Liquid-film cooled thrust chamber for rail posture control engine

Abstract

The invention discloses a liquid-film cooled thrust chamber for a rail posture control engine. A first propellant chamber is arranged on the outer side of the head of the thrust chamber, and a secondpropellant chamber is arranged on the outer side of the middle position of the body of the thrust chamber. A plurality of first spray holes communicating with the first propellant chamber are formed in the shell wall of the head of the thrust chamber. A plurality of combustion jet holes and a plurality of liquid film jet holes are evenly formed in the shell wall of the body of the thrust chamber in the circumferential direction. A second propellant is sprayed to the head and the throat of the thrust chamber through the combustion jet holes and the multiple liquid film jet holes respectively, aliquid film is sprayed towards the throat of the thrust chamber, and a tangential liquid feeding mode is adopted, so that loss of the liquid film can be reduced. The cooling performance of the liquidfilm is given full play to. In addition, the combustion jet holes face the head of the thrust chamber, a tangential liquid feeding mode is adopted, the cooling performance of the liquid film can be achieved, meanwhile, the liquid film can react with the first propellant, therefore the proportion of the liquid film in the propellant can be reduced, and whole-body cooling of the thrust chamber is achieved.

Description

technical field [0001] The invention relates to an engine thrust chamber, in particular to a liquid film cooling rail attitude control engine thrust chamber. Background technique [0002] The improvement of the specific impulse performance of the orbit attitude control engine can effectively prolong the working life of the spacecraft or increase the quality of the payload, which can bring very significant economic and military benefits. The main factors restricting the improvement of the specific impulse performance of the orbit attitude control engine are: high-performance injector technology, high-temperature resistant material technology and inefficient use of liquid film. Among them, the inefficient use of liquid film has become the primary restrictive factor leading to the reduction of engine specific impulse. [0003] In traditional orbital attitude control engines, there are two ways of liquid film cooling: [0004] One is that the propellant is sprayed to the wall ...

AI Technical Summary

Problems solved by technology

[0010] In order to solve the problem in the background technology that the proportion of liquid film in the thrust chamber of the existing orbital attitude control engine remains high, resulting in a decrease in the specific impulse performance of the engine, the present invention provides a liquid film cooling orbital attitude control engine thrust chamber

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