一种计算再生冷却推力室温度场的方法  

Method of Computing Temperature Field in Regeneratively-Cooled Thrust Chamber

作　　者：李军伟[1] 刘宇[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2004年第4期550-556,共7页Journal of Aerospace Power

基　　金：国家863-2高技术航天领域基金资助项目(863-2-3-4-10);高等学校博士学科点专项科研基金资助课题(2000000619)

摘　　要：为了能够快速而准确地得到再生冷却推力室的温度分布,建立了一种计算再生冷却推力室温度场的方法。首先建立了轴对称推力室的一维冷却模型,并使用换热经验公式,得到了推力室壁面在轴线方向上的温度分布;其次建立了推力室的冷却套二维导热模型,使用数值模拟的方法和一维计算的结果,得到了冷却套的温度场。然后使用这种方法研究了气壁材料、气壁厚度和冷却液流量对推力室再生冷却的影响,获得了比较满意的结果。从计算时间和准确性来说,这种方法能够为推力室的优化设计和性能估算提供参考。To quickly and accurately obtain temperature distribution in regeneratively-cooled thrust chamber, a method of computing temperature field in thrust chamber was developed. One-dimensional cooling model of axial symmetrical thrust chamber was formulated and empirical formulas were used. Temperature of gas wall along thrust chamber axis was obtained. Two-dimensional conductive model of cooling jacket was set up and numerical simulation was carried out using one-dimensional results. Temperature field in cooling jacket was computed. Using this method, the influences of gas wall material, gas wall thickness and flow rate of coolant on regenerative cooling of thrust chamber were investigated. In terms of computing time and accuracy of results, this method could provide a reference for optimization design and performance estimation.

关 键 词：航空、航天推进系统 液体推进剂火箭发动机 推力室 再生冷却 温度场 计算方法 

分 类 号：V434.14[航空宇航科学与技术—航空宇航推进理论与工程]