叶片型线曲率,特别是前缘的曲率不连续现象对于压气机叶型损失有较大影响。针对前缘形状对压气机叶型损失的影响开展数值模拟研究,原始叶型的前缘为圆弧形,数值模拟结果表明吸力面前缘分离诱导层流边界层转捩,叶型总压损失显著增大。使用曲率连续的叶片前缘后,消除了小冲角工况下前缘的分离泡,推迟了叶型损失的增大。而在冲角较大的工况,使用曲率连续前缘的叶片尽管也产生了前缘分离泡,但是能够有效减小分离泡的大小,因此叶型在大冲角工况下的损失同样得到降低。
The blade surface curvature,especially the discontinuous curvature around the leading edge,has important influence on the profile loss of compressor.The effect of leading edge shape on the profile loss was investigated numerically.The original blade has circular leading edge.Numerical results show that the transition of laminar boundary layer is induced by the leading edge separation, and that the profile loss increases significantly.The continuous curvature leading edge eliminates the separation bubble at small incidences,and the increase of the profile loss is delayed.At larger incidences,the separation bubble arises,but the size of the separation bubble is effectively reduced by the continuous curvature leading edge,so the profile loss is also reduced.