Crack development in gas turbine blades is a vital feature to be regulated in most of the power and aerospace industries since it significantly impacts the turbine blade's natural frequency and stress distribution. Furthermore, the investigation is necessary to extend the turbine's operational life by removing the possibility of resonance. In this regard, a cloud point model for turbine blades is created first, followed by a detailed study to investigate blade crack formation and its impact on natural frequency and stress distribution. The blade's stiffness decrease is accounted for by the slow propagation of material abnormality/crack in ANSYS utilizing five separate models based on the Block Lanczos method. The results are formulated by removing the number of elements in a sequential order (starting from 0 to 4) from the blade model to obtain subsequent natural frequency and stress distribution for ten vibration modes. As the crack propagates, both the natural frequency and the stress concentration decrease. Furthermore, both of these are closely related to the mode of vibrations. Based on the assessment, it is noted that the proposed model analysis gives a viable approach to significantly handle the operational barriers of the gas turbine in the industrial sector.

Keywords: Model Analysis, Turbine Blade, Crack formation, Natural Frequency, Stress Distribution