WO2018176004A1 - Rotor de production d'énergie éolienne avec diffuseur ou système de déviation pour une éolienne - Google Patents

Rotor de production d'énergie éolienne avec diffuseur ou système de déviation pour une éolienne Download PDF

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Publication number
WO2018176004A1
WO2018176004A1 PCT/US2018/024203 US2018024203W WO2018176004A1 WO 2018176004 A1 WO2018176004 A1 WO 2018176004A1 US 2018024203 W US2018024203 W US 2018024203W WO 2018176004 A1 WO2018176004 A1 WO 2018176004A1
Authority
WO
WIPO (PCT)
Prior art keywords
diverter
rotor
diverters
power generating
wind power
Prior art date
Application number
PCT/US2018/024203
Other languages
English (en)
Inventor
Carsten Hein Westergaard
Søren HJORT
Original Assignee
Hover Energy, LLC
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 Hover Energy, LLC filed Critical Hover Energy, LLC
Publication of WO2018176004A1 publication Critical patent/WO2018176004A1/fr

Links

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 
    • F03D3/04—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
    • F03D3/0427—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 with converging inlets, i.e. the guiding means 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 
    • F03D3/04—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
    • 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
    • F03D3/0409—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 surrounding the rotor
    • F03D3/0418—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 surrounding the rotor comprising controllable elements
    • 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
    • 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

  • Figure 22 illustrates a cross section of a VAWT with a single curved plate internal diverter
  • Figure 51 illustrates the overall system efficiency (shown as the relative power coefficient) as a function of the gap size (the gap size is normalized to the rotor diameter) based on system modeling of which results of FIG. 50 is a subset of illustrations to the effects;
  • Figure 52 illustrates a computation result of a wind power generating rotor system according to the present disclosure without a gap
  • Figure 54 depicts another embodiment of a wind power generating rotor system according to the present disclosure
  • the ratio between the rotor area A roto r, i.e., the area of the circle defined by rotation of the rotor blades around the axis of the rotor, and the exit area A ex i t , i.e., the area through which wind exiting the rotor area passes, is called the expansion ratio. It has been shown that the above statements concerning Betz hold accurate, and the rotor based C p is dependent on the expansion ratio. It is understood that height of the rotor and the exit area is implied when one references this as an area, and is left out of the description for convenience.
  • Geurts et. al. (2010) provides computation of a rotor between two airfoils, for a configuration very similar to Watanabe. Here, details of the forces acting on the individual surfaces are illustrated. The forces on the rotor blades for the shrouded versus the free rotor exhibit similarities and, when aggregated, results in the proportional relationship between a free and shrouded rotor as discussed above.
  • the present inventors realized that one way of improving the performance of a drag-based rotor is to shield the stroke of the rotation which is going against the wind, basically eliminating (or more correctly minimizing) the negative force on the airfoil rotor in parts of the rotation cycle (see again Figure 6).
  • a drag-based rotor is shielded minimizing the negative work in the return stroke, defined from approximately 240 to 360 degrees, continuing from 0 to 60, in Figure 6 (note also Figure 11).
  • One important aspect of some embodiments of the diverter assemblies described herein is the combination of inner diverters and the return stroke shielding.
  • the inner diverters' upwards induced lift in Figure 6 essentially makes the air completely still in the return stroke significantly, or almost completely, eliminating the potential losses.
  • the present inventors realized, based on the above research and analysis, that the principle of getting more power out of a "drag-based" rotor is a combination of adequately shielding the return stroke, amplifying the torque stroke with high speed up effects, amplifying the speed up effects in the work stroke, modifying the return path so as not to have negative impact.
  • the inventors further realized that one successful approach to expand the operational envelope of such a system is an
  • a lift-based rotor may not benefit as much from a throat-like design using multiple stacked inner diverters, so such may be left out of the design configuration (note Figure 16).
  • one or more inner diverter may be used to deflect wind from a rotation shaft (note, for example, Figures 41-43).
  • FIG. 32 illustrates a horizontal section of most components of the embodiment of FIG. 10.
  • rotor system provides a rotor assembly 1010 and a diverter assembly 1020.
  • the rotor assembly has a rotor axis 1030, typically arranged vertically, and a plurality of rotor blades 1040.
  • the rotor blades 1040 are structured and arranged for rotation around the rotor axis 1030 along a rotation path 1050 in response to wind passing the rotor blades. Accordingly, the rotor assembly 1010 captures kinetic energy from wind.
  • the plurality of diverters are arranged outside the rotation path 1050, and the diverter assembly may be symmetric, or quasi-symmetric.
  • the plurality of diverters may comprise at least one primary diverter 1060, or in the embodiment shown, two primary diverters 1060a, b.
  • the plurality of diverters may further comprise flap diverters 1070, in this case, each of the primary diverters 1060a, b, has three associated flap diverters 1070a, b, c.
  • the flap diverters will be referred to herein based on the primary diverter from which it extends, referring to flap diverter 1070ab as the "b" flap diverter associated with the "a" primary diverter.
  • a gap 1080 is typically provided between the diverters of the assembly, such that air can pass between a primary diverter 1060 and its associated flap diverters 1070, and between the secondary diverters themselves. Further, as shown, a leading edge 1100 of the first flap diverter 1070aa in a sequence is adjacent the trailing edge 1110 of the corresponding primary diverter 1060a.
  • slot diverters 1120 are provided and associated with each of the primary diverters. Accordingly, the slot diverter 1120a associated with the first of the primary diverters 1060a is adjacent the leading edge 1090 of the corresponding primary diverter.
  • a top endplate 1130 and a bottom endplate 1140 may be located perpendicular to the rotor axis 1030. These endplates 1130, 1140 may be shaped to function as diverters as well. Accordingly, while most embodiments shown and discussed herein are shown in two dimensions, it will be understood that three dimensional embodiments are contemplated as well. Some examples of such
  • the flap diverters 1070 are connected to the primary diverters, while in others they are positioned near the primary diverters by a separate superstructure.
  • the endplates 1030, 1040 may retain the various diverters, or extensions 1170 of the endplates may be provided for locating the diverters.
  • the design of the diverter assembly 1020 and the placement of the individual diverters may be optimized to increase an expansion ratio of the rotor system.
  • the expansion ratio A e xit/A rot or is based on the ratio of the rotor area A roto r, shown as 1150 and an exit area A ex i t , shown as 1160.
  • the number of flap diverters 1070 may be increased specifically in order to allow for an expansion of the exit area A exit , which in turns increase the expansion ratio.
  • FIGS. 11, 13-20 a wide variety of asymmetric configurations for a diverter assembly 2020 for a wind power generating rotor system 2000 are contemplated.
  • the rotor system 2000 provides a rotor assembly 2010 and a diverter assembly 2020.
  • the rotor assembly 2010 has a rotor axis 2030, typically arranged vertically, and a plurality of rotor blades 2040.
  • the rotor blades 2040 are structured and arranged for rotation around the rotor axis 2030 along a rotation path 2050 in response to wind passing the rotor blades.
  • the rotor assembly 2010 captures kinetic energy from wind.
  • the diverter assembly 2020 typically comprises a primary diverter 2060 and a secondary diverter 2070, as well as at least one flap diverter 2080. Further, in many asymmetric configurations, the diverter assembly further comprises at least one internal diverter 2090 located within the circle formed by the rotation path 2050 of the rotor blades 2040.
  • the primary diverter 2060 and the secondary diverter 2070 are located opposite the rotor assembly 2010 from each other, and they have different profiles from each other.
  • the flap diverters 2080 are located in the lee of the primary diverter 2060. While the primary diverter 2060 may not be shaped as a typical airfoil, it still has a leading edge 2100, which is the edge first encountered by
  • the primary diverter 2060 may, in combination with an internal component 2120 of the diverter assembly, form an airfoil shape enveloping at least part of the rotation path 2050.
  • the primary diverter 2060 has an airfoil shape that abuts the rotation path 2050, and the rotation path passes through and disrupts a portion of the airfoil shape.
  • the inner diverter 2090 may take the form of one or more airfoils.
  • the asymmetric configurations are usually illustrated with rotor blades 2040 shown in the drag based configuration, with the rotor blades substantially perpendicular to the perimeter of the rotation path 2050.
  • FIG. 16 this is because the asymmetric configuration is designed to direct airflow towards the blades in a workstroke flow zone, i.e., where the wind interacts with the scooped side of the blade, and to shield the return stroke of the blades.
  • the symmetric configurations are usually illustrated with rotor blades 1040 shown in a lift based configuration, with the rotor blades substantially tangential to the perimeter of the rotation path 1050.
  • the predetermined gap 3000 is between approximately 3.5% and 25% of a diameter 3010 of the perimeter of the rotation path 2050. In some embodiments, the predetermined gap 3000 is approximately 15% of the diameter 3010 of the rotation path 2050.
  • diverter structures may be provided with flexibility, such that abnormal and gusting winds result in an automatic adjustment of the gap 3000.
  • tight tolerances may be maintained between the primary diverter 2060 and the perimeter of the rotation path 2050, while a gap may be provided between the secondary diverter 2080 and the rotation path 2050.
  • the gap between the rotor and the diverter is defined between the rotor circumference and the diverter where the gap is 25%>X>3.5% of the rotor diameter. If the rotor diameter is 2000 mm, the gap should be bigger than 75 mm. For example, the optimum gap may be 250 mm on a 2000 mm rotor.
  • performance may be selected. This could for example be from the well-known
  • the diverters may be slotted, such that the aerodynamic shape of one or both of the two sides is composed by a sequence of airfoils instead of just one airfoil.
  • Arranging airfoils in a carefully geometrically designed sequence is done in order to exploit the flap-effect, i.e., to allow a certain amount of by-pass flow through the channel s/slots such that a higher overall curvature of the flow can be obtained without stalling the flow.
  • the higher curvature of the airfoil sequence will deflect the flow more, and thereby create more lift (i.e., more suction) of the flow through the rotor positioned in the throat of the diverter system, enhancing the mass-flow-rate and increasing potential for power extraction. Exploitation of the flap-effect is known from, e.g., the aircraft industry, where commercial aircrafts use flaps to increase the lift-force upon take-off and landing.
  • the air mixing which occurs in the gaps provides the high lift of the diverter, which in turn gives high speed up and thereby high efficiency of the embedded rotor.
  • the bypass flow also supports stabilization of the wake region behind the rotor.
  • the "wake region” is used in two senses here, the first of which is that of the airfoils and diverters themselves. The second sense is the wake region for the wake produced by the rotor power extraction efforts. The two are closely related to the joint and entire system performance. This is a function which is normally not effective in a multi-element airfoil, such as on an airplane wing.
  • Figure 14 illustrates a cross section of a slotted asymmetric diverter VAWT with a double slotted 2150 high-lift diverter assembly comprising a primary diverter 2060 and two flap diverters 2080.
  • the embodiment further comprises a low-lift secondary diverter airfoil 2070.
  • a high-velocity work-stroke flow zone 2220 and a low- velocity work-stroke flow zone 2230 are indicated in Figure 14 as well.
  • Figure 22 illustrates a cross section of a VAWT with a single curved plate internal diverter 4010.
  • Figure 27 illustrates a cross section of a VAWT with multiple curved plates 4040a, b, c, d combining to form an internal diverter assembly 4050.
  • Figure 47 shows a gap between the outer perimeter defined by rotation of the rotor blades in this embodiment drag-based rotor blades and the opposing outer surfaces of external diverters for a slotted asymmetric diverter assembly VAWT.
  • Figure 48 illustrates air flow entering a gap between the outer perimeter defined by rotation of the rotor blades (in this embodiment drag-based rotor blades) and the opposing outer surfaces of external diverters for an asymmetric diverter assembly VAWT (the solid line circles indicate the inner and outer perimeters of the rotor blades as the rotor blades rotate around the vertical axis of the rotor assembly).
  • Figure 50 is a graph showing the idealized potential losses from the gap introduction as a function of the diverter location (the gap size is the diverter location minus 1 in this graph);
  • Figure 51 illustrates the overall rotor efficiency (shown as the relative power coefficient) as a function of the gap size (the gap size is normalized to the rotor diameter);
  • Figure 59 illustrates a cross section of an asymmetric diverter assembly perpendicular-axis HAWT with airfoil-shaped rotor blades and with a different number of rotor blades and internal diverters, than the embodiment depicted in Figure 58, on a rooftop.
  • Figure 60 illustrates a cross section of an asymmetric diverter assembly perpendicular-axis HAWT with a differently configured diverter assembly, than the embodiments depicted in Figures 58 and 59, on a roof-top.
  • Figure 61 illustrates an asymmetric diverter assembly perpendicular-axis HAWT on a rooftop as seen in perspective.
  • a horizontal-axis low TSR wind turbine is provided. This may be, for example, a rooftop mounted low TSR horizontal-axis wind turbine with asymmetric diverter, oriented perpendicular to the wind direction. Two features are characteristic of this embodiment:

Abstract

L'invention concerne un système de rotor de production d'énergie éolienne pour une éolienne. Le système de rotor comprend un ensemble rotor ayant un axe de rotor et une pluralité de pales de rotor structurées et agencées pour une rotation autour de l'axe de rotor par passage du vent à travers des pales de rotor, ce qui permet de capturer l'énergie cinétique du vent. Un ensemble déflecteur est pourvu d'une pluralité de déflecteurs structurés et disposés à l'intérieur et à l'extérieur d'un périmètre défini par la rotation des pales de rotor, ce qui permet d'augmenter la puissance du système de rotor.
PCT/US2018/024203 2017-03-23 2018-03-23 Rotor de production d'énergie éolienne avec diffuseur ou système de déviation pour une éolienne WO2018176004A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201762475344P 2017-03-23 2017-03-23
US62/475,344 2017-03-23

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WO2018176004A1 true WO2018176004A1 (fr) 2018-09-27

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU13907A1 (ru) * 1929-05-16 1930-03-31 Ф.В. Лузалов Ветр ный двигатель
SU34409A1 (ru) * 1933-03-19 1934-01-31 А.П. Давыдов Ветр ный двигатель с двум и четырьм ветр ными колесами
RU2391554C1 (ru) * 2009-02-05 2010-06-10 Борис Львович Историк Низконапорная ортогональная турбина
US20120029627A1 (en) * 2003-12-23 2012-02-02 Sadra Medical, Inc. Methods and Apparatus for Endovascular Heart Valve Replacement Comprising Tissue Grasping Elements
US20140356157A1 (en) * 2013-05-30 2014-12-04 Universal Wind Power, Llc Wind turbine device with diverter panels and related systems and methods

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU13907A1 (ru) * 1929-05-16 1930-03-31 Ф.В. Лузалов Ветр ный двигатель
SU34409A1 (ru) * 1933-03-19 1934-01-31 А.П. Давыдов Ветр ный двигатель с двум и четырьм ветр ными колесами
US20120029627A1 (en) * 2003-12-23 2012-02-02 Sadra Medical, Inc. Methods and Apparatus for Endovascular Heart Valve Replacement Comprising Tissue Grasping Elements
RU2391554C1 (ru) * 2009-02-05 2010-06-10 Борис Львович Историк Низконапорная ортогональная турбина
US20140356157A1 (en) * 2013-05-30 2014-12-04 Universal Wind Power, Llc Wind turbine device with diverter panels and related systems and methods

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