固体火箭发动机射流中存在障碍物时的流场分析  

Flow field analysis on solid rocket motor with barrier in the jet-flow

作　　者：冯喜平[1] 赵胜海[1] 李进贤[1] 唐金兰[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》2009年第4期396-399,429,共5页Journal of Propulsion Technology

摘　　要：基于N-S控制方程和RNGk-ε湍流模型,采用FLUENT软件对某固体火箭发动机存在球形障碍物的射流流场进行了数值模拟,得到了球形障碍物尺寸及距离喷管出口位置对射流流场的影响规律。计算结果表明,当障碍物处于第一个膨胀压缩过程之后与第二个膨胀压缩波过程之前的特殊位置时,它对整个射流火焰宽度的影响最为显著,该计算结果与某次发动机试车失败时所观测的现象相符。Based on N-S control equations and RNG k-ε turbulence model,using the FLUENT software,the jet flow field of certain solid rocket motor where a spherical barrier exists was simulated.The effect of the barrier size and distance from nozzle exit on the jet flow field was obtained.The results show that when the barrier is between the first expansion-compression process and the second one,its effect on jet flame width is remarkable.The calculated results match the motor abortive test results well.

关 键 词：固体火箭发动机 射流 流场仿真 障碍物 数值仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]