Numerical 3-D conjugate flow and heat transfer investigation of a transonic convection-cooled thermal barrier coated turbine guide vane

摘要

This paper presents a 3D-numerical investigation of the aerodynamics and aerothermics of a transonic convection-cooled vane with APS (atmospheric plasma spray) thermal barrier coating including the bond coat. The investigated ZrO{sub}2-coating has a thickness of 175 microns. The thermal barrier coating is bonded by a 60-micron MCrAlY-layer. Our numerical scheme developed calculates the fluid flow and heat transfer in a conjugate manner without having to derive any heat transfer data beforehand. The substrate material temperatures are lowered up to 22.8 K compared to the uncoated vane. The trailing edge is too thin to be cooled, so it is subjected to high thermal loads. In this area of the vane, the substrate material temperature is hardly influenced by the coating on both the pressure and the suction side.