Paper Title
Design And Thermal Analysis Of Gas Turbine Blade

Abstract
Gas turbines have an important role in electric power generation. Gas turbine technology is used in a variety of configurations for electric power generation. Turbine rotor blades are the most important components in a gas turbine power plant. Turbine blades are mainly affected due to static loads. Also the temperature has significant effect on the gas turbine rotor blades. This paper summarizes the design and steady state thermal analysis of gas turbine rotor blade, on which Cosmo software is used for deign of solid model of the turbine blade. ANSYS14.5 software is used for analysis of finite element model generated by meshing of the blade and design calculation is computed by using MATLAB software. The materials of the gas turbine rotor blade are chosen as copper, titanium and nickel. The existing turbine blade material is copper. The gas turbine rotor blade height is 0.0826m, rotor blade chord is 0.0645m, rotor blade thickness is 0.0129m and the numbers of gas turbine rotor blade are 92 blades. The gas turbine rotor blade inlet temperature is 1622C and rotor blade outlet temperature is 1478C. Total thermal heat flux of theoretical result for copper is 2.6453MW/, for titanium is 0.9927MW/m2 and for nickel is 1.9559MW/m2. Simulation result of total thermal heat flux for copper is 3.0060MW/m2, for titanium is 1.1503MW/m2 and for nickel material is 2.1810MW/m2. According to the comparison of the theoretical result and simulation result, titanium material has the least heat flux. So this material is better than the two other materials. Index terms Ansys14.5, Cosmo, gas turbine, rotor blade, steady state thermal analysis