Experiments were carried out to study the effects of compound angle, hole arrangement, and blowing ratio on the film cooling performance of multiple rows of holes on the suction surface of a turbine blade. The turbine worked at rotational speed of 600 rpm corresponding to the rotational Reynolds number of 5.36 × 10⁵. Three rows of cylindrical holes arranged in line or in stagger were drilled on the rotor blade suction surface at the streamwise location of 12.4%, 17.8%, and 23.2%, respectively. Three compound angles, with the same streamwise angle of 45° but different lateral deflection angles of 45°, 0°, and −45°, were studied. The film cooling effectiveness was obtained using pressure sensitive paint (PSP) technique with average blowing ratios varied from 0.5 to 2.0. The results showed that the application of compound angle changes the jet direction in the near-hole region and makes the film spread laterally. Compared with the film cooling without compound angle, using positive and negative compound angle can improve overall average film cooling effectiveness by about 20% and 25%, respectively. The effects of the secondary flow also can be weakened. A stagger film trajectory arrangement can achieve more uniform film coverage with higher overall film cooling effectiveness. The film trajectory arrangement of a positive compound angle injection is determined by the combined effect of hole arrangement and blowing ratio. While, the film trajectory arrangement of a negative compound angle injection is almost the same as the hole arrangement and nearly does not change with the blowing ratio.

进行了实验，以研究复合角，孔的布置和吹塑比对涡轮叶片吸力表面上多排孔的膜冷却性能的影响。涡轮以600 rpm的转速工作，对应于5.36×10 ⁵的旋转雷诺数。在转子叶片吸力表面上，在流向分别为12.4％，17.8％和23.2％的位置上钻了三排成行或交错排列的圆柱孔。研究了三个复合角，其中相同的流向角为45°，但横向​​偏角分别为45°，0°和-45°。使用压敏涂料（PSP）技术获得的薄膜冷却效果，平均吹塑比在0.5到2.0之间变化。结果表明，复合角的应用改变了近孔区域的射流方向，并使薄膜横向扩散。与没有复合角的薄膜冷却相比，使用正和负复合角可以分别将整体平均薄膜冷却效率提高约20％和25％。二次流的影响也可以被削弱。错开的薄膜轨迹排列可以实现更均匀的薄膜覆盖，并具有更高的整体薄膜冷却效率。正角复合喷射的薄膜轨迹布置是由孔布置和吹塑比的综合作用决定的。同时，负复合角喷射的薄膜轨迹布置与孔布置几乎相同，并且几乎不随着吹塑比而变化。