Thermo-Fluid Investigation on the Effect of Rotation on Film Cooling Performace at Pressure & Suction Side of the Leading-Edge of a Gas Turbine Blade

Numerical study investigation has been performed to investigate the effects of the rotation on the film cooling effectiveness distributions of the leading-edge regions of a gas turbine blade. The Study was carried out at Re=100,000, Density Ratio of 1.5, 2 and 2.5, blowing ratio of M=1. The leading edge model has three rows of film cooling holes located along the stagnation line 0° and at ±30° respectively. The Realizable K-ε has been used for modeling of turbulence. After validation of numerical result of current study, five Rotaion number of 0.12, 0.24, 0.36, 0.48 and 0.6 have been selected and analyzed for investigation of relational influence on film cooling effectiveness. The results demonstrates at pressure side (PS) of the leading edge, the film cooling effectiveness increases and at suction side (SS) decreases with increasing of Rotation number. With growing of Rotaion number from 0.12 to 0.6, area-averaged film cooling effectiveness increases from 0.38 to 0.46 at pressure side (PS) and reduces monotonously about 26% at suction side (SS) of leading edge. Moreover increasing of Density Ratio from 0.15 to 0.25 has a increases of 45% on overall area-averaged film cooling effectiveness