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首页> 外文会议>ASME turbo expo >FILM COOLING EFFECTIVENESS DISTRIBUTION ON FIRST-STAGE VANE ENDWALL WITH AND WITHOUT LEADING-EDGE FILLETS PART I: EFFECT OF LEADING EDGE GEOMETRY
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FILM COOLING EFFECTIVENESS DISTRIBUTION ON FIRST-STAGE VANE ENDWALL WITH AND WITHOUT LEADING-EDGE FILLETS PART I: EFFECT OF LEADING EDGE GEOMETRY

机译：带有和不带有前沿边角的第一阶段叶片端面的膜冷却效率分布第一部分：前沿几何形状的影响

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The paper is focused on the effect of leading edge airfoil geometry on endwall film cooling. Fillets placed at the junctions of the leading edge and the endwall are used in investigation. Three types of fillet profiles are tested, and the results are compared with baseline geometry without fillet. The design of the fillet is based on the suggestion by previous literature data indicating that sharp is effective in controlling the secondary flow. Three types of sharp slope fillet with the length to height ratio of 2.8,1.2 and 0.5 are made using stereo lithography (SLA) and assessed in the experiment. Distributed with the approximately inviscid flow direction, four rows of compound angle laidback fan-shaped holes are arranged on the endwall to form full covered coolant film. The four rows of fanshaped holes are inclined 30 deg to the endwall surface and held an angle of 0, 30, 45 and 60 deg to axial direction respectively. The fanshaped holes have a lateral diffusion angle of 10 deg from the hole-centerline and a forward expansion angle of 10 deg to the endwall surface. The Reynolds number based on the axial chord and inlet velocity of the free-stream flow is 3.5*105, and the testing is done in a four-blade cascade with low Mach number condition (0.1 at the inlet) while the blowing ratio of the coolant through the discrete holes varies from 0.4 to 1.2. The film-cooling effectiveness distributions are obtained using the PSP (pressure sensitive paint) technique, by which the effect of different fillet geometry on passage induced flow and coolant is shown. The present paper compares the film cooling effectiveness distributions in a baseline blade cascade with three similar blades with different leading edge by adding fillets. The results show that with blowing ratio increasing, the film cooling effectiveness increases on the endwall. For specific blowing ratio, the effects of leading edge geometries could be illustrated as follows. The baseline geometry provides the best film cooling performance near leading edge pressure side. As for the leading edge suction side, the best leading edge geometry depends on the blowing ratio. The longfillet is the more effective in controlling horseshoe vortex at low blowing ratio, but for the high blowing ratio shortfillet and mediumfillet are better.
机译：本文重点研究前缘翼型几何形状对端壁薄膜冷却的影响。放置在前缘和端壁交界处的圆角用于调查。测试了三种类型的圆角轮廓，并将结果与​​没有圆角的基线几何图形进行了比较。圆角的设计基于先前文献数据的建议，表明锋利可有效控制二次流。使用立体光刻（SLA）制作了三种长高比分别为2.8、1.2和0.5的尖锐倒角圆角，并在实验中进行了评估。在大致不粘稠的流动方向上分布，在端壁上布置了四排复合角后置扇形孔，以形成完全覆盖的冷却液膜。四排扇形孔相对于端壁表面倾斜30度，并分别相对于轴向保持0、30、45和60度的角度。扇形孔与孔中心线的横向扩散角为10度，到端壁表面的向前扩展角为10度。基于自由流的轴向弦和入口速度的雷诺数为3.5 * 105，并且在低马赫数条件（入口处为0.1）的四叶栅叶栅中进行测试，而通过离散孔的冷却液从0.4到1.2不等。使用PSP（压敏涂料）技术获得薄膜的冷却效果分布，通过该技术可以显示出不同的圆角几何形状对通道感应流和冷却剂的影响。本文通过添加圆角比较了基准叶片级联和三个具有不同前缘的类似叶片的薄膜冷却效率分布。结果表明，随着吹塑比的增加，薄膜的冷却效果在端壁上增加。对于特定的吹风比，前缘几何形状的影响可以说明如下。基准几何形状在前缘压力侧附近提供了最佳的薄膜冷却性能。至于前缘吸力面，最佳前缘几何形状取决于吹塑比。长角焊片在低吹气比下更有效地控制马蹄涡流，但对于高吹气比，短角焊和中角切肉效果更好。

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