Safran Aircraft Engines

Cécile Thiriet

Laurent Donatien Behaghel

Erwan Pierre Antoine Perse

Yvan Yoann Guezel

Stephane Geyl

A turbine engine includes an element (), comprising a wall () and at least one load-bearing member () extending substantially perpendicularly relative to the wall (), with said member () being intended to be attached onto a mounting () used for the attachment thereof onto an aircraft structural part. A thermal protection member () surrounds said member (), with said thermal protection member () including a base flexibly supported on the wall () of the element (), with said base matching the shape of said wall and at least one covering part which surrounds said load-bearing member.

Growing community of inventors

Moissy-Cramayel, France

Cécile Thiriet