Patent ID: 11912416
Assignee: HAMILTON SUNDSTRAND CORPORATION
Field: Transport (Mechanical engineering)
Classification: CPC B  H  Y | IPC B

Claim 14:
15. An aircraft comprising:
a fuselage;
wings; and
a pressurized fuel tank containing a pressurized fuel;
a turbo-compressor comprising a turbo expander and a compressor operably coupled by a shaft, wherein the turbo expander is configured to receive the pressurized fuel from the pressurized fuel tank, the turbo expander configured to decrease a pressure of the pressurized fuel to generate low pressure fuel, wherein the low pressure fuel has a pressure that is less than the pressurized fuel;
a fuel-to-air heat exchanger configured to receive the low pressure fuel from the turbo expander as a first working fluid and compressed air as a second working fluid from the compressor, the heat exchanger configured to cool the compressed air to generate conditioned air and warm the fuel to generate treated fuel;
an aircraft cabin configured to receive the conditioned air; and
a fuel consumption system configured to consume the treated fuel to generate power,
wherein the fuel consumption system is installed to at least one of the fuselage and the wings.