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An external air bleed device based on the cooling of a hypersonic aircraft nozzle

A technology for nozzle cooling and aircraft body, applied to jet propulsion devices, machines/engines, etc., can solve the problems affecting the performance of other components, difficult to ensure the amount of bleed air, etc., and achieve the effect of increasing the Mach number

Active Publication Date: 2022-07-15
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The air film cooling method can achieve a good cooling effect. However, air film cooling requires a certain pressure and needs to be bleed from the air inlet and other devices. It is difficult to ensure the amount of bleed air, and it will affect the performance of other components; liquid film cooling needs to carry additional cooling media, etc. Reasons limit its use

Method used

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  • An external air bleed device based on the cooling of a hypersonic aircraft nozzle
  • An external air bleed device based on the cooling of a hypersonic aircraft nozzle
  • An external air bleed device based on the cooling of a hypersonic aircraft nozzle

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Embodiment Construction

[0014] In order to make the objectives, technical solutions and advantages of the implementation of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to be used to explain the present application, but should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present...

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Abstract

The application belongs to the technical field of hypersonic aircraft design, and particularly relates to an external air bleed device based on the cooling of a hypersonic aircraft nozzle. A lower web is arranged on the lower wall of the aircraft body to form a cooling passage with the aircraft body. The front end of the cooling passage is an air inlet, the rear end is an exhaust port, and an air intake compression throat is arranged at the air inlet. The lower wall of the body forms the upper wall of the intake compression throat, the lower web forms the lower wall of the air bleed device of the intake compression throat at the front end, the upper wall of the exhaust port is the outer wall of the nozzle, and the lower wall of the exhaust port is formed by the lower abdomen. The rear end of the board is constructed. The external air bleed device provided by the present application can provide high-pressure and low-temperature gas through an intake compression pipeline, and the introduced gas passes through the outer wall of the high-temperature nozzle, on the one hand, the nozzle is cooled to protect the nozzle, and on the other hand, the gas is heated High temperature gas is generated and exhausted, and the Mach number of the exhaust is increased to generate exhaust thrust.

Description

technical field [0001] The application belongs to the technical field of hypersonic aircraft design, and particularly relates to an external air bleed device based on the cooling of a hypersonic aircraft nozzle. Background technique [0002] The nozzle is a necessary exhaust system for the aircraft propulsion device, and it is the main part of the aircraft to ensure the normal operation of the engine. At the same time, because the nozzle is connected to the rear of the high temperature and high pressure combustion chamber, its working environment is quite harsh, and the nozzle can be reused. The tube generally adopts high temperature alloy and regenerative cooling method to cool the nozzle, and the disposable nozzle generally adopts carbon carbon material of ablation material. Due to cost requirements and repeated use of aircraft, active cooling is generally adopted to reduce the temperature of the nozzle wall and ensure the life of the nozzle. And with the increase of flig...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K1/82
CPCF02K1/822F02K1/82
Inventor 王俊伟朱伟刘艳金凤新
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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