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Hydrocarbon-fuel/copper combustion chamber liner compatibility, corrosion prevention, and refurbishmentAn evaluation is made of combustion product/combustion chamber compatibility in the case of a LOX/liquid hydrocarbon booster engine based on copper-alloy thrust chamber which is regeneratively cooled by the fuel. It is found that sulfur impurities in the fuel are the primary causes of copper corrosion, through formation of Cu2S; sulfur levels as low as 1 ppm can result in sufficiently severe copper corrosion to degrade cooling channel performance. This corrosion can be completely eliminated, however, through the incorporation of an electrodeposited gold coating on the copper cooling-channel walls.
Document ID
19910057106
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rosenberg, S. D.
(Aerojet-General Corp. Sacramento, CA, United States)
Gage, M. L.
(Aerojet-General Corp. Sacramento, CA, United States)
Homer, G. D.
(Aerojet-General Corp. Sacramento, CA, United States)
Franklin, J. E.
(Aerojet, Propulsion Div., Sacramento CA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 91-2213
Accession Number
91A41729
Funding Number(s)
CONTRACT_GRANT: NAS3-25070
Distribution Limits
Public
Copyright
Other

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