CN106050566A - Control device and method for circulation of blunt trailing edge wind turbine airfoil - Google Patents
Control device and method for circulation of blunt trailing edge wind turbine airfoil Download PDFInfo
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- CN106050566A CN106050566A CN201610551249.0A CN201610551249A CN106050566A CN 106050566 A CN106050566 A CN 106050566A CN 201610551249 A CN201610551249 A CN 201610551249A CN 106050566 A CN106050566 A CN 106050566A
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Classifications
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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
- F03D7/00—Controlling wind motors
- F03D7/02—Controlling wind motors the wind motors having rotation axis substantially parallel to the air flow entering the rotor
- F03D7/022—Adjusting aerodynamic properties of the blades
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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
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/0608—Rotors characterised by their aerodynamic shape
- F03D1/0633—Rotors characterised by their aerodynamic shape of the blades
- F03D1/0641—Rotors characterised by their aerodynamic shape of the blades of the section profile of the blades, i.e. aerofoil profile
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- 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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- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a control device and method for circulation of a blunt trailing edge wind turbine airfoil, and relates to the technical field of active flow control. The control device is characterized in that a flow control method is utilized, relative principles of Coanda Effect are combined, and the wind turbine airfoil is subjected to modification and remolding treatment; a jet flow device is loaded inside a wind turbine blade and communicates with the external air through a nozzle; the nozzle is connected with a jet flow channel, and the jet flow channel is connected with a pneumatic pump through a pipeline; the wind turbine blade, loaded with a circulation control device, composed of the remolded airfoil generates trailing edge jet flow under the action of the jet flow device inside; and under the influence of the Coanda Effect, the jet flow flows, adhering to the curved surface of a trailing edge, an entire flow filed is influenced, the surrounding flow circulation of the airfoil is increased, the purpose of lift augmentation is achieved, and the aerodynamic efficiency of the wind turbine blade is improved.
Description
Technical field
The present invention relates to active Flow Control technical field, particularly to a kind of blunt trailing edge wind mill airfoil circulation control dress
Put and method.
Background technology
At the initial stage seventies, due to energy scarcity, energy problem is increasingly paid attention to by countries in the world.Then cleaning, renewable
One of the energy just study hotspot having become energy field.Wherein wind energy is drawn again as natural energy resources pollution-free, reproducible
Play the attention of people.
Through the development of decades, the scale of wind energy conversion system is increasing, and pneumatic equipment blades length is the most increasing, large-scale wind
The length of power machine blade is even up to more than 50 meter.When length of blade is excessive, the structural strength of blade will become one very
Important problem.In recent years in order to strengthen blade construction intensity and aerodynamic characteristic, scholar is had to propose blunt trailing edge wind mill airfoil
Concept.The thickness of this kind of aerofoil profile reaches maximum at chord length 25%-40%, about the 30% of chord length, and rear edge thickness
The 10% even 20% of chord length can be reached.This kind of aerofoil profile has the following characteristics that (1) structural strength is high, it is easy to processing and manufacturing；(2)
Surface contamination sensitivity is low, i.e. dust, rainwater and bird excrement etc. are less on the impact of its aerodynamic characteristic；(3) aerodynamic characteristic is good,
Maximum lift coefficient is big, and stalling angle is big.
But meanwhile, this type of blunt trailing edge aerofoil profile can produce body-shedding vortex at trailing edge, and rear edge thickness is the biggest, body-shedding vortex intensity
The biggest, profile drag coefficient will become big.
Due to the increase of profile thickness, the lifting of the lift coefficient brought is relatively limited, and the increase of resistance coefficient makes
Its overall pneumatic efficiency is undesirable.Then a lot of related researcher is had to begin to use the method for passive control to this kind of blunt trailing edge
Wind mill airfoil be optimized, such as add dividing plate to weaken the intensity etc. of body-shedding vortex at airfoil trailing edge.But this kind of passive control
The effect of method inconspicuous, and this control method is set in advance, is unable to reach optimal under off-design behaviour
Control effect.
Summary of the invention
Embodiments provide a kind of blunt trailing edge wind mill airfoil circulation control device and method, existing in order to solve
Problem present in technology.
A kind of blunt trailing edge wind mill airfoil circulation control device, described control device includes pulsometer, pipeline, fluidic channel
And spout, described control device is arranged on pneumatic equipment blades, and described wind mill airfoil is the section shape of described pneumatic equipment blades
Shape, described wind mill airfoil has relative top airfoil and a lower aerofoil, and relative leading edge and trailing edge, and described Pipe installing exists
Inside described pneumatic equipment blades, described fluidic channel be opened in described pneumatic equipment blades internal near described top airfoil and described after
The position of edge, described fluidic channel one end connects with one end of described pipeline, and the other end of described fluidic channel is described spout,
Described notch setting is between described top airfoil and described trailing edge, and described spout is towards described trailing edge, another of described pipeline
End connects with described pulsometer, and described trailing edge is one section of circular arc.
Preferably, the thickness of described trailing edge is the 10% of the aerofoil profile chord length of described wind mill airfoil, and described aerofoil profile chord length is
Distance between described leading edge and trailing edge.
Preferably, described trailing edge and distance is described aerofoil profile chord length the 0.5% of described top airfoil, described trailing edge is with described
The distance of lower aerofoil is also the 0.5% of described aerofoil profile chord length.
Preferably, the height of described spout is the 0.2% of described aerofoil profile chord length.
Present invention also offers a kind of blunt trailing edge wind mill airfoil circulation control method, described method includes:
After carrying out early stage installation and debugging efforts, when wind speed is suitable for wind turbine power generation, now wind energy conversion system starts routine
Work, spout is closed, wherein said notch setting between the top airfoil and trailing edge of wind mill airfoil, described wind-force
Airfoil type is the section shape of pneumatic equipment blades, and described spout is with the fluidic channel being opened within described pneumatic equipment blades even
Logical, described fluidic channel is positioned at the internal close described top airfoil of described pneumatic equipment blades and the position of described trailing edge, and described spray
Mouth is towards the trailing edge of described wind mill airfoil, and described fluidic channel one end is described spout, and the described fluidic channel other end passes through
It is arranged on the pipeline within described pneumatic equipment blades to connect with pulsometer；
After the normal operation state of described wind energy conversion system is stable, opens described spout and pulsometer, regulate described pulsometer
Pressure, make described nozzle formed an initial jets, stream field carries out a preliminary control；
When after the stable working state of described wind energy conversion system, by the air pressure sensing device being arranged on described pneumatic equipment blades
Measure the angle of attack and speed flowed, set momentum of impinging jet coefficient accordingly according to the described angle of attack flowed and speed calculation；
Pressure size according to pulsometer described in described setting momentum of impinging jet coefficient adjustment；
Measured air pressure and the air velocity of described nozzle by the air pressure sensing device of described nozzle, calculate and penetrate in real time
Amount of flow coefficient and with described setting momentum of impinging jet coefficients comparison, it is thus achieved that corresponding comparative result；
Comparative result is fed back to described pulsometer, if described real-time momentum of impinging jet coefficient moves less than described setting jet
Coefficient of discharge, tunes up the pressure of described pulsometer；Otherwise, the pressure of described pulsometer is turned down, until described spout is described
Momentum of impinging jet coefficient stops test, feedback and regulating step time identical with described setting momentum of impinging jet coefficient in real time, and holding should
Duty.
The invention discloses a kind of blunt trailing edge wind mill airfoil circulation control device and method, described control device utilizes stream
Flowing control method, in conjunction with the relative theory of Coanda effect, carries out wind mill airfoil correction of the flank shape and remodeling processes；And by fluidic cartridge
Put and be downloaded to, inside pneumatic equipment blades, be connected with outside atmosphere by spout；Spout connects fluidic channel, and fluidic channel passes through pipeline
Connect pulsometer.The pneumatic equipment blades being loaded with circulation control device being made up of the aerofoil profile after retrofiting, at inner jet device
Effect under produce trailing edge jet.Under the influence of Coanda effect, attachment trailing edge curved surface is flowed by jet, and impact is whole further
Individual flow field, increases profile flow circular rector, reaches the purpose of lift-rising, thus improve the pneumatic efficiency of pneumatic equipment blades.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to
Other accompanying drawing is obtained according to these accompanying drawings.
Fig. 1 is for having the plan structure figure of the pneumatic equipment blades controlling device that the embodiment of the present invention provides；
Fig. 2 is the side view of pneumatic equipment blades in Fig. 1；
Fig. 3 be in Fig. 2 pneumatic equipment blades along the sectional structure chart in A-A direction；
Fig. 4 is the airfoil structure schematic diagram of DU97-W-300；
Fig. 5 be aerofoil profile in Fig. 4 is carried out correction of the flank shape after the DU97-W-300-flatback airfoil structure schematic diagram that obtains；
Fig. 6 is to detail view when aerofoil profile is retrofited in Fig. 5；
Fig. 7 is the airfoil structure schematic diagram in Fig. 6 after airfoil modification；
Fig. 8 is that in Fig. 4, aerofoil profile is flow field figure when 10 ° at the angle of attack；
Fig. 9 is that in Fig. 5, aerofoil profile is flow field figure when 10 ° at the angle of attack；
Figure 10 is that in Fig. 7, aerofoil profile is flow field figure when 10 ° at the angle of attack；
The flow chart of steps of a kind of blunt trailing edge wind mill airfoil circulation control method that Figure 11 provides for the embodiment of the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Describe, it is clear that described embodiment is only a part of embodiment of the present invention rather than whole embodiments wholely.Based on
Embodiment in the present invention, it is every other that those of ordinary skill in the art are obtained under not making creative work premise
Embodiment, broadly falls into the scope of protection of the invention.
With reference to Fig. 1, Fig. 2 and Fig. 3, the invention provides a kind of pneumatic equipment blades 100 being loaded with aerofoil profile circulation control device,
Described pneumatic equipment blades 100 includes root of blade 110, blade body 112 and connects described root of blade 110 and blade body
The blade transition section 111 of 112, the section shape of described pneumatic equipment blades 100 is the aerofoil profile 120 of described pneumatic equipment blades 100, institute
State aerofoil profile 120 and include top airfoil 121, lower aerofoil 122, leading edge 123 and trailing edge 124, described top airfoil 121 and lower aerofoil 122 phase
To setting, described leading edge 123 and trailing edge 124 are oppositely arranged, and internal near described top airfoil at described pneumatic equipment blades 100
121 and the position of described trailing edge 124 offer fluidic channel 125, described fluidic channel 125 is by being arranged on described blade body
Pipeline within 112 connects with pulsometer, and described fluidic channel 125, pipeline and pulsometer constitute the aerofoil profile ring in the present invention
Amount control device.
Described aerofoil profile 120 obtains after correction of the flank shape and reshaping for the original aerofoil profile 200 shown in Fig. 4.Described original aerofoil profile
200 is the DU97-W-300 aerofoil profile in TU Delft Polytechnics Special Airfoil of Wind Turbine wind tunnel experiment model in 2003,
The thickness of its prototype trailing edge 210 is less.
Correction of the flank shape to described original aerofoil profile 200 is carried out according to below equation:
x1=x0
Wherein, x1、y1For the correction of the flank shape aerofoil profile 300 that obtains through correction of the flank shape in coordinate system O as shown in Figure 51X1Y1In coordinate,
x0、y0For described original aerofoil profile 200 in coordinate system O as shown in Figure 40X0Y0In coordinate, δ is airfoil trailing edge thickness before and after correction of the flank shape
Increments, c is aerofoil profile chord length, xtFor the abscissa of correction of the flank shape original position, n is correction of the flank shape index parameters.Described correction of the flank shape aerofoil profile
300, i.e. DU97-W-300-flatback are blunt trailing edge aerofoil profiles, as it is shown in figure 5, the thickness of the trailing edge 330 after its correction of the flank shape is
The 10% of aerofoil profile chord length c.In formula " ± " it is the top airfoil 310 after distinguishing correction of the flank shape and the lower aerofoil 320 after correction of the flank shape, when calculating institute
Use when stating the coordinate of the top airfoil after correction of the flank shape 310 "+", use "-" when calculating the coordinate of the lower aerofoil 320 after correction of the flank shape.
With reference to Fig. 6, detail view during for retrofiting described correction of the flank shape aerofoil profile 300, the method for remodeling is:
(1) lower section of top airfoil 310 after described correction of the flank shape and described repair respectively near the trailing edge 330 after described correction of the flank shape
Two, the top picture of the lower aerofoil 320 after shape is the most parallel with the top airfoil 310 after described correction of the flank shape and the lower aerofoil 320 after correction of the flank shape
And distance be aerofoil profile chord length 0.5% curve m, n (as shown in Figure 6)；
(2) at curve m, draw between n simultaneously and circle that trailing edge 330 after m, n and described correction of the flank shape is tangent, and determine circle
Point of contact E, F, P of trailing edge 330 after heart O and curve m, n, correction of the flank shape and circle；
(3) cross the top airfoil 310 after E, F make described correction of the flank shape respectively and the vertical line of the lower aerofoil 320 after correction of the flank shape and determine vertical
Foot C, D, connect CE, DF, it is known that CE=DF=0.5%c；
(4) taking camber line EPF is trailing edge curved surface, and starts to take 0.2% that a segment length is aerofoil profile chord length from E on line segment CE
～0.3% line segment as the height of spout, preferably the 0.2% of aerofoil profile chord length, as shown in Fig. 6 middle conductor EH；
(5) inside described correction of the flank shape aerofoil profile 300, described fluidic channel 125 is offered at nozzle, as shown in Figure 7.
After remodeling obtain described aerofoil profile 120 as it is shown in fig. 7, described camber line EPF constitute trailing edge curved surface be described after
Edge 124, the space between described top airfoil 121 rear end and described trailing edge 124 is described spout 126, it is seen then that described spout
126 with the perpendicular of described trailing edge 124.
Wherein said fluidic channel 125 connects described pulsometer by described pipeline.Owing to described pipe given by described pulsometer
Road pressurizes, and makes described pipeline internal gas pressure more than external atmosphere pressure, and gas the most therein will be through described fluidic channel 125 from institute
State spout 126 to spray.Owing to described spout 126 is the narrowest, when described pipeline internal gas pressure is bigger, gas passes through described spout 126
Speed can be very big, thus form high-speed jet.The power of jet can represent with momentum of impinging jet coefficient, and the value of this coefficient is more
Big expression jet intensity is the biggest.Described momentum of impinging jet coefficient is a nondimensional coefficient, and its physical significance is described spout 126
The mean momentum of place's gas is with aerofoil profile front from the ratio of the momentum of origin stream, and computing formula is as follows:
Wherein: CμFor momentum of impinging jet coefficient, h is the height of described spout 126, and w is that described spout 126 is along blade radial
Length, ρJETFor the density of gas, U at described spout 126JETFor the speed of gas at described spout 126, b is described blade footpath
To length, ρ∞For the density from origin stream, U∞For the speed from origin stream,For mass flowrate, q is the pressure that flows, and S is ginseng
Examine area.High-speed jet is after described spout 126 sprays, and due to Coanda effect, attachment trailing edge curved surface is flowed by jet, from
And drive ambient gas to follow jet flow, and make peripheral flow field change, profile flow circular rector increases, and lift coefficient is the most therewith
Increase.Owing to described trailing edge 124 is curved surface, the body-shedding vortex intensity at described trailing edge 124 rear will weaken.Add the work of jet
With, body-shedding vortex can be dispelled by jet, and its intensity weakens further.The pressure drag of the most described aerofoil profile 120 and common blunt trailing edge
Aerofoil profile is compared and is greatly reduced, and therefore resistance coefficient reduces the most therewith.And jet also can produce corresponding propulsive thrust, can offset
A part of resistance.The most actively control to add stability and the controllability, beneficially wind power plant of pneumatic equipment blades work
Grid-connected related work.
According to the numerical simulation result of aerofoil profile each in Fig. 4, Fig. 5 and Fig. 7, as shown in Fig. 8, Fig. 9 and Figure 10, from origin stream
In the case of the angle of attack is 10 °: the lift coefficient of described original aerofoil profile 200 (i.e. DU97-W-300) is 1.4426, and resistance coefficient is
0.0244；The lift coefficient of described correction of the flank shape aerofoil profile 300 (i.e. DU97-W-300-flatback) is 1.6065, and resistance coefficient is
0.0458；Described aerofoil profile 120, momentum of impinging jet coefficient be lift coefficient when 0.035 be 2.7756, resistance coefficient is
0.0194。
In Fig. 8, Fig. 9 and Figure 10, the position of leading edge stationary point S can reflect the size of each profile flow circular rector indirectly, i.e.
Position, stationary point circular rector the most rearward is the biggest, and the size of circular rector reflects the biggest aerofoil profile of the size of wing section lift coefficient, i.e. circular rector further
Lift coefficient is the biggest.
The appearance near described prototype trailing edge 210 of described original aerofoil profile 200 separates bubble, after described prototype trailing edge 210
Side has body-shedding vortex to occur.After correction of the flank shape, owing to trailing edge 330 thickness after described correction of the flank shape becomes big, trailing edge separation bubble collapse.But it is described
The body-shedding vortex intensity at trailing edge 330 rear after correction of the flank shape becomes big, although the thickness increasing the trailing edge 330 after described correction of the flank shape brings liter
The lifting of power, but owing to the intensity of body-shedding vortex becomes big, resistance increases to 0.0458 from 0.0244.For the institute obtained after remodeling
State aerofoil profile 120, only need the least energy input, make described spout 126 form jet, thus change profile flow, increase circular rector,
Dispel body-shedding vortex, make lift coefficient increase, reach 1.93 times of described original aerofoil profile 200, be also described correction of the flank shape aerofoil profile 300
1.73 again；Make resistance coefficient reduce simultaneously, reach the 79.3% of described original aerofoil profile 200, be also described correction of the flank shape aerofoil profile 300
42.3%.
Can be seen that jet is fairly obvious to the castering action of lift coefficient.By proposed by the invention, there is described aerofoil profile
The pneumatic efficiency of the pneumatic equipment blades of circulation control device has significant improvement than common pneumatic equipment blades.And, by
The energy consumed in jet is little, and controllability is good, therefore can be big by regulating air pressure in described pipeline under different operating modes
Little, make pneumatic equipment blades reach optimal duty.
Based on same inventive concept, present invention also offers a kind of blunt trailing edge wind mill airfoil circulation control method, such as figure
Shown in 11, the method includes:
Step 400, installs and after debugging efforts, when wind power plant reaches corresponding working condition, i.e. carrying out early stage
When wind speed is suitable for wind turbine power generation, now wind energy conversion system starts routine work, is i.e. not turned on spout.
Step 410, after the normal operation state of wind energy conversion system is stable, opens spout and pulsometer, the pressure of regulation pulsometer
Power, makes nozzle form more weak jet, i.e. an initial jets, and stream field carries out a preliminary control.
Step 420, when after the stable working state in step 410, by the air pressure sensing being arranged on pneumatic equipment blades
Device measures the angle of attack and speed flowed, and sets momentum of impinging jet coefficient accordingly according to the angle of attack flowed and speed calculation.
Step 430, according to setting momentum of impinging jet coefficient adjustment pulsometer pressure size.
Step 440, measures air pressure and the air velocity of nozzle by the air pressure sensing device of nozzle, calculates and penetrates in real time
Amount of flow coefficient and with set momentum of impinging jet coefficients comparison, it is thus achieved that corresponding comparative result.
Step 450, feeds back to pulsometer by comparative result.If momentum of impinging jet coefficient is less than setting momentum of impinging jet system in real time
Number, tunes up pulsometer pressure；Otherwise, pulsometer pressure is turned down.
Step 460, repeats step 440 and arrives step 450, until the real-time momentum of impinging jet coefficient of spout and setting momentum of impinging jet
Stop a series of test, feedback and regulating step when coefficient is identical, and keep this duty.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creation
Property concept, then can make other change and amendment to these embodiments.So, claims are intended to be construed to include excellent
Select embodiment and fall into all changes and the amendment of the scope of the invention.
Obviously, those skilled in the art can carry out various change and the modification essence without deviating from the present invention to the present invention
God and scope.So, if these amendments of the present invention and modification belong to the scope of the claims in the present invention and equivalent technologies thereof
Within, then the present invention is also intended to comprise these change and modification.
Claims (5)
1. a blunt trailing edge wind mill airfoil circulation control device, it is characterised in that described control device includes pulsometer, pipe
Road, fluidic channel and spout, described control device is arranged on pneumatic equipment blades, and described wind mill airfoil is described wind energy conversion system leaf
The section shape of sheet, described wind mill airfoil has relative top airfoil and a lower aerofoil, and relative leading edge and trailing edge, described
Pipe installing is inside described pneumatic equipment blades, and it is internal near described upper limb that described fluidic channel is opened in described pneumatic equipment blades
Face and the position of described trailing edge, described fluidic channel one end connects with one end of described pipeline, the other end of described fluidic channel
For described spout, described notch setting is between described top airfoil and described trailing edge, and described spout is towards described trailing edge, described
The other end of pipeline connects with described pulsometer, and described trailing edge is one section of circular arc.
Control device the most as claimed in claim 1, it is characterised in that the thickness of described trailing edge is the wing of described wind mill airfoil
The 10% of type chord length, described aerofoil profile chord length is the distance between described leading edge and trailing edge.
Control device the most as claimed in claim 2, it is characterised in that described trailing edge is the described wing with the distance of described top airfoil
The 0.5% of type chord length, described trailing edge is also the 0.5% of described aerofoil profile chord length with the distance of described lower aerofoil.
Control device the most as claimed in claim 2, it is characterised in that the height of described spout is described aerofoil profile chord length
0.2%～0.3%.
5. a blunt trailing edge wind mill airfoil circulation control method, it is characterised in that described method includes:
After carrying out early stage installation and debugging efforts, when wind speed is suitable for wind turbine power generation, now wind energy conversion system starts routine work,
Spout is closed, wherein said notch setting between the top airfoil and trailing edge of wind mill airfoil, described wind-force wing
Type is the section shape of pneumatic equipment blades, and described spout connects with the fluidic channel being opened within described pneumatic equipment blades, institute
Stating fluidic channel, to be positioned at described pneumatic equipment blades internal near described top airfoil with the position of described trailing edge, and described spout towards
The trailing edge of described wind mill airfoil, described fluidic channel one end is described spout, and the described fluidic channel other end is by being arranged on
Pipeline within described pneumatic equipment blades connects with pulsometer；
After the normal operation state of described wind energy conversion system is stable, opens described spout and pulsometer, regulate the pressure of described pulsometer
Power, makes described nozzle form an initial jets, and stream field carries out a preliminary control；
When, after the stable working state of described wind energy conversion system, being measured by the air pressure sensing device being arranged on described pneumatic equipment blades
The angle of attack flowed and speed, set momentum of impinging jet coefficient accordingly according to the described angle of attack flowed and speed calculation；
Pressure size according to pulsometer described in described setting momentum of impinging jet coefficient adjustment；
Measured air pressure and the air velocity of described nozzle by the air pressure sensing device of described nozzle, calculate real-time jet and move
Coefficient of discharge and with described setting momentum of impinging jet coefficients comparison, it is thus achieved that corresponding comparative result；
Comparative result is fed back to described pulsometer, if described real-time momentum of impinging jet coefficient is less than described setting momentum of impinging jet system
Number, tunes up the pressure of described pulsometer；Otherwise, the pressure of described pulsometer is turned down, until described spout described in real time
Stop test, feedback and regulating step when momentum of impinging jet coefficient is identical with described setting momentum of impinging jet coefficient, and keep this work
State.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610551249.0A CN106050566B (en) | 2016-07-13 | 2016-07-13 | A kind of blunt trailing edge wind mill airfoil circulation control device and method |
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| CN201610551249.0A CN106050566B (en) | 2016-07-13 | 2016-07-13 | A kind of blunt trailing edge wind mill airfoil circulation control device and method |
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| CN106050566A true CN106050566A (en) | 2016-10-26 |
| CN106050566B CN106050566B (en) | 2018-11-16 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106593786A (en) * | 2017-02-15 | 2017-04-26 | 西北工业大学 | Reverse co-flow jet controlling method and device used for wind turbine blade pneumatic braking |
| CN106762402A (en) * | 2016-12-28 | 2017-05-31 | 西北工业大学 | Pneumatic equipment bladess flow control apparatus and its control method based on united jet flow technology |
| CN108087193A (en) * | 2017-12-28 | 2018-05-29 | 江苏金风科技有限公司 | Blade, blade synergistic device and wind power generating set |
| CN108860597A (en) * | 2018-06-22 | 2018-11-23 | 上海理工大学 | A kind of flapping wings type capacitation device using circulation control lift-rising |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2395050Y (en) * | 1999-11-17 | 2000-09-06 | 王晓川 | Wind energy utilizing device of multiple pump collection energy and jet increasing energy speed regulation |
| CN1930394A (en) * | 2004-03-18 | 2007-03-14 | 弗兰克·丹尼尔·洛特里翁特 | Turbine and rotor therefor |
| CN101258071A (en) * | 2005-07-13 | 2008-09-03 | 城市大学 | An element for generating a fluid dynamic force |
| CN101725467A (en) * | 2008-10-27 | 2010-06-09 | 通用电气公司 | Active circulation control of aerodynamic structures |
| CN101749186A (en) * | 2008-12-08 | 2010-06-23 | 王晓川 | Wing tip jet energizing speed-regulating wind power generation |
| CN102052264A (en) * | 2009-11-05 | 2011-05-11 | 通用电气公司 | Systems and method of assembling an air distribution system for use in a rotor blade of a wind turbine |
| CN102889176A (en) * | 2011-07-19 | 2013-01-23 | 西门子公司 | Control of a wind turbine, rotor blade and wind turbine |
| US20140301864A1 (en) * | 2011-11-23 | 2014-10-09 | Lm Wp Patent Holding A/S | Wind turbine blade |
| CN205779470U (en) * | 2016-07-13 | 2016-12-07 | 西北工业大学 | A kind of blunt trailing edge wind mill airfoil circulation control device |
-
2016
- 2016-07-13 CN CN201610551249.0A patent/CN106050566B/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2395050Y (en) * | 1999-11-17 | 2000-09-06 | 王晓川 | Wind energy utilizing device of multiple pump collection energy and jet increasing energy speed regulation |
| CN1930394A (en) * | 2004-03-18 | 2007-03-14 | 弗兰克·丹尼尔·洛特里翁特 | Turbine and rotor therefor |
| CN101258071A (en) * | 2005-07-13 | 2008-09-03 | 城市大学 | An element for generating a fluid dynamic force |
| CN101725467A (en) * | 2008-10-27 | 2010-06-09 | 通用电气公司 | Active circulation control of aerodynamic structures |
| CN101749186A (en) * | 2008-12-08 | 2010-06-23 | 王晓川 | Wing tip jet energizing speed-regulating wind power generation |
| CN102052264A (en) * | 2009-11-05 | 2011-05-11 | 通用电气公司 | Systems and method of assembling an air distribution system for use in a rotor blade of a wind turbine |
| CN102889176A (en) * | 2011-07-19 | 2013-01-23 | 西门子公司 | Control of a wind turbine, rotor blade and wind turbine |
| US20140301864A1 (en) * | 2011-11-23 | 2014-10-09 | Lm Wp Patent Holding A/S | Wind turbine blade |
| CN104220746A (en) * | 2011-11-23 | 2014-12-17 | Lmwp专利控股有限公司 | A wind turbine blade |
| CN205779470U (en) * | 2016-07-13 | 2016-12-07 | 西北工业大学 | A kind of blunt trailing edge wind mill airfoil circulation control device |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106762402A (en) * | 2016-12-28 | 2017-05-31 | 西北工业大学 | Pneumatic equipment bladess flow control apparatus and its control method based on united jet flow technology |
| CN106593786A (en) * | 2017-02-15 | 2017-04-26 | 西北工业大学 | Reverse co-flow jet controlling method and device used for wind turbine blade pneumatic braking |
| CN106593786B (en) * | 2017-02-15 | 2023-03-31 | 西北工业大学 | Reverse combined jet flow control method and device for pneumatic brake of wind turbine blade |
| CN108087193A (en) * | 2017-12-28 | 2018-05-29 | 江苏金风科技有限公司 | Blade, blade synergistic device and wind power generating set |
| CN108860597A (en) * | 2018-06-22 | 2018-11-23 | 上海理工大学 | A kind of flapping wings type capacitation device using circulation control lift-rising |
| CN111322198A (en) * | 2020-03-10 | 2020-06-23 | 上海理工大学 | Wind turbine wing section for improving pneumatic performance through jet flow |
| CN111572704A (en) * | 2020-06-23 | 2020-08-25 | 西北工业大学 | Open-loop active flow control device of underwater glider based on steady jet |
| EP3981981A1 (en) * | 2020-10-09 | 2022-04-13 | Wobben Properties GmbH | Rotor blade for a wind turbine, wind turbine and method for designing a rotor blade |
| US11867145B2 (en) | 2020-10-09 | 2024-01-09 | Wobben Properties Gmbh | Rotor blade for a wind power installation, wind power installation, and method for designing a rotor blade |
| CN113619772A (en) * | 2021-10-09 | 2021-11-09 | 中国航空研究院 | Jet-type second grade spout circulation control wing section in coordination |
| CN114021277A (en) * | 2021-11-02 | 2022-02-08 | 华北电力大学 | Method and system for evaluating dynamic aerodynamic characteristics of wind turbine |
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