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Tests of NASA ceramic thermal barrier coating for gas-turbine enginesA two-layer thermal barrier coating system with a bond coating of nickel-chromium-aluminum-yttrium and a ceramic coating of yttria-stabilized zirconia was tested for corrosion protection, thermal protection and durability. Full-scale gas-turbine engine tests demonstrated that this coating eliminated burning, melting, and warping of uncoated parts. During cyclic corrosion resistance tests made in marine diesel fuel products of combustion in a burner rig, the ceramic cracked on some specimens. Metallographic examination showed no base metal deterioration.
Document ID
19790011947
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Liebert, C. H. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1979
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-79116
E-9846-1
Report Number: NASA-TM-79116
Report Number: E-9846-1
Meeting Information
Meeting: Intern. Conf. on Met. Coatings
Location: San Diego, CA
Country: United States
Start Date: April 23, 1979
End Date: April 27, 1979
Accession Number
79N20118
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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