Three dimensional low Mach number film cooling of turbine blade have been conducted using computational fluid dynamics (CFD) software FLUENT. Strong anisotropic of film cooling turbulence and flow complexities require capable turbulence model such as Reynolds Stress Model (RSM) or Large Eddy Simulation (LES) model to solve film cooling flow field. Film cooling with holes arrangement on blade leading edge, pressure and suction were tested in present study. The effects of film cooling parameters such as blowing ratio, surface curvature, injection angle, hole spacing, hole length, and plenum geometry have been investigated. The results presented in adiabatic film cooling effectiveness as well as plots of temperature and velocity contour. Present study reveals that blowing ratio, injection angles and coolant holes arrangements are significant parameters in film cooling process. Performances of film cooling highly depend on a combination of parameters. Present study represents the feasibility of CFD utilization as an innovative predictive tool in turbine blade film cooling design
