Wind turbine blade with trailing edge flaps

The invention relates to a rotor blade of a rotor of a wind power plant, with over the rotor blade length extending Blattvorderund Blade trailing edge.

Rotor blades of the type mentioned are preferably radially to several disposed about a hub. The rotor blades are preferably twisted. They serve as propulsion organs incident airflow generating a rotational movement around the hub. In known wind turbines are rotors according to the site anticipated wind conditions designed blades or selected one rotor blade (Einflügler), ie, the shape, twist, Leaf length, leaf depth and so on are in the preparation of may have been tailored to the use and location therefore will not be changed during operation.

Object of the invention is to provide a rotor blade of a rotor of a to provide wind power plant, the customization of its operations be adapted to the prevailing situation in each case can.

This object is achieved in that the area the blade trailing edge at least over a portion of the rotor blade length is constructed as aerodynamic flap. The pivotable, and thus the aerodynamic properties of the Blade changing flap can in their swivel angle such be adjusted to provide a performance adjustment takes place. It Therefore, an adaptation to the incoming flow and / or resistance and buoyant conditions occur. The aerodynamic lift can reinforce or reduce or targeted to stall influence. The invention is a load reduction operation, For example, at extremely high flow, possible.

It is advantageous if the flap in the direction toward the top and / or pivoted towards the underside of the rotor blade is mounted. Thus it can be from a central neutral position pivot both in the one and in the other direction. In this way it is possible for the profile center line of the Rotor blade according to influence. The result is a corresponding aerodynamic behavior.

It is advantageous if one, the flap into the desired pivot position Shifting and retaining control device is provided. The controller pivots the flap into the desired Position and fixes this position until by renewed control commands a new position to be occupied.

Preference is given more independently in the swivel angle adjustable flaps provided on a rotor blade. The flaps are all within the area of ​​the blade trailing edge, said due to their radial arrangement the turning circle of the rotor at least one flap is present, which lies further away from the axis of rotation of the rotor as another flap which is located more towards the rotational axis. The peripheral velocity is therefore greater on the flap, the further away it is from the axis of rotation. Since the plurality of flaps be adjusted independently of each other in their position can be very precisely metered aerodynamic changes can make to the airfoil.

The flap chord one stone may vary depending on the rotor blade depth be determined in the design. If more Flaps are provided on a rotor blade, it is advantageous if these different sized flap chord exhibit. That's the way it is for example, possible to use a flap with large flap chord for the Braking the rotor, or to use a starting aid of the rotor. Another flap with smaller flap chord can be used, the performance in normal operation optimally adjust.

In particular, it may be provided that at the trailing edge adjoin the rotor blade located flaps directly, So -about the length of the blade as seen directly adjacent to each other.

It is advantageous if the flap as the curvature of the profile of Rotor blade formed by pivoting influencing Flap is. Since the pivot position of the flap the profile center line changes, in particular bulges, is such a flap as Flap designated. With the change in the course of the profile center line to change the aerodynamic properties of the rotor blade.

The flap can preferably as airbrake and / or as starting aids flap be formed.

The pivoting of the flap may preferably continuously or in Levels are adjusted. Continuous adjustment can a particularly fine tuning to the respective existing wind technology Situation.

The drawings illustrate the invention with reference to embodiments specifically:<dl tsize="7"><dt>figure 1</dt><dd>a plan view of a portion of an aerodynamic two Flaps provided rotor blade,</dd><dt>figure 2</dt><dd>appropriate, another embodiment of the figure 1 view</dd><dt>figure 3</dt><dd>a cross-section through the profile of a rotor blade,</dd><dt>figure 4</dt><dd>a side rear view of a portion of a rotor blade,</dd><dt>figure 5</dt><dd>a cross sectional view of a rotor blade in the neutral position with standing and flap</dd><dt>figure 6</dt><dd>a cross-sectional view of a rotor blade with far deflected flap.</dd></dl>

1 shows an unspecified portion of a rotor blade 1 a Rotor of a wind turbine shown. The rotor may three for example, by 120 ° staggered rotor blades 1 exhibit. In operation, the rotor rotates about the in figure 1 indicated rotational axis 2. The rotation is in the figure 1 arrow 3 indicated.

The rotor blade 1 comprises a leading edge 4 and a trailing edge, 5 on. The leading edge 4 is in rotation 3; the blade trailing edge 5 is opposite to the direction of rotation. 3 In the area the blade trailing edge 5 of the blade 1 is a first flap 6 and - it angrenzend- a second flap 7 formed. Both flaps 6, 7 are pivotally movable about a rotation axis 8 and Rotational axis 9 mounted on the rotor blade. 1 The two axes of rotation 8 and 9 have radial or approximately radial course in relation to the rotor and are aligned in the embodiment of Figure 1 with each other. By means of a control device not shown in detail can be the flaps 6 and 7 are pivoted about their respective axis of rotation 8 and 9. FIG. The respective pivoting takes place continuously (infinitely) each flap 6, 7 -According to Figure 3 in the direction of the Top 10 of the rotor blade 1 can be pivoted so that the dashed position gives 11 or there is a swiveling possible in the opposite direction, whereby the dashed drawn position 12 sets.

The embodiment of Figure 2 essentially corresponds the embodiment of Figure 1, so that below only the changes will be discussed. It is seen that the Flap chord 13 of the two flaps 6 and 7 is different in size, the flap 6 with the larger flap chord 13 closer to him the axis of rotation 2 and the flap 7 with the lower flap chord 13 further away is from the rotational axis. 2 Due to the different Flaps depths 13 of the two flaps 6 and 7 have also the axes of rotation 8 and 9 different locations, that is, they are parallel or approximately parallel to one another offset.

Figure 4 illustrates the deployed position a flap 6 in side view the rotor blade 1. The rotation axis 2 is located in the plane; the rotor blade moves in accordance with numeral 3 in the Leaf level inside. The position marked with the flap 11 6, which is correspondingly also from the Figure 3, is in the direction oriented on the top 10 of the rotor blade, while the opposite Position of the flap 6, which is marked with 12, an orientation of the flap 6 in the direction of the underside 14 of the

Rotor blade 1 features.

5 shows a flap 6 in the middle or neutral position, ie, the profile center line 15 of the rotor blade 1 is substantially straight or slightly curved. If the flap 6 in a position pivoted according to FIG 6, then amends also the History profile center line 15, so that correspondingly different aerodynamic properties of the rotor blade 1 result.

The inventive aerodynamic flap that particular may be formed as Flaps, is an adaptation to the incident flow and / or the resistance characteristic and / or the buoyancy characteristics possible. The adjustment is made by appropriate pivoting of one or more flaps. In the embodiments are blades with multiple flaps shown. Of course, it is also conceivable that a rotor blade only having a flap. It is also possible that a flap or that a plurality of flaps over the entire length of the rotor blade 1 extends / extend. Using the controller leaves change the position of one or more flaps such that braking effect occurs. On the other hand, it is also conceivable to facilitate the start-up of the rotor flaps in a position bring to where it easier to pull off, so a larger aerodynamic lift effect. Further, it is due to the flaps possible to reduce the blade loading, provided that due the aerodynamic conditions high material stress occurs. Further, a limitation of rotor speed means the flap adjustable, can be proceeded in a manner that there is a deliberate stall and / or a targeted Reduction of aerodynamic lift occurs. A total of is thus the attainable torque of the rotor in accordance with affected. The flap 6 in the embodiment of FIGS 1 and 2, preferably to brake or as a start- be used. The flap 7 in the embodiments of Figures 1 and 2 is preferably the performance adjustment, in particular the increase in load or the load reduction.

It is preferred also conceivable that in case of multiple flaps these be adjusted in opposite directions to each other, ie, a flap is in Direction on the upper surface 10 of the rotor blade 1 and a different Flap adjusted in the direction of the underside 14 of the rotor blade 1, thereby providing an effective and individually customized.

Notwithstanding be arising from the from the embodiments Rotation axes 8, 9 of the flaps 6, 7, can also have a different be provided mechanism which to a corresponding removal or In pivoting the flaps leads, this movement but not carried out to a linear axis of rotation, but along a corresponding displacement path.