摘要
The interaction between a shock wave and a boundary layer on a suction side of gas turbine profile,namely Transition Location Effect on Shock Wave Boundary Layer Interaction,was one of main objectives of TFAST project.A generic test section in a transonic wind tunnel was designed to carry out such investigations.The design criteria were to reproduce flow conditions on the profile in wind tunnel as the one existing on the suction side of the turbine guide vane.In this paper,the effect of film cooling and jet vortex generators on the shock wave boundary layer interaction and shock induced separation is presented.Numerical results for Explicit Algebraic Reynolds Stress Model with transition modeling are compared with experimental data.
基金
supported by the 7 EU framework project and was carried out within the research project with the acronym TFAST(Transition Location Effect on Shock Wave Boundary Layer Interaction)
supported by CI TASK
PL-Grid Infrastructure。
