Rocket engine valve

A rocket engine, valve technology

Active Publication Date: 2021-03-12
THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The seal specific pressure required by the design is large, and a large operating force or actuating chamber structure is required, and the leakage rate is larger than that of a soft seal.

Method used

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  • Rocket engine valve
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Embodiment Construction

[0035] In order to make the purpose, technical solution and advantages of the present application clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention. In addition, the technical features involved in the various embodiments of the present invention described below can be combined with each other as long as they do not constitute a conflict with each other.

[0036] like figure 1 As shown, the invention includes a valve body 1 , a valve stem 2 , a valve seat 3 , a valve core 4 , a first sealing device 5 and a second sealing device 6 . The valve body 1 includes an inlet 11 and an outlet 12, the inlet 11 is arranged on the side wall of the valve body 1, the outlet 12 is arranged at the bottom of the valve body 1, the valve seat 3 is arranged at the...

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PUM

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Abstract

The invention discloses a rocket engine valve, and relates to the technical field of spaceflight. The rocket engine valve comprises a valve body, a valve rod, a valve seat, a valve element, a first sealing device and a second sealing device. According to the rocket engine valve provided by the invention, 1, due to the fact that a plurality of through holes are arranged on the valve element, on onehand, the dead weight of a product is reduced, on the other hand, the total medium resultant force borne during closing is reduced, the size of an actuating device needed by the valve can be reduced,and weight reduction of a valve product is achieved. 2, the first sealing device is of an internal pressure self-tightening structure, so that medium pressure auxiliary sealing is realized, the actuating force required for ensuring reliable sealing in a closed state of the valve is further reduced, the weight of the valve product is reduced, and the sealing effect is further enhanced. 3, according to the rocket engine valve provided by the invention, the parts which are subjected to auxiliary sealing by utilizing the non-metal performance are stressed and not subjected to tensile force, so that the risk of falling off is avoided, and the product yield is high.

Description

technical field [0001] The present application relates to the field of aerospace technology, in particular to a rocket engine valve. Background technique [0002] With the vigorous development of commercial aerospace at home and abroad, low-cost cryogenic liquid rocket engines are currently a hot spot in research and development. At present, the propellants used in domestic low-temperature liquid rocket engines mainly include liquid hydrogen, liquid oxygen, and liquid methane. The temperature range of the medium is usually around 20K-120K, and the pressure is above 10MPa. [0003] The valve is an important executive part of the liquid rocket engine, which regulates and controls the fluid in the entire rocket engine system. There are two structural schemes for the valve core and seat of the active cryogenic liquid rocket engine valve: [0004] 1) The soft sealing structure of the valve core and valve seat. The valve seat is designed with an annular boss with a semicircular ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/58
CPCF02K9/58F02K9/566
Inventor 黄峰王小波肖凯王小雨方欢王涛峰张方陈巍周磊李健
Owner THE GENERAL DESIGNING INST OF HUBEI SPACE TECH ACAD
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