气膜孔出口覆盖多孔介质层对冷却效果的影响
Cooling performance induced by film holes with coverage of porous media layer
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摘要: 综合气膜冷却和发汗冷却的特点,提出一种在气膜孔出口局部覆盖多孔介质层的冷却结构,利用数值模拟的手段对比研究该结构与常规斜圆孔气膜结构的冷却效果,计算考虑了0.61,0.91和1.22三种吹风比,结果表明:由于多孔介质对冷却射流的扩散作用,该结构的壁面冷却效率高于气膜冷却,同时壁面温度梯度得到了有效的抑制,是一种适合于未来燃气轮机叶片的冷却结构.Abstract: By attaching a layer of porous media coverage to the local zone around film-hole exits,a new cooling scheme which combines the features of film cooling and transpiration cooling was introduced in the present study.The cooling effects of the present scheme and the traditional cylindrical hole film cooling were compared numerically for three kinds of blowing ratio M=0.6,0.91 and 1.22.The results show that the new scheme provides higher wall cooling effectiveness and moderate temperature gradients,which enables it to be a better candidate for blade cooling for future high performance gas turbine.
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Key words:
- aerospace propulsion system /
- film cooling /
- transpiration cooling /
- porous layer /
- numerical simulation
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