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公开(公告)号：US20230167768A1
公开(公告)日：2023-06-01
申请号：US17940055
申请日：2022-09-08
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Jonathan A. CHERRY , Paul R. DAVIES , David A. JONES , Andrew J. NEWMAN , Benjamin J. SELLERS , Stephen J. BRADBROOK
CPC classification number: F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
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公开(公告)号：US20240077023A1
公开(公告)日：2024-03-07
申请号：US18233592
申请日：2023-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： James G. COLE , David A. JONES
CPC classification number: F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, and a first heat exchanger module. The first thermal bus includes 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 or each first electric machine, and the first heat exchanger. Waste heat energy generated by at least one of the first gas turbine engine, and the or each first electric machine, is transferred to the first heat transfer fluid. The first heat exchanger module includes a first flow path and a second flow path. The first flow path is configured to direct a flow of the heat transfer fluid to a first heat dissipation portion.
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公开(公告)号：US20240076053A1
公开(公告)日：2024-03-07
申请号：US18233502
申请日：2023-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Paul R. DAVIES , Alexander T. JOYCE , David A. JONES
CPC classification number: B64D33/08 , F02C6/18 , F05D2260/20
Abstract: A thermal management system for an aircraft includes a first thermal bus including one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources. The vapour compression system includes a compressor, a condenser, a receiver, a first side of a recuperator, an expansion valve, an evaporator, a second side of the recuperator, and the compressor. A first heat flow (Q1) of waste heat energy generated by the first heat sources is transferred via the first heat transfer fluid to the heat sink. A second heat flow (Q2) of waste heat energy generated by the second heat source(s) being transferred via the evaporator to a refrigerant. A third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid. The controller is configured to ensure that:
1.1*Q2-
公开(公告)号：US20250092823A1
公开(公告)日：2025-03-20
申请号：US18969412
申请日：2024-12-05
Applicant: ROLLS-ROYCE PLC
Inventor： Natalie C. WONG , Thomas S. BINNINGTON , David A. JONES , Daniel BLACKER
IPC: F02C7/04 , B64D27/10 , B64D27/20 , B64D33/02 , B64D33/04 , B64D33/08 , B64D33/10 , F01D9/06 , F02C7/08 , F02C7/12 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/075 , F02K3/115
Abstract: An aircraft comprises a machine body which encloses a turbofan gas turbine engine. The turbofan gas turbine engine includes a heat exchanger module, fan assembly, compressor module, turbine module, and exhaust module. The heat exchanger module communicates with the fan assembly by an inlet duct. The heat exchanger module includes first heat transfer elements that transfer heat energy from a first fluid within the transfer elements to an airflow passing over a surface of the transfer elements before entry of the airflow into a fan assembly inlet. The first fluid contained within transfer elements has a temperature, and the airflow passing over the transfer element surface has a temperature. The turbofan gas turbine engine further includes at least one second heat transfer element, with the or each second heat transfer element transfers heat energy from the first fluid to a second fluid.
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公开(公告)号：US20240077022A1
公开(公告)日：2024-03-07
申请号：US18233533
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , David A. JONES , Richard G. MOCHRIE
CPC classification number: F02C7/16 , B64D27/10 , F05D2260/232
Abstract: A thermal management system for an aircraft comprises a first gas turbine engine, one or more first electric machines rotatably coupled to the first gas turbine engine, a first thermal bus, a first heat exchanger, and one or more first ancillary systems. 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 or each first electric machine, the first gas turbine engine, the first heat exchanger, and the or each first ancillary system. Waste heat energy generated by at least one of the first gas turbine engine, the or each first electric machine, and the or each first ancillary system, is transferred to the first heat transfer fluid. The first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a dissipation medium.
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Patent Agency Ranking
公开(公告)号：US20220112843A1
公开(公告)日：2022-04-14
申请号：US17484897
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S BINNINGTON , David A. JONES , Daniel BLACKER
Abstract: A turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly comprises a plurality of fan blades defining a fan diameter (D), and the heat exchanger module comprises a plurality of heat exchanger elements.
The heat exchanger module is in fluid communication with the fan assembly by an inlet duct, with the heat exchanger module having an axial length along a central axis between an upstream-most face of the heat exchanger elements and a downstream-most face of the heat exchanger elements. The axial length is in the range of 0.1*D to 5.0*D.-
公开(公告)号：US20220112842A1
公开(公告)日：2022-04-14
申请号：US17484622
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S. BINNINGTON , David A. JONES , Daniel BLACKER
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 combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling 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 cooling flow prior to an entry of the entire fluid cooling flow into the fan module.
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公开(公告)号：US20220112841A1
公开(公告)日：2022-04-14
申请号：US17484873
申请日：2021-09-24
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S. BINNINGTON , David A. JONES , Daniel BLACKER
IPC: F02C7/14
Abstract: A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter PEX (W/N) defined as PEX=H/T is 0.4 to 6.0.
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公开(公告)号：US20240077019A1
公开(公告)日：2024-03-07
申请号：US18233518
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R. DAVIES , Alexander T. JOYCE , David A. JONES
CPC classification number: F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, first thermal bus, first heat exchanger, one or more first ancillary systems, vapour compression system, one or more second ancillary systems and second heat exchanger. A waste heat energy generated by a first gas turbine engine, and a first ancillary system, transfers to the first heat transfer fluid. A waste heat energy generated by a second ancillary system transfers to a second heat transfer fluid, and the second heat exchanger transfers the waste heat energy from the second heat transfer fluid to the first heat transfer fluid. The waste heat energy generated by a second ancillary system transfers to the first heat transfer fluid, and the first heat exchanger transfers the waste heat energy to a dissipation medium. The waste heat energy transferred to the second heat transfer fluid ranges from 20 kW to 300 kW.
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公开(公告)号：US20220112866A1
公开(公告)日：2022-04-14
申请号：US17497606
申请日：2021-10-08
Applicant: ROLLS-ROYCE plc
Inventor： Natalie C. WONG , Thomas S. BINNINGTON , David A. JONES , Daniel BLACKER
Abstract: An aircraft comprises a machine body which encloses a turbofan gas turbine engine. The turbofan gas turbine engine includes a heat exchanger module, fan assembly, compressor module, turbine module, and exhaust module. The heat exchanger module communicates with the fan assembly by an inlet duct. The heat exchanger module includes first heat transfer elements that transfer heat energy from a first fluid within the transfer elements to an airflow passing over a surface of the transfer elements before entry of the airflow into a fan assembly inlet. The first fluid contained within transfer elements has a temperature, and the airflow passing over the transfer element surface has a temperature. The turbofan gas turbine engine further includes at least one second heat transfer element, with the or each second heat transfer element transfers heat energy from the first fluid to a second fluid.
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