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公开(公告)号：US20240077021A1
公开(公告)日：2024-03-07
申请号：US18233531
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R DAVIES , Richard G MOCHRIE , David A JONES
CPC classification number: F02C7/16 , B64D27/10 , F05D2260/20
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. Waste heat energy generated by at least one first gas turbine engine, and first electric machine, transfers to the first heat transfer fluid. The first heat exchanger directs a first proportion of the first heat transfer fluid through a first heat dissipation portion wherein a first proportion of the waste heat energy transfers to a first dissipation medium dependent on the first dissipation medium temperature and mass flow rate. The first heat exchanger directs a second proportion of the first heat transfer fluid through a second heat dissipation portion wherein the second proportion of waste heat energy transfers to a second dissipation medium dependent on the second dissipation medium temperature and mass flow rate.
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Patent Agency Ranking
公开(公告)号：US20230279815A1
公开(公告)日：2023-09-07
申请号：US18166268
申请日：2023-02-08
Applicant: Rolls-Royce plc
Inventor： Richard G MOCHRIE , Graeme E F Sutcliffe , Jade Whittle
CPC classification number: F02C9/26 , F02C7/224 , F02C7/22 , F02C7/14 , 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.
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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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公开(公告)号：US20230286658A1
公开(公告)日：2023-09-14
申请号：US18170604
申请日：2023-02-17
Applicant: ROLLS-ROYCE plc
Inventor： Graeme E F SUTCLIFFE , Richard G MOCHRIE , Jade WHITTLE
CPC classification number: F02K7/16 , F02C7/04 , F05D2220/10 , F05D2220/323 , F05D2240/10 , F05D2260/213
Abstract: A ram-air duct system includes a ram-air duct configured to receive a flow of ram-air from a ram-air inlet and discharge the flow to a ram-air outlet. The system also includes a heat exchanger configured to exchange heat with air within the ram-air duct, an auxiliary air passageway and an electrically-driven air mover configured to move a flow of auxiliary air along the auxiliary air passageway for discharge into the ram-air duct through an intermediate inlet between the ram-air inlet and the ram-air outlet. The air duct system further includes a controller configured to selectively operate the ram-air duct system in an auxiliary supply mode in which the air mover and/or a control valve are controlled to cause the flow of auxiliary air to be discharged into the duct through the intermediate inlet, to thereby control a rate of heat exchange between the heat exchanger and air within the duct.
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公开(公告)号：US20240077020A1
公开(公告)日：2024-03-07
申请号：US18233521
申请日：2023-08-14
Applicant: ROLLS-ROYCE PLC
Inventor： Richard G MOCHRIE , David A JONES
CPC classification number: F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213 , F05D2270/303
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, and a first heat exchanger module. 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 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 comprises a first flow path and a second flow path. The first flow path is configured to direct a flow of the first heat transfer fluid either to a first heat dissipation portion in which a first proportion QA of the waste heat energy from the first heat transfer fluid is transferred to a first dissipation medium, or additionally to a second heat dissipation portion in which a second proportion QB of the waste heat energy from the first heat transfer fluid is transferred to a second dissipation medium, in dependence on a temperature of the first heat transfer fluid entering the first heat exchanger module, a temperature of the first heat dissipation medium, and a temperature of the second heat dissipation medium. The second flow path is configured to direct the flow of the first heat transfer fluid to a second heat dissipation portion in which a second proportion QB of the waste heat energy from the first heat transfer fluid is transferred to a second dissipation medium, or additionally to the first heat dissipation portion in which a first proportion QA of the waste heat energy from the first heat transfer fluid is transferred to a first dissipation medium, in dependence on a temperature of the first heat transfer fluid entering the first heat exchanger module, a temperature of the first heat dissipation medium, and a temperature of the second heat dissipation medium.
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公开(公告)号：US20240076052A1
公开(公告)日：2024-03-07
申请号：US18233495
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Paul R DAVIES , David A JONES , Richard G MOCHRIE
CPC classification number: B64D33/08 , F02C7/12 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a first gas turbine engine, one or more first electric machines, a first thermal bus, and a first heat exchanger. The first thermal bus includes a first heat transfer fluid 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 first heat transfer fluid. When airspeed of aircraft is less than Mn0.6, the first heat exchanger transfers the waste heat energy from the first heat transfer fluid to a first dissipation medium. When the airspeed of the aircraft is greater than Mn0.6, the first heat exchanger is configured to transfer the waste heat energy from the first heat transfer fluid to a second dissipation medium.
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