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). Said member (17) is to be attached onto a mounting (18) for attachment onto an aircraft structural part, where a thermal protection member (23) surrounds said member (17). Said thermal protection member (23) includes a base flexibly supported on the wall (11) of the element (3). Said base closely fits said wall and at least one covering part that surrounds said load-bearing member.
