Abstract: In order to explore the limit of the loading，two low reaction design methodologies based on an increase on inlet pre-swirl flow angle and exit axial velocity of the rotor were both exploited to achieve an aerodynamic design of a fan stage with a tip speed of 370m/s. The 3D numerical simulation results show that at design point，the fan stage enables a single stage pressure ratio of 2.39 at a through-flow efficiency of 90.84% with a bleed mass fraction of 5.5%，which meets its design objective. Further flow field analysis shows that the higher loss coefficient of the stator blade near the hub is related to the stronger shock and the blockage incurred by too large bleed flow at the hub. The redesign should consider reducing the strength of the inlet shock or decreasing the suction flow，that is，to increase the back pressure at suction slot outlet or to reduce the suction area.

Key words: High-load fan stage；Low-reaction；Aspiration；Aerodynamic performance

摘要： 为了探索研究风扇负荷极限，采用基于增加进口正预旋和动叶轴向速度提升的两种低反动度设计方法，对叶尖切线速度为370m/s的风扇级进行了气动设计研究。通过三维数值计算，结果表明，在设计点，风扇级实现了2.39的单级压比，通流效率达90.84%，且抽吸流量仅为进口的5.5%，达到了设计目标。进一步的流场分析表明，静叶根部较高的损失系数一方面与较强的激波有关，另一方面与端壁过大的抽吸流量导致的堵塞有关。改型设计应从降低根部入口激波强度或降低抽吸流量，即增加抽吸背压或缩小抽吸面积入手。

关键词: 高负荷风扇级；低反动度；附面层抽吸；气动性能