压气机叶片钝头前缘对边界层气动影响

Due to various reasons, like machining error and foreign objects damage (FOD), the leading-edge 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.