Modelling and Multi-Disciplinary Analysis of Aero Engine Turbine Blade

Abstract

Abstract Turbine blades in gas turbines convert thermal to mechanical energy, driving the compressor and producing thrust. Their design and materials ensure efficiency under extreme heat, pressure, and centrifugal forces. CATIA V5 is used to Modelling of Aero Engine Turbine Blade & ANSYS Workbench is used for Structural & Modal analysis. The Structural analysis is done for 5 materials: -Udimet 500, Mar M247, Rhenium, Inconel 738, Magnesium ZA80. Structural analysis is carried out by applying rotational velocity to entire blade & fixing the root of the blade. The Thermal analysis is done for 5 materials: - Udimet 500, Mar M247, Rhenium, Inconel 738, Magnesium ZA80. By applying Convection for Leading Edge, Heat flow for Pressure side & fixed temperature for root of the blade As a result, the Rhenium has a least deformation (0.8906 mm), least stress (752.87 Mpa), least strain (0.0041), Maximum temperature resistance of 2461.6°C & best heat dissipation efficiency of 2.9822 W/mm2 compare to other 4 materials. The modal analysis is done only for Rhenium materials because is has good in structural & thermal properties compare to another materials. The modal analysis is carried out by fixing the root of the blade.