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Journal of Materials for Energy Systems

, Volume 1, Issue 4, pp 47–58 | Cite as

Thermal barrier coatings: Burner rig hot corrosion test results

  • Philip E. Hodge
  • Stephan Stecura
  • Michael A. Gedwill
  • Isidor Zaplatynsky
  • Stanley R. Levine
Article

Abstract

A Mach 0.3 burner rig test program was conducted to examine the sensitivity of thermal barrier coatings to Na and V contaminated combustion gases simulating potential utility gas turbine environments. Coating life of the standard ZrO2-12Y2O3/Ni-16.2Cr5.6Al-0.6Y (composition in weight percent unless stated otherwise) NASA thermal barrier coating system which was developed for aircraft gas turbines was significantly reduced in such environments. Two thermal barrier coating systems, Ca2SiO4/Ni16.2Cr-5.6Al-0.6Y and ZrO2-8Y2O3/Ni-16.4Cr-5.1Al-0.15Y and a less insulative cermet coating system, 50 vol pct MgO-50 vol pct Ni-19.6Cr-17.1Al-0.97Y/Ni16.2Cr-5.6Al-0.6Y, were identified as having much improved corrosion resistance compared to the standard coating.

Keywords

Bond Coat Thermal Barrier Coating Coated Specimen Bond Coating Thermal Barrier Coating System 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© American Society for Metals 1980

Authors and Affiliations

  • Philip E. Hodge
    • 1
  • Stephan Stecura
    • 1
  • Michael A. Gedwill
    • 1
  • Isidor Zaplatynsky
    • 1
  • Stanley R. Levine
    • 1
  1. 1.National Aeronautics and SpaceAdministrationLewis Research CenterCleveland

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