WO2011013105A2 - Aérogénérateur doté d'un rotor à écoulement interne libre - Google Patents

Aérogénérateur doté d'un rotor à écoulement interne libre Download PDF

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Publication number
WO2011013105A2
WO2011013105A2 PCT/IB2010/053481 IB2010053481W WO2011013105A2 WO 2011013105 A2 WO2011013105 A2 WO 2011013105A2 IB 2010053481 W IB2010053481 W IB 2010053481W WO 2011013105 A2 WO2011013105 A2 WO 2011013105A2
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WO
WIPO (PCT)
Prior art keywords
rotor
blades
airfoil
way
rotation
Prior art date
Application number
PCT/IB2010/053481
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English (en)
Other versions
WO2011013105A3 (fr
Inventor
Mario Rosario Chiarelli
Original Assignee
Massai, Andrea
Bolognesi, Paolo
Russo, Giovanni
Atzeni, Davide
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Massai, Andrea, Bolognesi, Paolo, Russo, Giovanni, Atzeni, Davide filed Critical Massai, Andrea
Priority to EP10754561A priority Critical patent/EP2459871A2/fr
Publication of WO2011013105A2 publication Critical patent/WO2011013105A2/fr
Publication of WO2011013105A3 publication Critical patent/WO2011013105A3/fr

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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
    • 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
    • F03D3/00—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor 
    • F03D3/005—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  the axis being vertical
    • 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 
    • F03D3/04—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels
    • F03D3/0436—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels for shielding one side of the rotor
    • F03D3/0472—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels for shielding one side of the rotor the shield orientation being adaptable to the wind motor
    • F03D3/049—Wind motors with rotation axis substantially perpendicular to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels for shielding one side of the rotor the shield orientation being adaptable to the wind motor with converging inlets, i.e. the shield intercepting an area greater than the effective rotor area
    • 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
    • F03D3/062—Rotors characterised by their construction elements
    • F03D3/066—Rotors characterised by their construction elements the wind engaging parts being movable relative to the rotor
    • F03D3/067—Cyclic movements
    • F03D3/068—Cyclic movements mechanically controlled by the rotor structure
    • 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 
    • F03D7/06—Controlling wind motors  the wind motors having rotation axis substantially perpendicular to the air flow entering the rotor
    • 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
    • F05B2240/301—Cross-section characteristics
    • 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
    • F05B2250/00—Geometry
    • F05B2250/20—Geometry three-dimensional
    • F05B2250/23—Geometry three-dimensional prismatic
    • F05B2250/232—Geometry three-dimensional prismatic conical
    • 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
    • F05B2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05B2260/72—Adjusting of angle of incidence or attack of rotating blades by turning around an axis parallel to the rotor centre line
    • 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
    • F05B2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05B2260/79—Bearing, support or actuation arrangements therefor
    • 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 refers to the technical field relative to the machines suitable for the exploitation of the energy of a fluid mass in movement (for example, air or water) .
  • the invention concerns a high efficiency aero-generator with vertical-axis rotor.
  • aero-generators are widely used to produce electric energy thanks to the transformation of the mechanical energy of the rotor set in movement by the air flow that collides with it.
  • a transfer of energy of the flow that causes the rotation of the blades is obtained which, rotating, produce mechanical energy.
  • the rotation of the blades can then be transmitted to appropriate electrical generators or to mechanical devices.
  • the efficiency of an aero-generator is defined as the relation between the instantaneous mechanical power available on the axis of the rotor and the instantaneous power of the fluid mass that collides with the rotor itself and depends on the configuration of the rotor itself.
  • a first example of aero-generator concerns the horizontal-axis aero-generators, which have a maximum efficiency of about 45%-50%.
  • the supporting elements which are typically constituted by straight or twisted blades, present problems of structural stability that increase when the dimensions of the blades is greater and that influence the performance.
  • the pitch of the blades is in fact reduced to avoid dynamic overstress to the detriment of the productivity of the machine itself.
  • the pressure gradients that are produced on the blade along its extension, and in particular in the area of the free end are the cause of a non negligible noise.
  • a complex airfoil like in the case airfoil used in the turbo-machinery sector, for example, not only has a very variable thickness along the chord and therefore with the upper surface and the lower surface of very different shapes between them, but it is also normally characterized by a very curved skeleton (the middle line between upper surface and lower surface) .
  • the airfoil is univocally defined by different parameters, among which the polynomial equations that define the upper surface and the lower surface, together with the polynomial equation that defines the skeleton of the airfoil.
  • such equations can also be described in a particularly efficient manner by means of SPLINE, BSPLINE o NURBS functions.
  • some basic characterizing elements are the mathematical function that represents the progress, along the chord, of the radius of curvature of the skeleton (middle radius of curvature R) , the mathematical function that defines the skeleton itself and the mathematical function that defines the percentage thickness (t/c) of the airfoil along the chord.
  • a profile can therefore be considered as of low curvature when, for example, of the said parameters the middle radius of curvature R exceeds some threshold values or the maximum value of the percentage thickness t/c remains below some threshold values.
  • airfoils of low curvature can be considered as the profiles wherein, basically, the following are verified: a) the ratio between the coordinate Ymax of the skeleton and the chord C is below 0.2; b) the percentage thickness (t/c) is uniform or, along the chord, always remains below 0.15; c) the function that represents the middle radius of curvature R of the skeleton presents a variation interval with an absolute minimum point above 0.35 and, at the same time, an absolute maximum point above 2.2 (these last values to be intended as referred to a unitary chord) .
  • a wind turbine 10 is described realized through a plurality of plates 12 that, in pairs, comprise among them a rotor system 14.
  • the rotor system comprises a circular roof 16 and a circular base 18 between which a plurality of blades result comprised arranged in a circumferential manner so as to realize a free internal volume within which the air flow can flow freely without encountering obstacles.
  • the rotor system 14 is connected in a rotatable manner between two consecutive plates 12 through a rotatory pivot that connects the roof
  • the rotor system 14 can freely rotate with respect to the two plates within which it results comprised, leaving the said internal volume free from obstacles for the circulating flow.
  • a plurality of stators 30 are then arranged in a fixed position in a circumferential manner with respect to the plate 12 so as to appropriately shield the blades from wind flows that would obstacle the rotation of the rotor
  • the configuration of the pre-chosen blades does not present a specific airfoil but is substantially constituted by a bent flat plate of a subtle and uniform thickness.
  • the curvature is low and the pitch angle improper .
  • the rotor (I' ) comprises an upper bulkhead (3) and a lower bulkhead (2) connected between them through a plurality of blades (1) .
  • the blades have also a predetermined airfoil and are further distanced among them to allow the passage (entry/exit) through the chamber (20) of a circulating flow, for example air.
  • the blades are also arranged according to a predetermined blade pitch angle so that, when in use, when the flow collides with the chamber (20), the flow can go into the chamber (20) from a side undergoing a first deviation and go out from the opposite side further undergoing a second deviation in such a way as to generate lift on a greater number of blades and cause a rotation of the rotor (I' ) .
  • the blades have an airfoil with high curvature and are arranged according to a blade pitch angle comprised between a range that varies from 30° to 60°, preferably between 37° and 52°.
  • the skeleton (80) of the airfoil must be such as to result that can be represented through a polynomial function at least of the sixth degree wherein, further, the ratio between the maximum coordinate Ymax of the skeleton and the Chord (Ymax/Corda) is comprised within a range that varies from 0.2 to 0.5.
  • R of the skeleton along the chord must vary within an interval comprised between a minimum of 0.25 and a maximum of 2.2.
  • the mathematical function (90), or curve, representing the percentage thickness (t/c) of the airfoil must foresee an absolute maximum (only maximum value of the curve) variable within a range between 0.15 and 0.35 and arranged in a zone substantially comprised between the 10% and the 20% of the chord.
  • the present rotor can further comprise a flow recovery device (200) hinged around the axis (7) in such a way as to convey into the chamber (20) the flow going into the device (200) .
  • the conveyance device can comprise an entry section (201) and an exit section (202) , of a smaller area with respect to the entry section, in such a way that the air flow conveyed along the said recovery device increases its speed along the path towards the rotor.
  • the recovery device can comprise two hinge arms (204) to connect the device to the rotor (1') through two shafts (7', 7") and at least a tab (203), preferably two opposed tabs, connected to the said arms in the hinge point and that extend posteriorly to the exit section so as to be able to self-orientate on the basis of the direction of the flow that collides with it.
  • the recovery device can comprise a system of servo-controlled orientation in case the posterior tabs are not present.
  • the exit section (202) can have a shape that substantially traces the external profile of the rotor (I' ) in such a way that the device is placed close to the rotor itself.
  • the recovery device (200) can also comprise two or more internal channels (210', 210'') into which the fluid is directed towards the exit section (202), the said channels being configured in such a way as to direct the fluid in a substantially tangential manner to the airfoil of the blades that face each channel.
  • the exit section can substantially trace half of the external profile of the rotor.
  • adjustment means can be included to change the blade pitch angle of the blades.
  • the said adjustment means can comprise according to a possible solution:
  • a circular crown (410) at least partially dented and concentric to the blades;
  • Two gear wheels (400) preferably diametrically opposed, each one connected in the pivoting point of a blade in such a way by which the rotation of the said wheel (400) rigidly drags in rotation the blade, changing its blade pitch angle.
  • the wheels (400) are meshed with the circular crown (410) in such a way that the rotation of the crown (410), through the setting in rotation of the control wheels (401), causes the rotation of the blades through the wheels (400).
  • all the blades are reciprocally connected through the leading edge by hinged arms (501) in such a way that the rotation of the wheels (400) is rigidly transmitted to all the remaining blades, causing an equivalent change of blade pitch angle.
  • the adjustment means can comprise a pair of irreversible actuators (500) fixed to the ends of two blades diametrically opposed, together with the connection system of all the blades with hinged arms (501) .
  • the bulkheads (2, 3) can be configured in such a way that their surface that faces the internal chamber (20) of the rotor is shaped, instead of flat, so as to progressively restrict the internal volume of the chamber, producing a pressure reduction and an increase of the speed of the flow inside the rotor.
  • FIG. 1 and figure 2 show respectively a view of the whole of an aero-generator provided with a rotor 1' in accordance with the invention
  • FIG. 3 shows a plan section of the rotor 1' so as to highlight the path of the flow going into and going out of the rotor;
  • FIG. 4 shows, for clarity purposes, an axonometric view of the rotor of figure 3;
  • FIG. 12 Figures from 5 to 12 show graphics on the basis of the position along the chord wherein the airfoil of the invention is represented, the relative skeleton, the polynomial equations that represent upper surface and lower surface, together with a progress (always adimensionalized on the basis of the chord) of the radius of curvature of the skeleton and, last, again the skeleton and the percentage thickness (t/c) with the relative polynomial equations;
  • Figure 15 shows a known formula for the calculation of the radius of curvature of a flat line that defines a generic geometrical airfoil
  • FIG. 25 to 27 Figures from 25 to 27 show a flow recovery device in accordance with the present invention.
  • Figure 28 shows a stator
  • Figure 29 shows an airfoil, as described, having mobile surfaces
  • Figures 30 and 31 show systems to render the blade pitch angle variable.
  • the blades 1 of the rotor 1' being part of the aero-generator are described.
  • the blades result interposed between an upper bulkhead 3 and a lower bulkhead 2 and directly connected to them by one of their ends in such a way as to realize an internal chamber 20, for example cylindrical, (see also figure 3 or figure 4) .
  • a vertical supporting base 12 realized by a tower 12 of a tubular or pylon structure, supports the rotor group 1' through a rotatable shaft V assembled idle on the tower through a support provided with bearings 8. In such a manner, the rotor 1' is free to rotate with respect to the tower around the said axis 7.
  • the supporting base 12 also supports, in a rotatable manner, a dented wheel 6.
  • the dented wheel 6 is arranged in axis with the rotor 1' through a connection to the rotatable shaft 7' in such a way that the rotation of the rotor 1' is transmitted to the wheel through the shaft.
  • a spacer 5 is arranged between wheel and rotor.
  • the wheel 6 engages with gear wheels belonging to a power generator group 9 arranged on a support 10 rigidly fixed to the tower 12. In such a manner, the rotation of the rotor 1' is transmitted to the generator 9 through the wheel 6, causing the production of current.
  • a control and electrical efficiency board 13 and a base 14 complete the structure.
  • FIG. 2 A second possible embodiment is described in figure 2 and is identical to the preceding one except for some aspects that will be described below.
  • some mass-balance weights 50 are comprised and arranged in correspondence of the upper and lower bulkhead so as to better balance the rotation of the rotor 1' .
  • the tower includes an internal axial housing so as to hold a power generator group 109 arranged in axis with the rotor 1'.
  • a joint 16 is included that connects the axis of the rotor 1' to the axis of the power generator group 109.
  • a braking support 15 is included for a brake 17 and a Planetary gearbox 18.
  • the preferred configuration of the invention comprises an internal volume 20 free from any structural element.
  • the rotation shaft 7' is connected directly to the lower bulkhead in such a way as to avoid that it extends inside the chamber 20.
  • Such a solution is naturally advantageous since the circulating air flow in the chamber does not encounter obstacles that might reduce the energy.
  • the generation of the torque is obtained thanks to the action of the lift forces that develop on the blades.
  • Such lift forces are correlated to the deviation of the fluid current, and therefore to the variation of the quantity of motion of the flow that is verified both outside and inside the rotor itself.
  • the fluid current impacts against the front blades of the rotor 1' (that is the blades that are at that moment opposite the flow) and undergoes a first deviation during the entry into the internal free volume. Inside the volume 20 the flow proceeds freely until it impacts against the back blades, thus undergoing a second deviation in exit.
  • the deviation of the overall fluid current is therefore correlated to the lift forces that are generated on the supporting blades of the rotor and therefore on the basis of the form of the airfoil and of the blade pitch angle.
  • figure 5 shows a base airfoil with high curvature used in accordance with the invention.
  • the said airfoil has been found to be surprisingly a high efficiency airfoil for the case in question.
  • the graphic shows an interpolation of the upper surface points 60 whose coordinates have been adimensionalized with respect to the length of the chord C and an interpolation of the upper surface points 70 always with coordinates adimensionalized with respect to the chord.
  • the sequence of circular points 80 provides the geometrical description of the skeleton calculated as the average of the coordinates Y of the upper surface and the lower surface.
  • the equations that represent, through a polynomial of the sixth degree, the said curves of the upper surface 60 and the lower surface 70, are shown.
  • Figure 6 shows the curve, with relative equation of polynomial of the sixth degree, relative to the said skeleton 80 together with the graphic 100 that represents the evolution of the radius of curvature R of the said skeleton, from now onwards called, for simplicity purposes, middle radius of curvature R (100) .
  • the figure in question highlights how the curve representing the middle radius of curvature 100 (always adimensionalized with respect to the chord of the airfoil) is comprised within a range of values, being the minimum equal to 0.3 in the front zone of the airfoil (about 15% of the chord) and the maximum equal to 1.2 in the back zone of the airfoil (about 80% of the chord) .
  • the same graphic also shows the evolution of the percentage thickness 90 (t/c) along the chord, which presents a maximum of 0.2, while the ratio between the Ymax of the skeleton and the chord is of about 0.3.
  • the graphics that follow show percentage variations (-25%, +50% e +75%) in order to obtain, starting from the optimal airfoil, other airfoils with high curvature with high aerodynamic features.
  • figures 7 and 8 show a range of variation of the airfoil with high curvature with a reduction of the quote Y of the points of the upper surface and of the lower surface of 25%.
  • Figure 7 therefore shows an Ymax, adimensionalized with respect to the chord, of about 0.2.
  • Figure 8 shows an evolution of the middle radius of curvature R of the curve of the skeleton interpolated whose minimum has a value of about 0.3 (front part of the airfoil at about the 10% of the chord) and a maximum of about 1.4 (back zone of the airfoil at about 80% of the chord) .
  • the same figure shows a ratio (t/c) with absolute maximum of about 0.15.
  • figures 9 and 10 show an increase of the 50% in the coordinates Y relative to the points representing upper surface and lower surface with an Ymax, adimensionalized with respect to the chord, of about 0.45.
  • the middle radius of curvature of the skeleton has a minimum of about 0.3 in the central zone of the airfoil and a maximum of about 1.65 in the front zone.
  • the ratio (t/c) presents an absolute maximum of about 0.3.
  • figures 11 and 12 show a variation of the airfoil with an increase of the 75% in the coordinates Y relative to the points representing upper surface and lower surface.
  • the adimensionalized Ymax is of 0.5
  • the middle radius of curvature presents a minimum of 0.25 in the central zone of the airfoil and a maximum of 2,20 in the front zone.
  • the ratio (t/c) presents an absolute maximum of about 0.35.
  • the middle radius of curvature R has been calculated according to the formula written for easy reading in figure 15.
  • the formula well known in the background art, indicates that the reciprocal of the radius of curvature (1/R) is equal to the ratio between a numerator and a denominator.
  • the numerator includes the second derivative of the function v(x), which mathematically describes the line of which to calculate the radius of curvature (in this case v(x) is the equation of the skeleton) preceded by the minus sign (to obtain positive values of R)
  • the denominator includes the sum of the coefficient one with the squared first derivative of the said function and all the denominator raised to three halves.
  • a skeleton (80) that can be represented through a polynomial function at least of the sixth degree wherein, further, the ratio between the maximum coordinate Ymax of the skeleton and the Chord (Ymax/Corda) is comprised within a range variable from 0.2 to 0.5;
  • t/c a percentage thickness (t/c) of the airfoil whose representing function comprises an absolute maximum variable within a range between 0.15 and 0.35 and arranged in a zone substantially comprised between the 10% and the 20% of the chord.
  • the middle radius of curvature R presents two maximum points, not necessarily absolute, respectively at about the 30% of the chord and at about the 80% of the chord.
  • Figure 13 and figure 14 show, always in accordance with the invention, a range of blade pitch angles for the assembly of the said airfoils with high curvature and that further optimize the efficiency of the rotor.
  • Figures 16 and 17 show a solution of aero-generator, as previously described, with the blades of the rotor arranged in such a way as to form a cylindrical internal chamber 20.
  • Figures 21 and 22 show a solution with a spherical rotor 1'
  • the subsequent figures 23 and 24 show a solution with semispheric or semielliptical rotor 1' .
  • a flow recovery device 200 arranged on the rotor 1' in such a way as to optimize the conveyance of the air flow inside the chamber 20, reducing the lateral leaks due to, for example, the rotation itself of the rotor.
  • Figure 25 schematizes the recovery device that comprises an entry section 201 of the air and an exit section 202 for the air. Always figure 25 shows the two back tabs 203 that allow a self-adjustment of the device 200 on the basis of the direction of the wind.
  • the shaft 7' finishes on the lower bulkhead on the opposite side to that of incidence of the blades, while a further shaft 1' ' (both of rotational axis 7) results emerging from the upper bulkhead always on the opposite side to that of incidence of the blades.
  • the conveyor can thus be hinged to the said shafts through two arms 204 in such a way as to result rotatable as well with respect to the axis 7.
  • Figure 26 shows a top view that clearly highlights how the recovery device reduces its transversal area from the entry section 201 towards the exit section 202 so as to capture a greater quantity of flow and convey it into the chamber 20. Moreover, figure 26 highlights how the exit section 202 substantially follows the external profile of the rotor 1' in such a way as to be able to be arranged close to the blades.
  • the entry section is able to convey a great quantity of air flow which, above all, by means of the tapering of section, increases its speed.
  • the recovery device can further comprise inside channels 210 that substantially direct the flow according to such an angle by which the flow surrounds the blades positioned in front of the rotor so that these result mainly supporting.
  • Figure 27 in fact shows how the channel 210' conveys the flow according to such an entry direction (see arrow in figure) such that the flow surrounds in a substantially tangential manner the airfoil of the blades that face the said channel. Otherwise, the said blades would be braking since the flow would impact orthogonally to the airfoil itself.
  • Always figure 27 shows the entry of the flow that is conveyed along the blades into the channel 210' ' .
  • the conveyance device 200 can be in all the configurations arranged at a distance of 0.05 up to 1.5 times the radius of the rotor 1' from the external profile of the rotor.
  • Figure 28 shows, as an alternative to the conveyor, a simple stator, self-adjustable as well on the basis of the direction of the wind.
  • the stator comprises a directional wing 300, arranged superiorly, and a front shielding part 301 and a back conveyance part 302 in such a way as to shield the blades that would be braking on the basis of the direction of the wind.
  • the stator is assembled in a rotatable manner on the rotor 1' around the axis 7.
  • Figure 29 shows, as per all the configurations of airfoil described, the profile can include mobile parts in order to further vary the form.
  • the airfoil of the blades can be fixed or modifiable in the front and/or back part in the same way as what has been realized for aircraft wings.
  • the curvature can be varied through an adjustment system, inserted in the two end bulkheads that activates the eventual front (slat) and back (flap) mobile surfaces.
  • figure 30 and figure 31 show systems for the variation of the blade pitch angle.
  • figure 30 shows a rotation obtainable through the use of gear wheels 400 and of a partially dented crown 410
  • figure 31 shows the use of two actuators 500.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Sustainable Development (AREA)
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  • Combustion & Propulsion (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Wind Motors (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Lubricants (AREA)

Abstract

La présente invention concerne un rotor innovant (1’) pour un aérogénérateur comprenant une cloison supérieure (3), une cloison inférieure (2) et un axe de rotation (7) autour duquel le rotor peut tourner. Plusieurs pales (1) sont raccordées par l’une de leurs extrémités à la cloison supérieure (3) et par leur extrémité opposée à la cloison inférieure (2) de manière à former une chambre interne (20), pouvant tourner autour dudit axe de rotation (7). Les pales, présentant un plan de sustentation prédéterminé, sont en outre distancées les unes des autres afin de permettre le passage à travers la chambre (20) d'un écoulement, de préférence un écoulement d'air, et sont disposées selon un certain angle de pas de pale de sorte que, lors de l'utilisation, lorsque l'écoulement entre en collision avec la chambre (20), celui-ci puisse pénétrer dans la chambre (20) depuis un côté en subissant une première déviation et sortir du côté opposé en subissant en outre une seconde déviation, générant ainsi une portance sur les pales avec lesquelles il entre en collision et provoquant par conséquent une rotation du rotor (1'). Conformément à l'invention, les pales présentent un plan de sustentation présentant une courbure importante et sont en outre disposées selon un angle d’incidence compris dans une plage variable allant de 30° à 60°, de préférence de 37° à 52°, de manière à accroître les forces de portance.
PCT/IB2010/053481 2009-07-31 2010-07-30 Aérogénérateur doté d'un rotor à écoulement interne libre WO2011013105A2 (fr)

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Application Number Priority Date Filing Date Title
EP10754561A EP2459871A2 (fr) 2009-07-31 2010-07-30 Aérogénérateur doté d'un rotor à écoulement interne libre

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITPI2009A000096A IT1397762B1 (it) 2009-07-31 2009-07-31 Aerogeneratore con rotore a flusso interno libero
ITPI2009A000096 2009-07-31

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WO2011013105A2 true WO2011013105A2 (fr) 2011-02-03
WO2011013105A3 WO2011013105A3 (fr) 2011-04-07

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WO (1) WO2011013105A2 (fr)

Cited By (12)

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Publication number Priority date Publication date Assignee Title
FR2971303A1 (fr) * 2011-02-05 2012-08-10 Gallo Sabrina Steinke Modules d'extension de pales pour une eolienne a axe verticale
EP2341245A3 (fr) * 2009-12-30 2014-01-08 General Electric Company Appareil pour augmenter la portance d'une pale d'éolienne
BE1020627A4 (fr) * 2012-04-24 2014-02-04 Citius Engineering S A Eolienne a axe vertical a rotor spherique.
WO2014036611A1 (fr) * 2012-09-07 2014-03-13 Csr Building Products Limited Aérateur et aube pour celui-ci
EP2729699A1 (fr) * 2011-07-07 2014-05-14 7142871 Canada Inc Éolienne à plusieurs étages horizontaux
US20150219347A1 (en) * 2012-09-07 2015-08-06 Csr Building Products Limited Rotor ventilator
DE102014002078A1 (de) * 2014-02-14 2015-08-20 Thorsten RATH Vertikal-Windgenerator
GB2500199B (en) * 2012-03-12 2016-01-27 Power Collective Ltd A wind turbine assembly
WO2016149755A1 (fr) * 2015-03-23 2016-09-29 Ivr Group Pty Ltd Évent
CN107476935A (zh) * 2017-09-20 2017-12-15 罗彪 垂直轴风力叶片、风轮及风力发电装置
DE102017120908A1 (de) * 2017-09-11 2019-03-14 Kastel Maschinenbau Gmbh Vertikalwindkraftanlage
WO2024028658A1 (fr) 2022-08-04 2024-02-08 Massai Simone Aérogénérateur

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DE4317617A1 (de) * 1993-05-27 1994-12-01 Ferenc Tabori Windrad mit Windkasten
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JPH1089234A (ja) * 1996-09-12 1998-04-07 Arutetsukusu:Kk 風力発電用風車
US20030209911A1 (en) * 2002-05-08 2003-11-13 Pechler Elcho R. Vertical-axis wind turbine
WO2004074679A2 (fr) * 2003-02-19 2004-09-02 Eole Canada Inc. Eoliennes
WO2008086944A2 (fr) * 2007-01-18 2008-07-24 I.C.I. Caldaie S.P.A. Turbine éolienne à axe vertical
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Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2341245A3 (fr) * 2009-12-30 2014-01-08 General Electric Company Appareil pour augmenter la portance d'une pale d'éolienne
FR2971303A1 (fr) * 2011-02-05 2012-08-10 Gallo Sabrina Steinke Modules d'extension de pales pour une eolienne a axe verticale
CN103827479A (zh) * 2011-07-07 2014-05-28 7142871加拿大有限公司 水平多级风力涡轮
EP2729699A4 (fr) * 2011-07-07 2015-04-15 7142871 Canada Inc Éolienne à plusieurs étages horizontaux
EP2729699A1 (fr) * 2011-07-07 2014-05-14 7142871 Canada Inc Éolienne à plusieurs étages horizontaux
GB2500199B (en) * 2012-03-12 2016-01-27 Power Collective Ltd A wind turbine assembly
US9732728B2 (en) 2012-03-12 2017-08-15 The Power Collective Ltd Wind turbine assembly
BE1020627A4 (fr) * 2012-04-24 2014-02-04 Citius Engineering S A Eolienne a axe vertical a rotor spherique.
WO2014036611A1 (fr) * 2012-09-07 2014-03-13 Csr Building Products Limited Aérateur et aube pour celui-ci
US20150219347A1 (en) * 2012-09-07 2015-08-06 Csr Building Products Limited Rotor ventilator
US9664399B2 (en) 2012-09-07 2017-05-30 Csr Building Products Limited Ventilator and blade therefor
AU2013313029B2 (en) * 2012-09-07 2017-04-13 Csr Building Products Limited Ventilator and blade therefor
US9644854B2 (en) * 2012-09-07 2017-05-09 Csr Building Products Limited Rotor ventilator
DE102014002078B4 (de) * 2014-02-14 2017-08-31 Thorsten RATH Vertikal-Windgenerator
DE102014002078A1 (de) * 2014-02-14 2015-08-20 Thorsten RATH Vertikal-Windgenerator
US9932965B2 (en) 2014-02-14 2018-04-03 Thorsten Rath Vertical wind generator
WO2016149755A1 (fr) * 2015-03-23 2016-09-29 Ivr Group Pty Ltd Évent
US10724751B2 (en) 2015-03-23 2020-07-28 Ivr Group Pty Ltd Vent
AU2016236842B2 (en) * 2015-03-23 2021-07-15 Ivr Group Pty Ltd Vent
DE102017120908A1 (de) * 2017-09-11 2019-03-14 Kastel Maschinenbau Gmbh Vertikalwindkraftanlage
CN107476935A (zh) * 2017-09-20 2017-12-15 罗彪 垂直轴风力叶片、风轮及风力发电装置
WO2024028658A1 (fr) 2022-08-04 2024-02-08 Massai Simone Aérogénérateur

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WO2011013105A3 (fr) 2011-04-07
ITPI20090096A1 (it) 2011-02-01
IT1397762B1 (it) 2013-01-24
EP2459871A2 (fr) 2012-06-06

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