Self-forcing cooling high-temperature resisting mechanical sealing device

Abstract

The invention relates to a self-forcing cooling high-temperature resisting mechanical sealing device. A movable ring, a static ring seat and a heat insulation ring of the sealing device are mounted ona rotating shaft in a sleeving mode; a flow guiding groove is formed in the movable ring; an annular shell is mounted on the heat insulation ring and the static ring seat in a sleeving mode, one sideof the annular shell and the heat insulation ring are fixed and sealed, a liquid medium annular inlet is formed by the inner wall of the other side of the annular shell and the surface of the outer circle of the static ring seat, an annular membrane piece group is mounted on the heat insulation ring in a sleeving mode, a gap is formed between the annular membrane piece group and the outer ring wall of the heat insulation ring, and the outer edges of the two sides of the annular membrane piece group and the static ring seat as well as the heat insulation ring are subjected to full-length welding in the circumferential direction, so that a cavity is formed between the annular shell and the annular membrane piece group; a small hole communicating with the cavity is formed in the outer wall of the annular shell; and a cooling channel is formed by the liquid medium annular inlet, the cavity and the small hole. The problems that unstable work, leakage of a sealing face and even sealing failure of mechanical seal occur due to the fact that vaporization appears on a liquid medium are solved by arranging the flow guiding groove and the cooling channel.

Description

technical field [0001] The invention relates to the technical field of sealing, in particular to a self-forced cooling high temperature resistant mechanical sealing device. Background technique [0002] The turbopump assembly in the prior art is the core component of the liquid rocket engine propellant supply system, which mainly realizes the pressurization of the incoming medium, and delivers the propellant to the combustion chamber according to the flow and pressure required by the design, usually in the liquid rocket engine turbopump A set of mechanical sealing device is arranged on the rotating shaft between the pump inlet and the turbine, the purpose is to realize a small amount or no propellant leakage of the propellant medium into the turbine cavity. [0003] When the existing mechanical seal device works, the maximum PV value is close to 60MPa.m / s, so there will be the following problems: [0004] 1. The temperature of the end surface of the mechanical seal friction...

AI Technical Summary

Problems solved by technology

[0004] 1. The temperature of the end surface of the mechanical seal friction pair rises rapidly, and the friction pair appears dry grinding, thermal cracking, deformation and other phenomena

[0005] 2. The temperature of the turbine cavity is as high as 650-800°C. The existing mechanical seal device has no auxiliary cooling function and can only rely on its own ability to dissipate heat. The liquid medium around the friction pair will vaporize, resulting in unstable operation of the mechanical seal, leakage of the sealing surface or even Seal failure and other issues

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