Scramjet and active control method thereof for stable and self-sustained knocking

Abstract

The invention discloses a scramjet and an active control method thereof for stable and self-sustained knocking. A combustion chamber is included, a plurality of pressure sensors are arranged at equalintervals on the side wall of the upstream and midstream of the combustion chamber, and a current propagation position of a knocking wave is determined according to the pressure signals monitored by the corresponding pressure sensor; a plurality of suction holes are formed at equal intervals in the upper and lower side walls of the upstream and midstream of the combustion chamber, and the suctionholes communicate with pipelines in the wall of the combustion chamber and are connected with a suction pump through the pipelines; a current effective suction region is determined according to the real-time information of the propagation position of the knocking wave, the suction pump and electronic valves of each suction hole in the current effective suction region are opened, and the wall boundary suction is carried out in the effective suction region; and a concave cavity is formed in the lower side wall of the downstream of the combustion chamber. The wall boundary suction can suppress the pre-transmission of the knocking wave, the concave cavity can promote the knocking initiation and achieve the forward transmission of the knocking wave, and the two complement each other so that theknocking wave can achieve dynamic stable propagation.

Description

technical field [0001] The invention relates to the technical field of dynamic and stable propagation control of detonation under supersonic incoming flow conditions, in particular to a scramjet engine and an active control method for its detonation stability and self-sustainability. 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 combustio...

AI Technical Summary

Problems solved by technology

In these basic studies, a hot jet tube that independently supplies fuel and oxidant is used for hot jet injection and ignition and detonation, without considering the specific engine application.

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