A TWO-LAYER ALGEBRAIC TURBULENCE MODEL FOR COMPRESSIBLE FLOW IN TURBOMACHINERY CASCADE

The objective of the present paper is to examine the Baldwin-Lomax turbu-lence model in a finite volume solver to introduce a computer code for complex two-dimensional flows in turbomachinery. The turbulent model was tested with investigating the turbulent flow over a flat plate and other test cases. Three test cases are presented and the computed results are compared with experimental data. The calculated velocity profile agreed well with the experimental data in plate test case and the solver is validated in test case of flow over a semi NACA-0012 airfoil. The good agreement of pressure distribution with experi-mental data, in turbulent flow around NACA-0012 airfoil with angle of attack, gives the robustness of the code and the implemented schemes in transonic flows with the existence of adverse pressure gradients and the interaction of shock and boundary layer. All the conditions studied in test cases may happen in a casca-de problem. As a final presentation of the solver capabilities the flow around a multi-blade stage of axial compressor is studied in two locations of rotor. The solver is used for flow through a multi-blade cascade of an axial compressor i