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公开(公告)号：US20240117967A1
公开(公告)日：2024-04-11
申请号：US18359346
申请日：2023-07-26
Applicant: ROLLS-ROYCE plc
Inventor： Stephen C. HARDING
Abstract: There is described a fuel injector for a gas turbine engine. The fuel injector comprises an air passageway having an inlet region and an outlet region in fluid communication with the inlet region at an air passageway interface, the inlet region being configured to receive a flow of air from a compressor of the gas turbine engine at an air inlet, the outlet region being configured to receive the flow of air from the inlet region via the air passageway interface and discharge the flow of air to a combustor head of the gas turbine engine. The fuel injector also comprises a fuel passageway having a fuel outlet configured to discharge a flow of fuel into the combustor head. A width of the inlet region in a direction perpendicular to a centreline of the air passageway decreases continuously from the air inlet to the air passageway interface.
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公开(公告)号：US20240117744A1
公开(公告)日：2024-04-11
申请号：US18467387
申请日：2023-09-14
Applicant: ROLLS-ROYCE plc
Inventor： Bogachan ALPAN , Jonathan M. PEACE , Thomas P. HOUGHTON
Abstract: 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.
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公开(公告)号：US11954408B2
公开(公告)日：2024-04-09
申请号：US16726992
申请日：2019-12-26
Applicant: ROLLS-ROYCE plc
Inventor： Martin Rose , Stuart Marshall
CPC classification number: G06F30/17 , F01D5/141 , B23P15/02 , B23P15/04 , F01D5/16 , F04D29/38 , F05D2230/50 , F05D2260/81 , F05D2260/961
Abstract: A method of designing a modified aerofoil shape, the method comprising the steps of: determining a plurality of resonant frequencies of a baseline aerofoil shape; determining that one of the resonant frequencies falls within a predetermined range of frequencies; providing a plurality of aerofoil sections defining the baseline aerofoil shape; and defining a modified aerofoil shape by displacing at least one of the plurality of aerofoil sections relative to its baseline position in the baseline aerofoil shape until one of the plurality of resonant frequencies previously falling within the range of frequencies is shifted outside the range of frequencies.
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公开(公告)号：US20240114790A1
公开(公告)日：2024-04-04
申请号：US18244774
申请日：2023-09-11
Applicant: Rolls-Royce plc
Inventor： Jia LI , Seok Woo LEE , Vincent B. Gill
CPC classification number: H10N10/13 , F01D15/10 , F02C6/08 , H10N10/17 , F05D2260/606
Abstract: A thermoelectric generator system comprising a thermoelectric generator, a vortex tube for receiving a compressed gas from a flow input and separating the compressed gas into a hot flow exiting a first output and a cold flow exiting a second output, a sensor system for determining a first parameter, a second parameter, and a third parameter, the third parameter being indicative of a temperature of a third fluid flow, a radiator system comprising a first and second heat exchangers disposed on opposing sides of the thermoelectric generator; a tube system to separately direct the hot, cold, and third fluid flows towards a switch arrangement configured to be moveable between a first configuration, a second configuration, and a third configuration, with a control unit for controlling the switch arrangement based on the first, second, and third parameter.
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公开(公告)号：US20240110517A1
公开(公告)日：2024-04-04
申请号：US18372836
申请日：2023-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
CPC classification number: F02C7/18 , F02C7/06 , F02C7/32 , F05D2260/232 , F05D2260/98
Abstract: A method of operating a gas turbine engine for an aircraft including: a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor; a fan; turbomachinery bearings; a power gearbox; and a heat management system configured to provide lubrication and cooling to the gearbox and turbomachinery bearings. The method includes operating the heat management system to provide a first amount of heat and a second amount of heat such that a first proportion of heat generated by the gearbox and the turbomachinery and dissipated to air at 85% of a core shaft maximum take-off speed is in the range of from 0.25 to 0.70; and operating the fan at cruise condition to provide a fan pressure ratio in the range of from 1.35 to 1.43.
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Patent Agency Ranking
公开(公告)号：US20240110512A1
公开(公告)日：2024-04-04
申请号：US18463641
申请日：2023-09-08
Applicant: Rolls-Royce plc
Inventor： Mark P. Reid
Abstract: A heat management system includes a fuel tank storing a fuel; a first heat exchanger thermally coupled to the fuel tank; a hydraulic pump for circulating a hydraulic fluid; a hydraulic circuit including first and second hydraulic lines fluidly coupled to the first heat exchanger and the hydraulic pump, such that the first heat exchanger brings the hydraulic fluid and the fuel into a heat exchange relationship; an oil circuit; and a second heat exchanger thermally coupled to the oil circuit and at least one of the first and second hydraulic lines, such that the second heat exchanger brings the hydraulic fluid and the oil into a heat exchange relationship, thereby allowing heat transfer between the fuel and the oil via the hydraulic fluid.
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公开(公告)号：US20240110508A1
公开(公告)日：2024-04-04
申请号：US18372814
申请日：2023-09-26
Applicant: ROLLS-ROYCE plc
Inventor： Andrea MINELLI
Abstract: A geared gas turbine engine includes a heat management system configured to provide lubrication and cooling to a power gearbox and turbomachinery bearings, and including a pipe assembly adapted to provide a lubricant flow to the power gearbox and turbomachinery bearings to remove the heat generated by the power gearbox and turbomachinery bearings, an air-lubricant heat exchanger to dissipate a first amount of heat, and a fuel-lubricant heat exchanger to dissipate a second amount of heat wherein the heat management system is configured to provide the first amount of heat and the second amount of heat such that at cruise conditions a proportion of heat generated by the gearbox and the turbomachinery and dissipated to air is in the range of from 0.35 to 0.80.
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公开(公告)号：US20240102652A1
公开(公告)日：2024-03-28
申请号：US18215271
申请日：2023-06-28
Applicant: ROLLS-ROYCE plc
Inventor： Ewan F THOMPSON
Abstract: A liner for use with a gas turbine engine includes a first liner portion including a first upstream surface and a first downstream surface. The liner further includes a second liner portion spaced apart from the first liner portion. The second liner portion includes a second upstream surface and a second downstream surface. The second upstream surface faces the first downstream surface. Each of the first liner portion and the second liner portion at least circumferentially and radially extends with respect to a central axis. Each of the first liner portion and the second liner portion includes a substrate made of a metallic material and a wear resistant coating disposed on at least a portion of the substrate. The wear resistant coating is made of a polymeric material. The wear resistant coating at least forms the first downstream surface and the second upstream surface.
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公开(公告)号：US11927378B2
公开(公告)日：2024-03-12
申请号：US18057270
申请日：2022-11-21
Applicant: ROLLS-ROYCE plc
Inventor： Chloe J. Palmer , Ian M. Bunce
CPC classification number: F25B49/02 , F25B9/008 , F25B9/06 , G01N25/12 , F25B2309/061 , F25B2600/2515
Abstract: A sensor assembly is shown for sensing a crossing of the critical point in a system utilising a working fluid in a transcritical cycle passing through the critical point. A first broadband acoustic sensor is located upstream of a component and a second broadband acoustic sensor is located downstream of the component, each of which are arranged to detect high-frequency and low-frequency sounds caused by the crossing of the critical point. A flow regulation device regulates flow of working fluid through the component in response to the output of one or both of the first broadband acoustic sensor and the second broadband acoustic sensor, thereby adjusting the location of the crossing of the critical point.
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公开(公告)号：US20240077025A1
公开(公告)日：2024-03-07
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
CPC classification number: F02C7/16 , 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 is exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.
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