涡轮叶片尾缘劈缝气膜冷却特性实验研究  

Experimental Investigation on the Film Cooling Characteristics of Turbine Blade Trailing Edge Cutback

作　　者：魏建生[1] 朱惠人[1] 张丽[1] 刘存良[1] 宋辉[1] 宋伟 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中航工业沈阳发动机研究所,沈阳110000

出　　处：《工程热物理学报》2016年第9期1988-1993,共6页Journal of Engineering Thermophysics

基　　金：国家重点基础研究发展计划资助项目(No.2013CB035702);航空科学基金(No.2014ZB53023);国家自然科学基金资助项目(No.51306152)

摘　　要：本文将层板冷却应用于涡轮叶片尾缘冷却中。为了研究肋形状对其劈缝气膜冷却特性的影响,在四种吹风比下,实验测量了直肋和倒斜角肋两种肋结构下的气膜冷却效率和换热系数,结果发现:1)倒斜角肋结构在劈缝下游的气膜冷却效率分布比直肋更均匀,倒斜角肋结构的平均气膜冷效高于直肋结构;2)两种结构的换热系数在劈缝出口处受吹风比影响较大,相同吹风比下,倒斜角肋结构的换热系数略高于直肋结构。The lamilloy cooling configuration was applied in the cooling of turbine blade trailing edge.To investigated the effect on the film cooling characteristics of rib shape,the film cooling effectiveness and heat transfer coefficient of straight-rib and beveling-rib configurations were measured at four blowing ratio.Results show：1） The film cooling effectiveness distribution downstream the cutback of the beveling-rib configuration is more uniform than that of straight-rib configuration,and the averaged film cooling effectiveness of beveling-rib configuration is higher than straight-rib configuration;2） The heat transfer coefficient of both the two configurations are affected strongly by the blowing ratio at the outlet of cutback;at the same blowing ratio,the heat transfer coefficient of the beveling-rib configuration is slightly higher than the straight-rib configuration.

关 键 词：叶片尾缘 层板冷却结构 劈缝 气膜冷却特性 

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]