膨胀循环推力室再生冷却换热的数值模拟  

Heat transfer characteristics of expander cycle thrust chamber

作　　者：韩非[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》2007年第11期1939-1946,共8页Journal of Aerospace Power

摘　　要：为了解液体火箭发动机膨胀循环推力室再生冷却换热特性,采用数值模拟方法,研究了冷却剂流动方式、推力室圆柱段长度、圆柱段室壁加肋和气壁面粗糙度等因素对冷却通道压降、冷却剂温升、壁面热流密度和温度分布等换热特性的影响.计算过程中采用k-ε双方程湍流模型.计算结果表明:采取顺流冷却要比逆流冷却的冷却通道压降低,但同时冷却剂温升也低;对于室壁加肋结构,在肋个数相同而只改变肋高度的情况下,总换热量正比于总换热面积.In order to understand the heat transfer characteristics of expander cycle regeneratively-cooled thrust chamber, three dimensional computational models of expander cycle thrust chamber were established and numerical simulation was employed. The influence of a number of factors, such as increased length of chamber cylinder, different cooling routing, different surface roughness and rib configurations on the heat transfer characteristics like coolant heat pick-up, pressure loss in the cooling circuit, wall temperature and heat flux distribution was investigated, k-ε turbulence model was adopted for the computation. The results show that the co-flow cooling routing contributes to lower pressure loss in cooling circuit but yet lower coolant heat pick-up, when comparing with converse cooling routing. The compared results of the two uncooled ribs with different rib heights demonstrate that the increase of the heat flux is proportional to the increase of the total surface area exposed to hot gas.

关 键 词：航空 航天推进系统 液体推进剂火箭发动机 膨胀循环 推力室 再生冷却 数值模拟 换热 壁面粗糙度 

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]