Chapter 50. Ceramic Composite Turbine Engine Component Evaluation

  1. John B. Wachtman Jr
  1. W. R. Fohey,
  2. J. M. Battison and
  3. T. A. Nielsen

Published Online: 26 MAR 2008

DOI: 10.1002/9780470314715.ch50

Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures - A: Ceramic Engineering and Science Proceedings, Volume 16, Issue 4

Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures - A: Ceramic Engineering and Science Proceedings, Volume 16, Issue 4

How to Cite

Fohey, W. R., Battison, J. M. and Nielsen, T. A. (1995) Ceramic Composite Turbine Engine Component Evaluation, in Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures - A: Ceramic Engineering and Science Proceedings, Volume 16, Issue 4 (ed J. B. Wachtman), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470314715.ch50

Author Information

  1. Williams International, Walled Lake, MI 48390; Capt. S. Hastings, WL/MLLM, WPAFB, OH 34433

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 1995

ISBN Information

Print ISBN: 9780470375372

Online ISBN: 9780470314715

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Keywords:

  • turbine;
  • fabrication;
  • considerable;
  • baseline;
  • coefficients

Summary

Four different fiber reinforced ceramic matrix composite combustor sets were designed, fabricated and tested to demonstrate their utility in limited life gas turbine engines. Materials evaluated included: General Atomics C/Si3N4, Dow Corning/Kaiser Aerotech SiC/SiNC and DuPont Lanxide Composites SiCF&P/Al2O3 D1MOX (Directed Metal OXidation) and HPZ/SiC. Fabrication methods included isothermal and thermal gradient CVI, polymer pyrolysis and DIMOX. Material properties were evaluated for all four materials, with limited testing being done to the SiCF&P /Al2O3 material. The four material systems were fabricated into combustor sets (primary and cover plate) and engine tested in a WR24-7 test bed gas turbine engine for a combined run time of 74 hours and 36 minutes at material surface temperatures between 1093°C and 1482°C, at the writing of this abstract.