Targeting the high flow incidence angle induced by inlet endwall boundary layer skew in compressor

the LESB(leading edge strake blade) concept was elucidated with reference to the strake wing theory from aircraft. The modeling method was developed by adding leading edge strake to main blade

and the LESB technique was formed. In order to validate the effect of technique

the LESB modeling was applied to the NACA65 diffuser cascade with turning angle 60° after the numerical method was verified by cascade test data. The performance improvement was compared between original blade and LESB at 0° and 5° incidence angles with endwall boundary layer skew through the flow field structure

performance parameters and action mechanism. The results show that LESB technique can organize effectively the flow field near endwall and improve the compressor performance. The LESB modeling with 15% span can improve the performances of 30% and 40% span at 0° and 5° incidence angles separately.