Cryogenic cooling system for an aircraft
AssigneeRtx Corporation
InventorsFrederick M. Schwarz, Michael Winter, Charles E. Lents, Nathan Snape, Alan H. Epstein
Life of this patent
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Abstract
A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.
Claims20
A gas turbine engine of an aircraft, the gas turbine engine comprising:
- a compressor section;
- a turbine section operably coupled to the compressor section;
- a means for selectively releasing a cooling fluid flow produced on board the aircraft at a cryogenic temperature;
- and
- a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow, the plumbing system configured to route the cooling fluid flow to either or both of the compressor section and the turbine section.
A method comprising:
- determining, by a controller, a flight phase of an aircraft;
- determining, by the controller, an operating parameter of a gas turbine engine of the aircraft;
- and
- selectively releasing liquid air from a liquid air source to a plumbing system configured to route a cooling fluid flow from the liquid air source to either or both of a compressor section and a turbine section of the gas turbine engine based on either or both of the flight phase and the operating parameter of the gas turbine engine.
A system for an aircraft, the system comprising:
- a gas turbine engine comprising a compressor section and a turbine section operably coupled to the compressor section;
- a cryogenic cooling system operable to receive one or more air flows from the gas turbine engine and output a cooling fluid flow produced on board the aircraft at a cryogenic temperature;
- and
- a plumbing system in fluid communication with the cryogenic cooling system, the plumbing system configured to route the cooling fluid flow from the cryogenic cooling system to either or both of the compressor section and the turbine section.
Dependencies are inferred from the claim text.