Blade and method of fabricating said blade

Patent metadata

Field	Value
Publication number	US-9302764-B2
Application number	US-201213355728-A
Country	US
Kind code	B2
Filing date	Jan 23, 2012
Priority date	Jan 31, 2011
Publication date	Apr 5, 2016
Grant date	Apr 5, 2016

Abstract

A blade ( 1 ) provided with a fitting ( 2 ) for fastening to a hub and with an airfoil element ( 10 ) having a spar ( 20 ) extending spanwise from an attachment zone ( 21 ) towards a distal zone ( 22 ), said attachment zone ( 21 ) surrounding a centrifugal force transmission bushing ( 31 ) that is connected to said fitting ( 2 ) by a through pin ( 3 ). The blade comprises a twisting force transmission member ( 40 ) provided with a first half-shell ( 41 ) and with a second half-shell ( 42 ) that together surround said attachment zone ( 21 ), each half-shell ( 41, 42 ) having a perforated first portion ( 43′, 43 ″) giving visual access to said bushing ( 31 ) when said airfoil element is removed from the fitting, and a second portion ( 44′, 44 ″) co-operating with a torsion box ( 50 ) surrounding said distal zone ( 22 ), said transmission member ( 40 ) being secured to said fitting in rotation about a torsion axis (AX) of the blade ( 1 ).

First claim

What is claimed is:

1. A blade provided with a fitting for fastening to a hub and with an airfoil element having a spar extending spanwise from an attachment zone towards a distal zone, the attachment zone surrounding a centrifugal force transmission bushing that is connected to the fitting by a through pin, wherein the blade includes a twisting force transmission member provided with a first half-shell and with a second half-shell that together surround the attachment zone, each half-shell having a perforated first portion giving visual access to the bushing when the airfoil element is removed from the fitting, and a second portion, the blade further including a torsion box surrounding the distal zone, the respective second portions of the first half-shell and the second half-shell co-operating with the torsion box, the transmission member being secured to the fitting in rotation about a torsion axis (AX) of the blade.

2. The blade according to claim 1 , wherein the torsion box is placed around the distal zone of the spar, with an outer covering that covers the torsion box.

3. The blade according to claim 1 , wherein filler means are arranged between the torsion box and an outer covering.

4. The blade according to claim 1 , wherein a filler member is arranged between the spar and the transmission member.

5. The blade according to claim 1 , wherein the first portion of the first half-shell and the second portion of the second half-shell together form a cylinder secured in rotation with the fitting.

6. The blade according to claim 1 , wherein the first portion of the first half-shell and the first portion of the second half-shell act together to form a contact surface secured in rotation with the fitting by stop means.

7. The blade according to claim 6 , wherein the stop means comprise a flat of the contact surface.

8. The blade according to claim 1 , including assembly means for assembling the first half-shell to the second half-shell.

9. The blade according to claim 1 , wherein the spar includes fibers extending in a longitudinal direction of the blade, the torsion box including fibers extending in a direction that presents an acute angle relative to the longitudinal direction.

10. A method of fabricating a blade according to claim 1 , the method comprising the following steps:
fabricating a spar extending from an attachment zone towards a distal zone, the attachment zone surrounding a bushing, and then pre-polymerizing the spar;
arranging a twisting force transmission member provided with a first half-shell and a second half-shell on the attachment zone, each half-shell comprising a perforated first portion giving access to the bushing, and a second portion;
fabricating a torsion box around the second portion of each half-shell and the distal zone of the spar;
fabricating an outer covering around the torsion box and then polymerizing the assembly comprising the spar, the transmission member, the torsion box, and the outer covering in order to obtain an airfoil element; and
inserting the airfoil element in a fitting and connecting the fitting to the bushing by a through pin.

11. The blade according to claim 1 , wherein the second portions of the half-shells are in contact with the torsion box.

12. The blade according to claim 11 , wherein the torsion box is disposed on the second portions of the half-shells.

13. The blade of claim 1 , wherein the torsion box extends about the respective second portions of the first half-shell and the second half-shell.

14. The blade of claim 1 , wherein the blade includes only one torsion box.

15. A blade provided with a fitting for fastening to a hub and with an airfoil element having a spar extending spanwise from an attachment zone towards a distal zone, the attachment zone surrounding a centrifugal force transmission bushing that is connected to the fitting by a through pin, wherein the blade includes a twisting force transmission member provided with a first half-shell and with a second half-shell that together surround the attachment zone, each half-shell having a perforated first portion giving visual access to the bushing when the airfoil element is removed from the fitting, and a second portion co-operating with a torsion box surrounding the distal zone, the transmission member being secured to the fitting in rotation about a torsion axis (AX) of the blade, wherein the second portion of the first half-shell and the second portion of the second half-shell act together to form a frustoconical surface in contact with the torsion box.

16. The blade according to claim 15 , wherein the frustoconical surface has elliptical sections.

17. The blade according to claim 15 , wherein the torsion box is placed around the distal zone of the spar, with an outer covering that covers the torsion box, and wherein the spar includes fibers extending in a longitudinal direction of the blade, and the torsion box includes fibers extending in a direction that presents an acute angle relative to the longitudinal direction.

18. A blade provided with a fitting for fastening to a hub and with an airfoil element having a spar extending spanwise from an attachment zone towards a distal zone, the attachment zone surrounding a centrifugal force transmission bushing that is connected to the fitting by a through pin, wherein the blade includes a twisting force transmission member provided with a first half-shell and with a second half-shell that together surround the attachment zone, each half-shell having a perforated first portion giving visual access to the bushing when the airfoil element is removed from the fitting, and a second portion co-operating with a torsion box surrounding the distal zone, the transmission member being secured to the fitting in rotation about a torsion axis (AX) of the blade, wherein each of the first portion of the first half-shell and the first portion of the second half-shell includes a fastener stud, with the fitting having one longitudinal slideway and one circularly arcuate slideway per stud.

19. The blade according to claim 18 , wherein each stud extends in a longitudinal direction over a predetermined length, and each circularly arcuate slideway extends longitudinally over a length that is longer than the predetermined length in order to present clearance when the stud is inserted in the circularly arcuate slideway.

20. The blade according to claim 18 , wherein the torsion box is placed around the distal zone of the spar, with an outer covering that covers the torsion box.

Assignees

• Bianchi Laurent
• Isidore Nicolas
• Gaffiero Jacques
• Michel Bernard
• Airbus Helicopters

Inventors

• Bianchi Laurent
• Isidore Nicolas
• Gaffiero Jacques
• Michel Bernard

Classifications

• B64C11/26 Primary

  Fabricated blades · CPC title

• B64C27/48

  Root attachment to rotor head · CPC title

• B21K3/04

  blades, e.g. for turbines; Upsetting of blade roots · CPC title

• B64C11/20 Primary

  Constructional features · CPC title