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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。
The flow field in a solid rocket motor with a submerged nozzle and a rectangular channel was measured by phase-doppler particle analyzer (PDPA). The effects of Reynolds number and cavity shape on the flow field in the dorsal wall influences. The results show that, with the increase of Reynolds number, the gas flow separation point moves downstream and the backflow velocity increases. The backflow velocity of back wall formed by oval backseat and rectilinear nozzle back wall is higher than that of round back head and step spray Tube back wall. For the large depth of the nozzle, the air flow in the combustion chamber wall separation, the back wall area to form a strong vortex; and into the depth of the nozzle, the separation point will be moved to the back head, the back of the back of the formation of weak vortex .