US Pat. No. 9,386,730

MODULAR POWER ELECTRONICS DISTRIBUTION SYSTEM

Rolls-Royce Corporation, ...

1. A modular power electronics distribution system, comprising:
a plurality of modules connectable to a pluggable interface, the interface configured to receive and distribute power to the
plurality of modules;

wherein the plurality of modules each include:
at least one fault isolation switch;
a coolant system including an inlet and return line, and a metering valve;
at least one power bus configured to provide electrical power to at least one of a load or source via a functional segment,
wherein the functional segment is operable to supply electrical power in a desired form to the load; and

a controller in communication with the plurality of modules, the controller configured to control at least one of the at least
one fault isolation switch and metering valve.

US Pat. No. 9,500,080

METHOD OF REPLACING DAMAGED AEROFOIL

Rolls-Royce plc, (GB) Ro...

1. A method of replacing a damaged blade of an integrally bladed rotor assembly including a disc and a plurality of blades
extending outwardly from a rim of the disc, the method including the steps of:
removing the damaged blade to leave a blade repair stub projecting from the rim;
locating sacrificial supports at the underside of the rim beneath the repair stub, the supports projecting axially beyond
the trailing and leading edges of the rim;

depositing metal around the trailing and leading edges of the repair stub, the deposited metal, supported by the sacrificial
supports, projecting axially beyond the trailing and leading edges of the rim;

attaching a replacement blade to the repair stub by linear friction welding; and
removing excess deposited metal, upset metal from the linear friction welding, and the sacrificial supports.

US Pat. No. 9,556,750

COMPARTMENTALIZATION OF COOLING AIR FLOW IN A STRUCTURE COMPRISING A CMC COMPONENT

Rolls-Royce North America...

1. A gas turbine engine structure comprising:
a static metal component;
a CMC component spaced apart from the static metal component and separated therefrom by a cavity having sections with respective
passages for receiving cooling air into the cavity through the static metal component and removing cooling air from the cavity
through the CMC component; and

at least one rope seal located between the static metal component and the CMC component,
the rope seal dividing the cavity into the sections to thereby compartmentalize the cavity and cooling air flow is ensured.

US Pat. No. 9,482,451

ADAPTIVE TRANS-CRITICAL CO2 COOLING SYSTEMS FOR AEROSPACE APPLICATIONS

Rolls-Royce Corporation, ...

18. An aircraft comprising:
a turbine engine; and
a cooling system for the aircraft comprising:
a heat exchanger through which a refrigerant flows, in which heat is rejected to a fluid;
a set of valves arranged to:
direct the refrigerant through a first circuit having a fluid expansion device; direct the refrigerant through a second circuit
having a fluid expansion machine; or

direct the refrigerant through both circuits, based on ambient conditions; and
a third circuit having a heater coupled to the first and second circuits, the third circuit including a second expansion device
and the heater configured to receive waste heat from the aircraft, wherein the refrigerant is directed through the heater
and the second expansion machine such that the second expansion machine is configured to extract energy from heated refrigerant
that exits from the heater.

US Pat. No. 9,371,811

METHODS AND SYSTEMS FOR OPERATING A GAS TURBINE ENGINE

Rolls-Royce North America...

1. A method of operating a turbine engine, comprising:
operating an electrical machine to rotate a spool of the gas turbine engine;
determining a torque of the electrical machine during rotation of the spool using a starter motor current measurement;
controlling the rotation of the spool based on the torque;
simultaneously measuring a speed of rotation of the spool and the starter motor current measurement to determine real time
speed versus torque, wherein the speed and torque are maintained as a record of speed versus torque;

augmenting an engine health monitoring data set with the measured torque and speed; and
utilizing the engine health monitoring data set to do at least one of:
reduce turbine engine start up time;
reduce turbine engine start up temperature;
identify turbine engine failure conditions;
adjust for turbine engine aerodynamic changes; or
adjust turbine engine light-off timing.

US Pat. No. 9,046,497

INTELLIGENT AIRFOIL COMPONENT GRAIN DEFECT INSPECTION

Rolls-Royce Corporation, ...

1. A system comprising:
a component manipulator structured to position a component in response to a positioning algorithm;
a surface scanner configured to:
output electromagnetic radiation directed at a surface of the component,
detect reflected electromagnetic radiation from the surface of the component, and
produce a reflectivity signal in response to detecting the reflected electromagnetic radiation; and
a processor configured to:
apply a fuzzy logic algorithm to the reflectivity signal to determine a solution set in response to the reflectivity signal;
and

produce a grain structure characterization in response to the solution set.

US Pat. No. 9,481,448

AERODYNAMIC FAIRINGS SECONDARILY ATTACHED TO NOSECONE

Rolls-Royce Corporation, ...

1. A one-piece aerodynamic fan nosecone assembly comprising:
a fan nosecone having a leading edge and a trailing edge with an aerodynamic exterior surface extending between the leading
and trailing edge;

a plurality of aerodynamic fairings spaced apart and affixed to said aerodynamic exterior surface of the fan nosecone, at
least one of the fairings including:

a base having an aerodynamic portion, and
an attachment feature that mounts an underside of the base to the fan nosecone;
and an insert having a portion projecting from the base that enhances aerodynamic sealing between the fan nosecone and a blade
member, wherein the insert includes a filler material.

US Pat. No. 9,482,236

MODULATED COOLING FLOW SCHEDULING FOR BOTH SFC IMPROVEMENT AND STALL MARGIN INCREASE

Rolls-Royce Corporation, ...

1. A turbine engine comprising:
a compressor having a mid-compression station and an exit pressure station;
a low pressure turbine and a high pressure turbine;
a first gas flow line interposed between the exit pressure station of the compressor and the high pressure turbine;
a second gas flow line interposed between the mid compression station of the compressor and the low pressure turbine;
a first valve coupled to the first gas flow line and configured to modulate a first flow rate of coolant in the first gas
flow line;

a second valve coupled to the second gas flow line and configured to modulate a second flow rate of coolant in a second coolant
flow line;

a controller configured to operate the first and second valves based on an operating condition of the turbine engine; and
a computer programmed to instruct the controller to modulate the first and second valves based on the operating condition,
wherein the computer is programmed to instruct the controller to modulate the second valve to a full open position based on
the operating condition that comprises one of an acceleration and a bodie.

US Pat. No. 9,260,976

ENGINE HEALTH MONITORING AND POWER ALLOCATION CONTROL FOR A TURBINE ENGINE USING ELECTRIC GENERATORS

Rolls-Royce North America...

12. A method for controlling the allocation of power extracted from a plurality of shafts of a turbine engine, the shafts
having one or more electrical machines coupled to each of the shafts, the method comprising:
receiving, via feedback control of the turbine engine, data relating to one or more turbine engine operating conditions including
fuel flow, temperature, pressure, and/or speed;

generating an assessment of the health of the turbine engine based on changes in the one or more operating conditions over
time;

using a model-based algorithm to predict a change in the health of the turbine engine based on the operating conditions and
a healthy engine profile, wherein the change in health of the turbine engine is indicative of a wear characteristic of the
turbine engine;

determining an optimal power extraction allocation between the electrical machines based on the predicted change in engine
health, the operating conditions, and one or more optimization parameters including fuel efficiency, engine performance, and/or
engine reliability; and

controlling the electrical machines to implement the optimal power extraction by configuring the one or more electrical machines
coupled to each of the plurality of shafts to generate a part of a total amount of electrical energy.

US Pat. No. 9,228,497

GAS TURBINE ENGINE WITH SECONDARY AIR FLOW CIRCUIT

Rolls-Royce Corporation, ...

1. A gas turbine engine, comprising:
a compressor having an impeller;
a diffuser having a plurality of diffuser vanes;
wherein the impeller is a centrifugal impeller, and wherein the diffuser is a radial diffuser;
wherein the diffuser forms a flowpath downstream of the impeller;
wherein the diffuser vanes extend across the flowpath; and
wherein at least one of the diffuser vanes has a first opening extending through the diffuser vanes and across the flowpath;
a combustor in fluid communication with the compressor;
a turbine in fluid communication with the combustor; and
a secondary flow circuit operative to deliver secondary air flow to the impeller for controlling a temperature of a portion
of the impeller, wherein the secondary air flow is delivered to the impeller from across the flowpath through the first opening;
and

one or more walls defining a cavity separate from the flowpath, the one or more walls further having an opening therein configured
to supply the secondary air flow from the cavity to at least one diffuser vane, wherein the impeller includes a plurality
of blades and a back face opposite the plurality of blades, further comprising a static structure spaced apart from the back
face and configured to direct the secondary air flow from a radially outer tip portion of the impeller radially inward along
the back face of the impeller.

US Pat. No. 9,249,684

COMPLIANT COMPOSITE COMPONENT AND METHOD OF MANUFACTURE

Rolls-Royce Corporation, ...

1. A composite component comprising
a bonded portion made from a ceramic matrix composite material and
an un-bonded portion made from the ceramic matrix composite material and coupled to the bonded portion to move relative to
the bonded portion in response to application of a load to cause the composite component to deform in a controlled manner
without fracture of the composite component,

wherein the un-bonded portion includes a first un-bonded section coupled to the bonded portion to move relative to the bonded
portion in response to application of the load, a second un-bonded section coupled to the bonded portion to move relative
to the bonded portion and the first un-bonded section in response to application of the load, and a third un-bonded section
coupled to the bonded portion to move relative to the bonded portion, the first un-bonded section, and the second un-bonded
section in response to application of the load.

US Pat. No. 9,458,726

DOVETAIL RETENTION SYSTEM FOR BLADE TRACKS

Rolls-Royce Corporation, ...

1. A turbine shroud comprising
a metallic inner carrier formed to include a plurality of apertures,
a plurality of ceramic blade track segments each including an arcuate runner arranged radially inward from the metallic inner
carrier and a dovetail post extending radially outward from the arcuate runner through one of the apertures formed in the
metallic inner carrier, and

a plurality of segment retainers arranged radially outward from the metallic inner carrier, each segment retainer formed to
include a retention channel mated with a portion of a corresponding dovetail post, and each segment retainer sized to block
movement of the corresponding dovetail post through the aperture so that the plurality of ceramic blade track segments are
coupled to the metallic inner carrier.

US Pat. No. 9,435,267

INTEGRATED HEALTH MANAGEMENT APPROACH TO PROPULSION CONTROL SYSTEM PROTECTION LIMITING

Rolls-Royce North America...

1. An engine system comprising:
a controller system that controls demand on a first component of an engine, wherein the controller system includes at least
one controller and is configured to:

access a first set of prognostic data about the first component, wherein the first set of prognostic data includes a remaining
lifespan approximation of the first component operating at a present operating condition;

identify a temporal length of an engine procedure operating at the present operating condition;
decrease a maximum hard current limit of the first component to increase the remaining lifespan approximation of the first
component beyond the temporal length; and

implement the current limit constant associated with the first component so that the first component does not fault during
engine operation.

US Pat. No. 9,051,881

ELECTRICAL POWER GENERATION AND WINDMILL STARTING FOR TURBINE ENGINE AND AIRCRAFT

Rolls-Royce Corporation, ...

1. A single engine air vehicle, comprising:
a gas turbine engine, wherein the gas turbine engine includes:
a first spool configured as a high pressure spool;
a second spool configured to operate at lower pressures than the high pressure spool; and
a single electrical rotor machine coupled to the second spool,
wherein the electrical rotor machine is configured to extract mechanical power from the second spool during a windmilling
event, convert the mechanical power to electrical power, and supply the electrical power to the first spool for use in effecting
a windmill start of the gas turbine engine;

wherein the single electrical rotor machine is configured to supply electrical power to the air vehicle during normal gas
turbine engine operation as the sole source of electrical power for the air vehicle.

US Pat. No. 9,051,882

SEALS FOR A GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

1. A seal assembly for use in a gas turbine engine comprising
a rotating engine component configured to rotate about a rotational axis,
a stationary engine component positioned in a fixed orientation relative to the rotational axis and spaced apart from the
rotating engine component to form a gap therebetween, and

a sealing unit positioned in the gap between the stationary engine component and the rotating engine component, the sealing
unit including a body and a coating, the body including a first surface and a second surface, the coating coupled to the first
surface establishes a coated first surface and at least a portion of the second surface is free from the coating to establish
an uncoated portion of the second surface, and the coated first surface directly engages the stationary engine component and
the uncoated portion of the second surface directly engages the rotating engine component to form a mechanical seal between
the stationary engine component and the rotating engine component.

US Pat. No. 9,506,356

COMPOSITE RETENTION FEATURE

Rolls-Royce North America...

14. A retention feature for use in a gas turbine engine comprising
a ceramic post including a body adapted to be coupled to a turbine engine component and a head coupled to the body, the head
formed to include a space,

a first insert arranged in the space, and
a first braze layer extending from the ceramic post to the first insert to bond the first insert to the ceramic post,
wherein the first insert is U-shaped such that a gap exists between two opposed sides thereof.

US Pat. No. 9,556,743

VISUAL INDICATOR OF COATING THICKNESS

Rolls-Royce Corporation, ...

1. An article comprising:
a substrate;
a coating on the substrate, wherein the coating comprises:
at least one abradable layer;
a neodymium silicate layer;
an erbium silicate layer; and
a gadolinium silicate layer, wherein the neodymium silicate layer, the erbium silicate layer, and the gadolinium silicate
layer are adjacent to each other within the coating.

US Pat. No. 9,222,676

SUPERCRITICAL OR MIXED PHASE FUEL INJECTOR

Rolls-Royce Corporation, ...

1. An apparatus, comprising:
a main fuel supply fluidly coupled to a main fuel valve;
an arcuate fuel passage receiving main fuel through the main fuel valve, wherein the arcuate fuel passage comprises a passage
diameter and a radius of curvature structured to provide sufficient rotational acceleration to the main fuel such that a liquid
portion of the main fuel is deposited on an outer wall of the arcuate fuel passage; and

a fuel injector nozzle structured to receive the main fuel from the arcuate fuel passage, and to inject the main fuel into
a combustion chamber for a turbine engine;

wherein the main fuel valve is structured to maintain a backpressure on the main fuel supply such that fuel in the main fuel
supply is a liquid phase.

US Pat. No. 9,046,130

GAS TURBINE ENGINE AND HIGH SPEED ROLLING ELEMENT BEARING

Rolls-Royce Corporation, ...

1. A high speed rolling element bearing system for reacting a primary thrust load, comprising:
a first high speed rolling element thrust bearing;
a second high speed rolling element thrust bearing, wherein the first high speed rolling element thrust bearing and the second
high speed rolling element thrust bearing are dimensionally configured to react the primary thrust load in parallel;

a clutch operable for selectively coupling first and second rotatable spools together, the clutch adapted to transmit the
primary thrust load during a clutching operation and remove the primary thrust load upon completion of the clutching operation;

a preload generator operative to generate a thrust preload between the first high speed rolling element thrust bearing and
the second high speed rolling element thrust bearing upon removal of the primary thrust load; and

wherein the preload generator includes a split spacer with a pair of substantially U-shaped cavities opposing one another
and a spring engaged within the opposing cavities.

US Pat. No. 9,458,768

ALGAE-DERIVED FUEL/WATER EMULSION

Rolls-Royce Corporation, ...

6. A method comprising:
processing a wet algae material having been subjected to a refinement process without a water separation phase;
providing a wet biofuel including an algae-grown biofuel and the wet algae material having at least a portion of a water phase;
supplying the wet biofuel as an emulsion with a source supply device structured to deliver the wet biofuel to a gas turbine
engine; and

operating the gas turbine engine with the wet biofuel, and
wherein said providing the wet biofuel further includes reducing a generation of a quantity of nitrogen oxides in said operating
the gas turbine engine with a determined amount of the portion of the water phase, and wherein the operating the gas turbine
engine further includes combusting the wet biofuel in a combustor of the gas turbine engine.

US Pat. No. 9,046,272

COMBUSTION LINER ASSEMBLY HAVING A MOUNT STAKE COUPLED TO AN UPSTREAM SUPPORT

Rolls-Royce Corporation, ...

16. A method comprising:
spacing an inner liner of a gas turbine engine combustor from an outer liner, the inner liner having a through passage and
the outer liner having a through passage;

installing a mount stake that is elongate between the inner liner and the outer liner of a gas turbine engine combustor such
that an outer end of the mount stake extends past the through passage of the outer liner and an inner end of the mount stake
extends past the through passage of the inner liner, wherein the mount stake fails to contact a gas turbine engine casing
located near the outer liner of the gas turbine engine,

wherein the mount stake is radially oriented between the inner liner and outer liner and includes a radial length larger than
a cross sectional dimension taken along the length of the mount stake, wherein the mount stake is structured to retain a spaced
relation of the inner liner and the outer liner;

forming a flow space between the mount stake and a neighboring mount stake such that a bulk flow of working fluid is permitted
to pass; and

coupling an intermediate portion of the mount stake to a structure of the gas turbine engine at a point upstream of the mount
stake

further including a support assembly coupled to the structure of the gas turbine engine, and wherein the support assembly
is directly coupled to the mount stake.

US Pat. No. 9,527,777

COMPLIANT LAYER FOR CERAMIC COMPONENTS AND METHODS OF FORMING THE SAME

ROLLS-ROYCE CORPORATION, ...

12. A ceramic matrix composite (CMC) component with an interface coating system thereon, the interface coating system comprising;
a bond coating on a surface of the CMC component, wherein the bond coating comprises Si;
an interface coating on the bond coating,
wherein the interface coating comprises a layer of
90-95 wt % Ir, 5-10 wt % Co, 1-2 wt % Al, 1-2 wt % Si;
a corrosion-resistant coating on the interface coating, wherein the corrosion resistant coating comprises an alloy comprising
at least one of Ti, Al, or V, an alloy comprising at least one of Ti, Al, Sn, Zr, or Mo, or an alloy comprising Ni and Cr;
and

a compliance-enhancing coating on the corrosion-resistant coating, wherein the compliance-enhancing coating comprises at least
one of Pt, Ag, Cu, Ni, Cr, Co, or Mo.

US Pat. No. 9,267,533

LOCKING FASTENER

Rolls-Royce Corporation, ...

1. A locking fastener comprising: a hollow lock bolt having a drive head formed proximate a first end and external threads
formed proximate a second end, the hollow lock bolt further having a relatively smooth internal wall with an angled taper
extending along at least a portion thereof; and
a lock stud constructed to engage the hollow lock bolt, the lock stud having a drive head proximate a first end and external
threads formed proximate a second end, the lock stud further having a relatively smooth external wall with an angled taper
formed along a portion thereof,

wherein the locking fastener is configured for clamping a first component between at least a portion of the hollow lock bolt
and a second component; and

wherein the lock stud and hollow lock bolt are configured so that the drive head of the lock stud extends past an interface
between the first component and the second component in an installed condition of the locking fastener; and

wherein the taper angle of the hollow lock bolt and the lock stud are different from one another.

US Pat. No. 9,482,156

VEHICLE RECUPERATOR

Rolls-Royce Corporation, ...

1. A system comprising:
an engine having:
a compressor and a turbine coupled together with a flow path there between by which a fluid flow stream is flowable from the
compressor to the turbine, the compressor having a compressor discharge through which the fluid flow stream exits the compressor,
the turbine being configured to generate power;

a combustor located between the compressor and the turbine, the combustor being configured to provide heat to the fluid flow
stream before entering the turbine;

at least one recuperator disposed downstream of the compressor, the recuperator being configured to transfer heat with the
fluid flow stream en route to the combustor;

an electric generator operatively coupled to the turbine to receive at least a portion of the power generated by the turbine,
the electric generator further being in communication with the at least one recuperator; and

a controller configured to operate the engine in a low power mode, a high power mode, and at least one intermediate speed/power
mode, the controller configured to selectively distribute energy from the electric generator between the at least one recuperator
and a load, the controller configured to direct energy to the at least one recuperator while reducing a fuel flow to the engine
when in the intermediate speed/power mode to maintain a speed/power setting of the engine;

wherein the recuperator is configured in an off condition in the low power mode.

US Pat. No. 9,175,605

GAS TURBINE ENGINE SURGE MARGIN BLEED POWER RECUPERATION

Rolls-Royce Corporation, ...

1. A gas turbine engine, comprising:
a compressor;
a combustor in fluid communication with said compressor;
a turbine in fluid communication with said combustor;
a surge margin bleed system in fluid communication with said compressor and operative to bleed air from said compressor as
surge margin bleed air to control surge margin;

a power recuperation system in fluid communication with said surge margin bleed system and operative to recapture power from
the surge margin bleed air; and

an accessory drive system;
wherein said power recuperation system includes an auxiliary turbine in the form of an air turbine in direct fluid communication
with the surge margin bleed system such that the surge margin bleed system provides a continuous surge margin bleed flow not
controlled by a valve system to the air turbine; and

wherein said power recuperation system further includes a first generator mechanically coupled to said auxiliary turbine;
a system electrical bus, wherein said first generator is electrically coupled to said system electrical bus and operative
to provide power recaptured from the surge margin bleed air to said system electrical bus; and

a controller communicatively coupled to said first generator and to said system electrical bus, and wherein said controller
is configured to execute program instructions to control the electrical power provided from said first generator to said system
electrical bus.

US Pat. No. 9,127,770

TUNED FLUID SEAL

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a shaft;
a rotating seal extending from and spaced apart radially from the shaft, wherein the rotating seal extends circumferentially
around the shaft;

a static seal configured for cooperation with the rotating seal to restrict fluid flow therebetween; and
an arm configured to support the static seal, wherein the arm is tuned to asymmetrically move in response to a change of operating
conditions in the apparatus and configured to maintain a desired gap between the static seal and the rotating seal during
and after the change of operating conditions.

US Pat. No. 9,551,299

CHECK VALVE FOR PROPULSIVE ENGINE COMBUSTION CHAMBER

Rolls-Royce Corporation, ...

1. A combustion chamber comprising
an inner wall; and
an outer wall surrounding the inner wall;
the inner wall having a plurality of effusion holes in fluid communication with an inside of the combustion chamber, the outer
wall having a plurality of cooling side holes in fluid communication with a cooling source;

the inner wall and the outer wall defining a flow passage therebetween that fluidly connects one or more of the cooling side
holes with one or more of the effusion holes,

the flow passage having a geometric configuration to permit forward flow of gases through the flow passage from the cooling
source to the inside of the combustion chamber and to restrict reverse flow of gases through the flow passage from the inside
of the combustion chamber to the cooling source, and

the permitted flow rate being greater than the restricted flow rate,
wherein the geometric configuration includes a backflow inhibiting portion formed by a forwardly directed pointed conical
portion flanked by a pair of deflector portions and each deflector portion is defined by a forwardly opening curved wall.

US Pat. No. 9,116,126

TECHNIQUES FOR REMOVING A CONTAMINANT LAYER FROM A THERMAL BARRIER COATING AND ESTIMATING REMAINING LIFE OF THE COATING

Rolls-Royce Corporation, ...

1. A method comprising:
outputting electromagnetic energy at a first energy setting from an energy source;
exposing a portion of an article comprising a substrate, a thermal barrier coating comprising a thermally grown oxide on the
substrate, and a thermally insulative layer on the thermally grown oxide to the first energy setting to ablate the portion
of the article, wherein the portion of the article comprises a portion of the thermally insulative layer;

collecting a spectrum of electromagnetic energy emitted by the portion of the article after ablation;
determining, based on the collected spectrum of electromagnetic energy, that a component of the thermally insulative layer
is present in the portion of the article;

outputting electromagnetic energy at a second energy setting from the energy source, wherein the second energy setting is
different than the first energy setting,

exposing a portion of the thermally grown oxide to the second energy setting;
detecting electromagnetic energy fluoresced by the portion of the thermally grown oxide in response to exposure to the second
energy setting; and

estimating a remaining life of the thermal barrier coating based on the electromagnetic energy fluoresced by the portion of
the thermally grown oxide.

US Pat. No. 9,593,591

ENGINE HEALTH MONITORING AND POWER ALLOCATION CONTROL FOR A TURBINE ENGINE USING ELECTRIC GENERATORS

Rolls-Royce Corporation, ...

1. A method for controlling an allocation of power extracted from a plurality of shafts of a turbine engine, the shafts having
one or more electrical machines coupled thereto, the method comprising, with a controller, during operation of the turbine
engine:
monitoring a plurality of operating parameters of the turbine engine over time;
assessing a health of the turbine engine over time based on the plurality of operating parameters as they are monitored, wherein
the health of the turbine engine is indicative of a wear characteristic of the turbine engine; and

varying the allocation of power extraction between the plurality of electrical machines over time in response to the assessing
of the health of the turbine engine by assigning a part of a total power extraction to the one or more electrical machines
coupled to each of the plurality of shafts.

US Pat. No. 9,561,763

CONTROL SYSTEM FOR A DUAL REDUNDANT MOTOR/GENERATOR AND ENGINE

Rolls-Royce Corporation, ...

1. An electrical system comprising:
a power plant operable to provide motive power;
a first motor/generator and a second motor/generator operatively coupled to a common gear shaft, and to the power plant via
a gearbox and drive shaft; and

a system controller configured to selectively operate at least one of the first motor/generator and the second motor/generator
in one of a motor operating mode and a generator operating mode based on at least one parameter, and to alter the operating
mode when the at least one parameter exceeds a predetermined threshold;

wherein at least one of the first motor/generator and the second motor/generator provides power to the power plant in the
motor operating mode, and extracts power from the power plant in the generator operating mode;

wherein the at least one parameter includes a temperature of at least one of the first motor/generator and the second motor/generator.
US Pat. No. 9,328,620

METHOD FOR MAKING GAS TURBINE ENGINE COMPOSITE STRUCTURE

Rolls-Royce Corporation, ...

1. A method for making a gas turbine engine matrix composite structure comprising:
providing at least one metal core element;fabricating a matrix composite component about the metal core element; and
removing at least part of the metal core element from the matrix composite component by introduction of a halogen gas.

US Pat. No. 9,512,044

CERAMIC MATRIX COMPOSITES AND METHODS FOR PRODUCING CERAMIC MATRIX COMPOSITES

Rolls-Royce Corporation, ...

1. A method of producing a ceramic matrix composite, comprising the steps of:
forming a network of silicon carbide fibers;
depositing an interface layer on the silicon carbide fibers before depositing a matrix material; and
depositing the matrix material comprising silicon and carbon onto the silicon carbide fibers to form silicon carbide;
wherein the depositing the matrix material comprises at least one of the group consisting of (1) depositing substantial amounts
of silicon in excess of silicon carbide stoichiometric amounts, (2) introducing an oxygen containing gas, (3) introducing
a halogen gaseous species, (4) introducing an organometallic gaseous species, or (5) a combination thereof and

wherein the depositing the matrix material comprises depositing silicon in an amount in excess of the silicon carbide stoichiometric
amount, wherein the excess amount is about 10 atomic percent to about 20 atomic percent.

US Pat. No. 9,151,438

AUTOMATED OBJECT MANIPULATION SYSTEM

Rolls-Royce Corporation, ...

1. A method comprising:
grasping a gas turbine engine component with a plurality of fingers of a first manipulator;
handing off the gas turbine engine component to a second manipulator structured to rotate in a carriage that also includes
the first manipulator;

rotating the gas turbine engine component about a first axis and a second axis fixed in the carriage prior to the handing
off such that the first axis and second axis rotate with the carriage.

US Pat. No. 9,534,640

CLUTCH COUPLED TO GAS TURBINE ENGINE AND METHOD FOR COOLING

Rolls-Royce Corporation, ...

8. A gas turbine engine power transmission assembly comprising
a stack of axially aligned annular shape power transmission disks capable of selectively transmitting power from a drive shaft
of a gas turbine engine to a driven aircraft component, the annular shape power transmission disks together defining a dry
clutch assembly having an axially extending central passage;

a transmission shaft that extends through the axially extending central passage of the annular shape power transmission disks
and that defines an axially extending fluid transfer passage that extends through the transmission shaft at least the length
of the axially extending central passage, the transmission shaft includes a central shaft portion that extends at least the
length of the axially extending central passage and defines at least a portion of the fluid transfer passage, and a converging
shaft portion downstream of the central shaft portion in which a wide end of the converging shaft portion is joined to the
central shaft portion; and

means for transferring a heat conducting fluid through the axially extending fluid transfer passage of the transmission shaft.

US Pat. No. 9,347,899

THERMOGRAPHIC INSPECTION TECHNIQUES

Rolls-Royce Corporation, ...

1. A system comprising:
a fluid source fluidically coupled to a plenum;
a thermal camera;
a flow meter; and
a computing device communicatively connected to the at least one flow meter and the thermal camera, wherein the computing
device is configured to:

receive flow rate values for an exit orifice of a first component from the flow meter, wherein the first component is fluidically
coupled to the plenum;

receive thermographic image data captured by the thermal camera during flowing thermographic testing of a second component
fluidically coupled to the plenum, wherein the first component and the second component have a substantially similar geometry;
and

associate the flow rate values for the exit orifice of the first component with the thermographic image data for a corresponding
exit orifice of the second component to produce quantitative flowing thermographic image data.

US Pat. No. 9,080,457

EDGE SEAL FOR GAS TURBINE ENGINE CERAMIC MATRIX COMPOSITE COMPONENT

Rolls-Royce Corporation, ...

1. A gas turbine engine ceramic matrix composite (CMC) component comprising:
first and second outer layers of plies, and an intermediate layer of plies between the first and second outer layers of plies;
the intermediate layer of plies being offset relative to the first and second outer layers of plies;
wherein the offset forms a protrusion on one side of the CMC component and a recess in an opposite side of the CMC component
such that when two CMC components are assembled together, the protrusion of the one CMC component engages the recess of the
other CMC component to form an edge seal between the CMC components, wherein the protrusion is less infiltrated than other
portions of the CMC component.

US Pat. No. 9,586,690

HYBRID TURBO ELECTRIC AERO-PROPULSION SYSTEM CONTROL

Rolls-Royce Corporation, ...

8. A hybrid turbo electric aero-propulsion system comprising:
a turbine engine;
a generator to receive rotational energy from the turbine engine;
an energy storage subsystem to receive electrical input from the generator, the energy storage subsystem comprising one or
more of: an energy storage device, a power converter, and an inverter;

a motor to receive electrical input from the energy storage subsystem;
a fan that may be driven by either the engine or the motor; and
a control to optimize the efficiency of the turbo-electric aero-propulsion system by computing optimal set point values for
each of the turbine engine, the generator, the energy storage subsystem, the motor, and the fan to electronically control
the turbine engine, the generator, the energy storage subsystem, the motor and the fan.

US Pat. No. 9,523,149

RAPID CERAMIC MATRIX COMPOSITE PRODUCTION METHOD

Rolls-Royce Corporation, ...

1. A method of producing a ceramic matrix composite comprising a) applying a fiber interface coating to fibers b) coating
the fibers via chemical vapor infiltration to create a coated fiber composite, and c) infiltrating the coated fiber composite
with a molten material via melt infiltration, wherein the fibers are not removed from a tool in a furnace between steps (a),
(b), and (c), and wherein the tool comprises a tool inlet port configured to accommodate the intake of gas and of molten material,
and a tool exhaust port, wherein the tool exhaust port includes an outlet with a material in the outlet, the material permitting
gas flow therethrough and creating a seal by blocking particulate and/or reacting with the molten material.

US Pat. No. 9,513,200

DETERMINATION OF A THRESHOLD CRACK LENGTH

ROLLS-ROYCE CORPORATION, ...

1. A method comprising:
determining a fatigue crack length and a fatigue crack angle of a fatigue crack of a machine component, wherein the fatigue
crack angle is measured as an angle between a normal to a plane defined by the fatigue crack and a direction of the anticipated
cyclic load force to be applied to the machine component;

determining a component threshold stress intensity factor for the fatigue crack, wherein the component threshold stress intensity
factor is determined from a dataset formed by at least conducting an asymmetric four point bend test on a test specimen having
an initial notch, wherein the dataset includes at least one respective threshold stress intensity factor and at least one
mixed-mode phase angle, wherein each respective threshold stress intensity factor of the at least one respective threshold
stress intensity factor is associated with a corresponding mixed-mode phase angle of the at least one mixed-mode phase angle,
and wherein the component threshold stress intensity factor is based at least in part on a threshold stress intensity factor
associated with a mixed-mode phase angle that corresponds to the fatigue crack angle;

determining a threshold crack length for the component threshold stress intensity factor based on the following equation:
where ath is the threshold crack length, ?Kth is the component threshold stress intensity factor, ?? is the anticipated stress cycle to be applied to the machine component,
? is a geometry correction factor, and a? is a small-crack correction factor; and
categorizing a condition of the machine component based at least in part on a comparison between the threshold crack length
and the fatigue crack length of the fatigue crack in the machine component.

US Pat. No. 9,291,060

HIGH STRENGTH JOINTS IN CERAMIC MATRIX COMPOSITE PREFORMS

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine component construction suitable for operational use in an operating environment associated with a gas
turbine engine, the component construction including a first ceramic matrix composite preform component comprising a first
end surface and a second ceramic matrix composite preform component comprising a second end surface, the first composite preform
component including a plurality of extended fibers having an extended portion that protrudes away from the first end surface,
the extended fibers received within an internal space of a body of the second composite preform component such that the body
of the second composite preform component at least partially envelopes the extended portion of the plurality of extended fibers
and creates a joint between the first composite preform component and the second composite preform component at an interface
of the first end surface and the second end surface; and wherein the extended fibers are woven into the first ceramic matrix
composite preform but not woven into the second ceramic matrix composite preform.

US Pat. No. 9,541,844

METHOD AND APPARATUS FOR CALIBRATING A PROJECTED IMAGE MANUFACTURING DEVICE

Rolls-Royce Corporation, ...

1. A method comprising:
positioning an imaging plate at a manufacturing position relative to a manufacturing device, wherein the manufacturing device
comprises a projector and an optical train, and wherein the imaging plate comprises a surface comprising a contrasting image;

projecting a test image from the projector through the optical train onto the surface comprising the contrasting image such
that the test image is positioned with the contrasting image on the surface of the imaging plate; and

calibrating at least one of the projector or the optical train based on registration between the test image and the contrasting
image,

wherein calibrating at least one of the projector or the optical train comprises tuning magnification, skew, and parallelism
of the test image in relation to the contrasting image until registration between the test image and the contrasting image
on the surface of the imaging plate is achieved before manufacturing a solid part with the manufacturing device.

US Pat. No. 9,394,830

INVERTED CAP IGNITER TUBE

Rolls-Royce Corporation, ...

14. An igniter tube assembly comprising:
an igniter tower with a radially extending portion;
a ferrule with a radially extending portion; and
a retainer with a radially extending portion;
wherein the radially extending portion of the igniter tower is disposed between the radially extending portion of the retainer
and the radially extending portion of the ferrule; and

wherein the igniter tower is formed of a first material and the ferrule is formed of a second material, and wherein the first
material is a different material from the second material.

US Pat. No. 9,133,770

FUEL NOZZLE ENCLOSURE

Rolls-Royce Corporation, ...

1. An enclosure assembly for a portion of a fuel delivery system comprising:
a nozzle body cover portion operable to enclose at least a portion of a fuel nozzle body; and
a fuel line cover portion unitary with said nozzle body cover portion and operable to enclose a portion of a fuel supply line
connected to the fuel nozzle body, wherein both of said nozzle body cover portion and said fuel line cover portion are defined
by first and second half-shells operable to cooperate together in a clam shell arrangement.

US Pat. No. 9,423,137

FUEL INJECTOR WITH FIRST AND SECOND CONVERGING FUEL-AIR PASSAGES

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine having a fuel injector including
a first fuel circuit for delivering fuel to a first air passage and
a second fuel circuit for delivering fuel to a second air passage, the first air passage adjacent to the second air passage,
the first fuel circuit structured to deliver fuel transverse to an airflow passing through the first air passage and
the second fuel circuit including a fuel filmer structured to deliver fuel to a shear region of the fuel injector defined
by the airflow from the first air passage and an airflow from the second air passage,

wherein the second fuel circuit includes an opening in a radially outer wall of the second air passage that is structured
to deliver fuel to a filming surface of the second air passage, the second fuel circuit including a fuel swirler upstream
of the opening,

wherein the first air passage is located radially outward of the second air passage, and
wherein the first fuel circuit includes a plain jet injector, and the fuel injector is operable to produce a film of fuel
on a surface of the first air passage opposite the plain jet injector.

US Pat. No. 9,194,242

THERMAL BARRIER COATINGS INCLUDING CMAS-RESISTANT THERMAL BARRIER COATING LAYERS

Rolls-Royce Corporation, ...

1. An article comprising:
a superalloy substrate; and
a calcia-magnesia-alumina-silicate (CMAS)-resistant thermal barrier coating (TBC) layer overlying the superalloy substrate,
wherein the CMAS-resistant TBC layer comprises:

between about 50 wt. % and about 90 wt. % of a TBC composition, wherein the TBC composition comprises at least one of hafnia
or zirconia stabilized with the following rare earth oxides:

between about 20 mol. % and about 40 mol. % ytterbia,
between about 10 mol. % and about 20 mol. % samaria, and
between about 10 mol. % and about 20 mol. % of at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia, wherein
the TBC composition comprises more ytterbia than samaria and more ytterbia than the at least one of lutetia, scandia, ceria,
gadolinia, neodymia, or europia, and

between about 10 wt. % and about 50 wt. % of a CMAS-resistant composition, wherein the CMAS-resistant composition comprises
alumina, silica, and an oxide of at least one of Sc, Y, La, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Yb, Dy, Ho, Er, Tm, Tb, or Lu.

US Pat. No. 9,156,560

INTELLIGENT INTEGRATED PROPULSION CONTROL SYSTEM AND METHOD

Rolls-Royce Corporation, ...

1. A system, comprising:
at least one aircraft engine operable to generate a power output in response at least in part to an operator power request
and sensed parameters from a flight sensor;

an engine control subsystem configured to control operation of the at least one aircraft engine;
an electrical power subsystem including at least one electrical power device that is operable to demand electric power during
operation of the at least one aircraft engine; and

a propulsion controller connected to the engine control subsystem and to the electrical power subsystem with a propulsion
system data bus, wherein the propulsion controller is configured to determine an anticipatory electric power demand of the
at least one electrical device based on current operating conditions and provide control signals to the engine control subsystem
to control the at least one aircraft engine to generate the power output to meet a total power demand, wherein the total power
demand includes at least the anticipatory electric power demand and a nominal power demand based at least in part on the operator
power request, and wherein the propulsion controller is configured to initiate compensation for the anticipatory electric
power demand prior to the at least one aircraft engine receiving an increased demand for power output.

US Pat. No. 9,541,003

AIR PARTICLE SEPARATOR

Rolls-Royce Corporation, ...

17. A method comprising:
starting a gas turbine engine including accelerating a rotatable compressor;
activating a flow source apart from the rotatable compressor of the gas turbine engine to provide an ejector flow;
forming a clean flow and a dirty flow downstream of an inlet of the gas turbine engine;
routing the clean flow to the accelerating compressor; and
entraining the dirty flow with the ejector flow.

US Pat. No. 9,488,104

GAS TURBINE ENGINE LUBRICATION SYSTEM

Rolls-Royce Corporation, ...

9. A gas turbine engine comprising
an engine core including an inlet, a compressor, a turbine, and an exhaust
a bearing sump arranged in the engine core, and
an air system coupled to the bearing sump and configured to provide pressurized air to the bearing sump to cool a bearing
included in the bearing sump, the air system including (i) a delivery line coupled to the bearing sump to deliver pressurized
air to the bearing sump, (ii) a first bleed line coupled to the engine core to receive pressurized air from the engine core
for transportation to the bearing by the delivery line, (iii) a heat exchanger filled with a coolant coupled between the delivery
line and the first bleed line to cool air before delivery to the bearing sump, and (iv) a vent valve coupled to the heat exchanger,
the vent valve configured to vent coolant to the atmosphere during operation of the gas turbine engine based on the temperature
of the coolant to control pressure and phase of the coolant in the heat exchanger in order to provide a predetermined amount
of cooling to pressurized air passing through the heat exchanger.

US Pat. No. 9,470,097

AIRFOIL WITH LEADING EDGE REINFORCEMENT

Rolls-Royce Corporation, ...

1. An airfoil for a gas turbine engine comprising
a core body having a leading edge, a trailing edge, a first surface extending between the leading edge and the trailing edge,
and a second surface extending between the leading edge and the trailing edge;

a leading edge member having a tip, a first leg extending from a first proximal end at the tip to a first distal end, a second
leg extending from a second proximal end at the tip to a second distal end, the first distal end of the first leg being joined
to the first surface of the core body, the second distal end of the second leg being joined to the second surface of the core
body, and an interior cavity located between the first leg and the second leg at the tip of the leading edge member; and

a reinforcement member located within the interior cavity of the leading edge member, the reinforcement member being joined
to the proximal end of the first leg of the leading edge member and joined to the proximal end of the second leg of the leading
edge member.

US Pat. No. 9,133,541

ARTICLE INCLUDING ENVIRONMENTAL BARRIER COATING SYSTEM

Rolls-Royce Corporation, ...

1. An article comprising:
a silicon containing substrate having a surface;
a composite mullite bond coat including a mullite phase, a second oxide phase other than BSAS, and a dopant material over
the surface, wherein the dopant material comprises at least one of an alkali metal or an alkali metal oxide, and wherein the
second oxide phase comprises at least one of a transition metal oxide, a rare earth oxide, a rare earth silicate, or a NZP
ceramic; and

a silica scale between the substrate and the composite mullite bond coat and having gaps in a continuous network structure
of the silica scale, wherein the silica scale includes the at least one of an alkali metal or an alkali metal oxide.

US Pat. No. 9,341,586

THERMOGRAPHIC INSPECTION TECHNIQUES

Rolls-Royce Corporation, ...

1. A system comprising:
a source of dry ice;
a thermal camera; and
a computing device configured to:
control the source of dry ice to cause dry ice to be introduced into an internal passage of a tested component to remove at
least some debris from the internal passage;

receive, from the thermal camera, thermographic image data representative of the thermal response of the tested component
to the dry ice; and

output a representation based on the thermographic image data.

US Pat. No. 9,752,592

TURBINE SHROUD

Rolls-Royce Corporation, ...

8. The turbine shroud of claim 7, wherein the round carrier includes a connection flange adapted to be coupled to a turbine case, a connector arranged to
extend inwardly in the radial direction from the connection flange and having a frustoconical shape, and a support band arranged
to extend inwardly in the radial direction from the connector and connection flange, and the plurality of keys extend inwardly
in the radial direction from the support band.

US Pat. No. 9,238,973

GAS TURBINE ENGINE AND FOIL BEARING SYSTEM

ROLLS-ROYCE CORPORATION, ...

1. A gas turbine engine, comprising:
a compressor;
a turbine;
a static structure;
a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static
structure, wherein the foil bearing system includes a foil bearing and a self-aligning foil bearing mount coupled to the foil
bearing, wherein the self-aligning foil bearing mount is operative to align the foil bearing with an axis of rotation of the
at least one of the compressor and the turbine;

a snubber operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure in
parallel with the foil bearing,

wherein the self-aligning foil bearing mount includes at least two components configured to align the foil bearing by sliding
displacement between the at least two components;

wherein the foil bearing system is configured to prevent a rotation of the at least two components of the self-aligning foil
bearing mount about the axis of rotation of the rotor; and

wherein the self-aligning foil bearing mount is a spherical bearing, a first one of the at least two components of the bearing
mount includes a convex crown having a spherical shape and being circumferentially disposed about the axis of rotation of
the rotor and a second one of the at least two components is a concave receiver surface having a spherical shape, wherein
the concave receiver surface receives the convex crown to permit the sliding displacement between the at least two components,
wherein the convex crown is configured to rotate about an axis of rotation that is perpendicular to the axis of rotation of
the rotor.

US Pat. No. 9,115,594

COMPRESSOR CASING TREATMENT FOR GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine compressor having a bladed rotor enclosed by an annular shroud and disposed within a portion of a compressor
casing section, the bladed rotor having an upstream side and a downstream side, the annular shroud having an upstream end
and a downstream end as referenced relative to a flow stream through the bladed rotor;

an airflow passage formed between the compressor casing section and the annular shroud, the airflow passage having an inlet
defined by the downstream end of the annular shroud and an outlet defined by the upstream end of the annular shroud such that
the inlet is located downstream to the outlet as referenced by the flow stream through the bladed rotor; and

an airfoil-shaped airflow member attached to the shroud and disposed within the airflow passage, the airfoil-shaped airflow
member oriented transverse to the bladed rotor thereby forming an angle between the airfoil-shaped airflow member and a neighboring
blade of the bladed rotor such that as air enters from the inlet is turned to reduce an absolute tangential velocity of the
air across the airfoil-shaped airflow member.

US Pat. No. 9,423,129

SHELL AND TILED LINER ARRANGEMENT FOR A COMBUSTOR

Rolls-Royce Corporation, ...

1. A combustor for use in a gas turbine engine, the combustor comprising
an annular metallic shell forming an annular cavity, the annular metallic shell including an outer shell member and an inner
shell member nested concentrically inside the outer shell member, and

an annular liner arranged in the annular cavity of the annular metallic shell and defining an annular combustion chamber,
the annular liner including a plurality of ceramic tiles arranged to shield the annular metallic shell from combustion in
the combustion chamber,

wherein one of the outer shell member and the inner shell member of the annular metallic shell includes a wall and a plurality
of dimples extending from the wall toward the annular liner and each of the plurality of ceramic tiles is formed to include
a hollow sized and arranged to receive at least a portion of one of the dimples included in the annular metallic shell.

US Pat. No. 9,366,140

CERAMIC MATRIX COMPOSITE REPAIR BY REACTIVE PROCESSING AND MECHANICAL INTERLOCKING

ROLLS-ROYCE CORPORATION, ...

1. A method for modifying a ceramic matrix composite component comprising:
removing at least a portion of a non-conforming region of the ceramic matrix composite component to create an exposed surface
of the ceramic matrix composite component;

applying a reactive constituent surface region on at least one of the exposed surface of the ceramic matrix composite component
or a surface of a perform;

positioning the preform to provide a contact region between the exposed surface of the ceramic matrix composite component
and the preform, wherein the reactive constituent surface region is positioned between the ceramic matrix composite component
and the perform; and

reacting the reactive constituent surface region in an equilibrium reaction at the contact region to form a bond structure
between the ceramic matrix composite component and the preform.

US Pat. No. 9,366,182

INTEGRATED ELECTRICAL POWER AND THERMAL MANAGEMENT SYSTEM

Rolls-Royce Corporation, ...

1. An electrical power and thermal management system, comprising:
a power plant operable to provide motive power to an electrical generation device;
at least one conversion/distribution assembly configured to provide electrical power to a first electrical power bus;
a thermal management system configured to circulate coolant to at least one heat source; and
a controller in communication with the power plant, the electrical generation device, the conversion/distribution assembly,
the electrical power bus, and the thermal management system, the controller configured to integrally manage electrical and
thermal steady and transient demands, wherein the controller is operable to selectively distribute power to the electrical
power bus and regulate produced thermal energy in response to electrical and thermal demands, respectively.

US Pat. No. 9,228,958

PROTOCOL-BASED INSPECTION SYSTEM

Rolls-Royce Corporation, ...

1. A system comprising:
an illumination source configured to illuminate an engine component using visible light;
an imaging system configured to capture a surface image of the engine component based on the illumination of the engine component
using the visible light;

a component manipulation system configured to position the engine component in a variety of orientations relative to at least
one of the illumination source and the imaging system; and

a computer based user interface comprising an inspection processor, wherein the computer based user interface is configured
to allow a user to select an automated inspection protocol, and wherein the inspection processor is configured to perform
the automated inspection protocol to:

acquire surface images of the engine component at the variety of positions using the illumination system, the imaging system,
and the component manipulation system,

perform a fuzzy logic analysis on at least one of the surface images of the engine component to detect a defect on a surface
of the engine component, and

report the defect to the computer based user interface.

US Pat. No. 9,091,172

ROTOR WITH COOLING PASSAGE

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine having a compressor rotatably coupled to a turbine with a spool shaft;
a flow path formed internal to the spool shaft structured to provide a working fluid to the turbine;
a cooling flow path coupled to a turbine rotor and rotatable therewith, the cooling flow path having an inlet for receiving
the working fluid from the flow path internal to the spool shaft and an outlet for delivering the working fluid to suppress
temperatures of the turbine rotor;

wherein the cooling flow path radially extends from an inner portion of the turbine rotor and is bounded by an axially forward
cooling flow path portion and an axially aft cooling flow path portion, the axially forward cooling flow path portion and
axially aft cooling flow path portion being separate components from one another, and the axially forward cooling flow path
portion and the axially aft cooling flow path portion separate from the turbine rotor and located on a common side of the
turbine rotor; and

wherein the cooling flow path is coupled to an axially aft portion of the turbine rotor.

US Pat. No. 9,056,795

SUPPORT FOR A FIRED ARTICLE

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a free-form fabricated ceramic mold article capable of being thermally processed from a pre-fired shaped to a fired-shape
to produce a fired ceramic mold; and

a sacrificial structural material that is a separate component comprised of different material from that of the free-form
fabricated ceramic mold article, the sacrificial structural material coupled with the free-form fabricated ceramic mold article
to stabilize an orientation of the free-form fabricated ceramic mold article,

wherein the sacrificial structural material is configured to evolve into a rigid structure during a part of the time when
the free-form fabricated ceramic mold article is thermally processed from the pre-fired shape to the fired shape to produce
the fired ceramic article;

the sacrificial structural material configured to be dispersible during a part of the time when the free-form fabricated ceramic
mold article is thermally processed from the pre-fired shaped to the fired shape to produce the fired ceramic article.

US Pat. No. 9,657,969

MULTI-EVAPORATOR TRANS-CRITICAL COOLING SYSTEMS

Rolls-Royce Corporation, ...

1. A multi-evaporator cooling system, comprising:
a compressor circuit that generates multiple levels of evaporating pressures, the circuit comprising at least one compressor
configured to compress a refrigerant to a first pressure;

a heat exchanger configured to receive the compressed refrigerant from the at least one compressor and cool the compressed
refrigerant;

a first evaporator circuit configured to receive the compressed refrigerant from the heat exchanger, expand the compressed
refrigerant to a second pressure that is lower than the first pressure, and return the refrigerant to the compressor circuit;
and

a second evaporator circuit configured to receive the compressed refrigerant from the heat exchanger, expand the compressed
refrigerant to a third pressure that is lower than the second pressure, and return the refrigerant to the compressor circuit;

wherein the first and second evaporator circuits each comprise a respective expansion device and heat load heat exchanger,
wherein refrigerant from each heat load heat exchanger passes to a respective first and second ejector at approximately the
respective second and third pressures, expands in each of the first and second ejectors, and passes to an inlet of a compressor
of the at least one compressor circuit.

US Pat. No. 9,404,658

GAS TURBINE ENGINE FUEL AIR MIXER

Rolls-Royce Corporation, ...

8. An apparatus comprising:
a gas turbine engine fuel module having a main mixer and a pressure swirl pilot mixer, the gas turbine engine fuel module
including:

the pressure swirl pilot mixer having a pilot fuel opening structured to deliver fuel to a pilot passage that includes a swirler,
the pilot mixer including a fuel aperture and an annular passage for passage of air that surrounds the fuel aperture, the
pilot mixer including a pilot convergent-divergent portion that converges at a narrowest diameter of a throat thereof, wherein
the pilot fuel opening through which the fuel exits is downstream of the narrowest diameter, and wherein all the air passing
through the pilot mixer passes through the swirler before entering the pilot convergent-divergent portion; and

the main mixer having a main flow path that includes a first flow path having a first swirler radially inward from a second
flow path having a second swirler and both the first flow path and second flow path merge to a common flow path prior to a
main mixer outlet, the main mixer also having a fuel opening positioned in the first flow path and structured to dispense
a fuel upstream of the common flow path.

US Pat. No. 9,759,079

SPLIT LINE FLOW PATH SEALS

Rolls-Royce Corporation, ...

1. A gas turbine engine assembly, the assembly comprising
a first component comprising ceramic matrix materials, the first component including a panel arranged to separate a high pressure
zone from a low pressure zone and formed to include a first chamfer surface that extends from a high pressure surface of the
first component facing the high pressure zone to a first side surface of the first component,

a second component comprising ceramic matrix materials, the second component including a panel arranged to separate the high
pressure zone from the low pressure zone and formed to include a second chamfer surface that extends from a high pressure
surface of the second component facing the high pressure zone to a second side surface of the first component,

a seal assembly arranged in a channel formed by the first chamfer and the second chamfer when the first side surface of the
first component is arranged in confronting relation to the second side surface of the second component, the seal assembly
including a rod configured to block gasses from passing through the interface of the first side surface included in the first
component with the second side surface included in the second component and a rod locator configured to engage the rod to
hold the rod in place relative to the first component and the second component,

wherein the seal assembly includes a bias member configured to push the rod into contact with the first chamfered surface
of the first component and the second chamfered surface of the second component, and

wherein the rod locator and the bias member are included in a singular component.

US Pat. No. 9,422,865

BI-METAL FASTENER FOR THERMAL GROWTH COMPENSATION

Rolls-Royce Corporation, ...

1. A fastener system for use with a gas turbine engine comprising:
a ceramic tile having a linear coefficient of expansion value of ?2;

a spacer having a linear coefficient of expansion value of ?3;

a combustor shell having a linear coefficient of expansion value of ?4; and

a securing member extending through the ceramic tile, spacer and combustor shell, the securing member having a linear coefficient
of expansion value of ?1,

wherein the spacer has the linear coefficient of expansion ?3 value that is greater than that of the securing member linear coefficient of expansion ?1; and

wherein the spacer is positioned between the combustor shell and the ceramic tile, and the spacer contacts a first surface
of the ceramic tile and contacts a second surface of the combustor shell, and the spacer extends from the first surface to
the second surface.

US Pat. No. 9,387,512

SLURRY-BASED COATING RESTORATION

Rolls-Royce Corporation, ...

1. A method comprising:
identifying a damaged area in an environmental barrier coating of an in-service component;
applying a restoration slurry to the damaged area of the environmental barrier coating, wherein the restoration slurry comprises
a liquid carrier and a restoration coating material, and wherein the restoration coating material comprises at least two of
mullite, a rare earth silicate, a rare earth oxide, alumina, zirconia, hafnia, ZrSiO4, HfSiO4, TiO2, Ta2O5 carbon, boron oxide, borosilicate, alkali metal oxide, alkali earth metal oxide, silicon, silicon alloy, aluminum, boron,
germanium, silica, barium strontium aluminosilicate, barium aluminosilicate, calcium aluminosilicate, magnesium aluminosilicate,
or lithium aluminosilicate;

drying the restoration slurry to form a dried restoration slurry; and
heat treating the dried restoration slurry to cause a reaction between the at least two of mullite, the rare earth silicate,
the rare earth oxide, alumina, zirconia, hafnia, ZrSiO4, HfSiO4, TiO2, Ta2O5, carbon, boron oxide, borosilicate, alkali metal oxide, alkali earth metal oxide, silicon, silicon alloy, aluminum, boron,
germanium, silica, barium strontium aluminosilicate, barium aluminosilicate, calcium aluminosilicate, magnesium aluminosilicate,
or lithium aluminosilicate to form a restored portion of the environmental barrier coating comprising a glass phase.

US Pat. No. 9,194,243

SUBSTRATE FEATURES FOR MITIGATING STRESS

Rolls-Royce Corporation, ...

1. An airfoil comprising:
a tip that defines an edge;
a patterned array of features on a surface of the tip, wherein the patterned array of features is proximate to the edge, and
wherein none of the features on the surface of the tip intersect the edge and each of the features on the surface of the tip
is at least 0.254 millimeters from the edge; and

an abrasive coating on the surface of the tip and the patterned array of features and extending over substantially all of
the tip to the edge of the tip.

US Pat. No. 9,731,836

PROPULSION, ELECTRICAL, AND THERMAL MANAGEMENT DEVICE FOR A SMALL UNMANNED AERIAL VEHICLE

Rolls-Royce North America...

1. A system for providing propulsion, electrical generation and thermal management to an airframe from a single prime mover,
comprising:
an engine providing power to an engine output shaft;
a speed change transmission, said transmission having an input shaft and at least two output shafts, said input shaft operatively
connected to said engine output shaft to distribute power from said engine to a first transmission output shaft and a second
transmission output shaft, said first transmission output shaft operatively coupled to an electric machine and to a propeller
such that both said electric machine and said propeller are driven by said first transmission output shaft, and said second
transmission output shaft operatively coupled to a refrigerant compressor of a refrigeration system, wherein said refrigerant
compressor is coupled with said propeller via said first transmission output shaft and via said second transmission output
shaft, and

a condenser for said refrigeration system mounted on a structure that surrounds said propeller.

US Pat. No. 9,581,025

AIRCRAFT POWER PLANT

Rolls-Royce Corporation, ...

1. An apparatus comprising:
an aircraft power plant having a first work producing device and a second work producing device; and
a first unducted air moving device and in serial flow communication with a second unducted air moving device, the first unducted
air moving device powered by the first work producing device and the second unducted air moving device powered by the second
work producing device, and

a controller configured to develop a command signal based upon a function of airspeed, and
wherein the first unducted air moving device is capable of rotating at a first rotational velocity, the second unducted air
moving device is capable of rotating at a second rotational velocity, and the controller is configured to provide the command
signal to one of the first work producing device and the first unducted air moving device to cause the first rotational velocity
of the first unducted air moving device to be different than the second rotational velocity of the second unducted air moving
device.

US Pat. No. 9,400,256

THERMOGRAPHIC INSPECTION TECHNIQUES

ROLLS-ROYCE CORPORATION, ...

1. A system comprising:
a thermal camera; and
a computing device configured to:
receive master image data representative of a geometry and a thermal response of at least one of a theoretical component,
a fabricated gold standard component, or an average of a plurality of components;

receive, from the thermal camera, thermographic image data representative of a thermal response of a tested component;
morph the thermographic image data to substantially align with the geometry of the master image data and produce morphed thermographic
image data; and

output a representation based on the morphed thermographic image data for display.

US Pat. No. 9,624,786

BRAZE MATERIALS AND METHOD FOR JOINING OF CERAMIC MATRIX COMPOSITES

Rolls-Royce Corporation, ...

1. A melt alloy for use as a braze material for joining ceramic matrix composites, the melt alloy comprising:
a homogeneous mixture of two or more materials in powder form, one of the two or more materials being a braze alloy comprising
silicon and another of the two or more materials being a high melting point material or alloy,

wherein the homogeneous mixture of the two or more materials in powder form is selected from the group consisting of (in wt.
%): Ti-9Si (5%)+71Si—Cr (95%), 75Si—Ti (97%)+C (3%), 75Si—Ti (97%)+B (3%), 75Si—Ti (50%)+71Si—Cr (50%), 75Si—Ti (50%)+Ti-43Cr
(50%), 75Si—Ti (50%)+12.5Si—Co (50%), and Ti-25Cr-23Si (97%)+C (3%).

US Pat. No. 9,399,271

HEAT TREATING AND BRAZING OF AN OBJECT

Rolls-Royce Corporation, ...

1. A method for manufacturing an assembly, the method comprising:
brazing the assembly in a furnace, including:
applying a braze filler metal adjacent to a joint in the assembly;
providing a radiation heat shield conforming to a shape of only a portion of the assembly, wherein the radiation heat shield
is configured to reduce radiative heat transfer to the portion of the assembly;

positioning the radiation heat shield on the assembly, wherein the radiation heat shield is supported by the assembly in a
location between a portion of the assembly and a heat source included in the furnace to shield the portion of the assembly
from the heat source and the entire radiation heat shield maintains a spaced-apart relationship with the braze filler metal
and the joint;

placing the assembly and the radiation heat shield in the furnace;
heating the assembly and the radiation heat shield in the furnace to melt the braze filler metal into the joint; and
removing the radiation heat shield from the assembly.

US Pat. No. 9,771,867

GAS TURBINE ENGINE WITH AIR/FUEL HEAT EXCHANGER

Rolls-Royce Corporation, ...

1. An aircraft propulsion gas turbine engine, comprising:
a first compressor stage configured to produce a pressurized air flow;
a second compressor stage disposed downstream of the first compressor stage;
a primary annular flowpath fluidly coupling the first compressor stage and the second compressor stage, wherein the primary
annular flowpath is disposed within the aircraft propulsion gas turbine engine;

a combustor disposed downstream of the second compressor stage;
a fuel injector configured to inject a fuel into the combustor, wherein the combustor is configured to combust the fuel injected
therein by the fuel injector; and

an air/fuel heat exchanger disposed in the primary annular flowpath, the air/fuel heat exchanger including a first flowpath
and a second flowpath, the first flowpath having a first fuel inlet and a first fuel outlet for distributing fuel in a first
direction through a first side of the air/fuel heat exchanger, and the second flowpath having a second fuel inlet and a second
fuel outlet for distributing fuel in a second direction through a second side of the air/fuel heat exchanger;

wherein the air/fuel heat exchanger is an annular heat exchanger with the first direction being a first circumferential direction
and the second direction being a second circumferential direction;

wherein the air/fuel heat exchanger is in fluid communication with the fuel injector, the first compressor stage and the second
compressor stage; and

wherein the air/fuel heat exchanger is configured to receive the pressurized air flow from the first compressor stage, to
discharge the pressurized air flow to the second compressor stage, to heat the fuel by heat exchange with the pressurized
air flow prior to delivery of the fuel to the fuel injector, and to cool the pressurized air flow by heat exchange with the
fuel.

US Pat. No. 9,657,594

GAS TURBINE ENGINE, MACHINE AND SELF-ALIGNING FOIL BEARING SYSTEM

Rolls-Royce Corporation, ...

1. A gas turbine engine, comprising:
a compressor;
a turbine;
a static structure having a bearing pilot feature configured to pilot a bearing system; and
a self-aligning foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine
to the static structure, wherein the foil bearing system includes:

a foil bearing;
a housing configured to receive the foil bearing and configured to be at least partially received within the bearing pilot
feature;

a fulcrum extending outward from the housing toward the bearing pilot feature; and
an axial spring configured to impart an axial load on the housing and to generate a predetermined radial frictional damping
characteristic of the housing,

wherein the self-aligning foil bearing system is operative to align the foil bearing with an axis of rotation of the at least
one of the compressor and the turbine.

US Pat. No. 9,249,055

PROSTHETIC IMPLANT AND METHOD FOR FORMING A PROSTHETIC IMPLANT

Rolls-Royce Corporation, ...

1. A bone-implantable prosthetic device, comprising:
an interface portion operative to interface the bone-implantable prosthetic device with an other structure; and
a stem coupled to said interface portion, wherein the stem is structured for implantation to a desired depth into a bone tissue,
and wherein the stem includes:

a metallic body having a length corresponding to the desired depth of implantation; wherein said metallic body includes a
support structure and a hollow pin, fin and/or lattice structure formed as a unitary structure and configured to transfer
load between said stem and the bone tissue, wherein said pin, fin and/or lattice structure includes an outer ring shape that
is integral with, disposed radially outward of, and fully encircles said support structure such that an offset is provided
to create a space between the outer ring shape and the support, said pin, fin and/or lattice structure further including an
inner ring shape that is integral with and fully encircles said support structure, the inner ring shape being disposed radially
inward of the outer ring shape, and said pin, fin and/or lattice structure further including an intermediate ring shape that
is integral with and fully encircles said support structure, the intermediate ring shape being disposed radially inward of
the outer ring shape and outward of the inner ring shape.

US Pat. No. 9,708,914

GAS TURBINE ENGINE AIRFLOW MEMBER HAVING SPHERICAL END

Rolls-Royce Corporation, ...

1. A gas turbine engine comprising
a variable position airfoil member that includes a hub end having a leading edge and a trailing edge, the variable position
airfoil member disposed within a flow path annulus adjacent a hub flow path surface having a divot that includes a downstream
end in which a radial rate of growth of the downstream end is increasing, the variable position airfoil member pivotable around
an adjustment axis and capable of being moved between a first position and a second position where the first position provides
a flow area greater than a flow area in the second position, the hub end offset from the divot to permit pivoting movement
of the variable position airfoil member without interference from the flow path surface between the first position and the
second position, wherein the offset between the flow path surface of the divot and the hub end of the variable position airfoil
member is constant as the variable position airfoil member moves between the first position and the second position, wherein
the hub end is spherical, the variable position airflow member includes a tip end that is spherical, and the axial extent
of spherical shape at the tip end forward of a pivot axis of the variable position airflow member is shifted backward relative
to the axial extent of the spherical shape at the hub end forward of the pivot axis.

US Pat. No. 9,062,565

GAS TURBINE ENGINE CONTAINMENT DEVICE

Rolls-Royce Corporation, ...

1. A containment system for rotating turbomachinery, comprising:
a gas turbine engine flow path structure having an annular shape;
an outer ring located radially outward of the gas turbine engine flow path structure, the outer ring operable to be at least
partially radially in-line with a rotating blade of a gas turbine engine, wherein the outer ring includes first and second
protrusions extending radially inward from a surface to form an inner space of the outer ring; and

an abutment structure coupling the outer ring to the gas turbine engine flow path structure in an interference fit;
wherein the gas turbine engine flow path structure includes first and second standoffs extending from the same base, wherein
the standoffs and base form a monolithic structure, the first and second standoffs forming a portion of the abutment structure
coupling the outer ring to the gas turbine engine flow path structure;

wherein the first and second standoffs are located between the first and second protrusions.

US Pat. No. 9,593,049

METHOD FOR INCORPORATING REFRACTORY METAL ELEMENT INTO CERAMIC MATRIX COMPOSITE

Rolls-Royce High Temperat...

1. A method of forming a ceramic matrix composite comprising:
infiltrating a fiber preform with a solution comprising a refractory precursor in solution with a solvent, the refractory
precursor comprising a compound having at least one refractory metal element;

removing the solvent from the fiber preform; and
reducing the refractory precursor to form a refractory metal comprising the refractory metal element.

US Pat. No. 9,745,856

PLATFORM FOR CERAMIC MATRIX COMPOSITE TURBINE BLADES

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a disk having at least a first airfoil slot and a second airfoil slot;
a first ceramic matrix composite airfoil coupled to the disk and mounted within the first slot;
a second ceramic matrix composite airfoil coupled to the disk and mounted within the second slot;
a platform disposed between the first airfoil and the second airfoil;
the platform comprising a first axial extension and a second axial extension, and further comprising a first radial extension
and a second radial extension;

the first axial extension extending adjacent to the first airfoil and extending axially fore and aft of the first airfoil;
the second axial extension extending adjacent to the second airfoil and extending axially fore and aft of the second airfoil;
the first radial extension extending radially into and conforming to the first slot;
the second radial extension extending radially into and conforming to the second slot; and
further comprising a first groove disposed between the first axial extension and the first radial extension, wherein the first
groove houses a first sealing dynamic damper.

US Pat. No. 9,341,118

VARIOUS LAYERED GAS TURBINE ENGINE COMPONENT CONSTRUCTIONS

ROLLS-ROYCE CORPORATION, ...

1. An apparatus comprising:
a gas turbine engine component composition having a first foamed material portion located on a hot side of the component,
a second foamed material portion coupled with the first foamed material portion, and a third foamed material portion coupled
with the second foamed material portion and located on a cold side of the composition, the first foamed material portion,
the second foamed material portion, and the third foamed material portion each having a plurality of pores arranged along
their thicknesses between the hot side and the cold side, the first foamed material portion, the second foamed material portion,
and the third foamed material portion structured to permit the passage of a cooling working fluid between the cold side and
the hot side to provide transpiration cooling, wherein the second foamed material portion has a higher porosity than the first
foamed material portion and the third foamed material portion, and the first foamed material portion includes a cellular configuration
having a working fluid passage formed therethrough and wherein the first foamed material portion is a support structural portion
that provides strength to the gas turbine engine component composition, wherein the first foamed material portion and second
foamed material portion of the gas turbine engine component construction are sufficiently rigid to maintain a shape of the
component construction.

US Pat. No. 9,719,357

TRENCHED COOLING HOLE ARRANGEMENT FOR A CERAMIC MATRIX COMPOSITE VANE

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a shape operable as a gas turbine engine component;
an internal cavity within the shape including a radius;
a trench on an external surface of the shape including a rear face tangential to an arc centered on the radius of the internal
cavity; and

a cooling hole extending from the internal cavity and exiting to the trench through the rear face of the trench,
wherein a cooling fluid introduced to the internal cavity flows through the cooling hole and into the trench during operation
of the gas turbine engine component, the rear face extends to a point spaced a first distance from a suction sidewall defined
by the external surface of the shape, the cooling hole is spaced a second distance from the suction sidewall greater than
the first distance, and the rear face of the trench is centered on a centerline of the radius of the internal cavity.

US Pat. No. 9,845,688

COMPOSITE BLADE WITH AN INTEGRAL BLADE TIP SHROUD AND METHOD OF FORMING THE SAME

Rolls-Royce Corporation, ...

1. A gas turbine engine airflow member, comprising:
a blade core portion;
a shroud tip portion extending from the blade core portion;
an airfoil portion formed exteriorly to and surrounding the blade core portion and terminating at the shroud tip portion forming
a shroud interface at a lateral portion of the shroud tip portion; and

wherein the blade core portion and the shroud tip portion are constructed as a first unitary structure and the airfoil portion
is constructed as a second structure,

wherein the first unitary structure is formed of a single-piece monolithic material and the second structure is formed of
a composite material having a plurality of fiber plies with a two dimensional orientation,

wherein the single-piece monolithic material comprises a first composite material and wherein the second structure comprises
a second composite material, and

wherein the first composite material includes a first plurality of fiber plies having a three dimensional orientation, and
wherein the second composite material includes a second plurality of fiber plies having a two dimensional orientation,

further including a sealing knife portion extending from the shroud tip portion opposite the shroud interface.

US Pat. No. 9,822,817

HIGH SPEED BEARING ASSEMBLY

Rolls-Royce Corporation, ...

1. A bearing assembly comprising
an inner race that extends around a central axis,
an outer race that extends around the central axis radially outward of the inner race,
a plurality of internal rotating components arranged radially between the inner race and the outer race to engage the inner
race and the outer race, and

a cage that extends around the central axis radially between the inner race and the outer race, the cage including a cage
rail formed to include a plurality of apertures that receive the plurality of internal rotating components to locate the plurality
of internal rotating components relative to one another within the bearing assembly and a plurality of lubricant-ejector fins
that extend radially outward from the cage rail that are shaped to push lubricant between the cage rail and the outer race
out of the bearing assembly during rotation of the cage relative to the outer race in a direction of rotation so that hot
lubricant is removed from the bearing assembly to make room for cooler lubricant introduced into the bearing assembly during
rotation of the cage.

US Pat. No. 9,803,486

BI-CAST TURBINE VANE

Rolls-Royce North America...

1. A gas turbine engine vane, comprising:
an airfoil having an outer surface extending between a leading edge and a trailing edge and between a first end and a second
end;

a through slot extending between the first and second ends of the airfoil; and
a spar slidingly engaged with the slot of the airfoil, the spar including a pair of extensions with at least one bi-cast groove
formed on opposing ends thereof,

wherein the extensions of the spar are configured to engage with corresponding apertures formed in a pair of opposing endwalls.

US Pat. No. 9,309,769

GAS TURBINE ENGINE AIRFOIL SHAPED COMPONENT

ROLLS-ROYCE CORPORATION, ...

7. An apparatus comprising:
a compressor blade of a gas turbine engine capable of being rotated to produce a pressure rise in a working fluid during operation
of the gas turbine engine, the compressor blade including a main blade portion having a first camber shape that is blended
with a tip portion having a second camber shape, the second camber shape producing a relatively low pressure near the leading
edge of the tip to induce a local jet of stream-wise momentum flow,

wherein the second camber shape includes a normalized camber angle defined as

 where ?iis inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location; and

wherein normalized camber angle reaches at least 0.4 in the first 10% of normalized chord.

US Pat. No. 9,592,573

LASER DEPOSITION USING A PROTRUSION TECHNIQUE

Rolls-Royce Corporation, ...

1. A method of applying a laser metal formed build layer on a surface of an article, the method comprising the operations
of
surveying a first portion of an article to form a build layer thereon using a laser deposition process,
identifying an area of the first portion including at least one of an edge and a corner of the article,
determining a first location for forming a first protrusion within the identified area,
melting-the article at the first location using a light source to establish a first melt pool,
injecting powdered metal into the first melt pool,
solidifying the first melt pool to form the first protrusion, the first protrusion having a first microstructure,
determining a second location for forming a second protrusion within the identified area,
melting-the article at the second location using a light source to establish a second melt pool,
injecting powdered metal into the second melt pool, and
solidifying the second melt pool to form the second protrusion, the second protrusion having the first microstructure.

US Pat. No. 10,047,624

TURBINE SHROUD SEGMENT WITH FLANGE-FACING PERIMETER SEAL

Rolls-Royce North America...

1. A turbine shroud segment comprisinga carrier segment comprising metallic materials, the carrier segment formed to define an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment portion that extends radially outward from the runner into an attachment-receiving space channel formed by the carrier segment, and
a seal member configured to resist the movement of gasses into the attachment-receiving space, the seal member shaped to extend around the attachment portion of the blade track segment and arranged to engage a radially-outwardly facing surface of the runner, wherein the seal member is formed to include a plurality of radially-extending bleed holes adapted to conduct a flow of buffer air through the seal member to resist the movement of gasses into the attachment-receiving space.

US Pat. No. 10,072,511

ENGINE NACELLE

Rolls-Royce North America...

1. A nacelle for a jet engine comprisingan inner surface defining an opening for air to flow to an engine intake,
an outer surface positioned external to the inner surface, and
a leading surface circumscribing the opening, the leading surface connecting the inner surface and the outer surface, the leading surface defining a line of stagnation and formed to include a plurality of vortex generators positioned on leading surface along the line of stagnation,
wherein the vortex generators comprise a plurality of tabs extending from the leading surface, the tabs oriented to disrupt air flow flowing laterally across the leading surface,
wherein the tabs comprise a body and a plurality of leading edges that are generally perpendicular to the line of stagnation, and
wherein each of the tabs has converging sides that each terminate in the leading edges.

US Pat. No. 10,018,059

ENGINE NACELLE

Rolls-Royce North America...

1. A nacelle for a jet engine comprisingan inner surface defining an opening for air to flow to an engine intake,
an outer surface positioned external to the inner surface, and
a leading surface circumscribing the opening, the leading surface connecting the inner surface and the outer surface, the leading surface defining a line of stagnation and formed to include a plurality of vortex generators positioned on leading surface along the line of stagnation,
wherein the vortex generators comprise a plurality of tabs extending from the leading surface, the tabs oriented to disrupt air flow flowing laterally across the leading surface,
wherein the tabs comprise a body and a plurality of leading edges that are generally perpendicular to the line of stagnation, and
wherein each of the tabs has converging sides that each terminate in the leading edges.

US Pat. No. 9,771,157

AIRCRAFT AND AIRBORNE ELECTRICAL POWER AND THERMAL MANAGEMENT SYSTEM

Rolls-Royce Corporation, ...

1. An electrical power and thermal management system, comprising:
a gas turbine engine including: a combustor and a turbine in fluid communication with the combustor;
a generator powered by the turbine and configured to provide electrical power to an electrical load;
a refrigerant compressor powered by the turbine;
a condenser in fluid communication with the refrigerant compressor; and
at least one evaporator in fluid communication with the condenser, wherein the at least one evaporator is configured to extract
heat from at least one heat source;

wherein the gas turbine engine, the generator, the refrigerant compressor, the at least one evaporator, and the condenser
are disposed in an external pod for a vehicle.

US Pat. No. 10,012,100

TURBINE SHROUD WITH TUBULAR RUNNER-LOCATING INSERTS

Rolls-Royce North America...

1. A turbine shroud comprisingan annular metallic carrier arranged around a central axis of the turbine shroud and formed to include a plurality of keyways extending in a radial direction into the annular metallic carrier, and
a blade track including a ceramic annular runner and a plurality of ceramic inserts extending outward in a radial direction away from the ceramic annular runner,
wherein each of the plurality of ceramic inserts are tubular and are arranged to extend into a corresponding one of the plurality of keyways formed in the annular metallic carrier to locate the blade track and the annular metallic carrier relative to the central axis while allowing radial growth of the annular metallic carrier and the blade track at different rates during use of the turbine shroud.

US Pat. No. 9,566,665

VARIABLE WORKING DISTANCE FOR LASER DEPOSITION

Rolls-Royce Corporation, ...

1. A method of applying a laser metal formed build layer on a surface of an article, the method comprising the operations
of
determining a first distance between a laser deposition head and a first area of a surface included in an article to cause
a first melt pool having a first melt-pool cooling rate to be provided,

moving the laser deposition head including a light source and a nozzle relative to the article to establish the first distance,
melting the first area using the light source of the laser deposition head to establish the first melt pool, and
injecting powdered metal into the first area at a first flow rate using the nozzle, and
solidifying the first melt pool,
determining a second distance between the laser deposition head and a second area of the surface of the article that causes
a second melt pool having the first melt-pool cooling rate

moving the laser deposition head relative to the article to establish the second distance,
melting the second area using the light source of the laser deposition head to establish the second melt pool,
wherein the laser deposition head is moved from the first distance to the second distance in a continuous motion.

US Pat. No. 9,938,198

METHOD FOR INTEGRAL JOINING INFILTRATED CERAMIC MATRIX COMPOSITES

Rolls-Royce Corporation, ...

1. A method of making an integrated ceramic matrix composite component for use in a gas turbine engine, the method comprising the steps ofmanufacturing a first green body subpart formed to include a first slot,
manufacturing a second green body subpart formed to include a second slot,
inserting a green body biscuit into the first slot of the first green body subpart and the second slot of the second green body subpart to create a green assembly with a joint between the first green body subpart and the second green body subpart, and
slurry infiltrating the green assembly with ceramic-containing matrix to integrally join the green assembly and produce an integrated ceramic matrix composite component.

US Pat. No. 9,598,321

MELT INFILTRATION WICK ATTACHMENT

Rolls-Royce Corporation, ...

1. A wick attachment comprising:
a wick;
a component; and
a weld material;
wherein the wick and the component are attached together using the weld material that is selected from the group of materials
consisting of Si/Zr, Si, Zr/Si, ZrB2 and TiB2, wherein the weld material has a first melting point and the wick is for fluidly communicating an infiltrant haying a second
melting point to the component, and wherein the first melting point of the weld material is higher than the second melting
point of the infiltrant.

US Pat. No. 9,570,958

GENERATOR WITH CONTROLLED AIR COOLING AMPLIFIER

Rolls-Royce Corporation, ...

1. A gas turbine generator cooling system comprising:
a gas turbine engine generating bleed air; and
a generator including a generator housing and at least one fluid entrainment feature, said at least one fluid entrainment
feature utilizing a fraction of said bleed air to generate a cooling air flow through said generator housing.

US Pat. No. 9,938,845

GAS TURBINE ENGINE VANE END DEVICES

Rolls-Royce Corporation, ...

6. A gas turbine engine assembly comprisinga turbomachinery component having a wall that defines a flow path of the gas turbine engine assembly,
a rotatable vane positioned adjacent the wall and configured to move relative to the wall, and
a brush seal coupled to the rotatable vane for movement therewith, the brush seal being located between the rotatable vane and the wall, and the brush seal including a base member, a plurality of bristles that extend outwardly away from the base member toward the wall, and a clamp arranged around a portion of the base member and the bristles to couple the bristles with the base member,
wherein the rotatable vane includes a leading edge and a trailing edge spaced apart from the leading edge to define a chord of the rotatable vane, the brush seal extends at least partway along the chord, and a height of the plurality of bristles varies along the chord,
wherein the rotatable vane is moveable between a first position and a second position and at least one portion of the bristles does not contact the wall in at least one of the first position and the second position.

US Pat. No. 9,624,583

SLURRY-BASED COATING TECHNIQUES FOR SMOOTHING SURFACE IMPERFECTIONS

Rolls-Royce Corporation, ...

1. A method comprising:
depositing a first coating over at least a portion of a substrate, wherein the substrate comprises at least one of a superalloy,
a ceramic, or a ceramic matrix composite, wherein the substrate defines a surface imperfection, and wherein a surface of the
first coating opposite the substrate substantially reproduces the surface imperfection;

depositing from a slurry a second coating over at least a portion of the surface of the first coating, wherein, upon deposition
of the second coating, a surface of the second coating opposite the first coating does not substantially reproduce the surface
imperfection, and wherein the second coating comprises mullite and at least one of a rare earth silicate, a rare earth oxide,
boron oxide, an alkali metal oxide, an alkali earth metal oxide, barium strontium aluminosilicate, barium aluminosilicate,
strontium aluminosilicate, calcium aluminosilicate, magnesium aluminosilicate, or lithium aluminosilicate; and

reacting the mullite with the at least one of the rare earth silicate, the rare earth oxide, boron oxide, the alkali metal
oxide, the alkali earth metal oxide, barium strontium aluminosilicate, barium aluminosilicate, strontium aluminosilicate,
calcium aluminosilicate, magnesium aluminosilicate, or lithium aluminosilicate to form at least one of a rare earth aluminosilicate
glass phase, an alkali aluminosilicate glass phase, an alkali earth aluminosilicate glass phase, or a borosilicate glass phase.

US Pat. No. 10,100,649

COMPLIANT RAIL HANGER

Rolls-Royce North America...

1. A turbine shroud comprisinga plurality of carrier segments comprising metallic materials and arranged circumferentially adjacent to one another around an axis, each carrier segment including a body and a bracket that extends inwardly in a radial direction from the body toward the axis, and
a plurality of blade track segments comprising ceramic-matrix composite materials and arranged circumferentially adjacent to one another around the axis, each blade track segment including a runner and at least one hanger that extends outwardly in the radial direction from the runner,
wherein at least one of the hangers of each blade track segment engages with the bracket of at least one carrier segment to couple the plurality of blade track segments to the carrier segments, the bracket of each carrier segment is formed to include a plurality of circumferentially spaced apart fingers extending generally axially from the body and arranged to be engaged by the hangers of the blade track segments, and the fingers are configured to flex inward in the radial direction when engaged by the hangers of the blade track segments.

US Pat. No. 10,030,540

FAN CASE LINER REMOVAL WITH EXTERNAL HEAT MAT

Rolls-Royce North America...

1. A method of replacing a fan case liner in a fan case, the method comprisingapplying heat to a portion of an exterior surface of a fan case to soften an adhesive layer bonding a first fan case liner panel to an inner surface of the fan case,
removing the first fan case liner panel and adhesive residue from the fan case to produce an undisrupted inner surface of the fan case, and
bonding a second fan case liner panel to the undisrupted inner surface of the fan case, wherein
applying heat to the portion of the exterior of the fan case is performed on the portion of the fan case containing the first fan case liner panel.

US Pat. No. 9,890,640

GAS TURBINE ENGINE TIP CLEARANCE CONTROL

ROLLS-ROYCE NORTH AMERICA...

1. An apparatus comprising:
a gas turbine engine having a flow path wall disposed around an airfoil shaped component;
a battery;
a first thermoelectric device disposed in thermal communication with a first portion of the flow path wall, the first thermoelectric
device operable to generate heat and thereby affect a thermal transfer between the first thermoelectric device and the first
portion of the flow path wall, wherein the first thermoelectric device is powered by the battery;

a controller adapted to regulate heat generated by the thermoelectric device; and
a second thermoelectric device disposed in thermal communication with a second portion of the flow path wall, the second thermoelectric
device adapted to convert waste heat into electrical power used to charge the battery;

wherein thermal transfer between the first thermoelectric device and the flow path wall affects a change in size of the first
portion of the flow path wall and thereby changes a tip clearance between the flow path wall and the airfoil shaped component.

US Pat. No. 9,581,041

ABRADABLE CERAMIC COATINGS AND COATING SYSTEMS

Rolls-Royce Corporation, ...

1. A system comprising:
a first coating deposited on a first substrate, the first coating comprising a first non-ceramic bond layer, a second non-ceramic
bond layer, and a first ceramic outer layer, wherein the second non-ceramic bond layer is between the first non-ceramic bond
layer and the first ceramic outer layer, wherein the first non-ceramic bond layer defines a first porosity and the second
non-ceramic bond layer defines a second porosity that is greater than the first porosity; and

a second coating deposited on a second substrate, the second coating comprising a third non-ceramic bond layer deposited on
the substrate and a second ceramic outer layer deposited on the third bond layer, wherein the second coating is configured
to abrade the first coating, and wherein during operation of the system, the second coating abrades the first ceramic outer
layer of the first coating.

US Pat. No. 10,082,085

SEAL FOR GAS TURBINE ENGINES

Rolls-Royce North America...

1. A gas turbine engine assembly comprisinga support component formed to include a notch,
an engine component, the engine component mounted in spaced-apart relation to the support component so that a gap is formed between the support component and the engine component and so that the notch opens into the gap, and
a seal adapted to close the gap, the seal including a rope gasket arranged to block gasses from passing through the gap and a rope-biasing clip arranged between the support component and the rope gasket to push the rope gasket toward engagement with the engine component, the rope-biasing clip being formed to include a first spring lobe and a second spring lobe that cooperate with notch surfaces defining the notch in the support component to define a cavity,
wherein a first portion of the gap between the support component and the engine component extends from a first side of the notch and is arranged to receive a first portion of the gasses at a first pressure, a second portion of the gap between the support component and the engine component extends from a second side of the notch opposite the first side of the notch and is arranged to receive a second portion of the gasses at a second pressure, and the second pressure is lower than the first pressure such that the notch is configured to be pressurized by the first portion of the gasses from the first portion of the gap that extends from the first side of the notch.

US Pat. No. 9,945,256

SEGMENTED TURBINE SHROUD WITH SEALS

Rolls-Royce Corporation, ...

1. A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprisinga first shroud segment including a first carrier segment and a first blade track segment, the first blade track segment made from a ceramic-matrix-composite material and coupled to the first carrier segment,
a second shroud segment arranged circumferentially adjacent to the first shroud segment around the central axis, the second shroud segment including a second carrier segment and a second blade track segment, the second blade track segment made from a ceramic-matrix-composite material and coupled to the first carrier segment, and
a circumferential seal arranged between the first shroud segment and the second shroud segment to block gasses from passing through a circumferential interface of the first shroud segment and the second shroud segment, the circumferential seal including a first seal support coupled to the first shroud segment, a second seal support coupled to the second shroud segment, and a seal element that extends from the first seal support to the second seal support,
wherein the first blade track segment includes an arcuate runner and a first attachment post that extends from the arcuate runner to the first carrier segment.

US Pat. No. 9,938,846

TURBINE SHROUD WITH SEALED BLADE TRACK

Rolls-Royce North America...

1. A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprisinga first shroud segment including a first carrier segment, a first blade track segment, and a first retainer that couples the first carrier segment to the first blade track segment, the first blade track segment made from a ceramic-matrix-composite material,
a second shroud segment arranged circumferentially adjacent to the first shroud segment around the central axis, the second shroud segment including a second carrier segment, a second blade track segment, and a second retainer that couples the second carrier segment to the second blade track segment, the second blade track segment made from a ceramic-matrix-composite material, and
a circumferential seal arranged between the first shroud segment and the second shroud segment to block gasses from passing through a circumferential interface of the first shroud segment and the second shroud segment, the circumferential seal engaging a first seal-locating feature formed in the first carrier segment and a second seal-locating feature formed in the second carrier segment so that the circumferential seal is held in place circumferentially between the first shroud segment and the second shroud segment,
wherein the each carrier segment includes a central attachment body engaged with a corresponding blade track segment and a pair of end caps that extend circumferentially in opposing directions from the central attachment body and each end cap is formed to include a seal-locating feature, and
wherein a closed cavity is formed by the first shroud segment between the first carrier segment and the first blade track segment, the closed cavity extends along the central attachment body of the first carrier segment, the closed cavity is radially bounded by the blade track segment, and the closed cavity is circumferentially bounded by the pair of end caps.

US Pat. No. 10,087,770

SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT

Rolls-Royce Corporation, ...

1. A segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the shroud comprising:a carrier comprising a portion defining a pin-receiving carrier bore;
a ceramic matrix composite (CMC) seal segment comprising an arcuate flange having a surface facing the turbine and a portion defining a pin-receiving seal segment bore;
an elongated pin extending through said carrier bore and said seal segment bore,
wherein said elongated pin comprises a lateral cross-sectional dimension of at least three-eighths inches; and
wherein said CMC seal segment portion defining the pin-receiving seal segment bore is radially spaced from said arcuate flange by a spacing flange extending radially outward from said arcuate flange to thereby effect receipt within the seal segment bore of said elongated pin, said spacing flange having an axial dimension and a circumferential dimension, wherein said axial dimension is greater than said circumferential dimension of said spacing flange.

US Pat. No. 9,982,676

SPLIT AXIAL-CENTRIFUGAL COMPRESSOR

Rolls-Royce North America...

1. A gas turbine engine comprisinga compressor including an axial compression stage and a centrifugal compression stage arranged aft of the axial compression stage along an engine axis,
a turbine arranged aft of the centrifugal compression stage and coupled to the compressor to drive rotation of the axial compression stage and the centrifugal compression stage about the engine axis, and
a transmission coupled to the turbine and the compressor, the transmission configured to transmit rotational power generated by the turbine about the engine axis to at least one of the axial compression stage and the centrifugal compression stage to drive rotation of at least one of the axial compression stage and the centrifugal compression stage at a first speed offset from a turbine speed,
wherein (i) the axial compression stage has an outlet radius and the centrifugal compression stage has an inlet radius that is about equal to the outlet radius of the axial compression stage to facilitate a smooth transition of air from the axial compression stage to the centrifugal compression stage, (ii) the centrifugal compression stage is coupled to the turbine for common rotation therewith about the engine axis, and (iii) the axial compression stage is coupled to the turbine through the transmission for rotation about the engine axis at the first speed offset from the turbine speed.

US Pat. No. 10,100,659

HANGER SYSTEM FOR A TURBINE ENGINE COMPONENT

Rolls-Royce North America...

14. A method of assembling a component of a turbine, the method comprising:advancing a seal ring segment forward to engage a hanger of the seal ring segment with a rail of a carrier segment,
positioning a retainer aft the hanger of the seal ring segment, and
securing the retainer to the carrier segment, via a fastener extending through the carrier segment into a bottom surface of a groove in the retainer such that the hanger is secured between the carrier segment and the retainer.

US Pat. No. 10,024,537

COMBUSTOR ASSEMBLY WITH CHUTES

Rolls-Royce North America...

1. A combustor for use in a gas turbine engine, the combustor comprising:a combustion liner that defines a combustion chamber, the combustion liner including an outer liner surface facing away from the combustion chamber, an inner liner surface facing toward the combustion chamber, and a chute-receiving aperture that extends through the outer liner surface and the inner liner surface, and
a chute that extends through the chute-receiving aperture of the combustion liner and defines a passageway sized to convey air from an environment outside the combustion chamber through the combustion liner into the combustion chamber,
wherein the chute includes a chute body that extends through the chute-receiving aperture and defines the passageway, a flared head located outside of the combustion chamber that extends outwardly from the chute body away from the passageway so that the flared head is sized to block movement of the chute through the combustion liner into the combustion chamber, and a locating shoulder located inside of the combustion chamber that extends outwardly from the chute body away from the passageway so that the locating shoulder is sized to block movement of the chute through the combustion liner away from the combustion chamber,
wherein the combustion liner includes a plurality of cooling holes that extend through the combustion liner and that are arranged around the chute-receiving aperture and the locating shoulder is formed to include a plurality of cooling scallops arranged to face away from the chute body to provide a flow path for the air to flow from the environment outside of the combustion chamber through the plurality of cooling holes into the combustion chamber.

US Pat. No. 10,100,654

IMPINGEMENT TUBES FOR CMC SEAL SEGMENT COOLING

Rolls-Royce North America...

1. A turbine shroud comprisinga plurality of carrier segments comprising metallic material and arranged circumferentially adjacent to one another around an axis,
a plurality of blade track segments comprising ceramic-matrix composite material and arranged circumferentially adjacent to one another around the axis, each blade track segment coupled to one of the carrier segments, and
a plurality of impingement tubes, each impingement tube extending into one of the carrier segments and configured to direct a flow of cooling air toward a radially-outward facing side of the blade track segment,
wherein each blade track segment includes a runner and at least two attachment features extending radially outward from the runner, the at least two attachment features axially spaced apart from one another and circumferentially extending along the runner, and
wherein each impingement tube is positioned between one of the at least two attachment features and the runner of a corresponding blade track segment.

US Pat. No. 10,016,846

SYSTEM, METHOD, AND APPARATUS FOR REPAIR OF COMPONENTS

ROLLS-ROYCE CORPORATION, ...

1. A method for repairing a component through laser deposition, the method comprising:providing the component for repair, the component comprising a material selected from the group consisting of titanium and a titanium alloy;
providing a laser metal powder deposition device;
enclosing the component in a shielding device;
delivering a flow of inert gas to the shielding device to ensure an oxygen content remains below a first threshold and that a water vapor content remains below a second threshold in a target area of the component; and
depositing a metal material on the component, wherein the depositing comprises operating the laser deposition device along a tool path including a plurality of tool passes, delivering the metal material at a deposition device velocity specification, and heating the metal material at a laser power specification,
wherein the laser power specification is calculated in real-time during the depositing and changed during operations based on a deposited material representative temperature provided by a temperature sensor, and
wherein a respective deposition layer of the metal material is formed by performing multiple tool passes and each consecutive tool pass of the multiple tool passes overlaps a previous tool pass of the multiple tool passes in the respective deposition layer by at least 30%.

US Pat. No. 9,879,861

GAS TURBINE ENGINE WITH IMPROVED COMBUSTION LINER

Rolls-Royce Corporation, ...

1. A gas turbine engine variable porosity combustor liner comprising:
a laminated alloy structure having combustion chamber facing holes on one side and cooling plenum facing holes on a radially
opposite side, the combustion chamber facing holes being in fluid communication with the cooling plenum facing holes via axially
and circumferentially extending flow passages disposed between metal alloy sheets of the laminated alloy structure;

wherein at least one of the combustion chamber facing holes and the cooling plenum facing holes are oriented at a first angle
with respect to an axis of the combustor liner;

wherein porous zones having respective different cooling flow amounts are formed in the laminated alloy structure;
wherein the combustion chamber facing holes include holes of a first diameter and holes of a second diameter that is different
from the first diameter; and

wherein the holes oriented at the first angle are diffusion shaped holes, the diffusion shaped holes having an entrance at
a first size, and an exit at a second size that is greater than the first size.

US Pat. No. 9,803,553

METHOD TO CONTROL ELECTRIC STARTER GENERATOR FOR GAS TURBINE ENGINES

Rolls-Royce North America...

1. A gas turbine engine starting system comprising:
an electric start generator (ESG) free of temperature sensors and configured to provide torque to a gas turbine engine, wherein
the ESG comprises a plurality of subcomponents;

a fuel metering module configured to provide a quantity of fuel to the gas turbine engine; and
an electronic control system (ECS) that:
determines a future temperature of the ESG based on a plurality of historical ESG thermal trending information and an input
ambient temperature;

determines whether at least one of an ongoing start and an uninitiated start will be unsuccessful, wherein the determination
of whether at least one of the ongoing start and the uninitiated start will be unsuccessful is based on the future temperature
of the ESG; and

indicates the determination of whether at least one of the ongoing start and the uninitiated start will be unsuccessful to
an operator.

US Pat. No. 9,630,885

METHOD FOR MAKING CERAMIC MATRIX COMPOSITE ARTICLES

Rolls-Royce Corporation, ...

1. A method of forming a composite article, the method comprising:
impregnating an inorganic fiber preform with a slurry composition, wherein the slurry composition comprises a particulate,
a solvent, and a pre-gellant material;

initiating gelation of the pre-gellant material in the slurry composition to immobilize the particulate and yield a gelled
article;

removing substantially all solvent from the gelled article to form a green composite; and
infiltrating the green composite article with a molten infiltrant to form the composite article.

US Pat. No. 9,568,009

GAS TURBINE ENGINE FLOW PATH GEOMETRY

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine flow path structure structured for use to define a flow path in a turbomachinery component, the flow
path structure having a flow surface that extends along an upstream portion and a downstream portion and where the upstream
portion and the downstream portion are coincident with a bladed turbomachinery component such that the upstream portion and
the downstream portion are immediately radially outside of the bladed turbomachinery component, the upstream portion having
a cylindrical shape that extends aft from a first axial location to a second axial location, the downstream portion having
a conical shape with linear slope extending from the second axial location to a third axial location such as to form a flat
cone, the conical shape having a larger radius at the second axial location than a radius at the third axial location, wherein
the second axial location is coincident with a vibratory modal axis of the bladed turbomachinery component.

US Pat. No. 9,963,990

CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE

Rolls-Royce North America...

1. A segmented turbine shroud for radially encasing a turbine in a gas turbine engine, the shroud comprising:a carrier;
a ceramic matrix composite (CMC) seal segment comprising an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin; and
one or more elongated pins,
wherein said CMC seal segment is carried by said carrier by at least one of said elongated pins being received within said bore,
wherein said CMC seal segment portion defining a pin-receiving bore comprises a curved outer surface and is radially spaced from said arcuate flange by an elongated spacing flange extending radially outward from said arcuate flange, said elongated spacing flange having an axial dimension parallel to the axis of said bore and a lateral dimension less than the axial dimension of said flange and less than a lateral dimension of said portion defining the bore, and wherein said CMC seal segment portion defines a bore having a length that is at least 70% of the length of said elongated pin received therein.

US Pat. No. 9,617,857

GAS TURBINE ENGINE COMPONENT

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a rotatable turbomachinery blade component having an inner core extending from a base and made from a first material;
an outer flow surface made from a second material and captured between the base and a cap that is fastened to the core, the
core extending substantially into an interior of the outer flow surface; and

a fugitive spacer placed between the inner core and the outer flow surface, the fugitive spacer structured to be removed by
heating,

wherein the first material is metallic and the second material includes is a ceramic matrix composite.

US Pat. No. 10,094,239

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

Rolls-Royce North America...

1. A vane assembly for a gas turbine engine, the assembly comprisingan inner platform made from a metallic material,
an outer platform made from a metallic material,
a ceramic-containing airfoil that extends from the inner platform to the outer platform and engaged with at least one of the inner platform and the outer platform so that some aerodynamic loads applied to the ceramic-containing airfoil are transferred directly to at least one of the inner platform and the outer platform, and
a reinforcement spar made from a metallic material that extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil and engages an interior surface of the ceramic-containing airfoil so that some aerodynamic loads applied to the ceramic-containing airfoil are transferred to at least one of the inner platform and the outer platform,
wherein the ceramic-containing airfoil includes a first end and a second end and the interior surface of the ceramic-containing airfoil engages the reinforcement spar adjacent to the second end of the ceramic-containing airfoil,
wherein the first end of the ceramic-containing airfoil is received in one of the inner platform and the outer platform to transfer load,
wherein the ceramic-containing airfoil is disengaged from the inner platform adjacent to the second end of the ceramic-containing airfoil.

US Pat. No. 10,048,168

SYSTEM AND METHOD FOR OPTIMIZING COMPONENT LIFE IN A POWER SYSTEM

Rolls-Royce North America...

1. An aircraft, comprising:first and second gas turbine engines, each having a first power circuit and a second power circuit, the first power circuit having a first aircraft component coupled thereto, and the second power circuit having a second aircraft component coupled thereto that is redundant with the first aircraft component; and
an engine health monitoring system (EHMS) coupled to the first and second gas turbine engines, wherein the EHMS:
receives sensor feedback from the first aircraft component and the second aircraft component;
generates a remaining useful life (RUL) of the first aircraft component and of the second aircraft component;
generates a rate-of-life consumption of the first aircraft component and of the second aircraft component;
indicates when failure of the first aircraft component and failure of the second aircraft component will occur based on the RUL of each and based on the respective rate-of-life consumption of each;
provides instructions for altering operation of the aircraft that affects the RUL of the first aircraft component or the second aircraft component; and
the EHMS varies an amount of load on the first power circuit and the second power circuit to increase the RUL of the aircraft component with the lowest RUL, by reducing an amount of load on the power circuit having the aircraft component with the lowest RUL and increasing an amount of load on the other power circuit, such that the first aircraft component and the second aircraft component each have a generally converged time of failure.

US Pat. No. 9,650,906

SLOTTED LABYRINTH SEAL

Rolls-Royce Corporation, ...

1. A seal for a machine, the seal comprising:
a first rotating member having a cavity formed between a first runner and a second runner that extend axially in a first linear
direction from the first rotating member;

a second rotating member having at least one fin with outer and inner surfaces tapering transversely toward each other and
extending axially to a distal end in a second linear direction from the second rotating member and toward the first rotating
member, the fin having a base section with the outer and inner surfaces at the base section spanning wider than the cavity,
the fin having a tapered section extending from the base section towards the first rotating member, the tapered section having
an aperture extending between the outer and inner surfaces at the tapered section, the fin having an elongated section with
an axial length and a radial width, wherein the length of the elongated section extends axially from the tapered section to
the distal end of the fin and into the cavity between the first runner and the second runner, wherein the width of the elongated
section is generally uniform, wherein the length of the elongated section of the fin is larger than an axial length of the
cavity, and wherein blockage of the aperture by at least one of the first and second runners is resisted due to the length
of the elongated section being greater than the length of the cavity and due to a width of the tapered section being greater
than a radial width of the cavity;

a first clearance between the cavity and the fin; and
a second clearance between the cavity and the fin,
wherein said first and second rotating members are arranged to rotate at different speeds about a common rotational axis.

US Pat. No. 9,657,590

AIRCRAFT ENGINE CLEANING SYSTEM

Rolls-Royce Corporation, ...

1. An aircraft comprising
a cabin air system,
a gas turbine engine including an engine core coupled to the cabin air system to provide compressed bleed air to the cabin
air system and a cleaning agent supply connector coupled to the engine core to conduct a cleaning agent to the engine core,
and

a pneumatic coupling system including a first valve coupled between the cabin air system and the engine core, a second valve
coupled between the engine core and the cleaning agent supply connector, and a controller coupled to the first valve, the
controller configured to automatically close the first valve and block compressed bleed air that may contain cleaning agent
moving through the engine core from moving into the cabin air system in response to receipt of an input associated with a
cleaning cycle.

US Pat. No. 9,850,779

LUBRICATION SYSTEM FOR A GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

1. A lubrication system for a gas turbine engine, the lubrication system comprising
an oil tank,
a sump housing a bearing, and
a breather assembly coupled to the oil tank, the sump, and atmosphere, the breather assembly including a breather housing
that defines a breather cavity, a tank port arranged to transport oil droplets and carrier air from the oil tank into the
breather cavity, a vent port arranged to transport air from the breather cavity to the atmosphere, a sump air-bleed port arranged
to transport pressurized air from the sump into the breather cavity, and a sump oil-return port arranged to transport oil
from the breather cavity to the sump,

wherein the breather assembly further includes a baffle arranged in the breather cavity between the tank port and the sump
air-bleed port to block pressurized, relatively high-velocity air from the sump air-bleed port from directly impinging into
the tank port.

US Pat. No. 9,650,303

SILICON CARBIDE CERAMIC MATRIX COMPOSITES

Rolls-Royce Corporation, ...

1. A method of producing a silicon carbide (SiC) ceramic matrix composite (CMC), the method comprising:
forming a SiC fiber preform;
incorporating a slurry comprising yttrium or ytterbium into the SiC fiber perform via slurry infiltration; and
infiltrating the SiC fiber perform with a melt comprising silicon, therby forming the SiC ceramic matrix composite.

US Pat. No. 9,574,575

MULTI-PASSAGE DIFFUSER WITH REACTIVATED BOUNDARY LAYER

Rolls-Royce Corporation, ...

8. An apparatus comprising:
a diffuser of a gas turbine engine, the diffuser having diverging inner and outer walls useful to decrease a velocity and
raise a static pressure of a fluid stream, the diffuser also including

a splitter having a bluff forebody disposed intermediate a downstream end and upstream end of the diffuser to create a restriction
and thereby promote a pressure field across the diffuser, between the inner and outer walls, that is sufficient to re-start
a boundary layer along each of the inner and outer walls.

US Pat. No. 9,562,476

GAS TURBINE ENGINE THERMALLY CONTROLLED FLOW DEVICE

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine flow device including an inner member and a surrounding member;
the inner member having a first coefficient of thermal expansion; and
the surrounding member at least partially surrounding the inner member and having a second coefficient of thermal expansion
that is different from the first coefficient of thermal expansion of the inner member;

the surrounding member including at least two walls that include a planar first wall and a cylindrical second wall that form
a variable flow gap between an end of the second wall and an outer periphery of the first wall,

wherein the inner member is oriented relative to the at least two walls of the surrounding member such that, based on the
difference in the first and second coefficients of thermal expansion, the inner member expands relatively greater than the
surrounding member or the surrounding member expands relatively greater than the inner member, according to a temperature
change to correspondingly enlarge or reduce the size of the variable flow gap between the at least two walls.

US Pat. No. 9,920,634

METHOD OF MANUFACTURING A TURBOMACHINE COMPONENT, AN AIRFOIL AND A GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

13. An airfoil for a turbomachine, comprising:
a body having an airfoil shape, wherein the body includes:
an internal portion of the airfoil having a composite foam cooling passage configured to pass a cooling fluid into the composite
foam cooling passage at a first end face and out of the composite foam cooling passage at a second end face, the first end
face and the second end face positioned on a same side of the body; and

a plurality of composite wrap plies enveloping the internal portion of the airfoil.

US Pat. No. 9,874,108

CLEANING SYSTEM FOR A TURBOFAN GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

1. A turbofan gas turbine engine comprising
a fan adapted to be rotated about an axis to accelerate air,
an engine core coupled to the fan to drive rotation of the fan, the engine core including a compressor, a combustor, and a
turbine,

an annular frame including an inner wall that extends around the engine core and an outer wall that extends around the inner
wall, the inner wall and the outer wall cooperating to define a bypass duct radially there between in fluid communication
with the fan to receive bypass air accelerated by the fan,

a cleaning system configured to conduct a cleaning agent from a supply radially through the bypass duct to the engine core
and to inject the cleaning agent from the supply into the compressor of the engine core, and

an inlet guide vane assembly including a bypass inlet vane ring arranged between the fan and the bypass duct of the annular
frame to redirect air moving from the fan to the bypass duct, a core inlet vane ring arranged between the fan and the compressor
of the engine core to redirect air moving from the fan to the compressor, and a splitter coupled radially between the bypass
inlet vane ring and the core inlet vane ring,

wherein the cleaning system includes at least one injector mounted in the core inlet vane ring and formed to include an aperture
configured to conduct the cleaning agent from the supply into the compressor, and

wherein the cleaning system includes a conduit located axially aft of the bypass inlet vane ring that extends radially from
the outer wall of the frame through the bypass duct to the inner wall of the frame and a transfer tube that extends axially
within the splitter to one of the injectors.

US Pat. No. 9,753,014

DETECTION AND MEASUREMENT OF DEFECT SIZE AND SHAPE USING ULTRASONIC FOURIER-TRANSFORMED WAVEFORMS

Rolls-Royce Corporation, ...

1. A system comprising:
a data analysis device configured to:
receive from an ultrasonic waveform detector ultrasonic waveform data representative of an ultrasonic waveform that propagated
through a sample and resonated within a defect within the sample;

select a portion of the ultrasonic waveform data;
apply a Fast Fourier Transform to the portion of the ultrasonic waveform data to transform the portion from a time domain
to a frequency domain;

identify a characteristic frequency of the portion in the frequency domain; and
determine a characteristic of the defect by at least one of (1) comparing the characteristic frequency to a calibration curve
or (2) calculating an approximate size of the defect using at least one equation that relates the characteristic frequency
to the approximate size of the defect.

US Pat. No. 9,688,414

INTELLIGENT INTEGRATED CONTROL SYSTEM AND METHOD

ROLLS-ROYCE CORPORATION, ...

1. A system, comprising:
at least one engine operable to generate a power output in response at least in part to an operator power request and sensed
parameters from a sensor;

an engine control subsystem configured to control operation of the at least one engine;
an electrical power subsystem including at least one electrical power device that is operable to demand electric power during
operation of the at least one engine; and

a controller connected to the engine control subsystem and to the electrical power subsystem with a system data bus, wherein
the controller is configured to determine an anticipatory electric power demand of the at least one electrical device based
on current operating conditions and provide control signals to the engine control subsystem to control the at least one engine
to generate the power output to meet a total power demand, wherein the total power demand includes at least the anticipatory
electric power demand and a nominal power demand based at least in part on the operator power request, and wherein the controller
is configured to initiate compensation for the anticipatory electric power demand prior to the at least one engine receiving
an increased demand for power output.

US Pat. No. 9,937,803

ELECTRIC DIRECT DRIVE FOR AIRCRAFT PROPULSION AND LIFT

Rolls-Royce North America...

1. An apparatus of an aircraft propulsion system, comprising:a prime mover coupled to a generator;
an electric motor directly electrically coupled to said generator;
a propeller coupled to and driven by said electric motor; and
a bi-directional power converter coupled to said generator and further coupled to an energy storage device;
wherein said energy storage device is selectively coupled to said electric motor, and
wherein said energy storage device comprises an engine generator.

US Pat. No. 9,882,513

SYNCHRONIZING MOTORS FOR AN ELECTRIC PROPULSION SYSTEM

Rolls-Royce North America...

1. An electric propulsion system comprising:
an AC drive circuit that includes:
a plurality of propulsor motors;
an AC power bus; and
an AC generator that delivers AC electrical power to the AC power bus for simultaneously driving the plurality of propulsor
motors;

a synchronization circuit configured to individually synchronize, with the AC generator, a single propulsor motor from the
plurality of propulsor motors, one at a time; and

a control unit configured to:
determine whether the single propulsor motor is not synchronized with the AC generator; and
maintain synchronicity between the single propulsor motor and the AC generator by engaging the synchronization circuit with
the single propulsor motor in response to determining that the single propulsor motor is not synchronized with the AC generator.

US Pat. No. 9,764,989

REACTIVE FIBER INTERFACE COATINGS FOR IMPROVED ENVIRONMENTAL STABILITY

Rolls-Royce Corporation, ...

1. A composite material comprising:
a matrix, and
a plurality of coated fibers suspended in the matrix, the coated fibers each including a fiber and a multilayer interface
coating deposited on the fiber,

wherein the multilayer interface coating includes an oxide layer, a silicon containing compound layer, and a silicate that
is formed at an interface of the oxide layer and the silicon containing compound layer and that is disposed between the fiber
and the matrix, and wherein the oxide layer and the silicon containing compound layer are in direct contact with each other
along the interface adjacent to the silicate.

US Pat. No. 9,605,550

BI-METAL STRIP-SEAL

Rolls-Royce Corporation, ...

1. A seal for use with a machine comprising:
an open fluid path in a machine, the fluid path extends between fixed members that are components of the machine; and
a first bi-metal valve that is located in proximity to the open fluid path, the valve is made of a bi-metal strip that is
operable to move between a first position and a second position during a heating event, the valve is operable to block the
fluid path;

wherein:
each of the fixed members is a tile formed of ceramic material, the tile is used in conjunction with a component of the machine;
and

the bi-metal valve is secured to the component by the fastener.

US Pat. No. 9,593,596

COMPLIANT INTERMEDIATE COMPONENT OF A GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a first gas turbine engine component structured for use in a gas turbine engine and having a first mating portion;
a second gas turbine engine component having a second mating portion formed to receive within it the first mating portion
of the first component to interlockingly secure the first component for use during operation of the gas turbine engine; and

a load bearing intermediate component positioned between the first mating portion of the first component and the second mating
portion of the second component, the load bearing intermediate component including:

a main body having a portion configured to bear a loading imparted by contact between the first mating portion and the second
mating portion, the main body captured on one of the first mating portion and the second mating portion through a plurality
of finger portions extending from the main body,

wherein the plurality of finger portions each contact the second mating portion of the second gas turbine engine component
at a different location and the plurality of finger portions includes a first finger portion that contacts the second component
at a first location, a second finger portion that contacts the second component at a second location spaced from the first
location in a circumferential direction, and a third finger portion that contacts the second component at a third location
spaced discreetly from the first location in both the circumferential direction and an axial direction.

US Pat. No. 10,071,936

METHOD FOR MAKING CERAMIC MATRIX COMPOSITE ARTICLES

Rolls-Royce Corporation, ...

1. An article comprising an inorganic fiber preform impregnated with a slurry composition, wherein the slurry composition comprises a particulate, a solvent comprising water, and a pre-gellant material, wherein the pre-gellant material comprises a monomer that is polymerizable to form a gel.

US Pat. No. 9,719,684

GAS TURBINE ENGINE VARIABLE POROSITY COMBUSTOR LINER

Rolls-Royce North America...

1. A gas turbine engine combustor liner comprising:
a hot side wall and a cold side wall configured for installation in a gas turbine engine to separate a combustion chamber
from a cooling air source, the hot side wall and the cold side wall each comprising metal alloy sheet material;

the hot side wall having a plurality of hot side holes projecting through its thickness for fluid communication with the combustion
chamber;

the cold side wall having a plurality of cold side holes projecting through its thickness for fluid communication with the
cooling air source and including a plurality of pedestals that connect to the hot side wall such that a plurality of fluid
flow passages are defined between the hot side wall and cold side wall and between the pedestals;

the cold side holes being in fluid communication with the hot side holes via the fluid flow passages so as to create a cooling
flow path from the cooling air source to the combustion chamber; and

first and second arrangements of a plurality of the hot side holes, the cold side holes, and the fluid flow passages defining
respective first and second porous regions in the combustor liner having respective first and second porosities;

wherein at least one of 1) the plurality of hot side holes or 2) the plurality of cold side holes include holes of a first
diameter and of a second diameter that is different from the first diameter; and

wherein the first arrangement that defines the first porous region has the hot side holes of the first diameter, and the second
arrangement that defines the second porous region has the hot side holes of the second diameter that is different than the
first diameter.

US Pat. No. 9,598,975

BLADE TRACK ASSEMBLY WITH TURBINE TIP CLEARANCE CONTROL

Rolls-Royce Corporation, ...

1. A turbine shroud comprising
a carrier arranged around an axis and formed to include a first guide slot extending outward in a radial direction from the
axis and along a portion of the circumference of the carrier,

a blade track concentric with the carrier, the blade track movable between a radially-inward position having a first inner
diameter and a radially-outward position having a second inner diameter larger than the first inner diameter, and

an actuator configured to change size in response to a change in temperature, the actuator coupled to the blade track to move
the blade track between the radially-inward position and the radially-outward position when the actuator changes size in response
to a change in temperature, wherein the actuator is coupled to the carrier by a mover pin that extends from the actuator into
the first guide slot and that is configured to move along a length of the first guide slot so that the blade track moves along
a portion of the circumference of the carrier around the axis when the actuator changes size.

US Pat. No. 10,208,668

TURBINE ENGINE ADVANCED COOLING SYSTEM

ROLLS-ROYCE CORPORATION, ...

1. A gas turbine engine defining a longitudinal axis, the gas turbine engine comprising:a compressor;
a turbine;
a combustor arranged axially between the compressor and the turbine and configured to drive the turbine with a stream of gas, the combustor comprising at least one liner defining a combustion chamber;
a shield positioned axially between the compressor and the turbine, wherein the shield extends from a first plane positioned axially forward of the combustor to a second plane extending through an aft end of the combustion chamber, the first plane and the second plane each being perpendicular to the longitudinal axis;
a combustor case;
a drive shaft mechanically coupling the compressor to the turbine;
a conduit configured to supply a cooling fluid to an annulus defined by the combustor case and the shield, the annulus configured to supply the cooling fluid to a first end of a gap between an outer surface of the drive shaft and the shield, the drive shaft and the shield configured to guide the cooling fluid from the first end of the gap to a second end of the gap, wherein the cooling fluid flows from the second end of the gap into an outlet of the compressor during operation of the gas turbine engine;
a flow restrictor positioned in the gap and located between the first end of the gap and the second end of the gap, wherein the flow restrictor is a seal, wherein the seal is configured to limit fluid flow through the gap; and
a radial pre-swirler configured to direct the cooling fluid from the annulus toward the drive shaft and into the gap, the radial pre-swirler configured to swirl the cooling fluid in a direction of rotation of the drive shaft, the radial pre-swirler positioned at an aft end of the shield and axially aft of the flow restrictor.

US Pat. No. 10,174,619

GAS TURBINE ENGINE COMPOSITE VANE ASSEMBLY AND METHOD FOR MAKING SAME

Rolls-Royce North America...

1. A method for forming a gas turbine engine airfoil assembly, comprising:providing at least two gas turbine engine airfoil composite preform components,
interlocking the airfoil composite preform components with a first locking component, and
interlocking the first locking component and at least one of the airfoil composite preform components with a second locking component, and
after interlocking with each of the first and second locking components, rigidizing the assembly of aircraft component preform components, the first locking component, and the second locking component,
wherein the airfoil composite preform components comprise an airfoil and an endwall, and the first locking component interlocks the airfoil and the endwall and the second locking component interlocks the first locking component and the endwall, and the second interlocking comprises inserting the second locking component into a through hole in the first locking component and a through hole in the endwall.

US Pat. No. 9,573,354

LAYERED DEPOSITION FOR REACTIVE JOINING OF COMPOSITES

Rolls-Royce Corporation, ...

1. A method comprising:
applying layers of a first constituent and a second constituent on a surface of a ceramic matrix composite component to form
a first outer coating, the first outer coating including the first constituent;

applying layers of the first constituent and the second constituent on a component surface of a gas turbine engine component
to form a second outer coating, the second outer coating including the second constituent, wherein the first constituent and
the second constituent are capable of producing a thermodynamic non-equilibrium condition between the first constituent and
the second constituent;

forming a component assembly with the ceramic matrix composite component coupled to the gas turbine engine component and with
the first outer coating of the ceramic matrix composite component in contact with the second outer coating of the gas turbine
engine component;

adding an energy to facilitate an equilibrium reaction between the first constituent of the first outer coating and the second
constituent of the second outer coating;

as a result of the adding the energy, forming a bond structure in the component assembly with a product of the equilibrium
reaction, the bond structure affixing the ceramic matrix composite component to the gas turbine engine component, wherein
the bond structure defines a level of porosity; and

applying a melt infiltrant to the bond structure to at least partially reduce the level of porosity in the bond structure.

US Pat. No. 9,958,159

COMBUSTOR ASSEMBLY FOR A GAS TURBINE ENGINE

Rolls-Royce Corporation, ...

1. A combustor assembly for a gas turbine engine, comprising: a hanger having a first flange portion extending radially inward therefrom, said first flange portion forming a step including a first wall portion at a first wall thickness and a second wall portion at a second wall thickness that is less than said first wall thickness;a combustor liner fixed to said hanger, said combustor liner having an inner surface extending along an axis of a combustion chamber;
a heat shield having a-second flange portions extending radially outward therefrom, said second flange portion in contact with said first wall portion and said second wall portion of said first flange portion, said heat shield at least partially overlapping and confronting said inner surface of said combustor liner along said axis to form an axially extending gap, said heat shield releasably engaged with said hanger, said heat shield forming a plurality of radially outer surfaces between said second flange portions, said radially outer surfaces oppose said first wall portion to form circumferentially extending gaps between said second flange portions, said heat shield forming recesses that oppose said second wall portion to form radially extending gaps, such that air flow passes from the circumferentially extending gaps into said radially extending gaps and into said axially extending gap; and
fasteners passing through said first flange portion and said second flange portions and extending in a direction parallel with said axis.

US Pat. No. 9,945,243

TURBINE SHROUD WITH BIASED BLADE TRACK

Rolls-Royce Corporation, ...

1. A turbine shroud for a gas turbine engine that extends around a central axis, the turbine shroud comprisinga metallic carrier that extends around the central axis,
a ceramic-containing composite blade track coupled to the metallic carrier, and
a plurality of biasing members arranged between the metallic carrier and the ceramic-containing composite blade track to bias the ceramic-containing composite blade track outwardly in a radial direction away from the central axis to locate the ceramic-containing composite blade track relative to the metallic carrier,
wherein the metallic carrier is formed to include a plurality of retention arms each arranged radially between at least a portion of a corresponding runner and a corresponding retention head of a blade track segment, each retention arm is engaged by at least one biasing member and formed to include a slot that receives at least a portion of a biasing member to locate the biasing member relative to the metallic carrier, and the slot of each retention arm extends radially toward the corresponding runner without extending radially all the way through the retention arm.

US Pat. No. 9,840,747

WALL MEMBER USEFUL IN QUENCHING

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a reservoir of quenching fluid configured to provide the quenching fluid;
a pallet supporting a plurality of workpieces, the pallet including through-holes structured to pass the quenching fluid,
wherein the pallet and plurality of workpieces are submerged in the reservoir of quenching fluid; and

a plurality of upturned wall portions extending from the pallet and substantially surrounding the exteriors of the plurality
of workpieces, the plurality of upturned wall portions located in relative orientation to the plurality of workpieces to regulate
heat transfer coefficients of the plurality of workpieces during a quenching operation.

US Pat. No. 9,835,048

TURBINE ENGINE FLEET WASH MANAGEMENT SYSTEM

Rolls-Royce Corporation, ...

1. A system to optimize cleaning of a turbine engine, the system comprising:
a wand, and
one or more computing devices configured to:
by a communication link between a turbine engine and a cleaning schedule optimizer, receive engine health data from the turbine
engine over time during operation of the turbine engine;

by the cleaning schedule optimizer, periodically execute an cleaning optimization routine to evaluate instances of the engine
health data using cleaning schedule optimization criteria, wherein the cleaning schedule optimization criteria include flight
plans of the turbine engine, operating conditions, and characteristics of a cleaning technique or a foamed cleaning agent
used to clean the turbine engine; and

in response to one or more instances of the engine health data meeting an engine health criterion, cause the foamed cleaning
agent to be discharged from the wand coupled to a cleaning system into the turbine engine according to an optimized engine
cleaning schedule,

wherein the operating conditions comprise one or more of flight duration, altitude, frequency of accelerations or cruising
segments.

US Pat. No. 9,751,147

FIXTURE FOR HIGH TEMPERATURE JOINING

Rolls-Royce Corporation, ...

1. A fixture comprising:
a plurality of alloy pressure pads shaped to contact a component to be brazed or diffusion bonded;
a plurality of springs, wherein each spring of the plurality of springs is shaped with a horseshoe or a capital omega symbol
shape; and

at least one generally annular alloy support, wherein the plurality of springs are between and contacting the at least one
generally annular alloy support and the plurality of alloy pressure pads to exert spring forces on the plurality of alloy
pressure pads.

US Pat. No. 9,719,353

INTERFACIAL DIFFUSION BARRIER LAYER INCLUDING IRIDIUM ON A METALLIC SUBSTRATE

ROLLS-ROYCE CORPORATION, ...

1. An article comprising:
a nickel-based superalloy substrate including between about 2 wt. % and about 5 wt. % aluminum and between about 2 wt. % and
about 5 wt. % titanium, wherein the nickel-based superalloy substrate comprises between 40 volume percent and 55 volume percent
gamma-prime precipitate phase;

a diffusion barrier layer on the substrate, wherein the diffusion barrier layer comprises an alloy comprising iridium and
silicon, and wherein the alloy comprises a majority iridium; and

a nickel-based protective layer comprising nickel and at least one of aluminum or chromium on the diffusion barrier layer.

US Pat. No. 9,651,258

SHELL AND TILED LINER ARRANGEMENT FOR A COMBUSTOR

Rolls-Royce Corporation, ...

1. A combustor for use in a gas turbine engine, the combustor comprising
an annular metallic shell forming an annular cavity, and
an annular liner arranged in the annular cavity of the annular metallic shell and defining an annular combustion chamber,
the annular liner including a first ceramic tile coupled to the metallic shell by a first fastener extending through the first
ceramic tile and a second ceramic tile coupled to the metallic shell by a second fastener extending through the second ceramic
tile,

wherein an overlapped portion of the first ceramic tile is arranged to extend between the second fastener that extends through
the second ceramic tile and the annular combustion chamber to shield the second fastener from the annular combustion chamber,

wherein the annular metallic shell is formed to include portions that define dimples, the portions that define the dimples
extending outward in a radial direction away from a central axis of the combustor around which the combustion chamber extends.

US Pat. No. 10,190,434

TURBINE SHROUD WITH LOCATING INSERTS

Rolls-Royce North America...

1. A turbine blade track comprisingan annular ceramic runner formed to include a plurality of cutouts extending inward in a radial direction from an outer radial surface of the annular ceramic runner toward an inner radial surface of the annular ceramic runner, and
a plurality of inserts coupled to the annular ceramic runner, each insert including a stem arranged in the cutout and a cap arranged outside the cutout that extends from the stem in a circumferential direction and in an axial direction along the outer radial surface of the annular ceramic runner.

US Pat. No. 10,060,277

TURBINE WHEEL WITH CLAMPED BLADE ATTACHMENT

Rolls-Royce North America...

1. A turbine wheel for a gas turbine engine, the turbine wheel comprising a disk formed to include a fir tree slot that extends through the disk in an axial direction from a forward side to an aft side of the disk and inwardly in a radial direction from an outer diameter of the disk toward a central axis,a blade comprising ceramic-containing materials, the blade integrally formed to include an airfoil that extends outwardly in the radial direction from the outer diameter of the disk and a root that extends into the fir tree slot, the root including a stem that extends from the airfoil into the fir tree slot and a retention head arranged in the fir tree slot that extends from the stem, and
a blade retention assembly including at least two clamp blocks that cooperate to form a fir tree shape corresponding to the fir tree slot, wherein the at least two clamp blocks engage the retention head of the root and are received in the fir tree slot of the disk so that centrifugal forces applied to the blade when the turbine wheel is rotated about the central axis are transferred from the retention head through the blade retention assembly to the disk, wherein the clamp blocks are shaped to extend radially inward to a point substantially similar to a radially-innermost surface of the blade, and wherein the retention head extends in axially forward and aft direction out from the stem.

US Pat. No. 10,060,300

SECTIONED GAS TURBINE ENGINE DRIVEN BY SCO2 CYCLE

Rolls-Royce North America...

1. A sectioned heat exchanger system for a gas turbine engine, comprising:an inlet manifold configured to receive a working fluid;
a plurality of circuits including at least first and second circuits configured to transfer heat with respect to the working fluid, each of the first and second circuits having a circuit inlet valve, a circuit heat exchange channel, and a circuit outlet valve;
an outlet manifold configured to pass the working fluid to an outlet;
a first sensor configured to measure a first parameter of the first circuit;
a second sensor configured to measure a second parameter of at least one of the outlet and the second circuit; and
a controller of the gas turbine engine and configured to selectively isolate at least one of the plurality of circuits by closing at least one of the first and second circuits in response to detecting a leak based on a parameter difference between the first and second parameters.

US Pat. No. 9,817,393

ADAPTIVE MACHINING OF COMPONENTS

Rolls-Royce Corporation, ...

1. An adaptive machining system comprising:
a numerical control (NC) machine configured to machine a component based on a machine tool program code;
a model comparison unit configured to compare electronic measured dimensional surface data of the component with an electronic
surface model of the component;

a compromise shape determination unit configured to determine a compromise shape for the component based on the comparison,
wherein the compromise shape determination unit comprises a model transformation determination unit configured to modify the
electronic surface model based on the comparison, wherein the compromise shape determination unit comprises an offset distribution
determination unit that is configured to determine a compromise offset distribution between the modified electronic surface
model and the electronic measured dimensional surface data, wherein the offset distribution determination unit is configured
to apply the compromise offset distribution to the modified electronic surface model to have a rate of contour deviation within
a predetermined tolerance of 0.005 inch/inch; and

a program modification unit configured to modify the machine tool program code based on the compromise shape by modifying
at least one line of the machine tool program code.

US Pat. No. 9,765,698

FLEXIBLE BELLOWS IGNITER SEAL

Rolls-Royce Corporation, ...

1. A gas turbine engine comprising:
an igniter having a top flange;
a diffuser case having a first opening;
a combustor liner having a second opening;
a flexible bellows seal having a first end and a second end opposite of the first end, and a flange at the first end;
a fastener to secure the flexible bellows seal to an inner surface of the diffuser case via the flange of the flexible bellows
seal, and the igniter to an outer surface of the diffuser case via the top flange of the igniter; and

a coating applied on a too surface of the combustor liner and extending around a circumference of the flexible bellows seal;
wherein the igniter extends into an interior of the flexible bellows seal through the first opening and aligned with the second
opening; and

wherein the second end of the flexible bellows seal is in contact with the coating.

US Pat. No. 9,689,502

ROTARY EXHAUST VALVE SYSTEM

Rolls-Royce Corporation, ...

1. A rotary exhaust valve system, comprising:
an arcuate ring having a first plurality of apertures therein;
a rotary valve ring disposed in an overlapping relation with the arcuate ring, the rotary valve ring having a second plurality
of apertures formed therein corresponding to at least some of the first plurality of apertures;

a first crank disposed in a first side of the rotary exhaust valve system; and
a second crank disposed in a second side of the rotary exhaust valve system, the second crank connected to the first crank
and the rotary valve ring, wherein the first side is separated from the second side via a separation member, wherein a crankshaft
passing through the separation member connects the first crank to the second crank, wherein the first crank actuates the second
crank and moves the rotary valve ring to align the at least some of the second plurality of apertures with the at least some
of the first plurality of apertures forming openings that are closed and opened by movement of the rotary valve ring.

US Pat. No. 9,630,706

POSITIONABLE EJECTOR MEMBER FOR EJECTOR ENHANCED BOUNDARY LAYER ALLEVIATION

Rolls-Royce Corporation, ...

1. An apparatus comprising:
an aircraft having a power plant configured to discharge a fluid stream to provide a force that affects a movement of the
aircraft, the fluid stream adapted for use as a primary flow stream of an ejector;

a flow surface over which a working fluid passes to form a boundary layer as the aircraft is in motion, the flow surface comprising
a nacelle of the power plant;

an ejector having an ejector shroud structured to be moveable fore and aft relative to the flow surface between an open position
and a closed position, the ejector shroud capable of producing a gap between a portion of the ejector shroud and the flow
surface, wherein the gap serves to capture at least a portion of the boundary layer from the flow surface and provide it as
a secondary flow stream of the ejector; and

a controller configured to operate upon a determined condition and actuate the ejector shroud to a variety of positions between
the open position and the closed position as a function of the determined condition to control the ejector, and the determined
condition includes one of a determined aircraft altitude, static temperature, static pressure, total temperature, total pressure,
and aircraft configuration.

US Pat. No. 9,598,777

METHOD FOR FABRICATING MULTILAYER ENVIRONMENTAL BARRIER COATINGS

Rolls-Royce Corporation, ...

5. A method of making a multilayer environmental barrier coating for a ceramic matrix composite, the method comprising:
plasma spray coating an oxide-based bond coat over top of the ceramic matrix composite, wherein the oxide-based bond coat
consists of HfSiO4+Si; and wherein the Si is present in the oxide-based bond coat in an amount between about 10 wt. % and about 40 wt. %, and
the balance of the oxide-based bond coat is HfSiO4;

selecting a method of applying a columnar top coat over the oxide-based bond coat, wherein the method of applying the columnar
top coat is selected from the group consisting of electron beam physical vapor deposition and directed vapor deposition; and

depositing a columnar top coat over the oxide-based bond coat according to the selected method of applying the columnar top
coat.

US Pat. No. 10,038,397

MULTIPLE ENGINE CONDITION MATCHING VIA ELECTRICAL POWER EXTRACTION CONTROL

Rolls-Royce Corporation, ...

1. A multi-engine power system comprising:a load requiring a total amount of electrical power;
a first engine configured to provide a first portion of the total amount of electrical power to be provided to the load;
a second engine configured to provide a second portion of the total amount of electrical power to be provided to the load; and
a controller configured to:
determine the total amount of electrical power to be provided to the load;
estimate a respective service time associated with each of the first and second engines; and
control each of the first and second engines to provide the total amount of electrical power to the load and to coordinate the respective service times associated with the first and second engines.

US Pat. No. 9,970,317

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

Rolls-Royce North America...

1. A vane assembly for a gas turbine engine, the assembly comprisingan inner platform,
an outer platform,
a ceramic-containing airfoil that extends from the inner platform to the outer platform and is received in the inner platform and the outer platform so that substantially all aerodynamic loads applied to the ceramic-containing airfoil are transferred directly to the inner platform and the outer platform, and
a clamp mechanism that extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil to couple the inner platform and the outer platform to the ceramic-containing airfoil while maintaining a spaced-apart relationship with the ceramic-containing airfoil so that aerodynamic loads applied to the ceramic-containing airfoil bypass the clamp mechanism, wherein the clamp mechanism includes a perforated impingement tube that extends through the hollow core of the ceramic-containing airfoil to conduct cooling air into the ceramic-containing airfoil.

US Pat. No. 9,945,413

LOCKING FASTENER

Rolls-Royce Corporation, ...

1. A locking fastener comprising:a hollow lock bolt having a drive head formed proximate a first end and external threads formed proximate a second end thereof, the hollow lock bolt further having a relatively smooth internal wall with an angled taper extending along at least a portion thereof, and
a lock stud constructed to engage the hollow lock bolt, the lock stud having a drive head proximate a first end and external threads formed proximate a second end thereof, the lock stud further having a relatively smooth external wall with an angled taper formed along a portion thereof, an angle of the angled taper of the hollow lock bolt and an angle of the angled taper of the lock stud being different from one another,
wherein the locking fastener is configured for clamping a first component between at least a portion of the hollow lock bolt and a second component and the lock stud and the hollow lock bolt are configured so that the drive head of the lock stud extends past an interface between the first component and the second component in an installed condition of the locking fastener, and
wherein the lock stud includes a solid portion and a circumference of the relatively smooth external wall of the lock stud engages a circumference of the relatively smooth internal wall of the hollow lock bolt to cause the solid portion to block fluid communication through the hollow lock bolt in the installed condition of the locking fastener.

US Pat. No. 9,915,151

CMC AIRFOIL WITH COOLING CHANNELS

Rolls-Royce Corporation, ...

1. An airfoil comprising:
a ceramic matrix composite (CMC) body having an inner surface and a strut that define a leading edge chamber and a second
chamber within the CMC body, the leading edge chamber and the second chamber separated by the strut; and

a support piece positioned in the leading edge chamber of the CMC body, the support piece including an interior cavity,
wherein the support piece comprises a channel in a surface of the support piece,
wherein the surface of the support piece is in contact with the inner surface of the CMC body,
wherein the channel and the inner surface of the CMC body define a passageway for a cooling fluid,
wherein the passageway includes a first section and a second section,
wherein the first section of the passageway is configured to guide the cooling fluid in a first direction along a circumference
of the support piece and the second section of the passageway is configured to guide the cooling fluid in a second direction
that is substantially opposite of the first direction, wherein the second direction is also along the circumference of the
support piece, and

wherein the support piece includes an inlet configured to provide the cooling fluid to the passageway, and the inlet is in
communication with the interior cavity included in the support piece.

US Pat. No. 9,747,410

DEVELOPMENT TOOL

Rolls-Royce Corporation, ...

1. A method for iteratively designing a gas turbine engine part, the method comprising, with at least one computing device:
generating a neutral file including information related to an initial design of the gas turbine engine part, wherein the neutral
file is constructed based on a first GUI-generated reusable module and the neutral file comprises data representing user knowledge
relating to the initial design;

conducting an analysis of the initial design using a second GUI-generated reusable module, the data in the neutral file, and
module actions recorded in the second reusable module, wherein the module actions are captured by a program-by-GUI technique;
and

presenting a result of the analysis.

US Pat. No. 9,739,200

COOLING SYSTEMS FOR HIGH MACH APPLICATIONS

Rolls-Royce Corporation, ...

1. A cooling system for an aircraft, comprising:
an air intake;
a first heat exchanger configured to receive air passing into the air intake when the aircraft is operating at Mach speed,
and configured to receive compressed refrigerant from a first compressor at a first pressure;

an evaporator positioned within the aircraft and configured to receive heated air from a compartment within the aircraft;
at least one of an expansion valve and a turbine; and
the compressed refrigerant rejects heat in the first heat exchanger to the air, expands in the at least one of the expansion
valve and the turbine, and receives heat in the evaporator from the heated air;

wherein the at least one of the expansion valve and the turbine further comprise:
a first turbine configured to provide a first power, and output the refrigerant to the first compressor;
a second turbine coupled to the first turbine via a shaft, wherein the second turbine provides a second power to the first
turbine, and output the refrigerant to the first compressor; and

an expansion valve configured to receive refrigerant from the first heat exchanger and expand the refrigerant to provide expanded
refrigerant to the evaporator.

US Pat. No. 9,759,095

GAS TURBINE ENGINE ACCESS PANEL

Rolls-Royce Corporation, ...

12. A method comprising:
rotating a row of removable gas turbine blades to a circumferential position for removing a blade included in the row of removable
gas turbine blades;

opening a nacelle access panel;
compressing an energy member during the opening the nacelle access panel; and
moving while the nacelle access panel is open, the blade toward the nacelle access panel to remove the blade from the row
of removable gas turbine blades, wherein the nacelle access panel is on an inner flow path surface of an aircraft nacelle
which is oriented at an angle relative to a direction of moving the blade, the direction of moving being parallel to an axis
of rotation of the rotatable blade retaining device.

US Pat. No. 9,759,132

GAS TURBINE ENGINE PERFORMANCE SEEKING CONTROL

Rolls-Royce Corporation, ...

1. An apparatus comprising:
an aircraft gas turbine engine controller comprising:
a baseline controller structured to generate a command to affect an operation of an engine,
a delta controller operable to generate an offset command to be summed with the command generated by the baseline controller,
the delta controller comprising:

a module structured to determine a model of engine performance; and
an optimization routine that together determine the offset command,
wherein an objective function of the optimization routine is derived from an output relationship of an observer in which the
states of the output relationship are resolved by assuming the dynamic states in the observer to be in steady state, and

wherein the observer is structured to operate upon a sensitivity relationship determined on the basis of a set of sensitivity
relations defined at a flight condition and arranged as a function of a gas turbine engine pressure, the sensitivity relationship
determined by:

correcting a first condition pressure to a reference pressure;
evaluating the set of sensitivity relations based upon the reference pressure to produce a reference sensitivity relation;
and

adjusting the reference sensitivity relation to a first condition sensitivity relation to create the model of engine performance.

US Pat. No. 9,708,226

METHOD FOR PRODUCING HIGH STRENGTH CERAMIC MATRIX COMPOSITES

Rolls-Royce Corporation, ...

1. A method of making a high strength ceramic matrix composite, the method comprising the steps of:
forming a fiber preform that is either self supporting or is constrained by a tool for subsequent processing, wherein the
fiber preform comprises fibers that each have a diameter and that define a fiber volume;

coating the fiber preform with about 0.1 ?m to about 5 ?m of silicon carbide to form a structural coating on the fibers that
increases the diameters of the fibers and effectively increasing the fiber volume, wherein the method further comprises cleaning
the fiber preform including the fibers after forming the fiber preform and prior to coating the fiber preform to enhance bonding
between the fibers and the structural coating;

coating the structural coating of silicon carbide with about 0.05 ?m to about 2 ?m boron nitride, carbon or other interface
layer to form an interface layer overlying the structural coating; and

coating the interface layer with about 0.2 ?m to about 40 ?m of silicon carbide.

US Pat. No. 9,853,581

LIFING AND PERFORMANCE OPTIMIZATION LIMIT MANAGEMENT FOR TURBINE ENGINE

Rolls-Royce Corporation, ...

1. A control for a turbine engine system comprising a plurality of components including a multi-shaft turbine engine and one
or more electrical machines coupled to the shafts of the turbine engine, the control comprising:
a vehicle manager;
a constraint analyzer to determine applicable component limits based on current operating conditions of the turbine engine
system, wherein each of the component limits defines an operating region in which, if the component limit is exceeded, the
life or safety of the component may be compromised; and

a limit management optimizer to generate a desired operating point and one or more possible operating points for the system
based on the current operating conditions, the applicable component limits, and an optimization objective, wherein the one
or more possible operating points each represents an objective trade-off involving a modification of the optimization objective
to maintain the component limits or a modification of one or more of the component limits;

wherein the limit management optimizer communicates data relating to the desired operating point and the possible operating
points to the vehicle manager, and the vehicle manager selects the desired operating point or one of the possible operating
points based on a trade-off between two or more of performance, efficiency, lifing, reliability, and stability;

wherein the limit management optimizer communicates a control signal to one or more system controllers for the system to achieve
the selected operating point, and wherein the one or more system controllers control the turbine engine system to achieve
the selected operating point in response to the control signal.

US Pat. No. 9,739,157

COOLED CERAMIC MATRIX COMPOSITE AIRFOIL

Rolls-Royce Corporation, ...

1. A ceramic matrix composite airfoil comprising:
a longitudinal shaped laminate core comprising a core wrap formed of a plurality of ceramic composite plies,
a cooling fluid flow network formed of one or more ceramic foam components at least partially positioned around the longitudinal
shaped laminate core;

an airfoil skin formed of a ceramic fiber lamina disposed about the longitudinal shaped laminate core and the cooling fluid
flow network;

a rotatable blade formed from the ceramic composite airfoil;
a blade platform connected to the rotatable blade; and
at least one ceramic foam component positioned within the blade platform,
wherein the at least one ceramic foam component positioned in the blade platform is fluidly connected to the one or more ceramic
foam components positioned around the longitudinal shaped laminate core, and

wherein the at least one ceramic foam component positioned in the blade platform is generally orthogonal to the one or more
ceramic foam components positioned around the longitudinal shaped laminate core.

US Pat. No. 9,759,225

MULTI-PIECE IMPELLER

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a gas turbine engine turbomachinery impeller useful for changing a pressure of a working fluid that flows through the impeller
during operation of a gas turbine engine, the impeller having:

a bladed shell from which extends a plurality of centrifugal blades, the bladed shell having a first end and a second end,
the first end having a smaller radius than the second end, the bladed shell having a shoulder that includes a load bearing
surface;

a backside plate located with the second end and having a protrusion extending toward the first end of the bladed shell and
past the load bearing surface such that the load bearing surface is interposed between an end of the protrusion and the backside
plate; and

a fastener used to secure the protrusion of the backside plate to the bladed shell in which the fastener engages the protrusion
and bears against the load bearing surface,

wherein the backside plate is a cover used to at least partially enclose a cavity on a backside of the bladed shell and a
bearing is disposed within the cavity to rotatingly support the impeller for driven rotation by a shaft.

US Pat. No. 9,726,025

CERAMIC MATRIX COMPOSITE

Rolls-Royce Corporation, ...

1. A ceramic matrix composite comprising:
at least one layer of non-crimped fibers positioned substantially parallel to one another;
an elastic fiber bent around the non-crimped fibers to stitch the non-crimped fibers together, wherein a diameter of the elastic
fiber is less than a diameter of the non-crimped fibers; and

a ceramic matrix deposited around the at least one layer of non-crimped fibers.

US Pat. No. 9,759,082

TURBINE BLADE TRACK ASSEMBLY

Rolls-Royce Corporation, ...

1. An apparatus comprising:
a blade track including a segment portion comprising ceramic matrix composite materials and having a first radially-facing
surface and a second radially-facing surface opposite the first radially-facing surface, wherein the first radially-facing
surface is arcuate;

a first attachment portion comprising ceramic matrix composite materials and extending radially outward from the second surface
and circumferentially between a first circumferentially-facing surface and a second circumferentially-facing surface opposite
the first circumferentially-facing surface, wherein a coupling region of the first attachment portion has a dovetail shaped
cross section, and

a second attachment portion comprising ceramic matrix composite materials and extending radially outward from the second surface
and circumferentially between a third circumferentially-facing surface and a fourth circumferentially-facing surface opposite
the third circumferentially-facing surface, wherein a coupling region of the second attachment portion has a dovetail shaped
cross section,

wherein the second attachment portion is spaced apart axially from the first attachment portion, and
wherein the ceramic matrix composite materials of the second attachment portion include a first reinforcement wrap, a second
reinforcement wrap, a third reinforcement wrap, a fourth reinforcement wrap, a first preform insert, and a second preform
insert, the first reinforcement wrap and the second reinforcement wrap are positioned adjacent one another, first end portions
of the first reinforcement wrap and the second reinforcement wrap are spaced apart from one another, the first preform insert
is positioned between the spaced apart first end portions of the first reinforcement wrap and the second reinforcement wrap,
the third reinforcement wrap and the fourth reinforcement wrap are positioned adjacent one another, first end portions of
the third reinforcement wrap and the fourth reinforcement wrap are spaced apart from one another, and the second preform insert
is positioned between the spaced apart first end portions of the third reinforcement wrap and the fourth reinforcement wrap.

US Pat. No. 9,701,578

REACTIVE MELT INFILTRATED-CERAMIC MATRIX COMPOSITE

Rolls-Royce Corporation, ...

1. A method comprising:
providing a ceramic fiber preform;
coating the ceramic fiber preform with a boron nitride interface coating;
infiltrating the ceramic fiber preform with a ceramic matrix material;
infiltrating the ceramic fiber preform with a constituent material comprising boron carbide, boron, carbon or combinations
thereof; and

infiltrating the ceramic fiber preform with a eutectic melt material.

US Pat. No. 9,689,069

COATING SYSTEM INCLUDING DIFFUSION BARRIER LAYER INCLUDING IRIDIUM AND OXIDE LAYER

Rolls-Royce Corporation, ...

1. An article comprising:
a gas turbine engine disk comprising:
a superalloy substrate that defines at least one fir tree recess; and
a coating on the superalloy substrate, wherein the coating is on a surface of the at least one fir tree recess and not on
a surface of the gas turbine engine disk other than the surface of the at least one fir tree recess, and wherein the coating
comprises:

a diffusion barrier layer on the superalloy substrate, wherein the diffusion barrier layer comprises iridium, and
a wear resistant oxide layer over the diffusion barrier layer, wherein the wear resistant oxide layer comprises silica.

US Pat. No. 10,215,056

TURBINE SHROUD WITH MOVABLE ATTACHMENT FEATURES

Rolls-Royce Corporation, ...

1. A segmented turbine shroud that extends around a central axis, the segmented turbine shroud comprisinga carrier segment that extends partway around the central axis and that forms a radially inwardly-opening cavity,
a blade track segment comprising ceramic-containing materials, the blade track segment formed to include a runner that extends partway around the central axis and a positioner attachment post that extends radially outward from the runner into the radially inwardly-opening cavity of the carrier segment, the positioner attachment post formed to include a track-positioning surface that extends both radially and axially, and
a track attachment system adapted to couple the blade track segment to the carrier segment, and the track attachment system including a positioner coupled to the carrier segment to move axially from a disengaged position out of contact with the positioner attachment post to an engaged position contacting the positioner attachment post to engage the track-positioning surface of the positioner attachment post with a position-setting surface that extends both radially and axially at an angle corresponding to that of the track-positioning surface.

US Pat. No. 10,184,352

TURBINE SHROUD SEGMENT WITH INTEGRATED COOLING AIR DISTRIBUTION SYSTEM

Rolls-Royce North America...

1. A turbine shroud segment adapted for use in a gas turbine engine, the turbine shroud segment comprisinga carrier segment comprising metallic materials, the carrier segment formed to include an attachment-receiving space,
a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend at least partway around a central axis and an attachment box portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment, and
an attachment assembly including an attachment post that extends from the carrier segment into the attachment box portion of the blade track segment, the attachment post formed to include a post passageway that provides part of a cooling system configured to conduct cooling air into the attachment box portion of the blade track segment to cool the blade track segment when the turbine shroud segment is used in a gas turbine engine, wherein the attachment box portion included in the blade track segment defines a box interior bounded by a radially-outwardly facing surface of the runner included in the blade track segment so that cooling air conducted into the box interior by the post passageway cools the radially-outwardly facing surface of the runner, and wherein the box interior defined by the attachment box portion of the blade track segment is open for fluid communication with the attachment-receiving space formed by the carrier segment and the carrier segment is formed to include a plurality of vent holes configured to conduct used cooling air out of the attachment-receiving space.

US Pat. No. 9,828,658

COMPOSITE NIOBIUM-BEARING SUPERALLOYS

Rolls-Royce Corporation, ...

1. A composite niobium bearing alloy consisting of 2.2 to 4 wt. % aluminum, 0.01 to 0.05 wt. % boron, 0.02 to 0.06 wt. % carbon,
6 to 15 wt. % chromium, 0 to 20 wt. % cobalt, 0 to 0.5 wt. % hafnium, 1 to 3 wt. % molybdenum, 8.5 to 15 wt. % niobium, 0
to 0.6 wt % silicon, 1 to 5 wt. % tantalum, 0 to 2.5 wt. % titanium, 1 to 3 wt. % tungsten, 0.04 to 0.1 wt. % zirconium and
the balance nickel and incidental impurities,
wherein the alloy includes globular or acicular delta phase, aluminum containing delta phase, and eta phase precipitates singularly
or in combination, and gamma prime phase precipitates in the gamma phase,

including a lamellar structure of gamma phase and delta phase, gamma prime phase precipitates in the gamma phase, and wherein
the volume percentage of delta phase and eta phase is about 2% to about 40%.

US Pat. No. 9,797,263

MONOLITHIC CERAMIC RODS TO ENABLE COOLING HOLES IN CMC

Rolls-Royce Corporation, ...

1. A method to form a hole in a ceramic matrix composite component, the method comprising:
inserting a monolithic rod into a porous ceramic preform comprising a plurality of ceramic fibers;
forming the ceramic preform into a ceramic matrix composite body, the ceramic matrix composite body including the monolithic
rod; and

removing a first portion of the monolithic rod, wherein a second portion of the monolithic rod remaining in the ceramic matrix
composite body after the first portion is removed includes walls that define an opening in the ceramic matrix composite body.

US Pat. No. 9,765,640

SYSTEM AND METHOD TO MANAGE TRANSIENTS FOR RAPID POWER DEMAND CHANGES

Rolls-Royce Corporation, ...

1. A system comprising:
a gas turbine engine having at least one compressor section and at least one turbine section mounted on at least one spool,
the at least one compressor section being configured to receive an inlet air stream, the gas turbine engine being configured
to operate at an engine power level to satisfy an engine power demand;

at least one generator operatively coupled to the gas turbine engine, the at least one generator being configured to generate
electrical power based at least in part on the engine power demand;

at least one heating element in communication with the at least one generator, the at least one heating element being configured
to receive electrical power from the at least one generator and generate thermal energy; and

at least one control unit coupled to the at least one heating element, the at least one control unit being configured to energize
the at least one heating element during at least one condition of an anticipated increase in the engine power demand;

wherein energizing the at least one heating element occurs a predetermined time frame prior to an actual increase in the engine
power demand when the at least one condition exists.

US Pat. No. 9,829,401

STRAIN GAUGE AND ACCELEROMETER MEASUREMENT FOR THRUST ESTIMATION

Rolls-Royce Corporation, ...

1. A system for estimating thrust from an engine, comprising: a vehicle having a propulsion device that is capable of producing
thrust, said propulsion device is attached by at least one mounting structure; a plurality of strain gauges mounted on said
mounting structure, said strain gauges for producing strain gauge signals indicative of stress; at least one accelerometer
mounted on one of said propulsion device or vehicle, said accelerometer producing a signal indicative of acceleration; and
at least one processor in communication with said plurality of strain gauges and accelerometer for executing instructions
to estimate thrust from strain gauge signals and said acceleration signals, wherein the at least one processor decomposes
the strain gauge signals to arrive at a single strain gauge value or a 3-dimensional strain gauge value.