航空科学技术
航空科學技術
항공과학기술
AERONAUTICAL SCIENCE AND TECHNOLOGY
2015年
1期
49-54
,共6页
气膜孔%气膜冷却%肾状涡%射流%实验研究
氣膜孔%氣膜冷卻%腎狀渦%射流%實驗研究
기막공%기막냉각%신상와%사류%실험연구
iflm cooling holes%iflm cooling%counter-rotating vortex pair%jet%experimental investigation
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。
採用穩態液晶測溫法對基準孔和3箇在計算中有較好冷卻效率的帶抑渦支孔結構新型氣膜孔進行瞭實驗研究。實驗結果錶明:新型氣膜孔的抑渦支孔對主氣膜孔起到瞭保護作用,使新型孔在不同吹風比下的冷卻效率要高于普通基準孔,特彆是在高吹風比的情況下,這種現象更加明顯。在低吹風比情況下,三種不同結構新型孔的冷卻效率差彆不大;而在高吹風比時,支孔與主孔平行孔型和支孔在主孔下遊孔型要高于支孔在主孔上遊的孔型,該現象隨著吹風比增加會愈加明顯。
채용은태액정측온법대기준공화3개재계산중유교호냉각효솔적대억와지공결구신형기막공진행료실험연구。실험결과표명:신형기막공적억와지공대주기막공기도료보호작용,사신형공재불동취풍비하적냉각효솔요고우보통기준공,특별시재고취풍비적정황하,저충현상경가명현。재저취풍비정황하,삼충불동결구신형공적냉각효솔차별불대;이재고취풍비시,지공여주공평행공형화지공재주공하유공형요고우지공재주공상유적공형,해현상수착취풍비증가회유가명현。
Conducted experimental studies on iflm cooling effectiveness of a baseline hole and three anti-vortex holes, which have good performance of iflm cooling in numerical simulations, with steady-state liquid crystal themometry. The results showed that: the lfow from auxiliary holes can help to attach the lfow 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 iflm cooling holes, specially at high blowing ratio. At the low blowing ratio condition, the three anti-vortex holes showed similar levels of iflm 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 iflm cooling. As the blowing ratio increased, the phenomenon was more obvious.