涡轮叶片吸力面双排分区复合角气膜冷却特性
Film Cooling Performance on Suction Side of Turbine Blade With Two Rows of Subregional Compound Angle Holes
王晨枫 1李国庆 2刘浩 2李昂 2张燕峰 2卢新根2
作者信息
- 1. 江苏大学流体机械工程技术研究中心,镇江 212013;中国科学院工程热物理研究所,北京 100190;轻型涡轮动力全国重点实验室,北京 100190
- 2. 中国科学院工程热物理研究所,北京 100190;中国科学院大学航空宇航学院,北京 100190;轻型涡轮动力全国重点实验室,北京 100190
- 折叠
摘要
通道二次流作用下,涡轮叶片吸力面气膜轨迹呈收缩状从叶片两端朝叶中偏转.针对该问题,本文设计了高压涡轮叶片吸力面双排分区域复合角气膜冷却模型,并采用数值模拟的方法,分析了二次流和复合角对气膜冷却特性的影响.结果表明,在近端区,叶片上游孔排SS1形成的气膜受马蹄涡的作用偏转较小,叶片下游孔排SS2形成的气膜受较强通道涡的影响偏转角远大于上游气膜;在叶片吸力面增加朝向端壁的复合角设计,可以改善气膜覆盖的均匀性,复合角增大至30°左右时,可以消除射流的脱壁现象,最大复合角工况相比于简单角工况的展向平均气膜冷却效率提高了 13.9％.
Abstract
Under the function of passage secondary flow,the film track on the suction side de-flects from both ends to the middle of the blade.In order to solve this problem,a film cooling model with two row subregional compound angle holes for high pressure turbine blade suction sur-face is designed in this paper.The effects of secondary flow and compound angle on film cool-ing performance were analyzed by numerical simulation.The results show that in the root re-gion,the upstream films of SS1 are less deflected by the horseshoe vortex,but the downstream films of SS2 is much more deflected by the stronger passage vortex than the upstream films.The uniformity of film.coverage can be improved by adding subregional compound angle towards the endwall on the suction side.When the compound angle increases to about 30°,the detachment phenomenon of jet can be eliminated.Comparing with the simple Angle condition,the aver-aged spanwise film cooling effectiveness in the maximum compound angle condition is increased by 13.9％.
关键词
涡轮导叶/气膜冷却/通道二次流/分区域复合角/冷却效率Key words
turbine guide vane/film cooling/passage secondary flow/subregional compound angle/film cooling effectiveness引用本文复制引用
基金项目
国家自然科学基金(51976214)
国家科技重大专项(J2019-Ⅱ-0002-0022)
出版年
2024
NETL
NSTL
万方数据