Title: Design and Analysis of Aero Turbine Disc by FEA
Abstract:The gas turbine 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.The aer...The gas turbine 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.The aero engine works on the phenomena of gas turbine. The deformation and fracture of gas turbine parts like turbine disc which are subjected to high temperature and other mechanical loads, depends mainly on temperature and time and hence due to creep. The objective of this paper is to highlight the stress and deformation distribution to assist in the design of a disc as well as to demonstrate the importance of using finite element (FE) analysis in simulating an actual design case. Then, to present the real model, a three dimensional (3D) axisymmetric model for a non-uniform disc was analyzed using FE analysis. The stresses and deformations developed as a result of the disc operating conditions at high thermal gradients were evaluated using conduction heat transfer modes taking into consideration the material behavior at elevated temperatures. A model is created with the help of software CATIA V5 and transient thermal and structural analysis are performed in ANSYS 16.0 work bench. An attempt is made to suggest best material for a turbine disc to be used as high pressure and low pressure combustion stages by comparing the results obtained for three different materials (Super alloy A286, Inconel 718 and Udimet 720). Based on the plots and results Udimet 720 and Inconel 718 are best suited as high pressure turbine to use at first stage of combustion and gives advantage over Super alloy A286. Results also suggest that Inconel 718 and Super alloy A286 are suitable for turbine disc material to be use at later stages of combustion.Read More