Heat Transfer Analysis of Gas Turbine Rotor Blade Cooling Through Staggered Holes using CFD

Abstract

In a gas turbine engine, the turbine blade operated higher temperature then the melting point of the blade material. Cooling of gas turbine blades is a major consideration for continuous safe operation of gas turbines with high performance. 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. In the present work CFD analysis is used to examine the heat transfer analysis of gas turbine with six different model consisting of 5,9&13 inline one row of holes and compared with 9&13 model in staggered holes arranged in the three rows and developed a new model with 14 holes in the staggered arrangement. The prediction is commonly used CFD software FLUENT (a turbulence realizable k-e model with enhanced wall treatment). On evaluating the contour plot of the pressure, velocity& velocity vector we found that the temperature distribution on the 13 staggered holes, uniformly distributed along the blade area, as compared to 13 inline holes. And the heat transfer is also increases in the 13 & 14 staggered holes arrangements.