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.
TURBINE ENGLINE, SUCH AS FOR EXAMPLE AN AIRCRAFT TURBOJET ENGINE OR A TURBOPROP ENGINE
2017-10-12
Patent
Electronic Resource
English
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.
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