Design and Computational Study of Gas Turbine Blades Cooling

The objective of this paper is to study the heat transfer problem in a gas turbine blade to give the optimum cooling. Various techniques have been proposed for the cooling of blades and one such technique is to have axial holes along the blade span. Cooling of blades has been a major concern since they are in a high temperature environment. In a high temperature gas turbine, turbine blade cooling designs require key technologies. Gas Turbine Blade Model is created using Gambit, mesh is created using CFD (Fluent) software, to perform the flow analysis. k-e turbulence model is used for this analysis. Three models(6,8,12) with Titanium-Aluminum alloy and Nickel-Chromium alloy were analyzed to find out the optimum number of holes for better cooling rate, better material with temperature distribution. To determine cooling rate of gas turbine blade with different holes and different materials. Cooling rate of gas turbine blade with temperature distribution for different materials is 20%.Graphs are plotted for velocity, pressure and temperature distribution for existing design. When the numbers of holes are increased in the blade, the temperature distribution falls down.