Film Effectiveness Performance of an Arrowhead-Shaped Film-Cooling Hole Geometry
Film Effectiveness Performance of an Arrowhead-Shaped Film-Cooling Hole Geometry
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DOI：
10.1115/1.2437781
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发表时间：
2007-04
影响因子：
1.7
通讯作者：
Y. Okita;M. Nishiura
中科院分区：
文献类型：
--
作者：
Y. Okita;M. Nishiura
本文介绍了第一个实验和数值计算工作的膜效率性能的一种新的薄膜冷却方法与箭头形孔的几何形状。实验结果表明，所提出的孔的几何形状改善了一般涡轮机翼型的吸力面和压力面上的膜效率。在发动机典型雷诺数和马赫数下，在中等高温主流流的高速风洞中，将一排孔的油膜效率数据与大尺寸翼型模型上与表面成35 °相同倾角的扇形孔的油膜效率数据进行了比较。使用压敏漆收集薄膜有效性数据。数值结果表明，冷却剂膜与建议的孔的几何形状保持良好的附着到表面和扩散的横向方向相比，传统的悠闲的扇形孔的冷却剂主流吹风比为0.6-3.5。
This paper presents the first experimental and numerical work of film effectiveness performance for a novel film-cooling method with an arrowhead-shaped hole geometry. Experimental results demonstrate that the proposed hole geometry improves the film effectiveness on both suction and pressure surface of a generic turbine airfoil. Film effectiveness data for a row of the holes are compared to that of fan-shaped holes at the same inclination angle of 35 deg to the surface on a large-scale airfoil model at engine representative Reynolds number and Mach number in a high-speed tunnel with moderately elevated temperature mainstream flow. The film effectiveness data are collected using pressure-sensitive paint. Numerical results show that the coolant film with the proposed hole geometry remains well attached to the surface and diffuses in the lateral direction in comparison with the conventional laidback fan-shaped holes for coolant to mainstream blowing ratios of 0.6-3.5.