A cooling system (300) for an aircraft (40) includes an air intake (50), a heat exchanger (304) configured to receive air passing into the air intake (302) when the aircraft (40) is operating at Mach speed, and configured to receive compressed refrigerant from a first compressor (326) at a first pressure, an evaporator (318) positioned within the aircraft (40) and configured to receive heated air from a compartment within the aircraft (40), at least one of an expansion device (310) and an expansion machine (328), and the compressed refrigerant rejects heat in the heat exchanger (304) to the air, expands in the at least one of the expansion device (310) and the expansion machine (328), and receives heat in the evaporator (318) from the heated air.
Cooling systems for high mach applications
Kühlsysteme für Überschallanwendungen
Systèmes de refroidissement pour des régimes supersoniques
2018-11-14
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Considerations of turbine cooling systems for Mach 3 flight
TIBKAT | 1968
|Electronic Equipment Cooling Design Concepts for High Mach Number Aircraft
SAE Technical Papers | 1984