Investigating the Effect of Wear on the Creepage Life of Jet Engine Turbine Blades Model 250-C20

The stationary and rotating blades of jet engines and turboshaft turbines, particularly in the hot section, are subjected to extreme stresses at high temperatures. Consequently, they are constantly exposed to various forms of damage and failure, including hot corrosion, oxidation, creep damage, erosion, fatigue, foreign object damage, and cracking. A key challenge in turbine engine maintenance is the accurate estimation of the lifespan of critical components, particularly turbine blades. This study used finite element analysis in ABAQUS software to conduct a numerical analysis of a first-row turbine blade from the C20-250 engine, including its thermal barrier coatings. The stress and strain distribution over the operational period were determined, highlighting the areas most susceptible to creep failure. Based on the rupture strain of the turbine blade material, the creep life of the blade was estimated. The numerical results were compared with experimental data from three turbine blade samples to validate the estimated creep life. These findings provide crucial insights for predictive maintenance strategies, enhancing the durability and cost-effectiveness of turbine engines.