潜入喷管背壁区流场影响因素实验研究

Effects of Reynolds number and aft-end cavity configuration on aft-end SRM internal flow field

应用相位多普勒粒子分析仪 (PDPA)对含潜入喷管、通道为矩形的固体火箭发动机冷流模型内流场进行测量 ,研究了雷诺数和背壁空腔形状对背壁区流场的影响。结果表明 ,随着雷诺数增大气流分离点向下游移动 ,回流速度增大 ,椭圆形后封头、直线形喷管背壁构成的背壁区回流速度比圆形后封头、台阶形喷管背壁大。对于潜入深度大的喷管 ,气流在燃烧室壁面分离 ,背壁区形成强旋涡 ;而潜入深度小的喷管 ,分离点会后移至后封头上 ,在背壁区后部形成弱旋涡。

Internal flow field in a cold flow model of solid rocket motor with rectangular channel and submerged nozzle was measured using phase doppler particle analyzer (PDPA) The effects of Reynolds number and aft end cavity configuration on aft end flow field were studied It is showed that the separation point of the flow moves downstream and recirculation velocity increases with Reynolds number increasing Recirculation velocity of the aft end cavity with ellipse aft dome and line back surface is higher than that with round aft dome and sidestep back surface For large submergence, the flow separates at combustion channel and a strong vortex forms in the aft end cavity However, for little submergence the flow separates at aft dome and a weak vortex forms in the rear of the cavity