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

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.