Chapter 46. Residual Stresses in Thermal Barrier Coatings for a Cu–8Cr–4Nb Substrate System

  1. Hau-Tay Lin and
  2. Mrityunjay Singh
  1. Louis J. Ghosn1 and
  2. Sai V. Raj2

Published Online: 26 MAR 2008

DOI: 10.1002/9780470294758.ch46

26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: B: Ceramic Engineering and Science Proceedings, Volume 23, Issue 4

26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: B: Ceramic Engineering and Science Proceedings, Volume 23, Issue 4

How to Cite

Ghosn, L. J. and Raj, S. V. (2008) Residual Stresses in Thermal Barrier Coatings for a Cu–8Cr–4Nb Substrate System, in 26th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures: B: Ceramic Engineering and Science Proceedings, Volume 23, Issue 4 (eds H.-T. Lin and M. Singh), John Wiley & Sons, Inc., Hoboken, NJ, USA. doi: 10.1002/9780470294758.ch46

Author Information

  1. 1

    Ohio Aerospace Institute 21000 Brookpark Rd. Cleveland, Ohio 44135

  2. 2

    NASA Glenn Research Center 21000 Brookpark Rd. Cleveland, Ohio 44135

Publication History

  1. Published Online: 26 MAR 2008
  2. Published Print: 1 JAN 2002

ISBN Information

Print ISBN: 9780470375792

Online ISBN: 9780470294758

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Keywords:

  • thermal barrier coatings;
  • residual stresses;
  • substrate system;
  • rocket engine environment;
  • plasma spraying

Summary

Analytical calculations were conducted to determine the thermal stresses developed in a coated copper-based alloy, Cu–8%(at.%)Cr–4%Nb (designated as GRCop–84), after plasma spraying and during heat-up in a simulated rocket engine environment. Finite element analyses were conducted for two coating systems consisting of a metallic top coat, a pure copper bond coat and the GRCop–84 The through the thickness temperature variations were determined as a function of coating thickness for two metallic coatings, a Ni–17%(wt%)Cr–6%Al–0.5%Y alloy and a Ni–50%(at.%)Al alloy. The residual stresses after low-pressure plasma spraying of the NiCrAlY and NiAl coatings on GRCop–84 substrate were also evaluated. These analyses took into consideration a 50.8 μm copper bond-coat and the effects of an interface coating roughness. The through the thickness thermal stresses developed in coated liners were also calculated after 15 minutes of exposure in a rocket environment with and without an interfacial roughness.