A cooling system for an aircraft includes an air intake, a heat exchanger configured to receive air passing into the air intake when the aircraft is operating at Mach speed, and configured to receive compressed refrigerant from a first compressor at a first pressure, an evaporator positioned within the aircraft and configured to receive heated air from a compartment within the aircraft, at least one of an expansion device and an expansion machine, and the compressed refrigerant rejects heat in the heat exchanger to the air, expands in the at least one of the expansion device and the expansion machine, and receives heat in the evaporator from the heated air.
Cooling systems for high mach applications
2017-08-22
Patent
Elektronische Ressource
Englisch
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