CN110110427A - A kind of Design of Aerodynamic Configuration method of high-power wind mill blade - Google Patents
A kind of Design of Aerodynamic Configuration method of high-power wind mill blade Download PDFInfo
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Abstract
The invention discloses a kind of Design of Aerodynamic Configuration methods of high-power wind mill blade, iteratively solve complicated, low success rate of problem in the process for conventional vane design, the present invention is according to the rule of vortex in wake, derive the loss coefficient of blade tip and blade root, axial and circumferential inducible factor is solved based on momentum theory, thrust caused by blade tip and blade root, torque loss are modified；Novel chord length formula is constructed by the method for interpolation, obtains accurate chord length at blade design initial stage, and then calculate aerofoil profile and run Reynolds number, provides foundation to accurately calculate profile lift, resistance coefficient and selection optimal attack angle；The unitary nonlinear equation about inflow angle is established on the basis of loss coefficient and chord length formula are improved, is proposed the new method for solving blade aerodynamic formal parameter, is substantially reduced the Design of Aerodynamic Configuration period of blade.It is learnt through foline theoretical validation, the 10MW high-power wind-driven generator leaf model designed according to the present invention can achieve design power.
Description
Technical field
The present invention relates to technical field of wind power generator, and in particular to a kind of aerodynamic configuration of high-power wind mill blade
Design method.
Background technique
21st century, with the weary and increasingly severe environmental problem of the increasingly plaque of the resources such as coal, petroleum, wind energy
Have become one of the resource that country encourages preferential development to utilize.In recent years, wind-powered electricity generation career development in China's is swift and violent, some large size wind
Power generator group is built up in succession, and huge contribution is made that the problem of China's energy shortages and electricity shortage to alleviate.2019,
China's Wind Power Generation Industry continues to keep rapid growth, and installation scale is constantly soaring, and accumulative installed capacity reaches 1.96 × 105MW,
As the incontrovertible leader in the whole world.After thermal power generation, hydroelectric generation, wind-powered electricity generation has become the third-largest next of China's electric energy
Source.
Blade is the core part of Wind turbines capture wind energy, referred to as " soul " of wind energy conversion system.The direct shadow of its design
The utilization efficiency for arriving wind energy is rung, performance quality directly affects complete machine operation and stablizes.Therefore, the Design of Aerodynamic Configuration of blade is aobvious
It obtains particularly important.Under the trend that wind-driven generator single-machine capacity develops to enlargement, pneumatic equipment bladess become more and more longer, lead
Its flexibility is caused to become larger, it is easier to deform.This soft blade of length will bring various accessory problems, such as: leaf quality increase causes
Rotary inertia increases, and influences the coupled vibrations characteristic of blade；Blade twist rigidity increases to influence the dynamic stability of wind energy conversion system
Property；Large-scale flexible blade will consider the factors such as modal frequency, the economy of material, its processing, transport and installation.
The Aerodynamics narrow scope of application developed, the theoretical insufficient meeting of the classical blade design in part are brighter
It is aobvious, such as: the increase of wind energy conversion system single-machine capacity, will lead to blade tip position operation Mach number is more than 0.3, needs to consider air pressure at this time
The problems such as contracting, and classical wind energy conversion system theory is derived from the Incoercibility based on air.Therefore it needs to large scale wind power machine
Blade aerodynamic configuration design theory expansion further investigation, convenient for more clearly from dissecting blade aeromechanical mechanism.
Wind energy conversion system single-machine capacity to enlargement, high power development background under, traditional theory using solution by iterative method it is non-
The mode of system of linear equations, this method is unreasonable there are the selection of initial value and Equation Iterative solves difficulty, or even without solution
The problems such as.The present invention is deduced the unitary nonlinear equation using inflow angle as independent variable, is mentioned based on classical BEM theory
The new method for solving blade aerodynamic formal parameter is gone out, has laid a good foundation for further investigation blade aerodynamic performance.
Summary of the invention
For traditional theory using the problems of solution by iterative method Nonlinear System of Equations, the main object of the present invention exists
It is that the optimization design of pneumatic equipment bladess and aeroelasticity are stablized in providing a kind of Design of Aerodynamic Configuration method of pneumatic equipment bladess
Property research provide theoretical foundation.
Technical solution provided by the invention includes: to derive the blade tip, the blade root loss coefficient that are suitable for high-power wind mill；It adopts
The mathematical model that novel chord length solves is constructed with the method for interpolation；The unitary nonlinear equation about inflow angle is constructed, axis is solved
To the specific value of inducible factor and circumferential inducible factor, and then calculate the parameters such as thrust and torque；Determine foline aerofoil profile, each leaf
Element operation Reynolds number solves parameter of aerodynamic characteristics, analyzes the aerodynamic characteristic of aerofoil profile.The step of specific design scheme, is such as
Under:
(1) according to the rule of vortex in wake, the tip loss coefficient F suitable for high-power wind mill is derivedtAnd blade root
Loss coefficient Fr:
F in formulat--- tip loss coefficient；
Fr--- blade root loss coefficient；
μ --- aerofoil position radius ratio；
rhub--- hub radius；
B --- blade quantity；
R ' --- foline aerofoil profile position.
Based on momentum theory, axial direction inducible factor a and circumferential inducible factor are solved by simultaneous thrust and torque expression formula
The expression formula of a ':
A in formula --- axial inducible factor；
A ' --- circumferential inducible factor；
φ --- inflow angle；
R --- wind wheel radius；
C --- chord length；
Cx--- tangential tractive force coefficient；
Cy--- axial thrust coefficient；
N --- blade quantity；
F --- total losses coefficient.
(2) chord length formula is constructed by the way of curve matching, establishes a kind of chord length method for solving:
C=(0.076875-0.06875 μ) Lb
L in formulab--- length of blade (m).
(3) determination for passing through step (2) chord length, is designed the aerodynamic configuration of high-power wind-driven generator blade.
(3.1) suitable foline aerofoil profile is selected, guarantees the pneumatic efficiency of wind energy conversion system.
(3.2) determine that each foline operation Reynolds number, the Fluent of XFOIL software and FInite Element based on panel method are soft
Part calculates the parameter of aerodynamic characteristics such as pitch axes, lift coefficient, resistance coefficient, the optimal attack angle of aerofoil profile, and to the pneumatic of aerofoil profile
Characteristic is analyzed.
(4) parameter of aerodynamic characteristics of aerofoil profile is obtained by step (3), is asked in conjunction with loss coefficient and the step (2) of step (1)
The chord length of solution constructs the unitary nonlinear equation about inflow angle, by asking for the nonlinear multivariable solving equations based on BEM method
Topic becomes the solution of unitary nonlinear equation.
The angular velocity of rotation (rad/s) of Ω in formula --- air-flow；
v∞--- arrives stream wind speed (m/s)；
CD--- resistance coefficient；
CL--- lift coefficient.
As y=0, equation root seeks to the inflow angle solved.
(5) wing section lift coefficient, the resistance coefficient obtained according to the inflow angle of step (4) solution and step (3) calculates leaf
The tangential tractive force coefficient C of plain aerofoil profilexWith axial thrust coefficient Cy。
(6) the tangential tractive force coefficient C that step (5) is calculatedx, axial thrust coefficient CyEnter with what step (4) solved
Flow angle φ and substitute into axial direction inducible factor a and circumferential inducible factor a ' expression formula, solve axial inducible factor and it is circumferential induce because
The specific value of son.
(7) this method is based on the momentum theory derivation of equation, is verified using foline theory to actual power, and and Denmark
10 megawatts of power wind energy conversion systems of technology university's design compare.
Chord length formula and tip loss coefficient proposed by the present invention, blade root loss coefficient are not necessarily to participate in iterative solution, can
Immediately arrive at design result, make the solution procedure of inflow angle from the problem of solution nonlinear multivariable equation group become solve unitary it is non-
The problem of linear equation, provides a set of feasible technical solution for large-scale wind electricity machine blade aerodynamic configuration design.
Detailed description of the invention
Present invention will be further explained below with reference to the attached drawings and specific embodiments.
Fig. 1 is the flow chart of method involved by the present invention.
Fig. 2 is hypothesis wake flow vortex filament model (three blade wind machine) provided by the present invention.
Fig. 3 is x '-y ' plane vortex filament distribution map provided by the present invention.
Fig. 4 is selected aerofoil profile figure provided by the invention.
Fig. 5 is GAS60 aerofoil profile finite element model provided by the invention.
Fig. 6 is the GAS60 aerofoil profile aerodynamic characteristic curve that the present invention creates.
Fig. 7 is foline velocity composite figure provided by the invention and stress composite diagram.In figureFor the angle of attack, β be torsional angle, φ is
Inflow angle.1 in figure is lift coefficient, and 2 be resistance coefficient, and 3 be lift resistance ratio.
Fig. 8 is axial inducible factor provided by the invention and circumferential inducible factor along spanwise distribution rule.A is axial
Inducible factor, a ' are circumferential inducible factor.
Fig. 9 is the blade plane figure that the present invention creates.
Figure 10 is 10 megawatts of concept wind energy conversion system power contrast's curve graphs that the present invention is designed with Technical University Of Denmark.It is described
10MW is the wind energy conversion system power curve that the present invention designs, 10 megawatts of concept wind energy conversion systems that DTU10MW designs for Technical University Of Denmark
Power curve.
Specific embodiment
Embodiments of the present invention are described further below in conjunction with attached drawing.Fig. 1 is a kind of wind energy conversion system of the invention
The flow chart of the Design of Aerodynamic Configuration method of blade.Specific implementation step of the invention is as follows:
(1) computation model of novel blade tip, blade root loss coefficient is established.
When wind energy conversion system works, wind wheel downstream forms spiral shape complex vortex, and vortex system diameter has the deformations such as expansion and shows
As each blade generates a vortex filament.The size of limited blade wind motor wake flow speed constituent in order to obtain, this hair
It is bright that model simplification is carried out to wake flow vortex filament, complicated wake model is mapped as to the point unit vortex model of plane incompressible flow, thus sharp
With the complex potential principle of Plane Fluid Field, the Analytical Solution of limited blade wind motor blade tip, blade root loss coefficient is realized；
Specifically, assuming that wake flow vortex sheet and vortex filament pitch diameter are constant, that is, ignore wake flow expansion, as shown in Figure 2.Set trip
Vortex filament screw pitch is d, and whirlpool column radius is r ', helical angle φ.Using Fig. 3-a) in wherein a vortex filament is research object, such as Fig. 3-b
It is shown).Single wake flow vortex filament tip loss coefficient F is derived by the complex potential principle of Plane Fluid Fieldt1Expression formula are as follows:
R ' in formula --- foline aerofoil profile position；
R --- length of blade, r '/R ∈ [0,1].
Limited each blade of blade wind motor is installed on wheel hub, constitutes parallel system --- wind wheel.Whirlpool number of lines and wind
Wheel blade the piece number is equal, therefore for limited blade wind motor tip loss coefficient FtExpression formula are as follows:
According to tip loss coefficient expressions, with hub radius rhubInstead of r ' in above formula and transformation is normalized, obtains
Blade root loss coefficient (wheel hub loss coefficient) expression formula is as follows:
Total losses coefficient are as follows:
F=Ft·Fr
(2) it is based on momentum theory, derives blade inducible factor expression formula, specific steps:
(2.1) according to momentum theorem, the expression formula of thrust and torque is obtained:
DT=4 π ρ r2v∞Ω(1-a)aFdr
DM=4 π ρ r3v∞Ω(1-a)a′Fdr
T in formula --- axial thrust (N)；
M --- wind wheel torque (Nm)；
ρ --- atmospheric density (Kg/m3)；
According to tip loss coefficient and blade root loss coefficient that this method is established, total losses coefficient is updated to above two
Formula can be obtained new based on thrust derived from momentum theory and torque expression formula.
Lanzafame R etc. proposes thrust and torque expression formula such as following formula:
(2.2) by the thrust of the propositions such as Lanzafame R and torque expression formula with new based on being pushed away derived from momentum theory
Axial inducible factor a and circumferential inducible factor a ' expression formula can be obtained in power and torque expression formula simultaneous solution are as follows:
(3) fitting of chord length solves；
For chord length calculation formula, there are many kinds of methods, common are two kinds:
Based on chord length formula, such as following formula derived from shellfish hereby theory:
Based on above formula propose simplified formula, such as following formula:
Two kinds of formula are undesirable in high-power wind mill blade design, the string of the chord length formula as derived from shellfish hereby theory
Long calculated value is bigger than normal, and the chord length calculated by simplified formula is again less than normal.Therefore megawatt wind power machine chord length is calculated, the present invention uses
The method of mathematical interpolation rebuilds chord length formula.
Specifically, megawatt wind power machine maximum chord length is generally 7% of length of blade or so, it is typically in blade 0.1R
Place, and chord length is generally 1.5% of length of blade or so at 0.9R, therefore chord length expression formula can be obtained according to the above principle are as follows:
C=(0.076875-0.06875 μ) Lb
From the above equation, we can see that foline chord length is the function of length of blade, after being applied in BEM method, can avoid iterating
Process.
(4) suitable foline aerofoil profile is selected, guarantees the aeroperformance of wind energy conversion system；
After the chord length value for determining each section foline of blade, suitable aerofoil profile is selected.The present invention is in blade root position using China
The aerofoil profile (present invention indicates this aerofoil profile with GAS60) that the relative thickness of academy of sciences's research and development is 60% is guaranteeing blade root intensity
Under the premise of, middle part and blade tip position use NACA family of aerofoil sections.
Specifically, aerofoil profile selected by 10 megawatts of high-power wind mills of design is respectively GAS60, WORTMANN FX
77-W-343, WORTMANN FX 77-W-258, NACA 63A018, NACA 63-015A and NACA 4412.Fig. 4 is the present invention
The profile diagram of selected aerofoil profile.
(5) calculating of foline aerofoil profile Reynolds number；
After aerofoil profile is selected, the design method proposed according to the present invention determines each foline operation Reynolds number.It is typically chosen
When the angle of attack of aerofoil profile, the optimal attack angle under aerofoil profile operating Reynolds number is taken, so that blade aerodynamic performance is optimal.Aerofoil profile Reynolds number
It is calculate by the following formula:
γ in formula --- air movement viscosity (m2/ s), 1.385 × 10 are taken in normal conditions-5m2/s；
V --- it is parallel to the wind speed (m/s) of string (i.e. 0 ° of aerofoil profile becomes a mandarin)；
(6) calculating of the parameter of aerodynamic characteristics such as wing section lift coefficient, resistance coefficient and optimal attack angle；
After the design method proposed according to the present invention determines each foline operation Reynolds number, and then aerofoil profile is solved in specific Reynolds
Lift coefficient C under severalL, resistance coefficient CDAnd the parameter of aerodynamic characteristics such as optimal attack angle α.Calculating for parameter of aerodynamic characteristics, can
Using the XFOIL software direct solution based on panel method, or the FInite Element based on Fluent software.The present invention is with the GAS60 wing
For type, using the finite element model for solving based on Fluent software, remaining aerofoil profile aerodynamic characteristic is solved using XFOIL software.
Specific step is as follows:
(6.1) GAS60 aerofoil profile grid dividing.
For GAS60 aerofoil profile, using the O-shaped grid in ICEM software, GAS60 aerofoil profile finite element as shown in Figure 5
Model.According to the principle of similitude, the practical chord length of aerofoil profile is contracted to 1m and is calculated.First layer web thickness takes 0.02mm, grid
Growth rate is 1.005.Grid sum is 64800, and wherein airfoil surface number of grid is 800, and fluid domain number of grid is
64000；Node total number is 64400.
(6.2) GAS60 aerofoil profile Aerodynamic characteristics.
It is designed due to using blunt trailing edge, when the GAS60 aerofoil profile angle of attack after solution is 0 °~20 ° of ranges, there are bright for trailing edge
Aobvious vortex；When angle of attack≤9 °, trailing edge vortex does not clearly result in the separation of top airfoil air-flow, ensure that the aerofoil profile optimum pneumatic
Energy；When angle of attack≤10 °, separation takes place in top airfoil air-flow, and with the increase of the angle of attack, gradually forward edge is mobile for burble point, this
When resistance start substantial increase, lift is begun to decline.From GAS60 aerofoil profile aerodynamic characteristic curve shown in fig. 6 it can be concluded that this
The optimal attack angle position of aerofoil profile is at α=9 °.
(7) calculating of foline aerofoil profile inflow angle；
Specifically, foline velocity composite figure and stress composite diagram as shown in Figure 7, the air-flow behind wind wheel section is axial
Speed is v∞(1-a), by angular momentum theorem it is found that tangential velocity at this time is Ω r (1+a '), aggregate velocity W, each variable with
The relationship of inflow angle are as follows:
The new relational expression about inflow angle of construction, can obtain:
By novel chord length formula, axial inducible factor and circumferential inducible factor expression formula substitute into above formula, can obtain:
As y=0, equation root seeks to the inflow angle solved.
(8) tangential tractive force coefficient C is calculatedxWith axial thrust coefficient Cy；
According to power composition principle, define:
Cx=CLcosφ+CDsinφ
Cy=CLsinφ-CDcosφ
Since near optimal attack angle, lift resistance ratio is generally all very big, therefore if ignoring profile drag, above-mentioned two formula can
It indicates are as follows:
Cx≈CLcosφ
Cy≈CLsinφ
(9) specific value of inducible factor is calculated；
By the inflow angle φ solved, tangential tractive force coefficient CxWith axial thrust coefficient CySubstitute into the axial direction that (2.2) obtain
Inducible factor a and circumferential inducible factor a ' expression formula, solve the specific value of axial inducible factor and circumferential inducible factor.
Axial inducible factor as shown in Figure 8 and circumferential inducible factor are regular along spanwise distribution it is found that axial induction
There is obvious difference in the regularity of distribution that factor a extends length direction, reflects different airfoil profiles race and is applied to same leaf
When on piece, there is a problem of pneumatic compatibility.Circumferential inducible factor a ' extends length direction and regular downward trend is presented, and is by each
Caused by foline inflow angle.Axial direction inducible factor a is up to 0.3068 as the result is shown, shows that the calculating that the present invention is derived is public
Formula and the scope of application for being less than momentum theorem, while also and being less than Betz limit.Therefore the design method that the present invention derives
Meet objective law, be applied on high-power wind mill blade Design of Aerodynamic Configuration, is practicable.
(10) calculating of aerofoil profile torsional angle；
The inflow angle φ of foline aerofoil profile is obtained about the unitary nonlinear equation of inflow angle by constructing, by based on limited
The Fluent software of first method and the XFOIL software based on panel method obtain the optimal attack angle of aerofoil profile.According to Fig.7, torsional angle with enter
The relationship of angle and the angle of attack is flowed, and then obtains torsional angle β are as follows:
β=φ-α
(11) according to the calculating and analysis of the above blade parameter, 10 megawatts of high-power wind power generations that the present invention designs are obtained
The design parameter of machine blade, as shown in table 2.Fig. 9 is the blade plane figure that the present invention creates.
2 10 megawatts of pneumatic equipment bladess parameter lists of table
Table 2Airfoil profile
(12) power of designed blade is verified；
Because the design method is based on the momentum theory derivation of equation, therefore actual power is verified using foline theory.According to
The torque formula of foline theory deduction calculates power, torque expression formula are as follows:
Corrected performance after calculating torque, function of the high-power wind mill designed according to the method for the present invention under declared working condition
Rate is 11.08 megawatts, has reached design requirement.
Figure 10 is 10 megawatts of concept wind energy conversion system power contrast's curve graphs that the present invention is designed with Technical University Of Denmark.Due to leaning on
It is 60% aerofoil profile that nearly blade root, which has used relative thickness, this aerofoil profile can be provided at low wind speeds compared with lift, therefore wind energy conversion system
Low speed starting performance comparative superiority, in the low wind speed region of 4~9m/s, power is compared with 10 megawatts of wind that Technical University Of Denmark designs
Power machine is high by 13% or more.
Claims (2)
1. a kind of Design of Aerodynamic Configuration method of high-power wind mill blade derives blade tip, the leaf for being suitable for high-power wind mill
Root loss coefficient；The mathematical model that novel chord length solves is constructed using the method for interpolation；It constructs non-thread about the unitary of inflow angle
Property equation, solve the specific value of axial inducible factor and circumferential inducible factor, and then calculate the parameters such as thrust and torque；It determines
Foline aerofoil profile, solves parameter of aerodynamic characteristics at each foline operation Reynolds number, analyzes the aerodynamic characteristic step of aerofoil profile；
It is characterized by: specific step is as follows,
(1) according to the rule of vortex in wake, the tip loss coefficient F suitable for high-power wind mill is derivedtIt is lost with blade root and is
Number Fr:
F in formulat--- tip loss coefficient；
Fr--- blade root loss coefficient；
μ --- aerofoil position radius ratio；
rhub--- hub radius；
B --- blade quantity；
R ' --- foline aerofoil profile position；
Based on momentum theory, solve axial direction inducible factor a's and circumferential inducible factor a ' by simultaneous thrust and torque expression formula
Expression formula:
A in formula --- axial inducible factor；
A ' --- circumferential inducible factor；
φ --- inflow angle；
R --- wind wheel radius；
C --- chord length；
Cx--- tangential tractive force coefficient；
Cy--- axial thrust coefficient；
N --- blade quantity；
F --- total losses coefficient；
(2) chord length formula is constructed by the way of curve matching, establishes a kind of chord length method for solving:
C=(0.076875-0.06875 μ) Lb
L in formulab--- length of blade (m)；
(3) determination for passing through step (2) chord length, is designed the aerodynamic configuration of high-power wind-driven generator blade；
(3.1) suitable foline aerofoil profile is selected, guarantees the pneumatic efficiency of wind energy conversion system；
(3.2) each foline operation Reynolds number, the Fluent software of XFOIL software and FInite Element based on panel method, meter are determined
The parameter of aerodynamic characteristics such as pitch axes, lift coefficient, resistance coefficient, the optimal attack angle of aerofoil profile are calculated, and to the aerodynamic characteristic of aerofoil profile
It is analyzed；
(4) parameter of aerodynamic characteristics of aerofoil profile is obtained by step (3), is solved in conjunction with the loss coefficient of step (1) and step (2)
Chord length constructs unitary nonlinear equation about inflow angle, and the problem of nonlinear multivariable solving equations based on BEM method is become
At the solution of unitary nonlinear equation；
The angular velocity of rotation rad/s of Ω in formula --- air-flow；
v∞--- arrives stream wind speed m/s；
CD--- resistance coefficient；
CL--- lift coefficient；
As y=0, equation root seeks to the inflow angle solved；
(5) wing section lift coefficient, the resistance coefficient obtained according to the inflow angle of step (4) solution and step (3) calculates the foline wing
The tangential tractive force coefficient C of typexWith axial thrust coefficient Cy；
(6) the tangential tractive force coefficient C that step (5) is calculatedx, axial thrust coefficient CyThe inflow angle solved with step (4)
φ substitutes into axial direction inducible factor a and circumferential inducible factor a ' expression formula, solves axial inducible factor and circumferential inducible factor
Specific value；
(7) this method be based on the momentum theory derivation of equation, actual power is verified using foline theory, and with Denmark's technology
10 megawatts of power wind energy conversion systems of university's design compare.
2. a kind of Design of Aerodynamic Configuration method of high-power wind mill blade according to claim 1, it is characterised in that: mention
Chord length formula and tip loss coefficient, blade root loss coefficient out is not necessarily to participate in iterative solution, can immediately arrive at design result,
The problem of making the solution procedure of inflow angle become solution unitary nonlinear equation from the problem of solution nonlinear multivariable equation group, it is
Large-scale wind electricity machine blade aerodynamic configuration design provides a set of feasible technical solution.
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| CN117436322A (en) * | 2023-12-21 | 2024-01-23 | 浙江远算科技有限公司 | Wind turbine blade aeroelastic simulation method and medium based on phyllin theory |
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