A turbine engine includes 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. A thermal protection member (23) surrounds said member (17), with said thermal protection member (23) including 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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    Title :

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



    Publication date :

    2020-09-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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