DEVICE WITH AN ASYMMETRIC, ADJUSTABLE WING PROFILE

Description

[0001] The invention relates to a device with an asymmetrical wing profile and with an adjustment device.

[0002] The device with the asymmetrical airfoil and adjustment mechanism can be designed as a wind turbine, a water turbine, or an aircraft. Versions combining several of these features are also possible, for example, an aircraft that can be used as a wind turbine or water turbine, or that possesses both.

[0003] Within the scope of the invention, the general term "aircraft" refers in particular to rotary-wing vehicles such as helicopters, but also to airplanes with wings. In the case of aircraft, the airflow is composed of the ground speed, the wind speed, and the speed of the respective flight maneuver, as well as, in the case of helicopters, the rotational speed of the rotor blades, forming a resultant or relative airflow. In contrast, in the case of wind and water turbines, the airflow results from the speed of the respective flow and the rotational speed of the rotor blades. State of the art

[0004] Adjustable rotor blades for wind or water turbines and for rotary-wing vehicles, such as watercraft, aircraft, and especially helicopters, are known per se. Adjustable airfoils are found on aircraft, for example, on the wings, where parts of the empennage, such as ailerons, flaps, and leading-edge slats with air gaps that open when actuated, and a multitude of movable flaps are provided. These flaps significantly disrupt the ideally laminar airflow over the variable airfoil of a wing. Known solutions for the blade pitch adjustment of rotor blades with a symmetrical or asymmetrical airfoil utilize a gearbox with pushrods, so that the rotor blades are subjected to abrupt load changes during a revolution. This changes, for example, the angle of attack of the airfoil chord of the rotor blade.In a helicopter, a wind turbine with a vertical axis of rotation, or even a Voith Schneider propeller, this occurs abruptly. The resulting violent load-change reactions are directly transmitted to the structure of a rotary-wing vehicle and a wind or water turbine, causing extreme dynamic stresses on the respective overall system and propagating as pressure waves in the surrounding fluid. Perhaps the most prominent example of such rotary-wing kinematics is a helicopter. Compared to a fixed-wing aircraft, the helicopter has the advantage of not requiring a runway and being able to take off and land vertically. The ability to hover, i.e., remain stationary in the air, and the capacity to fly sideways or perform a slow rotation around the vertical axis are further specific advantages of this rotary-wing aircraft.However, these advantages are offset by some disadvantages, which are briefly mentioned below. The helicopter is not inherently stable; its center of gravity is located above the fuselage, so the pilot must continuously adjust the flight attitude through control inputs. By moving the swashplate up or down, the angle of attack of the rotor blades is directly changed, thereby increasing or decreasing the lift of the main rotor, causing the helicopter to climb or descend. This maneuver alone involves a change in engine or turbine power and requires counter-steering with the tail rotor. During straight and level flight, the swashplate and the rotor plane are tilted in the direction of flight. The maximum speed of a helicopter is limited by the aerodynamics of the rotor blades, as the forward-moving blade has a higher speed due to the oncoming airflow than the rear-moving blade.This creates an imbalance between the leading and trailing blades. The leading blade's forward speed and rotational speed overlap, so that with a rotor diameter of, for example, ten meters, the speed of sound is exceeded very quickly at the blade tips. Reaching this point results not only in aerodynamic disadvantages but also in unpleasant noise. Therefore, the top speed of a helicopter is around 200-300 km / h, although a combat helicopter can reach speeds of over 400 km / h. At these speeds, the helicopter is subjected to very strong vibrations caused by the swashplate. In addition to the lower speed of this aircraft compared to a fixed-wing airplane, there is a limited service ceiling, typically around 5,000 meters, which can reach up to 12,000 meters for a combat helicopter.The improved flight performance comes at the cost of increased fuel consumption. As a special type of helicopter, the gyroplane has established itself as a small aircraft. Its ability to autorotate in the event of engine failure and the space-saving folding of the rotor blades along the axis of rotation offer the possibility of a customized mobility solution that combines the advantages of a motor vehicle with those of a small aircraft. However, the inherent disadvantages of the rotary wing kinematics of a helicopter remain. In the field of control technology, current developments in actuators for electromagnetic valve control in internal combustion engines are noteworthy. Internal combustion engines typically operate at speeds of 7000 rpm, making the high frequency and stability required for an electromagnetic actuator particularly suitable for controlling the rotary wing kinematics of a helicopter.Current developments for rotary-wing vehicles are adopting the principle of the Voith Schneider propeller as an aircraft propulsion system. The Voith Schneider propeller is not a pure lift-driven rotor, but rather, with its special rotary wing kinematics, it pushes off from the fluid at specific rotor positions, resulting in high loads on the gearbox and a limited rotational speed. While the Voith Schneider propeller has good efficiency at low speeds, its drive power decreases rapidly with increasing speed of a watercraft, reaching an upper limit at around seven knots. Therefore, the application of this ship propeller is limited to slow-moving watercraft such as tugboats and towboats, as well as to shuttle boats and other watercraft specialized for short distances. Wind turbines with a vertical axis of rotation are known as...Darrieus rotors, named after their inventor, have a significant advantage over wind turbines with a horizontal axis of rotation: they do not need to be aligned with the prevailing wind direction. The Darrieus rotor operates quietly because it achieves its optimal performance at a tip speed ratio that is three to four times the wind speed. The rotor blades are arranged radially from the axis of rotation and have a symmetrical airfoil.Based on Betz's law, which sets the theoretical upper limit for the utilization of the kinetic energy stored in a flow cross-section at 16 / 27 of the total kinetic energy of the flow cross-section, known vertical-axis rotors with a symmetrical airfoil achieve an efficiency of only about 30% to a maximum of 45%, while the maximum efficiency of horizontal-axis rotors with an asymmetrical airfoil exceeds 50%. This significant difference can be explained by the fact that, under the same flow conditions, a symmetrical airfoil provides only about two-thirds of the lift of an asymmetrical airfoil. Coastal sections where specific topographic features cause high flow velocities due to ebb and flow, such as those found in [example missing], are potential locations for the extensive use of hydropower.This is the case at the Oosterschelde barrier in the Netherlands. Between the piers of this barrier, the water impounded in the Oosterschelde flows into the North Sea at low tide at high velocity, currently unused. Tidal power plants and ocean current power plants will play a crucial role in the generation of renewable energy in the future. Further expansion of inland hydropower suffers from the conflicting objectives of generating electricity at transverse structures across rivers and the associated disruption of natural fish migration routes. Therefore, it cannot simply be continued using existing hydropower technologies.

[0005] US Patent 4,383,801 A discloses a pivotable rotor blade for a wind turbine with a vertical axis of rotation, which in the preferred embodiment is formed in one piece, but as therein in Fig. 4The design can also be two- or three-part and is adjusted by means of an external gearbox on the axis of rotation. DE 10 2020 007 543 B3 discloses a wind turbine with a vertical axis of rotation in which the suction side of the rotor blades changes from the outside to the inside of the orbit twice during one rotor revolution. A pneumatic adjustment device formed by hoses moves the front and rear blade segments of the three-part rotor blades.

[0006] US patent 2017 / 0051720A1 describes a wind turbine with a vertical axis of rotation, in which the suction side of multi-part, adjustable rotor blades can be aligned towards the leeward side by means of cables or push rods and by means of gearboxes in one revolution of the rotor blade.

[0007] From DE 38 25 241 A1 emerges a wind turbine with a vertical axis of rotation, in which rotor blades composed of segments are equipped with a supporting central spar made of steel and with ballast weights, wherein at least the segment with the trailing edge is movable.

[0008] From DE 10 2010 047 918 A1 emerges a wind turbine with a horizontal axis of rotation in which the trailing edges of the rotor blades are designed to be movable by means of pneumatic muscles in order to adapt the rotor blades to the respective aerodynamic load in order to increase the performance of the rotor.

[0009] US Patent 5 114 104 A describes an adjustable rotor blade in which a kinematic chain is provided between a leading and a trailing edge segment of the rotor blade to transform the symmetrical airfoil profile in a basic position into an asymmetrical airfoil profile.

[0010] From DE 10 2008 025 414 A1 emerges an aerodynamically deformable profile with a contour that can be reversibly deformed by means of actuators for aircraft and in particular for rotary-wing aircraft, in which a skin is connected to a shear-resistant sandwich core and to flexible webs arranged transversely to the direction of deformation.

[0011] US patent 2010 / 0247314A1 describes a rotor blade for a wind turbine with an adjustable trailing edge, in which paired actuators each have a stack of piezoelectric elements, so that the adjustment of the rotor blade trailing edge is effected by a change in the length of the piezoelectric elements.

[0012] German patent DE 699 16 360 T2 discloses an airfoil profile for an aircraft with movable leading and trailing edges. The airfoil profile has two elastically deformable elastomer plates at the leading edge, which are adjustable by means of a rotary actuator, while the trailing edge is adjustable by means of a linear actuator.

[0013] US patent 3 716 209 A describes an adjustable leading edge for the wing of an aircraft, in which the profile contour is maintained by means of a kinematic structure formed by compression rods and by means of a rotatable nose segment.

[0014] The KR 10 2012 0 041 722 A design is a wind turbine with a vertical axis of rotation and three-part rotor blades, in which the blade adjustment is effected by means of a translational movement of actuators for the front and rear wing segments.

[0015] WO 2017 / 089 047 A1 describes a wind turbine with a vertical axis of rotation, in which one-piece rotor blades are rotatably mounted on a circular path and can be aligned with a curved upper surface in the downwind direction.

[0016] From DE 10 2010 011 708 A1 emerges a turbine with passive blade positioning, in which a gearbox with a linkage enables the rotor blades to be adjusted in such a way that the suction side is always oriented towards the leeward side of the wind direction.

[0017] The DE 10 2017 011 890 A1 design reveals an aircraft in which a rotary wing kinematic system is implemented with a linkage located outside the rotor blade.

[0018] US 9 346 535 B1 describes an aircraft with a rotary wing arrangement, in which the blade pitch adjustment of one-piece rotor blades is achieved by means of a cycloidal gearbox with linkage.

[0019] US 2008 / 0 011 900 A1 describes a rotary wing arrangement for an airship in which the rotor blades are adjusted by means of a gearbox and linkage. WO 2017 112 973 A1 describes an aircraft with rotary wing rotors whose rotor blades are adjustable by means of a gearbox and linkage in one revolution of the rotary wing rotor.

[0020] GB 1 023 766 A discloses a device comprising an asymmetric airfoil and an adjustment device, the asymmetric airfoil having an airfoil thickness and an airfoil chord extending between a leading edge and a trailing edge, the asymmetric airfoil having a three-part variable airfoil in at least one longitudinal section, in which a front and a rear wing segment are articulated to a middle wing segment by means of two hinges with axes of rotation and are arranged to allow a rotational movement about the associated axis of rotation relative to the middle wing segment, wherein simultaneous rotation in or out of the front and rear wing segments in opposite directions of rotation is possible, and wherein the angle of attack of the airfoil chord changes during rotation in or out. Task

[0021] Based on the prior art described above, the invention aims to provide a new device with an asymmetric airfoil and an adjustment device designed to influence the lift resulting from the airflow over the asymmetric airfoil. This objective is achieved by the subject matter of claim 1.

[0022] A device has an asymmetrical airfoil and an adjustment device. The asymmetrical airfoil has a profile thickness and a chord extending between the leading and trailing edges of the wing. In at least one longitudinal section, the asymmetrical airfoil has a three-part variable airfoil, in which a front and a rear wing segment are hinged to a central wing segment by means of two hinges with pivot axes and are configured to allow rotational movement about the associated pivot axis relative to the central wing segment. The central wing segment is designed as a rigid housing for receiving an adjustment device and has a hollow profile as a longitudinal member of the asymmetrical airfoil, which forms an abutment for the adjustment device in at least one longitudinal section.The adjustment device is designed to enable, with the aid of at least one electric motor, simultaneous rotation of the front and rear wing segments in opposite directions, such that a variable suction side of the asymmetrical wing profile is created, and preferably the angle of attack of the profile chord changes when the front and rear wing segments are rotated in or out.

[0023] Further advantageous properties and embodiments of the invention are evident from the dependent claims.

[0024] Specifically, the invention preferably has the following advantageous properties or embodiments: Specification of a rotor blade for wind or water turbines that generates a tangential driving force derived from lift at ten of the twelve exemplary rotational positions; specification of a rotor blade for a rotary-wing vehicle that generates a thrust force derived from lift acting in any direction of travel at ten of the twelve exemplary rotational positions; specification of a straight, U-shaped, or polygonal rotor blade; specification of a three-part airfoil whose surfaces carry photovoltaic cells; specification of a rotor blade for a wind turbine with operating positions for wind speeds 3-5 and 5-9 as well as 9-12 according to the Beaufort scale; specification of two pitch sectors located opposite each other on the orbit to avoid abrupt load changes in the airflow; specification of a fully electric, contactless pitch control device for a rotor blade with a three-part airfoil.Specification of an electromechanical adjustment device with bevel gear or cylinder locks for the three-part airfoil of a water turbine; specification of a rotor blade that is directly or indirectly connected at least at one end to a motor-generator; specification of a laminated core for the stator of an electric adjustment device; specification of a water turbine with a disc-shaped float; specification of a fish-passable transverse structure with a plurality of water turbines; specification of a storm surge barrier with water turbines; specification of electromechanical adjustment devices for the rotor blades of water turbines; specification of fully electric adjustment devices for the rotor blades of rotary-wing aircraft and in particular for helicopters; specification of an airfoil for an aircraft with a variable chord line and a variable camber on the suction side.Specification of a wind turbine with a horizontal axis of rotation for radial rotor blades in a plane of rotation; specification of a pitch-stall control for a wind turbine by means of a negative angle of attack of the chord line of the three-part airfoil; specification of a wind or water turbine for a diametrically reversing air or water flow; specification of a rotary vane drive for a diametrically reversing air or water flow; specification of a horizontal spoked wheel with a vertical axis of rotation, the outer ring carrier of which carries a plurality of rotor blades aligned parallel to the axis of rotation; specification of a horizontal spoked wheel with cable bracing for the longitudinal member of the rotor blade; specification of a horizontal, cable-braced spoked wheel with vertically arranged suspension cables that result in a polygonal course of the radial support and tension cables; specification of a bow thruster effective in two directions.Specification of straight, uniaxially curved rotor blades coated on both sides with PV cells; specification of a common floating body formed by a buoy for a wind turbine and for a water turbine, with a vertical axis of rotation. Fully electric adjustment devices

[0025] In a preferred embodiment, the adjustment device is fully electric and consists of a double-sided stepper motor with stator and rotor.

[0026] The stepper motor is integrated into the housing formed by the central wing segment, which, as a longitudinal member of the airfoil, provides a support for the stator in each longitudinal section of the airfoil. The stator houses two opposing excitation windings for the two rotors of the radial stepper motor. The rotors are articulated to lever arms of the front and rear wing segments and rotate about the pivot axes of the central wing segment's hinges. In doing so, they act as counterweights to the front and rear wing segments of the rotor blade. Alternating polarity permanent magnets in the rotors create an air gap on both sides, establishing a contactless magnetic or electromagnetic connection between the central wing segment and the front and rear wing segments.By reversing the polarity of the stator's excitation windings, the electrical rotation of the front and rear blade segments is effected simultaneously, each in opposite directions. In a further, particularly advantageous embodiment for purely electric blade pitch control of the rotor blade, the pitch control mechanism consists of two linear motors integrated into the central blade segment. The rotors of the linear motors are assigned to the front and rear blade segments and are connected to the central blade segment by a lever arm. A control unit causes the suction side of the variable airfoil to change its orientation twice at each of the positioning positions of a freely adjustable diameter of the orbit, from the inside to the outside of the orbit.The positioning function of the two rotors is activated by applying an electrical voltage. Alternatingly polarized permanent magnets interact with a reversible excitation winding of the stator, allowing the oscillating linear motion of the linear motors to adjust the pitch angle of the rotor blade chord, for example on a helicopter, by up to 30 load cycles per second. Each rotor has two tongues, each with a row of alternatingly polarized permanent magnets. An air gap on both sides between the stator and the rotor's permanent magnets establishes a direct, contactless (magnetic) connection between the center blade segment and the leading and trailing blade segments. Controlled polarity reversal of the stator's excitation windings causes the leading and trailing blade segments to rotate simultaneously in opposite directions. Electromechanical adjustment devices

[0027] In a particularly advantageous embodiment for rotating the front and rear wing segments, an electromechanical adjustment device is provided, in which electric motors with a step-detent gearbox are designed for retaining elements in each longitudinal section of the asymmetrical wing profile. In a first embodiment, the shaft of the electric motor is arranged transversely to the longitudinal axis of the rotor blade and connected to cylinder locks for locking the front and rear wing segments. In a second embodiment, the shaft of the electric motor is arranged parallel to the axes of rotation of the hinges of the middle blade segment and locks the front and rear blade segments by means of a worm gear. In the case of a single rotor blade, the direction of rotation of the electric motor with the step-detent gearbox changes at each of the blade's rotational positions.In another advantageous electromechanical design for the simultaneous rotation of the front and rear wing segments of the asymmetrical airfoil, linear motors are arranged coaxially and concentrically to the axes of rotation and actuate slides. Threads of the front and rear blade segments engage with threads of the slide moved by the linear motor, causing the opposing rotation of the front and rear blade segments. Air bearings between the hinge threads and between the rotor and stator minimize friction and are supplied with compressed air through the hollow profile of the hinges. Due to the design of the linear motor, the electromagnetically induced field of the excitation windings can be aligned either parallel or perpendicular to the rotor's direction of movement.The linear motor allows for precise positioning of the slider, which acts as a runner, enabling the exact setting and variation of the positive angle of attack for the blade segments. The adjustment device, with its positioning and holding function, is designed to withstand considerable aerodynamically induced suction forces and, in the case of a rotor blade, centrifugal forces. The leading and trailing blade segments can be individually adjusted and locked in each longitudinal section. The shallow thread pitch allows for a gear ratio of preferably 1:10. Rotor blade and rotor module

[0028] The rotor blade with its asymmetric airfoil is subdivided into multiple longitudinal sections and is designed to be straight, U-shaped, or polygonal. Multiple rotor blades, connected at least at one end to a motor-generator, form a rotor module. The rotor module rotates around an axis of rotation on a radius-defined orbit, which can be divided into two halves by a freely adjustable diameter with two positions within a 360-degree radius. The suction surfaces of the variable airfoil are oriented by the adjustment mechanism to the outside of the orbit in the first half and to the inside in the second half. At the diameter with the adjustment positions, the asymmetric airfoil temporarily assumes the shape of a symmetrical airfoil, whose chord line is tangential to the circular orbit of the rotor module.By simultaneously rotating the leading and trailing wing segments in opposite directions, the airfoil chord acquires an angle of attack that is positive in both halves of the orbit. In each longitudinal section of the asymmetric airfoil, the central wing segment forms a housing for the adjustment mechanism, which is powered by at least one electric motor. It also forms a longitudinal member of the rotor blade with a box-shaped hollow profile, the opposing flanges of which form part of the surface of the asymmetric airfoil. A multitude of these hollow longitudinal members are connected at their nodes to transversely stiffening ring members, creating a self-supporting rotor module that is rigid in terms of bending, shear, and torsion.The straight, U-shaped, or polygonal rotor blade of a rotor module is aligned parallel to the axis of rotation in at least one longitudinal section. At the freely adjustable positions within a full angular range of one diameter of the orbit, the adjustment device formed by electric motors is actuated such that the suction side of the variable airfoil changes from the outer to the inner side of the orbit and vice versa in one revolution of the rotor blade.The front and rear wing segments are each adjustable at their positions in the pivot axes of the hinges of the middle wing segment by up to eight degrees in the opposite direction of rotation to the middle wing segment formed by the longitudinal beam, so that a positive angle of attack of the profile chord is maintained in both halves of the orbit of the variable wing profile either electromagnetically by means of the air gap between the rotors and the stators of the electric motors or by means of retaining elements of a step-detent drive connected to the electric motors.Between the wing segments of the three-part wing profile, joint gaps are formed between the front wing segment with the wing nose and the middle wing segment arranged in the area of ​​the maximum profile thickness of the wing profile and the rear wing segment with the wing trailing edge, so that preferably with the exception of the joint gaps the wing surfaces of the three-part wing profile can carry photovoltaic cells over their entire area. Rotary vane turbines and rotary vane vehicles

[0029] Unlike a rotary-wing turbine, in a rotary-wing vehicle the suction sides of the asymmetric airfoil, at the freely adjustable diameter across the full angle, can be aligned with the positions on the rotor blades' orbit in both halves of the rotor module's orbit to the respective direction of travel and are designed to generate thrust in the direction of flight or travel, or reverse thrust against the direction of flight or travel. In the case of a wind or water turbine, the suction sides of the asymmetric airfoil, at the freely adjustable diameter across the full angle, can be aligned with the positions on the orbit to the leeward side of the flow, independent of a horizontally or vertically oriented axis of rotation. A particularly advantageous embodiment relates to rotary-wing turbines and rotary-wing vehicles in which the direction of the flow regularly changes diametrically. This is, for example,This is the case in a wave power plant with an air chamber, where the wave displaces a volume of air from the chamber, thus harnessing an onshore airflow to drive a wind turbine. An offshore airflow generated by the returning wave further drives the wind turbine while maintaining its direction of rotation, as the suction side of radially arranged rotor blades in a plane of rotation is switched to the side facing away from the flow by means of a pitching device. A periodically changing direction of flow is also generated by tidal currents, so a water turbine essentially has the same design as a wind turbine.

[0030] For both wind and water turbines, it is advantageous that in a neutral transition position when the direction of the flow changes, the chord line of the variable airfoil is arranged parallel to the plane of rotation, and that by means of the adjustment device the chord line can have a positive angle of attack of up to four degrees relative to the symmetrical airfoil temporarily present in a transition position, so that the lift generated by the resulting flow on the plane of rotation causes a maximum tangential driving force.As a counterpart to the wind or water turbine, which is designed for a diametrically changing direction of flow, a transverse bow thruster driven by the motor generator is proposed for a watercraft, in which the suction side of the rotor blades arranged radially in a rotor plane with the asymmetrical airfoil profile can be oriented in the thrust direction as required, without changing the direction of rotation of the motor generator. Rotary-wing vehicles and aircraft

[0031] In one embodiment, the rotary-wing vehicle is designed as a helicopter, comprising either a single rotor module or front and rear rotor modules rotating in opposite directions. The helicopter's rotor blade is U-shaped and has an asymmetrical airfoil, consisting of a lower longitudinal section that leads the rotor module in the direction of rotation, a middle longitudinal section, and an upper longitudinal section that trails the rotor module in the direction of rotation. The lower longitudinal section is offset by approximately 10 degrees relative to the upper longitudinal section in the circumferential direction, while the middle longitudinal section connects the lower and upper longitudinal sections obliquely and is parallel to the axis of rotation with a slope in the direction of rotation.In the lower and upper longitudinal sections of the rotor module, the diameter can be adjusted in the direction of flight, and in the middle longitudinal section, it can be adjusted perpendicular to the direction of flight. In a particularly advantageous embodiment of the helicopter, a rotor module consisting of four U-shaped rotor blades, together with a rear-mounted propeller assembly connected to the teardrop-shaped fuselage of the helicopter, forms a hybrid propulsion system.The four U-shaped rotor blades rotate in pairs and in opposite directions around the rotational axis of the rotor module and around the streamlined fuselage, which includes a rear-mounted propeller assembly. Each U-shaped rotor blade has a longitudinal section positioned above and below the fuselage, parallel to the longitudinal axis. These longitudinal sections are connected at their outer ends by the central longitudinal section, which is also parallel to the rotational axis. This central longitudinal section is designed to generate thrust in any desired direction of flight from a standstill by allowing its diameter to be adjusted perpendicular to the desired flight direction in a 360-degree radius.Another particularly advantageous embodiment of the variable asymmetric airfoil with the adjustment device relates to the wing of an aircraft, in which, in at least one longitudinal section of the wing, the central wing segment is designed as a housing for an electric motor. The leading and trailing wing segments of the three-part airfoil are connected to the retaining element of an adjustment device formed by a step-detent mechanism in such a way that, by actuating the adjustment device, the lift generated by the suction side of the variable airfoil can be adapted to the respective flight situation of the aircraft. The step-detent mechanism preferably has a power transmission ratio of 1:10. At the aircraft's design speed, the wings preferably have an angle of attack of approximately two degrees relative to the longitudinal axis of the aircraft.By operating the adjustment mechanism, not only does the camber of the asymmetrical airfoil increase, but also the angle of attack to approximately three to four degrees, enabling a climb simply by operating the adjustment mechanism. During takeoff and landing, maximum camber results in an angle of attack of up to six degrees. Therefore, extendable leading-edge slats and tail flaps, which are aerodynamically suboptimal due to ventilated gaps, can be largely dispensed with. Consequently, the wing, with its longitudinal spar rigidly connected to the fuselage and movable leading-edge and trailing-edge wing segments, requires neither conventional leading-edge slats and flaps nor landing flap carrier fairings, so-called canopies, on the underside of the wing. Wind and water turbines with a vertical axis of rotation

[0032] In initial embodiments for wind and water turbines, the rotor blades of a rotor module rotate on a cylindrical orbit around a vertical axis of rotation and change the orientation of the suction side of the asymmetric airfoil at a diameter of the orbit that can be aligned perpendicular to the flow direction. At this diameter with the adjustment positions, the suction side of the asymmetric airfoil of the rotor blade is aligned with the respective flow direction in both halves of the rotor module's orbit by means of the adjustment device. A particularly advantageous embodiment of the wind turbine relates to a rotor module that utilizes the inertia caused by gyroscopic moments to stabilize the rotational axis of the rotor module against changes in direction.In this case, the rotor module features a spoked wheel that rotates around a vertical axis of rotation in a horizontal plane. Support and tension cables connect an outer ring carrier, radially spaced from the axis of rotation, to a hub. The ring carrier, designed as a compression ring, supports a plurality of straight rotor blades arranged parallel to the vertical axis of rotation. The longitudinal members of the rotor blades are rigidly connected to the ring carrier and can be further stabilized by means of a cable bracing system attached to the longitudinal member, connected to the support and tension cables of the spoked wheel.The hub of the spoked wheel is connected to a supporting structure of the wind turbine at an upper and a lower pivot bearing, such that an air gap is formed between at least one stator on the supporting structure, arranged coaxially and concentrically to the axis of rotation, and at least one rotor on the hub side of the motor-generator of the wind turbine. The wind turbine with the gyroscope can be anchored onshore or offshore in a building site, with the gyroscope effect preferably being used for a wind turbine whose supporting structure includes a floating body designed as a ballasted buoy, which can be anchored to the seabed by means of ropes and anchors.The upper and lower radial spokes, formed by cables, can be connected to each other by vertical hangers and triangulated circumferentially, resulting in a spoked wheel with a lightweight structure featuring predominantly axially stressed load-bearing elements. This allows for diameters of several hundred meters. The larger the diameter, the lower the centrifugal stress on the rotor blades. This relationship also applies to wind turbines where multiple rotor modules are stacked vertically and supported by a base-side spoked wheel with a ring support formed by a compression ring. In this case, multiple rotor modules each have a three-part, asymmetrical airfoil. The suction side of the airfoil changes from the outside to the inside of the orbit and vice versa at a diameter that can be oriented within a 360° radius relative to the wind direction.The rotor blades are spaced a radius from the vertical axis of rotation and connected at their upper and lower ends to a circumferentially braced ring support. The base-side ring support has compression members that connect the rotor formed by the stacked rotor modules to the lower pivot bearing of a hub, while pairs of V-shaped tension spokes are braced to the upper pivot bearing of the hub in such a way that a vertical lever arm is formed between the upper and lower pivot bearings to transfer the rotor's tilting moment via the hub to a cantilevered base of the wind turbine. With a forward area of, for example, 14.The 000 square meters of the delicate, cylindrical, cable-stayed lattice shell achieve a peak output of approximately seven MW at wind speeds up to twelve m / s, while at wind speeds exceeding twelve m / s, two to three times the output compared to a conventional wind turbine is achievable. At these wind speeds, a conventional wind turbine can only operate at reduced speed and is shut down completely during storms. Water turbines with a vertical axis of rotation are anchored in a flowing body of water, either in a transverse structure or as floating turbines. A floating water turbine has a float that sits on the water's surface and houses an annular, gearless motor-generator with a shaft. It is anchored to the bottom of the water body by means of at least one anchor and anchor cables.The rotor module of the water turbine is arranged below the floating body at a radial distance to the axis of rotation and consists of an upper and a lower ring support which are connected to each other by the longitudinal supports of a plurality of three-part rotor blades and together form a bending-, shear- and torsionally stiff rotor module by means of a radial cable bracing with the shaft of the motor generator.

[0033] The floating body is designed either as a rectangular raft with PV collectors (PV = photovoltaics) on its upper surface, or as a disc-shaped disk or a floating ring. The central wing segment, located in the area of ​​the maximum profile thickness of the asymmetrical airfoil, serves as a housing for the electric motors of the adjustment device. This segment forms a longitudinal beam of the asymmetrical airfoil, subdivided into several longitudinal sections, and acts as a support for the opposing rotational movements of the leading edge of the front wing segment and the trailing edge of the rear wing segment.

[0034] By means of the adjustment device for the wing segments of the three-part airfoil, the angle of attack of the chord line of the asymmetric airfoil relative to a temporarily usable symmetric airfoil can be adjusted such that a tangential driving force can be derived from the lift of the variable airfoil in the case of a wind or water turbine, and a thrust force in the case of a rotary-wing vehicle. A rotor blade, which is straight, rotates on an annular orbit in the rotor plane around the axis of rotation. The longitudinal member of the rotor blade, formed by the middle wing segment, is designed as a blade root at either its outer or inner end and is rigidly connected to the motor-generator. In the case of a wind or water turbine, the adjustment device is designed to align the suction side of the variable airfoil towards the leeward side in a periodically diametrically changing flow direction. Wind and water turbines with a horizontal axis of rotation

[0035] In wind or water turbines, the rotor module rotates around a horizontal axis of rotation in a vertical plane. A cable-tensioned spoked wheel with a hub and an outer ring support designed as a pressure ring is aligned with the flow direction by means of an azimuth bearing on a mast, with a plurality of rotor blades rotating on an annular orbit with an inner and an outer radius around the horizontal axis of rotation.The central wing segments of the twisted rotor blades, designed as longitudinal spars, are rigidly connected to the ring carrier by means of a clamping mechanism attached to opposing pairs of rotor heads. This ensures that in each longitudinal section of the rotor blade, the chord line of the asymmetric airfoil exhibits a positive angle of attack of up to seven degrees relative to the oncoming airflow resulting from the wind and rotational speeds. Thus, the asymmetric airfoil maintains an adjustable positive angle of attack along the entire length of the rotor blade. For a stall, the leading and trailing wing segments of the rotor blade are rotated to windward, resulting in a negative angle of attack for the chord line of the asymmetric airfoil.A water turbine with a horizontal axis of rotation can be advantageously combined with a storm surge barrier, whereby rotor modules with a horizontal axis of rotation are arranged between the piers for lockable gates and a bridge, which can be driven by the current during both ebb and flow and used for power generation. The motor generator

[0036] A freewheel between the rotor module and the motor-generator enables the motor-generator to operate as a generator in a rotary-wing vehicle, for example, when anchored in a current or in a descending flight. In a wind or water turbine, the motor-generator operates as a motor until the respective design speed of the rotor module is reached.

[0037] Further advantageous embodiments and features of the invention are shown in the figures.

[0038] They show: Fig. 1 a helicopter with four bow-shaped rotor blades in perspective overview and schematic cross-section, Fig. 2 the helicopter to Fig. 1 with a top view showing the lift forces in the lower and upper longitudinal sections of the four bow-shaped rotor blades of the rotor module, Fig. 3 a helicopter with two rotor modules, each with four bow-shaped rotor blades, in a perspective overview, Fig. 4 the helicopter to Fig. 3 with a top view showing the lift forces in the lower and upper longitudinal sections of the bow-shaped rotor blades, Fig. 5 the central longitudinal section of the bow-shaped rotor blades of the helicopters Figs. 1-4 with a representation of the thrust forces oriented in the direction of flight in the schematic horizontal section, Fig. 6 a floating water turbine, shown above in a perspective detail view and below in a schematic cross-section, Fig. 7 the fluid dynamic forces of a wind turbine at twelve exemplary rotational positions of the variable asymmetric airfoil in schematic section, Fig. 8 Reduced, fluid-dynamically induced forces of a wind turbine at twelve exemplary rotational positions of the variable symmetrical airfoil in schematic section, Fig. 9 greatly reduced, fluid-dynamically induced forces of a wind turbine at twelve exemplary rotational positions of the variable asymmetric airfoil in the operating position for storm conditions, Fig. 10 a rotor blade at a positioning position of the orbit intended for a fully electric blade adjustment of the three-part airfoil in the perspective exploded view, Fig. 11 the rotor blade after Fig. 10with the fully electric adjustment device for the three-part wing profile, at the top at the positioning positions of the orbit, in the middle and at the bottom each in one half of the orbit with the variable profile chord in schematic cross-section, Fig. 12 a rotor blade with a fully electric adjustment device formed by linear motors for the three-part airfoil, top with reversed suction sides for two sectors of the orbit and bottom with a schematic longitudinal section representation of a linear motor, Fig. 13 a rotor blade with an electromechanical adjustment device for the three-part airfoil, shown above in overview and below in detail of a linear motor, each as an exploded view. Fig. 14a rotor blade with an electromechanical adjustment device with a cylinder lock for the three-part airfoil, at the top at the adjustment positions of the orbit, in the middle and at the bottom each in one half of the orbit with reversed suction sides of the variable airfoil in schematic cross-section, Fig. 15 a rotor blade with an electromechanical adjustment and locking device with a worm gear for the three-part airfoil in a perspective exploded view, Fig. 16 a storm surge barrier with a water turbine in cross-section, Fig. 17 a wind turbine with a rotor module formed by a cylindrical grid shell with a vertical axis of rotation, Fig. 18 a wind turbine with a rotor module formed by a spoked wheel with a vertical axis of rotation, Fig. 19 a floating wind turbine with a rotor module formed by a spoked wheel with a vertical axis of rotation, Fig. 20In the middle, a turbine that converts the kinetic energy of a periodically diametrically changing flow into a rotary motion; in the cutaway perspective, above, the variable three-part airfoil for one flow direction and below, for the other flow direction, each in cross-section. Fig. 21 a wind turbine with a rotor module formed by a spoked wheel with a horizontal axis of rotation, Fig. 22 a rotor blade of the wind turbine after Fig. 21 with an electromechanical adjustment and locking device in three exemplary cross-sections, Fig. 23 a helicopter as a ten-seater aircraft, shown above in a perspective overview in flight and below in a view after landing, Fig. 24 Above is an overview of an aircraft whose wings have a three-part airfoil, and in the middle and below are three schematic cross-sections of the wing with the variable airfoil.

[0039] Fig. 1 Figure 1 shows a helicopter 130 as an embodiment from the family of rotary-wing vehicles 13 with four U-shaped rotor blades 1, each divided into three longitudinal sections L1-L3 and each having a three-part airfoil 21. The longitudinal members of the U-shaped rotor blades 2 are formed by the central airfoil segment 212 of the variable airfoil 2 and form a housing 14 with a support 140 for the front airfoil segment 211, which is articulated to the central airfoil segment 212 by means of the adjustment device 15, and for the rear airfoil segment 213, cf. Fig. 10 As in Fig. 2As shown, the lower longitudinal section L1, which leads in the direction of rotation, and the upper longitudinal section L3, which trails in the direction of rotation, of a rotor blade 1 are designed to generate lift and thrust in the direction of flight D, while the longitudinal section L2 is designed to hold the helicopter 130 in its respective flight position in hovering flight with a thrust force that can be controlled in any direction within a 360-degree radius. The thrust in the longitudinal sections L2 and the diameters can be oriented in any desired direction of flight D using the control positions C1. The rotor module 10 is connected to an engine via a shaft and has a rotational axis y formed by the vertical axis of the helicopter and rotates above the cabin enclosed by the fuselage. The rotary wing kinematics of the variable airfoils 2 of the rotor blades 1 replace a swashplate, as shown in Fig. 2As shown, in straight flight, the diameter is aligned with the positioning positions C2 in the lower and upper longitudinal sections L1, L3 of the U-shaped rotor blade 1 in the direction of flight D, in order to generate equal amounts of lift and thrust in the direction of flight D by means of a different positive angle of attack α of the airfoil chord p in the left and right halves of the rotor module 10 with respect to the direction of flight D. The lower longitudinal section L1, which leads in the direction of rotation, and the upper longitudinal section L3, which trails in the direction of rotation, are vertically spaced apart by the longitudinal section L2 and radially offset from each other by an offset angle β of approximately 10 degrees, with the middle longitudinal section L2 obliquely connecting the outer lower end of the longitudinal section L1 to the outer upper end of the longitudinal section L3.With two layers of lift-generating longitudinal sections L1 and L3 of the rotor blades 1, the helicopter 130 can be advantageously used as a heavy-lift helicopter that can maintain a stable position in hovering flight and develop thrust in any direction from a standstill. Without a swashplate, the rotor module 10 is characterized by very smooth running and is free of unwanted vibrations.

[0040] Fig. 2 shows the helicopter 130 towards Fig. 1with a schematic representation of the longitudinal sections L1, L3 of the U-shaped rotor blades 1, shown above in the overview and below in detailed sections of the asymmetrical airfoil 2, each for the left and right halves of the orbit U with respect to the flight direction D. In straight flight of the helicopter 130, the resulting airflow is determined by the rotational speed and the airspeed, so that, with respect to the flight direction D, different lift forces, shown as dashed vectors, would result on the rotor blades 1 in the left and right halves of the orbit U. Due to the in Fig. 1The described blade pitch adjustment at the positioning positions C2 of the leading and trailing longitudinal sections L1, L3 of the rotor blades 1 generates equal lift forces in the left and right halves of the rotor module 10, so that the helicopter 130 maintains a stable flight attitude in straight and level flight. In the longitudinal section L2 with the positioning positions C1 of the rotor blade 1, as described in Fig. 5 The illustration shows a blade pitch control system in which the thrust can be directed in any desired flight direction D within a 360-degree radius. This is particularly advantageous for a precise landing approach and also for maintaining a specific flight attitude, e.g., in crosswinds. During climb, the sum of the lift forces in both halves of the orbit U is equal, so that no pitch control of the wing segments 211, 213 is required in the longitudinal sections L1, L3 of rotor blade 1 during climb.

[0041] Fig. 3Figure 1 shows a helicopter 130 with two rotor modules 10 rotating in opposite directions about the axes of rotation y. The front and rear rotor modules 10 each have four U-shaped rotor blades 1, which are subdivided into a lower longitudinal section L1 leading in the direction of rotation and an upper longitudinal section L3 trailing in the direction of rotation, as well as a longitudinal section L2 connecting the upper and lower longitudinal sections L1, L3, which is preferably inclined in the direction of rotation, and which have a continuous airfoil 14 formed by the central wing segment 212. As in Fig. 1As explained, the diameter is aligned with the adjustment positions C2 in the direction of flight, so that by changing the positive angle of attack α of the chord line p of the variable airfoil 2, the rotor modules 10 generate equal lift forces on both the port and starboard sides during straight flight of the helicopter 130, with the front and rear rotor modules 10 being inclined in the direction of flight D. The offset angle β between the lower longitudinal section L1 and the upper longitudinal section L3 ensures optimal airflow over the four rotor blades 1 of the rotor module 10. In the longitudinal sections L2 of the U-shaped rotor blades 1, which are aligned parallel to the rotation axes y of the helicopter 130, the diameter is adjusted with the adjustment positions C1, as shown in Fig. 5The rotor blades are shown oriented transversely to the direction of flight D, so that the suction sides (-) of the variable airfoil 2 in the longitudinal section L2 of the rotor blades 1 generate thrust in the direction of flight D. The helicopter module proposed here has the advantage that the rotor modules 10 at the nose and tail can be arranged at the same height relative to the longitudinal axis, rather than being offset vertically from each other as is currently customary, since the orbits U do not overlap. The two-layer arrangement of the radial longitudinal sections L1, L3 results in a significantly large wing surface area, which can generate high lift forces, making the helicopter 130 particularly suitable as a cargo helicopter. The smooth transition of the angle of attack α at the control positions C1 and C2 results in quiet rotor operation and avoids vibrations transmitted to the entire structure, compared to the previously common abrupt change of the angle of attack α using a rotor swashplate.Assuming a blade speed of 800 km / h for the central longitudinal section L2 of the U-shaped rotor blade 1 with a radius r1 of 5 m, this results in 440 revolutions of the rotor module 10 per minute and a frequency of 20 Hz for the adjustment device of the rotor blade 1 in the longitudinal section L2. The in . Figs. 10-13 The electromechanical adjustment devices shown meet this requirement.

[0042] Fig. 4 shows the helicopter 130 towards Fig. 3In a top view of the twin rotors with a vector representation of the fluid dynamically induced forces on a rotor module 10 in the longitudinal sections L1, L3 of the bow-shaped rotor blades 1 and with detailed sections of the variable asymmetric airfoil 2 for the right and left halves of the orbit U, relative to the flight direction D. In straight flight of the helicopter 130, the resulting airflow is composed of the rotational speed and the airspeed, so that, relative to the flight direction D, different lift forces result on the rotor blades 1 in the left and right halves of the orbit U. These forces are balanced at the diameter oriented in the flight direction D with the control positions C2 by the fact that the positive angle of attack α of the airfoil chord p changes twice in one revolution of the rotor blade 1, and therefore an equal lift force is generated in the starboard and port halves of the two rotor modules 10.In the longitudinal section L2 of rotor blade 1, as shown in . Fig. 5 The illustration shows a blade pitch control system in which the thrust can be directed in any desired flight direction D within a 360-degree radius. This is particularly advantageous for a precise landing approach and also for maintaining a specific flight attitude, e.g., in crosswinds. During climb, the sum of the lift forces in both halves of the orbit U is equal, so that no adjustment of the angle of attack α of the airfoil chord p is required in the longitudinal sections L1, L3 of rotor blade 1 during climb.

[0043] Fig. 5 shows the helicopter's straight flight path to Figs. 1-4in a schematic horizontal section of the longitudinal section L2. The diameter with the orbital positions I-XII can be aligned in any position of two opposing positioning positions C1 of the orbit U in the longitudinal section L2. While the rotor blades 1 generate lift in the longitudinal sections L1,L3, as shown in Figs. 2 to 4As shown, the longitudinal section L2 serves to generate thrust that can be directed in any desired flight direction D within a 360-degree radius. In calm conditions, the pitch control device 15 of the rotor blades 1 in the longitudinal sections L2 is deactivated during hovering flight, so that the thrust forces generated by the variable asymmetric airfoils 2 cancel each other out. By means of the pitch control device 15 of the rotor blades 1, the helicopter 130 is very controllable and can maintain its flight position very precisely even in strong crosswinds, and, as shown here, accelerate from a standstill in flight direction D, which is also particularly advantageous for takeoff and landing.

[0044] Fig. 6Figure 1 shows a floating water turbine 12, anchored to the bottom of a body of water with a current F, and featuring a disc-shaped float 120 at the water's surface. The float is anchored to the bottom of the water body by means of an anchor 121 and anchor cables. The housing 14 of the motor-generator is rigidly connected to the disc-shaped float 120. The motor-generator shaft has, for example, an upper and a lower, watertight tapered roller bearing and is clamped to the float 120. It is torsionally rigidly connected to a rotor module 10 by means of two vertically spaced sets of radial bladed spokes. The rotor module 10 rotates on a circular orbit U with radius r1 around the axis of rotation y and has six rotor blades 1. The longitudinal beams of these blades are each connected to an upper and a lower ring support 122 of the submerged rotor module 10 and form a housing 14 for the adjustment device 15.To accommodate the adjustment devices 15 of the variable airfoil 2, the longitudinal beams of the three-part airfoils 21 are subdivided into five longitudinal sections L1-L5 and form the abutment 140 and the housing 14 for the adjustment devices 15 assigned to the longitudinal sections L1-L5. The water turbine 12 is anchored in the flowing water by means of anchor cables (not specified in detail) for the anchor 121 and joints on the disc-shaped float 120 anchored in the flow F, in such a way that it can follow different water levels.

[0045] Fig. 7Figure 1 shows twelve different rotational positions I-XII of the variable asymmetric airfoil 2 for wind and water turbines 11, 12 on the circular orbit U defined by the radius r1. With respect to the direction of the flow F, the suction side (-) of the variable asymmetric airfoil 2 is oriented towards the inside of the orbit U during the upwind rotation and towards the outside of the orbit U during the downwind rotation. Thus, in the case of a wind turbine 11, the variable airfoil 2, acting as a Clark-YM-15 airfoil, generates a tangential driving force, indicated by arrows pointing in the direction of rotation, at wind speeds of 3-6. At the diameter with the adjustment positions C1, the suction side (-) of the variable airfoil 2 switches from the outside to the inside of the orbit U and vice versa, with the variable airfoil 2 exhibiting a symmetric airfoil 2 in a transitional position in each case.In the upwind and downwind rotation, the resulting flow, as a vector sum of the flow velocity and the rotational speed of the rotor module 10, therefore causes a lift force inclined in the direction of rotation, which is about one third greater for the asymmetric airfoil 2 than for the one in . Fig. 8The symmetrical airfoil profile 2 is considered. This results in a significantly improved efficiency of the rotary vane turbine, which can be designed as a wind or water turbine 11, 12, compared to a conventional Darrieus rotor. In a large wind turbine 11 with a rotor diameter of two hundred meters, the rotation period of the rotor blade 1 is more than half a minute, so that sufficient time is available for blade pitch adjustment at the control positions C1. In contrast to a Darrieus rotor, where a sudden load change at the control positions C1 is disadvantageous and places extreme stress on the structure of the wind turbine 11, the gradual blade pitch adjustment described here reduces aerodynamically induced load peaks at the control positions C1, thus relieving the structure of the wind turbine 11.

[0046] Fig. 8 shows twelve different rotation positions I-XII of the variable symmetrical airfoil 2 of the rotor blades 1 for the in Fig. 7 The wind and water turbines 11,12 shown have a symmetrical airfoil 2. For the in Fig. 7 The wind turbine designated 11 is designed with this uniform rotor blade position for wind speeds 6-9 on the Beaufort scale, in order to utilize a one-third reduction in lift force for the operation of the wind turbine during storms. Compared to the ones in Fig. 7 The depicted wing positions of the rotor blades 1 result in the variable wing profile 2 being a symmetrical wing profile 2, generating a lower lift force and a resulting reduced tangential driving force.

[0047] Fig. 9 shows twelve different rotation positions I-XII of the variable asymmetric airfoil 2 of the rotor blades 1 for the in Fig. 7 and Fig. 8 The rotary vane turbines shown. The variable asymmetric airfoil 2 of the in Fig. 7 The wind turbine 11 shown here is opposite the one in Fig. 7The described orientation of the suction sides (-) of the asymmetric airfoil 2 is an inverse position with a negative angle of attack of the airfoil chords of the asymmetric airfoil 2. With respect to the direction of the flow F, the suction side (-) of the asymmetric airfoil 2, in the form of a Clark-YM-15 airfoil, is oriented towards the outside of the orbit U in the upwind rotation and towards the inside of the orbit U in the downwind rotation, so that the variable airfoil 2, with the exception of the control positions C1, causes a reduced tangential driving force at orbit positions V-VIII and XI at extreme wind speeds 9-12 on the Beaufort scale, which is opposed at orbit positions III, IV and IX by a tangential drag acting against the direction of rotation.However, since the tangential driving force predominates, the wind turbine 11 also rotates in hurricanes and even in a hurricane according to the Saffir-Simpson hurricane scale and converts some of the storm's kinetic energy into a rotational motion, which is an advantage compared to the wind turbine 11 being stationary.

[0048] Fig. 10 Figure 1 shows a perspective exploded view of a rotor blade 1 with a symmetrical variable airfoil 2, for a rotary-wing vehicle 13 with reference to Fig. 5 in which the diameter in the middle longitudinal sections L2 of the bow-shaped rotor blades 1 can be aligned orthogonally to the respective flight direction D with the adjustment positions C1 and for a wind or water turbine 11,12 with reference to Fig. 7where the diameter can be aligned perpendicular to the direction of the flow F at the adjustment positions C1. In both cases, the variable airfoil 2 temporarily exhibits a symmetrical airfoil 2 at the adjustment positions C1, which is oriented mirror-symmetrically to the airfoil chord p and a tangent to the orbit U with radius r1. The rotor blade 1 is constructed from three rigid extruded hollow profiles 141, consisting of a leading edge segment 211 with a leading edge n, a middle segment 212 in the region of maximum airfoil thickness q, and a trailing edge segment 213 with a trailing edge e. The middle segment 212 serves as a housing 14 for an adjustment device 15 formed by paired electric motors 16. The front and rear wing segments 211,213 are hinged to the middle wing segment 212, which is formed by an extruded hollow profile 141.The central wing segment 212 forms a housing 14 and a support 140 for two stators 161 with laminated cores 162 and excitation windings and establishes a contactless electrical connection with an air gap a on both sides to the rotor 160 of a sectionally acting stepper motor 164, which is formed by alternatingly polarized permanent magnets 163. As in . Fig. 11To explain in more detail, the rotation of the front and rear blade segments 211, 213 around the axes of rotation z is achieved by reversing the polarity of the excitation windings 162 on the two laminated cores of the stator 161. The rotors 160, together with the permanent magnets 163, form a counterweight 216 to the front and rear blade segments 211, 213, so that a balance of forces exists during rotation. With a rotor module with a diameter of 3 meters and 800 revolutions per minute, up to 40 load changes per second are possible, which can be achieved with this all-electric adjustment device 15 within 3.2 milliseconds.

[0049] Fig. 11 The rotor blade 1 indicates Fig. 10 in three schematic cross-sections, at the top at the positioning positions C1 of a diameter of the orbit U with radius r1, which can be aligned transversely to the direction of travel D, as in Fig. 5As shown, in the schematic cross-sections of the variable airfoil 2 in the middle and below, the suction sides (-) in both halves of the orbit U can be oriented towards the inner and outer sides of the orbit U. At the positioning positions C1, the variable, three-part airfoil 21 is designed as a symmetrical airfoil, which is mirror-symmetrical to the airfoil chord p and a tangent to the orbit U with radius r1. The rotor blade 1, for example, is constructed from three rigid extruded hollow profiles 141, which have a leading edge segment 211 with a leading edge n, a middle segment 212 in the region of the maximum airfoil thickness q for receiving the stators 161, and a trailing edge segment 213 with a trailing edge e.The central wing segment 212 is designed as a longitudinal member of the rotor blade 1 and forms the housing 14 and the abutment 140 for the adjustment device 15, which is formed by (preferably radial) stepper motors 164. Joint gaps 210 between the wing segments 211-213 enable laminar flow around the variable airfoil 2 in every operating position. The adjustment device 15 causes the airfoil chord p, which is tangential to the orbit U at the adjustment positions C1, to assume a positive angle of attack α of up to three degrees relative to a tangent to the orbit U in the upwind and downwind halves of the orbit U.

[0050] Fig. 12Figure 1 shows a rotor blade 1 with a three-part airfoil 21 and an adjustment device 15 formed by two linear motors 165 integrated into the central airfoil segment 212 of the rotor blade 1. A lever arm 215 of the front and rear airfoil segments 211, 213 is each articulated with radius r2 to the hinges 214 with the axes of rotation z of the central airfoil segment 212 and connected to the rotors 160 of the linear motors 165. By means of a control unit (not shown), the suction side (-) of the variable airfoil 2 changes, as shown in Figure 1. Fig. 5As shown, at each of the positioning positions C1 of a freely adjustable diameter of the orbit U, the orientation from the inside to the outside of the orbit U is changed twice. The positioning function of the adjusting device 15 formed by the two linear motors 165 is activated by applying an electrical voltage, whereby alternately polarized permanent magnets 163 interact with reversible excitation windings 162 of the stators 161, so that, as in Fig. 5As shown in both halves of the orbit U in the longitudinal sections L2 of the rotor blades 1 of a helicopter 130, the positive angle of attack α of the airfoil chord p of the rotor blade 1 changes its orientation from the inside to the outside of the orbit U 20 times within one second by means of the oscillating linear motion of the paired electric motors 16. This applies to a rotor module 10 of the helicopter 130 with a diameter of approximately ten meters at a rotational speed of 800 km / h. Each rotor 160 has two tongues, each with a plurality of permanently magnets 163 arranged in series and alternately polarized, which engage in slot-shaped pockets of the stator 161. A contactless electromagnetic connection between the wing segments 212-213 can be established through the air gap a on both sides between the rotors 160 and the stators 161 of the two linear motors 165.

[0051] Fig. 13Figure 1 shows electromagnetic adjustment devices 15 as an example for a longitudinal section L1-Ln of the rotor blade 1, at the top at an adjustment position C1 with the variable symmetrical airfoil 2. The hinges 214 are each arranged concentrically and coaxially to the axes of rotation z for the leading blade segment 211 and the trailing blade segment 213 and serve as cable channels for the power supply of the two adjustment devices 15, each formed by a slide 217. In the simple embodiment shown above, an iron sleeve or a radial laminated core of the hinge 214 forms the stator 161 with an excitation winding 162 for the adjustment device 15 formed by a slide 217.By reversing the polarity of the excitation winding 162 at the iron sleeve, as shown above, or at radial laminated cores of the hinge 214, as shown below on the linear motor 165, the slide 217 performs an oscillating movement at a frequency of 20-30 Hz on a hollow hinge pin. Threaded projections of the front and rear blade segments 211, 213 and threaded receptacles of the slide 217, moved by the linear motor 165, engage and cause a rotational movement in opposite directions at the front and rear blade segments 211, 213. Air bearings between the threads of the hinges 214 and between the rotor 160 and the stator 161 keep the frictional forces low and are supplied with compressed air through the hollow profile 141 of the hinges 214.In the embodiment shown above, the electromagnetically induced field is aligned parallel to the axes of rotation z, whereas in the linear motor 165 shown below, a plurality of excitation windings 162 of the stator 161 are each aligned radially to the axes of rotation z of the blade segments 211, 213, and the rotor 160, arranged concentrically and coaxially to the hinges 214, has a plurality of corresponding permanent magnets 163. The linear motor 165 allows for precise positioning of the slide 217, which is designed as the rotor 160 of the linear motor 165, so that the positive angle of attack α for the blade segments 211, 213 can be set and varied very precisely.The adjusting device 15 with the adjusting and holding function is designed to absorb considerable aerodynamically induced suction forces as well as centrifugal forces, wherein the front and rear wing segments 211,213 in each longitudinal section L1-Ln of the rotor blade 1 are individually adjustable and lockable.

[0052] Fig. 14The figure above shows a rotor blade 1 in which the adjustment device 15 has an electric motor 16, the axis of rotation z' of which is aligned parallel to the chord line p of the variable symmetrical airfoil 2 at the adjustment positions C1, and in which the retaining element 151 of the adjustment device 15 has a cylinder lock 152. In the middle and below, the variable asymmetrical airfoil 2 with reversed suction sides (-) is shown. The front wing segment 211 and the rear wing segment 213 are each articulated to a rotation axis z of the middle wing segment 212 and are adjusted by a bevel gear driven by the electric motor 16 such that the front and rear wing segments 211, 213 rotate inwards or outwards at the positioning positions C1 in opposite directions towards the inside or outside of the orbit U, whereby the direction of rotation of the electric motor 16 changes twice at the positioning positions C1 in one revolution of the rotor blade 1.The perspective exploded view shows the adjustment device 15 for a section within a longitudinal segment of the rotor blade 1 with wing segments 211-213, which can be manufactured as hollow profiles 141, e.g., as extruded aluminum profiles with unspecified screw channels for connecting the individual parts of the rotor blade 1. The step-detent gearbox with cylinder locks 152 shown here requires no additional energy expenditure to maintain the variable asymmetric wing profile 2 with reversed suction sides (-) in the two halves of the orbit U, so that only comparatively small adjustment forces have to be applied by the electric motor 16, since the variable wing profile 2 can be adjusted at the positioning positions C1 as shown in the figure. Fig. 5 and Figs. 7-9 shown in a flag position.

[0053] Fig. 15Figure 1 shows a rotor blade 1, in which the adjusting device 15 has an electric motor 16 and the holding element 151 has a worm gear, in the perspective exploded view of a section of the rotor blade 1 at the adjustment positions C1 of the orbit U, as in Figs. 7-9 shown. Rotor blade 1 essentially corresponds in its construction to the one shown. Fig. 14 detailed example of implementation. In contrast to Fig. 14The step-stop gearbox here has an electric motor 16 whose axis of rotation z' is aligned parallel to the axes of rotation z of the front and rear wing segments 211,213 and whose locking device is formed by an unspecified worm gear which transmits the adjusting force at the positioning positions C1 to the front and rear wing segments 211,213 by means of bevel gears, wherein the middle wing segment 212 forms a support 140 for the worm gear of the electric motor 16 and changes the direction of rotation of the electric motor 16 twice in one revolution of the rotor blade 1.

[0054] Fig. 16Figure 1 shows a schematic cross-sectional view of a storm surge barrier, such as the one built on the Oosterschelde estuary. The transverse structure consists of piers and bridge elements, as well as an A-shaped foundation that rises ramp-like on the Oosterschelde side and has a step on the North Sea side. At low tide, the water of the Oosterschelde flows at high velocity through a narrow passage between the A-shaped foundation and an upper longitudinal beam of the barrier. Between the piers of the barrier, approximately 30-meter-long, drum-shaped rotor modules (10) with a diameter of about 10 meters are spanned, stiffened at 4-meter intervals by disc-shaped crossbeams.A total of six rotor blades 1 with a three-part airfoil 21 connect the disc-shaped crossbeams to one another, forming a rotor drum that is rigid in bending, shear, and torsion. The shaft of this drum is anchored to a watertight bearing in the barrier and connected to a motor-generator inside the pylons. At the diameter with the positioning positions C1, the suction side of a rotor blade 1 switches from the inner to the outer side of the orbit U twice per revolution. The rotor blades have a chord length of 2 m and an airfoil thickness of 0.4 m.

[0055] Fig. 17 Figure 11 shows a wind turbine 11 with a vertical axis of rotation y and a base-side spoked wheel 17, which carries five vertically stacked rotor modules 10, each with eight rotor blades 1. The rotor blades 1 are subdivided into longitudinal sections L1-Ln and have a three-part asymmetric airfoil 21, which corresponds to the one shown in Figure 1. Figs. 10-11The illustrated embodiment corresponds to this. As shown in Fig. 7 As shown, the suction side (-) of the airfoil 2 changes from the outside to the inside of the orbit and vice versa at the positioning positions C1 of a diameter C1 that can be oriented within a radius of 360° to the respective wind direction. The eight rotor blades 1 are spaced a distance from the vertical axis of rotation y by a radius r1 and are each connected at their upper and lower ends to a circumferentially spanning ring support 122. Photovoltaic cells, not otherwise specified, preferably cover the area with the exception of the joint gap 210. Fig. 11The surfaces of the three-part airfoil profiles 21 of the rotor blades 1 are alternately oriented on the inside and outside of the orbit U to the sun during the rotation of the rotor modules 10. The base-side ring support 122 has sixteen compression members that connect the rotor formed by the five stacked rotor modules 10 to the lower pivot bearing T' of a hub 170, while sixteen pairs of V-shaped tension spokes are braced to the upper pivot bearing T of the hub 170 in such a way that a vertical lever arm is formed between the upper pivot bearing T and the lower pivot bearing T' to transfer the tilting moment of the rotor via the hub 170 into a cantilevered base of the wind turbine 11. The inflow area of ​​the wind turbine 11 corresponds to 14.The rotor diameter of a conventional seven MW wind turbine with a horizontal axis of rotation is 000 m², meaning that up to a wind speed of twelve m / s, the wind turbine 11 shown here can also achieve a peak output of seven MW. However, when the rotational speed of a conventional wind turbine has to be reduced at wind speeds above twelve m / s, it can achieve two to three times the output. Due to its consistent lightweight construction with predominantly axially stressed support members, the wind turbine 11, which stabilizes itself like a gyroscope, requires only half the structural weight of a conventional wind turbine with a horizontal axis of rotation.

[0056] Fig. 18Figure 11 shows a wind turbine 11 in which ten rotor blades 1 with an asymmetric airfoil 2 are supported by a horizontally arranged spoked wheel 17, which forms a rotor module 10. The rotor blades 1 are connected to an outer ring support 122, which is connected to a hub 170 by means of a plurality of radial spokes. The spoked wheel 17 has a diameter of three hundred meters, with the rotor blades 1 being divided into two halves, each fifty meters long, by the ring support 122. A rigid connection formed by a cable bracing 142 is formed between the ring support 122 and the longitudinal member of the three-part airfoil 21. The hub 170 of the spoked wheel 17, arranged coaxially and concentrically to the vertical axis of rotation y, is rotatably mounted on a central support structure by means of an upper rotary bearing T and a lower rotary bearing T', which preferably accommodates at least one motor generator in the area of ​​the hub 170.Thanks to its lattice tower, which widens towards the ground, wind turbine 11 can be anchored both offshore (in front of the coast) and onshore (on the mainland). With a wind-facing area of ​​30,000 square meters, the wind turbine is designed for a peak output of 30 megawatts.

[0057] Fig. 19 shows a floating wind turbine 11, whose rotor module 10 corresponds to the one in Fig. 18The embodiment shown corresponds to the embodiment shown. Here, too, the hub 170 of the spoked wheel 17 is rotatably mounted on a central support structure via an upper pivot joint T and a lower pivot joint T'. This support structure houses a machine house for several motor-generators in the area of ​​the hub 170 and has a float 120 and a buoy 171 with a ballast at its lower end. The support structure can also be referred to as the supporting framework. Anchor cables are attached approximately at the waterline of the floating wind turbine 11 and are connected to anchors 121 on the seabed. The inertia caused by gyroscopic moments serves to stabilize the vertical axis of rotation y of the floating wind turbine 11.In a flowing body of water or in a tidal current, a water turbine with an analogous construction can rotate below the waterline around the same axis of rotation y in the opposite direction of rotation, so that the ballasted buoy carries a floating wind turbine 11 and a water turbine not shown here.

[0058] Fig. 20Figure 11 shows a wind or water turbine 11, 12 with rotor blades 1 arranged radially to the axis of rotation y in a plane of rotation R, designed for a flow F, F' that changes direction regularly and diametrically. The six rotor blades are connected to a motor-generator arranged coaxially and concentrically to the axis of rotation y and maintain their direction of rotation when the direction of the flow F, F' changes. This is the case, for example, in a wave power plant with a casing 14, where the shaft displaces a volume of air from the casing 14, thus utilizing an onshore airflow to drive a wind turbine. Here, an offshore airflow generated by the returning shaft continues to drive the wind turbine 11 while maintaining its direction of rotation, as the suction side (-) of the six radial rotor blades 1 is switched to the side facing away from the flow by means of the adjustment device 15.A periodically changing direction flow F,F' is also generated by tidal currents, so that a water turbine 12 has essentially the same design as an air turbine. For both the wind and water turbines 11,12, it is advantageous that in a neutral transition position when the direction of the flow F,F' changes, the chord line p of the variable airfoil is arranged parallel to the plane of rotation R, and by means of the adjustment device 15, the chord line p has a positive angle of attack α of up to four degrees relative to the temporarily existing symmetrical airfoil 2, so that a maximum tangential driving force can be derived from the lift force in the plane of rotation R resulting from the flow velocity and the rotational speed.The section view in the middle shows the transition position of the rotor blades 1 of the rotor module 10, in which the variable asymmetric airfoil 2 temporarily has a symmetric airfoil 2.

[0059] Fig. 21Figure 11 shows a wind turbine 11 with a rotor module 10, which has a cable-tensioned spoked wheel 17 with a plurality of radial support and tension cables that are tensioned to an outer ring support 122 arranged in the plane of rotation R' and to a hub 170. In the plane of rotation R' of the spoked wheel 17, ten rotor blades 1 are arranged radially to the axis of rotation y and each has a three-part airfoil 21, the central airfoil segment 212 of which is clamped to two rotor heads of the ring support 122 that are diametrically opposed to each other in the plane of rotation R'. The rotor module 10 is supported by a fork that is articulated to the upper end of a mast in an azimuth bearing (rotary bearing).The ten radial rotor blades 1 rotate in the vertical plane of rotation R' of the spoked wheel 17 on an annular orbit U, defined by an inner radius r1 and an outer radius r2 around the axis of rotation y, and together with the spoked wheel 17 form a rotor module 10 of extremely lightweight construction. The ring support 122, the support and tension cables, and the rotor blades 1 are preferably made at least partially of carbon fiber composite materials. The ten rotor blades 1 are twisted by ten degrees over a length of sixty meters, with a stepped arrangement enabling the formation of a plurality of straight longitudinal sections L1-Ln, so that the rotor blade 1 is shaped as in . Fig. 22shown to be adjustable such that in the operating position a positive angle of attack α of five degrees is formed, wherein the symmetrical airfoil 2 has a positive angle of attack α of one degree and a negative angle of attack α' of three degrees is required for the stall position, so that the adjustment range of the three-part airfoil 21 is a total of seven degrees. The electromechanical adjustment device 15 integrated into the housing 14 formed by the middle blade segment 212 corresponds to that shown in Fig. 14 or Fig. 15 The example shown. Wind turbine 11 after Fig. 21It can be operated without restrictions at wind speeds exceeding 12 m / s. If, for example, a positive angle of attack α of the asymmetric airfoil 2 of the rotor blades 1 alternates regularly with a negative angle of attack α', the rotational speed of the wind turbine can be continuously regulated by means of the adjustment device 15. The suction side (-) of the rotor blade 1, oriented against the wind direction, generates thrust that can be offset against the thrust acting in the wind direction, thus relieving the load on the supporting structure. Furthermore, the stall position allows the wind turbine 11 to be shut down for maintenance and cleaning work.

[0060] Fig. 22 shows an electromechanical adjusting device 15, which corresponds to the one in Fig. 14 The described embodiment corresponds to three cross-sections of the asymmetrical airfoil 2 of a rotor blade 1 of the wind turbine 11 according to Fig. 21in the area of ​​the longitudinal sections L1-Ln of the rotor blade 1 adjacent to the ring carrier 122. The rotor blades 1 are twisted and are inclined at their end facing the axis of rotation y to a maximum degree relative to the plane of rotation R' of the spoked wheel 17, while the inclination angle decreases continuously towards the outer end of the rotor blade 1. The central blade segment 212 forms a housing 14 and a support 140 for the [unclear - possibly referring to a specific component or element] in Fig. 14The adjustment device 15, as described, is integrated into the hollow profile 141 of the longitudinal beam. The adjustment range between a positive and a negative angle of attack α,α', achievable in all longitudinal sections L1-Ln of the rotor blade 1 by means of the adjustment device 15, enables stepless adaptation to the respective wind speed down to the standstill of the rotor module 10 with stall-pitch control. The chord line p of the three-part airfoil profiles 21 has a negative angle of attack α', as shown in the lower profile cross-section. The asymmetric airfoil profile 2 above shows a positive angle of attack α of 4 degrees, which is designed so that the rotor blade 1 generates a maximum tangential lift force acting in the direction of rotation.For wind speeds above 12 m / s, a symmetrical airfoil of the three-part airfoil 21 can be used temporarily, whereby the lift force and also the tangential driving force are reduced by about one-third compared to the asymmetrical airfoil 2 shown above. By further simultaneously rotating the leading wing segment 211 and the trailing wing segment 213 upwind, the angle of attack α' becomes negative and, in the case of the asymmetrical airfoil 2 shown below, causes the suction side (-) to change from the leeward side to the upwind side, resulting in a stall position in which the tangential driving force acts against the direction of rotation.

[0061] Fig. 23Figure 1 shows a rotary-wing vehicle 13, designed as a helicopter 130 with a rotor module 10 formed by four U-shaped rotor blades 1, in which two pairs of opposing rotor blades 1 rotate in opposite directions around the axis of rotation y. The fuselage of the helicopter 130 is designed as a cabin for preferably nine passengers and a pilot and preferably has a streamlined teardrop shape, at the rear of which a propeller assembly 131 is arranged. The four U-shaped rotor blades are each connected to the fuselage at their upper and lower ends via pivot bearings T, T'. Each rotor blade 1 is subdivided into three longitudinal sections L1-L3, with the outermost longitudinal section L2 encircling the fuselage, including the propeller assembly 180, at the rear and designed as shown in Figure 1. Fig. 5The helicopter 130 is shown to be able to direct thrust in any direction within a 360° radius during hovering flight, while the rotor module 10 is designed in longitudinal sections L1 and L3 to generate lift, which is controllable by means of the adjustable asymmetric airfoil 2. The propeller assembly 131 at the rear, formed by two counter-rotating propellers, serves exclusively to generate thrust in the direction of flight, thus enabling flight speeds of up to 500 km / h with a hybrid propulsion concept. A drive power of 600 to 800 kW is sufficient to achieve this flight performance.

[0062] Fig. 24Figure 18 shows an aircraft 18 in which the variable asymmetric airfoil 2 is used to form the wings 180. The central wing segment 212 of the asymmetric airfoil 2 is rigidly connected to the fuselage of the aircraft 18 and serves as a longitudinal spar for the wing 180. The electrically powered aircraft 18 is designed for an operating speed of, for example, 500 km / h. The electromechanical adjustment device 15 corresponds to that shown in Figure 1. Fig. 15The illustrated embodiment. The first cross-section, viewed from top to bottom, shows an asymmetric airfoil 2 whose chord line p has a positive angle of attack α of 1.5 to 2 degrees relative to the oncoming airflow δ and the longitudinal center axis x of the aircraft, while the second cross-section shows a wing configuration with a larger angle of attack α of approximately three to four degrees, which increases the lift generated by the wing 180. The lower cross-section shows a wing configuration for takeoff and landing, in which the leading edge wing segment 211 and the trailing edge wing segment 213 are so deeply rotated relative to the central wing segment 212 formed by the longitudinal spar that the chord line p has a positive angle of attack α of 6 degrees relative to the longitudinal center axis x of the aircraft 18. Joint gaps 210 between the three wing segments 211-213 allow laminar flow over the airfoil 2 of the wing 180.The complete integration of the adjustment device 15 into the housing 14 formed by the central wing segment 212 eliminates the need for conventional leading-edge slats and flaps, including the landing flap carrier fairings, the so-called canoes on the underside of the wing.

[0063] Naturally, various variations and modifications are possible within the scope of the present invention. Reference symbol list Rotor blade 1 Asymmetrical wing profile 2 Rotor module 10 suction side (-) Wind turbine 11 Angle of attack, positive, negative α,α' water turbine 12 Offset angle β Floating bodies 120 Airflow δ anchor 121 air gap a Ring bearer 122 Positions C1,C2 Rotary wing vehicle 13 wing trailing edge e helicopter 130 flow F, F' Propeller arrangement 131 Flight direction D Housing 14 longitudinal section L1-Ln abutment 140 wing nose n Hollow profile 141 Profile tendon p Rope tensioning 142 Profile thickness q Adjustment device 15 radius r1,r2 retaining element 151 plane of rotation R , R ' Cylinder lock 152 pivot bearing T,T ' electric motor 16 orbit U runner 160 Longitudinal axis x stator 161 axis of rotation y Excitation development 162 axis of rotation z,z' Permanent magnet 163 Three-part wing profile 21 stepper motor 164 joint space 210 Linear motor 165 Front wing segment 211 spoked wheel 17 Middle wing segment 212 hub 170 Rear wing segment 213 Ballasted buoy 171 hinge 214 Airplane 18 Lever arm 215 wing 180 counterweight 216 Circulation positions I-XII Slider 217

Claims

1. A device comprising an asymmetrical wing profile (2) and an adjusting device (15), which asymmetrical wing profile (2) has a profile thickness (q) and a chord line (p) extending between a leading edge (n) and a trailing edge (e) of the wing, which asymmetrical wing profile (2) has a three-part variable wing profile (21) in at least one longitudinal section (L1-Ln), in which wing profile (21) a front and a rear wing segment (211, 213) are hinged to a middle wing segment (212) by means of two hinges (214) with axes of rotation (z) and are configured to enable a rotary movement about the assigned axis of rotation (z) relative to the middle wing segment (212), which middle wing segment (212) forms an inherently rigid housing (19) for receiving the adjusting device (15) and, as a longitudinal carrier of the asymmetrical wing profile (2), has a hollow profile (141) which forms an abutment (140) for the adjusting device (15) in at least one longitudinal section (L1-Ln), wherein the adjusting device (15) has at least one electric motor (16) provided in the middle wing segment (212) and is configured to enable simultaneous rotating in or rotating out of the front and rear wing segment (212, 213) in directions of rotation opposite to each other with the aid of the at least one electric motor (16) and thus to enable a variable suction side (-) of the asymmetrical wing profile (2), wherein the angle of attack (α,α') of the chord line (p) changes when the front and rear wing segment (212, 213) are rotated in or rotated out.

2. The device according to claim 1, which has a plurality of the asymmetrical wing profiles (2) and a motor generator, which wing profiles (2) are formed as rotor blades (1), which rotor blades (1) form a rotor module (10), which rotor module (10) is formed to rotate on an orbit (U) with radii (r1, r2) about an axis of rotation (y), which rotor blades (1) are connected to the motor generator, and which rotor blades (1) are preferably formed to be straight, bow-shaped or polygon-shaped.

3. The device according to claim 2, in which the plurality of rotor blades (1) is connected at at least one end to the motor generator, and in which rotor module (10) a diameter with setting positions (C1) divides the orbit (U) into two halves, wherein the suction sides (-) of the variable wing profile (2) are adjusted by means of the adjusting device (15) in a first half of the orbit (U) on the outer side and in a second half on the inner side of the orbit (U) and wherein the variable wing profile (2) at the diameter with the setting positions (C1) temporarily has a symmetrical wing profile (2), the chord line (p) of which is oriented tangentially to the circular orbit (U) of the rotor module (10) at the setting positions (C1), and the chord line (p), by rotating in and rotating out the front and rear wing segments (211, 213), in each case in opposite directions of rotation, has a positive angle of attack (α) relative to a tangent to the orbit (U) in both halves of the orbit (U), and the longitudinal carrier (14) of the middle wing segment (222) is formed as a box-shaped hollow profile (141), the flanges of which, which are opposite each other on the orbit (U), form part of the surface of the asymmetrical wing profile (2), and a plurality of hollow profiles (141) is connected at nodal points to transversely stiffening ring carriers (122) and forms a self-supporting rotor module (10) that is inherently resistant to bending, shear and torsion.

4. The device according to claim 2 or 3, in which the rotor blades (1) are oriented parallel to the axis of rotation (y) in the at least one longitudinal section (L1-Ln), wherein the adjusting device (15), at a diameter of the orbit (U) with the radius (r1), at setting positions (C1) opposite to each other and freely adjustable over the entire angular range, is actuated in such a way that the suction side (-) of the variable wing profile (2) changes from the outer to the inner side of the orbit (U) and vice versa in one revolution of the rotor blade (1), wherein the front and rear wing segments (211, 213) are each adjustable at the setting positions (C1) in the axes of rotation (z) of the hinges (214) with opposite directions of rotation by a maximum of 9 degrees and preferably by a maximum of 8 degrees relative to the middle wing segment (212) formed by the longitudinal carrier (14).

5. The device according to any of claims 2 to 4, which is configured to enable rotation of the rotor module (2) about a horizontal axis of rotation (y) and rotation of a cable-tensioned spoke wheel (17) with a hub (170) and with an outer ring carrier (122), formed as a compression ring, in a vertical plane of rotation (R'), which rotor module (2) is alignable to the respective direction of the flow (F) by means of an azimuth bearing on a mast, and which device is configured to rotate a plurality of rotor blades (1) on a ring-shaped orbit (U) with radii (r1, r2) about the horizontal axis of rotation (y) and, in the vertical plane of rotation (R'), to connect the middle wing segments (212) of the intrinsically twisted rotor blades (1) to the ring carrier (122) in a flexurally rigid manner by means of rotor heads located opposite each other in pairs in such a way that in each longitudinal section (L1-Ln) of an intrinsically twisted rotor blade (1) the chord line (p) of the asymmetrical wing profile (2) has a positive angle of attack (α) of up to 7 degrees relative to a flow (A) resulting from the wind speed and the rotational speed, wherein, for stall pitch control, the device is preferably configured to cause a negative angle of attack (α') of the chord line (p) relative to the flow resulting from the wind speed and the rotational speed.

6. The device according to any of claims 2 to 5, in which the adjusting device (15) is formed as an electromechanical adjusting device (15) with holding elements (151), wherein in each longitudinal section (L1-Ln) of the rotor blade (1) at least one of the electric motors (16) is provided with a step-lock gear, and which holding elements (151) are formed either by a cylinder lock (152) connected to the shaft of the electric motor (16) or by a worm wheel connected to the shaft of the electric motor (16), wherein the direction of rotation of the electric motor (16) with the step-lock gear changes in one revolution of the rotor blade (1) respectively at the setting positions (C1) of the orbit (U).

7. The device according to any of claims 2 to 6, which is formed as a rotary wing vehicle (13) or as a wind turbine (11) or as a water turbine (12), wherein - in the case of the rotary wing vehicle (13), at the setting positions (C1) of the orbit (U), the suction side (-) of the variable wing profile (2) of the rotor blades (1) is alignable to the respective flight direction (D) by means of the adjusting device (15) in both halves of the orbit (U) of the rotor module (10) and the motor generator is operated as a motor to generate thrust, and - in the case of the wind or water turbine (11, 12), the suction side (-) of the variable wing profile (2) of the rotor blades (1) is alignable, at the setting positions (C1) of the orbit (U), to the leeward side of the flow (F) by means of the adjusting device (15), independently of a horizontally or vertically oriented axis of rotation (y), and the motor generator is operable at least temporarily as a generator and is operable at least temporarily as a motor in order to accelerate the wind or water turbine (11, 12) to a speed required for self-running when the flow (F) is weak.

8. The device according to any of claims 2 to 7, which is formed as a rotary wing vehicle (13), in particular as a helicopter (130), and is formed either with a rotor module (10) or with a frontside and a rear-side rotor module (10), each rotating in opposite directions of rotation, wherein the rotor blade (1) is formed in the shape of a bow and has a lower longitudinal section (L1) leading in the direction of rotation of the rotor module (10), a middle longitudinal section (L2) and an upper longitudinal section (L3) trailing in the direction of rotation of the rotor module (10), wherein the lower longitudinal section (L1) has an offset angle (β) in the circumferential direction relative to the upper longitudinal section (L3) and the middle longitudinal section (L2) connects the lower longitudinal section with the upper longitudinal section (L1, L3) and is formed with a pitch in the direction of rotation, in which rotor modules (10) in the lower and upper longitudinal sections (L1, L3) the diameter is alignable with the setting positions (C1) respectively in the direction of flight (D) and in the middle longitudinal section (L2) respectively transversely to the direction of flight (D), wherein the offset angle (β) is preferably approximately 10 degrees.

9. The device according to any of claims 2 to 8, which is formed as a helicopter (13), in which a rotor module (10) formed by four bow-shaped rotor blades (1) together with a tail-side propeller arrangement (131) connected to the fuselage of the helicopter (130) forms a hybrid drive system, in which the four bow-shaped rotor blades (1) each rotate in pairs and in opposite directions of rotation about the axis of rotation (y) and about a streamlined fuselage including the tail-side propeller arrangement (131), wherein a bow-shaped rotor blade (1) has a respective longitudinal section (L1, L3) arranged above and below the fuselage parallel to the longitudinal axis (x) and the longitudinal sections (L1, L3) are each connected at their outer ends by a longitudinal section (L2) arranged parallel to the axis of rotation (y), which longitudinal section (L2) is formed to align the diameter with the setting positions (C1) through an angle range of 360 degrees respectively perpendicular to a selectable flight direction (D) to generate thrust from a standing position in the selectable flight direction (D).

10. The device according to any of claims 2 to 9, which is formed as a water turbine (12) having a horizontally or vertically oriented axis of rotation (y), which is anchored in a body of water with a flow (F), either in a transverse structure of the flowing body of water or floating in the flowing body of water, and which has a floating body (120) on the water surface, which (120) is anchored to the bottom of the body of water by means of at least one anchor (121) and anchor ropes and receives the ring-shaped, gearless motor generator with a shaft which, below the floating body (120), has a radial distance with the radius (r1) to at least one upper and one lower ring carrier (122) of the rotor module (10), and which upper and lower ring carriers (122) are connected together with the shaft and with the longitudinal carriers (14) of the three-part wing profiles (21) to form a rotor module (10) which is resistant to bending, shear and torsion, wherein the floating body (120) is preferably formed either as a rectangular raft with PV collectors on the top face or as a discus-shaped disk or as a floating ring.

11. The device according to any of claims 2 to 10, in which the rotor blades (1) are formed straight and rotate on an orbit (U) with an inner and an outer radius (r1, r2) in a plane of rotation (R) about the axis of rotation (y), wherein the longitudinal carrier (14) of the rotor blade (1) formed by the middle wing segment (212) is connected, either at its outer or at its inner end, to the motor generator, and the adjusting device (15) - in the case of a wind turbine (11) or a water turbine (12) is formed to align the suction sides (-) of the variable wing profiles (2) with the leeward side in a flow (F, F') which periodically changes direction diametrically, and - in the case of a rotary wing vehicle (13) is formed to generate a thrust in the direction of flight (D) or a reverse thrust against the direction of flight (D), or - in the case of a rotary wing vehicle (13) with a transverse thruster as a transverse thruster is formed to generate thrust in one of two possible directions.

12. The device according to any of claims 2 to 11, which is formed as a wind turbine (11) or as a water turbine (12), and which is configured to change, in a flow (F, F') which regularly changes direction, the suction side (-) of a plurality of rotor blades (1) arranged perpendicularly and radially to an axis of rotation (y) by means of the adjusting device (15) synchronously with the change in flow direction respectively towards the side facing away from the flow, wherein the variable wing profile (2) of the rotor blade (1) in a transitional position temporarily has a symmetrical wing profile (2) with an angle of attack (α) of the chord line (p) of zero degrees and the respective work position of the asymmetrical wing profile (2), by actuation of the adjusting device (15), has a positive angle of attack (α), which positive angle (α) is preferably up to four degrees in each of the two directions of the flow (F,F').

13. The device according to any of claims 2 to 12, which is formed as a wind turbine (11), in which the rotor module (10) is formed as a gyroscope for using the mass inertia caused by gyroscopic moments and gyroscopic forces to stabilize the vertical axis of rotation (y) of the rotor module (10) formed as a spoked wheel (17) with a horizontal plane of rotation (R'), in which rotor module (10) supporting and tensioning cables connect an outer ring carrier (122), which is spaced apart from the axis of rotation (y) by a radius (r1), to a hub (170), wherein the ring carrier (122) formed as a compression ring carries a plurality of straight rotor blades (1) arranged parallel to the axis of rotation (y), which are connected by means of a cable tensioning (142) of the longitudinal carriers (14) to the ring carrier (122) and with the spokes of the spoked wheel (17), which spokes are formed by supporting and tensioning cables, to the hub (170) and, via an upper and a lower pivot bearing (T, T'), to a carrier structure of the wind turbine (11) such that an air gap is formed between at least one stator on the support structure side, arranged coaxially and concentrically to the axis of rotation (y), and at least one rotor-side rotor of the motor generator of the wind turbine (11), wherein the supporting structure can be anchored onshore or offshore in a foundation and the gyroscopic effect is preferably used for a wind turbine (11), the supporting structure of which has a floating body (120) formed as a ballasted buoy (171), which floating body (120) can be anchored to the bottom of the sea by means of ropes and anchors (121), wherein the rotor module (10) can preferably be formed with a diameter of more than one hundred meters, more preferably of more than two hundred meters.

14. The device according to any of claims 2 to 13, which is formed as a wind turbine (11), in which a plurality of rotor modules (10) is stacked vertically on top of each other and is supported by a base-side ring carrier (122), which forms the compression ring of a spoke wheel (17) that is resistant to bending, shear and torsion, the hub (170) of which, arranged concentrically and coaxially to the axis of rotation (y), receives the rotor of the motor generator on the inner side and is connected, by means of an upper pivot bearing (T) and a lower pivot bearing (T'), via an air gap, to a stator of the motor generator arranged coaxially and concentrically to the axis of rotation (y), which stator is coupled either to a cantilever arm of the base of the wind turbine (11) or, in the case of a floating wind turbine (11), to a ballasted buoy (171).

15. The device according to any of the preceding claims, which is formed as an aircraft (18) with at least one lift-generating surface (180), wherein the adjusting device (15) has a step-lock gear and a holding element (151), wherein, in at least one longitudinal section (L1-Ln) of the asymmetrical wing profile (2), the middle wing segment (212) is connected to at least one electric motor (16) and the front and rear wing segments (211, 213) of the three-part wing profile (21) are connected to the holding element (151) of the adjusting device (15) in such a way that the lift generated by the suction side (-) of the variable wing profile (2) can be adapted to the respective flight situation of the aircraft (18) by actuating the adjusting device (15), wherein the step-lock gear preferably enables a ratio of the setting force of 1 to 10.