Modelling and Simulation of Gas Turbine Blade with Different Geometrical Perforated Holes and Blade Materials: Software Analyses

Abstract

In the gas turbine, the power is generated at higher temperature and large magnitude, the results of which it generates lots of heat, so the cooling of turbine blade is very much required. Geometrical changes in the gas turbine blade as well as the changes in designs of turbine, which may be in the form of perforations, are required for the optimization and efficient cooling. In the present work, effects of perforations on the turbine blade have been studied for small jet engine gas turbine manufactured by Williams International for CJ1 (Cessna Citation Jet ) Model 525 engine by improving its geometry using the software called CATIA and also analyses at different boundary conditions by the analysis software called as ANSYS 14.0 workbench. Material of the turbine blade has also been optimized to improve performance of the gas turbine. After analyses, maximum temperature at tip i.e. 1050°C and minimum heat flux i.e. 509.99 W/m2 have been found for INCONEL-718 blade material without holes but the minimum temperature at tip i.e. 971°C and maximum heat flux i.e. 575.73 W/m2 have been achieved for NIMONIC-115 with holes which are good for gas turbine blade. In this research work NIMONIC-115 has been recommended as blade material and hole in the blade geometry has been suggested as improvement in the design of blade.