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

Claim 19:
20. 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
modulating mass flowrate of the flow of compressed fluid to the turbine based at least on a flow control device upstream of the turbine and downstream of the compressor section, wherein modulating mass flowrate of the flow of compressed fluid to the turbine comprises:
providing, from the flow control device, a first portion of the flow of compressed fluid to the turbine, wherein the first portion of the flow of compressed fluid corresponds to a difference between the pressure requirement at the cooling system and the pressure parameter of the flow of compressed fluid from the compressor section; and
providing, from the flow control device, a second portion of the flow of compressed fluid to the cooling system, wherein the second portion of the flow of compressed fluid corresponds to a pressure requirement at the cooling system.