气膜孔形状对导叶冷却效果影响的数值研究  

Numerical study of cooling effectiveness of different film cooling holes on stator blade

作　　者：姚玉[1] 张靖周[1] 郭文[2] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]中国燃气涡轮研究院,成都610500

出　　处：《航空动力学报》2008年第9期1666-1671,共6页Journal of Aerospace Power

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,针对簸箕形、锥形和缝形气膜孔的流场和冷却特性同圆形气膜孔进行了对比研究.研究结果为:随着冷气入口压力的增加,各种冷却结构的冷却效果也在增加;而在相同的冷气入口压力条件下,各种形状气膜孔的冷却流量和冷却效果不尽相同,在该研究条件下,簸箕形和缝形气膜孔的冷却效果最好,锥形孔次之.The flow field and film cooling characteristics on the blade surface were numerically investigated using the shear-stress transport （SST） two-equation turbulent model, so as to understand the influences of film-cooling holes on cooling effectiveness. The flow and cooling effectiveness for four configurations of film cooling holes were compared. Results show that the cooling effectiveness for each film cooling hole increases with the increment of the coolant entrance total pressure. Under the same coolant entrance total pressure, the cooling effectiveness of the dustpan and slot film cooling holes are the best, followed by that of the taper film cooling hole.

关 键 词：涡轮叶片 气膜冷却 数值计算 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]