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

Claim 16:
17. 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; and
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
wherein generating the output torque via expanding at least the portion of the flow of compressed fluid across the turbine comprises converting excess pressure of the flow of compressed fluid from the compressor section into the output torque at the driveshaft; and
wherein an amount of the flow converted as part of converting excess pressure of the flow of compressed fluid corresponds to a difference between a pressure requirement of the flow of compressed fluid at the cooling system and the pressure parameter of the flow of compressed fluid at the compressor section.