Rotorcraft rotor fitted with lead-lag dampers housed in sleeves connecting blades to a hub of the rotor

• US 9,284,051 B2
• Filed: 07/09/2013
• Issued: 03/15/2016
• Est. Priority Date: 07/12/2012
• Status: Active Grant

• Current Assignee: Airbus Helicopters
• Original Assignee: Airbus Helicopters
• Inventors: Amari, Andre, Gaffiero, Jacques
• Primary Examiner(s): Nguyen, Ninh H
• Application Number:
  US13/937,660
• Publication Number:
  US 20140017085A1
• Time in Patent Office: 980 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: B64C 27/51 Damping of blade movements
• CPC Class Codes: B64C 27/635 specially for controlling lag-lead movements of blades

Abstract

A rotorcraft rotor fitted with a device for damping lead-lag oscillations of the blades (2) of the rotor. The blades (2) are hinge-mounted on a rotary hub (1) of the rotor via respective sleeves (3). The damper device comprises a set of dampers (6), each individually housed in a respective one of said sleeves (3) and deformable between two fastening points (8, 9), one with the sleeve and the other with an engagement member (7) for engaging the hub (1) via a linkage (10). For each of the sleeve (3), the damper (6) housed by a given sleeve (3) is in hinged engagement with the linkage (10) via a lever arm (11) hinged to the sleeve (3).

Claims

1. A rotorcraft rotor fitted with a damper device for damping lead-lag oscillations of the blades of the rotor, the blades being individually hinge-mounted on a rotary hub of the rotor via respective sleeves, each sleeve being hinged to the hub, at least about a lead-lag axis oriented substantially parallel to the axis of rotation (A) of the hub, the damper device comprising a set of dampers each individually housed in a said sleeve, each damper being elastically deformable between two fastening points via which fastening points the damper is placed under stress between the sleeve housing it and an engagement member for engaging the hub via a linkage, wherein for each of the sleeves, the damper housed by a given sleeve is in hinged engagement with the linkage via a lever arm hinged to the sleeve.

2. A rotorcraft rotor according to claim 1, wherein the lever arms fitted to the sleeves are tools for adjusting lead-lag oscillation damping characteristics of the blades by the damper device, depending on the relative positions on a given lever arm between the hinge of the lever arm with the sleeve, the hinge of the linkage with the lever arm, and the hinge of either one of said fastening points of the damper with the lever arm.

3. A rotorcraft rotor according to claim 1, wherein the damper housed in a given sleeve is in hinged engagement at either one of its said fastening points with the linkage via the lever arm, and is in hinged engagement at the other one of its said fastening points with the sleeve.

4. A rotorcraft rotor according to claim 1, wherein the damper housed in a given sleeve is in hinged engagement with the sleeve housing it at a proximal fastening point, either directly with the sleeve or indirectly via a structure of the hub used for mounting the sleeve on the hub.

5. A rotorcraft rotor according to claim 1, wherein:

the linkage is hinged via a ball joint to the lever arm;

the lever arm is hinged via a pivot to the sleeve about a pivot axis orientated parallel to the lead-lag axis of the blade carried by the sleeve; and

the damper is hinged either via a pivot or via a ball joint at its fastening points respectively to the lever arm and to the sleeve.

6. A rotorcraft rotor according to claim 1, wherein the sleeves are mounted individually on the hub via respective spherical abutment members, and the damper housed in a given sleeve is in hinged engagement with the sleeves via a mounting structure for mounting the spherical abutment member on the hub.

7. A rotorcraft rotor according to claim 1, wherein the lever arm is of generally rectilinear shape.

8. A rotorcraft rotor according to claim 1, wherein the lever arm is of generally dihedral shape.

9. A rotorcraft rotor according to claim 1, wherein the hinge of the damper and the hinge of the linkage with the lever arm are arranged on either side of the hinge of the lever arm with the sleeve.

10. A rotorcraft rotor according to claim 1, wherein the hinge of the lever arm with the sleeve is arranged at one end of the lever arm, and the hinge of the damper and the hinge of the linkage with the lever arm are both arranged at the other end of the lever arm.

11. A rotorcraft rotor according to claim 1, wherein the hinge of the linkage with the lever arm is arranged between the hinge of the lever arm with the sleeve and the hinge of the damper with the lever arm.

12. A rotorcraft rotor according to claim 1, wherein the damper may equally well be a cylindrical damper providing damping in twisting or an elongate damper providing damping in traction/compression.

13. A rotorcraft rotor according to claim 1, wherein the damper is an elongate damper extending inside the sleeve in the general direction in which the sleeve extends, with one of its ends, considered as being a distal end, being hinged to the lever arm, and with the other end of its ends, considered as being a proximal end, being hinged equally well to the sleeve or to the hub.

14. A rotorcraft rotor according to claim 1, wherein the sleeve is arranged as a cover for confining the damper and for housing the lever arm, said cover having a window passing therethrough for passing a branch of the lever arm to which the linkage is hinged.

15. A rotorcraft rotor according to claim 1, wherein the sleeve includes means for cooling the damper.

16. A rotorcraft rotor according to claim 15, wherein the sleeve is arranged as a cover for confining the damper and for housing the lever arm, said cover having a window passing therethrough for passing a branch of the lever arm to which the linkage is hinged, and wherein the cover formed by the sleeve includes at least one forced-air passage passing therethrough for cooling the damper.

17. A rotorcraft rotor according to claim 15, wherein the body of the damper is provided with a finned heat exchanger.

18. A rotorcraft rotor according to claim 1, wherein said engagement member engaging the linkage with the hub is an attachment member incorporated equally well with the hub or with a sleeve adjacent to the sleeve housing the damper engaged with said linkage.

19. A rotorcraft rotor according to claim 1, wherein the linkage includes at least one transmission element, if not a set of hinged-together transmission elements.

20. A rotorcraft fitted with a rotor according to claim 1.