涡轮导叶压力面分区域复合角气膜冷却特性  

Multi region compound angle film cooling characteristics on pressure side of turbine guide vane

作　　者：张深 李国庆[1,2] 刘浩 康忠[1,3] 张燕峰 卢新根 ZHANG Shen;LI Guoqing;LIU Hao;KANG Zhong;ZHANG Yanfeng;LU Xingen(Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;School of Aeronautics and Astronautics,University of Chinese Academy of Sciences,Beijing 100049,China;School of Energy,Power and Mechanical Engineering,North China Electric Power University,Beijing 102206,China)

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学航空宇航学院,北京100049 [3]华北电力大学能源动力与机械工程学院,北京102206

出　　处：《航空动力学报》2024年第3期42-51,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(51976214);航空发动机及燃气轮机基础科学中心项目(2022-B-Ⅱ-006-004)。

摘　　要：针对通道二次流造成涡轮叶片压力面气膜轨迹发生偏转的现象,提出了沿展向分区域布置复合角的设计概念。以高压涡轮导叶HS1A为研究对象,采用数值模拟的方法,在出口雷诺数为2.3×10^(5)的工况下,分析了二次流、复合角和吹风比对气膜冷却特性的影响。结果表明:近端区二次流产生的径向潜流具有促进气膜展向覆盖的能力,相较于叶中区提高了气膜孔出口下游的冷却效率,但也会加剧射流和主流的掺混,减小气膜的有效覆盖长度;针对不同展向区域的二次流大小,精细化布置各区域的气膜孔复合角,可以将气膜轨迹的偏转角度全部修正为0°,同时将平均气膜冷却效率提升了10.42%;复合角冷却模型在吹风比为0.5~1.0时具有较好的范围适用性,吹风比增大至1.3时气膜轨迹会发生反向偏转。In view of the phenomenon that the secondary flow in the channel causes the deflection of the film trajectory on the pressure surface,the concept of multi region compound angle along the spanwise direction was proposed.Numerical simulation was conducted to investigate the film cooling characteristics of turbine guide vane HS1A.The influences of secondary flow,compound angle and blowing ratio on the film cooling characteristics were analyzed under the condition of turbine outlet Reynolds number of 2.3×10^(5).The results showed that the secondary flow in the near endwall had the ability to promote the spanwise coverage of the film,which improved the cooling effectiveness downstream the film hole outlet compared with the mid blade region,but also intensified the mixing of the jet and the mainstream,and reduced the effective coverage length of the film;according to the secondary flow in different spanwise regions,the film hole compound angle in each region was finely arranged,which can correct all the deflection angles of the film trajectory to 0°,and the average film cooling effectiveness was increased by 10.42%;the compound angle cooling model had good applicability within the range of blowing ratio of 0.5−1.0.When the blowing ratio increased to 1.3,the film trajectory could deflect reversely.

关 键 词：涡轮导叶 气膜冷却 通道二次流 分区域复合角 气膜冷却效率 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]