Abstract
The failure of a gas turbine blade, made of a nickel-base superalloy GTD-111, was studied by metallurgical approaches. The turbine has been operating for around 73,500 h before the blade failure. As a result of the blade failure, the turbine was damaged rigorously. The analysis began with a comprehensive visual examination of the turbine and the blades’ exteriors. Afterward, the examination was continued by fractography of the fracture surfaces, microstructural examinations, and chemical analysis. Fracture was found to occur by micro-cracks spreading on the leading edge as the result of hot corrosion from overheating, together with precipitation of continuous grain boundary carbides. The overheating was resulted from blockage of air channels of the blade as a consequence of improper filtration of inlet compressor air.
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