COOLING SYSTEMS FOR HIGH MACH APPLICATIONS

摘要

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.

主权项

1. A cooling system for an aircraft, comprising:
an air intake; a first 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 valve and a turbine; and the compressed refrigerant rejects heat in the first heat exchanger to the air, expands in the at least one of the expansion valve and the turbine, and receives heat in the evaporator from the heated air; wherein the at least one of the expansion valve and the turbine further comprise: a first turbine configured to provide a first power, and output the refrigerant to the first compressor; a second turbine coupled to the first turbine via a shaft, wherein the second turbine provides a second power to the first turbine, and output the refrigerant to the first compressor; and an expansion valve configured to receive refrigerant from the first heat exchanger and expand the refrigerant to provide expanded refrigerant to the evaporator.