Chapter 39. Design of CMC Inlet Vane for a Model Air Breathing Engine

  1. Waltraud M. Kriven and
  2. Hua-Tay Lin
  1. Tetsuya Morimoto

Published Online: 26 MAR 2008

DOI: 10.1002/9780470294826.ch39

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

Morimoto, T. (2003) Design of CMC Inlet Vane for a Model Air Breathing Engine, 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.ch39

Author Information

  1. National Aerospace Laboratory of JAPAN, 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 2003

ISBN Information

Print ISBN: 9780470375846

Online ISBN: 9780470294826

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Keywords:

  • fundamental component;
  • ceramic matrix composites;
  • aerodynamic configuration;
  • fuel cooling;
  • breathing engines

Summary

An air breathing engine (ABE) is a fundamental component in several concept designs of two-stage to orbit (TSTO) type reusable space vehicles. One of the challenges of the ABE design is to utilize ceramic matrix composites (CMCs) components for the high temperature sections. In particular, the inlet strut vane approaches the stagnation point temperature, although the aerodynamic configuration conditions the cooling.

This study outlines a design concept of CMC air inlet for a model ABE, which will be evaluated in supersonic wind tunnel tests. FEM temperature analyses are made on CMC and fuel cooling concept designs applying the thermal conductivity data of Tyrannohex SiC/SiC composite.