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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：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：US20240077024A1
公开(公告)日：2024-03-07
申请号：US18233607
申请日：2023-08-14
Applicant: ROLLS-ROYCE plc
Inventor： Alexander T. JOYCE
CPC classification number: F02C7/16 , F02C6/18 , F05D2220/323 , F05D2260/213
Abstract: A thermal management system for an aircraft includes a thermal bus including one or more first heat sources; a heat sink; a vapour compression system including 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; and one or more second heat sources. A heat transfer fluid transfers waste heat energy generated by the first heat sources to the heat sink. A second flow of waste heat energy from the second heat source(s) is transferred to a refrigerant. A third flow of heat energy in the refrigerant is transferred to the heat transfer fluid. The compressor includes a supplementary refrigerant reservoir, and the volume of refrigerant in the vapour compression system is increased during operation when a temperature of the heat transfer fluid is at or below a temperature of the second heat source(s).
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