EP3247902A1 - Multifunktionales flap als rueckstromklappe - Google Patents
Multifunktionales flap als rueckstromklappeInfo
- Publication number
- EP3247902A1 EP3247902A1 EP16723243.8A EP16723243A EP3247902A1 EP 3247902 A1 EP3247902 A1 EP 3247902A1 EP 16723243 A EP16723243 A EP 16723243A EP 3247902 A1 EP3247902 A1 EP 3247902A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flap
- rotor blade
- buoyancy
- actuator
- flaps
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D7/00—Controlling wind motors
- F03D7/02—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor
- F03D7/022—Adjusting aerodynamic properties of the blades
- F03D7/0232—Adjusting aerodynamic properties of the blades with flaps or slats
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/46—Varying camber by inflatable elements
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03B—MACHINES OR ENGINES FOR LIQUIDS
- F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
- F03B3/12—Blades; Blade-carrying rotors
- F03B3/121—Blades, their form or construction
- F03B3/123—Blades, their form or construction specially designed as adjustable blades, e.g. for Kaplan-type turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
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- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
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- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D7/00—Controlling wind motors
- F03D7/02—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor
- F03D7/0244—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor for braking
- F03D7/0252—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor for braking with aerodynamic drag devices on the blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
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- F15D1/00—Influencing flow of fluids
- F15D1/10—Influencing flow of fluids around bodies of solid material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05B2210/00—Working fluid
- F05B2210/16—Air or water being indistinctly used as working fluid, i.e. the machine can work equally with air or water without any modification
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05B2240/305—Flaps, slats or spoilers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05B2240/305—Flaps, slats or spoilers
- F05B2240/3052—Flaps, slats or spoilers adjustable
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05B2240/31—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05B2240/00—Components
- F05B2240/20—Rotors
- F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05B2240/31—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape
- F05B2240/311—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor of changeable form or shape flexible or elastic
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05B2240/90—Mounting on supporting structures or systems
- F05B2240/98—Mounting on supporting structures or systems which is inflatable
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05B2260/00—Function
- F05B2260/50—Kinematic linkage, i.e. transmission of position
- F05B2260/507—Kinematic linkage, i.e. transmission of position using servos, independent actuators, etc.
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05B2260/00—Function
- F05B2260/90—Braking
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- F05B2270/00—Control
- F05B2270/40—Type of control system
- F05B2270/402—Type of control system passive or reactive, e.g. using large wind vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2270/00—Control
- F05B2270/40—Type of control system
- F05B2270/404—Type of control system active, predictive, or anticipative
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/30—Wing lift efficiency
Definitions
- a model wing a with detached flow; b: with detached flow with flap (from St.d.T. Pantone G ET AL)
- the invention relates in particular to a return flap on a wing, in which further increased by displacement and / or reduction of Endkanten-Ablensewirbel the buoyancy and / or the minimum (start) speed is reduced than in conventional return flow flaps (improvement area A + B in Figure 1). Furthermore, by providing a combination A passive with an active return flap allows a precautionary / avoidance reaction to an impending gust situation as a safety system (Improvement Area D: Overspeed Control).
- the lower permanent alternating load (in particular the maximum values) of the long rotor blades or blades achievable thereby has great significance with regard to their actual service life due to fatigue phenomena, in particular of GFRP or CFRP materials used there (It has been found that FIG For example, the wing deformation during the lifetime increases and these must remain within a limited framework).
- the device according to the invention in the form of a wind turbine rotor blade with a passive and / or active flap system has the yield improvement at least in the areas of improvement A and / or B and / or C and / or D, in the form of one with a Fluid inflatable (inflatable) actuator element, and possibly a flap if necessary very easy to retrofit and / or attachable and / or interchangeable,
- Low wind, and / or Overspeedschutz and / or vibration damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure equalization openings and / or ice and snow removal system, can be used, characterized in that means for increasing the rigidity of the flap and / or means for Wegbegrenzung and that the travel limit limits the opening angle of the flap of ⁇ 90 degrees, preferably ⁇ 75 degrees, very particularly preferably ⁇ 60 degrees, and that at least one actuator element and / or a component thereof can be filled with a fluid (inflatable) is, and this can be folded at least simultaneously in the initial state.
- Disadvantages of these embodiments are the short life of the materials used under real weather conditions such as ice, rain, sand, UV radiation.
- the low mechanical stability under conditions of use, such as in strong gusts and winds and the possibly necessary cleaning of an aircraft wing is disadvantageous.
- surface flaps / backflow flaps in the wind tunnel were carried out with surface flaps / backflow flaps in the wind tunnel to explore their potential as for influencing flow separation (see Meyer, Robert K.J., Experimental investigations on hydrofoils to influence flow separation.
- the return valves used here have a solid plate as a flap and are hinged with elastic connecting elements.
- a rotor blade for a driven horizontal rotor of a lifting or support screw with at least one flap integrated in the rotor blade, which is pivotable relative to a main body of the rotor blade about a longitudinal direction of rotation of the horizontal rotor longitudinal axis of the rotor blade is presented, layed out.
- the object of the invention is to disclose a rotor blade in which the dynamic flow separation is displaced by passive measures to higher angles of attack or to higher speeds. This is realized by means of an elastic return flap.
- the flap has a basic position in which it rests flat against the top of the main body. In other words, it is a so-called surface flap.
- This flap is passively swingable against an elastic restoring force from its basic position away from the top of the main body. That is, the flap will not be actively brought by any actuators into a working position swung away from the top of the main body but by forces resulting from the operation of the rotor blade, i. H. aerodynamic forces and possibly inertial forces. Accordingly, it is sufficient to match the elastic restoring force on the flap of the new rotor blade on its position, shape and dimensions. There is no need to provide an actuator for the flap and also no control for such an actuator.
- a rotor blade for a wind turbine is described.
- the essence of the invention is that at least an aerodynamic element is mounted on the surface of the rotor blade by means of a rotary joint, and that the aerodynamic element is arranged and designed on the surface of the rotor blade, which automatically engages the aerodynamic element alone by the force of a flow at the surface of the rotor blade swings out predetermined flow.
- the aerodynamic element is a passive aeroelastic return flap. Disadvantage is in reality a flutter of the return flap, which can also produce noise and is a lifetime problem.
- JP2004183640 describes a rotor blade for a wind turbine which has an active flap with a return flap arranged on the rotor underside, which increases the buoyancy and thereby the energy efficiency. Furthermore, the breakage of the rotor blade is prevented in strong winds.
- the disadvantage here is the use of movable flaps that firstly have to be very elastic and are maintenance-intensive (experience from the aircraft industry). Furthermore, these moving parts of the flap are very expensive to produce. The icing problem is also present.
- US Pat. No. 7293959B2 / EP16231 1 1 B1 describes a rotor blade consisting of an active elastic (brake) flap (only to reduce lift) and an activation device for a wind turbine, which constitutes a part of a lift regulation device.
- the buoyancy control device can control and advantageously influence the return flow flaps.
- the invention is based on the object, the energy efficiency of aerodynamic / hydrodynamic bodies, in particular a) aircraft by higher wing lift (at least in high-lift situations such as takeoff and landing)
- the invention is also based on the object, if necessary, of simultaneously displaying a safety device on a wing, in which, by reducing the gust susceptibility of the wing, in particular strong wind, by an actively actuated return flap with e.g. to provide slowly increasing braking effect. If necessary, this can also react quickly, so that it can be compensated for individual gusts, even in this way.
- a multifunctional flap / flap which additionally can compensate / dampen different modes of vibration of the wind turbine / rotor / rotor blade by means of an active return flap by means of actuators and / or by means of mass moment of inertia (weights). This can lead to an increased life of components and the wind turbine itself.
- this can proactively, at least partially eliminate snow and ice.
- inventions according to the invention can in particular be retrofitted and in many variants do not require any major Changes to the wind power plant or aircraft.
- the base element may in this case assume a reinforcing function of the return flow flap and / or the wing / rotor blade.
- the device according to the invention in the form of a wind turbine rotor blade with a passive and / or active flap system has the yield improvement at least in the areas A and / or B and / or C and / or D, in the form of one with a Fluid inflatable (inflatable) actuator element, and possibly a flap if necessary very easy to retrofit and / or attachable and / or interchangeable,
- Low-wind, and / or Overspeedschutz and / or vibration-damping system by means of at least one buoyancy-reducing buoyancy element and possibly with closable pressure equalization openings and / or ice and snow removal system, can be used, characterized in that means for increasing the stiffness of the flap and / or means for Wegbegrenzung and that the travel limit limits the opening angle of the flap of ⁇ 90 degrees, preferably ⁇ 75 degrees, very particularly preferably ⁇ 60 degrees, and that at least one actuator element and / or a component thereof can be filled with a fluid (inflatable) is, and this can be folded at least simultaneously in the initial state.
- the object of the invention is, moreover, the advantageous properties of existing techniques (St.DT of a backflow flap on a wing to benefit in order to obtain an overall optimal design due to requirements, especially in wind turbines, the invention.
- the object of the invention is to show a return flow flap on a wing, in which the lift is further increased and / or the minimum speed is reduced, in particular by reducing and / or acting on the end edge separation vortex.
- the combination of an active and passive return valve allows a multifunctional flap / flap system with the possibility to compensate / dampen various vibrations of the wind turbine / rotor / rotor blade, in particular in stable mode and in the overspeed area.
- the devices and methods according to the invention can be used in all aerodynamic and / or hydrodynamic objects, preferably wings or rotors of vehicles, in particular in aircraft and power generation plants.
- an embodiment designated as a backflow flap is suitable for generating a higher lift coefficient CA at higher angles of attack Alpha (17) of the wing than with a conventional wing.
- the return flow flaps (8, 9, 10) according to the invention are suitable for producing an even higher lift coefficient CA by displacement of the end edge vortex (1).
- return flow flaps (8, 9, 10) in active form with an actuator element (22) are suitable for being used as a brake flap even at higher speeds and with a small wing angle of attack Alpha.
- the hitherto known return flaps in aviation have a fixed or flexible flap and a second component to a joint. Furthermore, if necessary stop / Wegbegrenzungsstoff be used by means of cords or bends.
- FIG. 3 shows computational 3D simulation of the return flow.
- FIG. 4 in the variations a, b, c In general, all the variants of the return flow flaps (8,9, 10) according to the invention shown here have the property that they at least partially have an aerodynamic or hydrodynamic body, in particular wings Shift of the flap area delimitation (21) by the return flap (8,9, 1 0) and its demarcation component / s (5) in case of partial and / or complete installation of the return flap (8,9, 1 0) form / takes place, thereby affecting the end edge separation vortices (1) and / or valve separation vortices (2).
- the left edge (position) of the Endkanten-Abspösenwirbels (1) corresponds to the flap area delineation (21).
- the flap area boundary (21) of the inventive return flap (8,9, 10) moves, so to speak, from the area of the return flap (4) to St.d.T. by their spatial extent / effect of the inventive return flap (8,9, 1 0) from left to right, towards the profile end edge (6) or in extreme cases even beyond.
- the inventive backflow flap (8,9, 1 0) due to their additional components, higher relative stiffness and higher damping of vibrations, as the fluid, preferably gas, such as air, the actuator element (22) also Vibration-damping effect.
- This inventive novelty then also results in a higher lift coefficient CA than in a return flow flap (4) according to St.d.T.
- the flap area delineation (21) can take place completely (FIG. 5) as far as or over the profile end edge (6) or only to a part to the left in front of the profile end edge (6) (FIG. 5). This results in a more or less large distance between flap detachment vertebrae (2) and the end edge detachment vertebra (1), which at a ner scrubströmklappe (4) after the St.dT only the thickness of the remindströmklappen material (4).
- this return flow flap (8, 9, 10) can be formed at least from the flap (4) and the delimitation component (5) and a joint (7).
- this can consist of the support surface / connection point (16) and / or the parallelogram or the triangular or the circle segment (area) -shaped demarcation components (5).
- This bearing surface / connection point (16) can also be arranged against the flow direction in front of the return flow flap (FIG. 7). Also, this support surface / connection point (16), as in FIGS. 17 and 18, can consist of a base element (23) projecting beyond the end edge and a fastening means (27).
- the return flap (8,9,10) according to the invention can also be designed from a plurality of these components, as well as a polygon.
- Condition as in the return flow damper after the St.dT is that this is itself mounted movable and / or movable.
- this is represented by the joints (7), preferably made of elastic materials (1 1) such as films or textiles or adhesive tapes, Velcro, preferably textile or fiber-reinforced adhesive tapes.
- textile fiber, glass or aramid fiber joints are very durable and smooth.
- the weather resistance with respect to UV radiation plays an important role here for the lifetime.
- conventional hinges, joints, such as piano bands or ball joints, or other thin-walled elastic materials can be used.
- the materials used here must also be weather-resistant and reasonably light.
- Lightweight materials such as aluminum, plastics, GRP, CFRP, aramid or basalt fiber reinforced plastics are preferably used here, the plastic matrix preferably having a high weathering resistance, such as e.g.
- the outer shape of the return flap / flap can conventionally be in a rectangular shape, but preferably due to the rotational flow (oblique flow on the profile) on the rotor blade of the wind turbine a parallelogram-shaped outer contour (top view in the folded state). This can then preferably still 2 or 3 dimensionally deformed / curved to fit optimally to the profile.
- This curvature can preferably be so strong that the return flap module can be applied to the largest possible areas of the rotor blade (due to the curvature of the profile) (also so that the hose fits well below it, with parallelogram-shaped return flap without additional hose only a slight Warping, so that this fits on the profile), since this slight to moderate warping at speeds from V Ne nn has little aerodynamic influence.
- Control / regulation of the angle of attack is gradually reduced with higher wind speed, to shutdown at V Ma xNormai at usually 25 m / sec).
- a double-walled hose or the combination of the closed parallelogram-shaped return flap and an internal hose can be used, resulting in a redundant and diverse, and thus very high security.
- a magneto-rheological actuator could be combined with a pneumatic emergency actuation system.
- the control of the actuation of actuator elements (22) can be realized via known sensor technology in wired or wireless form.
- an optical camera system is used, which controls all return flow flaps on a rotor blade and possibly simultaneously monitors the load on the blade / rotor blade.
- the return flow flap (4, 8, 9, 10) may be provided by means for limiting the travel (26) eg by ropes, rubber, wires, rods, levers, bands which, nets, springs, walls, foils, folding elements have stops (especially lateral) for a Wegbegrenzung. Also, the travel limit can be made by the actuator itself by the return flap is attached thereto or integrated.
- the actuator element (22) may be significantly smaller than the return flow flap, e.g. to produce a braking effect of the return flap in strong wind.
- the generation of the corresponding forces then takes place via the hydraulic or pneumatic or magneto-rheological pressure in the actuator element (22) and its lever arm translation to the flap, which is exposed to the back pressure of the return flow flap.
- the back pressure can be used as a sensor size for the pressure actuation / control / regulation.
- the contact face / junction (s) (16) of the return flap to the wing are exemplified in Figures 6c and 7 and may be e.g. very long-lasting, in particular also subsequently, also removable again, can be realized safely (re-dissolvable adhesives, for example under the influence of temperature or electromagnetic fields as used, for example, in the automobile industry).
- the contact surface / connection point (s) 16 of the return flow flap can also be regarded as a base element (23), from a contact surface of 5% of the return flap surface, in particular from a support surface of 10% of the return flap surface, especially from a contact surface of 20% of the return flap surface , preferably from a contact surface of 30% of the return flap area.
- the demarcation component may only be temporary
- FIG. 6 the complete displacement of the flap area delimitation (21) by the delimitation component (5) in the closed state at a profile end edge (6) is shown by way of example on a triangular (8) and circular segment-shaped one (9) and parallelogram-shaped (10) return valve.
- the flow and the return flow flaps are at the profile at small angles of attack ⁇ (17) which occur at higher speeds, as is the case with the return flow flaps after the St.d.T. is known.
- the area delineation by the demarcation component (5) as well as all components of the return flow flap (4,8,9,10) can in this case also from fluid-permeable materials with small (micro) or larger openings (macro), such as toothed plate, perforated films, slit or fabric or nonwovens or plates, as well as in shape of gratings and nets.
- fluid-permeable materials with small (micro) or larger openings (macro) such as toothed plate, perforated films, slit or fabric or nonwovens or plates, as well as in shape of gratings and nets.
- the effect achieved by a better / smaller hysteresis of the return flow flaps can also be done by channels due to embossing / punching.
- known diffusion-open materials such as those used in the construction or clothing sector, which are correspondingly weather-resistant and durable, can be used here.
- flutter valves primary valves that open and close by air pressure differences
- flap areas in the longitudinal direction of the wing can also be delimited by known techniques from rudders, if necessary in addition, e.g. with winglets, flow straighteners, flow dividers, turbulators, e.g. Vortex turbulators or spiral turbulators.
- the material for the return valves consists for example of flexible and / or elastic thin materials such as films of metal, in particular with stiffening / embossing, Völb Modell as stiffening and preferably made of plastic, very particularly preferably Kunststoffatffe, very light and stiff fiber-reinforced GRP, CFK, basalt, aramid fiber reinforced plastics.
- stiffening / embossing Völb
- Kunststoffatffe very light and stiff fiber-reinforced GRP, CFK, basalt, aramid fiber reinforced plastics.
- a return flow flap (4, 8, 9, 10) may be configured such that the material thickness is e.g. Wedge-shaped decreases to increase the flexibility in the edge area outside. This can of course also be stepped.
- FIG 7 the exemplary combination of multiple return valves is shown.
- return flow flaps (4) according to the prior art are combined with a parallelogram-shaped return flow flap (10) according to the invention at a profile end edge.
- There is the free combination possibility such as the fastening of the connection point to the wing (16) of the prior art return flow flaps (4) on the parallelogram-shaped passive return flap (10) according to the invention.
- the parallelogram-shaped return flap (10) may include and / or consist of a resilient material (12), e.g. the parallelogram-shaped return flap (10) returns to the closed position by spring force. This can also be done the other way round and the parallelogram-shaped return flow flap (10) is kept closed only by means of negative pressure and turns on again by ventilation by spring force.
- FIG. 8 shows the exemplary combination of a plurality of return flow flaps.
- return flow flaps (4) according to the prior art are combined with a parallelogram-shaped return flow flap (10) according to the invention at a profile end edge.
- the application of a more flexible end edge of the return flow flap (4, 8,9,10) is possible.
- the components of the return flow flap (4, 8,9,10), in particular this end edge slotted, jagged, serrated, wavy or otherwise changed to positively affect the flow (also bionic effects such as the aerodynamically favorable sharkskin structure). This can positively influence the aerodynamics and also the flutter / vibration inclination of the flaps.
- an actuator for actively actuating the return flow flap (10) e.g. represented in the form of a hydraulic or pneumatic cylinder.
- any form of actuator e.g. mechanical (levers, ropes, gears, timing belts) and / or electrical (linear or rotary electric motor, electric magazines, piezo actuators) and / or pneumatic / hydraulic (cylinders, pneumatic-muscles, hoses, balloons, cushions) Find application.
- the lift reducing and / or resistance generating and / or braking variants of the return flow flap can be realized in the form of a brake flap (in particular with smaller angles of attack (17)).
- the advantageous embodiment of the hydraulically or pneumatically or magneto-rheologically actuated actuator element (22) is preferably in the form of a preferably foldable tube (13).
- the passive return flow flap (4, 8, 9, 10) reacts to changes in the angle of incidence of the flows, in particular by gusts which lead to high angles of attack, relatively quickly within a few seconds / second fractions.
- FIGS. 9, 10, 11, 12. Exemplary variants of the active backflow flap (8, 9, 10) are shown in FIGS. 9, 10, 11, 12. These may also be e.g. by fluid / air supply through the fluid flow (back pressure) without external energy, e.g. be activated by means of air inlets in the flow direction. It is equally conceivable that their deactivation by vacuum generating nozzles / tubes such. Venturi nozzle, Prandl tube, Reichman nozzle, Braunschweig nozzle, Pitot tube through the ambient air flow. This has the advantage that no external energy is necessary and therefore only via a fluid
- Speed measurement a relatively simple triggering of the establishment of the return flow flap (8, 9, 10) by means of known techniques. agile is. This could be done with foresight, since the setup time will take a bit more time due to slightly increased dynamic pressure (a hysteresis between setting up and creating seems to make sense). For example, from a fluid overpressure or. Vacuum reservoir supplied actuator this can be done comparatively very quickly.
- Figure 9 shows a prior art reflux valve (4) combined with a demarcation member (5) in the form, e.g. a balloon or hose or cushion (13), which is also actuated as an actuator hydraulically or pneumatically or magneto-rheologically and thereby becomes an active return flap (8,9,10).
- the fluid / gas filling area (14) is shown hatched here.
- a fluid / gas connection (18) to communicate with e.g. Air can be filled e.g. when retrofitted via a hose, e.g. be attached to the profile / wing end edge (6) flow and cost.
- a connection within the wing may serve to carry out the fluid supply.
- the demarcation component can be designed as desired.
- Figure 10 shows a triangular-shaped return flow flap (8) which is e.g. has installed an aforementioned tube (13) as an active actuator.
- FIG. 11 shows a triangular-shaped return flow flap (8), which is e.g. is completely closed in its three-dimensional design to communicate via a fluid / gas connection (18) with e.g. To be filled with air and thus acts as an actuator itself. Also here a corresponding e.g. triangular shaped or folded tube are used. This is a very simple and safe actuator.
- FIG. 12 shows a parallelogram-shaped return flow flap (8) which, for example, in its three-dimensional embodiment, is completely closed. sen is to be filled via a fluid / gas connection (18) with eg air and thereby acts as an actuator itself.
- a fluid / gas connection (18) with eg air and thereby acts as an actuator itself.
- a correspondingly parallelogram-shaped or round or flat-shaped or folded tube (in particular at the ends) can be used.
- a particularly preferred and simple embodiment of the return flow flap (10), in particular active backflow flap (10) according to the invention which is formed only by a flattened and / or folded, in particular closed, tube (13) ,
- this hose (13) is similar to a parallelogram-shaped return flow flap (10).
- this hose is at the same time flap, limiting component (5) and actuator (22). This is particularly advantageous for cost-effective retrofitting z.B
- Wind turbines In a fixed position, this or similar embodiment can also be used as a turbulator / vortex generator. This can, for example, be reduced in its height by the back pressure of the flow at higher speeds and thus can be adapted simply in terms of its intensity to the small vortex generation and thus enable the desired small turbulence generation at lower speeds.
- actuators such as levers and rods, electromagnets, steering gear drives (eg model making) can be used for this purpose.
- the magneto-rheological actuator variant is also interesting here, because if you have attached the electromagnetic field generator on the hose (13) or even integrated, this very simply by applying to the Wing / rotor blade could be retrofitted. It is also conceivable to erect a slightly stiffer outer and larger tube through a smaller actuator tube, so that the outer and larger tube acts as a reflux flap (approximately parallelogram-shaped).
- Hose is composed of 2 curved half-shells and by e.g. Residual stress and thus resilient, the approximate parallelogram-shaped shape assumes as a return flow flap and is brought by negative pressure in a flat, possibly slightly curved shape.
- Figure 14 shows a return flow flap (8,9,10), in particular inventive active return flap (8,9,10), wherein to improve the braking effect, this with a fluid / gas connection (18) between the wing top and wing bottom are connected.
- This has the consequence that the higher pressure from the bottom with the lower pressure of the wing / profile top at least partially compensates and thereby the buoyancy is greatly reduced.
- This effect is known in Schempp-Hirt-brake flaps, which can be mounted on the wing top and bottom and require a complete penetration of the wing.
- a base element (23) fixed to the end edge can preferably be used for articulating the return flow flap (4, 8, 9, 10) with a hinge or elastic hinge (7, 1 1) and for the second to provide a large attachment surface with end edge reinforcement properties.
- the fluid / gas connections (18) to be mounted in the wing could also be marked / affixed.
- this fluid / gas connection (18) from the wing top only in the hollow wing interior lead which is optionally provided with a central opening at another point to the outside, for example, edge bow, to this pressure equalization effect achieve.
- FIG. 15 shows the exemplary arrangements / positions of the passive and / or active return valves (4,8,9,10).
- the arrangement in the region of the profile end edge at the top or bottom (6) to increase the lift and the area of the largest profile thickness (19), especially for use with braking / buoyancy reduction / resistance increase is advantageous.
- the passive and / or active return flap (4,8,9,10) in the wing profile (3) be integrated so that no flap transition (20) in the form of a slope or curve is required (Spaltarm / -ok).
- the flap transition (20) is preferably realized aerodynamically advantageous with an elastic, slightly curved plastic band.
- Hazardous operating conditions can be disruptions or other relevant influences on the system.
- the following exemplary measuring systems for recognizing further exemplary hazard operating states are applicable:
- Camera measuring systems in particular intelligent cameras or webcams
- c) cameras in particular also IR cameras and / or laser measuring systems for surface measurement
- the measuring systems can in particular by fixed and / or movable / moving brackets (eg wing scissors, winglets, wires, strips, profiles) on the wing / rotor (3) and / or on the spinner (rotor nose) and / or mast and / or ground held and / or moved, in particular along the wing / rotor (3).
- the movement can be done by common actuators.
- the velocity measurement of the fluid / air / wind can be directly done e.g. directly or with a small distance (environment) to the wing.
- the measurement is at least one point of the wind power and / or wind farm, most preferably at least 3 points of the wind farm.
- the positions of the return flow flaps can also be determined by means of one of these measuring systems, and from this also hazard states can be derived and warnings can be forwarded therefrom.
- a mechanical visual and / or, wired and / or wireless communication are applicable for this purpose.
- Figure 16 is a preferred embodiment of the active parallelogram return flap (10) on the wing top, to
- Return flap (10) is designed so that it acts as an actuator by this includes a foldable hose, which exactly the contours of the actuator (folded parallelogram-shaped
- FIG. 17 is an active parallelogram return flap (10) on the wing top and bottom with integrated tube (13), to improve the noise reduction with St.dT methods with a noise-reducing base element (25, 23 ) which in this example is V-shaped and pushed onto the end edge of the wing and then attached / attached.
- the attachment can also be done by spring force of the base member (23) and / or possibly friction forces and / or adhesive forces.
- attachment of the base member (23) may be achieved by means of mechanically known releasable and non-releasable means (27), such as e.g. Rivets and screws, and done by means of high-performance Velcro.
- releasable and non-releasable means such as e.g. Rivets and screws
- high-performance Velcro e.g. Rivets and screws
- a folded tube (13) located therein serves as an actuator element (22).
- the fastening means (27) of the base element (23) is in this case one each an upper side and underside surface adhesive bond to the wing (3).
- Figure 18 is an active parallelogram return flow flap (10) on the wing bottom and simplest variant with hose (8) and combined with St.d.T. Return flap (4) on the top of the wing, with noise-reducing base element (25, 23).
- the return flow flap (4) is movably attached to a hinge (1 1, 7).
- the damper may operate as a combined active and passive damper / flap, depending on how and where the return damper is mounted.
- a passive and active triangular reverse flow door (8) (in the actuated position) with vibration damping system based on inertia on the wing top (in one direction only), with V-shaped base elements (23) at the wing noses and wing end edge.
- the aim is in particular to compensate for accelerations caused by wind gusts (storm control) at higher wind speeds from V Ne nn (improvement area C + D) in the plane of the profile (3) perpendicular to the chord.
- a lever (29) is mounted on a joint (7) on the base element (23) of the wing nose and on this lever (29) an inertia element (28) in the form of a weight, preferably an aerodynamically shaped steel. or lead weight, is attached.
- the simple triangular return flow flap (8) shown here is likewise connected to a lever (29), so that over two further levers (29) kinematics are created which equals a movable parallelogram lever system.
- the inertia element (28) (initial position in the neutral position in the direction of the chord) now remains in its spatial position due to the inertia and the lever (29) attached thereto moves towards profile bottom as shown here.
- the lever mechanism (29) Via the lever mechanism (29), the movement of the inertia element (28) is transmitted to the triangular return flow flap (8), so that it moves upwards and thereby takes a braking effect as a brake flap with buoyancy reduction.
- This buoyancy reduction leads to a corresponding counter-movement of the wing (3) which was generated by the gust of wind.
- this principle can also be applied on the other side.
- Figure 20 is a passive and active parallelogram return flap (8) over the Profilendkante protruding with vibration damping system based on the inertia on the wing top (in both directions), with base elements (23) on the wing tabs and wing trailing edge.
- the aim is in particular accelerations by wind gusts (storm control) at higher wind speeds from V Ne nn (improvement range C + D) in the plane of the profile (3) perpendicular to the chord
- a lever (29) is mounted on a joint (7) on the base element (23) of the wing nose and an inertia element (28) in the form of a weight, preferably a weight, on this lever (29) aerodynamically shaped steel or lead weight.
- the parallelogram return flow flap (10) shown here is likewise connected to a lever (29), so that over two further levers (29) a kinematics is created which equals a movable parallelogram lever system.
- Lever mechanism (29) the movement of the inertia element (28) on the parallelogram return flap (10) is transmitted, so that it moves upward and thereby takes a braking effect as a brake flap with buoyancy reduction.
- This buoyancy reduction leads to a corresponding counter-movement of the wing (3) which was generated by the gust of wind. This works with appropriate design of the joints and the parallelogram Return flap (10) also in the opposite direction of the acceleration through the gust of wind.
- inertia element (28) To compensate for the yawing vibrations on the long lever (29) is also an inertia element (28) attached, which remains at a leading acceleration in the direction of the profile nose in the direction of inertia to Profilendkante and thereby the parallelogram return valve (10) (part behind the profile end edge) moves downwards and thus generates more buoyancy and also more profile resistance. This results in a countermovement to the causing gust of wind and a damping of this yawing motion / acceleration.
- this system can also be used individually or only in certain wing areas.
- variants of the return flow flaps according to the invention shown in FIGS. 19 and 20 can, of course, also be combined with a normal rudder / flap (possibly additionally set), so that this is of interest in new wind power plants. Also, the variants can be combined with an active actuator element so that passive and active actuation can take place.
- FIG. 21 shows a passive and active parallelogram return flow flap (10) on a rotatably mounted wing or wing part with a vibration damping system on the basis of the mass inertia on the wing upper side (in one direction only), with base elements (23) at the wing noses and wing end edge.
- the aim is in particular accelerations by wind gusts (storm control) at higher wind speeds from V Ne nn (improvement Area C + D) in the plane of the profile (3) perpendicular to the chord (as in Figure 19) compensate / attenuate.
- an inertia element (28) is attached to the lever (29). If the wing (3) is now moved / accelerated in the direction of the profile top, the inertia element (28) (initial position in the neutral position in the direction of the professional tendon) now retains its spatial position due to the inertia of inertia in its spatial position.
- Zero point of the profile / wing (31) mounted wing or wing part undergoes a moment by the inertia element (28) and thus also remains slightly behind, resulting in a reduction in pitch and thus buoyancy reduction. This counteracts the gust of wind thus dampening / compensating. Due to the bearing in the moment-zero point of the profile / wing (31), the buoyancy forces F A (32) remain unaffected at this point.
- a kind of outer wing can additionally be actively activated / controlled / regulated.
- an end piece of a folded tube is exemplified by the example of the bottom / tail of a soup bag, such as a folded tube, e.g. can be effectively closed by reibschwei Shen, so that it participates permanently in the folding process or Entfaltvorgang under pressure and possibly negative pressure.
- FIG. 23 shows by way of example an end piece of an unfolded hose using the example of the bottom / end piece of a soup bag, as a folded tube can be closed by friction welding, for example, so that the folding process or unfolding process under superimposition and overfeeding If necessary, permanently participate in negative pressure.
- the end piece of a folded tube is exemplified by the example of the bottom / tail of a foldable beverage container with a raised bottom, such as a folded tube, e.g. can be effectively closed by friction welding, so that this permanently participates in the folding process or unfolding process under pressure and possibly negative pressure.
- the tail of a deployed hose is exemplified by the example of the bottom / tail of a foldable beverage container with a buckle bottom, such as a folded hose, e.g. can be effectively closed by friction welding, so that it permanently participates in the folding process or unfolding process under overpressure and possibly underpressure.
- any shaped plug, shaped element can be permanently closed.
- such a plug can be conical or otherwise mechanically designed to take over its permanent sealing function (if necessary, the connecting piece can be attached thereto).
- this plug can be aerodynamically shaped to produce little or much vortex.
- the variants illustrated in FIGS. 1 to 25, in particular 22 to 25, can also be combined with the magneto-rheological actuator type. For this purpose, a magnetic field generating is preferred Element in the immediate vicinity of the hose (13) to act on this.
- the magnetic field generating element is preferably attached / integrated in and / or in the hose (13).
- a fluid flow velocity measurement in the vicinity of the wing can be measured by means of pneumatic and / or electrical pressure probes and / or acceleration sensors (in particular for gusts of wind) mounted at a distance on the outer wing, possibly on a chassis element (23).
- a perforated foil preferably made of synthetic material, has proven itself. This has a thickness of 0.1 to 1 mm and has at least 5, preferably 10 holes / slots per cm 2 , more preferably with at least 20 holes per cm 2 .
- Lightweight stiffeners to reduce the flutter and possibly for the angle limitation can be used here.
- the following property rights and literature are part of this application and can be freely combined with their content:
- the invention relates in particular to a device of a hydraulic and / or pneumatic and / or magneto-rheological actuator (2) without pistons, for generating a 2-dimensional actuator movement (11) and force , preferably rotational movement and a torque with a very simple structure which allows a good force / torque effect.
- the invention is based on the object, the energy efficiency of a hydraulic and / or pneumatic and / or magneto-rheological actuator (2) without piston, in particular by a very compact design and thus application-optimized design and size to produce a limited rotational movement to improve, by a novel design, in the form of, for example, a movable parallelogram as an actuator.
- the invention is also based on the object at the same time to use this inventive actuator as a safety-relevant device by this can be operated at least simply redundant and possibly diversified.
- a three-dimensional movement can also be made possible, as occurs in robot arms or artificial limbs.
- moveable systems may couple in combination with known sensors and control and / or regulation systems and provide industrial benefits SOLUTION
- the object of the invention is to provide an energy-efficient and safety-technically very reliable solution by means of a novel and compact design of a hydraulic and / or pneumatic and / or magneto-rheological actuator.
- the devices and methods according to the invention can be used in all technical devices on land, under water and in the air. Exemplary applications are shown in the claims and in the description.
- This actuator (2) in the folded state consists of at least one surface / wall (5,6,7), preferably from 3 (triangular shape), more preferably 4 (parallelogram-shaped), most preferably from an even number Surfaces / walls (5,6,7), and at least one, with fluid-fillable space (10), in particular foldable actuator (2), and at least one articulated element (9), preferably the foldable tube (10) and / or actuator (2).
- FIG. 1 shows a parallelogram-shaped actuator, which, due to its 90/180 angular mobility, can preferably be used in technical applications.
- FIG. 2 shows that when the fluid-filled space is acted upon, Hose (10) with a fluid, through an opening, not shown here, it can by virtue of its expansion / filling of the actuator (2) due to the pressure in the fluid-filled space / hose (10), by means of erecting movement generated thereby ( 1 1), stand up / unfold.
- the entire actuator (2) is thus, in a possible first position, e.g. collapsed resting position, a flat outer contour similar to one, preferably thin, plate and in a second possible and preferred position, e.g. 90 degrees twisted, in an unfolded working position.
- this actuator (2) and / or the attached device (14) as shown in Figure 2 form e.g. a shape of a polygonal cross-sectional outer contour, e.g. Triangular, quadrangular, parallelogram-shaped, hexagonal, polygonal, scissor-shaped, off, Several such directly juxtaposed actuators form a honeycomb structure of this Patecke.
- This actuator (2) is arranged so that this actuator (2), at least between these two positions, in the form of a rotational movement, at least one, preferably at least 3, most preferably at least 4 articulated elements (9) movable and / or is positionable.
- These articulated members (9) may be formed by known hinges, tapes, cloths, adhesives, tubing, films, other elastic materials, or the actuator itself (eg, by 3D printing).
- a preferred embodiment has the same number of gelenkformigen elements (9), as the number of surfaces / walls (6,7,8), most preferably the gelenkformigen elements (9) of a component, preferably a tubular member (10 ), educated.
- the device according to the invention has a straight or curved and / or reinforced surface / wall (6, 7, 8), such as, for example, by means of macro, micro, nano-structuring, for example by means of arched structures made of metals or plastics , and / or reinforcements, such as by means of fiber reinforced plastics, such as GRP or CFRP and / or nanoparticle reinforcements and / or surfaces such as nano-carbon fibers.
- the front ends of the actuator (2) and / or hose and / or sheath (10) are closed by means of a camber-bottom and / or folding structure and / or flattened and thus fluid-tight and / or preferably in the folded state of the actuator ( 2) flat.
- the fluid supply can be designed specifically in each individual case and thus configured from any direction of the actuator. Particularly preferred is a immovable design from the direction of the body and / or through it.
- the fluid supply can be carried by an actuator through or attached to this inside or outside.
- a workpiece (4) which is moved with a basic movement (12) in the -X direction of the coordinate system (5) and with one produced by the actuator (2) Aligning movement (13) in - Y direction of the coordinate system (5) in this direction realigned, without the basic movement (12), on the support plate (3), for example, comes to a stop on a roller or treadmill.
- This can thus be used, for example, in a sorting station or workpiece switch, for example in packaging systems or the like.
- Such lifting devices may be lifting tables, lifting platforms and the like, for example, as they come to the application even in lorries or ramps in the cargo reporting.
- Such devices may be attached to height adjustment desks, also e.g. be used in single or multiple scissors design for subsequent cultivation.
- Such adjustment devices can be operated at a fairly low pressure by means of a slow upward movement by e.g. a low-cost and quiet overpressure diaphragm pump can be actuated.
- the downward movement can be done by way of example by weight, by venting the actuator by means of a manual valve.
- this can also be done by switching to negative pressure at a positive / negative pressure pump.
- the rotational movement (1 1) and force generation via compressed air positive and / or negative pressure, preferably positive and / or negative pressure accumulator (25,26) eg compressed air / CO2 cartridge, take place, such as for security systems, such as the emergency opening of escape doors, emergency closing of ventilation fire dampers.
- the force generated acts in proportion to the effective Aktuatorf laugh and the pneumatic and / or hydraulic fluid pressure in the direction of rotational movement (1 1) and thus over one or more surfaces / walls (6,7 , 8) and / or devices / lever arms (14) exerts a torque.
- This force / torque can be linear and non-linear nature.
- a connecting rod or more preferably a crosshead and a connecting rod can be used.
- FIGs 5 and 6 a safety-relevant device in the form of a device (19) of a rack for flood protection with an attached thereto actuator (2) is shown.
- This illustrated device is e.g. Partially erected with the actuator (2) and then completely finished by hand.
- a multi-walled arrangement with at least one actuator (2), in particular for increased safety, in particular for use in highly reliable and / or safety-relevant systems, and / or a vibration-damping function.
- the / the Gelenk / e (9) by the actuator (2) itself is formed, and that this actuator (2) in the form of at least one at least 2-dimensional radially deformable and / or elastic hose / Sleeve (10), more preferably at least 2 nested tubes / Sheaths (10) is formed, wherein the surface / n / Wänd / e (6,7,8) between and / or can be arranged outside and / or inside.
- Elastic means here 3-dimensionally deformable.
- the already mentioned conventional hinges can also be used.
- FIGS. 7 and 8 show, by way of example, an emergency tunnel and rescue system (22), preferably for vehicle drive tunnels or other buildings for evacuating persons (23).
- the double parallelogram rescue tunnel (22) is kept stationary in the folded / folded state, fastened to the tunnel wall, until it is to be used in the event of an application. For example, People or conventional fire alarm systems then trigger the rescue system.
- the rescue tunnel (22) made of fire-resistant material can also be ventilated directly and possibly vented to the outside through pressure relief valves.
- the rescue tunnel (22) can be reused by bringing it back into the resting / waiting position, eg by means of negative pressure, via any actuator, preferably the actuator according to the invention.
- FIG. 9 shows, by way of example, a double-arranged actuator (2) with the likewise double-separated and fluid-filled spaces / tubes (10) for generating an erecting / unfolding rotational movement of the actuator comprising 180 degrees of angle
- the two actuators (2) are connected to each other via articulated elements (9). Both actuators (2) are fastened to the bottom surface (6) on the base body (1) and are supplied with fluid via at least one bore via pipelines (27). Via these pipes (27), the supply of the fluid via at least one way valve or control valve (24) is controlled or regulated and the fluid from the overpressure (25) and vacuum reservoir (26) fed.
- FIG. 10 shows an example of a double arrangement
- the two actuators are connected to each other via articulated elements (9).
- Both actuators (2) are attached to the bottom surface (6) on the base body (1) and are supplied in each case via at least 1 bore via pipes (27) with fluid. Via these pipelines, the supply of the fluid is controlled or regulated via at least one directional control valve (24) and the fluid is supplied by the overpressure (25) and vacuum reservoir (26).
- a compressor (30) which can ideally generate positive and negative pressure.
- a control or regulation system (29) the directional control valve (24) can be controlled or regulated by means of additional travel sensors or force sensors (not shown).
- FIG. 11 shows, by way of example, as the main body (1) an aerofoil with a very simple embodiment according to the invention in a scissor-type design.
- the scissors shape is formed by the bottom surface (6) and the side surface (7) of the actuator (2) and a fluid-fillable space / tube (10) therebetween.
- This arrangement enables an active and / or passive use of the flap / side surface (7) for the advantageous aerodynamic influence of the flow on the wing, for the improvement of energy efficiency and / or storm safety.
- FIG. 12 shows by way of example as base body (1) an end edge of a wing with a likewise very simple design according to the invention in a triangle-shaped design.
- the triangular shape is formed by the bottom surface (6) and the side surfaces (7) of the actuator (2) and a fluid fillable space / tube (10) therebetween.
- This arrangement differs from the arrangement in FIG. 11 in that the two right-hand side surfaces (7) simultaneously also form a travel limit of the actuator (2) or the left side surface (7).
- Figure 12 shows a fastening means (31) for attachment of the bottom surface (6) of the actuator (2) at the end edge of the wing.
- the path limitation can also be formed only by ropes, belts, nets or the like.
- This arrangement also allows an active and / or passive use of the flap / side surface (7) for advantageous aerodynamic influence of the flow on the wing, to improve energy efficiency and / or storm safety. In particular, such systems can also be retrofitted.
- the devices according to the invention shown in FIGS. 1 to 12 can be used to move the two-dimensional actuator movement (11) in order to move and / or exert force and / or open and / or close and / or position and / or straightening and / or aligning and / or shifting and / or lifting and / or Weichenstellend of attached and / or non-fastened components (4),
- a possible first position e.g. collapsed rest position, preferably Druckarm position, occupies and
- the 2-dimensional actuator movement in particular a rotational movement (1 1), with about 90 degrees, more preferably up to about 180 degrees, the at least 1 - dimensional movement and / or clamping of components (4) such as technical devices of any kind cause.
- a method which the arrangement of several such actuators (2) to a 2 or 3-dimensional movement (1 1) of the overall actuator (2) and the components to be moved (4) and / or devices (19) provides, such as in artificial hands, robotic arms or artificial limbs / prostheses for humans and animals.
- a method for producing the parallelogram-shaped actuator (2) according to the invention is disclosed, which can be produced in the following steps: a) Creation of the surfaces / walls (6, 7, 8) to corresponding dimensions
- the actuator (2) can be checked for leaks with overpressure and underpressure and optionally subsequently filled with a process fluid / element, such as the magneto-rheological fluid / polymer
- a double / triple walling coating the previously manufactured actuator (2) with an outer shell (10) with fluid supply passage with the already mentioned methods and / or shrinking of shrink film / tube (10) and optionally attachment additional surfaces / walls (6,7,8) with the mentioned methods
- the actuator (2) can be checked for leaks with overpressure and underpressure and, if necessary, filled according to the following with a process fluid / element, such as the magnetorheological fluid / polymer
- the operating principle is based on the parallelogram (polygonal) actuator and / or tube actuator.
- the actuator principle is shown below.
- the actuator is shown in 3 positions zero degrees, 45 degrees and 90 degrees position.
- the complete finger in 3 positions is shown below.
- the MF actuator may also be located exactly on the inside of the finger joint so that the main hinge is arranged on the outside.
- the joint may also be e.g. be made of one or more ball heads, movably designed plastic sheet hinges to realize a high number of movement cycles and life of the actuator.
- Parts of the MF actuator or the whole, in particular composite materials made of aluminum and plastic or metal-coated plastics or Texti Reinforced plastics can be made here. Correspondingly locally controlled or regulated valves allow the over- and / or vacuum supply of the respective MF actuator.
- the arrangement and use of the finger (bone) elements as a positive / negative pressure reservoir / reservoir seems particularly favorable. These reservoirs are then supplied via an inside or attached or outside lying pipe, preferably flexible hose further with positive / negative pressure.
- the finger bone) elements can serve only as a static element and / or pipeline.
- the actuator may consist of a polygon, which forms a parallelogram in principle, but for example partially includes arcuate elements, which may serve as joints and / or elastic hinges.
- the MF actuator can only be used in its static structure of its parallelogram shape to be controlled by a pneumatic or hydraulic cylinder via a lever.
- the aforementioned embodiment can also be used as an alternative to the MF actuator with appropriate sealing of the piston rod relative to the MF actuator, z.b. to
- UV radiation resistant materials and coatings can be used.
- an actuator may also be used to close luggage compartments in aircraft from luggage compartments of cars, and the like. serve.
- the actuator can also be used with magnetorheological fluids or. Polymer / electrorheological fluids are combined.
- a simple rotary element with strong rotatable magnets is applicable to actuate the fluids and / or materials and / or the flaps.
- FIG. 1 is a diagrammatic representation of FIG. 1:
- FIG. 2 is a diagrammatic representation of FIG. 1
- Model wing a with detached flow; b: ditto, with flap Figure 3:
- FIG. 4 is a diagrammatic representation of FIG. 4
- FIG. 5 is a diagrammatic representation of FIG. 5
- FIG. 6 is a diagrammatic representation of FIG. 6
- FIG. 7 Wing profile with closed parallelogram-shaped return flow flap (8) with complete displacement of the flap area delineation (21) FIG. 7:
- FIG. 8 is a diagrammatic representation of FIG. 8
- FIG. 9 is a diagrammatic representation of FIG. 9
- FIG. 10 is a diagrammatic representation of FIG. 10
- Triangular-shaped return flap (8) which is e.g. a hose (13) has been installed as an active actuator.
- FIG. 1 1 is a diagrammatic representation of Triangular-shaped return flap (8) which is e.g. a hose (13) has been installed as an active actuator.
- Triangular-shaped return flow flap (8) which in its three-dimensional design is completely closed in order to pass through a fluid / gas Bond (18) to be filled with, for example, air Figure 12:
- Parallelogram-shaped return flap (8) which is e.g. is completely closed in its three-dimensional configuration to communicate via a fluid / gas connection (18) with e.g. To be filled with air
- FIG. 13 is a diagrammatic representation of FIG. 13
- active return flap (10) which is formed only by a flattened closed tube
- FIG. 14 is a diagrammatic representation of FIG. 14
- Active return flap (8,9,10) to improve the braking effect with a fluid / gas connection (18) between the wing top and wing bottom
- FIG. 15 is a diagrammatic representation of FIG. 15
- FIG. 16 is a diagrammatic representation of FIG. 16
- FIG. 17 is a diagrammatic representation of FIG. 17
- FIG. 18 is a diagrammatic representation of FIG. 18
- FIG. 20 is a diagrammatic representation of FIG. 20.
- Passive and active parallelogram backflow flap (8) protruding beyond the profile end edge with vibration damping system based on the inertia on the top of the wing (in both directions), with base elements (23)
- FIG. 21 is a diagrammatic representation of FIG. 21.
- FIG. 22 is a diagrammatic representation of FIG. 22.
- FIG. 23 is a diagrammatic representation of FIG. 23.
- FIG. 24 End piece of a folded tube on the example of the bottom / tail of a foldable beverage container with arched base
- FIG. 25 is a diagrammatic representation of FIG. 25.
- FIG. 1 is a diagrammatic representation of FIG. 1:
- FIG. 2 is a diagrammatic representation of FIG. 1
- FIG. 29 is a diagrammatic representation of FIG. 29.
- FIG. 30 is a diagrammatic representation of FIG. 30.
- FIG. 32 is a diagrammatic representation of FIG. 32.
- FIG. 33 is a diagrammatic representation of FIG. 33.
- FIG. 34 An actuator (2) according to the invention with an attached safety / rescue tunnel device in the unfolded state in the end / working position
- FIG. 36 is a diagrammatic representation of FIG. 36.
- FIG. 39 is a diagrammatic representation of FIG. 39.
- FIG. 40 is a diagrammatic representation of FIG. 40.
- FIG. 41 is a diagrammatic representation of FIG. 41.
- FIG. 43 is a diagrammatic representation of FIG. 43.
- FIG. 44 Model of the parallelogram according to the invention in combination with a pneumatic cylinder (without piston rod) slightly bent for 2 phalanges
- Parallelogram according to the invention in combination with a pneumatic cylinder (with 2 levers and a piston rod) for 2 phalanges flexed with control details
- FIG. 46 Model of a pneumatic retractable landing gear according to the invention FIG. 46:
- FIG. 47 is a diagrammatic representation of FIG. 47.
- FIG. 48 is a diagrammatic representation of FIG. 48.
- Triangular-shaped return flap (Flap / buoyancy element) 9. Arc-shaped return flap (Flap / buoyancy element)
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Abstract
Description
Claims
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
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DE202015000665.5U DE202015000665U1 (de) | 2015-01-24 | 2015-01-24 | Vorrichtung eines Sicherheitssystems und/oder Ressourcen-/Energieeffizienz-Verbesserungs - Systems zur Stömungsbeeinflussung eines Aero- oder Hydrodynamischen Körpers (3), nach dem Prinzip einer Rückstromklappe (4) |
DE102015113374.1A DE102015113374B4 (de) | 2014-08-18 | 2015-08-13 | Anordnung zum erfassen einer spannung, batteriestapel sowie verfahren zum bereitstellen einer elektrischen konnektivität zu einem batteriestapel eines kraftfahrzeugantriebssystems |
DE102015114617.7A DE102015114617A1 (de) | 2015-01-24 | 2015-09-01 | Künstliche Hand mit MF-Aktuator |
PCT/DE2016/100029 WO2016116102A1 (de) | 2015-01-24 | 2016-01-24 | Multifunktionales flap als rueckstromklappe |
Publications (1)
Publication Number | Publication Date |
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EP3247902A1 true EP3247902A1 (de) | 2017-11-29 |
Family
ID=53547414
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP16723243.8A Withdrawn EP3247902A1 (de) | 2015-01-24 | 2016-01-24 | Multifunktionales flap als rueckstromklappe |
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US (1) | US20180171975A1 (de) |
EP (1) | EP3247902A1 (de) |
CN (1) | CN107810140A (de) |
DE (1) | DE202015000665U1 (de) |
WO (1) | WO2016116102A1 (de) |
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CN114320736A (zh) * | 2022-01-04 | 2022-04-12 | 上海电气风电集团股份有限公司 | 风电叶片及其叶片动态失速控制方法 |
CN114506442B (zh) * | 2022-01-28 | 2024-07-05 | 中国商用飞机有限责任公司 | 带有扰流辅助装置的机翼及包括其的飞行装置 |
CN117365825A (zh) * | 2022-06-30 | 2024-01-09 | 江苏金风科技有限公司 | 叶片以及风力发电机组 |
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CN116698932B (zh) * | 2023-08-01 | 2023-09-26 | 四川圣诺油气工程技术服务有限公司 | 一种用于带压管道的微生物膜监测传感器 |
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US2616509A (en) * | 1946-11-29 | 1952-11-04 | Thomas Wilfred | Pneumatic airfoil |
SE331952B (de) * | 1967-12-22 | 1971-01-18 | Ingelman Sundberg A | |
GB2157774A (en) * | 1984-04-26 | 1985-10-30 | Lawson Tancred Sons & Company | Wind turbine blades |
JP2004183640A (ja) | 2002-12-04 | 2004-07-02 | Tokiwa Kogyo Kk | フラップを具備する風車ブレード |
DK200300670A (da) * | 2003-05-05 | 2004-11-06 | Lm Glasfiber As | Vindmölleving med opdriftsregulerende organer |
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GB0902685D0 (en) * | 2009-02-18 | 2009-04-01 | Airbus Uk Ltd | Aircraft wing assembly |
US8425190B2 (en) * | 2009-10-26 | 2013-04-23 | United Ship Design And Development Center | Pressure relief device |
EP2336555A1 (de) * | 2009-12-14 | 2011-06-22 | Lm Glasfiber A/S | Magnetische Aktivklappe |
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DE102010041111A1 (de) * | 2010-09-21 | 2012-03-22 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Rotorblatt mit integrierter passiver Oberflächenklappe |
US8516899B2 (en) * | 2010-10-06 | 2013-08-27 | Siemens Energy, Inc. | System for remote monitoring of aerodynamic flow conditions |
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EP2535269B1 (de) * | 2011-06-17 | 2013-10-16 | EUROCOPTER DEUTSCHLAND GmbH | Rotorblatt mit aktiver Klappe |
US8491262B2 (en) * | 2011-10-27 | 2013-07-23 | General Electric Company | Method for shut down of a wind turbine having rotor blades with fail-safe air brakes |
DE102012000431A1 (de) | 2012-01-12 | 2013-07-18 | Smart Blade Gmbh | Rotorblatt |
ES2609240T3 (es) * | 2012-04-04 | 2017-04-19 | Siemens Aktiengesellschaft | Disposición de aleta flexible para una pala de rotor de turbina eólica |
US20150050154A1 (en) * | 2013-05-23 | 2015-02-19 | Kristian R. DIXON | Airfoil trailing edge apparatus for noise reduction |
WO2014207015A1 (en) * | 2013-06-27 | 2014-12-31 | Siemens Aktiengesellschaft | Rotor blade with noise reduction means |
EP2908001B1 (de) * | 2014-02-12 | 2016-09-21 | Siemens Aktiengesellschaft | Mittel zur Verminderung der Belastung eines Windturbinenrotorblatts |
-
2015
- 2015-01-24 DE DE202015000665.5U patent/DE202015000665U1/de not_active Expired - Lifetime
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2016
- 2016-01-24 US US15/545,830 patent/US20180171975A1/en not_active Abandoned
- 2016-01-24 CN CN201680017450.9A patent/CN107810140A/zh active Pending
- 2016-01-24 EP EP16723243.8A patent/EP3247902A1/de not_active Withdrawn
- 2016-01-24 WO PCT/DE2016/100029 patent/WO2016116102A1/de active Application Filing
Also Published As
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CN107810140A (zh) | 2018-03-16 |
DE202015000665U1 (de) | 2015-06-26 |
WO2016116102A1 (de) | 2016-07-28 |
US20180171975A1 (en) | 2018-06-21 |
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