冷气流量比对三维涡轮导叶全气膜冷却效率的影响  

Effects of Coolant Flow Rate Ratio on the Full Film Cooling Characteristics of Three-dimensional Turbine Guide Vane

作　　者：付仲议 李益民 黄琦 朱惠人[3] FU Zhong-yi;LI Yi-min;HUAGN Qi;ZHU Hui-ren(Hunan Aviation Powerplant Research Institute,Aero Engine(Group)Corporation of China,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Medium and Small Aero-Engine,Zhuzhou 412002,China;School of Power and Energy,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]中国航空发动机集团有限公司湖南动力机械研究所,株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,株洲412002 [3]西北工业大学动力与能源学院,西安710072

出　　处：《汽轮机技术》2024年第2期107-112,共6页Turbine Technology

基　　金：湖南省自然科学基金资助项目(2021JJ40646)。

摘　　要：为了研究不同主流湍流度下冷气质量流量比对三维涡轮导叶全气膜冷却特性的影响,使用热色液晶测量了在主流湍流度为1%和15%,流量比为5.5%、8.4%和12.5%下三维涡轮导叶的全气膜冷却效率分布。结果表明:在不同的叶片区域和主流湍流度下,流量比对气膜冷却特性的影响规律也有所不同;在低主流湍流度下,冷却效率整体上随着流量比的增大而升高,但是在叶片的叶尖和吸力面中截面区域冷却效率在大流量比下降低,且叶片吸力面中弦区域的冷气呈波纹状分布;高主流湍流度使冷气射流与主流之间的掺混更加剧烈,可以抑制吸力面的冷气脱离壁面且使其分布更加均匀,冷却效率随流量比增大而升高。In order to study the effects of the coolant mass flow rate ratio on the full film cooling characteristics of a three-dimensional turbine guide vane with different mainstream turbulence intensities,the full film cooling effectiveness of a three-dimensional turbine guide vane model were measured using transient liquid crystal technique.The mainstream turbulence intensities are 1%and 15%,and the coolant flow rate ratios are 5.5%,8.4%and 12.5%.The results show that the effects of the flow rate ratio on the film cooling characteristics are different in different regions and mainstream turbulence intensities.Under low mainstream turbulence intensity condition,the film cooling effectiveness generally increases with flow rate ratio increasing,however,the film cooling effectiveness in the mid region of the suction side and the top region decreases in high flow rate ratio,and the coolant distribution on the mid chord region of suction side appears to be wavy.The high mainstream turbulence enhances the mixing of mainstream and coolant,which restrains the lift-off of the coolant from the vane surface and makes the coolant distribution uniform.

关 键 词：主流湍流度 流量比 涡轮导叶 气膜冷却效率 努赛尔数 液晶 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]