为了揭示吹风比和偏角对交叉孔气膜冷却的影响,通过改变吹风比及交叉孔的偏角,利用数值模拟的技术,进行气膜冷却特性研究.湍流模型选择k-ε模型,壁面函数采用增强壁面函数.结果表明:①随着吹风比的增大,涡旋中心与壁面间距增大,反肾涡旋对的影响范围变大,这使气膜的覆盖面积增大,同时气膜的贴壁性变差；吹风比为1.5时显示了较好的冷却效果；②随着偏角的增大,反肾涡旋对间距加大,这使气膜的覆盖面积增大,同时也导致气膜在下游的分离提前；偏角25度显示了较好的冷却效果.%Film cooling characteristics were numerically analyzed on the crossed circular- holes based on models with different drift angle and conditions of blowing ratio to disclose the influences of blowing ratio and drift angle for double-jet film-cooling. Choosing k-ε model as the turbulence model and enhanced wall treatment as near-wall treatment in the simulation. The results show that the distance between the core of vortex and the wall and the range of the anti-kidney vortex pair become wider and wider as the increasing of blowing ratio, As the result, the area of film-cooling increases , but the cooling film could not stick to the wall well at the same time. It can get better cooling effectiveness when blowing ratio is 1.5. Apart from that, as the increasing of drift angle, the space of the anti-kidney vortex pair adds, so the area of film-cooling increases and the film becomes separated earlier. It shows better cooling effectiveness when drift angle is 25°.
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