Journal
JOURNAL OF THE AMERICAN CERAMIC SOCIETY
Volume 97, Issue 9, Pages 3004-3011Publisher
WILEY
DOI: 10.1111/jace.13017
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Funding
- Air Force Office of Scientific Research (AFOSR) Young Investigator Program Award [FA9550-10-1-0189]
- National Science Foundation Early Faculty Career Award under Division of Materials Research grant [0954110]
- AFOSR-Multidisciplinary University Research Initiative Program Award [FA9550-10-1-0563]
- Direct For Mathematical & Physical Scien
- Division Of Materials Research [0954110] Funding Source: National Science Foundation
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Carbon-carbon (C-C) composites are ideal for use as aerospace vehicle structural materials; however, they lack high-temperature oxidation resistance requiring environmental barrier coatings for application. Ultra high-temperature ceramics (UHTCs) form oxides that inhibit oxygen diffusion at high temperature are candidate thermal protection system materials at temperatures >1600 degrees C. Oxidation protection for C-C composites can be achieved by duplicating the self-generating oxide chemistry of bulk UHTCs formed by a composite effect upon oxidation of ZrB2-SiC composite fillers. Dynamic Nonequilibrium Thermogravimetric Analysis (DNE-TGA) is used to evaluate oxidation in situ mass changes, isothermally at 1600 degrees C. Pure SiC-based fillers are ineffective at protecting C-C from oxidation, whereas ZrB2-SiC filled C-C composites retain up to 90% initial mass. B2O3 in SiO2 scale reduces initial viscosity of self-generating coating, allowing oxide layer to spread across C-C surface, forming a protective oxide layer. Formation of a ZrO2-SiO2 glass-ceramic coating on C-C composite is believed to be responsible for enhanced oxidation protection. The glass-ceramic coating compares to bulk monolithic ZrB2-SiC ceramic oxide scale formed during DNE-TGA where a comparable glass-ceramic chemistry and surface layer forms, limiting oxygen diffusion.
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