压气机叶片钝头前缘对边界层气动影响

Aerodynamic Influence of Compressor Blade with Blunt Leading Edge on Boundary Layer Performance

由于加工误差、外物损伤等原因,压气机叶片前缘容易产生钝头变形。为分析其带来的影响,使用SST湍流模型并结合γ-θ转捩模型进行了数值模拟。通过叶片吸力面边界层形状因子、法向平均间歇因子和叶栅出口总压损失系数等参量,研究了钝头前缘对边界层发展所带来的影响。同时针对一种前缘曲率连续的改进叶型进行了研究。结果表明在很宽的攻角范围内,压力面边界层受钝头变形影响极小。吸力面边界层受影响程度则会随着攻角增大而提高,当攻角超过一定范围,钝头前缘会显著改变边界层发展,影响整个主流流场。

Due to various reasons,like machining error and foreign objects damage（FOD）,the leadingedge of the compressor blade is likely to blunting. In order to study the blunting influence,numerical simulation based on SST Model and γ-θ Transition Model is used. The influence of blunt leading-edge on boundary layer is studied by analyzing the boundary layer＇s shape factor,normal average intermittency factor,blade cascade＇s total pressure loss and other parameters. Besides,an optimized blade shape with continuous leading-edge curve is also analyzed. It is demonstrated that pressure surface boundary layer is hardly influenced by blunt leading-edge within a wide range of incidence angle. Suction surface boundary layer is more seriously affected with incidence angle enlargement. When the incidence angle is beyond the limits,the blunt leading-edge will significantly influence the boundary layer,and even the whole main flow field.