Binary plug nozzle and aircraft with binary plug nozzle

A plug-type nozzle and nozzle technology, which is applied in the direction of machines/engines, jet propulsion devices, etc., can solve problems such as temperature deformation, influence on nozzle function, and poor heat dissipation performance, and achieve low cost, simple structure, and heat reduction effect Good results

Active Publication Date: 2015-08-19
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] In the prior art, each component in the nozzle is usually a solid structure, its heat dissipation performance is poor, and it is easy to cause local deformation due to temperature, which affects the proper function of the nozzle

Method used

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  • Binary plug nozzle and aircraft with binary plug nozzle
  • Binary plug nozzle and aircraft with binary plug nozzle
  • Binary plug nozzle and aircraft with binary plug nozzle

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Embodiment Construction

[0023] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. 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 invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. 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. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses a binary plug nozzle and an aircraft with the binary plug nozzle. The binary plug nozzle comprises a first side wall panel, a second side wall panel, a first cone body, a second cone body, a first cam and a second cam, wherein the first side wall panel and the second side wall panel are in a hollow structure and used for arranging a cooling pipeline; the first cone body and the second cone body are in the hollow structure; the first cam and the second cam is in the hollow structure; the cooling pipeline is respectively arranged in the first side wall panel and the second side wall panel, one end of each pipeline is connected with a cooling air source, and the other end respectively extends into the hollow parts of the first cone body, the second cone body, the first cam and the second cam and used for accessing cooling gas into the first cone body, the second cone body, the first cam and the second cam. According to the binary plug nozzle, the cooling pipeline is respectively arranged in the first side wall panel and the second side wall panel and used for accessing the cooling gas to reduce temperature of all parts. The binary plug nozzle is simple in structure, low in cost and good in cooling effect.

Description

technical field [0001] The invention relates to the technical field of aero-engine nozzles, in particular to a binary plug nozzle and an aircraft with it. Background technique [0002] The rapid development of the space shuttle has led to a very wide range of the engine's working envelope, and the drop pressure ratio of the nozzle has reached tens or even hundreds. Due to the need to turn on the afterburner during the ascent, the state of the engine needs to change at any time. [0003] The nozzle is used as the injection device of the engine's high-temperature gas, and it usually needs to withstand extremely high temperatures. [0004] In the prior art, each component in the nozzle is usually a solid structure, and its heat dissipation performance is poor, and it is easy to cause local deformation due to temperature, which affects the proper function of the nozzle. [0005] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K1/06F02K1/78F02K1/15
Inventor 张少丽赵春生周吉利
Owner AECC SHENYANG ENGINE RES INST
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