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首页> 外文期刊>International Journal of Heat and Mass Transfer >Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different radial angles
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Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different radial angles

机译：径向角不同的圆柱孔和后孔的前缘膜冷却实验研究

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摘要

Film cooling performances of the cylindrical film holes and the laid-back film holes on the turbine blade leading edge model are investigated in this paper. Experimental measurements have been carried out to investigate the influence of the inclined angle in the spanwise direction (i.e. radial angle for a blade in the engine) on the film cooling performances of these two kinds of holes. Three rows of holes are arranged in a semi-cylinder model which is used to model the blade leading edge. Two inclined angles and three blowing ratios are tested. Transient heat transfer measurement technique with double thermochromic liquid crystals is employed in the present experiment. The results show that the trajectory of the film jets in the leading edge region deviates from the mainstream direction to the spanwise direction gradually as the blowing ratio increases. Under large blowing ratio, more area can benefit from the film protection and the film cooling effectiveness distribution is more uniform than those under small blowing ratio, while the heat transfer coefficient is also higher. The basic distribution features of heat transfer coefficient are similar for all the tested models. The heat transfer coefficient in the region where the jet core flows through is relatively lower, while the heat transfer coefficient in the jet edge region is relatively higher. Compared with the cylindrical holes, the jets from the laid-back holes have better film coverage and meanwhile make more area have relatively higher heat transfer coefficient, especially under large blowing ratio. Under the same blowing ratio, the jets from film holes with small radial angle can attach on the wall surface better and give higher film cooling effectiveness in the region close to the hole exit than the film holes with large radial angle, while they also produce relatively higher heat transfer coefficient.
机译：本文研究了涡轮叶片前缘模型上的圆柱形薄膜孔和后备薄膜孔的薄膜冷却性能。已经进行了实验测量以研究在翼展方向上的倾斜角（即，发动机中的叶片的径向角）对这两种孔的膜冷却性能的影响。在半圆柱模型中排列了三排孔，该模型用于对叶片前缘进行建模。测试了两个倾斜角度和三个吹气比。本实验采用双热致变色液晶的瞬态传热测量技术。结果表明，随着吹塑比的增加，前缘区域中的薄膜射流的轨迹逐渐从主流方向向翼展方向偏离。在大鼓风比下，与小鼓风比相比，更大的面积可以受益于薄膜保护，薄膜的冷却效果分布更均匀，同时传热系数也更高。对于所有测试模型，传热系数的基本分布特征均相似。射流芯流过的区域中的传热系数相对较低，而射流边缘区域中的传热系数相对较高。与圆柱孔相比，后置孔的射流具有更好的覆膜性，同时使更大的面积具有相对较高的传热系数，特别是在大吹塑比下。在相同的吹塑比下，具有较小径向角的薄膜孔的射流可以比具有较大径向角的薄膜孔更好地附着在壁表面上，并在靠近孔出口的区域提供更高的薄膜冷却效果，同时它们也产生相对较大的角度。更高的传热系数。

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