摘要
燃气轮机叶片前缘处有很多高换热区,其中叶片前缘表面处是最先与高温燃气接触的位置,存在承受较高的热负荷的问题,目前较为常见的解决办法是气膜加冲击冷却。通过实验对比不同吹风比、不同曲率位置气膜冷却排孔的温度分布,得出以下结论:冷却效果以出气孔为起点向下游不断减弱,并且在不同的排孔处,下游减弱的趋势不同;当吹风比M<1时,吸力面气膜冷却有效度随吹风比的增加而逐渐增加;当吹风比M>1时,气膜冷却有效度随吹风比的增加而减小;下游曲率的增加可以有效地增加气膜冷却效果。
At the leading edge of the gas turbine blade,there are many high heat transfer zones,in which the leading edge surface of the blade is at the position where the blade is in contact with the high-temperature gas firstly and is subjected to a higher heat load. At present,the more common solution is the film cooling plus the impact of cooling. The following conclusions were obtained by comparing the temperature distributions of air-film cooling holes with different blowing ratios and different curvature positions. The cooling effect was weakened from the outlet to the downstream,and the trend of the downstream weakening was different at the different row of holes. When the blowing ratio was less than1,the effectiveness of the film cooling on the suction side increased with the increase of the blowing ratio. When the blowing ratio was more than 1,the film cooling effectiveness decreased with the increase of the blowing ratio. The increase of the downstream curvature could effectively increase the film cooling effect.
作者
卫国华
赵志军
吴艳芳
WEI Guo-hua;ZHAO Zhi-jun;WU Yan-fang(School of Energy and Power Engineering, University of Shanghai for Science and Technology Shanghai 200093, Chin)
出处
《能源工程》
2017年第6期28-31,共4页
Energy Engineering
关键词
燃气轮机
前缘表面
气膜冷却
吹风比
gas turbine
surface of gas turbine blades
film cooling
blowing ratio
