用于爆震引燃的激波聚焦无反应流场数值模拟  

Numerical investigations on cold flowfields of shock focussing for ignition of pulse detonation

作　　者：王春[1] 司徒明[2] 韩肇元[1] 

机构地区：[1]中国科技大学力学与机械系,安徽合肥230027 [2]航天科工集团公司31所,北京100074

出　　处：《推进技术》2003年第2期156-159,共4页Journal of Propulsion Technology

基　　金：航天支撑基金;科学院力学所LHD开放课题

摘　　要：通过对用于脉冲爆震引燃的内楔表面激波聚焦冷态流场的数值模拟,分析了不同角度内楔表面在激波聚焦时流场结构的不同特点。数值计算的结果表明:对于大内楔角的情况,激波进入内楔角之后产生规则反射,温度的大幅度升高发生在激波于内楔顶点反射之后;对于小内楔角的情况,激波进入内楔角之后产生马赫反射,温度的升高在入射激波到达内楔顶点之前就已经发生,而在入射激波于内楔顶点反射之后得到进一步的提升。同时,还对不同角度内楔的反射激波后气流温度进行了比较。The cold flowfield of shock focussing for ignition of pulse detonation was numerically investigated for different geometric structures. The results show that the flow fields of inner wedge with different angle have different features when applied to shock focussing. For the case of large-angle inner wedge, regular reflection was observed, and the temperature rising takes place just after the reflection of shock wave front. For the case of small-angle inner wedge, Mach reflection was observed, and the temperature has been raised before the reflection of shock wave front and been raised higher after the reflection of shock wave front. The temperatures after the reflection of shock wave front with different inner angles are also compared.

关 键 词：脉冲爆震发动机 激波聚焦 冷流 流动分布 数值仿真 

分 类 号：V235.221[航空宇航科学与技术—航空宇航推进理论与工程]