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Investigation of the effect of ceramic coatings on rocket thrust chamber lifeCylindrical rocket thrust chamber cylinders were coated with a 0.203 mm (0.008 in.) layer of zirconium oxide using a process that employed electrodeposition of metal to a spray coated mandrel. The cylinders were cyclically tested using hydrogen oxygen propellants at a nominal chamber pressure of 4.14 MN/sq m (600 psia) to show the effect of the coating on life. Both cylinders failed prematurely due to causes unrelated to the coatings. Post destructive analysis showed no cooling passage wall deformation. Where erosion of the coating occurred, the coating thickness stabilized at 0.061 mm (0.0024 in.) within 80 cycles and remained well adhered throughout the tests.
Document ID
19780018230
Document Type
Conference Paper
Authors
Quentmeyer, R. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Kasper, H. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Kazaroff, J. M.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-78892
E-9630
AIAA PAPER 78-1034
Meeting Information
Meeting: Propulsion Conf.
Location: Las Vegas, NV
Country: United States
Start Date: July 25, 1978
End Date: July 27, 1978
Sponsors: Soc. of Automotive Engr., AIAA
Accession Number
78N26173
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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