隔热罩对火箭发动机推力室温度场的影响  

The Effect of Heat Shield on Temperature Distribution of Rocket Engine Thrust Chamber

作　　者：洪流[1] 石晓波[2] 张锋[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]西安航天动力研究所,陕西西安710100

出　　处：《上海航天》2009年第4期47-51,共5页Aerospace Shanghai

摘　　要：对某带隔热罩火箭发动机推力室的温度场进行了求解。所得结果与文献[1]的相关实验结果定性吻合。计算结果表明：加隔热罩后,推力室液膜冷却保护区壁温基本不变;气膜保护区壁温有一定幅度的上升,最大温升出现在喷管下游;壁温最高的喉部区域壁温上升幅度较小,仅为壁面平均辐射温度升的1/6-1/5。通过合理设计,可将壁面最高温度的升高幅度控制在10-20℃。The temperature field of a thruster chamber with heat shield was solved in this paper. The computed results were qualitatively in agreement with the corresponding experimental data published by reference 1. The results showed that the heat shield had little effect on the wall temperature of thrust chamber in the liquid film region. The wall temperature was high in the gas film region, especially in the downstream region of the nozzle, however, its increment at the throat region was very small, only about 1/6-1/5 of the mean value. With reasonable design, it was feasible to control the increment of the highest wall temperature to the range of 10-20 ℃.

关 键 词：液体火箭发动机 隔热罩 推力室 温度场 经验模型 机理模型 

分 类 号：V431[航空宇航科学与技术—航空宇航推进理论与工程]