利用FLUENT的用户自定义函数定义固体推进剂燃面的边界移动和燃面的质量添加,考虑压力和流速对侵蚀效应的影响,对内孔燃烧固体火箭发动机的瞬态内流场进行了研究。采用标准k-ɛ湍流模型,隐式耦合算法计算了喷管和燃烧室一体化内流场。得到了内弹道各参数随时间变化和空间分布情况、装药动态燃烧过程,以及侵蚀效应对发动机燃烧室压力分布和固体火箭发动机工作过程的影响。

Based on the FLUENT user defined function dealing with the boundary moving and mass-flow-inlet in the buring surface of propellant, considering the pressure and flow velocity on the erosion effect, the transient internal flowfield in a bore-burning solid rocket motor was studied. The integrational chamber-nozzle internal flowfield was simulated using standard k -e turbulence model and implicit coupling algorithm. The ballistic parameters changes with time and space distribution, dynamic burning process, and the erosion effect on the pressure distribution and working process in a solid rocket motor were obtained.