WO2011141444A2 - Erfindung betreffend rotorblätter, insbesondere für windkraftanlagen - Google Patents
Erfindung betreffend rotorblätter, insbesondere für windkraftanlagen Download PDFInfo
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- WO2011141444A2 WO2011141444A2 PCT/EP2011/057466 EP2011057466W WO2011141444A2 WO 2011141444 A2 WO2011141444 A2 WO 2011141444A2 EP 2011057466 W EP2011057466 W EP 2011057466W WO 2011141444 A2 WO2011141444 A2 WO 2011141444A2
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- rotor blade
- blade according
- edge
- coupling
- trailing edge
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Classifications
-
- 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
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0658—Arrangements for fixing wind-engaging parts to a hub
-
- 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
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
-
- 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
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0675—Rotors characterised by their construction elements of the blades
-
- 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
- F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor
- F03D3/06—Rotors
- F03D3/061—Rotors characterised by their aerodynamic shape, e.g. aerofoil profiles
-
- 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
-
- 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
- F03D7/024—Adjusting aerodynamic properties of the blades of individual blades
-
- 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
- F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
- F03D9/20—Wind motors characterised by the driven apparatus
- F03D9/25—Wind motors characterised by the driven apparatus the apparatus being an electrical generator
-
- 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
- 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
-
- 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
- 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
-
- 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
- F05B2260/00—Function
- F05B2260/50—Kinematic linkage, i.e. transmission of position
- F05B2260/502—Kinematic linkage, i.e. transmission of position involving springs
-
- 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
- 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
- Y02E10/74—Wind turbines with rotation axis perpendicular to the wind direction
Definitions
- the present invention is concerned with rotor blades, in particular for use in wind turbines (WKA) and in particular the general investigation of the fluid structure interaction of a passive concept
- FSI fluid-structure interaction
- Wind turbines are constantly changing loads. These load changes result from passing through the atmospheric boundary layer, fluctuation of wind speed due to turbulence and gust, tower pre-tower or rotor blade oscillations. These effects cause a change in the angle of attack under which the profile is impinged and, consequently, a change in pressure along the profile. Under these operating conditions, the components of a wind turbine are claimed so that the life of 20 years of parts of the plant is not reached. With regard to the development of measures with which such load fluctuations can be controlled, care must be taken that these components themselves achieve the required reliability and the system complexity remains manageable.
- the object of the invention is therefore to provide a profile of rotor blades, in particular for use in wind turbines, which avoids the disadvantages of the prior art.
- the present invention pursues the approach pressure variations on a profile, resulting from a change in the angle of attack to dampen by a passive adjustment of the profile curvature.
- the goal is to increase lift, i. keep the loads on the profile constant.
- the invention inherent in the concept consists of a flap profile (as profiling of the rotor blades), which achieves this reduction by a curvature change.
- the curvature change is initiated by the flow itself.
- the change in the curvature is made possible by an elastically and / or rotatably mounted flap system consisting of leading edge and trailing edge flap. Both flaps are kinematically coupled with each other.
- the kinematics for rigid coupling can be performed differently. In the simplest case, it consists of a crank mechanism, but there are conceivable transmission of any kind which produce the same kinematics.
- the crank mechanism is shown schematically in FIG. 1.
- the firmly connected to one flap permanently connected horns of length L1 and L2 are connected to the connecting rod L. Core principle of the arrangement is that in each case a rowing horn upwards (below) and the other one at the top (top), so one door rotates clockwise and the other door turns counterclockwise at the same time.
- gear ratios (L1 / L2) from 2 to 3 have been found to be optimal and sufficient.
- the choice of gear ratio is related to the choice of spring stiffness.
- the gear ratio determines the measure of the increase or decrease of the buoyancy with increasing or decreasing angle of attack (slope of the function that describes the lift coefficient over angle of attack).
- the force resulting from the pressure change controls the deflection of the leading edge flap and at the same time the trailing edge flap. Thus, an increase or decrease is possible.
- Trailing edge flap twisted.
- the deflections of the elastic trailing edge or the trailing edge flap are greater than that of the elastic front edge or the leading edge flap by the ratio L1 / L2.
- the difference in pressure between the upper and lower sides in the front profile area caused by the flow around the profile is much greater than in the rear area.
- the pressure difference is dependent on the profile shape at a constant angle of attack. This fact determines the lengths of the elastic edges or flaps. It has been proven that the length of the leading edge flap should be 15% to 20% of the tread depth, the length of the trailing edge flap should be 20% to 30% of the tread depth.
- Wind turbines are constantly changing loads due to their operating conditions.
- fluctuating bending stresses at the root of the rotor blades result from the fluctuating aerodynamic loads.
- These alternating voltages reduce the fatigue strength of the wings.
- Due to the higher peripheral speeds, the largest forces are generated on the rotor blade in the outer area of the wing.
- the loads on the rotor blade can thus be controlled by changing the lift coefficient.
- the lift coefficient depends, among other things, on the profile curvature.
- the curvature can be changed by the use of flaps and leads to a parallel shift of the c / - _ curve, as shown in Figure 2.6.
- the invention makes use of this change in the angle of incidence for a passive curvature change.
- An increase in the angle of attack results in a higher suction tip in the nose area of the profile.
- This pressure increase deflects a leading edge flap installed on the profile, as shown in Figure 2.7.
- a spring mounted on the crank of the leading elastic edge or leading edge flap allows adjustment of the working range of the system by superimposing the biasing force of the spring on the flow forces acting on the leading edge.
- the ratio of the preload force to the angle of rotation can be defined by the choice of spring stiffness.
- the choice of spring stiffness is related to the choice of gear ratios.
- the spring stiffness determines the measure of the increase or decrease of the buoyancy with increasing or decreasing angle of attack (slope of the function, which describes the lift coefficient over the angle of attack).
- the preload force or the preload torque depends on the selected design point. The higher the preload moment, the higher the lift at the design point.
- a damper is attached to the crank of the rear edge to stabilize the system.
- the rotation can be limited to certain angles, whereby the working range of the system can also be limited.
- working area is meant in which area the profile behaves elastically or dense or buckled.
- the profile behaves like a rigid profile. That the buoyancy increases or decreases in a further increase or decrease in the angle of attack according to the then set profile contour.
- Fig. 2.7b Concept of the flap profile with return spring, damping and stop.
- kinematic coupling in any known to those skilled form, possible types of kinematic coupling are any type of transmissions such as joints, spur gear, bevel gear, planetary gear, worm gear, friction gear, helical, wedge gear, chain drives, toothed belt, flat belt, V-belt transmissions, crank mechanisms, toggle mechanism, lever mechanism.
- torsion spring As a spring, the following elements are in principle suitable: torsion spring, tension spring, compression spring, disc spring, pneumatic actuators.
- tension spring As a spring, the following elements are in principle suitable: torsion spring, tension spring, compression spring, disc spring, pneumatic actuators.
- compression spring As a spring, the following elements are in principle suitable: torsion spring, tension spring, compression spring, disc spring, pneumatic actuators.
- spring elements with non-linear spring characteristic is in question.
- dampers oil dampers, air dampers, viscous dampers.
- the structural behavior is described using an equation of motion.
- the motion equation can be derived with the substitute model shown in Figure 2.8.
- Fig. 2.8 Flap model with one degree of freedom
- the ordinate of the right-angled coordinate system lies on the chord, the origin is at half the profile depth (c / 2).
- the rotation angle g describes the deflection of the leading edge flap, the rotation angle b the deflection of the
- the restoring force on the leading edge flap results from the torsional stiffness k Y and the deflection y.
- the damping d ß _ is taken into account at the trailing edge flap on the angular velocity ß-point.
- the coupling of the two flaps takes place via the transmission ratio
- the degree of freedom ß is a function of ⁇ , which means linear motion
- an integrated compliant structure is also anticipated.
- a material for rubber, latex, fiber-plastic composites and / or intelligent materials in question for. SMA or piezo materials.
- the coupling then takes place through an integrated force flow through the structure from front to back.
- For stabilization then continue to use damping elements as described above.
- the use of active dampers and stiffness elements is possible.
- the coupling can also be actively adjusted using the principles / gearing types listed above.
- Flap angle trailing edge
- the operating method of the rotor profile remains passively coupled. Only the type of coupling or damping or stiffness is variable. After setting the new parameters, the coupling between the front edge and the rear edge of the profile is again passive.
- the panel method according to Hess and Smith (1966) is used. Due to the time-dependent discretization of the wake, unsteady vortex shedding can be taken into account. The structure is mapped using a discrete substitute model and described using a linear equation of motion.
- Panel methods are based on the Laplace equation. This is derived below with the help of the mass conservation theorem and considering the potential theory. Thus, the flow is considered incompressible and frictionless.
- each punk can be assigned a velocity vector. Mathematically speaking, this is a vector field. If this vectorial flow field has a potential, one speaks of Potenr strömuiag. According to the definition of the potential, the flow field in each point is vortex-free, i. the rotation disappears:
- This equation is a linear differential equation. This means their solution can tion from the Super Posi 'of several individual solutions are constructed in the Strömungsmeehanik which takes place from the superposition of Eiementarstmmungen. To the ivory aromas
- the ProMutMeroniasg is derived from an explanation of sources wd vortex "micde ftsies Angewöma? Esrafctek In this case, first, the ProSloberface's discrete section is an ect etectic; Pimek, These will become »the source « «Bd Vortex
- the PSEEISI is delimited by the points a: i and x 2 d is ge
- Plane Source Distribution and f cercinae and the x-axis are reduced by the angle. The representation is done in .cannon coordinates, so that the panel is parallel to the x-axis.
- x - (l-cas (2.18) where ß is calculated as n + 1 fast oM-sateik, the k irds xiii are counted beginning at the K mrks fe, you run along the d-Prailunterseite entla g to ⁇ fed «dcsn. re un e dfe top back With reference to the x-axis a Jettes panel el.oe Gradient defined by Make! &.
- 2.2ft ⁇ j is because index for the panel, ⁇ , ⁇ , ® * ⁇ "nd B * s are the Maamen the Eirf" ssköefimsn- tea. The hoAgestsilters. Ind. N., And fef the normal and tangeirna.
- the second boundary dingung that must be eriiilk * is the tioschs Afef-issfeedsii mf. It gives the finite value of the hermantas a finite value: must have. Dm Sorösmmg. the Upper Universe of the Hymnet Came reaches ata first and learns n are sufficient, it satisfies the conditional wg with the tangential components
- the compression factor asr depends on the weight. Nads Bemoultl applies.
- Ce ed budget. (2G5) proposes to do justice to this vortex by a panel on the back to re-eSJ to do the co-ordination of the ohsofs.
- the swirl strength is supposed to be constant over the panel s.
- b the irbel-strong two more occur: ösibekärmte on * the length of the pasel and its jtasteSuag M x-axis.
- the vortex displaced in zone fc counts to free vortex in the next step, and a new vortex beats out as the trailing edge. In every night vision, the number of vertebrae increases in the night
- the Gesdwndägkekspoieofta! can be determined by integrating the Gesd-i indlgkeiisfe! the along ⁇ ST Stmn ⁇ ie earth, as it m.
- Image 2.5 is dauß scsenmsch, ⁇ iti ground the kfeemsdschen constraint st the Pr & surface-che as already mentioned a Stronili- me s sRanurafcieits from the önesdliäien oint for storage leads. There. only differences of the
- MATLAB addresses specific functions and their computational efficiency.
- the verification for the stationary panel procedure is done with Xfoil.
- the Wagner function is used as a reference.
- the coupling of the structure and flow model is discussed and the solution method used is described.
- the MATLAB code is shown below.
- the panel method (Hess-Smith panel method) was realized in MATLAB with several functions, the so-called function files. These contain the algorithm for the individual operations.
- Figure 3.1 shows the associated schedule.
- the analysis of the flow starts after the suction angle and the profile geometry as arguments to steady.
- the geometry must be stored in a so-called structure artay (data field). It is a data type that allows scalars, vectors and strings to be stored in a contiguous variable in the workspace. In this way, information about profile geometry is bundled into a single variable. This is called af and asked the following structure:
- Zureichst K must nml - ak8s and angle E £ of .Pasels be ersauft. To do so with steady.is the public function distr.ss. As an insurgent, Fsofilkoonisif will be handed over.
- $ i 2.193 JBBSS to be paid attention to the choice of the Aksstarsgess.
- the etafache Affasföngerss offers now the possibility the angles for each position of the pasage korskt d & rajsielkii
- the Vfesbsrefch besefe kr. on - ⁇ 8 ⁇ " ⁇ ( ⁇ ).
- the operator first tests the: properties of the matrix l and then decides which linen strategy best suits g. Since the matrix l is fully square d and if there is no symmetry the Gad-E & Bm & tlon is used (Schweifet (20093 ), the command is heard more dirantly in the maxims and kurer;
- si; -i is the mu vector as defined in Gkidk g 2,43.
- the solution should be lineaen. the direct best! the bwerses of the Mains l by means of the fiction is ⁇ T) be waived.
- the Ifecfekesis operaror is often more favorable for the time of change, especially in large matrices for such betts.
- the mercury field emlasg was found at the determined Qtselles and vortex strength.
- the Profilofeer dache determined, earth. From this, the ünieriudkdos cp_dist.m the Ii fcYeg * eilunj> (2.46: ⁇ , The integration of the pressure ettlarsg the Prafifebertlädie provides the Res Aierende force, which acts on the Proil., Your iatompo eBS seakrecfet to Amtmm Bg results in the "Germanedebshel ert. c s. Anigxnisd der De & rafcfoa der Kb mHpimk"
- the furfcem s t e dy ⁇ rs may be c,. cL, c ,,. cac d, S i ng, Ar: in the A-.
- f contains the Frough suffer Stract-Array MC; contains dd DistatslerLSii of the profile (Ps- -Stract-Array
- the msiatiönae bill requires the definition of initial values. Make 2.55 and 2.65 s for each calculation values from previous time intervals necessary. At the moment £ ⁇ , these starting values must be available. "Hiera” is the Fonkdkm init.rs. You eredmei unsetz with the help of steady from the argtime eri afQ nd alpha eme
- Frofilgesmetne Struct- ⁇ rrsy af contains the new Proilgeomeirc StracE-Array; rs ,. Ct, EisHusskoeffiaisintefi of the Nachlaufe Matrx
- oils in the x- and m s-plows are calculated in the ⁇ Bterhmfcöos el.
- the function red, s creates the new pm-fiordordlords mk from the i ⁇ & p m ⁇ ..-> are ersrft the asels and ö müpaste for the new Pmligeometrle i flcoefi:.. calculated ⁇ , the input liusskoeffizietaeii the .Pasels, he two guess "called skrioise" lei s relative to the stationary reader unchanged modeling.
- FTE LAB uses ms solution of the system, an iterative, Erfahe., Ais Anfaäigswen 's feed the source and Wirbekriifkeri the previous Zeitschrkfs used, we the irts If this is the case, the solution can be checked for convergence. * If sk Werr s -xi f lag ⁇ ⁇ ---- 1 is returned, then the remdons ro ess erfclgyekh, otherwise the calculation will be aborted ,
- the solid line shows the determinant of the course for a floor-level VOT 200, which compares with a pass with 20 pasels in the line Csrridhjnmkrfert's line ⁇ "It is to be recognized that the area at the leading edge, dk, the ssisgspir e and the Statiptmkt at too low AAS & ⁇ g incorrect 'abgebiids *: will.
- Plan «ad becomes with $> (s) bexefchiifit, where s ilr the disiezosouite time stA srnd over
- deSmeri £.
- the liveliness of the wind gives it da m;
- ⁇ is the resfe wiiz Isr. wxd over 2..56 if twv
- the time i is. m the fenoden-d animal T Service.
- the German & e iime gives the quasi-high-speed start-up .
- "Ieder. Through the Efofiussd.es aehlaiifs isrdsr ⁇ felholz the festadönlrsn Beiracfiiiig ssmysrsAob n.
- the ⁇ btftde stelk sieve ... as v ⁇ m voters (I92S) b envy, vemöge «.
- the city-standard model gives the same results, since in the present article there are different levels of oil, which lie in the field of oil, the aeroeiastici Sinridatlonesi mfc Bueck on äm rsche. In this case the rotation and the direction of the satellite are taken into account by the wing of the wing.
- FIG. 4.1 show the elephants of thickening. "As expected, the medmeraag of the limbs is expected to increase, as shown in Table 4,1, to Heacfee.”
- Figure 4.2 shows the flow of damping.
- the flap deflections become smaller and the reduction of the amplitudes decreases, see Table 4.2.
- the diminishing constant increases, there is a phase shift of the lift coefficient c. L of the elastic profile relative to the rigid profile to observe.
- the flap extension at the trailing edge is shown for dg- 5 ⁇ (dot-dashed line).
- the outputs are also out of phase but delayed. It can be assumed that due to the deceleration the circulation of the profile will be so influenced that the maximum lift coefficient will be reached prematurely with increasing damping. However, this connection can not be conclusively clarified in the context of this work.
- Figure 4.3 shows the c ; - - ⁇ Gradients with variation of the translation.
- a momentum of impact is again seen, as is the case with rigidity.
- the flap folds in Table 4.3 that the profile curves too much.
- a phase shift can be seen. This is due to the fact that the damping force is dependent on the flap speed, which in turn depends on the oversampling ratio. If one compares this relationship with the results from Fig. 4.2b, the different phase shift with the higher flap deflections can be explained with increasing translation.
- the moment of inertia assumed in the previous simulations is based on the. Weight of a long flap. This consists of a Glasmaschineoberftumblee with polystyrene core. The moments of inertia of the leading and trailing edges are:
- Figure 4.5 shows the flows of buoyancy when the flap leaves are varied.
- the length of the trailing edge flap is always kept constant.
- Table 4.5 shows that the change of the rear edge cap. less influence on the ample-plumed denier than the v-neck edge flap. in the case of a 30% rotor wrap, the reduction is nearly the same for all trailing edge flapii.
- profile curvature was varied on a four-digit NACA profile.
- the profile thickness is 10% and the curvature reserve is 50% of the tread depth.
- the results are shown in Figure 4.7.
- the associated reductions and flap deflections are given in Table 4.7. It can be seen »that the influence of profile curvature is of secondary importance.
- V ! t! ib is the wind speed at hub height, ⁇ the angle of rotation of the wing, r the radial position on the flights! and SSQ the roughness length.
- Trailing edge flap The profile curvature plays no role in reducing the loads. Here, the same results are achieved with different profile curvatures. In contrast, with increasing profile thickness, the amplitudes of the loads can be reduced, while the flap deflections remain the same.
- Embodiment 1 The kinematics for rigid coupling can be performed differently. In the simplest case, it consists of a crank mechanism.
- the crank mechanism is shown schematically in Fig. 1 and Fig. 2.7b.
- the rudder horns of length L1 and L2, firmly connected to one flap each, are connected to the connecting rod L. With one helm horn pointing up (down) and the other down (up) so one flap rotates clockwise and the other flap rotates counterclockwise at the same time.
- the gear ratios (L1 / L2) has a value of 2 to 3.
- the length of the leading edge flap is 15% to 20% of the tread depth and the length of the trailing edge flap is 20% to 30% of the tread depth.
- a spring is attached to the crank of the leading edge flap. This allows adjustment of the working range of the system by superimposing the biasing force of the spring on the flow forces acting on the leading edge.
- the ratio of the preload force to the angle of rotation is defined by the choice of spring stiffness.
- a damper is attached to the crank of the trailing edge which stabilizes the system.
- the kinematic coupling is designed as a crank mechanism with a connecting rod
- the gear ratio is between 2 and 3
- the length of the leading edge flap is between 15% and 20%, that of the trailing edge flap between 20% and 30 %, on the crank of the trailing edge flap
- a damper is mounted and the rotation of the flaps is limited by means of dampers.
- the length of the crank mechanism is variable. This change is made manually or actively by regulation and control.
- the length of the rudder horn is changeable at the trailing edge. This change is made manually or actively by regulation and control.
- the length of the rudder horn at the front edge is changeable. This change is made manually or actively by regulation and control.
- the length of the rudder horn at the leading edge, the length of the rudder horn at the trailing edge and the length of the crank mechanism are variable. These changes are made manually or actively by regulation and control.
- the rudder horns and / or the crank mechanism are designed as a gear, especially as linear drives.
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- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluid Mechanics (AREA)
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Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201180023801.4A CN102933840B (zh) | 2010-05-10 | 2011-05-10 | 涉及转子叶片特别是风力涡轮发电机的转子叶片的发明 |
EP11718116.4A EP2569535B1 (de) | 2010-05-10 | 2011-05-10 | Erfindung betreffend rotorblätter, insbesondere für windkraftanlagen |
ES11718116.4T ES2601778T3 (es) | 2010-05-10 | 2011-05-10 | Invención relativa a palas de rotor, particularmente para aerogeneradores |
DK11718116.4T DK2569535T3 (en) | 2010-05-10 | 2011-05-10 | Invention relating to the blade, especially for wind projects |
US13/697,056 US9353728B2 (en) | 2010-05-10 | 2011-05-10 | Invention relating to rotor blades, in particular for wind power installations |
Applications Claiming Priority (2)
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EP10162448 | 2010-05-10 | ||
EP10162448.4 | 2010-05-10 |
Publications (2)
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WO2011141444A2 true WO2011141444A2 (de) | 2011-11-17 |
WO2011141444A3 WO2011141444A3 (de) | 2012-05-03 |
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ID=44626175
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/EP2011/057466 WO2011141444A2 (de) | 2010-05-10 | 2011-05-10 | Erfindung betreffend rotorblätter, insbesondere für windkraftanlagen |
Country Status (6)
Country | Link |
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US (1) | US9353728B2 (de) |
EP (1) | EP2569535B1 (de) |
CN (1) | CN102933840B (de) |
DK (1) | DK2569535T3 (de) |
ES (1) | ES2601778T3 (de) |
WO (1) | WO2011141444A2 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102996367A (zh) * | 2012-11-29 | 2013-03-27 | 南京航空航天大学 | 一种风力机叶片可动小翼装置 |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103291539B (zh) * | 2013-05-09 | 2015-05-13 | 哈尔滨工业大学 | 一种叶片摆翼的设计方法和一种带叶片摆翼的h型立轴风力机 |
FR3019237B1 (fr) * | 2014-03-31 | 2019-03-29 | Universite D'aix-Marseille | Rotor de type savonius |
CN106202782B (zh) * | 2016-07-20 | 2019-11-08 | 昆明理工大学 | 一种水轮机导叶主动旋转输入功率的数值计算方法 |
CN106894948A (zh) * | 2017-03-07 | 2017-06-27 | 上海理工大学 | 基于仿生学的垂直轴风力机 |
CN110005640B (zh) * | 2018-01-04 | 2020-07-03 | 中国航发商用航空发动机有限责任公司 | 一种风扇叶片、压气机及航空发动机 |
ES2825025T3 (es) * | 2018-01-29 | 2021-05-14 | Siemens Gamesa Renewable Energy As | Conjunto de borde de salida |
CN109737004A (zh) * | 2019-01-17 | 2019-05-10 | 沈阳航空航天大学 | 通过调整叶片弯度提高水平轴风力机叶片启动性能的方法 |
CN112231836B (zh) * | 2020-10-21 | 2022-08-02 | 华中科技大学 | 一种基于遗传算法和数值仿真的翼型优化方法 |
CN113931807B (zh) * | 2021-08-25 | 2023-04-21 | 华北电力大学 | 一种风电叶片运行攻角测量方法 |
CN114818020A (zh) * | 2022-03-24 | 2022-07-29 | 北京航空航天大学 | 基于势流理论的阵风预测方法和装置 |
Family Cites Families (11)
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US2055928A (en) * | 1934-10-08 | 1936-09-29 | Russell R Hays | Rotating blade means for aircraft |
US2622686A (en) | 1942-07-21 | 1952-12-23 | Chevreau Rene Louis Pier Marie | Wind motor |
US2716460A (en) * | 1952-02-28 | 1955-08-30 | Raymond A Young | Blade and control mechanism for helicopters |
US3332383A (en) * | 1965-06-24 | 1967-07-25 | Wright Edward Morris | Variable camber airfoil |
FR2456211A1 (fr) * | 1979-05-10 | 1980-12-05 | Trudon Des Ormes Amaury | Pales d'helice articulees a courbures variables asservies a leur variation de pas |
US4383801A (en) * | 1981-03-02 | 1983-05-17 | Pryor Dale H | Wind turbine with adjustable air foils |
US5181678A (en) * | 1991-02-04 | 1993-01-26 | Flex Foil Technology, Inc. | Flexible tailored elastic airfoil section |
US5367970A (en) * | 1993-09-27 | 1994-11-29 | The United States Of America As Represented By The Secretary Of The Navy | Controllable camber fin |
US7918646B2 (en) * | 2007-01-22 | 2011-04-05 | Lonestar Inventions LLP | High efficiency turbine with variable attack angle foils |
ES2324002B1 (es) * | 2007-06-22 | 2010-05-13 | GAMESA INNOVATION & TECHNOLOGY, S.L. | Pala de aerogenerador con alerones deflectables. |
CN101225794B (zh) * | 2008-01-25 | 2010-06-23 | 严强 | 垂直轴风力发电机的叶片结构、风轮及发电机装置 |
-
2011
- 2011-05-10 CN CN201180023801.4A patent/CN102933840B/zh not_active Expired - Fee Related
- 2011-05-10 DK DK11718116.4T patent/DK2569535T3/en active
- 2011-05-10 US US13/697,056 patent/US9353728B2/en not_active Expired - Fee Related
- 2011-05-10 WO PCT/EP2011/057466 patent/WO2011141444A2/de active Application Filing
- 2011-05-10 EP EP11718116.4A patent/EP2569535B1/de not_active Not-in-force
- 2011-05-10 ES ES11718116.4T patent/ES2601778T3/es active Active
Non-Patent Citations (2)
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ABBOT, VON DOENHOFF, ANZAHL AN PROFILKOORDINATEN ZURÜCKZUFÜHREN, 1959 |
VON DRELA, JAHREN AM MASSACHUSETTS INSTITUTE OF TECHNOLOGY, 1989 |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102996367A (zh) * | 2012-11-29 | 2013-03-27 | 南京航空航天大学 | 一种风力机叶片可动小翼装置 |
Also Published As
Publication number | Publication date |
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EP2569535A2 (de) | 2013-03-20 |
CN102933840B (zh) | 2016-08-03 |
DK2569535T3 (en) | 2016-12-05 |
CN102933840A (zh) | 2013-02-13 |
WO2011141444A3 (de) | 2012-05-03 |
EP2569535B1 (de) | 2016-10-05 |
US20130119673A1 (en) | 2013-05-16 |
ES2601778T3 (es) | 2017-02-16 |
US9353728B2 (en) | 2016-05-31 |
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