Modulation of Vane Shocks with Pulsating Coolant Flows

This paper demonstrates the ability of pulsating coolant flows to actively control shock waves. The pulsating coolant is fed into the base region of a supersonic turbine airfoil. This implementation results additionally on an alternative management strategy of the base pressure. The shocks strength modulation and adjustment of the base pressure represent viable options to reduce the aerothermal loss in a vane row, and the aero-structural coupling with a downstream blade row. A scaled model derived from a real cooled high-pressure inlet guide vane has been experimentally investigated at the von Karman Institute, in an isentropic compression tube facility at engine representative (Mach numbers 0.8 - 1.2 and Reynolds numbers of 4 – 6 million). URANS simulations of the cascade were performed at the University of Florence with a second order accurate scheme.