涡轮叶片尾缘半劈缝冷却结构压力系数的实验研究

Pressure coefficient measurements of turbine blade trailing edge slots

对九种不同几何结构的尾缘半劈缝结构的压力系数进行了实验研究,在不同吹风比和雷诺数下测得了缝中心和肋中心后沿流向压力系数的分布,分析了各种因素对压力系数的影响。结果表明肋中心后和缝中心后的压力系数没有多大的差别。半劈缝的几何结构对压力系数有很大的影响,当缝宽-肋宽比增大(在0.67到1.5的范围内)时,压力系数随之增大;当缝高-唇厚比增大(在0.53到2的范围内)时,压力系数变化不是很大,但主流和二次流的参混距离减小。在几何结构一定的情况下,压力系数随雷诺数(5,000到15,000)的增大有小幅度增大,在X/H小于某一值时,压力系数随着吹风比(0.5到2.0)的增加是增大的,但在X/H大于这一值时压力系数随着吹风比(0.5到2.0)的增加却是减小的,但是变化幅度并不是很大。

Pressure coefficients of turbine blade trailing edge slots were investigated. , there are nine different scale of slot, pressure coefficients with coolant injection were determined at different blowing ratio （ between 0. 5 and 2. 0） and Reynolds number（ between 5,000 and 15,000）. The results show that Pressure coefficients of the tailing edge slot are differet little in different bowing ratio and Reynolds number at same scale. But for slot of different scale, the distribution of Pressure coefficients is very geatly. Pressure coefficients will rise when slot width to rib width ratio （ between 0. 67 and 1.5） rises ; Pressure coefficients will minish when slot height to lip thickness ratio（ between 0. 53 and 2） rises.