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Industry tests of NASA ceramic thermal barrier coatingCeramic thermal barrier coating (TBC) system was tested by industrial and governmental organizations for a variety of aeronautical, marine, and ground-based gas turbine engine applications. This TBC is a two-layer system with a bond coating of nickel-chromium-aluminum-yttrium (Ni-16Cr-6Al-0.6Y, in wt. percent) and a ceramic coating of yttria-stabilized zirconia (ZrO2-12Y2O3, in wt. percent). Seven tests evaluated the system's thermal protection and durability. Five other tests determined thermal conductivity, vibratory fatigue characteristics, and corrosion resistance of the system. The information presented includes test results and photographs of the coated parts. Recommendations are made for improving the coating procedures.
Document ID
19790016852
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Liebert, C. H. (NASA Lewis Research Center Cleveland, OH, United States)
Stepka, F. S. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TP-1425
E-9846
Meeting Information
Meeting: Intern. Vacuum Metallurgy Conf.
Location: San Diego, CA
Country: United States
Start Date: April 23, 1979
End Date: April 27, 1979
Accession Number
79N25023
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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