US 12,358,638 B2
Thermal management system for an aircraft
Paul R Davies, Bristol (GB); Alexander T Joyce, Derby (GB); and David A Jones, Bristol (GB)
Assigned to ROLLS-ROYCE plc, London (GB)
Filed by ROLLS-ROYCE PLC, London (GB)
Filed on Aug. 14, 2023, as Appl. No. 18/233,502.
Claims priority of application No. 2212949 (GB), filed on Sep. 6, 2022.
Prior Publication US 2024/0076053 A1, Mar. 7, 2024
Int. Cl. B64D 33/08 (2006.01); F02C 6/18 (2006.01)
CPC B64D 33/08 (2013.01) [F02C 6/18 (2013.01); F05D 2260/20 (2013.01)] 10 Claims
OG exemplary drawing
 
1. A thermal management system for an aircraft, the thermal management system comprising a first thermal bus, the first thermal bus comprising, in a closed loop flow sequence, one or more first heat sources, a heat sink, a vapour compression system, and one or more second heat sources, and
wherein the vapour compression system comprises, in closed loop flow sequence, 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, each of the compressor and the expansion valve being controlled by a controller,
wherein the first thermal bus comprises a first heat transfer fluid, and 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, and
wherein the vapour compression system comprises a refrigerant fluid, a second heat flow (Q2) of waste heat energy generated by the or each second heat source is transferred via the evaporator to the refrigerant, and a third heat flow (Q3) of heat energy in the refrigerant is transferred via the condenser to the first heat transfer fluid, and the controller is configured to ensure that:
1.1*Q2<Q3<3.0*Q2.