Chapter 40. Testing and Characterization of CMC Combustor Liners

  1. Waltraud M. Kriven and
  2. Hua-Tay Lin
  1. R. Craig Robinson1 and
  2. Michael J. Verrilli2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470294826.ch40

27th Annual Cocoa Beach Conference on Advanced Ceramics and Composites: B: Ceramic Engineering and Science Proceedings, Volume 24, Issue 4

27th Annual Cocoa Beach Conference on Advanced Ceramics and Composites: B: Ceramic Engineering and Science Proceedings, Volume 24, Issue 4

How to Cite

Robinson, R. C. and Verrilli, M. J. (2003) Testing and Characterization of CMC Combustor Liners, in 27th Annual Cocoa Beach Conference on Advanced Ceramics and Composites: B: Ceramic Engineering and Science Proceedings, Volume 24, Issue 4 (eds W. M. Kriven and H.-T. Lin), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470294826.ch40

Author Information

  1. 1

    QSS Group, Inc., NASA Glenn Research Center, Cleveland, OH 44135

  2. 2

    NASA Glenn Research Center, Cleveland, OH 44135

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2003

ISBN Information

Print ISBN: 9780470375846

Online ISBN: 9780470294826

SEARCH

Keywords:

  • annular designs;
  • simulated gas turbine;
  • ceramic matrix composites;
  • thermal stress;
  • gas velocities

Summary

Multiple combustor liner applications, both segmented and fully annular designs, have been configured for exposure in NASA's High Pressure Burner Rig (HPBR). The segmented liners were attached to the rig structure with SiC/SiC fasteners and exposed to simulated gas turbine conditions for nearly 200 hours. Test conditions included pressures of 6 atm., gas velocity of 42 m/s, and gas temperatures near 1450°C. The temperatures of both the cooled and combustionflow sides of the liners were measured using optical and contact measurement techniques. Minor weight loss was observed, but the liners remained structurally sound, although damage was noted in some fasteners.