铣槽结构液体火箭发动机推力室壳体热应力分析  

Thermal stress analyses of liquid propellant thruster chamber wall with milled slots

作　　者：董飞[1] 何国强[1] 

机构地区：[1]西北工业大学,陕西西安710072

出　　处：《火箭推进》2007年第3期43-46,共4页Journal of Rocket Propulsion

摘　　要：介绍了液体火箭发动机推力室铣槽结构热应力的数值分析方法,通过建立液体火箭发动机推力室的流场燃烧和导热理论模型,运用有限体积法考虑液膜冷却计算出发动机工作时的燃气、燃烧室壳体和冷却工质的温度场,将得出的结果作为壳体热应力计算模型的边界条件进行热应力场有限元分析。内、外壁温度的计算数据与实验结果基本相符。The method of thermal stress analyses of the combustion chamber with milled slots of a liquid propellant engine is introduced. Through the estabilishing of therotic model of combustion and heat transfer of liquid rocket engine fluid field, temperature fields of the hot gas, chamber wall and coolant were calculated considering film cooling. The results of calculated temperatures of the inner and out wall of the chamber meet well with the former experiments data.

关 键 词：推力室 有限元法 有限体积法 热应力 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]