CN101705922A - Large-scale composite material wind-power blade and preparation method thereof - Google Patents
Large-scale composite material wind-power blade and preparation method thereof Download PDFInfo
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- CN101705922A CN101705922A CN200910227056A CN200910227056A CN101705922A CN 101705922 A CN101705922 A CN 101705922A CN 200910227056 A CN200910227056 A CN 200910227056A CN 200910227056 A CN200910227056 A CN 200910227056A CN 101705922 A CN101705922 A CN 101705922A
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Abstract
The invention discloses a large-scale composite material wind-power blade which comprises a suction face shell (1), a pressure face shell (2) and a cutting webplate (3) fixedly connected between the two shells, wherein the suction face shell (1) and the pressure face shell (2) are both sandwich type structural parts of an envelope (4) for covering a core material; the core material comprises a main blade bearing beam (5), a flange reinforcement part (6) of the blade and a filling material (7) arranged between the main blade bearing beam (5) and the reinforcement part (6); and the main blade bearing beam (5) and the reinforcement part (6) both use mixtures of carbon fibers/glass fibers as an reinforcement material. The large-scale composite material wind-power blade has the advantages of light weight, extended critical length, excellent mechanical property, and the like.
Description
Technical field
The present invention relates to a kind of wind electricity blade and preparation method thereof, relate in particular to a kind of wind electricity blade of using Composite Preparation and preparation method thereof.
Background technique
Along with the raising of blade of wind-driven generator designing technique, maximization and lightweight have become the important trend of composite material wind-power blade development.At present large-scale composite material wind-power blade mainly be with glass fibre as reinforcing material, yet the blade large scale development is more and more higher to the requirement of blade strength, rigidity, length of blade and deadweight are also increasing, so that glass fibre is difficult to bear.According to the analysis to glass fibre reinforced composion (GFRP, Glass Fiber Reinforced Polymer) blade, the blade critical length that its strength and stiffness can bear is about 60m at present.Based on the requirement of blade large scale development, in order effectively to increase the blade critical length, blade tip does not touch pylon to guarantee to carry down in extreme wind by blade, need blade be improved, so that blade has enough strength and stiffness.Wherein, blade material being improved is a kind of comparatively feasible approach.
In addition, the application of large-scale composite material wind-power blade also faces a technical problem, promptly how the preparation process of thick cross section, large scale wind electricity blade member is optimized, existing wind electricity blade preparation process adopts the prepreg wet therapy forming process more, not only manufacturing cycle is long, efficient is low, and mass stability is relatively poor, needs special devices such as pre-dipping machine in addition, the cost height.
Summary of the invention
The technical problem to be solved in the present invention is to overcome the deficiencies in the prior art, provide that a kind of quality is light and handy, critical length prolongs, the large-scale composite material wind-power blade of mechanical property excellence, the preparation method of this composite material wind-power blade that a kind of technology is simple, adaptability is strong, cost is low also is provided.
For solving the problems of the technologies described above, the technological scheme that the present invention proposes is a kind of large-scale composite material wind-power blade, described wind electricity blade comprises the suction surface housing, pressure side housing and be fixed in shear web between the two housings, described suction surface housing, the pressure side housing is the sandwiched member that covering coats core, described core comprises the main bearing beam of blade, the edge of a wing reinforcing part of blade and the packing material between main bearing beam and edge of a wing reinforcing part is characterized in that: described main bearing beam and edge of a wing reinforcing part all are to mix as reinforcing material with carbon fibers/fiberglass.
Carbon fiber is a kind of high-performance reinforcing material of excellent performance, is widely used in fields such as Aero-Space.Carbon fiber specific strength and specific modulus height be a kind of ideal material for development lightweight, high-strength and large-scale composite material wind-power blade, but its fancy price have greatly restricted the application of carbon fiber in the wind electricity blade field.In order to alleviate the quality of maximization wind electricity blade, satisfy the intensity and the rigidity requirement of blade simultaneously, also to overcome the problem of cost restriction, technique scheme has adopted a kind of novel reinforcing material system, be about to described carbon fibers/fiberglass hybrid materials and be incorporated into the wind electricity blade field, specifically be with the reinforcing material of these hybrid materials as composite material wind-power blade main bearing beam and edge of a wing reinforcing part, because carbon fibre reinforced composite (CFRP, CarbonFiber Reinforced Polymer) specific strength (strength/density) approximately is 2 times of GFRP, specific modulus (modulus/density) is 3 times of GFRP approximately, therefore adopt the carbon fibers/fiberglass hybrid materials to make the advantage that wind electricity blade can not only be given full play to the high-elastic lightweight of carbon fiber, improve the rigidity and the intensity of blade greatly, increase the critical length of blade, and price more helps the promotion and application of carbon fiber in the wind electricity blade field than adopting pure carbon fiber will to reduce greatly as reinforcing material.
In the main bearing beam reinforcing material (carbon fibers/fiberglass mixes) of technique scheme, the volume ratio of described carbon fiber and glass fibre is preferably 7: 3～and 9: 1, promptly carbon fiber relative volume mark (carbon fiber volume and carbon fiber volume add the ratio of glass volume sum) is 70%～90%.Theoretical and experimental result shows, carbon fiber relative volume mark is that 70%～90% carbon fibers/fiberglass mixes the intensity that the pure glass fibre of the strength ratio that strengthens main bearing beam strengthens main bearing beam and improves 40%～60%, modulus improves 100%～130%, therefore need not to use full carbon fiber to strengthen the requirement that main bearing beam just can fully satisfy the carrying of wind electricity blade main bearing beam.Add the relative volume mark and be 10%～30% glass fibre as the main bearing beam reinforcing material, be for reducing cost on the one hand, but the more important thing is that reason is toughness and the fracture strain in order to increase main bearing beam: because carbon fiber fragility height, the CFRP fracture strain is little, in order to prevent the brittle fracture of main bearing beam under limit wind carries, the glass fibre that adds relative volume mark 10%～30% can effectively improve the toughness and the fracture strain of main bearing beam.In addition, the saturating machine of glass fibre is better than carbon fiber, and the adding of glass fibre can improve the speed that resin adhesive liquid is flooded thick cross section main bearing beam.
In the edge of a wing reinforcing part reinforcing material (carbon fibers/fiberglass mixes) of technique scheme, described carbon fiber is preferably 1: 9 with glass fibre volume ratio～and 3: 7, promptly the relative volume mark of carbon fiber is 10%～30%.Existing blade edge of a wing reinforcing part is to replace foam core with pure GFRP, and purpose is exactly in order to improve the rigidity on the edge of a wing, thereby prevents that blade blade edge of a wing in transportation, installation and running from being destroyed whole aerodynamic configuration and the generating efficiency that influences blade.But for the super sized type blade, the rigidity on the pure GFRP edge of a wing may be difficult to meet the demands, so the form that the present invention adopts carbon fibers/fiberglass to mix improves edge of a wing rigidity.Our research and experiment show, carbon fiber relative volume mark is that the modulus of the pure GFRP of modular ratio of 10%～30% carbon fibers/fiberglass hybrid materials improves 30%～60%, because the edge of a wing is not the primary load bearing parts, modulus improves 30%～60% to be enough to meet the demands, consider the cost problem simultaneously, need not to adopt full carbon fiber reinforced form.
In the technique scheme, described carbon fiber can be the carbon fiber of various forms, but preferably adopts the carbon fibre cloth of continuous fiber braiding; Described glass fibre can be the glass fibre of various forms, but the glass fiber cloth of preferred continuous fiber braiding.Described carbon fibers/fiberglass mixes preferably and is combined by carbon fiber preshaped body and glass fibre preform body, described carbon fiber preshaped body is meant that multilayer carbon fibre cloth shop covers a carbon fibre cloth shop layer body that forms, and described glass fibre preform body is meant that the multilayer woven glass fabric shop covers a glass fiber cloth shop layer body that forms.The two-dimensional fiber cloth why preferred continuous fiber weaves be because two-dimensional fiber cloth is convenient to lay and adjustment, and cost of labor is low as reinforcing material, is particularly suitable for using in the large-scale composite material wind-power blade that thickness changes with shape.
In the technique scheme, the sandwich style sandwich that described carbon fibers/fiberglass mixes for upper and lower interlayer clamping intermediate core layer mixes. and in described main bearing beam and edge of a wing reinforcing part, this sandwich style sandwich hybrid structure has the different forms of expression because of interlayer is different with core material; In described main bearing beam, this upper and lower interlayer is the carbon fiber preshaped body, and intermediate core layer is the glass fibre preform body, thereby forms the structure (referring to accompanying drawing 6) of upper and lower carbon fiber preshaped body interlayer clamping intermediate glass fiber preshaped body sandwich layer; And in the reinforcing part of the described edge of a wing, on, following interlayer is the glass fibre preform body, intermediate core layer is the carbon fiber preshaped body, thereby in the formation, the structure (referring to accompanying drawing 7) of subglass fiber preshaped body interlayer clamping middle carbon fiber preshaped body sandwich layer. in the described sandwich style sandwich hybrid structure, last interlayer, intermediate core layer, the volume ratio of following interlayer is preferably 3: 2: 3. in main bearing beam, why adopt the carbon fiber preshaped body as last, following interlayer, and the glass fibre preform body is as sandwich layer, its reason is: the interlayer of this sandwich structure (skin) bears main load under flecition power, the characteristic that is better than GFRP according to intensity and the modulus of CFRP as can be known, the hybrid structure of above-mentioned main bearing beam and force way can be given full play to the high-performance of carbon fiber; And stressed the be similar to simply supported beam of blade under wind carries, mainly bear the impact force that flexural stress and wind carry, the bending resistance of the promiscuous mode of this main bearing beam and shock resistance optimum. and in the reinforcing part of the edge of a wing, the carbon fibers/fiberglass promiscuous mode adopts the glass fibre preform body as last, following interlayer, the carbon fiber preshaped body is as sandwich layer, its reason is: after blade suction surface housing and the pressure side case bonding, being equivalent to two glass fibre preform bodies at place, the blade edge of a wing is interlayer, the carbon fiber preshaped body is that the sandwich structure of sandwich layer is bonding mutually, bonding plane is a glass fibre layer, and the structure after bonding so also is similar to the sandwiched structure of above-mentioned carbon fiber interlayer clamping glass fibre sandwich layer.
In the technique scheme, described sandwich style sandwich mixes preferably by the stitching thread puncture and is stitched into one; Described stitching thread is one or more in carbon fiber yarn, aramid fibre yarn, quartz fibre yarn, glass fiber yarn, the high-siloxy fibre yarn.With described stitching thread to the stitching of puncturing of carbon fibers/fiberglass preshaped body, can significantly improve the interlayer performance of composite material, weaken its anisotropy, improve its overall performance, particularly its strength and stiffness can be greatly improved, and it is the effective way that improves the composite material overall performance, gives full play to material property that puncture is sewed up.In addition, for thick section structural member, the line hole that stitching thread stays is equivalent to the infiltration lane of macroscopical resin adhesive liquid on the thickness direction, can improve the impregnating speed of resin adhesive liquid on thickness direction in the preparation process greatly.
In the technique scheme, described carbon fibre cloth is preferably one or more in carbon fiber-free weft fabric, carbon fiber plain cloth, carbon fiber three axial cloth, carbon fiber twilled cloth, the carbon fiber forging line cloth; Described glass fiber cloth is preferably the glass single shaft in cloth, glass three axial cloth, glass woven roving, glass plain cloth one or more of cloth, glass twin shaft.Loading characteristic according to blade, the stressed distribution of blade is not uniform, we must guarantee that the intensity of each point of blade all reaches force request when carrying out the layer design of structure shop, and described multiple fibre cloth is convenient to the blade integral structure is designed and lay, and this several cloth stressed respectively has characteristics, can realize having complementary advantages, satisfy the Blade Design requirement, convenient and practical.
In the technique scheme, described covering reinforcing material is preferably glass fibre; Preferred Balsa wood of described packing material and PVC foam.Described shear web is the sandwiched member of web covering coating web core, and described web covering reinforcing material is preferably glass fibre, and described web core is preferably the PVC foam.
The present invention also provides a kind of preparation method of above-mentioned large-scale composite material wind-power blade, may further comprise the steps:
(1) adopt vacuum to import moulding technology (Vacuum Infusion Molding Process) preparation shear web;
(2) mix as reinforcing material with carbon fibers/fiberglass, and adopt vacuum to import the prefabricated main bearing beam of moulding technology;
(3) mix reinforcing material with carbon fibers/fiberglass, and adopt vacuum to import moulding technology to prepare described suction surface housing and pressure side housing as blade edge of a wing reinforcing part;
(4) with the above-mentioned shear web that makes, suction surface housing and pressure side case bonding, make large-scale composite material wind-power blade.
It is a kind of advanced person's the molded technology of composite material low cost liquid that above-mentioned vacuum imports moulding technology (claiming vacuum perfusion process again), have low cost, environmental protection and be suitable for advantages such as large-sized composite material member global formation, its technological principle is to coat, seal the reinforcing material preshaped body with the flexible vacuum bag film on the single face rigid die, get rid of the gas in the die cavity under the negative pressure of vacuum, utilize resin flow, infiltration to realize the dipping of resin, and solidifying obtain composite element to fiber and fabric thereof.This vacuum is imported the preparation that moulding technology is applied to composite material wind-power blade assembly of the present invention, and its advantage more can be given full play of.
Compared with prior art; the invention has the advantages that: make full use of the complementation of carbon fiber and glass fibre performance; prepare the composite material wind-power blade that carbon fibers/fiberglass mixes; both effectively avoided the expensive problem of pure carbon fiber composite material wind-power blade; solved the problem of glass fiber compound material wind electricity blade critical length limitation again; significant to improving the composite material wind-power blade critical length and developing the maximization composite material wind-power blade. as a further improvement on the present invention; the present invention adopts the puncture sewing to handle the reinforcing material preshaped body of blade shell main bearing beam; increase the permeability of preshaped body thickness direction; it is relatively poor to efficiently solve the carbon fiber wetting property; the problem that thick section structural member is difficult to soak into; import the Integratively formed preparation carbon fibers/fiberglass of moulding technology in conjunction with vacuum simultaneously and mix main bearing beam; import the blade shell of moulding technology global formation by vacuum; good integrity; simultaneously can also reduce the waste of material and the discharging of styrene gas, help reducing cost and protecting environment.
Adopt the carbon fibers/fiberglass hybrid composite blade of technique scheme preparation, than pure glass fiber compound material blade, the weight of blade can reduce by 20%～40%, and the critical length of blade can improve 40%～60%.Under same thickness and identical shop layer state, than pure glass fiber compound material blade, the wind resistance that carbon fibers/fiberglass mixes the reinforced composite blade carries flexural modulus and can improve 100%～120%, and the blade tip maximum distortion can reduce by 120%～130%.
Description of drawings
Fig. 1 is the plan view of embodiment of the invention composite material wind-power blade;
Fig. 2 is the profile at A-A place among Fig. 1;
Fig. 3 is the process flow diagram of preparation shear web in the embodiment of the invention;
Fig. 4 is the process flow diagram of prefabricated main bearing beam in the embodiment of the invention;
Fig. 5 is the process flow diagram of moulding suction surface housing and pressure side housing in the embodiment of the invention;
Fig. 6 is three layers of sandwiched structural representation of main bearing beam reinforcing material in the embodiment of the invention;
Fig. 7 is three layers of sandwiched structural representation that the edge of a wing strengthens the body reinforcing material in the embodiment of the invention;
Wherein A represents the carbon fiber preshaped body, and B represents the glass fibre preform body.
Marginal data:
1, suction surface housing 2, pressure side housing
3, shear web 31, web covering
4, covering 5, main bearing beam
6, edge of a wing reinforcing part 7, packing material
Embodiment
Below in conjunction with accompanying drawing and specific embodiment technological scheme of the present invention is described in detail.
Embodiment:
A kind of large-scale composite material wind-power blade of the present invention as depicted in figs. 1 and 2, comprise suction surface housing 1, pressure side housing 2 and be fixed in shear web 3 between the two housings, suction surface housing 1, pressure side housing 2 is the sandwiched composite element that covering 4 coats core, suction surface housing 1, the matrix of pressure side housing 2 is epoxy-resin systems, the reinforcing material of covering 4 is selected glass fibre for use, core comprises the main bearing beam 5 of blade, the blade edge of a wing located the edge of a wing reinforcing part 6 of reinforing function and be filled in main bearing beam 5 and edge of a wing reinforcing part 6 between packing material 7, comprise Balsa wood and PVC foam in the packing material 7.Main bearing beam 5 and edge of a wing reinforcing part 6 all are to mix as reinforcing material with carbon fibers/fiberglass.Shear web 3 is similarly the sandwiched structure that web covering 31 coats the web core, and the web core is selected the PVC foam for use.
In carbon fibers/fiberglass mixes, it is mainly combined by carbon fiber preshaped body and glass fibre preform body, the carbon fiber preshaped body is that the carbon fibre cloth shop layer body that forms covered in multilayer carbon fibre cloth shop, the glass fibre preform body is that the glass fiber cloth shop layer body that forms covered in the multilayer woven glass fabric shop, carbon fibre cloth is wherein selected carbon fiber-free weft fabric for use, glass fiber cloth selects for use the glass single shaft to cloth. as shown in Figure 6 and Figure 7, carbon fibers/fiberglass mixes for last, the sandwich style sandwich of following interlayer clamping intermediate core layer mixes. as shown in Figure 6, in the carbon fibers/fiberglass of main bearing beam 5 mixes, on, following interlayer is carbon fiber preshaped body A, intermediate core layer is glass fibre preform body B, last interlayer, intermediate core layer, the fiber volume fraction of following interlayer is 3: 2: 3. as shown in Figure 7, in the carbon fibers/fiberglass of edge of a wing reinforcing part 6 mixes, on, following interlayer is glass fibre preform body B, intermediate core layer is carbon fiber preshaped body A, last interlayer, intermediate core layer, the fiber volume fraction of following interlayer is similarly 3: 2: 3. this sandwich style sandwich hybrid structure is stitched into one by the puncture of stitching thread aramid fibre yarn.
The preparation process of composite material wind-power blade specifically may further comprise the steps in the present embodiment:
1, preparation shear web
Preparation process's flow process of shear web 3 as shown in Figure 3, concrete preparation method comprises following operation successively:
1.1 shear web shaping die pretreatment
The cleaning mould is repaired smoothly, sprays releasing agent then on shear web shaping die surface.
1.2 cutting and lay web covering reinforcing material and web core
Select surface density 1200g/m
2Three axial weaving fiberglass cloth and surface density 800g/m
2Twin shaft to the reinforcing material of weaving fiberglass cloth as web covering 31 (on the branch covering and following covering), the web core is density 60kg/m
3The PVC foam.At first covering reinforcing material under the web that cuts is laid on the web molding mould, the web core that covering reinforcing material surface lay cuts under the good web of lay then, covering reinforcing material on the good web core surface lay web of lay obtains shear web sandwiched structure preshaped body at last.
1.3 release cloth is covered in cutting and shop
Used release cloth is the R85PA66 type release cloth that Shanghai drop High Seience Technology Co., Ltd. produces, surface density 85g/m
2The release cloth that cuts is laid in the shear web sandwiched structure preshaped body surface that obtains in the step 1.2, and makes it to cover fully this preshaped body.
1.4 lay the auxiliary material system
Lay flow-guiding cloth, honeycomb duct and air pipe equal vacuum at above-mentioned release cloth upper surface and import the moulding technology auxiliary material, and set gum-injecting port and vacuum pumping opening in the die cavity.
1.5 vacuum bag film phonograph seal
Adopt above-mentioned preshaped body and the auxiliary material system of double-layer vacuum bag film phonograph seal, used vacuum bag film is the Vacfilm400Y26100 type vacuum bag film that French Aerorac company produces.At first on mould, seal whole preshaped body and auxiliary material system with first layer vacuum bag film, airtight gum-injecting port also is connected bleeding point with vacuum pump, vacuumize then and detect the sealing die cavity tightness (require degree of vacuum≤-0.098Mpa and can keep negative pressure of vacuum 30min); After first layer vacuum bag film packaging air tightness reaches requirement,, and vacuumize continuation inspection tightness, reach requirement (requirement can continue to keep negative pressure of vacuum) until tightness with the whole first layer bag of the vacuum bag film phonograph seal film system of the second layer.
1.6 resin system mold filling dipping preshaped body
Blade special epoxy resin 1564 and curing agent 3486 systems that used resin system provides for Huntsman company; Open the resin system that gum-injecting port will stir and handle through deaeration and utilize the above-mentioned preshaped body of dipping in the negative pressure of vacuum injection moulding die cavity, treat to close gum-injecting port behind the resin system thorough impregnation preshaped body, and continue to vacuumize the degree of vacuum that keeps in the shaping mold cavity.
1.7 solidifying and reprocessing
Must keep the interior degree of vacuum of shaping mold cavity until completion of cure in the solidification process, carry out reprocessings such as the demoulding, finishing and cleaning after curing is finished and obtain the shear web member.
2, prefabricated main bearing beam
The technological process of prefabricated main bearing beam 5 as shown in Figure 4, concrete preparation method comprises following operation successively:
2.1 main bearing beam shaping die pretreatment
The cleaning mould is repaired smoothly, sprays releasing agent then on main bearing beam shaping die surface.
2.2 cutting and lay main bearing beam reinforcing material
As shown in Figure 6, select for use carbon fibre cloth and glass fiber cloth, the part carbon fibre cloth that at first will cut (12KT300 carbon fiber-free weft fabric, centre plane density 800g/m as reinforcing material
2) be laid on the shaping die, lay thickness accounts for 3/8 of reinforcing material design thickness H, again with glass fiber cloth (surface density 1250g/m
2The glass single shaft of band 50g felt is to cloth) be laid on the aforementioned carbon fibre cloth, lay thickness accounts for 1/4 of reinforcing material design thickness H, the aforesaid carbon fibre cloth of the whole laies of thickness of residue 3/8.
2.3 the main bearing beam preshaped body is sewed up in puncture
Adopt stitching thread that the lamination after lay finishes in the step 2.2 is sewed up to handle and obtain the main bearing beam preshaped body, used stitching thread is the aramid fibre yarn that du pont company produces, the trade mark is Kevlar-29 (3200 dawn), and sewing density is 50mm * 50mm, and sewing up stitching is the lock-stitch stitching.
2.4 release cloth is covered in cutting and shop
(the R85PA66 type release cloth that drop High Seience Technology Co., Ltd. in Shanghai produces, surface density is 85g/m with the release cloth that cuts
2) be laid in the main bearing beam preshaped body upper surface after the stitching, and make it to cover fully preshaped body.
2.5 lay the auxiliary material system
Lay flow-guiding cloth, honeycomb duct and air pipe equal vacuum at the release cloth upper surface and import the moulding technology auxiliary material, and gum-injecting port and vacuum pumping opening are set in die cavity.
2.6 vacuum bag film phonograph seal
Adopt double-layer vacuum bag film phonograph seal preshaped body and auxiliary material system, used vacuum bag film is the Vacfilm400Y26100 type vacuum bag film that French Aerorac company produces.At first on mould, seal whole main bearing beam preshaped body and auxiliary material system with first layer vacuum bag film, airtight gum-injecting port also is connected bleeding point with vacuum pump, vacuumize then and detect the sealing die cavity tightness (require degree of vacuum≤-0.098Mpa and can keep negative pressure of vacuum 30min); After first layer vacuum bag film packaging air tightness reaches requirement,, and vacuumize continuation inspection tightness, reach requirement (requirement can continue to keep negative pressure of vacuum) until tightness with the whole first layer bag of the vacuum bag film phonograph seal film system of the second layer.
2.7 resin system mold filling dipping main bearing beam preshaped body
Blade special epoxy resin 1564 and curing agent 3486 systems that used resin system provides for Huntsman company; Open the resin system that gum-injecting port will stir and the process deaeration is handled and utilize dipping main bearing beam preshaped body in the negative pressure of vacuum injection moulding die cavity, treat to close gum-injecting port behind this preshaped body of resin system thorough impregnation, and continue to vacuumize the degree of vacuum that keeps in the shaping mold cavity.
2.8 solidifying and reprocessing
Must keep the interior degree of vacuum of shaping mold cavity until completion of cure in the solidification process, carry out reprocessings such as the demoulding, finishing, cleaning after curing is finished and obtain main bearing beam 5 prefabricated components.
3, moulding suction surface housing and pressure side housing
The integral forming technique flow process of suction surface housing 1 and pressure side housing 2 as shown in Figure 5, the concrete preparation method of suction surface housing 1 comprises following operation (pressure side housing 2 is with reference to the preparation process of suction surface housing 1):
3.1 housing shaping die pretreatment
The cleaning mould is repaired smoothly, sprays releasing agent then, sprays gel coat again.
3.2 cutting and preparation housing covering reinforcing material and core
According to covering 4 reinforcing materials, edge of a wing reinforcing part 6 reinforcing materials and the packing material 7 of designing requirement cutting suction surface housing 1, prefabricated main bearing beam 5 prefabricated components in the above-mentioned steps are handled in finishing simultaneously.Covering 4 reinforcing materials are selected surface density 1200g/m for use
2Glass three axial weave cloth, surface density 800g/m
2The glass twin shaft to weave cloth and surface density 1250g/m
2The glass single shaft of band 50g felt is to weave cloth (housing covering 4 comprises covering and following covering); Used packing material 7 comprises density 150kg/m
3Balsa wood and density 60kg/m
3The PVC foam; The reinforcing material at edge of a wing reinforcing part 6 places is that carbon fibers/fiberglass mixes, and used carbon fiber is carbon fiber-free weft fabric (12KT300 carbon fiber-free weft fabric, centre plane density 800g/m
2), used glass fibre is surface density 1250g/m
2The glass single shaft of band 50g felt is to cloth, and the volume ratio that mixes of carbon fiber and glass fibre is 1: 3.
3.3 lay covering reinforcing material and core
1 time covering reinforcing material of lay suction surface housing on the shaping die of suction surface housing 1 at first is then at the reinforcing material (carbon fibers/fiberglass of preparation mixes reinforcing material in the step 3.2) at relevant position, covering reinforcing material surface lay main bearing beam 5 prefabricated components, packing material 7 (Balsa wood and the PVC foam prepared in the step 3.2) and edge of a wing reinforcing part 6 places down; Last on lay suction surface housing 1 on the good core of aforementioned lay the covering reinforcing material, obtain suction surface housing 1 preshaped body of sandwiched structure.Wherein, the carbon fibers/fiberglass of edge of a wing reinforcing part 6 mixes the lay mode as shown in Figure 7, the part glass single shaft that at first will cut is laid on the shaping die to cloth, lay thickness accounts for 3/8 of the reinforcing material design thickness H of this place, again carbon fiber-free weft fabric is laid in aforementioned glass single shaft on cloth, lay thickness accounts for 1/4 of reinforcing material design thickness H, the aforesaid glass single shaft of the whole laies of thickness of residue 3/8 is on cloth, the edge of a wing reinforcement preshaped body that obtains need puncture to sew up and handle, used stitching thread is the aramid fibre yarn that du pont company produces, the trade mark is Kevlar-29 (3200 dawn), sewing density is 50mm * 50mm, and sewing up stitching is the lock-stitch stitching.
3.4 release cloth is covered in cutting and shop
(the R85PA66 type release cloth that drop High Seience Technology Co., Ltd. in Shanghai produces, surface density is 85g/m with the release cloth that cuts
2) be laid in the suction surface housing 1 preshaped body upper surface that step 3.3 obtains, and make it to cover fully this preshaped body.
3.5 lay the auxiliary material system
Lay flow-guiding cloth, honeycomb duct and air pipe equal vacuum at above-mentioned release cloth upper surface and import the moulding technology auxiliary material, and gum-injecting port and vacuum pumping opening are set in die cavity.
3.6 vacuum bag film phonograph seal
On suction surface housing shaping die, adopt double-layer vacuum bag film phonograph seal suction surface housing 1 preshaped body and auxiliary material system, used vacuum bag film is the Vacfilm400Y26100 type vacuum bag film that French Aerorac company produces. at first on this mould, seal whole suction surface housing 1 preshaped body and auxiliary material system with first layer vacuum bag film, airtight gum-injecting port also is connected bleeding point with vacuum pump, vacuumize then and detect the sealing die cavity tightness (require degree of vacuum≤-0.098Mpa and can keep negative pressure of vacuum 30min); After first layer vacuum bag film packaging air tightness reaches requirement,, and vacuumize continuation inspection tightness, reach requirement (requirement can continue to keep negative pressure of vacuum) until tightness with the whole first layer bag of the vacuum bag film phonograph seal film system of the second layer.
3.7 resin system mold filling dipping suction surface housing preshaped body
Blade special epoxy resin 1564 and curing agent 3486 systems that used resin system provides for Huntsman company; Open the resin system that gum-injecting port will stir and the process deaeration is handled and utilize dipping suction surface housing 1 preshaped body in the negative pressure of vacuum injection moulding die cavity, treat to close gum-injecting port behind this preshaped body of resin thorough impregnation, and continue to vacuumize the degree of vacuum that keeps in the shaping mold cavity.
3.8 solidifying and reprocessing
Must keep the interior degree of vacuum of shaping mold cavity until completion of cure in the solidification process, carry out the suction surface housing 1 that reprocessings such as the demoulding, finishing and cleaning obtain global formation after curing is finished.
Again according to above operation briquetting pressure face-piece body 2.
In above-mentioned manufacturing process, the preparation process of shear web 3 and main bearing beam 5 prefabricated components can be carried out simultaneously, and the moulding preparation process of suction surface housing 1 and pressure side housing 2 also can be carried out simultaneously.
4, whole bonding
The suction surface housing 1, pressure side housing 2 and the shear web 3 that prepare in the above-mentioned steps is bonding, the structure glue XD4734/XD4735 system that used bonded structural adhesive provides for Huntsman company is cleared up finishing after structure glue curing is finished and is waited reprocessing promptly to obtain the wind electricity blade that carbon fibers/fiberglass of the present invention mixes composite reinforcing material.
Claims (9)
1. large-scale composite material wind-power blade, described composite material wind-power blade comprises suction surface housing (1), pressure side housing (2) and be fixed in shear web (3) between the two housings, described suction surface housing (1), pressure side housing (2) is the sandwiched structural member that covering (4) coats core, described core comprises blade main bearing beam (5), the edge of a wing reinforcing part (6) of blade and be positioned at main bearing beam (5) and edge of a wing reinforcing part (6) between packing material (7), it is characterized in that: described main bearing beam (5) and edge of a wing reinforcing part (6) all are to mix as reinforcing material with carbon fibers/fiberglass.
2. large-scale composite material wind-power blade according to claim 1 is characterized in that: during the carbon fibers/fiberglass of described main bearing beam (5) mixed, the volume ratio of carbon fiber and glass fibre was 7: 3～9: 1; During the carbon fibers/fiberglass of described edge of a wing reinforcing part (6) mixed, the volume ratio of carbon fiber and glass fibre was 1: 9～3: 7.
3. large-scale composite material wind-power blade according to claim 1 and 2, it is characterized in that: it is to be combined by carbon fiber preshaped body and glass fibre preform body that described carbon fibers/fiberglass mixes, described carbon fiber preshaped body is meant that multilayer carbon fibre cloth shop covers a carbon fibre cloth shop layer body that forms, and described glass fibre preform body is meant that the multilayer woven glass fabric shop covers a glass fiber cloth shop layer body that forms.
4. large-scale composite material wind-power blade according to claim 3 is characterized in that: the sandwich style sandwich that described carbon fibers/fiberglass mixes for upper and lower interlayer clamping intermediate core layer mixes; In described main bearing beam (5), this upper and lower interlayer is the carbon fiber preshaped body, and intermediate core layer is the glass fibre preform body; In described edge of a wing reinforcing part (6), upper and lower interlayer is the glass fibre preform body, and intermediate core layer is the carbon fiber preshaped body.
5. large-scale composite material wind-power blade according to claim 4 is characterized in that: in the described sandwich style sandwich hybrid structure, the volume ratio of last interlayer, intermediate core layer, following interlayer is 3: 2: 3.
6. large-scale composite material wind-power blade according to claim 4 is characterized in that: described sandwich style sandwich mixes by stitching thread puncture and is stitched into one; Described stitching thread is one or more in carbon fiber yarn, aramid fibre yarn, quartz fibre yarn, glass fiber yarn, the high-siloxy fibre yarn.
7. large-scale composite material wind-power blade according to claim 3 is characterized in that: described carbon fibre cloth is one or more in carbon fiber-free weft fabric, carbon fiber plain cloth, carbon fiber three axial cloth, carbon fiber twilled cloth, the carbon fiber forging line cloth; Described glass fiber cloth is the glass single shaft in cloth, glass three axial cloth, glass woven roving, glass plain cloth one or more of cloth, glass twin shaft.
8. large-scale composite material wind-power blade according to claim 1 and 2 is characterized in that: described shear web (3) coats the sandwiched member of web core for web covering (31); The reinforcing material of described web covering (31) and covering (4) is glass fibre; Described web core is the PVC foam; Described packing material (7) is Balsa wood and PVC foam.
9. preparation method as each described large-scale composite material wind-power blade in the claim 1～8 may further comprise the steps:
(1) adopts vacuum to import moulding technology and prepare shear web;
(2) mix as reinforcing material with carbon fibers/fiberglass, and adopt vacuum to import the prefabricated main bearing beam of moulding technology;
(3) mix reinforcing material with carbon fibers/fiberglass, and adopt vacuum to import moulding technology to prepare described suction surface housing and pressure side housing as blade edge of a wing reinforcing part;
(4) with the above-mentioned shear web that makes, suction surface housing and pressure side housing bonding, make wind electricity blade.
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