Design and Analysis of Aero Turbine Disc by FEA

Abstract

A gas turbine, also called a combustion turbine, is a type of internal combustion engine obtains its power by utilizing the energy of burnt gases and the air which is at high temperature and pressure by expanding through the several rings of fixed and moving blades mounted over a disc. The major function of the turbine is to extract energy from the hot gas flow to drive the compressor and the accessory gearbox. Gas turbine discs work mostly at high temperature gradients and are subjected to high rotational velocity. High speed results in large centrifugal forces in discs and simultaneous high temperature results in thermal stress. The stress which greatly influence the design of turbine disc is the thermal stress. Thus a model of H.P turbine is created using CATIA V5 and the exported to ANSYS 16.0 to perform transient thermal analysis. The thermal analysis performed with three different materials i.e. SUPERALLOY A286, INCONEL 718, and UDIMET 720. The comparison of all material will result in better use of turbine disc material at different stages of combustion.