To protect the copper liners of liquid-fuel rocket combustion chambers, a thermal barrier coating can be applied. Previously, a new metallic coating system was developed, consisting of a NiCuCrAl bond-coat and a Rene 80 top-coat, applied with high velocity oxyfuel spray (HVOF). The coatings are tested in laser cycling experiments to develop a detailed failure model, and critical loads for coating failure were defined. In this work, a coating system is designed for a generic engine to demonstrate the benefits of TBCs in rocket engines, and the mechanical loads and possible coating failure are analysed. Finally, the coatings are tested in a hypersonic wind tunnel with surface temperatures of 1350 K and above, where no coating failure was observed. Furthermore, cyclic experiments with a subscale combustion chamber were carried out. With a diffusion heat treatment, no large-scale coating delamination was observed, but the coating cracked vertically due to large cooling-induced stresses. These cracks are inevitable in rocket engines due to the very large thermal-strain differences between hot coating and cooled substrate. It is supposed that the cracks can be tolerated in rocket-engine application.


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    Titel :

    Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics


    Weitere Titelangaben:

    Notes Numerical Fluid Mech.


    Beteiligte:
    Adams, Nikolaus A. (Herausgeber:in) / Schröder, Wolfgang (Herausgeber:in) / Radespiel, Rolf (Herausgeber:in) / Haidn, Oskar J. (Herausgeber:in) / Sattelmayer, Thomas (Herausgeber:in) / Stemmer, Christian (Herausgeber:in) / Weigand, Bernhard (Herausgeber:in) / Fiedler, Torben (Autor:in) / Rösler, Joachim (Autor:in) / Bäker, Martin (Autor:in)


    Erscheinungsdatum :

    2020-10-27


    Format / Umfang :

    13 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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