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Thermal barrier coatings

  • Chapter
Metallurgical and Ceramic Protective Coatings

Abstract

The fundamental driving force for the development of thermal barrier coatings has been the continuing quest for ever higher temperatures in gas turbines. Over the period 1940–1970, the temperature capability of superalloys for gas turbine blades, which is defined in terms of 100 h life at 20000 psi (138 MPa) stress, was increased from approximately 1400°F (760°C) to 1900 °F (1040 °C) [1]. This was a costly process which required the development of numerous generations of new superalloys. It was a necessary and successful step, however, in producing the highly reliable and efficient gas turbine engines that we know today. Between 1940 and 1970, higher temperature superalloys, along with improved engine design, allowed specific fuel consumption to be reduced by more than half, thrust-to-weight ratios to be tripled, and time between overhaul to be increased from less than 100 h to over 12000 h [1]. A recent review of the effect of materials on current and future gas turbine performance has been given by Kool [2].

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Authors
  1. R. L. Jones
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  1. Chemistry Division, Naval Research Laboratory, 20375-5342, Washington D.C., USA

    Kurt H. Stern

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© 1996 Chapman & Hall

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Jones, R.L. (1996). Thermal barrier coatings. In: Stern, K.H. (eds) Metallurgical and Ceramic Protective Coatings. Springer, Dordrecht. https://doi.org/10.1007/978-94-009-1501-5_8

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  • DOI: https://doi.org/10.1007/978-94-009-1501-5_8

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