Abstract—Gas turbine blades have numerous applications in the aerospace industry. In this study, the stresses and deformations of a turbine were studied. The goal was to highlight the stress and deformation distribution to assist in the design of a blades. The stresses and deformations developed as a result of the blade operating conditions at high rotational speeds and thermal gradients were evaluated using two types of heat transfer modes-conduction and convection, taking into consideration the material behavior at elevated temperatures. The greatest stresses in the blades result from the thermal load caused by conduction, and they are located between the blades and disc. In addition an analytical method was used to evaluated and predict the stresses along the blades it gave a good estimate of the stress values compared to the finite element. It is important to design for as high temperatures gas as possible in order to attain a high thermal efficiency in gas turbines. In the case of power generating gas turbines, the increase of temperature leads to lower fuel consumption, reduced pollution and thus lower costs.

Index Terms—Fretting fatigue, Super alloy, Failure analysis, Elevated temperature

Cite: Rajni Dewangan, Jaishri Patel, Jaishri Dubey, Prakash Kumar Sen, and Shailendra Kumar Bohidar, "Gas Turbines Blades-A Critical Review of Failure on First and Second Stages," International Journal of Mechanical Engineering and Robotics Research, Vol. 4, No. 1, pp. 216-223, January 2015.