Combustion chamber structure and liquid rocket engine

Abstract

The invention discloses a dissimilar metal combustion chamber structure and a combustion chamber. The dissimilar metal combustion chamber structure comprises a combustion chamber outer wall, a combustion chamber inner wall and connecting parts for fixing the combustion chamber outer wall and the combustion chamber inner wall, the two ends of the combustion chamber outer wall communicate, the interior of the combustion chamber outer wall is provided with a flow channel, the two ends of the combustion chamber inner wall communicate, and the interior of the combustion chamber inner wall is provided with a flow channel; and positions, between the combustion chamber inner wall and the combustion chamber outer wall, of the connecting parts form convex ribs between the combustion chamber inner wall and the combustion chamber outer wall. The combustion chamber outer wall is located at the outer side of the combustion chamber inner wall, a plurality of first open grooves are evenly formed in the circumferential inner surface of the combustion chamber outer wall, and a plurality of second open grooves matched with the first open grooves are formed in the circumferential outer surface of the combustion chamber inner wall. The two ends, in the radial direction of the combustion chamber outer wall, of the connecting parts are tightly attached to the inner walls of the first open grooves and the second open grooves so that the combustion chamber outer wall can be connected with the combustion chamber inner wall. Cooling channels for liquid and / or gas media to circulate are formed at the position, between the combustion chamber inner wall and the combustion chamber outer wall, between the adjacent connecting parts. The structure is reasonable in design and convenient to operate.

Description

Technical field [0001] The present invention relates to the field of liquid rockets, and more particularly to a combustion chamber structure and a liquid rocket engine. Background technique [0002] Spacecraft engine technology has quickly upgraded with the development of the aerospace industry. As the main components of the engine, the combustion chamber of the liquid rocket engine, the heat exchanger is a key component that performs the energy conversion of the propellant and generates a thrust. In the combustion chamber, the heat exchanger is composed of the inner wall, the outer wall, and is generally necessary to connect the inner wall with the groove to the outer wall, and perform the pressure of the medium through the groove. [0003] When the inner wall is connected to the outer wall, in order to combat heat conduction, strength, weight and other factors, in the combustion chamber design, the inner wall is usually used to be copper-outer walls of steel, titanium and other...

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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