摘要
根据导向叶片的曲面结构,运用剪应力输运方程(SST)湍流模型,在不同冷气入口压力条件下,对涡轮叶栅通道内部的三维流场和圆形气膜孔叶片型面的冷却效果进行了数值模拟.计算针对两种情形,即叶片内部有对流换热的情形和无对流换热的情形,结果表明随着冷气入口压力的增加,叶片有无内部对流换热的冷却效果也在增加;有内部对流换热的冷却效果较纯气膜冷却的高,尤其是在叶片前缘.
The film cooling effectiveness on the blade surface under different coolant entrance pressures was numerically investigated using the shear-stress transport （SST） twoequation turbulent model, so as to understand the influences of film-cooling holes on cooling effectiveness. Three-dimensional turbulent flow in the turbine cascade and the cooling effectiveness on the blade surface with cylindrical film cooling hole were simulated in two cases： with/without heat transfer in the blade. The results show that the cooling effectiveness increases with the increment of the coolant entrance total pressure, and the cooling effectiveness with heat transfer in the blade is better than that without heat transfer in the blade, especially in the leading edge region.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第9期1672-1677,共6页
Journal of Aerospace Power
关键词
涡轮叶片
涡轮叶栅
气膜冷却
数值计算
turbine blade
turbine cascade
film cooling
numerical computation
