Means for alleviating strain on a wind turbine rotor blade
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F03D-001/06
F03D-007/02
출원번호
US-0101043
(2015-01-22)
등록번호
US-10247169
(2019-04-02)
우선권정보
EP-14154895 (2014-02-12)
국제출원번호
PCT/EP2015/051259
(2015-01-22)
국제공개번호
WO2015/121044
(2015-08-20)
발명자
/ 주소
Gonzalez, Alejandro Gomez
Loeven, Alex
Torgard, Sigmund Wenningsted
출원인 / 주소
Siemens Aktiengesellschaft
대리인 / 주소
Schmeiser, Olsen & Watts, LLP
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
A rotor blade for a wind turbine with an aerodynamic device, and an aerodynamic device is provided. The rotor blade includes a main body defining a pressure side and a suction side of the rotor blade, and includes a main body trailing edge section. The rotor blade includes an aerodynamic device with
A rotor blade for a wind turbine with an aerodynamic device, and an aerodynamic device is provided. The rotor blade includes a main body defining a pressure side and a suction side of the rotor blade, and includes a main body trailing edge section. The rotor blade includes an aerodynamic device with an attachment section for attaching the aerodynamic device to the main body trailing edge section, an aerodynamic section for influencing the aerodynamic properties of the rotor blade, and a buckling section for controlling the orientation and/or the shape of the aerodynamic section with regard to the main body. The aerodynamic device is configured such that it deforms elastically for a force component acting in flapwise direction on the buckling section, and deforms abruptly if a force component of about the size of the stability limit of the buckling section acts in flapwise direction on the buckling section.
대표청구항▼
1. A rotor blade for a wind turbine, the rotor blade comprising: a main body defining a pressure side and a suction side of the rotor blade, the main body having a main body trailing edge section, a leading edge section, and a span; andan aerodynamic device, the aerodynamic device having an attachme
1. A rotor blade for a wind turbine, the rotor blade comprising: a main body defining a pressure side and a suction side of the rotor blade, the main body having a main body trailing edge section, a leading edge section, and a span; andan aerodynamic device, the aerodynamic device having an attachment section for attaching the aerodynamic device to the main body trailing edge section along a portion of the span, an aerodynamic section for influencing the aerodynamic properties of the rotor blade, and a buckling section to control a configuration of the aerodynamic section with regard to the main body;wherein the aerodynamic device has a device trailing edge that extends past the main body trailing edge section within the portion of the span in a direction distal to the leading edge section of the main body;wherein the aerodynamic device is configured such that the aerodynamic device: deforms elastically for a force component below an elasticity limit acting in flapwise direction on the buckling section, anddeforms abruptly if a force component of a size that is within a predetermined range from of a stability limit of the buckling section acts in flapwise direction on the buckling section,wherein the configuration of the aerodynamic section with regard to the main body is changed if the buckling section deforms abruptly, and load on the rotor blade is alleviated due to the change of the configuration of the aerodynamic section. 2. The rotor blade according to claim 1, wherein the aerodynamic device is shaped as a flap. 3. The rotor blade according to claim 1, wherein the aerodynamic section of the aerodynamic device comprises a plurality of serrations to reduce emission of noise. 4. The rotor blade according to claim 1, wherein at least the buckling section of the aerodynamic device is made of rubber and/or silicone to realize the abrupt deformation if a force component of the size that is within a predetermined range from of the stability limit of the buckling section acts in flapwise direction on the buckling section. 5. The rotor blade according to claim 1, wherein the attachment section and/or the aerodynamic section of the aerodynamic device are substantially rigid with regard to the force component acting in flapwise direction on the aerodynamic device. 6. The rotor blade according to claim 1, wherein the aerodynamic device comprises a device leading edge section and a device trailing edge section, the device leading edge section being attached to the main body trailing edge section, and the device trailing edge section builds the trailing edge section of the rotor blade. 7. The rotor blade according to claim 1, wherein the aerodynamic device comprises at least one stabilizer for reducing the deformation of the aerodynamic device in substantially flapwise direction, for the force component being smaller than the stability limit of the buckling section. 8. The rotor blade according to claim 7, wherein the at least one stabilizer extends in substantially chordwise direction of the rotor blade. 9. The rotor blade according to claim 7, wherein the at least one stabilizer delimits the aerodynamic device at a radially inner edge of the aerodynamic device, and a further stabilizer delimits the aerodynamic device at a radially outer edge of the aerodynamic device. 10. The rotor blade according claim 7, wherein the at least one stabilizer is attached to the buckling section by an angle which is smaller than 150 degrees. 11. The rotor blade according claim 7, wherein the at least one stabilizer is attached to the buckling section by an angle of substantially 90 degrees. 12. The rotor blade according to claim 7, wherein the at least one stabilizer is bent towards the pressure side or towards the suction side of the rotor blade. 13. The rotor blade according to claim 7, wherein the at least one stabilizer comprises a corrugation to control more accurately the abrupt deformation of the buckling section if the force component of the size that is within a predetermined range from of the stability limit of the buckling section acts in flapwise direction on the buckling section. 14. The rotor blade according to claim 1, wherein the buckling section comprises a nonlinear spring to realize the abrupt deformation if the force component of the size that is within a predetermined range from of the stability limit of the buckling section acts in flapwise direction on the buckling section. 15. The rotor blade according to claim 1, wherein the buckling section comprises a first end and a second end, the first end is attached to the main body trailing edge section, and the second end is attached to the aerodynamic section of the aerodynamic device. 16. The rotor blade according to claim 1, wherein the aerodynamic device comprises a plurality of connection members for connecting the aerodynamic section of the aerodynamic device to the main body trailing edge section, and each connection member of the plurality of connection members comprises a buckling section and an attachment section. 17. The rotor blade according to claim 10, wherein the angle is smaller than 120 degrees. 18. An aerodynamic device, comprising: an attachment section for attaching the aerodynamic device to a main body trailing edge section along a portion of a span of a rotor blade for a wind turbine,an aerodynamic section for influencing the aerodynamic properties of the rotor blade, anda buckling section to control a configuration of the aerodynamic section with regard to a main body of the rotor blade;wherein the aerodynamic device has a device trailing edge that extends past the main body trailing edge section within the portion of the span in a direction distal to the leading edge section of the main body;wherein the aerodynamic device is configured such that the aerodynamic device: deforms elastically for a force component below an elasticity limit acting in flapwise direction on the buckling section, anddeforms abruptly if a force component of a size that is within a predetermined range from a stability limit of the buckling section acts in flapwise direction on the buckling section,wherein the configuration of the aerodynamic section with regard to the main body is changed if the buckling section deforms abruptly, and load on the rotor blade is alleviated due to the change of the configuration of the aerodynamic section.
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이 특허에 인용된 특허 (6)
Jacobsen, Eric Morgan; Busbey, Bruce Clark; Zhu, Qi; Riddell, Scott Gabell; Esser, Juergen; Bakhuis, Jan Willem; Nagabhushana, Pradeepa, Attachment system for a wind turbine rotor blade accessory.
Merzhaeuser, Thomas; Buravalla, Vidyashankar Ramasastry; Krishnamurthy, Sriram; Lin, Wendy Wen-Ling, Method and system for tensioning tension fabrics in wind-turbine.
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