在叶尖切线速度U=480 m/s的条件下,对级压比为2.4、负荷系数为0.42的风扇进口级进行了初步的气动设计,并进行了数值验证.分析了转子尖部和静子根部的设计难点,重点考察了进口预旋分布、设计压比分布、转子叶尖激波前马赫数、静子根部进口马赫数以及静子出口气流角等参数,以及静子附面层抽气对性能的影响及其内部机制.结果表明:采用常规设计的转子能够达到0.42的负荷系数;在该负荷条件下,静子根部会出现进口超声的情况,并在根部通道中产生强烈的正激波;如果静子根部存在贯穿通道的正激波,即D因子较小,仍会发生严重的分离失速. Under the condition of the tip tangential speed U = 480 m / s, the preliminary aerodynamic design of the fan inlet stage with the stage pressure ratio of 2.4 and the load coefficient of 0.42 was carried out, and the numerical verification was carried out.The tip and stator The main difficulties in the design are: the pre-swirl distribution, the design pressure ratio distribution, the rotor Mach-Zehnder Mach number, the inlet Mach number at the stator root and the exit angle of the stator exit, The results show that the rotor with the conventional design can achieve a load coefficient of 0.42. Under this load condition, the imported sonotrode will appear at the root of the stator and a strong forward shock wave will be generated in the root channel. If the stator There is a positive shock wave penetrating the channel at the root, that is, the D factor is small, and serious separation stall may still occur.