Ceramic matrix composites (CMCs) play an increasingly significant role in the modern aerospace industry due to their excellent high-temperature mechanical properties. Fatigue property at elevated temperature is an essential issue for their application, especially for the turbine blades subjected to cyclic loading under high temperature and high pressure conditions in the aircraft engines. A progressive damage approach was established to predict the damage initiation and evolution of braided SiC/SiC CMCs under tension-tension cyclic loading. The main framework was achieved via a user-material subroutine UMAT in ABAQUS with FORTRAN. Different initial damage criteria were introduced for fiber bundles, matrix and interface. Related experimental results revealed that the main reasons for the failure of composites under cyclic loading are the lost of bearing capacity of the matrix, the decrease of fiber strength in high-temperature oxidation environment and the interface wear. Hence, the stiffness and strength degradation of matrix and fiber bundles as well as the interfacial shear stress(ISS) reduction were used as the description of damage at different temperatures in this method. Subsequently, the numerical results were compared with relevant experimental results at 1100°C and 1300°C. It indicated that the stiffness degradation of composites with the increase of cycles in the simulation was in good agreement with that measured during the experiments. Additionally, the fatigue lives also exhibited an acceptable consistency.


A Damage-Based Fatigue Model of Braided Ceramic Matrix Composites at Elevated Temperature

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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