Chapter 5. CMC Combustor Liner Design for a Model Ram Jet Engine

  1. Edgar Lara-Curzio and
  2. Michael J. Readey
  1. Tetsuya Morimoto,
  2. Shinji Ogihara,
  3. Hideyuki Taguchi,
  4. Takayuki Kojima,
  5. Kazuo Shimodaira,
  6. Keiichi Okai and
  7. Hisao Futamura

Published Online: 26 MAR 2008

DOI: 10.1002/9780470291184.ch5

28th International Conference on Advanced Ceramics and Composites A: Ceramic Engineering and Science Proceedings, Volume 25, Issue 3

28th International Conference on Advanced Ceramics and Composites A: Ceramic Engineering and Science Proceedings, Volume 25, Issue 3

How to Cite

Morimoto, T., Ogihara, S., Taguchi, H., Kojima, T., Shimodaira, K., Okai, K. and Futamura, H. (2004) CMC Combustor Liner Design for a Model Ram Jet Engine, in 28th International Conference on Advanced Ceramics and Composites A: Ceramic Engineering and Science Proceedings, Volume 25, Issue 3 (eds E. Lara-Curzio and M. J. Readey), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470291184.ch5

Author Information

  1. 1)Japan Aerospace Exploration Agency (JAXA) 7–44–1 Jindaiji Higashi-machi Chofu-shi Tokyo 182–8522 JAPAN

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2004

ISBN Information

Print ISBN: 9780470051498

Online ISBN: 9780470291184

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Keywords:

  • CMCs;
  • TBCC;
  • TSTO;
  • UBE;
  • JAXA

Summary

The development of high temperature resistant ceramic fibers has led to potential applications of ceramic matrix composites (CMCs) for aerospace engine components such as combustion chamber liner, turbine blade, and nozzle. the superior temperature capability of CMCs may then enable in the near future the turbine based combined cycle (TBCC) be the practical thruster for the launch system of two-stages to orbit (TSTO). the current study presents an engineering approach to design the CMC combustion liner for a model RAM jet engine that will be tested in supersonic wind tunnel. FEM thermal analyses have revealed with the thermal parameters of Tyrannohex and SA-Tyrannohex SiC/SiC composites (UBE Industry Co., UBE Japan) the maximum heat flux through the combustor liner implying the limitation in the engine operation.