Abstract Gas turbines are extensively used for air craft propulsion, land based power generation and industrial applications. Thermal efficiency of a gas turbine can be improved by increasing turbine the rotor inlet temperature. The current rotor inlet temperature in advanced gas turbine is far above the melting point of blade material. So a sophisticated cooling system must be developed for continuous safe operation of gas turbines with high performance. Several methods have been suggested for the coolingof blades and one such technique is to have radial holes to pass high velocity cooling air along theblade span. The present work is carried out by performing the heat transfer analysis of gas turbine with four differentmodels consisting of blade with, without holes and blades with varying number of holes (5, 9&13). The analysis is carried out using commercial CFD software FLUENT. On evaluating the graphs drawnfor total heat transfer rate and temperature distribution, the blade with 13 holes is considered to be moreoptimum. The Steady state thermal and structural analysis is done using ANSYS software withdifferent blade materials such as Chromium steel and N155. While comparing the results, N155 has proved to have better thermal properties and also induced stresses are less than the Chromium steel.