For the next generation of reusable launch vehicles, NASA is investigating introducing ceramic matrix composites (CMCs) in place of current superalloys for structural propulsion applications (e.g., nozzles, vanes, combustors, and heat exchangers). The higher use temperatures of CMCs will reduce vehicle weight by eliminating and/or reducing cooling system requirements. The increased strength-to-weight ratio of CMCs relative to superalloys further enhances their weight savings potential. However, in order to provide safe designs for components made of these new materials, a comprehensive life-prediction methodology for CMC structures needs to be developed.
A robust methodology for lifing composite structures has yet to be adopted by the engineering community. Current industry design practice continues to utilize deterministic empirically based models borrowed from metals design for predicting material life capabilities. The deterministic nature of these models inadequately addresses the stochastic character of brittle composites, and their empirical reliance makes predictions beyond the experimental test conditions a risky extrapolation.
A team of engineers at the NASA Glenn Research Center has been developing a new life-prediction engineering model. The Probabilistic Residual Strength (PRS) model uses the residual strength of the composite as its damage metric. Expected life and material strength are both considered probabilistically to account for the observed stochastic material response. Extensive experimental testing has been carried out on C/SiC (a candidate aerospace CMC material system) in a controlled 1000 ppm O2/argon environment at elevated temperatures of 800 and 1200 °C. The test matrix was established to allow observation of the material behavior, characterization of the model, and validation of the model's predictive capabilities. Sample results of the validation study are illustrated in the graphs.
Residual strength of C/SiC after 15 hr, 30 ksi, 1200 °C, 1000-ppm O2 exposure.
Long description.
Time to failure of C/SiC under 30 ksi, 1200 °C, 1000-ppm O2 exposure.
Long description.
Research in this area is ongoing with current efforts focusing on improving the representation of environmental effects within the PRS model. A testing program with SiC/SiC (a material proposed for aerocombustor and aerovane applications) in high-temperature air is also underway.
Verrilli, Michael J.; Calomino, Anthony; and Thomas, David J.: Stress/Life Behavior of a C/SiC Composite in a Low Partial Pressure of Oxygen Environment. I--Static Strength and Stress Rupture Database. Proceedings of the 26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A, American Ceramic Society, Westerville, OH, 2002, pp. 435-442.
Calomino, Anthony; Verrilli, Michael J.; and Thomas, David J.: Stress/Life Behavior of C/SiC Composites in a Low Partial Pressure of Oxygen Environment. II--Stress Rupture Life and Residual Strength Relationship. Proceedings of the 26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A, American Ceramic Society, Westerville, OH, 2002, pp. 443-451.
Thomas, David J.; Calomino, Anthony M.; and Verrilli, Michael J.: Stress/Life Behavior of C/SiC Composites in a Low Partial Pressure of Oxygen Environment. III--Life Prediction Using Probabilistic Residual Strength Model. Proceedings of the 26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: A, American Ceramic Society, Westerville, OH, 2002, pp. 453-460.
Ohio Aerospace Institute (OAI) contact: Dr. David J. Thomas, 216-433-5664, David.J.Thomas@grc.nasa.gov
Authors: Dr. David J. Thomas, Michael J. Verrilli, Dr. Anthony M. Calomino
Headquarters Program Office: OAT
Programs/Projects: UEET, NGLT
Last updated: January 20, 2005
Responsible NASA Official:
Gynelle.C.Steele@nasa.gov
216-433-8258
Point of contact for NASA Glenn's Research & Technology reports:
Cynthia.L.Dreibelbis@nasa.gov
216-433-2912
SGT, Inc.
Web page curator:
Nancy.L.Obryan@nasa.gov
216-433-5793
Wyle Information Systems, LLC
