High speed aircraft flight technologies

A hypersonic and turbine engine technology, applied in aircraft, high-efficiency propulsion technology, supersonic aircraft, etc., can solve problems such as heat increase and thermal management problems

Pending Publication Date: 2020-10-30
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

for example, thermal management becomes far more problematic in high-speed operations due to the increased heat generated by hypersonic shock waves at hypersonic flight speeds

Method used

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  • High speed aircraft flight technologies
  • High speed aircraft flight technologies
  • High speed aircraft flight technologies

Examples

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Embodiment Construction

[0107] Reference will now be made in detail to 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. Like or similar numerals have been used in the drawings and description to indicate like or like parts of the present invention.

[0108] The word "exemplary" is used herein to mean "serving as an example, instance, or demonstration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations.

[0109] As used herein, the terms "first," "second," and "third" are used interchangeably to distinguish one element from another, and are not intended to denote the position or importance of individual elements.

[0110] The terms "forward" and "aft" refer to relative positions within the gas turbine engine or vehicle, and to the normal operating attit...

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PUM

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Abstract

The invention relates to high speed aircraft flight technologies. A hypersonic propulsion engine comprises: a turbine engine comprising a compressor section, a combustion section and a turbine sectionarranged in serial flow order, the turbine section defining a turbine engine inlet upstream of the compressor section and a turbine engine exhaust downstream of the turbine section; a ducting assembly defining a bypass duct having a substantially annular shape and extending around the turbine engine, an afterburning chamber located downstream of the bypass duct and at least partially aft of the turbine engine exhaust, and an inlet section located at least partially forward of the bypass duct and the turbine engine inlet; and an inlet precooler positioned at least partially within the inlet section of the ducting assembly and upstream of the turbine engine inlet, the bypass duct, or both for cooling an airflow provided through the inlet section of the ducting assembly to the turbine engineinlet, the bypass duct or both.

Description

[0001] priority information [0002] This application claims priority to U.S. Provisional Patent Application Serial No. 62 / 840697, filed April 30, 2019, which is incorporated herein by reference. technical field [0003] This topic generally relates to technologies that allow high-speed aircraft to fly. Background technique [0004] High-speed hypersonic propulsion engines facilitate supersonic and hypersonic air transport. Operating at such high speeds creates a number of problems that do not exist or are less prevalent in subsonic and supersonic flight operations. For example, thermal management issues become far more problematic in high-speed operations due to the increased heat generated by hypersonic shock waves at hypersonic flight speeds. Therefore, improvements to aircraft and hypersonic propulsion engines for aircraft that help overcome these problems would be useful. Contents of the invention [0005] Aspects and advantages of the invention will be set forth ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K3/06F02C7/143F01D9/02
CPCF02K3/06F02C7/143F01D9/02F05D2220/80F02C7/224F02K7/16F02C7/04F02K3/11Y02T50/60B64C30/00B64D33/02B64D2033/024B64D2033/026B64D27/12B64D33/08F02K3/025B64D33/04
Inventor B.F.鲍威尔N.D.乔世T.J.索默乐N.W.拉泰W.D.格尔斯特勒K.K.辛赫B.W.米勒
Owner GENERAL ELECTRIC CO
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