Manufacturing method of thrust chamber pressure sandwich for liquid rocket engine

Abstract

The invention provides a manufacturing method of a pressure-resistant interlayer of a thrust chamber of a liquid rocket motor. The manufacturing method comprises the following steps that brazing filler metal electroplating is conducted on the surface of a rib of an inner wall at least; a half nickel shell is tightly pressed on the inner wall, wherein the inner surface of the half nickel shell is in close contact with the rib; the half nickel shell is located to be welded to the inner wall; the half nickel shell and the rib of the inner wall are welded together along the rib of the inner wall;multiple times of repeating welding are conducted on the half nickel shell and the rib of the inner wall along the rib of the inner wall according to the technology requirements; the outer surface ofthe half nickel shell after being welded is polished smoothly; and nickel layer electroforming or steel bushing wrapping and clamping is conducted on the surface of the half nickel shell. According tothe manufacturing method of the pressure-resistant interlayer of the thrust chamber of the liquid rocket motor, the degree of automation of thrust chamber body part machining can be remarkably improved, the bearing strength of the thrust chamber is improved, the quality is stabilized, and the cost is lowered.

Description

technical field [0001] The invention relates to the technical field of liquid rocket engines, in particular to a method for manufacturing a thrust chamber of a liquid rocket engine, in particular to a method for manufacturing a pressure-resistant interlayer of a thrust chamber of a liquid rocket engine. Background technique [0002] The body of the thrust chamber is the part responsible for the mixed combustion of fuel in the liquid rocket engine to generate high-temperature and high-pressure gas, which is then accelerated and discharged through the throat to obtain reverse thrust. In order to withstand the high temperature of the gas, the nozzle generally adopts regenerative cooling technology. A propellant flows through hundreds of tiny channels in the nozzle structure to take away the heat of the gas. It is composed of the inner wall and the outer wall of the milling groove. like figure 1 shown. [0003] Since the pressure of the coolant flowing in the cooling channel i...

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Problems solved by technology

[0013] In view of this, the technical problem to be solved by the present invention is to provide a method for manufacturing a pressure-resistant interlayer of a thrust chamber of a liquid rocket engine, which can solve the problems of high laser reflection and unstable welding during laser welding of existing copper alloys

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