WO1998031934A1 - Rotor with multiplane blades and wind power engine comprising such rotors - Google Patents

Rotor with multiplane blades and wind power engine comprising such rotors Download PDF

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Publication number
WO1998031934A1
WO1998031934A1 PCT/FR1998/000091 FR9800091W WO9831934A1 WO 1998031934 A1 WO1998031934 A1 WO 1998031934A1 FR 9800091 W FR9800091 W FR 9800091W WO 9831934 A1 WO9831934 A1 WO 9831934A1
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WO
WIPO (PCT)
Prior art keywords
rotor
blade
elements
blades
rotors
Prior art date
Application number
PCT/FR1998/000091
Other languages
French (fr)
Inventor
Grégoire Alexandroff
Georges Alexandroff
Original Assignee
Aerospatiale
Alexandroff Gregoire
Georges Alexandroff
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 Aerospatiale, Alexandroff Gregoire, Georges Alexandroff filed Critical Aerospatiale
Publication of WO1998031934A1 publication Critical patent/WO1998031934A1/en

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D1/00Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/02Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having a plurality of rotors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D1/00Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06Rotors
    • F03D1/0608Rotors characterised by their aerodynamic shape
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D1/00Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
    • F03D1/06Rotors
    • F03D1/065Rotors characterised by their construction elements
    • F03D1/0675Rotors characterised by their construction elements of the blades
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D7/00Controlling wind motors 
    • F03D7/02Controlling wind motors  the wind motors having rotation axis substantially parallel to the air flow entering the rotor
    • F03D7/0244Controlling wind motors  the wind motors having rotation axis substantially parallel to the air flow entering the rotor for braking
    • F03D7/0252Controlling 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03DWIND MOTORS
    • F03D9/00Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
    • F03D9/20Wind motors characterised by the driven apparatus
    • F03D9/25Wind motors characterised by the driven apparatus the apparatus being an electrical generator
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2220/00Application
    • F05B2220/70Application in combination with
    • F05B2220/706Application in combination with an electrical generator
    • F05B2220/7066Application in combination with an electrical generator via a direct connection, i.e. a gearless transmission
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00Components
    • F05B2240/20Rotors
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00Components
    • F05B2240/20Rotors
    • F05B2240/30Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/301Cross-section characteristics
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00Components
    • F05B2240/90Mounting on supporting structures or systems
    • F05B2240/91Mounting on supporting structures or systems on a stationary structure
    • F05B2240/915Mounting on supporting structures or systems on a stationary structure which is vertically adjustable
    • F05B2240/9152Mounting on supporting structures or systems on a stationary structure which is vertically adjustable by being hinged
    • F05B2240/91521Mounting on supporting structures or systems on a stationary structure which is vertically adjustable by being hinged at ground level
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05BINDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2270/00Control
    • F05B2270/10Purpose of the control system
    • F05B2270/1016Purpose of the control system in variable speed operation
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02EREDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00Energy generation through renewable energy sources
    • Y02E10/70Wind energy
    • Y02E10/72Wind turbines with rotation axis in wind direction
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02EREDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00Energy generation through renewable energy sources
    • Y02E10/70Wind energy
    • Y02E10/728Onshore wind turbines

Definitions

  • the invention relates to a rotor with at least two blades, usable in particular on an aerogenerator, on a rotorcraft or on any other rotary machine.
  • the invention also relates to an aerogenerator comprising two to four rotors mounted on a pivoting V-shaped support, as described in document EP-A-0 761 964.
  • biplane plane rotor One of the known means, described in document FR-A-2 574 113, consists in using biplane blades, which increases their resistance to bending and twisting forces.
  • This type of biplane plane rotor also has the advantage of having better finesse on an equal surface, compared to a blade rotor. usual monoplanes. Such a biplane plane rotor therefore has a high specific speed.
  • the invention is mainly intended to improve the manufacture and the mechanical characteristics of rotors with multiplane blades, in particular in order to allow the economical manufacture of the counter-rotating rotors necessary to constitute wind turbines comprising two to four rotors.
  • This result is obtained by means of a rotor with at least two blades, characterized in that each blade is multiplane and comprises:
  • the materials used are those of the aerospace industry based on plastic compounds or else materials having the advantage of being able to be recycled or of being renewable, for example the aluminum alloys in the form of sheets or profiles obtained. by spinning, or glued laminated wood.
  • the profiled elements which constitute the leading edges and the trailing edges are produced in several separate elements or in one piece, for example by spinning.
  • profile elements are fixed laterally on the connection elements of the beam, to give these connection elements profiled shapes.
  • the connecting elements are advantageously arranged obliquely in the direction of flow of the air flow between upstream and downstream, each of these elements describing a conical surface of a different angle according to its distance from the axis of rotation of the rotor.
  • the spar then advantageously comprises three connecting elements inclined respectively by approximately 10 °, 15 ° and 20 ° relative to a direction perpendicular to a longitudinal axis of the blade, starting from the tail of the blade.
  • leading edge elements are hollow and form air ducts open at the end of the blade, air intake windows being pierced in the lower surface of said elements and normally closed by flexible spring valves, capable of opening under the effect of a predetermined pressure difference.
  • the flat parts are preferably twisted and exactly superimposed with respect to the direction of the real wind.
  • the lower plane part (or to the wind) is therefore slightly in front and the upper plane part (or downwind) slightly behind.
  • the planar parts drop out simultaneously and the upper planar part is partially masked by the lower planar part (FIG. 6 of the appended drawings).
  • the planar parts form at least one venturi channel with respect to the direction of the relative wind and the flow speed is increased in the intermediate space between the planar parts, a phenomenon which increases the lift and the engine torque ( Figure 5 of the accompanying drawings).
  • each blade can be tapered or rectangular.
  • the rotor comprises two blades, the blade tails of which are embedded in a beam and joined by a tie rod which opposes centrifugal force.
  • the invention also relates to an aerogenerator, characterized in that it comprises at least two rotors associated with two multipole alternators with variable speed, fixed by means of two forks to the tops of two arrows of a pivoting support in V.
  • each multipole alternator is contained in a rigid shell-shaped envelope, fixed on one of the forks.
  • Each envelope may in particular have the shape of an ellipsoid of revolution, with a horizontal axis, the section of which is more or less flattened.
  • the beam on which the tails of the rotor blades are fixed is connected by a yoke to the shaft of the corresponding alternator.
  • the length of the beam is substantially equal to the outside diameter of the alternator.
  • Orientation or disorientation maneuvers with respect to the wind direction are carried out by temporarily desynchronizing one of the alternators with respect to the other, or by maneuvering an air brake flap fixed to one of the arrows.
  • the aforementioned characteristics make it possible to improve the manufacture and operation of a birotor aerogenerator of medium power, for example of 2000 kW. in 13 m / sec wind.
  • the rotors are around 40 m in diameter and the alternators 6 m in diameter.
  • This twin-rotor wind generator has the advantage of being simpler and less expensive than two conventional single-rotor wind generators sweeping the same surface and brought to the same height of 50 m for example.
  • FIG. 1 is a front view of a birotor wind turbine, equipped with rotors according to one invention
  • FIG. 3 is a front view of the rotor and the alternator placed in the wind of the wind generator of Figures 1 and 2;
  • FIG. 4 is a front view of the rotor and the alternator placed in the wind, also showing in dotted lines the position of the alternator downwind;
  • FIG. 6, already described, is a sectional view of the biplane blade of the rotor, showing the flow in aerodynamic stall sequence
  • FIG. 7 is an exploded perspective view of the components of a biplane blade according to the invention.
  • FIG. 8 is a sectional view in detail, illustrating the structure of a biplane blade made of plastic compound
  • FIG. 9 is a sectional view of the same blade in its end portion
  • FIG. 10 is a sectional view of the cylindrical beam, illustrating the embedding of the blade tail
  • - Figure 11 is a sectional view of one of the connecting elements between the two flat parts;
  • - Figure 12 is a sectional view of the mold for manufacturing a beam of composite plastic material of the biplane blade;
  • FIG. 13 is a sectional view of one stack of glued wooden strips constituting an alternative embodiment of the same spar;
  • FIG. 14 is a front view in partial section showing an alternative embodiment of a rotor with biplane blades, the planes of which are rectangular, as well as its alternator;
  • FIG. 15 shows in partial section, one of the biplane blades of the rotor of Figure 14, whose leading edges are hollow;
  • FIG. 16 is a sectional view of the biplane blade of Figure 15;
  • FIG. 17 is a detail view illustrating the air intake windows in the hollow biplane blade of Figures 15 and 16;
  • FIG. 18 is a sectional view of one of the connecting elements of the same hollow biplane blade.
  • FIGS. 1 and 2 represent a twin-rotor aerogenerator, constituting an advantageous application of the rotor with bi-plane blades in accordance with the invention.
  • the rotor according to the invention can equip wind turbines of different types, such as wind turbines with one or four rotors.
  • the birotor aerogenerator of FIGS. 1 and 2 comprises two rotors, each of which is formed by two biplane blades 1, 2 and 3, 4 with fixed pitch and at high speed. specific.
  • Each rotor is associated with a multipole alternator without gears and with variable speed 5, 6 fixed by means of a fork 7, 8 (FIG. 4) at the top of each of the two arrows 9, 10 of a pivoting support in V 11.
  • the two rotors are coplanar and counter-rotating and an air brake flap 12 is fixed to the arrow 9 of the rotor in the wind.
  • each biplane blade such as 1 is formed by a lower planar part 13, or in the wind, reached first by the wind, and by an upper planar part 14, or downwind, then reached by the wind.
  • These two flat parts 13, 14 form a dihedral and are twisted and exactly superimposed with respect to the direction of the real wind.
  • the flat parts 13 and 14 are tapered.
  • the two flat parts 13 and 14 of the blade 1 converge to form a blade tail 18, which is embedded in a beam 19, itself immobilized by a yoke 20 on the shaft 21 of the corresponding alternator 5.
  • the two blades 1 and 2 of each rotor are joined by a tie rod 26 which passes through the blade tails 18. This tie rod 26 opposes centrifugal force.
  • the flat parts 13, 14 are connected by connecting elements 15, 16, 17 (three in Figures 3 and 4). These elements 15, 16 and 17 are inclined respectively by approximately 10 °, 15 ° and 20 ° relative to a direction perpendicular to the longitudinal axis of the blade 1, starting from the tail 18 thereof.
  • each multipole alternator 5, 6 are contained in a rigid shell-shaped envelope 22.
  • this envelope is in the form of an ellipsoid of revolution, with a horizontal axis combined with that of the alternator. Its section is more or less flattened.
  • Each biplane blade, such as 1 comprises a beam 23, which constitutes at the same time and in a single piece the two flat parts 13, 14, the connecting elements 15, 16, 17 and the blade tail 18.
  • Profiled elements leading edge 24 and trailing edge 25 are fixed laterally on the flat parts of the spar 23.
  • Profile elements 29, 30 are also fixed laterally on each of the connecting elements 15, 16, 17.
  • the spar 23, "variable or constant section, can be made flat, from plastic compounds, in a mold 54 ( Figure 12) composed of removable parts 55, 56, 57 which allow the release. It can also be manufactured by stacking of glued strips 28 (FIG. 13).
  • the profiled elements of leading edge 24 and trailing edge 25 are blocks made of rigid plastic foam 31 and coated of fibers glass 32.
  • the spar 23 is made of carbon fibers around a rigid foam core 33.
  • FIGS. 14 to 18 there is shown in FIGS. 14 to 18 a partially hollow biplane blade.
  • the two flat parts 36, 37 of this blade are rectangular and twisted and the two biplane blades are associated as before with a multipole alternator 38 whose rigid casing 22 has a flattened shape.
  • the biplane blade 35 comprises a spar 39 also made of carbon fibers and profiled elements of leading edge 40 and trailing edge 41, made of folded aluminum sheets or by spinning. In the case where profiled elements obtained by spinning are used, these are twisted by torsion and follow the twist of the spar.
  • Air intake windows 42 are drilled in the lower surface of the two leading edge profiled elements 40. These windows 42 open into two air ducts 43, 44 open at the end of the blade, formed in the profiled elements leading edge 40. The windows 42 are closed by flexible valves forming springs 45.
  • the valves 45 are raised when the pressure differential between the interior of the air ducts 43, 44 and the pressure of the lower surface reaches a predetermined value.
  • the valves 45 open, for example by excessive wind, there is a centrifugal air flow, ejected at the end of the blade, which limits the engine torque and the speed of rotation of the rotor.
  • the invention relates not only to fixed pitch rotors, but also to variable pitch rotors.

Abstract

The invention concerns a rotor with multiplane blades and a wind power engine comprising such rotors. Each blade of the rotor comprises a spar (23) made of a single piece, forming at the same time two plane parts, linking elements (15, 16, 17) and a blade tail (18). Each blade also comprises streamlined elements of leading edges (24) and trailing edges (25), fixed on the plane parts of the spar (23). The invention also concerns a double rotor wind power engine in which each rotor with fixed pitch and high specific speed is associated with a multipole gearless alternator with variable speed: Each alternator is contained in a rigid streamlined shell, borne by a fork at the top of jibs pivoting in V.

Description

ROTOR A PALES MULTIPLANES ET AEROGENERATEUR COMPRENANT MULTIPLANE BLADES ROTOR AND AEROGENERATOR INCLUDING
DE TELS ROTORS DESCRIPTIONOF SUCH ROTORS DESCRIPTION
Domaine techniqueTechnical area
L'invention concerne un rotor à au moins deux pales, utilisable notamment sur un aérogénérateur, sur un giravion ou sur toute autre machine tournante.The invention relates to a rotor with at least two blades, usable in particular on an aerogenerator, on a rotorcraft or on any other rotary machine.
L'invention concerne également un aérogénéra- teur comprenant deux à quatre rotors montés sur un support en V pivotant, de la manière décrite dans le document EP-A-0 761 964.The invention also relates to an aerogenerator comprising two to four rotors mounted on a pivoting V-shaped support, as described in document EP-A-0 761 964.
Etat de la technique A ce jour, l'amélioration de la compétitivité de l'exploitation de l'énergie éolienne nécessite un abaissement des coûts et donc une simplification des mécanismes utilisés. On connaît par exemple les alternateurs multipôles sans engrenages de la société allemande ENERCON, qui simplifient beaucoup les aérogénérateurs .State of the art To date, improving the competitiveness of wind energy exploitation requires lowering costs and therefore simplifying the mechanisms used. We know for example the multipole alternators without gears of the German company ENERCON, which greatly simplify wind turbines.
Il est possible également, en adoptant le concept du birotor, décrit dans le document EP-A- 0 761 964, de simplifier et d'"alléger les rotors en supprimant les mécanismes de pas variable.It is also possible, by adopting the concept of the birotor, described in document EP-A-0 761 964, to simplify and "lighten the rotors by eliminating the variable pitch mechanisms.
Il existe des moyens d'éviter l'emballement d'un rotor à pas fixe et à pales creuses.There are ways to avoid the runaway of a fixed pitch rotor with hollow blades.
L'un des moyens connus, décrit dans le document FR-A-2 574 113, consiste à utiliser des pales biplanes, ce qui augmente leur résistance aux efforts de flexion et de torsion. Ce type de rotor à pales biplanes présente également l'avantage d'avoir une meilleure finesse à surface égale, par rapport à un rotor à pales monoplanes usuelles. Un tel rotor à pales biplanes possède donc une vitesse spécifique élevée.One of the known means, described in document FR-A-2 574 113, consists in using biplane blades, which increases their resistance to bending and twisting forces. This type of biplane plane rotor also has the advantage of having better finesse on an equal surface, compared to a blade rotor. usual monoplanes. Such a biplane plane rotor therefore has a high specific speed.
Cependant, dans le document FR-A-2 574 113 le problème de la liaison des deux parties planes n'a pas été entièrement résolu. D'autre part, les liaisons entre les parties planes provoquent des traînées parasites néfastes. Il a été proposé de percer les pièces de liaison profilées pour permettre la libre circulation des écoulements d'intrados et d'extrados. Toute- fois, ces perforations affaiblissent encore les liaisons .However, in document FR-A-2 574 113 the problem of the connection of the two flat parts has not been entirely resolved. On the other hand, the connections between the planar parts cause harmful parasitic streaks. It has been proposed to drill the profiled connecting pieces to allow the free circulation of the intrados and extrados flows. However, these perforations further weaken the bonds.
Un autre moyen connu pour combattre l'emballement éventuel d'un rotor à pas fixe consiste à provoquer une circulation d'air centrifuge à l'intérieur de pales creuses. Cette technique est décrite dans le document FR-A-1 085 771.Another known means for combating the possible runaway of a rotor with a fixed pitch consists in causing a circulation of centrifugal air inside hollow blades. This technique is described in document FR-A-1 085 771.
Exposé de 1 ' inventionStatement of the invention
L'invention est principalement destinée à amé- liorer la fabrication et les caractéristiques mécaniques des rotors à pales multiplanes, notamment afin de permettre la fabrication économique des rotors contra- rotatifs nécessaires pour constituer des aérogénérateurs comprenant deux à quatre rotors. Ce résultat est obtenu au moyen d'un rotor à au moins deux pales, caractérisé par le fait que chaque pale est multiplane et comprend :The invention is mainly intended to improve the manufacture and the mechanical characteristics of rotors with multiplane blades, in particular in order to allow the economical manufacture of the counter-rotating rotors necessary to constitute wind turbines comprising two to four rotors. This result is obtained by means of a rotor with at least two blades, characterized in that each blade is multiplane and comprises:
- un longeron en une seule pièce, formant à la fois au moins deux parties planes, des éléments de liaisons et une queue de pale ; et- A spar in one piece, forming at least two flat parts, connecting elements and a blade tail; and
- des éléments profilés de bords d'attaque et de bords de fuite fixés latéralement sur les parties planes du longeron . Les matériaux utilisés sont ceux de l'industrie aérospatiale à base de composés plastiques ou bien des matériaux ayant l'avantage de pouvoir être recyclés ou d'être renouvelables, par exemple les alliages d'alumi- nium sous forme de tôles ou de profilés obtenus par filage, ou encore le bois lamellé-collé .- profiled elements of leading edges and trailing edges fixed laterally on the flat parts of the spar. The materials used are those of the aerospace industry based on plastic compounds or else materials having the advantage of being able to be recycled or of being renewable, for example the aluminum alloys in the form of sheets or profiles obtained. by spinning, or glued laminated wood.
Les éléments profilés qui constituent les bords d'attaque et les bords de fuite sont fabriqués en plusieurs éléments séparés ou bien d'un seul tenant, par exemple par filage.The profiled elements which constitute the leading edges and the trailing edges are produced in several separate elements or in one piece, for example by spinning.
De préférence, afin d'améliorer les caractéristiques aérodynamiques, sans pour autant affaiblir les liaisons, des éléments de profils sont fixés latéralement sur les éléments de liaison du longeron, pour don- ner à ces éléments de liaison des formes profilées.Preferably, in order to improve the aerodynamic characteristics, without weakening the connections, profile elements are fixed laterally on the connection elements of the beam, to give these connection elements profiled shapes.
Les éléments de liaison sont avantageusement disposés obliquement dans le sens de l'écoulement du flux d'air entre l'amont et l'aval, chacun de ces éléments décrivant une surface conique d'un angle diffé- rent selon son éloignement de l'axe de rotation du rotor .The connecting elements are advantageously arranged obliquely in the direction of flow of the air flow between upstream and downstream, each of these elements describing a conical surface of a different angle according to its distance from the axis of rotation of the rotor.
Le longeron comprend alors, avantageusement, trois éléments de liaison inclinés respectivement d'environ 10°, 15° et 20° par rapport à une direction perpendiculaire à un axe longitudinal de la pale, en partant de la queue de la pale.The spar then advantageously comprises three connecting elements inclined respectively by approximately 10 °, 15 ° and 20 ° relative to a direction perpendicular to a longitudinal axis of the blade, starting from the tail of the blade.
Dans une forme de réalisation préférée de l'invention, les éléments de bord d'attaque sont creux et forment des canalisations d'air ouvertes en bout de pale, des fenêtre d'admission d'air étant percées dans l'intrados desdits éléments et normalement fermées par des valves flexibles formant ressorts, aptes à s'ouvrir sous l'effet d'une différence de pression prédéterminée .In a preferred embodiment of the invention, the leading edge elements are hollow and form air ducts open at the end of the blade, air intake windows being pierced in the lower surface of said elements and normally closed by flexible spring valves, capable of opening under the effect of a predetermined pressure difference.
Afin d'assurer le meilleur contrôle aérodynamique ainsi qu'une sécurité de fonctionnement améliorée, les parties planes sont, de préférence, vrillées et exactement superposées par rapport à la direction du vent réel.In order to ensure the best aerodynamic control as well as improved operating safety, the flat parts are preferably twisted and exactly superimposed with respect to the direction of the real wind.
Par rapport au vent relatif, la partie plane inférieure (ou au vent) est donc légèrement en avant et la partie plane supérieure (ou sous le vent) légèrement en arrière. Lorsqu'on limite le régime de rotation du rotor par rapport à sa vitesse optimale, les parties planes décrochent simultanément et la partie plane supérieure se trouve partiellement masquée par la par- tie plane inférieure (figure 6 des dessins annexés) . En régime de rotation optimale les parties planes forment au moins un canal venturi par rapport à la direction du vent relatif et la vitesse d'écoulement est augmentée dans l'espace intercalaire entre les parties planes, phénomène qui accroît la portance et le couple moteur (figure 5 des dessins annexés) .Relative to the relative wind, the lower plane part (or to the wind) is therefore slightly in front and the upper plane part (or downwind) slightly behind. When the rotational speed of the rotor is limited relative to its optimum speed, the planar parts drop out simultaneously and the upper planar part is partially masked by the lower planar part (FIG. 6 of the appended drawings). In optimal rotation regime, the planar parts form at least one venturi channel with respect to the direction of the relative wind and the flow speed is increased in the intermediate space between the planar parts, a phenomenon which increases the lift and the engine torque ( Figure 5 of the accompanying drawings).
Selon le cas, les parties planes de chaque pale peuvent être effilées ou rectangulaires.Depending on the case, the flat parts of each blade can be tapered or rectangular.
Selon un agencement préférentiel, le rotor comprend deux pales dont les queues de pales sont encastrées dans un fléau et réunies par un tirant qui s'oppose à la force centrifuge.According to a preferred arrangement, the rotor comprises two blades, the blade tails of which are embedded in a beam and joined by a tie rod which opposes centrifugal force.
L'invention a aussi pour objet un aérogénérateur, caractérisé par le fait qu'il comprend au moins deux rotors associés à deux alternateurs multipôles à vitesse variable, fixés par l'intermédiaire de deux fourches aux sommets de deux flèches d'un support pivotant en V. Afin d'améliorer 1 ' aérodynamisme des alternateurs multipôles, nécessairement de grand diamètre, chaque alternateur multipole est contenu dans une enveloppe rigide en forme de coque, fixée sur l'une des fourches. Chaque enveloppe peut notamment avoir la forme d'une ellipsoïde de révolution, à axe horizontal, dont la section est plus ou moins aplatie.The invention also relates to an aerogenerator, characterized in that it comprises at least two rotors associated with two multipole alternators with variable speed, fixed by means of two forks to the tops of two arrows of a pivoting support in V. In order to improve the aerodynamics of the multipole alternators, necessarily of large diameter, each multipole alternator is contained in a rigid shell-shaped envelope, fixed on one of the forks. Each envelope may in particular have the shape of an ellipsoid of revolution, with a horizontal axis, the section of which is more or less flattened.
Le fléau sur lequel sont fixées les queues de pales du rotor est relié par un carcan à l'arbre de l'alternateur correspondant. La longueur du fléau est sensiblement égale au diamètre extérieur de l'alternateur.The beam on which the tails of the rotor blades are fixed is connected by a yoke to the shaft of the corresponding alternator. The length of the beam is substantially equal to the outside diameter of the alternator.
Les manoeuvres d'orientation ou de désorienta- tion par rapport à la direction du vent s'effectuent en désynchronisant temporairement l'un des alternateurs par rapport à l'autre, ou bien en manoeuvrant un volet aérofrein fixé à l'une des flèches.Orientation or disorientation maneuvers with respect to the wind direction are carried out by temporarily desynchronizing one of the alternators with respect to the other, or by maneuvering an air brake flap fixed to one of the arrows.
Les caractéristiques précitées permettent d'améliorer la fabrication et l'exploitation d'un aéro- générateur birotor de puissance moyenne, par exemple de 2000 kW. par vent de 13 m/sec.. Dans ce cas, les rotors ont environ 40 m de diamètre et les alternateurs 6 m de diamètre .The aforementioned characteristics make it possible to improve the manufacture and operation of a birotor aerogenerator of medium power, for example of 2000 kW. in 13 m / sec wind. In this case, the rotors are around 40 m in diameter and the alternators 6 m in diameter.
Cet aérogénérateur birotor présente l'avantage d'être plus simple et moins coûteux que deux aérogénérateurs monorotors usuels balayant la même surface et portés à la même hauteur de 50 m par exemple.This twin-rotor wind generator has the advantage of being simpler and less expensive than two conventional single-rotor wind generators sweeping the same surface and brought to the same height of 50 m for example.
Brève description des dessinsBrief description of the drawings
On décrira à présent, à titre d'exemples non limitatifs, différentes formes de réalisation de rotors conformes à l'invention, appliqués à un aérogénérateur birotor, en se référant aux dessins annexés, dans lesquels :We will now describe, by way of nonlimiting examples, various embodiments of rotors according to the invention, applied to an aerogenerator. birotor, with reference to the accompanying drawings, in which:
- la figure 1 est une vue de face d'un aérogénérateur birotor, équipé de rotors conformes à 1 ' inven- tion ;- Figure 1 is a front view of a birotor wind turbine, equipped with rotors according to one invention;
- la figure 2 représente le même aérogénérateur vu de profil ;- Figure 2 shows the same wind turbine seen in profile;
- la figure 3 est une vue de face du rotor et de l'alternateur placés au vent de 1 ' aérogénérateur des figures 1 et 2 ;- Figure 3 is a front view of the rotor and the alternator placed in the wind of the wind generator of Figures 1 and 2;
- la figure 4 est une vue de face du rotor et de l'alternateur placés au vent, montrant également en pointillé la position de l'alternateur sous le vent ;- Figure 4 is a front view of the rotor and the alternator placed in the wind, also showing in dotted lines the position of the alternator downwind;
- la figure 5, déjà décrite, est une vue en coupe de la pale biplane du rotor, montrant la direction de l'écoulement en régime de fonctionnement normal ;- Figure 5, already described, is a sectional view of the biplane rotor blade, showing the direction of flow in normal operating conditions;
- la figure 6, déjà décrite, est une vue en coupe de la pale biplane du rotor, représentant l'écou- lement en séquence de décrochage aérodynamique ;FIG. 6, already described, is a sectional view of the biplane blade of the rotor, showing the flow in aerodynamic stall sequence;
- la figure 7 est une vue en perspective éclatée des éléments constitutifs d'une pale biplane conforme à l'invention ;- Figure 7 is an exploded perspective view of the components of a biplane blade according to the invention;
- la figure 8 est une' vue en coupe et en détail, illustrant la structure d'une pale biplane en composé plastique ;- Figure 8 is a sectional view in detail, illustrating the structure of a biplane blade made of plastic compound;
- la figure 9 est une vue en coupe de la même pale dans sa partie d'extrémité ;- Figure 9 is a sectional view of the same blade in its end portion;
- la figure 10 est une vue en coupe du fléau cylindrique, illustrant l'encastrement de la queue de pale ;- Figure 10 is a sectional view of the cylindrical beam, illustrating the embedding of the blade tail;
- la figure 11 est une vue en coupe de l'un des éléments de liaison entre les deux parties planes ; - la figure 12 est une vue en coupe du moule de fabrication d'un longeron en matériau plastique composite de la pale biplane ;- Figure 11 is a sectional view of one of the connecting elements between the two flat parts; - Figure 12 is a sectional view of the mold for manufacturing a beam of composite plastic material of the biplane blade;
-- la figure 13 est une vue en coupe de 1 ' empi- lement des lamelles collées en bois constituant une variante de réalisation du même longeron ;- Figure 13 is a sectional view of one stack of glued wooden strips constituting an alternative embodiment of the same spar;
- la figure 14 est une vue de face et en coupe partielle représentant une variante de réalisation d'un rotor à pales biplanes dont les plans sont rectangulai- res, ainsi que son alternateur ;FIG. 14 is a front view in partial section showing an alternative embodiment of a rotor with biplane blades, the planes of which are rectangular, as well as its alternator;
- la figure 15, représente en coupe partielle, une des pales biplanes, du rotor de la figure 14, dont les bords d'attaque sont creux ;- Figure 15, shows in partial section, one of the biplane blades of the rotor of Figure 14, whose leading edges are hollow;
- la figure 16 est une vue en coupe de la pale biplane de la figure 15 ;- Figure 16 is a sectional view of the biplane blade of Figure 15;
- la figure 17 est une vue en détail illustrant les fenêtres d'admission d'air dans la pale biplane creuse des figures 15 et 16 ;- Figure 17 is a detail view illustrating the air intake windows in the hollow biplane blade of Figures 15 and 16;
- la figure 18 est une vue en coupe de l'un des éléments de liaison de la même pale biplane creuse.- Figure 18 is a sectional view of one of the connecting elements of the same hollow biplane blade.
Description détaillée de formes de réalisation préférées de 1 ' inventionDetailed description of preferred embodiments of the invention
Les figures 1 et 2 représentent un aérogénéra- teur birotor, constituant une application avantageuse du rotor à pales biplanes conforme à l'invention.FIGS. 1 and 2 represent a twin-rotor aerogenerator, constituting an advantageous application of the rotor with bi-plane blades in accordance with the invention.
Il est à noter que des applications d'un tel rotor sont possibles dans d'autres domaines techniques, tels que ceux des rotors de giravions ou des rotors basculants équipant certains aéronefs.It should be noted that applications of such a rotor are possible in other technical fields, such as those of rotorcraft rotors or tilting rotors fitted to certain aircraft.
Par ailleurs, le rotor selon l'invention peut équiper des aérogénérateurs de types différents, tels que des aérogénérateurs à un ou quatre rotors. L' aérogénérateur birotor des figures 1 et 2 comprend deux rotors, dont chacun est formé de deux pales biplanes 1, 2 et 3, 4 à pas fixe et à grande vitesse . spécifique. Chaque rotor est associé à un alternateur multipole sans engrenages et à vitesse variable 5, 6 fixé par l'intermédiaire d'une fourche 7, 8 (figure 4) au sommet de chacune des deux flèches 9, 10 d'un support pivotant en V 11.Furthermore, the rotor according to the invention can equip wind turbines of different types, such as wind turbines with one or four rotors. The birotor aerogenerator of FIGS. 1 and 2 comprises two rotors, each of which is formed by two biplane blades 1, 2 and 3, 4 with fixed pitch and at high speed. specific. Each rotor is associated with a multipole alternator without gears and with variable speed 5, 6 fixed by means of a fork 7, 8 (FIG. 4) at the top of each of the two arrows 9, 10 of a pivoting support in V 11.
Selon la variante de réalisation représentée, les deux rotors sont coplanaires et contrarotatifs et un volet aérofrein 12 est fixé sur la flèche 9 du rotor au vent .According to the variant embodiment shown, the two rotors are coplanar and counter-rotating and an air brake flap 12 is fixed to the arrow 9 of the rotor in the wind.
Sur la droite de la figure 1, on a ^représenté la manoeuvre de fixation de l'alternateur 6 sur la fourche 8 de la flèche 10.On the right of Figure 1, there is shown ^ fixing operation of the alternator 6 of the fork 8 of the arrow 10.
Comme l'illustrent notamment les figures 4 à 6, chaque pale biplane, telle que 1, est formée d'une partie plane inférieure 13, ou au vent, atteinte en premier par le vent, et d'une partie plane supérieure 14, ou sous le vent, atteinte ensuite par le vent. Ces deux parties planes 13, 14 forment une dièdre et sont vrillées et exactement superposées par rapport à la direction du vent réel. Dans la forme de réalisation des figures 3 à 11, les parties- planes 13 et 14 sont effilées.As illustrated in particular in FIGS. 4 to 6, each biplane blade, such as 1, is formed by a lower planar part 13, or in the wind, reached first by the wind, and by an upper planar part 14, or downwind, then reached by the wind. These two flat parts 13, 14 form a dihedral and are twisted and exactly superimposed with respect to the direction of the real wind. In the embodiment of Figures 3 to 11, the flat parts 13 and 14 are tapered.
Les deux parties planes 13 et 14 de la pale 1 convergent pour former une queue de pale 18, qui est encastrée dans un fléau 19, lui-même immobilisé par un carcan 20 sur l'arbre 21 de l'alternateur 5 correspon- dant.The two flat parts 13 and 14 of the blade 1 converge to form a blade tail 18, which is embedded in a beam 19, itself immobilized by a yoke 20 on the shaft 21 of the corresponding alternator 5.
Les deux pales 1 et 2 de chaque rotor sont réunies par un tirant 26 qui passe au travers des queues de pales 18. Ce tirant 26 s'oppose à la force centrifuge.The two blades 1 and 2 of each rotor are joined by a tie rod 26 which passes through the blade tails 18. This tie rod 26 opposes centrifugal force.
Les parties planes 13, 14 sont reliées par des éléments de liaison 15, 16, 17 (trois sur les figures 3 et 4) . Ces éléments 15, 16 et 17 sont inclinés respectivement d'environ 10°, 15° et 20° par rapport à une direction perpendiculaire à l'axe longitudinal de la pale 1, en partant de la queue 18 de celle-ci.The flat parts 13, 14 are connected by connecting elements 15, 16, 17 (three in Figures 3 and 4). These elements 15, 16 and 17 are inclined respectively by approximately 10 °, 15 ° and 20 ° relative to a direction perpendicular to the longitudinal axis of the blade 1, starting from the tail 18 thereof.
Le rotor et le stator de chaque alternateur multipôles 5, 6 sont contenus dans une enveloppe rigide en forme de coque 22. Dans la forme de réalisation de la figure 4, cette enveloppe est en forme d'ellipsoïde de révolution, d'axe horizontal confondu avec celui de l'alternateur. Sa section est plus ou moins aplatie. Chaque pale biplane, telle que 1, comprend un longeron 23, qui constitue à la fois et en une seule pièce les deux parties planes 13, 14, les éléments de liaison 15, 16, 17 et la queue de pale 18. Des éléments profilés de bord d'attaque 24 et de bord de fuite 25 sont fixés latéralement sur les parties planes du longeron 23. Des éléments de profils 29, 30 sont également fixés latéralement sur chacun des éléments de liaison 15, 16, 17.The rotor and the stator of each multipole alternator 5, 6 are contained in a rigid shell-shaped envelope 22. In the embodiment of FIG. 4, this envelope is in the form of an ellipsoid of revolution, with a horizontal axis combined with that of the alternator. Its section is more or less flattened. Each biplane blade, such as 1, comprises a beam 23, which constitutes at the same time and in a single piece the two flat parts 13, 14, the connecting elements 15, 16, 17 and the blade tail 18. Profiled elements leading edge 24 and trailing edge 25 are fixed laterally on the flat parts of the spar 23. Profile elements 29, 30 are also fixed laterally on each of the connecting elements 15, 16, 17.
Le longeron 23, à "section variable ou constante, peut être fabriqué à plat, à partir de composés plastiques, dans un moule 54 (figure 12) composé de pièces amovibles 55, 56, 57 qui permettent le démoulage. Il peut être également fabriqué par empilement de lamelles collées 28 (figure 13) . Dans la forme de réalisation illustrée sur les figures 2 à 11, les éléments profilés de bord d'attaque 24 et de bord de fuite 25 sont des blocs fabriqués en mousse rigide plastique 31 et revêtus de fibreS de verre 32. Le longeron 23 est fabriqué en fibres de carbone autour d'une âme en mousse rigide 33.The spar 23, "variable or constant section, can be made flat, from plastic compounds, in a mold 54 (Figure 12) composed of removable parts 55, 56, 57 which allow the release. It can also be manufactured by stacking of glued strips 28 (FIG. 13). In the embodiment illustrated in FIGS. 2 to 11, the profiled elements of leading edge 24 and trailing edge 25 are blocks made of rigid plastic foam 31 and coated of fibers glass 32. The spar 23 is made of carbon fibers around a rigid foam core 33.
Selon une variante de réalisation, on a représenté sur les figures 14 à 18 une pale biplane partiel- lement creuse. Les deux parties planes 36, 37 de cette pale sont rectangulaires et vrillées et les deux pales biplanes sont associées comme précédemment à un alternateur multipole 38 dont l'enveloppe rigide 22 a une forme aplatie. La pale biplane 35 comprend un longeron 39 également en fibres de carbone et des éléments profilés de bord d'attaque 40 et de bord de fuite 41, fabriqués en tôles d'aluminium pliées ou par filage. Dans le cas où l'on utilise des éléments profilés obtenus par filage, ceux-ci sont vrillés par torsion et épousent le vrillage du longeron.According to an alternative embodiment, there is shown in FIGS. 14 to 18 a partially hollow biplane blade. The two flat parts 36, 37 of this blade are rectangular and twisted and the two biplane blades are associated as before with a multipole alternator 38 whose rigid casing 22 has a flattened shape. The biplane blade 35 comprises a spar 39 also made of carbon fibers and profiled elements of leading edge 40 and trailing edge 41, made of folded aluminum sheets or by spinning. In the case where profiled elements obtained by spinning are used, these are twisted by torsion and follow the twist of the spar.
Des fenêtre d'admission d'air 42 sont percées dans l'intrados des deux éléments profilés de bord d'attaque 40. Ces fenêtres 42 débouchent dans deux canalisations d'air 43, 44 ouvertes en bout de pale, formées dans les éléments profilés de bord d'attaque 40. Les fenêtres 42 sont fermées par des valves flexibles formant ressorts 45.Air intake windows 42 are drilled in the lower surface of the two leading edge profiled elements 40. These windows 42 open into two air ducts 43, 44 open at the end of the blade, formed in the profiled elements leading edge 40. The windows 42 are closed by flexible valves forming springs 45.
Les valves 45 se soulèvent lorsque le différentiel de pression entre l'intérieur des canalisations d'air 43, 44 et la pression d'intrados atteint une valeur prédéterminée. Quand les valves 45 s'ouvrent, par exemple par vent de force excessive, il se produit une circulation d'air centrifuge, éjectée en bout de pale, qui limite le couple moteur et la vitesse de rotation du rotor.The valves 45 are raised when the pressure differential between the interior of the air ducts 43, 44 and the pressure of the lower surface reaches a predetermined value. When the valves 45 open, for example by excessive wind, there is a centrifugal air flow, ejected at the end of the blade, which limits the engine torque and the speed of rotation of the rotor.
Sur la figure 15, on a représenté en coupe l'organisation interne de l'alternateur 38 associé au rotor à pales biplanes. De façon plus générale, les pales biplanes de chaque rotor peuvent être remplacées par des pales multiplanes, et notament triplanes, dont toutes les parties planes appartiennent à un longeron en une seule pièce, sur lequel sont fixés des éléments profilés de bord d'attaque et de bord de fuite.In Figure 15, there is shown in section the internal organization of the alternator 38 associated with the rotor with biplane blades. More generally, the biplane blades of each rotor can be replaced by multiplane blades, and in particular triplane blades, all the flat parts of which belong to a spar in one piece, on which are fixed leading edge elements and trailing edge.
Enfin, l'invention concerne non seulement les rotors à pas fixe, mais aussi les rotors à pas variable. Finally, the invention relates not only to fixed pitch rotors, but also to variable pitch rotors.

Claims

REVENDICATIONS
1. Rotor à au moins deux pales (1,2 ; 3,4 ; 35), caractérisé par le fait que chaque pale (1,2 ; 3,4 ; 35) est multiplane et comprend :1. Rotor with at least two blades (1,2; 3,4; 35), characterized in that each blade (1,2; 3,4; 35) is multiplane and comprises:
- un longeron (23,39) en une seule pièce, formant à la fois au moins deux parties planes (13, 14 ; 36, 37), des éléments de liaison (15,16,17) et une queue de pale (18) ; et - des éléments profilés de bords d'attaque (24,40) et de bords de fuite (25,41) fixés latéralement sur Les parties planes du longeron (23,39).- a spar (23,39) in one piece, forming at least two flat parts (13, 14; 36, 37), connecting elements (15,16,17) and a blade tail (18 ); and - profiled elements of leading edges (24.40) and trailing edges (25,41) fixed laterally on the flat parts of the spar (23,39).
2 Rotor selon la revendication 1, dans lequel des éléments de profils (29,30) sont fixés latéralement sur les éléments de liaison (15,16,17) du longeron (23,39), pour donner à ces éléments de liaison des formes profilées.2 Rotor according to claim 1, wherein the profile elements (29,30) are fixed laterally on the connecting elements (15,16,17) of the beam (23,39), to give these connecting elements shapes profiled.
3. Rotor selon l'une quelconque des revendications précédentes, dans lequel les éléments de liaison (15,16,17) sont disposés obliquement dans le sens de l'écoulement du flux d'air entre l'amont et l'aval, chacun de ces éléments décrivant une surface conique d'un angle différent selon son eloignement de l'axe de rotation du rotor. 3. Rotor according to any one of the preceding claims, in which the connecting elements (15,16,17) are arranged obliquely in the direction of flow of the air flow between upstream and downstream, each of these elements describing a conical surface of a different angle according to its distance from the axis of rotation of the rotor.
4. Rotor selon la revendication 3, dans lequel le longeron (23,39) comprend trois éléments de liaison (15,16,17) inclinés respectivement d'environ 10°, 15° et 20° par rapport à une direction perpendiculaire à un axe longitudinal de la pale, en partant de la queue de la pale (18) .4. Rotor according to claim 3, wherein the beam (23,39) comprises three connecting elements (15,16,17) inclined respectively by about 10 °, 15 ° and 20 ° relative to a direction perpendicular to a longitudinal axis of the blade, starting from the tail of the blade (18).
5. Rotor selon l'une quelconque des revendications précédentes, dans lequel les éléments de bord d'attaque (40) sont creux et forment des canalisations d'air (43,44) ouvertes en bout de pale, des fenêtres d'admission d'air (42) étant percées dans l'intrados desdits éléments et normalement fermées par des valves flexibles formant ressorts (45), aptes à s'ouvrir sous l'effet d'une différence de pression prédéterminée.5. Rotor according to any one of the preceding claims, in which the leading edge elements (40) are hollow and form pipes. air (43,44) open at the blade tip, air intake windows (42) being pierced in the lower surface of said elements and normally closed by flexible spring-forming valves (45), able to open under the effect of a predetermined pressure difference.
6. Rotor selon l'une quelconque des revendications précédentes, dans lequel les parties planes (13, 14 ; 36, 37) forment une dièdre et sont vrillées et exactement superposées par rapport à la direction du vent réel.6. Rotor according to any one of the preceding claims, in which the planar parts (13, 14; 36, 37) form a dihedral and are twisted and exactly superimposed with respect to the direction of the real wind.
7. Rotor selon la revendication 6, dans lequel les parties planes (13, 14) sont effilées.7. Rotor according to claim 6, wherein the planar parts (13, 14) are tapered.
8. Rotor selon la revendication 6, dans lequel les parties planes (36, 37) sont rectangulaires. 8. Rotor according to claim 6, wherein the planar parts (36, 37) are rectangular.
9. Rotor selon l'une quelconque des revendications précédentes, comprenant deux pales (1, 2 ; 3, 4 ; 35) dont les queues de pales (18) sont encastrées dans un fléau (19) et réunies par un tirant (26) qui s'oppose à la force centrifuge. 10. Aérogénérateur, caractérisé par le fait qu'il comprend au moins deux rotors associés à deux alternateurs multipôles à vitesse variable (5,6), fixés par l'intermédiaire de deux fourches (7,8) aux sommets de deux flèches (9,9. Rotor according to any one of the preceding claims, comprising two blades (1, 2; 3, 4; 35) whose blade tails (18) are embedded in a beam (19) and joined by a tie rod (26) which opposes centrifugal force. 10. Aerogenerator, characterized in that it comprises at least two rotors associated with two multipole alternators with variable speed (5,6), fixed by means of two forks (7,8) to the tops of two arrows (9 ,
10) d'un support pivotant en V (11). 10) of a pivoting V-shaped support (11).
11. Aérogénérateur selon la revendication 10, dans lequel chaque alternateur multipole (5,6) est contenu dans une enveloppe rigide (22) en forme de coque, fixée sur l'une des fourches (7,8).11. An aerogenerator according to claim 10, in which each multipole alternator (5,6) is contained in a rigid shell (22) in the form of a shell, fixed on one of the forks (7,8).
12. Aérogénérateur selon la revendication 11, dans lequel chaque enveloppe (22) a la forme d'une ellipsoïde de révolution, à axe horizontal.12. The wind generator according to claim 11, wherein each envelope (22) has the shape of an ellipsoid of revolution, with a horizontal axis.
13. Aérogénérateur selon l'une quelconque des revendications 10 à 12, combiné avec la revendication 8, dans lequel le fléau (19) est relié par un carcan (20) à l'arbre (21) de l'un des alternateurs (5,6).13. An aerogenerator according to any one of claims 10 to 12, combined with claim 8, in which the beam (19) is connected by a yoke (20) to the shaft (21) of one of the alternators (5,6).
14. Aérogénérateur selon l'une quelconque des revendications 10 à 13, d'une puissance d'environ 2000 kW, dans lequel les rotors ont environ 40 m de diamètre et des mouvements d'orientation ou de désorientation par rapport à la direction du vent sont effectués en désynchronisant les régimes de rotation des deux alternateurs (5,6). 14. An aerogenerator according to any one of claims 10 to 13, with a power of about 2000 kW, in which the rotors have about 40 m in diameter and movements of orientation or disorientation relative to the direction of the wind. are performed by desynchronizing the rotation speeds of the two alternators (5,6).
PCT/FR1998/000091 1997-01-20 1998-01-19 Rotor with multiplane blades and wind power engine comprising such rotors WO1998031934A1 (en)

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FR9700521A FR2758594B1 (en) 1997-01-20 1997-01-20 IMPROVEMENTS ON BIROTORS AIR GENERATORS
FR97/00521 1997-01-20

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US8177517B2 (en) 2005-10-17 2012-05-15 Lm Glasfiber A/S Blade for a wind turbine rotor
US8469672B2 (en) 2005-10-17 2013-06-25 Lm Glasfiber A/S Blade for a wind turbine rotor
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US20100303631A1 (en) * 2009-05-29 2010-12-02 Vestas Wind Systems A/S Wind Turbine Rotor Blade Having Segmented Tip
CN102242693A (en) * 2010-05-12 2011-11-16 陈显锋 Wind wheel of wind driven generator
CN101865077A (en) * 2010-06-23 2010-10-20 傅筱懿 Fan blade structure of a wind generator
CN103807111A (en) * 2014-01-26 2014-05-21 桐乡市石门永新玻璃钢制品有限公司 Blade of 50KW wind generating set
US10253753B2 (en) 2014-09-25 2019-04-09 Winfoor Ab Rotor blade for wind turbine
US20170022967A1 (en) * 2015-07-21 2017-01-26 Winnova Energy LLC System and method for improving efficiency of turbine airfoils
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FR2758594B1 (en) 1999-04-02

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