Liquid oxygen methane thrust chamber injector

Abstract

The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector, so as to solve the problem that in the current working process of the liquid oxygen methane injector, since both liquid oxygen and methane belong to liquid low-temperature propellants, the The structure of the DC shear nozzle or the impact injector will lead to the poor mixing effect of the propellant in the thrust chamber injector and the problem of insufficient combustion efficiency. A liquid oxygen methane thrust chamber injector includes a plurality of injection units, a midsole, and a top cover, a flow guide and an inner bottom that are coaxially arranged on the midsole in sequence; the plurality of injection units are fixed in the midsole. On the bottom, the deflector and the inner bottom; a liquid oxygen cavity is formed between the top cover, the middle bottom and multiple injection units, and a methane cavity is formed between the mid bottom, inner bottom and multiple injection units; multiple injection units All nozzles with indented chambers are used, and the nozzles include central area nozzles, main combustion area nozzles, and edge area nozzles.

Description

technical field [0001] The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector. Background technique [0002] Oxygen and methane are natural resources with abundant reserves, and methane is a widely used hydrocarbon fuel with low price, abundant reserves and no pollution. As a liquid rocket engine propellant combination, the specific impulse of the combination of liquid oxygen and methane is between that of liquid oxygen and liquid hydrogen. Compared with kerosene, liquid methane has better cooling performance, its coking temperature is higher than that of kerosene, and its combustion products have less carbon deposits, so it has greater advantages as a coolant. Compared with liquid oxygen and liquid hydrogen, methane is a low-temperature propellant, but its low price and high density can effectively reduce the launch cost of rockets. Therefore, the combination of liquid oxygen and methane propellants has broad ap...

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Problems solved by technology

[0005] The present invention proposes a liquid oxygen methane thrust chamber injector, the purpose of which is to solve the problem of using direct current shear nozzles or impact spray nozzles during the working process of the liquid oxygen methane injector because both liquid oxygen and methane belong to liquid low-temperature propellants. The structure of the injector will lead to poor propellant mixing effect and insufficient combustion efficiency of the thrust chamber injector, which is difficult to meet the technical problems of the existing injector design requirements for high efficiency and stable combustion

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