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
An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.
Claims20
An engine-driven cryogenic cooling system for an aircraft, the engine-driven cryogenic cooling system comprising:
- a first air cycle machine comprising a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream from a first engine bleed source of the gas turbine engine;
- a second air cycle machine operable to output a chilled air stream at a cryogenic temperature from a second engine bleed source cooled by the cooling air stream of the first air cycle machine;
- and
- a means for condensing the chilled air stream into liquid air for an aircraft use.
A method comprising:
- driving rotation of a plurality of components of a first air cycle machine through a gearbox operably coupled to a shaft of a gas turbine engine to produce a cooling air stream from a first engine bleed source of the gas turbine engine;
- outputting a chilled air stream at a cryogenic temperature from a second air cycle machine from a second engine bleed source cooled by the cooling air stream of the first air cycle machine;
- and
- condensing the chilled air stream into liquid air for an aircraft use.
A system for an aircraft, the system comprising:
- a gas turbine engine operable to produce thrust for the aircraft;
- a means for cryogenically cooling the aircraft;
- and
- a means for transferring energy from the gas turbine engine to the means for cryogenically cooling the aircraft comprising:
- a first air cycle machine comprising a plurality of components operably coupled to the gearbox and configured to produce a cooling air stream from a first engine bleed source of the gas turbine engine;
- a second air cycle machine operable to output a chilled air stream at a cryogenic temperature from a second engine bleed source cooled by the cooling air stream of the first air cycle machine;
- and
- a liquid air collection system operable to condense the chilled air stream into liquid air for an aircraft use.
Dependencies are inferred from the claim text.