Abstract: Gas turbines are used extensively for aircraft propulsion, land-based power generation, and industrial applications. The stress and displacement analysis of the rotor blade of any turbo machine in the field of design played a very important roll. Rotor blade is the very critical component in the field of turbo machines. The major cause of break down is due to different loadings such as fluid or gas forces and centrifugal forces are acting on the rotor blades. In this study, the first stage rotor blade of the gas turbine is created in SolidWorks software. The material of the blade is structural steel. This rotor blade has been analyzed by using ANSYS14.5. The gas forces namely tangential, axial were determined by constructing velocity triangles at inlet and exist of rotor blades. Three different models with different number of holes (5, 9 and 13) were analyzed to find out the optimum number of holes for good performance.