摘要
将单入口-双出口孔分别布置在叶片型面压力面和吸力面进行试验,研究了吹风比分别为1.0,1.5和2.0时,气膜孔下游气膜冷却特性。结果表明:吸力面吹风比为1.5时冷却效率最大,吹风比为1.0时冷却效率最小,沿流向冷却效率降幅随吹风比增加而减小;压力面冷却效率分布较为复杂,气膜孔出口附近吹风比为1.0时冷却效率最高,下游较远处吹风比为2.0时冷却效率最大,吹风比为1.0时冷却效率最小,沿流向不同吹风比下的冷却效率变化规律不同。
An experimental investigation was conducted to obtain the detailed film cooling efficiency distributions on both pressure side and suction side of turbine blade with a novel film hole injection. The blowing ratios of the coolant through the discrete holes are 0.5,1.0 and 2.0, respectively. Detailed film cooling efficiency distributions and spatially averaged film cooling efficiency were obtained. The results show that the film cooling efficiency at the pressure side and the suction side was different. The suction side had the high- est cooling efficiency at blowing ratio of 1.5. The increasing blowing ratio led to a much faster decrease in the spanwise averaged efficiency. The cooling efficiency distribution of the pressure side was complicated. The cooling efficiency at the hole exit reached the highest at blowing ratio of 1.0,while that at the down stream reached the highest at blowing ratio of 2.0 and the lowest at 1.0. The efficiency distributions were different with the various blowing ratios.
出处
《热力发电》
CAS
北大核心
2015年第5期17-21,29,共6页
Thermal Power Generation
基金
国家自然科学基金(51406124)
关键词
叶片型面
气膜冷却
双出口孔
吹风比
冷却效率
blade surface, film cooling, double outlet hole, blowing ration, cooling efficiency
作者简介
张魏（1980-），女，讲师，主要研究方向为燃气轮机气动热力学。E-mail：emma7691@163．com
