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本文以航空发动机涡轮转子叶片前缘为模型,对冲击孔形状分别为长圆形和圆形的两种结构进行数值模拟,并对长圆形冲击孔结构进行实验研究。得到了不同流动参数下的流阻系数、平均流量系数及两种结构冲击腔内壁面的平均努塞尔数。结果表明:1)流阻系数及平均流量系数受射流雷诺数的影响不大;2)从圆形冲击孔冲击到冲击腔内壁时的流体折转角更大,圆形冲击孔结构的流阻系数要大于长圆冲击孔结构;3)对于叶片前缘,相对于圆形,气流经过长圆形冲击孔冲击后,冲击腔内壁面的换热更均匀,换热效果也更好。
In this paper, the leading edge of aero-engine turbine rotor blade is taken as a model to simulate two kinds of structures, the shape of the impact hole being oval and round, respectively, and the structure of the oval hole is experimentally studied. The flow resistance coefficient, the average flow coefficient and the average Nusselt number of the impact wall of the two structures were obtained under different flow parameters. The results show that: 1) the coefficient of flow resistance and the average flow coefficient are not significantly affected by the Reynolds number of the jet; 2) the deflection angle of the fluid from the circular impact hole to the inner wall of the impact cavity is larger, Which is larger than the oblong impact hole structure; 3) For the leading edge of the blade, relative to the circular shape, after the impact of the air flow passes through the oblong impact hole, the heat exchange inside the impact cavity inner wall is more uniform and the heat exchange effect is better.