Title
Ceramic composites for high temperature aerospace structures and propulsion systems
Conference Dates
November 5-9, 2017
Abstract
The development of ceramic composites with optimized fiber architectures for application in hypersonics, turbine engines, and rocket nozzles will be discussed. The most extreme applications use active cooling, enabled by the use of thin textile-based hot skins that are able to tolerate extreme thermal gradients. They can also be formed into structures that enable other functionality, including transpiration and film cooling, mitigation of thermal stresses, and shape-morphing structures with potential use in combustion flow paths of hypersonic vehicles. The major challenges and strategies for realizing the potential of these ceramic composite structures will be discussed
Recommended Citation
David Marshall, Olivier Sudre, and Brian Cox, "Ceramic composites for high temperature aerospace structures and propulsion systems" 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/52