Wind turbine rotor blade joint

• US 8,172,539 B2
• Filed: 06/17/2010
• Issued: 05/08/2012
• Est. Priority Date: 06/17/2010
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Kootstra, Dirk Jan
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): HTAY, AYE SU MON
• Application Number:
  US12/817,549
• Publication Number:
  US 20110299995A1
• Time in Patent Office: 691 Days
• Field of Search: 416/223.R, 416/225, 416/226
• US Class Current: 416/223.R
• CPC Class Codes: F03D 1/0658 Arrangements for fixing wind-engaging parts to a hub
• CPC Class Codes: F03D 1/0675 of the blades
• CPC Class Codes: F05B 2230/60 Assembly methods
• CPC Class Codes: F05B 2240/302 Segmented or sectional blades
• CPC Class Codes: Y02E 10/72 Wind turbines with rotation axis in wind direction
• CPC Class Codes: Y02P 70/50 Manufacturing or production processes characterised by the final manufactured product
• CPC Class Codes: Y02T 70/50 Measures to reduce greenhouse gas emissions related to the propulsion system

Abstract

A blade joint for joining a first blade segment and a second blade segment, each having an aerodynamic profile, in a rotor blade is disclosed. The blade joint includes a first joint segment and a second joint segment each having an outer surface, an inner surface, and a thickness therebetween. The outer surface of each joint segment has an aerodynamic profile. The first joint segment and the second joint segment each further have a joint interface end, a blade interface end, and a length therebetween. The joint interface end of the first joint segment and the joint interface end of the second joint segment are configured to couple the first joint segment and second joint segment together.

Claims

1. A blade joint for joining a first blade segment and a second blade segment, each having an aerodynamic profile, in a rotor blade, the blade joint comprising:

a first joint segment and a second joint segment each having an outer surface, an inner surface, and a thickness therebetween, the outer surface of each joint segment having an aerodynamic profile, the first joint segment and the second joint segment each further having a joint interface end, a blade interface end, and a length therebetween,

wherein the joint interface end of the first joint segment and the joint interface end of the second joint segment are configured to couple the first joint segment and second joint segment together, wherein the aerodynamic profile of the outer surface of the first joint segment corresponds to the aerodynamic profile of the first blade segment, and wherein the aerodynamic profile of the outer surface of the second joint segment corresponds to the aerodynamic profile of the second blade segment.

2. The blade joint of claim 1, wherein the thickness of each joint segment increases along at least a portion of the length of the joint segment from the blade interface end to the joint interface end.

3. The blade joint of claim 1, wherein the joint interface end of the first joint segment is a female joint interface end and the joint interface end of the second joint segment is a male joint interface end.

4. The blade joint of claim 1, wherein the first joint segment and the second joint segment each have a width, and wherein the width of each joint segment increases along at least a portion of the length of the joint segment from the blade interface end to the joint interface end.

5. The blade joint of claim 1, wherein the aerodynamic profile of the first joint segment corresponds to the aerodynamic profile of the first blade segment, and wherein the aerodynamic profile of the second joint segment corresponds to the aerodynamic profile of the second blade segment.

6. The blade joint of claim 1, wherein the aerodynamic profile of the first joint segment corresponds to the aerodynamic profile of the second joint segment.

7. The blade joint of claim 1, wherein the first joint segment is bonded to the first blade segment, and wherein the second joint segment is bonded to the second blade segment.

8. The blade joint of claim 1, wherein the second joint segment includes a tensioning mechanism configured to secure the first joint segment and second joint segment together.

9. The blade joint of claim 1, wherein the joint interface end of the first joint segment and the joint interface end of the second joint segment are configured to couple the first joint segment and second joint segment together without the use of mechanical fasteners.

10. A blade segment for a rotor blade having an aerodynamic profile and formed from a plurality of blade segments, the blade segment comprising:

a shell segment having a generally aerodynamic profile and a length, the shell segment further defining a cutaway portion;

a plurality of spar caps extending at least partially through the length of the shell segment, each of the spar caps having a width and a thickness; and

,

a joint segment disposed in the cutaway portion and bonded to the shell segment and the plurality of spar caps, the joint segment having an outer surface, an inner surface, and a thickness therebetween, the outer surface of the joint segment having an aerodynamic profile corresponding to the aerodynamic profile of the shell segment, the joint segment further having a joint interface end, a blade interface end, and a length therebetween.

11. The blade segment of claim 10, wherein the thickness of the joint segment increases along at least a portion of the length of the joint segment from the blade interface end to the joint interface end.

12. The blade segment of claim 11, wherein each of the spar caps includes a tapered joint interface end having a rate of taper, and wherein the thickness of the joint segment increases at a rate substantially similar to the rate of taper of each of the spar caps.

13. The blade segment of claim 10, wherein a width of the joint segment at the blade interface end is approximately equal to the width of each of the spar caps.

14. The blade segment of claim 10, wherein the joint interface end is configured to couple the blade segment to an adjacent blade segment.

15. The blade segment of claim 14, wherein the joint interface end is a female joint interface end.

16. The blade segment of claim 14, wherein the joint interface end is a male joint interface end.

17. The blade segment of claim 10, further comprising a tensioning mechanism configured to secure the blade segment to an adjacent blade segment.

18. The blade segment of claim 17, wherein the tensioning mechanism is mounted to the joint segment.

19. The blade segment of claim 10, wherein the aerodynamic profile of the shell segment and the aerodynamic profile of the joint segment correspond to the aerodynamic profile of the rotor blade.

20. A rotor blade comprising:

a first blade segment comprising;

a shell segment having an aerodynamic profile and a length, the shell segment further defining a cutaway portion;

a plurality of spar caps extending at least partially through the length of the shell segment, each of the spar caps having a width and a thickness; and

,

a joint segment disposed in the cutaway portion and bonded to the shell segment and the plurality of spar caps, the joint segment having an outer surface, an inner surface, and a thickness therebetween, the outer surface of the joint segment having an aerodynamic profile corresponding to the aerodynamic profile of the shell segment, the joint segment further having a female joint interface end, a blade interface end, and a length therebetween; and

,

a second blade segment comprising;

a shell segment having an aerodynamic profile and a length, the shell segment further defining a cutaway portion;

a plurality of spar caps extending at least partially through the length of the shell segment, each of the spar caps having a width and a thickness; and

,

a joint segment disposed in the cutaway portion and bonded to the shell segment and the plurality of spar caps, the joint segment having an outer surface, an inner surface, and a thickness therebetween, the outer surface of the joint segment having an aerodynamic profile corresponding to the aerodynamic profile of the shell segment, the joint segment further having a male joint interface end, a blade interface end, and a length therebetween,

wherein the aerodynamic profile of the joint segment of the first blade segment corresponds to the aerodynamic profile of the joint segment of the second blade segment, and wherein the female joint interface end and the male joint interface end are configured to couple the first blade segment and the second blade segment together.