Turbine wheel provided with an axial retention device that locks blades in relation to a disk

1. A turbine wheel comprising:

a plurality of blades, each blade presenting an airfoil, a platform, and an attachment member;

a disk having the blades mounted at a periphery thereof, the attachment member of each blade being engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite faces of the disk, the housings being separated by teeth;

an axial retention device for retaining the blades by locking the blades axially relative to the disk;

wherein

at least one of the blades comes into abutment against a first stop member of the disk to block the blade relative to the disk in a first axial direction, the first stop member extending radially outward from an outermost radial surface of one of the teeth of the disk at a downstream portion thereof, the first stop member being received in a cavity of the blade and abutting a contact face of the platform of the blade,

the platform of the blade includes a projection projecting axially beyond one of the faces of the disk, the projection including a second stop member, and

the axial projection, the second stop member, and the face of the disk form a groove facing towards the axis of the disk, the groove serving to receive the axial retention device such that the axial retention device, in the assembled position, comes into abutment in the first axial direction against the second stop member, and against the face of the disk in a second axial direction opposite to the first axial direction, whereby the blade is prevented from moving relative to the disk in the second axial direction.

2. A turbine wheel according to claim 1 , wherein at least one bulge is provided between the axial retention device and the blade to establish mechanical contact between the blade and the axial retention device.

3. A turbine wheel according to claim 2 , wherein the at least one bulge is formed on the axial retention device.

4. A turbine wheel according to claim 2 , wherein a recess of shape complementary to the at least one bulge is formed in the element facing the bulge, and is formed such that the at least one bulge is received in the recess.

5. A turbine wheel according to claim 4 , wherein at least one of the at least one bulge or the recess is made on or in a portion of the platform that does not support the blade airfoil radially.

6. A turbine wheel according to claim 1 , wherein the disk presents an anti-rotation stop configured to prevent the axial retention device from moving in an azimuth direction relative to the disk.

7. A turbine wheel according to claim 1 , wherein the disk further presents at least one safety stop configured to prevent the axial retention device from making centripetal movements.

8. A turbine wheel according to claim 1 , wherein the axial retention device is a split ring.

9. A turbine wheel according to claim 1 , wherein the second stop member forms a nib.

10. A turbine wheel according to claim 9 , wherein the nib forms a portion of a ring extending over at least a portion of the azimuth length of the axial projection of the platform of the blade.

11. A turbomachine including at least one turbine wheel according to claim 1 .

12. A turbine wheel comprising:

a plurality of blades, each blade presenting an airfoil, a platform, and an attachment member;

a disk having the blades mounted at a periphery thereof, the attachment member of each blade being engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite faces of the disk, the housings being separated by teeth;

an axial retention device for retaining the blades by locking the blades axially relative to the disk;

wherein

at least one of the blades comes into abutment against a first stop member of the disk to block the blade relative to the disk in a first axial direction,

the platform of the blade includes a projection projecting axially beyond one of the faces of the disk, the projection including a second stop member,

the axial projection, the second stop member, and the face of the disk form a groove facing towards the axis of the disk, the groove serving to receive the axial retention device such that the axial retention device, in the assembled position, comes into abutment in the first axial direction against the second stop member, and against the face of the disk in a second axial direction opposite to the first axial direction, whereby the blade is prevented from moving relative to the disk in the second axial direction,

at least one bulge is provided between the axial retention device and the blade to establish mechanical contact between the blade and the axial retention device, and

the at least one bulge is formed under the axial projection on the bottom of the groove.

13. A turbine wheel comprising:

a plurality of blades, each blade presenting an airfoil, a platform, and an attachment member;

a disk having the blades mounted at a periphery thereof, the attachment member of each blade being engaged in a housing that opens into the periphery of the disk and that extends axially between two opposite faces of the disk, the housings being separated by teeth;

an axial retention device for retaining the blades by locking the blades axially relative to the disk;

wherein

at least one of the blades comes into abutment against a first stop member of the disk to block the blade relative to the disk in a first axial direction,

the platform of the blade includes a projection projecting axially beyond one of the faces of the disk, the projection including a second stop member,

the axial projection, the second stop member, and the face of the disk form a groove facing towards the axis of the disk, the groove serving to receive the axial retention device such that the axial retention device, in the assembled position, comes into abutment in the first axial direction against the second stop member, and against the face of the disk in a second axial direction opposite to the first axial direction, whereby the blade is prevented from moving relative to the disk in the second axial direction,

at least one bulge is provided between the axial retention device and the blade to establish mechanical contact between the blade and the axial retention device, and

the at least one bulge is made on a portion of the platform that does not support the blade airfoil radially.