Effect of Bypass Duct Backward Swept Stator Blade on Performance of Fan/Compressor

To meet the challenge of a high bypass ratio fan/compressor optimization design on noise reduction,using the circumferentially-averaged method and the multi-blade-row computational techniques,the aerodynamic performance of three types with swept bypass stator at 0°,22.5° and 30° sweep angle were simulated at 100% design rotational speed,and the detailed results were analyzed respectively and compared with results obtained from 3D numerical simulation software NUMECA.The results show that the axial sweep degree will make the blade surface pressure of the stator static pressure increase in tip,and the blade surface static pressure distribution of root become more uniform,then the aerodynamic performance margine of fan/compressor bypass is changed a little.But larger sweep degree will increase blade tip surface load,decrease bypass surge margin,furthermore it affects the aerodynamic performance of the fan/compressor bypass.