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. 9,426,843

ELECTRICAL CONNECTORS

ROLLS-ROYCE plc, London ...

1. An electrical raft installed in a gas turbine engine, the electrical raft comprising:
a rigid material having multiple electrical conductors embedded therein; and
an electrical connector comprising a housing that is distinct from and mounted in the rigid material, the housing having a
first end and a second end, with a first set of electrical contacts being at the first end and a second set of electrical
contacts being at the second end, the first set of electrical contacts connected to at least one of the electrical conductors,
and the second set of electrical contacts for electrical connection to a component, wherein:

the electrical raft is installed in the gas turbine engine and has a first major surface separated by a thickness from a second
major surface, the first major surface configured to receive the housing within; and

the electrical connector housing is mounted in the rigid material so as to form a mounting angle in the range of from 20 degrees
to 70 degrees with the first major surface, such that the second set of electrical contacts are accessible from outside the
electrical raft, thereby allowing the electrical raft to be electrically connected to said component.

US Pat. No. 9,699,833

ELECTRONIC UNIT MOUNTING

ROLLS-ROYCE plc, London ...

1. A gas turbine engine comprising:
a nacelle; and
an electrical assembly that comprises:
an electrical raft having a rigid material with at least one electrical conductor embedded therein; and
an electronic unit mounted on the electrical raft and in electrical connection with the electrical raft,
wherein:
the electrical raft is mechanically fixed to a component of the gas turbine engine; and
at least a part of the electronic unit has an external surface that is flush with an external surface of the nacelle and is
exposed to free-stream flow.

US Pat. No. 9,426,844

ELECTRICAL RAFT WITH MAP

ROLLS-ROYCE PLC, London ...

1. A gas turbine engine having an electrical raft, the electrical raft comprising:
components embedded in a rigid material, the components including embedded electrical conductors that form at least a part
of an electrical system of the gas turbine engine, the electrical conductors configured to carry electrical signals for the
gas turbine engine; and

a raft map comprising lines indicating paths of at least some of the embedded electrical conductors within the electrical
raft, the raft map being visible from outside the electrical raft, wherein the electrical raft has at least one outer surface,
on which the raft map is provided.

US Pat. No. 9,148,040

ELECTROMAGNETIC COMPONENT FOR A STATOR SEGMENT OF AN ELECTRICAL MACHINE

ROLLS-ROYCE plc, London ...

1. An electromagnetic stator segment for mounting in a framework so as to provide a separately removable stator segment of
an electrical machine comprising a plurality of modular stator segments, the stator segment comprising:
a magnetic flux guide;
an electrical winding for electromagnetic interaction with the magnetic flux guide;
electrical terminals for connecting the electrical winding to an electrical network;
at least one fluid pathway for receiving a flow of cooling fluid in normal use;
at least one fluid connector for coupling the fluid pathway to a source of cooling fluid; and
a mounting arrangement for cooperating with the framework to mount one or both of the fluid connector and the electrical terminals
to a respective electrical or fluid location point of the electrical machine;

wherein the mounting arrangement comprises a rail or channel, which cooperates in use with a corresponding channel or rail
of the framework.

US Pat. No. 9,562,828

ENGINE HEALTH MONITORING

ROLLS-ROYCE PLC, London ...

1. A raft monitoring system for a vehicle, comprising:
a rigid dressing raft including:
a rigid material;
at least a part of a component or system of the vehicle provided to the rigid material; and
at least one electrically conductive elongate fibre element that is integral to the rigid material,
the raft monitoring system further comprising an electrical measurement circuit electrically connected to the elongate fibre
element so as to supply an electrical current thereto, and configured to determine a resistance of the elongate fibre element,
the determined resistance being representative of at least one property of the rigid dressing raft.

US Pat. No. 9,382,962

VIBRATION DAMPING STRUCTURES

ROLLS-ROYCE plc, London ...

20. A vibration damping body comprising an auxetic cellular structure having cell walls defining a plurality of adjoining
cells therein, said cell walls being formed substantially of a first material having a first stiffness, the cellular structure
further comprising a second material attached to said cell walls, the second material being selectively located throughout
the cellular structure so as to comprise less than 50% by mass thereof and having a second stiffness which is lower than said
first stiffness, wherein
the second material is attached between adjoining cell walls of adjacent cells within the cellular structure.

US Pat. No. 9,200,595

NOSE CONE ASSEMBLY

ROLLS-ROYCE PLC, London ...

1. A nose cone assembly comprising
a nose cone and a support ring, the nose cone is mounted on the support ring;
wherein the support ring comprises a plurality of circumferentially distributed resilient attachment tabs, via which the nose
cone is mounted on the support ring, the support ring further comprises a load spreader, wherein the load spreader comprises
a continuous ring that is coaxial with the support ring, each of the resilient attachment tabs is operably connected to the
load spreader, and wherein each of the resilient attachment tabs is positioned radially outward of the load spreader.

US Pat. No. 9,383,533

PROBING CABLE

ROLLS-ROYCE plc, London ...

1. A probing cable for deployment inside a pipe formation, the cable having a resiliently deformable tip member which extends
from the end of the cable at an angle from the length direction of the cable, the cable including an outer casing with a helical
track configured to allow the cable to screw into the pipe formation.

US Pat. No. 9,097,132

GAS TURBINE ENGINE

ROLLS-ROYCE PLC, London ...

1. A gas turbine engine comprising:
an engine axis;
a first component and a second component, wherein the first component is rotatable relative to the second component about
the engine axis; and

a signal transmission system including
a signal transmitter mounted on one of the components,
a signal receiver mounted on the other of the components, and
a waveguide cavity: i) that forms a separate enclosed environment provided by a propagation channel that constrains therein
signal transmission between the signal transmitter and the signal receiver, ii) at least part of which is centered on the
engine axis, and iii) that is annular about the engine axis, wherein the waveguide cavity is formed of at least two elongate
sections disposed end to end, the elongate sections, or at least two of the elongate sections, being rotatable relatively
to each other the engine axis; and

at least one rotating choke coupled to the waveguide cavity, wherein the rotating choke is a rotatable choke joint, and the
relatively rotatable elongate sections are coupled to each other at the rotatable choke joint.

US Pat. No. 9,260,785

INSPECTION OF A COMPONENT

ROLLS-ROYCE plc, London ...

1. A method of manufacturing a component, comprising:
applying a cladding layer to a substrate by a cladding process, thereby forming the component: and
inspecting the component comprising the cladding layer bonded to the substrate, the inspecting comprising:
recording a first image of an inspection portion of the cladding layer, the inspection portion having a pattern of markings;
causing or allowing a temperature change in the component;
recording a second image of the inspection portion; and
identifying a deformation of the pattern of markings on the inspection portion by reference to relative movement of the respective
markings between the first image and the second image,

wherein the steps of applying the cladding layer and inspecting the compartment are applied concurrently to adjacent portions
of the component.

US Pat. No. 9,260,980

ROTATING FLUID PUMPING SYSTEM

ROLLS-ROYCE plc, London ...

1. A gas turbine engine oil scavenge mechanism comprising a first rotor assembly rotatable about a rotational axis, the first
rotor assembly having: a fluid pathway, and a pump for driving oil along the fluid pathway, wherein the fluid pathway and
the pump are separate elements, the fluid pathway and the pump are in fluid communication, the fluid pathway and the pump
are provided in the first rotor assembly and together form a cycle that allows the driving oil to be scavenged and returned,
and the cycle resides entirely within the first rotor assembly and the cycle rotates entirely about the rotational axis with
the first rotor assembly.

US Pat. No. 9,228,741

LIQUID FUEL SWIRLER

Rolls-Royce plc, (GB)

1. An injector for producing an atomized spray of liquid comprising: a) an annular injector body; b) a first annular flow
directing body mounted inboard of the injector body, the first flow directing body including an inboard surface and opposed
outboard surface, wherein a plurality of flow channels are defined in the outboard surface of the first flow directing body
for conducting fluids flowing through the first flow directing body, wherein each flow channel includes a channel floor spaced
apart from the outboard surface and a sidewall extending from the channel floor to the outboard surface of the first flow
directing body, and wherein a swirl port extends through the sidewall of each flow channel and though the first flow directing
body to the inboard surface thereof; and c) a second annular flow directing body mounted radially inboard of the first flow
directing body and including an outboard surface with an annular swirl chamber defined therein for receiving liquid from the
swirl ports of the first flow directing body to form a swirling sheet of liquid for atomization downstream of the second flow
directing body.

US Pat. No. 9,085,992

TURBOMACHINE CASING ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A turbomachine casing assembly, comprising:
one or more rotating aerofoil elements of a turbomachine, having an axis of rotation;
a first casing element located radially outward of the one or more rotating aerofoil elements, and having a first, forward,
end;

a second casing element located radially distal to the first casing element, and having a first, forward, end; and
a void, provided between the first casing element and the second casing element, at the first end of the first casing element;
each of the first and second casing elements comprising, at the first end thereof, respective co-operating second and first
interface portions;

whereby upon failure of one of the rotating aerofoil elements, the second interface portion slides along the first interface
portion and the first end of the first casing element enters the void; wherein

the first casing element comprises a rack disposed at a second end thereof, the second casing element comprises a corresponding
pawl disposed at a second end thereof, and wherein in use the pawl engages with the rack to allow uni-directional movement
of the first casing element along the axis of rotation.

US Pat. No. 9,302,765

VARIABLE PITCH PROPELLER ROTOR

ROLLS-ROYCE plc, London ...

1. A variable pitch bladed rotor comprising a rotor body carrying a plurality of blades, each blade having a blade root supported
by bearings in a blade hub of the rotor body so as to be pivotable relative to the rotor body about respective spanwise pitch
axes, each blade being drivably coupled to a pitch control mechanism by a respective pitch input shaft which is aligned with
the pitch axis and which is drivingly connected to the blade by a harmonic drive reduction gear, the harmonic drive reduction
gear comprising a circular spline in toothed engagement with a flex spline and a wave generator arranged to generate a travelling
wave in the flex spline, wherein the circular spline is fixedly mounted on the blade hub and the flex spline is secured to
the blade root.

US Pat. No. 9,266,617

PROPULSIVE SYSTEM

ROLLS-ROYCE plc, London ...

1. An aircraft comprising:
a first propulsive unit including:
a first fan having a first axis of rotation, the first fan including a duct having an inlet and an outlet, the duct of the
first enclosing a plurality of blades of the first fan between the inlet and the outlet of the first fan, and

a first drive configured to drive rotation of the first fan; and
a second propulsive unit including:
a second fan having a second axis of rotation, the second fan including a duct having an inlet and an outlet, the duct of
the second fan enclosing a plurality of blades of the second fan between the inlet and the outlet of the second fan, and

a second configured to drive rotation of the second fan, wherein:
the rotational axis of the first fan is proximate to a surface of the aircraft relative to the rotational axis of the second
fan such that the first fan receives boundary layer air, and

the second fan is arranged to receive free stream air, and the second fan is located so as to receive an airflow including
accelerated boundary layer air exhausted from the outlet of the first fan at a position upstream of the outlet of the second
fan.

US Pat. No. 9,217,186

ALLOY STEEL

ROLLS-ROYCE PLC, London ...

1. A turbine shaft comprising an alloy steel consisting essentially of the following composition: Ni 5-9 wt %; Cr 8-12 wt
%; Co 7-10 wt %; Mo 2-4 wt %; W 2-3 wt %; Ti<0.01 wt %; Al 1-2.5 wt %; the balance being Fe save for incidental impurities.

US Pat. No. 9,470,262

BEARING ARRANGEMENT AND METHOD

ROLLS-ROYCE plc, London ...

1. A bearing arrangement comprising:
a first thrust bearing and a second thrust bearing, each of the first thrust bearing and the second thrust bearing including:
an inner race disposed on a shaft; and
an outer race supported by at least one resilient element, wherein:
applying a shaft thrust load elastically deforms the at least one resilient element of the respective outer races of the first
thrust bearing and the second thrust bearing so as to axially displace the respective outer races of the first thrust bearing
and the second thrust bearing such that the shaft thrust load is shared between the first thrust bearing and the second thrust
bearing;

when in an undeformed condition, each of the resilient elements is within a projected axial length of the respective first
thrust bearing and second thrust bearing; and

when in an elastically deformed condition, each of the resilient elements extends beyond the projected axial length of the
respective first thrust bearing and second thrust bearing.

US Pat. No. 9,410,431

NOSE CONE ASSEMBLY

ROLLS-ROYCE PLC, London ...

1. A nose cone assembly comprising:
a nose cone having an apex; and
a support ring, the support ring comprises:
an annular main body; and
an annular attachment flange projecting from the annular main body, the annular main body having a portion extending radially
inwardly from a base of the annular attachment flange,

the annular attachment flange terminating in a plurality of circumferentially spaced attachment tabs, wherein the annular
attachment flange forms with the annular main body a cross-section having at least two C shaped curves,

the annular attachment flange has a first portion extending radially and axially away from the annular main body towards the
apex of the nose cone, the annular attachment flange has a second portion extending radially with respect to the annular main
body, the annular attachment flange has a third portion extending radially and axially away from the annular main body towards
the apex of the nose cone, wherein the annular attachment flange forms with the annular main body a cross-section having at
least two C shaped curves, a first C shaped curve is formed between a radially inner end of the second portion of the annular
attachment flange and the base of the annular attachment flange, a second C shaped curve is formed between a radially outer
end of the second portion of the annular attachment flange and a base region of the attachment tabs, and

wherein the nose cone is mounted on the plurality of attachment tabs of the support ring.

US Pat. No. 9,352,412

METHOD OF FORMING A BONDED ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A method of forming a bonded assembly, the method comprising:
providing at least first and second parts of an assembly to be bonded;
assembling the first and second parts in a required relative position to define a bond interface region therebetween;
sealing part way along an edge of the bond interface region using laser beam welding to define a cavity between the first
and second parts;

in a vacuum environment, sealing the remainder of the edge of the bond interface region using electron beam welding to form
a fluid tight seal around the cavity; and

applying heat and pressure to an external surface of the cavity to diffusion bond the first and second parts together.

US Pat. No. 9,328,662

GAS TURBINE ENGINE NACELLE HAVING A SYMMETRIC FLOWPATH

ROLLS-ROYCE plc, London ...

1. A nacelle for a gas turbine engine, the nacelle comprising:
an intake portion at an upstream end of the nacelle, the intake portion having in flow series,
an intake lip, and
a diffuser;
an exhaust portion at a downstream end of the nacelle, wherein
the intake lip has a highlight which is a closed loop defining a boundary between an inner surface of the intake lip and an
outer surface of the intake lip at which a tangent to the inner surface is coincident with a tangent to the outer surface;

the highlight lies in a highlight surface which is either planar or curved in only one principal direction; and
at each of one or more, but not all, positions on the highlight and in a respective longitudinal section through the nacelle,
one portion of the intake lip crosses a tangent to the highlight surface at that position on the highlight and surfaces of
the intake lip neighbouring the one portion of the intake lip are adjusted to provide smoothly blended surfaces.

US Pat. No. 9,206,706

TURBOMACHINE CASING ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A turbomachine casing assembly, comprising:
a first casing element located radially outward of one or more rotating aerofoil elements of a turbomachine;
a second casing element located radially outward of the first casing element; and
a void, provided between the first casing element and the second casing element, at a first end of the first casing element;
wherein

the first end of the first casing element is located against a corresponding first end of the second casing element by a plurality
of resilient leaf elements, the leaf elements being biased towards a radially proximal face of the first casing element,

the first casing element comprises a cantilever, the cantilever being arranged in a region extending along the first casing
element from the first end of the first casing element and having a pivot axis at a mid portion of the first casing element,
and

the first casing element comprises an infill element disposed between the radially proximal face and a distal face of the
first casing element, and the plurality of leaf elements are each bonded to a first end of the infill element,

whereby upon release of one of the rotating aerofoil elements, the cantilever bends into the void provided between the first
and second casing elements, which causes the resilient leaf elements to deform and to thereby absorb at least some of the
impact energy resulting from the released rotating aerofoil element.

US Pat. No. 9,200,535

AEROFOIL BLADE OR VANE

ROLLS-ROYCE plc, London ...

1. An aerofoil blade or vane for the turbine of a gas turbine engine, the blade or vane including:
an aerofoil body comprising a base end, a trailing edge, a leading edge and an internal space and which, in use, extends radially
across a working gas annulus of the engine, a coolant inlet being formed at the base end of the aerofoil body for entry of
a flow of cooling air into the internal space, a corresponding coolant exhaust being formed at the trailing edge of the aerofoil
body for the flow of spent cooling air from the internal space, and a passage within the internal space determining the route
of cooling air and connecting the inlet to the exhaust,

a first wall of the passage comprising a fence within the internal space, the fence extending at an acute angle to a radial
line at the trailing edge from a start position at the base end of the aerofoil body adjacent the trailing edge to an end
position in a mid-region of the internal space, and

a second wall of the passage extending around the fence at an acute angle to the radial line at the trailing edge, the second
wall extending substantially parallel to the fence from a start position at the base end of the aerofoil body on a first side
of the fence to the mid-region of the internal space, and extending substantially parallel to the fence from the mid-region
to an end position on a second side of the fence, the end position of the second wall being adjacent the base end and the
trailing edge,

wherein the passage loops around the fence thereby routing cooling air from the inlet first towards the leading edge of the
aerofoil body and then turning the cooling air back towards the trailing edge exhaust.

US Pat. No. 9,188,018

FLAP SEAL AND SEALING APPARATUS

ROLLS-ROYCE PLC, London ...

2. A turbine comprising:
a plurality of structural components with a first gap between said structural components;
a plurality of sealing components sealing the first gap, the plurality of sealing components comprising
a plurality of primary sealing components, and
at least one sealing plate, each of the at least one sealing plate being arranged for sealing a second gap between a pair
of the plurality of primary sealing components, the at least one sealing plate having a sealing portion and a connection portion,
wherein:

the sealing portion has a width that is greater than a width of the connection portion;
the plurality of primary sealing components seal a majority of the first gap, with the second gap being present between each
pair of the plurality of primary sealing components to allow for expansion or movement of said plurality of primary sealing
components; and

the sealing portion of the sealing plate seals the second gap between the pair of the plurality of primary sealing components.

US Pat. No. 9,169,777

GAS TURBINE ENGINE WITH WATER AND STEAM INJECTION

ROLLS-ROYCE plc, London ...

1. A method of operating a gas turbine engine having in flow series:
a compressor section,
a combustor, and
a turbine section;
wherein the method includes the steps of:
during an engine start-up period, delivering liquid water to the combustor and mixing the delivered water in a liquid state
with working gas in the combustor, and

after the start-up period,
i) shutting off the liquid water supply to the combustor, and
ii) delivering steam to the combustor and mixing the delivered steam in a gaseous state with the working gas in the combustor,
wherein the engine start-up period is defined by the time taken for a steam generator to reach an operational pressure at
which the steam generator is able to supply steam to the combustor; and

wherein, after the start-up period, continuously delivering the steam to the combustor.

US Pat. No. 9,097,140

CAVITY VENTILATION

ROLLS-ROYCE PLC, London ...

1. A ventilation arrangement for a substantially annular cavity located about a core engine of a gas turbine, the annular
cavity having an inner wall located about the core engine and an outer wall radially spaced from the inner wall, the outer
wall being interposed between the cavity and an engine bypass duct, the ventilation arrangement comprising:
one or more ventilation ducts passing through said outer wall so as to allow fluid communication between the bypass duct and
the cavity; and,

a flow diverter arranged at an oblique angle to the outer wall, the flow diverter having a flow exit opening that is separated
from the outer wall such that the flow diverter is configured to induce, in the ventilation flow from the ventilation ducts,
a vortical flow within the cavity about the inner wall, the vortical flow having a vortex width of magnitude substantially
equal to that of a diameter of the annular cavity.

US Pat. No. 9,267,688

HEAD PART OF AN ANNULAR COMBUSTION CHAMBER

ROLLS-ROYCE plc, London ...

14. A method of installing a burner collar of a head part of an annular combustion chamber for a gas turbine, the head part
comprising:
an end wall with a passage opening for accommodating a burner;
the burner collar adapted to fit within the passage opening and receive the burner, the burner collar comprising a protruding
portion radially protruding from an outer surface of the burner collar; and

a ring member in contact with the protruding portion of the burner collar on a back side surface of the ring member wherein
the back side surface faces the combustion chamber;

wherein the method comprises;
engaging the back side of the end wall in direct contact with a radially outer portion of the ring member; and
engaging the protruding portion of the burner collar in direct contact on a radially inner portion of the ring member, the
radially inner portion of the ring member being set back in a direction away from the combustion chamber from the radially
outer portion of the ring member with respect to the back side of the end wall.

US Pat. No. 9,249,729

TURBINE COMPONENT COOLING WITH CLOSED LOOPED CONTROL OF COOLANT FLOW

ROLLS-ROYCE plc, London ...

1. A gas turbine engine having, in flow series, a compressor section, a combustor, and a turbine section, and further having:
a cooling system which diverts an air flow received from the compressor section to a heat exchanger and then to the turbine
section to cool a component thereof, the air flow by-passing the combustor and being cooled in the heat exchanger, and the
cooling system having a valve arrangement which regulates the air flow downstream of the heat exchanger; and

a closed-loop controller apparatus operable to control operation of the valve arrangement by sending for a current time step
of a series of time steps, a current demand signal, the closed-loop controller comprising:

at least one sensor for monitoring a real-time parameter of the component over the series of time steps,
a processor for calculating a demand signal at each time step to operate the valve arrangement to control the air flow,
a memory for storing one or more most recent demand signals calculated at the most recent in the series of time steps,
the processor configured for determining an error between a pre-defined target parameter and the real-time parameter sensed
at the current time step and determining the current demand signal to cause the valve arrangement to control the air flow
to address the error, wherein the step of determining the current demand signal involves a calculation using, the error and
a most recent demand signal of the one or more most recent demand signals stored in the memory of the controller.

US Pat. No. 9,228,495

VORTEX REDUCER

ROLLS-ROYCE plc, London ...

1. A vortex reducer for a bleed flow in an axial turbomachine comprising a rotor disc, the vortex reducer comprising:
one or more guide channels arrangeable adjacent to a first side of the rotor disc to at least partially de-swirl the bleed
flow;

a passage connectable to a high pressure flow source, the passage being adapted to provide a secondary flow from the high
pressure flow source to mix with the bleed flow on the first side of the rotor disc, wherein

the one or more guide channels are each defined by one or more guide portions adapted to guide and at least partially de-swirl
the bleed flow, and

an outlet of the passage is provided in a further channel provided within the guide portions.

US Pat. No. 9,121,350

SEAL ARRANGEMENT AND A METHOD OF REPAIRING A SEAL ARRANGEMENT

ROLLS-ROYCE PLC, London ...

1. A method of repairing a seal arrangement between a first component and a second component, a fluoropolymer seal member
is positioned between the first component and the second component, the method comprising the steps of:—
(a) disassembling the seal arrangement,
(b) removing the fluoropolymer seal member from between the first component and the second component,
(c) removing corroded material from the first component, and
(d) positioning a first protecting member between the fluoropolymer seal member and the first component, the first protecting
member consisting of a polymer and hydroxyapatite or apatite,

wherein the first component comprises a metal wherein the first component has a first recess and the fluoropolymer seal is
positioned in the recess, step (c) comprises increasing a depth of the first recess in the first component and step (d) comprises
positioning the first protecting member in the first recess such that the first protecting member is between the fluoropolymer
seal member and the first component.

US Pat. No. 9,329,377

BOROSCOPE AND A METHOD OF PROCESSING A COMPONENT WITHIN AN ASSEMBLED APPARATUS USING A BOROSCOPE

ROLLS-ROYCE plc, London ...

1. A boroscope comprising:
a tube of the boroscope including:
a first end of the tube of the boroscope including an end of an optical fiber and a light source, and
a second end of the tube of the boroscope opposite of the first end of the tube of the boroscope;
a working head removably attached to the first end of the tube of the boroscope, the working head including:
a first portion configured to be attached to the first end of the tube of the boroscope,
a second portion opposite of the first portion, and
an electrical motor secured to the second portion of the working head;
a tool attached to the electrical motor, the tool being configured to be driven by the electrical motor; and
an electrical cable extending from the electrical motor to the second end of the tube of the boroscope.

US Pat. No. 9,322,332

INSPECTION DEVICE FOR AN INTERNAL COMBUSTION ENGINE

ROLLS-ROYCE plc, London ...

1. An internal combustion engine having a cavity for inspection, comprising:
an inspection device mounted within a housing, the housing at least partially located adjacent the cavity to be inspected
and having a shutter which is actuable between a closed configuration and an open configuration, wherein the inspection device
is retractable between a stowed position and an inspection position; and

an actuation mechanism for moving the shutter between the closed configuration and the open configuration, wherein the shutter
is configured to be actuated by the inspection device when the inspection device is moved between the stowed and inspection
positions.

US Pat. No. 9,239,011

METHOD OF INHIBITING ICE ACCRETION WITHIN A TURBINE ENGINE AND CONTROL SYSTEM THEREFOR

ROLLS-ROYCE plc, London ...

1. A method of inhibiting ice accretion within a turbine engine having a fan and a compressor wherein the fan provides a majority
of thrust of the turbine engine, the method comprising the steps:
operating the fan at a predetermined rotational velocity; and
driving the compressor of the turbine engine at an elevated rotational velocity which is greater than a nominal rotational
velocity of the compressor at the predetermined rotational velocity of the fan so as to inhibit ice accretion within the compressor,
wherein the predetermined rotational velocity of the fan is maintained when the compressor is driven at the elevated rotational
velocity, and wherein the compressor of the turbine engine is driven at the elevated rotational velocity using power provided
from a power supply external to the turbine engine.

US Pat. No. 9,184,591

ELECTRICAL SYSTEM

ROLLS-ROYCE PLC, London ...

1. A multiple phase electrical system, comprising:
a first and a second electrical lane, each lane having a generator and a load connected by a bus system, and a rectifier between
the generator and load;

a transformer connected between the two lanes, the transformer having a plurality of power windings across each of which corresponding
phases of the first and second lanes are connected, and a plurality of phase shift windings, each power winding being electrically
shorter than each phase shift winding; and

a filter provided between mid-points of the power windings to remove higher order harmonic currents, the filter having a plurality
of filter branches, each filter branch corresponding to one of the phases, and each filter branch having a first end directly
connected to a mid-point of a respective one of the power windings so as to be center-tapped to the respective one of the
power windings and having a second opposite end directly connected to a common coupling point of the plurality of filter branches.

US Pat. No. 9,266,290

METHOD OF FORMING AN ARTICLE

ROLLS-ROYCE plc, London ...

1. A method of forming an article from a composite material, the composite material provided in sheet form and comprising
a plurality of tows embedded within a matrix material and arranged widthwise across the sheet, each of a plurality of tows
comprising a plurality of filaments, the filaments extending continuously lengthwise along the composite material, the method
comprising steps of:
a. selectively perforating the composite material to split, slit or sever at least one, but not all, of the filaments of each
of one or more of the plurality of tows;

b. exerting a force on an upper surface of the composite material in a direction substantially normal to a plane of the composite
material thereby extending each of the one or more partially split, slit, or severed tows, and deforming the one or more extended
tows out of the plane of the composite material, a degree of perforation being chosen to result in a pre-determined extension,
the force being exerted by applying a suction force across an area of the composite material, the area corresponding to a
three-dimensionally shaped former;

c. placing a surface of the composite material into contact with the three-dimensionally shaped former, such that each of
the extended tows conforms to a respective lengthwise surface profile of the former to form a shaped body; and

d. curing the shaped body to form the article.

US Pat. No. 9,243,654

PANEL ATTACHMENT SYSTEM

ROLLS-ROYCE plc, London ...

1. A gas turbine engine exhaust panel attachment system, comprising:
a panel;
a casing substantially parallel to the panel;
a centre mount fixedly connecting the panel and the casing so as to maintain the positional arrangement of the panel and the
casing by preventing all relative movement between the panel and the casing at the centre mount; and

a plurality of panel attachment devices, each of the panel attachment devices comprising:
a first bracket;
a second bracket; and
a link having a first end and an opposite second end, the first end being removably connected to the first bracket, the second
end being removably connected to the second bracket, and each of the first end and the second end being located by, and rotatable
relative to, the first bracket and the second bracket, respectively, wherein:

each of the first brackets of the plurality of panel attachment devices is fixedly connected to the panel, and
each of the second brackets of the plurality of panel attachment devices is fixedly connected to the casing.

US Pat. No. 9,228,444

ANNULUS FILLER

ROLLS-ROYCE plc, London ...

1. A rotor assembly for a gas turbine engine, the rotor assembly comprising:
a disc supporting a plurality of radially extending blades,
the blades defining passages between their circumferentially-facing surfaces and each of these passages having an annulus
filler assembly; and

the annulus filler assembly comprising at least two bodies and a brace,
each of the bodies being mounted to one of adjacent said blades and the brace occupying a position centrally of the at least
two bodies,

each of the bodies and the brace interacting with one another to form an airwash surface,
the interaction of the brace with at least one said body forming a floating and moveable seal,
the seal having a lip arranged to overlap a co-operating feature, and
the feature having a radially outer opposing wall and a radially inner opposing wall to define a slot by way of a radial gap
between the opposing walls and the lip being located centrally therebetween so as to be within the slot and movable relative
to the opposing walls.

US Pat. No. 9,182,311

ROTOR BALANCING METHOD

ROLLS-ROYCE PLC, London ...

1. A method for balancing a physical rotor, the method comprising the steps of:
determining a first balance state of the physical rotor;
identifying one or more balance zones on a surface of the physical rotor;
providing a computerised simulation of the physical rotor having the first balance state;
providing a first test mass in a first test location within one of the balance zones on the physical rotor simulation;
determining a second balance state of the physical rotor simulation;
providing at least one subsequent test mass in at least one subsequent test location within a balance zone on the physical
rotor simulation and determining at least one subsequent balance state of the physical rotor simulation;

selecting a mass and location from one of the first and subsequent test masses and test locations which provides a predetermined
balance state; and

performing a material deposition process to add the selected mass of material to the selected location on the physical rotor,
the selected mass being formed of a plurality of progressively smaller segments fused to the selected location on the physical
rotor.

US Pat. No. 9,453,416

AEROFOILS

ROLLS-ROYCE plc, London ...

1. An aerofoil having a leading edge point within a leading edge region and a pressure surface with a profile, wherein
within the leading edge region, the pressure surface profile has a local minimum of curvature, and
the leading edge region extends along a fraction of a length of the pressure surface from the leading edge point, the fraction
being less than 0.05 of the length of the pressure surface Sp.

US Pat. No. 9,306,656

WIRELESS SIGNAL PROPAGATION APPARATUS

ROLLS-ROYCE plc, London ...

1. Apparatus for propagation of a wireless signal through a barrier, the apparatus comprising:
a first antenna for location on a first side of the barrier,
a second antenna for location on a second side of the barrier, and
a waveguide, the waveguide comprising a conducting member arranged to pass through said barrier between the first and second
sides, the conducting member being held spaced from a surrounding metal wall of the waveguide, the conducting member having
a first end portion arranged to terminate on the first side of the barrier, a second end portion arranged to terminate on
the second side of the barrier and an intermediate portion therebetween, wherein the first and second end portions are integral
with the respective first and second antennas, wherein the first and second end portions protrude beyond the surrounding metal
wall and provide the respective first and second antennas, whereby in use a wireless signal received by the waveguide on the
first side of the barrier is transmitted along the waveguide and radiated on the second side.

US Pat. No. 9,243,513

FLUID IMPINGEMENT ARRANGEMENT

ROLLS-ROYCE PLC, London ...

1. A gas turbine engine comprising:
a fluid impingement arrangement including:
a supply manifold;
at least one nozzle exit arranged as a Coanda surface having a restriction, the at least one nozzle exit being coupled to
the supply manifold, wherein the Coanda surface includes a curved surface from upstream of the restriction to a downstream
end of the nozzle exit, and wherein the at least one nozzle exit impinges fluid on a wall of the gas turbine engine; and

at least one static pressure tapping that directly cross-connects two regions of the at least one nozzle exit at the restriction
such that passive oscillation is induced in a fluid jet passing through the nozzle exit.

US Pat. No. 9,239,167

LEAN BURN INJECTORS HAVING MULTIPLE PILOT CIRCUITS

Rolls-Royce plc, London ...

1. A fuel injector for a gas turbine engine comprising:
a) a nozzle body defining a central axis and having three fuel circuits comprising a main fuel circuit having a main fuel
inlet, a primary pilot fuel circuit having a primary pilot fuel inlet and a secondary pilot fuel circuit having a secondary
pilot fuel inlet, wherein the main fuel circuit includes a pre-filming air-blast atomizer;

b) an air circuit formed within the nozzle body inboard of the main fuel circuit;
c) a primary pilot fuel circuit formed within the nozzle body inboard of the air circuit;
d) a secondary pilot fuel circuit formed within the nozzle body inboard of the air circuit and outboard of the primary pilot
fuel circuit, wherein the primary pilot fuel circuit is configured and adapted to have a lower flow number than the secondary
pilot fuel circuit; and

e) a pilot air circuit inboard of the secondary pilot fuel circuit, wherein the primary pilot fuel circuit is inboard of the
pilot air circuit.

US Pat. No. 9,133,731

JOINT ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A joint assembly comprising:
a first gas turbine engine casing having a first flange and a second gas turbine engine casing having a second flange,
the first and second flanges extending parallel to each other,
the first flange having a plurality of first apertures extending there-through,
the second flange having a plurality of second apertures extending there-through, and
the second apertures in the second flange being aligned with the first apertures in the first flange;
a plurality of bolts and a plurality of nuts, each bolt extending through a respective first aperture in the first flange
and a respective second aperture in the second flange, and each nut being secured on a respective one of the bolts; and

at least one collar,
the at least one collar being arranged around a shank of one of the bolts,
the at least one collar being arranged between one of the flanges and the respective nut or between one of the flanges and
a head of the respective bolt, and

the at least one collar comprising a first member and a second member,
the second member being thicker than a mid portion of the first member,
the second member being arranged at a first end of the first member,
the first member of the collar being annular,
the second member having a first radially inner end, a second radially inner end and a radially outer mid portion,
the second member between the first radially inner end and the second radially inner end being a unitary monolithic annular
member and being substantially U-shaped or V-shaped in cross-section,

the second member defining an axial space between the first radially inner end and the second radially inner end of the second
member, and

the first member and the second member are structured such that, when a crushing load is applied, the first radially inner
end abuts the second radially inner end before the first member is crushed.

US Pat. No. 9,074,817

FLUIDISED BED TREATMENT

ROLLS-ROYCE PLC, London ...

1. A process for treating a treatment part of a component, the component having the treatment part and a non-treatment part,
the process comprising:
providing a treatment chamber having a bed of powder;
flowing a fluidising gas into the treatment chamber from a fluidising gas inlet to fluidise the bed of powder;
preventing loss of powder from the fluidised bed of powder entrained in the fluidising gas by providing a powder screen between
the treatment chamber and a fluidising gas outlet from which the fluidising gas is removed from the treatment chamber; and

moving the treatment chamber with respect to a source of pressurized fluidizing gas;
moving the treatment chamber to surround only the treatment part of the component;
contacting only the treatment part of the component with the fluidised bed of powder to treat the treatment part of the component;
wherein:
the fluidising gas inlet is supplied with the fluidising gas via a fluidising gas inlet conduit, and
the fluidising gas inlet conduit is connected to the source of pressurised fluidising gas.

US Pat. No. 9,273,782

LEAF SEAL

ROLLS-ROYCE plc, London ...

1. A leaf seal for effecting a seal between two, coaxial, relatively rotating components, the leaf seal having an annular
pack of stacked leaves, the pack being mountable to a first one of the components with interleaf gaps formed between working
portions of neighboring leaves and the leaves extending towards the other component such that end edges at ends of the leaf
working portions are presented for wiping contact with the other component and, in use, a pressure drop is maintained axially
across the pack;
wherein the end edge at the end of the leaf working portions of each leaf has a rear section at or adjacent a low pressure
side of the pack and a front section that extends from the rear section to a high pressure side of the pack, the rear sections
of the leaves being thicker than their respective front sections to reduce the interleaf gaps at the rear sections such that
most of the pressure drop across the pack is over the rear sections.

US Pat. No. 9,222,368

TURBOMACHINE CASING ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A turbomachine casing assembly, comprising:
a first casing element located radially outward of one or more rotating aerofoil elements of a turbomachine;
a second casing element located radially outward of the first casing element; and
a void, provided between the first casing element and the second casing element, at a first end of the first casing element,
a radially distal face of the first casing element being angled relative to a radially proximal face of the second casing
element, such that the void is provided therebetween, wherein

the first end of the first casing element is located against a corresponding first end of the second casing element by an
energy absorbing element,

the first casing element comprises a cantilever, the cantilever being arranged in a region extending along the first casing
element from the first end and having a pivot axis at a mid portion of the first casing element,

the radially distal face of the first casing element comprises a slit, the slit being disposed along the cantilever pivot
axis on the radially distal face of the first casing element and extending substantially through a core of the first casino
element, the slit comprising a plurality of apertures extending linearly along the cantilever pivot axis on the radially distal
face of the first casing element,

upon release of one of the rotating aerofoil elements, the cantilever bends into the void provided between the first and second
casing elements, which causes the energy absorbing element to deform and to thereby absorb at least some of the impact energy
resulting from the released rotating aerofoil element,

the second casing element comprises a rack disposed at the first end thereof, and the first casing element comprises a pawl
disposed at the first end thereof, and

in use, the pawl engages with the rack to allow radially outward, unidirectional movement of the first casing element relative
to the second casing element.

US Pat. No. 9,085,057

FIXTURE FOR SECURING A THIN-WALLED COMPONENT

ROLLS-ROYCE plc, London ...

1. A fixture for securing a thin-walled component, the fixture including:
a support having one or more securing devices for securing the component to the support, and
an inflatable pressure element which, in use, is positioned within the secured component and is adapted to press outwardly,
when inflated, against a flexible liner, the flexible liner being adapted to fit between the pressure element and an inner
thin wall of the component,

wherein the fixture has one or more elastic members that comprise an elastomeric material and which bias the liner against
the outward expansion of the inflated pressure element and the inflated pressure element and the liner damp vibrations in
the component during machining of an outer side of the thin wall, and

wherein the liner has slits between portions which assist the liner to collapse with the pressure element when the pressure
element is deflated.

US Pat. No. 9,366,260

SPOOL FOR TURBO MACHINERY

ROLLS-ROYCE plc, London ...

1. A spool for turbo machinery and having at least one turbine, the spool comprising:
a common shaft;
a fluid flow path defined by an axial compressor stage adjacent to a mixed flow compressor stage, the axial compressor stage
and the mixed flow compressor stage being mounted to the common shaft, and the axial compressor stage and the mixed flow compressor
stage being rotatable about a common axis, wherein

the axial compressor stage and the mixed flow compressor stage are both driven by the at least one turbine.

US Pat. No. 9,163,728

STRIP SEALS

ROLLS-ROYCE plc, London ...

1. A strip seal for providing a seal between opposed faces of adjacent components, the opposed faces of the components each
having formed therein a first groove and a second groove angled with respect to and intersecting the first groove, the grooves
of respective components being opposed to one another when the components are assembled, the strip seal comprising:
a first strip section to span between and be received in the opposed first grooves; and
a second strip section to span between and be received in the opposed second grooves;
wherein one end of the first strip section is arranged to butt against the second strip section at the intersection of the
grooves, the other end of the first strip section having at least one deformable projection that can engage the end of the
first groove, whereby the projection can deform as it engages the end of the groove to urge said one end of the first strip
section against the second strip section.

US Pat. No. 9,074,476

NICKEL ALLOY

ROLLS-ROYCE plc, London ...

1. A nickel-base alloy having the following composition (in weight percent unless otherwise stated):
Cr 13.8-14.7; Co 3.5-4.6; Fe 8.0-9.2; Si 0.5-0.6; Mn 0.0-0.95; Mo 2.1-2.3; W 2.7-3.0; Al 2.2-2.8; Nb 5.4-5.7; Ti 0.00-0.85;
Ta 1.95-3.25; Hf 0.0-0.5; C 0.01-0.05; B 0.02-0.04; Zr 0.04-0.06; Mg 0.015-0.025; S<50 ppm; P<50 ppm; the balance being Ni
and incidental impurities.

US Pat. No. 9,338,830

RAFT ASSEMBLY

ROLLS-ROYCE plc, London ...

1. An electrical raft assembly for a gas turbine engine, the electrical raft assembly comprising:
a rigid raft formed of a rigid material that has an electrical system comprising electrical conductors embedded therein, and
a mounting fixture for mounting the electrical raft assembly to a mounting structure, and
one or more clamps for mounting one or more tubular members to the rigid raft;
wherein:
the rigid material forms at least part of an exterior surface of the electrical raft assembly, the mounting fixture being
attached to a part of the exterior surface formed by the rigid material, and

each of the one or more clamps has:
a first clamp block and a second clamp block which, in use, clamp together to grip each of the one or more tubulars members
between the first and second clamp blocks, the first clamp block being fixed to the rigid raft, and

a fastener operatively extending between the first and second clamp blocks, the fastener being tightenable to apply a clamping
load between the first and second clamp blocks, and releasable to remove the clamping load such that the second clamp block
can be moved relative to the first clamp block to allow the one or more tubular members to be received between or removed
from between the first and second clamp blocks.

US Pat. No. 9,175,950

POSITION MEASUREMENT

ROLLS-ROYCE plc, London ...

1. A measurement fixture for use in determining the position and orientation of an object, the measurement fixture mountable
in use in a fixed spatial relationship with the object and comprising:
a plurality of optically-detectable elements that in use can be detected by an optical measuring device remote from the measurement
fixture, the optically-detectable elements being distributed around the measurement fixture such that in use at least three
reference points are within the field of view of the optical measuring device for all positions and orientations of the object;

a base; and
a plurality of projections extending from the base,
the optically-detectable elements being located on the plurality of projections, and
the optically-detectable elements being equally spaced around the projections in at least three positions.

US Pat. No. 9,459,320

FAULT DETECTION IN BRUSHLESS EXCITERS

ROLLS-ROYCE plc, London ...

1. A method for detecting a fault in an exciter circuit, suitable for use in a brushless generator, the exciter circuit including
an exciter armature winding, having a plurality of armatures, arranged to generate a multiphase AC signal, each armature of
the plurality of armatures providing a respective signal component of the multiphase AC signal, and

a rectifier circuit for receiving the signal components from the respective armatures, the rectifier circuit comprising a
plurality of diodes arranged to rectify the signal component of each armature to provide a rectified output signal, wherein

the method includes the steps of:
acquiring, for each signal component of at least two of the plurality of armatures, a respective characteristic value for
a first characteristic of each signal component;

acquiring, for each signal component of the at least two of the plurality of armatures, a respective further characteristic
value for a second characteristic of each signal component;

calculating the magnitude of the nth order harmonic component for each acquired characteristic value;

calculating the magnitude of the nth order harmonic component for each acquired further characteristic value;

on the basis of the calculated magnitudes, calculating the nth order harmonic admittance and/or impedance of the rectifier circuit; and

determining whether a fault has occurred in the exciter circuit on the basis of the nth order harmonic admittance and/or impedance of the rectifier circuit.

US Pat. No. 9,456,472

RIGID RAFT

ROLLS-ROYCE plc, London ...

1. A gas turbine engine comprising:
a rigid raft being formed of a rigid material, the rigid raft comprising:
multiple electrical conductors embedded in the rigid material, the multiple electrical conductors being at least a part of
an electrical system of the gas turbine engine; and

a tank that provides a liquid to a fluid system, the tank being integrally formed with the rigid raft.

US Pat. No. 9,088,154

TURBINE ARRAY AND A METHOD OF CONTROLLING A TURBINE ARRAY DURING A LOSS-OF-GRID EVENT

ROLLS-ROYCE plc, London ...

1. A tidal or tidal stream turbine array comprising:
a plurality of tidal or tidal stream turbines together creating a local grid;
an electrical machine connected to each of the turbines and to an electrical grid; wherein at least one of the electrical
machines is a motor-generator which can operate in a motor mode or a generator mode, and wherein the other electrical machines
are generators; and

a controller for detecting a loss-of-main-grid event;
wherein the controller is configured to switch motor-generator to the motor mode when a loss-of-main-grid event is detected,
the motor-generator being driven by the generators and thereby providing a load to the generators, thereby allowing the generators
to drive the motor-generator via local grid power.

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. 9,397,543

ELECTRICAL MACHINE

ROLLS-ROYCE PLC, London ...

1. An electromagnetic machine, comprising:
a first stator winding having a first number of pole pairs;
a second stator winding having a second number of pole pairs which is different to the first number of pole pairs, wherein
the first and second stator windings are fixed relative to each other; and

a modulator having a plurality of high magnetic permeability pole pieces arranged relative to the first and second stator
winding so as to modulate electromagnetic fields produced by the first and second stator windings, thereby matching harmonic
spectra of the first and second stator windings, wherein each of the modulator and either the first or second stator winding
has a back iron portion such that the modulator and the first and second stator windings are located within the back iron
of the modulator and the back iron of the first or second stator winding thereby providing a magnetic envelope for the modulated
electromagnetic fields, and

wherein:
either the first or second stator winding is positioned between the other of the first or second stator winding and the modulator,
the modulator is rotatable and the first and second stator winding are stationary relative to each other and the modulator,
and

the modulator is positioned adjacent to one side of either the first or the second stator winding.

US Pat. No. 9,290,825

METHOD AND AN APPARATUS FOR PRESTRESSING COMPONENTS BY ELECTRICAL DISCHARGE

ROLLS-ROYCE plc, London ...

1. A method of pre-stressing a component, the method comprising:
directing a beam of radiation in a path through a medium adjacent to the component between a pair of electrodes to produce
a path of reduced electrical resistance through the medium; and

producing an electrical discharge between the pair of electrodes along at least a portion of the path of reduced electrical
resistance through the medium to produce a pressure pulse in the medium adjacent to the component without the electrical discharge
directly contacting the component, the pressure pulse impacting a surface of the component to produce a region of compressive
residual stress within the component,

wherein the beam directed in the path between the pair of electrodes is selected from the group consisting of a laser beam,
an x-ray beam, a microwave beam and a gamma ray beam.

US Pat. No. 9,291,351

COMBUSTION CHAMBER AND A METHOD OF MIXING FUEL AND AIR IN A COMBUSTION CHAMBER

ROLLS-ROYCE plc, London ...

14. A method of mixing fuel and air in a combustion chamber, the method comprising:
injecting the fuel into a mainstream flow of air with a first fuel injector;
injecting the fuel into the mainstream flow of air with a second fuel injector, the second fuel injector arranged downstream
of the first fuel injector;

injecting the fuel into the mainstream flow of air with the first fuel injector such that a resulting mixture between the
first fuel injector and the second fuel injector has an equivalence ratio less than a lean flame stability limit;

injecting the fuel into the mainstream flow of air with the second fuel injector such that a combustion zone is provided downstream
of the second fuel injector;

injecting the fuel with the second fuel injector within an aperture in an upstream end wall of the combustion chamber;
passing the mainstream flow through an expanding cowl portion configured to: (i) longitudinally overlap with a diffuser portion
arranged upstream of the combustion chamber and downstream of the compressor exit, (ii) receive the mainstream flow of air,
and (iii) supply the mainstream flow of air through the aperture in the upstream end wall of the combustion chamber, and expanding
in a cross-sectional area in a direction of the mainstream flow of air;

injecting the fuel with the first fuel injector within the expanding cowl portion, the second fuel injector being provided
within the expanding cowl portion and being provided at a downstream end of the expanding cowl portion.

US Pat. No. 9,248,502

HOT ISOSTATIC PRESSING TOOL AND A METHOD OF MANUFACTURING AN ARTICLE FROM POWDER MATERIAL BY HOT ISOSTATIC PRESSING

ROLLS-ROYCE plc, London ...

1. A hot isostatic pressing tool comprising a canister and a support structure, the canister forming an annular chamber to
receive a powder material to be hot isostatically pressed, the support structure comprising at least one annular member arranged
radially within the canister, the at least one annular member being located radially within the canister to support the canister
at a predetermined axial position, the canister having a radially inner diameter and the at least one annular member being
located radially within the radially inner diameter of the canister.

US Pat. No. 9,121,305

FLUID CALMING MEMBER

ROLLS-ROYCE PLC, London ...

1. A bearing arrangement comprising:
a bearing housing;
a rolling-element bearing within the bearing housing, the rolling-element bearing having a plurality of individual roller
elements; and

a fluid calming member substantially surrounding the bearing and mounted to an inner wall of the bearing housing via a mounting
structure, the mounting structure passing through the fluid calming member and the inner wall of the bearing housing to secure
the fluid calming member to the inner wall,

the fluid calming member being formed of a porous metallic material, and
the fluid calming member being arranged to reduce the velocity of oil striking the fluid calming member and thereby inhibit
splashing of oil within the bearing housing.

US Pat. No. 9,087,165

AUTOMATIC EXTREMUM DETECTION ON A SURFACE MESH OF A COMPONENT

ROLLS-ROYCE PLC, London ...

1. A computer-implemented method of defining a datum line on a surface mesh of an aerofoil for use in a simulation, the surface
mesh of the aerofoil including nodes interconnected by edges, the method comprising the steps of:
a) defining a reference coordinate system including a direction X with respect to the aerofoil;
b) defining a span variable that varies monotonically along the aerofoil in a forwards marching direction that is not coincident
with the direction X;

c) selecting a first frontal node n1 on the datum line of the aerofoil;

d) using a Pareto front algorithm to define a datum line at an extremity of the surface mesh with respect to the X direction
of the aerofoil, the Pareto front algorithm evaluating a criterion for dominated nodes and operating on a Pareto variable
to select successive connected frontal nodes that form the datum line of the aerofoil, wherein the Pareto variable is the
X coordinate and the criterion for dominated nodes is a span value less than that of the selected frontal node n1; and

e) outputting the defined datum line such that a geometrical feature of the aerofoil is identified for determining a fluid
flow domain of a fluid flow across a surface of the aerofoil.

US Pat. No. 9,422,956

PANEL MOUNTING ARRANGEMENT

ROLLS-ROYCE PLC, London ...

1. A panel mounting system comprising:
a panel comprising a plurality of first attachment points;
a foundation comprising a plurality of second attachment points;
a plurality of hangers connecting the panel to the foundation, each hanger having a first plane; and
a center mount positioned at a geometric center of the panel, the center mount rigidly connecting the panel to the foundation,
wherein:
the plurality of hangers are arranged across the surface of the panel such that the first plane of each of the plurality of
hangers intersects at the geometric center of the panel, and

the panel is constrained by the plurality of hangers such that movement of each first attachment point relative to the corresponding
second attachment point is constrained to a plane that is normal to the surface of the panel at the first attachment point,
and is aligned with a direction of thermal expansion of the panel in the first plane of each of the plurality of hangers at
the first attachment point.

US Pat. No. 9,310,073

LIQUID SWIRLER FLOW CONTROL

Rolls-Royce plc, (GB)

1. An injector for producing an atomized spray of liquid comprising:
a) an annular injector body;
b) an annular first flow directing body mounted inboard of the injector body, the first flow directing body including an inboard
surface and opposed outboard surface,

wherein a plurality of flow channels are defined in the outboard surface of the first flow directing body for conducting fluids
flowing through the first flow directing body,

wherein each flow channel includes a channel floor and a sidewall extending from the channel floor to the outboard surface
of the first flow directing body, and

wherein a swirl bore extends through the first flow directing body from each channel floor to the inboard surface of the first
flow directing body at an oblique angle relative to the channel floor for imparting a tangential swirl component onto fluids
flowing through the swirl bore; and

c) an annular second flow directing body mounted radially inboard of the first flow directing body and including an outboard
surface with an annular swirl chamber defined therein for receiving liquid from the swirl bores of the first flow directing
body to form a swirling sheet of liquid for atomization downstream of the second flow directing body;

wherein a terminus section of each flow channel defines a dogleg with respect to the flow channel upstream of the terminus
section;

wherein the dogleg is angled relative to the flow channel upstream of the dogleg;
wherein the swirl bore of each flow channel defines a swirl bore radius, wherein the terminus section of each flow channel
defines a semi-circular pad in the channel floor having a radius between about two to about five times the swirl bore radius.

US Pat. No. 9,270,200

METHOD OF CONTROLLING AN INVERTER AND A CONTROLLER FOR CONTROLLING AN INVERTER

ROLLS-ROYCE PLC, London ...

1. A method of controlling an inverter for converting a DC input to an AC output, the method including:
measuring a voltage of an AC output produced by the inverter;
determining a modified drive voltage for controlling the inverter, the modified drive voltage being provided by a difference
between a measured voltage and frequency and a target voltage and frequency, or a difference between a measured real power
and reactive power and a target real power and reactive power; and

if a difference in amplitude and/or phase between the modified drive voltage and the measured voltage exceeds a predetermined
threshold, further limiting the modified drive voltage to reduce the difference in amplitude and/or phase between the modified
drive voltage and the measured voltage, and if the difference in amplitude and/or phase between the modified drive voltage
and the measured voltage does not exceed the predetermined threshold, not further limiting the modified drive voltage, wherein:

the measured voltage is transformed into a measured voltage vector representative of the measured voltage in a stationary
or rotating reference frame;

the modified drive voltage is provided as a drive voltage vector representative of the modified drive voltage in the stationary
or rotating reference frame; and

the method includes, comparing the drive voltage vector and the measured voltage vector and determining whether there is a
difference between the drive voltage vector and the measured voltage vector in the stationary or rotating reference frame
that exceeds a pre-determined threshold, and if the difference exceeds the pre-determined threshold, then limiting the drive
voltage vector to reduce the difference between the drive voltage vector and the measured voltage vector in the stationary
or rotating reference frame.

US Pat. No. 9,255,547

TURBINE ENGINE WITH ACCESS DOOR TO ENGINE CORE

ROLLS-ROYCE PLC, London ...

1. A turbine engine comprising:
an engine core bounded by a bypass duct;
a first portion of the bypass duct defined by a fan casing having a first radially inner wall and a first radially outer wall;
a second portion of the bypass duct defined by a second radially inner wall and a second radially outer wall;
a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and
a thrust reverser mechanism coupled to the fan casing, wherein
the at least one access door is pivotable between an open position and a closed position relative to the thrust reverser mechanism;
the second radially outer wall is a separate component to the access door and remains in place around the engine core when
the access door is opened;

the flow guide structure has a first panel spaced apart from a second panel such that in the closed position the first panel
forms a continuous flow surface with the second radially outer wall and the second panel forms a continuous flow surface with
the second radially inner wall and covers a section of the engine core;

in the open position, the access door provides access to the engine core; and
when the access door is in the open position and the second radially inner wall is open, the second radially inner wall provides
access to the engine core.

US Pat. No. 9,206,905

LEAF SEAL

ROLLS-ROYCE PLC, London ...

1. A leaf seal for effecting a seal between two coaxial and relatively rotating components, the seal having an annular pack
of stacked leaves, the pack being mountable to a first one of the components at root portions of the leaves and extending
towards the other component such that end edges of the leaves are presented for air-riding interaction with the other component
during relative rotation between the components and, in use, a pressure drop is maintained axially across the pack; wherein
the pack comprises a first set of leaves arranged around the pack, each of which is configured to present an end edge at least
part of which is in intimate relationship with the other component; and a second set of leaves circumferentially interspersed
throughout the first set, the leaves of the first and second sets cooperating to define, around the pack, a plurality of circumferential
spaces between the end edges of successive leaves of the first set, said spaces being configured to create a circumferential
variation in pressure around the pack which contributes to the generation of hydrodynamic lift between the pack and the other
component during relative rotation between the components,
wherein each leaf of said second set defines a radial gap between at least a region of its end edge and the other component,
said radial gaps defining a radial dimension of said circumferential spaces.

US Pat. No. 9,194,429

BEARING CAGE DEFLECTOR

ROLLS-ROYCE plc, London ...

1. An annular bearing arrangement configured for providing free rotation between two coaxially aligned bodies between which
the bearing arrangement is coaxially aligned, the bearing arrangement including:
a bearing chamber having a gas inlet and a lubricant inlet and arranged to house a rolling element bearing assembly,
the rolling element bearing assembly including a bearing cage having
a cage body close to or in axial alignment with the gas inlet and having an inner surface defining a bore coaxially aligned
with the principal rotational axis of the bearing cage,

a plurality of pockets, each pocket housing a rotatable rolling element of the rolling element bearing assembly, the pockets
being arranged sequentially around the cage body with respect to the principal rotational axis of the bearing cage, and

a skirt projecting from the cage body in the axial direction and past the lubricant inlet,
wherein:
the bearing cage includes a flow deflector projecting from the skirt in the radial direction at an axial position which is
between the lubricant inlet and the gas inlet and which is arranged to intercept gas flow entering by the gas inlet so as
to deflect the gas flow away from the cage body.

US Pat. No. 9,289,950

MANDREL FOR FORMING A COMPONENT

ROLLS-ROYCE plc, London ...

1. A mandrel for forming a component with a cavity, the mandrel having a longitudinal axis and defining a cavity profile,
the mandrel comprising:
a support structure;
a plurality of main sectors carried by the support structure and each having a main forming surface;
a plurality of intermediate sectors carried by the support structure and each having an intermediate forming surface; and
a drive device,
wherein:
the main sectors and intermediate sectors are alternately arranged around the axis, the main sectors being moveable relative
to the support structure between a radially inner main retracted position and a radially outer main forming position in which
each main forming surface defines a part of the cavity profile, and in which the main sectors are spaced apart to define circumferential
gaps;

the intermediate sectors being moveable relative to the support structure between a radially inner intermediate retracted
position and a radially outer intermediate forming position in which the intermediate sectors extend into the respective gaps,
and in which each intermediate forming surface defines a further part of the cavity profile;

the drive device is configured to move the main sectors and intermediate sectors from their respective retracted positions
to their respective forming positions;

the drive device comprises a plurality of drive units, each drive unit including a carrier block on which a main sector and
an adjacent intermediate sector are mounted, each carrier block being arranged to move the mounted main sector and the mounted
adjacent intermediate sector from their respective retracted positions to their respective forming positions and being configured
such that each main sector reaches its main forming position before any of the adjacent intermediate sectors reaches its intermediate
forming position; and

a lost motion connection is provided between each drive unit and the respective main sector.

US Pat. No. 9,291,058

MACHINING PROCESS AND APPARATUS FOR MACHINING

ROLLS-ROYCE plc, London ...

1. A method of determining a tool path to machine a component, the method comprising the steps of:
securing the component to a fixture having a zero point alignment datum, the component and the fixture having respective mobile
reference points;
aligning the fixture mobile reference points to target reference points on a machine tool;aligning a digitized model of the component to the component mobile reference points;
determining the position of the component on the fixture from the component mobile reference points and the fixture mobile
reference points; and adjusting a nominal tool path for the machine tool dependent on the position of the component,

wherein the nominal tool path is adjusted before the fixture is located on the machine tool.

US Pat. No. 9,248,521

METHOD OF LINEAR FRICTION WELDING

ROLLS-ROYCE plc, London ...

1. A method of linear friction welding, the method comprising:
a friction phase comprising oscillating a first workpiece relative to a second workpiece with a surface of the first workpiece
being forced against a surface of the second workpiece, such that a plasticised layer is formed at the interface between the
first and second workpieces;

wherein the friction phase is divided into a plurality of sub-phases, each subphase being configured to form a plasticised
layer at the interface between the first and second workpieces, each plasticised layer comprising a stagnation zone; wherein
the stagnation zone of one sub-phase is offset from the stagnation zone of another sub-phase.

US Pat. No. 9,382,808

MACHINE CAVITY SEAL

ROLLS-ROYCE plc, London ...

1. A seal assembly comprising:
a support structure to which a resiliently deformable seal member is mounted; and
a seal land opposingly spaced from the support structure to define a gap therebetween, the height of the seal member in an
undeformed condition being greater than the height of the gap such that the seal member is deformingly pressed against the
seal land by the support structure to seal the gap therebetween,

wherein the support structure and/or seal land comprise an actuable member that comprises a shape memory material, said actuable
member being actuable in response to an adverse condition so as to move in a direction towards the other of the support structure
and seal land to improve the resistance of the seal assembly to the adverse condition.

US Pat. No. 9,376,918

AEROFOIL COOLING ARRANGEMENT

ROLLS-ROYCE plc, London ...

1. An aerofoil for a gas turbine engine, the aerofoil comprising:
a pressure wall, a suction wall and a web, wherein
the web extends between the pressure wall and the suction wall,
the suction wall comprises an inner leaf and an outer leaf that define a first cavity and a second cavity therebetween,
the pressure wall defines a first outlet and a second outlet,
at least one first passage extends from the first cavity through the web and to the first outlet,
at least one second passage extends from the second cavity to the second outlet through the web wherein the pressure wall
and the suction wall meet at a leading edge and at a trailing edge of the aerofoil, and the first cavity is closer to the
leading edge than the second cavity.

US Pat. No. 9,300,926

APPARATUS AND A METHOD OF INSPECTING A TURBOMACHINE

ROLLS-ROYCE plc, London ...

1. A method of inspecting a turbomachine, the turbomachine comprising a rotor having at least one stage of rotor blades and
a casing surrounding the rotor and at least one stage of rotor blades, each rotor blade comprising a platform portion and
an aerofoil portion, the aerofoil portion having a leading edge, a trailing edge, a concave surface, a convex surface and
a tip, the method comprising the steps of:
a) providing a plurality of boroscopes,
b) inserting each boroscope through a respective one of a plurality of apertures in a casing of the turbomachine, at least
one of the apertures in the casing being upstream of the rotor blades, at least one of the apertures in the casing being downstream
of the rotor blades,

c) rotating the rotor of the turbomachine,
d) providing reference measurements of the rotor blades and/or reference measurements between the rotor blades and the boroscopes,
e) viewing the leading edge and at least a portion of the concave surface or viewing the leading edge and at least a portion
of the convex surface of each of the rotor blades of the turbomachine as the rotor is rotated using the boroscope in the at
least one of the apertures in the casing upstream of the rotor blades and supplying the image of each of the rotor blades
to the processor,

f) viewing the trailing edge and at least a portion of the convex surface or viewing the trailing edge and at least a portion
of the concave surface of each of the rotor blades of the turbomachine as the rotor is rotated using the boroscope in the
at least one of the apertures in the casing downstream of the rotor blades and supplying the image of each of the rotor blades
to the processor, and

g) analysing the images of the rotor blades and using the reference measurements of the rotor blades and/or reference measurements
between the rotor blades and the boroscopes to determine the position and size of any defect on any of the rotor blades.

US Pat. No. 9,190,892

ELECTRO-MAGNETIC COUPLING SYSTEM

ROLLS-ROYCE PLC, London ...

1. An electro-magnetic coupling system for transferring torque between a pair of coaxial spools of a gas turbine engine, the
system including a first rotor rotatable with one of the spools, a second rotor rotatable with the other of the spools, and
a stator, the first and second rotors and the stator being coaxial with each other, and the second rotor operably coupling
the first rotor and the stator;
wherein:
the first rotor carries a plurality of magnetic flux-producing formations which produce a first magnetic field,
the stator carries a plurality of electrical winding coils which are energisable to generate a second magnetic field, and
the second rotor carries an arrangement of interpoles which modulate the first and second magnetic fields such that the modulated
fields interact to transfer torque between the spools.

US Pat. No. 9,285,122

FUEL INJECTOR

ROLLS-ROYCE plc, London ...

1. A fuel injector comprising:
a circumferential dispersion structure which, in use, spreads fuel in a circumferential direction; the circumferential dispersion
structure comprising

a first surface which is an outer surface of an inner annular member, and
a second surface which is an inner surface of an outer annular member, the inner annular member and the outer annular member
being arranged in co-axial alignment;

a plurality of discrete fuel sources spaced around a circumference of one of the first surface or the second surface; and
a plurality of radially convex portions spaced around a circumference of the other one of the first surface or the second
surface, the plurality of radially convex portions being separated from one another by a plurality of troughs and defining
a prefilmer,

wherein the plurality of discrete fuel sources and the plurality of radially convex portions are arranged with respect to
each other such that jets of fuel emerging from the discrete fuel sources impinge at peaks of the plurality of radially convex
portions, whereby the plurality of radially convex portions cause the fuel to be dispersed from points of impingement at the
peaks in the circumferential direction towards adjacent ones of the plurality of troughs.

US Pat. No. 9,353,686

METHOD AND APPARATUS FOR GENERATING MOTIVE POWER

ROLLS-ROYCE PLC, London ...

5. A method of delivering a cooling medium supply to a machine, the machine further comprising a gas turbine engine, a self-contained
fuel supply, an ignition system and a starting system, the gas turbine engine being operatively connected to the cooling medium
pump mechanism, the method comprising the steps of:
(a) sensing a loss of supply of a cooling medium to the machine through a first cooling medium delivery apparatus:
(b) generating a signal indicative of the loss of supply of the cooling medium;
(c) receipt of the signal by a controller;
(d) in response to the signal, supplying the gas turbine engine with a fuel from a pressurised fuel container;
(e) activating the starting system to thereby activate the gas turbine engine to thereby cause the cooling medium pump mechanism
to deliver the cooling medium to the machine through a second cooling medium delivery apparatus;
and
(f) operating the engine until the fuel supply is exhausted.

US Pat. No. 9,121,491

OIL SCAVENGE ARRANGEMENT

ROLLS-ROYCE PLC, London ...

1. An epicyclic gearbox having a rotational axis, the gearbox comprising:
a sun gear;
a ring gear radially outward of the sun gear;
an array of planet gears that each mesh with the sun gear and the ring gear and rotate relative thereto;
a planet carrier that couples the planet gears in relative position to each other; wherein the planet carrier comprises:
interplanetary portions that are each located between adjacent pairs of the planet gears and that each have a first and a
second circumferential surface, each of the first and second circumferential surfaces facing an adjacent one of the planet
gears; and

direction features on at least one of the circumferential surfaces that, in use, direct fluid ejected with a radial component
from the planet gears and direct it substantially in an axial direction of the gearbox.

US Pat. No. 10,052,716

MANUFACTURE OF A DRUM FOR A GAS TURBINE ENGINE

ROLLS-ROYCE PLC, London ...

1. A method for the manufacture of a blisk drum for use in a gas turbine engine, the method comprising, in sequence;providing a plurality of disc forging, at least one of which is proportioned to enable a blisk to be cut from the forging and each including sacrificial material;
arranging two disc forging in axial alignment for welding in an inertia welding machine;
performing inertia welding to provide a joined disc forging;
fashioning at least some of the sacrificial material into blades whereby to form a blisk drum;
wherein the sacrificial material on a disc forging is configured to provide at least one planar force balancing surface to which an axial force can be applied during inertia welding and at least one holding surface which can be fixed in position with respect to an inertia welding machine used to perform the inertia welding.

US Pat. No. 9,309,777

TIP CLEARANCE CONTROL DEVICE

ROLLS-ROYCE plc, London ...

1. A pressure activated tip clearance control device adapted to control the clearance of a rotating aerofoil structure with
a surrounding casing portion, the device comprising:
a member operatively connected to the casing portion and responsive to pressurized fluid for moving the casing portion, the
member having at least a first configuration in which the casing portion is at a first radial position and a second configuration
in which the casing portion is at a second radial position;

an aerofoil structure tip clearance control system adapted to control a radial position of the casing portion by moving the
casing portion from the first radial position to the second radial position upon expansion of an expandable chamber;

a conduit coupled to a fluid supply for pressurized fluid, the conduit being arranged to selectively provide pressurized fluid
to the aerofoil structure tip clearance control system to move the casing portion between the first and second radial positions
by selectively providing pressurized fluid from the fluid supply to expand the expandable chamber; and

a sensor passage in communication with the expandable chamber, the sensor passage arranged to sense radial growth of the rotating
aerofoil structure and to relieve pressure in the expandable chamber to move the casing portion from the second radial position
to the first radial position, wherein

configuration of the member is controlled by magnetic flux in a magnetic circuit which includes at least one ferromagnetic
element comprising ferromagnetic material, whereby the configuration of the member is responsive to the temperature of the
ferromagnetic element, and

the magnetic circuit is disposed to restrict flow through the conduit in the first configuration and permit flow through the
conduit in the second configuration.

US Pat. No. 9,242,721

AIRCRAFT PROPULSION SYSTEM AND A METHOD OF CONTROLLING THE SAME

ROLLS-ROYCE plc, London ...

14. A method of reducing the noise generated by an aircraft propulsion system comprising at least one propulsive rotor assembly
having a plurality of rotor blades and rotatable about an axis of rotation, the method comprising the steps of:
installing a plurality of vanes in a circumferential arrangement around the axis of rotation to direct an airflow entering
the first propulsive rotor assembly so as to reduce the velocity of the redirected airflow relative to the rotor blades; and

modifying the propulsive rotor blade assembly by adding at least one additional rotor blade to thereby reduce the noise generated
by the propulsive rotor assembly when in use.

US Pat. No. 9,097,114

ROTOR CASING LINER

ROLLS-ROYCE PLC, London ...

1. A power plant comprising:
a rotor mounted for rotation;
a rotor casing; and
a rotor casing liner, comprising a plurality of sections, positioned between the rotor and the rotor casing;
wherein at least one section of the plurality of sections of the rotor casing liner is sized to enable removal of the at least
one section without adapting the rotor.

US Pat. No. 9,303,526

TURBINE COOLING SYSTEM

ROLLS-ROYCE plc, London ...

1. A cooling system for cooling a turbine of a gas turbine engine, the system comprising:
a first flow path and a second flow path that guide cooling air received from a core flow of a compressor of the engine, the
start of both flow paths being at the core flow and the routes of both flow paths bypassing a combustor of the engine, the
combustor comprising a combustion chamber having a wall, a compressor exit downstream of the compressor and upstream of the
combustor, the first flow path flowing radially outwardly from the compressor exit, the second flow path at least partially
defined by the combustion chamber wall; and

a preswirler including a plurality of interconnected walls that define a receiving chamber that receives the cooling air through
a first inlet and a second inlet at the ends of the first flow path and the second flow path, respectively, the preswirler
swirling the cooling air tangentially to an engine axis, and delivering the swirled cooling air to a rotor of the turbine,
wherein

the first flow path is routed through a heat exchanger which cools the cooling air guided by the first flow path relative
to the cooling air guided by the second flow path, wherein

between the heat exchanger and the preswirler the first flow path is routed through nozzle guide vanes of the turbine,
the receiving chamber includes flow-metering outlet nozzles through which flow exits from the receiving chamber, the outlet
nozzles having a flow area that determines the volume flow rate of cooling air delivered from the receiving chamber to the
turbine rotor,

the rotor is defined by a set of interconnected walls that are different from the plurality of interconnected walls of the
receiving chamber, and

when the flow is obstructed in either the first flow path or the second flow path, the non-obstructed flow path increases
the flow of cooling air to the receiving chamber in order to compensate for the obstructed flow path and maintain the volume
flow rate of cooling air delivered to the receiving chamber.

US Pat. No. 9,249,733

GAS TURBINE ENGINE STAND

ROLLS-ROYCE plc, London ...

1. A gas turbine engine stand configured for supporting a core engine comprising:
an engine frame supporting the core engine;
a base frame having a slide rail to enable axial translation of the engine frame relative to the base frame;
a load transfer arrangement comprising a first engagement feature to engage with a part of the engine frame and a second engagement
feature to slidingly engage with the slide rail;

a locking mechanism to lock the engine frame to the base frame to prevent relative axial translation,
wherein one of the locking mechanism and the load transfer arrangement is selected and engaged as a load path between the
engine frame and the base frame.

US Pat. No. 9,387,923

GAS TURBINE ENGINE

ROLLS-ROYCE plc, London ...

1. A propeller gas turbine engine having an axial flow direction therethrough in use, the propeller gas turbine engine comprising:
one or more rotor stages, each rotor stage comprising at least one rotor blade, each rotor blade having a root portion; and
a shroud located upstream of the one or more rotor stages relative to the axial flow direction, the shroud extending about
a nose cone of the propeller gas turbine engine, wherein:

the one or more rotor stages comprise two contra-rotating rotor stages,
the shroud has an inner surface that cooperates with an outer surface of the nose cone to define a through passageway extending
from an inlet at a leading edge of the shroud to an outlet at a trailing edge of the shroud, the shroud being configured to
reduce an axial velocity of air exiting the outlet relative to the air entering the inlet in use,

the trailing edge of the shroud is spaced from a core inlet of the propeller gas turbine engine in the axial flow direction,
and

the outlet is configured to direct the air exiting the outlet substantially towards the root portion of the at least one rotor
blade.

US Pat. No. 9,228,959

APPARATUS AND METHOD FOR INSPECTING AN ARTICLE

ROLLS-ROYCE plc, London ...

1. A method of optically determining the orientation of a grain structure in a component, the method comprising;
presenting a surface of the component to a detector and illuminating the surface with a beam from a light source;
manipulating the relative orientation of the surface, beam and a detector and determining the relative orientation which provides
the peak reflectance of the beam from the surface to the detector;

presenting a first further surface of the component to the detector and illuminating the first further surface with a beam
from a light source;

manipulating the relative orientation of the first further surface, beam and detector and determining the relative orientation
which provides the peak reflectance of the beam from the surface to the detector;

presenting a second further surface of the component to the detector and illuminating the second further surface with a beam
from a light source;

manipulating the relative orientation of the second further surface, beam and detector and determining the relative orientation
which provides the peak reflectance of the beam from the surface to the detector;

calculating the orientation of the grain structure from the determined relative peak reflectance orientations of the surface,
first further surface and second further surface.

US Pat. No. 9,145,846

GAS TURBINE ENGINE EXHAUST NOZZLE INCLUDING A PLURALITY OF FLAPS MOVABLE OVER A FLOW CONTROL SURFACE

ROLLS-ROYCE plc, London ...

1. A gas turbine engine exhaust nozzle having a nozzle exit and comprising a nozzle body and a plurality of slats which extend
generally axially of the nozzle body and are distributed circumferentially around the nozzle exit, at least some of the slats
being movable inwardly and/or outwardly with respect to the nozzle axis, radially extending flow control surfaces being provided
on flow control walls that are fixed with respect to the nozzle axis, the flow control walls being disposed between adjacent
ones of the movable slats, whereby respective circumferential edges of the adjacent slats are movable of the respective oppositely
disposed flow control surfaces of the respective common flow control walls, and circumferential edges of the movable slats
move over the flow control surfaces during movement of the slats, a surface area of each radially extending flow control surface
being greater than a circumferential surface area of each flow control wall, wherein a radially inwardly surface of each movable
slat is configured to receive a ducted fan exhaust flow, and a radially outwardly facing surface of each movable slat is configured
to receive an air flow from a nacelle.

US Pat. No. 9,120,123

SPRAY NOZZLE

ROLLS-ROYCE plc, London ...

1. A spray nozzle for a laser deposition apparatus, comprising:
an array of nozzle apertures arranged side-by-side; and
a powder supply chamber in concurrent fluid communication with each of the array of nozzle apertures and arranged in use to
supply powder to the array of nozzle apertures under pressure so as to cause a wide powder sheet to be ejected from the array
of nozzle apertures, wherein at least one nozzle aperture of the array of nozzle apertures is provided with a controllable
flow regulator configured to alter the flow rate of powder through the at least one nozzle aperture within the array of nozzle
apertures, the controllable flow regulator being disposed within the at least one nozzle aperture.

US Pat. No. 9,121,506

LEAF SEAL

ROLLS-ROYCE PLC, London ...

1. A leaf seal arrangement, comprising:
a first component having a high pressure area and a low pressure area therein;
a second component which passes from the high pressure area to the low pressure area;
a leaf seal having an array of leaf elements between the high and low pressure areas, each leaf element having a fixed end
and a free end, wherein the fixed end is attached to the first component and the free end defines a sealing surface through
which the second component sealably passes, a sealing gap therebetween;

wherein the sealing gap generally converges from the high pressure area toward the lower pressure area; and,
wherein the leaf elements have an axial width between the high pressure area and the low pressure area, the convergent portion
of the sealing surface extending across between 60% and 100% of the width of the sealing surface.

US Pat. No. 9,123,166

METHOD OF CONNECTING MESHES

ROLLS-ROYCE plc, London ...

1. A method of connecting three-dimensional structured meshes to form a conformal mesh, for solutions of flow problems, the
method comprising the steps of:
forming an interface by overlaying surfaces of two structured meshes, each structured mesh comprising hexahedra;
defining an interface set of mesh points in the interface comprising mesh points from each surface and intersection mesh points
formed at the intersection of mesh lines;

identifying mesh points in the interface set that are within a first predetermined distance of each other and merging them
to form merged mesh points, the first predetermined distance is in the range of 5 to 25% of a mesh size of the smaller of
the two structured meshes;

identifying mesh points of one mesh in the interface that are within a second predetermined distance of a line of the other
mesh and projecting these mesh points to the corresponding mesh line to form projected mesh points;

generating an interface layer in the form of an unstructured mesh formed of triangles and quadrilaterals, including the mesh
points from each surface, the merged mesh points, the projected mesh points and the intersection mesh points; and

inserting a node at the center of each hexahedra, and producing an unstructured layer of cells between the two structured
meshes by joining the nodes to the mesh points of the interface layer so as to form tetrahedra and pyramids.

US Pat. No. 9,814,101

HEATED RIGID ELECTRICAL HARNESS FOR A GAS TURBINE ENGINE

ROLLS-ROYCE plc, London ...

1. A gas turbine engine comprising:
an electrical harness arranged to transmit electrical signals around the gas turbine engine, wherein the electrical harness
comprises a rigid electrical raft that is mounted directly to the gas turbine engine, and the rigid electrical raft comprises:

electrical conductors embedded in a material so as to be surrounded and contacted by, and thereby fixed in position by, the
material over their entire length, at least some of the electrical conductors being arranged to transmit the electrical signals;
and

electrical heating elements embedded in the material so as to be surrounded and contacted by, and thereby fixed in position
by, the material, the electrical conductors and the electrical heating elements being spaced apart, and the electrical heating
elements being arranged to provide electrical heating, wherein

a cross-sectional area of the electrical heating elements is smaller than a cross-sectional area of the electrical conductors,
and/or the electrical heating elements are constructed from a higher resistance material than the electrical conductors.

US Pat. No. 9,255,492

GAS TURBINE ENGINE HAVING A MULTI-VARIABLE CLOSED LOOP CONTROLLER FOR REGULATING TIP CLEARANCE

ROLLS-ROYCE plc, London ...

1. A gas turbine engine having, in flow series, a compressor section, a combustor, and a turbine section, and further having
a system (i) for cooling the turbine section and (ii) for providing tip clearance control between turbine blades of the turbine
section and circumferentially distributed segments which form an annular shroud surrounding outer tips of the turbine blades,
the system including:
a turbine section cooling sub-system which diverts a first cooling air flow received from the compressor section to a heat
exchanger and then to the turbine section to cool components thereof, the first cooling air flow by-passing the combustor
and being cooled in the heat exchanger, and the turbine section cooling sub-system having a first valve arrangement which
regulates the first cooling air flow;

a tip clearance control sub-system which supplies a second cooling air flow to an engine case to which the circumferentially
distributed segments are mounted, the second cooling air flow regulating thermal expansion of the engine case and thereby
controlling a tip clearance between the circumferentially distributed segments and the outer tips of the turbine blades, and
the tip clearance control sub-system having a second valve arrangement which regulates the second cooling air flow;

and a closed-loop controller configured to issue first and second demand signals to respectively the first and the second
valve arrangements, each of the first and second demand signals being determined on the basis of: (i) a value of the first
demand signal at at least one previous time step, and a measurement or estimate of a turbine section component temperature,
and (ii) a value of the second demand signal at at least one previous time step, and a measurement or estimate of tip clearance.

US Pat. No. 9,157,532

HYDRAULIC SEAL ARRANGEMENT

ROLLS-ROYCE plc, London ...

1. A hydraulic seal arrangement for a rotating machine, the hydraulic seal arrangement comprising:
a hydraulic seal; and
an annular reservoir fluidly coupled to the hydraulic seal;wherein the annular reservoir is arranged to retain fluid from the hydraulic seal when the machine is shutdown and to return
the retained fluid to the hydraulic seal under centrifugal force after the machine is restarted;
the reservoir comprises an inner chamber having an opening, an outer chamber having an opening and a central chamber in fluid
communication with the inner and outer chambers;

the inner, outer, and central chambers are separated by partitions;
the partitions extend around only a portion of the circumference of the annular reservoir and terminate in a transition region
where fluid may traverse between chambers; and

the transition region is radially confined between a first partition wall and a second partition wall, includes a first circumferential
end that is in direct fluid communication with all the chambers, and includes a second circumferential end that is in fluid
communication only with the central chamber but separates the transition region from the inner chamber and the outer chamber.

US Pat. No. 9,140,140

COMPOSITE FLANGE ELEMENT

ROLLS-ROYCE plc, London ...

1. A composite flange element, the flange element comprising a portion of a gas turbine engine casing and an adjoining flange
portion, the flange element having a ply layup defining the portion of the gas turbine engine casing and defining the adjoining
flange portion, the ply layup comprising:
a plurality of first plies forming part of both the portion of the gas turbine engine casing and the flange portion;
a plurality of second plies forming part of the flange portion, one or more of the second plies forming part of the flange
portion only; and

a plurality of third plies forming part of the portion of the gas turbine engine casing, one or more of the third plies forming
part of the gas turbine engine casing only;

wherein the first, second and third plies are selected to provide desirable properties for the portions which they form part
of, each of the first, second, and third plies having a different construction;

the flange element further comprising:
one or more load spreading features associated with the flange portion; and
one or more stress reduction features associated with the region where the portion of the gas turbine engine casing meets
the flange portion, and wherein the second plies that form part of the flange portion only are next to the first plies and
at least one of the second plies extends to the gas turbine casing and at least two of the first plies are adjacent to both
of the at least one of the second plies and one of the second plies that form part of the flange portion only.

US Pat. No. 9,316,118

BEARING CHAMBER APPARATUS

ROLLS-ROYCE plc, London ...

14. A method of preventing oil leakage from a bearing chamber in a gas turbine engine, the bearing chamber having leakage
paths between an interior of the chamber and an exterior of the chamber, the method comprising the steps of:
providing one or more pumps in fluid communication with the interior of the chamber;
providing a controllable valve in fluid communication with the interior of the chamber;
operating the pump and the valve to maintain a positive pressure differential exceeding a predetermined value between the
exterior and the interior of the chamber so that air is drawn into the bearing chamber through the leakage paths;

providing a vent pump connected to a vent line, the vent line being in fluid communication with the interior of the bearing
chamber, the valve being connected to the vent line so as to bypass the vent pump when open; and

closing the valve when the pressure at the exterior of the bearing chamber is lower than a discharge pressure of the vent
line, so that the vent pump operates to reduce the pressure within the bearing chamber.

US Pat. No. 9,234,433

FLAP SEAL SPRING AND SEALING APPARATUS

ROLLS-ROYCE PLC, London ...

1. A biasing means for securing a plurality of primary sealing components and secondary sealing components, the primary and
secondary sealing components being arranged to seal at least one gap between adjacent structural components in a turbine,
the biasing means comprising:
at least three foot regions joined in a substantially linear fashion by two resilient curved arms, each arm including securing
means for securing the biasing means to one of primary and secondary sealing components such that: (i) at least two foot regions
is in direct contact with at least two respective secondary sealing components, (ii) one foot region is in direct contact
with the primary sealing component, and (iii) one of said secondary sealing components and the curved arms urge the primary
sealing components towards one of said structural components so that the secondary sealing components form a seal over the
at least one gap between said structural components.

US Pat. No. 9,231,444

SUPERCONDUCTOR WINDING

ROLLS-ROYCE plc, London ...

1. A superconducting electrical machine, comprising:
a superconducting winding at least partially surrounded by a magnetic flux guide,
wherein the magnetic flux guide includes a binder loaded with a magnetic material, and wherein the magnetic flux guide includes
a pole face portion and a back iron portion having different loadings of magnetic material by volume;

wherein the relative magnetic permeability of the magnetic flux guide is between 5 and 20; and
wherein the bulk relative permeability for the pole face portion is lower than the bulk relative permeability of the back
iron portion.

US Pat. No. 9,091,174

METHOD OF REDUCING ASYMMETRIC FLUID FLOW EFFECTS IN A PASSAGE

ROLLS-ROYCE plc, London ...

1. A method of reducing the fluid flow effects of one or more obstacles in a passage of a gas turbine engine, the method comprising:
providing a plurality of aerofoil structures in the passage upstream of the one or more obstacles, wherein the geometry of
each aerofoil structure is substantially the same;

shortening at least one trailing edge of one or more selected aerofoil structures in a chordwise direction and over at least
a spanwise portion of the one or more selected aerofoil structures such that, when in use, the direction of the fluid flow
in the vicinity of the one or more selected aerofoil structures is altered and the fluid flow effects of the one or obstacles
in the passage are reduced; and

arranging the aerofoil structures such that a setting angle of each aerofoil structure is approximately equal; and
varying an amount that is shortened from each of the trailing edges such that at least one of the trailing edges is not shortened
and is provided adjacent to at least one trailing edge that is shortened.

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. 9,051,056

FUEL HEAT MANAGEMENT SYSTEM

ROLLS-ROYCE plc, London ...

1. A fuel heat management system comprising:
a fuel line for conveying fuel to engine burners of a gas turbine engine,
a fuel/oil heat exchanger which receives fuel flowing through the fuel line,
an oil line for circulating oil from an engine oil system to the fuel/oil heat exchanger and back to the engine oil system,
such that the fuel/oil heat exchanger brings the oil and the fuel into heat exchange relationship, and

an air/oil heat exchanger which receives oil flowing through the oil line, the air/oil heat exchanger bringing the oil and
air into heat exchange relationship,

wherein:
the fuel heat management system further comprises an air/fuel heat exchanger which receives fuel flowing through the fuel
line, the air/fuel heat exchanger bringing the fuel and air into heat exchange relationship to reduce a temperature of the
fuel,

the air/fuel heat exchanger is downstream on the fuel line from the fuel/oil heat exchanger, and
the fuel/oil heat exchanger brings the oil and the fuel into heat exchange relationship to increase the temperature of the
fuel.

US Pat. No. 9,383,097

SYSTEMS AND METHOD FOR COOLING A STAGED AIRBLAST FUEL INJECTOR

Rolls-Royce plc, (GB)

1. A staged fuel injector comprising:
a) a main fuel circuit for delivering fuel from an upstream end to a main fuel atomizer at a downstream end, the main fuel
atomizer including a radially outer prefilmer and a radially inner fuel swirler, a radially inner surface of the radially
outer prefilmer and a radially outer surface of the radially inner fuel swirler being joined from the upstream end to a midstream
region to form said main fuel circuit and spaced apart from the midstream region to a downstream end to define walls of an
annular spin chamber, wherein portions of the main fuel circuit are formed in the prefilmer and fuel exit ports associated
with the main fuel circuit are formed in the prefilmer and exit into the annular spin chamber; and

b) a pilot fuel circuit for delivering fuel to a pilot fuel atomizer which is located radially inward of the main fuel atomizer,
wherein portions of the pilot fuel circuit are formed in the prefilmer and in the fuel swirler and are positioned proximate
to and in thermal contact with the fuel exit ports and a portion of the pilot fuel circuit formed in the prefilmer is positioned
downstream of the fuel exit ports in a wall of the annular spin chamber defined by the prefilmer.

US Pat. No. 9,321,538

SUPERCONDUCTING ELECTRICAL SYSTEM

ROLLS-ROYCE plc, London ...

1. An aircraft having a superconducting electrical network, comprising:
an electrical system including a plurality of superconducting electrical equipment;
at least one electrical generator for supplying current to the plurality of superconducting electrical equipment;
a cryogenic system including one or more refrigeration units for providing coolant to the plurality of superconducting electrical
equipment;

a controller configured to control delivery of the current and delivery of the coolant to each of the plurality of the superconducting
electrical equipment independently of others,

the controller configured to monitor the operating condition of each of the plurality of superconducting electrical equipment
and on detection of a fault within one of the plurality of superconducting electrical equipment isolate the supply of coolant
to that faulted superconducting electrical equipment and increase the flow of coolant to one or more of the remaining non-isolated
plurality of superconducting electrical equipment and drive one or more of the remaining non-isolated plurality of superconducting
electrical equipment harder whereby to increase the power output thereof and compensate for the isolated superconducting electrical
equipment.

US Pat. No. 9,300,182

DYNAMO-ELECTRIC MACHINE

ROLLS-ROYCE plc, London ...

1. A dynamo-electric machine comprising:
a stator having a plurality of stator windings; and
a rotor configured to rotate within the stator, the rotor including:
an annular core of ferromagnetic material having a rim circumferentially disposed on a radially outer side of the annular
core; and

a plurality of external circumferential layers disposed radially outward of the rim, the plurality of layers including:
an environmental enclosure made of an electrically conductive material, the environmental enclosure being an outermost layer
of the plurality of layers, and

at least one sleeve made of an electrically conductive material, the at least one sleeve being disposed between the rim of
the rotor core and the environmental enclosure;

wherein an electrical resistance of the environmental enclosure is higher than an electrical resistance of the at least one
sleeve.

US Pat. No. 9,176,488

METHOD OF POSITIONING A CONTROL SURFACE TO REDUCE HYSTERESIS

ROLLS-ROYCE PLC, London ...

1. A method of determining an actual position of a control surface, the method comprising:
receiving a signal indicating a required position of the control surface;
repositioning the control surface in response to the signal by moving an actuator;
measuring a secondary position indicator including providing a force measurement;
calculating the actual position of the control surface based on the secondary position indicator;
comparing the calculated actual position with the required position; and
outputting the compared actual position.

US Pat. No. 9,133,939

SEAL

ROLLS-ROYCE plc, London ...

1. A hydraulic seal arrangement for a rotating machine comprising:
an annular hydraulic seal comprising radially inwardly extending walls and a radially outwardly extending web, the walls and
the web defining a hydraulic fluid filled space therebetween filled with oil such that, in operation, the oil prevents leakage
of other fluids across the space;

a hydraulic trap, wherein:
the hydraulic seal has a U-shaped cross-section comprising the walls and the web is located between the walls;
the walls and the web are relatively rotatable and define the space therebetween that is sealed with the oil:
the hydraulic seal is arranged to prevent leakage from the hydraulic seal into the hydraulic trap when the machine is shut
down;

the hydraulic trap is arranged to retain the oil from the hydraulic seal when the machine is shut down; and
the hydraulic trap comprises at least one pocket that extends circumferentially to a greater extent than a radial depth and
extends circumferentially around part, but not all, of the circumference of the hydraulic seal to increase the amount of oil
that can be retained; and

two first passages in fluid communication between the hydraulic seal and the hydraulic trap, wherein the two first passages
are at diametrically opposite positions.

US Pat. No. 9,125,296

ELECTRICAL HARNESS

ROLLS-ROYCE plc, London ...

1. A gas turbine engine having an electrical harness formed from a flexible printed circuit board which provides a plurality
of spaced conductive tracks, wherein: the conductive tracks are grouped into plural layers of tracks, the track layers being
spaced apart and extending substantially parallel to each other, the tracks of each track layer forming respective circuits
which all have impedances lying within a respective range for a respective track layer, and the impedance ranges being non-overlapping,
wherein the plural layers of tracks comprises a first track layer and a second track layer, the tracks of the first track
layer all forming relatively low impedance circuits, and the tracks of the second track layer all forming relatively high
impedance circuits compared to the tracks of the first track layer, and

the high impedance circuits are circuits that are not protected directly or indirectly to ground.

US Pat. No. 9,096,312

AIRCRAFT

ROLLS-ROYCE PLC, London ...

1. An aircraft comprising a longitudinal centre line, a pair of wings, each wing extending from a respective side of the longitudinal
centre line and having a selectively deployable high lift device, and a propulsion system, the propulsion system comprising
a plurality of electrically driven propulsors and a generator arrangement comprising a gas turbine engine driving one or more
electrical power generators, each electrical power generator being electrically coupled to one or more electrically driven
propulsors, such that each gas turbine engine provides power for a plurality of the electrically driven propulsors, wherein
the electrically driven propulsors are located forward of a leading edge of the wings and the high lift device such that an
airstream generated by the propulsors flows over the wings and high lift device in use.

US Pat. No. 9,097,139

CONTAINMENT CASING

ROLLS-ROYCE plc, London ...

1. A containment casing for containing a blade or a blade fragment of a gas turbine engine, the containment casing comprising:
a radially outer layer;
a radially inner layer;
an intermediate energy absorbing layer disposed between the radially outer layer and the radially inner layer; and
a retention framework disposed axially and circumferentially along the containment casing and extending substantially radially
inwardly through the intermediate energy absorbing layer, the retention framework terminating in a plurality of radially inwardly
facing engagement features, the inwardly facing engagement features are located immediately adjacent to the inner layer and
taper radially inwardly in a direction oriented towards a surface of the radially inner layer; and

at least one engagement feature penetrates through the entire thickness of the radially inner layer in response to the blade
or the blade fragment impacting the containment casing.

US Pat. No. 9,399,521

AIRCRAFT VAPOUR TRAIL CONTROL SYSTEM

ROLLS-ROYCE PLC, London ...

1. An aircraft propulsion control system comprising:
a plurality of gas turbine engines mounted at different spaced positions relative to an airframe;
one or more sensor arranged to sense a condition indicative of a property of a vapour trail formed by an exhaust flow from
one or more of the plurality of engines; and

a controller arranged to be responsive to said sensed condition and a thrust demand for the aircraft and selectively to control
operation of each of the engines so as to modify the exhaust flow of at least one engine relative to at least one further
engine according to the positions of the engines on the airframe relative to one or more portion of the airframe that induces
a vortical wake flow during flight.

US Pat. No. 9,182,174

FLUIDISED BED TREATMENT

ROLLS-ROYCE plc, London ...

1. A process for the treatment of a component using a fluidised bed of solid particles, the process comprising:
forming the fluidised bed in a treatment chamber and retaining the fluidised bed in the treatment chamber by one or more containment
surfaces;

placing at least one treatment part of the component in the fluidised bed and locating at least one non-treatment part of
the component outside the chamber and out of contact with the fluidised bed; and

maintaining the at least one treatment part in a stationary position with respect to the treatment chamber during treatment,
wherein the boundary between the at least one treatment part and the at least one non-treatment part of the component is defined
by a boundary containment surface of the treatment chamber at a fixed location with respect to the component, the boundary
containment surface being a sealing surface directly contacting the component when the at least one treatment part is placed
in the fluidised bed,

the component is initially installed in the treatment chamber before the solid particle bed is fluidised so that the at least
one treatment part of the component is located above the surface of the solid particle bed before fluidisation, and

on fluidisation, the at least one treatment part of the component is then completely submerged under the rising surface of
the fluidised bed.

US Pat. No. 9,120,173

BONDING OF METAL COMPONENTS

ROLLS-ROYCE PLC, London ...

1. A method of bonding a first component comprising titanium to a second metallic component containing nickel, the method
comprising:
providing the first component comprising titanium, and the second metallic component comprising a nickel-titanium shape memory
alloy;

interposing a plurality of metallic layers between the first component and the second component; and
heating the plurality of metallic layers so as to form a bond between the first component and the second component by brazing,
wherein the heating comprises heating the plurality of metallic layers to a temperature at which only a portion of the plurality
of metallic layers melts such that at least a remaining portion of the plurality of metallic layers remains solid during the
brazing.

US Pat. No. 9,114,496

METHOD OF TIP GRINDING THE BLADES OF A GAS TURBINE ROTOR

ROLLS-ROYCE plc, Derby (...

6. A grinding apparatus for grinding a tip of a blade that forms part of a rotor for a gas turbine engine, the grinding apparatus
comprising:
a mount for holding the rotor blade assembly;
an abrasive member for grinding the tip of the blade;
a nozzle in fluid communication with a source of compressed fluid, wherein the nozzle can be adapted to project the compressed
fluid onto each of a plurality of blades of the blade assembly so as to position each blade in a predetermined position relative
to the rotor blade assembly.

US Pat. No. 9,090,353

MOUNTING ASSEMBLY

ROLLS-ROYCE PLC, London ...

1. A mounting assembly for attaching a ducted fan gas turbine engine to an aircraft, the engine having an air intake, a propulsive
fan, a fan case surrounding the fan, and a core engine, the air intake being attached to the front of the fan case such that
loads acting on the air intake are primarily transmitted to the fan case, wherein the assembly includes:
a support structure extending in an axial direction of the engine and having a rearward region which is adapted to attach
to the aircraft, and

a front engine mount comprising a load distribution ring that is coaxial with, and perpendicular to, the fan case and a thrust
reverse unit and that is rearward of the fan case and forward of the thrust reverse unit, the load distribution ring integrally
forming a single, non-disassemblable body with the fan case, and being joined to a forward region of the support structure;
and

wherein, in use, the support structure and the load distribution ring provide a primary load path for the loads transmitted
to the fan case by the air intake, and thence to the aircraft.

US Pat. No. 9,091,178

SEALING ARRANGEMENT

ROLLS-ROYCE PLC, London ...

1. A sealing arrangement between first and second components which are rotatable relatively to each other, the sealing arrangement
comprising a sealing ring rotationally secured to the first component and disposed between a pair of runners rotationally
secured to the second component to define fluid riding gaps between the sealing ring and the runners, and to define a buffer
cavity between the sealing ring, the runners and the second component, the buffer cavity communicating with a source of buffer
fluid through a port in the first or second component; wherein
the sealing ring has a passage extending from a surface of the sealing ring adjacent the first component and communicating
with the buffer cavity, and the passage extends from a recess in the surface of the sealing ring adjacent the first component.

US Pat. No. 9,068,475

STATOR VANE ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A stator vane assembly, comprising:
a support structure arranged to be mounted to a mounting structure and having first and second circumferentially extending
axially spaced rails arranged to be retained within corresponding first and second channels provided in the mounting structure
and a circumferentially extending platform section axially extending therebetween;

a stator vane radially extending from the platform section; and
a continuity member coupled to the support structure and having a first portion disposed between the first rail and the first
channel and a second portion disposed between the second rail and the second channel, and a central portion extending across
and substantially in contact with the platform section between the first and second portions, thereby providing a substantially
continuous gas-washed surface across the mounting structure and the support structure.

US Pat. No. 9,061,347

METHOD OF SEALING COOLING HOLES

ROLLS-ROYCE plc, London ...

1. A method of selectively sealing at least one cooling hole provided on an aerofoil component, the method comprising:
heating a surface of the aerofoil component such that the surface is above room temperature;
applying a thermoplastic material in a molten phase to the surface of the aerofoil component to cover one or more selected
cooling holes while the surface is heated above room temperature to facilitate adhesion; and

cooling the thermoplastic material to set the thermoplastic material.

US Pat. No. 9,056,352

CLIPPING DIE FOR CLIPPING A COMPONENT

ROLLS-ROYCE plc, London ...

1. A clipping die for clipping a component, the clipping die comprising:
a riser having a support surface with a cutting edge for clipping the component under the action of a punch;
two independently movable referencing members provided for engagement with reference portions located at opposing ends of
the component; and

two resilient elements built to be independent of each other, wherein
the two referencing members are each mounted on a respective one of the resilient elements, and
under the action of the punch: (i) the riser moves through clipping steels to clip the component, and (ii) each of the resilient
elements can independently displace the respective one of the two referencing members into a position such that the component
is fully supported by the support surface.

US Pat. No. 9,309,811

FUEL DELIVERY SYSTEM

ROLLS-ROYCE plc, London ...

1. A fuel delivery system for an engine, the system comprising:
a vapour trail detection sensor configured to generate a detection signal indicative of a characteristic of a vapour trail;
a regulator configured to regulate a volume of a first and a second fuel composition delivered to the engine as resultant
fuel composition; and

a controller arranged to undertake a search of trial fuel compositions by controlling the regulator to deliver to the engine
a plurality of trial fuel compositions having different ratios of the first and second fuel compositions and to control delivery
of a resultant fuel composition to the engine in response to the vapour trail characteristic detection signals for said plurality
of trial fuel compositions,

wherein the search comprises a first coarse search to identify a sub-range or point for which a desirable value of the vapour
trail characteristic is sensed, and a second search which identifies an optimal final fuel composition in the vicinity of
said sub-range or point.

US Pat. No. 9,289,827

MOULD ASSEMBLY FOR A HOT ISOSTATIC PRESSING PROCESS

ROLLS-ROYCE PLC, London ...

1. A mould assembly for a hot isostatic pressing, HIP, process for fabricating a component, comprising:
a first part which includes a shaped surface for forming a first external surface of the component, the shaped surface having
at least one recess formed within the shaped surface;

a second part arranged to move relative to the first part during the HIP process so as to compress a powder in-fill held therebetween
and form a second external surface of the component, wherein the first part is made from a substantially incompressible material
which does not deform during the HIP process so as to be re-usable, and wherein the second part includes a formation corresponding
to at least one recess in the first part, the formation being configured to focus pressure toward a first end of the recess
so as to aid consolidation of the powder in-fill at a second end of the recess.

US Pat. No. 9,222,369

JOINT ASSEMBLY FOR AN ANNULAR STRUCTURE

ROLLS-ROYCE plc, London ...

1. A joint assembly for an annular structure comprising:
a first annular member which is a casing having a first radially extending flange;
a second annular member which is a casing having a second radially extending flange, the first radially extending flange having
a plurality of circumferentially spaced first apertures extending axially there-through, the second radially extending flange
having a plurality of circumferentially spaced second apertures extending axially there-through, the first and second apertures
being circumferentially aligned;

a plurality of fasteners, each fastener being arranged to extend through a respective pair of the first and second apertures
to join the first and second annular members together, the first radially extending flange having a plurality of circumferentially
spaced third apertures extending axially there-through, the second radially extending flange having a plurality of circumferentially
spaced fourth apertures extending axially there-through, the third and fourth apertures being circumferentially aligned; and

a plurality of extending members, a first extending member of the plurality of extending members being arranged to extend
axially through a respective pair of the third and fourth apertures, the first extending member having at least one circumferentially
extending flange, each circumferentially extending flange having an extending member aperture extending axially there-through
and a first fastener of the plurality of fasteners extending through the extending member aperture in the at least one circumferentially
extending flange of the first extending member to clamp the first extending member against the first flange, the first fastener
further extending through the respective pair of the first and second apertures.

US Pat. No. 9,204,497

ELECTRICAL STRUCTURE HAVING A GROUNDING PLANE

ROLLS-ROYCE PLC, London ...

1. A rigid electrical raft assembly having a rigid electrical raft, the rigid electrical raft assembly comprising:
a rigid material having multiple electrical conductors embedded therein; and
an electrically conductive screen layer, wherein:
the rigid electrical raft assembly further comprises a mounting fixture for attaching the rigid electrical raft assembly to
a mounting structure of an apparatus;

the mounting fixture is in electrical contact with the electrically conductive screen layer;
the mounting fixture comprises an electrically conductive raft fastner that passes through the rigid electrical raft;
one end of the electrically conductive raft fastener is in electrical contact with the electrically conductive screen layer;
and

another end of the electrically conductive raft fastener extends through the rigid electrical raft for connection with said
mounting structure of said apparatus.

US Pat. No. 9,168,686

APPARATUS FOR FORMING A COMPOSITE COMPONENT

ROLLS-ROYCE plc, Derby (...

1. An apparatus for forming a composite component, the apparatus comprising:
a deformable mould tool at least partially defining a mould cavity, the deformable mould tool having a first stiffness;
at least two peristaltic actuators configured to generate a peristaltic pressure wave in the mould tool, each peristaltic
actuator including rollers; and

a monolithic interface layer provided between an external surface of the mould tool and the at least two peristaltic actuators,
the interface layer extending continuously over at least the mould cavity, the interface layer having a second stiffness greater
than the first stiffness, and the rollers of the at least two peristaltic actuators being mounted to contact the interface
layer and roll across a surface of the interface layer.

US Pat. No. 9,133,539

METHOD AND EQUIPMENT FOR SHAPING A CAST COMPONENT

ROLLS-ROYCE plc, London ...

1. A method for deforming a component cast from a titanium alloy, such that each of a volume or the component, a density of
the component, and a surface area of the component remains substantially constant throughout a deformation process, the method
comprising:
heating the component to a plastic temperature such that the component becomes plastically deformable;
applying a force in a predetermined direction to at least one region of the component while the component is at the plastic
temperature, the force being applied by a deformation member configured to engage with a least a part of a surface of the
component, the deformation member comprising a substantially rigid body, the substantially rigid body being provided with
location features for engagement with the surface of the component, the location features defining a desired component geometric
shape, and the component being provided with location pads for engagement with the location features of the substantially
rigid body, the force being communicated from the deformation member to the location pads the reacted upon at the location
pads by a base member; and

reducing a temperature of the component to below the plastic temperature to thereby plastically deform the component to the
desired component geometric shape.

US Pat. No. 9,045,834

SACRIFICIAL ANODE

ROLLS-ROYCE PLC, London ...

1. A metallic body comprising:
a sacrificial anode located within a recess of the metallic body, the sacrificial anode comprising:
a first layer of a first material; and,
a second layer of a second material which is located proximate to the first layer, wherein the first material is more anodic
with respect to a galvanic series than the second material,

wherein the sacrificial anode is separated from the metallic body by a channel and electrically connected thereto, wherein
the metallic body is more cathodic with respect to a galvanic series than the first and second materials, wherein the channel
is formed by the anode being located within the recess and separated from sides of the channel such that a fluid can flow
around and contact sides of the anode and a bottom surface of the recess, and

wherein (i) the recess is defined by fluid washed surfaces of the metallic body and (ii) a surface of the second material
is exposed and is located in a same plane as a fluid washed surface of the metallic body other than the fluid washed surfaces
defining the recess.

US Pat. No. 9,447,817

BEARING STRUCTURE

ROLLS-ROYCE plc, London ...

1. A bearing structure comprising:
a first bearing having a first inner race, a first outer race and a first set of rolling elements housed between the first
inner race and the first outer race;

a second bearing having a second inner race, a second outer race and a second set of rolling elements housed between the second
inner race and the second outer race;

a housing surrounding the first bearing;
a first compliant element, the first compliant element fixedly connected to the first outer race,
a rigid diaphragm having a radially inner end fixedly connected to the first outer race at a position spaced from the connection
between the first compliant element and the first outer race, and a radially outer end flexibly connected to the housing,

wherein the first compliant element, first outer race and rigid diaphragm at least partly define a pressure chamber; and
wherein the first outer race is axially slidable relative to the second outer race such that an increase in pressure in the
pressure chamber causes a change in axial spacing between the first and second outer races.

US Pat. No. 9,404,385

SHAFT BREAK DETECTION

ROLLS-ROYCE PLC, London ...

1. A method to detect shaft break comprising:
monitoring a first parameter and a second parameter;
defining a two-dimensional parameter space that is a function of the first and second parameters, the two-dimensional parameter
space comprising integration regions;

defining an integration function for each integration region;
for measured values of the first and second parameters, determining an applicable integration region of the integration regions
and applying the integration function to the first parameter to give an integration result;

incrementing a counter when the integration result crosses a predetermined threshold; and
setting a shaft break signal to TRUE and reducing or stopping a drive to a shaft when the counter reaches a predetermined
level.

US Pat. No. 9,255,521

GAS TURBINE ENGINE INSTALLATION INCLUDING A FLEXIBLE PRINTED CIRCUIT BOARD HARNESS FOR TRANSFERRING ELECTRICAL SIGNALS AROUND THE GAS TURBINE ENGINE INSTALLATION

ROLLS-ROYCE plc, London ...

1. A gas turbine engine installation comprising:
a flexible printed circuit board harness arranged to transfer electrical signals around the gas turbine engine installation,
the flexible printed circuit board harness being a thin, elongate member having upper and lower parallel major surfaces defined
by a length (x) and a width (y), the flexible printed circuit harness further having a thickness (z) normal to the parallel
major surfaces, the width (y) being longer than the thickness (z); and

at least one clip holding the flexible printed circuit board harness, each clip comprising a generally U-shaped member defined
by a base having a first end and a second end, the base spanning the width (y) between the first end and the second end, each
clip further comprising a first sidewall extending from the first end and a second sidewall extending from the second end,
and an opening opposite the base and between the first and second sidewalls for the insertion of the flexible printed circuit
board harness wherein:

the first sidewall has a first side-tooth extending therefrom, and the second sidewall has a second side-tooth extending therefrom;
the base has a first set of base-teeth and a second set of base-teeth arranged such that a first portion of the flexible printed
circuit board harness is gripped between tips of the first set of base-teeth and a tip of the first side-tooth, and a second
portion of the flexible printed circuit board harness is gripped between tips of the second set of base-teeth and a tip of
the second side-tooth; and

the width (y) of the flexible printed circuit board harness is contained entirely between the first and second sidewalls.

US Pat. No. 9,199,309

HOT ISOSTATIC PRESSING TOOL AND A METHOD OF MANUFACTURING AN ARTICLE FROM POWDER MATERIAL BY HOT ISOSTATIC PRESSING

ROLLS-ROYCE plc, London ...

17. A method of manufacturing an article from powder material by hot isostatic pressing, the method comprising the steps of:
—
a) forming a plurality of canister members,
b) providing interlocking features on an at least one set of adjacent canister members, the interlocking features forming
a U-shaped or a Z-shaped leakage flow path between the at least one set of adjacent canister members,

c) sealing the canister members together to form a hot isostatic pressing tool,
d) supplying powder material into a chamber defined between the plurality of canister members of the hot isostatic pressing
tool,

e) evacuating gases from the chamber and then sealing the chamber,
f) applying heat and pressure to consolidate the powder material within the chamber of the hot isostatic pressing tool to
form a consolidated powder material article, and

g) removing the hot isostatic pressing tool from the consolidated powder material article.

US Pat. No. 9,102,025

ADHESIVE FASTENING ELEMENTS FOR HOLDING A WORKPIECE AND METHODS OF DE-BONDING A WORKPIECE FROM AN ADHESIVE FASTENING ELEMENT

ROLLS-ROYCE plc, London ...

1. An adhesive fastening element for holding a workpiece, comprising a plurality of pins which are individually movable along
a longitudinal axis of the adhesive fastening element to conform to the workpiece, one or more of the pins having an embedded
adhesive delivery tube configured to supply adhesive to an exterior surface of the adhesive fastening element to bond the
pins to the workpiece.

US Pat. No. 9,051,850

SUPPORT STRUCTURE FORMING METHOD

ROLLS-ROYCE plc, London ...

1. A method of forming an annular support structure for fastening a component of a gas turbine engine to a static part of
the engine, the support structure having:
a substantially frustoconical skin portion which, in use, extends inwardly from the static part; and
a flange portion which extends inwardly from an inner edge of the skin portion, and to which, in use, is attached a mating
flange extending outwardly from the component, the flange portion having an engagement face against which a corresponding
face of the mating flange is secured, and the flange portion further having an inwardly-facing land at an outer edge of the
engagement face which restrains the component against radial movement,

the method comprising:
providing a blank;
flow-forming the blank over a mandrel into a near net-shape of the support structure; and
removing excess material from the near net-shape to form the land and finish the support structure.

US Pat. No. 9,046,270

CONTROLLABLE FLAMEHOLDER

ROLLS-ROYCE plc, London ...

1. A flameholder for holding a flame comprising a flow of combusting fluid, comprising:
a magnetic-field generator comprising a first pole piece having a cavity within which a second pole piece is located in such
a way that an opening is formed between the first and second pole pieces, the opening having an inlet and an outlet, and the
opening providing a flow path for the combusting fluid, the magnetic-field generator in use generating a magnetic field across
the opening,

wherein the first pole piece has a first recess and a second recess on an inner surface of the first pole piece that faces
the second pole piece, and the second pole piece has a first recess and a second recess on an outer surface of the second
pole piece that faces the first pole piece,

wherein in use the combusting fluid flows in the flow path through the magnetic field such that an electric current is induced
in the combusting fluid, thereby generating a force on the combusting fluid that is opposed to a flow direction of the combusting
fluid, the induced electric current being in a form of a closed loop in a plane perpendicular to the flow direction of the
combusting fluid such that in use the induced electric current can flow in the closed loop entirely within the combusting
fluid.

US Pat. No. 9,472,872

ELECTRICAL HARNESS

ROLLS-ROYCE PLC, London ...

1. An electrical harness formed from a flexible printed circuit board, the harness comprising:
the flexible printed circuit board comprising at least one terminating region and being configured to form the harness and
to be wound around at least a part of a gas turbine engine, at least a portion of the flexible printed circuit board being
enclosed in an elastically deformable material;

a plurality of conductive tracks; and
at least one harness connector at the at least one terminating region of the flexible printed circuit board configured to
join the harness to a complementary connector, wherein

the harness connector includes a back-shell and at least one elongate terminal supported at a position within the back-shell
such that, in use, when the harness connector joins with the complementary connector, the elongate terminals are presented
for electrical connection at a first connection end thereof with mating terminals of the complementary connector,

the at least one terminating region of the flexible printed circuit board has at least one receiving hole penetrating through
the at least one terminating region perpendicularly to a plane of the at least one terminating region and joining to the respective
conductive track of the harness, the at least one terminating region being covered by a detachable lid of the back-shell and
making a detachable press fit connection to the respective harness connector such that a second connection end of the elongate
terminal of the harness connector is received in the receiving hole to electrically connect the elongate terminal with the
conductive track, the detachable lid being detachable from the rest of the back-shell to facilitate engagement and detachment
of the at least one terminating region to the harness connector,

the elongate terminal is supported within the harness connector such that, when the harness connector is disconnected from
the complementary connector, and when the at least one terminating region is detached from the harness connector, the elongate
terminal retains said position within the back-shell,

the elongate terminal extends substantially perpendicularly to the plane of the at least one terminating region of the flexible
printed circuit board, and

the flexible printed circuit board has a length dimension that is greater than a width dimension, the flexible printed circuit
board and the plurality of conductive tracks formed therein extend away from the at least one terminating region in the direction
of the length dimension so as to form the electrical harness.

US Pat. No. 9,356,502

MAGNETIC GEAR ARRANGEMENT HAVING A VARIABLE GEAR RATIO

ROLLS-ROYCE plc, London ...

1. A magnetic gear arrangement comprising:
a magnetically active gear member for generating a first magnetic field,
a magnetically passive gear member, and
a number of interpoles between said magnetically active gear member and said magnetically passive gear member for modulating
the first magnetic field, wherein:

a number of magnetic poles are generated within the magnetically passive gear member by the modulated first magnetic field,
the generated poles forming a second magnetic field,

the magnetically passive gear member is formed of sufficiently magnetically hard material that the first magnetic field couples
to the second magnetic field to produce a gear ratio between the magnetically active and the magnetically passive gear members,
and

a magnetically active gear member has a plurality of poles, the number of generated magnetic poles is equal to a sum of the
number of poles on the magnetically active gear member and the number of interpoles.

US Pat. No. 9,327,446

JOINT STRUCTURE AND METHOD

ROLLS-ROYCE plc, Derby (...

1. A joint between a substrate and an adjacent body, the substrate comprising a first metal material and having a first surface
and the adjacent body being formed of a second material and having an opposing surface, the joint comprising:
a fastening projection extending outwardly from the first surface into the adjacent body for retaining the adjacent body relative
to the substrate, the fastening projection defining a stiffness-regulating cavity and including:

a stem portion adjacent the first surface,
a first plurality of branches extending from the stem portion, and
a second plurality of branches extending from at least one branch of the first plurality of branches,
wherein (i) at least one branch of the first plurality of branches and at least one branch of the second plurality of branches
define a dendritic structure and (ii) the first plurality of branches and the second plurality of branches are embedded into
the adjacent body such that the branches disperse a load applied to the joint over a wider area or volume of the adjacent
body.

US Pat. No. 9,291,269

INTERSHAFT SEAL

ROLLS-ROYCE PLC, London ...

1. An assembly, the assembly comprising:
a rotatable inner shaft;
a rotatable outer shaft, wherein the rotatable inner shaft and the rotatable outer shaft are coaxial, and the rotatable inner
shaft and the rotatable outer shaft both rotate relative to each other;

an intershaft seal that is located in an annular space between the rotatable inner shaft and the rotatable outer shaft, wherein
the intershaft seal maintains an axial pressure differential between a fluid pressure on a first side of the intershaft seal
and a different fluid pressure on a second side of the intershaft seal, the intershaft seal including:

a first runner which extends circumferentially around one of the rotatable inner shaft and the rotatable outer shaft and projects
therefrom into the annular space, and

a sealing ring which is coaxial with both the shaft and the rotatable outer shaft and has a first end face, the first runner
forming a first annular sealing interface with the first end face of the sealing ring,

wherein the sealing ring has a main body portion formed of a first material having a first stiffness,
a retaining ring fixedly fitted to a radially outward side of the main body portion of the sealing ring and formed of a second
material having a second stiffness, the second stiffness being greater than the first stiffness such that the retaining ring
reduces or prevents radial growth of the sealing ring relative to the rotatable outer shaft under centrifugal loading, the
retaining ring having a first anti-rotation formation projecting from an outer side of the retaining ring, wherein an outer
surface of the retaining ring and the first anti-rotation formation opposes an inner surface of the rotatable outer shaft.

US Pat. No. 9,074,478

DAMPED ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A damped assembly for a gas turbine engine, comprising:
a first member and a second member mechanically connected via an intermediate vibration dampener which has at least first
and second surfaces for contacting the first and second members respectively,

wherein either or both of the first and second surfaces include a plurality of raised portions in direct contact with the
respective member and a plurality of recessed portions which contain adhesive for bonding the intermediate vibration dampener
to the respective member,

wherein the ratio of the raised portion surface area to the recessed portion surface area for each of the first and second
surfaces is predetermined so as to provide a required dampening for a predetermined frequency range,

wherein a distribution of the raised portions and recessed portions on either or both of the first and second surfaces is
non-uniform,

wherein the second member is an elongate member and the intermediate vibration dampener is a sleeve positioned over an end
of the elongate member, and

wherein a dimension, with respect to a longitudinal axis of the second member, of at least one of the recessed and/or raised
portions is extended as compared to at least one other of the recessed and/or raised portions, along the longitudinal axis
of the second member.

US Pat. No. 9,051,972

TORQUE-LIMITING COUPLING

ROLLS-ROYCE PLC, London ...

1. A torque-limiting coupling for connecting coaxial, first and second rotating shafts, the coupling comprising:
a first connecting part on an end of the first shaft,
a second connecting part on an end of the second shaft, and
an interconnector which joins to the first connecting part at a first engagement formation, and which joins to the second
connecting part at a second engagement formation;

wherein the first engagement formation is a threaded engagement formation which threadingly joins the interconnector to the
first connecting part, and the second engagement formation is configured to resist rotational movement of the interconnector
relative to the second connecting part, but to allow movement of the interconnector in the axial direction of the shafts,
wherein the interconnector is configured to be elastically deformed when joined to the first connecting part and the second
connecting part, the elastic deformation exerting a predetermined radial pressure on the threaded engagement formation;

whereby, when a torque transmitted by the shafts exceeds a predetermined value, the interconnector rotates relative to the
first connecting part at the threaded engagement formation, the resistance to rotational movement relative to the second connecting
part causing the interconnector to move in an axial direction of the shafts and come out of engagement with the first and/or
the second connecting part.

US Pat. No. 9,429,074

AERODYNAMIC SWEPT VANES FOR FUEL INJECTORS

Rolls-Royce plc, (GB)

1. A fuel nozzle for a gas turbine engine comprising:
a) a nozzle body having a longitudinal axis;
b) an annular air passage defined within the nozzle body; and
c) a plurality of circumferentially spaced apart axially extending aerodynamic swirl vanes disposed within the annular air
passage, each of the swirl vane having an axially swept cross-sectional profile along the radial extent thereof,

wherein the cross-sectional profile of each of the swirl vane has proportions that vary along the radial extent of the swirl
vane.

US Pat. No. 9,410,444

SHAFT BREAK DETECTION

ROLLS-ROYCE plc, London ...

1. A method of detecting shaft break in a shaft system comprising a shaft coupled between two masses, the method comprising
steps to:
define a time-dependent rotational speed equation for the shaft in terms of system inertia for an engine transient event;
discretize the rotational speed equation in terms of a discrete time constant in a discrete domain;
recursively define the discretized equation to give a recursive equation;
solve the recursive equation to determine the discrete time constant;
define a threshold as a function of engine power, wherein the threshold is a value of the discrete time constant calculated
as the function of engine power; and set a shaft break detection signal to TRUE and reduce or stop a drive to the shaft if
the discrete time constant is less than the threshold.

US Pat. No. 9,383,310

APPARATUS AND METHOD FOR INSPECTING AN ARTICLE

ROLLS-ROYCE plc, London ...

1. A method of determining the value of a boundary between a primary grain and a secondary grain in a component, the method
comprising the steps of:
identifying a boundary between a primary grain and a secondary grain which are presented on a surface of the component;
illuminating the primary grain with a beam from a light source and manipulating the relative orientation of the surface, beam
and a detector detecting the light reflected from the surface and determining a first relative orientation which provides
the peak reflectance of the beam to the detector;

illuminating the secondary grain with a beam from a light source and manipulating the relative orientation of the surface,
beam and the detector detecting the light reflected from the surface and determining a second relative orientation which provides
the peak reflectance of the beam to the detector; wherein the difference between the first and second relative orientations
gives a value that indicates the magnitude of the angle boundary.

US Pat. No. 9,372,176

ULTRASONIC INSPECTION METHOD

ROLLS-ROYCE PLC, London ...

1. An ultrasonic inspection method for inspecting a first article, the method comprising, in a first inspection process:
determining a distance between a first surface of the first article and a nominal axis of a transducer arrangement at three
or more measurement locations along the axis of the surface;
using the determined distances to produce a mathematical model of the surface of the first article;
using the transducer arrangement to transmit a first ultrasonic wave from a first side of the first article through the first
surface of the first article at a plurality of inspection locations along the nominal axis, and receiving a first transmitted
waveform which has passed through the first surface;

using the model to normalise each first transmitted waveform at each inspection location to the nominal axis; and
identifying the location of a first signature signal from the first normalised transmitted waveform at each inspection location.

US Pat. No. 9,354,151

APPARATUS FOR FOUR-POINT BEND TESTING

ROLLS-ROYCE plc, Derby (...

1. A rig for testing an aerofoil component in four-point bending, the aerofoil component having a first aerofoil surface and
an oppositely-facing second aerofoil surface, the rig including a first fixture and a second fixture movable relative to each
other to apply a cyclically varying load to the first aerofoil surface and the second aerofoil surface of the aerofoil component,
the first fixture having two first loading formations which are positioned to apply the load to the first aerofoil surface
of the component, the two first loading formations being spaced apart in a spanwise direction of the component, and

the second fixture having two second loading formations which are positioned to apply the load to the second aerofoil surface
of the component, the two second loading formations also being spaced apart in the spanwise direction of the component, the
spanwise spacing of the two second loading formations being less than the spanwise spacing of the two first loading formations,
and the two second loading formations being positioned relative to the two first loading formations such that the first fixtures
and the second fixtures apply the load in a four-point bending arrangement;

wherein the second fixture is configured so that the two second loading formations are movable relative to each other in a
direction of application of the load to balance the load between the two second loading formations during the cyclical load
variation.

US Pat. No. 9,316,231

CATCHER RING ASSEMBLY

ROLLS-ROYCE plc, London ...

1. A catcher ring assembly configured to limit axial movement of a turbomachine shaft assembly during a failure mode, the
catcher ring assembly comprising:
a catcher ring disposable about and connectable to the shaft assembly, both the catcher ring and the shaft assembly include
a protrusion and a recess, the recess of the catcher ring corresponding in shape to the protrusion of the shaft assembly,
and the recess of the shaft assembly corresponding in shape to the protrusion of the catcher ring, the protrusions and the
recesses being circumferentially disposed about a longitudinal axis of the shaft assembly, and the protrusion of the catcher
ring extending away from the catcher ring in an axial direction and the protrusion of the shaft assembly extending away from
the shaft assembly in an opposing axial direction, and

a nut assembly including an intermediate element and a nut, the intermediate element being provided between the nut and the
catcher ring, wherein:

the catcher ring assembly includes a spline or recess for engagement with a corresponding recess or spline provided on the
shaft assembly respectively, the recess and spline being configured to limit rotation of the catcher ring assembly relative
to the shaft assembly, and

the intermediate element includes the spline or recess for engagement with the corresponding recess or spline provided on
the shaft assembly respectively.

US Pat. No. 9,236,830

ELECTRICAL MACHINE

ROLLS-ROYCE plc, London ...

1. An electrical machine comprising:
a stator including a plurality of three or more electrical phases;
a rotor having a plurality of magnets, each electrical phase comprising at least one coil and power electronics;
a power supply for supplying power to each of the power electronics;
electrical connections connecting each phase to at least two other phases while bypassing the power supply;
means to detect an electrical short circuit in at least one of the coils to determine a faulted turn of the at least one coil,
and

means to supply an electrical current to the at least one of the coils having a faulted turn when an electrical short circuit
is detected in the at least one of the coils, wherein:

the means to supply the electrical current to the at least one of the coils having a faulted turn comprises electrical connections
between at least one un-faulted electrical phase of the electrical machine and the phase containing the at least one of the
coils having a faulted turn, and

the at least one un-faulted electrical phase of the electrical maching is arranged to supply the electrical current to the
electrical phase containing the at least one of the coils having a faulted turn.

US Pat. No. 9,169,804

DUCT AND METHOD FOR DAMPING PRESSURE WAVES CAUSED BY THERMOACOUSTIC INSTABILITY

ROLLS-ROYCE plc, London ...

1. A duct comprising:
a locking Helmholtz resonator positioned on a circumference of the duct, the locking Helmholtz resonator being tuned to a
first frequency; and

one or more damping Helmholtz resonators tuned to a second frequency different from the first frequency of the locking Helmholtz
resonator, the one or more damping Helmholtz resonators being positioned on the circumference of the duct:

at 90 degrees and/or 270 degrees from the locking Helmholtz resonator, or
adjacent to 90 degrees and/or 270 degrees from the locking Helmholtz resonator, the one or more damping Helmholtz resonators
being adjacent to 90 degrees and/or 270 degrees from the locking Helmholtz resonator include: (i) a pair of damping Helmholtz
resonators positioned at either side of 90 degrees, and/or (ii) a pair of damping Helmholtz resonators positioned at either
side of 270 degrees.

US Pat. No. 9,169,045

GAS TURBINE ENGINE BLADE CONTAINMENT ARRANGEMENT

ROLLS-ROYCE plc, London ...

1. A turbofan gas turbine engine comprising a fan, a fan casing and a fan blade containment arrangement,
the fan comprising a fan rotor having a plurality of fan blades,
the fan casing surrounding the fan rotor and fan blades,
the fan blade containment arrangement surrounding the fan rotor and fan blades, the fan blade containment arrangement being
arranged radially between the fan casing and the fan, the fan blade containment arrangement being axially shorter than the
fan casing, the fan blade containment arrangement comprising a first layer of cellular material radially within an inner surface
of the fan casing, a septum layer radially within an inner surface of the first layer of cellular material, a second layer
of cellular material radially within an inner surface of the septum layer, a ductile layer radially within an inner surface
of the second layer of cellular material and a layer of abradable material radially within an inner surface of the ductile
layer, the ductile layer being axially shorter than the fan casing, the ductile layer having a higher yield stress than the
layer of abradable material, the ductile layer having ductility which is greater than a crush initiation limit of the first
and second layers of cellular material and the ductile layer being arranged to contain at least a portion of a detached blade
without rupturing.

US Pat. No. 9,170,182

METHOD OF FATIGUE TESTING A COMPONENT

ROLLS-ROYCE PLC, London ...

1. A method of fatigue testing a component comprising the steps of:
a) providing a component having a surface and machining a channel of predetermined depth and predetermined width in the surface
of the component such that the channel has a closed bottom, a first side, and a second side and is open at the surface of
the component,

b) applying a salt solution into the channel in the surface of the component and heating the component to a suitable temperature
to evaporate the solvent from the salt solution to deposit the salt in the channel in the surface of the component,

c) placing the component in a corrosive atmosphere for a predetermined period of time at a predetermined temperature to precondition
the grain boundaries, and

d) fatigue testing the component.

US Pat. No. 9,163,513

BALANCED ROTOR FOR A TURBINE ENGINE

ROLLS-ROYCE plc, London ...

11. A balanced rotor for a turbine engine, comprising:
a rotor component extending around an axis and having a circumferential slot;
a row of rotor blades extending radially outwardly from the circumference of the rotor component, each blade having a blade
root inserted within the circumferential slot; and

a balance weight wholly within the circumferential slot, the weight having aloud which extends beneath a blade root and having
a mass-adjustment protrusion extending from the land in a radial direction relative to the axis of the rotor component and
which lies wholly between the blade root and an adjacent blade root and has a width in the axial direction that is less than
the axial width of the slot, wherein

the land has edges that extend in a circumferential direction, the edges each having a lip aligned with a respective root
chamfer for prohibiting axial movement of the weight relative to the root.

US Pat. No. 9,109,733

HYDRAULIC FLUID TRANSFER COUPLING

ROLLS-ROYCE plc, London ...

1. A hydraulic fluid transfer coupling having a stator, a first coaxial rotor rotatable about the stator, and a second coaxial
rotor rotatable about the stator, the first rotor being radially inwards of the stator, the second rotor being radially outwards
of the stator, at least part of the first rotor axially overlapping with the stator across a first rotary interface, and at
least part of the second rotor axially overlapping with the stator across a second rotary interface;
wherein the first rotor carries one or more first rotating fluid lines, the second rotor carries one or more second rotating
fluid lines, and the stator carries one or more first static fluid lines corresponding to the first rotating fluid lines and
one or more second static fluid lines corresponding to the second rotating fluid lines, each pair of a first rotating fluid
line and the corresponding first static fluid line being fluidly coupled across the first rotary interface and each pair of
a second rotating fluid line and the corresponding second static fluid line being fluidly coupled across the second rotary
interface, whereby hydraulic fluid is transferable between each static fluid line and the corresponding rotating fluid line,
and

wherein the first static fluid lines are grouped at one side of the stator, and the second static fluid lines are grouped
at another side of the stator.

US Pat. No. 9,102,396

MECHANICAL JOINT

ROLLS-ROYCE PLC, London ...

1. A mechanical joint for joining two components, the mechanical joint comprising:
a male part on one component and a corresponding female part on the other component, the male and female parts including:
respective castellations that intercalate on insertion of the male part into the female part along a direction of insertion,
the respective castellations having indentations, and

respective abutment surfaces formed on projections of the respective castellations, the respective castellations being capable
of rotating relative to each other around the direction of insertion upon insertion of the male part into the female part,
and in response to rotation of the respective castellations: (i) the respective abutment surfaces of the male and female parts
are face aligned to prevent the parts from being pulled apart, and (ii) the indentations of the respective castellations are
face aligned; and

one or more locking members configured to removably insert into the aligned indentations to prevent further relative rotation
of the male and female parts.

US Pat. No. 9,074,484

COOLED ROTOR BLADE

ROLLS-ROYCE PLC, London ...

1. A cooled turbine rotor blade, for a gas turbine engine which has an annular flow path for conducting working fluid though
the engine, wherein the blade comprises:
an aerofoil section for extending across the annular flow path,
a root portion radially inward of the aerofoil section for joining the blade to a rotor disc of the engine, the root portion
comprising a recess portion; and

a platform between the aerofoil section and the root portion and that is radially outward of the recess portion, the platform
extending laterally relative to a radial direction of the engine to form an inner boundary of the annular flow path and to
provide a rear overhang portion which projects rearwardly;

wherein the platform contains at least one internal elongate plenum chamber for receiving cooling air, the longitudinal axis
of the plenum chamber being substantially aligned with the circumferential direction of the engine, wherein the longitudinal
axis of the plenum chamber is a longest dimension of the plenum chamber, the plenum chamber supplying the cooling air to a
plurality of exit holes formed in an external surface of the rear overhang portion to cool that portion, wherein the exit
holes communicate with the annular flow path, and the plenum chamber is located radially inward of a trailing edge of the
rear overhang portion, and wherein the longitudinal axis of the plenum chamber passes through a position in the platform radially
aligned with the trailing edge of the aerofoil section.

US Pat. No. 9,062,561

ENDWALL COMPONENT FOR A TURBINE STAGE OF A GAS TURBINE ENGINE

ROLLS-ROYCE PLC, London ...

1. A component forming an endwall for a working gas annulus of a turbine stage of a gas turbine engine comprising:
one or more internal passages behind the endwall which, in use, carry a flow of cooling air providing convective cooling for
the component at the endwall, the internal passages comprising:

a plurality of straight passage sections which connect in end-to-end series to provide a single flow path such that the connections
between nearest-neighboring passage sections form angled bends,

wherein a first portion of the passage sections lie in a first plane, a second portion of the passage sections lie in a second
plane which is spaced from and parallel to the first plane, and a third portion of the passage sections extend between the
first and the second planes,

wherein the internal passages extend between the first and second planes multiple times along the length of each internal
passage, and

wherein the first plane and the second plane are both spaced from and parallel to a gas washed plane of the endwall.

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. 9,730,274

ELECTRICAL CONNECTORS

ROLLS-ROYCE plc, London ...

1. An electrical raft assembly for a gas turbine engine comprising:
an electrical raft; and
an electrical unit of a gas turbine engine,
the electrical raft comprising:
a rigid material having multiple electrical conductors in the form of a flexible printed circuit embedded therein such that
the rigid material surrounds the electrical conductors and fixes the electrical conductors in position, the electrical conductors
being a part of an electrical harness of the gas turbine engine;

an electrical connector that electrically connects the electrical conductors in the electrical raft to the electrical unit;
linking conductors being provided between the electrical conductors and the electrical connector; and
a mounting surface on which the electrical unit is mounted, the electrical connector being provided in a recess extending
from the mounting surface into the rigid material; wherein

the electrical connector comprises:
an embedded portion that is embedded in the rigid material;
a contact portion, at least partially protruding from a surface of the rigid material, and being in electrical contact with
a unit electrical connector on the electrical unit; and

a resiliently biased portion configured to bias the contact portion away from the embedded portion when the contact portion
is moved towards the embedded portion, the resiliently biased portion acting in a direction substantially parallel to the
mounting surface, and wherein

the electrical unit and the electrical raft are mechanically fixed together using mechanical fixings that are independent
of the electrical connector.

US Pat. No. 9,538,643

COMPOSITE STRUCTURE AND RAFT FOR GAS TURBINE ENGINE

ROLLS-ROYCE PLC, London ...

11. A rigid raft for a gas turbine engine comprising a composite structure formed of rigid composite material in which non-metallic
continuous fibres reinforce a polymer matrix, the continuous fibres being electrically conductive, and the structure having
electrodes electrically connected to the continuous fibres,
wherein the composite material contains one or more insulating barriers which electrically divide the structure so that a
first portion of the material in electrical contact with one of the electrodes can be held at a different electrical potential
to a second portion of the material in electrical contact with another one of the electrodes, whereby, in use, an electrical
unit can be provided to electrically bridge the first and second portions of the material such that electrical signals can
be transmitted between the electrodes and the electrical unit via the continuous fibres, and

wherein the raft has at-least one of an electrical system in which metallic electrical conductors are embedded in the composite
material and a fluid system embedded in the composite material.

US Pat. No. 9,409,262

MATERIAL REMOVAL METHOD

ROLLS-ROYCE plc, Derby (...

1. A method of repairing a rotor or stator blade of a gas turbine engine, the method comprising:
in a first step, maneuvering a laser ablation tool within the gas turbine engine to a rotor or stator blade that is to be
repaired within the gas turbine engine, and directing an energy beam from the laser ablation tool toward the rotor or stator
blade to ablate a first region of material to form a gap extending through the rotor or stator blade between a repair region
and a base region of the rotor or stator blade, such that subsequent to the first step, the repair region and the base region
are joined by a connecting portion formed by a region of material not removed in the first step; and

in a second step, directing the energy beam toward the rotor or stator blade to ablate the repair region to remove the repair
region from the rotor or stator blade.

US Pat. No. 9,355,748

ROTARY ACTUATOR

ROLLS-ROYCE plc, London ...

1. A rotary actuator comprising:
a driven element comprising an axis of rotation and a plurality of recesses, the recesses being spaced around the axis of
rotation by a spacing angle; and

first, second and third latch elements, each latch element being movable between a retracted position, and an extended position
in which it engagingly locates against one or more of the plurality of recesses;

wherein the first latch element is angularly offset from the second and third latch elements respectively in rotationally
opposite directions around the axis of rotation by an offset angle, the offset angle being greater than the spacing angle;

whereby sequential movement of the first, second and third latch elements between respective retracted and extended positions
causes rotation of the driven element.

US Pat. No. 9,341,511

TIMING ANALYSIS

ROLLS-ROYCE plc, London ...

10. A method of processing individual blade timings detected by a stationary timing probe associated with an assembly of rotating
blades mounted on a rotor, the stationary timing probe detecting times at which the individual blade passes the stationary
timing probe, the method comprising:
obtaining blade timings detected by the stationary timing probe to obtain timing data, the timing data corresponding to an
actual position of the individual blade at a given time, the stationary timing probe being disposed relative to the individual
blade such that the stationary timing probe detects blade timings;

determining, for successive rotations of the individual blade, respective correlation factors for the individual blade, each
correlation factor quantifying a degree of correlation between the blade timings detected by the stationary timing probe for
the individual blade on a particular rotation and the blade timings detected by the stationary timing probe for the individual
blade on a previous rotation;

identifying in the timing data at least one resonant vibration event from a group consisting of: a synchronous vibration event
and an asynchronous vibration event, when at least one of the correlation factors crosses a predetermined threshold;

fitting an averaging curve to the blade timings outside the at least one identified resonant vibration event;
interpolating sections for the averaging curve at the blade timings inside the at least one identified one resonant vibration
event;

augmenting the averaging curve with the interpolated sections;
subtracting the augmented averaging curve from the blade timings to produce zeroed blade timings; and
outputting the zeroed blade timings indicating at least one resonant vibration event in order to modify or maintain: (i) a
design, (ii) an operation and/or (iii) a maintenance of the individual blade, the rotor, and/or the engine.

US Pat. No. 9,228,915

METHOD AND SYSTEM FOR DETECTING A FLOW BLOCKAGE IN A PIPE

ROLLS-ROYCE plc, London ...

1. A method of detecting a flow blockage in a pipe, the method comprising the steps of:
(a) arranging a fluid flow along the pipe, the pipe being in fluid communication with a pressure sensor;
(b) configuring the pressure sensor to measure a pressure within the pipe;
(c) recording a plurality of measurements of the pressure within the pipe;
(d) sampling ‘n’ successive values of the pressure within the pipe;
(e) performing an analytical test on the ‘n’ successive values, the analytical test producing an output value, the output
value being representative of a variation in the individual ones of the ‘n’ successive values;

(f) comparing the output value to a pre-defined threshold value, the threshold value being indicative of a lack of variation
in the individual ones of the ‘n’ successive values; and

(g) if the output value is less than the threshold value, generating an alert to thereby provide a user with an indication
of the presence of a flow blockage in the pipe.

US Pat. No. 9,203,286

MAGNETIC SHIELD

ROLLS-ROYCE plc, London ...

1. A superconducting rotary electrical machine having a winding on a rotor and a winding on a stator, wherein
at least one of the winding on the rotor and the winding on the stator is a superconducting winding;
a superconductor magnetic shield comprised of a superconducting material on the outside of the stator and at least partially
surrounding the windings on the rotor and the stator; and

a second magnetic shield at least partially surrounding the superconductor magnetic shield.

US Pat. No. 9,180,508

PRESS BRAKE

ROLLS-ROYCE plc, London ...

1. A press brake tool mounting device comprising a locking assembly that mounts a press brake tool and comprises:
a recess having a T-shaped cross section,
a location member having a T-shaped cross section and being located in part by the recess, and
a locking assembly engagement surface,
wherein:
the location member has a stem and an upper part, the upper part comprising a left hand top limb and a right hand top limb,
the location member is configured to engage with a beam of a press brake and comprises a location member engagement surface
provided on the left hand top limb of the location member,

the locking assembly comprises a locking arrangement configured to permit selective movement of the locking assembly engagement
surface between an unlocked position and a locked position,

in the unlocked position, the locking assembly engagement surface is configured to not press against the location member engagement
surface such that the locking assembly can be moved relative to the location member,

in the locked position, the locking assembly engagement surface is configured to press against the location member engagement
surface to hold the locking assembly and a bottom tool in a position relative to the location member, and

the recess is configured to receive the upper part of the location member so as to permit lateral movement of the locking
assembly relative to the location member when the locking arrangement is in the unlocked position.

US Pat. No. 9,140,131

METHODS FOR CONTROLLING FRICTION BETWEEN HETEROGENEOUS CONTACT SURFACES

ROLLS-ROYCE plc, London ...

1. A method of conditioning a first, heterogeneous contact surface for operational engagement with a second contact surface,
the method comprising: performing a smoothing operation on part or all of the first contact surface whilst subjecting said
part or all of the first contact surface respectively to a contact pre-stress acting directly on the part or all of the first
contact surface on which the smoothing operation is being performed, the contact pre-stress corresponding to a nominal operational
contact stress between the first and second contact surfaces.

US Pat. No. 9,390,821

GRIPPER MECHANISM

ROLLS-ROYCE plc, London ...

1. A gripper mechanism for moving an object having a surface cavity, the gripper mechanism comprising:
an actuation end moveable in an axial direction;
a rotary body;
a first mechanism configured such that movement of the actuation end in an axial direction rotates the rotary body;
a gripper moveable between an engaged position and a disengaged position, wherein in the engaged position the gripper is capable
of engaging an object and in the disengaged position the gripper is capable of being received into and removed from a cavity
of an object,

wherein the gripper is connected to the rotary body by a second mechanism configured such that rotary motion of the body moves
the gripper between the engaged position and the disengaged position; and

a latching arrangement comprising an internal latch enclosed within the gripper mechanism, wherein:
the latching arrangement is configured to prevent the gripper moving from the engaged to the disengaged position before the
actuation end is moved by a predetermined distance; and

the latching arrangement is configured such that axial movement of the actuation end in a direction opposite to a desired
direction of motion of the gripper mechanism at least partially unlatches the latching arrangement.

US Pat. No. 9,376,213

DISTRIBUTED PROPULSION SYSTEM AND METHOD OF CONTROL

ROLLS-ROYCE plc, London ...

1. A method of controlling power distribution in an electrical aircraft propulsion system, the electrical aircraft propulsion
system including: (i) a plurality of electrical propulsion units, each of the plurality of electrical propulsion units having
a plurality of rotatable blades on a rotor, each blade of the plurality of blades having an adjustable pitch; (ii) a pitch
adjusting mechanism for each of the plurality of electrical propulsion units, each pitch adjusting mechanism being configured
to adjust the pitch of the plurality of blades of each of the plurality of propulsion units simultaneously so as to avoid
a non-symmetrical load profile on a hub; (iii) at least one electrical machine electrically connected to the plurality of
electrical propulsion units so as to provide electrical power when in use; and (iv) a control system, the method comprising
steps of:
determining a required propulsion;
determining whether the plurality of propulsion units are collectively delivering the required propulsion; and
simultaneously adjusting a pitch angle of the plurality of blades of at least one of the plurality of propulsion units so
as to increase or decrease the propulsion provided by that propulsion unit.

US Pat. No. 9,366,654

METHOD OF MEASURING A CRYSTALLOGRAPHIC ORIENTATION OF AN OBJECT

ROLLS-ROYCE plc, London ...

1. A method of measuring a crystallographic orientation of an object using an ultrasonic transducer and a detector array comprising
a plurality of ultrasonic detectors, the method comprising:
determining a minimum distance (dmin) between the transducer and a detector of the detector array closest to the transducer;

placing the transducer and the detector array in contact with a surface of the object such that the transducer and the detector
of the detector array closest to the transducer are separated by at least the minimum distance (dmin);

using the transducer to generate an ultrasonic surface wave pulse in the surface of the object, the ultrasonic surface wave
pulse having a pulse duration (tw) and comprising a longitudinal surface wave and a Rayleigh wave; and

measuring a time of flight of a surface wave generated by the transducer between the transducer and each detector of the array
to determine the crystallographic orientation of the object;

wherein the minimum distance (dmin) is the distance at which the minimum time of flight of the Rayleigh wave (tR) is at least the sum of the maximum time of flight of the longitudinal surface wave (tL) and the maximum pulse duration (tw).

US Pat. No. 9,347,855

INSPECTION ARRANGEMENT

ROLLS-ROYCE plc, London ...

1. An inspection arrangement comprising an inspection element and a positioning tool for positioning the inspection element,
the inspection element being attachable to the positioning tool by an attachment arrangement, and having a fixing element
to present the inspection element in use, the fixing element comprising a plurality of radially extending resilient elements,
wherein the inspection arrangement further comprises a controller element at a proximal in use end of the inspection arrangement
configured to control release of the inspection element from the positioning tool, the controller element having a radio transmitter.

US Pat. No. 9,284,852

FLEXIBLE PRINTED CIRCUIT BOARD HARNESS

ROLLS-ROYCE plc, London ...

1. A gas turbine engine installation comprising:
a flexible printed circuit board harness arranged to transfer electrical signals around the gas turbine engine installation;
and

at least one clip holding the flexible printed circuit board harness, each clip comprising a jaw extending from a base, the
jaw comprising:

a mouth having a width for receiving the flexible printed circuit board harness; an upper set of teeth comprising at least
two teeth, each tooth in the upper set of teeth being separated from other tooth or teeth in the upper set of teeth in a direction
pointing from the mouth to the base; and

a lower set of teeth comprising at least two teeth, each tooth in the lower set of teeth being separated from other tooth
or teeth in the lower set of teeth in a direction pointing from the mouth to the base, wherein:

each tooth is elastically deformable and has a root and a tip, and extends across at least a part of the width of the mouth,
the upper set of teeth and the lower set of teeth being configured to grip the flexible printed circuit board therebetween;
and

teeth of at least one of the upper set of teeth and the lower set of teeth extend from the root to the tip in a direction
that has a component pointing from the mouth to the base.

US Pat. No. 9,243,963

TOTAL TEMPERATURE PROBE

ROLLS-ROYCE PLC, London ...

1. A gas turbine engine comprising a total temperature probe, the total temperature probe comprising:
a hollow elongate shroud defined by a shroud wall that envelops a first cavity, the shroud wall comprising an inner skin and
an outer skin which enclose a second cavity therebetween, the inner skin and the outer skin being separated by a constant
distance; and

a temperature sensor mounted in the first cavity,
wherein the total temperature probe is disposed inside of the gas turbine engine and, in use, fluid flow for the gas turbine
engine is received into the first cavity, passes through at least one aperture in the inner skin into the second cavity and
thence passes out of the shroud through at least one aperture in the outer skin, such that heat conduction across the inner
skin is minimal, the at least one aperture in the inner skin being axially and/or circumferentially displaced from the at
least one aperture in the outer skin.

US Pat. No. 9,172,295

MAGNETIC GEAR ARRANGEMENT

ROLLS-ROYCE plc, London ...

16. A magnetic gear arrangement comprising:
a first gear member for generating a first magnetic field,
a second gear member for generating a second magnetic field, and
a plurality of interpoles disposed between the first gear member and the second gear member for coupling said first magnetic
field and said second magnetic field to control a gear ratio between said first gear member and said second gear member, wherein

at least one interpole comprises wiring and a switch to activate said wiring, such that activation of said wiring alters magnetic
flux at said interpole so as to vary the coupling between said first magnetic field and said second magnetic field,

said wiring is electrically connected to an electronic filter, which modifies current passing through said wiring, so as to
modify influence of said wiring on the magnetic flux at said interpole,

the electronic filter is a variable filter, and
the magnetic gear arrangement includes a control system for controlling operation of the electronic filter, the control system
being configured to provide different filtering effects in response to different gear ratios of the magnetic gear arrangement
or different speeds of the gear members.

US Pat. No. 9,139,144

ELECTRICAL HARNESS CONNECTOR

ROLLS-ROYCE plc, London ...

1. A connector for joining two electrical harnesses, each of the harnesses being formed from a flexible printed circuit board
including a plurality of conductive tracks, and each of the harnesses having a substantially planar terminating region at
which the conductive tracks of the harness fan out, wherein one or more receiving holes are formed in each terminating region
to extend to respective conductive tracks, and each of the one or more receiving holes extends in a direction substantially
perpendicularly to a plane of the respective substantially planar terminating region, the connector including:
a connection formation, wherein the connection formation, in use, is sandwiched between respective terminating regions of
the two electrical harnesses, the connection formation having one or more pins arranged so that one end of each of the one
or more pins enters one of the one or more receiving holes of one of the terminating regions and the other end of the pin
enters one of the one or more receiving holes of the other of the terminating regions to electrically connect the respective
conductive tracks; and

a housing configured to hold the respective terminating regions of the two electrical harnesses in face-to-face relationship
with the connection formation sandwiched therebetween, the housing having one or more apertures through which the harnesses
can exit the housing as each of the harnesses extends away from the terminating region of the harness, wherein:

each of the one or more pins has a circular cross section, and
the connection formation has a substantially planar retaining body that holds the one or more pins in fixed positions relative
thereto, the ends of each of the one or more pins projecting from opposing sides of the body.

US Pat. No. 9,086,362

LAYERED COMPOSITE COMPONENTS

ROLLS-ROYCE plc, London ...

1. A method of testing a layered composite component, the method comprising:
providing an acoustic filter in at least two layers of the composite component, each acoustic filter operable to filter a
different predetermined frequency band out of an acoustic test signal;

applying an acoustic test signal to the composite component;
detecting the acoustic test signal after it has passed through the composite component; and
analyzing differences between the applied signal and the detected signal to determine which layers the applied signal has
passed through.

US Pat. No. 9,194,414

FASTENER

ROLLS-ROYCE plc, London ...

1. A fastener for clamping a first component to a second component, the fastener comprising:
two resiliently deformable snap-fit members which, in use, are inserted from a first side of the first and second components
through two channels in each of the first and second components, each of the resiliently deformable snap-fit members being
insertable into a respective one of the two channels, the two channels being formed in each of the first and second components,
each of the snap-fit members having an abutment surface which, in said use, on emerging from the respective channel, enters
into a snap-fit engagement with an opposing second side of the components to prevent retraction of the respective snap-fit
member; and

a spring arrangement which, in said use, presses on the first side of the components between the channels on the insertion
of the snap-fit members to apply a compressive clamping force across the components between the spring arrangement and the
abutment surfaces,

wherein the spring arrangement and the two resiliently deformable snap-fit members are arranged in a common plane such that
the fastener is substantially flat, and

wherein the spring arrangement comprises one or ore spring arms configured to press on the first side of the components between
the channels.

US Pat. No. 9,172,250

ELECTRICAL DISTRIBUTION SYSTEM

ROLLS-ROYCE plc, London ...

1. An electrical distribution system for use with a gas turbine engine, the system comprising:
a plurality of generators including a primary generator and a secondary generator, the plurality of generators configured
to be connected to a gas turbine engine and to output power, the plurality of generators driven at mechanical frequencies
that differ from each other;

a common bus configured to receive the power output from the generators;
one or more converters disposed between each generator and the bus, the one or more converters configured to influence the
frequency of the power output from the generators; and

a control system configured to (i) set an AC bus frequency in accordance with the power output from the primary generator
and (ii) control the converters of the secondary generator to match the primary generator so that the converters feed energy
into or draw energy from the generators so that all generators supply the power output at the bus frequency.

US Pat. No. 9,115,898

FUEL INJECTOR MOUNTING SYSTEM

ROLLS-ROYCE PLC, London ...

1. A system for mounting a fuel injector to a gas turbine engine casing having an aperture formed therein, said system comprising:
a fuel injector having an integral flange for mounting the fuel injector to the casing with the fuel injector extending through
the aperture, the flange being configured to pass through the aperture, and

an intermediate ring which mediates the mounting of the flange to the casing at the aperture, the intermediate ring being
positioned inside the casing at the aperture and defining an opening from which an outer end of the fuel injector extends
through the aperture while an inner end of the fuel injector extends into the engine with the flange positioned inward of
the ring, the intermediate ring having within the casing an outer diameter greater than that of the aperture in the casing
such that the intermediate ring cannot be removed from the engine through the aperture and such that the flange cannot pass
through the opening in the intermediate ring;

wherein to mount the fuel injector to the casing the flange is dismountably sealed to an inner surface of the intermediate
ring with the fuel injector extending through the opening, and the intermediate ring is dismountably sealed to an inner surface
of the casing adjacent the aperture, such that only the fuel injector and the intermediate ring together seal the aperture,
and on dismounting the flange from the intermediate ring, the fuel injector can be displaced into the casing to allow the
intermediate ring, when dismounted from the casing, to be moved away from the aperture, such that the fuel injector can be
withdrawn from the casing through the aperture at which the intermediate ring and flange were sealed.

US Pat. No. 9,104,199

ENGINE MONITORING

ROLLS-ROYCE PLC, London ...

1. A method comprising:
monitoring, by a processor, a gas turbine engine across a flight envelope of an aircraft powered by the gas turbine engine,
the monitoring comprising:

measuring, by a processor, one or more operating parameters of the gas turbine engine and a performance parameter of the gas
turbine engine during one or more operational periods of the gas turbine engine;

recording, by a processor, a plurality of data points, each data point comprising the operating parameters and the associated
performance parameter;

identifying, by a processor, one or more steady state regions in the performance parameter and selecting a plurality of the
data points from the one or more steady state regions in the performance parameter;

selecting, by a processor, one or more groups of the steady state data points in the operating parameter space by virtue of
a predetermined density of the steady state data points in the operating parameter space;

comparing, by a processor, the performance parameter within the groups so as to identify a change in the performance of the
gas turbine engine;

counting, by a processor, the number of steady state data points neighbouring a particular steady state data point within
a predetermined domain about the particular steady state data point in the operating parameter space;

repeating, by a processor, for each steady state data point; and
grouping, by a processor, steady state data points with a number of neighbouring steady state data points above a predetermined
threshold into the one or chore groups, wherein all points defining a boundary of the predetermined domain in the operating
parameter space are equidistant from the particular steady state data point.