叶片前缘双出口孔射流冷却效率数值模拟
Numerical simulation of film cooling effectiveness with one inlet and double outlet hole on leading edge
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摘要: 利用数值模拟的方法研究了叶片前缘双出口孔射流冷却效率.该孔型是一种新概念气膜孔.吹风比变化范围为1.0~3.5,主流通道入口湍流度30%.结果表明,圆柱孔射流冷却效率和实验数据吻合较好,随着吹风比增加,单孔射流冷却效率减小.双出口孔有效地改善了叶片前缘冷却效率.吹风比从1.0增加到2.5时,冷却效率显著增加,吹风比为2.5和3.0时的冷却效率没有显著差别,吹风比为3.5时的冷却效率较低.双出口孔射流冷却效率径向分布比较均匀.Abstract: Film cooling effectiveness with one inlet and double outlet hole injection on leading edge was studied by numerical simulation.This hole was of novel concept geometry.Blowing ratios varied from 1.0 to 3.5.Turbulence intensity at the inlet of the tunnel was 30%.The result shows that the distribution of the cooling effectiveness with cylindrical hole injection agrees with the experimental data.The film cooling effectiveness with cylindrical hole decreases with the rising blowing ratios.Film cooling effectiveness is improved by one inlet and double outlet hole injection.The cooling effectiveness increases as the blowing ratios increase from 1.0 to 2.5,but differs little if the blowing ratios are of 2.5 and 3.0.The cooling effectiveness is small at the blowing ratio of 3.5.The spanwise distribution of cooling effectiveness with the double outlet hole is uniform.
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Key words:
- turbine blade /
- film cooling /
- cooling effectiveness /
- double outlet hole /
- numerical simulation
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