Aviation turbine engine fan assembly including a fitted platform
A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.
1. A fan assembly for an aviation turbine engine, the assembly comprising a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, said platform comprising a box of composite material made from fiber reinforcement densified by an organic matrix, said box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall; wherein the box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, said locking key being blocked at each of its ends by blocking means.
2. An assembly according to claim 1 , wherein the blocking means for blocking the locking key at its downstream end is a hook projecting from the tooth of the fan disk.
3. An assembly according to claim 1 , further comprising an upstream shroud, the locking key being blocked at its upstream end by means of said upstream shroud.
4. An assembly according to claim 3 , wherein the locking key presents at its upstream end a folded portion extending radially along an upstream face of the tooth of the fan disk, said folded portion having passing therethrough a fastener element for mounting the upstream shroud on the fan disk.
5. An assembly according to claim 4 , wherein the folded portion of the locking key is extended by an axial portion positioned under the tooth of the fan disk.
6. An assembly according to claim 3 , wherein the upstream end of the locking key is locked in a housing formed in the upstream shroud.
7. An assembly according to claim 1 , wherein the bottom wall of the box is pierced by an opening passing a hook projecting from the tooth of the fan disk, said hook being configured to have the locking key that is received in the box pass therethrough.
8. An assembly according to claim 1 , wherein the locking key is a plane bar or a cylindrical rod.
9. An aviation turbine engine fan including an assembly according to claim 1 , wherein the fan disk presents at least two teeth defining between them a slot, and at least one blade provided with a root mounted in the slot of the fan disk.
10. A method of mounting an assembly according to claim 1 , the method comprising:
bringing the platform to the tooth of the fan disk in a substantially radial direction;
inserting the locking key into the box of the platform via the upstream opening of the box; and
blocking the ends of the locking key by the blocking means.