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2.2μm;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。
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%(from100 ℃ 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.
出处
《火箭推进》
CAS
2014年第5期92-98,共7页
Journal of Rocket Propulsion
关键词
机械密封
传热模型
温度场
热载变形
mechanical seal
heat-transfer model
temperature field
heat deformation
