Propeller for a turbine engine of an aircraft with a variable-pitch vane and a geared counterweight device
An assembly for a propeller of a turbine engine of an aircraft is provided. The assembly includes a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis aligned with a vane pitch axis which passes through the root, a base rigidly connected to the vane to rotate together with the vane about the axis and connected to a portion of a toothed wheel extending around the axis, and a counterweight device having a shaft which can rotate about an axis substantially perpendicular to the axis, the shaft being connected to at least one flyweight and to a pinion meshed with the toothed wheel portion. The toothed wheel portion can be attached to the base by at least one shear pin.
1. An assembly for a propeller of a turbine engine of an aircraft, the assembly comprising:
a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis coincident with a pitch axis of the vane which passes through the root;
a base secured in rotation to the vane about the pitch axis and connected to a toothed wheel portion extending about the pitch axis; and
a counterweight device having a shaft movable in rotation about a substantially concurrent axis perpendicular to the pitch axis, the shaft being connected to at least one weight and to a pinion portion geared with the toothed wheel portion,
wherein the toothed wheel portion is attached to the base by at least one shear bolt.
2. The assembly according to claim 1 , wherein the toothed wheel portion is attached to the base by a plurality of shear bolts.
3. The assembly according to claim 1 , wherein the at least one shear bolt extends along a first axis of elongation which is parallel to the pitch axis.
4. The assembly according to claim 1 , wherein the at least one shear bolt comprises:
a first head bearing on the toothed wheel portion; and
a first body which passes through first orifices of the toothed wheel portion and first orifices of the base.
5. The assembly according to claim 4 , wherein the first body comprises:
a first segment threaded and screwed into the first orifice of the base, which is tapped; and
a second segment defining a smaller section of the first body.
6. The assembly according to claim 5 , wherein the second segment comprises an annular groove.
7. The assembly according to claim 5 , wherein the second segment comprises at least one hole.
8. The assembly according to claim 1 , further comprising at least one retention screw for retaining the toothed wheel portion on the base, the at least one retention screw being non-functional as long as the at least one shear bolt is unbroken and the at least one retention screw being functional when the at least one shear bolt is broken.
9. The assembly according to claim 8 , wherein the at least one retention screw has a second head which is configured, on the one hand, to be at a distance from the toothed wheel portion when the at least one shear bolt is not broken, and, on the other hand, to be able to come to bear on and retain the toothed wheel portion when the at least one shear bolt is broken.
10. The assembly according to claim 8 , the at least one retention screw extends along a second axis of elongation which is parallel to the pitch axis.
11. The assembly according to claim 8 , wherein the at least one retention screw has a second body which passes through the second orifices in the toothed wheel portion and in the base.
12. The assembly according to claim 11 , wherein the second body comprises:
a third segment threaded and screwed into the second orifice of the base, which is tapped; and
a fourth non-threaded segment engaged in the second orifice of the toothed wheel portion.
13. The assembly according to claim 8 , wherein the at least one shear is staggered with the at least one retention screw.
14. A propeller for a turbine engine of an aircraft, the propeller comprising a plurality of assemblies according to claim 1 .
15. The assembly according to claim 6 , wherein the annular groove has a diameter smaller than a diameter of the first body.
16. The assembly according to claim 1 , wherein the toothed wheel portion comprises first toothings configured to gear with second toothings of the counterweight device.
17. An assembly for a propeller of a turbine engine of an aircraft, the assembly comprising:
a variable-pitch vane having a blade connected to a root, the vane having a longitudinal axis coincident with a pitch axis of the vane which passes through the root;
a base secured in rotation to the vane about the pitch axis and connected to a toothed wheel portion extending about the pitch axis; and
a counterweight device having a shaft movable in rotation about a substantially concurrent axis perpendicular to the pitch axis, the shaft being connected to at least one weigh and to a pinion portion geared with the toothed wheel portion,
wherein the toothed wheel portion is attached to the base by at least one shear bolt, and
wherein the assembly further comprising at least one retention screw for retaining the toothed wheel portion on the base, the at least one retention screw being non-functional as long as the at least one shear bolt is unbroken and the at least one retention screw being functional when the at least one shear bolt is broken.