Balancing flyweight, rotor disk equipped therewith, rotor and aircraft engine comprising them
View Patent ↗The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts together. The two apexes are aligned on a longitudinal axis. The two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to said the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.
1. A rotor disk of a turbomachine, said disk comprising:
cells, said cells having two active sides;
blade roots which are inserted in the cells which form a gap between the blade roots in a direction tangential to the disk; and
at least one balancing flyweight disposed in said gap,
wherein the balancing flyweight comprises first and second pyramid-shaped end parts each of the first and second pyramid-shaped end parts including a base and an apex, and an intermediate part which connects the two bases of the first and second end parts together.
2. The rotor disk as claimed in claim 1 , wherein said two apexes are aligned on a longitudinal axis.
3. The rotor disk as claimed in claim 2 , wherein the balancing flyweight comprises a plane of symmetry perpendicular to said longitudinal axis.
4. The rotor disk as claimed in claim 1 , wherein the balancing flyweight includes a hollow.
5. The rotor disk as claimed in claim 4 , wherein said hollow is a traversing hole oriented in a direction perpendicular to a longitudinal axis which connects the two apexes.
6. The rotor disk as claimed in claim 2 , wherein the two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to said longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.
7. The rotor disk as claimed in claim 6 , wherein said polygons are four sided polygons, such that each end part has the shape of a pyramid with four faces and such that the intermediate part has the shape of a parallelepiped.
8. The rotor disk as claimed in claim 7 , wherein said four-sided polygons are rectangles.
9. The rotor disk as claimed in claim 7 , wherein said four-sided polygons are squares.
10. The rotor disk as claimed in claim 9 , wherein the balancing flyweight includes eight active faces which are the eight faces of the two end parts.
11. The rotor disk as claimed claim 1 , wherein the balancing flyweight has rounded edges and rounded apexes.
12. The rotor disk as claimed in claim 1 , wherein the balancing flyweight includes at least one of a nickel-based alloy, titanium-based alloy, aluminum-based alloy or steel.
13. The rotor disk as claimed in claim 1 , wherein said balancing flyweight comprises two active faces disposed on one of the end parts.
14. The rotor disk as claimed in claim 13 , wherein the two active faces are symmetrical with each other with respect to a median plane perpendicular to a longitudinal axis which connects the two apexes of the flyweight.
15. The rotor disk as claimed in claim 14 , wherein said active faces respectively come into contact with one of the active sides of the cell when said rotor disk is driven in rotation.
16. A turbomachine rotor comprising at least one rotor disk as claimed in claim 1 .
17. A turbomachine, comprising at least one rotor disk as claimed in claim 1 .
18. An aircraft engine comprising at least one rotor disk as claimed in claim 1 .
19. The rotor disk as claimed in claim 14 , wherein an angle of inclination between the longitudinal axis and one of the active faces is between 30 degrees and 60 degrees.