Machining method of dissimilar metal combustion chamber structure and combustion chamber

Abstract

The invention discloses a machining method of a dissimilar metal combustion chamber structure and a combustion chamber. The machining method comprises the following steps that a plurality of first open grooves are evenly formed in the circumferential inner surface of the outer wall of the combustion chamber, and a plurality of second open grooves are formed in the circumferential outer surface of the inner wall of the combustion chamber; the combustion chamber inner wall enters the interior of the combustion chamber outer wall from one end of the combustion chamber outer wall in the axial direction of the combustion chamber outer wall to reach a preset position, and the matching end faces of the combustion chamber inner wall and the combustion chamber outer wall are aligned; and the connecting part enters spaces formed by the first open grooves and the second open grooves from the outer sides of the combustion chamber outer wall and the combustion chamber inner wall, so that the two ends, in the radial direction of the combustion chamber outer wall, of the connecting part are clamped with the inner sides of the first open grooves and the second open grooves correspondingly, and the combustion chamber outer wall is connected to the combustion chamber inner wall. Accordingi to the machining method of the dissimilar metal combustion chamber structure and the combustion chamber, the combustion chamber machining method is reasonable in design and convenient to operate, the welding requirement for the dissimilar metal is lowered, the whole combustion chamber is stable in structure, and the production efficiency can be improved.

Description

technical field [0001] The invention relates to the field of liquid rockets, in particular to a method for processing a combustion chamber structure of dissimilar metals and the combustion chamber. Background technique [0002] The spacecraft engine technology has been rapidly upgraded with the development of the aerospace industry. As the main components of the engine, the combustion chamber and heat exchanger of the liquid rocket engine are the key components to complete the energy conversion of the propellant and generate thrust. The combustion chamber and the heat exchanger are respectively composed of an inner wall and an outer wall. Usually, the inner wall with grooves needs to be connected with the outer wall for pressure bearing and medium circulation through the grooves. [0003] When the inner wall is connected to the outer wall, in order to take into account factors such as heat conduction, strength, and weight, the design of the combustion chamber usually adopts...

AI Technical Summary

Problems solved by technology

Due to the severe corrosion of copper and titanium at high temperature, the weldability between some titanium alloys (such as TA15, TC4, etc.) is poor, which increases the difficulty of welding the inner wall and outer wall and affects the production efficiency of the combustion chamber.

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