References

1. S. Carnot, Reflections sur la puissance motrice du feu, Chez Bachelier Libraire, Paris, 1824.

2. W. N. Harrison, D. G. Moore, and J. C. Richmond, Review of an investigation of ceramic coatings for metallic turbine parts and other high-temperature applications, NACA TN-1186,1947.

3. S. Stecura, Two-layer thermal barrier coating for turbine airfoils -- furnace and burner rig test results, NASA TM X-3425, 1976.

4. C. H. Liebert, R. E. Jacobs, S. Stecura and C. R. Morse, Durability of zirconia thermal barrier ceramic coatings on air-cooled turbine blades in cyclic jet engine operation, NASA TM X-3410, 1976.

5. W. R. Sevcik and B. L. Stoner, An analytical study of thermal barrier coated first stage blades in a JT9D engine, NASA CR-135360, 1978 (Pratt & Whitney Aircraft).

6. S., Stecura, Effect of compositional' changes on the performance of a"thermal barrier coating system, NASA TM-78976, 1978.

7. S. Stecura, Effects of plasma spray parameters on two-layer thermal barrier coating system life. NASA TM-81724,1981.

8. S. Stecura, Effects of yttrium, aluminum, and chromium concentrations in bond coating on the performance of zirconia-yttria thermal barriers, NASA TM-79206, 1979.

9. I. E. Sumner and D. L. Ruckle, Development of improved durability plasma sprayed ceramic coating for gas turbine engines, NASA TM-81724, 1981; also AIAA-80-1193.

10. P. A. Siemers and W. B. Hillig, Thermal barrier coated turbine blade study, NASA CR-165351, 1981 (General Electric Company).

11. N. P. Anderson and K. D. Sheffler, Development of strain tolerant thermal barrier coating systems, Tasks 1-3, NASA CR-168251, 1983 (Pratt and Whitney

Ai rcraft).

12. E. C. Duderstadt and P. Agarwal, Energy efficient engine high pressure turbine thermal barrier coating support technology report, NASA CR-168037, 1983 (General Electric Company).

13. T. E. Strangman, J. Neumann, and A. Liu, Thermal barrier coating life-prediction model development, Final Report, NASA CR-179648, 1987 (Garrett Turbine Engine Company).

14. R. A. Miller, Surf, and Coatings Technol., 30(1987)1.

15. R. A. Miller and C. E. Lowell, Thin Solid Films, 95(1982)265.

16. R. A. Miller and C. C. Berndt, Thin Solid Films, 119(1984)195.

18. R. A. Miller, Progress towards life modelling of thermal barrier coatings for aircraft gas turbine engines, Trans. ASME -J. Eng. Gas Turb. and Power, 109(1987)448.

19. J. T. DiMasi, M. Ortiz, K. D. Sheffler, Thermal barrier coating life prediction model development; Final Report, NASA Contractor Report, to be published (Pratt & Whitney Ai rcraft).

20. R. V. Hillery, B. H. Pilsner, R. L. McKnight, T. S. Cook, and M.S. Hartle, Thermal barrier coating life prediction model, Final Report, NASA CR-180807 (General Electric Company).

21. R. A. Miller, J. L. Smialek, and R. G. Garlick.in A. H. Heuer and L. W. Hobbs (eds), Science and technology of zirconia I, American Ceramic Society, Columbus, Ohio , 1981, 241-253.

22. R. A. Miller, R. G. Garlick, Smialek, Am. Ceram Soc. Bull., 62(1983)1355.

23. R. A. Miller, Ceramic thermal barrier coatings for electric utility gas turbine engines, in A. V. Levy (ed.), Proceedings of corrosion-erosion-wear of materials at elevated temperatures, National Association of Corrosion Engineers, Houston, Texas, 1987, 52-60.

24. R. C. Bill, Plasma-sprayed zirconia gas path seal technology: A state-of-the-art review, NASA TM-79273, 1979.

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