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对跨声速涡轮静子端壁气膜冷却进行了数值研究。研究发现涡轮静子端壁存在几个强换热区域:叶片前缘马蹄涡及前缘马蹄涡区域、吸力面马蹄涡分支覆盖区域、通道中靠近压力面侧和尾缘附近及尾缘后区域。针对端壁区域复杂的换热分布,设计了1种新型端壁全气膜冷却布置。通过数值研究对比了在不同进口吹风比情况下的壁面Nu、壁面气膜冷却效果和壁面热负荷。结果表明:存在最佳的进口吹风比,即在前缘Minlet=1.0时,尾缘Minlet=4.0时,端壁区域冷却效果最好。
The numerical study of film cooling at the transonic turbine stator endwall was carried out. It is found that there are several strong heat exchange zones in the turbine stator endwall: the leading edge of the horseshoe vortex and the leading edge of the horseshoe vortex, the suction surface of the horseshoe vortex, and the passage near the pressure side and near the trailing edge and the trailing edge. Aiming at the complicated heat transfer distribution in the endwall area, a new type of endwall air film cooling arrangement was designed. Numerical simulation is conducted to compare wall Nu, wall film cooling effect and wall heat load at different inlet blowing ratios. The results show that there is the best inlet blowing ratio, that is, when the leading edge Minlet = 1.0, the cooling effect of the end wall is best when the trailing edge Minlet = 4.0.