom ends and defining a through opening extending between the top and bottom ends for leading through and attaching a valve stem of the gas exchange valve;
a main body having an outwardly extending plate-shaped portion aligned transverse to the tubular wall; and
at least one cavity formed in the main body, the at least one cavity having a closed top and an open bottom.

US Pat. No. 10,794,240

INTERNAL COMBUSTION ENGINE AND STRADDLED VEHICLE HAVING THE SAME

YAMAHA HATSUDOKI KABUSHIK...

1. An internal combustion engine comprising:a cylinder head provided with a port having an opening that is open toward a combustion chamber;
a cylindrical valve guide disposed in the cylinder head;
a valve having a valve stem end and a valve body end opposite to the valve stem end, the valve being configured to open and close the opening of the port, the valve including
a valve stem extending straight from the valve stem end and slidably inserted into the valve guide, and
a valve body provided at the valve body end of the valve and located inside the opening of the port;
a first valve spring seat supported by the cylinder head;
a second valve spring seat supported by the valve stem end of the valve;
a valve spring, which is a compression coil spring, placed between the first valve spring seat and the second valve spring seat and supported by the first valve spring seat and the second valve spring seat;
a valve lifter disposed on the valve stem end; and
a cam configured to periodically push the valve lifter as the cam rotates, wherein:
the valve spring includes an array of elemental wire portions extending in a coil axial line direction, wherein each elemental wire portion represents one helical round of the valve spring,
the array of elemental wire portions includes first elemental wire portions defining a closely-wound section supported by the first valve spring seat and second elemental wire portions defining a sparsely-wound section extending from the closely-wound section to the second valve spring seat,
the first elemental wire portions of the closely-wound section are closely in contact with each other in the direction of the coil axial line while the valve closes the opening of the port,
the second elemental wire portions of the sparsely-wound section are spaced apart from each other in the direction of the coil axial line while the valve closes the opening of the port,
a first seat portion, on which one of the second elemental wire portions is supported, of the second valve spring seat has a diameter greater than a second seat portion, on which one of the first elemental wire portions is supported, of the first valve spring seat, such that a coil outer diameter of at least a part of the closely-wound section, including the one of the first elemental wire portions disposed on the first seat portion of the first valve spring seat, is smaller than a coil outer diameter of each elemental wire portion of the sparsely-wound section, including the one of the second elemental wire portions disposed on the second seat portion of the second valve spring seat, and
at least a part of the closely-wound section is in direct contact with an outer surface of the valve guide.

US Pat. No. 10,794,239

ROTARY MANIFOLD FOR A COHESION-TYPE DRIVE

MCGUIRE AERO PROPULSION S...

1. A cohesion-type drive, comprising:a) a casing;
b) a shaft rotatably supported in the casing for rotation about a drive axis in a circumferential forward direction;
c) a disc pack supported in the casing coaxial with the shaft and fixed to rotate with the shaft, the disc pack including a plurality of discs spaced axially apart from one another by disc spaces, the disc spaces comprising a plurality of compression chambers and a plurality of turbine chambers, the plurality of turbine chambers alternating axially with and in fluid isolation of the plurality of compression chambers;
d) a hub manifold in the casing radially inward of the disc pack and fixed to rotate with the shaft about the drive axis, the hub manifold including: a hub body coaxial with the drive axis, a compression chamber inlet ductwork internal the hub body and in fluid communication with the plurality of compression chambers for conducting a first fluid into the plurality of compression chambers to compress the first fluid during rotation of the disc pack in the circumferential forward direction, and a turbine chamber outlet ductwork internal the hub body and in fluid communication with the plurality of turbine chambers for evacuating a second fluid from the plurality of turbine chambers, the turbine chamber outlet ductwork in fluid isolation of the compression chamber inlet ductwork; and
e) a shroud manifold in the casing radially outward of the disc pack, the shroud manifold including a compression chamber outlet ductwork in fluid communication with the plurality of compression chambers for evacuating the first fluid from the plurality of compression chambers, and a turbine chamber inlet ductwork in fluid communication with the plurality of turbine chambers for conducting the second fluid into the plurality of turbine chambers to urge rotation of the disc pack in the circumferential forward direction, the turbine chamber inlet ductwork in fluid isolation of the compression chamber outlet ductwork.

US Pat. No. 10,794,238

METHOD FOR CHANGING GEAR RATIO IN A GEARBOX OF A VEHICLE

17. A computer program product stored on a non-transitory computer-readable medium, said computer program product for changing gear ratio in a gearbox of a vehicle, said gearbox being arranged to transfer torque between a four stroke internal combustion engine and at least one driving wheel, said four stroke internal combustion engine comprising: one or more cylinders; a piston arranged in each cylinder of the one or more cylinders; one or more inlet valves arranged in each cylinder of the one or more cylinders, which each inlet valve of the one or more inlet valves is connected with an inlet system; at least one first camshaft which controls each inlet valve of the one or more inlet valves; one or more exhaust valves arranged in each cylinder of the one or more cylinders, which exhaust valve of the one or more exhaust valves is connected with an exhaust system; at least one second camshaft which controls each exhaust valve of the one or more exhaust valves; and a crankshaft which controls each camshaft, said computer program product comprising computer instructions to cause one or more electronic control units or computers to perform the following operations:a) receive a first signal that the gear ratio should be changed;
b) calculate a braking torque that the four stroke internal combustion engine should provide in order to reduce a rotational speed of the four stroke internal combustion engine to a target rotational speed at which the four stroke internal combustion engine should be running after the gear ratio has been changed;
c) phase-shift the at least one second camshaft in relation to the crankshaft, so that the at least one second camshaft is phase-shifted to a state, where the at least one exhaust valve of the one or more exhaust valves is controlled in such a way, that it is opened during an expansion stroke of the four stroke internal combustion engine and closed during an exhaust stroke of the four stroke internal combustion engine, wherein the phase shifting of the at least one second camshaft is controlled, in order to control compression during the exhaust stroke, for achieving stepless control an amount of braking torque during engine braking, so that the amount of braking torque that the four stroke internal combustion engine provides is dependent on how many degrees the at least one second camshaft is phase-shifted;
d) disconnect the four stroke internal combustion engine from the at least one driving wheel;
e) open and close the at least one exhaust valve of the one or more exhaust valves with a decompression device in a transition area between an exhaust stroke and an inlet stroke and also between a compression stroke and an expansion stroke, when the piston is at a top dead center in the at least one cylinder of the one or more cylinders in order to achieve engine braking through compression in the at least one cylinder of the one or more cylinders during the exhaust stroke and a compression stroke; and
f) shift a gear in the gearbox.

US Pat. No. 10,794,237

CONTROL DEVICE FOR INTERNAL COMBUSTION ENGINE

MITSUBISHI JIDOSHA KOGYO ...

1. A control device for an internal combustion engine having a variable valve timing mechanism which changes an opening or closing timing of one or both of an intake valve and an exhaust valve, comprising:a processor device;
a memory device storing a program controlling the processor device;
a first sensor detecting atmospheric pressure; and
a second sensor detecting an amount of air flowing through an intake air flow path,
wherein the program causes the processor device to,
calculate a charging efficiency based on the amount of air detected by the second sensor,
calculate a volumetric efficiency from the amount of air and the atmospheric pressure detected by the first sensor,
calculate a charging efficiency valve opening timing of the intake valve based on the charging efficiency,
calculate a volumetric efficiency valve opening timing of the intake valve based on the volumetric efficiency, and
set the valve opening timing or valve opening timings of at least one of the intake valve and the exhaust valve by the variable valve timing mechanism based on one of the charging efficiency valve opening timing and the volumetric efficiency valve opening timing,
wherein program causes the processor device to compare the calculated charging efficiency valve opening timing and the calculated volumetric efficiency valve opening timing, and set, whichever is calculated to be a more advanced angle side, as the valve opening timing of the intake valve.

US Pat. No. 10,794,236

TAPPET

OTICS CORPORATION, Nishi...

1. A tappet comprising:a hydraulic lash adjuster which supports a lower end portion of a push rod; and
a tappet case to which the lash adjuster is internally fitted and which is reciprocally displaced in a vertical direction according to a rotating cam,
wherein an inner peripheral surface of the tappet case is provided with an air-vent passage through which air existing between the tappet case and the lash adjuster is discharged upward when the lash adjuster is being assembled.

US Pat. No. 10,794,235

AUTOMATIC LASH ADJUSTER FOR USE WITH HIGH COMPRESSION INTERNAL COMBUSTION ENGINES

1. An internal combustion engine comprising:an engine block at least partially defining a cylinder;
a piston at least partially positioned within the cylinder and configured to move with respect to the cylinder;
a cylinder head coupled to the engine block and at least partially enclosing the cylinder, the cylinder head defining a first runner open to the cylinder and a second runner open to the cylinder;
a first valve mounted to the cylinder head and configured to move between an open position, in which the first runner is in fluid communication with the cylinder, and a closed position, in which the first runner is fluidly isolated from the cylinder;
a second valve mounted to the cylinder head and configured to move between an open position, in which the second runner is in fluid communication with the cylinder, and a closed position, in which the second runner is fluidly isolated from the cylinder;
a valve bridge extending between and in contact with the first valve and the second valve;
a first cam lobe with a profile corresponding to positive power operation;
a second cam lobe with a profile corresponding to engine braking operation;
a first input in operable communication with the first cam lobe and the valve bridge;
a second input in operable communication with the second cam lobe and the valve bridge; and
a hydraulic lash adjuster is configured to selectively transmit force between the valve bridge and one of the first input and the second input, wherein the hydraulic lash adjuster is a normally open lash adjuster.

US Pat. No. 10,794,234

DEVICE FOR VARYING LOAD OF VALVE SYSTEM

Hyundai Motor Company, S...

1. A device for varying a load of a valve system, the device comprising:a first spring retainer configured to move together with a valve in accordance with rotation of a cam;
a first valve spring having a first end supported by a cylinder head and a second end supported by the first spring retainer;
a second valve spring disposed to surround a portion of the first valve spring, the second valve having a first end supported by the cylinder head;
a second spring retainer supported by a second end of the second valve spring; and
a piston configured to move in a longitudinal direction of the valve with respect to the second spring retainer so as to selectively switch between (a) a first position in which the piston is engaged with and supported by the first spring retainer, and (b) a second position in which the piston is spaced apart from the first spring retainer,
wherein the piston moves together with the second spring retainer when in the first position so as to enable compression of the first valve spring and the second valve spring, and
wherein compression of only the first valve spring is enabled when the piston is in the second position.

US Pat. No. 10,794,233

VALVE DRIVE DEVICE

Daimler AG, Stuttgart (D...

1. A valve drive device, comprising:an axially shiftable cam unit allocated to a valve, wherein the cam unit has at least three cam tracks; and
a switching unit, wherein the switching unit includes a displacement body, wherein the cam unit is displaceable in a first actuation direction and in a second actuation direction by the displacement body, and wherein the first actuation direction is opposite the second actuation direction;
wherein the displacement body has at least two contact surfaces;
wherein the at least two contact surfaces are angled in relation to each other.

US Pat. No. 10,794,232

PLANT AND METHOD FOR THE SUPPLY OF ELECTRIC POWER AND/OR MECHANICAL POWER, HEATING POWER AND/OR COOLING POWER

1. A plant for the supply of electric power, mechanical power, heating power and/or cooling power to an end-user by making use of a single working fluid configured to absorb heat transferred by a heat source, the plant comprising:i. isenthalpic flow rate regulation means configured to divide overall flow rate of said working fluid circulating in said plant into a first and second share of said working fluid;
ii. downstream of said isenthalpic flow rate regulation means, a first circuit comprising:
first adiabatic two-phase compression means configured to increase the pressure and consequently the temperature of said working fluid;
isobaric vapor generation means for generating vapor of said working fluid thermally activated by heat transferred by said heat source;
first adiabatic expansion means configured to generate said electric power and/or mechanical power due to expansion of said working fluid;
isobaric condensation means configured to condense said working fluid with resulting supply of heating power to said end-user;
isobaric thermal regeneration means functionally associated to said first adiabatic two-phase compression means and to said first adiabatic expansion means configured to promote a transfer of heating power from said working fluid circulating downstream of a stage of said first adiabatic expansion means to said working fluid circulating downstream of a stage of said first adiabatic two-phase compression means;
iii) downstream of said isenthalpic flow rate regulation means, a second circuit comprising:
first isobaric thermal dissipation means configured to promote the heat transfer from said working fluid to environment external to the plant;
second adiabatic two-phase expansion means configured to generate said electric power and/or mechanical power due to expansion of said working fluid;
isobaric evaporation means configured to evaporate said working fluid with resulting supply of cooling power to said end-user;
second adiabatic two-phase compression means adapted to increase the pressure and consequently the temperature of said working fluid;
wherein said first and second circuit are in communication with each other, and configured to combine said first share of said working fluid when circulated in said first circuit downstream of said first adiabatic expansion means and said second share of said working fluid when circulated in said second circuit, in said second adiabatic two-phase compression means or downstream said first adiabatic expansion means and said second adiabatic two-phase compression means;
iv) a third circuit downstream of said second adiabatic two-phase compression means comprising, upstream of said isenthalpic flow rate regulation means, second thermal dissipation means configured to promote the transfer of thermal energy from said working fluid to the environment external to the plant; and
v) bypass means comprising:
first deviation means configured to deviate said working fluid when circulated in said first circuit, bypassing respective condensation means ; and
second deviation means configured to deviate said working fluid between said first circuit downstream of said first adiabatic expansion means and said third circuit upstream of said second thermal dissipation means bypassing said second circuit : and
vi) control means configured to distribute said working fluid between said circuits and said bypass means
whereby the plant is configured to the following alternative functionalities:
feeding said first share of said working fluid in said first circuit through said condensation means and said first adiabatic expansion means towards said second adiabatic two-phase compression means in said second circuit, for supplying electric power, mechanical power, heating power and cooling power;
deviating said first share of said working fluid in said first circuit through said first deviation means and said first adiabatic expansion means towards said second adiabatic two-phase compression means of for supplying electric power and/or mechanical power, and cooling power; and
feeding an overall flow rate of said working fluid in said first circuit through said condensation means and said first adiabatic expansion means and then through said second deviation means towards said third circuit of for supplying electric power and/or mechanical power, and heating power.

US Pat. No. 10,794,231

REVERSIBLE SYSTEM FOR DISSIPATING THERMAL POWER GENERATED IN A GAS-TURBINE ENGINE

SAFRAN, Paris (FR)

1. A reversible system for dissipating heat power generated in a gas turbine engine, the system comprising:a condenser-forming first heat exchanger for exchanging heat between a refrigerant fluid and a cold source;
an evaporator-forming second heat exchanger for exchanging heat between the refrigerant fluid and a hot source generating heat power;
a scroll compressor arranged upstream from the first heat exchanger and downstream from the second heat exchanger; the scroll compressor for operating as a compressor when a temperature of the cold source is higher than a predefined threshold temperature and as a turbine when the temperature of the cold source is lower than the predefined threshold temperature;
an expander and a pump arranged in parallel downstream from the first heat exchanger and upstream from the second heat exchanger; and
a control valve arranged upstream from the expander and the pump for directing the refrigerant fluid to the expander when the temperature of the cold source is higher than the threshold temperature and to the pump when the temperature of the cold source is lower than the threshold temperature.

US Pat. No. 10,794,230

WASTE HEAT RECOVERY SYSTEM

HYUNDAI MOTOR COMPANY, S...

1. A waste heat recovery system having a Rankine cycle in which a plurality of boilers, an expander, a condenser, and a circulation pump are installed on a circulation path in which working fluid is circulated, the waste heat recovery system comprising:a first boiler configured to exchange heat between an exhaust gas and the working fluid and be connected to the circulation path of the Rankine cycle through a first connection pipe;
a second boiler configured to exchange heat between an exhaust gas recirculation (EGR) gas and the working fluid and be connected to the circulation path of the Rankine cycle through a second connection pipe;
a first and a second direction control valves configured to be installed at a top and at a bottom of the plurality of boilers to shift flow directions of the working fluid to the plurality of boilers; and
an electronic control unit (ECU) configured to receive information of a vehicle and information of the waste heat recovery system to control the first and second direction control valves,
wherein:
the first boiler and the second boiler are connected to each other to be directly communicated with each other through a direct connection pipe, and
an opening and closing valve is installed at the direct connection pipe and configured to control the working fluid flowing between the first boiler and the second boiler.

US Pat. No. 10,794,229

BINARY POWER GENERATION SYSTEM AND STOPPING METHOD FOR SAME

Kobe Steel, Ltd., Hyogo ...

5. A method for stopping a binary cycle power generation system, the system including:a working fluid circulation line through which a working fluid circulates;
an evaporator provided in the working fluid circulation line, and configured to evaporate the working fluid owing to a gained thermal energy;
an expander provided at a downstream side with respect to the evaporator in the working fluid circulation line, and configured to expand the working fluid coming from the evaporator;
an energy recovery apparatus configured to recover a kinetic energy generated in the expander;
a condenser provided at a downstream side with respect to the expander in the working fluid circulation line, and configured to condense the working fluid coming from the expander owing to a heat exchange with a cooling medium;
a pump provided at a position downstream of the condenser and upstream of the evaporator in the working fluid circulation line, and configured to cause the working fluid coming from the condenser to go to the evaporator;
a temperature detector provided in a portion between the condenser and the pump in the working fluid circulation line and configured to detect a temperature of the working fluid in the portion;
a pressure detector provided in the portion and configured to detect a pressure of the working fluid in the portion; and
a cooling temperature detector provided in a supply line of the cooling medium to the condenser, and configured to detect a temperature of the cooling medium in the supply line, wherein
the method, when stopping the system, sequentially execute:
a detection information reception step of receiving temperature information from the temperature detector, pressure information from the pressure detector, and cooling temperature information from the cooling temperature detector one after another;
a calculation step of calculating a saturation temperature Ts from the pressure information;
a determination step of determining whether a supercooling degree (Ts?Tr1) that is a difference between the saturation temperature Ts and a temperature Tr1 of the working fluid at the outlet of the condenser is a predetermined value or more;
a rotational speed reduction step of reducing a rotational speed of a motor of the pump by a predetermined value when the determination in the determination step results in affirmation; and
a cooling temperature comparison step of comparing cooling temperature information before and after execution of the rotational speed reduction step,
the rotational speed reduction step and the cooling temperature comparison step being repeated when the comparison in the cooling temperature comparison step results in that the cooling temperature information after the execution of the rotational speed reduction step is lower than the cooling temperature information before the execution of the rotational speed reduction step.

US Pat. No. 10,794,228

SYSTEM AND METHOD FOR THE GENERATION OF HEAT AND POWER USING MULTIPLE LOOPS COMPRISING A PRIMARY HEAT TRANSFER LOOP, A POWER CYCLE LOOP AND AN INTERMEDIATE HEAT TRANSFER LOOP

XYZ ENERGY GROUP, LLC, S...

1. A method for generating power, comprising:a) providing four or more discreet heat transfer devices, arranged in series, and confined within a contained housing;
b) circulating an intermediate heat transfer fluid through the housing and about the four or more discreet heat transfer devices;
c) heating a primary heat transfer fluid using an external heat source to provide a heated primary heat transfer fluid;
d) circulating a first portion of the heated primary heat transfer fluid through a first of the four or more discreet heat transfer devices within the housing and circulating a second portion of the heated primary heat transfer fluid through a second of the four or more discreet heat transfer devices within the housing, whereby the intermediate heat transfer fluid is indirectly heated by the heated primary heat transfer fluid from both the first and second discreet heat transfer devices;
e) circulating at least a portion of a power cycle fluid through a third of the four or more discreet heat transfer devices within the housing and circulating the at least a portion of the power cycle fluid through a fourth of the four or more discreet heat transfer devices within the housing to provide a heated power cycle fluid, whereby the power cycle fluid is indirectly heated within the third and fourth discreet heat transfer devices by the intermediate heat transfer fluid; and
f) generating power using the heated power cycle fluid exiting the housing.

US Pat. No. 10,794,227

SYSTEM AND METHOD FOR HARNESSING LATENT HEAT TO GENERATE ENERGY

1. A method for harnessing latent heat to generate energy, the method comprising:generating vapor with a vapor source;
carrying the vapor through a vapor source conduit to a vapor expander;
recovering, by the vapor expander, the expansion work of the vapor, whereby energy and exhaust is generated;
urging, with the generated energy from the vapor expander, articulation of a primary load, whereby electricity is generated;
carrying the exhaust through a vapor expander exhaust conduit to a vapor condenser, whereby the vapor condenser causes the exhaust to form a condensate;
powering a compressor with the energy generated by the vapor expander;
compressing a gas from a gas expander with the compressor, whereby the compression of the gas raises the temperature of the gas;
carrying the compressed and the heated gas through a hot gas transfer conduit to a heat exchanger, whereby the compressed and heated gas releases heat and consequently cools to a cooled gas while passing through the heat exchanger;
heating the condensate from the vapor condenser with the released heat from the heat exchanger, the condensate is heated;
carrying the heated condensate to the vapor source through a heated condensate return conduit, whereby the condensate is recycled to the vapor state;
carrying a first portion of the cooled gas that has passed through the heat exchanger through a cooled gas transfer conduit to a receiver accumulator, whereby the gas is stored;
carrying a second portion of the cooled gas that has passed through the heat exchanger through the cooled gas transfer conduit to the vapor condenser;
transferring heat from the exhaust formed in the vapor expander to the cooled gas in the vapor condenser, thereby reheating the gas;
carrying the re-heated gas through a re-heated gas conduit, to the gas expander;
expanding the re-heated gas in the gas expander to produce energy for driving a gas expander load;
urging, with the generated energy from the gas expander, articulation of a gas expander load, whereby electricity is generated; and
carrying at least a portion of the re-heated gas from the gas expander to the compressor for further compression and heating of the gas, through a gas expander exhaust conduit.

US Pat. No. 10,794,226

POWER PLANT WITH HEAT RESERVOIR

Siemens Aktiengesellschaf...

1. A power plant comprising:a steam circuit which is supplied, in a region of a heat recovery steam generator, with thermal energy for producing steam, wherein the steam circuit comprises, in the region of the heat recovery steam generator, a high-pressure part, a medium-pressure part and a low-pressure part,
a heat reservoir which has a phase change material, which is not arranged in the region of the heat recovery steam generator, wherein the phase change material is different than water,
a supply line proceeding from the high-pressure part or the medium-pressure part for the supply of thermally treated water to the heat reservoir, and
a discharge line for a discharge of thermally treated water from the heat reservoir, and the discharge line opens into the medium-pressure part, the low-pressure part or a steam turbine.

US Pat. No. 10,794,225

TURBINE WITH SUPERSONIC SEPARATION

UOP LLC, Des Plaines, IL...

1. A process for recovering power from a vapor stream with a turbine, the process comprising:condensing a portion of the vapor stream in a supersonic separator, the supersonic separator comprising a baffle configured to impart a swirl at or above a sonic velocity on the vapor stream passing therethrough;
separating the condensed portion from the vapor stream with the supersonic separator to provide a superheated vapor stream; and,
recovering power from the superheated vapor stream in a turbine, the turbine comprising a turbine wheel configured to transmit rotational movement to an electrical generator,
wherein the supersonic separator comprises a body with an inlet for the vapor stream, an outlet for a liquid stream comprising the condensed portion from the vapor stream, and an outlet for the superheated vapor stream, and
wherein the turbine is disposed within the body.

US Pat. No. 10,794,224

GAS TURBINE AND METHOD OF ATTACHING A TURBINE NOZZLE GUIDE VANE SEGMENT OF A GAS TURBINE

1. A gas turbine, comprising:a combustion chamber including a combustion chamber casing;
a high-pressure turbine including;
a turbine casing including an axial groove with respect to a rotational axis of the gas turbine; the axial groove being defined by two opposing side walls and a connecting base surface and
a first turbine guide vane ring that is arranged downstream of the combustion chamber, wherein the first turbine guide vane ring includes a turbine nozzle guide vane segment, wherein the turbine nozzle guide vane segment includes:
at least one guide vane;
an outer platform;
an inner platform; and
a guide vane hook;
an outer housing, including the combustion chamber casing and the turbine casing, wherein the guide van hook is positioned in the axial groove of the turbine casing to fix the turbine nozzle guide vane segment in a radial direction with respect to the rotational axis, and wherein occurring radial loads are transferred into the outer housing;
a first turbine rotor blade ring arranged downstream from the first turbine guide vane ring and including a rotor blade; and
a structure arranged axially downstream from the first turbine guide vane ring, wherein the structure is an outer boundary of a main flow path of the rotor blade, and wherein the structure is fixed in the radial direction via a portion of the structure being inserted between the two side walls of the axial groove.

US Pat. No. 10,794,223

ENCLOSED JACKING INSERT

RAYTHEON TECHNOLOGIES COR...

1. A gas turbine engine, comprising:a static frame component comprising a first flange;
a low-pressure compressor aft of the static frame component;
a case around the low-pressure compressor and aft of the static frame component, the case comprising a second flange;
a bulkhead disposed between the first flange and the second flange, the second flange being retained against both the bulkhead and the static frame component by a snap fit, the bulkhead including a clearance opening; and
a jacking insert having a D-shaped back plate configured for positioning within a D-shaped recess disposed within the second flange, the jacking insert further having a cylinder extending from the D-shaped back plate and through the second flange and a threaded opening in alignment with the clearance opening and extending through both the back plate and the cylinder.

US Pat. No. 10,794,222

SPRING FLOWER RING SUPPORT ASSEMBLY FOR A BEARING

General Electric Company,...

1. A support assembly for a bearing of a gas turbine engine including a shaft extending along an axial direction, the support assembly comprising:an outer race positioned radially exterior to the bearing such that the outer race supports the bearing; and
a spring finger ring positioned radially exterior to the outer race and at least partially supporting the outer race, the spring finger ring comprising:
an outer ring positioned radially exterior to the outer race;
an inner ring positioned radially interior to the outer ring such that the inner ring and outer ring define a gap therebetween; and
a plurality of spring fingers extending between the inner and outer rings such that the plurality of fingers provides damping of the outer race, wherein at least a portion of the plurality of spring fingers is configured as two-sided spring fingers and each include a first ligament coupled to the outer ring and extending at a first circumferential angle relative to the axial direction to a first radial bumper proximate to the inner ring at a first circumferential location to define a first circumferential side of each the two-sided spring fingers and a second ligament coupled to the inner ring at a second circumferential location and extending at a second circumferential angle relative to the axial direction, the second circumferential angle different than the first circumferential angle, to a second radial bumper proximate to the outer ring to define a second circumferential side of each of the two-sided spring fingers, and wherein each of the two-sided spring fingers defines a first radial gap between the first radial bumper and the inner ring and a second radial gap between the second radial bumper and the outer ring.

US Pat. No. 10,794,221

GAS TURBINE ENGINE WITH GEOPOLYMER SEAL ELEMENT

UNITED TECHNOLOGIES CORPO...

1. A gas turbine engine comprising:a rotatable component and a non-rotatable component;
a seal carried on one of the rotatable component or the non-rotatable component to provide sealing there between, the seal including a geopolymer seal element that is an inorganic material that has a covalently bonded, amorphous network produced by condensation of tetrahedral aluminosilicate units, with alkali metal ions balancing the charge associated with tetrahedral aluminum.

US Pat. No. 10,794,220

TEMPERATURE SENSOR ARRAY FOR A GAS TURBINE ENGINE

Raytheon Technologies Cor...

1. A gas turbine engine component comprising:a conformal surface;
an array of resistance temperature detector (RTD) sensors disposed across at least a portion of the conformal surface;
a plurality of printed circuit traces deposited on said conformal surface and connecting each of said RTD sensors to a controller via a corresponding four wire circuit; and
wherein each circuit trace in said plurality of circuit traces extends to a circumferential edge of said conformal surface; and
wherein each of said RTD sensors is a printed precision RTD sensor comprising a primary trace and a plurality of secondary traces, a subset of the plurality of secondary traces being shorted by a conductive layer of the RTD sensor.

US Pat. No. 10,794,219

AXIAL CASE RING TO MAXIMIZE THRUST BUSHING CONTACT AREA OF VARIABLE VANE

Rolls-Royce Corporation, ...

1. A variable vane system comprising an arcuate casing;a plurality of vane assemblies arranged circumferentially around the arcuate casing;
each assembly of the plurality of vane assemblies comprising:
a penny bore defined by the arcuate casing, the penny bore extending radially outward from an inner surface of the arcuate casing;
a bushing bore defined by the arcuate casing, the bushing bore extending radially inward from an outer surface of the arcuate casing;
a spindle bore defined by the arcuate casing, the spindle bore extending between and connecting the penny bore and the bushing bore;
the penny bore, bushing bore and spindle bore share a common axis and form a first annular face defined by an interface between the penny bore and the spindle bore, a second annular face defined by an interface between the spindle bore and bushing bore, and an interconnecting face that extends between the first annular face and the second annular face and defines an inner diameter of the spindle bore, and the second annular face being opposite the first annular face;
the penny bore and the bushing bore having respective inner diameters greater than the inner diameter of the spindle bore;
a variable vane having a penny with a blade extending from a first side of the penny and a spindle extending from an opposing side of the penny;
a cylindrical bushing arranged to extend between a first terminal end and a second terminal end, wherein the second terminal end is spaced apart from the first terminal end relative to the common axis and the cylindrical bushing is seated within the bushing bore such that the second terminal end is spaced apart from the second annular face, the cylindrical bushing having an inner diameter less than or equal to the inner diameter of the spindle bore;
a thrust bushing seated in the penny bore, the thrust bushing having an inner diameter equal or greater than the inner diameter of the spindle bore;
wherein the penny is seated on the thrust bushing and the spindle extends through the thrust bushing, through the spindle bore and is seated within the cylindrical bushing, wherein the variable vane is rotatable about the axis; and
wherein the vane system further includes a ring seal arranged around the spindle and located between the second terminal end of the cylindrical bushing and the second annular face.

US Pat. No. 10,794,218

DISCHARGE FLOW DUCT OF A TURBINE ENGINE COMPRISING A VBV GRATING WITH VARIABLE SETTING

Safran Aircraft Engines, ...

1. A hub for a dual-flow turbine engine, the hub comprising:a first shroud defining a primary flow space for a primary gas flow of the dual-flow turbine engine,
a second shroud defining a secondary flow space for a secondary gas flow of the dual-flow turbine engine,
a discharge stream duct extending between the first shroud and the second shroud, the discharge stream duct defining a discharge flow space for a discharge gas flow, wherein a wall of the second shroud comprises an opening, the opening being an outlet for the discharge gas flow into the secondary flow space of the second shroud, such that a discharge plane of the discharge stream duct is coincident with the wall of the second shroud comprising the opening, and
an upstream fin and a downstream fin, both the upstream fin and the downstream fin disposed in the discharge stream duct at the opening, the downstream fin being downstream from the upstream fin relative to a direction of flow of the secondary gas flow in the secondary shroud, wherein:
the upstream fin is located adjacent to an upstream surface of the discharge stream duct relative to the direction of flow of the secondary gas flow in the secondary shroud, the upstream fin having a skeleton line, and a leading edge arranged facing the discharge gas flow in the discharge stream duct,
the downstream fin is located adjacent to a downstream surface of the discharge stream duct relative to the direction of flow of the secondary gas flow in the secondary shroud, the downstream fin having a respective skeleton line, and a leading edge arranged facing the discharge gas flow in the discharge stream duct, and
an upstream acute angle (?upstream) between the discharge plane and a tangent to the skeleton line at the leading edge of the upstream fin is smaller than a downstream acute angle (?downstream) between the discharge plane and a tangent to the respective skeleton line at the leading edge of the downstream fin.

US Pat. No. 10,794,217

BLEED VALVE SYSTEM

RAYTHEON TECHNOLOGIES COR...

1. A bleed valve system for a gas turbine engine, comprising:a retaining ring that abuts an end of a bleed air duct, the retaining ring defining a plurality of retaining ring apertures;
a metering ring that is at least partially disposed within the bleed air duct and abuts the retaining ring, the metering ring defining a plurality of metering ring apertures, the metering ring being rotatable relative to the retaining ring to selectively facilitate a fluid flow through the bleed air duct, the metering ring having at least one bracket; and
a drive shaft that extends into the bleed air duct and is operatively connected to the at least one bracket by a lever arm.

US Pat. No. 10,794,216

FAN DRIVE GEAR SYSTEM DC MOTOR AND GENERATOR

Raytheon Technologies Cor...

1. A gas turbine engine comprising:a fan driven by a fan shaft rotatable about an engine axis;
a fan drive electric motor providing a supplemental drive input to the fan, wherein the fan drive electric motor includes a permanent magnet rotor mounted to the fan shaft and a first stator phase and a second stator phase supported on a static structure surrounding the permanent magnet rotor;
a turbine section driving an input shaft;
a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and
a generator configured to communicate electric power to power the fan drive electric motor, the generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor,
wherein the generator includes a first stator and a first rotor including a first set of poles providing power to the first stator phase of the fan drive electric motor and a second stator and a second rotor including a second set of poles providing power to the second stator phase of the fan drive electric motor;
the fan drive electric motor is electrically coupled to the first stator and the second stator and the first set of poles and the second set of poles are clocked relative to each other such that rotation of the input shaft commutates the first phase and the second phase to drive the fan drive electric motor; and
the geared architecture is configured to provide a ratio between an input speed of the input shaft and an output speed of the fan shaft and commutation of the plurality of poles of the fan drive electric motor corresponds with a gear ratio and the number of poles in each of the first set of poles and the second set of poles.

US Pat. No. 10,794,215

COOLING ARRANGEMENT FOR A TURBINE CASING OF A GAS TURBINE ENGINE

ROLLYS-ROYCE PLC, London...

1. A cooling arrangement for a turbine casing of a gas turbine engine, comprising a first cooling duct that is located within a second cooling duct, wherein the first cooling duct is for a first cooling fluid flow, wherein the second cooling duct is for a second cooling fluid flow which in use flows around the first cooling duct, and wherein the second cooling duct is provided with a shielded tray on an outer surface thereof, the shielded tray being defined by a wall of the second cooling duct and one or more lips projecting from the second cooling duct.

US Pat. No. 10,794,214

TIP CLEARANCE CONTROL FOR GAS TURBINE ENGINE

United Technologies Corpo...

1. A clearance control system for a gas turbine engine comprising:at least one case support associated with an engine case defining an engine center axis;
a clearance control ring positioned adjacent the at least one case support to form an internal cavity between the engine case and the clearance control ring, and wherein the clearance control ring includes a first mount feature;
an outer air seal having a second mount feature cooperating with the first mount feature such that the clearance control ring can move independently of the engine case in response to changes in temperature, wherein the outer air seal includes a seal support portion separate from the second mount feature and fir to the engine case adjacent to the at least one case support, a ring mount portion that includes the second mount feature, and a main seal portion that extends from the ring mount portion to face the engine component, and wherein the clearance control ring is not directly tied to the engine case or the seal support portion; and
an injection source to inject flow into the internal cavity to control a temperature of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and an engine component.

US Pat. No. 10,794,213

BLADE TIP CLEARANCE CONTROL FOR AN AXIAL COMPRESSOR WITH RADIALLY OUTER ANNULUS

Rolls-Royce North America...

1. A compressor shroud assembly in a turbine engine having a dynamically moveable shroud segment for encasing a rotor segment comprising a bladed disc in an axial compressor and maintaining a clearance gap between the shroud segment and the blade tips of the bladed disc, said assembly comprising:a static compressor casing;
a shroud segment mounted to said casing, said shroud segment comprising a flowpath boundary member spaced radially inward from said casing, said flowpath boundary member being moveable relative to said casing in a radial direction, wherein said flowpath boundary member is spaced radially inward from said casing by a pair of tangs each extending from the casing to the flowpath boundary member, each of said tangs configured for radial flexion relative to said casing; and
an actuator mounted to said casing and coupled to said shroud segment for effecting the movement of said flowpath boundary member.

US Pat. No. 10,794,212

ROTOR HAVING IMPROVED STRUCTURE, AND TURBINE AND GAS TURBINE INCLUDING THE SAME

Doosan Heavy Industries C...

1. A rotor that is installable in a casing of a turbine and configured to be rotated by a flow of combustion gas and cooled by a flow of compressed air, the rotor comprising:a disk having an outer circumferential surface;
a platform installed on the outer circumferential surface of the disk; and
a blade airfoil formed on an upper surface of the platform, the blade airfoil including:
an airfoil end situated opposite to the platform, the airfoil end having an upstream side and a downstream side with respect to a flow direction of the combustion gas, and
an upstream surface that faces the flow of the combustion gas and includes an inclined portion forming an acute angle with respect to a seating surface of the platform on which the blade airfoil is seated, the upstream surface configured to guide the combustion gas along the upstream surface to the airfoil end,
wherein the blade airfoil is formed so that, when the rotor is installed in the casing, the downstream side of the airfoil end is closer to an inner surface of the casing than the upstream side of the airfoil end.

US Pat. No. 10,794,211

SEAL GEOMETRIES FOR REDUCED LEAKAGE IN GAS TURBINES AND METHODS OF FORMING

Raytheon Technologies Cor...

1. A turbomachine sealing component comprising:a substrate (63; 65) having a circumferential surface (61; 66); and
a coating (60) on the circumferential surface;wherein:the coating or a layer thereof is patterned to form circumferential sealing ridges (150; 170) effective to form grooves in something that is circumferentially rubbed against the turbomachine sealing component; and
an abradable material (180) of the coating is in gaps between the ridges.

US Pat. No. 10,794,210

STIFFNESS CONTROLLED ABRADEABLE SEAL SYSTEM AND METHODS OF MAKING SAME

Raytheon Technologies Cor...

1. A stiffness controlled abradable seal system for a gas turbine engine, comprising:a solid lubricant material comprising at least one metal combined with at least one member of a class of ternary compounds, said at least one metal combined with said at least one member of a class of ternary compounds is defined by the general composition M.sub.n+1AX.sub.n, wherein M is an early transition metal selected from groups IIIB, IVB, VB, and VIB, A is an element selected from groups IIIA, IVA, VA, VIA, and VIIA, X is either carbon or nitrogen, and n is an integer between 1 and 3 to minimize a friction coefficient, wherein said solid lubricant material includes an about 25% volume fraction of a MAX phase content material.

US Pat. No. 10,794,209

TURBINE ROTOR BLADE AND ROTARY MACHINE

MITSUBISHI HEAVY INDUSTRI...

1. A turbine rotor blade comprising:a plurality of blade bodies which are mounted so as to extend in a radial direction from a rotor body rotatable about an axis in a casing, the plurality of blade bodies being disposed at intervals in a circumferential direction of the rotor body; and
an annular tip shroud connected to each tip end part of the plurality of blade bodies,
wherein the tip shroud includes at least one first through hole, and the at least one first through hole penetrates the tip shroud in the radial direction so as to bring a first cavity and an inter-blade flow passage into communication,
wherein
the first cavity is defined between a first seal fin and a second seal fin,
the first seal fin extends in the radial direction from one of an outer peripheral surface of the tip shroud or an inner peripheral surface of the casing toward the other of the outer peripheral surface or the inner peripheral surface, and has a tip part,
the first seal fin forms a gap between the tip part and the other of the outer peripheral surface or the inner peripheral surface,
the second seal fin extends in the radial direction from one of the outer peripheral surface of the tip shroud or the inner peripheral surface of the casing toward the other of the outer peripheral surface or the inner peripheral surface at a position spaced apart from the first seal fin in a direction of the axis, and has a tip part,
the second seal fin forms a gap between the tip part and the other of the outer peripheral surface or the inner peripheral surface,
the inter-blade flow passage is formed between a pair of adjacent blade bodies in the circumferential direction of the rotor body,
the at least one first through hole includes a first opening opened on a side of the first cavity and a second opening opened on a side of the inter-blade flow passage,
the first opening is formed at an intermediate position between the first seal fin and the second seal fin, and
the second opening is formed at a position facing the inter-blade flow passage, the position of the second opening having the same static pressure as a static pressure at the intermediate position facing the first opening.

US Pat. No. 10,794,208

NON-CONTACT SEAL ASSEMBLY FOR ROTATIONAL EQUIPMENT WITH LINKAGE BETWEEN ADJACENT ROTORS

Raytheon Technologies Cor...

1. An assembly for rotational equipment, the assembly comprising:a stator;
a rotor extending axially along a centerline, the rotor including a linkage, a first rotor disk, and a second rotor disk, wherein the linkage extends axially from the first rotor disk to the second rotor disk, and wherein the linkage is removably attached to the second rotor disk; and
a seal assembly configured for sealing a gap radially between the stator and the linkage, wherein the seal assembly includes a hydrostatic non-contact seal that comprises:
an annular base;
a plurality of shoes arranged around and radially adjacent the linkage; and
a plurality of spring elements, each of the spring elements radially between and connecting a respective one of the shoes to the base, and each of the spring elements discrete and physically separated from circumferentially adjacent ones of the spring elements;
wherein the non-contact seal is positioned directly radially above and is axially aligned with a cylindrical surface of a seal portion of the linkage; and
wherein the seal portion of the linkage has a hardface which forms the cylindrical surface.

US Pat. No. 10,794,207

GAS TURBINE ENGINE AIRFOIL COMPONENT PLATFORM SEAL COOLING

RATHEON TECHNOLOGIES CORP...

12. A method of cooling a gas turbine engine component array comprising the steps of:providing cooling fluid to a cavity between adjacent components that provide a gap circumferentially between axially lateral faces of the adjacent components;
flowing cooling fluid from the cavity through a cooling hole in a seal provided between the adjacent components, wherein the seal is arranged circumferentially between the adjacent components, and the lateral faces overlap the cooling hole in a circumferential direction, the cooling hole having a circumferential width that is larger than the gap; and
diffusing the cooling fluid through the cooling hole on a gas path flow side of the seal opposite the cavity to create a cooling film in the gap provided between adjacent platforms of the components.

US Pat. No. 10,794,206

CMC BOAS INTERSEGMENT SEAL

RAYTHEON TECHNOLOGIES COR...

1. A blade outer air seal assembly, comprising:a support structure;
a blade outer air seal extending circumferentially about an axis and mounted in the support structure;
a flow guide having a plurality of flow guide segments arranged between the blade outer air seal and the support structure; and
an intersegment seal at a circumferential end of at least one of the flow guide segments, wherein the intersegment seal has an anti-rotation feature in engagement with the flow guide.

US Pat. No. 10,794,205

CERAMIC SEAL COMPONENT FOR GAS TURBINE ENGINE AND PROCESS OF MAKING THE SAME

Rolls-Royce North America...

1. A process of manufacturing a ceramic seal component, comprising:deinfiltrating an edge of respective preimpregnated plies such that the deinfiltrated edge is defined by a plurality of ceramic fibers extending away from a portion edge of a matrix infiltrated portion of each of the plies, the plurality of ceramic fibers defining a less infiltrated portion than the matrix infiltrated portion;
placing the plies with the deinfiltrated edge in a stacked relationship, and orienting the edge of each of the plies in alignment with each other to define a stacked structure;
curing the stacked structure into a rigid green body having a pre-ceramic polymer matrix material structure with the deinfiltrated edge being an exposed free ceramic fiber edge of the rigid green body;
further deinfiltrating the exposed free ceramic fiber edge of the rigid green body before firing; and
firing the stacked structure to form a ceramic seal component having a flexible seal edge formed by the plurality of ceramic fibers projecting from a rigid body formed by the matrix infiltrated portion of each of the plies.

US Pat. No. 10,794,204

ADVANCED STATIONARY SEALING CONCEPTS FOR AXIAL RETENTION OF CERAMIC MATRIX COMPOSITE SHROUDS

General Electric Company,...

1. A gas turbine sealing assembly defining an axial direction and a radial direction, comprising:a first static gas turbine wall;
a second static gas turbine wall; and
a seal disposed between the first static gas turbine wall and the second static gas turbine wall, the seal comprising:
a shield wall constructed from a first material, the shield wall comprising:
a first shield wall portion extending in the axial direction;
a second shield wall portion extending in the axial direction;
a first crimp extending in the radial direction such that the first crimp is perpendicular to the first shield wall portion; and
a second crimp extending in the radial direction such that the second crimp is perpendicular to the second shield wall portion; and
a spring constructed from a second material, the spring comprising a first spring portion directly connected to a second spring portion,
wherein the first shield wall portion is adjacent to the first spring portion and the second shield wall portion is adjacent to the second spring portion,
and further wherein the first crimp is bent over an end of the first spring portion such that the first crimp permits axial and radially inward movement of the first spring portion but prevents radially outward movement of the first spring portion, and the second crimp is bent over an end of the second spring portion such that the second crimp permits axial and radially inward movement of the second spring portion but prevents radially outward movement of the second spring portion relative to an axial centerline axis of a gas turbine to which the sealing assembly is positioned.

US Pat. No. 10,794,203

SCAVENGE TUBE FOR A GAS TURBINE ENGINE

General Electric Company,...

1. A scavenge tube for conveying oil within an engine, the scavenge tube comprising:an inner tube that defines a second surface and that is configured to be fluidly connected to a source of oil;
an outer tube that defines a first surface;
a space that is defined between the outer tube and the inner tube such that the first surface opposes the second surface; and
a plurality of bumps positioned within the space,
wherein each of the plurality of bumps has a flat base disposed on one of the first surface and the second surface, and extends radially from the flat base toward the other of the first surface and the second surface to a high point,
wherein, for at least for one of the plurality of bumps, a first contact area is formed between the flat base and the one of the first surface and the second surface, and
wherein, for at least for one of the plurality of bumps, a second contact area smaller than the first contact area is formed between the high point and the other of the first surface and the second surface.

US Pat. No. 10,794,202

MIXED FLOW OPTIMIZED TURBINE

Turboden S.p.A., Brescia...

1. A mixed flow turbine for the expansion phase of a steam thermodynamic cycle or an organic Rankine cycle comprising:a first section in which a first expansion of a main flow of a working fluid takes place in a substantially radial direction, said first section comprising at least one row of stator blades and at least one rotor stage
a second section in which a second expansion of the main flow of the working fluid takes place in a substantially axial direction, said second section comprising at least one row of stator blades and at least one rotor stage,
between said first and second section, at least one angular row of stator blades which deflect the main flow of the working fluid from the initial radial direction to a substantially axial expansion direction,
said turbine being characterized by means for injection and/or means for extraction of a second flow of the working fluid, accommodated within the angular row of stator blades; and
wherein said means for injection and/or means for extraction of the second flow of the working fluid are configured so that the injection and/or means for extraction takes place in a portion of the angular row of stator blades delimited by a pair of surfaces, wherein the pair of surfaces includes, a first surface of the pair which corresponds to an expansion level of the working fluid between 5% and 25% and a second surface of the pair which corresponds to an expansion level of the working fluid between 10% and 50% of the overall expansion in the angular row of stator blades.

US Pat. No. 10,794,201

METHOD FOR ASSEMBLING TURBOMACHINE PARTS AND ASSEMBLY USED DURING SUCH A METHOD

SAFRAN AIRCRAFT ENGINES, ...

1. A method for assembly of a first turbomachine part with a second turbomachine part, comprising:injecting a vulcanisable elastomer in an injection zone at a junction between the first and second turbomachine parts; and
heating only of the injection zone so as to vulcanise the vulcanisable elastomer,
wherein the heating only of the injection zone is implemented using an assembly for assembling the first and second turbomachine parts, the assembly comprising a support and a ring, the support comprising an annular support wall for the ring, the ring being formed from a first material and a second material, the first material being a thermal insulating material and the second material being a heat conducting material.

US Pat. No. 10,794,200

INTEGRAL HALF VANE, RINGCASE, AND ID SHROUD

United Technologies Corpo...

1. A vane stage comprising:a ringcase extending circumferentially about a center axis of the vane stage, wherein the ringcase extends completely about the center axis to form a first ring;
an inner shroud extending circumferentially about the center axis of the vane stage, wherein the inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis; and
a plurality of stationary half vanes extending radially between the ringcase and the inner shroud, wherein the plurality of stationary half vanes are circumferentially spaced about the center axis;
wherein the plurality of stationary half vanes are integral with the ringcase and the inner shroud;
wherein the ringcase is axially longer than the inner shroud and increases in diameter aft of the plurality of stationary half vanes; and
wherein the ringcase comprises:
a plurality of ribs formed on an outer surface of the ringcase aft of the plurality of stationary half vanes, each of the plurality of ribs increasing in radial thickness in an aft direction, wherein each of the plurality of ribs comprises:
an axial rib extending parallel to the center axis;
a first angled rib intersecting the axial rib at a node; and
a second angled rib intersecting the axial rib and the first angled rib at the node.

US Pat. No. 10,794,199

ROTOR BLADE ASSEMBLY COMPRISING A RING SEGMENT SHAPED OR DISC SEGMENT SHAPED BLADE CARRIER AND A RADIALLY INNER REINFORCEMENT STRUCTURE

1. A rotor blade assembly group for an engine, comprising:a blade carrier including a plurality of rotor blades that are provided along a first circle line about a central axis of the rotor blade assembly group,
the blade carrier including a carrier section that extends radially inward in a direction toward the central axis with respect to the plurality of rotor blades,
the carrier section comprising a connection area positioned at a radially innermost portion of the carrier section farthest from the plurality of rotor blades,
at least one stiffening ring fixedly attached at the connection area of the carrier section,
the at least one stiffening ring being arranged at a first or a second face side of the blade carrier,
the blade carrier being formed in a ring-segment-shaped or a disc-segment-shaped manner,
the connection area of the carrier section including a profile that includes at least one axial projection, with the profile having a T-shaped, I-shaped, or fir tree shaped cross-section, the at least one stiffening ring engaging around the profile in a form-fit manner, such that the at least one axial projection is received at least partially between a radially outer section and a radially inner section of the at least one stiffening ring, and
a sleeve-shaped connection component for connecting the blade carrier to at least one other adjacent blade carrier via a bolt connection element, and such that the bolt connection element connects the sleeve-shaped connection component and an extension of the at least one stiffening ring to the blade carrier,
wherein the blade carrier includes a passage hole that extends axially with respect to the central axis and that is radially delimited by a radially innermost edge of the carrier section, and a portion of the radially inner section of the at least one stiffening ring axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section.

US Pat. No. 10,794,198

CLIP WITH FLUID DYNAMIC SHAPE

1. A clip for attachment to a structure comprising, an outside surface, said clip having a nose end and a slot end, said slot end including a slot adapted to receive the structure to be attached to said clip, said clip having two sides between said nose end and said slot end, each of said two sides starting a midpoint of said nose end and leading towards said slot end, said sides forming said outside surface of said clip, each of said sides being composed of five arcs, said five arcs comprising a first arc each of said sides starting at said midpoint of said nose end having an arc radius of 0.35080 inches and an arc length of 0.22395 inches, a second arc of each of said sides connected to said first arc having an arc radius between 0.09480 inches and 0.35080 inches and an arc length between 0.08660 inches and 0.09480 inches, a third arc of each of said sides connected to said second arc having an arc radius between 0.41000 inches and 0.35080 inches and an arc length between 0.15750 inches and 0.16910 inches, a fourth arc of each of said sides connected to said third arc having an arc radius between 0.36000 inches and 0.35080 inches and an arc length between 0.22980 inches and 0.23070 inches, a fifth arc of each of said sides connected to said fourth arc having an arc radius between 0.36000 inches and 0.35080 inches and an arc length between 0.11270 inches and 0.19450 inches, said fifth arc of each side forming said blade end and said blade slot.

US Pat. No. 10,794,197

COATED TURBINE COMPONENT AND METHOD FOR FORMING A COMPONENT

GENERAL ELECTRIC COMPANY,...

1. A coated turbine component, comprising:a substrate comprising a hot gas path surface and a curved trailing edge face;
a coating disposed on the hot gas path surface and the curved trailing edge face; and
a discontinuous transition feature configured to discourage hot gas flow along the hot gas path surface from flowing along the curved trailing edge face,
wherein the discontinuous transition feature is formed from an additional portion of the coating extending outward from the coating over a portion of the curved trailing edge face, and
wherein the coating is a thermal barrier coating or an environmental barrier coating.

US Pat. No. 10,794,196

STEAM TURBINE

Mitsubishi Hitachi Power ...

1. A stationary blade for a steam turbine, comprising:a joint assembly that joins a main unit having a hollow structure formed from a metal plate by plastic forming with a blade tail section formed separately from the main unit; wherein
the blade tail section is a metal block formed into the blade tail section shape, the blade tail section has a recess on a blade suction-side and a slit on a blade pressure side,
the main unit has a suction-side protrusion, which forms a part of a blade suction-side blade surface and covers the recess when joining with the blade tail section, and
a space of the joint assembly formed by the suction-side protrusion and the recess in the blade tail section communicates with an outside of the blade through only the slit.

US Pat. No. 10,794,195

AIRFOIL HAVING FORWARD FLOWING SERPENTINE FLOW

RAYTHEON TECHNOLOGIES COR...

1. An airfoil for a gas turbine engine, the airfoil comprising:an airfoil body having a leading edge and a trailing edge, a root region and a tip region, wherein an aftward direction is from the leading edge toward the trailing edge and a radially outward direction is from the root region to the tip region;
a forward-flowing serpentine flow path formed within the airfoil body, the forward-flowing serpentine flow path defined by a first serpentine cavity, a second serpentine cavity, and a third serpentine cavity, wherein the first serpentine cavity is aftward of the second serpentine cavity, and the second serpentine cavity is aftward of the third serpentine cavity;
a tip flag cavity extending aftward from proximate the leading edge to the trailing edge along the tip region of the airfoil body; and
at least one shielding cavity located between a portion of the forward-flowing serpentine flow path and an external surface of the airfoil body,
wherein a cooling air flow is supplied into the forward-flowing serpentine flow path from a serpentine inlet at the first serpentine cavity, and the cooling air flow passes through the first serpentine cavity, the second serpentine cavity, the third serpentine cavity, into and through the tip flag cavity, and exits through the trailing edge of the airfoil body,
wherein at least one of the at least one shielding cavities is located on a pressure side of the airfoil body between a portion of the forward-flowing serpentine flow path and an external pressure side of the airfoil body.

US Pat. No. 10,794,194

STAGGERED CORE PRINTOUT

Raytheon Technologies Cor...

1. A method of manufacturing a gas turbine engine component comprising:providing a body extending between first and second ends to define a length and extending between first and second edges to define a width;
forming a plurality of openings within a wall surface of the body wherein the plurality of openings are positioned to be staggered relative to each other such that at least two adjacent openings are offset from each other in at least one direction;
defining an arc segment along the length of the body, wherein the openings are spaced apart from each other along the arc segment; and
forming the openings via one of a casting, EDM, laser, or additive manufacturing method.

US Pat. No. 10,794,193

AIR FOIL WITH GALVANIC PROTECTION

UNITED TECHNOLOGIES CORPO...

1. An airfoil for a gas turbine comprising:a body comprising multiple chambers formed therein, wherein the body comprises a first metallic material, wherein the multiple chambers comprise a first chamber and a second chamber, with raised portions of the body disposed between the first chamber and the second chamber to separate the first chamber from the second chamber;
a sheath coupled to the body, the sheath comprising a second metallic material; and
multiple filler sections corresponding to and at least partially occupying the multiple chambers of the body, wherein the multiple filler sections comprise at least one first filler section comprising a first filler material disposed in the first chamber and at least one second filler section comprising a second filler material disposed in the second chamber;
wherein the first filler material is selected to have a comparatively more negative electrode potential than the first metallic material, the second metallic material, and the second filler material;
wherein the second filler material is selected to have a comparatively higher mechanical yield strength than the first filler material.

US Pat. No. 10,794,192

GAS TURBINE ENGINE AIRFOIL

RAYTHEON TECHNOLOGIES COR...

1. An airfoil for a turbine engine comprising:an airfoil having pressure and suction sides and extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position, wherein the trailing edge sweep angle is in a range of 0° to 10° in a range of 10-20% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span.

US Pat. No. 10,794,191

GAS TURBINE ENGINE AIRFOIL FREQUENCY DESIGN

Raytheon Technologies Cor...

1. A turbomachine airfoil element comprising:an airfoil having pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges, the airfoil extending in a radial direction a span that is in a range of 0.78-0.91 inch;
a chord length extending in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.49-0.62 inch; and
at least two of:
a first mode has a frequency of 3533 up to ±15% Hz;
a second mode has a frequency of 8291 up to ±15% Hz;
a third mode has a frequency of 17362 up to ±15% Hz;
a fourth mode has a frequency of 23365 up to ±15% Hz; and
wherein the frequencies are at zero speed and ambient conditions, and the frequency of any given mode does not exceed the frequency of a higher order mode;
wherein the first mode is an ND0-TE@ID mode, the second mode is an ND0-LE@ID mode and the third mode is an ND51-1EBLE mode, the ND0-TE@ID mode corresponds to deflections in unison axially forward and aft at an inner diameter of the trailing edge, the ND0-LE@ID mode corresponds to deflections in unison axially forward and aft at an inner and outer diameter of the leading edge, and the ND51-1EBLE mode corresponds to a lowest aliased nodal diameter in which there are fifty-one peaks/troughs vibrating in the radial direction at each of inner and outer diameters of a stator stage of an array of airfoils;
wherein the airfoil is part of a stator; and
wherein the airfoil is a nickel-based superalloy, the nickel-based superalloy has a density of 0.28-0.32 lb/in3 (7.7-8.9 g/cm3), and the nickel-based superalloy has a modulus of elasticity of 27-36 Mpsi (186-248 GPa) at room temperature.

US Pat. No. 10,794,190

CAST INTEGRALLY BLADED ROTOR WITH BORE ENTRY COOLING

Florida Turbine Technolog...

1. An air cooled integrally bladed rotor for a gas turbine engine comprising:an axial bore formed within a rotor disk;
a plurality of turbine rotor blades;
a circumferential cooling air supply channel located below the plurality of turbine rotor blades;
a plurality of radial cooling air supply channels;
each radial cooling air supply channel having an inlet opening into the axial bore and an outlet opening into the circumferential cooling air supply channel;
a plurality of bulbous chambers extending outward from the circumferential cooling air supply channel;
a radial cooling air passage formed in each of the turbine rotor blades;
each radial cooling air passage having an inlet opening into one of the plurality bulbous chambers and an outlet opening onto a tip of the turbine rotor blade; and,
the rotor disk and the turbine rotor blades are cast as a single piece.

US Pat. No. 10,794,189

TURBINE ENGINE ASSEMBLY COMPRISING A NOSE CONE AND A FRONT SHROUD

SAFRAN AIRCRAFT ENGINES, ...

1. An assembly for a turbine engine extending about a longitudinal axis, the assembly comprising:a nose cone comprising a conical body extending about the longitudinal axis or an axis parallel to the longitudinal axis and a flange arranged downstream of the conical body, in the gas flow direction, the flange comprising a first contact surface extending into the extension of an inner surface of the conical body,
a front shroud comprising a generally annular body extending about the longitudinal axis or the axis parallel to said longitudinal axis and a flange arranged upstream of the annular body, in the gas flow direction, the flange comprising a first contact surface extending into the extension of an outer surface of the annular body, the first contact surface of the nose cone being in contact with the first contact surface of the front shroud, and
fasteners configured to clamp the first contact surface of the nose cone flange against the first contact surface of the front shroud flange,
wherein the first contact surface of the nose cone and the first contact surface of the front shroud are inclined from upstream to downstream, in the gas flow direction, towards the longitudinal axis, so that the flange of the nose cone grips the flange of the front shroud, even when the fasteners are not yet positioned.

US Pat. No. 10,794,188

ROTOR BLADE ASSEMBLY COMPRISING A RING-SHAPED OR DISC-SHAPED BLADE CARRIER AND A RADIALLY INNER REINFORCEMENT STRUCTURE

1. A rotor blade assembly group for an engine, comprising:a ring-shaped or disc-shaped blade carrier including a plurality of rotor blades that are provided along a first circle line about a central axis of the rotor blade assembly group,
the blade carrier including a carrier section that extends radially inwards in a direction toward the central axis with respect to the plurality of rotor blades,
the carrier section comprising a connection area positioned at a radially innermost portion of the carrier section farthest from the plurality of rotor blades,
at least one stiffening ring fixedly attached at the connection area of the carrier section,
the at least one stiffening ring being arranged at a first or a second face side of the blade carrier, and
the connection area of the carrier section including a profile that includes at least one axial projection, with the profile having a T-shaped, I-shaped, or fir tree shaped cross-section, the at least one stiffening ring engaging around the profile in a form-fit manner, such that the at least one axial projection is received at least partially between a radially outer section and a radially inner section of the at least one stiffening ring,
wherein the blade carrier includes a passage hole that extends axially with respect to the central axis and that is radially delimited by a radially innermost edge of the carrier section, and a portion of the radially inner section of the at least one stiffening ring axially extends radially inwardly of the radially innermost edge of the carrier section and is positioned directly radially between the central axis and the radially innermost edge of the carrier section,
wherein the at least one stiffening ring is separate from a connection component that connects the blade carrier to at least one other adjacent blade carrier.

US Pat. No. 10,794,187

ROTARY COMPRESSOR WITH A VALVE IN THE VANE

LG Electronics Inc., Seo...

1. A rotary compressor, comprising:a case;
a driving motor located inside of the case;
a rotating shaft coupled to the driving motor and configured to transmit rotational force from the driving motor;
a cylinder that is located inside of the case and that defines a compression space inside of the cylinder, the cylinder further defining a vane slot that is recessed from an inner circumferential surface of the cylinder and that communicates with the compression space;
a roller coupled to the rotating shaft and configured to rotate in the compression space based on the rotational force from the driving motor;
a first bearing coupled to an upper portion of the cylinder;
a second bearing coupled to a lower portion of the cylinder; and
a vane that is configured to protrude from the cylinder along the vane slot toward the roller, that is configured to contact the roller, and that is configured to, based on contacting the roller, partition the compression space into a suction chamber and a compression chamber,
wherein the vane comprises:
a vane housing that defines a valve space located inside of the vane housing, and a communication hole that extends from the valve space to a front end portion of the vane housing, the valve space and the communication hole defining a flow path of refrigerant, and
a valve that is located in the valve space of the vane housing, that is configured to slidably move in the valve space relative to the vane housing, and that is configured to, based on movement of the valve in the valve space relative to the vane housing, selectively allow communication between the valve space and the compression chamber.

US Pat. No. 10,794,186

ROTARY PISTON AND CYLINDER DEVICES

Lontra Limited, Warwicks...

1. A rotary piston and cylinder device, comprising:a rotor, the rotor comprising a piston, the rotor is arranged to rotate about an axis of rotation,
a stator,
the rotor and the stator defining an annular working chamber, and a rotor surface in part defining the working chamber,
the device further comprising a rotatable shutter which serves to divide the working chamber, but which comprises a slot to nevertheless allow passage of the piston, and
the rotor surface being a concave surface which faces generally radially inwards towards the axis of rotation of the rotor, the piston extending from the concave surface and the concave surface in part defining the working chamber.

US Pat. No. 10,794,185

CYLINDER BLOCK AND SWASH PLATE TYPE LIQUID-PRESSURE ROTATING APPARATUS INCLUDING SAME

KAWASAKI JUKOGYO KABUSHIK...

1. A cylinder block comprising:a plurality of cylinder bores including respective openings formed on a piston insertion end surface of the cylinder block, a plurality of pistons being inserted in respective cylinder bores of the plurality of cylinder bores and being configured to reciprocate and slide in the respective cylinder bores of the plurality of cylinder bores when the cylinder block rotates; and
a cooling portion including a plurality of cooling holes formed between adjacent cylinder bores of the plurality of cylinder bores and extending from the piston insertion end surface in an axial direction of the cylinder block, the plurality of cooling holes not extending to a side surface of the cylinder block, and an axial depth of each cooling hole of the plurality of cooling holes is within a range of depth from the piston insertion end surface to a deepest portion of the plurality of cylinder bores.

US Pat. No. 10,794,184

RECYCLABLE SAND-CONSOLIDATED ANCHOR HEAD PRESTRESSED ANCHOR, ANCHORAGE JACK AND ITS APPLICATION METHOD

INSTITUTE OF ROCK AND SOI...

1. A recyclable anchor, comprising: a bolt body (6), a rigid frame (5), a load member (1), a sand column (2), a pressure bearing member (4), a cut-off piece (3) and an anchor pier (8), whereinone end of the rigid frame (5) is fixedly connected to the pressure bearing member (4), and the other end of the rigid frame (5) is fixedly connected to the anchor pier (8);
a first through hole (18) placed in a center of the pressure bearing member (4), the cutoff member (3) in the first through hole (18), is configured to move in one direction along the axial direction of the pressure bearing receiving member (4); and
the anchor body (6) is configured to sequentially slide with the outer walls of a second through hole (15), a third through hole (16), a fourth through hole (17), and a fifth through hole (23) in the center of the load member (1),
wherein the load-bearing member (1), the cut-off piece (3) and the bolt body (6) are magnetic and the magnetic poles of the load-bearing member (1) are the same as those of the cut-off piece member (3), and the magnetic poles of the bolt body (6) are opposite to those of the load-bearing member (1) and the stop member (3).

US Pat. No. 10,794,183

SELF-DRILLING DIFFERENTIAL GROUTING COMBINED BOLT AND ANCHORING METHOD THEREFOR

CHINA UNIVERSITY OF MININ...

1. A self-drilling differential grouting composite rock bolt, consisting essentially of a drill bit (1), a grouting pipe (2), a main shaft (3), an anchor head assembly and an anchor tail assembly, whereinthe drill bit (1) is connected to a front end of the main shaft (3); the grouting pipe (2) is sleeved over the main shaft (3), and an inner diameter of the grouting pipe (2) is greater than a diameter of the main shaft (3), so a grouting passage is formed between the grouting pipe (2) and the main shaft (3);
the anchor head assembly comprises a sliding ring (7), a limiting pipe (6), and a plurality of pairs of driven connecting rods (501) and driving connecting rods (502); the sliding ring (7) is sleeved over the main shaft (3) and connected to a front end of the grouting pipe (2); the limiting pipe (6) is sleeved over the main shaft (3) and located between the drill bit (1) and the sliding ring (7), and the limiting pipe (6) is provided with a plurality of grouting holes; a length of the limiting pipe (6) is smaller than a total length of one pair of driving connecting rod and driven connecting rod; the driven connecting rods (501) are uniformly distributed along a circumferential direction and hinged to the front end of the main shaft (3); the driving connecting rods (502) are uniformly distributed along the circumferential direction and hinged to the sliding ring (7); the driven connecting rods (501) and the driving connecting rods (502) are hinged with each other; and
the anchor tail assembly comprises an anchor plate (11) and a connecting nut (12); the anchor plate (11) is sleeved over a rear end of the grouting pipe (2), and the connecting nut (12) is sleeved over the main shaft (3) and blocks the rear end of the grouting pipe (2); the connecting nut (12) is provided with a grouting hole connected with the grouting passage in the grouting pipe (2); the anchor plate is provided with a grouting hole and an exhaust hole.

US Pat. No. 10,794,182

SYSTEMS AND METHODS FOR CONTROLLING A LONGWALL MINING SYSTEM BASED ON A FORWARD-LOOKING MINE PROFILE

JOY GLOBAL UNDERGROUND MI...

1. A longwall mining system comprising:an armored face conveyer;
a shearer configured to travel along the armored face conveyor in a first direction or a second direction, the shearer including a shearer housing, a first cutter drum extended in the first direction away from the shearer housing, and a second cutter drum extended in the second direction away from the shearer housing;
a first camera configured to generate a first signal associated with the first direction of travel for the shearer;
a second camera configured to generate a second signal associated with the second direction of travel for the shearer; and
a controller including a non-transitory computer readable medium and a processor, the controller comprising computer executable instructions stored in the computer readable medium for controlling operation of the longwall mining system to:
receive the first signal from the first camera,
receive the second signal from the second camera,
analyze at least one of the first signal and the second signal to identify one or more edges of a structure of the longwall mining system ahead of the shearer in either the first direction or the second direction,
generate a forward-looking mine profile based on the one or more edges, and
control the longwall mining system based on the forward-looking mine profile.

US Pat. No. 10,794,181

BIT/HOLDER WITH ENLARGED BALLISTIC TIP INSERT

The Sollami Company, Her...

1. A bit tip insert comprising:a body comprising a tip and a base subjacent the tip, the body having a diameter of at least five-eighths inch at a widest part of the body;
an overlay on an outer surface of the tip;
an overfill portion extending outwardly of the overlay at the widest part of the body, the overfill portion generally disposed between the tip and the base of the body.

US Pat. No. 10,794,180

MINESHAFT-STRATUM FRACTURE COUPLED FLOWING SIMULATION EXPERIMENT DEVICE AND METHOD

SOUTHWEST PETROLEUM UNIVE...

1. A mineshaft-stratum fracture coupled flowing simulation experiment device, comprising: a simulated mineshaft flowing system, a simulated stratum system, a simulated fracture system and a data acquisition system;wherein the simulated mineshaft flowing system comprises a simulated mineshaft, a simulated drilling rod, a drilling fluid storage tank, a stirring motor, and a drilling fluid screw pump;
the simulated drilling rod is located in the center of the simulated mineshaft;
the stirring motor is provided in the drilling fluid storage tank;
the drilling fluid screw pump is connected to an inlet end of the simulated drilling rod through the drilling fluid storage tank;
the simulated stratum system comprises a simulated stratum, a clean water storage tank, a separation tank, a gas storage tank, a gas air-compressor, and a clean water screw pump;
the gas storage tank is connected to the gas air-compressor and is connected to the simulated stratum through a gas pressure regulating valve;
the clean water screw pump is connected to the simulated stratum through the clean water storage tank;
the simulated stratum is connected to the separation tank;
the simulated fracture system comprises two sets of upper and lower simulated fractures, each set of simulated fractures being a space formed by two parallel transparent resin plates;
two sides of each of the simulated fractures are connected to the simulated mineshaft and the simulated stratum respectively;
a high-definition camera is provided in front of each of the simulated fractures;
the data acquisition system comprises a gas flow meter, at least one liquid flow meter, a pressure sensor, a high-definition camera, and a computer.

US Pat. No. 10,794,179

POROMECHANICAL IMPACT ON YIELD BEHAVIOR IN UNCONVENTIONAL RESERVOIRS

ConocoPhillips Company, ...

1. A method of obtaining hydrocarbon from a reservoir in a subterranean formation, the method comprising:a) measuring a poromechanic pressure change due to lithostatic load sharing in the subterranean formation;
b) mapping the poromechanic pressure change to one or more locations in the subterranean formation;
c) identifying one or more local pressure peaks in the poromechanic pressure change, wherein the one or more local pressure peaks are each marked by a pressure escalation and subsequent pressure depletion; and
d) determining one or more regions in the reservoir exhibiting single phase hydrocarbon production.

US Pat. No. 10,794,178

ASSEMBLIES FOR COMMUNICATING A STATUS OF A PORTION OF A DOWNHOLE ASSEMBLY AND RELATED SYSTEMS AND METHODS

Baker Hughes, a GE compan...

1. A downhole assembly, comprising:at least one sensor configured to sense at least one parameter relating to a downhole condition; and
a communications assembly comprising:
at least one device for controlling a characteristic of fluid flow through the downhole assembly; and
a processor in communication with the at least one sensor, the processor configured to generate at least one signal that can be interpreted by an operator without assistance of a decoding system by selectively and slowly altering the characteristic of fluid flow through the downhole assembly with the at least one device in response to data received from the at least one sensor.

US Pat. No. 10,794,177

MUD PUMP STROKE DETECTION USING DISTRIBUTED ACOUSTIC SENSING

Halliburton Energy Servic...

1. A system for detecting mud pump stroke information, comprising:a distributed acoustic sensing (DAS) data collection system coupled to a downhole drilling system;
a stroke detector coupled to a mud pump of the downhole drilling system, the stroke detector configured to detect strokes in the mud pump and to generate mud pump stroke information based on the detected strokes, wherein the stroke detector comprises:
a stroke sensor coupled to the mud pump; and
a fiber disturber coupled to an optical fiber of the DAS data collection system, wherein the fiber disturber encodes the mud pump stroke information into DAS data signals by causing disturbances in the optical fiber of the DAS data collection system based on a mud pump information sensed by the stroke sensor; and
a computing system comprising a processor, a memory, and a pulse detection module, the pulse detection module operable to:
transmit optical signals into the optical fiber of the DAS data collection system;
receive the DAS data signals in response to the transmitted optical signals; and
detect the mud pump stroke information encoded in the received DAS data signals.

US Pat. No. 10,794,176

DRILL STRING LENGTH MEASUREMENT IN MEASUREMENT WHILE DRILLING SYSTEM

Erdos Miller, Inc., Hous...

10. A method of determining a length of a drill string in a measurement while drilling system, the drill string having a fluidic medium in the drill string, the method comprising:situating a first module that includes an electromagnetic wave transmitter, a downhole processor and a pulser at a distal end of the drill string;
situating a second module that includes an uphole processor, a pressure sensor, and an electromagnetic wave antenna at a proximal end of the drill string;
directing the pulser and the electromagnetic wave transmitter, by the downhole processor, to provide a pressure pulse through the fluidic medium and to transmit an electromagnetic wave at the same time;
sensing the pressure pulse at the pressure sensor;
receiving signals from the pressure sensor and the electromagnetic wave antenna at the uphole processor; and
determining a distance from the first module to the second module based on the signals from the pressure sensor and the electromagnetic wave antenna to determine the length of the drill string.

US Pat. No. 10,794,175

MULTI-PARAMETER OPTICAL FIBER SENSING FOR RESERVOIR COMPACTION ENGINEERING

Halliburton Energy Servic...

10. A tubular cable for distributed sensing and simultaneous monitoring of multiple parameters in sub-surface wells comprising:multiple fiber optic cables tightly coupled within a uniformly tubular cable sheath;
one or more of the multiple fiber optic cables comprising an internal optical fiber surrounded by a fiber cladding material, and an outer polymer coating; and
a suitable strain coupling filler material surrounding the multiple fiber optic cables and the multiple fiber optic cables coupled to the uniformly tubular cable sheath for strain transfer.

US Pat. No. 10,794,174

DYNAMICALLY SELF-BALANCING PRESSURIZED BOREHOLE-SEALING APPARATUS AND METHOD THEREOF FOR COAL SEAM GAS PRESSURE MEASUREMENT

SHANDONG UNIVERSITY OF SC...

1. A dynamically self-balancing pressurized borehole sealing apparatus for coal seam gas pressure measurement, comprising a pressure measuring tube arranged in a borehole, wherein one end of the pressure measuring tube is provided with a pressure measuring unit for measuring a gas pressure, an expansion airbag is surrounded and wrapped on the pressure measuring tube, a pressure introducing hole is opened on the pressure measuring tube, the pressure introducing hole communicates with the expansion airbag and with gas from the coal seam, both sides of the expansion airbag on the pressure measuring tube are surrounded and wrapped with a front borehole sealing airbag and a rear borehole sealing airbag respectively, a gel injection chamber is reserved between the three of the front borehole sealing airbag, the rear borehole sealing airbag and the expansion airbag and an inner wall of the borehole, the gel injection chamber is filled with a sealing gel body, the front borehole sealing airbag and the rear borehole sealing airbag are connected to an inflating unit outside the borehole through an inflating pipe, and the gel injection chamber is connected to a gel injecting unit outside the borehole through a gel injection pipe, wherein, in response to receiving of the gas from the coal seam, the expansion airbag is configured to expand to squeeze the sealing gel body in the gel injection chamber to allow the sealing gel body to enter fracture-pores of a coal rock around the borehole, realizing dynamically pressurized sealing.

US Pat. No. 10,794,173

BEARING FAULT DETECTION FOR SURFACE PUMPING UNITS

Weatherford Technology Ho...

1. A method for operating a rod pumping unit for a wellbore, comprising:measuring vibration data in the time domain using at least one sensor attached to a wrist pin housing at least partially enclosing a wrist pin bearing of the rod pumping unit;
converting the vibration data in the time domain to vibration data in the frequency domain;
determining that:
at least one frequency component of the frequency-domain vibration data in a first frequency band has a power above a first threshold; or
a number of frequency components of the frequency-domain vibration data in a second frequency band having power above a second threshold is above a third threshold, wherein at least one of the at least one frequency component in the first frequency band or the frequency components in the second frequency band are characteristic of the wrist pin bearing; and
taking an action related to operating the rod pumping unit, based on the determination, wherein taking the action comprises causing the rod pumping unit to cease pumping.

US Pat. No. 10,794,172

DOWNHOLE DRILLING METHODS AND SYSTEMS WITH TOP DRIVE MOTOR TORQUE COMMANDS BASED ON A DYNAMICS MODEL

Halliburton Energy Servic...

1. A downhole drilling system that comprises:a top drive, the top drive having a motor with an adjustable torque and a rotating shaft coupled to the motor;
a drillstring coupled to the rotating shaft via a connector; and
a controller coupled to the motor, the controller configured to provide torque commands to the motor, wherein the torque commands are based at least in part on a dynamics model and operate to dampen vibrations due to torsional wave propagation along the drillstring.

US Pat. No. 10,794,171

SYSTEMS AND METHODS FOR DRILL BIT AND CUTTER OPTIMIZATION

Halliburton Energy Servic...

11. A method of drill bit analysis using a sensor in a drill bit in a wellbore, the method comprising:collecting a data signal using the sensor disposed proximate to a cutter on the drill bit;
measuring, using a processor and the collected data signal, a resistivity profile from the sensor through a formation;
calculating, using the processor, a distance between the sensor and the formation;
deriving actual drilling properties of the wellbore from the resistivity profile and the distance;
comparing between the actual drilling properties and expected drilling properties;
determining a drilling parameter based on the comparison between the actual drilling properties and the expected drilling properties; and
performing an adjustment of the drilling parameter.

US Pat. No. 10,794,170

SMART SYSTEM FOR SELECTION OF WELLBORE DRILLING FLUID LOSS CIRCULATION MATERIAL

Saudi Arabian Oil Company...

1. A wellbore drilling system comprising:a plurality of particulate size distribution analyzers, each particulate size distribution analyzer configured to determine a size distribution of particulates in a wellbore drilling fluid circulated through the wellbore drilling system, each particulate size distribution analyzer coupled to a respective wellbore drilling fluid flow pathway, the particulates comprising lost circulation material (LCM) configured to reduce loss of the wellbore drilling fluid into a geologic formation in which the wellbore is being drilled;
a particulates reservoir coupled to the plurality of particulate size distribution analyzers, the particulates reservoir configured to carry particulates of different physical properties, the particulates reservoir configured to release certain particulates into a drilling fluid tank of the wellbore drilling system to be mixed with the wellbore drilling fluid circulated through the drilling fluid tank; and
a processing system coupled to the plurality of particulate size distribution analyzers and to the particulates reservoir, the processing system configured to perform operations while drilling the wellbore, the operations comprising:
receiving drilling parameters identifying wellbore drilling conditions of the wellbore drilling system;
receiving size distributions of particulates in the wellbore drilling fluid from the plurality of particulate size distribution analyzers;
determining, based on the received drilling parameters and the received size distributions of the particulates, a quantity of the particulates to be added to the wellbore drilling fluid to increase a concentration of the particulates to a level sufficient to reduce the loss of the wellbore drilling fluid into a geologic formation in which the wellbore is being drilled;
controlling the particulates reservoir to release the certain particulates into the drilling fluid tank based, in part, on the received drilling parameters, the received size distributions of the particulates, and determining the quantity of particulates to be added;
developing a history of particulate concentrations added to the drilling fluid based on a history of drilling conditions and particulate size distributions; and
determining quantities of particulates needed to make-up the drilling fluid responsive, in part, to the developed history, for a subsequent drilling operation.

US Pat. No. 10,794,169

SYSTEMS, DEVICES, AND METHODS FOR GENERATING DRILLING WINDOWS

NABORS DRILLING TECHNOLOG...

1. A method of directing the operation of a drilling system, comprising:generating, with a controller, a plurality of drilling windows around a portion of a drill plan, each of the plurality of drilling windows having a shape with an outer boundary representing drilling tolerances at a particular location along the drill plan;
drilling with a bottom hole assembly comprising a bit disposed at an end of a drill string to create a drilled bore;
receiving sensor data from one or more sensors by electronic communication, the one or more sensors adjacent to or carried on the bottom hole assembly;
determining, with the controller, a position of the bottom hole assembly based on the received sensor data, wherein the received sensor data is associated with an orientation of a toolface, and wherein determining the position of the bottom hole assembly comprises determining the orientation of the toolface;
determining, with the controller the determined position of the bottom hole assembly is within the outer boundary of one window of the plurality of drilling windows;
generating, with the controller, a corrective action to move the bottom hole assembly into one of the plurality of drilling windows if the controller determines that the bottom hole assembly is not within the outer boundary of one of the plurality of drilling windows;
displaying, on a display device, a first drilling window of the plurality of drilling windows at a first location along the drill plan and a second drilling window of the plurality of drilling windows at a second location different than the first location along the drill plan; and
displaying, on the display device, the position of the bottom hole assembly relative to the first and second drilling windows and using the position of the bottom hole assembly relative to the first and second drilling windows as a reference to change the position of the bottom hole assembly.

US Pat. No. 10,794,168

CONTROLLING WELLBORE OPERATIONS

Halliburton Energy Servic...

1. A computer-implemented method of controlling a bottom hole assembly (BHA) to follow a planned wellbore path, the method comprising:determining sensor measurements from the BHA;
determining a model of BHA dynamics based on the sensor measurements from the BHA;
determining weighting factors that correspond to different drilling objectives associated with a drilling operation;
determining an objective function comprising the different drilling objectives, weighted by the weighting factors, and one or more constraints, wherein:
the objective function includes future system states of the BHA,
determining the objective function includes determining a predicted future deviation from the planned wellbore path, and
the weighting factors are automatically adapted during the drilling operation to selectively emphasize the different drilling objectives in the objective function in response to changing conditions in the wellbore, wherein the changing conditions in the wellbore comprise different layers of rock and differently-shaped portions of the planned wellbore path;
determining a control input to the BHA that satisfies the objective function and the one or more constraints; and
applying the control input to the BHA.

US Pat. No. 10,794,167

METHOD AND SYSTEM FOR REMOVING CONTAMINANTS FROM A GAS STREAM USING A LIQUID ABSORBENT

SCHLUMBERGER TECHNOLOGY C...

9. A method, comprising:providing a feed gas stream containing contaminants to a first end of a first linear contactor having a second end thereof opposite the first end thereof;
providing a first absorbent aerosol to the first end of the first linear contactor;
flowing the feed gas stream and the first absorbent aerosol to the second end of the first linear contactor;
separating the first absorbent aerosol from the feed gas stream to form a first recovered absorbent;
recycling a portion of the first recovered absorbent to the first end of the first linear contactor as a first recycled absorbent;
mixing the first recycled absorbent with a first fresh absorbent to form the first absorbent aerosol;
providing a second fresh absorbent at the second end of the first linear contactor;
recovering an intermediate gas stream at the second end of the first linear contactor;
providing the intermediate gas stream to the first end of a second linear contactor having a second end thereof opposite the first end thereof;
providing a second absorbent aerosol to the first end of the second linear contactor;
flowing the intermediate gas stream and the second absorbent aerosol to the second end of the second linear contactor;
separating the second absorbent aerosol from the intermediate gas stream to form a second recovered absorbent;
recycling a portion of the second recovered absorbent to the first end of the second linear contactor as a second recycled absorbent;
mixing the second recycled absorbent with a third fresh absorbent to form the second absorbent aerosol;
providing a fourth fresh absorbent at the second end of the second linear contactor;
recovering a clean gas stream at the second end of the second linear contactor;
determining a contaminant composition of the feed gas stream and the clean gas stream;
determining a theoretical minimum amount of absorbent needed to remove the contaminants from the feed gas stream based on stoichiometry of the absorption reaction;
determining a chemical condition of the first and second recycled absorbents;
setting a flow rate of the first fresh absorbent, the third fresh absorbent, or both based on the determined theoretical minimum amount of absorbent;
setting a flow rate of the second fresh absorbent based on the determined chemical condition of the first recycled absorbent; and
setting a flow rate of the fourth fresh absorbent based on the determined chemical condition of the second recycle absorbent.

US Pat. No. 10,794,166

ELECTRIC HYDRAULIC FRACTURING SYSTEM

DRESSER-RAND COMPANY, Ol...

1. A hydraulic fracturing system, comprising:a fixed speed gas turbine mounted to a semi-trailer;
a hydraulic pump mounted to the semi-trailer and directly connected to an output shaft of the gas turbine; and
a hydraulically driven fracturing fluid pump mounted to the semi-trailer and being in fluid communication with the hydraulic pump, the hydraulic pump supplying fluid pressure to the hydraulically driven fracturing fluid pump,
wherein the fluid pressure supplied by the hydraulic pump is arranged to control a flowrate of the hydraulically driven fracturing pump,
wherein the hydraulically driven fracturing fluid pump receives fracturing fluid containing chemicals and proppants and pressurizes the fracturing fluid to a pressure sufficient for injection into a wellbore for a hydraulic fracturing operation.

US Pat. No. 10,794,165

POWER DISTRIBUTION TRAILER FOR AN ELECTRIC DRIVEN HYDRAULIC FRACKING SYSTEM

1. An electric driven hydraulic fracking system that positions a single variable frequency drive (VFD), a single shaft electric motor, and a single hydraulic pump mounted on a single pump trailer to pump a fracking media into a fracking well to execute a fracking operation to extract a fluid from the fracking well, comprising:a power generation system that is configured to generate electric power at a power generation voltage level, wherein the electric power generated at the power generation voltage level is a voltage level that the power generation system is capable to generate;
a power distribution trailer that is configured to:
distribute the electric power generated by the power generation system at the power generation voltage level to the single VFD positioned on the single pump trailer, wherein the single VFD converts the electric power at the power generation level to a VFD voltage level to control an operation of the single shaft motor and single hydraulic pump positioned on the single pump trailer,
convert the electric power generated by the power generation system at the power generation voltage level to an auxiliary voltage level that is less than the power generation voltage level, and
distribute the electric power at the auxiliary voltage level to the single VFD positioned on the single pump trailer, wherein the electric power at the auxiliary voltage level controls an operation of a plurality of auxiliary systems associated with the single pump trailer.

US Pat. No. 10,794,164

DOWNHOLE TOOL FOR FRACTURING A FORMATION CONTAINING HYDROCARBONS

Saudi Arabian Oil Company...

1. A tool for fracturing a formation containing hydrocarbons, the tool comprising:a body having an elongated shape; and
fracturing devices arranged along the body, each fracturing device comprising:
an antenna to transmit electromagnetic radiation; and
one or more pads that are movable to contact the formation, each pad comprising an enabler that heats in response to the electromagnetic radiation to cause fractures in the formation, the enabler having a structure that is powdery or granular to enable the one or more pads to conform at least partly to a surface of the formation, and a pad among the one or more pads being mounted to a corresponding fracturing device to enable at least partial rotation of the pad relative to the surface of the formation.

US Pat. No. 10,794,163

APPARATUS, SYSTEM AND METHOD FOR FLOW RATE HARMONIZATION IN ELECTRIC SUBMERSIBLE PUMP GAS SEPARATORS

HALLIBURTON ENERGY SERVIC...

1. A system for flow rate harmonization in electric submersible pump (ESP) gas separators comprising:a series of interchangeable funnels attachable to a fluid entrance of a crossover of the ESP gas separator;
each funnel of the series having a different inner diameter;
the inner diameter of a particular funnel of the series of interchangeable funnels determining an inlet area of a vent passage of the crossover when the particular funnel is attached to the fluid entrance of the crossover; and wherein interchanging the particular funnel attached to the crossover modifies flow rate output of the gas separator.

US Pat. No. 10,794,162

METHOD FOR REAL TIME FLOW CONTROL ADJUSTMENT OF A FLOW CONTROL DEVICE LOCATED DOWNHOLE OF AN ELECTRIC SUBMERSIBLE PUMP

BAKER HUGHES, A GE COMPAN...

1. A method of controlling flow in a tubular extending into a wellbore comprising:developing a pressure in the tubular with an electric submersible pump (ESP);
directing a flow of fluid through a flow control device into a collector arranged on the tubular downhole of the ESP in response to the pressure;
deploying coiled tubing supporting a distributed sensor into the tubular, the coiled tubing being independent of the tubular;
sensing a parameter of the flow of fluid with the distributed sensor;
generating a parameter profile corresponding to a plurality of locations along the collector; and
adjusting, in real time, a flow parameter of the flow control device with a shifting tool supported by the coiled tubing in response to the parameter of the fluid.

US Pat. No. 10,794,161

BIDIRECTIONAL ELECTROMAGNETIC PROPELLED THRUSTER DEVICE FOR USE IN TUBULARS

Pep Energy Systems Ltd., ...

1. A fluid transport system, comprising:a pipeline transporting fluid in a downstream direction from one geographic location to another, the pipeline comprising a plurality of electromagnetic elements spaced along a length of the pipeline, each electromagnetic element being selectively energized by a source of electrical energy that is controlled by a controller; and
a plurality of fluid thrusters disposed within and spaced at intervals along the pipeline, each fluid thruster comprising:
a thruster body having a downstream end and an upstream end, the downstream end facing in the downstream direction;
a magnetic element carried by the thruster body; and
a valve member carried by the thruster body, the valve member being actuatable between an open position that permits fluid flow to traverse the thruster body, and a closed position that prevents fluid flow to traverse the thruster body, the valve member being actuated from the closed position to the open position in response to fluid pressure applied from the upstream direction and from the open position to the closed position in response to fluid pressure applied from a downstream direction that is opposite to the upstream direction;
wherein the controller sequentially activates the electromagnetic elements to apply a motive force to the magnetic element and propel each fluid thruster, each fluid thruster being selectively propelled in either the upstream direction or the downstream direction, wherein, in the upstream direction, the valve member is actuated to the open position to permit fluid to flow past the thruster body, and in the downstream direction, the valve member is actuated to the closed position such that the fluid thruster pushes the fluid in the downstream direction, each fluid thruster reciprocating independently within the pipeline.

US Pat. No. 10,794,160

GEOTHERMAL HEAT RECOVERY DEVICE AND GEOTHERMAL HEAT RECOVERY DEVICE OPERATING METHOD

Kobe Steel, Ltd., Kobe-s...

1. A geothermal heat recovery device comprising:a circulation flow path provided with a circulation pump, a heat medium pressurized by the circulation pump circulating through the circulation flow path in a hot liquid state;
a heat exchanger installed underground and configured to heat the heat medium flowing through the circulation flow path with underground heat;
a binary electricity generation device configured to recover, as electrical energy, thermal energy from the heat medium heated by the heat exchanger;
a bypass path connected to the circulation flow path and bypassing the heat exchanger;
an adjustment mechanism configured to adjust a flow division ratio between a flow rate of the heat medium flowing into the heat exchanger and a flow rate of the heat medium bypassing the heat exchanger through the bypass path;
a flash tank disposed between an outflow end of the bypass path and the heat exchanger in the circulation flow path, the flash tank being configured to flash the heat medium heated by the heat exchanger;
a discharge mechanism configured to discharge the gaseous heat medium separated in the flash tank; and
a replenisher configured to replenish the circulation flow path with heat medium;
an opening and closing mechanism disposed on an exit side of the flash tank in the circulation flow path; and
a stop control unit configured to perform control to open the discharge mechanism and to close the opening and closing mechanism when the circulation pump is stopped.

US Pat. No. 10,794,159

BOTTOM-FIRE PERFORATING DRONE

DynaEnergetics Europe Gmb...

13. A method for perforating a wellbore casing or hydrocarbon formation, comprising:arming a perforating drone, wherein the perforating drone includes
a perforating assembly section,
a control module section including a hollow interior portion and a ballistic channel respectively positioned within the control module section, wherein the ballistic channel extends from the hollow interior portion in a direction towards the perforating assembly section,
a control module positioned within the hollow interior portion of the control module section, wherein the control module includes a housing and the housing encloses a detonator and a donor charge within a detonator channel within an inner area of the control module, wherein
the detonator is in ballistic communication with the donor charge and configured to initiate the donor charge upon detonating, and
the donor charge is positioned adjacent to the ballistic channel,
a receiver booster positioned within the ballistic channel,
a ballistic interrupt positioned within the ballistic channel between the donor charge and the receiver booster in a spaced apart configuration from the donor charge and the receiver booster, wherein the ballistic interrupt is movable between a closed state and an open state, wherein arming the perforating drone includes moving the ballistic interrupt from the closed state to the open state, and
at least one shaped charge received in a shaped charge aperture in a body of the perforating assembly section;
deploying the perforating drone into the wellbore; and
detonating the at least one shaped charge.

US Pat. No. 10,794,158

METHOD FOR SEALING CAVITIES IN OR ADJACENT TO A CURED CEMENT SHEATH SURROUNDING A WELL CASING

SHELL OIL COMPANY, Houst...

1. A method for sealing cavities in or adjacent to a cured cement sheath surrounding a well casing of an underground wellbore, the method comprising the steps of:providing an expansion device with edged expansion segments that is configured to be moved with the edged expansion segments in an unexpanded configuration up and down through a well casing which is surrounded by a cured cement sheath;
moving the unexpanded expansion device to a selected depth in the well casing; and
expanding the edged expansion segments at the selected depth, thereby pressing circumferentially spaced recesses into an inner surface of a selected casing section and expand an outer surface of the selected casing section into the cured cement sheath thereby sealing the cavities.

US Pat. No. 10,794,157

DOWNHOLE REMOTE TRIGGER ACTIVATION DEVICE FOR VLH BIG BORE AND MONO BORE CONFIGURED RUNNING TOOLS WITH PROGRAMMING LOGIC

Halliburton Energy Servic...

1. A method for activating a running tool, comprising:detecting a wellbore condition at said running tool;
upon receiving a signal from surface equipment within a predefined time period, initiating an isolation of pressure below said running tool from pressure above said running tool; and
if said signal is not received within said predefined time period, initiating said isolation of said pressure at an expiration of said predefined time period, wherein said predefined time period starts when said wellbore condition is detected at said running tool.

US Pat. No. 10,794,156

MULTI-BORE JUMPER INTERFACE

OneSubsea IP UK Limited, ...

1. A connecting interface for coupling a multi-bore jumper to equipment at a seabed with a seal plate, the interface comprising:a rotatable hub;
an alignment pin;
a central bore terminating adjacent a central location of the hub, the hub rotatable independently, both about the central bore and relative another hub at another interface at an opposite end of the jumper secured to other equipment at the seabed; and
at least one perimeter bore terminating at a perimeter location of the hub, the perimeter bore movable with the hub during any rotation thereof, the seal plate having a coupler to couple to the perimeter bore and an orifice for receiving the alignment pin to effect the rotation of the hub.

US Pat. No. 10,794,155

METHOD FOR EXPLOITING A HYDROCARBON DEPOSIT BY HISTORY MATCHING OF PRODUCTION AS A FUNCTION OF DIAGENESIS

IFP ENERGIES NOUVELLES, ...

1. A method for exploiting a subterranean formation including hydrocarbons, the formation including at least one facies which has undergone at least one diagenetic phase over geological time, from at least one sample of rock obtained from the formation, from measured production data relating to the formation and from a meshed representation representative of the formation with the meshed representation having been formed by meshes, each of the meshes of the meshed representation including at least one indicator relating to distribution of the at least one facies present in the mesh, comprising steps of:A. determining from at least measurements performed on the at least one sample of rock, for at least one of the facies of the formation and for each of the meshes of the meshed representation, a value of at least one parameter of a diagenetic state of the at least one facies of the formation; and
B. updating at least values of the parameters of the diagenetic state of at least one of the facies of the formation from the measured production data, for at least one mesh of the meshes of the meshed representation, according to the following steps:
i. determining at least one petrophysical property relating to flow in the formation for each of the meshes of the meshed representation, from the values of the parameters of the diagenetic state of the at least one facies of the formation;
ii. using a flow simulator and the meshed representation filled with petrophysical properties relating to the flow to simulate production data relating to production of the formation;
iii. determining an objective function measuring at least one difference between the measured production data and the simulated production data; and
iv. modifying at least the value of the parameters of the diagenetic state of the at least one facies of the formation from the objective function for at least one of the meshes of the meshed representation; and
reiterating steps i) to iv) until a predetermined stop criterion is reached; and
determining a scheme for exploiting the hydrocarbons of the formation and exploiting the hydrocarbons of the formation with at least the determined scheme for exploiting the hydrocarbons of the formation.