Document Type : Research Article

Authors

1 Assistant Professor, Department of Aerospace Engineering, Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran,

2 Department of Aerospace Engineering, Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran

3 Faculty of Graduate Studies, Shahid Sattari Aeronautical University of Science and Technology, Tehran, Iran

Abstract

The fixed and moving blades of turbines in the hot part of jet engines and turboshafts, due to bearing extreme stresses at high temperature, are constantly exposed to various damages and failures such as hot corrosion, oxidation, creep damage, erosion, fatigue foreign body damage, and cracking. On the other hand, one of the challenges engineers face in turbine engines is finding a way to estimate the lifetime of parts, especially their turbine blades. In this study, the numerical analysis of a sample of the first row of C20-250 engine turbine blades along with its thermal barrier coatings was performed in finite element ABAQUS software, and the distribution of stress and strain in the period was determined, and based on that, the areas with the maximum creep has been determined and then considering the rupture strain of the turbine blade, the blade creep life has been estimated. To validate the estimated lifetime of the turbine, the extracted numerical results have been compared with the experimental results of three turbine blade samples.

Keywords

Main Subjects