• R.D.V.PRASAD
• M.Sailaja
• V.Raviteja Behera
• Yathish Ramena
• M.S.S.Srinivasa Rao

In the present work the gas turbine rotor blade has been analyzed for structural and thermal by using ANSYS13.0, which is powerful finite element software. In the process of getting the thermal stresses, 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. 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 detail study can be carried out on the temperature effects to have a clear understanding of the combined mechanical and thermal stresses. Cooling of gas turbine blades is a major consideration to improve their efficiency. Several methods have been suggested for the cooling of blades and one such technique is to have radial holes to pass high velocity cooling air along the blade span. The forced convection heat transfer from the blade to the cooling air will reduce the temperature of the blade to allowable limits. In the present work, Finite element analysis is used extensively to examine steady state thermal & structural performance of blades fabricated with Inconel X-750, Hastelloy X nickel-chromium alloys. Their suitability to withstand high temperature in the range of 12000C is studied. Further the effect of cooling on the thermal and structural behavior of the blade materials is also evaluated. Three different models consisting of holes and blade with 9, 13 numbers of holes was analysed. In this paper, an attempt has been made to analyse the cooling of a gas turbine blade made of Nickel based Super alloy through Mechanical analysis. The turbine rotor blade was analysed for Thermal stress, Deformation and Temperatures distribution.

Gas turbine, Temperature, stress, deformation, Thermal and structural analysis.

"Thermal and structural analysis of gas turbine blade cooling system with nickle-chromium alloy", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.5, Issue 5, page no.238-244, May-2018, Available :http://www.jetir.org/papers/JETIR1805639.pdf

"Thermal and structural analysis of gas turbine blade cooling system with nickle-chromium alloy", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.5, Issue 5, page no. pp238-244, May-2018, Available at : http://www.jetir.org/papers/JETIR1805639.pdf