Method for preventing liquid rocket engine injector panel from being ablated by high-temperature fuel gas

Abstract

The invention discloses a method for preventing a liquid rocket engine injector panel from being ablated by high-temperature gas. The mixing ratio of engine fuel and an oxidant is rm, and the rm is more than or equal to 1.45. Part of the oxidant and the fuel are emitted from a oxidant nozzle of the outermost ring and a fuel nozzle respectively, the deflection angle of the oxidant nozzle of the outermost ring is alpha o, the alpha o is 45 degrees, the deflection angle of the fuel nozzle is alpha f, the alpha f is 40 degrees, two jet streams form high-temperature gas backflow after impacting below the injector panel, the high-temperature gas backflow is close to the inner wall of a combustion chamber, the combined momentum angle formed after the two jet streams are impacted is delta, and thecontrol value of the delta is 8-18 degrees. The method solves the problem of the edge region gas backflow ablates the injector panel caused by the fact that the combined momentum angle delta of the outermost ring of the injector panel of a liquid rocket engine in the prior art is too small. The method for preventing the liquid rocket engine injector panel from being ablated by the high-temperature gas is suitable for a wider working condition range, has strong applicability, can also be popularized to the design of dual-component liquid rocket engines in various thrust ranges, and has good technical expansibility.

Description

technical field [0001] The invention relates to a method for preventing a liquid rocket engine injector panel from being ablated by high-temperature gas, and belongs to the technical field of liquid rocket engine structures. Background technique [0002] Since the birth of the bicomponent liquid rocket engine, it has been developing towards high performance and high reliability, and the optimized design of the injector has played a key role in it. The direct current mutual impact injector is the most widely used injector for space liquid rocket engines in the world today. It has the characteristics of simple structure, high combustion performance, low processing difficulty, low cost, high reliability and good scalability. The design and control of synthetic momentum angle and mixing ratio are the most important in the design of the injector, which not only affects the performance of the product but also affects the reliability of the product. After the propellant is ejected...

AI Technical Summary

Problems solved by technology

[0010] The present invention aims to solve the problem of the gas backflow ablation injector panel in the side area caused by the outermost ring synthetic momentum angle δ of the liquid rocket engine injector panel of the prior art is too small, and further proposes a method to prevent liquid rocket engine injection The method that the panel of the device is ablated by high temperature gas

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