Detailed description of the invention
Referring more specifically to accompanying drawing, can be wind turbine manufacture as shown in Figure 1 and service sideMethod 100 embodiment of the disclosure described in the background of the wind turbine 200 shown in Fig. 2.It is turning initially to Fig. 1, describes the figure of wind turbine manufacture and method of servicing according to advantageous embodimentSolve.During pre-manufactured, wind turbine manufacture and method of servicing 100 can include in Fig. 2The specification of wind turbine 200 and design 102 and material purchases 104.
At production period, the component and the sub-component that carry out wind turbine 200 in Fig. 2 manufacture 106With the system integration 108.Then, the wind turbine 200 in Fig. 2 is in order to use 112 to carry outCalibrating and payment 110.When being used 112 by client, arrange the wind turbine 200 in Fig. 2Carry out regular maintenance and service 114, can include improving, reconfigure, renovate and other maintenancesOr service.
Each process of wind turbine manufacture and method of servicing 100 can be supplied by system synthesisBusiness, third party and/or operator perform.In these examples, operator can be client.ForThis description, system integrator can include but not limited to some wind turbine manufacturerWith main system subcontractor；Third party can include but not limited to some sellers, subcontractor and supplyBusiness；And operator can be Utilities Electric Co., leasing company, NGO, service organization etc.Deng.
With reference now to Fig. 2, describe the figure of the wind turbine that wherein can implement advantageous embodimentSolve.In this example, the wind turbine manufacture in Fig. 1 and method of servicing 100 wind is producedPower turbine 200, and wind turbine 200 can include tower 202, armature spindle 204, hub206, blade 208, gear-box 210, brakes 212, location engine 214 and electromotor216。
Depend on that enforcement can include other components some.Although showing wind turbine example,But different advantageous embodiments can apply to use other industries of aerofoil profile.One exemplaryExample is aircraft manufacture industry.
Tower 202 is the structure supporting other components in wind turbine 200.Such as, tower 202Support armature spindle 204, hub 206, blade 208, gear-box 210, brakes 212, locationElectromotor 214 and electromotor 216.Blade 208 connects hub 206.Hub 206 and then connection rotorAxle 204.When there is wind, blade 208 causes armature spindle 204 to rotate.
As used herein, the first component connection second component refers to that the first component can be directlyOr indirectly connect second component.In other words, extra component may reside in the first componentAnd between second component.When the first component is directly connected second component, the two component itBetween the most there is not extra component.
Electromotor 216 responds the rotation of armature spindle 204 and produces electricity.Gear-box 210 may be used for increasingThe rotating speed of big blade 208, thus the speed needed for match generator.Brakes 212 is permissibleFor making spin down and/or the stopping of armature spindle 204.
Equipment contained herein and method can manufacture kimonos by shown wind turbine in FIGUse during at least one stage of business method 100.As used herein, when lising with oneWhen mesh is used together, term " at least one " refers to use in cited projectOr multiple various combinations, and each project in list may have only to one.Such as," at least one in project A, project B and project C " can include, for example, but not limited to,Project A or project A and project B.This example can also include project A, project B and projectC or project B and project C.
In an illustrative example, can with when wind turbine 200 is in the use of Fig. 1Manufacture component or the similar mode of assembly component in FIG time in 112 and sub-component manufactures 106Middle manufacture component or assembly.
In another example, some apparatus embodiments, method can be used to implement in the production phaseComponent in example or a combination thereof, such as Fig. 1 and sub-component manufacture 106 and the system integration 108.WhenWhen referring to project, the one or more project of some fingers.Such as, some apparatus embodiments are oneIndividual or multiple apparatus embodiments.
When wind turbine 200 is in the maintenance used in 112 and/or in FIG and service 114Period can use some apparatus embodiments, embodiment of the method or a combination thereof.Use some differencesAdvantageous embodiment can accelerate significantly turbine 200 assembling process and/or reduce turbineThe cost of machine 200.
Different advantageous embodiments recognizes and considers some different Considerations.As used herein, some, when referring to project, refer to one or more project.Such as, " some examineWorry factor " it is one or more Considerations.Such as, different advantageous embodiments recognizes and examinesConsidering wind turbine blade and generally comprise two curved surfaces being fabricated by by fabric, fabric comprises noteEnter the glass fibre of liquid resin.These faces can also be referred to as shell.These shells existConnect at the leading edge of aerofoil profile and trailing edge.Additionally, some structural elements can exist between shell.ExampleAs, one or more beam columns can be inside turbine blade.
Different advantageous embodiments recognizes and considers: uses and currently available is applicable to wind turbineThe manufacturing technology of machine Leaf controls resin stream and is probably difficulty.Different advantageous embodiments is recognizedKnow and consider that the resin obtaining even amount throughout turbine blade is probably difficulty.ResinInconsistent level can cause the discordance needing to reform or abandon turbine blade.Such as,These discordances can include space.Space is that a part of turbine blade does not has resin.
Different advantageous embodiments recognizes and considers: a solution can include using preimpregnationTreatment of Carbon composite replaces the resin transfer process of vacuum aided.In other words, permissibleResin is used to have been injected into the fiber in fiber.These materials can be referred to as presoaking assembly.CanDifferent components is manufactured to lay these leachings process assembly.Then can be assembled these differentComponent formed blade.Different advantageous embodiments recognizes and consider can be by using at preimpregnationManage carbon fibre composite and avoid relating to a difficult problem for resin by injection.
Further, different advantageous embodiments recognizes and considers: fine with by resin implantation glassDimension formed aerofoil profile compare, by carbon fibre composite formed the most substantially without microgroove(wrinkle) aerofoil profile makes the intensity of aerofoil profile increase, and weight reduces.
Different advantageous embodiments recognizes and considers: use preimpregnation assembly can reduce inconsistentProperty, but but can not reduce the time manufacturing turbine blade as desired.Such as, differentAdvantageous embodiment recognizes and considers: can use composite by paver in a moldPreimpregnation assembly.Different advantageous embodiments recognizes and considers: mould is usually inner lining mould(interline mold).In other words, preimpregnation assembly is placed on mould inside.
Different advantageous embodiments recognizes and considers: can be with hands or computer numerical control (CNC)(CNC) preimpregnation assembly laid by lathe.Different advantageous embodiments recognizes and considers manually pavingIf preimpregnation assembly is time-consuming, and easily makes mistakes.Further, different advantageous embodimentsRecognize and consider: using cnc machine tool to be routed to be applicable to new parts by preimpregnation assemblyMould in may need the five axis program (five-axis for each shell and each designProgram), five axis programs are more complicated than intended.Additionally, different advantageous embodiments is recognizedKnow and consider: such process may remain a need for assembling single parts, thus completesBlade.
Different advantageous embodiments recognizes and considers: with currently available during independent of otherComponent forms each component of aerofoil profile and compares, and forms aerofoil profile during identical forming processDifferent component can reduce the formation time of aerofoil profile, energy and/or cost.
Therefore, different advantageous embodiments provides the method and apparatus forming aerofoil profile.Have at oneIn profit embodiment, equipment comprises framework and formation system.Framework is configured to protect relative to instrumentHold preimpregnation assembly.This formation system is associated with framework, and is configured to move relative to instrumentPreimpregnation assembly, thus change the first shape of preimpregnation assembly, and then form the aerofoil profile without microgrooveSecond shape.
With reference now to Fig. 3, describe the diagram of aerofoil profile manufacturing environment according to advantageous embodiment.At thisIn example, aerofoil profile manufacturing environment 300 may be used for manufacturing aerofoil profile 302.Aerofoil profile 302 may be used forWind turbine 200 in Fig. 2.Especially, aerofoil profile 302 can with use blade 304 form,And may be used for the blade 208 in Fig. 2.Aerofoil profile 302 such as can be flown to use other formsThe wing 306 of device.
In this illustrative example, use aerofoil profile to form system 308 and manufacture aerofoil profile 302.Aerofoil profileFormation system 308 comprises framework 310 and formation system 312.Framework 310 is configured to presoakAssembly 314 is positioned at aerofoil profile and is formed in system 308.Preimpregnation assembly 314 can also be referred to as dressMaterial (charge).Preimpregnation assembly is made up of some prepreg material layers.
In these illustrative examples, preimpregnation assembly 314 comprises and some has knitting of resin 320Nitride layer 318.If dry fibre layers 318 has different orientation, this depends on concrete enforcement.
In described example, if dry fibre layers 318 can be made up of some different materials.ExampleAs, if dry fibre layers 318 can be by carbon fiber, metallic fiber, glass-reinforced plastic, strengtheningThe material of carbon fiber plastic and/or other suitable type is constituted.If dry fibre layers 318 uses differenceForm.Such as, if dry fibre layers 318 can be the unipolarity band of different in width, plane volumeFabric, the fiber being woven together, the fiber being stitched together and/or some other suitable shapesFormula.These tissue layer can also be referred to as flaggy (ply).
In these examples, if resin 320 irrigates or is injected in dry fibre layers 318, thus shapeBecome preimpregnation assembly 314.Resin 320 can be to use different forms.Such as but not limited to, resin320 can be epoxy resin, shape-memory polymer and/or the material of some other suitable type.
In these illustrative examples, it is possible to use framework 310 positions pre-relative to instrument 322Leaching assembly 314.Instrument 322 can be to use some different forms.Such as, instrument 322 is permissibleIt is outer mold line 324, some mandrels 326 and/or the instrument of other suitable type.Outer mold line 324It is that preimpregnation assembly 314 is placed on the mould on the outer surface of outer mold line 324.Depend on specificImplementing, outer mold line 324 can also have not only one.Especially, instrument 322 be comprise manyThe Multi-part tool of individual parts 323.For lifting an illustrative example, multiple parts 323In each parts may each be mandrel.
In this illustrative example, framework 310 can have bottom 332, location section 334With motor system 336.In these examples, location section 334 keeps preimpregnation assembly 314.FixedPosition section 334 can move relative to bottom 332.Further, location section 334 is permissibleMove relative to instrument 322.
In these examples described, location section 334 is configured to relative to multiple parts 323If miscellaneous part in moves the dry part in multiple parts 323.Miscellaneous part can connect the endPortion 332.Location section 334 includes the first groove 335.First groove 335 is configured to receiveIf the dry part in multiple parts 323.
Such as, location section 334 can include connection system 337.Connection system 337 is configuredIf for the dry part in multiple parts 323 being connected the location section 334 in the first groove 335.Location section 334 can move relative to bottom 332 and instrument 322, in order to connects locationIf the dry part of section 334 is along with location section 334 is relative to multiple parts 323 of instrument 322In miscellaneous part move.
In these examples, if being not connected with the dry part positioning in multiple parts 323 of section 334Bottom connection 332.If the dry part in multiple parts 323 of the instrument 332 of 332 bottom connectionIncluding the parts for shaping preimpregnation assembly 314.Connect multiple parts 323 of location section 334If dry part in includes the parts being not currently used for shaping preimpregnation assembly 314.By location sectionIf the dry part in the 334 multiple parts 323 supported can be placed on bottom connection 332 multipleOn parts in parts 323 or be connected to connect bottom 332 multiple parts 323 in parts,For shaping preimpregnation assembly 314.
In these illustrative examples, motor system 336 controls location section 334.In other wordsSaying, motor system 336 can be along vertical axis 338 running fix section 334.Certainly, fixedPosition section 334 can move along other axles, and this depends on specifically implementing.Location section 334Can move relative to vertical axis 338, thus relative to instrument 322 location preimpregnation assembly 314.Motor system 336 can be to use the form of some actuators 340.The most some causesDynamic device 340 can be motor machine actuator.
In this illustrative example, formation system 312 is configured to as follows relative to workTool 322 move preimpregnation assembly 314, i.e. change preimpregnation assembly 314 the first shape 328 thusForm the second shape 330 of aerofoil profile 302.
First shape 328 is that preimpregnation assembly 314 is occurring the original shape before any alteration of formShape.Second shape 330 is the shape of component in aerofoil profile 302.Second shape 330 it may be thatSuch as but not limited to, beam column, shell and/or some other suitable shapes.Illustrative at someIn example, the second shape 330 can be the shape of whole aerofoil profile 302.
Second groove 342 is present in formation system 312.Additionally, between the second groove 342 hasGap 344.Gap 344 has the first side 346 and the second side 348.In these illustrative examplesIn, preimpregnation assembly 314 is placed in the gap 344 of the second groove 342.
In these examples, the part of the preimpregnation assembly 314 in the gap 344 of the second groove 342350 appear.Can be become relative to instrument 322 by formation system 312 in these examplesShape part 350.In these illustrative examples, formation system 312 comprises heating system 352With force application system 354.Heating system 352 is configured to some sections of heating preimpregnation assembly 314356, thus form the some heated section 358 of preimpregnation assembly 314.
In these illustrative examples, heating system 352 comprises the first heating assembly 362 andTwo heating assemblies 364.First heating assembly 362 is positioned at the of the gap 344 of the second groove 342Side 346.Second heating assembly 364 is positioned at second side in the gap 344 of the second groove 342348。
As it has been described above, these heating assemblies are both configured to heat the gap being positioned at the second groove 342Corresponding some sections 356 on the either side of 344.In these illustrative examples, if cadreSection 356 can be continuous print and/or discrete section.Such as, the portion in some sections 356Section can have discrete sub-section.In these examples, when some sections 356 are by heatingWhen system 352 heats, the part 350 in gap 344 is some heated sections 358.
Some heated sections 358 can be heated to enough causing some being added by heating system 352Hot section 358 changes into the temperature of its second shape 330 from the first shape 328 of aerofoil profile 302.Force application system 354 can perform the change of first shape the 328 to the second shape 330.Force systemSystem 354 is configured to relative to instrument 322, power 360 is put on some heated sections 358,So that the some heated section 358 of preimpregnation assembly 314 has the second shape in these examplesShape 330.
In these illustrative examples, some heated sections 358 are permissible, such as but not limited to,There is about 100 degrees Fahrenheits temperature to about 130 degrees Fahrenheits.Cause of course, it is possible to usePreimpregnation assembly 314 adapts to maybe to be changed any temperature of shape by force application system 354.
As it has been described above, force application system 354 comprises the first force assembly 366 and the second force assembly368.First force assembly 366 is associated on first side 246 in gap 344 with framework 310.Second force assembly 368 is associated on second side 348 in gap 344 with framework 310.?In these illustrative examples, the first force assembly 366 and the second force assembly 368 are configuredFor moving, power 360 is put on the some heated section 358 of preimpregnation assembly 314, in order toThere is the second shape 330 of aerofoil profile 302 in some heated sections 358.
In these illustrative examples, the first force assembly 366 comprises first some elongated members370 and first motor system 372.Second force assembly 368 comprises second some elongated members 374With secondary motion requirement 376.
First motor system 372 is configured to move first some elongated members relative to instrument 322370, thus power 360 is put on the some heated section 358 of preimpregnation assembly 314.SecondMotor system 376 is configured to move second some elongated members 374 relative to instrument 322, fromAnd power 360 is put on the some heated section 358 of preimpregnation assembly 314.
In these illustrative examples, can be positioned relative to the first side 378 of instrument 322One some elongated members 370, can position second relative to the second side 380 of instrument 322 simultaneouslySome elongated members 374.Therefore, power 360 is put on location by first some elongated members 370Some heated section 358 on the first side 378, second some elongated members 374 will simultaneouslyPower 360 puts on the some heated section 358 on the second side 380 of instrument 322.
First motor system 372 comprises some actuators.Secondary motion requirement 376 comprises some causesDynamic device.One or more actuators in first motor system 372 are configured to independent of firstThe Part II of some elongated members 37 moves the Part I of first some elongated members 370.In a similar manner, the some actuators in secondary motion requirement 376 are configured to independent ofThe Part II of two some elongated members 374 moves first of second some elongated members 374Point.
For one or more advantageous embodiments, by using preimpregnation assembly can reduce in aerofoil profileDiscordance.Further, for one or more advantageous embodiments, computer can be avoidedCost needed for Digit Control Machine Tool and programming.
In different illustrated examples, in addition to preimpregnation assembly 314, it is possible to use extraPreimpregnation assembly.Such as, in some illustrative examples, use except preimpregnation assembly 314 withOuter some preimpregnation assemblies 394 can manufacture aerofoil profile 302.Such as, preimpregnation assembly 314 can beThe shell of aerofoil profile 302, the most some preimpregnation assemblies 394 can form structural detail, the most someBeam column.
Moved relative to instrument 322 at preimpregnation assembly 314 and some preimpregnation assemblies 394,So that preimpregnation assembly 314 and some preimpregnation assemblies 394 are from the first shape 328 of aerofoil profile 302After changing into the second shape 330, can will preimpregnation assembly 314 and some along instrument 322Preimpregnation assembly 394 moves to heating chamber 396, and in heating chamber, heat 398 and/or pressure are used forSolidification preimpregnation assembly 314 and some preimpregnation assemblies 394, thus complete the formation of aerofoil profile 302.SoAfter, can be from aerofoil profile 302 removing tool 322.
The diagram of the aerofoil profile manufacturing environment 300 in Fig. 3 is not meant to that different advantageous embodiments canLimit with the physical restriction implemented or building.Can use in addition to that shown and/or replace instituteOther components shown.Some components can be need not in some advantageous embodiments.And, instituteThe block diagram shown is in order to illustrate some building blocks of functions.When implementing in different advantageous embodiments,One or more square frames in these square frames can combine and/or be divided into different square frames.
Such as, in some illustrative examples, the location section 334 in framework 310 can be closedMove in other axis in addition to vertical axis 338.Further, illustrative at someExample in, it may not be necessary to heating system 352.
About formation system 312, it is not necessary to be applicable to the complex three-dimensional program of different airfoil profiles.The most notNeed five expensive axis computer numerical control band laydown machines.Use simple program and relatively inexpensiveFive axis band laydown machines can build preimpregnation assembly.Further, formation system 312 also reducesOr avoid the need for operator multiple single pre-preg flaggies are placed on instrument 322.
With reference now to Fig. 4, describe aerofoil profile according to advantageous embodiment and form the diagram of system.Aerofoil profileFormation system 400 is to implement the example of formation system 312 in Fig. 3.In this illustrative exampleIn, aerofoil profile forms system 400 and includes framework 402 and formation system 404.Illustrative show at thisIn example, aerofoil profile forms system 400 and comprises framework 402, formation system 404 and instrument 406.?In these illustrative examples, instrument 406 is Multi-part tool.Especially, instrument 406 wrapsContaining multiple mandrels.
Framework 402 comprises bottom 408, location section 410 and motor system 412.Motor system412 comprise actuator 414.Motor system 412 is configured to relative to bottom 418 and instrument 406Running fix section 410.Motor system 412 is configured to move towards the direction of axis 416 determinesPosition section 410.
In this illustrative example, groove 418 is present in formation system 404.Gap 420It is present in groove 418.In these illustrative examples, instrument 406 can move toIn gap 420, then move the groove 422 to the section 410 of location.In these examples, ditchGroove 422 is orthogonal with groove 418.When location section 410 is moved towards the direction of arrow 424Time dynamic, instrument 406 can move the gap 420 to groove 418, then moves to groove422。
As it has been described above, formation system 404 comprises heating system 426 and force application system 428.At thisIn illustrative example, framework 402 can have the degree of depth 430, width 432 and height 434.In this example described, the degree of depth 430 can be about 55 feet, and width 432 can beAbout 19 feet, and height 434 can be about 15 feet.Certainly, depend on specificEnforcement, size can change.
In these illustrative examples, framework 402 can be made up of following material, such as but notIt is limited to, the material of steel, titanium, aluminum and/or other suitable type.Further, instrument 406 canThere to be following material to be constituted, such as but not limited to, nickel steel alloy, steel alloy and/or other are suitableThe material of type.
With reference now to Fig. 5, describe, according to advantageous embodiment, the figure that aerofoil profile forms the side view of systemSolve.In this aerofoil profile forms the side view of system 400, the heating system 426 of Fig. 4 comprises theOne heating assembly 500 and the second heating assembly 502.Force application system 428 comprises the first force assembly504, the second force assembly the 506, first motor system 508 and secondary motion requirement 510.
In this illustrative example, the first motor system 508 can be towards the direction of arrow 512Mobile first force assembly 504.Secondary motion requirement 510 can move towards the direction of arrow 514Dynamic second force assembly 506.First motor system 508 and secondary motion requirement 510 can compriseActuator.In this example, gap 420 can be along with the first motor system 508 and the second fortuneDynamic system 510 moves the first force assembly 504 and the second force assembly 506 and changes.
In this illustrative example, the first force assembly 504 and the second force assembly 506 all withFramework 402 is associated movably.Especially, the first force assembly 504 and the second force groupPart 506 is all associated movably with location section 410.First heating assembly 500 and secondHeating assembly 502 by the first force assembly 504 and the second force assembly 506 all with framework 402In location section 410 be associated.First heating assembly 500 and the second heating assembly 502 lead toCross heating preimpregnation assembly and bending force is put on preimpregnation assembly.
As it has been described above, the first force assembly 504 comprises elongated member 516 and removable beam 518.Second force assembly 506 comprises elongated member 520 and removable beam 522.In these examples,Elongated member 516 and elongated member 520 are respectively adopted bladder 524 and the shape of bladder 526Formula.Bladder is elongate inflatable device, is used for substantially homogeneous power or pressure during being formedPower puts on preimpregnation assembly.This bladder applies this power, in order to preimpregnation assembly meets instrument 406Surface configuration.
In this illustrative example, groove 418 in the location section 410 of framework 402 canFormed in trave lling girder 518 and removable beam 522.As it has been described above, part 528 includes shaping systemThe heating system 426 of system 404 and force application system 428.
With reference now to Fig. 6, describe a part of aerofoil profile according to advantageous embodiment and form the side-looking of systemFigure diagram.In this illustrative example, describe Fig. 5 middle part 528 according to advantageous embodimentMore detailed diagram.
In this example, the first heating assembly 500 comprises heater 600 and heater support plate602.Second heating assembly 502 comprises heater 604 and heater support plate 606.Say at thisIn the example of bright property, bladder 524 connects removable beam 518 by support beam 608.Bladder526 connect removable beam column 522 by support beam 610.
As it has been described above, heater support plate 602 connects removable beam 518.Heater support plate 606Connect removable beam 522.
With reference now to Fig. 7-Figure 14, describe the figure of the process forming aerofoil profile according to advantageous embodimentSolve.In the figure 7, describe according to advantageous embodiment have Multi-part tool aerofoil profile formed systemThe diagram of system.
As it has been described above, in these examples, instrument 406 comprises two parts, mandrel 700 and the heartAxle 702.Mandrel 700 connect location section 410, simultaneously mandrel 702 connect bottom 408.SpecialNot, mandrel 702 connects location section 410 by the connection system 703 of location section 410.
Connection system 703 can comprise, and such as, is attached to position some structural elements of section 410Part, it is configured to that some structural details are connected to some pins of mandrel 700 and/or other are suitableComponent.Certainly, in other illustrated examples, connection system 703 can comprise and be joinedIt is set to any number of component that mandrel 700 is connected to positions section 410.
In this illustrative example, location section 410 moves down towards the direction of axis 416The position of connection system 703 is may be coupled to mandrel 700.Then, location section 410 courtThe direction axis 416 moves up, thus moves mandrel 700 relative to mandrel 702.Change sentenceTalking about, location section 410 moves, in order to can move mandrel 700 away from mandrel 702, thusMake to position preimpregnation assembly relative to the top 706 of mandrel 702.
Location section 410 moves towards the direction of arrow 704 relative to bottom 408, until firstHeater support plate in heating assembly 500 and the second heating assembly 502 and the top of mandrel 702Portion 706 is substantially flush.The top 706 of mandrel 702 is for forming the pre-of beam column in aerofoil profileLeaching assembly location.
With reference now to Fig. 8, describe the aerofoil profile formation inserting preimpregnation assembly according to advantageous embodimentThe perspective view diagram of system.In this illustration, preimpregnation assembly 800 loads in groove 418.In advanceLeaching assembly 800 can by some different by the way of load groove 418.For example, it is possible to by behaviourWork person, robot, a combination of both or some other suitable systems load preimpregnation assembly 800.
With reference now to Fig. 9, according to advantageous embodiment describe for form beam column in aerofoil profile onePart aerofoil profile forms the diagram of system.In this illustrative example, heating preimpregnation assembly 800,So that section 900 and section 902 form the heated section that shape can change, thus shapeBecome the shape of aerofoil profile.In this example, this shape is exactly the shape of beam column of aerofoil profile.
First motor system 508 and secondary motion requirement 510 move removable beam 518 and 522,Thus position bladder 524 and capsule relative to section 900 and the section 902 of preimpregnation assembly 800Shape thing 526.In these examples, bladder 524 is moved in the direction towards arrow 904, andBladder 526 is moved in direction towards arrow 906.
Additionally, motor system 412 is towards the direction running fix section 410 of arrow 908.TheseThe mobile section 900 causing bladder 524 and bladder 526 to apply a force to presoak assembly 800With section 902 so that the beam column shape of aerofoil profile changed into by preimpregnation assembly 800 from its original-shape.Bladder 524 applies power to section 900 thus promotes section towards the side 910 of mandrel 702900.Bladder 526 moves, thus section 902 is applied power, in order to towards mandrel 702Section 902 is moved in side 912.
With reference now to Figure 10, describe beam column shape pre-with formation according to advantageous embodimentA part of aerofoil profile of leaching assembly forms the diagram of system.In this example, assembly 800 is presoakedShape has been changed to the shape of the beam column 1000 of aerofoil profile.
First motor system 508 of Fig. 5 and secondary motion requirement 510 are respectively towards arrow 1002Removable beam 518 and removable beam 522 is moved with the direction of arrow 1004.This moves and makes cryptomereThing 524 and bladder 526 move away from preimpregnation assembly 800.Additionally, heater 600 and addingHot device 604 can cut out, so that preimpregnation assembly 800 cools down.
With reference now to Figure 11, describe a part of aerofoil profile formation system according to advantageous embodiment and determinedPosition thus form the diagram of the shell of blade.In this example, location section 410 has moved,Thus mandrel 700 is placed on the top of mandrel 702.In this example, mandrel 700 is permissibleConnect mandrel 702.After movement, preimpregnation assembly 800 is positioned at mandrel 700 and mandrel nowBetween 702.Motor system 412 running fix section 410, in order to heater props up receiving plate and the heartTop 1100 basic horizontal of axle 700 or coupling.Removable beam 518 and removable beam 522 canMove with the direction towards arrow 1102 and arrow 1104, until contact mandrel 700.
With reference now to Figure 12, describe according to advantageous embodiment and insert the preimpregnation having vaned shellThe aerofoil profile of assembly forms the diagram of system.Then preimpregnation assembly 1200 is put in groove 418.First heating assembly 500 and the second heating assembly 502 can heat the section of preimpregnation assembly 1200.
With reference now to Figure 13, describe according to advantageous embodiment and there is the preimpregnation assembly that part is formedAerofoil profile formed system diagram.Removable beam 518 and removable beam 522 are towards arrow 1302Move with the direction of arrow 1304, in order to bladder 524 and bladder 526 are to preimpregnation assembly 1200Section 1306 and section 1308 apply power.In these illustrative examples, section 1306It is the heated section of preimpregnation assembly 1200 with section 1308.Bladder 524 and bladder526 extrude section 1306 and section towards the side 1310 of mandrel 700 and side 1312 respectively1308。
Additionally, pass through bladder 524 and bladder 526 respectively towards side 1310 and side 1308Put on section 1306 and the power of section 1308, add in conjunction with the first heating assembly 500 and secondThe bending force that hot assembly 502 applies, provides tension force as follows on preimpregnation assembly 1200,I.e., it is possible to form microgroove in preventing the independent flaggy in preimpregnation assembly 1200.In this example,Location section 410 moves towards the direction of arrow 1314.
With reference now to Figure 14, describe with the blade being done according to advantageous embodimentAerofoil profile is divided to form the diagram of system.The preimpregnation assembly in preimpregnation assembly 800 and Figure 12 in Fig. 81200 shapes having changed into aerofoil profile 1400 from its original-shape.As it can be seen, preimpregnation assembly1200 shells 1402 constituting aerofoil profile 1400.Preimpregnation assembly 800 constitutes the beam column of aerofoil profile 14001404.Now, aerofoil profile 1400, mandrel 700 and mandrel 702 can move to solidification aerofoil profile 1400Position.After solidification, can be with removal of the mandrel 700 and mandrel 702.
With reference now to Figure 15, describe the perspective view diagram of aerofoil profile according to advantageous embodiment.Such as figureShown in, the side 1500 of aerofoil profile 1400 has length 1502, and the side 1504 of aerofoil profile 1400There is length 1506.In this illustrative example, length 1502 is more longer than length 1506.
With reference now to Figure 16, describe another perspective view diagram of aerofoil profile according to advantageous embodiment.Further, in fig. 17, the side view diagram of aerofoil profile is described according to advantageous embodiment.
Turning now to Figure 18, describe the flow chart of the process shaping aerofoil profile according to advantageous embodimentDiagram.The aerofoil profile in Fig. 3 can be used to form system 308 and to implement the process shown in Figure 18.Especially, this process can be performed, thus form aerofoil profile from the preimpregnation assembly with the first shapeAnd/or there is the component of the aerofoil profile of the second shape.
This process begins with the location section multiple parts relative to the instrument of aerofoil profile of frameworkIn positioning parts preimpregnation assembly (operation 1800).This location section is configured to relative to workTool and the bottom of framework are moved, and be moved relative in multiple parts of instrument someParts.Such as, multiple parts can be multiple mandrel.
Then the some sections (operation 1802) in this process heating preimpregnation assembly.In operation 1802In, use aerofoil profile to form these the some sections of heating system heats in the shape formation system of system.These some sections in preimpregnation assembly are heated to enough allowing this some section energy by this heating systemBend and can meet the temperature of instrument.
Then, during this process applies a force to be heated to meet the preimpregnation assembly of instrument shouldSome sections, so that these sections in preimpregnation assembly meet has airfoil component shapeInstrument (operation 1804).Then, this process determines whether aerofoil profile completes (operation 1806).When preimpregnation assembly is already shaped into the second shape of aerofoil profile, aerofoil profile completes.Illustrative at someExample in, when some preimpregnation assemblies are already shaped into the shape of the different component of aerofoil profile, the wingType completes.
If aerofoil profile completes, then this process settings aerofoil profile (operation 1808), this process afterwardsTerminate.Otherwise, this process is back to operate as above 1800.When repetitive operation 1800,This operation is performed by using extra preimpregnation assembly.When performing operation 1800 for the first time, these partsIt it is first component.There is the first component presoaking the instrument that assembly clings of aerofoil profile the second shape,Preimpregnation assembly is formed on the first component of instrument and stays thereon.Mistake in repetitive operation 1800Cheng Zhong, positions extra preimpregnation assembly relative to the second component in multiple parts of instrument, withTime preimpregnation assembly still on first component.
With reference now to Figure 19, describe the flow chart figure shaping aerofoil profile process according to advantageous embodimentSolve.The aerofoil profile in Fig. 3 can be used to form system 308 and to perform the process shown in Figure 19.SpecialNot, perform this process thus form the aerofoil profile comprising some components.
By selecting preimpregnation assembly in some components of aerofoil profile, this process starts (operation 1900).Such as, component can be beam column or the shell of aerofoil profile.Then preimpregnation assembly is put into aerofoil profile and is formed systemFormation system groove in (operation 1901).Aerofoil profile forms system and comprises formation system and frameFrame.Framework comprises bottom and location section.Location section is configured to relative to bottom towards perpendicularThe direction of straight axis is moved.
In this illustrative example, location section is associated with formation system.In formation systemGroove has gap, and gap has the first side and the second side.The part of the preimpregnation assembly in gapIt is exposed to the groove formed in the section of location.Position in the groove in section and formation systemGroove is substantially vertical.
Then framework is used to position preimpregnation assembly (operation 1902) relative to the mandrel of instrument.?This illustrative exemplary center axle is a mandrel in multiple mandrels of instrument.In operation 1902In, location section moves down, thus relative to mandrel location preimpregnation assembly.Especially,When once performing this operation, preimpregnation assembly is just positioned at the top of mandrel.Illustrative show at thisIn example, the top section of mandrel has the shape of the beam column of aerofoil profile.In this illustrative example,Instrument can comprise any number of mandrel.
It is then possible in use formation system heating system heats preimpregnation assembly the first section andSecond section (operation 1904).First section of preimpregnation assembly is exposed in formation systemThe heating system of first side in the gap in groove.Second section of preimpregnation assembly is exposed to andThe heating system of second side in the gap in groove in shape system.
Heating system comprises the first heating assembly and the second heating assembly.First heating assembly is configuredPresoak the first section of assembly for heating, and the second heating assembly is configured to heat preimpregnation groupSecond section of part.
It follows that use the first motor system and secondary motion requirement to move the first force assembly respectivelyWith the second force assembly, thus it is respectively applied to power presoak the first section of assembly and the second section(operation 1906).First force assembly and the second force assembly are all the force systems in formation systemThe parts of system.
In operation 1906, applying power is so that the first section meets the first side and second section of mandrelMeet the second section of mandrel.Further, move towards contrary direction the first force assembly andSecond force assembly.
About whether having formed preimpregnation assembly so that preimpregnation assembly has the shape of assembly and makes and sentencingDisconnected (operation 1908).When presoaking the shape that assembly has particular elements, this component completes.If preimpregnation assembly does not have the shape of this component, then process is back to operate as above1906。
During repetitive operation 1906, location section moves down, in order to preimpregnation assemblyIn the gap of the groove that the first new section and the second new section are exposed in formation system.WithThis mode, the groove in the section of location is moved down on instrument.
Refer again to operate 1908, if preimpregnation assembly has the shape of component, then frameworkLocation section moves up relative to base of frame, in order to (behaviour in mandrel stayed by specific componentMake 1910).Then, whether complete to judge (operation 1912) about aerofoil profile.
If aerofoil profile completes, then this process settings aerofoil profile (operation 1914), subsequent process is eventuallyOnly.If aerofoil profile is not fully complete, then new mandrel is placed on current mandrel by running fix sectionTop (operation 1916).Preimpregnation assembly shapes in current mandrel.Shaping preimpregnation groupMandrel new during part connects location section.
In operation 1916, the movement of location section makes new mandrel move down, and is positioned atThe top of current mandrel.Further, operation 1916 in, by by new mandrel from locationSection disconnects the top that new mandrel is placed on current mandrel, in order to when location, section is upwards movedTime dynamic, new mandrel stays the top of current mandrel.
Then, this process is back to operate as above 1900.
Although these examples show the use of the instrument with two mandrels, but other examples canTo have other mandrel number.Such as, other enforcement can use to be placed on and push up each otherThree of portion or four mandrels.Further, these mandrels can also connect each other or canTo have the shape allowing mandrel to be in alignment with each other.
Flow chart and block diagram in described different embodiment show different favourable enforcementEquipment and method some possible structure, function and operations implemented in example.In this regard,Each square frame in flow chart or block diagram can be with representation module, section, function and/or operation or stepA rapid part.
In some interchangeable enforcements, the function mentioned in square frame can not be according to shown in figureOrder is carried out.Such as, under certain conditions, comprised function is depended on, two illustrated continuouslyIndividual square frame can substantially simultaneously perform, or sometimes square frame can perform in a reverse order.And, in addition to the square frame shown in flow chart or block diagram, other square frame can be increased.
In this way, different advantageous embodiments provides the method and apparatus forming aerofoil profile.?In one advantageous embodiment, equipment comprises framework and formation system.Framework is configured to relative to workTool keeps preimpregnation assembly.This formation system is associated with framework, and is configured to move relative to instrumentDynamic preimpregnation assembly, thus change the first shape of preimpregnation assembly, and then form the second shape of aerofoil profile.
The explanation of different advantageous embodiments is had been presented in order to illustrate and describe, and differentThe explanation of advantageous embodiment is not intended to limit or limits the embodiment of disclosed form.AbilityThe technical staff in territory will be apparent from, and can make some improvement and change.Further, withComparatively speaking, different advantageous embodiments can provide different advantages to other advantageous embodiments.Embodiment selected by selection and description is to be best described by the principle of embodiment, actual applicationWith others of ordinary skill in the art can be made to understand the disclosure, because having various improvementVarious embodiments be also applied for the application-specific anticipated.
Some examples in those embodiments are as follows:
A kind of equipment, wherein location section is configured to mobile preimpregnation assembly, in order in preimpregnation assemblyExtra section be heated, thus form the extra heated section of preimpregnation assembly, and power quiltPut on the extra section of preimpregnation assembly until preimpregnation assembly has the second shape of aerofoil profile.
Described equipment comprises the groove in formation system further, and wherein groove has gap, whereinHeating system is configured to heat the some sections in the preimpregnation assembly being positioned at groove, if being formedDo heated section, and the some heated section wherein presoaked in assembly is positioned at relativelyIn the gap of the position of instrument.
Described equipment, wherein location section is included in the groove in this location section, and it is configured toWhen moving when the parts of instrument relative to the miscellaneous part of instrument, for receiving the parts of instrument.
Described equipment, wherein said gap has the first side and the second side, wherein said heating systemComprising the first heating assembly and the second heating assembly, the first heating assembly is positioned at first side in gapOn；With second heating assembly be positioned on second side in gap, wherein said first heating assembly andSecond heating assembly is both configured to the section in described some sections of heating preimpregnation assembly.
Described equipment, wherein said first force assembly and the mobile change gap of the second force assemblySize.
Equipment according to claim 1, wherein said multiple parts have various shape, withJust can use multiple parts that multiple preimpregnation assemblies are formed as have multiple shape, and whereinLocation section is configured to move multiple parts relative to the miscellaneous part in multiple parts of instrumentIn each parts, in order to can relative in multiple parts corresponding component position multiple preimpregnationEach preimpregnation assembly in assembly.
Described equipment, wherein aerofoil profile is selected from wind turbine blade, aircraft blade and aircraft machineThe wing one of them.
Aerofoil profile forms system and comprises the framework having bottom with location section, wherein said location sectionThere is the first groove, and be configured to be positioned by preimpregnation assembly relative to the instrument comprising multiple partsIn the first groove；Move relative to the bottom of instrument and framework；And relative in multiple partsMiscellaneous part move the parts in multiple parts；Formation system comprises heating system, force application systemWith the second groove, wherein said heating system is associated with location section, and it is pre-to be configured to heatingSome sections in leaching assembly, thus form the some heated section in preimpregnation assembly, and itsDescribed in force application system be associated with alignment system, and be configured to apply a force to relative to instrumentSome heated section in preimpregnation assembly, in order to the described some heated sections in preimpregnation assemblyThere is the second shape of aerofoil profile.
Described method comprise further miscellaneous part in multiple parts of use instrument to some additionallyPreimpregnation assembly repeat location, the step that heats and apply.
Aerofoil profile is solidified after completing further contained in aerofoil profile by described method.