Blade for a wind turbine rotor
Provided is a blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, said rotor comprising a hub, from which the blade extends substantially radially when mounted, said blade having a chord plane extending between a leading edge and a trailing edge of said blade, a root area closest to the hub, an airfoil area furthest away from the hub, a transition area between the root area and the airfoil area, a first airfoil extending substantially along the entire airfoil area, and a second airfoil separately mounted to the blade, said second airfoil arranged at a mutual distance transverse to the chord plane and extending along the root area of the blades.
1. A blade ( 1 ) for a rotor of a wind turbine having a substantially horizontal rotor shaft, said rotor comprising a hub from which the blade ( 1 ) extends substantially radially when mounted, said blade ( 1 ) comprising:
a chord plane (K) extending between the leading edge ( 5 ) and the trailing edge ( 6 ) of said blade;
a root area ( 2 ) closest to the hub, an airfoil area ( 4 ) furthest away from the hub and a transition area ( 3 ) between the root area ( 2 ) and the airfoil area ( 4 );
a single airfoil substantially along the entire airfoil area ( 4 );
at least a first root segment ( 7 ) and a second root segment ( 8 ) along substantially the entire root area ( 2 ), the segments being arranged with a mutual spacing transverse to the chord plane (K),
wherein at least one of the root segments ( 7 , 8 ) has an airfoil profile, and wherein a total length of the root area and the transition area is between 5% and 35% of a total length of the blade.
2. The blade ( 1 ) according to claim 1 , wherein the chord plane (K) of the blade is twisted in the longitudinal direction (L) of the blade, where the twist is up to 80 degrees in the longitudinal direction (L) of the blade.
3. The blade ( 1 ) according to claim 1 , wherein the chord plane (K 1 , K 2 ) of the at least one root segment ( 7 , 8 ) with airfoil profile is substantially parallel to the chord plane (K) of the blade in the area closest to the hub.
4. The blade ( 1 ) according to claim 1 , wherein both the first and the second segments ( 7 , 8 ) are provided with airfoil profiles.
5. The blade ( 1 ) according to claim 1 , wherein the chord plane (K 1 , K 2 ) of the at least one root segment ( 7 , 8 ) with airfoil profile has a substantially constant width, the chord plane (K 3 , K 4 ) of the transition area ( 3 ) becoming wider with increasing distance (L) from the hub, and the chord plane (K) of the airfoil area ( 4 ) becoming narrower with increasing distance from the hub.
6. The blade ( 1 ) according to claim 1 , wherein the transition area ( 3 ) comprises at least a first transition segment ( 9 ) and a second transition segment ( 10 ), said segments being arranged with a mutual distance, as seen transverse to the chord plane (K), where at least one of the transition segments ( 9 , 10 ) is provided with an airfoil profile.
7. The blade ( 1 ) according to claim 6 , wherein the chord plane (K 1 , K 2 ) of the at least one transition segment ( 9 , 10 ) with airfoil profile is substantially parallel to the chord plane (K) of the blade itself at the transition between the transition area ( 3 ) and the airfoil area ( 4 ).
8. The blade ( 1 ) according to claim 6 , wherein the first and the second root segment ( 7 , 8 ) merge into the first and the second transition segment ( 9 , 10 ), where the first and the second transition segment ( 9 , 10 ) are joined with the portion of the transition area ( 3 ) furthest away from the hub.
9. The blade ( 1 ) according to any claim 1 , wherein the first and the second root segment ( 7 , 8 ) are joined at the portion of the transition area ( 3 ) closest to the hub.
10. The blade ( 1 ) according to claim 1 , wherein the first and the second root segment ( 7 , 8 ) are joined to form a common mounting area at the portion of the root area ( 2 ), said area preferably having a substantially circular cross-section.