Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
  • F03D—WIND MOTORS
  • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
  • F03D1/02—Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having a plurality of rotors
  • F03D1/025—Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having a plurality of rotors coaxially arranged
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
  • F03D—WIND MOTORS
  • F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor 
  • F03D1/04—Wind motors with rotation axis substantially parallel to the air flow entering the rotor  having stationary wind-guiding means, e.g. with shrouds or channels
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
  • F03D—WIND MOTORS
  • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
  • F03D9/10—Combinations of wind motors with apparatus storing energy
  • F03D9/11—Combinations of wind motors with apparatus storing energy storing electrical energy
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
  • F03D—WIND MOTORS
  • F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
  • F03D9/20—Wind motors characterised by the driven apparatus
  • F03D9/25—Wind motors characterised by the driven apparatus the apparatus being an electrical generator
  • F03D9/255—Wind motors characterised by the driven apparatus the apparatus being an electrical generator connected to electrical distribution networks; Arrangements therefor
• • 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
  • F05B2240/10—Stators
  • F05B2240/13—Stators to collect or cause flow towards or away from turbines
• • 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
  • F05B2240/10—Stators
  • F05B2240/14—Casings, housings, nacelles, gondels or the like, protecting or supporting assemblies there within
• • 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
  • F05B2250/70—Shape
  • F05B2250/71—Shape curved
  • F05B2250/711—Shape curved convex
• • 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
  • F05B2250/70—Shape
  • F05B2250/71—Shape curved
  • F05B2250/712—Shape curved concave
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
  • Y02E10/00—Energy generation through renewable energy sources
  • Y02E10/70—Wind energy
  • Y02E10/72—Wind turbines with rotation axis in wind direction
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
  • Y02E70/00—Other energy conversion or management systems reducing GHG emissions
  • Y02E70/30—Systems combining energy storage with energy generation of non-fossil origin

Definitions

• the invention relates to an aerogenerator having a tubular body comprising: a circular air inlet opening, - a circular exhaust opening, a non-limiting outer surface between the intake opening and the exhaust opening an inner surface defining an air passage connecting said openings, having a horizontal straight flow axis, and having a convergent section connected to the intake opening, and a diverging section connected to the exhaust opening, said sections being connected by a neck, a rotating means axially positioned near the neck and converting the air flow movement to the neck in a rotational movement of a coupling means connected to a first generating machine, and a first propeller rotatably mounted relative to the tubular body, upstream of the rotational means, axially placed in the convergent section of the inner surface.
• JP2005240668 and JP2003028043 for which the inner surface has a generally nozzle shape.
• the admitted air is accelerated in the convergent section, this increase in energy kinetics of the wind accompanied by a progressive decrease of the pressure.
• the shape of the diverging section creates an additional depression which has the effect of suctioning the inlet to the outlet ("Venturi" effect).
• These known wind turbines have the disadvantage of having an acceptable production of electrical energy only for a relatively high wind speed, and to have a relatively low overall efficiency given the low value of the ratio between the power captured by the rotating device at the neck and the power of the wind at the neck.
• the rotary means is a generator turbine supplying mechanical energy, for example to an electric generator.
• the upstream propeller is still in compressor mode to raise the Mach number from the airflow to Machi at the neck upstream of the turbine. This condition is the basic principle used in this document in order to recover a part of the internal energy of the fluid in the expansion which takes place in the turbine (passage from Machi to MachO at the outlet).
• This document also provides for the case where two propellers are placed upstream of the turbine. As above, they act as a compressor to raise the flow to Machi at the neck. They are always energy consumers.
• the propeller interposed between the first propeller and the turbine requires less energy than the first propeller located in the plane of the intake opening and without wind, allows to start the first propeller via the turbine, by mechanical drive. a transmission shaft.
• the (or) propeller (s) placed (s) upstream of the rotary means consisting solely of a turbine operates (s) in compressor mode, regardless of the natural wind speed.
• the outer shape has no particular effect on the operation of the aerogenerator because, although potentially depressing, the convergence angle of the convergent section T2 is too high and causes the sliding flux to detach on the outer surface, eliminating any influence of the external flow on the internal flow.
• the ratio between the neck diameter and the diameter of the intake opening is substantially equal to 0.3. This very low ratio is a necessity to achieve a speed close to Machi at the neck, this speed condition, mentioned in WO2006 / 054290, being the consequence of the use of a turbine for coupling to the electric generator. , said turbine being intended to recover a portion of the internal energy of the fluid by expansion in the turbine.
• the object of the invention is to provide an aerogenerator having increased overall efficiency.
• the aerogenerator according to the invention is remarkable in that: the rotary means is constituted by a second propeller rotatably mounted relative to the tubular body and configured to rotate in the opposite direction with respect to the first propeller, the ratio between the diameter of the neck and the diameter of the intake opening is between 0.6 and 0.8, the outer surface has a diverging section connected to the intake opening and a convergent section connected to the opening of exhaust, shaped to form a surface of revolution whose axis of revolution coincides with the axis of flow and a generating curve is formed by the extrados of an aircraft wing, a second reversible generating machine to which is connected to the first helix and connected to regulating means adapting the operation of the first helix as a function of at least one physical parameter related to the operation of the second helix ice.
• the aerogenerator according to the invention does not have the objective of recovering the internal energy of the fluid, merely considering the kinetic energy / pressure energy exchanges.
• the rotating means disposed near the neck and coupled to the first generating machine is constituted by a propeller which does not require a severe condition of air speed for its operation.
• the velocity at the neck is approximately equal to Mach 0.3, thanks to the relatively high ratio (between 0.6 and 0.8) between the neck diameter and the diameter of the inlet opening.
• This ratio can be even greater by the use of the outer surface in the form of Aircraft wing profile which greatly accelerates the flow of air sliding on the outer surface, without detachment of the flow through a suitable convergence angle, and generate a depression at the rear of the wind turbine sufficient to increase the velocity of fluid from the air passage.
• the operation of the first helix is conditioned to a physical parameter related to the second helix placed at the neck, which can vary between a fan operation, and a free operation for itself to generate energy by coupling. to a clean generator.
• FIG. 1 is an axial sectional view 2 is a left-hand view of the aerogenerator of FIG. 1;
• FIG. a view identical to Figure 1, but detailing the flow of air.
• the example of an aerogenerator comprises a tubular body 10 mounted to rotate along a vertical axis at the top of a supporting structure 11.
• the tubular body 10 has a general shape of revolution and therefore has an axis of revolution, which will subsequently correspond to the flow axis X of the air, rectilinear and horizontal.
• the orientation of the tubular body 10 with respect to the carrying structure 11 is practiced automatically, that is to say freely depending on the orientation of the wind, or by an orientation mechanism ensuring that the X axis of flow is collinear with the direction of the wind.
• the tubular body 10 defines a circular inlet opening OA, for the admission of air in windy conditions.
• the tubular body 10 delimits an escape opening OE of circular shape whose diameter may be slightly smaller than that of the intake opening OA ( as shown), even equal or slightly higher.
• the exhaust opening OE allows the air admitted by the intake opening OA to escape from the tubular body 10.
• the tubular body 10 has an outer surface 12 having an aerofoil shaped aircraft wing, with a bulge constituting a divergent section T1 from the inlet opening OA and along which the outer diameter increases gradually, and a convergent section T2 connecting the section T1 and the exhaust opening OE and along which the outer diameter decreases gradually.
• Such an aerodynamic profile has the effect of producing a vacuum at the OE exhaust opening.
• the outer surface 12 is therefore deprimogenic between the inlet opening OA and the exhaust opening OE.
• the sections T1 and T2 are shaped to form a surface of revolution whose axis of revolution coincides with the axis of flow X and a generating curve is formed by the extrados of an aircraft wing.
• the dimensional characteristics of the extrados can be adapted according to the expected natural wind speed (rope, camber, angle of attack, angle of convergence, angle of divergence, angle of leakage ).
• the tubular body 10 delimits internally an inner surface 13 having an aerodynamic profile in the form of wing-bottom, with a bulge constituting a convergent section T3 connected to the inlet opening OA and along which the internal diameter decreases progressively, and a diverging section T4 connecting the convergent section T3 and the exhaust opening OE and along which the inner diameter increases progressively.
• the two sections T3 and T4 of the inner surface 13 are connected by a neck 14.
• the inner surface 13 delimits an air passage 15 in the form of a nozzle connecting the openings OA and OE, and in which the air flows according to the flow axis X from the intake opening OA to escape through the exhaust opening OE.
• the ratio between the diameter of the neck 14 and the diameter of the inlet opening OA is between 0.6 and 0.8.
• the ratio between the axial length of the aerogenerator and the diameter of the intake opening OA is greater than 1, 4, preferably between 1, 5 and 2.
• the aerogenerator comprises a first helix H1 placed in the convergent section T3 and a rotating means placed at the neck 14 and converting the air flow movement at the neck 14 into a rotational movement of a shaft connected to a first machine generator G1.
• the rotary means is constituted by a second helix H2 rotatably mounted relative to the tubular body 10, in an axial position (along the X axis) near the neck 14.
• the second propeller H2 is connected to the first generating machine G1 by via a coupling means such as a fixed tube or a connecting shaft.
• the axis of rotation of the helices H2 and H1 coincides with the axis of flow X.
• the first generating machine G1 is an electrodynamic machine generating electric energy when its rotor is driven in a rotational movement relative to its axis. stator.
• the first helix H1 is rotatably mounted relative to the tubular body 10 upstream of the second helix H2, in an axial position (along the X axis) along the convergent section T3 of the inner surface 13.
• the first H1 propeller is linked to a second machine generating G2 reversible type. More specifically, the second generator machine G2 is a reversible electrodynamic machine.
• the diameter of the helix H1 is greater than that of the helix H2. It delimits, with the inner surface 13 and the propeller H2, a chamber for compression and acceleration CH of the air admitted through the opening OA. In the CH chamber, the air undergoes an increase in kinetic energy.
• the propellers H2 and H1 each comprise a plurality of blades angularly distributed in a variable pitch.
• the helix H2 is configured to rotate in the opposite direction with respect to the first helix H1.
• the aerogenerator comprises an electronic control device (see FIG. 3) comprising: regulation means 16 of the second reversible generator machine G2, by embedded example in the thickness of the tubular body 10, a sensor 17 measuring a physical parameter associated with the operation of the second helix H2, a power management system 18, for example integrated in the thickness of the tubular body 10, and connected energy storage means 19, and / or the electrical network 20 and external power supply means 21 in energy.
• the two generating machines G1 and G2 are electrically connected to the energy management system 18, respectively via connections marked 22 and 23.
• the energy management system 18 is electrically connected to the energy storage means 19 through a connection 24, and / or to the electrical network 20 via a connection 25 and to the external power supply means 21 via a connection 26.
• the regulation means 16 of the second generating machine G2 are electrically connected to the sensor 17 via a connection 27 and to the second generating machine G2 by a connection 28.
• the second generating machine G2 is reversible, it can be driving when it is supplied with electricity, its rotor then being rotated relative to its stator with the energy provided.
• the machine G2 can also operate as a generator: it generates electrical energy when the propeller H1 imposes on the rotor of the machine G2 a rotational movement relative to its stator.
• a not shown reversible coupling system (for example a centrifugal or electromagnetic clutch or by electrical control of the engine / generator of the machine G2) is interposed between the helix H1 and the second generator machine G2, in order to be able to ensure that the freely rotating H1 propeller is mounted in case of uncoupling.
• the connection 28 provides the connection between the coupling system and the regulation means 16.
• the propeller H1 When the propeller H1 is uncoupled from the generator machine G2, the propeller H1 is in "freewheeling" mode. In the opposite case, it is either in “motor” mode (corresponding to a motor operation of the generator machine G2), or in “generator” mode (corresponding to a generator operation of the generator machine G2).
• the purpose of the regulation means 16 is to select the mode of operation of the first propeller H1 ("motor”, “generator” or “free wheel") which is adapted at each instant.
• the selection, at any moment, of the operating mode of the H1 propeller makes it possible to adapt the operation of the first helix H1 as a function of at least one physical parameter (pressure, speed, temperature, etc.) measured by the sensor 17 and related to the operation of the second helix H2.
• the selection of the mode of the first propeller H1 is carried out by a corresponding action on the second generator machine G2 and on the coupling system, via the connection 28.
• the regulation means 16 can provide a modulation of the speed of rotation of the first propeller H1 as a function of the speed of rotation of the second propeller H2 measured by the sensor 17 when the latter is a tachometer.
• This type of modulation makes it possible in particular, in steady state, to avoid or at least to regulate the rotation of the air in the passage 15.
• the regulation means 16 integrate a first control law imposing on the first propeller H1: the "engine” mode as long as the rotation speed of the second helix H2 is less than a first predetermined threshold ⁇ 1, the "generator” mode when the rotational speed of the second helix H2 is greater than a second predetermined threshold ⁇ 2 greater than ⁇ 1, the "freewheel” mode when the rotational speed of the second helix H2 is between ⁇ 1 and ⁇ 2.
• the regulating means 16 may also incorporate a second control law, which has priority over the first control law, and imposes on the first propeller H1 the "motor" mode as soon as the difference between the rotational speed of the second propeller H2 and the rotation speed of the first helix H1 is greater than a third predetermined threshold ⁇ 3, itself possibly being a function of ⁇ 1.
• the operating mode of the first helix H1 is selected by the regulation means 16 via the connection 28, based on the information received from the sensor 17 via the connection 27.
• the energy management system 18 receives the electrical energy created by the first generating machine G1 via the connection 22.
• the energy management system 18 transmits the electrical energy required for the second generator machine G2 via the connection 23.
• the energy management system 18 receives the electrical energy produced by the second generator machine G2 via the connection 23.
• the energy management system produced 18 transmits the energy received from the first generating machine G1 (and possibly from the second generating machine G2 in the case of "generator” mode of the first helix H1) to the electrical network 20 by the connection 25 and / or the energy storage means 19 by the connection 24, and possibly receives, in case of "motor” mode of the first propeller H1, the energy needed for training the second generating machine G2 from the power grid 20 by the connection 25 and / or from the energy storage means 19 via the connection 24 and / or from the external power supply means 21 via the connection 26.
• the energy management system 18 comprises an interface between the signals exchanged with the generating machines G1, G2 and the signals exchanged with the electrical network 20, the energy storage means 19 and the means for external power supply 21.
• Such an interface may for example include transformers, frequency converters and rectifiers.
• the strategy carried out by the energy management system 18 with regard to its manner of ordering its exchanges with the other organs of the control device and with the two generators G1, G2 can be parameterized according to the applications.
• transmission to the electrical network 20 may be preferred in certain applications.
• the energy level in the storage means 19 and / or the management of consumption peaks will be preferred.
• the aerogenerator can be fictitiously decomposed into three successive zones A, B, C offset in the direction of the flow axis X and in the direction of passage of the air.
• the zone A of the aerogenerator corresponds to the part of the aerogenerator located between the plane passing through the opening of the The inlet OA and the plane passing through the end of the diverging section T1 of the outer surface 12.
• the zone B of the aerogenerator corresponds to the part of the aerogenerator between the zone A and the plane passing through the end of the section. Convergent T3 of the inner surface 13.
• the zone C of the aerogenerator is, in turn, constituted by the part of the aerogenerator between zone B and the plane passing through the exhaust opening OE. As illustrated in FIG. 4, the compression and acceleration chamber CH is included in the zone B of the aerogenerator.
• zone A whatever the mode of operation of the first helix H1, the flow of the air flow in the passage 15 is accelerated relative to the wind in which the wind turbine is placed.
• the flow of the airflow sliding on the outer surface 12 is also accelerated relative to the wind, but of a value lower than the acceleration experienced by the air in the passage 15.
• zone B the outside diameter decreases progressively, which has the effect of creating a depression and therefore an acceleration of the flow of the air flow sliding on the outer surface 12.
• the flow of the air flow in the passage 15 is also accelerated along the entire length of the zone B because of the convergent nature of the section T3. These inner and outer accelerations occur regardless of the operating mode of the first H1 propeller.
• the flow of the air flow in the passage 15 undergoes, parallel to its acceleration, a continuous and progressive increase in pressure along the entire length of zone B.
• the pressure increase is greater in chamber CH than on the rest of zone B, especially when the H1 propeller operates in the "engine" mode.
• zone C the flow of the airflow sliding on the outer surface 12 continues to accelerate.
• the inner diameter gradually increases to the OE exhaust opening which has the effect of creating an additional depression.
• zone D the air exiting through the exhaust opening OE is accelerated by the flow of the airflow sliding on the outer surface 12 which has a higher speed. This results in the creation of an additional depression behind the aerogenerator and a rejection of aerodynamic disturbances to the rear of the aerogenerator.
• the depression generated in zone D helps to maintain the process described previously. This global aerodynamic action makes it possible to accelerate the flow at the inlet of the aerogenerator.
• Photovoltaic cells 31 may be provided on all or part of the outer surface 12 to form the external power supply means 21. However, these means may be made by any suitable solution such as a hydraulic source or an auxiliary generator.
• the generating machines G1, G2 can be compact and arranged on the flow axis X.
• the generating machines G1, G2 can be in a ring, that is to say that the propellers H1, H2 associated itself constitutes the rotor of the generating machine G1, G2 and the stator is constituted by a peripheral ring carried vis-a-vis by the inner surface 13.
• an aerodynamic screen 30 extending axially between the helices H1, H2, for example having a cylindrical outer shape, to avoid aerodynamic disturbances near the X axis of flow. It is clear that such an aerodynamic screen 30 must maintain the mechanical uncoupling of the propellers H1, H2. In addition, it is possible to consider housing the second generating machine G2 inside the aerodynamic screen.
• the flow axis X is horizontal.
• the tubular body 10 has a depressing aerodynamic appendage 29 projecting from the outer surface 12 near the exhaust opening OE.
• This appendix 29 makes it possible to accentuate the acceleration subjected to the flow of the air flow sliding the convergent section T2 of the outer surface 12, and considerably reduces the noise produced by the flow of air on the outer surface 12.
• the "parachute" effect (appearance of turbulence at the outlet of the tubular body 10) occurs for much higher wind speeds than in the absence of appendix 29.
• the aerodynamic screen performs a centrifugal deviation of the flow relative to the X axis, further increasing the depression at the rear of the turbine. In other words, it generates a divergence of the air flow sliding on the outer surface 12 and an air depression behind the wind turbine.
• the aerodynamic appendix 29 has the shape of a ring held at a distance around the tubular body 10 and having an inner face facing the outer face 12, and an opposite outer face.
• the inner face of the crown has a convex aerodynamic profile with a bulge directed towards the outer surface 12, while the outer face of the crown has a concave aerodynamic profile with a hollow directed towards the outer surface 12.
• the ratio between the diameter of the aerodynamic appendix 29 and the diameter of the intake opening OA is less than 1.3, to limit the overall size of the wind turbine.
• control device described above can include functions to perform economic and energy assessments and maintenance forecasts.
• wind turbines according to the invention can be assembled in horizontal cascades, on a circular axis and / or on different axes and planes.
• a radiofrequency device can be associated with each wind turbine.
• the aerogenerator according to the invention does not use the internal energy of the air passing through the passage 15. The whole flow remains, whatever the operation, Mach less than 0.3. Mainly, only the kinetic energy / pressure energy exchanges are considered, neglecting in practice the internal energy variations of the fluid.
• the H1 propeller is used to accelerate the flow in engine mode, for low winds only. This operation triggers the start of the H2 propeller and makes it possible to operate more efficiently with low winds. Indeed, in this operating range the flow being higher, the second propeller H2 has a significantly better performance. This type of operation is imposed as long as the sum of the energies supplied by the helix H1 and consumed by the helix H2 is greater than the sum of the energies supplied by the two propellers both operating as generators.
• the convergence of the internal flow is used to increase the axial velocity of the flow without substantially increasing the density of the air: the higher velocity at the neck makes it possible to use a faster H2 helix, with a better efficiency.
• the helix H1 in generating operation, uses the wind energy linked to the axial component of the speed and restores a speed having a component in rotation (Euler relation). This rotating component is recovered by the helix H2 which restores a purely axial flow at the device outlet. Without the helix H1, the speed of the flow at the output of the helix H2 would necessarily have a component in rotation (Euler relation). The corresponding kinetic energy would then be lost.
• contra-rotating H1, H2 propellers have better performance than a single H2 propeller, despite the greater friction losses.
• the shape of the inner surface 12, the shape of the inner surface 13, the choice to take a helix constituting the rotary means to the neck, and the choice of a neck with a relatively small constriction, are chosen to reduce the point of attack. as close as possible to the OA inlet opening, contrary to the prior art.

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• Engineering & Computer Science (AREA)
• Life Sciences & Earth Sciences (AREA)
• Sustainable Development (AREA)
• Sustainable Energy (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Power Engineering (AREA)
• Wind Motors (AREA)
• Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
• Jet Pumps And Other Pumps (AREA)

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• 2007
  • 2007-10-11 FR FR0707124A patent/FR2922272A1/fr not_active Withdrawn
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  • 2008-10-10 WO PCT/FR2008/001425 patent/WO2009087288A2/fr active Application Filing
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