含潜入喷管发动机尾部流场冷流模拟  

Cold gas simulation on aft-end internal flow for solid rocket motor with submerged nozzle

作　　者：韩新波[1] 陈步学[1] 蔡体敏[1] 冯希顺 

机构地区：[1]西北工业大学航天工程学院,陕西西安710072

出　　处：《推进技术》2000年第3期34-37,共4页Journal of Propulsion Technology

摘　　要：为了揭示含潜入喷管的固体火箭发动机尾部流动特征 ,按照几何相近和气动相似原则设计了通道为矩形的二维冷流实验模型 ,利用相位多普勒粒子分析仪 (PDPA)对燃烧室尾部气流的时均速度和湍流脉动速度进行了测量。实验结果表明气流在潜入喷管入口上游发生分离 ,再附点位于喷管前端部外侧 ,背壁空腔内形成一个较为稳定的回流区 。To reveal aft end internal flow feature of a solid rocket motor with submerged nozzle, a two dimension cold flow test model with rectangular channel was designed The cold gas simulation was based on geometric similarity and aerodynamic analogy Mean and fluctuating velocity field was measured using phase doppler particle analyzer (PDPA) It showed that the flow separates at upstream of the submerged nozzle and reattaches on the tip of the nozzle nose A relatively steady recirculation zone formed in the aft end cavity Both axial component and radial component of turbulence intensity were quite high

关 键 词：固体推进剂火箭发动机 潜入式喷管 尾流 冷流 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]