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
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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