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US 2019/0292982 A1Published application
Chilled working fluid generation and separation for an aircraft
AssigneeUnited Technologies Corporation
InventorMichael Winter
Life of this patent
Estimating the term…
Abstract
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.
Claims20
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 a chilled working fluid at a temperature below a boiling point of oxygen and above a boiling point of nitrogen;
- and
- a means for providing the chilled working fluid for an aircraft use.
1 more element
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;
- and
- pumping the liquid air for an aircraft use.
1 more element
A system for an aircraft, the system comprising:
- a gas turbine engine operable to produce thrust for the aircraft;
- and
- a means for cryogenically cooling the aircraft based on an engine bleed source of the gas turbine engine.
Dependencies are inferred from the claim text.