喷嘴结构对非壅塞式固冲发动机结构匹配性的影响  

Influence of injection nozzle configuration on configuration matching of unchoked ducted rocket

作　　者：刘佩进[1] 吕翔[1] 何国强[1] 田维平[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《推进技术》2005年第5期398-400,403,共4页Journal of Propulsion Technology

摘　　要：采用雷诺平均N-S方程和k-ε双方程湍流模型,研究了燃气发生器喷嘴构形对补燃效率的影响。通过一次流、二次流流线和燃烧效率分析,提出了一次流切入点的概念。结果表明:按照良好的燃气切入点设计燃气发生器喷嘴,不仅可以获得较高的燃烧效率,而且可以获得对补燃室热结构有利的温度场分布,实现固冲发动机的结构匹配性。Using RANS and k-ε turbulence model, the influence of fuel-rich injection nozzle configuration on the combustion efficiency of unchoked ducted rocket was studied. Based on the analysis of the streamline of primary, and secondary flow in secondary, combustion chamber, flow-in position concept was put forward. The results indicate that higher combustion efficiency was obtained if the primary injection nozzle was designed by the flow-in position method. Meanwhile, temperature field in this situation is in favor of thermal structure of secondary, combustion chamber. Configuration matching of ducted rocket engine will be achieved.

关 键 词：冲压火箭发动机 喷嘴 燃烧效率 数值仿真 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]