摘要
为了提高凹槽叶顶的气膜冷却效率,提出了一种凹槽带肋叶顶结构。通过数值模拟方法,研究了叶顶结构在不同吹风比、滑移壁面条件下冷却气体在凹槽腔内的流动状态和气膜冷却效率分布,揭示了凹槽带肋叶顶改善叶顶气膜冷却效率机理。结果表明:吹风比为0.5时,气膜孔附近冷却效率最高;吹风比为1.5时,凹槽内吸力面附近冷却效率最高;肋片导流作用使冷气更大范围地覆盖在凹槽内,提高了平均冷却效率,这种效应在吹风比为0.5时更明显。
To enhance the cooling effectiveness of gas film on top of groove blade, a structure of groove blade with fins was proposed. The flow status and gas film cooling effectiveness distribution of cooling gas inside the groove were numerically simulated, under conditions with different blowing ratios and end wall slippage situations. The cooling effectiveness enhancement mechanism of the fins structure was revealed. The results show that, the highest cooling effectiveness appears near the film hole and the suction side at blowing ratio of 0. 5 and 1.5, respectively. The flow guidance effect the fins improves the film coverage, resulting in an increase in the average film cooling ef- fectiveness on the s（luealer tip, especially at blowing ratio of 0.5.
作者
李广超
张占东
张魏
寇志海
赵国昌
LI Guangchao ZHANG Zhandong ZHANG Wei KOU Zhihai ZHAO Guochang(Liaoning Key Lab of Advanced Measurement and Test Technology for Aviation Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University Shenyang 110136, China)
出处
《热力发电》
CAS
北大核心
2016年第10期23-28,共6页
Thermal Power Generation
基金
国家自然科学基金项目(51306126
51406124)
辽宁省自然科学基金项目(2015020112)
关键词
涡轮叶片
凹槽带肋叶顶
滑移壁面
压力面
吸力面
冷却效率
吹风比
turbine blade, squealer tip with fins, end wall slippage, pressure side, suction side, film coolingeffectiveness, blowing ratio
