Effects of Alloy Composition on the Performance of Yttria Stabilized Zirconia—Thermal Barrier Coatings

Author:

Kimmel Josh1,Mutasim Zaher1,Brentnall William1

Affiliation:

1. Solar Turbines Incorporated, San Diego, California 92186-5376

Abstract

Thermal barrier coatings (TBCs) provide an alloy surface temperature reduction when applied to turbine component surfaces. Thermal barrier coatings can be used as a tool for the designer to augment the power and/or enhance the efficiency of gas turbine engines. TBCs have been used successfully in the aerospace industry for many years, with only limited use for industrial gas turbine applications. Industrial gas turbines operate for substantially longer cycles and time between overhauls, and thus endurance becomes a critical factor. There are many factors that affect the life of a TBC including the composition and microstructure of the base alloy and bond coating. Alloys such as Mar-M 247, CMSX-4, and CMSX-10 are materials used for high temperature turbine environments, and usually require protective and/or thermal barrier coatings for increased performance. Elements such as hafnium, rhenium, and yttrium have shown considerable improvements in the strength of these alloys. However, these elements may result in varying effects on the coatability and environmental performance of these alloys. This paper discusses the effects of these elements on the performance of thermal barrier coatings. [S0742-4795(00)02603-X]

Publisher

ASME International

Subject

Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering

Reference11 articles.

1. Erickson, G. L. , 1995, “A New, Third-Generation, Single-Crystal, Casting Superalloy,” J. Met., 47, No. 4, pp. 36–39.

2. Brindley, W. J., and Miller, R. A., 1989, “TBCs for Better Engine Efficiency,” Advanced Materials and Processes, 8, No. 89, pp. 29–33.

3. Maricocchi, A., Bartz, A., and Wortman, D., 1995, “PVD TBC Experience on GE Aircraft Engines,” Thermal Barrier Coatings Workshop, NASA Conference Publication 3312, pp. 79–90.

4. Bose, S., and DeMasi, J. T., 1995, “Thermal Barrier Coating Experience in Gas Turbine Engine at Pratt & Whitney,” Thermal Barrier Coating Workshop, NASA Conference Publication 3312, pp. 63–78.

5. Mutasim, Z. Z., Rimlinger, C. M., and Brentnall, W. D., 1997, “Characterization of Plasma Sprayed and Electron Beam-Physical Vapor Deposited Thermal Barrier Coatings,” ASME Paper 97-GT-531.

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