固体火箭发动机斜切喷管两相流场特性数值模拟研究  

Simulation Research on Two-phase Flow Characteristics in Angle-cut Nozzle of Solid Rocket Motor

作　　者：温雄飞 赵瑜 马新建 赵志 孟浩 WEN Xiongfei;ZHAO Yu;MA Xinjian;ZHAO Zhi;MENG Hao(Shanghai Space Propulsion Technology Research Institute,Shanghai 201109,China)

机构地区：[1]上海航天动力技术研究所,上海201109

出　　处：《弹箭与制导学报》2023年第2期72-79,共8页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对固体火箭发动机斜切喷管两相流问题,运用Realizable k-ε湍流模型和颗粒轨道模型,采用单元内颗粒源法进行三维两相耦合计算,对斜切喷管内两相流场特性及气相与颗粒相的相互作用规律进行研究,并分析颗粒在Rosin-Rammler分布下直径大小对斜切喷管两相流场特性及推力的影响。分析结果表明:颗粒相的存在导致喷管轴线附近存在一个燃气温度较高、流动速度较低的区域,且斜切部分壁面附近存在无颗粒区。随着粒径增大,颗粒运动越集中于轴线附近且轨迹比较平直,无颗粒区域越大,同时发动机喷管轴线处气相速度先增大后减小,燃气温度先减小后增大;且颗粒直径越大,此温度和速度变化越小。两相流状态下计算的斜切喷管推力大于纯气相推力,且随着颗粒直径的增加,推力减小。Focus on the problem of the two-phase flow in angle-cut nozzle of solid rocket motor,the particle trajectory model and Realizable k-εturbulence model are applied to calculate the three-dimensional two phase flow coupling by using the particle source method in the computational unit.The characteristic of two-phase flow in angle-cut nozzle and the interaction between gas phase and particles is researched.The effect of particle diameter on the two-phase flow characteristic and thrust is also analyzed based on the Rosin-Rammler particle size distribution.The results show that the existence of particle phase leads to a region with high temperature and low flow velocity of gas near the nozzle axis,and a region without particles near the wall of the angle-cut section.With the increase of particle diameter,particles are concentrated near the axis and the trajectory is straight,and the region without particles is larger.At the same time,the gas phase velocity increases first and then decreases along the nozzle axis,the gas temperature decreases first and then increases.And the larger the particle diameter,the smaller are temperature and velocity change.In the two-phase flow state,the thrust of the angle-cut nozzle is larger than the gas phase thrust.And with the increase of particle diameter,the thrust decreases.

关 键 词：固体火箭发动机 斜切喷管 两相流 数值模拟 推力 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]