US Pat. No. 9,420,724

POWER CONVERTER ASSEMBLY

GE AVIATION SYSTEMS LLC, ...

1. A power converter assembly, comprising:
a housing;
a cold plate located within the housing;
a power converter module conductively coupled with the cold plate, receiving a power input, and providing a power output,
wherein the housing is enclosed such that a thermal output of the power converter module is greater than the rate of thermal
transfer out of the housing by natural heat transfer;

heat-sensitive circuitry located within the housing and having a predetermined thermal operating limit; and
a thermal composite overlying the power converter module and at least partially thermally insulating the power converter module
from the heat sensitive circuitry;

wherein the power converter module generates heat while converting the power input to the power output, the thermal composite
insulates the heat-sensitive circuitry from at least a portion of the generated heat such that the temperature of the heat-sensitive
circuitry does not rise above the thermal operating limit, and at least a portion of the generated heat is removed by way
of conduction through the cold plate.

US Pat. No. 9,519,019

METHOD FOR DETECTING OR PREDICTING AN ELECTRICAL FAULT

GE AVIATION SYSTEMS LLC, ...

1. A method of detecting and predicting an electrical fault in a node, the method comprising:
transmitting a transmission signal on the node;
generating a reference transmission signal of the transmission signal;
receiving a monitor signal indicative of an actual transmission signal for the transmission signal on the node;
comparing the monitor signal to the reference transmission signal;
determining a fault when the comparison satisfies a fault threshold; and
indicating the determination of the fault by at least recording the fault for subsequent retrieval.

US Pat. No. 9,509,194

GENERATOR ASSEMBLY

GE AVIATION SYSTEMS LLC, ...

1. A generator assembly comprising:
a stator having a core with multiple poles;
stator windings wound about the poles to define winding end turns at an end of the poles;
a heat transfer element having a body defining a face confronting the end turns and comprising an aluminum alloy including
a predetermined amount of Silicon Carbide (SiC) providing the body with a first coefficient of thermal expansion; and

a thermally conductive, dielectric coating deposited on at least a portion of the face of the heat transfer element and in
physical contact with the stator windings, and having a second coefficient of thermal expansion;

wherein the predetermined amount of SiC is selected such that the first and second coefficients of thermal expansion are related
that the thermal expansion of the heat transfer element and the dielectric coating in response to exposure to heat from the
end turns will not result in through-cracking of the dielectric coating during normal operation of the generator.

US Pat. No. 9,401,092

SYSTEM AND METHOD FOR AIRPORT CONTROL USING WAKE DURATION

GE AVIATION SYSTEMS LLC, ...

1. A method of air traffic control at an airport having at least one runway, comprising:
sensing an aircraft type for an aircraft landing or taking off on the at least one runway;
sensing wind conditions at the least one runway corresponding to the landing or taking off of the aircraft;
determining, based on a set of braking criteria, a runway braking operation for the aircraft;
providing the sensed aircraft type and wind conditions as input to a software-implemented algorithm to determine a wake duration;
setting an aircraft separation time based on the determined wake duration and runway braking operation; and
controlling usage of the at least one runway based on the set aircraft separation time.

US Pat. No. 9,256,786

METHOD OF IDENTIFICATION FROM A SPATIAL AND SPECTRAL OBJECT MODEL

GE AVIATION SYSTEMS LLC, ...

1. An object referencing method, comprising:
acquiring, from a first image capture device having a first perspective, a first set of images including spectral image data
and spatial image data;

acquiring, from a second image capture device having a second perspective, a second set of images including spectral image
data and spatial image data;

identifying, based at least in part on the spatial image data, a first set of spatial portions, of an object, based on the
first perspective and a second set of spatial portions, of the object, based on the second perspective;

associating, based at least in part on the spectral image data, spectral signatures with spatial portions included in the
first and second sets of spatial portions; and

generating a profile for the object including the first set and second sets spatial portions and associated spectral signatures.

US Pat. No. 9,400,722

METHOD OF PROVIDING HIGH INTEGRITY PROCESSING

GE AVIATION SYSTEMS LLC, ...

1. A method of communication fault detection in a high integrity processing system having redundant application processors
in a non-lockstep configuration running a same application, which are connected to respective custom logic devices by a first
communication channel and connected to at least one input/output processor by a second communication channel, the method comprising:
transferring a data message between the application processors and the respective custom logic devices via the first communication
channel and transferring the data message between the at least one custom logic device and the at least one input/output processor
via the second communication channel, wherein the data message includes a data field; and

providing a header in the data field having a source field containing source data that uniquely identifies the source of the
message as at least one of the redundant application processors or the input/output processor, an integrity field containing
integrity data indicating whether the data has been cross-checked, and a command field containing command data for the at
least one custom logic device to process-the message according to at least one of the source data or integrity data, wherein
the processing comprises directly cross-checking the data messages from the redundant application processors when the command
data includes an instruction for cross-checking.

US Pat. No. 9,522,744

METHOD FOR MANAGEMENT OF A MAINTENANCE ROUTINE FOR AN AIRCRAFT AND A MAINTENANCE SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A method for management of a maintenance routine for an aircraft with a maintenance system comprising multiple communication
terminals located physically about the aircraft and in data communication with each other, the method comprising:
executing, by the maintenance system, a maintenance software program for the maintenance routine comprising maintenance tests
corresponding to components of the aircraft;

defining, by the maintenance system, an ultimate user; and
assigning a maintenance test to a communications terminal associated with a corresponding component to define an associated
terminal for controlling the execution of the maintenance test by displaying a maintenance test indication on the associated
terminal;

wherein the ultimate user may override the assignment of the maintenance test, including allowing the ultimate user to control
a maintenance test being executed by a different user, or may end the maintenance routine before completion of the maintenance
test.

US Pat. No. 9,543,814

METHOD OF MAKING A HEAT TRANSFER ELEMENT FOR AN ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. A method of making a heat transfer element for an electric machine having a plurality of windings with end turns and the
heat transfer element has a body defining a face for contacting the end turns to transfer heat via conduction from the windings,
the method comprising:
placing at least the face of the heat transfer element in an expanded state by heating the body;
applying a dielectric coating on at least a portion of the face contacting the end turns while the face is in the expanded
state, wherein applying the dielectric coating includes applying the dielectric coating via plasma coating; and

placing the dielectric coating in a compressed state by cooling the heat transfer element;
wherein subsequent expansion of the body in response to an application of heat results in the expansion of the dielectric
coating to move it from a compressed state to an uncompressed state, thereby reducing the likelihood of crack propagation
in the dielectric coating during the expansion of the body.

US Pat. No. 9,490,674

ROTATING RECTIFIER ASSEMBLY FOR ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. A rectifier assembly for placement within a rotating shaft of an electric machine assembly having a first machine providing
an alternating current output and a second machine receiving a direct current input, with the rectifier assembly converting
the alternating current output to the direct current input, the rectifier assembly comprising:
a conductive frame having a least two elongated side elements defining an interior and having axially spaced and axially facing
conductive diode seats coupled to the side elements;

a set of axially spaced diodes supported by the diode seats and having an input electrically coupled with the alternating
current output and an output electrically coupled with the conductive frame;

at least one non-conductive segment supported by the at least one diode seat, wherein the non-conductive segment is opposite
of the diode and has radially arranged mounting connectors; and

an output bus bar electrically coupling the conductive frame to the direct current input of the second machine.

US Pat. No. 9,257,838

CIRCUIT AND METHOD FOR ALLOCATING POWER AMONG GENERATORS

GE AVIATION SYSTEMS LLC, ...

1. A circuit for allocating power among at least two generators to a single load on a shared DC bus, the circuit comprising:
a first generator and a second generator electrically parallel to each other;
a first sharing regulator serially connected to the first generator and a second sharing regulator serially connected to the
second generator;

a first filter serially connected between a first generator output and the DC bus and a second filter serially connected between
a second generator output and the DC bus;

a digital input to each of the first and second sharing regulators including a share command, wherein the share command provides
a desired unequal power ratio to be supplied by the first and second generators;

a first current feedback loop between an output of the first filter and an input of the first sharing regulator; and
a second current feedback loop between an output of the second filter and an input of the second sharing regulator;
wherein the share command at the digital input and current in the first and second current feedback loops will cause the first
and second sharing regulators to independently alter the power of the first generator at the first generator output and the
second generator at the second generator output, thereby allocating the load on the DC bus according to the power ratio of
the share command.

US Pat. No. 9,383,261

METHOD OF ELIMINATING SPURIOUS SIGNALS AND A RELATIVE NAVIGATION SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A method of eliminating spurious optical signals received by a relative navigation system, the method comprising:
projecting into space from a grid generator, on a first object, a polarized light having a first orientation to form at least
one optical grid line for an optical grid defining a first relative reference frame;

detecting, by a detector module at a second object having a second relative reference frame, the polarized light having the
first orientation; and

filtering, at the second object, polarized light having a second orientation, which is different from the first orientation
to eliminate spurious optical signals having the second orientation, which would otherwise appear as directly propagated light
signals to the detector module; and

wherein the detector module determines its position within the first relative reference frame based on the detected light
having the first orientation.

US Pat. No. 9,369,029

ROTATING RECTIFIER ASSEMBLY FOR ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. A rectifier assembly for placement within a rotating shaft of an electric machine assembly having a first machine providing
an alternating current output and a second machine receiving a direct current input, with the rectifier assembly converting
the alternating current output to the direct current input, the rectifier assembly comprising:
opposing first and second conductive segments, each conductive segment having a substantially arcuate cross section;
opposing first and second non-conductive segments, each non-conductive segment having a substantially arcuate cross section,
and coupling the first and second conductive segments such that the arcuate cross sections of the first and second conductive
segments and arcuate cross sections of the first and section non-conductive segments collectively define an annular elongated
rectifier structure defining an interior and extend in a longitudinal direction, with the first and second conductive segments
and the first and second non-conductive segments in a radially alternating adjacent arrangement in the annular rectifier structure;

a set of diode seats axially arranged along the longitudinal direction and provided on each of the first and second conductive
segments so as to face the interior, with a diode seat in one set being paired with a diode seat in the other set to define
axially spaced pairs of diode seats;

a biasing element overlying each of the diode seats; and
a non-conductive support for each of the diode seats and holding the biasing element in position relative to the diode seat;
wherein a diode seated on the diode seat is biased by the biasing element against the diode seat and held in place by the
non-conductive support.

US Pat. No. 9,217,417

RAM AIR TURBINE GENERATOR WITH EXTERNAL ROTOR HAVING PERMANENT MAGNETS

GE AVIATION SYSTEMS LLC, ...

1. A ram air turbine generator for an aircraft comprising:
a mounting plate configured to close a first end of a generator housing and mount to a pylon extendable from an aircraft;
a first shaft fixedly mounted to the mounting plate;
a stator fixedly mounted to the first shaft and having multiple windings;
a rotor housing rotatably mounted to the first shaft and at least partially encasing the stator;
multiple axially-oriented, permanent magnets, each defining a pole of the rotor and mounted to an inner surface of the rotor
housing in an orientation substantially parallel to the first shaft; and

a propeller operably coupled to the rotor housing via a second shaft and having multiple blades;
wherein air flowing over the blades rotates the propeller to rotate the second shaft, which rotates the rotor housing and
permanent magnets about the multiple windings to generate an electric current in the windings.

US Pat. No. 9,170,907

METHOD OF PROVIDING HIGH INTEGRITY PROCESSING

GE Aviation Systems LLC, ...

1. A method of providing synchronization and integrity checking in a high integrity processing system having at least two
redundant processing lanes, with each lane having an application processor (AP), with the APs running the same application
software in a non-lockstep configuration, and outputting transactions requiring access to an addressable space, the method
comprising:
outputting a first transaction from a first AP in a first processing lane and running application software in a non-lockstep
configuration;

storing the first transaction in a second buffer of a second processing lane and associated with a second AP;
effecting a processing of the first transaction in the first processing lane;
storing the effected processing of the first transaction in the second buffer;
outputting a second transaction from the second AP running the same application software in a non-lockstep configuration;
storing the second transaction in the second buffer;
comparing the first and second transactions to determine if they match; and
returning the effected processing of the first transaction to the second AP from the second buffer when the first and second
transactions match.

US Pat. No. 9,482,552

METHOD OF SIMULATING A REAL-TIME AIRCRAFT SYSTEM INPUT TO AN AVIONICS COMPONENT

GE AVIATION SYSTEMS LLC, ...

1. A method of simulating a real-time, aircraft system input to an avionics component for an aircraft, the method comprising:
receiving, during a non-flight operation, a user demand for a sequence of aircraft system input, wherein the aircraft system
input includes inputs generated during previously concluded flight operations;

retrieving data streams corresponding to the user demand from a data-base of data streams previously recorded from real-time
data streams generated during the previously concluded flight operations;

time-synchronizing the retrieved data streams;
providing the time-synchronized data streams to a deterministic avionics data bus communicatively coupled with the avionics
component; and

selective performing a simulation methodology on the avionics component in response to the time-synchronize data streams provided
by the deterministic avionics data bus, wherein the simulation methodology is selectively performed as if the avionics component
is operating under normal flight operations.

US Pat. No. 9,383,738

METHOD FOR HIGH FIDELITY MODELING OF AN AIRCRAFT ELECTRICAL POWER SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A method for modeling an electrical power system of an aircraft, comprising:
using a general purpose graphic processing unit-based supercomputer cluster to execute computer executable components stored
in a memory to perform the following acts:

obtaining a set of initial characteristics for the electrical power system;
modeling, based on electrical characteristics included in the set of initial characteristics, a set of currents and voltages
via a power electronics circuit based-solver;

modeling, via a field-based solver, at least one characteristic included in the set of initial characteristics, wherein the
modeling includes:

initiating a mesh for the at least one characteristic,
forming a matrix based at least in part on the mesh, and
solving the matrix, via a sparse linear equation solver, to represent the state of the at least one characteristic,
wherein the sparse linear equation solver includes at least one of finite element analysis or finite difference analysis,
and at least one of: the initiating the mesh, the forming the matrix, or the solving the matrix are distributed to multiple
graphic processing units; and

forming a final model of the electrical power system by collating outputs of the circuit-based solver and the field-based
solver.

US Pat. No. 9,313,276

METHOD FOR TRANSMITTING AIRCRAFT FLIGHT DATA

GE AVIATION SYSTEMS LLC, ...

1. A method of transmitting aircraft flight data for an aircraft to a destination server via a wireless communication link,
the method comprising:
determining an operational status of the aircraft, wherein the operational status includes a normal mode, an emergency mode,
a critical mode, and a user-defined mode;

determining a set of flight data to be transmitted based at least in part on the determined operational status of the aircraft,
wherein the set of flight data to be transmitted includes: flight recorder data when it is determined the operational status
of the aircraft is in the critical mode, at least one of fuel data or navigational data when it is determined the operational
status of the aircraft is in the normal mode, at least one of fault data, electrical and power systems data, or propulsion
data when it is determined the operational status of the aircraft is in the emergency mode;

assigning a priority value to at least one subset of the flight data based on a set of criteria;
assigning bandwidth to the at least one subset of the flight data based on the priority; and
transmitting the at least one subset of flight data over the wireless communication link to the destination server based on
the priority value and the bandwidth.

US Pat. No. 9,170,435

METHOD OF FORMING A GRID DEFINING A FIRST RELATIVE REFERENCE FRAME

GE Aviation Systems LLC, ...

1. A method of projecting into space, from a first object, a plurality of modulated lines to form a grid defining a first
relative reference frame, the method comprising:
projecting polarized light having a first orientation to form a horizontal grid line projecting into space from the first
object;

projecting polarized light having a second orientation different than the first orientation to form a vertical grid line projecting
into space from the first object;

modulating the horizontal grid line to carry a first grid word comprised of a number of modulated bits to identify the horizontal
grid line within the grid by the modulated first grid word; and

modulating the vertical grid line to carry a second grid word comprised of a number of modulated bits to identify the horizontal
grid line within the grid by the modulated second grid word.

US Pat. No. 9,251,502

MAINTENANCE SYSTEM FOR AIRCRAFT FLEET AND METHOD FOR PLANNING MAINTENANCE

GE AVIATION SYSTEMS LLC, ...

1. A maintenance system for a fleet of aircraft, the system comprising:
a maintenance database comprising at least one maintenance schedule comprising a list of routine maintenance actions for the
aircraft;

a non-routine maintenance database comprising at least non-routine maintenance historical data for the aircraft;
a health database comprising operation data for the aircraft; and
a planning module configured to query the maintenance database, non-routine maintenance database, and the health database,
such that the planning module is configured to identify anticipated non-routine maintenance tasks having a threshold probability
of occurrence based on historical data for the fleet and aircraft health data and having a correlation with at least one of
the routine maintenance actions, wherein the correlation includes that the anticipated non-routine maintenance tasks and the
at least one of the routine maintenance actions are located in a same area of the aircraft, and the correlation is based on
the timing and duration of the routine maintenance action in relation to an amount of the threshold probability of the occurrence
of the identified anticipated non-routine maintenance tasks; and

a generation module configured to generate a task schedule that is a combination of the maintenance schedule and at least
one of the identified anticipated non-routine maintenance tasks having the threshold probability of occurring, wherein the
generation module generates the task schedule prior to initiating a maintenance action.

US Pat. No. 9,322,651

SYSTEM AND METHOD FOR UTILIZING MULTIPLE SENSORS

GE AVIATION SYSTEMS LLC, ...

1. A sensor system having multiple sensors coupled to at least one aircraft, wherein each of the sensors is operably coupled
to the at least one aircraft through a tether, each sensor coupled proximate to one end of each tether and the other end of
each tether being attached to the aircraft, the sensor system, comprising:
a grid generator projecting into a space behind the aircraft a relative navigation grid;
multiple sensors located within the relative navigation grid and providing sensor outputs;
a position detector configured to detect the position of each of the multiple sensors relative to the relative navigation
grid and providing corresponding position outputs; and

a coordination engine configured to coordinate the multiple sensor outputs based on the corresponding position outputs provided
by the position detector and generate a single coordinated sensor output, wherein the coordination engine uses the precise
position of the multiple sensors in the navigation grid to provide coordination data necessary to combine the data into the
single coordinated sensor output such that dimensional artifacts can be extracted from the single coordinated sensor output
and true wide field stereolithography allowed.

US Pat. No. 9,273,705

AIRCRAFT HYDRAULIC SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. An aircraft hydraulic system for operating a plurality of hydraulically-operated actuators in the aircraft, comprising:
a hydraulic reservoir in which hydraulic fluid is stored;
a hydraulic distribution system coupling the hydraulic reservoir to the actuators and having a main flow line coupled to the
hydraulic reservoir;

a hydraulic pump fluidly coupled to the main flow line and the hydraulic reservoir to pump hydraulic fluid from the hydraulic
reservoir to the main flow line;

a main filtration system fluidly coupled to the main flow line upstream of at least some of the actuators; and
a self-cleaning filter fluidly coupled upstream of the main filtration system and having a body with a main flow portion,
coupled in-line to the main flow line, and a branch portion, with a branch filter located within the body to filter hydraulic
fluid passing through the branch portion and oriented relative to the main flow portion such that hydraulic fluid flowing
through the main flow portion cleans the branch filter.

US Pat. No. 9,217,436

IMPELLER FAN ASSEMBLY

GE AVIATION SYSTEMS LLC, ...

1. An impeller fan assembly comprising:
a housing having an inner peripheral wall defining a flow through opening;
a stator located within the flow through opening and comprising an annular array of stationary blades provided along the inner
peripheral wall;

a rotor comprising a hub and an annular array of non-stationary blades extending from the hub;
at least two spaced apart bearings mounted to the stator;
a shaft having a hollow portion rotatably supported by the bearings for rotation about a rotational axis;
a sump provided in the stator; and
a screw pump provided within the hollow portion of the shaft and having a screw pump inlet fluidly coupled to the sump and
a screw pump outlet in fluid communication with the bearings, whereby rotation of the screw pump pumps fluid from the sump
to the bearings,

wherein the sump spans the bearings such that when the shaft is oriented such that the rotational axis is horizontal, the
bearings are at least partially immersed within the fluid in the sump, and when the shaft is oriented such that the rotational
axis is vertical, at least one of the bearings is not immersed in the fluid within the sump.

US Pat. No. 9,485,113

DATA COMMUNICATIONS NETWORK FOR AN AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

1. A method of providing current operation data for a plurality of data generating components connected to a data communications
network of an aircraft and sending at least one data frame having an identifier and corresponding raw data, the method comprising:
a) generating a current value table (CVT) in memory connected to the communications network, by reserving a predetermined
first portion of the memory defining a memory address allocation for a set of identifiers and corresponding raw data, and
generating at least two circular buffers in the memory by reserving second portion of memory, different from the first portion
of the memory;

b) receiving a data frame over the network from at least one of the data generating components;
c) parsing the received data frame into the identifier and corresponding raw data;
d) determining, by way of a software look up table, if the parsed identifier corresponds to the reserved memory address allocation;
e) when the parsed identifier corresponds to the reserved memory address allocation, updating the determined reserved memory
address of the CVT with the parsed raw data by writing the parsed raw data to the reserved memory address, or, when the parsed
identifier does not correspond to the reserved memory address allocation, determining which one of the at least two circular
buffers to update based on the available data transmission rate of at least one of the port of destination, a UDP destination
address, an IP destination address, or a MAC destination address, and updating the one of the at least two circular buffers
with the parsed raw data by writing the parsed raw data to the one of the at least two circular buffers; and

f) repeating a)-f) for subsequent data frames for the data generating components whereby the CVT maintains the most up-to-date
data.

US Pat. No. 9,430,846

METHOD OF TRACKING OBJECTS USING HYPERSPECTRAL IMAGERY

GE AVIATION SYSTEMS LLC, ...

1. A method of tracking motion of at least one object of a group of moving objects using hyperspectral imaging, comprising:
obtaining a series of hyperspectral image frames;
comparing frames in the series to a template to determine changes in the image between frames;
identifying a group of pixels in the frames associated with the changes;
identifying the changes as motion of the moving objects;
correlating the pixel groups frame-to-frame to spatially determine at least one parameter of the motion of the objects; and
correlating the pixel groups with a spectral reflectance profile associated with the at least one object, and distinguishably
tracking, based on the spectral reflectance profile, the at least one object from the other moving objects.

US Pat. No. 9,435,635

SYSTEM AND METHODS OF DETECTING AN INTRUDING OBJECT IN A RELATIVE NAVIGATION SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A method of intrusion detection for a relative navigation system, the method comprising:
repeatedly projecting, from a grid generator, a set of lines defining a grid in three dimensional space to define a field
bounded by the projected grid and encoded with grid data configured to identify predetermined points on the grid; and

determining a presence of an intruding object within the field.

US Pat. No. 9,652,901

HEALTH MANAGEMENT UNIT AND METHOD FOR MONITORING HEALTH INFORMATION AND TRANSMITTING INFORMATION FROM THE AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

12. A health management unit for an aircraft having multiple systems for operating the aircraft and multiple radios operating
on different protocols for transmitting a message off the aircraft, the health management unit comprising:
a health management module receiving health-related information from one or more of the multiple systems, and creating a health-related
message from at least some of the health-related information along with a corresponding priority level; and

a communication module controlling assignment and transmission of the health-related message to one of the multiple radios
operating on different protocols based on capabilities of the multiple radios, wherein the capabilities comprises of: operative
or inoperative status, currently transmitting status, and availability during current portion of a flight plan, and priority
of the health-related message.

US Pat. No. 9,590,460

ELECTRIC MACHINE WITH A SLOT LINER

GE AVIATION SYSTEMS LLC, ...

1. An electrical machine comprising:
a rotor;
a stator having a core with at least one winding slot having an open top and terminating in opposing open ends;
a slot liner provided within the winding slot and having an electrical insulating element defining an open top and terminating
in opposing ends, which extend beyond the slot open ends, and a strengthening strip provided at each of the slot liner ends
and solely on an outer surface of the electrical insulating element; and

wherein the strengthening strip reduces the splitting of the corresponding slot liner end during an automatic winding process,
and is coupled with the slot liner via an adhesive.

US Pat. No. 9,810,155

METHOD FOR STARTING AIRCRAFT ENGINES

GE AVIATION SYSTEMS LLC, ...

1. A method of starting an aircraft having at least a first turbine engine having a first starter/generator (S/G) and a second
turbine engine having a second S/G using at least one inverter/converter and at least one of an AC power source having an
AC power output and a first DC power source having a DC power output, the method comprising:
selectively starting at least one of the first S/G or second S/G in an AC start mode, where the AC power output is supplied
to a first inverter/converter, which converts the AC power output to a second DC power output supplied to a second inverter/converter,
which inverts the second DC power output to a second AC power output, which is supplied to the at least one of the first S/G
or second S/G, and in a DC start mode, where the DC power output is supplied to the inverter/converter, which inverts the
DC power output to a second AC power output, which is then supplied to the at least one of the first S/G or second S/G.

US Pat. No. 9,589,318

METHOD AND SYSTEM FOR GENERATING AIRPORT SURFACE MAP GRAPHICS IN AIRCRAFT COCKPIT DISPLAYS

GE AVIATION SYSTEMS LLC, ...

1. A method of reducing a size of data representing an image in a graphical display wherein the data comprises triangle strings
representing polygons that form the image, the method comprising:
determining a size of a pixel in the image;
selecting a triangle string that defines a first polygon, wherein the triangle string consists of a set of vertices;
selecting a subset of vertices from the set of vertices;
determining a second polygon from the subset of vertices;
comparing the size of a pixel in the image to a dimension of the second polygon;
determining a number of triangles in the triangle string;
in response to the dimension of the second polygon being smaller than or about equal to the size of the pixel in the image,
reducing the number of triangles in the triangle string to at least one of one triangle or two triangles; and

in response to the dimension of the second polygon being larger than the size of the pixel in the image, leaving the number
of triangles in the triangle string unchanged.

US Pat. No. 9,475,590

METHOD OF IMPLEMENTING A MAINTENANCE SCHEDULE FOR AN AIRCRAFT AND A MAINTENANCE SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A method of implementing a maintenance schedule for an aircraft with a maintenance system comprising multiple communication
terminals located physically about the aircraft and in data communication with each other, the method comprising:
displaying, by a computing element of the maintenance system, a maintenance routine comprising maintenance tests corresponding
to components of the aircraft on a selected communication terminal of the multiple communication terminals, wherein the selected
communication terminal is a control terminal;

assigning, by the control terminal, a maintenance test of the maintenance tests to be performed by a user on a component of
the aircraft to another communication terminal of the multiple communication terminals by causing an indication of the maintenance
test to be displayed on the another communication terminal;

assigning, by the control terminal, another maintenance test of the maintenance tests to be performed by at least one of the
user or another user on another component of the aircraft to a further communication terminal of the multiple communication
terminals by causing an indication of the another maintenance test to be displayed on the further communication terminal;

sequentially assigning the another maintenance test to the further communication terminal after the maintenance test is identified
as being completed on the another communication terminal; and

upon completion of the maintenance tests, displaying a maintenance routine completion on the control terminal.

US Pat. No. 9,559,569

ARRANGEMENT FOR COOLING AN ELECTRIC MACHINE WITH A LAYER OF THERMALLY CONDUCTING AND ELECTRICALLY INSULATING MATERIAL

GE AVIATION SYSTEMS LLC, ...

1. An electric machine comprising:
a rotor having a set of rotor poles;
a stator having a set of stator poles;
at least one rotor pole in the set of rotor poles being formed by a rotor core with a post and wire wound about the post to
form a rotor winding, with the rotor winding having at least one end turn;

at least one stator pole in the set of stator poles being formed by a stator core with a post and wire wound about the post
to form a stator winding, with the stator winding having at least one end turn;

a liquid cooling conduit passing through the at least one rotor core, proximate to the at least one winding;
a layer of thermally conducting and electrically insulating material encircling the rotor winding and provided between a thermally
conductive cooling fin and the rotor winding, and the thermally conductive cooling fin encircling the insulating material
and provided between the insulating material and the conduit,

wherein the insulating material abuts both the rotor winding and the thermally conductive cooling fin to increase the thermal
conduction from the rotor winding to the liquid cooling conduit whereby liquid coolant passing through the liquid cooling
conduit will dissipate heat from the rotor winding, and the thermally conductive cooling fin is mounted to a portion of the
liquid cooling conduit, and the layer of thermally conducting and electrically insulating material has a conductivity equal
to or greater than about 0.75 W/mC;

a cooling system having at least one cooling passage passing through a jacket surrounding the stator core;
at least one coil support mounted between the cooling passage and the at least one end turn of the stator core, wherein the
coil support is conform-coated with a layer of thermally conducting and electrically insulating material to exchange heat
from the end turn through the coil support to the cooling passage without wetting the stator winding.

US Pat. No. 9,559,507

MOUNTING BRACKET ASSEMBLY FOR AN ELECTRICAL CABLE

GE AVIATION SYSTEMS LLC, ...

1. A mounting bracket assembly for an electrical cable, comprising:
a base configured to mount to a portion of an electricity-consuming apparatus;
a strain relief element including a crimp that fixes a portion of the electrical cable relative to the base;
a collar that extends from the crimp, wherein the crimp telescopically couples with a Faraday shield included in the electrical
cable, and the collar has an inner opening that enables passage of at least one conductor included in the electric cable,
wherein the Faraday shield surrounds the at least one conductor, and a non-conducting cable protector included in the electrical
cable surrounds the collar;

a first rib and a second rib axially spaced on the outer surface of the collar, wherein the second rib is positioned closer
to the crimp than the first rib, and the collar is configured to have a first ring clamp, positioned between the Faraday shield
and the non-conducting cable protector, to clamp the Faraday shield to the collar between the first rib and the second rib,
and a second ring clamp, positioned between the second rib and the crimp, to secure the non-conducting cable protector; and

an electrical ground path extending from the collar to the base such that when the cable is fixed by the strain relief element,
the collar is received within the Faraday shield to establish an electrical grounding of the Faraday shield to the electricity-consuming
apparatus via the electrical ground path.

US Pat. No. 9,590,477

ROTATING RECTIFIER ASSEMBLY FOR ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. A rectifier assembly for placement within a rotating shaft of an electric machine assembly having a first machine providing
an alternating current output and a second machine receiving a direct current input, the rectifier assembly comprising:
a rectifying subassembly having a bus bar electrically coupling with at least one of the direct current input of the second
machine or the alternating current output of the first machine, and wherein the rectifier subassembly is configured to convert
the alternating current output to the direct current input; and

a non-conductive sleeve having an outer surface and an inner surface defining an interior having a keyway, and configured
to axially receive the rectifying subassembly;

wherein the bus bar itself is a key, which, when radially aligned with the keyway, provides for the keyed axial insertion
of the rectifier subassembly within the sleeve, such that the rectifying subassembly is radially indexed within the sleeve
to properly align the rectifying subassembly and the sleeve.

US Pat. No. 9,853,714

DATA COMMUNICATIONS NETWORK FOR AN AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

1. A method of controlling data communication in a communications network having a plurality of remote input units (RIUs)
providing data and a plurality of subscriber units utilizing at least some of the data, the method comprising:
receiving, at an ingress port scheduler, the data;
generating, in the ingress port scheduler, a flow index based on a port number and selected bits of the data;
receiving, at a central data server (CDS), the data and the flow index;
forming, in the CDS, a current value table (CVT) generated from the most recent data from the RIUs;
determining, using the flow index, a first set of the data, wherein the first set of the data is comprised of sampling-type
data, to maintain in the CVT;

writing, via a first data concentrator, the first set of the data in the CVT;
determining, using the flow index, a second set of the data, wherein the second set of the data is comprised of queuing-type
data, to maintain in at least two circular buffers included in the CDS, wherein the at least two circular buffers are defined
by the data rate at which each operates at and are segregated by egress port speed, and wherein the flow index determines
which of the at least two circular buffers the second set of the data is maintained;

writing, via a second data concentrator, the second set of the data in the at least two circular buffers;
generating a custom message derived from a portion of the data in at least one of the CVT or the at least one circular buffer
for at least one of the subscriber units based on format requirements of the at least one of the subscriber units; and

sending the custom message over the communications network to the at least one of the subscriber units.

US Pat. No. 9,591,005

AVIONICS INTRUSION DETECTION SYSTEM AND METHOD OF DETERMINING INTRUSION OF AN AVIONICS COMPONENT OR SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A method of determining intrusion of an avionics component or avionics system in an aircraft having multiple avionics components
and avionics systems communicating over an aircraft communications network monitored by an intrusion system, the method comprising:
monitoring, by the intrusion system, data communication over the aircraft communications network for one or more of the avionics
components or avionics systems;

comparing, by the intrusion system, the monitored communications for at least one of the avionics components or avionics systems
to a corresponding operational profile that includes acceptable interactions between multiple avionics components or avionics
systems;

determining an intrusion for the at least one of the avionics components or avionics systems when the comparison indicates
that the at least one of the avionics components or avionics systems satisfies an intrusion profile based on data redundancy
checks and trend not matching; and

providing an alert of the determined intrusion.

US Pat. No. 9,611,947

VALVE ASSEMBLY AND METHOD OF CONTROLLING FLOW OF FLUID

GE AVIATION SYSTEMS LLC, ...

1. A valve assembly comprising:
a plenum having first, second, and third air source ports;
a flapper valve assembly pivotally movable between a first position, where the first air source port is closed by the flapper
valve assembly and the second and third air source ports are open and in fluid communication, and a second position, where
the second air source port is closed by the flapper valve assembly and the first and third air source ports are open and in
fluid communication;

a biasing device imparting a biasing force to the flapper valve assembly to bias the flapper valve assembly into the first
position to close off the first air source port; and

an air dam provided on the flapper valve assembly to confront the first air source port when the flapper valve assembly is
in the first position, wherein the air dam includes a wall, shaped to avoid contact with the plenum or the first air source
port, projecting from the flapper valve assembly, and air acting on the air dam generates a pressure force opposing the biasing
force.

US Pat. No. 9,852,643

TRAJECTORY AMENDMENT AND ARRIVAL TIME SLOT PROVISION SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A computing system for providing trajectory amendments, the system comprising:
one or more processors; and
one or more memory devices, the one or more memory devices storing instructions that when executed by the one or more processors
cause the one or more processors to:

identify an operator associated with an aircraft;
send an output to one or more computing devices of the operator associated with the aircraft for display via a user interface,
wherein the output is indicative of the aircraft, a trajectory amendment associated with the aircraft, and a projected operations
value associated with the trajectory amendment, and wherein the user interface allows for a selection of the trajectory amendment;

receive a set of data indicating that the operator associated with the aircraft has selected the trajectory amendment; and
send a second set of data indicating one or more parameters associated with the trajectory amendment to the one or more computing
devices of the operator associated with the aircraft.

US Pat. No. 9,606,147

APPARATUS FOR HIGH BANDWIDTH CURRENT SENSING

GE AVIATION SYSTEMS LLC, ...

1. A device for measuring electrical current in a line comprising:
a Hall effect sensor disposed with the line extending axially therethrough wherein a first response is generated by electrical
current in the line;

a current transformer disposed with the line extending axially therethrough and connected in series to the Hall effect sensor,
and having a low permeability core, wherein a second response is generated by the electrical current in the line; and

an equalizer connected to the Hall effect sensor and to the current transformer configured to flatten the first and second
responses relative to each other, the equalizer including a circuit to shape the first and second responses,

wherein a permeability magnetic path length and cross section is selected such that low frequency roll-off of the current
transformer is at a lower frequency than high frequency roll-off of the Hall effect sensor.

US Pat. No. 9,660,446

POWER DISTRIBUTION SYSTEM FOR AN AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

1. An aircraft power distribution system, comprising:
a first DC power distribution bus, a second DC power distribution bus, and a third DC power distribution bus;
a DC power source coupled with at least one of the first, second, or third DC power distribution buses;
a set of electrical couplings, wherein electrical couplings included in the set are coupled between the first, second, and
third DC power distribution buses, and the set of electrical couplings enable transmission of power between the first, second
and third DC power distribution buses; and

a solid state power controller positioned in-line on each electrical coupling, each solid state power controller comprising
two power switches in a back-to-back configuration, each power switch comprising a field-effect transistor (FET) connected
across a Schottky diode;

wherein a configuration of the first, second and third DC power distribution buses and the solid state power controllers defines
a ring-type bus configuration, and the solid state power controllers selectively couple and decouple the first, second, and
third DC power distribution buses across the set of electrical couplings.

US Pat. No. 9,692,322

INVERTER WITH IMPROVED SHOOT THROUGH IMMUNITY

GE AVIATION SYSTEMS LLC, ...

1. An inverter phase leg in a DC to AC converter comprising a high supply line and a low supply line across which a DC voltage
may be provided, a high side gate controlled switch connected to the high supply line and a low side gate controlled switch
connected to the low supply line, the switches connected between the high supply line and the low supply line with an output
node between the high side switch and the low side switch, comprising:
an inverting driver connected to the high side gate controlled switch and having an input voltage from a control signal, an
output voltage for switching the high side gate controlled switch, and a driving voltage; and

a source of a constant biasing first DC voltage between the output node and the inverting driver;
wherein the driving voltage is set to cause the output voltage of the inverting driver to be zero until the input voltage
exceeds the first DC voltage.

US Pat. No. 9,794,340

MECHANISM AND METHOD FOR ACCESSING DATA IN A SHARED MEMORY

GE AVIATION SYSTEMS LLC, ...

1. A mechanism for accessing data in a shared memory by one or more clients, comprising:
an allocation of data in the shared memory into at least one topic, wherein the allocation of data is accessible by a predetermined
constant address;

the at least one topic having a plurality of buffers, wherein a number of the buffers is equal to a number of the clients
accessing the at least one topic, wherein the plurality of buffers comprises two or more respective buffers for each of at
least one server accessing the at least one topic, and wherein the one or more clients and the at least one server have an
active access pointer; and

an active access pointer director to direct a number of active access pointers to the plurality of buffers based on a transaction
request from the one or more clients or the at least one server;

wherein the plurality of buffers comprises one or more respective buffers that include the most recent data in the shared
memory, and at least one buffer that is available to access data in the shared memory;

wherein the number of active access pointers are allocated among the plurality of buffers by the active access pointer director
using machine assembly language transactions configured to perform a zero-copy data exchange at an operating system level;
and

wherein the machine assembly language transactions provide the mechanism with asynchronous inter-process data communications
between the at least one server and the one or more clients in the shared memory.

US Pat. No. 9,749,256

DATA COMMUNICATIONS NETWORK FOR AN AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

1. A method for servicing multiple data queues in communication with a data communications network for an aircraft having
a scheduler and being serviced by a single server, the method comprising:
determining a priority value for data queues included in the set of data queues, by the scheduler, to define a dataset of
priority values;

determining a fullness value for data queues included in the set of data queues, by the scheduler, to define a data set of
fullness values;

determining a scheduling ruleset by addressing a lookup table based on a counter output and fullness value for data queues
included in the set of data queues, wherein the counter output is increased at intervals of a fixed period; and

servicing the data queues based on the determined dataset of priority values and scheduling ruleset.

US Pat. No. 9,621,011

STATOR ASSEMBLY

GE AVIATION SYSTEMS LLC, ...

1. A stator assembly for an electric machine comprising:
a stator core having multiple posts;
multiple windings, with a winding provided on each of the posts;
a stator sleeve located about the stator core and an inner surface confronting the windings and comprising:
a convection reservoir extending along and in a thermally conductive confronting relationship with at least a portion of the
windings,

a delivery reservoir extending along at least a portion of the length of the convection, and
a plurality of transfer ports fluidly coupling the convection reservoir with the delivery reservoir; and
a thermally conductive sleeve defining the inner surface and confronting the stator core, and defining a second surface, spaced
from the inner surface, confronting the stator sleeve, and defining at least a portion of the convection reservoir;

wherein the convection reservoir is located between the delivery reservoir and the inner surface, and the delivery reservoir
has an inlet and the convection reservoir has an outlet to define a coolant flow path, whereby coolant can be provided to
the inlet where it flows through the delivery reservoir, through the plurality of transfer ports to the convection reservoir,
and out the outlet.

US Pat. No. 10,070,562

METHOD AND APPARATUS FOR HEAT-DISSIPATION IN AN AVIONICS CHASSIS

GE Aviation Systems LLC, ...

1. An avionics chassis assembly, comprising: a housing having an outer surface, defining an exterior of the housing, an inner surface, defining an interior of the housing, and a set of walls at least partially separating the exterior of the housing from the interior of the housing; a heat generating component located within the interior of the housing; a thermal plane thermally coupled to the heat generating component and configured to direct heat away from the heat generating component; and an electronic circuit board wherein the heat generating component is mounted to the electronic circuit board, wherein an opening is included in the housing and the opening is configured to receive at least a portion of the thermal plane such that the at least a portion of the thermal plane passes through the opening and is located exteriorly of the housing to define an extending thermal plane portion, wherein the thermal plane overlies the electronic circuit board, and wherein the extending thermal plane portion comprises electromagnetic interference seals to ensure environmental compatibility with the interior of the housing; and wherein the housing comprises a selectively removable front cover, wherein the opening is located within the front cover, and wherein the opening comprises a laterally-extending slot.

US Pat. No. 9,745,052

DETERMINING ENHANCED OPERATING STATE FOR AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

1. A computer-implemented method of determining an operating state for an aircraft, the method comprising:
A) accessing, by one or more computing devices located on an aircraft, a database of precomputed operating parameters associated
with aircraft trim, the precomputed operating parameters determined without real time measurements;

B) receiving, by the one or more computing devices, a real time measurement of one or more dynamic operating parameters associated
with the aircraft flying at a current operating state having a current cost parameter;

C) determining, by the one or more computing devices, an aircraft trim operating parameter from the precomputed operating
parameters based on data indicative of a candidate operating point of the aircraft, the aircraft trim operating parameter
determined independent of the real time measurement of the one or more dynamic parameters;

D) determining, by the one or more computing devices, a candidate enhanced operating state for the aircraft during flight
of the aircraft having a cost parameter determined by at least the aircraft trim operating parameter and the real time measurement
of the one or more dynamic operating parameters;

E) comparing the cost parameter for the candidate enhanced operating state with the current cost parameter of the current
operating state; and

F) when the cost parameter for the candidate enhanced operating state is reduced compared with the current cost parameter,
operating the aircraft in accordance with the candidate enhanced operating state for the control of the aircraft, and when
the cost parameter for the candidate enhanced operating state is not reduced compared with the current cost parameter, iterating
through steps C)-F) with a new candidate operating point of the aircraft.

US Pat. No. 9,710,313

METHOD AND SYSTEM FOR ENSURING INTEGRITY OF CRITICAL DATA

GE AVIATION SYSTEMS LLC, ...

1. A method of ensuring integrity of critical data stored in a shared memory, the method comprising:
executing a restartable processing thread;
continuously monitoring, by a broker thread, the restartable processing thread and determining whether the restartable thread
is manipulating the critical data;

storing a pre-operation hook and a post-operation hook in a portion of memory included in a semaphore, wherein the broker
thread executes the pre-operation hook which sets a semaphore indicator to a first state, indicating a restartable processing
thread is manipulating the critical data or executes the post-operation hook which sets the semaphore indicator to a second
state, indicating that the restartable processing thread is not manipulating the critical data;

setting the semaphore indicator to either the first state or the second state based on whether the restartable thread is manipulating
the critical data;

receiving, by the broker thread, a restart request during the execution of the restartable processing thread;
automatically determining whether the broker thread has executed the pre-operation hook or the post-operation hook by checking
the semaphore indicator;

in response to the restart request, restarting the restartable processing thread when the semaphore is in the second state
and denying the restart request when the semaphore is in the first state.

US Pat. No. 9,943,016

COOLING STRUCTURE

GE AVIATION SYSTEMS LLC, ...

1. A cooling structure for a heat-producing power magnetics device having at least two faces, comprising:a first cold plate having a first coolant passage and conductively coupled with at least the first face of the magnetics device and wherein at least a portion of heat generated by the power magnetics device is removed from the device by way of thermal conduction to the first coolant passage;
a second cold plate having a second coolant passage and conductively coupled with at least the second face of the magnetics device and wherein at least another portion of heat generated by the power magnetics device is removed from the device by way of thermal conduction to the second coolant passage;
a coolant reservoir fluidly coupled with the first and second coolant passages; and
a third cold plate having a third coolant passage;
wherein the removal of heat from the device maintains the temperature of the device within a predetermined amount below the Curie temperature of the device, the power magnetics device comprises a first power magnetics device and a second power magnetics device, the first cold plate and second cold plate are thermally coupled with the respective first and second faces of the first power magnetics device, and the first cold plate and third cold plate are thermally coupled with the respective first and second faces of the second power magnetics device.

US Pat. No. 9,628,008

METHOD AND GENERATOR CONTROL UNIT FOR CONFIGURING AN OUTPUT FROM A GENERATOR

GE AVIATION SYSTEMS LLC, ...

1. A generator control unit comprising:
a four-leg power bridge having an input, three output phases, and a neutral phase output, wherein the input is operably coupled
with a generator direct current (DC) power output and the four-leg power bridge includes a first selectively enablable switchable
element having an alternating current (AC) position that electrically de-couples the three output phases and a DC position
that electrically couples the three output phases; and

a controller communicatively coupled with the four-leg power bridge and configured to operate the four-leg power bridge as
at least one of a DC-to-DC power converter or a DC-to-AC power inverter;

wherein the generator control unit is selectably operable in an AC operating mode when the first selectively enablable switchable
element is in the AC position and the controller operably controls the four-leg power bridge as a DC-to-AC power inverter,
and operable in a DC operating mode when the first selectively enablable switchable element is in the DC position and the
controller operably controls the four-leg power bridge as a DC-to-DC power converter.

US Pat. No. 9,837,868

ROTOR ASSEMBLY FOR AN ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. A rotor assembly for an electric machine comprising:
a rotor core having at least one post and a set of coolant passages included in a rotor of the rotor core;
a winding wound around the post having axial segments that run along a opposite first and second sides of the post, and an
end portion extending axially beyond a third side of the post, connecting the axial segments, to define an end turn segment,
wherein the post at least partially defines a first face for receiving the winding; and

a coolant tube, that at least partially encompasses the post and defines a second face for receiving the rotor windings, wherein
the coolant tube is located adjacent to, and extending axially in parallel with, the axial segments and at least partially
extending in parallel with the end turn segment; and

an end tube transition that defines a transition portion of the coolant tube, and fluidly couples the coolant tube to the
set of coolant passages included in the rotor,

wherein the coolant tube has at least a portion in a thermally conductive relationship with at least a portion of the end
turn segment, wherein heat from the end turn segment is transferred by conduction to the at least a portion of the coolant
tube.

US Pat. No. 9,687,927

MODULAR SOLDERING UNIT

GE AVIATION SYSTEMS LLC, ...

1. A mobile kit for a soldering station, comprising:
a first platform having a soldering iron holder, a liquid reservoir, and a top surface configured to receive at least one
other platform;

a second platform having a sponge proximate to a fluid port fluidly coupled with the reservoir, and wherein the second platform
is configured to be received on the top surface of the first platform;

a pump configured to dispense liquid contained in the liquid reservoir through the fluid port and onto the sponge;
a set of soldering tool holders removably affixed to one of the first or second platforms for holding a set of soldering tools,
wherein the set of soldering tools are configured to be rearrangable with respect to the set of holders, the first platform,
or the second platform and the set of soldering tool holders are configured to hold at least one of a brush, a pick, a wire
stripper, a scissors, or a tweezers;

a set of solder reels and a solder dispenser configured to dispenses solder from the set of solder reels; and
a set of solder wick reels and a solder wick dispenser configured to dispense solder wick from the set of solder wick reels.

US Pat. No. 9,870,093

SYSTEM AND METHOD FOR IMPROVING TOUCH SCREEN DISPLAY USE UNDER VIBRATION AND TURBULENCE

GE AVIATION SYSTEMS LLC, ...

1. A vehicle control system comprising:
a first sensor configured to transmit a first signal relative to a measured parameter of the vehicle;
a touch screen input and display system comprising:
a planar input and viewing surface having a plurality of edges and a touch activated area configured to generate a second
signal relative to a manual input received from a user; and

a bezel at least partially surrounding said surface proximate at least some of said plurality of edges, said bezel comprising:
a surface configured to engage one or more fingers of one or more hands of a user, said surface formed of an elastomeric material;
and

a second sensor configured to:
determine an anchor point represented by a number and placement of the one or more fingers on said surface of said bezel;
measure a motion of said one or more fingers relative to said bezel, said motion caused by at least one of vibration, shock,
and turbulence; and

generate a third signal representing a magnitude and direction of said motion; and
an input unit configured to:
receive the first signal, the second signal, and the third signal; and
relocate or resize the touch activated area based on the first signal and the third signal to compensate for said motion of
said one or more fingers caused by at least one of vibration, shock, and turbulence; and

adjust the second signal representing the manual input in a direction opposite said motion of said one or more fingers to
compensate for said motion.

US Pat. No. 9,762,509

APPARATUS AND METHOD OF OPERATING A NETWORK TRAFFIC POLICING MODULE

GE AVIATION SYSTEMS LLC, ...

1. An avionics data network comprising:
a network switch core uncertified for ARINC networks; and
a traffic policing module, comprising:
a data ingress port configured to connect to the network switch core and to receive all data frames received by the network
switch core;

a data egress port configured to connect to the network switch core and transmit a set of the data frames to the data egress
port;

a test module having a set of network protocol compliance tests; and
a processor connected to the test module, the data ingress port, and the data egress port, and configured to execute the set
of network protocol compliance tests on the data frames received at the data ingress port, and transmit to the data egress
port a set of data frames that are compliant with the set of network protocol compliance tests;

wherein the traffic policing module operations are configured to render the network switch core complaint with ARINC networks.

US Pat. No. 9,730,042

AIRCRAFT DATA HANDOFF

GE AVIATION SYSTEMS LLC, ...

1. A computer-implemented method of collecting aircraft data, comprising:
receiving, by one or more computing devices located on a first aircraft, a first transmission from a second aircraft, wherein
the first transmission comprises a first set of data associated with the second aircraft;

determining, by the one or more computing devices, a communication time period during which the first aircraft can receive
data sent from the second aircraft, wherein the communication time period is determined based at least in part on the first
set of data, a velocity associated with the first aircraft, a velocity associated with the second aircraft, and a distance
between the first and second aircrafts;

sending, by the one or more computing devices, a second transmission to the second aircraft, wherein the second transmission
comprises a second set of data indicative of at least the communication time period; and

receiving, by the one or more computing devices, one or more third transmissions from the second aircraft, wherein the one
or more third transmissions comprise a third set of data indicative of one or more parameters associated with the second aircraft,
and wherein a size of the third set of data is based at least in part on the communication time period.

US Pat. No. 9,646,505

METHOD OF AUTOMATICALLY CONTROLLING THE DESCENT PHASE OF AN AIRCRAFT USING AIRCRAFT AVIONICS EXECUTING A DESCENT ALGORITHM

GE AVIATION SYSTEMS LLC, ...

1. A method of automatically controlling the descent phase of an aircraft using aircraft avionics executing a descent algorithm,
the method comprising:
repeatedly receiving as input to the aircraft avionics an airspeed input indicative of the airspeed of the aircraft;
comparing by the aircraft avionics the airspeed input to a first reference airspeed;
determining by the aircraft avionics when airspeed input indicates an over-speed condition based on the comparison; and
placing the aircraft into a slip maneuver in response to the determined over-speed condition by the aircraft avionics.

US Pat. No. 9,596,289

METHOD AND SYSTEM FOR COMPRESSION FOR ACARS AND RELATED TRANSMISSIONS

GE AVIATION SYSTEMS LLC, ...

1. A method of communicating a data file over an aircraft communications addressing and reporting system (ACARS), the method
comprising:
determining a type of data represented in the data file;
analyzing data in the data file wherein the data has a data type of at least one of HTML, XML, Portable Network Graphics,
or Comma Separated Value;

selecting an encoding scheme from a plurality of encoding schemes based upon the type of data and the data in the data file;
encoding one or more messages to represent the data file according to the selected encoding scheme, wherein the one or more
messages comply with a protocol defined by ARINC 618 and the encoding losslessly compresses the data into the one or more
messages;

tagging the one or more messages to indicate the selected encoding scheme; and
transmitting the one or more messages over the character-oriented data link.

US Pat. No. 9,824,599

METHOD AND VEHICLE TRAFFIC CONTROL SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. A vehicle traffic control system, comprising:
a set of grid generators, at a vehicle traffic or vehicle parking zone, with a grid generator configured to project into space
a set of lines defining a relative navigation grid and encoded with grid data configured to identify predetermined points
on the relative navigation grid;

a vehicle having at least one detector module configured to generate a sensor output based on a location of the detector module
in the relative navigation grid;

a data module having information regarding vehicle size and dimensions and known physical features of the vehicle traffic
or vehicle parking zone; and

a control module configured to receive the sensor output, determine a location of the vehicle within the grid, retrieve or
receive information from the data module, generate plan information for the vehicle traffic or parking zone and display, on
a display, the generated plan information.

US Pat. No. 9,729,471

APPARATUS AND METHOD OF OPERATING A NETWORK TRAFFIC POLICING MODULE

GE AVIATION SYSTEMS LLC, ...

1. An avionics data network comprising:
a network switch core uncertified for ARINC networks; and
a traffic policing module, comprising:
a data ingress port configured to connect to the network switch core and to receive all data frames received by the network
switch core;

a data egress port configured to connect to the network switch core and transmit a set of the data frames to the data egress
port;

a test module having a set of network protocol compliance tests; and
a processor connected to the test module, the data ingress port, and the data egress port, and configured to execute the set
of network protocol compliance tests on the data frames received at the data ingress port, and transmit to the data egress
port a set of data frames that are compliant with the set of network protocol compliance tests;

wherein the traffic policing module operations are configured to render the network switch core complaint with ARINC networks.

US Pat. No. 9,778,868

DATA RECORDER FOR PERMANENTLY STORING PRE-EVENT DATA

GE AVIATION SYSTEMS LLC, ...

1. A data recorder for permanently storing pre-event data, the data recorder comprising:
a read-write memory;
a plurality of bit cells in the read-write memory, each bit cell having a bit state of at least one of a high value or a low
value;

a fusible structure in the data recorder and comprising a morphable element associated with each bit cell;
a temperature-triggered module thermally coupled to the ambient environment and configured to be electrically coupled to each
morphable element; and

wherein the temperature-triggered module is further configured to determine if a parameter of the ambient environment exceeds
a predetermined threshold, and then to transmit a burn signal to the fusible structure when the parameter of the ambient environment
exceeds the predetermined threshold so that each morphable element permanently secures the bit state for each bit cell in
response to the burn signal.

US Pat. No. 10,050,765

PROVIDING AN INTERFACE FOR AN AVIONICS DATA TRANSFER SYSTEM

GE Aviation Systems LLC, ...

1. A method of providing a virtual port interface for an end system in an avionics data transfer system associated with an aircraft and including at least one end system having one or more communication ports associated therewith, the method comprising:defining a set of virtual ports for the at least one end system of the avionics data transfer system wherein each virtual port of the set of virtual ports is associated with a corresponding communication port of the one or more communication ports;
mapping at least a subset of virtual ports in the set of virtual ports to a fixed definition in a memory space associated with the at least one end system of the avionics data transfer system, such that the fixed definition in the memory space specifies one or more memory addresses associated with each virtual port of the subset of virtual ports;
associating one or more virtual ports of the at least a subset of virtual ports with one or more physical ports associated with an interface between a host computing device and an end system in the avionics data transfer system by assigning to the one or more virtual ports a plurality of port parameters that define the respective one or more physical ports; and
managing, via the one or more virtual ports, the one or more physical ports by mapping each message to be transmitted and received via the one or more physical ports, at the transmission thereof to each virtual port via the at least one end system.

US Pat. No. 9,911,339

EXPERIMENTAL REAL-TIME PERFORMANCE ENHANCEMENT FOR AIRCRAFT

GE AVIATION SYSTEMS LLC, ...

1. A computer-implemented method of enhancing aircraft performance, the method comprising:
identifying, by at least one computing device, at least one sample operating state comprising at least one of airspeed or
altitude, for analyzing an aircraft operational cost during a flight while an aircraft is operating at the identified at least
one sample operating state;

receiving, by the at least one computing device, at least one real-time flight performance parameter indicative of the aircraft
operational cost while the aircraft is operating during the flight, at the identified at least one sample operating state;

generating during the flight, by the at least one computing device, an updated model that defines the aircraft operating cost
of the aircraft, wherein the updated model is generated using data received by the at least one real-time flight performance
parameter indicative of aircraft operating cost at the identified at least one sample operating state;

determining during the flight, by the at least one computing device, an enhanced operating state based at least in part on
the updated model; and

controlling the aircraft, by the at least one computing device, in accordance with the enhanced operating state.

US Pat. No. 10,069,779

METHOD OF HYBRID MESSAGE PASSING WITH SHARED MEMORY

GE AVIATION SYSTEMS LLC, ...

1. A method of communicating data between coprocessors, comprising:determining, at a first processor, whether data to be communicated exceeds a an adaptable size threshold, wherein the adaptable size threshold is based at least in part on a network latency;
in response to determining that the data is at least one of less than or equal to the predetermined size threshold, including the data in a message;
in response to determining that the data exceeds the predetermined size threshold, including a unique identifier associated with the data in the message;
determining whether there is metadata associated with the data;
in response to determining that there is metadata associated with the data, including the metadata in the message; and
transmitting the message to a second processor.

US Pat. No. 10,068,474

METHOD AND VEHICLE TRAFFIC CONTROL SYSTEM

GE Aviation Systems LLC, ...

1. A method of operating a vehicle in a vehicle traffic control system, comprising:receiving, by at least one detector module, a relative navigation grid projection from a set of grid generators;
generating, via a controller module, at least one navigation output based upon the received relative navigation grid projection;
transmitting, via the controller module, the at least one navigation output to a vehicle traffic control system;
receiving a vehicle traffic control plan from the vehicle traffic control system; and
controllably operating, via the controller module, at least one manned vehicle based on the vehicle traffic control plan;
wherein operating the at least one manned vehicle includes operating the at least one manned vehicle to execute the vehicle traffic control plan to control at least one movement of the at least one of the manned vehicle and to avoid collisions with another vehicle or a structure.

US Pat. No. 10,068,488

SYSTEMS AND METHODS OF PROVIDING A DATA UPDATE TO AN AIRCRAFT

GE Aviation Systems LLC, ...

1. A method of providing a data update to an aircraft, the method comprising:receiving an up-link route clearance;
determining the up-link route clearance includes a flight procedure that is not available in a static navigation database of the aircraft;
in response to the determining, triggering a request, by an update module of the aircraft, for a data update for a route to be flown by the aircraft, wherein the route is a predefined route that is set before flight of the aircraft;
receiving by a component of the aircraft, via a communication link, the data update, including flight procedure data, from a ground station in response to the request, wherein flight procedure data includes at least one of airport information, runway information, special activity spaces, or terminal procedures; and
updating the route to be flown based at least in part on the flight procedure data.

US Pat. No. 9,938,017

ENHANCING ENGINE PERFORMANCE TO IMPROVE FUEL CONSUMPTION BASED ON ATMOSPHERIC RAIN CONDITIONS

GE AVIATION SYSTEMS LLC, ...

1. A method of controlling an aircraft engine, comprising:identifying, by one or more processors, one or more points along a flight path of an aircraft;
accessing, by the one or more processors, a reflectivity measurement for each of the one or more points, the reflectivity measurement obtained from a device located on the aircraft;
determining, by the one or more processors, an estimate of liquid water content for each of the one or more points based at least in part on the reflectivity measurement for the point, wherein determining an estimate of liquid water content for each of the one or more points comprises:
determining, by the one or more processors, a set of estimated values for each of the one or more points as the aircraft travels along the flight path, each estimated value in the set of estimated values associated with an instance of a radar reflectivity measurement for the point; and
determining, by the one or more processors, the estimate of liquid water content based at least in part on the set of estimated values; and
controlling, by the one or more processors, at least one component of the aircraft engine based at least in part on the estimate of liquid water content for the one or more points.

US Pat. No. 10,037,166

TRACKING MEMORY ALLOCATION

GE Aviation Systems LLC, ...

1. A method for tracking memory allocation within shared memory comprising:receiving, by one or more processors, instructions to execute a process;
assigning, by the one or more processors, a process identifier to the process;
allocating, by the one or more processors, one or more blocks of the shared memory to store process specific data associated with the process, wherein the one or more blocks of the shared memory are addressable with a reference;
storing, by the one or more processors, the process identifier at an index in a first array;
storing, by the one or more processors, the reference to the one or more blocks of the shared memory at the index in a second array;
executing, by the one or more processors, the process;
determining a disruption in the execution of the process;
accessing, by the one or more processors, the first array to obtain the index comprising the process identifier;
accessing, by the one or more processors, the second array at the obtained index to obtain the reference to the one or more blocks of the shared memory; and
reinitializing, by the one or more processors, the process with the process specific data stored in the one or more blocks of the shared memory.

US Pat. No. 10,005,561

CONTROLLING AIRCRAFT USING THRUST DIFFERENTIAL TRIM

GE Aviation Systems LLC, ...

1. An aircraft comprising:one or more first engines located on a first side of the aircraft;
one or more second engines located on a second side of the aircraft;
a rudder;
a computing system comprising one or more processors and one or more memory devices located on the aircraft, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations comprising:
detecting a rudder deflection on a first side of the aircraft; and
performing a trim process in response to the rudder deflection, the trim process comprising:
determining an angle of the rudder;
controlling one or more of the one or more first engines to increase thrust;
controlling one or more of the one or more second engines to decrease thrust; and
repeating the trim process when the angle of the rudder is not within a threshold amount of zero degrees.

US Pat. No. 9,966,878

METHOD AND MODULAR SYSTEM FOR A POWER SYSTEM ARCHITECTURE

GE Aviation Systems LLC, ...

1. A modular system for assembling a power system architecture comprising:a common power module having a DC input/output and an alternating current (AC) input/output, wherein the common power module includes at least a three-leg power bridge, a controller module, a first communications port coupled with the controller module and a second communications port coupled with the controller module, and the controller module is communicatively coupled with the three-leg power bridge and configured to operate the three-leg power bridge to at least one of invert DC power received at the DC input/output to AC power provided to the AC input/output, or to convert AC power received at the AC input/output to DC power provided to the DC input/output;
an exciter power module having a second DC input configured to connect to the DC input/output and a second AC output, and wherein the exciter power module includes a fifth communications port wherein the fifth communications port is configured to selectively couple with at least one of the first or second communication ports; and
at least one of a direct current (DC) output module having a first DC input and a DC output or an AC output module having an AC input and a first AC output;
wherein the first DC input is configured to connect to the DC input/output or the AC input/output is configured to connect to one of the AC input, an AC input/output of a second common power module, or an AC generator output.

US Pat. No. 9,913,199

PROVIDING COMMUNICATION OVER A PLURALITY OF NETWORKS

GE AVIATION SYSTEMS LLC, ...

1. A system for providing communication over a plurality of networks comprising:
a first transmitter located on a vehicle configured to communicate over a first network;
a second transmitter located on the vehicle configured to communicate over a second network;
a communication management unit located on the vehicle configured to manage communications over the first network; and
an interceptor unit located on the vehicle comprising one or more processors configured to:
intercept a message from the communication management unit;
initiate a communication session with the first transmitter and the second transmitter; and
route the message among the first transmitter and the second transmitter,
wherein the communication management unit is unaware of the second transmitter.

US Pat. No. 10,028,408

AIR AGITATOR ASSEMBLIES

GE Aviation Systems LLC, ...

1. An air agitator assembly for use with a heat-emitting object having a contour, comprising:a first perforated flexible structure having a thermally absorbing first side confronting and spaced from a portion of the heat-emitting object to define a first air space there between and a second side opposite to the first side, wherein at least a portion of the first side of the first perforated flexible structure has a contour that matches a contour of a corresponding portion of the heat-emitting object;
at least one first piezoelectric structure located on the first perforated flexible structure and operably coupled to a power source;
a second perforated flexible structure having a thermally absorbing first side confronting and spaced from the second side of the first perforated flexible structure to define a second air space there between and a second side opposite to the first side of the second perforated flexible structure;
at least one second piezoelectric structure located on the second perforated flexible structure and operably coupled to the power source;
wherein heat emitted from the heat-emitting object is absorbed by the first side of the first perforated flexible structure and heat emitted from the first perforated flexible structure is absorbed by the first side of the second perforated flexible structure and actuation of the first and second piezoelectric structures result in movement of the corresponding first perforated flexible structure and the corresponding second perforated flexible structure to move volume of air located between the heat-emitting object and the agitator assembly with local ambient air.

US Pat. No. 10,002,257

CRYPTOGRAPHIC KEY LOADER EMBEDDED IN REMOVABLE DATA CARTRIDGE

GE AVIATION SYSTEMS LLC, ...

1. A removable data storage device, comprising:a key memory disposed within a housing, the key memory storing one or more cryptographic keys for use by a host system in cryptographic processing of data;
a data memory disposed within the housing, the data memory storing data subject to cryptographic processing by the host system;
at least one connector configured to be removably engaged with the host system;
a key memory interface in communication with the key memory and configured to communicate the one or more cryptographic keys to the host system via the at least one connector according to a first protocol;
a data memory interface in communication with the data memory and configured to communicate data for cryptographic processing by the host system via the at least one connector according to a second protocol;
a cryptographic key configuration (CKC) database, the cryptographic key configuration (CKC) database comprising a load script for loading the one or more cryptographic keys to the host system; and
a key loader, the key loader configured to load the one or more cryptographic keys for use by the host system in response to a request from the host system,
wherein the first protocol comprises a DS-101 or DS-102 protocol.

US Pat. No. 9,909,971

AIRCRAFT AND PARTICULATE DETECTION METHOD

GE AVIATION SYSTEMS LLC, ...

1. A particulate detection method for an aircraft having a jet engine comprising a core having a compressor and a combustion
chamber, the method comprising:
sensing particulates within the core and providing a corresponding particulate value for the sensed particulates;
determining at least one of a geographic position and altitude of the aircraft corresponding to the sensing of the particulates;
selecting a particulate reference value for the determined at least one of the geographic position and altitude;
comparing the particulate value to the particulate reference value; and
providing an indication based on the comparison,
wherein providing an indication based on the comparison further comprises providing the indication to a computer aboard the
aircraft, providing an alert on a flight deck of the aircraft and providing an indication to one or more ground systems, and

wherein sensing particulates further comprises sensing particulates during at least one of taxi, takeoff, descent, and landing,
but not sensing particulates during cruise.

US Pat. No. 10,003,398

SYSTEMS AND METHODS TO FORMAT AND ENCODE AVIATION DATA FOR IMPROVED TRANSMITTABILITY

GE AVIATION SYSTEMS LLC, ...

1. A computer-implemented method for encoding aviation data, the method comprising:obtaining, by one or more processors, a first plurality of aviation datasets, the first plurality of aviation datasets respectively descriptive of a plurality of conditions associated with an aircraft at a first time;
formatting, by the one or more processors, the first plurality of aviation datasets as a first data frame, the first data frame comprising a first plurality of encoding units that have respective positions within the first data frame, wherein each of the first plurality of aviation datasets is formatted as at least one of the first plurality of encoding units;
determining, by the one or more processors, at least a first period exhibited by at least a first dataset of the first plurality of aviation datasets;
obtaining, by the one or more processors, a second plurality of aviation datasets, wherein obtaining, by the one or more processors, the second plurality of aviation datasets comprises parsing, by the one or more processors, the first dataset according to the first period to form a second dataset, the second dataset included in the second plurality of aviation datasets, wherein each of the second plurality of aviation datasets corresponds to one of the first plurality of aviation datasets, and wherein the second plurality of aviation datasets respectively describe the plurality of conditions associated with the aircraft at a second time that is subsequent to the first time;
formatting, by the one or more processors, the second plurality of aviation datasets as a second data frame, the second data frame comprising a second plurality of encoding units that have the respective positions within the second data frame, and wherein each of the second plurality of aviation datasets is formatted as at least one of the second plurality of encoding units that has a same respective position as the corresponding at least one first encoding unit into which the corresponding first aviation dataset was formatted; and
encoding, by the one or more processors, the first data frame and the second data frame according to an encoding technique that uses motion estimation compression.

US Pat. No. 10,321,602

AIR AGITATOR ASSEMBLIES

GE Aviation Systems LLC, ...

1. An air agitator assembly for use with a heat-emitting object having at least a first side and a second side, comprising: a first air agitator having a first perforated flexible structure having a thermally absorbing first side spaced from a portion of the first side of the heat-emitting object to define a first air space there between and a second side opposite the first side of the first perforated flexible structure, where at least a portion of the first side of the first perforated flexible structure has a non-flat contour that matches a non-flat contour of a corresponding portion of the first side of the heat-emitting object, and at least one piezoelectric structure located on the first perforated flexible structure; and a second air agitator having a second perforated flexible structure having a thermally absorbing first side spaced from a portion of the second side of the heat-emitting object to define a second air space there between and a second side opposite the first side of the second perforated flexible structure, where at least a portion of the first side of the second perforated flexible structure has a non-flat contour that matches a non-flat contour of a corresponding portion of the second side of the heat-emitting object, and at least one piezoelectric structure located on the first perforated flexible structure; wherein heat emitted from the heat-emitting object is absorbed by the first side of the first perforated flexible structure and the first side of the second perforated flexible structure and actuation of piezoelectric structures results in movement of the corresponding first perforated flexible structure and the corresponding second perforated flexible structure to move the air such that the heat-emitting object is cooled by airflows created.

US Pat. No. 10,270,567

AVIONICS DATA NETWORKS

GE Aviation Systems Limit...

1. An avionics data network comprising:a network switch core configured for a time-sensitive networking (TSN) schema;
a set of ARINC 664 part 7 (A664p7) networking end nodes communicatively connected with the network switch core; and
an A664p7 legacy module connected with the network switch core and configured to receive a set of A664p7 networking data from the set of A664p7 networking end nodes, determine an available unallocated time slot of the TSN schema, and selectively scheduling the delivery of the set of A664p7 networking data from the network switch core to another A664p7 networking end node during the available unallocated time slot.

US Pat. No. 10,116,446

CRYPTOGRAPHIC IGNITION KEY (CIK) EMBEDDED IN REMOVABLE DATA CARTRIDGE

GE Aviation Systems LLC, ...

1. A removable data storage device, comprising:a housing comprising:
a data memory configured to store data subject to cryptographic processing;
at least one connector configured to be removably engaged with a host system;
a cryptographic ignition key device separate from the data memory, and comprising one or more cryptographic ignition keys to be transferred to the host system via a cryptographic ignition key interface for authentication of users;
a data memory interface in communication with the data memory and configured to communicate data subject to cryptographic processing to the host system via the at least one connector; and
the cryptographic ignition key interface configured to communicate the one or more cryptographic ignition keys to the host system to authenticate a user of the host system,
wherein the cryptographic ignition key and the data are transferred to the cryptographic ignition key device and the data memory of the removable data storage device, respectively, at a remote terminal, and
wherein once the user is authenticated at the host system, then the data from the removable data storage device is transferred to the host system.

US Pat. No. 10,125,873

VALVE ASSEMBLY WITH ROTATABLE ELEMENT

GE Aviation Systems LLC, ...

1. A method of rotating a valve element, comprising:providing a linear driving force to an output portion of an actuator having a yoke slot;
converting, through a mechanical linkage, the linear driving force of the output portion into a rotational driving force;
rotating a valve element from a first position to a second position utilizing the rotational driving force; and
wherein the mechanical linkage converts the linear driving force into a rotational driving force having a varying torque when the mechanical linkage moves along a gradient of the yoke slot varying between at least a gradual pitch profile section, a transition section, and a steep pitch profile, wherein the transition section has a slope value between a slope value of the gradual pitch profile and a slope value of the steep pitch profile and is located between the gradual pitch profile section and the steep pitch profile section, and each section corresponds to the varying torque.

US Pat. No. 10,108,189

INTEGRATED FLIGHT MANAGEMENT SYSTEM AND FLIGHT DIRECTOR

GE Aviation Systems LLC, ...

1. A method for controlling an aerial vehicle comprising:receiving, by one or more processors, a first signal from a first input device, wherein the first signal is related to a mode of a flight director;
outputting, by the one or more processors, a parameter on an output device,
wherein the parameter is related to the mode;
receiving, by the one or more processors, a second signal from a second input device, wherein the second signal causes the parameter to change to a new parameter, and wherein the second input device is mechanically coupled to the first input device;
outputting, by the one or more processors, the new parameter on the output device; and
receiving, by the one or more processors, a third signal from a third input device, wherein the aerial vehicle is controlled by the flight director based on the third signal, and wherein the second input device is mechanically coupled to the third input device;
wherein (i) the first input device is an outer knob, (ii) the second input device is an inner knob, the first input device surrounding the second input device, and (iii) the third input device is a button, the second input device surrounding the third input device.

US Pat. No. 10,455,740

ELECTRONIC CHASSIS WITH HEAT EXCHANGER

GE AVIATION SYSTEMS LLC, ...

1. An electronics chassis comprising:an electronics housing defining a space for at least one electronic component;
an air-to-air heat exchanger thermally coupled to at least a portion of the electronics housing and having a flow-through air path; and
a plenum coupled to the housing and defining a plenum chamber that is fluidly isolated from the space and fluidly coupled to the flow-through air path, the plenum having an air flow inlet and at least one entrainment slot, which are fluidly coupled to the plenum chamber, the air flow inlet has a diameter D and the at least one entrainment slot is spaced from the electronics housing a distance of at least half of the diameter or D/2.

US Pat. No. 10,103,604

ROTATING RECTIFIER ASSEMBLY FOR ELECTRIC MACHINE

GE Aviation Systems LLC, ...

1. A rectifier assembly for placement within a rotating shaft of an electric machine assembly having a first machine providing an alternating current output and a second machine receiving a direct current input, with the rectifier assembly converting the alternating current output to the direct current input, the rectifier assembly comprising:opposing first and second conductive segments extending in an axial direction;
axially-spaced, non-conductive supports coupling the first and second conductive segments to define an interior between the first and second conductive segments, wherein each non-conductive support has radially arranged mounting connectors;
a set of axially aligned diode seats comprising a first diode seat disposed on the first conductive segment and facing the interior, and a second diode seat disposed on the second conductive segment and facing the interior;
a diode stack comprising a first diode seated with the first diode seat and a second diode seated with the second diode seat, each diode having an input electrically coupled with the alternating current output and outputs electrically coupled with each respective conductive segments; and
an input bus bar for each set of diode seats, wherein the input bus bar is electrically isolated from each of the conductive segments by the non-conductive support and at least a portion of the input bus bar is mounted to at least one of the mounting connectors of the non-conductive support.

US Pat. No. 10,100,733

TURBINE ENGINE WITH ANTI-ICE VALVE ASSEMBLY, BLEED AIR VALVE, AND METHOD OF OPERATING

GE Aviation Systems LLC, ...

17. A method of operating an anti-ice valve, the method comprising:supplying a flow of hot compressed air to the anti-ice valve;
diverting a portion of the flow of hot compressed air to form a flow of muscle air; and
passing the flow of muscle air through a compact heat exchanger having dense finned surfaces, while supplying cooling air to a portion of the compact heat exchanger that is fluidly separate from the flow of muscle air to extract heat from the flow of muscle air to define a flow of cooled muscle air;
wherein the compact heat exchanger is located within a servo housing of the anti-ice valve, the servo housing forming a portion of a pneumatic servo controller, wherein the servo housing defines a cavity that houses the heat exchanger, the dense finned surfaces being inside the cavity, and wherein the cavity is formed at least by a first wall of the servo housing extending from a second wall of the servo housing to a third wall of the servo housing, the second and third walls being horizontal walls.

US Pat. No. 10,090,953

METHOD AND SYSTEM TO ADD AND COMMUNICATE WITH REMOTE TERMINAL ADDRESSES BEYOND A STANDARD BUS PROTOCOL

GE Aviation Systems LLC, ...

1. A method of messaging in a communication system comprising a bus controller and a set of remote terminals each with an address, wherein the bus controller and the set of remote terminals are communicatively interconnected by a serial bus that operates in accordance with a standard protocol that is limited in the number of uniquely addressable remote terminals based at least in part on a message frame that sequences messages into a limited number of time slots, the method comprising:redefining the message frame into a plurality of major frames;
segmenting each major frame into a set of minor frames, wherein a minor frame included in the set of minor frames addresses a subset of the remote terminals, wherein at least one of the subsets of remote terminals includes a plurality of remote terminals; and
sequencing messages into the minor frames such that the minor frames include a set of time-division multiplexed messages, each message in the minor frames including the address of the remote terminal to which the message is directed, and wherein the sequencing messages virtually addresses the remote terminals by combining a time synchronized marker with a local remote terminal address.

US Pat. No. 10,043,400

TRAJECTORY AMENDMENT AND ARRIVAL TIME SLOT PROVISION SYSTEM

GE Aviation Systems LLC, ...

1. A computing system for providing arrival time slots to aircraft operators, the system comprising:one or more processors; and
one or more memory devices, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to:
identify a plurality of aircraft operators;
provide for display in a user interface, to one or more computing devices of each of the plurality of aircraft operators, a first set of data identifying an arrival time slot associated with a landing area;
receive one or more second sets of data indicating that one or more of the aircraft operators has selected the arrival time slot;
select a first aircraft operator of the one or more aircraft operators for the arrival time slot; and
provide, to a computing device of the first aircraft operator, an output indicating that the first operator has been selected for the arrival time slot; determine, in real time, a trajectory amendment associated with an aircraft operated by the first aircraft operator based, at least in part, on a plurality of parameters associated with the aircraft using a four-dimensional flight trajectory optimization technique, wherein the trajectory amendment can include changing at least one of a flight plan, altitude constraints along the flight plan, and /or time/speed constraints along the flight plan;
determine a projected operations value and a price associated with the trajectory amendment;
make the trajectory amendment available for selection by communicating the projected operations value and price of the trajectory amendment to the first aircraft operator;
if the first aircraft operator selects the trajectory amendment, provide the first aircraft operator with the details of the trajectory amendment such that the first aircraft operator can implement the trajectory amendment with the aircraft.

US Pat. No. 10,344,710

ENGINE WITH A THRUST REVERSER LOCKOUT MECHANISM

GE Aviation Systems LLC, ...

1. A turbofan engine, comprising:a turbine engine;
a nacelle surrounding the turbine engine and defining an annular bypass duct between the nacelle and the turbine engine and extending through the turbofan engine to define a generally forward-to-aft bypass air flow path;
a thrust reverser having at least one movable control surface, movable to and from a reversing position where at least a portion of the bypass air flow is at least partially reversed;
a thrust reverser actuation system having multiple actuators and a synchronization mechanism to synchronize the multiple actuators, with at least one of the multiple actuators, comprising,
a housing;
a rotatable lead screw having one end defining a first axial end surface of the rotatable lead screw located within the housing; and
a piston operably coupled to the rotatable lead screw and driven thereby between an extended position and a retracted position and where the piston is operably coupled to the at least one movable control surface to move the at least one movable control surface into and out of the reversing position; and
a lockout mechanism having a lockout piston, axially adjacent to the rotatable lead screw, having a second axial end surface selectively coupled to the first axial end surface of one end of the rotatable lead screw within the housing and axially movable between an inhibit condition, wherein rotation of the rotatable lead screw is prevented by engagement of the first and second axial end surfaces and movement of the multiple actuators is prevented, and a permit condition, wherein rotation of the rotatable lead screw is permitted by disengagement of the first and second axial end surfaces and movement of the multiple actuators is permitted, the lockout mechanism also including a handle operably coupled to axially move the lockout piston through a rotatable link and configured to move between a first position where the lockout mechanism is in the permit condition and a second position where the lockout mechanism is in the inhibit condition.

US Pat. No. 10,312,849

AIRCRAFT STARTING AND GENERATING SYSTEM

GE Aviation Systems LLC, ...

1. An aircraft starting and generating system, comprising:a starter/generator that includes a main machine, an exciter, and a permanent magnet generator;
a direct current (DC) power output from the starter/generator;
a four leg inverter coupled with the DC power output and having an inverter/converter/controller (ICC) having a four leg metal oxide semiconductor field effect transistor (MOSFET)-based bridge configuration, and that generates DC power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts DC power, obtained from the starter/generator after the prime mover have been started, to alternating current (AC) power in a generate mode of the starter/generator; and
a four leg bridge gate driver configured to drive the four leg MOSFET-based bridge;
wherein the four leg bridge gate driver operates to drive the four leg MOSFET-based bridge during start and generate mode using bi-polar pulse width modulation (PWM).

US Pat. No. 10,304,342

GROUND-BASED DATA ACQUISITION SYSTEM

GE Aviation Systems LLC, ...

1. A ground unit for providing navigation assistance to an aerial vehicle comprising:a memory device; and
one or more processors configured to:
receive one or more geographic coordinates from a manual input;
receive a transmit signal from a first aerial vehicle, wherein the transmit signal is indicative of a communication window; and
transmit the one or more geographic coordinates in response to the received transmit signal to one or more aerial vehicles in the communication window.

US Pat. No. 10,239,466

AVIONICS DISPLAY FASTENER ASSEMBLY

GE Aviation Systems LLC, ...

1. A fastener assembly for cockpit electronics, comprising:a spring locking quarter turn fastener having a head on a non-display side of the assembly and a thread extending to a display side of the assembly, the spring locking quarter turn fastener is a quarter turn line fastener configured to mount to a cockpit rail;
a spring assembly including at least two leaf springs in a stacked configuration moveably coupled about at least a portion of the thread;
mounting hardware configured to secure the spring assembly to the thread; and
a bushing located about at least a portion of the spring locking quarter turn fastener and configured to space the spring assembly from a mounting flange of the cockpit electronics;
wherein flexion of the spring assembly is configured to allow a vertical displacement of the spring locking quarter turn fastener.

US Pat. No. 10,214,417

SOLID HYDROGEN REACTION SYSTEM AND METHOD OF LIBERATION OF HYDROGEN GAS

GE Aviation Systems LLC, ...

1. A solid hydrogen reaction system, comprising:a reactor having a body with a first end and a second end where the second end is wider than the first end and where the body includes a sidewall that defines a reaction chamber that has an increasing cross-sectional area from the first end to the second end;
an inlet disposed at the first end of the body for coupling the reaction chamber to a reactant;
a hydrogen storage solid provided within the reaction chamber;
a set of linear heat rods arranged in an array and provided in the reaction chamber between the hydrogen storage solid and sidewall of the reactor;
insulation layer provided around the body of the reactor exterior of the reaction chamber to prevent heat loss from the reaction chamber; and
a removable cover selectively mountable to the second end for selectively closing the reaction chamber;
wherein the reaction chamber is configured to receive the hydrogen storage solid and receive the reactant or heat introduced at the inlet to the reaction chamber to begin a chemical reaction to liberate hydrogen gas from the hydrogen storage solid.

US Pat. No. 10,179,430

HYBRID PART MANUFACTURING SYSTEM AND METHOD

GE Aviation Systems LLC, ...

1. A hybrid part manufacturing system comprising:a mold having a set of movable mold portions, wherein, in a first molding position, the set of mold portions cooperate to define an injectable mold cavity, and wherein, in a second additive manufacturing position, the set of mold portions have been repositioned to define an access area for additive manufacturing operations to be performed on a part formed inside the injectable mold cavity;
at least one material dispenser movably positioned with respect to the mold cavity configured to dispense an injectable material into the mold cavity when the mold is in the first molding position to form a portion of a part within the mold cavity; and
at least one printhead for performing additive manufacturing operations movably positioned with respect to the mold cavity configured to dispense a filament or wire form printable material onto the portion of the part formed within the mold cavity when the mold is in the second additive manufacturing position; and
wherein the part is formed by both a volume of the injectable material deposited into the mold cavity when the mold is in the first molding position and a volume of the printable material when the mold is in the second additive manufacturing position.

US Pat. No. 10,171,395

AIRCRAFT MESSAGE MANAGEMENT SYSTEM

GE Aviation Systems LLC, ...

1. A computer-implemented method of filtering aircraft messages, comprising:receiving, by one or more computing devices included in an aircraft from at least one of a first onboard system associated with the aircraft or a first remote system that is remote from the aircraft, a message comprising a plurality of data fields containing data associated with the message;
accessing, by the one or more computing devices, a set of configuration data, wherein the set of configuration data comprises a first set of data identifying a plurality of different message types, one or more message structures that can be associated with each of the different message types, and different parameters associated with each of the different message structures including one or more conditions for processing data fields of messages associated with each of the of the message structures, wherein each condition includes an action to be performed on a specified data field;
determining, based on the plurality of data fields included in the message including expected data fields matching one of the plurality of message types, a potential message type of the message;
determining, by the one or more computing devices, a determined message structure of the message based at least in part on the data fields and the determined potential message type;
processing, by the one or more computing devices, the message based at least in part on the determined message structure, and wherein processing comprises:
identifying one or more parameters associated with the determined message structure, and
accessing and editing, by the one or more computing devices, one or more of the data fields to perform an identified action including at least one of a removal, redaction, or replacement of the data contained in the respective data fields based at least in part on the one or more conditions associated with the one or more potential message types; and
generating and outputting, by the one or more computing devices, a filtered message that is based at least in part on the processed message.

US Pat. No. 10,146,473

SYSTEMS AND METHODS OF SUBJECT STATE CHANGE NOTIFICATION

GE Aviation Systems LLC, ...

1. A system for notifying one or more observers of a state change, the system comprising:at least one subject configured to write data to a buffer in a shared memory space;
one or more observers, each observer having an associated notification group comprising one or more buffer identifiers, each buffer identifier corresponding to a buffer in the shared memory space which is associated with the at least one subject; and
a scheduler in communication with the associated notification group and configured (i) to monitor each buffer to determine one or more state changes associated with one or more buffers in the shared memory space, the monitoring including determining a state change relative to each observer including comparing a current version of each buffer as specified to a last known version of the respective buffer as specified in the notification group and determining whether a match exists indicative of no change or a discrepancy indicative of a state change, and (ii) to provide an update notification based at least in part on the one or more detected state changes to the associated notification group which is accessible by the one or more observers.

US Pat. No. 10,106,267

ENHANCING ENGINE PERFORMANCE TO IMPROVE FUEL CONSUMPTION BASED ON ATMOSPHERIC ICE PARTICLES

GE Aviation Systems LLC, ...

1. A method of controlling an aircraft engine, comprising:identifying, by one or more processors, one or more points along a flight path of an aircraft;
accessing, by the one or more processors, reflectivity measurements for each of the one or more points, the reflectivity measurements obtained using a radar on the aircraft;
determining, by the one or more processors, a set of estimated ice water content values for each of the one or more points as the aircraft travels along the flight path, each of the estimated values being a correlation of an instance of the reflectivity measurements for the point and an ambient temperature measurement with the point obtained via a sensor;
determining, by the one or more processors, an estimate of ice water content for each of the one or more points by applying a weighted averaging function to the set of estimated ice water content values, wherein the applying assigns a greater weight to the values correlated with the instances of reflectivity measurements obtained for the points closer to the aircraft; and
controlling, by the one or more processors, at least one component of the aircraft engine based at least in part on the estimate of ice water content for the one or more points.

US Pat. No. 10,485,138

HEAT SINK ASSEMBLIES FOR TRANSIENT COOLING

GE Aviation Systems LLC, ...

2. A heat sink assembly for use with at least one heat-emitting component, comprising:a first frame holding a first phase change material that changes phase at a first temperature where the first frame has at least a portion conductively coupled to the at least one heat-emitting component;
a second frame holding a second phase change material that changes phase at a second temperature, which is greater than the first temperature; and
a conductive element defining a structural barrier between the first phase change material and the second phase change material and conductively coupling the first phase change material and the second phase change material;
wherein the first frame and the second frame are configured as honeycombs and the first phase change material changes phase in response to a conductive transfer of heat from the heat-emitting component and the second phase change material changes phase in response to a conductive transfer of heat from the first phase change material.

US Pat. No. 10,256,638

METHOD AND SYSTEM FOR OPERATING A SET OF GENERATORS

GE Aviation Systems LLC, ...

1. A method of operating a set of generators supplying power to a common power bus, the method comprising:obtaining, in a power sharing controller module, a first generator signal and a second generator signal;
determining, in the power sharing controller module, a common mode torsional oscillation value and a differential mode torsional oscillation value based on the obtained first and second generator signals;
determining, in the power sharing controller module, a first generator share command based on the summation of a predetermined share ratio value for the first generator and the differential mode torsional oscillation value;
determining, in the power sharing controller module, a second generator share command based on the difference of a predetermined share ratio value for the second generator and the differential mode torsional oscillation value;
modifying the first and second generator share commands by summating the respective share command with the common mode torsional oscillation value; and
applying the modified first and second generator share commands, wherein the applying damps the differential mode torsional oscillation and the common mode torsional oscillation of the first and second generators.

US Pat. No. 10,250,110

FASTENING ASSEMBLY FOR ELECTRIC MACHINE AND RECTIFIER THEREFOR

GE Aviation Systems LLC, ...

1. A method of assembling a rotating rectifier having multiple radially spaced bus bars each having a corresponding fastener to an electrical machine having at least one machine with a stator and a rotor mounted on a rotating shaft, the method comprising:inserting the rotating rectifier into a hollow portion of the rotating shaft;
axially aligning the fasteners with at least one corresponding radial opening in the rotating shaft;
inhibiting an inward radial movement of the fasteners by inserting an inhibiting tool into an interior defined by the multiple radially spaced bus bars; and
at least partially securing the fasteners of each bus bar to a corresponding fastener on at least one of the rotor and rotating shaft while the inhibiting tool resides in the interior.

US Pat. No. 10,240,609

SCREW PUMP AND IMPELLER FAN ASSEMBLIES AND METHOD OF OPERATING

GE Aviation Systems LLC, ...

1. An impeller fan assembly comprising:a housing having an inner peripheral wall defining a flow through passage;
a stator located within the flow through passage and having an annular array of stationary blades provided along the inner peripheral wall;
a rotor having a hub and an annular array of non-stationary blades extending from the hub;
at least two spaced apart bearings mounted to the stator;
a shaft having a hollow portion rotatably supported by the bearings for rotation about a rotational axis;
a sump provided in the stator;
a screw pump provided within the hollow portion of the shaft and having a screw pump inlet fluidly coupled to the sump and a screw pump outlet in fluid communication with the bearings, whereby rotation of the screw pump about a screw pump rotational axis pumps fluid from the sump to the bearings; and
a de-swirler located within the sump and configured to reduce rotational movement of the fluid within the sump as compared to movement of the fluid within the sump in an absence of the de-swirler;
wherein the de-swirler includes a deswirler hub having a centerline coaxial with the rotational axis and having fixed vanes extending radially from the deswirler hub, the vanes being curved relative to the centerline of the deswirler hub and wherein the curved vanes include curvature in a direction opposite from a rotational direction of the screw pump to redirect fluid toward the centerline.

US Pat. No. 10,240,477

TURBOFAN ENGINE WITH GENERATOR

GE Aviation Systems LLC, ...

1. A turbofan engine comprising:a turbine engine comprising a rotatable fan with a plurality of blades, wherein in a running mode the turbine engine rotates each of the plurality of fan blades;
a nacelle having a portion surrounding the blades; and
a generator comprising:
a main machine having a main rotor winding and a main stator winding;
an exciter having an exciter rotor winding and an exciter stator winding;
a rectifier electrically coupling the exciter rotor winding to the main rotor winding; and
a generator control unit (GCU) electrically coupled to the exciter stator winding and the main stator winding, and controlling the excitation of the main machine by supplying electricity to the exciter stator winding, and outputting electricity generated by the main stator winding;
wherein the main rotor winding and the exciter rotor winding define a rotor assembly that is located within at least one of the blades and proximate the nacelle, and the main stator winding and the exciter stator winding define a stator assembly that is fixedly located within the nacelle along a rotational path of the rotor assembly whereby the operation of the turbine engine rotates the fan, which rotates the rotor assembly along its rotational path past the stator assembly to generate electricity in the main stator winding.

US Pat. No. 10,242,578

FLIGHT PATH MANAGEMENT SYSTEM

GE Aviation Systems LLC, ...

1. A computer-implemented method of determining a flight path of an aircraft, the method comprising:identifying, by one or more computing devices associated with an aircraft, parameters associated with a moving target, the parameters including an initial location of the moving target, a track of the moving target, a speed of the moving target, and a reference time associated with the moving target;
determining, by the one or more computing devices, a moving circular flight path associated with the moving target such that the moving target is surrounded by the moving circular flight path based at least in part on the parameters associated with the moving target;
identifying, by the one or more computing devices, one or more conditions associated with at least one of the aircraft and the moving circular flight path, wherein the one or more conditions include predicted conditions, the predicted conditions including a planned speed change; and
determining, by the one or more computing devices, a flight path of the aircraft from a location of the aircraft to the moving circular flight path based at least in part on the parameters associated with the moving target and the one or more conditions associated with at least one of the aircraft and the moving circular flight path, wherein the flight path of the aircraft is determined as a minimum lateral time flight path associated with a minimum time for the aircraft to reach the moving circular path from the location of the aircraft.

US Pat. No. 10,230,451

AIRBORNE CELLULAR COMMUNICATION SYSTEM

GE Aviation Systems LLC, ...

1. An avionics communication system located on an aircraft for providing cellular communication between the aircraft and an infrastructure of ground communication nodes, comprising:a directional antenna;
one or more processors and one or more memory devices, the one or more memory devices storing instructions that when executed by the one or more processors cause the one or more processors to perform operations, the operations comprising:
identifying one or more ground communication nodes with which the aircraft plans to communicate in a given period of time, wherein identifying the one or more ground communication nodes with which the aircraft plans to communicate in the given period of time comprises:
determining a position of the aircraft during the given period of time;
determining a relative velocity of the aircraft;
determining a location of ground communication nodes; and
selecting one or more ground communication nodes based at least in part on the determined position of the aircraft, the determined relative velocity of the aircraft and the determined location of ground communication nodes relative to the determined position and relative velocity of the aircraft;
determining a signal power level for communicating between the aircraft and the one or more identified ground communication nodes; and
determining a frequency shift value for modifying communicated signals to account for expected Doppler effects associated with the communicated signals due to a velocity of the aircraft relative to the identified one or more ground communication nodes; and
a radio transmitter receiver configured to transmit and receive cellular communication signals between the aircraft and the identified one or more ground communication nodes using the directional antenna, determined signal power level and determined frequency shift value.

US Pat. No. 10,200,110

AVIATION PROTOCOL CONVERSION

GE Aviation Systems LLC, ...

1. A wireless communication unit (WCU) comprising:one or more memory devices; and one or more processors configured to:
(i) receive a message via an aviation messaging protocol;
(ii) encapsulate the message in a packet, wherein the packet comprises a User Datagram Protocol format; and
(iii) transmit the packet via an Ethernet connection;
wherein the one or more processors are further configured to:
(iv) receive a second message via the aviation messaging protocol;
(v) encapsulate the second message in a second packet, wherein the second packet comprises the User Datagram Protocol format; and
(vi) multiplex the first message and the second message into a stream.

US Pat. No. 10,199,907

METHOD AND ASSEMBLY OF A POWER GENERATION SYSTEM

GE Aviation Systems LLC, ...

1. A wet cavity electric machine comprising:a stator core having at least two stator poles formed by a set of stator windings, with the stator winding having end turns;
a rotor having at least two rotor poles, and configured to rotate relative to the stator core, and having a channel for liquid coolant to flow through the rotor to at least one nozzle;
at least one oscillating heat pipe received within the set of stator windings and having an evaporator portion extending through the stator core and a condenser portion extending axially past the stator core proximate to the at least one nozzle, and wherein the evaporator portion and the condenser portion are positioned between sealed opposing ends of the at least one oscillating heat pipe; and
a working fluid in the at least one oscillating heat pipe, wherein the working fluid is disposed in alternating liquid and vapor phases in the at least one oscillating heat pipe;
wherein liquid coolant from the at least one nozzle can be sprayed onto the condenser portion of the at least one oscillating heat pipe to cause the working fluid to oscillate and extract heat from the stator core.

US Pat. No. 10,161,356

INTEGRATED THRUST REVERSER ACTUATION SYSTEM

GE Aviation Systems LLC, ...

9. A thrust reverser comprising:at least one movable, control surface that includes a slidable portion of an inner cowling of a nacelle, movable to and from a reversing position with respect to a forward portion of the nacelle, wherein the nacelle surrounds at least a portion of a turbine engine and defines an annular bypass duct between the nacelle and the turbine engine defining a forward-to-aft bypass air flow path;
a thrust reverser actuation system having at least one actuator operably coupled to the at least one movable control surface to move the at least one movable control surface into and out of the reversing position; and
a guide that includes a rail having a guiding portion including three planar surfaces lying in three distinct, non-parallel, intersecting planes, wherein the three distinct, non-parallel, intersecting planes are distinct from one another and are perpendicular to a common cross section plane and wherein each plane of the three distinct, non-parallel, intersecting planes intersects the other two planes, and a bogie having three rotatable bearing surfaces coupled to the rail at the three planar surfaces for relative translational movement between the rail and the bogie;
wherein one of the rail and the bogie is mounted to the turbine engine and the other of the rail and the bogie is mounted to the at least one movable control surface such that operation of the at least one actuator moves the at least one movable control surface by translation movement between the rail and the bogie, and in the reversing position, the at least one movable control surface limits an annular bypass area of the annular bypass duct formed between the at least one movable control surface and the turbine engine; and
wherein the three bearing surfaces each comprise a rotatable bearing surface, each rotatable bearing surface in contact with and arranged to provide opposing bearing forces to a corresponding one of the three planar surfaces to prevent separation of the rail and the bogie during translational movement between the rail and the bogie.

US Pat. No. 10,128,662

POWER SYSTEM FOR AN AIRCRAFT WITH DUAL HYBRID ENERGY SOURCES

GE Aviation Systems LLC, ...

1. A power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, resulting in the aircraft having a transient-state power requirement in addition to an average power requirement, with the transient-state power requirement being greater than the average power requirement, the power system comprising:at least one generator having a power output sufficient to supply the average power requirement;
a power distribution buss coupling the generator to the power-consuming components;
a non-battery power source;
a battery power source;
a power controller selectively coupling the non-battery power source and the battery power source to the power distribution buss to satisfy the transient power requirements; and
a load spectrum selection filter that identifies the average power requirement and the transient-state power requirement.

US Pat. No. 10,399,689

OPTIMIZING AIRCRAFT CONTROL BASED ON NOISE ABATEMENT VOLUMES

GE Aviation Systems LLC, ...

1. An aircraft control system, comprising:a processor that executes the following computer executable components stored in a memory:
a set of sensors, gauges and positioning component that measure and estimate state of an aircraft, including a line-of-sight distance from the aircraft to a ground noise restriction location or to a geographical point of interest;
a mapping component that maps noise-restricted areas of a flight path defined by relative position of the aircraft to ground noise restriction locations; and
a noise abatement component that computes optimal thrust, flight, and engine control of the aircraft in a noise abatement volume, based on the line-of-sight distance from the aircraft, wherein the aircraft operates at the computed optimal thrust, flight, and engine control in the noise abatement volume, thereby minimizing direct operating cost (DOC) while obeying noise constraints.

US Pat. No. 10,365,047

ELECTRONICS COOLING WITH MULTI-PHASE HEAT EXCHANGE AND HEAT SPREADER

GE Aviation Systems LLC, ...

1. A system for cooling a surface comprising:a housing comprising:
an evaporator portion; and
a multi-domain heat exchanger having at least one trifurcated heat exchange portion comprising an array of unit cells defining a plurality of nested trifurcated domains, the array of unit cells of the multi-domain heat exchanger comprising:
a first structure comprising a trifurcated condenser portion, the trifurcated condenser portion coupled to the evaporator portion;
a second structure comprising a trifurcated coolant portion, the trifurcated coolant portion substantially surrounded by the trifurcated condenser portion; and
a trifurcated phase change material portion substantially surrounding the trifurcated condenser portion, the trifurcated phase change material portion configured to receive a phase change material.

US Pat. No. 10,348,162

METHOD AND ASSEMBLY OF AN ELECTRIC MACHINE

GE Aviation Systems LLC, ...

1. A generator comprising:a housing;
a rotor within the housing and rotatable about an axis of rotation; and
a set of coolant sumps within the housing and arranged axially parallel with the axis of rotation;
wherein the set of coolant sumps is configured to minimize an aeroline dimension of the generator.

US Pat. No. 10,293,916

AIRCRAFT AND METHOD OF COUNTERING AERODYNAMIC EFFECTS OF PROPELLER WAKE

GE Aviation Systems LLC, ...

1. An aircraft comprising:a fuselage having a centerline;
a wing extending from the fuselage and having a leading edge and a trailing edge defining a chord therebetween;
an engine mounted to the wing and having a rotating output shaft; and
a propeller operably coupled to the output shaft and configured to generate a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft;
wherein the propeller is located forward of the leading edge of the wing such that the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having a corresponding reduction in chord formed in the leading edge at the localized areas of effectively increased angle of attack to neutralize the otherwise increased wing loading, and localized areas of effectively decreased angle of attack generating a corresponding decreased wing loading, with the wing having a corresponding increase in chord formed in the leading edge at the localized areas of effectively decreased angle of attack to neutralize the otherwise decreased wing loading.

US Pat. No. 10,291,156

COMBINED HYBRID THERMIONIC AND THERMOELECTRIC GENERATOR

GE Aviation Systems LLC, ...

1. A power generation system for an aircraft, the power generation system comprising:a thermionic generator arranged to receive heat from at least one heat source, the thermionic generator configured to generate electrical power for one or more aircraft systems based at least in part on the heat received from the at least one heat source;
a thermoelectric generator arranged to receive waste heat from the thermionic generator;
wherein the thermoelectric generator comprises a silicon carbide metal oxide semiconductor field effect transistor and is configured to generate electrical power for one or more aircraft systems based at least in part on the waste heat received from the thermionic generator.

US Pat. No. 10,277,356

MULTI-PLATFORM LOCATION DECEPTION SYSTEM

GE Aviation Systems LLC, ...

1. A computer-implemented method of providing a synthetic track to one or more observation devices, comprising:determining, by one or more computing devices, a location range and a time range for a synthetic track to be created by at least a subset of a plurality of platforms;
determining, by the one or more computing devices, an emission location and an emission time for at least the subset of platforms of the plurality of platforms based at least in part on the location range and the time range, wherein the emission location is indicative of a location at which the respective platform is to generate an emission and the emission time is indicative of a time at which the respective platform is to generate the emission; and
sending, by the one or more computing devices, a set of data to each of the platforms of at least the subset of platforms, each respective set of data indicating the emission location and the emission time at which the respective platform is to generate the emission to create the synthetic track.

US Pat. No. 10,269,253

SYSTEM AND METHOD OF REFINING TRAJECTORIES FOR AIRCRAFT

GE Aviation Systems LLC, ...

1. A method of refining aircraft trajectories, the method comprising:obtaining from a trajectory predictor, data related to a set of four-dimensional trajectories for aircraft;
determining by a constraint selector module a set of constraints as at least one point along the set of four-dimensional trajectories that bound the set of four-dimensional trajectories;
mapping in a processor values for a goal associated with the set of four-dimensional trajectories based on the determined set of constraints;
estimating in the processor additional values for the goal based on the mapped values for the goal associated with the set of four-dimensional trajectories;
repeating the obtaining, determining, mapping, and estimating steps until the value for the goal associated with the set of four-dimensional trajectories exceeds a predetermined threshold to determine a final set of constraints;
optimizing an aircraft trajectory based on the determined final set of constraints; and
operating an aircraft according to the optimized aircraft trajectory;
wherein the predetermined threshold is a total amount of time or a number of computing cycles to be spent computing a refined trajectory.

US Pat. No. 10,260,471

AIRCRAFT STARTING AND GENERATING SYSTEM

GE AVIATION SYSTEMS LLC, ...

1. An aircraft starting and generating system, comprising:a starter/generator that includes a main machine, an exciter, and a permanent magnet generator;
a direct current power output from the starter/generator;
a load-leveling unit selectively coupled with the direct current power output and having an inverter/converter/controller having a load-leveling unit metal oxide semiconductor field effect transistor-based bridge configuration and that supplies direct current power to the direct current power output in a supply mode, and that receives direct current power from the direct current power output, in a receive mode; and
a load-leveling unit bridge gate driver configured to drive the load-leveling unit metal oxide semiconductor field effect transistor-based bridge;
wherein the load-leveling unit bridge gate driver operates to drive the load-leveling unit metal oxide semiconductor field effect transistor-based bridge during the supply mode and the receive mode using bi-polar pulse width modulation.

US Pat. No. 10,262,546

AIRCRAFT NAVIGATION USING EXPONENTIAL MAP

GE AVIATION SYSTEMS LLC, ...

1. A computer-implemented method of determining navigation information for an aircraft, comprising:accessing, by one or more processors, a satellite-based positioning signal received at a receiver on an aircraft, the satellite-based positioning signal comprising data indicative of a distance between a satellite and the receiver;
identifying, by the one or more processors, from the satellite-based positioning signal a first vector associated with the distance and direction between the satellite and the receiver;
identifying, by the one or more processors, from the satellite-based positioning signal a second vector associated with a distance and direction between a reference point and the satellite;
generating, by the one or more processors, a kinematic model for determining a geometric position of the aircraft using the first vector and the second vector, the kinematic model based at least in part on a robotic arm, wherein the aircraft is modeled as an end effector for the robotic arm, the satellite is modeled as a pivot point of the robotic arm, the first vector is modeled as a link extending between the pivot point and the end effector, the second end vector is modeled as a link extending between a base and the pivot point; and
determining, by the one or more processors, navigation information for the aircraft based at least in part on the kinematic model; and wherein determining navigation information comprises determining translation and attitude information simultaneously in a geometric manner.

US Pat. No. 10,227,137

HYBRID POWER SYSTEM FOR AN AIRCRAFT

GE Aviation Systems LLC, ...

1. A system for distributing electrical power in an aircraft, the system comprising:one or more gas turbine engines configured to provide propulsion and electrical power to an aircraft;
one or more electrical engines configured to provide propulsion for the aircraft;
one or more first electrical power systems configured to provide power to the one or more electrical engines for one or more electrical power propulsion loads on the aircraft, wherein one or more generators are coupled to a low spool shaft of the one or more gas turbine engines to generate power for the one or more first electrical power systems; and
one or more second electrical power systems configured to provide power for one or more non-propulsion electrical power loads of the aircraft.

US Pat. No. 10,199,834

METHOD FOR CONTROLLING THE SUPPLY OF POWER TO A POWER SYSTEM FOR AN AIRCRAFT

GE Aviation Systems LLC, ...

1. A method of controlling the supply of power to a power system for an aircraft having a plurality of power-consuming components, some of which have transient power requirements, resulting in the power system having a transient-state power requirement and a non-transient power requirement, the method comprising:supplying power to the power system with a generator having a predetermined power output incapable of providing sufficient power for the transient-state power requirement;
determining a transient power requirement of the power system;
comparing the determined transient power requirement to a predetermined power output;
determining the transient power requirement exceeds the predetermined power output;
supplying additional power to the power system from a non-battery power source in response to the determination that the transient power requirement exceeds the predetermined power output; and
supplying additional power to the power system from a battery power source in response to the determination that the transient power requirement exceeds a combination of the predetermined power output and the additional power from the non-battery power source.

US Pat. No. 10,169,175

PROVIDING FAILOVER CONTROL ON A CONTROL SYSTEM

GE Aviation Systems LLC, ...

1. A method of providing failover control in a computing system, the method comprising:monitoring a data stream generated by a plurality of computing nodes in a computing system; and
selecting a first subset of the plurality of computing nodes based at least in part on the monitored data stream;
generating one or more control grant signals for each computing node of the first subset;
determining that the one or more control grant signals for one or more of the computing nodes in the first subset satisfies a predetermined threshold;
in response to determining the one or more control grant signals for one or more of the computing nodes in the first subset satisfies the predetermined threshold, granting control authority of the computing system to the one or more computing nodes of the first subset;
subsequent to granting control authority of the computing system to the one or more computing nodes of the first subset, identifying at least one control capable computing node that has not been granted control authority of the computing system; and
selecting the at least one control capable computing node as a second subset of the plurality of computing nodes.

US Pat. No. 10,170,007

TRAJECTORY AMENDMENT SYSTEM

GE Aviation Systems LLC, ...

1. A computer-implemented method of providing trajectory amendments, comprising:identifying, by one or more first computing devices, an arrival time slot associated with a landing area;
providing, by the one or more first computing devices to one or more second computing devices of a plurality of operators, a first set of data identifying the arrival time slot;
receiving, by the one or more first computing devices, a second set of data indicating that a first operator of the plurality of operators has selected the arrival time slot; and
determining in real-time, by the one or more first computing devices, one or more trajectory amendments to allow a first aircraft associated with the first operator to meet the arrival time slot associated with the landing area;
determining, by the one or more first computing devices, a projected operations value associated with the one or more trajectory amendments; and
sending, by the one or more first computing devices, the one or more trajectory amendments.

US Pat. No. 10,137,980

HUB ASSEMBLY AND PROPELLER ASSEMBLIES

GE Aviation Systems LLC, ...

1. A propeller assembly, comprising:a partial hub, comprising:
a backing plate comprising a plate portion having contoured portions defining a set of partial root seats extending from the plate portion along its periphery; and
a set of clamps selectively operably couplable to the backing plate with each clamp defining a second partial root seat and wherein when a clamp is coupled to the backing plate, a root seat is formed; and
a variable pitch propeller blade having a root rotatably received within the root seat;
further comprising a cover operably coupled over the set of clamps, wherein the cover comprises at least one opening configured to accommodate a pitch control unit.

US Pat. No. 10,141,875

AIRCRAFT STARTING AND GENERATING SYSTEM

GE Aviation Systems LLC, ...

1. An aircraft starting and generating system, comprising:a starter/generator that includes a main machine, an exciter, and a permanent magnet generator;
an inverter/converter/controller (ICC) having a metal oxide semiconductor field effect transistor (MOSFET)-based bridge configuration that is connected to the starter/generator and that generates alternating current (AC) power to drive the starter/generator in a start mode for starting a prime mover of the aircraft, and that converts AC power, obtained from the starter/generator after the prime mover have been started, to direct current (DC) power in a generate mode of the starter/generator; and
a main bridge gate driver configured to drive the MOSFET-based bridge;
wherein the main bridge gate driver operates to drive the MOSFET-based bridge during start mode using Space Vector Pulse Width Modulation (SVPWM) and during generate mode using reverse conduction based inactive rectification.

US Pat. No. 10,125,880

AIR PRESSURE REGULATOR

GE Aviation Systems LLC, ...

1. An air pressure regulator comprising:a regulator body having a housing and defining a hollow interior;
an air inlet in communication with the hollow interior and configured to connect with a source of pressurized air;
an air outlet fluidly coupled with the air inlet;
a valve stem positioned at the air inlet and configured to regulate the pressure of the pressurized air for the air outlet by way of slidable movement of the valve stem relative to the air inlet;
a restraining element disposed within the hollow interior and coupled with the valve stem such that the valve stem and the restraining element move in unison wherein the restraining element includes an electrically conductive sleeve encircling a hollow bore; and
a magnet having a magnetic field mounted to the regulator body wherein the magnet is received by the hollow bore and the magnetic field encompasses at least part of the conductive sleeve;
wherein movement of the conductive sleeve relative to the magnetic field is retarded by Eddy currents generated in the conductive sleeve by the movement, and wherein the magnet is fixed relative to the housing and includes an adjuster configured to adjust the position of the magnet relative to the conductive sleeve.

US Pat. No. 10,408,218

FAN WITH SHUT-OFF VALVE AND METHOD OF OPERATING

GE Aviation Systems LLC, ...

1. A fan, comprising:a housing defining an interior and a flow path therein;
an impeller assembly including a motor, the impeller assembly slidably located within the interior and having a set of blades drivably coupled with an output shaft of the motor, wherein the set of blades of the impeller assembly is rotatable about an axis of rotation; and
a valve assembly, comprising:
a valve element disposed in the flow path and operably coupled to the impeller assembly and configured to rotate between an opened position and a closed position, wherein the valve element closes the flow path; and
a linkage assembly physically coupling the impeller assembly and the valve element;
wherein the valve element is configured to rotate between the open and closed positions based on slidable movement of the impeller assembly.

US Pat. No. 10,399,694

RAM AIR TURBINE SYSTEM

GE Aviation Systems LLC, ...

16. An aircraft comprising:a ram air turbine generator including:
a thermally conductive rotatable shaft;
a housing having a body defining an interior;
a generator located within the interior and having a stator and a rotor, wherein the rotor is operably and thermally coupled with the rotatable shaft;
a turbine having a first set of blades operably coupled with the rotatable shaft and configured such that an airstream passing through the first set of blades rotates the rotatable shaft;
a cooling system coupled to the housing and having a shield element with a set of ports and having a back wall with at least a portion of the rotatable shaft extending into the shield element; and
a second set of blades mounted to the rotatable shaft and provided within the shield element, rotatable coaxially with and in fluid communication with the first set of blades, arranged downstream from, and external to the housing, wherein the second set of blades are thermally coupled with the shaft;
wherein airstream flowing about the ram air turbine generator passing through the second set of blades provide for heat transfer from the second set of blades to the airstream.

US Pat. No. 10,380,809

SYSTEM AND METHOD OF FAULT DETECTION

GE AVIATION SYSTEMS LLC, ...

1. A fault monitoring system for an aircraft comprising:a plurality of sensors located at selected nodes in an electrical network of the aircraft,
a processor having a fault diagnosis algorithm, the processor remote from the plurality of sensors and commonly accessible to the plurality of sensors through a communications network,
a memory connected to the processor, and
a data collection algorithm in one of the processor or the plurality of sensors,
wherein each sensor is configured to continuously monitor voltage and current of the electrical network at its selected node, and
wherein upon the occurrence of a fault event, the data collection algorithm selects a subset of the data related to the fault event including at least a portion of the continuously monitored voltage and current immediately preceding the fault event and at least one sensor transmits the selected subset of the data to one of the processor or the memory.

US Pat. No. 10,365,304

DISCRETE INPUT DETERMINING CIRCUIT AND METHOD

GE Aviation Systems LLC, ...

1. A discrete input determining circuit, comprising:an input biasing network connected to a discrete input for providing a first input voltage;
a voltage divider network for dividing the first input voltage into a second input voltage and a third input voltage;
a first comparator, wherein a non-inverting input terminal of the first comparator receives the second input voltage; and
a second comparator, wherein an inverting input terminal of the second comparator receives the third input voltage;
wherein an inverting input terminal of the first comparator and a non-inverting input terminal of the second comparator receive a reference voltage, and an output terminal of the first comparator and an output terminal of the second comparator are configured to provide a logic output; and
wherein the input biasing network comprises a first power supply and a first resistive load connected between the discrete input and the first power supply, and a node between the discrete input and the first resistive load is connected to the voltage divider network.

US Pat. No. 10,273,012

DEICING MODULE FOR AN AIRCRAFT AND METHOD FOR DEICING

GE Aviation Systems LLC, ...

1. A deicing module for an aircraft comprising:a casing operably coupled to an aircraft surface where the aircraft surface encloses an interior of a wing of the aircraft;
at least two tracks inset within the interior of the wing;
at least two moveable members configured to move within their respective at least two tracks in opposite directions where an upper portion of each of the at least two movable members is located between the casing and the aircraft surface and a lower portion of the at least two moveable members is located within the track; and
a driving mechanism operably coupled to the at least two movable members and configured to move the at least one moveable member having a profile that conforms to the aircraft surface beneath the casing such that the at least one moveable member distorts the casing to an extent sufficient to release accumulations of ice thereon.

US Pat. No. 10,436,168

AIR STARTER AND METHODS FOR DETERMINING HYDROSTATIC LOCK

GE Aviation Systems LLC, ...

1. A method of determining hydrostatic lock in a combustion engine started with a turbine air starter, the method comprising:during a start sequence of the combustion engine, monitoring a speed parameter indicative of a rotational speed of the turbine air starter and a pressure parameter indicative of an inlet air pressure of the turbine air starter;
determining the monitored speed parameter satisfies a speed threshold and the monitored pressure parameter satisfies a pressure threshold;
in response to determining the monitored speed parameter satisfies the speed threshold and the monitored pressure parameter satisfies the pressure threshold, determining that a hydrostatic lock condition exists in the combustion engine; and
in response to the determining that a hydrostatic lock condition exists providing an indication of the hydrostatic lock condition or ceasing the start sequence.

US Pat. No. 10,381,833

SOLID STATE POWER CONTACTOR

GE AVIATION SYSTEMS LLC, ...

1. A power contactor, comprising:a first conductive terminal;
a second conductive terminal;
a flexible power overlay, comprising:
a conductive backplane;
a first solid state switch having a first source terminal connected with the conductive backplane and a first drain terminal connected with the first conductive terminal; and
a second solid state switch having a second source terminal connected with the conductive backplane and a second drain terminal connected with the second conductive terminal; and
a controller module configured to selectively operate the first and second solid state switches to enable conductive communication between the first conductive terminal and the second conductive terminal;
wherein the power contactor form is adapted to be physically interchangeable with a conventional electro-mechanical contactor.

US Pat. No. 10,381,900

METHOD AND ASSEMBLY OF AN ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. An electric machine assembly comprising:a main machine stator core having at least one stator post;
a set of stator windings wound about the at least one stator post and having a first end and an opposing second end, the stator windings defining a fluid channel disposed through the stator windings configured to carry a flow of coolant;
a coolant inlet housing defining an inlet passage disposed at an axial end of the electric machine assembly fluidly connected with the fluid channel of the first end of the set of stator windings; and
a coolant outlet housing defining an outlet passage disposed at the axial end of the electric machine assembly, proximate to the coolant inlet housing, and fluidly connected with the fluid channel of the second end of the stator windings;
wherein the coolant inlet passage, the fluid channel of the stator windings, and the coolant outlet passage define a coolant circuit configured to receive a supply of coolant to remove heat generated in the set of stator windings.

US Pat. No. 10,374,486

METHOD AND ASSEMBLY OF AN ELECTRIC MACHINE

GE AVIATION SYSTEMS LLC, ...

1. An electric machine assembly comprising:a housing;
a shaft configured to operably couple with a source of rotational force and rotate about a rotational axis and having a shaft cooling passage;
an arm carried by and extending radially outward from the shaft and having a first cooling passage different from the shaft cooling passage; and
an exciter rotor and a permanent magnet generator rotor carried by the arm;
wherein the exciter rotor and the permanent magnet generator rotor are substantially coplanar at a plane orthogonal to the rotational axis.

US Pat. No. 10,358,221

HYBRID METHOD AND AIRCRAFT FOR PRE-COOLING AN ENVIRONMENTAL CONTROL SYSTEM USING A POWER GENERATOR FOUR WHEEL TURBO-MACHINE

GE Aviation Systems LLC, ...

1. A method of providing bleed air to an environmental control system of an aircraft using a gas turbine engine, the method comprising:determining, by a controller module, a bleed air demand for the environmental control systems;
selectively supplying, by the controller module, low pressure bleed air and high pressure bleed air from a compressor of the gas turbine engine to a first turbine section and compressor section of a turbo air cycle machine rotationally coupled by a common shaft, with the first turbine section emitting a cooled air stream and the compressor section emitting a compressed air stream;
selectively supplying, by the controller module, the cooled air stream to at least one of a second turbine section, rotatably coupled with the first turbine section, with the second turbine section emitting a further cooled air stream, or to a bypass airflow, bypassing the second turbine section, wherein supplying the cooled air stream to the second turbine section creates excess mechanical power on the common shaft;
combining at least one of the cooled air stream emitted from the bypass airflow or the further cooled air stream emitted from the second turbine section with the compressed air stream emitted from the compressor section to form a conditioned air stream;
transforming excess mechanical power into electrical power via a generator rotatably coupled with the common shaft when the cooled air stream is supplied to the second turbine section; and
delivering electrical power to at least one device or system;
wherein the selectively supplying low pressure bleed air and high pressure bleed air and selectively supplying the cooled air stream are controlled such that the conditioned air stream satisfies the determined bleed air demand.

US Pat. No. 10,479,483

PITCH CONTROL ASSEMBLY AND PROPELLER ASSEMBLY AND METHOD OF ADJUSTING PITCH

GE AVIATION SYSTEMS LLC, ...

1. A propeller assembly, comprising:a spider hub comprising a hub defining an interior and a set of arms spaced circumferentially about the hub and projecting radially from the hub, wherein the set of arms are configured to receive a set of blades such that a blade root of a blade of the set of blades is rotationally mounted to an outer periphery of an arm included in the set of arms;
a crosshead located within the interior of the hub and axially moveable relative to the hub;
a torque tube located in the arm and extending into the hub, and having opposing first and second ends, with the first end configured to mount to a proximal most portion of the blade of the set of blades, the torque tube spanning a length, between the first end and second end, from the outer periphery of the arm to the interior of the hub; and
a motion converter located within the interior of the hub and coupling the crosshead to the second end of the torque tube, the motion converter configured for converting axial movement of the crosshead into rotational movement of the torque tube and a pitch angle of the blade can be adjusted by axially moving the crosshead to rotate the torque tube to effect a corresponding rotation of the blade.

US Pat. No. 10,444,748

IN-SITU MEASUREMENT LOGGING BY WIRELESS COMMUNICATION UNIT FOR COMMUNICATING ENGINE DATA

GE Aviation Systems LLC, ...

1. A method of monitoring a line-replaceable unit of an aerial vehicle, the method comprising:receiving a file associated with a wireless communication unit (WCU) located on an aerial vehicle, the file comprising at least one measurement from a sensor associated with the WCU and at least one time assigned to the at least one measurement, the at least one measurement having a value above a high threshold or a value below a low threshold;
predicting one or more operational conditions experienced by the line-replaceable unit (LRU) at least in part by comparing a predictive model to the at least one measurement, the one or more operational conditions comprising at least one condition affecting the operational life of the LRU, and the predictive model configured to output a predicted operational life of the LRU of the aerial vehicle; and
changing the predictive model based at least in part on the one or more operational conditions having been predicted, the predictive model upon having been changed being configured to output an updated predicted operational life of the LRU.

US Pat. No. 10,443,504

METHOD FOR ALLOCATING POWER IN AN ELECTRICAL POWER SYSTEM ARCHITECTURE

GE Aviation Systems LLC, ...

1. An electrical power system architecture, comprising:a power distribution bus configured to receive power generated by a first engine having a first generator system and a second generator system;
a first set of electrical buses connected with the power distribution bus and associated with the first engine;
a second set of electrical buses configured to selectively connect with the power distribution bus, including at least an essential bus, and associated with a second engine; and
a share regulator configured to provide a set of share ratios values to the first generator system and the second generator system, and configured to receive an operational status of the second engine;
wherein, upon receipt of non-operational status of the second engine, the power distribution bus is configured to selectively disconnect the second set of electrical buses except for the essential bus, and the share regulator is configured to provide the set of share ratio values to the first generator system and second generator system selected to enabled the first and second generator systems to share allocation of power generation sufficient to energize the first set of electrical buses and the essential bus.

US Pat. No. 10,326,352

CONTROL OF AC SOURCE INVERTER TO REDUCE TOTAL HARMONIC DISTORTATION AND OUTPUT VOLTAGE UNBALANCE

GE Aviation Systems LLC, ...

1. A control system for a DC to AC inverter configured to provide a multiphase output at a fundamental frequency, the control system comprising:a plurality of synchronous reference frame control structures, each synchronous reference frame control structure associated with a different frequency, each synchronous reference frame control structure comprising a voltage controller configured to provide a current reference based on a voltage feedback signal;
an outer voltage control loop in communication with at least one of the plurality of synchronous reference frame control structures, the outer voltage control loop comprising an outer voltage controller having an infinite gain at a frequency associated with a negative sequence component; and
a shared current controller configured to determine a voltage command for controlling one or more bridge circuits of the DC to AC inverter;
wherein the shared current controller is configured as an inner control loop relative to the voltage controller of each of the plurality of synchronous reference frame control structures.

US Pat. No. 10,316,898

METHOD AND DISCONNECTOR FOR DISCONNECTING A DRIVE SHAFT

GE Aviation Systems LLC, ...

1. A disconnector for disconnecting a drive shaft of a drive mechanism from rotating equipment, upon a failure of the drive mechanism or rotating equipment, comprising:a housing,
an arm extending from the housing and movable relative to the housing between a first position and a second position,
a parting tool on a distal end of the arm;
a biasing element mounted to the housing adjacent a proximal end of the arm configured to bias the arm toward the second position; and
a meltable element disposed in the housing in a position to restrain the arm in the first position against the bias of the biasing element;
wherein when the housing is mounted to at least one of a drive mechanism or rotating equipment, radially spaced from a drive shaft such that the parting tool will contact the drive shaft when the arm is in the second position, a failure in the at least one of the drive mechanism or rotating equipment will cause the meltable element to melt and release the arm for movement to the second position where the parting tool contacts the drive shaft causing a predetermined failure of the drive shaft at the point of contact.

US Pat. No. 10,318,451

MANAGEMENT OF DATA TRANSFERS

GE Aviation Systems LLC, ...

1. A wireless communication unit configured to be located in a nacelle associated with an engine of an aerial vehicle for communicating engine data within a time window, the wireless communication unit comprising:one or more memory devices; and
one or more processors configured to:
receive data;
separate the data into categories;
for each of the categories:
create a separate file comprising the separated data corresponding to the respective category; and
name the separate file, at least in part, based on the respective category and based on a file naming convention, the naming convention based at least in part on a wireless communication unit associated with the separated data;
prioritize the created files;
transmit an identification file comprising identification information for the wireless communication unit and the file naming convention; and
transmit the created files in an order based on the priority associated with the created files, wherein the higher the priority associated with a particular created file, the earlier the particular created file is transmitted, and wherein the wireless communication unit is identifiable based on the name of the file.

US Pat. No. 10,480,446

METHOD AND APPARATUS FOR COOLING A HEAT-GENERATING MODULE

GE Aviation Systems LLC, ...

1. A liquid cooling circuit comprises:a liquid reservoir for combustible fuel having an autoignition temperature;
a heat-generating module;
a conduit fluidly coupling the heat-generating module with the liquid reservoir;
a pump configured to move the combustible fuel through the conduit to cool the heat-generating module;
a temperature component configured to determine the temperature of the combustible fuel; and
a controller module configured to control the pumping of the combustible fuel by ceasing the pumping when the temperature of the combustible fuel satisfies a comparison with a predetermined temperature threshold relative to the autoignition temperature.

US Pat. No. 10,461,542

POWER DISTRIBUTION NETWORK

GE AVIATION SYSTEMS LLC, ...

1. A power system comprising:a first power source and a second power source arranged in a series to define a power source series;
a first electrical load and a second electrical load arranged in series with to define a load series, the load series in series with the power source series; and
a set of bypass current paths, each independently associated with one of at least a subset of: the first power source, the second power source, the first electrical load, and the second electrical load, and wherein the set of bypass current paths are configured to be selectably enabled to allow current to bypass a pair of components comprising at least one of the first power source and the second power source, and at least one of the first electrical load and the second electrical load.

US Pat. No. 10,461,595

ROTOR ASSEMBLY AND COOLING ARRANGEMENT FOR AN ELECTRIC MACHINE

GE Aviation Systems LLC, ...

1. A rotor assembly for an electric machine comprising:a rotor core having a rotatable shaft having hollow interior defining a coolant conduit and at least one post defining a winding pole;
a winding wound around the pole, and having axial segments that extend axially along the pole and end turn segments that extend axially beyond ends of the post;
a coolant manifold supported by the shaft and sealed from the winding but fluidly coupled to the coolant conduit wherein coolant can move between the coolant manifold and the coolant conduit, the coolant manifold having a thermally conductive face radially underlying at least a portion of the end turn segment and in thermal contact with the portion of an end turn segment, wherein heat from the end turn segment is transferred by conduction through the thermally conductive face of the coolant manifold to coolant in the coolant manifold; and
at least one coolant tube in fluid communication with the coolant manifold and extending axially along the post, wherein the coolant tube comprises a first thermally conductive face radially underlying, in thermal contact with, and at least partially supporting, an axial segment of a first winding and a second thermally conductive face radially underlying, in thermal contact with, and at least partially supporting, an axial segment of a second winding.

US Pat. No. 10,460,608

SYSTEM AND METHOD FOR DETERMINING UNCERTAINTY IN A PREDICTED FLIGHT PATH FOR AN AERIAL VEHICLE

GE Aviation Systems LLC, ...

1. A method for determining uncertainty in a predicted flight path for an aerial vehicle, wherein the predicted flight path is comprised of a temporal component and a spatial component, the method comprising:receiving, by one or more computing devices, a first data set comprising one or more parameters indicative of actual performance of the aerial vehicle from one or more sensors of the aerial vehicle;
comparing, by the one or more computing devices, the one or more received parameters of the first data set to one or more corresponding predicted parameters of a performance model of the aerial vehicle;
determining, by the one or more computing devices, uncertainty in the performance model of the aerial vehicle based at least in part on a variance between the one or more received parameters of the first data set and the one or more corresponding predicted parameters of the performance model;
receiving, by the one or more computing devices, a second data set comprising one or more parameters indicative of actual weather conditions for an environment in which the aerial vehicle is operating from the one or more sensors of the aerial vehicle;
comparing, by the one or more computing devices, the one or more received parameters of the second data set to one or more corresponding predicted parameters of a weather model of the aerial vehicle;
determining, by the one or more computing devices, uncertainty in the weather model indicative of weather conditions along the predicted flight path based at least in part on a variance between the one or more received parameters of the second data set and the one or more corresponding predicted parameters of the weather model;
determining, by the one or more computing devices, uncertainty in the predicted flight path based on the uncertainty in the performance model and the uncertainty in the weather model, wherein determining, by the one or more computing devices, uncertainty in the predicted flight path based on the uncertainty in the performance model and the uncertainty in the weather model comprises determining a confidence score indicative of a likelihood of the aerial vehicle flying the predicted flight path within constraints of the temporal component and the spatial component of the predicted flight path; and
generating, by the one or more computing devices, a notification indicating the uncertainty in the predicted flight path.

US Pat. No. 10,454,525

COMMUNICATION OF SIGNALS OVER FUEL LINES IN A VEHICLE

GE Aviation Systems LLC, ...

1. A system, comprising:a fuel line, the fuel line comprising at least one communication medium for communicating a communication signal;
a controller;
a network;
a first signal communication device in bidirectional communication with the network, the first signal communication device coupled to the fuel line, wherein the first signal communication device comprises a transducer comprising a transmit coil and a sensing coil, wherein the sensing coil is configured to receive the communication signal communicated over the fuel line; and
a second signal communication device in bidirectional communication with the controller, the second signal communication device coupled to the at least one fuel line, wherein the first signal communication device and the second signal communication device are in bidirectional signal communication with each other over the at least one fuel line, and
wherein at least one of the first signal communication device and the second signal communication device is further configured to encode the communication signal, and wherein the sensing coil detects varying magnetic fields surrounding the fuel line, and wherein the first signal communication device and the second communication device each comprise at least one transceiver and the second communication device comprises a transducer, and wherein the first signal communication device and the second communication device are each further configured to decode the communication signal, and wherein the at least one transceiver of the first signal communication device decodes signals received from the transducer of the first communication device into a digital format and the at least one transceiver of the second signal communication device decodes signals received from the transducer of the second communication device into a digital format.

US Pat. No. 10,455,431

LINE OF SIGHT AIRCRAFT DATA TRANSFER SYSTEM

GE Aviation Systems LLC, ...

1. A system, comprising:a first directional antenna;
a processor; and
a memory communicatively coupled to the processor, the memory having stored therein computer-executable components, the computer-executable components comprising:
a location component configured to:
in response to receiving a first signal from a first aircraft, determine a first line of sight that is unobstructed to a first antenna of the aircraft, and
in response to not being able to determine the first line of sight that is unobstructed to the first antenna of the first aircraft, determine a second line of sight to an intermediate node that can establish a second communication channel with the aircraft;
a communication component configured to:
in response to the determination of the first line of sight, transmit a first highly directional beamformed electromagnetic (EM) signal from the first directional antenna along a line of sight based on the first line of sight to establish a first communication channel with the aircraft, and
in response to the determination of the second line of sight, transmit the first highly directional beamformed EM signal from the first directional antenna along the line of sight based on the second line of sight to establish a first communication channel with the aircraft through the intermediate node.