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Thermal and Environmental Barrier Coatings for Advanced Turbine Engine ApplicationsCeramic thermal and environmental barrier coatings (T/EBCs) will play a crucial role in advanced gas turbine engine systems because of their ability to significantly increase engine operating temperatures and reduce cooling requirements, thus help achieve engine low emission and high efficiency goals. Advanced T/EBCs are being developed for the low emission SiC/SiC ceramic matrix composite (CMC) combustor applications by extending the CMC liner and vane temperature capability to 1650 C (3000 F) in oxidizing and water vapor containing combustion environments. Low conductivity thermal barrier coatings (TBCs) are also being developed for metallic turbine airfoil and combustor applications, providing the component temperature capability up to 1650 C (3000 F). In this paper, ceramic coating development considerations and requirements for both the ceramic and metallic components will be described for engine high temperature and high-heat-flux applications. The underlying coating failure mechanisms and life prediction approaches will be discussed based on the simulated engine tests and fracture mechanics modeling results.
Document ID
20050160251
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Zhu, Dong-Ming
(Army Research Lab. Cleveland, OH, United States)
Miller, Robert A.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
March 1, 2005
Subject Category
Nonmetallic Materials
Report/Patent Number
E-14972
NASA/TM-2005-213437
Meeting Information
Meeting: 2004 Fall Meeting
Location: Boston, MA
Country: United States
Start Date: November 29, 2004
End Date: December 3, 2004
Sponsors: Materials Research Society
Funding Number(s)
WBS: WBS 22-714-20-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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