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Evaluation of CVI SiC/SiC Composites for High Temperature ApplicationsSilicon carbide fiber reinforced silicon carbide (SiC/SiC) composites are candidate materials for various high temperature turbine engine applications because of their high specific strength and good creep resistance at temperatures of 1400 C (2552 F) and higher. Chemical vapor infiltration (CVI) SiC/SiC ceramic matrix composites (CMC) incorporating Sylramic-iBN SiC fiber were evaluated via fast fracture tensile tests (acoustic emission damage characterization to assess cracking behavior), tensile creep testing, and microscopy. The results of this testing and observed material behavior degradation mechanisms are reviewed.
Document ID
20170006628
Acquisition Source
Glenn Research Center
Document Type
Presentation
Authors
Kiser, D. (NASA Glenn Research Center Cleveland, OH United States)
Almansour, A. (NASA Glenn Research Center Cleveland, OH United States)
Smith, C. (NASA Glenn Research Center Cleveland, OH United States)
Gorican, D. (Vantage Partners, LLC Cleveland, OH, United States)
Phillips, R. (Vantage Partners, LLC Cleveland, OH, United States)
Bhatt, R. (Ohio Aerospace Inst. Cleveland, OH, United States)
McCue, T. (Science Applications International Corp. Cleveland, OH, United States)
Date Acquired
July 18, 2017
Publication Date
January 23, 2017
Subject Category
Composite Materials
Report/Patent Number
GRC-E-DAA-TN38830
Report Number: GRC-E-DAA-TN38830
Meeting Information
Meeting: Annual Conference on Composites, Materials, and Structures
Location: Cocoa Beach, FL
Country: United States
Start Date: January 23, 2017
End Date: January 26, 2017
Sponsors: NASA Headquarters
Funding Number(s)
WBS: WBS 109492.02.03.02.02
CONTRACT_GRANT: NNC13BA10B
CONTRACT_GRANT: NNC12BA01B
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
testing
acoustic emission
ceramic matrix composites
creep
oxidation
SiC/SiC

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