Abstract:

A new method is presented for calculating the ena-wan (?) lay(?) and the blade force defects inside the passage of axial compressor cascades based on associating boundary layer theory with secondary flow analysis in this paper. An integral equation of the boundary layer is used to calculate the longitudinal flow. Two layers of velocity modes are established to predict the transverse flow. An elliptic outer layer transverse flow associated with the secondary vorticity is computed by using differential method. The calculation is performed inside cascade passage, and conducted alternatively between the longitudinal flow and the transverse flow. The S-type transverse flow profiles are predicted automatically and accurately. Compared with experimental results, the predictions by this method show better agreement for two examples of heavily loaded cascades. It is apparent that this method is both practical and reliable. The bases are established for predicting the end wall boundary layers in multistage axial compressors in this paper.

Key words: axial compressor, cascades, end-wall boundary layer, blade force defect, secondary flow