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Strut for aircraft engine

An engine, prop technology, applied in the direction of machine/engine, engine manufacturing, engine components, etc.

Inactive Publication Date: 2019-04-02
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this may result in a relatively heavy strut for the strut assembly

Method used

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  • Strut for aircraft engine
  • Strut for aircraft engine
  • Strut for aircraft engine

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Embodiment Construction

[0022] Reference will now be made in detail to the 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 designations in the drawings and description have been used to refer to the same or similar parts of the present invention. As used herein, the terms "first," "second," and "third" may be used interchangeably to distinguish one element from another, and are not intended to indicate the location or location of individual elements. importance. The terms "upstream" and "downstream" refer to relative directions with respect to fluid flow in a fluid pathway. For example, "upstream" refers to the direction of fluid flow from, and "downstream" refers to the direction of fluid flow to.

[0023] figure 1 is a schematic representation of an aircraft gas turbine engine 10 according to one embodiment o...

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PUM

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Abstract

A strut for a gas turbine engine includes a body defining a first side and an opposite second side. The first side is spaced from the second side along the circumferential direction of the gas turbineengine. Additionally, the body includes an inner section, a middle section, and an outer section. Each of the inner, middle, and outer sections are arranged in series order along a span of the strutand define a thickness between the first and second sides of the strut. The thickness of the middle section is greater than the thicknesses of the inner section and of the outer section to increase the strut's resistance to buckling in response to forces exerted thereon.

Description

[0001] Federally Sponsored Research [0002] This invention was made with Government support under Contract No. FA8650-09-D-2922, United States Air Force. The government may have certain rights in this invention. technical field [0003] The subject matter generally relates to struts for aircraft engines. Background technique [0004] A gas turbine engine includes a fan section and a core engine. The core motor includes, in axial series flow relationship: a high pressure compressor to compress the air flow entering the core motor; a combustor in which a mixture of fuel and compressed air is combusted to generate a boost air stream; rotates, and it is connected by a shaft to drive a high pressure compressor. A typical bypass turbofan engine adds a low pressure turbine aft of the high pressure turbine, which drives a fan in a fan section ahead of the high pressure compressor. A splitter at the rear of the fan splits the fan flow exiting the fan into a core motor flow and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D9/02F01D9/04
CPCF01D9/02F01D9/047F05D2240/12F05D2240/128F05D2240/14F05D2250/00Y02T50/60F04D29/522F04D29/542F04D29/563
Inventor D.E.金W.E.科迪
Owner GENERAL ELECTRIC CO