A secondary flow model and a method for calculating blade deviation angle have been developed for multistage axial flow compressors.This model is a modification of Adkins-Smith model.The secondary flow vorticities are modeled based on the cal culated meridional flow including different kinds of spanwise mixing effects.The secondary flows are obtained on the fanlike surface downstream the blade rows with a standard separation of variables approach which yields a complex series.The secondary flow model includes effects of blade passage vortex

blade trailing edge vortex

blade en d clearances

blade end shrouding

blade boundary layer and wake centrifugation.The deviation angles are related to the calculated cross passage secondary velocities and a modified Carter ’s rule.Good agreement has been obtained between experimental data and the calculated results in the cases of design-point-type applications for which significant regions of separated flow are not present.