Development for a 3D Blade Design System Based on High-order Derivative

On the basis of quasi-3D aerodynamic design, a method that the second order derivative of the camber line for the airfoil is directly defined based on the cubic spline curve is proposed. The 3D blade is generated according to the stacking parameters of blade, and the corresponding three-dimensional blade geometry building system program is developed. The results indicates that the blade generating system can fully guarantee the smoothness of geometrical parameters for blade, which is beneficial to improve the aerodynamic load for highly-loaded compressor stage, to skillfully control shock wave shape and decrease its loss as well as diminish secondary flow in the endwall corner area, thus effectively expand stall margin for compressor.