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Thermal response of various thermal barrier coatings in a high heat flux rocket engineTraditional APS ZrO2-Y2O3 thermal barrier coatings (TBCs) formed by air plasma spraying and low pressure and air plasma sprayed ZrO2-Y2O3/NiCrAlY cermet coatings were tested in an H2-O2 rocket engine. The test cycle was approximately 1.2 s at 1400 C in a hydrogen-rich environment. During testing, the maximum metal temperature without a coating was 1310 C. The traditional ZrO2-Y2O3 TBCs with a 100-125 micron thick ceramic layer reduced the maximum metal temperature by approximately 350 C. Increasing the ceramic layer thickness to 200-225 microns resulted in an additional metal temperature reduction of 100 C. However, the cermet coatings, consisting of a ceramic and metal mixture, exhibited a much lower thermal protection capability by reducing the maximum metal temperature by approximately 100 C. It was also found that the surface roughness of the traditional TBCs had little effect on the thermal response.
Document ID
19920049775
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nesbitt, J. A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1990
Subject Category
Metallic Materials
Meeting Information
Meeting: International Conference on Metallurgical Coatings
Location: San Diego, CA
Country: United States
Start Date: April 2, 1990
End Date: April 6, 1990
Accession Number
92A32399
Distribution Limits
Public
Copyright
Other

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