NDLI: Improving turbine performance with ceramic matrix composites

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Improving turbine performance with ceramic matrix composites

Content Provider	NASA Technical Reports Server (NTRS)
Author	DiCarlo, James A.
Copyright Year	2007
Description	Under the new NASA Fundamental Aeronautics Program, efforts are on-going within the Supersonics Project aimed at the implementation of advanced SiC/SiC ceramic composites into hot section components of future gas turbine engines. Due to recent NASA advancements in SiC-based fibers and matrices, these composites are lighter and capable of much higher service temperatures than current metallic superalloys, which in turn will allow the engines to operate at higher efficiencies and reduced emissions. This presentation briefly reviews studies within Task 6.3.3 that are primarily aimed at developing physics-based concepts, tools, and process/property models for micro- and macro-structural design, fabrication, and lifing of SiC/SiC turbine components in general and airfoils in particular. Particular emphasis is currently being placed on understanding and modeling (1) creep effects on residual stress development within the component, (2) fiber architecture effects on key composite properties such as design strength, and (3) preform formation processes so that the optimum architectures can be implemented into complex-shaped components, such as turbine vanes and blades.
File Size	1544069
Page Count	25
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20080005534
Archival Resource Key	ark:/13960/t3xt0ph1r
Language	English
Publisher Date	2007-10-31
Access Restriction	Open
Subject Keyword	Composite Materials Structural Design Ceramic Matrix Composites Turbine Blades Supersonics Heat Resistant Alloys Gas Turbine Engines Vanes Airfoils Engine Parts Residual Stress Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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