基于Kriging代理模型构建了针对大涵道比涡扇发动机风扇叶片的气动优化设计方法，集成了参数化建模、TurboGrid网格划分和计算流体力学(CFD)组合优化技术.以风扇叶片的各叶高截面叶型为优化对象，进行基于叶片安装角扭转和最大厚度位置移动的叶型重构.选取失速点流量作为目标函数，对风扇叶片稳定运行范围进行评估并优化.与原叶片相比，优化叶片的稳定运行范围拓宽10.1%，且在稳定运行范围中表现出更高的性能.效率和压力系数的最大增幅分别为2.63%和9.27%，表明优化过程有效地拓宽了风扇叶片的稳定工作范围，并大幅提高了效率和总压升等性能指标.
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.
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