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Potential benefits of a ceramic thermal barrier coating on large power generation gas turbineThermal barrier coating design option offers benefit in terms of reduced electricity costs when used in utility gas turbines. Options considered include: increased firing temperature, increased component life, reduced cooling air requirements, and increased corrosion resistance (resulting in increased tolerance for dirty fuels). Performance and cost data were obtained. Simple, recuperated and combined cycle applications were considered, and distillate and residual fuels were assumed. The results indicate that thermal barrier coatings could produce large electricity cost savings if these coatings permit turbine operation with residual fuels at distillate-rated firing temperatures. The results also show that increased turbine inlet temperature can result in substantial savings in fuel and capital costs.
Document ID
19770020550
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Clark, J. S.
(NASA Lewis Research Center Cleveland, OH, United States)
Nainiger, J. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
June 1, 1977
Subject Category
Energy Production And Conversion
Report/Patent Number
E-9251
NASA-TM-73712
ERDA/NASA-5022/77/1
Report Number: E-9251
Report Number: NASA-TM-73712
Report Number: ERDA/NASA-5022/77/1
Accession Number
77N27494
Funding Number(s)
CONTRACT_GRANT: E(49-28)-1028
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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