次世代高温ガスタービン翼における熱伝達およびフィルム冷却に関する研究  [in Japanese] Study on Heat Transfer and Film Cooling for Next Generation High Temperature Industrial Gas Turbine Blades  [in Japanese]

Heat transfer coefficient and film cooling effectiveness on a rotating turbine blade have been studied by using a Low-Speed Research Turbine (LSRT) facility. The turbine model airfoils applied to LSRT were high loaded type suitable for next generation industrial gas turbines. The measurements of film cooling effectiveness on the platform have been conducted with pressure sensitive paint (PSP) technique. The horseshoe vortex, the passage vortex and the flow near the suction side of leading edge strongly influence heat transfer and film cooling around the inlet on the platform. They cause the increase of heat transfer and the decrease of film cooling effectiveness. In addition to the experimental works, this paper deals with CFD (Computational Fluid Dynamics) to predict the heat transfer coefficient around the turbine airfoil. The comparison between experimental results and the analytical one has been considered. The useful information to attain high performance cooling design for high reliability turbine blades has been obtained.