涡轮工作叶片不同区域簸箕形孔的气膜冷却特性实验

The distribution characteristics of film cooling effectiveness of dustpan shaped holes at different positions of suction surface and pressure surface of turbine blade were studied by pressure sensitive paint (PSP) measurement technique. The effects of blowing ratio (blowing ratio of 0.5，1.0，2.0) and turbulence intensity (turbulence intensity of 0.62%， 16.0%) on film cooling effectiveness were analysed. The experimental results showed that the optimum blowing ratios of the dustpan shaped holes on the suction surface and pressure surface were around blowing ratio of 1.0 and 2.0， respectively. The dustpan shaped holes on the suction surface had higher film cooling effectiveness under low turbulence and medium blowing ratio (blowing ratio of 1.0). The dustpan shaped holes on the pressure surface had larger film coverage area and film cooling effectiveness under high blowing ratio and high turbulence. The film coverage area and spanwise averaged film cooling effectiveness on the suction surface were significantly higher than those on the pressure surface. And the film cooling performance of dustpan shaped holes at the position with large curvature was the worst on the pressure surface. The influence of turbulence on film cooling effectiveness was similar to that of blowing ratio. The enhancement of turbulence reduced the film cooling effectiveness on the pressure surface，but improved the film cooling performance on the suction surface under high blowing ratio， and reduced the sensitivity of the film cooling performance to the change of blowing ratio on the suction surface.