Abstract
This chapter illustrates an experimental study and its main results of the turbulent boundary layer carried out in a highly loaded transonic compressor cascade at various Mach and Reynolds numbers representative for real turbomachinery conditions. The emerging shock system generally interacts with the laminar boundary layer causing shock-induced separation with turbulent reattachment. Furthermore, the chapter explores the cascade inlet flow and turbulent boundary layer downstream of the shock system with a 3D hot-wire anemometry system, which provides detailed information about the turbulence structures as a data base for numerical code validation purposes. It also examines the flow field in the shock layer interaction region by using a 2D laser-two-focus (L2F) system. It is noted that the strong adverse pressure gradient imposed by the shock wave mainly influences the turbulence structure, for example, the turbulent kinetic energy and the Reynolds stresses inside the boundary layer. The impact of the pressure gradient is much distinctive for the longitudinal component and it is observed that the Reynolds shear stresses are often influenced by the wall curvature and history effects.
Published Version
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