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A Flexible Compensation Connection Structure Between Asymmetric Nozzle and Engine

A technology for connecting structures and engines, applied in the directions of machines/engines, jet propulsion devices, etc., can solve the problems of increased cost, time-consuming and laborious, and achieve the effect of easy implementation, simple structure, and practical engineering requirements.

Active Publication Date: 2022-05-06
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, the above two methods have the disadvantage of time-consuming and labor-intensive increase of cost.

Method used

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  • A Flexible Compensation Connection Structure Between Asymmetric Nozzle and Engine

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Embodiment Construction

[0023] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with th...

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Abstract

The application belongs to the technical field of aircraft system design, and in particular relates to a flexible compensation connection structure between an asymmetrical nozzle and an engine. Includes: convergent extension and L-ring. The convergent extension has a first end and a second end, the first end of the convergent extension is connected to the engine outlet, and the convergent extension extends from the first end to the second end away from the engine outlet. end convergence; the L-shaped retaining ring has a first end and a second end, the first end of the L-shaped retaining ring is connected to the inlet end of the exhaust pipe, and the L-shaped retaining ring is sleeved on the convergent extension Outside, the second end of the L-shaped retaining ring and the second end of the converging extension section cross each other in the axial direction, and there is a gap in the radial direction. This application realizes the soft connection between the asymmetrical nozzle test and the engine body during installation, avoiding the transmission of excessive non-axial force and bending moment on the nozzle to the engine structure, the structure is simple, easy to implement, and can meet the requirements of actual engineering Require.

Description

technical field [0001] The application belongs to the technical field of aircraft system design, and in particular relates to a flexible compensation connection structure between an asymmetrical nozzle and an engine. Background technique [0002] For turbojet or turbofan engines equipped on aircraft, the nozzles are delivered together with the engine as an important part of the engine body, and the structure of the nozzles is basically axisymmetric. Under normal working conditions, all parts of the engine, including the nozzle, are mainly affected by axisymmetric forces. However, based on certain specific requirements or limited by installation conditions, it is necessary to design the nozzle into a special shape (non-axisymmetric curved configuration). The working state of the asymmetric nozzle is impacted by high-temperature and high-speed gas, and a large bending moment is generated on the connecting flange surface between it and the engine, which easily deforms or even ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/80
CPCF02K1/80
Inventor 吴宇周红任恒英
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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