Systematic experimental investigations of the transonic flow through a plane cascade consisting of profiles designed for a highly loaded gas turbine rotor of a high pressure stage were performed. The experiments comprise side wall pressure distribution measurements in a blade passage and both profile pressure distribution and wake traverse measurements in various planes from midspan to the side wall. The parameters varied are the inlet flow angle and the downstream Mach number. Schlieren photopraphs and oil flow patterns on the blades and on the side wall are included. The experimental results are interpreted with respect to the existing flow models describing shock wave boundary layer interactions and secondary flow effects. The experimental data are compared with three-dimensional viscous numerical results.

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