Published Paper Details:

The temperature of turbine blades in advanced gas turbines is above the melting point of the blade material. To ensure continuous safe operation of high- performance gas turbines, a cooling scheme must be developed. A radial hole to pass high velocity cooling air along the blade span is one of the suggested methods. In this project NACA 6409 airfoil is taking for turbine blade. Turbine blade is designed in CATIA V5R19 and for analysis we are using ANSYS 18.1 software. The turbine blades are cooled using convection cooling and radial holes to pass cooling air along the blade span. The heat transfer analysis of gas turbine with 6 different models consisting of No hole, 3, 5 and 7 inline one row of holes and compared with 7 and 9 models in staggered holes with different types of materials. Here we are using chromium steel, inconel-718 and inconel-625 as turbine blade material. CFD, Thermal and structural analysis is performing to determine the heat transfer rates, temperature distribution and stress of the blade.