24. Mechanical Properties of Ceramic Matrix Composites Exposed to Rig Tests

  1. Edgar Lara-Curzio and
  2. Michael J. Readey
  1. G. Y. Richardson1,
  2. C. S. Lei1 and
  3. Raj N. Singh2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470291191.ch24

28th International Conference on Advanced Ceramics and Composites B: Ceramic Engineering and Science Proceedings, Volume 25, Issue 4

28th International Conference on Advanced Ceramics and Composites B: Ceramic Engineering and Science Proceedings, Volume 25, Issue 4

How to Cite

Richardson, G. Y., Lei, C. S. and Singh, R. N. (2004) Mechanical Properties of Ceramic Matrix Composites Exposed to Rig Tests, in 28th International Conference on Advanced Ceramics and Composites B: Ceramic Engineering and Science Proceedings, Volume 25, Issue 4 (eds E. Lara-Curzio and M. J. Readey), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470291191.ch24

Author Information

  1. 1

    U. S. Naval Air Station, Bldg. 2188, MS 05, Patuxent River, MD 20670-1908

  2. 2

    Department of Chemical and Materials Engineering University of Cincinnati, P. O. Box 210012, Cincinnati, OH 45241-0012

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2004

ISBN Information

Print ISBN: 9780470051528

Online ISBN: 9780470291191

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Keywords:

  • ceramic matrix composite;
  • composite coating protection system;
  • ceramics;
  • gas turbine engines;
  • goodrich corporation

Summary

Mechanical properties of a ceramic matrix composite (CMC) consisting of a SiC fiber reinforced carbon matrix with an external composite coating protection system is measured over a temperature range of 25°-1076°C (2000°F) in the as-fabricated state and subsequent to a variety of preconditioning treatments simulating applications as exhaust (afterburner) components in an aircraft engine. Two types of exposures are given to the as fabricated CMCs. In one case samples are exposed in a burner rig under conditions simulating thermal transients. In the second case as-fabricated CMCs are exposed to salt fog and then further exposed to the burner rig thermal transients. Composites when tested for strength and modulus after burner rig cycles showed an insignificant degradation in mechanical properties from values in the as-fabricated state. Samples exposed to just salt fog and tested for mechanical properties also did not show any discernable loss in properties. However, CMCs exposed to combined salt fog and burner rig transients displayed a slight (up to 15%) reduction in strength. These observations are explained from examinations of the fractured cross-sections by SEM/EDAX, and evidence of hot-corrosion induced cracking of the external coatings following salt fog and burner rig exposures, thereby slightly degrading the overall mechanical properties of the composites.