Turbine engine including a thermal protection member
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.
1. A turbine engine, comprising:
at least one element comprising:
a wall;
a main yoke attached to a beam;
an auxiliary yoke clearance mounted on the beam, with said main yoke and said auxiliary yoke extending substantially perpendicularly to said wall, with said auxiliary yoke being adapted to take up stress in case of deformation of the element, breakage of the main yoke, or a combination thereof; and
a thermal protection member surrounding the auxiliary yoke only, with said thermal protection member comprising a base flexibly supported on the wall of the element, with said base matching a shape of said wall and at least one covering part which surrounds said auxiliary yoke.
2. The turbine engine according to claim 1 , wherein the element further comprises a second main yoke attached to the beam, and wherein the auxiliary yoke is positioned circumferentially between the main yokes.
3. The turbine engine according to claim 1 , wherein the thermal protection member is attached to the wall by means of first fastening members.
4. The turbine engine according to claim 3 , wherein the wall comprises an external surface and at least one annular flange which radially extends outwards from said external surface, with the first fastening members being attached to said external surface, said annular flange, or a combination thereof.
5. The turbine engine according to claim 1 , comprising second fastening members adapted for attaching the thermal protection member on the beam.
6. The turbine engine according to claim 1 , wherein the element is a casing, with said wall being an annular shroud.
7. The turbine engine according to claim 4 , wherein the external surface is cylindrical.
8. The turbine engine according to claim 4 , wherein the external surface is frustoconical.