潜入喷管背部容腔对点火初期压强振荡影响的数值研究  

Numerical simulation of effect of submerged nozzle cavity on pressure oscillation during initial stage of ignition

作　　者：郜冶 胡伟 

机构地区：[1]哈尔滨工程大学航天工程系,哈尔滨150001

出　　处：《固体火箭技术》2011年第4期448-452,共5页Journal of Solid Rocket Technology

摘　　要：为深入了解点火初期药柱表面的压强振荡情况,采用计算流体力学软件FLUENT对固体火箭发动机喷管堵盖打开前的点火增压过程进行了轴对称数值计算,探讨了潜入喷管背部容腔对压强振荡的影响。计算结果表明,发动机头部和背部容腔内压强振荡最为剧烈,压强峰值和升压梯度峰值随容腔体积的增加而递减。结论可为药柱裂纹的扩展研究及固体火箭发动机的潜入喷管设计提供参考。To pursue a better insight into pressure oscillation at grain surface,the ignition pressurization process of SRM with submerged nozzle was simulated numerically before the opening of nozzle closure by using the CFD software FLUENT.The effect of cavity volume induced by submerged nozzle on pressure oscillation was studied.The results indicate that the pressure at the motor head and in the cavity oscillate most intensely,and the pressure peak and pressurization rate peak decrease with increasing the volume of cavity.Such a conclusion can be used as a reference for study of crack propagation and submerged nozzle design of solid rocket motor.

关 键 词：点火冲击波 潜入喷管 压强振荡 升压梯度 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]