Chilled working fluid generation and separation for an aircraft
A system for an aircraft includes an engine bleed source of a gas turbine engine. The system also includes a means for chilling an engine bleed air flow from the engine bleed source to produce a chilled working fluid. The system further includes a means for providing the chilled working fluid for an aircraft use.
1. A system for an aircraft, the system comprising:
an engine bleed source of a gas turbine engine;
a means for chilling an engine bleed air flow from the engine bleed source to produce liquid air comprising a cryogenic cooling system comprising a heat exchanger system operable to pre-cool the engine bleed air flow, a compressor operable to further compress the engine bleed air flow as compressed air, and at least one turbine operable to expand and cool the compressed air as a cooled flow, wherein the heat exchanger system is configured to receive a cooling air intake that pre-cools the engine bleed air flow and cools the compressed air from the compressor prior to reaching the at least one turbine; and
a means for providing the liquid air for an aircraft use.
2. The system of claim 1 , wherein the cryogenic cooling system further comprises a vacuum system and a condensate pump system operable to condense the liquid air from the cooled flow and urge the liquid air through a feeder line.
3. The system of claim 2 , wherein the means for providing the liquid air for the aircraft use comprises at least one pump in fluid communication with the feeder line and a plumbing system comprising one or more lines and valves.
4. The system of claim 1 , wherein the aircraft use comprises cooling one or more components of the aircraft.
5. The system of claim 1 , wherein the aircraft use comprises an increased airflow to one or more of: components of the gas turbine engine, a cabin of the aircraft, and electronics of the aircraft.
6. The system of claim 1 , further comprising a cryogenic air separator operable to separate gaseous nitrogen from the liquid air as a gaseous nitrogen supply and separate liquid oxygen from the liquid air as a liquid oxygen supply.
7. The system of claim 6 , wherein at least a portion of the gaseous nitrogen supply is provided to one or more of: a fuel system of the aircraft and a location downstream of a combustor of the gas turbine engine.
8. The system of claim 6 , wherein at least a portion of the liquid oxygen supply is provided to one or more of: a cabin of the aircraft and a compressor stream of the gas turbine engine.
9. The system of claim 1 , wherein the compressor and the at least one turbine are mechanically linked together by a shaft.
10. The system of claim 1 , wherein the aircraft use comprises an increased airflow to a cabin of the aircraft.
11. The system of claim 1 , wherein the aircraft use comprises an increased airflow to electronics of the aircraft.
12. A method comprising:
providing an engine bleed air flow from an engine bleed source of a gas turbine engine to a cryogenic cooling system;
chilling the engine bleed air flow using the cryogenic cooling system to produce liquid air by:
pre-cooling the engine bleed air flow using a heat exchanger system;
compressing the engine bleed air flow as compressed air by a compressor of the cryogenic cooling system; and
expanding and cooling the compressed air as a cooled flow by at least one turbine of the cryogenic cooling system, wherein a cooling air intake is received at the heat exchanger system that pre-cools the engine bleed air flow and cools the compressed air from the compressor prior to reaching the at least one turbine; and
pumping the liquid air for an aircraft use.
13. The method of claim 12 , further comprising:
condensing the liquid air from the cooled flow; and
urging the liquid air through a feeder line.
14. The method of claim 12 , wherein the aircraft use comprises cooling and increasing an airflow to one or more components of the aircraft.
15. The method of claim 12 , further comprising:
separating gaseous nitrogen from the liquid air as a gaseous nitrogen supply; and
separating liquid oxygen from the liquid air as a liquid oxygen supply.
16. The method of claim 15 , further comprising:
providing at least a portion of the gaseous nitrogen supply to one or more of: a fuel system of the aircraft and a location downstream of a combustor of the gas turbine engine.
17. The method of claim 16 , further comprising:
providing at least a portion of the liquid oxygen supply to one or more of: a cabin of the aircraft and a compressor stream of the gas turbine engine.