IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0937183
(2007-11-08)
|
등록번호 |
US-8197218
(2012-06-12)
|
발명자
/ 주소 |
- Tangler, James L.
- Somers, Dan L.
|
출원인 / 주소 |
- Alliance for Sustainable Energy, LLC
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
2 인용 특허 :
5 |
초록
▼
Thick airfoil families with desirable aerodynamic performance with minimal airfoil induced noise. The airfoil families are suitable for a variety of wind turbine designs and are particularly well-suited for use with horizontal axis wind turbines (HAWTs) with constant or variable speed using pitch an
Thick airfoil families with desirable aerodynamic performance with minimal airfoil induced noise. The airfoil families are suitable for a variety of wind turbine designs and are particularly well-suited for use with horizontal axis wind turbines (HAWTs) with constant or variable speed using pitch and/or stall control. In exemplary embodiments, a first family of three thick airfoils is provided for use with small wind turbines and second family of three thick airfoils is provided for use with very large machines, e.g., an airfoil defined for each of three blade radial stations or blade portions defined along the length of a blade. Each of the families is designed to provide a high maximum lift coefficient or high lift, to exhibit docile stalls, to be relatively insensitive to roughness, and to achieve a low profile drag.
대표청구항
▼
1. A blade for large wind turbines rotatable about a horizontal axis, the blade being adapted for mounting to a hub on the turbines for rotation about said horizontal axis and extending a distance radially outward from the horizontal axis to a tip, the blade comprising: a primary span region extendi
1. A blade for large wind turbines rotatable about a horizontal axis, the blade being adapted for mounting to a hub on the turbines for rotation about said horizontal axis and extending a distance radially outward from the horizontal axis to a tip, the blade comprising: a primary span region extending from a point that is approximately sixty-five percent of the distance radially outward from the horizontal axis to a point that is approximately eighty-five percent of the distance radially outward from the horizontal axis; anda primary airfoil in the primary span region, the primary airfoil having a thickness of at least about twenty-one percent, a Reynolds number of at least about 4,000,000, and a maximum lift coefficient of about 1.6. 2. The blade of claim 1, wherein the blade has a length in the range of about 20 to 50 meters as measured from the horizontal axis to the tip. 3. The blade of claim 1, wherein the primary airfoil further comprises: an upper surface and a lower surface, both of which extend spaced-apart in relation to each other from a leading edge to a trailing edge; anda chord line with a length c extending in a straight line between the leading edge and the trailing edge, said upper surface and said lower surface having shapes and contours expressed by x/c values and y/c values, wherein the x/c values are dimensionless coordinates that represent locations on the length of the chord line and the y/c values are dimensionless coordinates that represent heights from the chord line to points on the upper surface and on the lower surface substantially as follows: Upper Lower SurfaceSurface x/cx/cy/c0.000060.001120.00004−0.00084.00321 .01040.00041 −.00254.01104 .02127.00138 −.00406.02343 .03307.00288 −.00560.04015 .04540.01318 −.01192.06101 .05794.02942 −.01794.08576 .07041.05165 −.02385.11413 .08253.07932 −.03013.14580 .09406.11146 −.03674.18042 .10474.14756 −.04351.21762 .11434.18687 −.05030.25699 .12262.22887 −.05701.29810 .12934.27253 −.06393.34048 .13417.31589 −.07002.38383 .13653.35873 −.07334.42854 .13632.40193 −.07288.47434 .13395.44627 −.06859.52084 .12962.49216 −.06086.56764 .12354.53971 −.04984.61431 .11592.59018 −.03645.66042 .10703.64307 −.02282.70550 .09715.69724 −.01029.74904 .08657.75132 .00013.79053 .07559.80381 .00775.82943 .06449.85314 .01212.86518 .05352.89755 .01296.89719 .04283.93491 .01083.92504 .03222.96391 .00721.94908 .02179.98422 .00357.96943 .01245.99611 .00096.98554 .005331.00000.00000.99621 .001201.00000.00000. 4. The blade of claim 1, wherein the primary airfoil is positioned at a blade radial station of about 0.75. 5. The blade of claim 1, further comprising: an intermediate span region extending from a point that is approximately eighty percent of the distance radially outward from the horizontal axis to a point that is approximately one hundred percent of the distance radially outward from the horizontal axis; andan intermediate airfoil positioned radially outboard from the primary airfoil in the intermediate span region, the intermediate airfoil having a thickness of at least about eighteen percent, a Reynolds number of at least about 3,500,000, and a maximum lift coefficient of about 1.5. 6. The blade of claim 5, wherein the intermediate airfoil is positioned at a blade radial station of about 0.90. 7. The blade of claim 5, wherein the intermediate airfoil further comprises: an upper surface and a lower surface, both of which extend spaced-apart in relation to each other from a leading edge to a trailing edge; and a chord line with a length c extending in a straight line between the leading edge and the trailing edge, said upper surface and said lower surface having shapes and contours expressed by x/c values and y/c values, wherein the x/c values are dimensionless coordinates that represent locations on the length of the chord line and the y/c values are dimensionless coordinates that represent heights from the chord line to points on the upper surface and on the lower surface substantially as follows: Upper SurfaceLowerx/cv/cSurfacex/c0.000040.000880.00004 −0.00080.00036 .00277.00017−.00155.00449 .01168.00041 −.00221.01307 .02201.00080 −.00281.02606 .03319.00134 −.00340.04333 .04479.00280 −.00458.06483 .05655.00966 −.00795.09031 .06828.02422 −.01170.11951 .07975.04525 −.01480.15212 .09077.07229 −.017%.18776 .10113.10441 −.0213122608.11064.14105 −.0247926663.11912.18146 −.0283130899.1263822509−.03171.35269 .1322627122−.0348539728.13659.31929 −.03752.44223.1391736859−.03951.48707.13978.41855−.0405453137.13799.46850 −.04013.57522.1334951847−.03767.61871.1264056861−.03326.66185.11707.61888 −.02718.70445.10608.66924 −.01993.74609.09394.71934 −.01226.78632.08116.76865 −00492.82460.06818.81639 .00118.86035.05544.86130 .00530.89294 .04327.90193 .00707.92180.03167.93666 .00668.94699.02083.96429.00489.96834.01157.98416.00263.98514.00481.99606.00077.99614.001051.00000.000001.00000.00000. 8. The blade of claim 1, further comprising: a tip span region extending from a point that is approximately ninety percent of the distance radially outward from the horizontal axis to a point that is approximately one hundred percent of the distance radially outward from the horizontal axis; anda tip airfoil positioned radially outboard from the primary airfoil in the tip span region, the tip airfoil having a thickness of at least about fifteen percent, a Reynolds number of at least about 2,500,000, and a maximum lift coefficient of about 1.4. 9. The blade of claim 8, wherein the intermediate airfoil is positioned at a blade radial station of about 1.0. 10. The blade of claim 8, wherein the intermediate airfoil further comprises: an upper surface and a lower surface, both of which extend spaced-apart in relation to each other from a leading edge to a trailing edge; and a chord line with a length c extending in a straight line between the leading edge and the trailing edge, said upper surface and said lower surface having shapes and contours expressed by x/c values and y/c values, wherein the x/c values are dimensionless coordinates that represent locations on the length of the chord line and the y/c values are dimensionless coordinates that represent heights from the chord line to points on the upper surface and on the lower surface substantially as follows: Upper SurfaceLower Surfacex/cy/cx/cy/c0.000000.000280.00010−0.00126.00011.00150.00026−.00194.00328.00973.00053−.00252.01071.01942.00094−.00303.02242.03000.00150−.00353.03830.04102.00188−.00380.05831.05217.00298−.00448.08228.015320.01074−.00728.11007.07390.02577−.00958.14137.08415.04734−.01088.17583.C9376.07510−.0119221310.10256.10825−.0129525274.11037.14628−.0140429436.11701.18846−.0152233747.1223323423−.0164938161.1261428287−.01779.42629.1282433377−.01907.47105 .1283038622−.02025.51577 .12599.43959−.02122.56040 .12129.49317 −.02188.60480 .11436.54634−.02208.64882 .10544.59843 −.02158.69229 .09486.64911 −.02005.73496 .08312.69821 −.01745.77642.07079.74555 −.01394.81614 .05839.79090−.00991.85352 .04638.83384 −.00585.88788 .03517.87378 −.0023491858.02488.90980.00013.94539 .01576.94089 .00144.%785.0083996513.00169.98514 .00333.98476 .00118.99619 .00069.99616 .000411.00000.000001.00000.00000. 11. A wind turbine that rotates about a horizontal axis, comprising: a plurality of turbine blades mounted to a hub of the wind turbine for rotation about the horizontal axis and extending a distance radially outward from the horizontal axis to a tip;an airfoil family defining cross-sections of each of the blades, the airfoil family comprising an inboard airfoil with a thickness of at least about 21 percent, a tip airfoil proximal to the tip of the blade with a thickness of at least about 15 percent, and an intermediate airfoil positioned between the inboard and tip airfoils with a thickness of at least about 18 percent;wherein the turbine blades have a length measured from the horizontal axis to the tip of at least about 20 meters and wherein each of the blades further comprises:a primary span region extending from a point that is approximately sixty-five percent of the distance radially outward from the horizontal axis to a point that is approximately eighty-five percent of the distance radially outward from the horizontal axis, wherein the inboard airfoil is positioned in the primary span region, the inboard airfoil having a Reynolds number of at least about 4,000,000 and a maximum lift coefficient of about 1.6;an intermediate span region extending from a point that is approximately eighty percent of the distance radially outward from the horizontal axis to a point that is approximately one hundred percent of the distance radially outward from the horizontal axis, wherein the intermediate airfoil is positioned radially outboard from the inboard airfoil in the intermediate span region, the intermediate airfoil having a Reynolds number of at least about 3,500,000 and a maximum lift coefficient of about 1.5; anda tip span region extending from a point that is approximately ninety percent of the distance radially outward from the horizontal axis to a point that is approximately one hundred percent of the distance radially outward from the horizontal axis, wherein the tip airfoil is positioned radially outboard from the intermediate airfoil in the tip span region, the tip airfoil having a Reynolds number of at least about 2,500,000 and a maximum lift coefficient of about 1.4.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.