Helicopter Rotor

• US 20100163668A1
• Filed: 11/02/2009
• Published: 07/01/2010
• Est. Priority Date: 11/11/2008
• Status: Active Grant

• Current Assignee: Leonardo S.p.A.
• Original Assignee: AgustaWestland SpA (Leonardo S.p.A.)
• Inventors: Ballerio, Dante, Nannoni, Fabio, Abdel Nour, Pierre
• Granted Patent: US 8,297,549 B2
• Time in Patent Office: Days
• US Class Current: 244/17.210
• CPC Class Codes: B64C 27/35 having elastomeric joints
• CPC Class Codes: B64C 27/51 Damping of blade movements
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft

Abstract

A rotor for a helicopter, having a drive shaft rotating about a first axis; a hub angularly integral with the drive shaft about the first axis; and at least two blades projecting from the hub, on the opposite side to the first axis, and extending along respective second axes crosswise to the first axis; each blade is movable with respect to the hub and the other blades about a respective fourth axis parallel to the first axis, about the respective second axis, and about a respective third axis crosswise to the first and respective second axis; the rotor also has a number of first dampers for damping vibration associated with at least oscillation of the relative blades about the respective fourth axes; the first dampers are connected to one another and each to a relative blade; and, in a radial direction with respect to the first axis, at least one first damper is located between the first axis and the fourth axis of the relative blade.

Claims

1. A rotor for a helicopter, comprising:

a drive shaft rotating about a first axis;

a hub angularly integral with said drive shaft about said first axis;

at least two blades projecting from said hub, on the opposite side to said first axis, and extending along respective second axes crosswise to said first axis;

each said blade being movable with respect to said hub and the other said blades about a respective fourth axis parallel to said first axis, about the respective said second axis, and about a respective third axis crosswise to said first and respective second axis; and

a number of first dampers for damping vibration associated with at least oscillation of the relative said blades about the respective said fourth axes;

said first dampers being connected to one another and each to a relative blade;

characterized in that, in a radial direction with respect to said first axis, at least one said first damper is located between said first axis and said fourth axis of the relative blade.

2. A rotor as claimed in claim 1, characterized in that at least one said blade comprises a connecting member hinged to said hub to move about the respective said second, third, and fourth axis;

and a shank defining a radially inner end of the blade with respect to said first axis, and cooperating with the relative said first damper.

3. A rotor as claimed in claim 1, characterized in that said first dampers define respective arms of a ring surrounding said first axis.

4. A rotor as claimed in claim 1, characterized in that said ring rotates freely with respect to said hub about said first axis.

5. A rotor as claimed in claim 1, characterized by comprising a second damper interposed between said hub and at least one said first damper.

6. A rotor as claimed in claim 5, characterized in that at least one of said first dampers comprises a tooth engaging a slot defined by said hub.

7. A rotor as claimed in claim 2, characterized in that each said first damper comprises an elastomeric member fitted through at least partly with said shank of the relative said blade;

and a body made of rigid material and defining a cavity housing said elastomeric member.

8. A helicopter comprising a main rotor;

and an antitorque tail rotor as claimed in claim 1.

9. A helicopter comprising an antitorque tail rotor;

and a main rotor as claimed in claim 1.