Published Paper Details:

In advanced gas turbines, the turbine blade operated temperature is for above the melting point of blade material. A cooling scheme must be developed for continuous safe operation of gas turbines with high performance. A vital role is played by the compressor on jet engine as it concerns about the initial compression on engine bleed system and aircraft cooling. Two types of compressor are used in jet engine and that is axial compressor and centrifugal compressor. Here we work on axial compressor. As its major application, gas turbine engines are in large use. In this project NACA6409, NACA6412 and NACA64012 airfoil is taking for turbine blade. Turbine blade is designed in CATIA V5R19 and for analysis we are using ANSYS 18.1 software. Here we are using chromium steel, inconel-718 and inconel-625 as turbine blade material. Thermal and structural analysis is performing to determine the heat flux, temperature distribution and stress of the blade. And finally conclude which material is better with blade.