Heat Transfer Enhancement Within a Turbine Blade Cooling Passage Using Ribs and Combinations of Ribs With Film Cooling Holes
Heat Transfer Enhancement Within a Turbine Blade Cooling Passage Using Ribs and Combinations of Ribs With Film Cooling Holes
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DOI：
10.1115/94-gt-232
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发表时间：
1994-06
期刊：
影响因子：
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通讯作者：
J. Shen;Z. Wang;P. Ireland;T. V. Jones;A. Byerley
中科院分区：
文献类型：
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作者：
J. Shen;Z. Wang;P. Ireland;T. V. Jones;A. Byerley
采用液晶瞬态传热方法，对一个涡轮机转子叶片通道的缩尺模型进行了研究。给出了先加肋后加肋加孔通道局部换热系数的详细等值线。孔的几何形状和实验无量纲流率是那些发生在发动机薄膜冷却孔的入口处的代表。肋通道的结果进行了比较，建立相关的发展流。定性的表面剪切应力分布与液晶确定。根据流场的解析解，讨论了传热系数的复杂分布。版权所有© 1994，ASME
A transient heat transfer method which uses liquid crystals has been applied to a scale model of a turbine rotor blade passage. Detailed contours of local heat transfer coefficient are presented for the passage in which the heat transfer to one wall was enhanced firstly by ribs and then with ribs combined with holes. The hole geometry and experimental dimensionless flow rates were representative of those occurring at the entrance to engine film cooling holes. The results for the ribbed passage are compared to established correlations for developed flow. Qualitative surface shear stress distributions were determined with liquid crystals. The complex distributions of heat transfer coefficient are discussed in the light of the interpreted flow field.Copyright © 1994 by ASME