Wear-resistant part for the support of a blade of a turbojet fan
View Patent ↗An aircraft turbojet fan including multiple fan blades including a support that includes a rear portion including a first surface located on an intrados side and a second surface located on an extrados side. A fan disk includes, between recesses, attaching flanges radially protruding towards the outside such that the first surface and the second surface are located respectively opposite two attaching flanges. The fan further includes a wear-resistant part installed on the blade to form a protective shell on each of the first and second surfaces of the support, preventing contact between each surface and the attaching flange located opposite it.
1. An aircraft turbojet fan comprising:
a fan blade, together with a fan disk including teeth defining a recess between two directly consecutive teeth on a periphery thereof, the two directly consecutive teeth delimiting the recess, wherein each blade includes an aerodynamic vane, a blade root held in the recess, and a support interposed between the vane and the root,
the support includes a rear portion including a first surface located on an intrados side of the vane, and a second surface located on an extrados side of the vane,
the fan disk including, between the recess, attaching flanges protruding radially outwards from a rear end of the teeth such that the first surface and the second surface are located respectively opposite two attaching flanges, each attaching flange being pierced with an aperture,
wherein the fan includes a wear-resistant part installed on the blade to form a protective shell on each of the first and second surfaces of the support, preventing contact between each surface and the respective attaching flange located opposite the surface, and
wherein the wear-resistant part includes at least one clip, and the wear-resistant part is installed on the blade by clip fixing on a platform of the blade via the at least one clip.
2. A fan according to claim 1 , wherein each protective shell is between 0.2 and 0.5 mm thick.
3. A fan according to claim 1 , wherein the wear-resistant part is manufactured from an alloy containing 80% nickel, 14% chromium, and 6% iron.
4. A fan according to claim 1 , wherein the wear-resistant part is manufactured by cutting and folding a plate.
5. A fan according to claim 1 , wherein each of the blades of the fan is fitted with a wear-resistant part.
6. A turbojet for aircraft including a fan according to claim 1 .
7. A fan according to claim 1 , wherein the wear-resistant part is T-shaped and includes a linking portion corresponding to a base of a T and an upper branch mounted on the linking portion, the linking portion including first and second members forming the protective shell on the first and second surfaces, wherein the at least one clip is a plurality of clips, and the clips are provided on opposite ends of the upper branch for clip fixing the wear-resistant part on the platform of the blade.
8. A fan according to claim 7 , wherein each presents a U-shape.
9. A fan according to claim 1 , wherein a tangential stop protruding towards the recess and facing the support is provided on the attaching flanges.