Assembly of sections of structural parts

Patent metadata

Field	Value
Publication number	US-9945356-B2
Application number	US-201314395458-A
Country	US
Kind code	B2
Filing date	Apr 16, 2013
Priority date	Apr 20, 2012
Publication date	Apr 17, 2018
Grant date	Apr 17, 2018

Abstract

A wing or blade in at least two sections facing each other. Each section has a longitudinal bearing structure provided with at least one sole of which the link between the sections includes at least one first link plate linking the end of the soles of the sections facing each other. A method of producing such wing or blade.

First claim

The invention claimed is:

1. A wing or blade in at least two sections facing each other, each section comprising a longitudinal bearing structure provided with at least one sole piece, the longitudinal bearing structure of each section comprising a longitudinal member perpendicular to the sole piece; wherein a link between the sections comprises at least one first link plate linking an end of the sole piece of each section facing each other; and wherein a slot is arranged between the longitudinal member and the sole piece of each section facing each other by reducing a height of the longitudinal member in a part receiving the first link plate, the first link plate linking the sole pieces being received in said slot.

2. The wing or blade as claimed in claim 1 , wherein the end of the sole piece of each section receiving the first link plate comprises an additional thickness of reinforcing material.

3. The wing or blade as claimed in claim 1 , wherein the end of the sole piece of each section receiving the first link plate forms a widened termination.

4. The wing or blade as claimed in claim 3 , wherein the sole pieces are made from axial folds of composite materials and are reinforced at a level of the widened terminations by biaxial folds to obtain a stack to absorb forces of fasteners.

5. The wing or blade as claimed in claim 1 , wherein the link further comprises at least one second link plate for connecting the longitudinal members of two consecutive sections.

6. The wing or blade as claimed in claim 5 , further comprising intrados and extrados skins that are secured to the sole pieces, and wherein the intrados and extrados skins comprise access doors to the first and second link plates.

7. The wing or blade as claimed in claim 5 , wherein the longitudinal bearing structure of each section is an H-section beam comprising two sole pieces and a longitudinal member linking the two sole pieces.

8. The wing or blade as claimed in claim 7 , wherein an end of the longitudinal bearing structure of each section receives at least one first link plate per sole piece and at least one second link plate on the longitudinal member.

9. The wing or blade as claimed in claim 1 , further comprising intrados and extrados skins that are secured to the sole pieces.

10. The wing or blade as claimed in claim 9 , further comprising internal profiles extending the sole pieces in a transverse direction in relation to the longitudinal bearing structure, the intrados and extrados skins and the internal profiles forming a sandwich structure of the blade.

11. The wing or blade as claimed in claim 10 , wherein assemblies of the intrados and extrados skins, the sole pieces and the internal profiles are composite assemblies secured by polymerization, the assemblies being connected by the first link plates.

12. The wing or blade as claimed in claim 1 , further comprising bolted connections to fasten the first link plates.

13. A method of producing a wing or blade comprising at least two sections as claimed in claim 1 , comprising the steps of:
laying up a first skin having a length of the wing on a form;
placing a first sole piece having a length of the wing on the first skin;
mating internal profiles on the first skin to either side of the first sole piece;
impregnating an assembly of the first skin, the first sole piece and the internal profiles with a resin, and polymerizing the assembly; and
placing the first link plate on the first sole piece which straddles a cutting zone of the wing in two sections, the link plate being secured to the first sole piece on a first side of the cutting zone.

14. The method as claimed in claim 13 , further comprising the step of bolting the first link plate to the first sole piece on the first side of the cutting zone.

15. The method as claimed in claim 13 , further comprising the step of gluing the first link plate to the first sole piece on the first side of the cutting zone.

16. The method as claimed in claim 13 , further comprising the step of temporarily fixing the first link plate to the first sole piece on a second side of the cutting zone.

17. The method as claimed in claim 13 , wherein each section comprises a longitudinal bearing structure comprising a second sole piece and a second skin, the method further comprises the step of repeating the steps of laying up the first skin, placing the first sole piece, mating the internal profiles, impregnating and polymerizing the assembly, and placing the first link plate for the second sole piece and the second skin.

18. The method as claimed in claim 17 , wherein the sections comprising longitudinal members which, together with the first sole pieces, form an H-section beam, the method further comprising the steps of:
jointing the longitudinal members of the sections by at least one second link plate; gluing the longitudinal members that are jointed on the first sole piece; and
gluing the second sole piece on the longitudinal member on a side opposite the first sole piece by a blind closure of the wing or blade to perform the gluing of the second skin on the first skin that is equipped with the longitudinal member and gluing of the longitudinal member on the second sole piece.

19. The method as claimed in claim 18 , further comprising the steps of releasing the wing, cutting the first and second skins and the sole pieces at a level of the cutting zone forming a junction of first and second sections, and dismantling the first link plate on a side of the second section.

20. The method as claimed in claim 19 , further comprising the steps of gluing the first link plate on a blade foot side of a section; and disassembling the sections after the step of cutting by dismantling the first link plate on a blade tip section side, the first link plate glued and remaining in position in a blade foot section, and dismantling the second link plate of the longitudinal member.

21. The method as claimed in claim 20 , further comprising the step of assembling the sections by inserting link plates of the blade foot section into the blade tip section by bolting the link plates on a sole piece of the blade tip section and by jointing the longitudinal members.

22. The method of producing a wing or blade comprising at least two sections as claimed in claim 1 , comprising the steps of:
laying up a first skin having a length of the wing on a form;
placing a first sole piece having a length of the wing on the first skin;
mating internal profiles on the first skin to either side of the first sole piece;
placing the first link plate on the first sole piece which straddles a cutting zone of the wing in two sections, the first link plate being configured to prevent gluing of the first link plate on the first sole piece on a second side of the cutting zone; and
impregnating an assembly of the first skin, the first sole piece, internal profiles and the first link plate with a resin, and polymerizing the assembly.

23. The method as claimed in claim 22 , further comprising the step of bolting the first link plate on the first sole piece on the first side of the cutting zone.

24. The method as claimed in claim 22 , further comprising the step of temporarily fixing the first link plate to the first sole piece on a second side of the cutting zone.

25. The method as claimed in claim 22 , wherein each section comprises a longitudinal bearing structure comprising a second sole piece and a second ski

Assignees

• Airbus Defence & Space Sas

Inventors

• Humblot Antoine
• Naud Francois

Classifications

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• Y02E10/721

  Cross-Sectional Technologies · mapped topic

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title

• Y02E10/728

  Onshore wind turbines · CPC title

• F05B2240/302

  Segmented or sectional blades · CPC title