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Load Axial force Centrifugal force Tangential force Coefficient of thermal expansion Moment Load Young's Modulus Moment Of Inertia Internal strain Energy External work done Displacement along X-direction Displacement along Y-direction Deflection Poisson's ratio Stress Stiffness matrix Strain Displacement matrix Nodal displacement Shape Function Length Diameter of shaft Bending, Twisting Moment RPM of turbine strain Torque transmitted by shaft approach Velocity theoretical exit velocity absolute air velocity Blade speed tangential component Area of throat Diameter of throat suffix for inlet, outlet conditions Power developed Thermal conductivity Convective heat transfer coefficient total mass of rotor blade density of gases Reynolds Number Nusselt number Prandtl number
In the present work the first stage rotor blade of a two stage gas turbine has been analyzed for structural, thermal, modal analysis using ANSYS 9.0.which is a powerful Finite Element Method[1–3] Software. The temperature distribution in the rotor blade has been evaluated using this software.
The design features of the turbine segment of the gas turbine have been taken from the preliminary design of a power turbine for maximization of an existing turbojet engine [8]. It was observed that in the above design, the rotor blades after being designed were analyzed only for the mechanical stresses but no evaluation of thermal stress was carried out. As the temperature has a significant effect on the overall stress on the rotor blades, it has been felt that a detail study can be carried out on the temperature effects to have a clear understanding of the combined mechanical and thermal stresses.
