The objective of this project is to design and stress analyze a gas turbine blade of a jet engine . An Investigation for usage of new materials is required. In the present work, turbine blade was designed with two different materials named as Inconel-718 & Titanium T-6.An attempt has been made to investigate effect of temperature, induced stresses on turbine blade. A Thermal analysis been carried out to investigate temperature flow. Structural analysis has been carried out to investigate various stresses of turbine blade developed due to coupling effect of thermal & centrifugal loads. An attempt as been made to suggest best materials for turbine blade by comparing obtained results.
Cooling of gas turbine blades is a major consideration because they are subjected to high temperature working conditions. Several methods have been suggested for the cooling of blades and one such technique is to have radial holes to pass high velocity cooling air along the blade span. The forced convection heat transfer from the blade to the cooling air will reduce the temperature of the blade to allowable limits. Finite element analysis is used in the present work to examine steady state thermal & structural performance.Four different models consisting of solid blade and blades with varying number of holes, were analyzed in this project to find out the optimum number of cooling hole. It is observed that as the number of holes increases the temperature distribution increases for cooling gas tubine blade.