公开(公告)号：US11988157B2

公开(公告)日：2024-05-21

申请号：US18166268

申请日：2023-02-08

Applicant: ROLLS-ROYCE plc

Inventor： Richard G Mochrie ,  Graeme E F Sutcliffe ,  Jade Whittle

IPC: F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F02C9/26

CPC classification number: F02C9/26 ,  F02C7/14 ,  F02C7/22 ,  F02C7/224 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2260/213

Abstract: A gas turbine engine comprising a combustor and a fuel management system. The fuel management system comprises a fuel supply line, recirculation line and heat exchanger. The fuel supply line is configured to supply fuel to the combustor. The recirculation line is configured to recirculate excess fuel from the fuel supply line to an engine-located fuel tank via a fuel cooling device. The fuel cooling device is configured to reject heat from the excess fuel in the recirculation line. The heat exchanger is configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel management system. The heat exchanger is disposed on the fuel supply line or on the recirculation line. The fuel supply line is configured to receive fuel from an external source and from the engine-located fuel tank.

公开(公告)号：US11988141B2

公开(公告)日：2024-05-21

申请号：US17494537

申请日：2021-10-05

Applicant: ROLLS-ROYCE plc

Inventor： Natalie C Wong ,  Thomas S Binnington ,  David A Jones ,  Daniel Blacker

IPC: F02C7/04 ,  F02C7/18 ,  B64D27/10 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D27/20 ,  B64D33/10 ,  F02K3/06 ,  F02K3/075 ,  F02C7/08 ,  F02C7/12 ,  F01D9/06 ,  F02C7/14 ,  F02K3/115

CPC classification number: F02C7/04 ,  B64D27/10 ,  B64D27/20 ,  B64D33/02 ,  B64D33/04 ,  B64D33/08 ,  B64D33/10 ,  F01D9/065 ,  F02C7/08 ,  F02C7/12 ,  F02C7/18 ,  F02K3/06 ,  F02K3/075 ,  B64D2033/024 ,  B64D2033/0286 ,  F02C7/14 ,  F02K3/115 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/213

Abstract: An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a turbine module, a combustor module, and an exhaust module.
The machine body comprises either one or two fluid inlet apertures. The or each fluid inlet aperture is configured to allow a fluid flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid flow prior to an entry of the fluid flow into the fan module, and thence into the compressor module, the turbine module, the combustor module, and the exhaust module.

公开(公告)号：US11986897B2

公开(公告)日：2024-05-21

申请号：US17734515

申请日：2022-05-02

Applicant: ROLLS-ROYCE plc

Inventor： James Kell ,  Graeme E Rigg ,  Shamraze Ahmed ,  Monica M Castro Palacios ,  Adam Clare

IPC: B23H9/10 ,  B23K26/035 ,  B23K26/36 ,  B23K101/00

CPC classification number: B23H9/10 ,  B23K26/035 ,  B23K26/36 ,  B23K2101/001

Abstract: A method for the removal of debris (75) from an aperture (60), the aperture comprising a first aperture diameter (64) and extending along a first axis (62) over a first distance (63), the method comprising the steps of aligning a beam of energy (80) with the first axis such that the beam of energy is coaxially aligned with the aperture, the beam of energy comprising both an energy sufficient to remove the debris, and a first beam diameter (82) which is less than the first aperture diameter; and, exposing the debris to the beam of energy in order to remove the debris from the aperture.

公开(公告)号：US20240159165A1

公开(公告)日：2024-05-16

申请号：US18447740

申请日：2023-08-10

Applicant: Rolls-Royce plc

Inventor： Rupert J. Taylor ,  Ngungunyana Mhlanga ,  Grant Mathieson ,  Ryan R. Allen ,  James Revell ,  Dinesh Perumalsamy ,  Carlos Javier Diaz Rodriguez

IPC: F01D25/24 ,  F01D25/12

CPC classification number: F01D25/24 ,  F01D25/12 ,  F05D2260/201

Abstract: A turbine shroud segment, e.g. for a gas turbine engine, which is coolable by a supply of cooling air, e.g. from a gas turbine engine compressor. The turbine shroud segment has a segment casing that has a radially outer surface and a radially inner surface. The segment casing houses a main plenum, a first layer of impingement chambers, a second layer of impingement chambers, and a plurality of effusion passages. The first layer of impingement chambers fluidly communicates with the main plenum via transfer passages that are formed in the segment casing. The second layer of impingement chambers fluidly communicates with the first layer of impingement chambers via impingement passages that are formed in the segment casing. The effusion passages run between impingement chamber core surface, which is a radially inner surface of an impingement chamber, and the radially inner surface of the segment casing.

公开(公告)号：US11982230B2

公开(公告)日：2024-05-14

申请号：US18233619

申请日：2023-08-14

Applicant: ROLLS-ROYCE PLC

Inventor： Paul R Davies ,  David A Jones ,  Alexander T Joyce ,  Richard G Mochrie

IPC: F02C7/16 ,  F25B27/02 ,  F02C6/18

CPC classification number: F02C7/16 ,  F25B27/02 ,  F02C6/18 ,  F05D2220/323 ,  F05D2260/213

Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, a first thermal bus, a first heat exchanger, and a chiller. The first thermal bus comprises a first heat transfer fluid, with the first heat transfer fluid being in fluid communication, in a closed loop flow sequence, between the first gas turbine engine, the first heat exchanger, and the chiller. Waste heat energy generated by the first gas turbine engine, is transferred to the first heat transfer fluid. The chiller is configured to lower a temperature of the first heat transfer fluid prior to the first heat transfer fluid being circulated through the gas turbine engine. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.

公开(公告)号：US20240150029A1

公开(公告)日：2024-05-09

申请号：US18378339

申请日：2023-10-10

Applicant: ROLLS-ROYCE PLC

Inventor： James G STARLEY

IPC: B64D29/06 ,  B64D27/12 ,  F02C7/04

CPC classification number: B64D29/06 ,  B64D27/12 ,  F02C7/04

Abstract: 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.

公开(公告)号：US11970975B2

公开(公告)日：2024-04-30

申请号：US17476129

申请日：2021-09-15

Applicant: ROLLS-ROYCE PLC

Inventor： Chloe J Palmer ,  Guy D Snowsill ,  Jonathan E Holt

IPC: F02C7/224 ,  F02C3/20 ,  F02C3/22 ,  F02C7/04 ,  F02C7/14 ,  F02C7/143 ,  F02C7/18 ,  F02C7/22 ,  F23R3/04 ,  F23R3/28 ,  F02C9/40

CPC classification number: F02C7/224 ,  F02C3/20 ,  F02C3/22 ,  F02C7/04 ,  F02C7/14 ,  F02C7/143 ,  F02C7/18 ,  F02C7/22 ,  F02C7/222 ,  F23R3/04 ,  F23R3/286 ,  F02C9/40 ,  F05D2220/32 ,  F05D2240/35

Abstract: 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.

公开(公告)号：US20240133314A1

公开(公告)日：2024-04-25

申请号：US18488217

申请日：2023-10-16

Applicant: ROLLS-ROYCE plc

Inventor： David M. DONNELLY ,  Caroline L. TURNER ,  Derek S. WALL ,  Peter F. DOUGLAS

IPC: F01D19/00 ,  F01D21/00

CPC classification number: F01D19/00 ,  F01D21/003 ,  F05D2260/80 ,  F05D2260/85

Abstract: 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.

公开(公告)号：US11964388B2

公开(公告)日：2024-04-23

申请号：US17992349

申请日：2022-11-22

Applicant: ROLLS-ROYCE plc

Inventor： Andrew D Norton ,  Matteo Russo ,  Xin Dong

IPC: B25J18/00 ,  B25J19/00

CPC classification number: B25J19/0004 ,  B25J18/00

Abstract: 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.

公开(公告)号：US20240123655A1

公开(公告)日：2024-04-18

申请号：US18475576

申请日：2023-09-27

Applicant: Rolls-Royce plc

Inventor： Kevin M. WORLD ,  Simon Groves ,  Wojciech Wasinski

IPC: B29C31/08

CPC classification number: B29C31/08 ,  B29C70/26

Abstract: 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.