Control of leak zone under blade platform
View Patent ↗A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.
1. A turbomachine blade-wheel comprising:
a disk presenting a plurality of substantially axial slots on its periphery;
a plurality of blades having roots retained in said slots, and which blades present platforms for defining a radially inner side of a stream of gas and upstream and downstream radial walls that extend from said platforms towards the periphery of said disk;
inter-blade cavities defined by said platforms and the periphery of said disk; and
sealing devices configured to seal the inter-blade spaces, the sealing devices including liners having edges that flare radially inwards and that are disposed in said cavities against the walls of the platforms of two adjacent blades;
wherein each said liner presents an elastic zone on one of its upstream and downstream flared edges, and the radial walls adjacent to said edge are connected to the platforms by inside surfaces that are inclined relative to a radial plane, and against which edges said elastic zone bears, such that said elastic zone is configured to move radially inwards in an event of said wheel ceasing to rotate, and said elastic zone is configured to move radially outwards under action of centrifugal forces to urge said liner to move axially towards the radial walls distant from said elastic zone to improve sealing in said elastic zone.
2. A wheel according to claim 1 , wherein the radial walls that are spaced apart from the elastic zones include abutments to limit axial movement of the liners under the action of centrifugal forces.
3. A wheel according to claim 1 , wherein the lateral walls that are adjacent to the elastic zones include abutments to limit inward sliding of said elastic zones.
4. A wheel according to claim 1 , wherein the elastic zones are circumferentially defined by two notches that are cut in the corresponding flared edges of the liners.
5. A wheel according to claim 1 , wherein the elastic zone is provided on the upstream edge.
6. A wheel according to claim 5 , wherein the wheel is a turbine blade-wheel.
7. A wheel according to claim 6 , wherein an angle of the inclined surface is greater than the slope of the platform relative to an axis of rotation of the turbomachine.
8. A turbomachine comprising:
a blade-wheel including,
a disk presenting a plurality of substantially axial slots on its periphery;
a plurality of blades having roots retained in said slots, and which blades present platforms for defining a radially inner side of a stream of gas and upstream and downstream radial walls that extend from said platforms towards the periphery of said disk;
inter-blade cavities defined by said platforms and the periphery of said disk; and
sealing devices configured to seal the inter-blade spaces, the sealing devices including liners having edges that flare radially inwards and that are disposed in said cavities against the walls of the platforms of two adjacent blades;
wherein each said liner presents an elastic zone on one of its upstream and downstream flared edges, and the radial walls adjacent to said edge are connected to the platforms by inside surfaces that are inclined relative to a radial plane, and against which edges said elastic zone bears, such that said elastic zone is configured to move radially inwards in an event of said wheel ceasing to rotate, and said elastic zone is configured to move radially outwards under action of centrifugal forces to urge said liner to move axially towards the radial walls distant from said elastic zone to improve sealing in said elastic zone.
9. The turbomachine according to claim 8 , wherein the radial walls that are spaced apart from the elastic zones include abutments to limit axial movement of the liners under the action of centrifugal forces.
10. The turbomachine according to claim 8 , wherein the lateral walls that are adjacent to the elastic zones include abutments to limit inward sliding of said elastic zones.
11. The turbomachine according to claim 8 , wherein the elastic zones are circumferentially defined by two notches that are cut in the corresponding flared edges of the liners.
12. The turbomachine according to claim 8 , wherein the elastic zone is provided on the upstream edge.
13. The turbomachine according to claim 12 , wherein the wheel is a turbine blade-wheel.
14. The turbomachine according to claim 13 , wherein an angle of the inclined surface is greater than the slope of the platform relative to an axis of rotation of the turbomachine.