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Ceramic Composites Portend Long Turbopump Lives
ISSN: 0148-7191, e-ISSN: 2688-3627
Published April 01, 1993 by SAE International in United States
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Use of continuous fiber reinforced ceramic matrix composites (FRCMC) for turbopump hot section components offers a number of benefits. The performance benefits of increased turbine inlet temperature are apparent and readily quantifiable. Perhaps less obvious are the potential benefits of increased component life. At nominal turbopump operating conditions, FRCMC offer increased operating temperature margin relative to conventional materials. This results in potential for significant life enhancement. Other attributes (e.g., thermal shock resistance and high cycle fatigue endurance) of FRCMC provide even greater potential to improve life and reduce maintenance requirements.
Silicon carbide (Sic) matrix composites with carbon fibers (C/SiC) do not degrade when exposed to hydrogenrich steam for 10 hours at 1200°C. This FRCMC is resistant to thermal shock transients far in excess of those anticipated for advanced, high temperature turbomachinery. Orthogonal, two-dimensional (2D), plain woven, C/SiC also does not degrade when subjected to tensile-tensile fatigue at room temperature for 4×105 cycles at 75% of the ultimate strength. Runout at >106 cycles occurs for axial specimens subjected to fully reversed, strain controlled fatigue at ambient temperature and 0.3% strain.
CitationHerbell, T., Eckel, A., Brockmeyer, J., and Mitchell, M., "Ceramic Composites Portend Long Turbopump Lives," SAE Technical Paper 931372, 1993, https://doi.org/10.4271/931372.
- Strobl W., 1991 A Case for the Development of a New National Launch System Now AIAA/SAE/ASME/ ASEE 27th Joint Propulsion Conference Sacramento, CA, AIAA-91-2384
- Brockmeyer J. W., 1993 Ceramic Matrix Composite Applications in Advanced Liquid Fuel Rocket Engine Turbomachinery ASME, Journal of-Engineering for Gas Turbines and Power 115 1 58 63
- Misra A. K., 1990 Thermodynamic Analysis of Chemical Stability of Ceramic Materials in Hydrogen Containing Atmospheres NASA Contractor Report 4271, Sverdrup Technology Inc., Cleveland, OH
- Herbell T. P. Eckel A. J., Hull D. R., Misra A. K., 1991 Effect of Hydrogen on the Strength and Microstructure of Selected Ceramics Published in Environmental Effects on Advanced Materials, Jones R. H. Ricker R. E. Proceedings of Fall 1990 TMS/ASM Meeting, The Minerals, Metals and Materials Society 159 172
- Brockmeyer, J. W. Schnittgrund, G. D. 1990 Fiber-Reinforced Ceramic Matrix Composites for Earth-to- Orbit Rocket Engine Turbines Phase I Final Report, NASA Contractor Report 185264 Rocketdyne Div., Rockwell International Cop. Canoga Park, CA
- Brindley, W. J. Nesbitt, J. A. 1989 Durability of Thermal Barrier Coatings in a High Heat Flux Environment NASA TM 102336
- Eckel, A. J. Herbell, T. P. 1990 Thermal Shock of Fiber Reinforced Ceramic Matrix Composites Proceedings of the la Annual Conference on Composite Materials and Structures, NASA CP-3054 1 153 162