A thermal barrier coated (TBC) turbine component design system, including an accurate TBC life prediction model, is needed to realize the full potential of available TBC engine performance and/or durability benefits. The objective of this work, which was sponsored in part by NASA under the Hot Section Technology (HOST) Program (Contract NAS3-23944), was to generate a life prediction model for electron beam-physical vapor deposited (EB-PVD) zirconia TBC. Specific results include EB-PVD zirconia mechanical and physical properties, coating adherence strength measurements, interfacial oxide growth characteristics, quantitative cyclic thermal spallation life data, and a spallation life model.
Thermal Barrier Coating Life Prediction Model Development
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Meier, S. M., Nissley, D. M., Sheffler, K. D., and Cruse, T. A. (April 1, 1992). "Thermal Barrier Coating Life Prediction Model Development." ASME. J. Eng. Gas Turbines Power. April 1992; 114(2): 258–263. https://doi.org/10.1115/1.2906581
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