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在吹风比为0.3~1.5,堵塞比为0.1~0.5范围内,对平板上单排倾斜气膜孔内局部堵塞所引起的冷气射流流动和冷却特性变化进行了数值研究,分析了堵塞比、堵塞位置和吹风比对绝热气膜冷却效率的影响.在研究参数范围内的研究结果表明:气膜孔出口端前缘的局部堵塞有利于抑制肾形涡,对气膜孔下游的绝热气膜冷却效率有改善作用,并且随着堵塞比和吹风比的增加,对冷却效果的改善越为明显.而在气膜孔出口端尾缘或侧边的堵塞则在较大的堵塞比下削弱气膜冷却效果.相对于气膜孔出气端的局部堵塞,在气膜孔进气端和中部的堵塞对绝热气膜冷却效率的影响要微弱得多.
In the range of 0.3-1.5 for blow-up ratio and 0.1-0.5 for plug-in ratio, the numerical simulation of the flow and cooling characteristics of the cold-air jets caused by local blockage in the single-row inclined gas film holes on the slab was carried out. Location and blowing ratio on the cooling efficiency of the adiabatic film.The results of the research within the parameter range show that the partial blockage at the leading edge of the film hole is beneficial to the suppression of kidney vortex and the adiabatic film cooling And improve the cooling effect with the increase of the blockage ratio and blowing ratio.The blockage at the trailing edge or side of the outlet end of the film hole weakens the air film at a larger blockage ratio Cooling effect.Compared with the local blockage at the air outlet end of the film hole, the blockage at the air inlet end and middle of the film hole has a much weaker effect on the cooling efficiency of the adiabatic film.