Assembly of a fan blade and of its damper, fan blade damper and method for calibrating the damper

1. A fan blade assembly of a turbojet comprising:

a fan blade including a root extending in an axial direction parallel to an axis of the turbojet, an airfoil extending in a radial direction perpendicular to the axial direction, and a platform; and

a fan blade damper being suitable for being attached in a housing formed in a lower face of the platform, said housing comprising an upstream side perpendicular to the root of the blade and extending in a transverse direction perpendicular to both the axial direction and the radial direction,

wherein the damper includes a front portion and a rear portion offset higher than the front portion, the front portion including a front edge with a first portion which is parallel to the upstream side of the housing and a second portion which is inclined relative to said upstream side of the housing relative to the transverse direction.

2. The assembly as claimed in claim 1 wherein the first portion parallel to the upstream side is in abutment against the upstream side of the housing.

3. The assembly as claimed in claim 1 , wherein an angle (α) formed between the first portion of the front edge and the second portion of the front edge is between 10° and 20°.

4. The assembly as claimed in claim 1 , wherein the second portion of the front edge forms a flat surface.

5. The assembly as claimed in claim 1 , wherein the second portion of the front edge forms a curved surface.

6. The assembly as claimed in claim 1 , wherein ridges of the second portion of the front edge are rounded.

7. The assembly as claimed in claim 1 , wherein an outer surface of the damper comprises at least one metallic contact zone.

8. The assembly as claimed in claim 1 , wherein the damper includes non-parallel lateral faces, and a distance between the lateral faces is less in the front portion relative to the rear portion.

9. The assembly as claimed in claim 1 , wherein an upper face of the damper includes a right upper face and a left upper face separated by an interface ridge, and one of the right or left upper faces is in contact with the lower face of the platform.

10. A fan blade damper of a turbojet, extending in its length along an axis oriented X, in its width along an axis oriented Y and in its height along an axis Z, comprising:

a first front portion and a second rear portion of polygonal cross section relative to the axis X;

an upper face comprising an upper right inclined face and an upper left inclined face; and

a front edge being formed at a front of the first front portion of the damper,

wherein the front edge includes a first face that is transverse relative to the axis X and a second face that is inclined relative to said first face relative to the axis Y.

11. A fan blade assembly of a turbojet including the damper as claimed in claim 10 .

12. A method for calibrating a damper of a fan blade assembly of a turbojet with fan and a fan blade damper comprising a weight reserve volume, the method comprising:

determining a reference weight Mref of the damper;

measuring an effective weight Meff of the damper;

cutting out the weight reserve volume so that the weight of the cut-out damper is equal to the reference weight Mref.

13. The method as claimed in claim 12 , wherein the weight reserve volume is situated at a front end of the damper.

14. The method as claimed in claim 12 , wherein the damper extends in its length along an axis oriented X, in its width along an axis oriented Y and in its height along an axis Z, the damper including:

a first front portion and a second rear portion of polygonal cross section relative to the axis X;

an upper face comprising an upper right inclined face and an upper left inclined face; and

a front edge being formed at a front of the first front portion of the damper,

wherein the front edge includes a first face that is transverse relative to the axis X and a second face that is inclined relative to said first face relative to the axis Y.