摘要
在涡轮叶栅端壁21%、51%、81%轴向弦长处和距前缘9%轴向弦长端壁处布置4排圆柱形气膜冷却孔,运用CFD方法模拟吹风比、轴向倾角α和展向倾角β3个影响因素共同作用下的端壁平均气膜冷却效率,通过正交方案选出最优孔排布置方式.结果表明:吹风比对端壁平均气膜冷却效率的影响最大,展向倾角β影响次之,轴向倾角α影响最小;吹风比为2.0,轴向倾角α为30°,展向倾角β为45°(第1、第3排冷却孔与y轴负方向成45°,第2、第4排冷却孔与y轴正方向成45°)布置时,端壁表面平均气膜冷却效率最高,为3个因素影响下的最优方案.
Four rows of cylindrical film cooling holes were cut on the turbine cascade endwall,respectively in the regions of 21%,51% and 81% axial chord length,and in the 9% upstream region of leading edge.The endwall film cooling effectiveness was analyzed using CFD method under different conditions of blowing ratio,axial angle and radial angle,based on which optimal arrangement of above cooling holes was obtained via orthogonal algorithm.Results show that the blowing ratio has greatest influence on the cooling effectiveness,followed by radial angle and axial angle;highest cooling effectiveness may be reached when the blowing ratio is 2.0,axial angle is 30°and radial angle is 45°(the first and third rows of cooling hole form a 45°angle to the negative direction of axis y,while the second and fourth rows of hole form a45°angle to the positive direction of axis y),which is seemed as the optimum scheme under combined action of above three factors.
出处
《动力工程学报》
CAS
CSCD
北大核心
2015年第2期119-125,共7页
Journal of Chinese Society of Power Engineering
基金
吉林省科技发展计划资助项目(20130101046JC)
关键词
涡轮端壁
气膜冷却
复合角度
气膜冷却效率
正交方案
turbine endwall
film cooling
compound angle
film cooling efficiency
orthogonal simulation
