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• W3096581521 abstract "Abstract 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." @default.
• W3096581521 created "2020-11-09" @default.
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• W3096581521 date "2020-10-27" @default.
• W3096581521 modified "2023-09-26" @default.
• W3096581521 title "Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics" @default.
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• W3096581521 doi "https://doi.org/10.1007/978-3-030-53847-7_19" @default.
• W3096581521 hasPublicationYear "2020" @default.
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