Efficient and stable combustion injector of medium and small thrust rocket engine

Abstract

The invention discloses an efficient and stable combustion injector for a medium and small thrust rocket engine. The efficient and stable combustion injector comprises an injection panel, centrifugal plasma nozzles and a high-voltage power supply, wherein the centrifugal plasma nozzles are uniformly distributed on the injection panel in a concentric circle mode, and the injection panel is an insulated single-layer injection panel or double-layer injection panel and can be well compatible with a plurality of plasma nozzles. The inner wall surface of the spraying end of an insulating outer nozzle is provided with a divergence angle alpha; an oxidant channel is arranged between an inner nozzle and the outer nozzle; the metal inner nozzle is grounded and has a retraction distance L; a metal ring sleeves the outer wall of the outer nozzle, is longer than L and is connected with a high-voltage power supply; and the atomization effect and the combustion efficiency can be adjusted by adjusting L and alpha. According to the efficient and stable combustion injector, the non-equilibrium plasma auxiliary combustion technology is combined with the design of the rocket engine injector, so that the effects of shortening the ignition delay of fuels such as methane, widening the ignition limit and rapidly diffusing flames to reach a stable state are achieved, and rapid ignition and efficient and stable combustion are realized.

Description

technical field [0001] The invention relates to the technical field of aerospace power devices, in particular to a high-efficiency and stable combustion injector for small and medium-thrust rocket engines. Background technique [0002] Hydrocarbon fuels represented by methane and kerosene have the advantages of green, non-toxic, high specific impulse, and abundant reserves, and are the first choice for future space propulsion devices. Among them, small and medium-thrust liquid oxygen / methane rocket engines are used as future vehicles and spacecraft The attitude and orbit control devices of the United States and Russia are getting more and more attention from space powers such as the United States and Russia. However, the harsh space environment and the need for future complex control tasks make the launch of small and medium-thrust liquid oxygen / methane rockets face many technical challenges such as reliable ignition in vacuum and low temperature, high-frequency pulse contin...

AI Technical Summary

Problems solved by technology

The traditional design process generally adopts the method of changing the structural parameters of the injector, but this method can only produce effects in limited working conditions. At the same time, because the spacecraft eng

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