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换热系数的局部分布;研究了不同几何结构参数对换热系数的影响规律,其中缝宽/肋宽比b1/b2的变化参数是0.67、1.0及1.5,缝高/唇厚比H/d的变化参数是0.5、1.0及2.0。试验结果表明:缝后中心线与肋后中心线的换热系数随轴向距离的增加其总的趋势都是减小;换热系数随着缝高/唇厚比的减小,曲线变得比较平缓;换热系数在不同的缝宽/肋宽比时,曲线基本整体地上下移动,但吹风比不同Bc不同时,曲线移动幅度区别较大。
Heat transfer coefficient of the back-step three dimensional slots injection, which describing 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 heat coefficient have been studied. The ratio of the slot width to the rib width changes from 0. 67 to 1.5 and the ratio of the slot height to the lip height changes from 0. 5 to 2. 0. The experimental results show that the profile of heat coefficients is different at the slot center line and the rib center line. Both ratios of the slot width to the rib width and the lip height to the slot height have evident influence on heat transfer coefficient. The sizes of the three dimensional mixing flow region is increased with the increase of both ratios.
出处
《热科学与技术》
CAS
CSCD
2006年第1期17-21,共5页
Journal of Thermal Science and Technology
关键词
涡轮叶片
三维缝隙
薄膜冷却
掺混流
turbine blade
trailing edge slot
film cooling
mixing flow
