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Thermal Barrier Coating Life Prediction Model Development PUBLIC ACCESS

[+] Author Affiliations
Susan Manning Meier, David M. Nissley, Keith D. Sheffler

Pratt & Whitney, East Hartford, CT

Thomas A. Cruse

Vanderbilt University, Nashville, TN

Paper No. 91-GT-040, pp. V005T13A003; 7 pages
doi:10.1115/91-GT-040
From:
  • ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation; Education; IGTI Scholar Award; General
  • Orlando, Florida, USA, June 3–6, 1991
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7902-3
  • Copyright © 1991 by ASME

abstract

A thermal barrier coated (TBC) turbine component design system, including an accurate TBC life prediction model, is needed to realize the full potential of available TBC engine performance and/or durability benefits. The objective of this work, which was sponsored in part by NASA under the Hot Section Technology (HOST) Program (Contract NAS3-23944), was to generate a life prediction model for electron beam - physical vapor deposited (EB-PVD) zirconia TBC. Specific results include EB-PVD zirconia mechanical and physical properties, coating adherence strength measurements, interfacial oxide growth characteristics, quantitative cyclic thermal spallation life data, and a spallation life model.

Copyright © 1991 by ASME
This article is only available in the PDF format.

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