Rotor damper device, and an associated rotor and aircraft
View Patent ↗A damper device ( 10 ) for a rotor ( 2 ) having a rotary ring ( 11 ) and a plurality of levers ( 12 ), each lever ( 12 ) extending from a first end ( 12 ′) connected to the ring ( 11 ) by a first mechanical connection ( 20 ) to a second end ( 12 ″) suitable for being hinged to a blade ( 4 ). The damper device ( 10 ) includes non-rotary damper means ( 30 ) secured to non-rotary fastener means ( 40 ) and to a non-rotary member ( 51 ) of an interface ( 50 ), the interface ( 50 ) being interposed between the non-rotary damper means ( 30 ) and the ring ( 11 ) to convert a rotary movement of a blade ( 4 ) transmitted to a lever ( 12 ) into a movement in translation acting on the damper means ( 30 ).
1. A damper device for a rotor having a rotary ring and a plurality of levers, each lever extending from a first end connected to the ring by a first mechanical connection to a second end suitable for being hinged to a blade, wherein the damper device includes non-rotary damper means secured to non-rotary fastener means and to a non-rotary member of an interface, the interface being interposed between the non-rotary damper means and the ring to convert a rotary lead-lag movement of a blade transmitted to a lever into a movement in translation acting on the damper means.
2. A damper device according to claim 1 , wherein the interface includes a rolling bearing provided with a first cage constrained to rotate with the ring and a second cage that is not rotary, representing the non-rotary member secured to the damper means, rolling members being arranged between the first cage and the second cage.
3. A damper device according to claim 1 , wherein the damper means comprise at least one viscoelastic member.
4. A damper device according to claim 1 , wherein the damper means comprise at least one damping annulus, the annulus being arranged between the interface and the non-rotary fastener means.
5. A damper device according to claim 4 , wherein the annulus is parallel to the ring.
6. A damper device according to claim 4 , wherein the damper means comprise a top annulus and a bottom annulus that are arranged on either side of the ring in elevation, the top annulus being above the ring.
7. A damper device according to claim 1 , wherein at least one mechanical connection comprises an arm for projecting radially from the ring.
8. A damper device according to claim 1 , wherein at least one mechanical connection comprises a connecting rod hinged to the ring and a rocker member hinged to the connecting rod and to the first end of a lever.
9. A rotor provided with a hub carrying a plurality of blades to rotate about an axis of rotation (AX) in elevation, the blades being hinged to the hub by hinges arranged in a fastening plane, wherein the rotor includes the damper device according to claim 1 and provided with a ring rotatable about the axis of rotation (AX) and with one lever per blade, each lever extending from a first end connected to the ring by a first mechanical connection to a second end hinged to a blade, the non-rotary damper means being not rotary about the axis of rotation (AX) , the interface being interposed between the damper means and the ring in order to convert rotary lead-lag movement of at least one blade into movement in translation acting on the damper means.
10. The rotor according to claim 9 , wherein the ring is parallel to the fastening plane.
11. The rotor according to claim 9 , wherein the hub has a top plate and a bottom plate for carrying the blades in the fastening plane (P 1 ), and the ring is arranged in the fastening plane (P 1 ).
12. The rotor according to claim 9 , wherein the damper means are centered on the axis of rotation (AX) of the rotor.
13. An aircraft comprising an airframe and a rotor provided with a hub carrying a plurality of blades to rotate about an axis of rotation (AX) in elevation, the blades being hinged to the hub by hinges that are arranged in a fastening plane (P 1 ), wherein the rotor includes the damper device according to claim 1 and a ring rotatable about the axis of rotation (AX) and with one lever per blade, each lever extending from a first end connected to the ring by a first mechanical connection to a second end hinged to a blade, the non-rotary fastener means being fastened to the airframe and to the non-rotary member of the interface, the interface being interposed between the damper means and the ring in order to convert rotary lead-lag movement of at least one blade into movement in translation in a plane parallel to the fastening plane (P 1 ).
14. The aircraft according to claim 13 , wherein the airframe includes a main gearbox driving the hub in rotation about the axis of rotation (AX), the fastener means comprising a pole fastened to a casing of the main gearbox.