Method and system for thermal management
AssigneeGeneral Electric Company
InventorsJeffrey Douglas Rambo, Scott Gregory Edens
Life of this patent
Estimating the term…
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.
A thermal management system for a propulsion system of an aircraft, the thermal management system comprising:
- a flow control device in fluid communication with a compressor section of the propulsion system, wherein the flow control device is configured to split a flow of compressed fluid from the compressor section into a first portion of the compressed fluid and a second portion of the compressed fluid;
- a first turbine disposed downstream from and in fluid communication with the flow control device, wherein the first turbine is configured to receive the first portion of the compressed fluid;
- a first thermal load in thermal communication with the first portion of the compressed fluid downstream from the compressor;
- a compressor disposed downstream from and in fluid communication with the flow control device;
- a second turbine disposed downstream from and in fluid communication with the compressor;
- and
- a second thermal load in thermal communication with the second portion of the compressed fluid downstream from the second turbine.
Dependencies are inferred from the claim text.