In the study and prediction of the development of fatigue cracks in highly loaded elements of energy machines, knowledge of the mechanism of fracture of materials has a key role. This knowledge includes various models of nucleation and development of cracks, models of the formation of the trajectory of the crack front, and also models of local fracture. The choice of the crack formation mechanism of one type or another is determined by the stress state (including the level of stress amplitudes) in the local volume of material of interest for the part under study. Models of cracking and fracture of the material allow us to estimate the magnitude of local stresses in a self-organized system of transformation and change in the energy of the elements of the structural interaction of the material. One of the reasons affecting the performance and resource of the working blades of gas turbines is the formation of cracks on the surface of the feather blades. The aim of this work is to study the laws of the process of crack development on the surface of a turbine blade by calculation methods using the Ansys Mechanical package.