Structural and thermal analysis of F class gas turbine compressor blade

In this study, the structural and thermal analysis of the final stage compressor rotor blades, which are known, performed by using ANSYS program. For that reason, 3D model of the existing compressor blade has been done. Later on, this model was transferred to the ANSYS program and analyzed. In the analysis, the parameters formed in the blade geometry were determined. By creating a design geometry with the selected parameters, the stress of the existing blade under operating conditions were examined. All external parameters in this study were taken from an F-class gas turbine operating under real field conditions. The stresses of the obtained values in different regions on the blade were examined. This study is also a reverse engineering study and the effects of real field conditions on the compressor blades have been analyzed. Before starting the analysis, general information about gas turbines have been presented. Gas turbines have been briefly introduced and then the basic operating principles of turbines have been explained. As it is known, gas turbines shaped based on thermodynamic principles. In this study, engineering thermodynamics in gas turbines briefly explained.