Constituent development for higher temperature capable ceramic matrix composites
November 5-9, 2017
Two of the highest capability priorities for the Air Force, energy-efficient turbine engines and long-range precision strike require high-temperature CMCs to enable increased turbine engine efficiency and thermal protection of hypersonic vehicles. Ceramic-matrix composites (CMCs) currently lack the temperature capability and durability required for long-life at the highest temperatures desired. This presentation highlights research that is addressing the need for improved high-temperature-capable CMCs, with a focus on CMC constituents and an understanding of their processing, microstructure, and behavior in relevant service environments. The most pervasive lifetime and temperature limitations for SiC/SiC CMCs are related to oxidation, creep and stress rupture of the fibers, oxidation-induced instability of the fiber-matrix interface, and instability of the matrix at temperatures >1400°C. Consequently, we are addressing these shortcomings by developing technologies to enable higher-temperature capable SiC fibers, oxidation-resistant fiber-matrix interfaces, and improvements in processing of refractory matrices for both turbine engine and hypersonic applications.
Michael K. Cinibulk, "Constituent development for higher temperature capable ceramic matrix composites" in "Advanced Ceramic Matrix Composites: Science and Technology of Materials, Design, Applications, Performance and Integration", Yutaka Kagawa, Tokyo University of Technology, Japan Dongming Zhu, NASA Glenn Research Center, USA Ram Darolia, GE Aviation (retired), USA Rishi Raj, University of Colorado, Boulder, USA Eds, ECI Symposium Series, (2017). https://dc.engconfintl.org/acmc/45