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公开(公告)号：US20240182180A1
公开(公告)日：2024-06-06
申请号：US18437873
申请日：2024-02-09
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Scott Gregory Edens
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.
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公开(公告)号：US20220242587A1
公开(公告)日：2022-08-04
申请号：US17164208
申请日：2021-02-01
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Scott Gregory Edens
Abstract: A method and structure for thermal management for a vehicle is provided. The method includes extracting a flow of compressed fluid from a compressor section of a propulsion system in which the flow of compressed fluid includes 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. The turbine is positioned downstream of the compressor section and upstream of a cooling system.
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公开(公告)号：US11897624B2
公开(公告)日：2024-02-13
申请号：US17164208
申请日：2021-02-01
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Scott Gregory Edens
Abstract: A method and structure for thermal management for a vehicle is provided. The method includes extracting a flow of compressed fluid from a compressor section of a propulsion system in which the flow of compressed fluid includes 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. The turbine is positioned downstream of the compressor section and upstream of a cooling system.
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公开(公告)号：US20230011409A1
公开(公告)日：2023-01-12
申请号：US17373127
申请日：2021-07-12
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Brandon Wayne Miller , Scott Gregory Edens
Abstract: A method of managing thermal energy in a propulsion system includes diverting a flow of bleed air from a compressor section of the propulsion system. An amount of the flow of bleed air diverted from the compressor section is at least 5% of an inlet flow at an inlet of a high pressure compressor of the compressor section. The flow of bleed air is provided to a thermal management system. The flow of bleed air is passed through an expansion turbine of the thermal management system. The flow of bleed air is provided to a thermal load.
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