The failure analysis of a broken blade with 25,000 EOH of operation has been carried out. The complementary analysis that consists of metallurgical and fractography techniques have been employed. The results of fractography proved that the cracks initiated from hot corrosion pits on the airfoil and propagated by hot corrosion fatigue mechanism and led to blade fracture.
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The authors would like to thank the R&D center of MAPNA group for their support.
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*Paper presented at the International Scientific Conference Fatigue and Thermofatigue of Materials and Structural Components (Kiev, 2013).
Translated from Problemy Prochnosti, No. 5, pp. 35 – 40, September – October, 2014.
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Asadikouhanjani, S., Torfeh, M. & Ghorbanf, R. Failure Analysis of a Heavy Duty Gas Turbine Blade*. Strength Mater 46, 608–612 (2014). https://doi.org/10.1007/s11223-014-9589-8
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DOI: https://doi.org/10.1007/s11223-014-9589-8