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[1]张树强,王 良,赵伟刚.液体火箭发动机涡轮泵用机械密封温度场及热载变形研究[J].火箭推进,2014,40(05):92-96.
　ZHANG Shu-qiang,WANG Liang,ZHAO Wei-gang.Research on temperature field and heat deformation of mechanical seal in liquid rocket engine turbopump[J].Journal of Rocket Propulsion,2014,40(05):92-96.
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液体火箭发动机涡轮泵用机械密封温度场及热载变形研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 40 期数: 2014年05期 页码: 92-96 栏目: 测控与试验 出版日期: 2014-10-28
Title:
Research on temperature field and heat deformation of mechanical seal in liquid rocket engine turbopump
作者:
张树强; 王 良; 赵伟刚
西安航天动力研究所，陕西 西安 710100
Author(s):
ZHANG Shu-qiang;  WANG Liang;  ZHAO Wei-gang
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
机械密封; 传热模型; 温度场; 热载变形
Keywords:
mechanical seal;  heat-transfer model;  temperature field;  heat deformation
分类号:
V434-34
文献标志码:
A
摘要:
基于ANSYS数值计算软件，建立了液体火箭发动机涡轮泵用机械密封的二维稳态传热模型，依靠经验公式确定了模型的对流换热系数。计算了密封环的温度场和热载变形，分析了密封端面比压、回流流量以及不同材质对密封温度场的影响规律。结果表明：密封端面最高温度发生在靠近密封环内径处，且密封端面比压越大密封环温度梯度越大；密封环热载变形呈收敛间隙，最大变形发生在动环端面的外径处，其值约为2.2 μm；密封环端面最高温度随回流流量增加而减小，当回流流量从0.1~0.6 kg/s变化时，密封环端面最高温度可降低18%（从100 ℃降至82 ℃）；当回流流量增大到0.3 kg/s时，继续提高对密封环端面温升的控制不再显著；采用高导热系数的摩擦副材料能够显著降低端面温升和温度梯度，提高密封工作可靠性。
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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备注/Memo

收稿日期：2014-04-17；修回日期：2014-07-03 作者简介：张树强（1986—），男，硕士，研究领域为流体密封技术

更新日期/Last Update: 1900-01-01