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Ceramic Composites for Rocket Engine Turbines
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English
Abstract
Use of ceramic materials in the hot section of the fuel turbopump of advanced reusable rocket engines promises increased performance and payload capability, improved component life and economics, and greater design flexibility. Severe thermal transients present during operation of the Space Shuttle Main Engine (SSME) push metallic components to the limit of their capabilities. Future engine requirements may be even more severe. In Phase I of this two Phase program, performance benefits have been quantified and continuous fiber reinforced ceramic matrix composite (FRCMC) components have demonstrated a potential to survive the hostile environment of an advanced rocket engine turbopump
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Citation
Herbell, T. and Eckel, A., "Ceramic Composites for Rocket Engine Turbines," SAE Technical Paper 911108, 1991, https://doi.org/10.4271/911108.Also In
References
- Brockmeyer J.W. Schnittgrund G.D. “Fiber-Reinforced Ceramic Composites for Earth-to-Orbit Rocket Engine Turbines,” Rocketdyne Division, Rockwell International Corp. NASA Lewis Contract NAS3-25468, Phase I-Final Report July 1990
- Holloway G.D. Eskridge R. Singh R. Ward S. “Fiber-Reinforced Ceramic Composites for Earth-to-Orbit Rocket Engine Turbines,” GE Aircraft Engines NASA Lewis Contract NAS3-25467, Phase I-Final Report, NASA CR-185290 July 1990
- Chandler W.T. “Materials for Advanced Rocket Engine Turbopump Turbine Blades,” Rockwell International Corp. NASA Lewis Contract NAS3-23536, Final Report NASA CR-174729 November 1983