Abstract
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.
Highlights
In the last decades, great attention has been paid and development has been done to maintain laminar boundary layer in many applications [1,2,3]
An aerothermal impact of AJVG in a linear turbine cascade under the influence of film cooling at different Mach and Reynolds numbers is presented in Ref. [6]
Shock wave boundary layer interaction and induced separation on the suction side of turbine blade is affected by the existing film cooling
Summary
Great attention has been paid and development has been done to maintain laminar boundary layer in many applications [1,2,3]. In the recent High Pressure (HP) gas turbine stages, highly loaded aerofoils are applied. In such cascades, transonic and even supersonic flow zones exist. The transition location effect on the shock wave boundary layer interaction, namely Transition Location Effect on Shock Wave Boundary Layer Interaction, was one of the objectives of the TFAST EU project Such interaction on highly loaded gas turbine profile with film cooling was the objective of one work package. An investigation of jet vortex generators application upstream of the shock wave to trip boundary layer and to reduce the separation was carried out. Flow structure in turbomachinery cascades, if applied film cooling, is complex and the application of (air) jet vortex generators (AJVG) requires careful consideration. An aerothermal impact of AJVG in a linear turbine cascade under the influence of film cooling at different Mach and Reynolds numbers is presented in Ref. [6]
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