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Liquid rocket engine combustion chamber forming method

A rocket engine and liquid rocket technology, which is applied in the field of mechanical equipment forming, can solve the problems of easy blockage of the inner wall cooling channel, complex equipment, poor fatigue, etc., and achieve the effect of avoiding low strength of the outer wall, good quality consistency, and high structural strength

Active Publication Date: 2020-01-07
湖北三江航天江北机械工程有限公司
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Problems solved by technology

[0003] The purpose of the present invention is to overcome the weak strength, long cycle, high cost, and poor fatigue of the existing electroforming outer wall technology of the combustion chamber, as well as the complex equipment of the vacuum brazing outer wall technology, high precision requirements for the complex surface of the outer wall, and the high precision of the inner wall. To solve the problem of easy blockage of cooling channels, provide a simple, fast and low-cost method for forming the combustion chamber of liquid rocket engines

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  • Liquid rocket engine combustion chamber forming method
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Embodiment Construction

[0019] Below in conjunction with accompanying drawing and specific embodiment the present invention is described in further detail:

[0020] The liquid rocket engine combustion chamber forming method designed by the present invention, such as figure 1 and 2 As shown, it includes the following steps:

[0021] Step 1: According to the requirements of the liquid rocket engine combustion chamber design drawings, the blank is processed into the shape of the liquid rocket engine combustion inner wall 1 by spinning method, and then the inner surface of the liquid rocket engine combustion inner wall 1 is processed, and then the liquid rocket engine combustion chamber is processed For the outer surface of wall 1, the processing deformation is strictly controlled during the processing. After the processing is completed, the surface roughness of the inner and outer surfaces of the liquid rocket engine combustion inner wall 1 is guaranteed to be less than or equal to Ra3.2; the inner and...

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Abstract

The invention relates to a liquid rocket engine combustion chamber forming method. The method comprises the following steps of 1 processing an inner wall; 2 forming an electroforming transition sealing layer, 3 processing the electroforming layer, 4 processing an outer wall, 5 performing sealing on the outer wall and the electroforming transition sealing layer and 6 welding accessories. The methodhas the advantages that the strength of the combined portions of the inner wall and the outer wall is good, and the quality consistency is good.

Description

technical field [0001] The invention relates to the technical field of mechanical equipment forming, in particular to a method for forming a combustion chamber of a liquid rocket engine. Background technique [0002] With the rapid development of commercial aerospace technology, the thrust requirements for liquid rocket engines are getting higher and higher. The development of liquid rocket engines in the direction of high thrust, high chamber pressure, short cycle, low cost, and reusability has put forward higher and higher requirements for high-efficiency and high-performance manufacturing processes for key structures such as combustion chambers. At present, the traditional combustion chamber adopts the method of milling the inner wall + electroforming nickel or brazing the outer wall. There are problems such as long cycle, high cost, poor reliability, low yield, and poor reusability. Contents of the invention [0003] The purpose of the present invention is to overcom...

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Application Information

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IPC IPC(8): B23P15/00
CPCB23P15/00B23P15/008
Inventor 徐海升卢启辉李毓磊朱云龙吴钦唐伟
Owner 湖北三江航天江北机械工程有限公司
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