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首次对流向倾角α为６０°、锥顶角γ分别为１５°和３０°的扇形气膜冷却喷孔射流下游的流动和传热进行了详细的实验研究，并与相同实验条件下圆孔射流的情形进行了比较，结果发现了扇形孔优越的气膜冷却性能和其下游速度边界层等值线的３种基本形态。扇形孔出口面积的增大能够有效地降低纵向耦合涡的强度，明显地增加射流的侧向覆盖区域，显著地提高气膜冷却效率η，尤其是提高了喷孔两侧下游位置上的冷却效率
For the first time, the flow and heat transfer downstream of the fan-shaped film cooling jet with fan angle α of 60 ° and cone angle γ of 15 ° and 30 ° were studied in detail. Compared with the same experiment, The results show that there are three basic morphologies of the film cooling performance and the contour of the velocity boundary layer downstream of the fan-shaped hole. The increase of fan orifice outlet area can effectively reduce the strength of longitudinally coupled vortex and obviously increase the lateral coverage area of jet and significantly improve the film cooling efficiency η, especially the cooling efficiency at downstream positions on both sides of the nozzle hole