MODEL ANALYSIS OF LP-1 IN738 GAS TURBINE BLADE

Abstract

As gas turbines become the integral part of the current power plant, automobile, medical, aerospace, defense, space craft, ships, submarines, missiles etc. hence the need of their care arises, as they drive these costlier systems very effectively. Here in this work we discussed the various causes of failure of gas turbine blade due to various reasons and found that most of the gas turbine failure associated with turbine blade which further associated with fatigue failure of the turbine blade. As these fatigue failure generally causes by vibration of the system components and specifically turbine blade, hence here we are concerned about determining the modal parameters for gas turbine blade and also the damping factor of blade by experimental modal analysis and computational modal analysis. But first we validated our experimental modal analysis results with computational modal analysis results with the help of a cantilever beam and determining the variation, on the basis of that we doing the same analysis on gas turbine blade and will be able to evaluating the modal parameters of gas turbine blade. Modal parameters of turbine blade are required because the vibration of the blade can be reduced by adding damper to the blade with appropriate damping so that the system remains in underdamping situation and life of the blade can be improved. If time permits we will apply damper coating to the blade then evaluating its modal parameters, else we will add this for future work. In order to evaluate all modal parameters of gas turbine blade and damping factor we have to use NV Gate 8.30 with OROS 36 vibration analyser for experimental modal analysis and ANSYS 15.0 version for computational modal analysis.