Hydrogen peroxide thrust chamber and engine

Abstract

The invention discloses a hydrogen peroxide thrust chamber and an engine, and relates to the technical field of airspace engines, the hydrogen peroxide thrust chamber comprises a decomposer, a distribution flow equalizer, a gas-liquid injector and a combustor which are sequentially connected in a sealed mode in the preset direction, and the distribution flow equalizer is provided with a center area and an annular area surrounding the center area; a plurality of first vent holes are distributed in the central area at intervals, and a plurality of second vent holes are annularly distributed in the annular area at intervals; the gas-liquid injector is provided with a fuel channel, a combustion channel and a throttling channel, the throttling channel surrounds the combustion channel, and the fuel channel is communicated with the combustion channel; the combustor comprises a lining and a shell which are stacked together in a sleeved mode, a combustion inner cavity is formed in the lining, and a plurality of spiral channels distributed in the circumferential direction at intervals are formed between the lining and the shell. The multiple first vent holes, the combustion channel and the combustion inner cavity communicate in sequence, an annular cavity is formed between the annular area and the gas-liquid injector, and the annular cavity, the throttling channel and the multiple spiral channels communicate in sequence.

Description

technical field [0001] The present disclosure relates to the technical field of aerospace engines, and in particular, to a hydrogen peroxide thrust chamber and an engine. Background technique [0002] In the field of aerospace engines, cooling the thrust chamber of the engine is related to the safety of the engine. [0003] For the hydrogen peroxide thrust chamber with small thrust, medium and low chamber pressure, and fast response, due to its small thrust, low system pressure, and small flow rate for cooling, it is more technically difficult to achieve good cooling of the thrust chamber. [0004] The traditional hydrogen peroxide thrust chamber adopts liquid film cooling, but due to the high mixing ratio and small fuel flow rate of the hydrogen peroxide thrust chamber with medium and small thrust, the use of fuel liquid film cooling will greatly reduce the specific impulse performance, and the cooling hole processing is difficult ( That is, it is difficult to obtain cooli...

AI Technical Summary

Problems solved by technology

[0004] The traditional hydrogen peroxide thrust chamber adopts liquid film cooling, but due to the high mixing ratio and small fuel flow rate of the hydrogen peroxide thrust chamber with small and medium thrust, the use of fuel liquid film cooling will greatly reduce the specific impulse performance, and the cooling hole processing is difficult ( That is, it is difficult to obtain cooling holes with small inner diameters), poor uniformity control; and the method of hydrogen peroxide liquid film cooling also has the disadvantages of poor reusability, thermal decomposition explosion risk, and insufficient safety

Therefore, it is not suitable for hydrogen peroxide thrust chambers with small and medium thrusts

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