Modeling and studying a gas turbine blade under mechanical and thermal loads

One of the key elements in airplane’s jet engine is the blades of gas turbine, accordingly modeling and analyzing them can be beneficial. Pressure distribution on external surface and inertia force of rotation leads to three-dimensional distribution on turbine’s blades. Engines works in high temperature situations and since a large amount of air are suckedin high velocity, they face various damages which causes failure indifferent sections. In general, engines are comprised of four parts, which are fan, compressor, combustion chamber and turbine. Turbine is at the bottom of the engine and high temperature are passes through it while experiencing different loads. The method to study the stress distribution of the blade and its holder disk is finite element, which the Abaqus software is used in this paper

Keywords:

gas turbine , stress analysis , mechanical load , finite element method