Abstract: According to an embodiment disclosed herein, a gurney flap assembly includes an actuator, and a flexible body attaching to the actuator, the body having a downwardly depending flap for moving into and out of an airstream in a pressure side of a wing, wherein the flexible body flexes in reaction to motion of the actuator. This increases the lift force of the rotor blade, wing or aerofoil blade.

Abstract: A wear-free, self-contained control device for an aerodynamic emergency brake of a wind energy converter is presented that comprises multiple components in order to provide a most effective means to control the rotation of a vertical axis wind turbine by a brake, which is able to activate itself without external actuation in malfunction situations and is able to shut down the vertical axis wind turbine. Therefore, a mass element is utilized to store mechanical energy which in turn is used to deploy an aerodynamic braking operation. It also represents a means to control and limit the amount of torque, as absorbed by the turbine in high-wind conditions, and thus provides the ability to harvest electrical/mechanical energy, beyond the normal operational wind speeds of turbines.

Abstract: A system and methods for reducing vibration in a rotatable member are provided. The system includes a blade tracking sensor, a rotatable member comprising an adjustable aspect, and a control computer. The control computer is configured to determine an axial position of each blade, determine a first blade that is displaced by a greatest distance along the axis in a first direction, modify an aspect of the first blade to facilitate reducing a vibration in the rotary blade system, determine if the vibration level in the rotary blade system is reduced, and select another rotatable member to modify such that a vibration in the rotary blade system is facilitated being further reduced.

Abstract: A system for actively controlling the span-wise rotational twist of a hollow beam along its longitudinal axis, including a hollow beam structure having a leading edge and a trailing edge region, the beam being split along its length, an actuator arranged between split surfaces of the beam, the actuator adapted to move the split surfaces in a longitudinal direction relative to each other, inducing a twist in the beam. The hollow beam is affixed to an external structure at one or both ends, with only the zero warping displacement points of the beam being attached to the external structure, material or device. In one embodiment, the actuator is a plurality of solid blocks with high thermal expansion coefficients arranged between frames of the split surfaces of the beam, with alternating blocks being heated by resistance heaters to cause expansion in the spanwise longitudinal direction.

Abstract: A band-type fan structure includes a transmission band body and multiple blades. The transmission band body has a lengthwise direction and a widthwise direction. The blades are side by side disposed on the transmission band body in parallel to each other and arranged in the lengthwise direction of the transmission band body. Each two adjacent blades define therebetween a flow way. The transmission band body is movable in the lengthwise direction, whereby the blades are driven by the transmission band body to transversely move to create an air volume. The band-type fan structure has a greatly minified volume. Also, the band-type fan structure overcomes the shortcoming of unstable operation of the conventional fan caused by deflection of the blades.

Abstract: An aerodynamic brake assembly for use with an airfoil such as the blade of a wind turbine rotor comprises deployable upper and/or lower spoiler plates incorporated in or attached to the airfoil. The spoiler plates can deploy under the influence of centrifugal forces when the rotating airfoil or rotor blade reaches a pre-determined rotational speed. The aerodynamic brake assembly may be integrated within the airfoil or attached to the tip of the airfoil such that, when not deployed, the upper and lower spoiler plates have a profile that approximately conforms to the profile of the part of the airfoil to which it the brake assembly is attached. Thus in a non-deployed state, the spoiler plates have a non-detrimental effect on the performance of the airfoil, and may even contribute to its aerodynamic lift properties.

Abstract: A wind turbine is provided. The wind turbine includes at least one blade having a pressure side, a suction side, a leading edge, and a trailing edge that define an airfoil-shaped profile. The pressure side has a morphable region. The wind turbine also includes a control system configured to activate the morphable region to alter the airfoil-shaped profile and reduce negative lift generated by the blade when the blade is oriented at a negative lift angle.

Abstract: Braking devices for wind turbines having a vertical axis are disclosed. An example braking device includes a flap able to tip about a tipping axis. The example flap has a center of gravity positioned outside the tipping axis. In addition, the example braking device disclosed herein includes a torque limiter having a disengagement torque. In addition, the example flap is mounted on the torque limiter, and the torque limiter is to allow the flap to tip through a tipping angle about the tipping axis for a rotational speed of the flap about the vertical axis which induces a torque at the torque limiter greater than or equal to the disengagement torque.

Abstract: A sensor system for measuring aerodynamic loads acting on a wind turbine rotor blade is disclosed. The measured aerodynamic loads can be converted to an angle of attack of the resulting wind which flows past the moving rotor blade. The sensor is realized as a trailing edge flap which is elastically moveable relative the main part of the wind turbine blade. By measuring motion of the trailing edge flap or corresponding motions of components of the sensor system, the aerodynamic forces acting on the blade can be determined. Due to the relative small dimensions of the sensor flap and the relative small displacements of the flap, the sensor system only affects the aerodynamic properties insignificantly.

Abstract: A variable chord morphing helicopter rotor blade is disclosed. The variable chord morphing helicopter rotor blade includes an extensible quasi-static chord section connected to the rotor blade, an adjusted airfoil chord length of the rotor blade corresponding to extension of the quasi-static chord section relative to a baseline airfoil chord length, the adjusted airfoil chord length determined according to helicopter flight conditions.

Abstract: A rotor blade assembly includes a rotor blade, a rotatable flap portion disposed along a span of the rotor blade. A rotary actuator is located inside the rotor blade and is operably connected to the flap portion to rotate the flap portion about a flap axis. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion disposed along a span of the rotor blade. A rotary actuator located inside the rotor blade and is operably connected to the flap portion to rotate the flap portion about a flap axis. The rotary actuator is absent oil, grease or other fluid lubricant.

Abstract: In accordance with one embodiment of the present application, an actuation system is configured for actuation of an airfoil member with a flap mechanism. The actuation system can include an upper drive tape and a lower drive tape, each partially wrapped around a first bearing and second bearing. An inboard frame can be actuated by at least one linear actuator. Similarly, an outboard frame can be actuated by at least one linear actuator. The inboard frame is coupled to the upper drive tape, while the outboard frame is coupled to the lower drive tape. An actuation of the inboard frame and outboard frame in a reciprocal manner acts move a flap input lever reciprocally upward and downward. A flap mechanism is configured to convert the movement of the flap input lever into rotational movements of the airfoil member.

Abstract: In accordance with one embodiment of the present application, an actuation system is configured for actuation of an airfoil member with a flap mechanism. The actuation system can include an upper drive tape and a lower drive tape, each partially wrapped around a first bearing and second bearing. An inboard frame can be actuated by at least one linear actuator. Similarly, an outboard frame can be actuated by at least one linear actuator. The inboard frame is coupled to the upper drive tape, while the outboard frame is coupled to the lower drive tape. An actuation of the inboard frame and outboard frame in a reciprocal manner acts move a flap input lever reciprocally upward and downward. A flap mechanism is configured to convert the movement of the flap input lever into rotational movements of the airfoil member.

Abstract: A rotor blade assembly includes a rotor blade and a movable trim tab located along a span of the rotor blade. A linear positioner is located inside the rotor blade and operably connected to the trim tab to move the trim tab thereby reducing rotor blade vibration. A method for reducing vibration of a rotor assembly includes energizing a linear positioner located inside a rotor blade of the rotor assembly and moving an output piston of the linear positioner. A trim tab located at the rotor blade is moved to a selected trim tab angle relative to the rotor blade by the output piston, and the linear positioner is deenergized thereby locking the trim tab at the selected trim tab angle.

Abstract: The system of the present application includes an adaptive twist system for a rotor blade. The adaptive twist system includes a slider mechanism coupled to a spar and to a skin. The slider mechanism provides structural connectivity between the spar and the skin while also selectively translated the skin relative to the spar, thereby causing the rotor blade to twist. A control system is used to operate the slider mechanism so that the rotor blade is automatically twisted into the optional shape during changes in flight modes.

Abstract: A rotor blade comprising a core blade section; and a trailing edge section, the trailing edge section being attached to the core blade section along a join interface. The trailing edge section comprises a shape memory material which is actuable so as to cause selective deformation of the trailing edge section between a first condition in which a trailing edge of the trailing edge section follows a substantially smooth profile and a second condition in which the trailing edge is perturbed. The direction of the perturbation may be oblique or perpendicular to the direction of flow over the blade in use. The rotor blade may be a fan or propeller for a gas turbine engine.

Abstract: A maximally efficient vertical axis wind turbine (MEVAWT) includes a rotatable circular frame having upper and lower concentric flat rings or disks which support a plurality of, typically three, four, five or six, pivotable cascades, each including a plurality of fixed, configurable airfoils. The airfoils preferably include a single, pivotable trailing flap and may include lateral extensions. The center and periphery of the lower ring are supported in suitable bearings to facilitate free rotation of the frame. Wind direction and velocity sensors provide data utilized to control drive mechanisms which orient each cascade and the flap of each airfoil to maximize the resultant power produced by the turbine.

Abstract: A pneumatic actuator system to provide for actuation of a device on a rotor blade. A high pressure volume unit mounted on the rotor blade, including an air inlet to allow entrance of air into the high pressure volume. At least one actuator on the rotor blade to actuate a device on the rotor blade, where the at least one actuator is connected to the high pressure volume to receive air from the high pressure volume for actuation. An air release unit connected to the at least one actuator to allow release of air from the at least one actuator. An air control unit connected to the high pressure volume unit to control air flow into the at least one actuator and is connected to the air release unit to control release of air from the at least one actuator.

Abstract: A hydraulic control valve (10) provided with at least one body (11) having a jacket (12) with a feed orifice (13). The hydraulic control valve (10) has a transfer rod (15) provided with at least one fluid transfer duct (16), at least one orifice (17) present inside the jacket (12), and a second orifice (18) arranged outside the jacket (12). The jacket (12) has a feed chamber (25) connected to said feed orifice (13) and a main fluid-return chamber (30) connected to discharge means (50) for discharging the fluid, control means (20) being secured to the jacket (12) in order to move the jacket (12) in translation relative to said transfer rod (15) so as to control the flow of fluid within said transfer rod (15).

Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.

Abstract: A rotor blade assembly includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator located inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator positioned inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant.

Abstract: A wind turbine rotor blade includes a root portion and an airfoil portion extending from the root portion and defined by a leading edge and a trailing edge. The airfoil portion further includes a main foil section and a trailing edge section that is pivotally connected to the main foil section along a span-wise extending pivot zone. The trailing edge section is biased to a neutral position wherein the trailing edge section is pivoted chord-wise to a low wind speed position relative to the main foil section.

Abstract: A helicopter includes an airframe, and a rotor system mounted to the airframe. The rotor system includes a plurality of rotor blades. Each of the plurality of rotor blades includes a root portion that extends to a tip portion through an airfoil portion. The airfoil portion includes first and second surfaces. An effector is mounted within the airfoil portion of at least one of the plurality of rotor blades. The effector includes a first end portion that extends to a second end portion through an intermediate portion, and a flap arranged at the second end portion. The effector is selectively actuated to shift from a first, stowed, position wherein the flap is positioned within the at least one rotor blade to a second, deployed, position, wherein flap projects through at least one of the first and second surfaces of the at least one rotor blade.

Abstract: An oil supply system for a propeller turbine engine including a propeller, a propeller gearbox connected to the propeller and a propeller adjusting device for altering the pitch angle of the propeller blades. The system includes an oil circuit and a propeller main pump for supplying the propeller gearbox and a propeller high-pressure pump supplying the propeller adjusting device with oil. The system includes an oil accumulator for providing, in the event of an undersupply of oil by the propeller main pump, oil contained in the oil accumulator to the inlet of the propeller high-pressure pump such that the pump inlet pressure at the inlet of the propeller high-pressure pump does not fall short of a certain minimum value. The oil accumulator is incorporated into the inflow to the propeller high-pressure pump to be continuously supplied and charged with oil of the propeller main pump.

Abstract: A method of controlling a wind turbine rotor blade, the blade comprising a pitch axis about which the blade can be pitched, and a flap movable to alter the aerodynamic profile of the blade, the method comprising the steps of: providing a pitch angle request (?) to a pitch actuator; determining an initial flap angle request (?_flap); providing a decoupled flap angle request (?) to a flap actuator; herein the decoupled flap angle request (?) is calculated from the pitch angle request (?) and the initial flap angle request (?_flap) such that the decoupled flap angle (?) provided to the flap actuator does not counteract the pitch angle request (?); and pitching the blade according to the pitch angle request (?) and moving the flap according to the decoupled flap angle request (?).

Abstract: A flap arrangement for a wind turbine rotor blade, which includes a leading edge, a trailing edge and a chord line between the leading edge and the trailing edge, is described. The flap arrangement includes a support portion and a flap portion which is passively moveable with respect to an angle between a surface normal of a surface of the flap portion and the chord line. The support portion and the flap portion are positioned relatively to each other such that the support portion provides a limit to the movement of the flap portion. Also described are a wind turbine rotor blade including the flap arrangement and a method of enhancing the aerodynamic performance of a blade.

Abstract: A slat (30) extending along an inboard portion of a wind turbine main blade element (22). The slat may have an end vortex modification appendage, such as winglet (34), endplate (64), raked wingtip (70), or down turned wingtip (72), and may be located behind a line defined perpendicular to a mean camber line of the main blade element at a leading edge of the main blade element. At least the leading edge (42S) of the slat may be disposed within a zone (48) of airflow that generally parallels the suction side (40) of the main blade element. The slat may have a flatback trailing edge (44F). Vortex generators (60) may be attached to the slat. Slats may be retrofitted to a wind turbine rotor (20) by attaching them to the spar caps (56) of the blades or to the hub (26) of the rotor.

Abstract: An enhanced performance rotorcraft rotor blade system and methods are presented. A rotor blade comprises an inboard blade portion, and at least one controllable surface coupled to the inboard blade portion. The at least one controllable surface is operable to improve a lift of the inboard blade portion by altering an angle of attack of the inboard blade portion independent of the rotor blade.

Abstract: Lift propulsion and stabilizing system and procedure for vertical takeoff and landing aircraft that consists in applying simultaneously and combined as lifters during the initial portion of the climb and at the end of the descent of: a) some fans or electric turbines, EDF, and b) at least one rotor with external blades and/or rotary and/or c) the engine flow directed downwards and/or d) pressure air jets injected on leading edges control fins, and/or e) water jets and/or f) supplemented with aerodynamic lift produced during frontal advance of the aircraft, the stabilization is achieved by the gyroscopic stiffness of the rotor and two or more lifting fans oscillating fins and/or air jets located on two or stabilizers more peripheral points in a plane perpendicular to the vertical axis of the aircraft.

Abstract: A rotor assembly for a rotary wing aircraft includes a plurality of rotor blades operably connected to a rotor shaft. Two or more active adaptive devices are located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A method of operating a rotor assembly of a rotary wing aircraft includes rotating a plurality of rotor blades about a rotor shaft. Two or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades are activated and change one or more operational characteristics of the rotor assembly.

Abstract: A wind turbine blade having a suction side and a pressure side, which sides are connected at a leading edge and a trailing edge, wherein one or more shape modifiable air foil sections are defined in the area of the trailing edge of the blade, and wherein said one or more shape modifiable air foil sections are attached to a blade body, each of the one or more modifiable air foil sections having an upper skin and a lower skin, a first one of the upper and lower skin being secured to the blade body, and a second one of the upper and lower skin being slidably movable with respect to the blade body, so that a force is applied to one of said skins cause said second skin to slide with respect to the blade body, so as to thereby modify the air foil shape of the trailing edge.

Abstract: A fluid turbine comprises a rotor rotatable in use about an axis transverse to the direction of fluid flow, the rotor having a first part carrying a plurality of arcuate blades that may be arranged selectably in compact straight shapes or in arcuate shapes and a second part journalled in a base structure by two or more bearings. Another aspect of the invention discloses an installation frame, devised to support the turbine or other elongated structures in a folded arrangement for transportation on a trailer, and to support assembly and erection thereof.

Abstract: A mechanism for synchronously varying pitch of a multi-blade rotor, such as rotors used in wind or hydraulic generator and helicopter is provided in the present invention.

Abstract: A wind turbine rotor blade includes a root portion and an airfoil portion extending from the root portion and defined by a leading edge and a trailing edge. The airfoil portion further includes a main foil section and a trailing edge section that is pivotally connected to the main foil section along a span-wise extending hinge line. A passive torsion element is coupled between the main foil section and the trailing edge section. The torsion element is biased to a neutral position wherein the trailing edge section is pivoted chord-wise to a low wind speed position relative to the main foil section. The trailing edge section is self-actuating from the low wind speed position to an increased wind speed position relative to the main foil section as a function of the biasing force of the torsion element and wind speed over the airfoil section.

Abstract: A method for shutdown of a wind turbine having one or more wind turbine blades includes detecting an operational condition of the wind turbine that calls for an expedited or emergency shutdown of the wind turbine by a manner other than normal pitch control shutdown. Upon detection of the operational condition, one or more air brake flaps configured on each of the turbine blades is deployed by removing power to a fail-safe actuator operatively coupled to each of the air brake flaps. The fail-safe actuator is configured to hold the respective air brake flap at a retracted position relative to a suction side of the turbine blade in a powered state of the fail-safe actuator and to release the air brake flap for automatic deployment to an open position upon loss of power to the fail-safe actuator.

Abstract: The invention relates to a wind turbine, comprising a hub, at least one blade, said blade being pivotably installed at said hub, at least one pitch bearing, said pitch bearing having an inner bearing ring and an outer bearing ring, said inner bearing ring having an inner wall in radial direction and a first end and a second end in axial direction and at least one reinforcing element to enhance the stiffness of said pitch bearing, wherein the reinforcing element is arranged adjoining the inner wall of the inner bearing ring.

Abstract: A system and method for controlling clearance between tips of moving blades of an aeroplane gas-turbine engine and a turbine shroud of an outer casing surrounding the blades. The method includes controlling, according to an operating speed of the engine, a valve positioned in an air duct opening at a stage of the compressor of the engine and leading into a control housing positioned around the outer surface of the turbine shroud and supplied with air coming only from the compressor stage. The valve is opened to cool the turbine shroud during a high-speed phase corresponding to takeoff and climb phases of an aeroplane propelled by the engine and during a nominal-speed phase following the high-speed phase and corresponding to a cruise phase of the aeroplane.

Abstract: Aircraft with an emission-free drive and method for emission-free driving of an aircraft. The aircraft includes a drive device, having a flapping wing device, structured and arranged to generate thrust, a lift device structured and arranged to generate lift, and a heat engine, having at least one flat-plate Stirling engine drivable by solar thermal radiation, structured and arranged to convert thermal energy into kinetic energy to drive the drive device.

Abstract: In this presentation, we study various aspects of the wind turbines or wind mills. We optimize the performances of both a single wind turbine and a wind farm, collectively. We study the nozzles on the blades and all the variations and accessories for the operation of a nozzle. We also explore flow patterns around the blades, the mechanisms to get air or other gasses to the blades, the couplers for the electrical connections and the gas connections, and the gaps, holes, channels, conduits, or openings on the body or structure of a tower. We also present various mathematical models and formulations for optimizations.

Abstract: A rotor blade assembly and a method for adjusting a loading capability of a rotor blade are disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade further defines a span and a chord. The rotor blade assembly further includes a spoiler assembly operable to alter a flow past a surface of the rotor blade. The spoiler assembly is incrementally deployable from the surface along one of a length or a width of the spoiler assembly.

Abstract: A fluid interface device, such as an airfoil assembly, can include a device structure and at least one movable band oriented such that the band moves in a direction of fluid flow. The at least one movable band can be supported on the device structure such that an outer surface of the movable band is exposed along the device structure and is capable of movement relative thereto such that a relative velocity can be maintained between the outer surface and the device structure. The fluid interface device can also include an edge extension disposed along the leading edge of the device structure. An airplane, a wind turbine and a method are also included.

Abstract: A blade extension for a rotor blade and a rotor blade assembly for a wind turbine are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge each extending in a generally span-wise direction between a tip and a root. At least one of the leading edge or the trailing edge has a modified aerodynamic contour. The rotor blade assembly further includes a blade extension including a first panel and an opposed second panel. Each of the first panel and the second panel includes an interior surface and an exterior surface each extending between a proximal end and a distal end. The distal end of each of the first panel and the second panel is spaced apart from the rotor blade in a generally chord-wise direction in a standard operation position.

Abstract: A turbine blade assembly includes an outboard blade section that folds onto an inboard blade section at a hinge located between the sections. When the outboard blade section is rotating to a folded position a longitudinal axis of the outboard blade section is transverse to a longitudinal axis of the inboard blade section. When the outboard blade section is in a fully folded position, the axes are parallel. The method of folding the outboard blade section includes adjusting the pitch of the turbine blade while it is rotating. Adjusting the pitch changes the pressure on a non-hinge side of the turbine blade and results in the outboard blade section folding with respect to the inboard blade section.

Abstract: A deformable trailing edge section (3) of a wind turbine blade (1), at least part of said section (3) being formed in a deformable material. The blade section (3) comprises one or more cavities (5) being in connection with or connectable to a fluid source in a way that allows fluid to stream from the fluid source to the cavity or cavities (5), so that the shape of the deformable trailing edge section (3) and thereby the camber of the blade cross-section (3) is changeable by the pressure of fluid in the cavity or cavities (5) with insignificant changes of the thickness and chord wise length of the deformable trailing edge section. Furthermore a wind turbine blade (1) is described, having at least one of such trailing edge section (s) (3) and to a system (11) for mounting a blade section (3) on a main blade (2) of a wind turbine. In addition a method of manufacturing a deformable trailing edge section (3) of a wind turbine blade (1) is disclosed.

Abstract: The system of the present application includes an adaptive twist system for a rotor blade. The adaptive twist system includes a slider mechanism coupled to a spar and to a skin. The slider mechanism provides structural connectivity between the spar and the skin while also selectively translated the skin relative to the spar, thereby causing the rotor blade to twist. A control system is used to operate the slider mechanism so that the rotor blade is automatically twisted into the optional shape during changes in flight modes.

Abstract: A wind turbine having at least a blade comprising a first component having an aerodynamic profile with a leading edge, a trailing edge, and suction and pressure sides between the leading edge and the trailing edge, and a second component, attached to the trailing edge and/or to the leading edge of the first component in at least a part of the blade, comprising one or several upwards and/or downwards deflectable flaps that allow changing the flow over the blade, in which a device for deflecting each of the flaps comprises an actuating force or torque provided by scaling devices connected to a predetermined location in the outer surface of the blade, through a duct, so that the changes in the wind pressure at this location can be scaled to the actuating force or torque.

Abstract: A wind turbine rotor blade extension portion having a permanent framework with one or more chord-wise members and a substantially span-wise member. A membrane is located over the framework to thereby generate a streamlined surface. The extension portion is configured to transmit aerodynamic loads from the membrane, along the chord-wise members to a rotor blade to which the extension portion is connected, in use.

Abstract: A blade extension for a rotor blade and a rotor blade assembly for a wind turbine are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge each extending in a generally span-wise direction between a tip and a root. The rotor blade assembly further includes a blade extension including a first panel and an opposed second panel. Each of the first panel and the second panel includes an interior surface and an exterior surface each extending between a proximal end and a distal end. The distal end of each of the first panel and the second panel is spaced apart from the rotor blade in a generally chord-wise direction in a standard operation position.

Abstract: The present invention relates to a wind turbine blade for a rotor of a wind turbine having a substantially horizontal rotor shaft and a hub connected to the rotor shaft, the blade extending in a substantially radial direction from the hub, when mounted to the hub, wherein the blade comprises: a profiled contour comprising a pressure side and a suction side and a leading edge and a trailing edge connecting the pressure side and the suction side, a lift regulating device, and an operation device comprising an electromagnet configured to operate the lift regulating device between a first state and a second state. The lift regulating device comprises a magnetisable material.

Abstract: A wind turbine rotor blade is equipped with an air chamber and equipped via the air chamber to route a modulation beam out of the rotor blade such that the air current along the rotor blade is changed. Thereby the laminar current is changed into a turbulent current on the one hand and its detachment and on the other hand its recreation is achieved in order to produce the laminar current. The control may occur via electrostatic actuators via a learnable control strategy based on neural forecasts, which take the complexity of the non-linear system into account and allow for the plurality of influencing factors. The stress on the rotor blades may be reduced, resulting in longer service life and reduced maintenance costs, a higher level of efficiency or quieter operation.