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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    Titel :

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


    Beteiligte:

    Erscheinungsdatum :

    2019-08-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



    Turbine engine part coated in a thermal barrier, and a method of obtaining it

    JOULIA AURÉLIEN / MALIE ANDRÉ HUBERT LOUIS / ANSART FLORENCE et al. | Europäisches Patentamt | 2022

    Freier Zugriff

    Experimental Study of Energy Balance in Thermal Barrier Coated Diesel Engine

    Modi, A.J. / Society of Automotive Engineers | British Library Conference Proceedings | 2012



    Experimental Study of Energy Balance in Thermal Barrier Coated Diesel Engine

    Modi, Ashish Jashvantlal | SAE Technical Papers | 2012