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Thermal Strain Tolerant Abradable Thermal Barrier Coatings PUBLIC ACCESS

[+] Author Affiliations
T. E. Strangman

Allied-Signal Aerospace Company, Phoenix, AZ

Paper No. 91-GT-039, pp. V005T13A002; 5 pages
doi:10.1115/91-GT-039
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

Thermal barrier coatings (TBCs) are applied to hot gas path surfaces to reduce metal temperatures and thermal stresses for improved turbine component durability. Improvements in engine performance are achieved when TBCs enable reductions in cooling air usage and turbine blade tip-shroud clearances.

This paper describes the development of thick TBCs with superior strain tolerance. A pattern of grooves or slant steps incorporated into the surface to be coated enables the development of shadow gaps in the ceramic layer during plasma spray deposition. These gaps segment the TBC, permitting ceramic-metal thermal expansion mismatch and thermal strains to be accommodated by free expansion.

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

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