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Systems and methods for removing heat from aircraft components

A technology for aircraft components and heat removal, applied in the field of aircraft components, can solve problems such as surface and internal temperature exceeding

Pending Publication Date: 2021-05-28
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] these heat sources can cause the surface and internal temperatures of such aircraft components to exceed their structural and / or operational capabilities, requiring expensive or exotic materials and changes in operational characteristics

Method used

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  • Systems and methods for removing heat from aircraft components
  • Systems and methods for removing heat from aircraft components
  • Systems and methods for removing heat from aircraft components

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Embodiment Construction

[0060] Reference will now be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. The same or similar symbols are used in the drawings and descriptions to refer to the same or similar parts of the present invention.

[0061] The following description is provided to enable those skilled in the art to make and use the described embodiments contemplated for carrying out the invention. However, various modifications, equivalents, variations and alternatives will still be apparent to those skilled in the art. Any and all such modifications, variations, equivalents and alternatives are intended to fall within the spirit and scope of the invention.

[0062] All directional references (e.g., radial, axial, proximal, distal, upper, lower, up, down, left, right, lateral, front, back, top, bottom, above, bel...

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PUM

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Abstract

A system for removing heat from an aircraft component includes: an aircraft component; a heat exchanger in proximity to the aircraft component and having an inlet, an outlet, and an internal surface coated with a catalyst; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger. A method of removing heat from an aircraft component includes the steps of: providing a heat exchanger in proximity to an aircraft component, the heat exchanger being in fluid communication with a source of hydrocarbon fuel and a source of water and having an internal surface coated with a catalyst; introducing a hydrocarbon fuel into the heat exchanger; introducing oxygen into the heat exchanger; contacting the hydrocarbon fuel with the catalyst; and cracking the hydrocarbon fuel to form a reformed hydrocarbon fuel and remove heat from the aircraft component.

Description

technical field [0001] The present invention relates to aircraft components, and more particularly, to those aircraft components that are exposed to heat during operation, such as during high speed flight. Background technique [0002] Many aircraft components are exposed to heat sources during operation, such as internal components of propulsion systems, including gas turbine engines. Especially during high speed flight operations, these components, as well as the exterior components of the aircraft itself, are exposed to heat from skin friction due to the speed at which the aircraft travels through the atmosphere. In addition to the temperature of the air entering the gas turbine engine, components such as aircraft skin, leading edges of structures such as wings, spines and control surfaces, and engine inlets may be particularly affected. [0003] These heat sources can cause the surface and interior temperatures of such aircraft components to exceed their structural and / ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/10B64D33/10B64D33/00
CPCB64D27/10B64D33/10B64D33/00B64C1/38B64D33/08B64D37/34F02C7/224
Inventor L·B·库尔N·D·乔西
Owner GENERAL ELECTRIC CO