Chapter 18. Cyclic Rig and Engine Testing of Ceramic Turbine Components

  1. William J. Smothers
  1. D. W. Richerson,
  2. K. M. Johansen,
  3. P. M. Ardans and
  4. K. P. Johnson

Published Online: 26 MAR 2008

DOI: 10.1002/9780470318782.ch18

Proceedings of the 6th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 3, Issue 9/10

Proceedings of the 6th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 3, Issue 9/10

How to Cite

Richerson, D. W., Johansen, K. M., Ardans, P. M. and Johnson, K. P. (1982) Cyclic Rig and Engine Testing of Ceramic Turbine Components, in Proceedings of the 6th Annual Conference on Composites and Advanced Ceramic Materials: Ceramic Engineering and Science Proceedings, Volume 3, Issue 9/10 (ed W. J. Smothers), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470318782.ch18

Author Information

  1. Garrett Turbine Engine Co. 113 S. 34th St., P.O. Box 5217, Phoenix, AZ 85281

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 1982

ISBN Information

Print ISBN: 9780470373972

Online ISBN: 9780470318782

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Keywords:

  • porcelain enameling;
  • distortion;
  • decarburized;
  • formability;
  • metalloid

Summary

Cyclic testing of ceramic components in the DARPA/Navy Ceramic Engine Demonstration Program was limited by contact-stress problems in the static structure. These problems were resolved by redesign of the turbine hot section under the AFWAL Ceramic Components for Turbine Engines Program, and the ceramic static-structure components were successfully rig tested under severe cyclic conditions at average turbine-inlet temperatures >1260°C. In a follow-on DARPA/Navy effort, a ceramic-bladed rotor was incorporated in a cooled, metal turbine engine and successfully operated under similar severe cyclic conditions at an average turbine-inlet temperature >1200°C.