Flexible compensation connection structure of asymmetric spray pipe 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 time-consuming, labor-intensive and cost-increasing, and achieve the effect of simple structure, easy implementation and practical engineering requirements.

Active Publication Date: 2019-12-13
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Description
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  • Application Information

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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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  • Flexible compensation connection structure of asymmetric spray pipe 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 invention belongs to the technical field of aircraft system design and particularly relates to a flexible compensation connection structure of an asymmetric spray pipe and an engine. The structurecomprises a convergent extension section and an L-shaped retaining ring; the convergent extension section is provided with a first end and a second end, the first end of the convergent extension section is connected to an outlet end of the engine, and the convergent extension section converges from the first end to the second end away from the outlet end of the engine; the L-shaped retaining ringis provided with a first end and a second end, the first end of the L-shaped retaining ring is connected to an inlet end of an exhaust pipe, and the convergent extension section is sleeved with the L-shaped retaining ring; and the second end of the L-shaped retaining ring and the second end of the convergent extension section cross each other in an axial direction, and a gap is formed in a radialdirection. According to the flexible compensation connection structure of the asymmetric spray pipe and the engine, a soft connection between the asymmetric spray pipe and an engine body during testand installation is realized, excessive non-axial force and bending moment on the spray pipe are prevented from being transmitted to an engine structure, the structure is simple, realization is easy,and actual engineering requirements are met.

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 Applications(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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