A scramjet engine based on detonation combustion

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 scramjet engine based on detonation combustion, and provides a design method for the realization of fuel injection mixing, thermal jet detonation of supersonic combustible gas and detonation dynamic stability control. Background technique [0002] The scramjet engine (Scramjet) has excellent performance under high Mach (Ma>5) flight conditions, and has become the preferred solution for the propulsion system of hypersonic aircraft. However, combined with the 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 engine is designed according to the Brayton isobaric combustion cycle, and its thermodynamic cycle efficiency is much lower than that of the detonation combustion of the approxim...

AI Technical Summary

Problems solved by technology

[0003] Scramjet engines have gradually moved towards engineering applications, but the conceptual design of scramjet engines based on detonation combustion has not yet been reported

Using the relatively mature engineering experience of scramjet engines, using detonation combustion to replace the isobaric combustion mode in the combustion chamber, compared with other types of detonation engines, the engine based on detonation combustion can be realized as soon as possible, but these studies are still in the theoretical stage. The stage does not consider the specific engine application implementation

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