Patent ID: 11897624
Assignee: GENERAL ELECTRIC COMPANY
Field: Transport (Mechanical engineering)
Classification: CPC B | IPC B

Claim 17:
18. A method for thermal management for an aircraft, the method comprising:
extracting a flow of compressed fluid from a compressor section of a propulsion system, wherein the flow of compressed fluid comprises a pressure parameter;
generating an output torque via expanding at least a portion of the flow of compressed fluid across a turbine operably connected to a driveshaft, wherein the turbine is positioned downstream of the compressor section and upstream of a cooling system; and
operating a turbomachine at the cooling system via the output torque from the turbine, wherein operating the turbomachine at the cooling system comprises:
providing, in serial flow arrangement, the flow of compressed fluid to a compressor at the turbomachine, a heat exchanger positioned downstream of the compressor, and an expander positioned downstream of the compressor.