Effect of Leading Edge Shape on the Aerodynamic Performance of Compressor

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.