Balancing flyweight, rotor disk equipped therewith, rotor and aircraft engine comprising them
AssigneeSnecma
InventorLaurent Gilles Dezouche
Life of this patent
Estimating the term…
Abstract
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 the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.
Claims23
(canceled)
The rotor disk as claimed in claim 14, wherein said two apexes are aligned on a longitudinal axis.
The rotor disk as claimed in claim 14, wherein it the balancing flyweight includes a hollow.
The rotor disk as claimed claim 14, wherein the balancing flyweight has rounded edges and rounded apexes.
The rotor disk as claimed claim 14, wherein the balancing flyweight includes at least one of a nickel-based alloy, titanium-based alloy, aluminum-based alloy or steel.
(canceled)
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.
(canceled)
(canceled)
Dependencies are inferred from the claim text.