Method and system for thermal management
AssigneeGeneral Electric Company
InventorsJeffrey Douglas Rambo, Scott Gregory Edens
Life of this patent
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Abstract
A thermal management system for a propulsion system of an aircraft includes a fluid circuit configured to provide a flow of a compressed fluid from a compressor section of the propulsion system to, in serial flow order, a first turbine, a compressor, a second turbine, a thermal load, and an exhaust sink. A heat exchanger is disposed in a fan stream of the propulsion system at a location along the fluid circuit between the compressor and the second turbine. The fluid circuit extends through and is in thermal communication with the heat exchanger.
Claims20
A thermal management system for a propulsion system of an aircraft, the thermal management system comprising:
- a fluid circuit configured to provide a flow of a compressed fluid from a compressor section of the propulsion system to, in serial flow order, a first turbine, a compressor, a second turbine, a thermal load, and an exhaust sink;
- and
- a heat exchanger disposed in a fan stream of the propulsion system at a location along the fluid circuit between the compressor and the second turbine, wherein the fluid circuit extends through and is in thermal communication with the heat exchanger.
Dependencies are inferred from the claim text.