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Design and Coupled Field Analysis of First Stage Gas Turbine Rotor Blades

 

 

Abstract

A gas turbine is a device designed to convert the heat energy of fuel into useful work such as mechanical shaft power. The gas turbine in its most common from is a rotary heat engine operating by means of series of processes consisting of air taken from the atmosphere increase of gas temperature by constant pressure combustion of the fuel the whole process being continuous. Turbine Blades are the most important components in a gas turbine power plant. A blade can be defined as the medium of transfer of energy from the gases to the turbine rotor. The turbine blades are mainly affected due to static loads. Also the temperature has significant effect on the blades. Therefore the coupled (static and thermal) analysis of turbine blades is carried out using finite element analysis software ANSYS. It was observed that in the preliminary design, the rotor blades after being designed were analyzed only for the mechanical stresses but no evaluation of thermal stress was carried out.

            In this paper the first stage rotor blade of the gas turbine is created in CATIA V5 R17 software. The material of the blade is Ni-Cr alloys. This model has been analyzed using ansys11.0. The gas forces namely tangential, axial were determined by constructing velocity triangles at inlet and exist of rotor blades. The convective heat transfer coefficients were calculated using the heat transfer empirical relations taken from the heat transfer design dada book.  After containing the heat transfer coefficients and gas forces, the rotor blade was then analyzed using ANSYS 11.0 for the couple field (static and thermal) stresses.     

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eywords: Gas turbine blade, Structural and Thermal Analysis, Finite Element Analysis  

 

 

 

 

 


International eJournal of Mathematics and Engineering

Volume 3, Issue 3, Pages:  1603 - 1612