Patents Assigned to Rolls-Royce plc
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Publication number: 20240151154Abstract: A rotary assembly for driving spool rotation includes a rotor and a flow modifier. The rotor is mechanically coupled to a spool of a gas turbine engine. The flow modifier receives flow from and/or direct flow to the rotor. The rotary assembly permits relative movement between the rotor and the flow modifier to move between: a turbine configuration wherein the rotor receives air from an external air source to drive the spool to rotate; and a compressor configuration wherein the rotor is driven to rotate by the spool and to receive and compress air from the gas turbine engine, and discharge the compressed air for supply to the airframe system. The rotary assembly also includes controller to control relative movement between the rotor and the flow modifier through a range of turbine positions of the turbine configuration to vary a torque applied to the rotor for driving the spool.Type: ApplicationFiled: October 13, 2023Publication date: May 9, 2024Applicant: ROLLS-ROYCE plcInventors: Christopher A MURRAY, Nicholas HOWARTH
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Publication number: 20240149472Abstract: A micromanipulator for mounting on the end of a macromanipulator, the micromanipulator comprising: a connection plate with a at least a first and second motor connected to a rigidly mounted base section, a first rotational section connected to the base section about a pivotable axis, the first rotational section being further connected to a slider rod which is connected to the first motor, and a second rotational section connected to the first rotational section about a pivotable axis, the second rotational section being further connected to a slider rod which is connected to the second motor and wherein the rotational joints between the base section and first joint section and the rotational joint between the first and second rotational sections are offset by 90°.Type: ApplicationFiled: October 10, 2023Publication date: May 9, 2024Applicant: ROLLS-ROYCE PLCInventors: Dragos A. AXINTE, Erhui SUN, Andres A. GAMEROS MADRIGAL, Abdelkhalick MOHAMMAD, Tianyi ZENG, Max B. KEEDWELL, Josue Israel CAMACHO ARREGUIN
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Publication number: 20240150029Abstract: An inner cowl arrangement for a gas turbine engine includes a first hinge and a second hinge pivotally connecting a first cowl member and a second cowl member, respectively, to a mounting structure. The inner cowl arrangement further includes a latch detachably securing the first and second cowl members. At least one of the first hinge, the second hinge, and the latch includes a pressure relief component that deforms or breaks when an applied load on the pressure relief component due to a pressure within an engine core is greater a normal operating load, causing at least one of the first cowl member and the second cowl member to move relative to the engine core, and forming an opening.Type: ApplicationFiled: October 10, 2023Publication date: May 9, 2024Applicant: ROLLS-ROYCE PLCInventor: James G STARLEY
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Patent number: 11976013Abstract: An article may include a substrate including a ceramic matrix composite (CMC); a composite coating layer including a first coating material that includes a rare-earth disilicate and a second coating material that includes at least one of a rare-earth monosilicate, a CMAS-resistant material, or a high-temperature dislocating material, where the second coating material forms a substantially continuous phase in the composite coating layer.Type: GrantFiled: September 21, 2018Date of Patent: May 7, 2024Assignees: Rolls-Royce Corporation, Rolls-Royce plcInventors: Stephanie Gong, Ngunjoh Lawrence Ndamka, Matthew R. Gold, Li Li, Taylor K. Blair, Sunny Chang, Ann Bolcavage
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Patent number: 11976611Abstract: A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of: S = ( Maximum ? Electrical ? Power ? Generated = P E ? M ? 1 ) ( Maximum ? Dry ? Thrust = T ) is in a range of between 2.0 and 10.0.Type: GrantFiled: September 8, 2022Date of Patent: May 7, 2024Assignee: ROLLS-ROYCE plcInventors: Paul R Davies, Gareth E Moore, Stephen M Husband, David R Trainer, David P Scothern, Luke George
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Publication number: 20240139892Abstract: The present disclosure provides a method of manufacturing a turbomachinery component for a gas turbine engine, comprising: receiving an ideal design of the turbomachinery component, the turbomachinery component comprising: an aerofoil portion comprising an aerofoil surface and having an ideal aerofoil wall thickness; and a platform portion comprising a platform surface coterminous with the aerofoil surface, the platform portion having an ideal radial platform thickness along a radial direction; determining an intermediate design of the turbomachinery component comprising an intermediate platform portion having an intermediate platform surface and an intermediate radial platform thickness which is greater than the ideal radial platform thickness; forming, by an investment casting process, an intermediate turbomachinery component based on the intermediate design, wherein the intermediate turbomachinery component comprises at least one detectable reference feature formed by an internal core element during the inType: ApplicationFiled: October 13, 2023Publication date: May 2, 2024Applicant: ROLLS-ROYCE plcInventor: Christopher NEALE
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Publication number: 20240141792Abstract: A fan blade includes an aerofoil portion including a leading edge extending from a root to a tip and defining a blade span therebetween. A leading edge thickness is defined as a thickness of a cross-section at a given radius at a location along a camber line that is 9% of the total length of the camber line from the leading edge. For cross-sections through the aerofoil portion at radii between 50% and 70% of the blade span from a root radius, the leading edge thickness includes a first maximum value. For cross-sections through the aerofoil portion at radii greater than 70% of the blade span from the root radius, the leading edge thickness includes a second maximum value that is between 105% and 125% of the first maximum value.Type: ApplicationFiled: October 27, 2023Publication date: May 2, 2024Applicant: ROLLS-ROYCE plcInventors: Michael BARTHOLOMEW, David HIGGINBOTTOM
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Publication number: 20240141795Abstract: Described herein is a flow splitter for a gas turbine engine, the flow splitter comprising a leading edge, wherein the radial and/or axial position of the leading edge varies circumferentially around the flow splitter, such that the leading edge is non-axisymmetric. Also described is a method of manufacture of a flow splitter and an engine comprising a flow splitter.Type: ApplicationFiled: October 17, 2023Publication date: May 2, 2024Applicant: ROLLS-ROYCE plcInventor: Samuel P. LEE
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Publication number: 20240146208Abstract: The disclosure relates to an electrical power system with current fault protection provided by current limiting diodes. Example embodiments include an electrical power system comprising: an electrical machine; an AC:DC power electronics converter connected to receive an input AC supply from the electrical machine and provide an output DC supply across first and second output terminals; a DC bus connected to first and second output terminals of the AC:DC power electronics converter; a load connected across the DC bus; a first circuit breaker switch and a first current limiting diode connected in series between the AC:DC power electronics converter and the DC bus; and a second circuit breaker switch and a second current limiting diode connected in series between the DC bus and the load, wherein the first current limiting diode is configured to limit current to a higher level than the second current limiting diode.Type: ApplicationFiled: October 17, 2023Publication date: May 2, 2024Applicant: ROLLS-ROYCE plcInventors: David R. TRAINER, Mark SWEET, Gian INCERPI, Jonathan M. STEVENS
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Fuel delivery system for delivering hydrogen fuel to a fuel injection system in a gas turbine engine
Patent number: 11970975Abstract: A fuel delivery system (201) is shown for delivering the hydrogen fuel from a cryogenic storage system to a fuel injection system in a gas turbine engine. The fuel delivery system includes a pump (301), a metering device (302), and a fuel heating system (303,304) for heating the hydrogen fuel to an injection temperature for the fuel injection system.Type: GrantFiled: September 15, 2021Date of Patent: April 30, 2024Assignee: ROLLS-ROYCE PLCInventors: Chloe J Palmer, Guy D Snowsill, Jonathan E Holt -
Publication number: 20240132227Abstract: An aircraft propulsion system fuel system comprises a fuel line configured to receive liquid hydrogen fuel from a fuel tank, a vaporizer configured to vaporize liquid hydrogen fuel from the fuel line to generate a supercritical or gaseous fuel, a main fuel pump configured to receive and to pump the gaseous or supercritical fuel from the vaporizer during operation of the propulsion system, and a heater provided downstream in fuel flow to the main fuel pump, and configured to raise the temperature of the gaseous or supercritical fuel to a propulsion system delivery temperature.Type: ApplicationFiled: October 8, 2023Publication date: April 25, 2024Applicant: ROLLS-ROYCE plcInventors: Marko BACIC, John COULL
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Publication number: 20240138108Abstract: A thermal management system for cooling at least one electronic component, the thermal management system including: a heat exchanger connectable to at least one electronic component, the heat exchanger configured to dissipate heat generated by the at least one electronic component; a plurality of cooling channels each connected to a respective pump and the heat exchanger, wherein: each cooling channel is configured to carry fluid between the heat exchanger and the respective pump, and each pump is configured to pump fluid along the respective cooling channel such that fluid carried by each cooling channel flows through the heat exchanger.Type: ApplicationFiled: September 26, 2023Publication date: April 25, 2024Applicant: ROLLS-ROYCE PLCInventors: Chandana J. GAJANAYAKE, Shuai WANG, Pranshu KHARBANDA
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Publication number: 20240133340Abstract: A combined gas turbine engine and hydrogen fuel cell system includes a hydrogen fuelled gas turbine engine, a cryogenic liquid hydrogen fuel tank, a first fuel offtake configured and arranged to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured and arranged to burn the portion of hydrogen fuel diverted from the main fuel conduit, a heat exchanger configured and arranged to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit, a second fuel offtake arranged to divert a portion of hydrogen fuel from the main fuel conduit downstream of the heat exchanger, and a hydrogen fuel cell configured and arranged to produce electric power using hydrogen fuel diverted from the second fuel offtake.Type: ApplicationFiled: October 12, 2023Publication date: April 25, 2024Applicant: ROLLS-ROYCE PLCInventors: Nicholas GRECH, Chloe J. PALMER, Jacopo TACCONI
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Publication number: 20240133343Abstract: A gas turbine engine fuel system includes a fuel offtake configured to divert a portion of hydrogen fuel from a main fuel conduit, a burner configured to burn the portion of hydrogen fuel diverted from the main fuel conduit, a heat exchanger configured to transfer heat from exhaust gasses produced by the burner to hydrogen fuel in the main fuel conduit and a power recovery device configured to extract power from exhaust gasses of the burner downstream of the heat-exchanger.Type: ApplicationFiled: October 12, 2023Publication date: April 25, 2024Applicant: ROLLS-ROYCE PLCInventors: Chloe J. PALMER, Jacopo TACCONI, Nicholas GRECH
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Publication number: 20240133314Abstract: There is provided a method of starting a gas turbine engine, comprising: selecting a baseline starting procedure of the gas turbine engine based on environmental data; receiving condition information for the gas turbine engine and/or for a starting system of the gas turbine engine, the condition information comprising at least one of: health information for the gas turbine engine and/or the starting system; maintenance information for the gas turbine engine and/or the starting system; and operation information relating to an expected future usage of the gas turbine engine. The method further comprises determining a predicted degradation profile for the gas turbine engine and/or the starting system based on the condition information; determining a starting procedure of the gas turbine engine by adapting the baseline starting procedure based on the predicted degradation profile; and controlling the gas turbine engine and/or the starting system according to the determined starting procedure.Type: ApplicationFiled: October 16, 2023Publication date: April 25, 2024Applicant: ROLLS-ROYCE plcInventors: David M. DONNELLY, Caroline L. TURNER, Derek S. WALL, Peter F. DOUGLAS
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Patent number: 11965467Abstract: An aircraft propulsion system comprises first and second thrust producing gas turbine engines. The system comprises a controller configured to determine a required overall propulsion system thrust level, and determine an engine core power level contribution from each aircraft gas turbine engine such that the overall propulsion system produces a minimum overall noise level and meets the required overall propulsion system thrust level. In meeting the minimum overall noise level, at least the first and second gas turbine engines are operated at different engine core power settings.Type: GrantFiled: September 9, 2022Date of Patent: April 23, 2024Assignee: ROLLS-ROYCE plcInventors: Peter Swann, Kevin M Britchford
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Patent number: 11964388Abstract: A locking system for a continuum arm robot system, the robot system includes: a continuum arm robot having a manipulatable tip, a passive robot section through which controls for the manipulatable tip, and at least one ferromagnetic collar, and at least one external controllable electromagnetic device which can be activated so that the ferromagnetic section on the continuum arm robot is attracted to the electromagnetic device.Type: GrantFiled: November 22, 2022Date of Patent: April 23, 2024Assignee: ROLLS-ROYCE plcInventors: Andrew D Norton, Matteo Russo, Xin Dong
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Publication number: 20240123655Abstract: A rodstock barrel drive having a first and second roller gears, each having a toothed section and a gripping surface section, such that the teeth of the roller gears intermesh, causing rotation of one of roller gear to rotate the other roller gear in the opposite direction, so as to draw a rodstock through a space between the gripping surfaces of the pair of roller gears, a ring gear which engages with one of the pair of roller gears, a drive gear which engages with the ring gear, and one or more idler gears which engage with the ring gear, all within a housing, the drive gear being connected to, and rotated by, a motor, which causes the rodstock to be drawn through the roller gears, wherein all the gears are all positioned within, and oriented parallel to, a common plane.Type: ApplicationFiled: September 27, 2023Publication date: April 18, 2024Applicant: Rolls-Royce plcInventors: Kevin M. WORLD, Simon Groves, Wojciech Wasinski
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Publication number: 20240123692Abstract: A needle apparatus for making a pinning hole in a composite material, the apparatus having a needle with a longitudinal axis, a collar fixed about the needle, a motor having an axis of rotation, and being fixed to the needle such that the needle can be rotated by the motor, the motor and the collar being situated within a motor housing, the motor housing having a first bush, and a second bush, wherein the collar is positioned between the first bush and second bush so as to prevent the needle from moving away from or towards the motor, but allow the needle to rotate freely around its longitudinal axis, wherein each needle apparatus further comprises a linear actuator connected to the motor such that the motor can be moved along the axis of rotation of the motor by the linear actuator.Type: ApplicationFiled: September 28, 2023Publication date: April 18, 2024Applicant: ROLLS-ROYCE plcInventors: Kevin M. WORLD, Simon GROVES, Wojciech WASINSKI, Neal WRIGHT
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Publication number: 20240117744Abstract: Disclosed is an aerofoil for a gas turbine engine comprising: a first conduit formed in the aerofoil; a second conduit formed in the aerofoil; and a dividing wall separating the first and second conduits, the dividing wall comprising a transfer port configured to permit fluid flow between the first and second conduits; wherein the dividing wall further comprises a reinforcing boss at least partially encircling the transfer port. Also disclosed is a gas turbine engine comprising the aerofoil and an aircraft comprising the gas turbine engine.Type: ApplicationFiled: September 14, 2023Publication date: April 11, 2024Applicant: ROLLS-ROYCE plcInventors: Bogachan ALPAN, Jonathan M. PEACE, Thomas P. HOUGHTON