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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Y. Xie, M. Wang, G. Zhang, and M. Chang, “Analysis of superalloy turbine blade tip cracking during service,” Eng. Fail. Anal., 13, No. 8, 1429–1436 (2006).
M. R. Khajavi, M. H. Shariat, “Failure of first stage gas turbine blades,” Eng. Fail. Anal., 11, No. 4, 589–597 (2004).
F. Starr, N. Wood, and R. Robertson, “Investigation of hot salt corrosion at a land-based gas turbine installation,” J. Phys. IV France, 03, C9-779–C9-786 (1993).
A. K. Koul, J. P. Immarigeon, R. V. Dainty, and P. C. Patnaik, “Degradation of high performance aero-engine turbine blades,” in: V. P. Swaminathan and N. S. Cheruvu (Eds.), Advanced Materials and Coatings for Combustion Turbines, Published by ASM International, Materials Park, OH (1994), pp. 69–74.
The authors would like to thank the R&D center of MAPNA group for their support.
*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
- failure analysis
- type II hot corrosion
- hot corrosion fatigue
- gas turbine