CN102529112B - Airfoil manufacturing system - Google Patents
Airfoil manufacturing system Download PDFInfo
- Publication number
- CN102529112B CN102529112B CN201110434628.9A CN201110434628A CN102529112B CN 102529112 B CN102529112 B CN 102529112B CN 201110434628 A CN201110434628 A CN 201110434628A CN 102529112 B CN102529112 B CN 102529112B
- Authority
- CN
- China
- Prior art keywords
- assembly
- preimpregnation
- instrument
- aerofoil profile
- relative
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000004519 manufacturing process Methods 0.000 title description 29
- 238000007493 shaping process Methods 0.000 claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims description 60
- 230000015572 biosynthetic process Effects 0.000 claims description 46
- 238000005755 formation reaction Methods 0.000 claims description 45
- 210000003932 Urinary Bladder Anatomy 0.000 claims description 21
- 230000000712 assembly Effects 0.000 claims description 12
- 238000000034 method Methods 0.000 description 27
- 238000010586 diagram Methods 0.000 description 21
- 229920005989 resin Polymers 0.000 description 18
- 239000011347 resin Substances 0.000 description 18
- 239000000463 material Substances 0.000 description 16
- 239000000835 fiber Substances 0.000 description 12
- 239000002131 composite material Substances 0.000 description 7
- 238000002386 leaching Methods 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 4
- 229910052799 carbon Inorganic materials 0.000 description 4
- 239000004744 fabric Substances 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 239000003365 glass fiber Substances 0.000 description 3
- 230000003252 repetitive Effects 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 229910000851 Alloy steel Inorganic materials 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 230000000875 corresponding Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000002349 favourable Effects 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 229920000914 Metallic fiber Polymers 0.000 description 1
- 229920000431 Shape-memory polymer Polymers 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminum Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000003466 anti-cipated Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000001808 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 238000002513 implantation Methods 0.000 description 1
- 238000001802 infusion Methods 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000009940 knitting Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- TWXTWZIUMCFMSG-UHFFFAOYSA-N nitride(3-) Chemical compound [N-3] TWXTWZIUMCFMSG-UHFFFAOYSA-N 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000002407 reforming Methods 0.000 description 1
- 238000009738 saturating Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 230000002194 synthesizing Effects 0.000 description 1
- 210000001519 tissues Anatomy 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 230000037303 wrinkles Effects 0.000 description 1
Abstract
The present invention relates to a kind of equipment for shaping aerofoil profile and method.The location section using framework presoaks assembly relative to the positioning parts in multiple parts of the instrument of described aerofoil profile.Described location section is configured to move relative to described instrument and base of frame, and if being moved relative to the dry part of multiple parts of described instrument.Heat the some sections in described preimpregnation assembly.Power is applied in the some sections in the most heated described preimpregnation assembly so that it is meet described instrument, so that the some sections in the most heated described preimpregnation assembly meet the instrument of the shape of the component with described aerofoil profile.
Description
Technical field
The disclosure relates generally to manufacture composite construction, and more particularly to the composite system of use
Make aerofoil profile.More specifically, it relates to manufacture composite wind turbine or aircraft aerofoil profile
(airfoil) method and apparatus.
Background technology
Wind power plant is a kind of power plant relying on wind-force to produce electric power.Wind power plant is permissible
Have tens to hundreds of wind turbine.Wind turbine in wind power plant can cover
Hundreds of sq. mi.
Wind turbine is configured as the rotary apparatus using wind to produce energy.Wind turbine
Respond the motion of wind and produce mechanical energy.This mechanical energy can be converted into electric energy.Wind turbine
Comprise the turbine blade being rotatably mounted in structure.Electromotor may be used for from turbine
The motion of blade produces electricity.
The wind turbine used in wind power plant typically has three blades, and by meter
The electromotor that calculation machine controls points to wind.These wind turbine blade ends can have exceed big
The speed of 200 miles the most per hour.Wind turbine blade can forward to big every about minutes 10
The rotating speed of 22 turns the most per minute rotates.
Blade in wind turbine is the aerofoil profile similar to aircraft wing shape.Traditionally,
Wind turbine blade has two curved surfaces or bent shell.These surfaces connect at leading edge and trailing edge.
Additionally, can have some structure beam columns (spar) at inner turbine machine blade.Use compound
It is labor-intensive that material manufactures wind turbine blade, and is expensive.
Large-scale wind turbine blade can be from about 13 meters to about 60 meters in length.
Along with the length of turbine blade increases, bending deformation obtains more difficult.Flexure is turbine blade
The change of shape.Therefore, along with the length of turbine blade increases, the intensity of turbine blade
Also increase thus reduce flexure.
These blades can be fabricated by by various materials, such as glass fibre, carbon, timber and/
Or other materials.During manufacturing blade, gel coat is typically placed in the mould table of shell
Face.Then, glass fabric layer and miscellaneous part can be placed on the inner surface of mould.The thinnest
Film is placed in this material member.Then under pressure or vacuum aided, glass fibers is infused resin into
In dimension material.Depend on the size of blade, can infuse resin into mould from multiple positions.
Manage so that resin is flowed through and the turbine blade uniform resin infusion of acquisition typically difficulty
's.Inconsistent can the causing of resin needs reform blade or abandon blade.Need turbine of reforming
Machine blade or abandon turbine blade and cause manufacturing the cost needed for wind turbine blade and time
Increase.
Accordingly, there exist a consideration at least some difficult problem discussed above and the side of other possible difficult problems
Method and equipment are just favourable.
Summary of the invention
In an advantageous embodiment, equipment comprises framework and formation system.Framework is configured to
Preimpregnation assembly is positioned relative to the instrument with multiple parts.This framework comprises bottom and location division
Section.Location section is configured to move relative to the bottom of instrument and framework, and in preimpregnation group
Part moves the parts in multiple parts relative to the miscellaneous part in multiple parts during shaping.Become
Shape system is associated with framework, and is configured to relative to preimpregnation component movement, described preimpregnation group
If part is to be positioned relative to the dry part in multiple parts of the instrument being connected to bottom, from
And when positioning section relative to movement of tool, change the first shape of preimpregnation assembly, and then shape
Become the second shape of aerofoil profile.
In another advantageous embodiment, aerofoil profile forms system and comprises framework and formation system.Should
Framework has bottom and location section.This location section has the first groove, and is configured to phase
Preimpregnation assembly is positioned in the first groove by the instrument for comprising multiple parts.This location section
It is configured to move relative to the bottom of instrument and framework, and relative to its in multiple parts
His parts move the parts in multiple parts.This formation system comprises heating system, force application system
With the second groove.This heating system is associated with location section, and is configured to heat preimpregnation group
Some sections in part thus form the some heated section in preimpregnation assembly.Force application system
It is associated with location section, and is configured to apply a force to presoak in assembly relative to instrument
Described some heated sections, in order to the described some heated sections tool in preimpregnation assembly
There is the second shape of aerofoil profile.
In another advantageous embodiment, it is provided that the method shaping aerofoil profile.Use determining of framework
Position section presoaks assembly relative to the positioning parts in multiple parts of the instrument of aerofoil profile.This location
Section is configured to move relative to instrument and base of frame, and makes in multiple parts of instrument
If dry part be moved relative to.Some sections in heating preimpregnation assembly.Applying power in
The most heated some sections in preimpregnation assembly so that it is meet instrument, so that
The heated some sections in preimpregnation assembly meet the instrument of the shape of the component with aerofoil profile.
Feature, function and advantage can realize in the various embodiments of the disclosure independently, or
It is can to realize with the combination of other embodiments, is appreciated that it with reference to following description and drawings
Middle further details.
Accompanying drawing explanation
Illustrate the novel feature being considered advantageous embodiment characteristic in the following claims.So
And, will be more preferably together with accompanying drawing by the detail specifications of the advantageous embodiment with reference to the following disclosure
Ground understands advantageous embodiment and preferred use pattern, further purpose and advantage thereof.Attached
In figure:
Fig. 1 shows manufacture and the method for servicing of the wind turbine according to advantageous embodiment；
Fig. 2 shows the wind turbine that can implement advantageous embodiment；
Fig. 3 shows the aerofoil profile manufacturing environment according to advantageous embodiment；
Fig. 4 shows that the aerofoil profile according to advantageous embodiment forms system；
Fig. 5 shows that the aerofoil profile according to advantageous embodiment forms the side view of system；
Fig. 6 shows that a part of aerofoil profile according to advantageous embodiment forms the side view of system；
Fig. 7 shows that the aerofoil profile with Multi-part tool according to advantageous embodiment forms system；
Fig. 8 shows that the aerofoil profile inserting preimpregnation assembly according to advantageous embodiment forms the saturating of system
View；
Fig. 9 shows a part of wing for forming beam column in aerofoil profile according to advantageous embodiment
Type forms system；
Figure 10 shows the preimpregnation assembly of the beam column shape with formation according to advantageous embodiment
A part of aerofoil profile forms system；
Figure 11 shows a part of wing being positioned as being formed the shell of blade according to advantageous embodiment
Type forms system；
Figure 12 shows the aerofoil profile shape of the preimpregnation assembly being inserted with blade shell according to advantageous embodiment
One-tenth system；
Figure 13 shows that the part according to advantageous embodiment forms the aerofoil profile formation of preimpregnation assembly and is
System；
Figure 14 shows a part of aerofoil profile with turbine blade according to advantageous embodiment
Formation system；
Figure 15 shows the perspective view of the aerofoil profile according to advantageous embodiment；
Figure 16 shows another perspective view of the aerofoil profile according to advantageous embodiment；
Figure 17 shows the side view of the aerofoil profile according to advantageous embodiment；
Figure 18 shows the flow chart of the shaping aerofoil profile process according to advantageous embodiment；And
Figure 19 shows the flow chart of the shaping aerofoil profile process according to advantageous embodiment.
Detailed description of the invention
Referring more specifically to accompanying drawing, can be wind turbine manufacture as shown in Figure 1 and service side
Method 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 embodiment
Solve.During pre-manufactured, wind turbine manufacture and method of servicing 100 can include in Fig. 2
The 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 106
With the system integration 108.Then, the wind turbine 200 in Fig. 2 is in order to use 112 to carry out
Calibrating and payment 110.When being used 112 by client, arrange the wind turbine 200 in Fig. 2
Carry out regular maintenance and service 114, can include improving, reconfigure, renovate and other maintenances
Or service.
Each process of wind turbine manufacture and method of servicing 100 can be supplied by system synthesis
Business, third party and/or operator perform.In these examples, operator can be client.For
This description, system integrator can include but not limited to some wind turbine manufacturer
With main system subcontractor；Third party can include but not limited to some sellers, subcontractor and supply
Business；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 embodiment
Solve.In this example, the wind turbine manufacture in Fig. 1 and method of servicing 100 wind is produced
Power turbine 200, and wind turbine 200 can include tower 202, armature spindle 204, hub
206, blade 208, gear-box 210, brakes 212, location engine 214 and electromotor
216。
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 exemplary
Example is aircraft manufacture industry.
Tower 202 is the structure supporting other components in wind turbine 200.Such as, tower 202
Support armature spindle 204, hub 206, blade 208, gear-box 210, brakes 212, location
Electromotor 214 and electromotor 216.Blade 208 connects hub 206.Hub 206 and then connection rotor
Axle 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 directly
Or indirectly connect second component.In other words, extra component may reside in the first component
And between second component.When the first component is directly connected second component, the two component it
Between 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 increasing
The rotating speed of big blade 208, thus the speed needed for match generator.Brakes 212 is permissible
For making spin down and/or the stopping of armature spindle 204.
Equipment contained herein and method can manufacture kimonos by shown wind turbine in FIG
Use during at least one stage of business method 100.As used herein, when lising with one
When mesh is used together, term " at least one " refers to use in cited project
Or 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 project
C or project B and project C.
In an illustrative example, can with when wind turbine 200 is in the use of Fig. 1
Manufacture component or the similar mode of assembly component in FIG time in 112 and sub-component manufactures 106
Middle manufacture component or assembly.
In another example, some apparatus embodiments, method can be used to implement in the production phase
Component in example or a combination thereof, such as Fig. 1 and sub-component manufacture 106 and the system integration 108.When
When referring to project, the one or more project of some fingers.Such as, some apparatus embodiments are one
Individual or multiple apparatus embodiments.
When wind turbine 200 is in the maintenance used in 112 and/or in FIG and service 114
Period can use some apparatus embodiments, embodiment of the method or a combination thereof.Use some differences
Advantageous embodiment can accelerate significantly turbine 200 assembling process and/or reduce turbine
The 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 examine
Worry factor " it is one or more Considerations.Such as, different advantageous embodiments recognizes and examines
Considering wind turbine blade and generally comprise two curved surfaces being fabricated by by fabric, fabric comprises note
Enter the glass fibre of liquid resin.These faces can also be referred to as shell.These shells exist
Connect at the leading edge of aerofoil profile and trailing edge.Additionally, some structural elements can exist between shell.Example
As, one or more beam columns can be inside turbine blade.
Different advantageous embodiments recognizes and considers: uses and currently available is applicable to wind turbine
The manufacturing technology of machine Leaf controls resin stream and is probably difficulty.Different advantageous embodiments is recognized
Know and consider that the resin obtaining even amount throughout turbine blade is probably difficulty.Resin
Inconsistent 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 preimpregnation
Treatment of Carbon composite replaces the resin transfer process of vacuum aided.In other words, permissible
Resin is used to have been injected into the fiber in fiber.These materials can be referred to as presoaking assembly.Can
Different components is manufactured to lay these leachings process assembly.Then can be assembled these different
Component formed blade.Different advantageous embodiments recognizes and consider can be by using at preimpregnation
Manage 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 glass
Dimension 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 inconsistent
Property, but but can not reduce the time manufacturing turbine blade as desired.Such as, different
Advantageous embodiment recognizes and considers: can use composite by paver in a mold
Preimpregnation 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 paving
If preimpregnation assembly is time-consuming, and easily makes mistakes.Further, different advantageous embodiments
Recognize and consider: using cnc machine tool to be routed to be applicable to new parts by preimpregnation assembly
Mould in may need the five axis program (five-axis for each shell and each design
Program), five axis programs are more complicated than intended.Additionally, different advantageous embodiments is recognized
Know and consider: such process may remain a need for assembling single parts, thus completes
Blade.
Different advantageous embodiments recognizes and considers: with currently available during independent of other
Component forms each component of aerofoil profile and compares, and forms aerofoil profile during identical forming process
Different 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 one
In profit embodiment, equipment comprises framework and formation system.Framework is configured to protect relative to instrument
Hold preimpregnation assembly.This formation system is associated with framework, and is configured to move relative to instrument
Preimpregnation assembly, thus change the first shape of preimpregnation assembly, and then form the aerofoil profile without microgroove
Second shape.
With reference now to Fig. 3, describe the diagram of aerofoil profile manufacturing environment according to advantageous embodiment.At this
In example, aerofoil profile manufacturing environment 300 may be used for manufacturing aerofoil profile 302.Aerofoil profile 302 may be used for
Wind 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 forms
The wing 306 of device.
In this illustrative example, use aerofoil profile to form system 308 and manufacture aerofoil profile 302.Aerofoil profile
Formation system 308 comprises framework 310 and formation system 312.Framework 310 is configured to presoak
Assembly 314 is positioned at aerofoil profile and is formed in system 308.Preimpregnation assembly 314 can also be referred to as dress
Material (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 320
Nitride 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.Example
As, if dry fibre layers 318 can be by carbon fiber, metallic fiber, glass-reinforced plastic, strengthening
The material of carbon fiber plastic and/or other suitable type is constituted.If dry fibre layers 318 uses difference
Form.Such as, if dry fibre layers 318 can be the unipolarity band of different in width, plane volume
Fabric, the fiber being woven together, the fiber being stitched together and/or some other suitable shapes
Formula.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 shape
Become preimpregnation assembly 314.Resin 320 can be to use different forms.Such as but not limited to, resin
320 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 322
Leaching assembly 314.Instrument 322 can be to use some different forms.Such as, instrument 322 is permissible
It is outer mold line 324, some mandrels 326 and/or the instrument of other suitable type.Outer mold line 324
It is that preimpregnation assembly 314 is placed on the mould on the outer surface of outer mold line 324.Depend on specific
Implementing, outer mold line 324 can also have not only one.Especially, instrument 322 be comprise many
The Multi-part tool of individual parts 323.For lifting an illustrative example, multiple parts 323
In each parts may each be mandrel.
In this illustrative example, framework 310 can have bottom 332, location section 334
With motor system 336.In these examples, location section 334 keeps preimpregnation assembly 314.Fixed
Position section 334 can move relative to bottom 332.Further, location section 334 is permissible
Move relative to instrument 322.
In these examples described, location section 334 is configured to relative to multiple parts 323
If miscellaneous part in moves the dry part in multiple parts 323.Miscellaneous part can connect the end
Portion 332.Location section 334 includes the first groove 335.First groove 335 is configured to receive
If the dry part in multiple parts 323.
Such as, location section 334 can include connection system 337.Connection system 337 is configured
If 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 location
If the dry part of section 334 is along with location section 334 is relative to multiple parts 323 of instrument 322
In miscellaneous part move.
In these examples, if being not connected with the dry part positioning in multiple parts 323 of section 334
Bottom connection 332.If the dry part in multiple parts 323 of the instrument 332 of 332 bottom connection
Including the parts for shaping preimpregnation assembly 314.Connect multiple parts 323 of location section 334
If dry part in includes the parts being not currently used for shaping preimpregnation assembly 314.By location section
If the dry part in the 334 multiple parts 323 supported can be placed on bottom connection 332 multiple
On 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 words
Saying, motor system 336 can be along vertical axis 338 running fix section 334.Certainly, fixed
Position section 334 can move along other axles, and this depends on specifically implementing.Location section 334
Can 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 causes
Dynamic device 340 can be motor machine actuator.
In this illustrative example, formation system 312 is configured to as follows relative to work
Tool 322 move preimpregnation assembly 314, i.e. change preimpregnation assembly 314 the first shape 328 thus
Form 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 form
Shape.Second shape 330 is the shape of component in aerofoil profile 302.Second shape 330 it may be that
Such as but not limited to, beam column, shell and/or some other suitable shapes.Illustrative at some
In 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 has
Gap 344.Gap 344 has the first side 346 and the second side 348.In these illustrative examples
In, 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 342
350 appear.Can be become relative to instrument 322 by formation system 312 in these examples
Shape part 350.In these illustrative examples, formation system 312 comprises heating system 352
With force application system 354.Heating system 352 is configured to some sections of heating preimpregnation assembly 314
356, thus form the some heated section 358 of preimpregnation assembly 314.
In these illustrative examples, heating system 352 comprises the first heating assembly 362 and
Two heating assemblies 364.First heating assembly 362 is positioned at the of the gap 344 of the second groove 342
Side 346.Second heating assembly 364 is positioned at second side in the gap 344 of the second groove 342
348。
As it has been described above, these heating assemblies are both configured to heat the gap being positioned at the second groove 342
Corresponding some sections 356 on the either side of 344.In these illustrative examples, if cadre
Section 356 can be continuous print and/or discrete section.Such as, the portion in some sections 356
Section can have discrete sub-section.In these examples, when some sections 356 are by heating
When 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 352
Hot 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 system
System 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 examples
Shape 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 use
Preimpregnation 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 assembly
368.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 configured
For moving, power 360 is put on the some heated section 358 of preimpregnation assembly 314, in order to
There 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 members
370 and first motor system 372.Second force assembly 368 comprises second some elongated members 374
With secondary motion requirement 376.
First motor system 372 is configured to move first some elongated members relative to instrument 322
370, thus power 360 is put on the some heated section 358 of preimpregnation assembly 314.Second
Motor system 376 is configured to move second some elongated members 374 relative to instrument 322, from
And 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 322
One some elongated members 370, can position second relative to the second side 380 of instrument 322 simultaneously
Some elongated members 374.Therefore, power 360 is put on location by first some elongated members 370
Some heated section 358 on the first side 378, second some elongated members 374 will simultaneously
Power 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 causes
Dynamic device.One or more actuators in first motor system 372 are configured to independent of first
The 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 of
The Part II of two some elongated members 374 moves first of second some elongated members 374
Point.
For one or more advantageous embodiments, by using preimpregnation assembly can reduce in aerofoil profile
Discordance.Further, for one or more advantageous embodiments, computer can be avoided
Cost needed for Digit Control Machine Tool and programming.
In different illustrated examples, in addition to preimpregnation assembly 314, it is possible to use extra
Preimpregnation assembly.Such as, in some illustrative examples, use except preimpregnation assembly 314 with
Outer some preimpregnation assemblies 394 can manufacture aerofoil profile 302.Such as, preimpregnation assembly 314 can be
The shell of aerofoil profile 302, the most some preimpregnation assemblies 394 can form structural detail, the most some
Beam 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 302
After changing into the second shape 330, can will preimpregnation assembly 314 and some along instrument 322
Preimpregnation assembly 394 moves to heating chamber 396, and in heating chamber, heat 398 and/or pressure are used for
Solidification preimpregnation assembly 314 and some preimpregnation assemblies 394, thus complete the formation of aerofoil profile 302.So
After, 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 can
Limit with the physical restriction implemented or building.Can use in addition to that shown and/or replace institute
Other components shown.Some components can be need not in some advantageous embodiments.And, institute
The 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 closed
Move in other axis in addition to vertical axis 338.Further, illustrative at some
Example 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 not
Need five expensive axis computer numerical control band laydown machines.Use simple program and relatively inexpensive
Five axis band laydown machines can build preimpregnation assembly.Further, formation system 312 also reduces
Or 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 profile
Formation system 400 is to implement the example of formation system 312 in Fig. 3.In this illustrative example
In, aerofoil profile forms system 400 and includes framework 402 and formation system 404.Illustrative show at this
In 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 wraps
Containing multiple mandrels.
Framework 402 comprises bottom 408, location section 410 and motor system 412.Motor system
412 comprise actuator 414.Motor system 412 is configured to relative to bottom 418 and instrument 406
Running fix section 410.Motor system 412 is configured to move towards the direction of axis 416 determines
Position section 410.
In this illustrative example, groove 418 is present in formation system 404.Gap 420
It is present in groove 418.In these illustrative examples, instrument 406 can move to
In gap 420, then move the groove 422 to the section 410 of location.In these examples, ditch
Groove 422 is orthogonal with groove 418.When location section 410 is moved towards the direction of arrow 424
Time dynamic, instrument 406 can move the gap 420 to groove 418, then moves to groove
422。
As it has been described above, formation system 404 comprises heating system 426 and force application system 428.At this
In 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 be
About 19 feet, and height 434 can be about 15 feet.Certainly, depend on specific
Enforcement, size can change.
In these illustrative examples, framework 402 can be made up of following material, such as but not
It is limited to, the material of steel, titanium, aluminum and/or other suitable type.Further, instrument 406 can
There to be following material to be constituted, such as but not limited to, nickel steel alloy, steel alloy and/or other are suitable
The material of type.
With reference now to Fig. 5, describe, according to advantageous embodiment, the figure that aerofoil profile forms the side view of system
Solve.In this aerofoil profile forms the side view of system 400, the heating system 426 of Fig. 4 comprises the
One heating assembly 500 and the second heating assembly 502.Force application system 428 comprises the first force assembly
504, 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 512
Mobile first force assembly 504.Secondary motion requirement 510 can move towards the direction of arrow 514
Dynamic second force assembly 506.First motor system 508 and secondary motion requirement 510 can comprise
Actuator.In this example, gap 420 can be along with the first motor system 508 and the second fortune
Dynamic 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 with
Framework 402 is associated movably.Especially, the first force assembly 504 and the second force group
Part 506 is all associated movably with location section 410.First heating assembly 500 and second
Heating assembly 502 by the first force assembly 504 and the second force assembly 506 all with framework 402
In location section 410 be associated.First heating assembly 500 and the second heating assembly 502 lead to
Cross 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 526
Formula.Bladder is elongate inflatable device, is used for substantially homogeneous power or pressure during being formed
Power puts on preimpregnation assembly.This bladder applies this power, in order to preimpregnation assembly meets instrument 406
Surface configuration.
In this illustrative example, groove 418 in the location section 410 of framework 402 can
Formed in trave lling girder 518 and removable beam 522.As it has been described above, part 528 includes shaping system
The 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 system
Figure diagram.In this illustrative example, describe Fig. 5 middle part 528 according to advantageous embodiment
More detailed diagram.
In this example, the first heating assembly 500 comprises heater 600 and heater support plate
602.Second heating assembly 502 comprises heater 604 and heater support plate 606.Say at this
In the example of bright property, bladder 524 connects removable beam 518 by support beam 608.Bladder
526 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 606
Connect removable beam 522.
With reference now to Fig. 7-Figure 14, describe the figure of the process forming aerofoil profile according to advantageous embodiment
Solve.In the figure 7, describe according to advantageous embodiment have Multi-part tool aerofoil profile formed system
The diagram of system.
As it has been described above, in these examples, instrument 406 comprises two parts, mandrel 700 and the heart
Axle 702.Mandrel 700 connect location section 410, simultaneously mandrel 702 connect bottom 408.Special
Not, 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 410
Part, it is configured to that some structural details are connected to some pins of mandrel 700 and/or other are suitable
Component.Certainly, in other illustrated examples, connection system 703 can comprise and be joined
It 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 416
The position of connection system 703 is may be coupled to mandrel 700.Then, location section 410 court
The direction axis 416 moves up, thus moves mandrel 700 relative to mandrel 702.Change sentence
Talking about, location section 410 moves, in order to can move mandrel 700 away from mandrel 702, thus
Make 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 first
Heater support plate in heating assembly 500 and the second heating assembly 502 and the top of mandrel 702
Portion 706 is substantially flush.The top 706 of mandrel 702 is for forming the pre-of beam column in aerofoil profile
Leaching assembly location.
With reference now to Fig. 8, describe the aerofoil profile formation inserting preimpregnation assembly according to advantageous embodiment
The perspective view diagram of system.In this illustration, preimpregnation assembly 800 loads in groove 418.In advance
Leaching assembly 800 can by some different by the way of load groove 418.For example, it is possible to by behaviour
Work 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 one
Part 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 shape
Become 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 800
Shape thing 526.In these examples, bladder 524 is moved in the direction towards arrow 904, and
Bladder 526 is moved in direction towards arrow 906.
Additionally, motor system 412 is towards the direction running fix section 410 of arrow 908.These
The mobile section 900 causing bladder 524 and bladder 526 to apply a force to presoak assembly 800
With 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 702
900.Bladder 526 moves, thus section 902 is applied power, in order to towards mandrel 702
Section 902 is moved in side 912.
With reference now to Figure 10, describe beam column shape pre-with formation according to advantageous embodiment
A part of aerofoil profile of leaching assembly forms the diagram of system.In this example, assembly 800 is presoaked
Shape 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 1002
Removable beam 518 and removable beam 522 is moved with the direction of arrow 1004.This moves and makes cryptomere
Thing 524 and bladder 526 move away from preimpregnation assembly 800.Additionally, heater 600 and adding
Hot 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 determined
Position 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 permissible
Connect mandrel 702.After movement, preimpregnation assembly 800 is positioned at mandrel 700 and mandrel now
Between 702.Motor system 412 running fix section 410, in order to heater props up receiving plate and the heart
Top 1100 basic horizontal of axle 700 or coupling.Removable beam 518 and removable beam 522 can
Move 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 shell
The 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 formed
Aerofoil profile formed system diagram.Removable beam 518 and removable beam 522 are towards arrow 1302
Move with the direction of arrow 1304, in order to bladder 524 and bladder 526 are to preimpregnation assembly 1200
Section 1306 and section 1308 apply power.In these illustrative examples, section 1306
It is the heated section of preimpregnation assembly 1200 with section 1308.Bladder 524 and bladder
526 extrude section 1306 and section towards the side 1310 of mandrel 700 and side 1312 respectively
1308。
Additionally, pass through bladder 524 and bladder 526 respectively towards side 1310 and side 1308
Put on section 1306 and the power of section 1308, add in conjunction with the first heating assembly 500 and second
The 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 embodiment
Aerofoil profile is divided to form the diagram of system.The preimpregnation assembly in preimpregnation assembly 800 and Figure 12 in Fig. 8
1200 shapes having changed into aerofoil profile 1400 from its original-shape.As it can be seen, preimpregnation assembly
1200 shells 1402 constituting aerofoil profile 1400.Preimpregnation assembly 800 constitutes the beam column of aerofoil profile 1400
1404.Now, aerofoil profile 1400, mandrel 700 and mandrel 702 can move to solidification aerofoil profile 1400
Position.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 figure
Shown in, the side 1500 of aerofoil profile 1400 has length 1502, and the side 1504 of aerofoil profile 1400
There 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 embodiment
Diagram.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 shape
And/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 framework
In positioning parts preimpregnation assembly (operation 1800).This location section is configured to relative to work
Tool and the bottom of framework are moved, and be moved relative in multiple parts of instrument some
Parts.Such as, multiple parts can be multiple mandrel.
Then the some sections (operation 1802) in this process heating preimpregnation assembly.In operation 1802
In, 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 system
Bend and can meet the temperature of instrument.
Then, during this process applies a force to be heated to meet the preimpregnation assembly of instrument should
Some sections, so that these sections in preimpregnation assembly meet has airfoil component shape
Instrument (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 some
Example in, when some preimpregnation assemblies are already shaped into the shape of the different component of aerofoil profile, the wing
Type completes.
If aerofoil profile completes, then this process settings aerofoil profile (operation 1808), this process afterwards
Terminate.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 parts
It 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 1800
Cheng Zhong, positions extra preimpregnation assembly relative to the second component in multiple parts of instrument, with
Time preimpregnation assembly still on first component.
With reference now to Figure 19, describe the flow chart figure shaping aerofoil profile process according to advantageous embodiment
Solve.The aerofoil profile in Fig. 3 can be used to form system 308 and to perform the process shown in Figure 19.Special
Not, 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 system
Formation system groove in (operation 1901).Aerofoil profile forms system and comprises formation system and frame
Frame.Framework comprises bottom and location section.Location section is configured to relative to bottom towards perpendicular
The direction of straight axis is moved.
In this illustrative example, location section is associated with formation system.In formation system
Groove has gap, and gap has the first side and the second side.The part of the preimpregnation assembly in gap
It is exposed to the groove formed in the section of location.Position in the groove in section and formation system
Groove 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 1902
In, 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 this
In 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 and
Second section (operation 1904).First section of preimpregnation assembly is exposed in formation system
The heating system of first side in the gap in groove.Second section of preimpregnation assembly is exposed to and
The 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 configured
Presoak the first section of assembly for heating, and the second heating assembly is configured to heat preimpregnation group
Second section of part.
It follows that use the first motor system and secondary motion requirement to move the first force assembly respectively
With 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 system
The parts of system.
In operation 1906, applying power is so that the first section meets the first side and second section of mandrel
Meet the second section of mandrel.Further, move towards contrary direction the first force assembly and
Second force assembly.
About whether having formed preimpregnation assembly so that preimpregnation assembly has the shape of assembly and makes and sentencing
Disconnected (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 above
1906。
During repetitive operation 1906, location section moves down, in order to preimpregnation assembly
In the gap of the groove that the first new section and the second new section are exposed in formation system.With
This 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 framework
Location section moves up relative to base of frame, in order to (behaviour in mandrel stayed by specific component
Make 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 eventually
Only.If aerofoil profile is not fully complete, then new mandrel is placed on current mandrel by running fix section
Top (operation 1916).Preimpregnation assembly shapes in current mandrel.Shaping preimpregnation group
Mandrel new during part connects location section.
In operation 1916, the movement of location section makes new mandrel move down, and is positioned at
The top of current mandrel.Further, operation 1916 in, by by new mandrel from location
Section disconnects the top that new mandrel is placed on current mandrel, in order to when location, section is upwards moved
Time 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 can
To have other mandrel number.Such as, other enforcement can use to be placed on and push up each other
Three of portion or four mandrels.Further, these mandrels can also connect each other or can
To have the shape allowing mandrel to be in alignment with each other.
Flow chart and block diagram in described different embodiment show different favourable enforcement
Equipment 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 step
A rapid part.
In some interchangeable enforcements, the function mentioned in square frame can not be according to shown in figure
Order is carried out.Such as, under certain conditions, comprised function is depended on, two illustrated continuously
Individual 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 work
Tool keeps preimpregnation assembly.This formation system is associated with framework, and is configured to move relative to instrument
Dynamic 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 different
The explanation of advantageous embodiment is not intended to limit or limits the embodiment of disclosed form.Ability
The technical staff in territory will be apparent from, and can make some improvement and change.Further, with
Comparatively 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 application
With others of ordinary skill in the art can be made to understand the disclosure, because having various improvement
Various 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 assembly
Extra section be heated, thus form the extra heated section of preimpregnation assembly, and power quilt
Put 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, wherein
Heating system is configured to heat the some sections in the preimpregnation assembly being positioned at groove, if being formed
Do heated section, and the some heated section wherein presoaked in assembly is positioned at relatively
In 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 to
When 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 system
Comprising the first heating assembly and the second heating assembly, the first heating assembly is positioned at first side in gap
On；With second heating assembly be positioned on second side in gap, wherein said first heating assembly and
Second 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 assembly
Size.
Equipment according to claim 1, wherein said multiple parts have various shape, with
Just can use multiple parts that multiple preimpregnation assemblies are formed as have multiple shape, and wherein
Location section is configured to move multiple parts relative to the miscellaneous part in multiple parts of instrument
In each parts, in order to can relative in multiple parts corresponding component position multiple preimpregnation
Each preimpregnation assembly in assembly.
Described equipment, wherein aerofoil profile is selected from wind turbine blade, aircraft blade and aircraft machine
The wing one of them.
Aerofoil profile forms system and comprises the framework having bottom with location section, wherein said location section
There is the first groove, and be configured to be positioned by preimpregnation assembly relative to the instrument comprising multiple parts
In the first groove；Move relative to the bottom of instrument and framework；And relative in multiple parts
Miscellaneous part move the parts in multiple parts；Formation system comprises heating system, force application system
With the second groove, wherein said heating system is associated with location section, and it is pre-to be configured to heating
Some sections in leaching assembly, thus form the some heated section in preimpregnation assembly, and its
Described in force application system be associated with alignment system, and be configured to apply a force to relative to instrument
Some heated section in preimpregnation assembly, in order to the described some heated sections in preimpregnation assembly
There is the second shape of aerofoil profile.
Described method comprise further miscellaneous part in multiple parts of use instrument to some additionally
Preimpregnation assembly repeat location, the step that heats and apply.
Aerofoil profile is solidified after completing further contained in aerofoil profile by described method.
Claims (10)
1. an equipment, comprises:
Framework, it is configured to position preimpregnation assembly, wherein relative to the instrument with multiple parts
Described framework comprises bottom and location section, and wherein said location section is configured to relative to institute
State the described bottom motion of instrument and described framework, and phase during described preimpregnation assembly shapes
The miscellaneous part being connected to described bottom in the plurality of parts of described instrument is moved
The parts being connected to described location section in the plurality of parts of described instrument；With
Formation system, it is associated with described framework, and is configured to relative to described preimpregnation assembly
Motion, described preimpregnation assembly is the plurality of relative to the described instrument being connected to described bottom
If the dry part in parts is positioned, thus when described location section is transported relative to described instrument
Time dynamic, change the first shape of described preimpregnation assembly, and then form the second shape of aerofoil profile.
Equipment the most according to claim 1, wherein said formation system comprises:
Heating system, its described preimpregnation being configured to heat the groove being positioned at described formation system
Some sections in assembly, thus form the some heated section in described preimpregnation assembly,
Wherein said groove has the described some heated portions in gap, and described preimpregnation assembly
Section is located relative to the position of described instrument in described gap；With
Force application system, it is configured to apply a force in described preimpregnation assembly relative to described instrument
Described some heated sections, in order to described some heated in described preimpregnation assembly
Section has described second shape of described aerofoil profile.
Equipment the most according to claim 2, wherein said second shape is selected from described aerofoil profile
Beam column and shell one of them.
Equipment the most according to claim 2, wherein said location section is configured to relatively
In the described some positioning parts being connected in the plurality of parts of described instrument of described bottom
Some extra preimpregnation assemblies, and described formation system is configured to relative to described instrument
If the described dry part in the plurality of parts moves described some extra preimpregnation assemblies, until
Form described aerofoil profile.
Equipment the most according to claim 2, wherein said force application system comprises:
First force assembly, it is associated with the described framework on first side in described gap；With
Second force assembly, it is associated, wherein with the described framework on second side in described gap
Described first force assembly and described second force assembly are configured to motion, thus relative to even
If power is applied by the described dry part being connected in the plurality of parts of the described instrument of described bottom
Described some heated sections in described preimpregnation assembly, in order in described preimpregnation assembly
Described some heated sections have described second shape of described aerofoil profile, and wherein said first
The motion of force assembly and described second force assembly changes the size in described gap.
Equipment the most according to claim 5, wherein said first force assembly comprises:
First some elongated members；With
First motor system, it is configured to move relative to described instrument described first some elongated
Element, thus apply a force to the described some heated sections in described preimpregnation assembly；And
And
Wherein said second force assembly comprises:
Second some elongated members；With
Secondary motion requirement, it is configured to the institute relative to the described instrument being connected to described bottom
If stating dry part to move described second some elongated members, thus apply a force to described preimpregnation group
Described some heated sections in part.
Equipment the most according to claim 6, wherein said first some elongated members and institute
Stating second some elongated members is multiple bladders.
Equipment the most according to claim 6, wherein, described first motor system comprises
One some actuators；Described secondary motion requirement comprises second some actuators；If described first
Dry actuator is configured to move independent of another part of described first some elongated members described
A part for first some elongated members；And described second some actuators are configured to independence
Another part in described second some elongated members moves the one of described second some elongated members
Part.
Equipment the most according to claim 1, wherein said instrument is selected from outer mold line, some
Mandrel and two-part moudle one of them.
10. the method shaping aerofoil profile, described method comprises:
The location section using framework is fixed relative to the parts in multiple parts of the instrument of described aerofoil profile
Position preimpregnation assembly, wherein said location section is configured to relative to described instrument and described framework
Bottom motion, and make during described preimpregnation assembly shapes in the plurality of parts of described instrument
The parts being connected to described location section relative to the quilt in the plurality of parts of described instrument
It is connected to the miscellaneous part motion of described bottom；
Heat the some sections in described preimpregnation assembly；And
Apply a force to the described some sections in the most heated described preimpregnation assembly to meet
State instrument, so that the described some sections in the most heated described preimpregnation assembly meet tool
There is the described instrument of the shape of the component of described aerofoil profile, use in the plurality of parts of described instrument
Miscellaneous part the step that some extra preimpregnation assemblies repeated location, heat and apply,
Until described aerofoil profile completes.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US12/968,473 | 2010-12-15 | ||
| US12/968,473 US8597015B2 (en) | 2010-12-15 | 2010-12-15 | Airfoil manufacturing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102529112A CN102529112A (en) | 2012-07-04 |
| CN102529112B true CN102529112B (en) | 2016-12-14 |
Family
ID=
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4475976A (en) * | 1983-12-23 | 1984-10-09 | The Boeing Company | Method and apparatus for forming composite material articles |
| US5547629A (en) * | 1994-09-27 | 1996-08-20 | Competition Composites, Inc. | Method for manufacturing a one-piece molded composite airfoil |
| CN1252754A (en) * | 1997-04-16 | 2000-05-10 | 西科尔斯基飞机公司 | Apparatus and method for assembling a helicopter main rotor blade subassembly |
| CN101348009A (en) * | 2003-03-06 | 2009-01-21 | 维斯塔斯风力系统公司 | Method for manufacturing preforming member |
| CN101367257A (en) * | 2008-09-27 | 2009-02-18 | 哈尔滨玻璃钢研究院 | Fibre reinforced resin based composite material fin piece molding mould |
| CN101811366A (en) * | 2009-02-23 | 2010-08-25 | 通用电气公司 | Make the apparatus and method of composite product |
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4475976A (en) * | 1983-12-23 | 1984-10-09 | The Boeing Company | Method and apparatus for forming composite material articles |
| US5547629A (en) * | 1994-09-27 | 1996-08-20 | Competition Composites, Inc. | Method for manufacturing a one-piece molded composite airfoil |
| CN1252754A (en) * | 1997-04-16 | 2000-05-10 | 西科尔斯基飞机公司 | Apparatus and method for assembling a helicopter main rotor blade subassembly |
| CN101348009A (en) * | 2003-03-06 | 2009-01-21 | 维斯塔斯风力系统公司 | Method for manufacturing preforming member |
| CN101367257A (en) * | 2008-09-27 | 2009-02-18 | 哈尔滨玻璃钢研究院 | Fibre reinforced resin based composite material fin piece molding mould |
| CN101811366A (en) * | 2009-02-23 | 2010-08-25 | 通用电气公司 | Make the apparatus and method of composite product |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2465667B1 (en) | Airfoil manufacturing system | |
| US11187203B2 (en) | Wind turbines, wind turbine blades, and methods for manufacturing wind turbine blades | |
| CN107000329B (en) | The turnover device for overturning the first mold component for manufacturing wind turbine blade component relative to the second mold component | |
| EP3019316B1 (en) | Method and tools for manufacturing a wind turbine blade | |
| EP3802090B1 (en) | A system and method for manufacturing a wind turbine blade | |
| CN105346100B (en) | A kind of preparation method of the big beam mould of wind electricity blade | |
| CN111712628B (en) | Wind turbine blades using segmented blade assemblies and manufacturing systems and methods | |
| CN101451492A (en) | Method and apparatus for fabricating wind turbine components | |
| EP2998106B1 (en) | Wind turbine blade segment and method of manufacturing the wind turbine blade segment | |
| CN109328129B (en) | Blade mould and method for manufacturing blade shell parts of wind turbine blade | |
| CN106457614A (en) | A wind turbine blade manufacturing system and method | |
| CN111655465A (en) | Apparatus for manufacturing composite airfoils | |
| US12070878B2 (en) | Modular molding units for fabrication of wind turbine blades | |
| CN111448057A (en) | System and method for manufacturing a reinforced wind turbine blade | |
| CN102529112B (en) | Airfoil manufacturing system | |
| KR20170110697A (en) | Method and apparatus for manufacturing preform | |
| CN114953501B (en) | Manufacturing method of blade counterweight box and wind power blade | |
| DK201570772A1 (en) | Tool and method for fabricating shear webs for a wind turbine blade | |
| EP4378673A1 (en) | Distribution mesh for a composite element, and manufacturing method | |
| CN102896780A (en) | Method for manufacturing wind turbine blade of wind generator set |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |