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Combined spray pipe structure and airplane with same

A nozzle and aircraft skin technology, which is applied to the combined nozzle structure and the aircraft field with the same, can solve the problem that the engine nozzle and the body skin are difficult to ensure seamless requirements, and can solve the problem of thermal compensation for axial elongation, The effect of convenient assembly and disassembly and maintenance, reducing maintenance costs

Active Publication Date: 2020-06-05
HIWING AVIATION GENERAL EQUIP
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In order to reduce the radar reflection cross section, there must be no gap between the engine nozzle and the skin. The traditional engine nozzle is difficult to achieve this. It is required that there must be a gap between the traditional engine nozzle and the aircraft skin; on the other hand, due to the requirements of engine disassembly and maintainability, the number of connection points between the engine and the body must be as small as possible, so that it is difficult to ensure the seamless requirement between the engine nozzle and the body skin

Method used

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  • Combined spray pipe structure and airplane with same
  • Combined spray pipe structure and airplane with same
  • Combined spray pipe structure and airplane with same

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Embodiment Construction

[0023] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

[0024] It should be noted that the terminology used here is only for describing specific implementations, and is not intended to limit t...

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Abstract

The invention discloses a combined spray pipe structure and an airplane with the same. The combined spray pipe structure comprises an engine spray pipe, a compensation spray pipe and a sealing assembly; the air outlet end of the engine spray pipe and the air inlet end of the compensation spray pipe are arranged in a spaced mode, and the air outlet end of the engine spray pipe and the air inlet endof the compensation spray pipe are detachably connected; the sealing assembly is used for sealing the joint of the air outlet end and the air inlet end, and the compensation spray pipe is further circumferentially attached and fixed to the inner wall of an aircraft skin. The combined spray pipe structure provided can solve the technical problem of contradiction between the requirements of axial heating elongation compensation of a traditional engine spray pipe and engine disassembly and maintenance on the structure and the requirements of aircraft backward stealth on the structure.

Description

technical field [0001] The invention relates to the technical field of aeroengine nozzle design, in particular to a combined nozzle structure and an aircraft with the same. Background technique [0002] Stealth aircraft and unconventional layout aircraft are developing rapidly in our country. Especially for stealth aircraft, the backward stealth requirement has always been a difficulty in the design of stealth aircraft. In order to reduce the radar reflection cross section, there must be no gap between the engine nozzle and the skin. The traditional engine nozzle is difficult to achieve this. It is required that there must be a gap between the traditional engine nozzle and the aircraft skin; on the other hand, due to the requirements of engine disassembly and maintainability, the number of connection points between the engine and the body must be as small as possible, so that it is difficult to ensure the seamless requirement between the engine nozzle and the body skin . ...

Claims

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Application Information

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IPC IPC(8): F02K1/80F02K1/82
CPCF02K1/805F02K1/82
Inventor 李轩孟范源于佰明杨晓亚张海征
Owner HIWING AVIATION GENERAL EQUIP
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