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Thermal barrier coating life prediction model developmentA 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, 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.
Document ID
19920032899
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Meier, Susan M. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Nissley, David M. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Sheffler, Keith D. (Pratt and Whitney Group East Hartford, CT, United States)
Cruse, Thomas A. (Vanderbilt University Nashville, TN, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Mechanical Engineering
Report/Patent Number
ASME PAPER 91-GT-40
Accession Number
92A15523
Funding Number(s)
CONTRACT_GRANT: NAS3-23944
Distribution Limits
Public
Copyright
Other

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