CN109583023A - A kind of pneumatic equipment bladess trailing edge modeling method - Google Patents
A kind of pneumatic equipment bladess trailing edge modeling method Download PDFInfo
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- CN109583023A CN109583023A CN201811271191.XA CN201811271191A CN109583023A CN 109583023 A CN109583023 A CN 109583023A CN 201811271191 A CN201811271191 A CN 201811271191A CN 109583023 A CN109583023 A CN 109583023A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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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
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
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- 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
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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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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention relates to a kind of pneumatic equipment bladess trailing edge modeling methods, method includes the following steps: being (1) converted to aerofoil profile original two dimensional coordinate data using aerodynamic center as origin, chord length direction isxThe two-dimensional coordinate of axis；(2) by three-dimensional modeling UG Software Create blade airfoil family and skin-surface, and blade shear web is established by way of plane cutting, obtain blade three-dimensional shells model；(3) trailing edge modeling is carried out, after the trapezoidal sketch of each aerofoil section of completing, solid element is generated to get three-dimensional reality-shell leaf model using scanning mixing order to all adjacent sketches；(4) select glass reinforced plastic epoxy resin composite material as blade laminated material；(5) after completing specific laying in ANSYS analysis project, static analysis module is introduced in analysis project, and multi-point constraint is applied with solid element respectively to the trailing edge modeling upper and lower aerofoil in region in the module；Boundary condition finally is applied to get reality-Shell Finite Element Method model to blade.Simulation analysis precision can be improved in the present invention.
Description
Technical field
The present invention relates to pneumatic equipment bladess technical field more particularly to a kind of pneumatic equipment bladess trailing edge modeling methods.
Background technique
Blade design is to acquire changing repeatedly for optimal compromise solution between Airfoil Design, structure design and aeroelasticity response
For process, finite element analysis is extremely important a part during blade design.The finite element mould used in most of documents
Type has simplified Flexural cantilever model, the model based on housing unit and the threedimensional model based on solid element.Theoretically, based on real
The threedimensional model of body unit have higher analysis precision, it is applied widely, but accompanying problem is that modeling complexity and
The increase of calculation amount strongly limits its application in actual analysis.In comparison, Flexural cantilever model modeling is simple and counts
It is counted as originally substantially reducing, the stress-strain analysis along spanwise beam section can be carried out, but the shortcomings that model is to cannot be used for
Geometrical nonlinear analysis and stability analysis, and in the inefficacy mechanism and mode for determining blade, geometrical nonlinear analysis and steady
Qualitative analysis is again essential, therefore Flexural cantilever model is only applicable to the iterative calculation of the first time in blade design.
Thus using in simulation analysis at most is the model based on housing unit, and the model is than solid finite meta-model
It more can accurately predict transverse shear stresses, but the practical blade of rigidity at Shell model trailing edge gluing connecting line position is inclined
It is low, this is because software can ignore the rigidity of laying lap, this undoubtedly will lead to blade trailing edge when carrying out blade laying
The deficiency of even entire blade stiffness, when causing structural response analysis not precisely.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of pneumatic equipment bladess trailing edges for improving simulation analysis precision to build
Mould method.
To solve the above problems, a kind of pneumatic equipment bladess trailing edge modeling method of the present invention, comprising the following steps:
(1) generate software Pro file using professional aerofoil profile to obtain using leading edge as coordinate origin, chord length direction isxAxis forward direction
Aerofoil profile original two dimensional coordinate data (x 0,y 0), then the two-dimensional coordinate is converted to using aerodynamic center as origin, chord length direction isx
Axis two-dimensional coordinate (x 1,y 1)；
The aerodynamic center to leading edge distance be usually (0.23 ~ 0.24) ×c；
Assuming that aerodynamic center coordinate be (X,Y), then (x 1, x 2)=(x 0,y 0)-(X,Y)；By coordinate (x 1, x 2) multiplied by respective cross-section
The chord length at place obtains discrete two-dimensional coordinate corresponding to practical chord length, these discrete two-dimensional coordinates are then substituted into rotational coordinates and are turned
Change formula to get each aerofoil profile real space three-dimensional coordinate (x,y,z)；
The rotational coordinates conversion formula isIt is transformed to obtain；Wherein:c For aerofoil profile chord length, unit m；θFor the wing
Type torsional angle, unit are °；r Distance for aerofoil profile away from blade root, unit m；
(2) by the practical three-dimensional coordinate data of aerofoil profile at each section of program calculation spanwise, and by the three-dimensional space of the aerofoil profile
Coordinate data passes through three-dimensional modeling UG Software Create blade airfoil family with the preservation of .dat file format；Successively choose each wing
Type generates three dimendional blade model, then the three dimendional blade model established in UG is imported finite element software with .IGS file format
In ANSYS, blade shear web is established by way of plane cutting, obtains blade three-dimensional shells model；
(3) the blade three-dimensional shells model is exported as into .IGS file, import progress trailing edge in 3 d modeling software Creo and build
Mould, modeling range are along the trailing edge gluing connecting line region of spanwise 1.5m to 25.5m, and each aerofoil profile within this range is cut
Isosceles trapezoid sketch is drawn on face, trapezoidal height is 80mm, and upper bottom length is corresponding aerofoil section distance up and down
One third；After the completion of each trapezoidal sketch drafting of aerofoil section, entity is generated using scanning mixing order to all adjacent sketches
Unit is to get three-dimensional reality-shell leaf model；
(4) select glass reinforced plastic epoxy resin composite material as blade laminated material；
(5) ACP(Pre is introduced in ANSYS analysis project) module, the three-dimensional reality-shell leaf model is imported,
Blade material attribute is set in Engineering Data, grid dividing, laying region division are carried out in Model and phase is set
The Name Selection answered, completes specific laying in Setup；Then static analysis module is introduced in analysis project is
Static structural module, then the composite shell data in ACP(Pre) module is transmitted to static
Structural module applies multi-point constraint with solid element respectively to the trailing edge modeling upper and lower aerofoil in region in the module；Most
Boundary condition is applied to get reality-Shell Finite Element Method model to blade afterwards.
Compared with the prior art, the present invention has the following advantages:
1, the present invention on the basis of housing unit to trailing edge gluing connecting line position introduce solid element, and by solid element with
Upper-lower casing aerofoil multi-point constraint, obtains reality-Shell model, solves the problems, such as pure Shell model trailing edge insufficient rigidity.
2, simulation analysis is carried out under limit loading conditions using the model that the method for the present invention is established, and is provided with certain enterprise
Blade limit static response test data compared, amount of deflection, in terms of all than pure Shell model have better one
Cause property, it was demonstrated that finite element model of the present invention improves the reliability of blade construction response prediction.
3, the reality-Shell model simulation result and error of test data established using the method for the present invention are minimum, prediction is tied
Fruit is most accurate, and under ultimate load effect, bending deformation does not occur for trailing edge region, can be used for ultimate strength assessment and stablizes
Property analysis.
Detailed description of the invention
Specific embodiments of the present invention will be described in further detail with reference to the accompanying drawing.
Fig. 1 is blade airfoil family of the invention.
Fig. 2 is blade three-dimensional shells model of the invention.
Fig. 3 is that blade trailing edge of the invention models isosceles trapezoid sketch.
Fig. 4 is reality of the invention-Shell Finite Element Method model.
Fig. 5 is the shimmy direct limit static(al) testing experiment schematic diagram of certain enterprise's blade, other directions are similar.
Fig. 6 is the loading method signal that aerodynamic center of the present invention is coupled with aerofoil profile.
Fig. 7 is three kinds of model trailing edge bending deformation comparisons.
Fig. 8 is the shimmy negative sense amount of deflection comparison of blade in three kinds of models and test.
Fig. 9 is three kinds of model trailing edge gluing connecting line camber data comparisons.
Figure 10 is that the negative sense strain of waving of blade in three kinds of models and test compares.
Specific embodiment
A kind of pneumatic equipment bladess trailing edge modeling method, comprising the following steps:
(1) generate software Pro file using professional aerofoil profile to obtain using leading edge as coordinate origin, chord length direction is (after leading edge is directed toward
Edge) bexAxis forward direction aerofoil profile original two dimensional coordinate data (x 0,y 0), then the two-dimensional coordinate is converted to aerodynamic center as original
Point, chord length direction arex Axis two-dimensional coordinate (x 1,y 1).
Aerodynamic center to leading edge distance be usually (0.23 ~ 0.24) ×c；
Assuming that aerodynamic center coordinate be (X,Y), then (x 1, x 2)=(x 0,y 0)-(X,Y)；By coordinate (x 1, x 2) multiplied by respective cross-section
The chord length at place obtains discrete two-dimensional coordinate corresponding to practical chord length, these discrete two-dimensional coordinates are then substituted into rotational coordinates and are turned
Change formula to get each aerofoil profile real space three-dimensional coordinate (x,y,z)；
Rotational coordinates conversion formula isIt is transformed to obtain。
Wherein:c For aerofoil profile chord length, unit m；θFor aerofoil profile torsional angle, unit is °；r Distance for aerofoil profile away from blade root, it is single
Position is m.
(2) by the practical three-dimensional coordinate data (referring to table 1) of aerofoil profile at each section of program calculation spanwise, and should
The three dimensional space coordinate data of aerofoil profile pass through the " insertion-curve-sample of three-dimensional modeling UG software with the preservation of .dat file format
Point in item-file " order imports each aerofoil profile coordinate data being calculated, and generates vane airfoil profile using cubic spline order
Race is as shown in Figure 1；Each aerofoil profile is successively chosen, three dimendional blade model is generated by " insertion-curved surface-passes through curve group " order, then
The three dimendional blade model established in UG is imported in FEM-software ANSYS with .IGS file format, passes through plane cutting
Mode establishes blade shear web, obtains blade three-dimensional shells model shown in Fig. 2.
Table 1
(3) blade three-dimensional shells model is exported as into .IGS file, import and carry out trailing edge modeling in 3 d modeling software Creo, build
Model is enclosed for along the trailing edge gluing connecting line region of spanwise 1.5m to 25.5m, each aerofoil section within this range
Draw isosceles trapezoid sketch shown in Fig. 3, trapezoidal height is 80mm, upper bottom length be corresponding upper and lower aerofoil section away from
From one third；After the completion of each trapezoidal sketch drafting of aerofoil section, all adjacent sketches are generated using scanning mixing order
Solid element is to get three-dimensional reality-shell leaf model.
(4) select glass reinforced plastic epoxy resin composite material as blade laminated material.
(5) ACP(Pre is introduced in ANSYS analysis project) module, three-dimensional reality-shell leaf model is imported,
Blade material attribute shown in table 2 is set in Engineering Data, grid dividing is carried out in Model, laying region is drawn
Divide and be arranged corresponding Name Selection, specific laying is completed in Setup；Then static(al) point is introduced in analysis project
Module, that is, static structural module is analysed, then the composite shell data in ACP(Pre) module is transmitted to
Static structural module applies multiple spot with solid element respectively to the trailing edge modeling upper and lower aerofoil in region in the module
Constraint.Specifically as shown in figure 4, trailing edge is first modeled the point on region top airfoil Curve of wing and the point two of solid element upper surface
Two establish solder joint connection, then the point on lower aerofoil Curve of wing is established solder joint with the point of solid element lower surface two-by-two and is connected,
Beam element is introduced respectively between solid element and upper and lower aerofoil any two points；Finally to blade apply boundary condition to get
Reality-Shell Finite Element Method model.
The primary structural material of 2 blade of table and the mechanics fundamental characteristics parameter of auxiliary material
1.5MW pneumatic equipment bladess Shell model, vane overall length 40.25m, the model and reality are established by 3 d modeling software UG
The blade construction on border is corresponding, is made of primary load bearing structure girder, upper and lower surface skins and shear web.
Fig. 5 is the shimmy direct limit static(al) testing experiment schematic diagram of certain enterprise's blade, other directions are similar, blade and test
Platform is connected by wheel hub, and blade root bolt applies 300KN pretightning force, uses crane at away from blade root 12m, 18m, 24m, 33m respectively
It loads straight up simultaneously, table 3 show the specific value for applying load.In order to which in simulation analysis, simulation is true as far as possible
Load condition, load is coupled using aerodynamic center shown in fig. 6 with aerofoil profile in software load by the way of, i.e. aerodynamic center and aerofoil profile
Load is applied to aerodynamic center by curve coupling constraint, and load is transmitted on blade surface by coupling constraint.
Table 3
In order to highlight the superiority of proposed trailing edge modeling method, in spanwise 1.5m to trailing edge gluing between 25.5m
Three kinds of different trailing edge models are established in connecting line region, respectively wave with deployment analysis in shimmy both direction, and be extracted
The data such as corresponding amount of deflection, strain, compare and analyze with test data.
[bending deformation analysis]
Limit basic load can cause large compressive strain and compression in trailing edge region, may result in trailing edge buckling shown in Fig. 7
Deformation.Wherein figure a indicates the simulation result based on pure Shell model, it is clear that under ultimate load, the part tail of pure Shell model
Edge region has occurred that serious bending deformation, shows that the ultimate load has been more than the yield load of pure Shell model, true
On be computed discovery, the yield load of pure Shell model has only reached the 86% of the ultimate load；In comparison, latter two mould
Type has better simulation result, the especially corresponding reality-Shell model of figure c, and there is no bending deformations, and simulation result is most
It is good.
[amount of deflection analysis]
Fig. 8 is the shimmy negative sense amount of deflection comparison of blade in three kinds of models and test, and horizontal axis indicates the span radius of blade, i.e., locally
The distance between position and blade root, the longitudinal axis indicate shimmy negative sense amount of deflection.As can be seen from the figure pure Shell model amount of deflection is maximum, more
The Shell model of point constraint takes second place, and reality-Shell model is minimum, this is because trailing edge modeling is so that trailing edge region rigidity is increased
Add, to slightly improve blade stiffness.On the whole, reality-Shell model amount of deflection and test data have better compatible degree.
In order to significantly more find out influence of three kinds of modeling strategies to trailing edge amount of deflection, extract on part trailing edge gluing connecting line
Deflection data is analyzed, as shown in figure 9, horizontal axis indicates distance of each point away from blade root on gluing connecting line, the longitudinal axis indicates shimmy
Positive amount of deflection.Obviously, waveform is presented in pure Shell model and multi-point constraint Shell model amount of deflection, this is because first two model
Trailing edge region has occurred bending deformation, and waveform as shown in the figure is the linear of trailing edge region entirety amount of deflection bending deformation with itself
Superposition；And reality-Shell model deflection value is essentially straight, and bending deformation does not occur from this position of the side illustration model,
The structural response of blade can be better anticipated.
[strain analysis] numerical simulation reliable for one, strain analysis is also of crucial importance, and Figure 10 is three kinds of models
Negative sense strain of waving with blade in test compares, and wherein horizontal axis indicates that span radius, the longitudinal axis indicate strain.It can from figure
Out between 9 ~ 22.5m of spanwise, the prediction strain of three kinds of models is close with the error of test data, has no obvious excellent
It is bad, however from strain data comparison between 22.5 ~ 36m it is clear that prediction of the reality-Shell model than first two model misses
Difference is smaller, as a result more acurrate.The strain data comparison in other directions has similar rule.
Claims (1)
1. a kind of pneumatic equipment bladess trailing edge modeling method, comprising the following steps:
(1) generate software Pro file using professional aerofoil profile to obtain using leading edge as coordinate origin, chord length direction isxAxis forward direction
Aerofoil profile original two dimensional coordinate data (x 0,y 0), then the two-dimensional coordinate is converted to using aerodynamic center as origin, chord length direction isx
Axis two-dimensional coordinate (x 1,y 1)；
The aerodynamic center to leading edge distance be usually (0.23 ~ 0.24) ×c；
Assuming that aerodynamic center coordinate be (X,Y), then (x 1, x 2)=(x 0,y 0)-(X,Y)；By coordinate (x 1, x 2) multiplied by respective cross-section
The chord length at place obtains discrete two-dimensional coordinate corresponding to practical chord length, these discrete two-dimensional coordinates are then substituted into rotational coordinates and are turned
Change formula to get each aerofoil profile real space three-dimensional coordinate (x,y,z)；
The rotational coordinates conversion formula isIt is transformed to obtain；Wherein:c For aerofoil profile chord length, unit m；θFor the wing
Type torsional angle, unit are °；r Distance for aerofoil profile away from blade root, unit m；
(2) by the practical three-dimensional coordinate data of aerofoil profile at each section of program calculation spanwise, and by the three-dimensional space of the aerofoil profile
Coordinate data passes through three-dimensional modeling UG Software Create blade airfoil family with the preservation of .dat file format；Successively choose each wing
Type generates three dimendional blade model, then the three dimendional blade model established in UG is imported finite element software with .IGS file format
In ANSYS, blade shear web is established by way of plane cutting, obtains blade three-dimensional shells model；
(3) the blade three-dimensional shells model is exported as into .IGS file, import progress trailing edge in 3 d modeling software Creo and build
Mould, modeling range are along the trailing edge gluing connecting line region of spanwise 1.5m to 25.5m, and each aerofoil profile within this range is cut
Isosceles trapezoid sketch is drawn on face, trapezoidal height is 80mm, and upper bottom length is corresponding aerofoil section distance up and down
One third；After the completion of each trapezoidal sketch drafting of aerofoil section, entity is generated using scanning mixing order to all adjacent sketches
Unit is to get three-dimensional reality-shell leaf model；
(4) select glass reinforced plastic epoxy resin composite material as blade laminated material；
(5) ACP(Pre is introduced in ANSYS analysis project) module, the three-dimensional reality-shell leaf model is imported,
Blade material attribute is set in Engineering Data, grid dividing, laying region division are carried out in Model and phase is set
The Name Selection answered, completes specific laying in Setup；Then static analysis module is introduced in analysis project is
Static structural module, then the composite shell data in ACP(Pre) module is transmitted to static
Structural module applies multi-point constraint with solid element respectively to the trailing edge modeling upper and lower aerofoil in region in the module；Most
Boundary condition is applied to get reality-Shell Finite Element Method model to blade afterwards.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110717224A (en) * | 2019-09-20 | 2020-01-21 | 湖北工业大学 | Method for calculating cross section characteristics of composite material wind turbine blade |
| CN112528426A (en) * | 2020-11-16 | 2021-03-19 | 中国航发西安动力控制科技有限公司 | Method for establishing three-dimensional cam materialized model based on coordinate point position conversion |
| CN112922774A (en) * | 2021-03-17 | 2021-06-08 | 兰州理工大学 | High-lift wind turbine wing section |
| CN113297776A (en) * | 2021-06-11 | 2021-08-24 | 广东工业大学 | Finite element modeling and layering method for wind turbine blade |
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| WO2008003330A1 (en) * | 2006-07-07 | 2008-01-10 | Danmarks Tekniske Universitet (Technical University Of Denmark) | Variable trailing edge section geometry for wind turbine blade |
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| WO2008003330A1 (en) * | 2006-07-07 | 2008-01-10 | Danmarks Tekniske Universitet (Technical University Of Denmark) | Variable trailing edge section geometry for wind turbine blade |
| CN105863954A (en) * | 2016-03-25 | 2016-08-17 | 天津工业大学 | Method for designing wind turbine airfoil profile blunt trailing edges based on geometric transformation |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110717224A (en) * | 2019-09-20 | 2020-01-21 | 湖北工业大学 | Method for calculating cross section characteristics of composite material wind turbine blade |
| CN112528426A (en) * | 2020-11-16 | 2021-03-19 | 中国航发西安动力控制科技有限公司 | Method for establishing three-dimensional cam materialized model based on coordinate point position conversion |
| CN112922774A (en) * | 2021-03-17 | 2021-06-08 | 兰州理工大学 | High-lift wind turbine wing section |
| CN113297776A (en) * | 2021-06-11 | 2021-08-24 | 广东工业大学 | Finite element modeling and layering method for wind turbine blade |
| CN113297776B (en) * | 2021-06-11 | 2022-09-23 | 广东工业大学 | Finite element modeling and layering method for wind turbine blade |
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Application publication date: 20190405 |