A reversing valve of a liquid rocket engine and the liquid rocket engine

Abstract

The invention provides a reversing valve of a liquid rocket engine and the liquid rocket engine, which include an auxiliary shell, a main shell, a seal, a thrust assembly and a valve main body. The inside of the auxiliary housing has a first channel for the flow of gas medium and a second channel with a different extension direction from the first channel; the main housing has a first medium inlet, a first medium outlet and a second medium outlet; the seal is sleeved on the The surface of the thrust assembly and the outer surface of the seal are in contact with the inner wall of the auxiliary housing; one end of the thrust assembly is arranged in the auxiliary housing through the seal, and the other end is used to push the valve body located in the main housing to move; the seal It is a Varise ring, which includes a main body, an annular accommodation part and an elastic part, the elastic part is arranged in the annular accommodation part, and the inner wall of the annular accommodation part is provided with an annular protrusion for matching and abutting against the elastic part; the circumferential outer part of the main body The surface is provided with an annular recess. Compared with the prior art, the sealing effect can be improved and the loss of liquid medium can be reduced.

Description

technical field [0001] The invention relates to the technical field of valves, in particular to a reversing valve of a liquid rocket engine and a liquid rocket engine. Background technique [0002] With the rapid development of the aerospace industry, various technologies involved in the rocket field have also achieved rapid progress. Valves are an important part in realizing the startup and shutdown of liquid rocket engines. The medium of cryogenic liquid rocket engine is ultra-low temperature propellant, the medium temperature range is usually around 20K ~ 120K, and the pressure is above 10MPa. The valve operating gas is usually high-pressure gas with a pressure of about 20MPa. [0003] At present, in addition to liquid hydrogen and liquid oxygen, the liquid propellants used in current domestic low-temperature liquid rocket engines, some liquid rocket models under development in China also use liquid methane as propellant. In order to facilitate the use of the propellan...

AI Technical Summary

Problems solved by technology

However, the forming of large-sized metal bellows is difficult, the production cycle is long, the space structure is large, the purchase cost is high, the service life is low, and the reliability is poor, etc.

In addition, the design of the precious metal-coated sealing ring will cause excessive friction, which will affect the efficiency of the valve.

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