Turbine blade failure in case of gas turbine engines is causing more concerns to the technological community, more importantly, when used in airplanes or as an alternative power generation in remote areas, in view of depleting fossil fuels. In this work, causes of blade failure for six different Nickel and Chromium based super alloys such as Inconel 738LC, Udimet 500, Rene 41, Inconel 625, MAR M246 and Inconel 718 are investigated by performing steady state thermal and structural analysis using Ansys 14.5. The solver is used to determine von Mises stress, von Mises strain and total deformation distribution of the turbine blade, by applying suitable boundary conditions. Centrifugal force is given, which is taken as a result of rotational, axial and tangential forces, that occurs due to the impingement of gases. Thermal load is given in the form of body temperature (900-1300°C), which is applied on the face of the gas turbine. The maximum deformation occurs at the tip of the blade and minimum at the root of the blade. Minimum stresses and strains are developed at the face of the blade. Udimet 500 is identified as the best suitable material for use as gas turbine blade as it shows lower deformation and strain developed for all temperatures.