非壅塞固冲发动机补燃室内凝相颗粒运动规律研究  

Study on collision law of condensed particles in secondary combustor of unchoked solid ducted motor

作　　者：刘佩进[1] 李强[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2007年第1期17-20,共4页Journal of Solid Rocket Technology

基　　金：西工大英才计划资助项目

摘　　要：采用Euler-Lagrangian方法,基于O′Rouke提出的液滴碰撞和聚合模型,针对非壅塞固冲发动机补燃室内高温凝相液态金属颗粒的运动过程及颗粒间的碰撞和聚合过程开展了数值模拟,分析了喷嘴结构对凝相颗粒碰撞次数的影响。结果表明,一次喷口数目是碰撞次数的关键影响因素,从七孔喷嘴喷出的凝相颗粒之间的碰撞次数明显高于三孔喷嘴;喷口中心线与补燃室轴线的角度增加对碰撞有催进作用,但影响效果相对较小;在相同的一次喷嘴当量直径条件下,凝相颗粒的碰撞动量与喷嘴结构之间的关系不大。Based on O＇Rourke＇s droplet collision and coalescence model, moving process of condensed particles in secondary combustor of solid ducted rocket motor was numerically simulated by using Euler-Lagrangian method. The influence of injection nozzle configuration on collision number was analyzed. The results indicate that the number of primary nozzle orifice plays an important role for collision number of condensed particles, and collision number of condensed particles released from injection nozzle with seven ports is much more than that of three ports. The increase of the angle between centerline of nozzle orifice and axis of secondary combustor can promote collision number, but the effect is small. The collision momentum of condensed particles has little relation with the injection nozzle configuration under the same primary nozzle equivalent diameter.

关 键 词：非壅塞固体火箭冲压发动机 颗粒碰撞 喷嘴结构 数值模拟 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]