Ducted rotor for an aircraft and a rotorcraft

Patent metadata

Field	Value
Publication number	US-9302769-B2
Application number	US-201414267264-A
Country	US
Kind code	B2
Filing date	May 1, 2014
Priority date	May 3, 2013
Publication date	Apr 5, 2016
Grant date	Apr 5, 2016

Abstract

A rotorcraft ducted rotor comprising a rotary assembly arranged in a passage to rotate about an axis of symmetry (AX 1 ). The rotary assembly ( 15 ) has a plurality of blades ( 20 ), each fastened to a hub ( 16 ), each blade ( 20 ) complies with a twisting relationship defining an angle of twist lying in the range zero degrees inclusive to 5 degrees inclusive. Spanwise, each blade ( 20 ) comprises a first zone ( 21 ) followed by a second zone ( 22 ), which second zone presents rearward sweep, being provided with a second trailing edge ( 30″ ) situated downstream from a first trailing edge ( 30′ ) of the first zone ( 21 ). Each first zone ( 21 ) includes a root ( 24 ) connected to the hub ( 16 ) by a fastener device ( 40 ) having a rolling bearing ( 45 ) without clearance and a conical laminated abutment ( 50 ).

First claim

What is claimed is:

1. A ducted rotor for controlling yaw movement of a rotorcraft, the ducted rotor comprising a duct defining an air-flow passage, said ducted rotor having a rotary assembly arranged in the passage to rotate about an axis of symmetry of said passage, said rotary assembly having a plurality of blades, each fastened to a hub, wherein:
each blade comprises a twisting relationship defining a maximum angle of twist (a) lying in the range of zero degrees inclusive to 5 degrees inclusive;
spanwise, each blade comprises a footing first zone that is fastened to the hub and that is followed by an end second zone, the second zone extending radially from said first zone to a distal end of the blade, said second zone presenting a rearward sweep, and being provided with a second trailing edge situated downstream from a first trailing edge of the first zone in the direction (ROT) of rotation of the blade in the passage; and
each first zone includes a root connected to the hub by a fastener device provided with a rolling bearing and a conical laminated abutment.

2. A rotor according to claim 1 , wherein said maximum angle (α) is zero.

3. A rotor according to claim 1 , wherein the center of gravity of the blade is situated on a geometric axis of symmetry of said bearing.

4. A rotor according to claim 1 , wherein said second zone includes a rearward sweep presenting an angle of inclination of at least 30 degrees.

5. A rotor according to claim 1 , wherein said bearing is a rolling bearing without clearance.

6. A rotorcraft, wherein the rotorcraft includes a ducted rotor according to claim 1 .

7. A rotor according to claim 1 , wherein said bearing is a ceramic roller bearing.

8. A rotor according to claim 7 , wherein said bearing includes a ring secured to said root.

9. A rotor according to claim 1 , wherein said laminated abutment comprises an outer strength member and an inner strength member, with an elastomer member of annular shape connecting the inner strength member to the outer strength member, said root passing through said bearing and the elastomer member in order to be fastened to the inner strength member by at least one fastener rod.

10. A rotor according to claim 9 , wherein said inner strength member is fastened to the hub.

11. A rotor according to claim 9 , wherein said ducted rotor includes one pitch lever per blade, each pitch lever being hinged to an inner strength member.

12. A rotor according to claim 9 , wherein at least one balance weight is fastened to said inner strength member.

13. A rotor according to claim 9 , wherein said elastomer member has radial thickness decreasing in compliance with a predetermined thickness reduction relationship on going from the inner strength member towards the outer strength member.

14. A rotor according to claim 9 , wherein said elastomer member comprises a succession of flexible layers of elastomer material and of rigid layers.

Assignees

• Airbus Helicopters

Inventors

• Certain Bernard

Classifications

• B64C2027/8254

  Shrouded tail rotors, e.g. "Fenestron" fans · CPC title

• B64C27/467

  Aerodynamic features · CPC title

• B64C27/82 Primary

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title