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Failure Mechanisms of Coating Systems Applied to Advanced Turbine Components FREE

[+] Author Affiliations
Joseph A. Daleo

BWD Turbines Limited, Ancaster, ON, Canada

Donald H. Boone

BWD Turbines Limited, Walnut Creek, CA

Paper No. 97-GT-486, pp. V004T12A024; 15 pages
doi:10.1115/97-GT-486
From:
  • ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition
  • Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award
  • Orlando, Florida, USA, June 2–5, 1997
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7871-2
  • Copyright © 1997 by ASME

abstract

The maintenance period of critical gas turbine components operating in advanced D, E and F technology industrial turbines is often determined by the life of the coating system applied to protect the base alloy substrate. The progressively higher firing temperatures used in all of the advanced engine designs results not only in very high metal surface temperatures but also in very high temperature gradients and concomitant thermal stresses Induced in part by the complex cooling systems. In order to develop optimum component life strategies, it is important to establish the actual operating conditions of each component, and, to define the predominant degradation modes.

Metallurgical life assessment of these advanced component designs has identified several distinct coating/base metal failure mechanisms not generally encountered in earlier generation turbines, in addition to the more usual degradation modes, accelerated by the increases in temperature. A review and examples of these degradation mechanisms encountered on service exposed coating systems currently used by some of today’s major manufactures are presented.

Copyright © 1997 by ASME
This article is only available in the PDF format.

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