高负荷低反动度吸附式风扇气动设计与性能分析

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.