Rotorcraft rotor blade assembly

Patent metadata

Field	Value
Publication number	US-10822954-B2
Application number	US-201816170414-A
Country	US
Kind code	B2
Filing date	Oct 25, 2018
Priority date	Jul 6, 2015
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.

First claim

What is claimed is:

1. A method of manufacturing a rotorcraft rotor blade assembly, the method comprising:
positioning a stub spar between an upper skin portion and a lower skin portion, the stub spar extending less than 80% of a full span of the rotor blade assembly, each of the upper skin portion and the lower skin portion extending substantially the full span of the rotor blade assembly, and the stub spar tapers as the stub spar extends away from an inboard end of the rotor blade assembly such that:
at a cross-section located closer to the inboard end of the rotor blade assembly, a thickness of the stub spar is substantially greater than a thickness of the upper skin portion or a thickness of the lower skin portion,
at a cross-section located away from to the inboard end of the rotor blade assembly, the thickness of the stub spar is substantially equal to or less than the thickness of the upper skin portion or the thickness of the lower skin portion, and
at a cross-section located nearer to the outboard end of the rotor blade assembly, there is no stub spar; and

attaching the upper skin portion and the lower skin portion to the stub spar.

2. The method of claim 1 , wherein the stub spar extends only up to 50% of the full span of the rotor blade assembly.

3. The method of claim 2 , wherein the stub spar extends only between 10% and 50% of the full span of the rotor blade assembly.

4. The method of claim 1 , further comprising pre-curing at least one of the stub spar, the upper skin portion or the lower skin portion before positioning the stub spar between the upper skin portion and the lower skin portion.

5. The method of claim 1 , wherein each of the stub spar, the upper skin portion and the lower skin portion is uncured, and wherein attaching the upper skin portion and the lower skin portion to the stub spar comprises bonding the upper skin portion, the lower skin portion and the stub spar after attaching the upper skin portion and the lower skin portion to the stub spar.

6. The method of claim 1 , wherein each of the upper skin portion and the lower skin portion include a composite material comprising a centrifugal material aligned substantially span-wise from the inboard end to more than 50% of the full span of the rotor blade assembly, a torque material torsionally wound around the upper skin portion and the lower skin portion from the inboard end to substantially the full span of the rotor blade assembly, and a shearing material aligned chord-wise from the inboard end to substantially all or part of the full span of the rotor blade assembly.

7. The method of claim 1 , wherein, at a location away from the inboard end of the rotor blade assembly, the thickness of the stub spar is substantially less than the thickness of the upper skin portion or the thickness of the lower skin portion.

8. The method of claim 1 , wherein the stub spar excludes material configured to support centrifugal loads of the rotorcraft rotor assembly.

9. The method of claim 8 , wherein a thickness of each of the upper skin portion and the lower skin portion is configured to support substantially 30% or more of the centrifugal loads by substantially 40% or less of the full span of the rotor blade assembly.

10. The method of claim 1 , wherein the stub spar excludes torsional material or material configured to support centrifugal loads of the rotorcraft rotor assembly.

11. The method of claim 1 , wherein the stub spar comprises at least one of a closed hollow cross-section of structural composite material, an open hollow cross section of composite material or a non-hollow cross-section.

12. The method of claim 11 , wherein the stub spar comprises a filler material.

13. A method of manufacturing a rotorcraft rotor blade assembly, the method comprising:
forming an upper skin portion extending substantially a full span of the rotor blade assembly;
forming a lower skin portion extending substantially the full span of the rotor blade assembly;
positioning a stub spar between the upper skin portion and the lower skin portion, the stub spar extending only between 10% and 80% of the full span of the rotor blade assembly, the stub spar tapering as the stub spar extends away from an inboard end of the rotor blade assembly such that:
at a cross-section located closer to the inboard end of the rotor blade assembly, a thickness of the stub spar is substantially greater than a thickness of the upper skin portion or a thickness of the lower skin portion,
at a cross-section located away from to the inboard end of the rotor blade assembly, the thickness of the stub spar is substantially equal to or less than the thickness of the upper skin portion or the thickness of the lower skin portion, and
at a cross-section located nearer to the outboard end of the rotor blade assembly, there is no stub spar; and

attaching the upper skin portion and the lower skin portion to the stub spar.

14. The method of claim 13 , wherein the stub spar extends only up to 50% of the full span of the rotor blade assembly.

15. The method of claim 13 , further comprising pre-curing at least one of the stub spar, the upper skin portion or the lower skin portion before positioning the stub spar between the upper skin portion and the lower skin portion.

16. The method of claim 13 , wherein each of the stub spar, the upper skin portion and the lower skin portion is uncured, and wherein attaching the upper skin portion and the lower skin portion to the stub spar comprises bonding the upper skin portion, the lower skin portion and the stub spar after attaching the upper skin portion and the lower skin portion to the stub spar.

17. The method of claim 13 , wherein each of the upper skin portion and the lower skin portion include a composite material comprising a centrifugal material aligned substantially span-wise from the inboard end to more than 50% of the full span of the rotor blade assembly, a torque material torsionally wound around the upper skin portion and the lower skin portion from the inboard end to substantially the full span of the rotor blade assembly, and a shearing material aligned chord-wise from the inboard end to substantially all or part of the full span of the rotor blade assembly.

18. The method of claim 13 , wherein, at a location away from the inboard end of the rotor blade assembly, the thickness of the stub spar is substantially less than the thickness of the upper skin portion or the thickness of the lower skin portion.

19. The method of claim 13 , wherein the stub spar excludes material configured to support centrifugal loads of the rotorcraft rotor assembly.

20. The method of claim 19 , wherein a thickness of each of the upper skin portion and the lower skin portion is configured to support substantially 30% or more of the centrifugal loads by substantially 40% or less of the full span of the rotor blade assembly.

21. The method of claim 13 , wherein the stub spar excludes torsional material or material configured to support centrifugal loads of the rotorcraft rotor assembly.

22. The method of claim 13 , wherein the stub spar comprises at least one of a closed hollow cross-section of structural composite material, an open hollow cross section of composite material or a non-hollow cross-section.

23. The method of claim 22 , wherein the stub spar comprises a filler material.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Oldroyd Paul K
• Sutton Drew
• Maresh Andrew
• Foskey Christopher

Classifications

• B64C27/473 Primary

  Constructional features · CPC title

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title