Abstract
AbstractThe current status of thermal barrier coatings (TBGs) is reveiewed with reference to gas turbine applications. The principal methods of TBC deposition are outlined and failure processes based on thermomechanical stress effect, bond coat oxidation, corrosion of constituents of the ceramic, and eroswn are described. The performance of TBG systems in engine trials is described and correlated wlth the various degradation processes and experimental data.
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