Confluence rocket ramjet wide-speed-range engine based on annular pressurization center body mixing section

A center body and engine technology, applied in ramjet engines, combined engines, mechanical equipment, etc., can solve the problems of insufficient engine ramming effect, low engine thrust performance, and low engine thrust-to-weight ratio.

Active Publication Date: 2021-04-20
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Conventional ramjet engines rely solely on the effect of air ramjet, so when the flight speed is low, the ramjet effect of the engine is not enough, and the thrust performance of the engine is low
The conventional rocket ramjet engine needs a long mixing section, so the engine weight is relatively large, and the thrust-to-weight ratio of the engine is low. At a high Mach number, the excessive length of the mixing section greatly affects the overall performance of the engine

Method used

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  • Confluence rocket ramjet wide-speed-range engine based on annular pressurization center body mixing section

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Embodiment Construction

[0031] specific implementation plan

[0032] 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 part of the embodiments of the present invention, not all of them. 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.

[0033] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relationship between the components in a certain posture (as shown in the accompanying drawings). Relative positional relationship, movement conditions, etc., if the specific posture changes, the directional indication will also change a...

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Abstract

The invention discloses a confluence rocket ramjet wide-speed-range engine based on an annular pressurization center body mixing section. The confluence rocket ramjet wide-speed-range engine based on the annular pressurization center body mixing section comprises a center body, an air inlet channel, a combustion chamber with a concave cavity and a spray pipe. An embedded rocket in a conventional rocket ramjet engine is arranged on the outer side of the center body in a front-arranged mode, mixed pressurization of the rocket gas and air is conducted in an annular mixing channel, and then central pipe flow is formed through confluence. Due to the fact that the contact area of rocket jet flow and air is increased, the mixing distance of two air flows can be effectively shortened. By the adoption of the scheme, the overall thrust performance of the rocket ramjet engine can be effectively improved.

Description

technical field [0001] The invention relates to the technical field of engines, in particular to a rocket ramjet wide-speed range engine that can work reliably at a wide flight Mach number. Background technique [0002] The speed range of the engine is an important design index of the engine. A wide speed range means a wider application range of the engine. The larger the flight envelope range, the more practical the engine and the wider the application prospect. Conventional ramjet engines rely solely on the effect of air ramjet, so when the flight speed is low, the ramjet effect of the engine is not enough, and the thrust performance of the engine is low. Conventional rocket ramjet engines require a long mixing section, so the weight of the engine is relatively large, and the thrust-to-weight ratio of the engine is low. When the Mach number is high, the length of the mixing section that is too long greatly affects the overall performance of the engine. Contents of the in...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K7/18
Inventor 顾瑞孙明波蔡尊李佩波姚轶智
Owner NAT UNIV OF DEFENSE TECH
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