Abstract

Cooling of gas turbine blades are major attention to high temperature working conditions. Numerous methods have been recommended for the cooling of blades and a unique technique is to be used to ensure radial holes to pass high velocity cooling air along the blade span. The forced convection heat transfer from the blade to the cooling air, it will reduce the temperature of the blade to permissible limits. Finite element analysis is used in the present work to examine steady state thermal andamp structural performance for stainless steel. Four different models comprising of solid blade and blades with varying number of holes 7, 8, 9 andamp 10 holes were evaluated in this project to find out the optimum number of cooling hole. It is observed that as the number of holes increases the temperature distribution will be increased consequently. The structural analysis is carried out after the thermal analysis in SOLID WORKS SIMULATION TOOL. It is observed that blade with 10 holes has showing more stresses than the remaining blades. Finally the blade with 9 holes has giving optimum performance for prescribed loading conditions with average temperature of 513.9 K, heat flux of 3.118 W m2 at the trailing edge and von misses stresses as 17.67 MPa. K Vidya Sagar | Dr. N. Mahesh Kumar | P. Siva Ram "Design and Structural Thermal Analysis of Gas Turbine Rotor Blade with Radial Holes using Solidworks" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-3 | Issue-1 , December 2018, URL: http://www.ijtsrd.com/papers/ijtsrd19077.pdf

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