Abstract: Modal analysis has been important to the designers and operators since the inception of the Turbo machinery. Blades typically fail because of low-cycle fatigue (LCF), and high-cycle fatigue (HCF), environmental attack, Creep, Oxidation, erosion, embrittlement. In the present work the turbine blade is modeled and analyzed using finite element method the eigen value extraction for flexural and torsional modes is obtained. Foreign object damage is simulated by considering a circular crack along the leading edge of the blade. It was found that the stretching induced by the centrifugal inertia force due to the rotational motion of the blades was the cause for the increment of the bending stiffness of the structure. This resulted in maximum operational Vonmises stresses; the object is to provide understanding and information for designers to improve the life and efficiency of gas turbines.