Chapter 26. Design and Development of a CMC Interturbine Seal

  1. John B. Wachtman Jr
  1. P. K. Khandelwal1 and
  2. W. D. Wildman2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470314715.ch26

Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures - A: Ceramic Engineering and Science Proceedings, Volume 16, Issue 4

Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures - A: Ceramic Engineering and Science Proceedings, Volume 16, Issue 4

How to Cite

Khandelwal, P. K. and Wildman, W. D. (1995) Design and Development of a CMC Interturbine Seal, in Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures - A: Ceramic Engineering and Science Proceedings, Volume 16, Issue 4 (ed J. B. Wachtman), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470314715.ch26

Author Information

  1. 1

    Allison Engine Company P. O. Box 420, Speed Code W-05 Indianapolis, Indiana 46206-0420

  2. 2

    Allison Engine Company P. O. Box 420, Speed Code S-49 Indianapolis, Indiana 46206-0420

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 1995

ISBN Information

Print ISBN: 9780470375372

Online ISBN: 9780470314715

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Keywords:

  • ARPA;
  • thermomechanical;
  • eccentricities;
  • transients;
  • labyrinth

Summary

An Allison AE 3007 turbofan engine interturbine seal has been selected by the ARPA funded LC3 program to develop and demonstrate the feasibility of the RTM process to fabricate and engine test a structurally sound 3-D braided Nextel™ 312/Blackglas™ component. Preliminary finite element heat transfer and stress analysis of the seal was conducted using the predicted thermomechanical properties of 2-D Nicalon™ and Nextel™ 312 reinforced Blackglas™ composites and a typical engine duty cycle. Heat transfer analysis indicated the maximum operating temperature to be 649°C with a maximum thermal gradient of 24°C. The maximum principal stresses were calculated for both CMC systems in the hoop, radial, and axial direction using finite element analysis (FEA). The maximum stress of 37.9 MPa was determined to be in the axial direction for both the material systems. The total equivalent stress was 54.5 MPa with a maximum strain of 0.1168 mm/mm.