Scramjet engine based on detonation combustion

A technology of scramjet and detonation combustion, which is applied in ramjet engines, mechanical equipment, etc., can solve the problems of not considering the application of engines, and the conceptual design of new scramjet engines has not been reported, so as to ensure detonation Detonation and control function, improving fuel premixing efficiency, increasing the effect of fuel premixing distance and time

Active Publication Date: 2017-08-22
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0003] The scramjet engine has gradually moved towards engineering applications, but the conceptual design of a new scramjet engine based on detonation combustion has not yet been reported
Using the relatively mature engineering experience of scramjet engines, using detonation combustion to replace the

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  • Scramjet engine based on detonation combustion
  • Scramjet engine based on detonation combustion
  • Scramjet engine based on detonation combustion

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Embodiment Construction

[0024] In order to make the objectives, technical solutions and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0025] The invention provides a scramjet based on knocking combustion. In a new scramjet based on knocking combustion, the compression of supersonic air flow, fuel injection, and mixing with compressed air can be realized in the combustion chamber. The thermal jet's detonation initiation and the dynamic and stable control of detonation combustion, so as to finally achieve stable thrust performance. The invention is mainly designed from the engine's intake port structure, fuel injection structure, detonation structure and combustion chamber dynamic control structure.

[0026] Reference figure 1 , This embodiment includes an intake port 1 and a combustion chamber 2. For the intake port, the isobaric combustion in the combustion chamber of the tra...

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Abstract

A scramjet engine based on detonation combustion comprises an air inlet channel and a combustion chamber. The air inlet channel of the engine is designed in a one-time linear compression mode. The upstream wall surface of the air inlet channel is provided with fuel injection holes. A detonation device is arranged behind the combustion chamber of the engine and comprises a hot jet oxidation agent pipeline and a hot jet device carrying with jet fuel. An inlet of the hot jet oxidation agent pipeline is formed in the upper stream of the air inlet channel and located above all the fuel injection holes. An outlet of the hot jet oxidation agent pipeline is connected with the hot jet device and conducts mixed ignition with the fuel carried in the hot jet device, and hot jet is generated. Compared with a traditional scramjet engine, the novel scramjet engine based on detonation combustion is simplified in structure and high in thermodynamic cycle efficiency and energy release rate, and by testing, the thrust performance of the engine based on detonation combustion can be 30% or above higher than that of an existing engine based on isobaric combustion.

Description

Technical field [0001] The invention relates to a super-combustion ramjet based on knock combustion, and provides a design method for the realization of fuel injection mixing, supersonic hot jet detonation of combustible gas, and detonation dynamic stability control. Background technique [0002] Scramjet (Scramjet) at high Mach (Ma> 5) Excellent performance under flight conditions, and has become the first choice for hypersonic aircraft propulsion systems. However, combined with current research and the US X-51A flight test, it can be known that the acceleration performance of the scramjet demonstrator is not obvious, and the net thrust is relatively small. Therefore, based on current research, there is an urgent need to improve engine thrust performance. The scramjet is designed according to the Brayton isobaric combustion cycle, and its thermodynamic cycle efficiency is much lower than the knock combustion of the approximate constant volume cycle. Therefore, if knock comb...

Claims

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Application Information

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IPC IPC(8): F02K7/10
CPCF02K7/10
Inventor 蔡晓东梁剑寒林志勇刘世杰陈伟强
Owner NAT UNIV OF DEFENSE TECH
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