23. Post Engine Test Characterization of Self Sealing Ceramic Matrix Composites for Nozzle Seals in Gas Turbine Engines

  1. Manuel E. Brito,
  2. Peter Filip,
  3. Charles Lewinsohn,
  4. Ali Sayir,
  5. Mark Opeka and
  6. William M. Mullins
  1. E. Bouillon1,
  2. C. Louchet1,
  3. P. Spriet1,
  4. G. Ojard2,
  5. D. Feindel2,
  6. C. Logan2 and
  7. K. Rogers2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470291283.ch23

Developments in Advanced Ceramics and Composites: Ceramic Engineering and Science Proceedings, Volume 26, Number 8

Developments in Advanced Ceramics and Composites: Ceramic Engineering and Science Proceedings, Volume 26, Number 8

How to Cite

Bouillon, E., Louchet, C., Spriet, P., Ojard, G., Feindel, D., Logan, C. and Rogers, K. (2005) Post Engine Test Characterization of Self Sealing Ceramic Matrix Composites for Nozzle Seals in Gas Turbine Engines, in Developments in Advanced Ceramics and Composites: Ceramic Engineering and Science Proceedings, Volume 26, Number 8 (eds M. E. Brito, P. Filip, C. Lewinsohn, A. Sayir, M. Opeka and W. M. Mullins), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470291283.ch23

Author Information

  1. 1

    SNECMA Propulsion Solide 33187 Le Haitian, FRANCE

  2. 2

    Pratt & Whitney 400 Main Street East Hartford, CT 06108 T. Arnold SNECMA Moteurs, Villaroche 77550 Moissy-Cramayel FRANCE

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2005

ISBN Information

Print ISBN: 9781574982619

Online ISBN: 9780470291283

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Keywords:

  • ceramic;
  • composites;
  • temperatures;
  • carbides;
  • photographic

Summary

The advancement of self-sealing ceramic matrix composites offers durability improvements in hot section components of gas turbine engines. These durability improvements come with no need for internal cooling and with reduced weight. Building on past material efforts, ceramic matrix composites based on either a carbon fiber or a SiC fiber with a sequenced self-sealing matrix have been developed for gas turbine applications. The specific application being pursued on this effort is an F100-PW-229 nozzle seal. Ground engine testing has been done to full design life for some seals. One material system has been tested to 150% of design life. The ground testing has demonstrated a significant durability improvement from the baseline metal design. Residual properties are being determined for both systems by extracting tensile and microstructural coupons from the ceramic matrix composite seal. This was done as a function of design life. Nondestructive interrogation was used as a guide in setting cutting diagrams. The results from this effort will be presented.