CN114714641A - Manufacturing method of carbon fiber composite blade and carbon fiber composite blade - Google Patents
Manufacturing method of carbon fiber composite blade and carbon fiber composite blade Download PDFInfo
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- CN114714641A CN114714641A CN202011532481.2A CN202011532481A CN114714641A CN 114714641 A CN114714641 A CN 114714641A CN 202011532481 A CN202011532481 A CN 202011532481A CN 114714641 A CN114714641 A CN 114714641A
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
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- 229920006231 aramid fiber Polymers 0.000 claims description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/36—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/382—Automated fiber placement [AFP]
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Robotics (AREA)
- Moulding By Coating Moulds (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
The invention discloses a manufacturing method of a carbon fiber composite blade, which comprises the following steps: installing carbon fiber yarns, sutures and a carbon fiber surface felt substrate on a fiber variable angle spread seam (VAT) device; drawing a fiber seam laying path by adopting professional software, setting the sewing density, and laying and sewing carbon fibers on a base material by fiber angle-variable seam laying (VAT) equipment according to a planned path to obtain a blade preformed body; and putting the preformed body into a metal mold, preparing a composite material blade blank by adopting a Vacuum Assisted Resin Transfer Molding (VARTM) process, cutting and polishing the blade blank to obtain a blade finished product. The method has high manufacturing efficiency, and the obtained carbon fiber composite material blade has good mechanical property and strong integrity and impact-resistant layering capability.
Description
Technical Field
The invention relates to the field of manufacturing of blades for aeroengines, in particular to a manufacturing method of a carbon fiber composite blade and the carbon fiber composite blade.
Background
The carbon fiber resin matrix composite material has wide application in the fields of aerospace, national defense, traffic, building, sports and the like by virtue of a plurality of excellent properties such as light weight, high strength, designability, fatigue resistance, corrosion resistance and the like. The carbon fiber resin matrix composite material is adopted to replace metal materials such as aluminum alloy, titanium alloy and the like to manufacture the aeroengine cold-end blade, and the current mainstream development trend is achieved. GE. The technology is widely adopted by the aeroengines of European and American companies such as Puhui, Roo-Luo and the like, and the aeroengines are successfully used for commercial and military aircrafts such as Boeing, air passenger and the like, so that the weight of the engines can be obviously reduced, the development cost of the engines is reduced, the performance of the engines is greatly improved, and remarkable economic and safety benefits are obtained.
The first generation of aeroengine composite material blades are made by adopting a prepreg paving process, and the biggest defects are that the interlaminar anti-cracking capability is poor and the mechanical property is low; at present, the mainstream technology is to adopt a 2.5-dimensional or three-dimensional weaving technology to manufacture a preformed body and then manufacture a composite material blade by a Resin Transfer Molding (RTM) liquid forming process, so that the damage resistance of the product is obviously improved, and the requirement of long-term use safety performance is met. However, the 2.5 and three-dimensional braiding techniques require a very long cycle time for producing preforms, require a large amount of labor, are expensive, and often are more than ten times the cost of raw materials and curing.
Patent specification CN106863848A discloses a method for forming a composite blade for an aircraft engine, comprising the following steps: spreading the carbon fiber tows, and impregnating the spread carbon fiber tows by using thermoplastic resin slurry to obtain intermediate tows; drying the intermediate tows; heating the intermediate filament bundle by adopting an ultrasonic vibration heating mode, laying the heated intermediate filament bundle layer by adopting a dry filament laying method, and forming a blade prefabricated part after laying; sleeving a carbon fiber fabric sleeve on the outer part of the blade prefabricated body, and sewing the edges of the carbon fiber fabric sleeve and the inner blade prefabricated body by adopting a three-dimensional sewing method; and putting the sewed blade preform and the carbon fiber fabric sleeve into an RTM mold, closing the blade preform and the carbon fiber fabric sleeve by adopting an RTM technology, and curing and molding to obtain the composite material blade. In the patent of the invention, Z-direction reinforcing fibers do not exist between layers of the thermoplastic blade preform, so that the interlayer cracking resistance is still not ideal, and in addition, the problem of poor compatibility exists between the thermoplastic preform inside the thermoplastic blade preform and thermosetting epoxy resin on the outer layer, and cracking separation is easy to occur under impact, damp heat, high and low temperature or periodic fatigue load.
Disclosure of Invention
The invention provides a manufacturing method of a carbon fiber composite material blade, which has high preparation efficiency and excellent mechanical property and impact-resistant layering capability of the blade.
A method of manufacturing a carbon fibre composite blade comprising:
(1) installing carbon fiber yarns, suture lines and a carbon fiber surface felt substrate on fiber variable angle seam laying (VAT) equipment;
(2) drawing a fiber seam laying path by adopting professional software, setting the sewing density, and laying and sewing carbon fibers on a base material by fiber angle-variable seam laying (VAT) equipment according to a planned path to obtain a blade preformed body;
(3) and putting the preformed body into a metal mold, preparing a composite material blade blank by adopting a Vacuum Assisted Resin Transfer Molding (VARTM) process, cutting and polishing the blade blank to obtain a blade finished product.
The invention adopts full-automatic equipment to manufacture the preformed body by a fiber variable angle seam laying (VAT) technology, and then manufactures the carbon fiber composite material blade by a Vacuum Assisted Resin Transfer Molding (VARTM) technology, thereby improving the manufacturing efficiency compared with 2.5 and three-dimensional weaving process methods; the whole blade is continuously made of a bundle of carbon fibers, so that the blade has high mechanical property.
In the step (1), the step (c),
the linear density of the carbon fiber is not more than 800 tex.
The grade specification of the carbon fiber comprises T300-1K, T300-3K, T300-6K, T700-12K, T800-6K, T800-12K, T1000-12K, M40-6K, M40-12K, M46-6K, M46-12K, M50-6K, M55-6K, M60-3K or M60-6K.
The linear density of the carbon fiber indicates the thickness degree, and when the linear density exceeds 800tex in the actual VAT seam laying process, the too thick fiber is not easy to bend or the turning radius is too large, so that a plurality of seam laying defects are easily generated.
The suture line comprises aramid fiber, polyethylene fiber, PBO fiber, terylene, chinlon, acrylic fiber and the like, and the linear density is not more than 3000D.
The suture form includes no twist and/or twisting.
The suture line is required to be thin, good in toughness and high in strength, is made of artificial organic fibers, is good in strength and toughness and is beneficial to enhancing the interlayer cracking resistance. The suture with the linear density exceeding 3000D is easy to cause too high arrangement density of the suture, excessive extrusion of carbon fibers by Z-direction fibers causes excessive defects, interlayer cracking resistance is reduced, and adverse effects are caused on X/Y-direction carbon fibers.
The carbon fiber surface felt substrate is used as a sewing substrate, and the surface density is not more than 50g/m2。
The form of the carbon fiber surfacing mat substrate comprises oriented mat or random mat.
When the surface felt surface density is too high, the thickness is large, the occupied volume is large, the performance of the composite material is not facilitated, and the deformation is difficult when the surface felt surface density is too thick, so that the surface felt surface density is not conducive to paving in a mold.
In the step (2),
the professional software is CAD two-dimensional drawing software, such as AutoCAD, CAXA and the like.
The stitch density includes 3 × 3, 5 × 5 or 8 × 8 (line space × needle space, mm).
When the sewing density is too high, the sewing thread is too much, and the sewing fails due to easy entanglement; too small, the stitching is not secure.
The carbon fiber seam laying path is formed by laying seams on a bundle of carbon fibers layer by layer, and the width of each layer of seam laying is reduced by 1-3mm from bottom to top to prepare a preformed body with thick middle and thin two ends.
The effect of thick middle and thin two ends can be realized only by reducing the width of each layer of seam. The effect that the transition is gentle can be realized to every layer reduction 1 ~ 3mm, guarantees that the blade outward appearance is smooth-going, accords with the aerodynamic appearance requirement.
In the step (3), the step (c),
at the placeThe surface of the female die and the male die of the metal die is paved with a layer of T300-3K carbon fiber woven cloth or prepreg, and the fiber surface density is not more than 240g/m2。
The T300-3K carbon fiber woven cloth or the prepreg comprises plain weave, twill weave or satin weave.
The woven cloth or the prepreg has ordered and beautiful surface lines, and can shield and fill fiber gaps existing in the sewing preform, thereby improving the appearance. The T300-3K plain weave, twill weave and satin weave cloth has the advantages of softness, easy covering, beautiful lines, high cost performance and the like. The surface density exceeds 240g/m2The woven cloth is too thick, the covering deformation is poor, and the excessive thickness of the blades or the space of the preformed body is easily occupied, so that the strength is adversely affected.
And after one-time VARTM glue injection is finished, unloading the pressure of the VARTM equipment, re-compacting, vacuumizing and injecting glue, and repeating the steps for 2-3 times.
Through injecting glue extrusion many times, ensure to get rid of the inside remaining space of combined material completely, obtain the carbon-fibre composite blade that the flooding is complete, get rid of and remain the hole, can reduce or even eliminate blade internal defect, improve the closely knit degree of blade, finally improve the external force damage resistance performance and the live-in-service life of blade.
And (3) polishing the surface of the demoulded blade blank by using 500-1500# abrasive paper, and putting the blade blank into the mould again for injecting glue and heating for curing.
The surface of the blade manufactured for the first time mostly has tiny closed air holes, namely surface defects. The closed holes can be changed into open holes by polishing with fine sand paper, and the air holes can be filled by injecting glue again, so that the defect of surface air holes is eliminated.
The invention also provides the carbon fiber composite blade prepared by the manufacturing method of the carbon fiber composite blade, and the carbon fiber composite blade has excellent mechanical property, surface finish and impact-resistant layering capability.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, the VAT technology is adopted to prepare the carbon fiber composite blade preformed body, so that the manufacturing efficiency is improved, the labor cost is reduced, and the precise cutting positioning and direction of the fiber angle can be ensured by machine laying, thereby being beneficial to improving the quality stability of the composite blade product;
(2) according to the invention, a bundle of carbon fibers is continuously paved, so that the mechanical property of the fiber material can be improved, the interlayer bonding strength can be increased due to the existence of the sewing line, and the integrity and the impact-resistant layering capacity of the composite material blade are finally improved;
(3) according to the invention, the composite material blade is prepared by adopting the technology of combining VAT and VARTM, compared with the traditional method, the weight is reduced, and the low-cost batch manufacturing requirement of the high-performance carbon fiber composite material blade is met.
Drawings
FIG. 1 is a schematic view of the overall structure of a carbon fiber composite blade;
fig. 2 is a schematic view of VAT production of a blade preform, wherein (a) is a schematic view of VAT principle, and (b) is a schematic view of layer-by-layer seam laying of the blade preform.
Detailed Description
The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings so that the objects, features and advantages of the invention can be more clearly understood. It should be understood that the embodiments shown in the drawings are not intended to limit the scope of the present invention, but are merely intended to illustrate the spirit of the technical solution of the present invention.
Example 1
FIG. 1 is a schematic view of the overall structure of a carbon fiber composite blade, which is composed of an upper tenon, a blade body, a lower tenon and a base, wherein the upper tenon, the blade body and the lower tenon are integrally laid by adopting VAT technology at one time; the base is thick, and multiple layers of carbon fiber woven cloth are adopted to be laid and thickened on the basis; and finally, preparing the carbon fiber composite material blade by adopting a VARTM process. The manufacturing method comprises the following steps:
(1) placing a roll of T700-6K carbon fiber and Kevlar29(400D) suture thread on a laying head of a VAT device, wherein two bundles of yarns pass through needle holes at the tail ends respectively through two groups of independent yarn guide rings; carbon fiber thin felt (30 g/m)2) The seam is placed on a seam laying worktable, flattened and fixed by clamping plates at the periphery to prevent sliding in the seam laying process;
(2) as shown in fig. 2(a), the basic principle of the fiber variable-angle pulling-stitching technique is to stitch a carbon fiber yarn on a base material by using a stitch line and a stitch needle according to a predetermined trajectory to prepare a blade preform. Drawing a seam paving path of the carbon fiber yarn by adopting CAD software, and guiding the seam paving path into VAT equipment; opening the control end, and setting the stitching density to be 3 multiplied by 3 (line spacing multiplied by needle spacing, mm); starting a program, starting to lay seam fibers layer by layer as shown in fig. 2(b) until all tasks are completed; finally, cutting the carbon fiber thin felt along the edge by using a pair of scissors to obtain a blade preformed body;
(3) cleaning the surfaces of a female die and a male die of the die, and coating a release agent; placing the preformed body into a mold cavity, adjusting the position to enable the preformed body to be tightly attached to the mold cavity, and locally trimming the preformed body by using tools such as scissors and the like if necessary; cutting 10 layers of 3K carbon fiber woven cloth with the size of 10cm multiplied by 3cm, and placing the cloth at the position of a mold cavity base for local thickening; in order to prevent the material from slipping, the material can be fixed by adopting conventional sizing glue spraying;
(4) after all materials are placed into a die cavity, the female die and the male die are closed, the die cavity and the male die are placed into a vulcanizing machine to be compressed (the pressure is 2-5MPa), an exhaust pipe and an injection pipe are connected, a vacuum pump is started to vacuumize the die cavity, the pressure is maintained for 15min, the change of a pressure gauge is observed, and the sealing is ensured. If the pressure change is overlarge, the air leakage position is checked, and the sealing strip, the glue injection pipe, the glue outlet pipe, the sealing gasket, the valve and the like are replaced again when necessary;
(5) and starting the glue injection machine, and slowly injecting the epoxy resin into the die cavity, wherein the glue injection pressure is 2MPa, and the glue injection time is 3 min. After the primary glue injection is completed, the pressure of the vulcanizing machine can be released and the vulcanizing machine is compressed again for secondary glue injection, so that the internal gaps can be eliminated, and the dipping effect can be improved. After the glue injection is finished, starting heating for curing (100 ℃, 2h) and post-curing (150 ℃, 2 h);
(6) and naturally cooling the mold to below 60 ℃, opening the mold, and taking out the product. Carrying out post-processing on the blade by adopting a tool to finally obtain a finished product of the carbon fiber composite blade;
the manufacturing period of the blade preform is 20 min; the tensile strength of the blade composite material is 1100MPa according to the test of the ASTM D3039 standard; according to the test of ADTM D7264 standard, the bending strength reaches 900 MPa; interlaminar shear strength (ILSS) of 60MPa was achieved according to ASTM D2344 notation; the compression strength after impact (CAI) reached 280MPa, tested according to ASTM D7137.
Example 2
Fig. 1 is a schematic view of the overall structure of a carbon fiber composite blade. The manufacturing method comprises the following steps:
(1) placing a T700-6K carbon fiber and Kevlar29(200D) suture reel on a laying head of VAT equipment, and enabling two bundles of yarns to respectively pass through a needle hole at the tail end through two groups of independent yarn guide rings; carbon fiber thin felt (30 g/m)2) The seam is placed on a seam laying worktable, flattened and fixed by clamping plates at the periphery to prevent sliding in the seam laying process;
(2) drawing a seam paving path of the carbon fiber yarn by adopting professional software, and guiding the seam paving path into VAT equipment; opening the control end, and setting the stitching density to be 3 multiplied by 3 (line spacing multiplied by needle spacing, mm); starting a program, and starting layer-by-layer seam laying of fibers until all tasks are completed; finally, cutting the carbon fiber thin felt along the edge by using a pair of scissors to obtain a blade preformed body;
(3) an automatic cloth cutting machine is used for cutting T300-3K woven cloth or prepreg, the size is 15cm multiplied by 8cm, the number is 2, the T300-3K woven cloth or prepreg is used as upper and lower surface materials of blades, and the appearance quality is improved;
(4) cleaning the surfaces of a female die and a male die of the die, and coating a release agent; firstly, laying cut T300-3K woven cloth or prepreg in a male die and a female die, and fixing the positions by using glue spraying; then putting the preformed body into a mold cavity, adjusting the position to enable the preformed body to be tightly attached to the mold cavity, and locally trimming the preformed body by using tools such as scissors and the like if necessary; cutting 10 layers of T300-3K carbon fiber woven cloth with the size of 10cm multiplied by 3cm, and placing the cloth at the position of a mold cavity base for local thickening; in order to prevent the material from slipping, the material can be fixed by adopting conventional sizing glue spraying;
(5) after all materials are placed into a die cavity, the female die and the male die are closed, the die cavity and the male die are placed into a vulcanizing machine to be compressed (the pressure is 2-5MPa), an exhaust pipe and an injection pipe are connected, a vacuum pump is started to vacuumize the die cavity, the pressure is maintained for 15min, the change of a pressure gauge is observed, and the sealing is ensured. If the pressure change is overlarge, the air leakage position is checked, and the sealing strip, the glue injection pipe, the glue outlet pipe, the sealing gasket, the valve and the like are replaced again when necessary;
(6) and starting the glue injection machine, and slowly injecting the epoxy resin into the die cavity, wherein the glue injection pressure is 3MPa, and the glue injection time is 5 min. After the primary glue injection is completed, the pressure of the vulcanizing machine can be released and the vulcanizing machine is compressed again for secondary glue injection, so that the internal gaps can be eliminated, and the dipping effect can be improved. After the glue injection is finished, starting heating for curing (100 ℃, 2h) and post-curing (150 ℃, 2 h);
(7) and naturally cooling the mold to below 60 ℃, opening the mold, and taking out the product. Carrying out post-processing on the blade by adopting a tool to finally obtain a finished product of the carbon fiber composite blade;
the manufacturing cycle of the blade preform is 25 min; the tensile strength of the blade composite material is 1200MPa according to the test of the ASTM D3039 standard; according to the test of ADTM D7264 standard, the bending strength reaches 850 MPa; interlaminar shear strength (ILSS) of 64MPa was achieved according to ASTM D2344 notation; the compression strength after impact (CAI) reached 275MPa, tested according to ASTM D7137.
Example 3
Fig. 1 is a schematic view of the overall structure of a carbon fiber composite blade. The manufacturing method comprises the following steps:
(1) placing a roll of T700-6K carbon fiber and Kevlar29(400D) suture thread on a laying head of a VAT device, wherein two bundles of yarns pass through needle holes at the tail ends respectively through two groups of independent yarn guide rings; carbon fiber thin felt (30 g/m)2) The seam is placed on a seam laying worktable, flattened and fixed by clamping plates at the periphery to prevent sliding in the seam laying process;
(2) drawing a seam paving path of the carbon fiber yarn by adopting professional software, and guiding the seam paving path into VAT equipment; opening the control end, and setting the stitching density to be 3 multiplied by 3 (line spacing multiplied by needle spacing, mm); starting a program, and starting layer-by-layer seam laying of fibers until all tasks are completed; finally, cutting the carbon fiber thin felt along the edge by using a pair of scissors to obtain a blade preformed body;
(3) an automatic cloth cutting machine is used for cutting T300-3K woven cloth or prepreg, the size is 15cm multiplied by 8cm, the number is 2, the T300-3K woven cloth or prepreg is used as upper and lower surface materials of blades, and the appearance quality is improved;
(4) cleaning the surfaces of a female die and a male die of the die, and coating a release agent; firstly, laying cut T300-3K woven cloth or prepreg in a male die and a female die, and fixing the positions by using glue spraying; then putting the preformed body into a mold cavity, adjusting the position to enable the preformed body to be tightly attached to the mold cavity, and locally trimming the preformed body by using tools such as scissors and the like if necessary; cutting 10 layers of T300-3K carbon fiber woven cloth with the size of 10cm multiplied by 3cm, and putting the cloth at the position of a mold cavity base for local thickening; in order to prevent the material from slipping, the material can be fixed by adopting conventional sizing glue spraying;
(5) after all materials are placed into a die cavity, the female die and the male die are closed, the die cavity and the male die are placed into a vulcanizing machine to be compressed (the pressure is 2-5MPa), an exhaust pipe and an injection pipe are connected, a vacuum pump is started to vacuumize the die cavity, the pressure is maintained for 15min, the change of a pressure gauge is observed, and the sealing is ensured. If the pressure change is overlarge, the air leakage position is checked, and the sealing strip, the glue injection pipe, the glue outlet pipe, the sealing gasket, the valve and the like are replaced again when necessary;
(6) and starting the glue injection machine, and slowly injecting the epoxy resin into the die cavity, wherein the glue injection pressure is 3MPa, and the glue injection time is 4 min. After the primary glue injection is completed, the pressure of the vulcanizing machine can be released and the vulcanizing machine is compressed again for secondary glue injection, so that the internal gaps can be eliminated, and the dipping effect can be improved. After the glue injection is finished, starting heating for curing (100 ℃, 2h) and post-curing (150 ℃, 2 h);
(7) and naturally cooling the mold to below 60 ℃, opening the mold, and taking out the product. The surface of the blade is carefully polished by using abrasive paper more than 600#, and for pinhole defects which locally appear, a sharp-pointed tool can be used for breaking pinholes to enable the pinholes to be in an open state; finally, cleaning the leaves with alcohol, and naturally drying the leaves;
(8) and (5) putting the blade into the mold again, and repeating the steps (5) to (6). The step can greatly improve the surface smoothness of the blade, the surface roughness is measured by adopting a surface profiler, and the Ra value is reduced to be within 0.5 mu m from 2-5 mu m;
(9) and naturally cooling the mold to below 60 ℃, opening the mold, and taking out the product. Carrying out post-processing on the blade by adopting a tool to finally obtain a finished product of the carbon fiber composite blade;
the manufacturing period of the blade preform is 18 min; the tensile strength of the blade composite material reaches 1150MPa according to the test of the ASTM D3039 standard; according to the test of ADTM D7264 standard, the bending strength reaches 825 MPa; interlaminar shear strength (ILSS) of 60MPa was achieved according to ASTM D2344 notation; the compressive strength after impact (CAI) reached 262MPa, tested according to ASTM D7137.
While the preferred embodiments of the present invention have been illustrated and described in detail, it should be understood that various changes and modifications of the invention can be effected therein by those skilled in the art after reading the above teachings of the invention. Such equivalents are intended to fall within the scope of the claims appended hereto.
Claims (10)
1. A method of manufacturing a carbon fibre composite blade comprising:
(1) installing the carbon fiber yarns, the suture lines and the carbon fiber surface felt base materials on fiber variable-angle seam paving equipment;
(2) drawing a fiber seam laying path by adopting software, setting a sewing density, and laying and sewing carbon fibers on a base material by using fiber angle-variable seam laying equipment according to a planned path to obtain a blade preformed body;
(3) and putting the preformed body into a metal mold, preparing a composite material blade blank by adopting a vacuum assisted resin transfer molding process, and cutting and polishing the blade blank to obtain a blade finished product.
2. The method for manufacturing a carbon fiber composite blade according to claim 1, wherein in the step (1), the linear density of the carbon fiber is not more than 800 tex.
3. The method for manufacturing the carbon fiber composite blade according to claim 1, wherein in the step (1), the sewing thread comprises aramid fiber, polyethylene fiber, PBO fiber, terylene, chinlon or acrylic fiber, and the linear density is not more than 3000D.
4. The method of manufacturing a carbon fiber composite blade as claimed in claim 1, wherein the method further comprises a step of forming a carbon fiber composite materialIn the step (1), the carbon fiber surface felt substrate is used as a sewing substrate, and the surface density is not more than 50g/m2。
5. The method of claim 1, wherein in step (2), the stitch density comprises 3 x 3, 5 x 5 or 8 x 8 mm.
6. The method for manufacturing the carbon fiber composite blade as claimed in claim 1, wherein in the step (2), the carbon fiber seam laying path is as follows: and (3) paving seams on a bundle of carbon fibers layer by layer, wherein the width of each layer of paved seams from bottom to top is reduced by 1-3mm, and a preformed body with thick middle and thin two ends is prepared.
7. The method for manufacturing the carbon fiber composite blade according to claim 1, wherein in the step (3), a layer of T300-3K carbon fiber woven cloth or prepreg is coated on the surfaces of the female die and the male die of the metal die, and the fiber areal density is not more than 240g/m2。
8. The method for manufacturing the carbon fiber composite blade according to claim 1, wherein in the step (3), after the glue injection of the resin transfer molding process is completed, the pressure of the resin transfer molding process equipment is unloaded, and the steps of compacting, vacuumizing and glue injection are repeated for 2-3 times.
9. The method for manufacturing the carbon fiber composite blade as claimed in claim 1, wherein in the step (3), the surface of the blade is polished by 500-1500# sandpaper from the blade blank after being demolded, and the blade is placed into the mold again for injecting glue and heating for curing.
10. A carbon fibre composite blade obtained by the method for manufacturing a carbon fibre composite blade according to any one of claims 1 to 9.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040074589A1 (en) * | 2000-12-08 | 2004-04-22 | Andreas Gessler | Method for producing multilayer tailored fiber placement (tfp) preforms using meltable fixing fibers |
| CN101228022A (en) * | 2005-07-22 | 2008-07-23 | 空中客车德国有限公司 | Method for producing in a tfp method one-or multi-layer layer fibre preforms and a support layer |
| CN108237739A (en) * | 2017-12-22 | 2018-07-03 | 中航复合材料有限责任公司 | A kind of preparation method of the pre- toughened fiber preform of self-fixing |
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2020
- 2020-12-22 CN CN202011532481.2A patent/CN114714641A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040074589A1 (en) * | 2000-12-08 | 2004-04-22 | Andreas Gessler | Method for producing multilayer tailored fiber placement (tfp) preforms using meltable fixing fibers |
| CN101228022A (en) * | 2005-07-22 | 2008-07-23 | 空中客车德国有限公司 | Method for producing in a tfp method one-or multi-layer layer fibre preforms and a support layer |
| CN108237739A (en) * | 2017-12-22 | 2018-07-03 | 中航复合材料有限责任公司 | A kind of preparation method of the pre- toughened fiber preform of self-fixing |
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