IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0022347
(2011-02-07)
|
등록번호 |
US-8226368
(2012-07-24)
|
발명자
/ 주소 |
- Standish, Kevin
- Herr, Stefan
|
출원인 / 주소 |
|
대리인 / 주소 |
Sutherland Asbill & Brennan LLP
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
5 |
초록
▼
Airfoils are provided for a wind turbine blade that is associated with a wind turbine hub. Each airfoil includes a blunt trailing edge, a substantially oval shaped suction side, and a substantially S-shaped pressure side. The airfoils decrease in cross-sectional area along the turbine blade in a dir
Airfoils are provided for a wind turbine blade that is associated with a wind turbine hub. Each airfoil includes a blunt trailing edge, a substantially oval shaped suction side, and a substantially S-shaped pressure side. The airfoils decrease in cross-sectional area along the turbine blade in a direction extending away from the wind turbine hub.
대표청구항
▼
1. A plurality of airfoils for a wind turbine blade, the wind turbine associated with a wind turbine hub, each airfoil comprising: a leading edge;a blunt trailing edge;a chord line extending from the leading edge to the blunt trailing edge;a substantially oval shaped suction side; anda substantially
1. A plurality of airfoils for a wind turbine blade, the wind turbine associated with a wind turbine hub, each airfoil comprising: a leading edge;a blunt trailing edge;a chord line extending from the leading edge to the blunt trailing edge;a substantially oval shaped suction side; anda substantially S-shaped pressure side, wherein the plurality of airfoils decrease in cross-sectional area along the turbine blade in a direction extending away from the wind turbine hub;wherein the substantially oval shaped suction sides comprise non-dimensional coordinate values of x/c and positive y/c within the ranges set forth in Tables 2, 4, 6, and 8, the x/c values representing locations on the chord lines in relation to the trailing edges and the positive y/c values representing distances from the chord lines to points on the suction sides;wherein the substantially S-shaped pressure sides comprise non-dimensional coordinate values of x/c and negative y/c within the ranges set forth in Tables 2, 4, 6, and 8, the x/c values representing locations on the chord lines in relation to the trailing edges and the negative y/c values representing distances from the chord lines to points on the pressure sides. 2. The plurality of airfoils of claim 1, wherein each substantially oval shaped suction side and substantially S-shaped pressure side does not intersect the chord line of the airfoil. 3. The plurality of airfoils of claim 1, wherein each of the plurality of airfoils is connected by a smooth curve. 4. The plurality of airfoils of claim 1, wherein each of the plurality of airfoils comprises a first width about the blunt trailing edge, a second width moving towards the leading edge, the second width being smaller than the first width, and a third width moving further towards the leading edge, the third width being larger than the first width. 5. The plurality of airfoils of claim 1, wherein each of the plurality of airfoils comprises a curved leading edge. 6. The plurality of airfoils of claim 1, each comprising an inboard region airfoil. 7. A wind turbine blade comprising: an inboard region comprising a plurality of airfoils, each airfoil comprising: a leading edge;a chord line extending from the leading edge to the blunt trailing edge;a blunt trailing edge;a substantially oval shaped suction side; anda substantially S-shaped pressure side, the plurality of airfoils decreasing in cross-sectional area along the turbine blade in a direction extending away from a wind turbine hub;an outboard region; anda tip region;wherein the substantially oval shaped suction sides comprise non-dimensional coordinate values of x/c and positive y/c within the ranges set forth in Tables 2, 4, 6, and 8, the x/c values representing locations on the chord lines in relation to the trailing edges and the positive y/c values representing distances from the chord lines to points on the suction sides;wherein the substantially S-shaped pressure sides comprise non-dimensional coordinate values of x/c and negative y/c within the ranges set forth in Tables 2, 4, 6, and 8, the x/c values representing locations on the chord lines in relation to the trailing edges and the negative y/c values representing distances from the chord lines to points on the pressure sides. 8. The wind turbine blade of claim 7, wherein on each airfoil the substantially oval shaped suction side and the substantially S-shaped pressure side does not intersect its chord line. 9. The wind turbine blade of claim 7, wherein each airfoil is connected by a smooth curve. 10. The wind turbine blade of claim 7, wherein each airfoil comprises a first width about the blunt trailing edge, a second width moving towards the leading edge, the second width being smaller than the first width, and a third width moving further towards the leading edge, the third width being larger than the first width. 11. The wind turbine blade of claim 7, wherein each airfoil comprises a curved leading edge. 12. The wind turbine blade of claim 7, wherein the plurality of airfoils include: a first airfoil having a radial location on the turbine blade between about 30 to 45% of a turbine blade rotor radius in a direction extending away from a wind turbine hub and a maximum thickness of about 30% of the first airfoil chord length;a second airfoil having a radial location on the turbine blade between about 27 to 30% of turbine blade rotor radius in a direction extending away from a wind turbine hub and a maximum thickness of about 35% of the second airfoil chord length;a third airfoil having a radial location on the turbine blade between about 23 to 27% of turbine blade rotor radius in a direction extending away from a wind turbine hub and a maximum thickness of about 40% of the third airfoil chord length; anda fourth airfoil having a radial location on the turbine blade between about 21 to 24% of turbine blade rotor radius in a direction extending away from a wind turbine hub and the maximum thickness of about 45% of the fourth airfoil chord length. 13. The wind turbine blade of claim 7, wherein a first of the plurality airfoils comprises a profile substantially in accordance with the ranges of non-dimensional coordinate values of x/c and y/c set forth in Table 2, the x/c values representing locations on the chord line in relation to the trailing edge and the y/c values representing distances from the chord line to points on the suction and pressure sides. 14. The wind turbine blade of claim 7, wherein a second of the plurality airfoils comprises a profile substantially in accordance with the ranges of non-dimensional coordinate values of x/c and y/c set forth in Table 4, the x/c values representing locations on the chord line in relation to the trailing edge and the y/c values representing distances from the chord line to points on the suction and pressure sides. 15. The wind turbine blade of claim 7, wherein a third of the plurality airfoils comprises a profile substantially in accordance with the ranges of non-dimensional coordinate values of x/c and y/c set forth in Table 6, the x/c values representing locations on the chord line in relation to the trailing edge and the y/c values representing distances from the chord line to points on the suction and pressure sides. 16. The wind turbine blade of claim 7, wherein a fourth of the plurality airfoils comprises a profile substantially in accordance with the ranges of non-dimensional coordinate values of x/c and y/c set forth in Table 8, the x/c values representing locations on the chord line in relation to the trailing edge and the y/c values representing distances from the chord line to points on the suction and pressure sides. 17. A turbine blade having a plurality of airfoils, comprising: a first airfoil comprising a profile with non-dimensional coordinate values of x/c and y/c within the ranges set forth in Table 2;a second airfoil comprising a profile with non-dimensional coordinate values of x/c and y/c within the ranges set forth in Table 4;a third airfoil comprising a profile with non-dimensional coordinate values of x/c and y/c within the ranges set forth in Table 6; anda fourth airfoil comprising a profile with non-dimensional coordinate values of x/c and y/c within the ranges set forth in Table 8,wherein for each airfoil the x/c values represent locations on a chord line for the airfoil in relation to its trailing edge and the y/c values represent distances from the chord line for the airfoil to points on its suction and pressure sides.
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