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本文在环形叶栅端壁30%、60%、90%轴向弦长处和距前缘-10%轴向弦长端壁处布置多排圆柱形气膜冷却孔,运用CFD方法在吹风比为1.0条件下,模拟分析端壁气膜冷却效率。结果表明,叶片两侧各有一支马蹄涡夹裹冷却气膜主体向吸力面偏移,致使压力面一侧端壁未冷却区域扩大,吸力面一侧端壁未冷却区域缩小。吸力面一侧端壁气膜冷却效率沿流向逐渐提升,并在流道中、下游完全冷却覆盖端壁,而压力面一侧端壁一直未能获得冷却气膜覆盖。在压力面壁角内增设冷却气膜孔,改进了壁角的冷却效果,消除了局部壁面超温的问题。
In this paper, a plurality of rows of cylindrical film cooling holes are arranged at the axial chord length of 30%, 60%, 90% of the annular cascade endwall and at the end of the 10% axial chord length from the leading edge. By using the CFD method, 1.0 conditions, simulation analysis of the end wall of the film cooling efficiency. The results show that there is a horseshoe vortex wrapping the main body of the cooling air film on both sides of the blade to offset the suction surface, so that the uncooled end of the pressure side expands, and the uncooled end of the suction side shrinks. The efficiency of the film cooling on the side of the suction side is gradually increased along the flow direction. In the middle and downstream of the flow channel, the end wall is completely cooled and the end wall on the pressure side has not been covered by the cooling film. In the pressure surface wall angle additional cooling film hole to improve the corner cooling effect, eliminating the problem of local wall over-temperature.