Delamination cracking in thermal barrier coating (TBC) system is studied with the newly developed theoretical model. A semi-infinite long interface crack is pre-existing. The thermal stress and temperature gradient in TBC system are designated by a membrane stress P and a bending moment M. In this case, the effects of plastic deformation, creep of ceramic coating, as well as thermal growth oxidation and temperature gradient in TBC system are considered in the model due to the fact that these effects are considered in the calculation of thermal stress. The energy release rate, mode I and mode II stress intensity factors, as well as mode mixed measure ψ, are derived. The emphatic discussion about PSZ/Ni-alloy reveals that the TBC system may not fail in the form of coating delamination during the period of heat hold. However, the failure may be in the form of coating delamination during cooling or in the heating period during the second cycle or later cycles. The conclusion is consistent with the experimental observations. The delamination of ceramic coating is induced by the compressive load in the coating.
Delamination Cracking in Thermal Barrier Coating System
Contributed by the IGTI Technical Committee of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received by the IGTI Technical Committee July 2000; final revision received by the ASME Headquarters September 2001. Associate Editor: J. Conner.
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Zhou, Y. C., and Hashida, T. (September 24, 2002). "Delamination Cracking in Thermal Barrier Coating System ." ASME. J. Eng. Gas Turbines Power. October 2002; 124(4): 922–930. https://doi.org/10.1115/1.1477194
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