Combined mechanical seal device

Abstract

The invention particularly relates to a combined mechanical seal device which comprises a moving ring, a static ring assembly, a static ring housing, a floating ring assembly and an O-shaped rubber ring. The static ring assembly is arranged in the static ring housing and comprises an end face block assembly, a rotation-preventing pin, a spring and a damping belt. The end face block assembly comprises a static ring, a static ring seat, a film box assembly and a rear ring which are arranged in sequence. The damping belt is located in an annular groove of the inner surface of the static ring housing. The floating ring assembly comprises a floating ring, a cover plate and a floating ring housing, wherein the floating ring penetrates through a rotor to be arranged in the floating ring housing, and a cover plate penetrates through a rotor to be fixedly arranged on two sides of the floating ring housing respectively. A cooling backflow channel comprises a bearing axial gap, a gap between the moving ring and a pressing ring, a static ring seat balance hole gap, a radial gap between a static ring seat and the static ring housing, a backflow channel I, an accumulated liquid cavity and a backflow channel II which are communicated in sequence. The combined mechanical seal device achieves long-service-life, low-friction and zero-leakage work of a mechanical seal under the working conditions of high temperature and high pressure.

Description

technical field [0001] The invention relates to the technical field of sealing, in particular to a combined mechanical sealing device, which can be used in turbo pumps of liquid rocket engines, in the fields of sealing devices in ships and nuclear industries, and in rotating devices that must ensure sealing and have narrow dimensions and spaces. Background technique [0002] The liquid rocket engine is the main power system of the rocket. The room temperature liquid rocket engine uses dinitrogen tetroxide as a common propellant. Because the propellant that provides thrust has the characteristics of high saturated vapor pressure, strong oxidation, easy vaporization of the medium, and poor cooling and lubrication performance, High-temperature gas (temperature 650℃~750℃) directly acts on the seal, causing vaporization of the medium in the sealing gap and deformation of the seal, making the sealing surface prone to dry friction and leakage, resulting in the occurrence of dinitrog...

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problems that the existing mechanical seals are prone to leakage, unable to meet the requirements of high speed, high pressure, large vibration, multiple starts and long-time working conditions of the turbo pump, and cannot ensure the reliability of high sealing, the present invention provides a A Combined Mechanical Seal Device Applicable to Liquid Rocket Engine

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