The beneficial effects of using thermal barrier coating (TBC) systems on hot-section components in gas turbines have been described with reference to increasing engine power and efficiency via the use of higher operating temperatures. Design philosophies have been outlined with reference to the use of thermal barrier systems on turbine vane and blade components. The range of available thermal barrier coatings and their deposition processes (plasma spraying and PVD) and degradation mechanisms comprising thermomechanical stress, corrosion, oxidation and erosion phenomena described, and the requirement of accurate life prediction highlighted. Engine service data has been reviewed and correlated with experimental test results. The importance of surface finish has been highlighted with reference to TBC performance.


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    Title :

    Thermal barrier coatings for turbine applications in aero engines


    Additional title:

    Waermeisolationsbeschichtungen fuer den Einsatz in Turbinen von Flugtriebwerken


    Contributors:

    Published in:

    Publication date :

    1989


    Size :

    9 Seiten, 11 Bilder, 2 Tabellen, 47 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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