摘要
针对涡轮叶片尾缘冷却结构特点,建立了后台阶三维缝隙结构气膜冷却特性试验台,测量了缝隙中心和肋中心下游气膜冷却效率的局部分布,研究了不同几何结构的影响,其中缝宽-肋宽比的变化参数是0.67,1.0及1.5,唇厚-缝高比的变化参数是0.5,1.0及1.89。试验结果表明:(1)缝隙中心下游的冷却效率沿流向呈逐渐下降趋势,肋中心下游的冷却效率呈先增加后下降的趋势;(2)缝宽-肋宽比对下游冷却效率有较大的影响,缝宽-肋宽比越大,冷却效率越高;(3)唇厚-缝高比增加时,缝隙下游的冷却效率呈增加趋势;肋后冷却效率随唇厚-缝高比增加在x/H<4的区域呈减小趋势,在x/H>4的区域呈增大趋势;(4)三维掺混区随着缝宽-肋宽比的减小呈减小趋势,随唇厚-缝高比越大,成增大趋势。
Film cooling effectiveness of back-step three dimensional slots injection, which modeling the trailing edge cooling of turbine blade, was measured at the slot center line and rib center line. The effects of geometry of slot on film cooling effectiveness were studied. The ratio of slot width to rib width changed from 0.67 to 1.5 and ratio of lip height to slot height changed from 0.5 to 1.89. The experimental results show that the profile of film cooling effectiveness is different at the slot center line and rib center line. Both ratios of slot width to rib width and lip height to slot height have evident influence on the film cooling effectiveness. The sizes of three dimensional mixing flow region increases with the increase of both ratio of slot width to rib width and lip height to slot height.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2006年第4期312-315,320,共5页
Journal of Propulsion Technology
