14. Net Shape Manufacturing of Fabric Reinford Oxide/Oxide Components Via Resin Transfer Moulding and Pyrolysis

  1. Edgar Lara-Curzio and
  2. Michael J. Readey
  1. Bernhard Heidenreich1,
  2. Walter Krenkel1,
  3. Martin Frieß1 and
  4. Heiner Gedon2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470291191.ch14

28th International Conference on Advanced Ceramics and Composites B: Ceramic Engineering and Science Proceedings, Volume 25, Issue 4

28th International Conference on Advanced Ceramics and Composites B: Ceramic Engineering and Science Proceedings, Volume 25, Issue 4

How to Cite

Heidenreich, B., Krenkel, W., Frieß, M. and Gedon, H. (2004) Net Shape Manufacturing of Fabric Reinford Oxide/Oxide Components Via Resin Transfer Moulding and Pyrolysis, in 28th International Conference on Advanced Ceramics and Composites B: Ceramic Engineering and Science Proceedings, Volume 25, Issue 4 (eds E. Lara-Curzio and M. J. Readey), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470291191.ch14

Author Information

  1. 1

    DLR - German Aerospace Center Institute of Structures and Design Pfaffenwaldring 38-40 D-70569 Stuttgart

  2. 2

    WIWEB-Wehrwissenschaftliches Institut für Werk-Explosiv- und Betriebsstoffe Institutsweg 1 D-85435 Erding

Publication History

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

ISBN Information

Print ISBN: 9780470051528

Online ISBN: 9780470291191

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Keywords:

  • liquid polymer infiltratio;
  • oxide fibres;
  • aircraft turbine engines;
  • chemical resistance;
  • thermal barrier coating

Summary

CMC materials on the basis of oxide fibres and oxide matrices offer inherent oxidation stability and chemical resistance and therefore can be used for long term applications at high temperatures. For these materials, one of the most interesting fields of application are aircraft turbine engines, e. g. for thin-walled structures of hot gas liners.

The DLR developed a modified process for the manufacture of oxide/oxide-CMC on the basis of the liquid polymer infiltration (LPI). Hereby, dry preforms made of fibre fabrics were pressure infiltrated with polysiloxane precursors and cured via resin transfer moulding (RTM) and pyrolized. To demonstrate the feasibility of this process for the manufacture of complex CMC structures, an exemplary intake ramp for a propulsion system was developed. The intake ramp was made in a near net shape technique by manufacturing seven thin-walled, tubular profiles which were inseparably assembled during an in situ joining process. With this technique, a thin-walled, complex structure with outer dimensions of 265 mm x 110 mm x 35 mm and a low mass of only 0.4 kg could be realized. In this paper, the material properties and the construction and manufacturing of the intake ramp are presented.