NDLI: Thermal and environmental barrier coating development for advanced propulsion engine systems

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Thermal and environmental barrier coating development for advanced propulsion engine systems

Content Provider	NASA Technical Reports Server (NTRS)
Author	Zhu, Dongming Miller, Robert A. Fox, Dennis S.
Copyright Year	2008
Description	Ceramic thermal and environmental barrier coatings (TEBCs) are used in gas turbine engines to protect engine hot-section components in the harsh combustion environments, and extend component lifetimes. Advanced TEBCs that have significantly lower thermal conductivity, better thermal stability and higher toughness than current coatings will be beneficial for future low emission and high performance propulsion engine systems. In this paper, ceramic coating design and testing considerations will be described for turbine engine high temperature and high-heat-flux applications. Thermal barrier coatings for metallic turbine airfoils and thermal/environmental barrier coatings for SiC/SiC ceramic matrix composite (CMC) components for future supersonic aircraft propulsion engines will be emphasized. Further coating capability and durability improvements for the engine hot-section component applications can be expected by utilizing advanced modeling and design tools.
File Size	4929896
Page Count	21
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20080012571
Archival Resource Key	ark:/13960/t3dz5768b
Language	English
Publisher Date	2008-01-01
Access Restriction	Open
Subject Keyword	Aircraft Propulsion And Power Life Durability Gas Turbine Engines High Temperature Engine Parts Thermal Stability Heat Flux Carbon-silicon Carbide Composites Supersonic Aircraft Thermal Control Coatings Supersonic Airfoils Ceramic Coatings Propulsion Thermal Conductivity Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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