Cryogenic cooling system for an aircraft
A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.
1. A cryogenic cooling system for an aircraft, the cryogenic cooling system comprising:
a first air cycle machine operable to intake air from a first air source and output a cooling air stream;
a second air cycle machine operable to intake air from a second air source and output a chilled air stream at a cryogenic temperature, wherein the second air source is cooled by the cooling air stream of the first air cycle machine; and
a means for collecting liquid air from the chilled air stream, wherein the means comprises a vacuum pump system.
2. The cryogenic cooling system of claim 1 , wherein the first air cycle machine comprises a first compressor section and a first turbine section, and the second air cycle machine comprises a second compressor section and a second turbine section.
3. The cryogenic cooling system of claim 2 , wherein the first compressor section comprises a first compressor wheel operably coupled to a first turbine wheel of the first turbine section and a first fan, and the second compressor section comprises a second compressor wheel operably coupled to a second turbine wheel of the second turbine section and a second fan.
4. The cryogenic cooling system of claim 3 , further comprising a first heat exchanger system operable to pre-cool a first air flow from the first air source prior to entry into the first compressor wheel and cool the first air flow after exiting the first compressor wheel, and a second heat exchanger system operable to pre-cool a second air flow from the second air source prior to entry into the second compressor wheel and cool the second air flow after exiting the second compressor wheel.
5. The cryogenic cooling system of claim 4 , wherein the first fan is operable to urge a first heat exchanger cooling flow across the first heat exchanger system, the second fan is operable to urge a second heat exchanger cooling flow across the second heat exchanger system, and the second heat exchanger cooling flow comprises the cooling air stream of the first air cycle machine.
6. The cryogenic cooling system of claim 5 , further comprising:
a first water separator in fluid communication with an output of the first compressor wheel and an input of the first turbine wheel, the first water separator operable to spray extracted water from the first air flow into the first heat exchanger cooling flow; and
a second water separator in fluid communication with an output of the second compressor wheel and an input of the second turbine wheel, the second water separator operable to spray extracted water from the second air flow into the second heat exchanger cooling flow.
7. The cryogenic cooling system of claim 1 , wherein the vacuum pump system is a liquid air collection system comprising:
a vacuum system;
a liquid air condensate pump system operable to urge the liquid air through a feeder line; and
a cryogenic liquid reservoir operably coupled to the feeder line.
8. The cryogenic cooling system of claim 7 , further comprising:
a cryogenic air separator in fluid communication with the liquid air collection system, the cryogenic air separator operable to separate gaseous nitrogen and liquid oxygen from the liquid air collected by the liquid air collection system.
9. The cryogenic cooling system of claim 8 , wherein the gaseous nitrogen is supplied to a fuel system of the aircraft, and the liquid oxygen is supplied to one or more of: a cabin of the aircraft and a compressor stream of a gas turbine engine of the aircraft.
10. The cryogenic cooling system of claim 1 , wherein the liquid air is supplied as a cooling fluid to one or more of: an electric fan propulsion motor of the aircraft, an environmental control system of the aircraft, a power system of the aircraft, and a gas turbine engine of the aircraft.
11. A method comprising:
outputting a cooling air stream from a first air cycle machine of a cryogenic cooling system for an aircraft, wherein the first air cycle machine intakes air from a first air source;
outputting a chilled air stream at a cryogenic temperature from a second air cycle machine of the cryogenic cooling system, wherein the second air cycle machine intakes air from a second air source cooled by the cooling air stream of the first air cycle machine; and
collecting liquid air from the chilled air stream by a means comprising a vacuum pump system.
12. The method of claim 11 , wherein the first air cycle machine comprises a first compressor section and a first turbine section, and the second air cycle machine comprises a second compressor section and a second turbine section, and further wherein the first compressor section comprises a first compressor wheel operably coupled to a first turbine wheel of the first turbine section and a first fan, and the second compressor section comprises a second compressor wheel operably coupled to a second turbine wheel of the second turbine section and a second fan.
13. The method of claim 12 , further comprising:
pre-cooling a first air flow from the first air source through a first heat exchanger system prior to entry into the first compressor wheel;
cooling the first air flow through the first heat exchanger system after exiting the first compressor wheel;
pre-cooling a second air flow from the second air source through a second heat exchanger system prior to entry into the second compressor wheel and cool the second air flow after exiting the second compressor wheel; and
cooling the second air flow through the second heat exchanger system after exiting the second compressor wheel.
14. The method of claim 13 , further comprising:
urging, by the first fan, a first heat exchanger cooling flow across the first heat exchanger system; and
urging, by the second fan, a second heat exchanger cooling flow across the second heat exchanger system, wherein the second heat exchanger cooling flow comprises the cooling air stream of the first air cycle machine.
15. The method of claim 11 , wherein the vacuum pump system is a liquid air collection system comprising a vacuum system, a liquid air condensate pump system, a feeder line, and a cryogenic liquid reservoir operably coupled to the feeder line, the method further comprising:
controlling the liquid air collection system to urge the liquid air through the feeder line.
16. The method of claim 11 , further comprising:
separating, by a cryogenic air separator, gaseous nitrogen and liquid oxygen from the liquid air collected by the liquid air collection system.
17. The method of claim 16 , further comprising:
supplying the gaseous nitrogen to a fuel system of an aircraft; and
supplying the liquid oxygen to one or more of: a cabin of the aircraft and a compressor stream of a gas turbine engine of the aircraft.
18. The method of claim 11 , further comprising:
supplying the liquid air as a cooling fluid to one or more of: an electric fan propulsion motor of an aircraft, an environmental control system of the aircraft, a power system of the aircraft, and a gas turbine engine of the aircraft.