| 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。 |
| 关键词: 冲压火箭发动机 喷嘴 燃烧效率 数值仿真 |
| DOI： |
| 分类号:V435; |
| 基金项目: |
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| Influence of injection nozzle configuration on configuration matching of unchoked ducted rocket |
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LIU Pei-jin,Lü Xiang,HE Guo-qiang,TIAN Wei-ping
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1.Coll.of Astronautics,Northwestern Polytechnical Univ.,Xi’an 710072,China;2.The 4th Academy of CASC,Xi’an 710025,China
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| Abstract: |
| 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. |
| Key words: Ducted rocket Injector Combustion efficiency Numerical simulation |
