Experimental investigation of turbulence structures in a highly loaded transonic compressor cascade with shock/laminar boundary layer interactions

An experimental study of the turbulent boundary layer was carried out in a highly loaded transonic compressor cascade at various Mach- and Reynolds numbers representative for real turbomachinery conditions. The emerging shock system interacts with the laminar boundary layer causing shock-induced separation with turbulent reattachment. The cascade inlet flow and the turbulent boundary layer downstream of the shock system are investigated with a 3D hot-wire anemometry system. The flow field in the shock/boundary layer interaction region is examined by using a 2D Laser-Two-Focus (L2F) system. The strong adverse pressure gradient imposed by the shock wave mainly influence the turbulence structure, e.g. the turbulent kinetic energy and the Reynolds stresses inside the boundary layer.