CN110821761A - Vortex generator and blade - Google Patents

Vortex generator and blade Download PDF

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Publication number
CN110821761A
CN110821761A CN201911154786.1A CN201911154786A CN110821761A CN 110821761 A CN110821761 A CN 110821761A CN 201911154786 A CN201911154786 A CN 201911154786A CN 110821761 A CN110821761 A CN 110821761A
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CN
China
Prior art keywords
preset
base
vortex generator
orthographic projection
partition
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Pending
Application number
CN201911154786.1A
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Chinese (zh)
Inventor
乔玉军
王向东
李成良
毛晓娥
丁惢
任旺
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sinomatech Wind Power Blade Co Ltd
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Sinomatech Wind Power Blade Co Ltd
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Publication date
Application filed by Sinomatech Wind Power Blade Co Ltd filed Critical Sinomatech Wind Power Blade Co Ltd
Priority to CN201911154786.1A priority Critical patent/CN110821761A/en
Publication of CN110821761A publication Critical patent/CN110821761A/en
Priority to PCT/CN2020/127296 priority patent/WO2021089019A1/en
Pending legal-status Critical Current

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    • 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
    • F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0025—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply
    • F15D1/003—Influencing flow of fluids by influencing the boundary layer using passive means, i.e. without external energy supply comprising surface features, e.g. indentations or protrusions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/97—Reducing windage losses
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Wind Motors (AREA)

Abstract

The embodiment of the invention provides a vortex generator and a blade. The vortex generator includes: a base comprising a first side and a second side; a wing disposed at a first side of the base at a predetermined angle; the wing panel is provided with a first preset partition and a second preset partition in the length direction of the base part, a first curve formed by orthographic projection of the wing panel on the base part corresponding to the first preset partition and a second curve formed by orthographic projection of the wing panel on the base part corresponding to the second preset partition are respectively positioned on two sides of a reference line, and the reference line is a connecting line between a first end point of the wing panel and a second end point of the wing panel. According to the vortex generator and the blade provided by the embodiment of the invention, the generation of parasitic resistance can be reduced in the rotating process of the blade provided with the vortex generator provided by the embodiment of the invention, so that the airfoil lift-drag ratio of a wind turbine is improved, and the output power of a wind driven generator is improved.

Description

Vortex generator and blade
Technical Field
The invention relates to the technical field of wind power generation, in particular to a vortex generator and a blade.
Background
The middle part to the root part of the large-scale wind driven generator blade generally needs to adopt the special airfoil profile of the large-thickness wind turbine to ensure the structural strength of the blade, however, the aerodynamic performance of the large-thickness airfoil profile is poor, and the separation of airflow is almost inevitable under the condition of a large power angle. Therefore, it is common to install vortex generators on the blades to delay or prevent the premature separation of the airflow at the blade surface to increase the output power of the wind turbine.
Although the vortex generators can reduce the pressure difference resistance generated by the airflow separation to a certain extent, the vortex generators still bring additional parasitic resistance to the blade to a certain extent because the vortex generators are installed on the surface of the blade. The vortex generators have different structures and can generate different parasitic resistance, and only when the parasitic resistance generated by the vortex generators is smaller than the pressure difference resistance generated by air flow separation, the airfoil lift-drag ratio of the blade can be improved, so that the output power of the wind driven generator is improved.
Therefore, it is an urgent need to provide a vortex generator that can reduce parasitic resistance when mounted on a blade and improve the output power of a wind turbine generator.
Disclosure of Invention
The embodiment of the invention provides a vortex generator and a blade, which can reduce parasitic resistance and further improve the output power of a wind driven generator.
In a first aspect, there is provided a vortex generator comprising:
a base;
the fins are arranged on the same side of the base at a preset angle;
the wing panel is provided with a first preset partition and a second preset partition in the length direction of the base part, the curve length of the wing panel in the first preset partition, a first curve formed by orthographic projection of the wing panel on the base part corresponding to the first preset partition and a second curve formed by orthographic projection of the wing panel on the base part corresponding to the second preset partition are respectively positioned on two sides of a reference line, and the reference line is a connecting line between the first end point of the wing panel and the second end point of the wing panel.
In the embodiment of the invention, the bottom edge of the wing is arranged in the length direction, and the design of the nonlinear function is carried out, so that the parasitic resistance generated by the vortex generator can be reduced, the lift-drag ratio of the wing profile is further improved, and the output power of the wind driven generator is improved.
In some realizations of the first aspect, the farthest distance r1 between a point on the first curve and the reference line and the farthest distance r2 between a point on the second curve and the reference line satisfy: r1 ═ k1 ═ r2, where k1 is a positive number.
In some realizations of the first aspect, the vortex generator further comprises:
the height of the wing panel is provided with a third preset subarea, a fourth preset subarea and a fifth preset subarea in the length direction of the base part;
the height parameter of the wing piece at the first endpoint of the third preset partition and the length of the extended distance of the corresponding wing piece from the starting end face to the corresponding first endpoint in the orthographic projection of the base part meet a first preset function;
the height parameter of the wing panel at the second endpoint of the fourth preset partition and the length of the extended distance of the corresponding wing panel from the starting end face to the corresponding second endpoint in the orthographic projection of the base part meet a second preset function;
the height parameter of the wing panel at the third end point of the fifth preset partition and the length of the orthographic projection of the extending distance of the corresponding wing panel from the starting end face to the corresponding third end point on the base part satisfy a third preset function.
In the embodiment of the invention, the parasitic resistance generated by the vortex generator can be reduced by the nonlinear design of the wing pieces in the height direction, so that the lift-drag ratio of the wing type is improved, and the output power of the wind driven generator is improved.
In some implementations of the first aspect, the first preset partition further includes: a first sub-partition and a second sub-partition; and the orthographic projection of the wing panel on the base part corresponding to the first sub-partition is superposed with the reference line.
In some implementations of the first aspect, the first preset function is a power function.
In some implementations of the first aspect, the second preset function and/or the third preset function is a quadratic function.
In a second aspect, there is provided a vortex generator comprising:
a base;
the fins are arranged on the same side of the base at a preset angle;
the wing panel is provided with a first preset partition and a second preset partition in the length direction of the base part, the orthographic projection of the wing panel on the base part corresponding to the second preset partition is positioned on one side departing from a first reference line, and the first reference line is a connecting line between the first end point and the second end point of other wing panels on the base part.
In some implementations of the second aspect, an orthographic projection of the flap at the base corresponding to the second predetermined division is a polyline or curve.
In some implementations of the second aspect, an orthographic projection of the airfoil at the base corresponding to the first predetermined partition coincides with a second reference line, the second reference line being a connection line between the first end point of the airfoil and the second end point of the airfoil.
In some implementations of the second aspect, an orthographic projection of the tab at the base corresponding to the first predetermined division is located on a side facing away from the first reference line.
In some implementations of the second aspect, an orthographic projection of the flap at the base corresponding to the first predetermined division is a polyline or curve.
In some realizations of the second aspect, the farthest distance r1 between a point of the tab on the orthographic projection of the corresponding base portion of the first preset partition and the second reference line and the farthest distance r2 between a point of the tab on the orthographic projection of the corresponding base portion of the second preset partition and the second reference line satisfy: r1 ═ k1 ═ r2, where k1 is a positive number.
In a third aspect, a blade is provided, the blade comprising the vortex generator provided in the first or second aspect.
The vortex generator and the blade provided by the embodiment of the invention can reduce the generation of parasitic resistance in the rotating process of the blade provided with the vortex generator provided by the embodiment of the invention, thereby improving the airfoil lift-drag ratio of a wind turbine and improving the output power of a wind driven generator.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments of the present invention will be briefly described below, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 illustrates a top view of a vortex generator according to an embodiment of the present invention;
FIG. 2 illustrates a schematic shape of the bottom edge of a fin of a vortex generator according to an embodiment of the present invention;
FIG. 3 shows a schematic shape of the bottom edge of a fin of a vortex generator according to another embodiment of the invention;
fig. 4 shows a schematic view of the shape of the fins of a vortex generator according to an embodiment of the invention in height direction;
FIG. 5 is a schematic view showing an orthographic projection of a tab at a corresponding base of a second predetermined area provided by an embodiment of the present invention;
FIG. 6 is a schematic view showing an orthographic projection of a tab at a corresponding base of a second predetermined area according to another embodiment of the present invention;
FIG. 7a is a schematic diagram showing an orthographic projection of the corresponding base of the airfoil provided by one embodiment of the present invention;
FIG. 7b is a schematic view showing an orthographic projection of the corresponding base of the airfoil provided by another embodiment of the present invention;
FIG. 7c is a schematic view showing an orthographic projection of the corresponding base of the tab according to still another embodiment of the present invention.
Detailed Description
Features and exemplary embodiments of various aspects of the present invention will be described in detail below, and in order to make objects, technical solutions and advantages of the present invention more apparent, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not to be construed as limiting the invention. It will be apparent to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The special airfoil profile for the large-thickness wind turbine is adopted from the middle part to the root part of the blade of the wind driven generator to ensure the structural strength of the blade, so that the separation of airflow can be caused under the condition of a large power angle, and the output power of the wind driven generator is further reduced.
Therefore, vortex generators are often installed on the blades of wind turbines to delay or resist the premature separation of the airflow at the blade surface, but due to their presence, they still generate additional parasitic drag to some extent on the blade. The vortex generators have different structures and can generate different parasitic resistance, and only when the parasitic resistance generated by the vortex generators is smaller than the pressure difference resistance generated by air flow separation, the airfoil lift-drag ratio of the blade can be improved, so that the output power of the wind driven generator is improved.
Therefore, the embodiment of the invention provides a vortex generator and a blade, which can generate less parasitic resistance when the vortex generator is installed on the blade, and further improve the output power of a wind driven generator.
The vortex generator and the blade provided according to the embodiment of the invention are described below with reference to the accompanying drawings. It should be noted that these examples are not intended to limit the scope of the present disclosure.
A vortex generator according to an embodiment of the present invention is described in detail below with reference to fig. 1.
In order to better understand the technical solution of the present invention, a vortex generator according to an embodiment of the present invention is described in detail below with reference to fig. 1, and fig. 1 is a plan view illustrating the vortex generator according to an embodiment of the present invention.
As shown in fig. 1, the vortex generator in the embodiment of the present invention includes:
a base 10, wherein the base 10 comprises a first side and a second side. For example, the first side may be the side of the base portion that is closer to the blade and the second side may be the side of the base portion that is further from the blade.
A flap 20 and a flap 30, wherein the flap 20 and the flap 30 are disposed at a predetermined angle on a first side of the base 10. For example, the wing 20 and the wing 30 may be disposed at a predetermined angle on both sides of the first side of the base 10 as shown in fig. 1.
In one embodiment of the present invention, it may be that the bottom edge of the flap 20 and the bottom edge of the flap 30 have a first predetermined division and a second predetermined division in the length direction of the base, with respect to the bottom edge arrangement of the flap. For example, the base length corresponding to the first predetermined partition may be 2-4 times the base length corresponding to the second predetermined partition. For example, the ratio of the base length corresponding to the first predetermined partition to the base length corresponding to the second predetermined partition is 8: 2. That is, 0% to 80% of the length of the base may be taken as the first preset partition, and 80% to 100% of the length of the base may be taken as the second preset partition.
Further, a connecting line between two end points (a first end point and a second end point) of the tab may be used as a reference line, and a first curve formed by orthographic projection of the tab on the base corresponding to the first preset partition and a second curve formed by orthographic projection of the tab on the base corresponding to the second preset partition are respectively located on two sides of the reference line.
According to the vortex generator provided by the embodiment of the invention, the first curve formed by the orthographic projection of the wing piece on the base part corresponding to the first preset partition and the second curve formed by the orthographic projection of the wing piece on the base part corresponding to the second preset partition are respectively positioned on the two sides of the reference line, so that the generation of parasitic resistance can be effectively reduced in the rotating process of the blade, the wing type lift-drag ratio of a wind turbine is further improved, and the output power of a wind driven generator is improved.
As shown in fig. 2, fig. 2 is a schematic view illustrating the shape of the bottom edge of the tab according to an embodiment of the present invention. The farthest distance r1 between a point on the first curve and the reference line and the farthest distance r2 between a point on the second curve and the reference line satisfy: r1 ═ k1 ═ r2, where k1 is a positive number.
In one embodiment of the invention, k1 may be such that: k1 is an element [ 2-6 ]
For example, the second curve formed by the orthographic projection of the tab at the base corresponding to the second predetermined segment may be a partial arc having a radius of 10 centimeters (cm), it being understood that the center of the circle may not lie on the reference line.
Furthermore, as an example, the point of the foil on the first curve which is furthest away from the reference line should be located within the projected area of the reference line in the direction of the wind. Likewise, the point of the airfoil on the second curve which is furthest from the second reference line should be located within the projected area of the reference line in the direction of the wind.
Further, the first curve and the second curve may be quadratic functions satisfying a preset condition. For example, the first curve satisfies the function:
S4＝k4*x(x-a) (1)
the second curve may satisfy the function of:
S5＝k5*(x-b)(x-c) (2)
in one embodiment of the present invention, the first curve and the second curve may also satisfy a cubic function.
In the embodiment of the invention, the first curve and the second curve formed in the length direction based on the wing pieces are curves formed according to the nonlinear function, so that the parasitic resistance generated by the vortex generator can be reduced, the lift-drag ratio of the wing profile is further improved, and the output power of the wind driven generator is improved.
In an embodiment of the present invention, the first preset partition may be further divided into a first sub-partition and a second sub-partition.
The base length corresponding to the second sub-partition may be 1-2 times the base length corresponding to the first sub-partition. For example, the ratio of the base length corresponding to the first sub-partition to the base length corresponding to the second sub-partition is 1: 1. That is, 0% to 45% of the base length may be defined as the first subdivision, and 45% to 80% of the base length may be defined as the second subdivision.
For example, as shown in fig. 3, fig. 3 shows a schematic shape of the bottom edge of a tab provided by another embodiment of the present invention.
And the orthographic projection of the wing panel on the base part corresponding to the first sub-partition is superposed with the reference line.
In the embodiment of the invention, the bottom edge of the wing panel is arranged in the length direction, and the combination design of the linear function and the nonlinear function is carried out, so that the parasitic resistance generated by the vortex generator can be reduced, the lift-drag ratio of the wing profile is further improved, and the output power of the wind driven generator is improved.
In one embodiment of the present invention, as for the height setting of the wing, it may be that the height of the wing 20 and the height of the wing 30 have a third preset partition, a fourth preset partition and a fifth preset partition in the length direction of the base.
In one embodiment of the present invention, a length of an orthographic projection of the third preset partition of the vane in the longitudinal direction of the base, a length of an orthographic projection of the fourth preset partition of the vane in the longitudinal direction of the base and a length of an orthographic projection of the fifth preset partition of the vane in the longitudinal direction of the base are put in a ratio of 3:12: 5.
For example, 0% to 15% of the length of the base portion may be defined as a third predetermined section of the height of the fin in the longitudinal direction of the base portion, 15% to 75% of the length of the base portion may be defined as a fourth predetermined section of the height of the fin in the longitudinal direction of the base portion, and 75% to 100% of the length of the base portion may be defined as a fifth predetermined section of the height of the fin in the longitudinal direction of the base portion.
In one embodiment of the invention, the height parameter of the wing at the first end point of the third preset partition and the length of the orthographic projection of the extending distance of the corresponding wing from the starting end face to the corresponding first end point on the base part satisfy a first preset function;
the height parameter of the wing panel at the second endpoint of the fourth preset partition and the length of the extended distance of the corresponding wing panel from the starting end face to the corresponding second endpoint in the orthographic projection of the base part meet a second preset function;
the height parameter of the wing panel at the third end point of the fifth preset partition and the length of the orthographic projection of the extending distance of the corresponding wing panel from the starting end face to the corresponding third end point on the base part satisfy a third preset function.
In an embodiment of the invention, the first preset function, the second preset function and the third preset function may be nonlinear functions.
In one embodiment of the present invention, as shown in fig. 4, fig. 4 shows a schematic shape view of a fin of a vortex generator according to an embodiment of the present invention in a height direction. Wherein the first preset function may be a power function.
For example, the first preset function S1 may be as shown in expression (3):
S1＝xn，n∈(1/6,1/2) (3)
wherein x is the extension distance of the fin from the starting end surface to the corresponding first end point.
In one embodiment of the present invention, the second preset function may be a quadratic function, for example, the second preset function S2 may be as shown in expression (4):
S2＝k2*(x-e)(x-f)，e∈(-0.6,-0.5)，f∈(1,1.1) (4)
wherein x is the extension distance of the fin from the starting end surface to the corresponding second end point.
For example, k2 may be 0.001.
In one embodiment of the present invention, the third preset function may be a quadratic function, for example, the third preset function S3 may be as shown in expression (5):
S3＝k3*(x-g)(x-h)，g∈(-0.8,-0.7)，h∈(3,4) (5)
wherein x is the extending distance between the starting end surface and the corresponding third end point of the fin.
For example, k3 may be 0.001.
In one embodiment of the present invention, the opening interval between the wing 20 and the wing 30 may be set to 0.3 to 0.5 times the wing length, and the wing length may be set to 0.2 to 0.3 times the chord length of the local section. The local section chord length may be obtained by cutting the blade along the length direction of the blade, selecting a preset number of profiles, and taking the average value of the preset number of profile chord lengths as the local section chord length.
By the nonlinear design of the fins in the height direction, parasitic resistance generated by the vortex generator can be reduced, so that the lift-drag ratio of the airfoil profile is improved, and the output power of the wind driven generator is improved.
The vortex generator provided by the embodiment of the invention can delay and prevent the premature separation of the airflow on the surface of the blade, reduce the generation of parasitic resistance and improve the output power of the wind driven generator.
In addition, in another embodiment of the invention, another vortex generator is provided. The vortex generator also includes a base and two fins. The two fins are respectively a first fin and a second fin. The first wing piece and the second wing piece are arranged on the same side of the base portion at preset angles respectively, and both the first wing piece and the second wing piece are provided with a first preset partition and a second preset partition in the length direction of the base portion.
The structure of the first wing corresponding to the second predetermined partition in the length direction of the base will be described in detail below by taking the first wing as an example. The orthographic projection of the first wing piece on the base part corresponding to the second preset partition is located on one side departing from a first reference line, and the first reference line is a connecting line between a first end point and a second end point of the second wing piece. It should be understood that for the second tab, the first reference line would be the line connecting the first and second end points of the first tab.
As shown in fig. 5, fig. 5 is a schematic diagram illustrating an orthographic projection of the tab at the corresponding base of the second predetermined area according to an embodiment of the present invention. The orthographic projection of the tab at the base corresponding to the second predetermined division may be a curve.
In another embodiment of the present invention, as shown in fig. 6, fig. 6 is a schematic diagram showing an orthographic projection of a tab provided by another embodiment of the present invention on a corresponding base portion of the second predetermined area. The orthographic projection of the flap on the base corresponding to the second preset partition may be a fold line.
In one embodiment of the invention, the orthographic projection of the tab at the base corresponding to the first predetermined division coincides with the second reference line. For the first wing, the second reference line is a connecting line between the first end point of the first wing and the second end point of the first wing; and for the second airfoil, the second reference line is a connection line between a first endpoint of the second airfoil and a second endpoint of the second airfoil.
In another embodiment of the invention, the orthographic projection of the tab at the base corresponding to the first predetermined division is located on a side facing away from the first reference line. And the orthographic projection of the wing panel on the base corresponding to the first preset partition is a broken line or a curve.
For example, as shown in fig. 7a, fig. 7a is a schematic diagram illustrating an orthographic projection of the corresponding base portion of the vane provided by an embodiment of the invention. Taking the first wing as an example, the orthographic projection of the first wing on the base corresponding to the first preset partition is overlapped with the second reference line, and the orthographic projection of the first wing on the base corresponding to the second preset partition is located on the side away from the first reference line. And the orthographic projection of the first wing piece on the base corresponding to the second preset partition can be a curve.
For another example, as shown in fig. 7b, fig. 7b is a schematic diagram illustrating an orthographic projection of the corresponding base portion of the vane according to another embodiment of the present invention. Continuing with the example of the first tab, the orthographic projection of the first tab on the base corresponding to the first preset partition is located on the side away from the first reference line, and the orthographic projection of the first tab on the base corresponding to the second preset partition is located on the side away from the first reference line. The orthographic projection of the first wing piece on the base portion corresponding to the first preset partition can be a curve, and the orthographic projection of the first wing piece on the base portion corresponding to the second preset partition can be a curve.
Alternatively, as shown in fig. 7c, fig. 7c is a schematic diagram showing an orthographic projection of the corresponding base portion of the vane according to still another embodiment of the present invention. Continuing with the example of the first tab, the orthographic projection of the first tab on the base corresponding to the first preset partition is located on the side away from the first reference line, and the orthographic projection of the first tab on the base corresponding to the second preset partition is located on the side away from the first reference line. And the orthographic projection of the first flap on the base corresponding to the first preset partition can be a fold line, and the orthographic projection of the first flap on the base corresponding to the second preset partition can be a fold line.
In one embodiment of the invention, the farthest distance r1 between the point of the tab on the orthographic projection of the corresponding base of the first preset partition and the second reference line and the farthest distance r2 between the point of the tab on the orthographic projection of the corresponding base of the second preset partition and the second reference line satisfy: r1 ═ k1 ═ r2, where k1 is a positive number. For example, k1 may be a linear equation satisfying: k1 is the same as [2 ~ 6 ].
Further, as an example, a point of the airfoil farthest from the second reference line on the orthographic projection of the corresponding base portion of the first preset partition is located within a projection area of the second reference line in the windward direction. Also, as an example, a point of the airfoil furthest from the second reference line on the orthographic projection of the corresponding base of the second preset partition is located within a projection area of the second reference line in the windward direction.
According to the vortex generator provided by the embodiment of the invention, based on the fact that the orthographic projection of the wing piece on the base part corresponding to the second preset partition is located on the side departing from the first reference line, and the first reference line is the connecting line between the first end point and the second end point of other wing pieces on the base part, the parasitic resistance of the blade in the rotating process can be effectively reduced, so that the wing profile lift-drag ratio of a wind turbine is improved, and the output power of the wind turbine is improved.
In an embodiment of the invention, the blade further includes a casing and the vortex generator provided by the embodiment of the invention, and the blade on which the vortex generator provided by the embodiment of the invention is installed reduces the generation of parasitic resistance in the rotating process, so that the airfoil lift-drag ratio of the wind turbine is improved, and the output power of the wind turbine is improved.
It is to be understood that relational terms such as "first," "second," and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. It is to be understood that the terms so used are interchangeable under appropriate circumstances such that the embodiments of the invention described herein are, for example, capable of operation or arrangement in sequences other than those illustrated or otherwise described herein.
The present invention may be embodied in other specific forms without departing from its spirit or essential characteristics. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Also, different features that are present in different embodiments may be combined to advantage. Other variations to the disclosed embodiments can be understood and effected by those skilled in the art upon studying the drawings, the specification, and the claims.
The present invention may be embodied in other specific forms without departing from its spirit or essential characteristics. For example, the algorithms described in the specific embodiments may be modified without departing from the basic spirit of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.

Claims (13)

1. A vortex generator, comprising:
a base;
the fins are arranged on the same side of the base at a preset angle;
the wing piece is provided with a first preset partition and a second preset partition in the length direction of the base part, a first curve formed by orthographic projection of the wing piece on the base part corresponding to the first preset partition and a second curve formed by orthographic projection of the wing piece on the base part corresponding to the second preset partition are respectively positioned on two sides of a reference line, and the reference line is a connecting line between a first end point of the wing piece and a second end point of the wing piece.
2. The vortex generator of claim 1 wherein the furthest distance r1 between a point on the first curve and the reference line and the furthest distance r2 between a point on the second curve and the reference line satisfy: r1 ═ k1 ═ r2, where k1 is a positive number.
3. The vortex generator of claim 1, further comprising:
the height of the wing panel is provided with a third preset subarea, a fourth preset subarea and a fifth preset subarea in the length direction of the base part;
the height parameter of the wing panel at the first endpoint of the third preset partition and the length of the orthographic projection of the extending distance of the corresponding wing panel from the starting end surface to the corresponding first endpoint on the base part satisfy a first preset function;
the height parameter of the wing panel at the second endpoint of the fourth preset partition and the length of the orthographic projection of the extending distance of the corresponding wing panel from the starting end surface to the corresponding second endpoint on the base part satisfy a second preset function;
the height parameter of the wing piece at the third end point of the fifth preset partition and the length of the extended distance of the corresponding wing piece from the starting end surface to the corresponding third end point in the orthographic projection of the base part meet a third preset function.
4. The vortex generator according to any of claims 1-3, wherein said first preset partition further comprises: a first sub-partition and a second sub-partition;
wherein, the orthographic projection of the vane on the base corresponding to the first sub-partition forms a third curve which is positioned on one side of the reference line, and the orthographic projection of the vane on the base corresponding to the second sub-partition is coincident with the reference line.
5. The vortex generator of claim 3, wherein the first predetermined function is a power function.
6. The vortex generator according to claim 3, wherein the second preset function and/or the third preset function is a quadratic function.
7. A vortex generator, comprising:
a base;
the fins are arranged on the same side of the base at a preset angle;
the wing panel is provided with a first preset partition and a second preset partition in the length direction of the base part, the orthographic projection of the wing panel on the base part corresponding to the second preset partition is positioned on one side departing from a first reference line, and the first reference line is a connecting line between the first end point and the second end point of other wing panels on the base part.
8. The vortex generator according to claim 7, wherein the orthogonal projection of the fins on the base of the second predetermined section is a broken line or a curved line.
9. The vortex generator according to claim 8, wherein an orthographic projection of the vane at the base corresponding to the first predetermined division coincides with a second reference line, the second reference line being a line connecting the first end point of the vane and the second end point of the vane.
10. The vortex generator according to claim 8, wherein an orthographic projection of the fin at the base of the first predetermined division is on a side facing away from the first reference line.
11. The vortex generator according to claim 10, wherein the orthogonal projection of the fins on the base corresponding to the first predetermined section is a broken line or a curved line.
12. The vortex generator according to any of claims 9-11, wherein the farthest distance r1 between a point of the vane on the orthographic projection of the base corresponding to the first preset zone and the second reference line and the farthest distance r2 between a point of the vane on the orthographic projection of the base corresponding to the second preset zone and the second reference line satisfy: r1 ═ k1 ═ r2, where k1 is a positive number.
13. A blade, characterized in that the blade comprises a vortex generator according to any of claims 1-6 or the blade comprises a vortex generator according to any of claims 7-12.
CN201911154786.1A 2019-11-07 2019-11-22 Vortex generator and blade Pending CN110821761A (en)

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PCT/CN2020/127296 WO2021089019A1 (en) 2019-11-07 2020-11-06 Apparatus and method for regulating airfoil aerodynamic performance of blade, vortex generator control system, unit control system of wind turbine, vortex generator, and blade

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