Changes in flow field due to the presence of shock waves in axial compressors are examined in the present work. A simple but realistic model is used to predict the static pressure, the relative Mach number, the total pressure and the total temperature distributions through the shock region. These distributions are strongly affected by the interaction between the shock waves and the shear layers or the secondary flow field.
Our well documented secondary flow code along with our fast compressible shear layer calculation method are utilized in order to provide the necessary quantities of the viscous flow for the approximate shock-viscous flow interaction procedure. The shock induced losses, along with the increased shear layer or secondary flow losses, are also predicted.
The complete procedure is successfully applied to several test cases including separation. The results of the proposed method are compared with results of previous calculations and the available experimental data.
Finally, the flow field through the rotor of a supersonic compressor is thoroughly analyzed, and major conclusions concerning the modification of the secondary flow field due to the shock wave appearance are given.