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带抑涡支孔结构新型气膜孔的实验研究

Experimental Investigation on Improvement of Film Cooling Effectiveness with Anti-vortex Holes

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【作者】 魏小峰吴宏

【Author】 WEI Xiaofeng;WU Hong;Shanghai Aircraft Design and Research Institute;National Key Lab on Air Engine, Beijing University of Aeronautics and Astronautics;

【机构】 上海飞机设计研究院北京航空航天大学航空发动机气动热力重点实验室

【摘要】 采用稳态液晶测温法对基准孔和3个在计算中有较好冷却效率的带抑涡支孔结构新型气膜孔进行了实验研究。实验结果表明:新型气膜孔的抑涡支孔对主气膜孔起到了保护作用,使新型孔在不同吹风比下的冷却效率要高于普通基准孔,特别是在高吹风比的情况下,这种现象更加明显。在低吹风比情况下,三种不同结构新型孔的冷却效率差别不大;而在高吹风比时,支孔与主孔平行孔型和支孔在主孔下游孔型要高于支孔在主孔上游的孔型,该现象随着吹风比增加会愈加明显。

【Abstract】 Conducted experimental studies on film cooling effectiveness of a baseline hole and three anti-vortex holes, which have good performance of film cooling in numerical simulations, with steady-state liquid crystal themometry. The results showed that: the flow from auxiliary holes can help to attach the flow from primary hole on the wall. Under different blowing ratios, the film cooling effectiveness of three anti-vortex film cooling holes were higher than the baseline film cooling holes, specially at high blowing ratio. At the low blowing ratio condition, the three anti-vortex holes showed similar levels of film effectiveness. At the high blowing ratio condition, the anti-vortex hole, which two small holes parallel the primary hole, had almost identical effectiveness with the anti-vortex hole, which two small holes laid in the downstream region. Compared to the other anti-vortex hole, this two had better performance of film cooling. As the blowing ratio increased, the phenomenon was more obvious.

  • 【文献出处】 航空科学技术 ,Aeronautical Science & Technology , 编辑部邮箱 ,2015年01期
  • 【分类号】V231
  • 【被引频次】3
  • 【下载频次】111
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