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实验采用GE-E~3高压涡轮进口导叶比例放大叶型,叶栅进口雷诺数为3 5×10~5,进口马赫数为0.1,气膜冷却吹风比范围控制在M=0.7至M=1.3。两组实验叶片的压力面气膜孔分别采用成型孔径向孔型和复合角孔型,复合角为300°,成型孔扩张角为5°。气膜有效度采用压力敏感漆进行测量,测量结果通过CCD采集后经处理得到气膜有效度分布云图。通过实验可以得出以下结论:1)当吹风比从M=0.7增加至M=1.3时,叶片表面气膜有效度有明显增加;2)当吹风比相同条件下,带有复合角的成型孔在接近前缘位置具有微弱的优势,在展向平均气膜有效度对比中复合角并没有明显作用;3)在端壁附近区域复合角孔型具有明显优势。
The experiment adopts GE-E ~ 3 high-pressure turbine inlet guide vane to enlarge the leaf type, the inlet Reynolds number is 35 × 10 ~ 5, the inlet Mach number is 0.1, the film cooling blow ratio range is controlled from M = 0.7 to M = 1.3. The pressure surface gas film holes of the two sets of experimental blades are respectively formed by the radial holes of the forming holes and the composite corner holes with the composite angle of 300 ° and the expanding angle of the forming holes of 5 °. The effectiveness of the gas film is measured with a pressure-sensitive paint, and the measured results are obtained after the CCD is collected and processed to obtain the cloudiness distribution of the gas film. The following conclusions can be drawn through the experiments: 1) When the blowing ratio increases from M = 0.7 to M = 1.3, the effectiveness of the film on the blade surface increases obviously. 2) When the blowing ratio is the same, There is a weak advantage near the leading edge, and the composite angle has no significant effect in the contrast of span-averaged film validity. 3) The composite corner hole has obvious advantages near the end wall.