Computational analysis of the influences of guide ribs/vanes on enhanced heat transfer of a turbine blade tip-wall
Gas turbine blade tips encounter large heat load as they are exposed to the high temperature gas. A common way to cool the blade and its tip is to design a serpentine passage with 180-deg turns under the blade tip-cap inside the turbine blade. Improved internal convective cooling is therefore required to increase the blade tip lifetime. In this paper, turbulent fluid flow and heat transfer through
