Braided spar for a rotor blade and method of manufacture thereof

• US 7,165,945 B2
• Filed: 08/22/2003
• Issued: 01/23/2007
• Est. Priority Date: 08/22/2003
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Kovalsky, David A., Viola, Kevin
• Primary Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US10/646,310
• Publication Number:
  US 20050042109A1
• Time in Patent Office: 1,250 Days
• Field of Search: 416/134.A, 416/141, 416/226, 416/230, 416/241.A, 416/228, 416/229.R, 416/237, 87/1, 87/5, 87/8, 87/11, 87/23, 87/28, 87/34, 87/9, 428/36.3, 428/107, 428/111, 428/113, 442204-207
• US Class Current: 416/226
• CPC Class Codes: B29C 70/222 the structure being shaped to form a three dimensional configuration
• CPC Class Codes: B29C 70/48 and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM] , e.g. by vacuum
• CPC Class Codes: B29L 2031/082 Blades, e.g. for helicopters
• CPC Class Codes: B64C 2027/4736 from composite materials
• CPC Class Codes: B64C 27/008 Rotors tracking or balancing devices
• CPC Class Codes: B64C 27/463 Blade tips
• CPC Class Codes: B64C 27/473 Constructional features
• CPC Class Codes: D04C 1/02 made from particular materials
• CPC Class Codes: D04H 3/07 otherwise than in a plane, e.g. in a tubular way
• CPC Class Codes: D10B 2403/02411 with a single array of unbent yarn, e.g. unidirectional reinforcement fabrics
• CPC Class Codes: D10B 2505/02 Reinforcing materials; Prepregs

Abstract

A braided rotor blade spar includes a tri-axle braid in which braided bias angled fibers are located non-parallel to a longitudinal axis of the spar. Zero degree fibers are located parallel to the axis and are positioned to be on the upper and lower surfaces of the spar. The bias angle fibers are braided around the zero degree fibers. In a method of manufacture of the braided spar, a braided sleeve is formed dry over a mandrel by a multi-axial braiding machine. Once the braided sleeve is formed upon the mandrel, the mandrel is located within a matched metal mold, resin impregnated, and cured. The mandrel is then removed from the finished braided spar.

Claims

1. A rotor blade assembly, comprising:

a composite rotor blade spar having a tri-axial braid having a multiple of braided bias angled fibers and a multiple of zero degree fibers interwoven with said multiple of braided bias angled fibers which form a braided sleeve with an elongated cross-sectional profile which surrounds a longitudinal axis, said braided bias angled fibers oriented non-parallel to said longitudinal axis to provide two axes of said tri-axial braid,

said zero degree fibers substantially parallel to said longitudinal axis to provide one axis of said tri-axial braid.

2. The assembly as recited in claim 1, wherein each of said braided bias angled fibers are offset approximately 40 degrees relative said longitudinal axis.

3. The assembly as recited in claim 1, wherein each of said braided bias angled fibers are offset approximately 45 degrees relative said longitudinal axis.

4. The assembly as recited in claim 1, wherein each of said braided bias angled fibers follow a spiral path around said longitudinal axis.

5. The assembly as recited in claim 1, wherein a leading edge and a trailing edge conic of said composite rotor blade spar comprise said braided bias angled fibers.

6. The assembly as recited in claim 1, wherein each of said braided bias angled fibers are oriented to accommodate a twist along said longitudinal axis.

7. The assembly as recited in claim 1, wherein said zero degree fibers are positioned adjacent an upper and lower aerodynamic surface of said composite rotor blade spar, said multiple of zero degree fibers maintained in tension.

8. The assembly as recited in claim 7, further comprising a separate composite sheet interwoven with said multiple of braided bias angled fibers and said multiple of zero degree fibers, said composite sheet located between said upper and lower aerodynamic surfaces.

9. The assembly as recited in claim 1, wherein said braided sleeve is formed to generally constrict toward said longitudinal axis.

10. The assembly as recited in claim 1, wherein said braided sleeve is resin impregnated.

11. The assembly as recited in claim 1, wherein said braided sleeve defines a race-track shaped elongated cross-sectional profile.

12. The assembly as recited in claim 1, wherein said braided sleeve defines an elliptical-shaped elongated cross-sectional profile.

13. The assembly as recited in claim 1, wherein said braided sleeve defines an airfoil-shaped elongated cross-sectional profile.

14. The assembly as recited in claim 1, wherein said braided sleeve is hollow.

15. A rotor blade assembly, comprising:

a composite rotor blade spar having a multiple of braided bias angled fibers and a multiple of zero degree fibers interwoven with said multiple of braided bias angled fibers which form a braided sleeve with an elongated cross-sectional profile which surrounds a longitudinal axis, said braided bias angled fibers oriented non-parallel to said longitudinal axis, said zero degree fibers substantially parallel to said longitudinal axis.

16. The assembly as recited in claim 15, wherein said longitudinal axis is a faying axis.

17. The assembly as recited in claim 15, wherein each of said braided bias angled fibers follow a spiral path around said longitudinal axis.

18. The assembly as recited in claim 15, wherein a leading edge and a trailing edge conic of said spar comprise only said braided bias angled fibers.

19. The assembly as recited in claim 15, wherein each of said zero degree fibers are positioned adjacent an upper and lower surface of said spar.

20. The assembly as recited in claim 15, further comprising a separate composite sheet interwoven with said multiple of braided bias angled fibers and said multiple of zero degree fibers.

21. The assembly as recited in claim 15, wherein said braided sleeve is formed to generally constrict toward said longitudinal axis.

22. The assembly as recited in claim 15, wherein said multiple of zero degree fibers are maintained in tension.

23. The assembly as recited in claim 15, wherein said braided sleeve is resin impregnated.

24. A rotor blade assembly, comprising:

a composite rotor blade spar including a multiple of braided bias angled fibers and a multiple of zero degree fibers interwoven with said multiple of braided bias angled fibers which form a braided sleeve which surrounds a longitudinal axis, said multiple of braided bias angled fibers oriented non-parallel to said longitudinal axis, said multiple of zero degree fibers substantially parallel to said longitudinal axis;

an upper skin which defines an upper aerodynamic surface; and

a lower skin which defines a lower aerodynamic surface.

25. The assembly as recited in claim 24, wherein said zero degree fibers are positioned adjacent an upper surface and a lower surface of said spar and a separate composite sheet is interwoven with said multiple of braided bias angled fibers and said multiple of zero degree fibers between said upper and lower aerodynamic surfaces.

26. The assembly as recited in claim 24, wherein said upper skin and said lower skin are formed from a multitude of prepreg composite material plies.

27. The assembly as recited in claim 24, further comprising a leading-edge sheath which interconnects said upper skin and said lower skin forward of said spar relative said longitudinal axis.

28. The assembly as recited in claim 27, further comprising a counterweight between said leading-edge sheath and said spar.