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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。
Leaf curvature, especially the leading edge of the curvature of the discontinuous phenomenon has a greater impact on compressor blade loss. A numerical simulation was carried out to study the influence of leading edge shape on the compressor blade loss. The leading edge of the blade was arc-shaped. The numerical simulation results show that the leading edge of the suction surface induces the transition of the laminar boundary layer and the total pressure loss of the blade is significant Increase. After using the curvature of the leading edge of the blade, the elimination of the small angle of attack edge separation bubble, postponed the increase of leaf loss. However, in the case of larger angle of attack, the leaves with continuous leading edge of curvature produced the leading edge separation bubble, but effectively reduced the size of the separation bubble. Therefore, reduce.