The invention relates to a turbine engine provided with an element (3), comprising a wall (11) and at least one load-bearing member (17) extending substantially perpendicularly relative to the wall (11), with said member (17) being intended to be attached onto a mounting (18) used for the attachment thereof onto an aircraft structural part, characterized in that a thermal protection member (23) surrounds said member (17), with said thermal protection member (23) comprising a base flexibly supported on the wall (11) of the element (3), with said base matching the shape of said wall and at least one covering part which surrounds said load-bearing member.


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    Titel :

    TURBINE ENGLINE, SUCH AS FOR EXAMPLE AN AIRCRAFT TURBOJET ENGINE OR A TURBOPROP ENGINE


    Beteiligte:

    Erscheinungsdatum :

    12.10.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



    Turbine engine, such as for example an aircraft turbojet engine or a turboprop engine.

    ERWAN PIERRE ANTOINE PERSE / LAURENT DONATIEN BEHAGHEL / STÉPHANE GEYL et al. | Europäisches Patentamt | 2020

    Freier Zugriff

    Turbojet and Turboprop Engine Controls

    MOCK, F.C. | SAE Technical Papers | 1951


    Icing problems for turbojet and turboprop aircraft

    Thompson, J.K. | Engineering Index Backfile | 1956


    From Turboprop to Turbojet

    Sambrooke, Stephen | Online Contents | 1998


    Design trends in turbojet and turboprop aircraft engines

    Farrar, E.V. | Engineering Index Backfile | 1947