Hydrogen-oxygen gas dynamic resonance surface igniter

Abstract

The invention discloses a hydrogen-oxygen gas dynamic resonance surface igniter, which belongs to the field of rocket engines. The hydrogen-oxygen gas dynamic resonance surface igniter consists of a hydrogen joint nozzle 1, an oxygen joint nozzle 2, a nozzle 3, a seal washer 4, a mixing cup 5, an ignition chamber 6, a resonating tube joint nozzle 7, a resonating tube spacer shim 8, a resonating tube 9 and an air joint nozzle 10, wherein the mixing cup is positioned between the nozzle and the ignition chamber and is provided with two rows of holes; the hydrogen and oxygen sprayed from the igniter nozzle pass through the mixing cup and then enter into the ignition chamber, thus being favor for blending and combusting; the resonating tube joint nozzle is positioned at the side face of the igniter, and the resonating tube joint nozzle is welded between the two rows of the holes of the mixing cup, thus being favor for igniting; the resonating tube stretches into the ignition chamber by means of the resonating tube joint nozzle, is fixed by screw threads between the air joint nozzle and the resonating tube joint nozzle, and can be sealed by utilizing the resonating tube spacer shim to regulate the depth of stretching into the ignition chamber of the resonating tube.

Description

【Technical field】 [0001] The invention relates to a gas-hydrogen / gas-oxygen dynamic resonance thermal surface igniter device. 【Background technique】 [0002] At present, the commonly used ignition methods of rocket engines include gunpowder ignition, high-energy electric spark, and self-igniting propellant ignition. The gunpowder ignition method is mature in technology, has the advantages of simple structure and reliable operation, and is widely used in various solid rocket and liquid rocket engines. And in the liquid rocket engine that adopts afterburning cycle, the solid particle that the gunpowder ignition mode produces can pollute the turbopump and the injector of the combustion chamber of the engine, is not an ideal ignition mode. The high-energy ignition method uses electric sparks to ignite the combustion chamber. Its main disadvantage is that it requires a large power supply, and the high-voltage circuit system has poor reliability under vacuum conditions, and it is...

AI Technical Summary

Problems solved by technology

In a liquid rocket engine that uses a post-combustion cycle, the solid particles produced by the gunpowder ignition method will pollute the turbo pump and the injector of the combustion chamber of the engine, which is not an ideal ignition method

The high-energy ignition method uses electric sparks to ignite the combustion chamber. Its main disadvantage is that it requires a large power supply, and the high-voltage circuit system has poor reliability under vacuum conditions, and it is difficult to overcome static and radio frequency interference. The instrument produces electrical interference, which makes it difficult to ignite the engine at high altitude

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