|Table of Contents|

Research on temperature field and heat deformation of mechanical seal in liquid rocket engine turbopump(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2014年05期
Page:
92-96
Research Field:
测控与试验
Publishing date:

Info

Title:
Research on temperature field and heat deformation of mechanical seal in liquid rocket engine turbopump
Author(s):
ZHANG Shu-qiang;  WANG Liang;  ZHAO Wei-gang
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
mechanical seal;  heat-transfer model;  temperature field;  heat deformation
PACS:
V434-34
DOI:
-
Abstract:
A two-dimensional steady-state heat-transfer model of mechanical seal in the liquid rocket engine turbopump was established based on ANSYS. The heat transfer coefficients of the model were determined according to the empirical formula. Based on the model, the temperature field and heat deformation of the sealing ring were calculated. The influences of specific pressure in seal face, cooling flow and different materials on the seal temperature distribution are analyzed. Simulation results show that the maximum temperature of the seal face appears near the inner of the seal ring and the temperature gradient increases with the increase in specific pressure; the heat deformation of the seal ring leads to a converged gap, and the maximum heat deformation occurs at the outer diameter of rotating seal ring, which is 2.2 μm; the maximum temperature decreases with an increase of the cooling flow, and the maximum temperature in the seal face decreases by 18% (from 100 ℃ to 82 ℃) when the cooling flow changes from zero to 0.6 kg/s; the maximum temperature reaches to a stable value, while the cooling flow increases to 0.3 kg/s. The sealing materials with high heat transfer coefficient can reduce the temperature rise and temperature gradient of the seal face dramatically, and improve the reliability of the seal.

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