www.tjprc.org SCOPUS Indexed Journal editor@tjprc.org NUMERICAL STUDY AND ANALYSIS OF GAS TURBINE BLADES NAWFEL M. BAQER, HAYDER H. KHALEEL & NOOR H. DHAHER Engineering Technical College / Najaf, Al- Furat Al-Awsat Technical University Al Najaf, Iraq ABSTRACT Gas turbine has great importance in the modern engineering applications, and it is the main element in the process of electric power generation. This paper presents a numerical analysis for gas turbine rotor blades to understand the behavior of gas turbine blades under the loads. The simulation was achieved by using solidworks 2018 and the numerical analysis by using ANSYS 15. Two materials were chosen to manufacture the gas turbine, which were Aluminum Alloy and Titanium Alloy under various values of load (5000,10000,15000)N to get many parameters such stress, total deformation, strain and shear stress. The results showed that by increasing the loads, all the values of obtained parameters were increased and it could be concluded that titanium alloy withstand the load more the aluminum alloy, and therefore it is recommended to use titanium alloy in manufacturing the gas turbine blades. KEYWORDS: Gas Turbine, Solid Works, ANSYS 15, Aluminum Alloy & Titanium Alloy Received: Mar 28, 2019; Accepted: Apr 18, 2019; Published: May 20, 2019; Paper Id.: IJMPERDJUN2019104 INTRODUCTION The gas turbine can be defined as a power plant to extract a large amount of mechanical power from the working fluid, with maximum efficiency. Gas turbine has a great role in the electric power generation, and by increasing the demand for power, the thermal efficiency of gas turbine and output power will be increased. A gas turbine is an engine that uses air as the working fluid and the fuel is continuously burnt with compressed air to produce a fast hot moving gas. Blades of gas turbine are the most important components, because they are subjected to high centrifugal tangential and axial forces during extracting energy from the high temperature and high pressure gases[1]. S. Gowreesh et.al [2] analyzed the design of the first stage rotor blade of a two stage gas turbine blade using by using finite elements analyzer software ANSYS. The evaluation of temperature field in the rotor blade was done and applied boundary conditions using this software model. The static loads and temperature had effect on the gas turbine blades. Theju V et.al [3] investigated the effect of temperature and induced stresses on jet engines turbine blade for two various materials titanium T-6 and inconel -718. It was observed that the titanium had a smaller value of deformation and lower strength. It was noticed that theInconel-718 has better thermal properties and higher strength compared with the titanium. Brahmaiah & Kumar [4] studied four various models of gas turbine blades with and without holes and analyzed the effect of changing the number of holes (5,9 and 13) on the blades behaviour. The structural analysis and steady state thermal were achieved by using ANSYS. The results of temperature distribution and transfer rate showed that the blade with 13 holes was considered as optimum. They had used two materials chromium steel and Inconel- 718 for their research, it was observed that the Inconel Original Article International Journal of Mechanical and Production Engineering Research and Development (IJMPERD) ISSN(P): 2249-6890; ISSN(E): 2249-8001 Vol. 9, Issue 3, Jun 2019, 959-966 © TJPRC Pvt. Ltd.