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US 11,897,624 B2Granted
Method for thermal management for an aircraft propulsion system using a flow of compressed fluid extracted from a compressor section
AssigneeGeneral Electric Company
InventorsJeffrey Douglas Rambo, Scott Gregory Edens
Life of this patent
Estimating the term…
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.
Claims20
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 first 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;
- determining a pressure requirement of the flow of compressed fluid at the cooling system;
- and
- providing at least a second portion of the flow of compressed fluid to the cooling system, wherein the portion of the flow of compressed fluid comprises the pressure requirement.
2 more elements
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, wherein generating the output torque via expanding at least the portion of the flow of compressed fluid across the turbine comprises:
- providing a first portion of the flow of compressed fluid to the turbine;
- and
- providing, from upstream of the turbine, 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.
2 more elements
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.
3 more elements
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
- operating a turbomachine at the cooling system via the output torque from the turbine, wherein operating the turbomachine at the cooling system comprises:
- providing, in serial flow arrangement, the flow of compressed fluid to a compressor at the turbomachine, a heat exchanger positioned downstream of the compressor, and an expander positioned downstream of the compressor.
2 more elements
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 then expanding the first portion of the flow of compressed fluid across the turbine;
- providing, from the flow control device, a second portion of the flow of compressed fluid to the cooling system.
3 more elements
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.
4 more elements
Dependencies are inferred from the claim text.