Adaptable rotor blade design for performance flexibility

Patent metadata

Field	Value
Publication number	US-10807705-B2
Application number	US-201715469463-A
Country	US
Kind code	B2
Filing date	Mar 24, 2017
Priority date	Mar 24, 2017
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

In one embodiment, a rotor blade may comprise a blade body, a spar structure, and a blade nose. The blade body may comprise a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge. The spar structure may comprise a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin. The blade nose may comprise a cavity, wherein the cavity is configured to house a plurality of modular weights at a plurality of radial blade locations, wherein the plurality of radial blade locations comprises a range of locations between the inboard end and the outboard end.

First claim

What is claimed is:

1. A rotor blade comprising:
a blade body comprising a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge;
a spar structure comprising a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin, the first spar cap and the second spar cap together defining a hollow blade nose including a cavity along the leading edge, the hollow blade nose configured for receiving a plurality of removable modular weights at a plurality of radial blade locations between the inboard end and the outboard end, wherein a distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to optimize blade performance; and
a clip configured to couple the first spar cap and the second spar cap; and
wherein the first spar cap and the second spar cap are separate structural components that are stationary and together form a non-contiguous spar structure.

2. The rotor blade of claim 1 , wherein the plurality of removable modular weights is distributed at first and second radial blade locations in the cavity of the blade nose.

3. The rotor blade of claim 1 , wherein the distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to increase rotor inertia.

4. The rotor blade of claim 1 , wherein the distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to reduce blade vibration.

5. The rotor blade of claim 1 , wherein the distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to increase blade stability.

6. The rotor blade of claim 1 , wherein the plurality of removable modular weights varies in shape and size.

7. The rotor blade of claim 1 , further comprising a compression molded fiberglass structure, wherein the compression molded fiberglass structure comprises the plurality of removable modular weights, and wherein the compression molded fiberglass structure is housed in the cavity of the blade nose.

8. The rotor blade of claim 1 , further comprising a weight pocket housed in the blade body, wherein the weight pocket is located near the outboard end.

9. The rotor blade of claim 1 , wherein the first spar cap and the second spar cap each comprise a plurality of layered composite plies, wherein the plurality of layered composite plies comprises a varying number of plies at different radial blade locations.

10. The rotor blade of claim 1 , wherein the skin comprises a carbon fiber skin, and wherein the blade body comprises a large cell carbon core.

11. A rotorcraft comprising:
a fuselage; and
a rotor comprising a plurality of rotor blades, wherein at least one rotor blade of the plurality of rotor blades comprises:
a blade body comprising a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge; and
a spar structure comprising a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin, the first spar cap and the second spar cap together defining a hollow blade nose including a cavity along the leading edge, the hollow blade nose configured for receiving a plurality of removable modular weights at a plurality of radial blade locations between the inboard end and the outboard end, wherein a distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to optimize blade performance; and
a clip configured to couple the first spar cap and the second spar cap; and
wherein the first spar cap and the second spar cap are separate structural components that are stationary and together form a non-contiguous spar structure not contiguous.

12. The rotorcraft of claim 11 , wherein the distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to increase rotor inertia.

13. The rotorcraft of claim 11 , wherein the distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to reduce blade vibration.

14. The rotorcraft of claim 11 , wherein the distribution of the plurality of removable modular weights in the cavity of the blade nose is configured to increase blade stability.

15. The rotorcraft of claim 11 , wherein the at least one rotor blade further comprises a compression molded fiberglass structure, wherein the compression molded fiberglass structure comprises the plurality of removable modular weights, and wherein the compression molded fiberglass structure is housed in the cavity of the blade nose.

Assignees

• Bell Helicopter Textron Inc

Inventors

• Sutton Drew A
• Wasikowski Mark E
• Maresh Andrew Ryan
• Phillips Nolan B

Classifications

• B64C27/008 Primary

  Rotors tracking or balancing devices · CPC title

• B64C2027/4736

  from composite materials · CPC title

• B64C27/473

  Constructional features · CPC title

• B64C2027/005

  using suspended masses · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title