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为了研究复合角度的圆形气膜孔对涡轮叶片冷却效果和气动性能的影响,利用SST的k-ω模型对涡轮叶栅进行数值模拟,对前缘区域冷却孔进行复合角度优化设计,给出前缘滞止线附近和吸力面改型前后的冷却特性分析。结果表明圆形气膜孔的复合角度对冷却和气动的影响明显,在前缘压力面,侧向角分别为85°,60°和45°,冷气在前缘处改变滞止点的位置,切向速度增大,冷却效果显著增强。在前缘吸力面上,冷却孔的入射角从45°变为30°,侧向角由-15°改为0°和30°,冷气与主流掺混减弱,壁面冷却效率增大,同时影响近壁面的主流从而改变流场结构。
In order to study the effect of circular film hole with complex angle on the cooling effect and aerodynamic performance of turbine blade, the turbine cascade was simulated by using k-ω model of SST, and the composite angle of the cooling hole in the leading edge was optimized. Analysis of cooling characteristics around the edge of stagnant line and before and after modification of suction surface. The results show that the composite angle of circular film hole has significant effect on cooling and aerodynamics. In the front pressure surface, the lateral angles are 85 °, 60 ° and 45 °, respectively. The cold air changes the position of stagnation point at the leading edge, Tangential speed increases, the cooling effect is significantly enhanced. On the suction side of the leading edge, the incident angle of the cooling hole changes from 45 ° to 30 °, the lateral angle changes from -15 ° to 0 ° and 30 °, the cold air mixes with the mainstream weakens, and the wall cooling efficiency increases while the influence Near the wall of the mainstream and thus change the flow field structure.