Abstract
CMAS corrosion of turbine blades is a crucial failure in turbine engines and their components. In this study, oxide/oxide CMCs (AS-N610), which are candidates for gas turbine (GT) applications, are investigated for its corrosion behaviour at different temperatures and time in presence of CMAS. The corrosion studies using CMAS coating of the CMCs reveal that CMCs had a weight gain of ∼6% owing to formation of α-Al2O3 at 1000 °C. The SE image indicated the penetration of CMAS into the porous CMC. At 1000 °C, CMAS degraded to form a black glassy substance (Calcium alumino silicate) with traces of Mg which led to corrosion of the matrix. Indentation fracture toughness of the oxide/oxide CMCs was 7.78 ± 0.5 MPa m0.5 which degraded by ∼12% at 1000 °C after 10 h in the presence of CMAS. A mathematical model derived through diffusion equation indicated weight gain of ∼0.3 g which was closer to experimental data.
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