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Potential use of ceramic coating as a thermal insulation on cooled turbine hardwareAn analysis was made to determine the potential benefits of using a ceramic thermal insulation coating of calcia-stabilized zirconia on cooled engine parts. The analysis was applied to turbine vanes of a high temperature and high pressure core engine and a moderate temperature and low pressure research engine. Measurements made during engine operation showed that the coating substantially reduced vane metal wall temperatures. Evaluation of the durability of the coating on turbine vanes and blades in a furnace and engine were encouraging.
Document ID
19760010053
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
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 3, 2013
Publication Date
February 1, 1976
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-3352
E-8557
Accession Number
76N17141
Funding Number(s)
PROJECT: RTOP 505-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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