Investigation of loss model applicable to large range of high subsonic cascades in axial-flow compressor

A set of procedure which was used to calculate large range of cascades' S1 flow field in axial-flow compressor was developed, which based on the old estimated loss model of subsonic cascade and combined with the inviscid S1 field and boundary layer interactive calculation. The design point loss model was built by corrected camber ratio and maximum thickness. An overall working condition loss model of large range cascade was developed through cascade's scope of work. The paper also analysed the influence of axial velocity ratio in cascade experiment. The results show that S1 flow field procedure and modified loss model are able to predict design point loss coefficient, error of loss are less than 0.006 and 0.004. Off-design point loss model estimates loss incidence characteristic effectively by the corrected scope of work. The accuracy of the loss model for predicting large range of high subsonic cascades' loss coefficient is proved.