A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.


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    Title :

    A TURBINE ENGINE PART COATED IN A THERMAL BARRIER, AND A METHOD OF OBTAINING IT



    Publication date :

    2019-08-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    C23C Beschichten metallischer Werkstoffe , COATING METALLIC MATERIAL / B64C AEROPLANES , Flugzeuge / C04B Kalk , LIME



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