Functionally gradient materials for thermal barrier coatings in advanced gas turbine systems

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Description

New designs for advanced gas turbine engines for power production are required to have higher operating temperatures in order to increase efficiency. However, elevated temperatures will increase the magnitude and severity of environmental degradation of critical turbine components (e.g. combustor parts, turbine blades, etc.). To offset this problem, the usage of thermal barrier coatings (TBCs) has become popular by allowing an increase in maximum inlet temperatures for an operating engine. Although thermal barrier technology is over thirty years old, the principle failure mechanism is the spallation of the ceramic coating at or near the ceramic/bond coat interface. Therefore, it is ... continued below

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7 p.

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Banovic, S.W.; Chan, H.M. & Marder, A.R. December 31, 1995.

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Description

New designs for advanced gas turbine engines for power production are required to have higher operating temperatures in order to increase efficiency. However, elevated temperatures will increase the magnitude and severity of environmental degradation of critical turbine components (e.g. combustor parts, turbine blades, etc.). To offset this problem, the usage of thermal barrier coatings (TBCs) has become popular by allowing an increase in maximum inlet temperatures for an operating engine. Although thermal barrier technology is over thirty years old, the principle failure mechanism is the spallation of the ceramic coating at or near the ceramic/bond coat interface. Therefore, it is desirable to develop a coating that combines the thermal barrier qualities of the ceramic layer and the corrosion protection by the metallic bond coat without the detrimental effects associated with the localization of the ceramic/metal interface to a single plane.

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7 p.

Notes

OSTI as DE96008959

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  • Advanced turbine systems (ATS) annual review, Morgantown, WV (United States), 17-18 Oct 1995

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  • Other: DE96008959
  • Report No.: DOE/MC/29061--96/C0659
  • Report No.: CONF-9510109--30
  • Grant Number: FC21-92MC29061
  • Office of Scientific & Technical Information Report Number: 219513
  • Archival Resource Key: ark:/67531/metadc667732

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  • December 31, 1995

Added to The UNT Digital Library

  • June 29, 2015, 9:42 p.m.

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  • Dec. 11, 2015, 4:47 p.m.

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Banovic, S.W.; Chan, H.M. & Marder, A.R. Functionally gradient materials for thermal barrier coatings in advanced gas turbine systems, article, December 31, 1995; United States. (digital.library.unt.edu/ark:/67531/metadc667732/: accessed July 18, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.