Abstract: Optimization of blade profile on camber line for a highly-loaded single stage fan has been carried out，based on a aerodynamic optimization method with three-dimensional numerical simulation flow field analysis and camber line discrete points blade angle controlling model. An optimizing mechanism and design principles of supersonic blade profile camber line are proposed to improve the design technology of the highly-loaded fan rotor. The optimization was evaluated by commercial fluid dynamics calculation software. The results show that the efficiency of the fan at design point increases by 1.1% after optimization，the mass flow by 1.01 kg/s and the surge margin at design rotation speed by 1.85%. In the meantime，the performance at low-medium speed is maintained. It is proved that blade profile area ratio，pressure distribution at the blade surface and shock wave structure are important for performance of blade profile. It can be more reasonable by controlling the blade angle on camber line to improve the performance of the fan rotor.

Key words: Supersonic speed；Highly loaded fan；Rotor；Numerical simulation； Blades optimization；Flow field analysis

摘要： 以高负荷单级风扇为研究对象，采用全三维数值模拟流场分析和叶型中弧线离散点弯角控制相结合的气动优化方法，研究超声速叶型中弧线优化机理和设计原则，以提高高负荷风扇转子的设计技术，并用商用气动计算软件对优化结果进行评估。计算结果显示，优化后设计点效率提高1.1%，设计点流量提高1.01kg/s，设计转速喘振裕度提高1.85%，中低转速性能基本不变。研究表明:叶型面积比、叶片表面静压分布和激波结构对叶型性能影响显著，通过控制中弧线局部区域的弯角，能够实现三者的合理分布，提高风扇转子性能。

关键词: 超声速；高负荷风扇；转子；数值模拟；叶型优化；流场分析