Blade platform and a fan disk for an aviation turbine engine
A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.
1. A platform suitable for being interposed between two adjacent blades of a fan, the platform comprising:
a passage wall for defining a fan air flow passage;
a bottom wall having a main surface for bearing against a fan disk;
the platform having axial and radial retention surfaces arranged at the two axial ends of the platform, the radial retention surface arranged at the upstream axial end of the platform being radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk, wherein the bottom wall has an inclined surface inclined relative to the main surface of the bottom wall and connecting the main surface of the bottom wall in continuous manner with the radial retention surface arranged at the upstream axial end of the platform, wherein the radial retention surface and the main surface of the bottom wall are parallel to each other.
2. The platform according to claim 1 , wherein the inclined surface is a rectilinear wall portion.
3. The platform according to claim 1 , wherein the inclined surface is a curvilinear wall portion.
4. The platform according to claim 1 , wherein the inclined surface and the passage wall are parallel.
5. The platform according to claim 1 , wherein the axial and radial retention surfaces arranged at the two axial ends of the platform are configured to retain the platform and hold the platform in position relative to the disk on which the platform bears while the disk is moving.
6. An assembly comprising at least one platform suitable for being interposed between two adjacent blades of a fan and a disk, the platform comprising:
a passage wall for defining a fan air flow passage;
a bottom wall having a main surface for bearing against a fan disk;
the platform having axial and radial retention surfaces arranged at the two axial ends of the platform, the radial retention surface arranged at the upstream axial end of the platform being radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk, wherein the bottom wall has an inclined surface inclined relative to the main surface of the bottom wall and connecting the main surface of the bottom wall in continuous manner with the radial retention surface arranged at the upstream axial end of the platform, the disk comprising:
an outer surface presenting a succession of slots for receiving fan blades and of teeth interposed between the slots in order to support the fan platforms;
an upstream face of the disk; and
a plurality of axial projections arranged radially around the axis A of the disk on the upstream face of the disk, and suitable for being fastened to a fan platform retention flange, the projections being radially offset towards the inside of the disk relative to the teeth of the disk, wherein upstream axial ends of the teeth of the disk present surfaces that are chamfered, the assembly further comprising at least one upstream retention flange for axially and radially retaining the upstream end of the platform, wherein the upstream retention flange is fastened on an axial projection of the upstream face of the disk.
7. The assembly according to claim 6 , wherein, when the platform bears against a tooth of the disk, an inclined surface of the bottom wall is in contact with the chamfered surface of the tooth of the disk, and the inclined surface and the chamfered surface are parallel.
8. The assembly according to claim 6 , wherein the upstream retention flange is a shroud.
9. A turbine engine fan comprising an assembly according to claim 6 together with a plurality of blades mounted in slots of the disk.
10. The assembly according to claim 6 , wherein the axial projections are studs machined on the upstream face of the disk.
11. The assembly according to claim 6 , wherein the fastening zone between the retention flange and the disk is offset radially towards the inside of the disk.
12. The assembly according to claim 6 , wherein the axial projections are in the shape of cubes and disposed circumferentially at regular intervals around the axis A.
13. The assembly according to claim 6 , wherein each axial projection has a fastener orifice in its upstream face suitable for receiving a screw or a bolt, and each axial projection includes an insertion orifice in its outer face, in which an insert that includes a tapped hole is inserted.