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作 者:杨成凤[1] 张靖周[1] 陈利强[1] 吴世勋[1]
机构地区:[1]南京航空航天大学能源与动力学院,南京210016
出 处:《航空动力学报》2008年第10期1765-1771,共7页Journal of Aerospace Power
基 金:航空基础科学基金(03C52019)
摘 要:设计了三种型面的气膜孔扩展结构,研究了气膜冷却效率、壁面换热系数及流量系数随吹风比的变化规律.研究结果表明,与典型的圆柱形气膜孔相比,有后向扩展型面的气膜孔具有相对较高的冷却效率和换热系数,流量系数略有降低.扩展型面的流向扩展角对冷却效率和换热系数的影响大于侧向扩展角的影响.侧向扩展角只在特定吹风比下才对提高气膜的侧向覆盖率、进而提高气膜冷却效率起作用,它使得位于二次流出流下游的低压区域范围增大,流量系数减小.Three types of expanded shape film cooling holes were designed to study the change of the film cooling efficiency, heat transfer coefficient at the wall and flow discharge coefficient with the blow ratio. The result shows that: the film cooling efficiency and heat transfer coefficient of the expanded film cooling holes are higher than the typical round film cooling holes, but the flow discharge coefficient is lower. The effect of the streamwise ex- panded angle on the film cooling effectiveness and heat transfer coefficient is more remarka ble than the laterally angle, which expands the area of the low pressure near the edge of the holes, leading to lower flow discharge coefficient.
分 类 号:V231.1[航空宇航科学与技术—航空宇航推进理论与工程]
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