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 the NS control equation and the RNGk-ε turbulence model, the jet flow field of a solid rocket motor with a spherical obstacle was numerically simulated by FLUENT software, and the influence of the spherical obstacle size and nozzle exit position on the jet flow field was obtained law. The calculation results show that when the obstacle is in the special place after the first expansion compression process and before the second expansion compression wave process, it has the most significant impact on the entire jet flame width. The observed phenomenon is consistent.