Manufacturing method of liquid-propellant rocket engine combustion chamber

Abstract

The invention discloses a manufacturing method of a liquid-propellant rocket engine combustion chamber. The manufacturing method includes the following steps that the inner wall front sealing end face, the inner wall rear sealing end face and the inner wall outer molded surface are finely finished, and fine finish allowances are reserved on the inner wall front sealing end face, the inner wall rear sealing end face and the inner wall outer molded surface; the outer wall front sealing end face, the outer wall rear sealing end face and the outer wall inner molded surface are finely finished; fine finish allowances are reserved on the outer wall front sealing end face, the outer wall rear sealing end face and the outer wall inner molded surface; the inner wall and the outer wall are pre-treated; the inner wall which is dried and dehydrated is sleeved with the inner side of the outer wall, and then connection treatment is conducted; defect detection, fine finish, a water pressure test for strength and cleaning and airing treatment are conducted on the combustion chamber. As is proved by practice, the manufacturing method is simple in operation and high in machining efficiency, diffusion connection can be finished in one day, and efficiency is improved by more than ten times compared with that of a traditional electroforming process and a traditional brazing process.

Description

technical field [0001] The invention relates to an aerospace vehicle power device, in particular to a method for manufacturing a combustion chamber of a liquid rocket engine. Background technique [0002] The liquid rocket engine is the power plant of the aerospace vehicle, which is composed of the main parts such as the injector, the combustion chamber and the tail nozzle. The combustion chamber is the combustion place of oxygen and fuel gas, and is an important part of the liquid rocket engine system. The two ends are respectively connected with the injector and the tail nozzle. At present, the liquid rocket engine combustion chamber is composed of a copper alloy inner wall with good thermal conductivity and a stainless steel outer wall with good high-temperature strength. Its structure is like an hourglass-shaped cavity, see the attached figure 1 As shown, many ultra-low temperature liquid fuel self-circulation cooling passages are processed on the outer surface of the i...

AI Technical Summary

Problems solved by technology

The electroforming process of the liquid rocket engine combustion chamber is to electroplate nickel on the outer surface of the inner wall of the copper alloy to protect the cooling tank surface that does not need nickel plating, but the processing technology of the electroforming process is complicated, and the electroforming process is 0.02 to 0.05 per hour. mm, cast to a certain thickness and then flatten the surface and then plate, the electroforming cycle is as long as 6 months, and the cost is high

The brazing process of the liquid rocket engine combustion chamber is to lay copper brazing material on the ribs of the cooling groove on the outer surface of the inner wall of the copper alloy. After heating, the brazing material melts to weld the inner and outer walls. The welding strength is low, and the processing accuracy of the parts is high. Complex process and poor reliability

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