The 3-D loss distribution along axial turbomachines has been investigated in the present work. For this purpose, our well documented secondary flow calculation method has been interactively coupled with our fast blade-to-blade shear layer calculation code, in order to predict the complete secondary flow and profile loss distribution.
The presence of an even moderate secondary flow field modifies the flow angle distributions, thus making clear the need of a reliable profile loss prediction method for off-design cases, especially in the presence of separation.
Accordingly, the blade-to-blade code predicts the profile loss distribution and subsequently provides the correct total pressure field for the secondary flow calculation.
The combination of the above mentioned codes finally gives a realistic picture of the flow quantities at any S3 surface along a machine at a minimal computer cost.
Several test cases, including axial compressor and turbine cascades as well as transonic axial compressor blade rows have been investigated. The results are in good agreement with the experimental data and are favourably compared with various recent correlations.