Abstract: An aerodynamic optimization design method for high bypass ratio fan blades based on the Kriging surrogate model was constructed, which integrated parametric modeling, TurboGrid meshing, and computational fluid dynamics (CFD) combined optimization technology. The optimization method was implemented for airfoils at several spans of a fan blade and redesign of airfoils from blade setting angle rotating and maximum-thickness position moving. The mass flow at stall points was chosen as target function to evaluate and optimize the stable operating range of fan blade. Compared with prototype design, the stable operating range of the blade optimized was expanded by 10.1%, among which the aerodynamic performance was also enhanced, with a maximum increment of 2.63% for efficiency and 9.27% for pressure coefficient. The results show that the optimization design system has broadened the stable operating range of fan blade effectively, and has also substantially improved efficiency and total pressure rise.

Key words: Kriging surrogate model, high bypass ratio fan blades, aerodynamic optimization design, airfoil redesign, stable operating range