采用任意中弧线叶片造型程序,将某单级跨声、常规设计的风扇改进为复合掠形设计.在改进设计过程中,通过调整风扇关键设计参数的分布,从设计上降低了激波及其关联的损失,克服了该风扇高相对马赫数与低损失、高效率的矛盾.内外函数值模拟结果表明,设计转速的风扇效率略微降低,但起飞转速的风扇效率得到显著提高,并且有效地改善了风扇/增压级的内外函气动性能匹配. In the process of improving the design, by adjusting the distribution of the key design parameters of the fan, the design of the shock wave and its reduced The correlation loss has overcome the contradiction between the high relative Mach number, low loss and high efficiency.The simulation results of internal and external function values ​​show that the fan speed at design speed slightly decreases, but the fan efficiency at takeoff speed is significantly improved and effectively improved The fan / supercharger level aerodynamic performance matching.