公开(公告)号：US20240183273A1

公开(公告)日：2024-06-06

申请号：US18508497

申请日：2023-11-14

申请人： ROLLS-ROYCE plc

发明人： John M. HARRISON

IPC分类号： F01D5/02

CPC分类号： F01D5/027 ,  F05D2220/323 ,  F05D2260/96

摘要： Disclosed is a gas turbine engine rotor balancing apparatus comprising: a rotor configured to rotate about a rotor axis; a substantially annular balancing mass configured to encircle the rotor; and a mass adjustment apparatus for adjusting the position of the balancing mass relative to the rotor.

公开(公告)号：US20240167393A1

公开(公告)日：2024-05-23

申请号：US18386049

申请日：2023-11-01

申请人： ROLLS-ROYCE plc

发明人： Simon PITT

IPC分类号： F01D21/00 ,  G01B13/18

CPC分类号： F01D21/003 ,  G01B13/18 ,  F05D2270/80

摘要： A probe for determining the swirl angle of the exhaust gasses of a turbine engine, has an elongate body with a fastener, the elongate body having a tip at its proximal end and a head at its distal end, the elongate body having at least two passageways extending from the tip to the head, each passageway having an aperture at the tip and a port at the head which is connectable to a pressure sensor.

公开(公告)号：US20240165795A1

公开(公告)日：2024-05-23

申请号：US18384099

申请日：2023-10-26

申请人： ROLLS-ROYCE PLC

发明人： Liam D. HARRISON ,  Ian KENNEDY ,  Thomas HOPPER ,  Andrew D. NORTON

IPC分类号： B25J9/06 ,  B25J9/12

CPC分类号： B25J9/065 ,  B25J9/12

摘要： An actuator pack for a continuum arm robot, the actuator pack including a plurality of actuator pack sections, with each section having a housing and an interface plate, each section further containing a bank consisting of a plurality actuators that are connected to their own respective drive electronics and the actuators being mounted to the housing or the interface plate and having their drive heads exposed through a hole in the interface plate, and wherein the sections of the actuator pack are configured to coupled together in one state.

公开(公告)号：US20240165679A1

公开(公告)日：2024-05-23

申请号：US18386104

申请日：2023-11-01

申请人： ROLLS-ROYCE plc

发明人： Najib Bin MOHAMED SALLEH ,  Sherilyn LIM

IPC分类号： B08B7/00 ,  B08B1/00 ,  B08B3/04 ,  B08B7/04 ,  C11D3/04 ,  C11D3/37 ,  C11D11/00

CPC分类号： B08B7/0014 ,  B08B1/005 ,  B08B3/04 ,  B08B7/04 ,  C11D3/04 ,  C11D3/3703 ,  C11D11/0041

摘要： A method for cleaning a surface of a component includes placing a volume of a cleaning agent onto the surface of the component. The method further includes performing a repair operation of the component either before or after placing the volume of the cleaning agent. The repair operation results in a generation of contaminant particles. Upon contact of the cleaning agent with the contaminant particles, the cleaning agent absorbs the contaminant particles by adhesion. The method further includes removing the cleaning agent from the surface of the component after the contaminant particles are absorbed by the cleaning agent.

公开(公告)号：US11988157B2

公开(公告)日：2024-05-21

申请号：US18166268

申请日：2023-02-08

申请人： ROLLS-ROYCE plc

发明人： Richard G Mochrie ,  Graeme E F Sutcliffe ,  Jade Whittle

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

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

摘要： 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

申请人： ROLLS-ROYCE plc

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

IPC分类号： 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分类号： 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

摘要： 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

申请人： ROLLS-ROYCE plc

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

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

CPC分类号： B23H9/10 ,  B23K26/035 ,  B23K26/36 ,  B23K2101/001

摘要： 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

申请人： Rolls-Royce plc

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

IPC分类号： F01D25/24 ,  F01D25/12

CPC分类号： F01D25/24 ,  F01D25/12 ,  F05D2260/201

摘要： 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

申请人： ROLLS-ROYCE PLC

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

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

CPC分类号： F02C7/16 ,  F25B27/02 ,  F02C6/18 ,  F05D2220/323 ,  F05D2260/213

摘要： 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

申请人： ROLLS-ROYCE PLC

发明人： James G STARLEY

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

CPC分类号： B64D29/06 ,  B64D27/12 ,  F02C7/04

摘要： 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.