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A rocket engine valve

A rocket engine and valve technology, applied in the aerospace field, can solve the problems of large leakage rate, high sealing specific pressure, etc., and achieve the effect of reducing size, increasing sealing specific pressure, and simple product process

Active Publication Date: 2022-04-29
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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  • A rocket engine valve
  • A rocket engine valve
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Embodiment Construction

[0035] In order to make the objectives, technical solutions and advantages of the present application clearer, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention, but 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 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 outl...

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Abstract

The application discloses a rocket engine valve, which relates to the field of aerospace technology, and comprises: a valve body, a valve stem, a valve seat, a valve core, a first sealing device and a second sealing device. 1. The rocket engine valve provided by this application has several through holes on the valve core, which reduces the self-weight of the product on the one hand, and on the other hand reduces the total resultant force of the medium when it is closed, which can reduce the valve required The size of the actuating device can reduce the weight of valve products. 2. Since the first sealing device is an internal pressure self-tightening structure, medium pressure auxiliary sealing is realized, which further reduces the operating force required to ensure reliable sealing when the valve is closed, realizes weight reduction of the valve product, and further enhances the sealing effect. 3. In the rocket engine valve provided by this application, the non-metallic properties of the auxiliary sealing parts are under pressure but not tension, so that there is no risk of falling off, 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 the current research hotspot. At present, the propellants used in domestic low-temperature liquid rocket engines mainly include liquid hydrogen, liquid oxygen and liquid methane. The medium temperature range is usually around 20K ~ 120K, and the pressure is above 10MPa. [0003] Valve is an important executive component of liquid rocket engine, regulating and controlling fluid in the whole rocket engine system. There are two structural solutions for the valve core and valve seat of the active cryogenic liquid rocket engine: [0004] 1) The valve core and valve seat have a soft sealing structure. The valve seat is designed with an annular boss with a semi-circular cross-section. Material, the non...

Claims

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Application Information

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Patent Type & Authority Patents(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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