[특허]Spar assembly for a wind turbine rotor blade

General Electric Company

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특허 상세정보

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Spar assembly for a wind turbine rotor blade

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F03D-011/00 F03D-001/06 F03D-001/00
출원번호	US-0096408 (2013-12-04)
등록번호	US-9605651 (2017-03-28)
발명자 / 주소	Busbey, Bruce Clark Stewart, Edward McBeth
출원인 / 주소	General Electric Company
대리인 / 주소	Dority & Manning, P.A.
인용정보	피인용 횟수 : 0 인용 특허 : 13

초록
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A spar assembly for a rotor blade of a wind turbine is disclosed. The spar assembly includes a first spar cap segment and a second spar cap segment. The first spar cap segment is configured on an interior surface of a first blade segment and the second spar cap segment is configured on an interior surface of a second blade segment. Each spar cap segment includes an end having a joint section that is joinable at a chord-wise joint. Each of the first and second joint sections includes a plurality of holes formed therein. Further, the spar assembly includes...

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1. A rotor blade assembly for a wind turbine, the rotor blade assembly comprising: a rotor blade comprising a first blade segment and a second blade segment, each segment comprising a pressure side shell member and an opposite suction side shell member; and,a spar assembly comprising a first spar cap segment and a second spar cap segment, the first spar cap segment configured on an interior surface of the first blade segment, the second spar cap segment configured on an interior surface of the second blade segment, each of the spar cap segments comprising respective adjacent ends having complementary first and second joint sections that are joinable at a chord-wise joint, each of the first and second joint sections including a plurality of holes formed therein, the spar assembly further comprising a plurality of dowel pins each having a solid cross-section inserted into the plurality of holes of the first and second joint sections to join the first and second blade segments, wherein the dowel pins are fixed in the plurality of holes with an adhesive. 2. The rotor blade assembly of claim 1, wherein the dowel pins comprise at least one of fiberglass or carbon. 3. The rotor blade assembly of claim 1, wherein the first spar cap segment is configured on one of the pressure side shell member or the suction side shell member of the first blade segment and the second spar cap segment is configured on a corresponding shell member of the second blade segment. 4. The rotor blade assembly of claim 3, wherein the spar assembly further comprises an additional spar cap disposed on an opposite shell member from the first and second spar cap segments, the additional spar cap being spaced apart from the first and second spar cap segments such that a cross-sectional area is defined directly between the first and second spar cap segments and the additional spar cap. 5. The rotor blade assembly of claim 4, further comprising a web between the first and second spar cap segments and the additional spar cap, wherein the web is oriented substantially perpendicularly to the first and second spar cap segments and the additional spar cap. 6. The rotor blade assembly of claim 5, further comprising a structural cover around at least a portion of the chord-wise joint to provide further stiffening to the rotor blade. 7. The rotor blade assembly of claim 1, wherein the first blade segment and the second blade segment abut against one another when the plurality of dowel pins of the first spar cap segment are inserted into the plurality of holes of the second spar cap segment. 8. The rotor blade assembly of claim 1, further comprising a middle spar cap segment configured on an interior surface of a middle blade segment, the middle blade segment configured between the first and second blade segments, the middle spar cap segment comprising complementary joint sections on its respective ends that are joinable at chord-wise joints, each of the joint sections of the middle spar cap segment including a plurality of holes formed therein, wherein a portion of the plurality of dowel pins are inserted into the plurality of holes of at least one of the joint sections to join the middle blade segment between the first and second blade segments. 9. The rotor blade assembly of claim 1, wherein the adhesive is located within or around the plurality of holes of the first and second spar cap segments. 10. The rotor blade assembly of claim 9, wherein the adhesive is one of an epoxy-based adhesive, a polyester-based adhesive, or a methyl methacrylate adhesive. 11. The rotor blade assembly of claim 1, wherein the plurality of dowel pins and corresponding plurality of holes are spaced apart at least three millimeters. 12. The rotor blade assembly of claim 1, wherein a gap between the first blade segment and the second blade segment has a tolerance of one millimeter or less. 13. The rotor blade assembly of claim 1, wherein the plurality of dowel pins comprise one of the following cross-sectional shapes: circle, square, rectangle, star, daisy, triangle, oval, or diamond. 14. A method of assembling a rotor blade for a wind turbine, the method comprising: providing first and second blade segments of the rotor blade, the first blade segment comprising a first spar cap segment, the second blade segment comprising a second spar cap segment;boring a plurality of holes within respective adjacent ends of the first and second spar cap segments;inserting a plurality of dowel pins each having a solid cross-section within the plurality of holes of the first spar cap segment; and,joining the first blade segment and the second blade segment by inserting the plurality of dowel pins of the first spar cap segment into the plurality of holes of the second spar cap segment to form a chord-wise joint, wherein the joined first and second spar cap segments improve stiffness of the rotor blade and wherein the dowel pins are fixed in the plurality of holes with an adhesive. 15. The method of claim 14, further comprising installing the first spar cap segment on an interior surface of one of the pressure side shell member or a suction side shell member of the first blade segment, and installing the second spar cap segment on a corresponding interior surface of the second blade segment. 16. The method of claim 14, further comprising: providing a middle blade segment having a middle spar cap segment;boring a plurality of holes within respective ends of the middle spar cap segment;inserting a plurality of dowel pins within the plurality of holes of at least one of the ends of the middle spar cap segment; and,joining the middle blade segment between the first and second blade segments by inserting the plurality of dowel pins of the first spar cap segment into the plurality of holes within one of the respective ends of the middle spar cap segment and inserting the plurality of dowel pins of the middle blade segment within the plurality of holes of the and second blade segment. 17. The method of claim 14, further comprising installing a structural cover around at least a portion of the chord-wise joint to provide further stiffening to the rotor blade. 18. The method of claim 14, wherein the adhesive is added within or around the plurality of holes of the first and second spar cap segments or around the chord-wise joint formed by the first and second spar cap segments. 19. The method of claim 18, further comprising inserting the plurality of dowel pins within the plurality of holes of the first spar cap segment; allowing the adhesive within the plurality of holes of the first spar cap segment to cure; after curing, inserting the plurality of dowel pins of the first spar cap segment within the plurality of holes of the second spar cap segment.

이 특허에 인용된 특허 (13)

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Spar assembly for a wind turbine rotor blade

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Spar assembly for a wind turbine rotor blade

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이 특허에 인용된 특허 (13)

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IPC 상세정보(version : 201201)

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