Abstract
The main objective of the current investigation is to determine numerically and experimentally the failure mechanisms of a cobalt-based superalloy X-45 used as a gas turbine vane. A numerical study was performed through the finite element method using ABAQUS software to determine temperature distribution as well as thermal stress induced by the thermal gradient in the vane segments. In addition, experimental studies were performed to study the effect of service-induced microstructural changes in the vane body through optical microscopy and also scanning electron microscopy. Furthermore, microhardness of the specimen was carried out to determine the effect of thermal stress on different zones of the vane. Finally, it was found that the vane was failed as a result of different failure mechanisms including cyclic thermal stress, oxidation, high-temperature corrosion and more importantly phases transition of primary carbides (M6C) to secondary ones (M23C6), due to high-temperature operations.
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