翼柱型药柱对发动机内流场及喷管收敛段烧蚀影响分析  

Effect of finocyl grain on internalflow field of SRM and nozzle convergence cone erosion

作　　者：李耿[1] 周为民[1] 张钢锤[1] 张光喜[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2010年第3期260-264,共5页Journal of Solid Rocket Technology

摘　　要：对具有翼柱型药柱结构的某固体火箭发动机内流场进行了三维两相流数值模拟,分析了发动机的内流场特征以及发动机工作过程中药型变化对内流场的影响,同时就翼柱型药柱结构对喷管收敛段绝热层烧蚀影响进行了分析。结果表明,发动机内流场呈现明显的周期对称特征,收敛段对应药柱翼槽部位的燃气速度及Al2O3粒子浓度明显高于周边位置;两相流中燃气速度及Al2O3粒子浓度的周期分布,导致喷管收敛段烧蚀也呈现周期分布的规律,对应于药柱翼槽部位收敛段绝热层烧蚀量明显大于非药柱翼槽对应部位的烧蚀量。Three-dimensional two-phase internal flow field in a solid rocket motor with finocyl grain structure was simulated.The flow characteristics and the effect of grain configuration change on internal flow during the motor working process were analyzed,and the effect of the finocy1 grain configuration on nozzle convergence cone insulation erosion was also investigated.The results show that the internal flow has a obvious characteristic of periodic symmetry distribution,and the combustion gas velocity and Al2O3 particle concentration in the grain fin slot corresponing to nozzle convergence cone are higher than that of peripheral position.The periodic distribution of combustion gas velocity and Al2O3 particle concentration result in the periodic distribution of the nozzle convergence cone erosion,and the erosion loss corresponing to fin slot is larger than that of other areas obviously.

关 键 词：固体火箭发动机 翼柱型药柱 两相流 烧蚀 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]