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Tensile Creep Behavior of Melt-Infiltrated SiC-SiC Composites for Gas Turbine Engine Applications

[+] Author Affiliations
Vijay V. Pujar

Goodrich Corporation, Brecksville, OH

Gregory N. Morscher

Ohio Aerospace Institute, NASA Glenn Research Center, Cleveland, OH

Paper No. GT2007-27491, pp. 261-266; 6 pages
doi:10.1115/GT2007-27491
From:
  • ASME Turbo Expo 2007: Power for Land, Sea, and Air
  • Volume 1: Turbo Expo 2007
  • Montreal, Canada, May 14–17, 2007
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4790-X | eISBN: 0-7918-3796-3
  • Copyright © 2007 by Goodrich Corporation and Ohio Aerospace Institute

abstract

SiC-SiC ceramic matrix composites (CMCs) manufactured by the melt-infiltration (MI) process are considered leading candidates for hot-section turbine engine components. MI composites consisting of different commercially available SiC fibers were fabricated and their room temperature and elevated temperature performance was evaluated. In this paper, results on the performance of composites under tensile creep conditions and the properties of these materials retained after creep are discussed. Specimens were subjected to 100-h creep tests at different stress levels. For samples that did not rupture during creep, retained tensile properties were measured after creep and compared to those on the as-produced samples. Interestingly, the after-creep specimens show higher 0.005% offset stresses (or matrix cracking strengths) relative to those in the as-produced materials, which is attributed to redistribution of stresses among the constituents during the tensile creep test. That is, the results show that the offset stresses in these materials can actually improve with use under tensile creep conditions, which is a desirable attribute for components of these materials for turbine engines.

Copyright © 2007 by Goodrich Corporation and Ohio Aerospace Institute

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