Thrust chamber and rocket engine

Abstract

The invention relates to the technical field of aerospace, in particular to a thrust chamber and a rocket engine. The thrust chamber comprises a thrust chamber head, a thrust chamber body and an injector. The thrust chamber body comprises a thrust chamber inner wall, a thrust chamber outer wall spaced from the thrust chamber inner wall, a cooling channel and a combustion cavity located in the thrust chamber inner wall. The injector is arranged at the end, close to the thrust chamber body, of the thrust chamber head and comprises an injector body, a fuel injection structure and an oxidizing agent injection structure, and the fuel injection structure and the oxidizing agent injection structure are arranged on the injector body and are independent of each other. The fuel injection structure comprises an edge injection structure arranged close to the thrust chamber inner wall and a middle injection structure arranged in the extending direction of the combustion cavity, and the oxidizing agent injection structure is adjacent to the middle injection structure. As the edge injection structure close to the thrust chamber inner wall injects fuel to a position close to the thrust chamber inner wall, no oxidizing agent is injected, a low-temperature protection layer can be formed at the position close to the thrust chamber inner wall, high-temperature fuel gas is prevented from directly acting on the thrust chamber inner wall, and damage is reduced.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a thrust chamber and a rocket engine. Background technique [0002] Rockets and space vehicles need the support of the power propulsion system during orbit change and attitude adjustment, and the rocket engine is the most critical component of the space propulsion power system. The thrust chamber is an important source of power for liquid rocket engines. Rocket engines need propellants to convert chemical energy into kinetic energy through the combustion process in the thrust chamber, thereby generating thrust to propel the rocket. [0003] The temperature inside the thrust chamber, especially the combustion chamber, will reach a very high value due to the chemical reaction of a large amount of fuel in a short period of time, usually in the range of 2000K-4000K. At this temperature, most common materials will be severely deformed or even melted. Destructive damage to rocket m...

AI Technical Summary

Problems solved by technology

[0003] The temperature inside the thrust chamber, especially the combustion chamber, will reach a very high value due to the chemical reaction of a large amount of fuel in a short period of time, usually in the range of 2000K-4000K. At this temperature, most common materials will be severely deformed or even melted. Destructive damage to rocket motor structure

In the prior art, the thrust chamber is mostly made of high-temperature resistant materials, and a reasonable cooling channel is provided between the outer wall and the inner wall of the thrust chamber body to enhance the heat dissipation effect of the thrust inner wall, but the temperature of the high-temperature gas produced by combustion is relatively high. high, it will still cause damage to the inner wall of the thrust chamber

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