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Propellant-resistant double-channel sealing structure

A sealing structure and propellant technology, which is applied in the direction of sealing surface connection, connecting components, screws, etc., can solve problems such as easy leakage, impact on sealing, deformation of ball head bell mouth, etc., and achieve leak rate reliability and extremely low leak rate , the effect of easy installation

Inactive Publication Date: 2020-07-31
SHANGHAI AEROSPACE SYST ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the self-generating pressurization system of conventional liquid launch vehicles transports high-temperature and high-pressure propellant steam from the outlet of the engine evaporator to the storage tank. Sealing, high requirements for sealing surface processing, high requirements for surface roughness, unreliable sealing structure, prone to leakage, and the deformation of the bell mouth of the ball head after repeated disassembly and assembly will also affect the sealing

Method used

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Embodiment approach

[0037]In a preferred embodiment, the compression rate of the copper gasket 5 is 15%-25%. The copper gasket 5 is arranged in the second sealing groove 8 formed by the nozzle 1 and the pipe joint 2. The first end surface 10 of the pipe joint 2 is in contact with the copper gasket. One end surface of the piece 5 is in contact, and the second end surface 11 of the nozzle 1 is in contact with the other end surface of the copper gasket 5. During operation, the copper gasket 5 is compressed and embedded in the groove of the first section of the pipe joint 2 and the second end surface 11 of the nozzle 1 Inside, when the copper gasket 5 satisfies the compressibility in the above-mentioned range, a more reliable seal is formed.

[0038] Example of use: Use nozzle 1 and pipe joint 2 with a diameter of 30mm. The nozzle 1 and pipe joint 2 are made of 1Cr18Ni9Ti stainless steel, and butyl rubber and ethylene propylene rubber O-ring 4 with a small diameter of 1.8mm and a height of 1.5mm are u...

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Abstract

The invention discloses a propellant-resistant double-channel sealing structure. The sealing structure comprises a filler neck, a pipe joint, a cap nut, an O-shaped ring and a copper gasket. One end of the filler neck and one end of the pipe joint are fixedly connected with a propellant conveying guide pipe, the other end of the filler neck is matched with the other end of the pipe joint, a firstconical sealing groove and a second sealing groove are formed in a matched position, the O-shaped ring is arranged in the first conical sealing groove, and the copper gasket is arranged on the secondsealing groove. The cap nut sleeves the pipe joint and is fixedly connected with the filler neck to ensure axial force required by the copper gasket and the O-shaped ring. The structure is provided with the two sealing grooves, and the copper gasket and the O-shaped ring serve as sealing elements, so that the sealing structure is resistant to the high temperature of 350 DEG C, can be repeatedly used, has the high-low-temperature cycling capability, is simple in structure and low in assembling requirement, and meets the requirement for the sealing leakage rate.

Description

technical field [0001] The invention belongs to the sealing field of propellant pipelines in launch vehicles, and in particular relates to an axial double-channel sealing structure which is resistant to propellant steam and is suitable for missiles, rockets and space vehicles. Background technique [0002] At present, the self-generating pressurization system of conventional liquid launch vehicles transports high-temperature and high-pressure propellant steam from the outlet of the engine evaporator to the storage tank. Sealing, high requirements for sealing surface processing, high surface roughness, unreliable sealing structure, prone to leakage, and the deformation of the bell mouth of the ball head after repeated disassembly and assembly will also affect the sealing. [0003] Therefore, there is a need for a more reliable sealing structure that can meet the requirements of the sealing leakage rate. Contents of the invention [0004] The invention provides a propellant...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16L19/03F16L19/028F16B39/02
CPCF16B39/02F16L19/0218F16L19/0237F16L19/0283
Inventor 徐鹏里蒋赞马璎滕丰健缪五兵何鹏张浩冯淑红蓝越新竹
Owner SHANGHAI AEROSPACE SYST ENG INST
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