CN114559680B - Forming die and forming method for ship propeller composite material blade autoclave - Google Patents
Forming die and forming method for ship propeller composite material blade autoclave Download PDFInfo
- Publication number
- CN114559680B CN114559680B CN202210103719.2A CN202210103719A CN114559680B CN 114559680 B CN114559680 B CN 114559680B CN 202210103719 A CN202210103719 A CN 202210103719A CN 114559680 B CN114559680 B CN 114559680B
- Authority
- CN
- China
- Prior art keywords
- die
- blade
- composite material
- prepreg
- cavity
- 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
- 239000002131 composite material Substances 0.000 title claims abstract description 182
- 238000000034 method Methods 0.000 title claims abstract description 44
- 238000000465 moulding Methods 0.000 claims abstract description 72
- 229910052751 metal Inorganic materials 0.000 claims abstract description 55
- 239000002184 metal Substances 0.000 claims abstract description 55
- 238000007723 die pressing method Methods 0.000 claims abstract description 35
- 238000004519 manufacturing process Methods 0.000 claims abstract description 17
- 238000003825 pressing Methods 0.000 claims abstract description 12
- 238000007789 sealing Methods 0.000 claims description 27
- 239000000463 material Substances 0.000 claims description 25
- 238000002360 preparation method Methods 0.000 claims description 24
- 238000013461 design Methods 0.000 claims description 18
- 238000011282 treatment Methods 0.000 claims description 18
- 239000012945 sealing adhesive Substances 0.000 claims description 13
- 238000006243 chemical reaction Methods 0.000 claims description 12
- 238000005520 cutting process Methods 0.000 claims description 12
- 238000001514 detection method Methods 0.000 claims description 12
- 238000010438 heat treatment Methods 0.000 claims description 12
- 239000002994 raw material Substances 0.000 claims description 9
- 238000004140 cleaning Methods 0.000 claims description 7
- 238000009966 trimming Methods 0.000 claims description 7
- 238000005498 polishing Methods 0.000 claims description 6
- 101100134058 Caenorhabditis elegans nth-1 gene Proteins 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 6
- 238000009434 installation Methods 0.000 description 6
- 238000012546 transfer Methods 0.000 description 5
- 239000003795 chemical substances by application Substances 0.000 description 4
- 239000011248 coating agent Substances 0.000 description 4
- 238000000576 coating method Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 239000004744 fabric Substances 0.000 description 4
- 238000009745 resin transfer moulding Methods 0.000 description 4
- 238000000926 separation method Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000007493 shaping process Methods 0.000 description 3
- 238000007711 solidification Methods 0.000 description 3
- 230000008023 solidification Effects 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009499 grossing Methods 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000003746 surface roughness Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910001018 Cast iron Inorganic materials 0.000 description 1
- 244000137852 Petrea volubilis Species 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000005253 cladding Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Classifications
-
- 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
- B29C70/34—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 shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—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 shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- 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
- B29C70/34—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 shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—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 shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/087—Propellers
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention relates to a molding die of an autoclave for a composite material blade of a ship propeller, which comprises a main body die, a die movable block and a die pressing plate; the main body die is provided with a blade cavity matched with the blade type value and a movable block chute matched with the die movable block, the blade cavity comprises a blade cavity and a blade root cavity, the movable block chute is arranged close to the blade root cavity, and the die movable block is inserted into the movable block chute through an upper end opening of the movable block chute; the die loose piece is provided with a blade root mounting groove matched with the metal connecting piece, and an opening is formed in one side of the die loose piece, which faces the blade cavity; the die pressing plate covers the upper end opening of the movable block chute and is fixedly connected with the main die for applying pre-pressing force to promote the product to be clamped in place; the requirement of the large-scale blade for the fractional molding can be met by additionally arranging the die backing plate, and the blades with other similar structures can be molded. The invention can realize the autoclave molding process of the large-scale propeller composite material blade, can improve the production efficiency and reduce the die cost while ensuring high yield.
Description
Technical Field
The invention relates to the technical field of ship propellers, in particular to a molding die and a molding method for an autoclave of a composite material blade of a ship propeller.
Background
At present, the domestic conventional ship propeller is basically manufactured by adopting metal. With the higher requirements of a ship system on the propeller propulsion efficiency, the noise reduction effect and the weight reduction effect, the composite material of the ship system gradually becomes an industry trend.
The composite material blade of the ship propeller has extremely complex structural shape and very high quality and size requirements. Such as very high blade curvature, high blade root connection requirements and different forms, large blade root thickness, thin blade tip and easy deformation. Very high demands are placed on the mould both from a technical and a cost point of view. On the premise of ensuring high yield, the die is expected to be heated up quickly, the product is solidified, cooled down quickly and demoulded, the whole production efficiency is improved, and the die cost is reduced. Therefore, the mold is particularly important as an important tool for producing composite blades.
For conventional composite blades, alternative manufacturing processes include RTM processes, molding processes, and autoclave processes. The RTM process and the mould pressing process both need double-mould moulds, the mould cost is high, when the large-size complex composite material blade is formed, the mould pressing process double-mould moulds are large in size and thickness, the heat transfer efficiency is low, complex heat transfer pipelines are needed to be arranged in the mould, the technical difficulty is very high, and the cost control is not facilitated; while autoclave technology only needs a single mode, the technology has great technical difficulty for forming large-size complex composite material paddles and has high technology cost.
In addition, the formation of composite articles is often unique. That is, the molding process is different for different products, and the required mold is also different. The existing RTM process, mould pressing process and autoclave process generally need to prepare a plurality of sets of moulds for the fractional forming of large-scale products, which is not beneficial to the control of cost.
Chinese patent CN212888465U discloses a blade pre-mold of a split composite propeller, comprising a pre-mold main body mold, wherein the pre-mold main body mold comprises a base, a spiral groove is arranged on the base, and a chute is arranged on one side of the base, which is positioned on the spiral groove; the sliding block is slidably arranged in the sliding groove; a concave part is arranged on the side surface of the sliding block adjacent to the spiral groove; the concave part and the spiral groove are enclosed to form a containing cavity which is matched with the outer contour of the blade. In the preforming process, the material sheets are firstly formed into designed specification sizes, and are orderly arranged according to the attaching sequence; and removing the sliding block from the sliding groove, paving a material sheet in the spiral groove of the pre-forming die, paving the material sheet in the concave part of the sliding block, splicing the sliding block in the sliding groove to be in butt joint with the spiral groove, and paving the material sheet in the spiral concave part to form the paddle pre-forming body. The mold design suffers from the following disadvantages: (1) The open type movable block design of the transverse moving die is difficult to ensure the air tightness required by the autoclave forming process, and is only suitable for the die pressing process; (2) The mold is only suitable for manufacturing the blade and the blade root of the blade which are formed by prepreg, and is not suitable for the blade with the blade root being a metal connecting piece; (3) The blade root of the large composite material blade with the complex structure is very thick in corner position, and the whole blade is difficult to form at one time, the blade root of the large composite material blade is formed at one time, and meanwhile, the patent CN111873449A is combined, and the comparative patent mold is only suitable for forming small blades; (4) The die cannot meet the requirement of the fractional molding of the large-scale propeller blade.
Disclosure of Invention
The invention aims to solve the technical problems of the prior art and provides a molding die and a molding method of an autoclave for a composite material blade of a ship propeller, the mold and the method can realize the autoclave molding process of the large-scale propeller composite material blade, ensure high yield, improve production efficiency and reduce mold cost.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a boats and ships screw combined material paddle autoclave forming die, autoclave forming die is monolithic mould, and the blade root of its combined material paddle of wanting to make is the metal connecting piece, and the metal connecting piece surface cladding has combined material outer skin;
The autoclave forming die comprises a main die, a die movable block and a die pressing plate; the main body die is provided with a blade cavity matched with the blade type value and a movable block chute matched with the die movable block, the blade cavity comprises a blade cavity and a blade root cavity which are communicated with each other, the movable block chute is arranged close to the blade root cavity, and the die movable block is inserted into the movable block chute through an upper end opening of the movable block chute; the die loose piece is provided with a blade root mounting groove matched with the metal connecting piece, and one side of the blade root mounting groove, which faces the blade cavity, is provided with an opening so as to connect the metal connecting piece with the composite material blade; the die pressing plate is used for covering the upper end opening of the movable block chute and is fixedly connected with the main die, so that pre-pressing force is applied in the manufacturing process to promote the product to be clamped in place.
In the above scheme, the forming die further comprises a die pad plate, wherein the die pad plate comprises a blade pad plate and a blade root pad plate; the bottom surface shape value of the blade pad is conformal with the blade cavity shape value so as to be conveniently installed in the blade cavity, the surface of the blade pad is provided with the blade pad cavity, and the blade pad cavity is matched with the blade structure of the composite material blade blank mold formed in a dividing mode or is matched with the blade structure of the composite material blade with a similar structure; the bottom surface type value of the blade root backing plate and the blade root cavity type value follow-up shape so as to be installed in the blade root cavity, the surface of the blade root backing plate is provided with the blade root backing plate cavity, and the blade root backing plate cavity is matched with the blade root structure of the composite material blade blank mold formed in a dividing mode or is matched with the blade root structure of the composite material blade with a similar structure.
In the scheme, the blade root backing plate and the blade backing plate are fixedly connected in a detachable mode.
In the scheme, a plurality of positioning clamping groove bolts are arranged on the periphery of the die backing plate, and the die backing plate is fixed in the corresponding cavity of the main die through the positioning clamping groove bolts.
In the scheme, a plurality of composite material blade raw material paving positioning datum points are arranged around the upper surface of the blade cavity of the main body die.
In the scheme, the main body die is of an integral structure, and hollow open holes are formed in all sides and the bottom.
In the above scheme, the blade root mounting groove is internally provided with the blade root positioning hole.
The invention also provides a molding process of the ship propeller composite material blade autoclave, which adopts the molding die of the ship propeller composite material blade autoclave to mold the composite material blade matched with the blade cavity, and comprises the following steps:
S1.1, completing related preparation work, including: the prepreg layering design, engineering drawing conversion, cutting and numbering for the composite material blade are completed, and a laser projection positioning data file is formed at the same time; completing the preparation of a laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
S1.2, paving and pasting prepreg at the lower half of the composite blade: directly paving the first layer of prepreg in a blade cavity of the main body die according to a laser projection positioning contour line on the main body die; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; then sequentially completing the prepreg paving of all paving numbers on the lower half of the composite material blade;
s1.3, loading the metal connecting piece into a blade root mounting groove of a die loose piece, and integrally assembling the die loose piece into a loose piece chute of a main body die;
S1.4, mounting a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the metal connecting piece is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured;
S1.5, repeating the step S1.2 to finish the paving of the prepreg on the upper half of the composite material blade;
S1.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
S1.7, placing the whole body die which is subjected to prepreg paving and integral sealing in an autoclave, heating, pressurizing and curing, wherein a curing system is specifically set according to prepreg performance, layering thickness and die structure size;
S1.8, moving the cured composite material blade out of the autoclave along with the die, demoulding, and trimming to obtain the composite material blade.
The invention also provides a molding process of the large-scale ship propeller composite material blade autoclave, which adopts the molding die of the ship propeller composite material blade autoclave to mold the large-scale composite material blade in a divided manner, and the large-scale composite material blade is firstly split into N blank molds and one product mold from the structure, wherein N is more than or equal to 1; the molding process comprises the following steps:
Step one, blank mold forming:
S2.1, completing related preparation work, including: preparing a die backing plate matched with the first layer of blade blank die, and respectively installing a blade backing plate and a blade root backing plate of the die backing plate in a blade cavity and a blade root cavity; the prepreg layer design, engineering drawing conversion, cutting and numbering for the composite material blade blank mold are completed, a laser projection positioning data file is formed at the same time, and the preparation of a laser projection positioning instrument is completed according to the main body mold positioning reference point and the laser projection positioning data file;
S2.2, paving and pasting prepreg at the lower half of the blank mold of the composite blade: the first layer of prepreg is paved according to the laser projection positioning contour line on the die backing plate; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; sequentially completing the prepreg paving of all paving numbers on the lower half side of the composite material blade blank mold;
s2.3, loading the metal connecting piece into a blade root mounting groove of the die loose piece, and integrally assembling the die loose piece into a loose piece chute of the main body die;
S2.4, mounting a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the metal connecting piece is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured;
S2.5, paving and pasting the prepreg at the upper half of the blank mold of the composite blade: s2.2, sequentially finishing the paving and pasting of all prepregs on the upper half side of the blank mold of the composite material blade;
s2.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
s2.7, placing the whole main body die in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the prepreg performance, the layering thickness and the structural size of the die;
s2.8, demolding the cured product to obtain a first layer of blade blank mold;
s2.9, when N is more than 1, repeating the steps S2.1-S2.8 to sequentially finish the manufacture of the Nth layer of blade blank mould, wherein after the lower half prepreg of the Nth layer of blade blank mould is paved, the Nth-1 layer of blade blank mould is arranged in a mould backing plate of the Nth layer of blade blank mould;
Secondly, molding the product:
S2.10, polishing the surface of the integral composite material of the blank mold to be rough, and cleaning for standby;
S2.11, removing the die backing plate and completing related preparation work, wherein the method comprises the following steps: the prepreg lay-up design, engineering drawing conversion, cutting and numbering for the composite material blade product mould are completed, and a laser projection positioning data file is formed at the same time; completing the preparation of a laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
S2.12, paving and pasting prepreg at the lower half of the composite blade product mould: the first layer of prepreg is paved according to the laser projection positioning contour line on the die main body; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; sequentially completing prepreg paving of all paving numbers on the lower half side of the composite material blade product mould;
s2.13, installing the die loose piece and the blank die which are standby in the step S2.10 into a main die;
S2.14, installing a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the whole blank die is fully contacted with the laid prepreg, and the bonding performance is ensured;
S2.15, paving and pasting prepreg on the upper half of the composite material blade product mould: s2.12, sequentially finishing the paving of all the prepregs on the upper half of the composite material blade;
S2.16, laying of the temperature-resistant molding auxiliary consumable materials is completed, and sealing is completed by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
S2.17, placing the whole main body die in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the prepreg performance, the layering thickness and the structural size of the die;
s2.18, demolding the cured product to obtain a finished product mold, and finishing trimming to obtain the composite propeller blade.
The invention also provides a molding process of the autoclave for the composite material blade of the large ship propeller, which adopts the molding die for the autoclave for the composite material blade of the ship propeller to mold the composite material blade with similar structure, and comprises the following steps:
S3.1, completing related preparation work, including: preparing a die backing plate matched with the composite material blade with the similar structure, and respectively installing a blade backing plate and a blade root backing plate of the die backing plate in a blade cavity and a blade root cavity; the prepreg ply design, engineering drawing conversion, cutting and numbering for the composite material blade with the similar structure are completed, a laser projection positioning data file is formed at the same time, and the preparation of the laser projection positioning instrument is completed according to the main body mold positioning reference point and the laser projection positioning data file;
s3.2, paving and pasting prepreg at the lower half of the blade made of the composite material with the similar structure: the first layer of prepreg is paved according to the laser projection positioning contour line on the die backing plate; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; sequentially completing prepreg paving of all paving numbers of the lower half of the composite material blade with the similar structure;
S3.3, loading the metal connecting piece into a blade root mounting groove of the die loose piece, and integrally assembling the die loose piece into a loose piece chute of the main body die;
s3.4, mounting a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the metal connecting piece is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured;
S3.5, paving and pasting prepreg on the upper half of the blade made of the composite material with the similar structure: s3.2, sequentially finishing the paving and pasting of all prepregs on the upper half of the composite material blade with the similar structure;
S3.6, laying of the temperature-resistant molding auxiliary consumable materials is completed, and sealing is completed by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
S3.7, placing the material into an autoclave, heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of the layer and the structural size of the die;
And S3.8, demolding the cured product to obtain the composite material blade with the similar structure.
The invention has the beneficial effects that:
1. The invention adds the die loose piece and the die pressing plate on the basis of the main die, installs the metal connecting piece at the root of the blade through the die loose piece, applies certain pressure in the manufacturing process through the die pressing plate, and pre-presses the metal connecting piece and the prepreg to be matched in place. The die loose piece is vertically and downwards clamped by the main die guide groove in the clamping process, and the die guide groove and the bottom plane are used as references, so that the accuracy in clamping in place is ensured; the vacuum bag film is paved and adhered to cover the upper surface of the whole main body die, the die movable block and the die pressing plate, and the sealing is completed by the heat-resistant sealing adhesive tape along the upper edge of the periphery of the main body die, so that the integral tightness of the main body die can be ensured, the subsequent autoclave process molding is facilitated, and the autoclave process molding of the large-size blade can be realized.
2. The whole die is made of metal, and the main die is of an integrated structure, so that the air tightness, the high temperature resistance and the pressure resistance of the whole die are guaranteed; the bottom and the side of the main body die are hollowed and perforated, so that the die is beneficial to the overall efficient heat transfer, and the uniformity of temperature rise and temperature reduction is good, the production efficiency can be improved while the product quality is ensured, and the die is particularly suitable for autoclave forming technology and particularly suitable for forming large-size paddles.
3. The innovative design of the die backing plate is very beneficial to realizing the autoclave process, so that the requirement of the large-scale propeller composite material blade for the fractional molding can be met, the composite material blade with other similar structures can be molded, and the die cost is further reduced; the die backing plate can be designed and manufactured in a blocking mode according to the requirement, and the die manufacturing cost is further reduced. The RTM process and the mould pressing process are difficult to realize the design of the mould backing plate, and are unfavorable for the realization of the forming process, so that a plurality of sets of moulds are needed to be prepared during the fractional forming.
4. In the manufacture of large paddles, it is a matter of difficulty how the raw materials are positioned because the size of the raw materials is limited and the size, location and shape of the raw materials during the application process are constantly changing. According to the invention, the plurality of composite material blade raw material paving positioning reference points are arranged around the upper surface of the blade cavity of the main body die, and the positioning of the laser projection positioning instrument is completed by matching with the laser projection positioning data file, so that the paving positioning of raw materials can be accurately realized.
5. The mold adopts a single-piece mold structure form, is favorable for heat transfer in the process of molding the composite material blade and demolding of molded products, and particularly has obvious advantages of simple process and mold cost.
6. According to the molding process designed by the molding die, the composite material blade manufacturing process is simple to operate, and the quality (the shape value, the strength, the noise performance and the hydrodynamic performance) of the prepared composite material blade finished product meets the structural design requirement, so that the anti-corrosion effect is good; each composite blade is independently formed, thereby being beneficial to maintenance and replacement.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic view of a composite blade to be made by an autoclave forming mold of the present invention;
FIG. 2 is a schematic view of the structure of a main body mold of the autoclave molding mold of the present invention;
FIG. 3 is a schematic view of the body mold of FIG. 2 at another angle;
FIG. 4 is a schematic view of the structure of a die block of an autoclave molding die of the present invention;
FIG. 5 is a schematic view of the structure of a mold platen of an autoclave molding mold according to the present invention;
FIG. 6 is a schematic view of the structure of a die pad of the autoclave molding die of the present invention;
FIG. 7 is a schematic diagram of a mold closing process of an autoclave forming mold of the present invention;
FIG. 8 is a schematic diagram of the closing of autoclave forming mold according to the present invention;
fig. 9 is a structural cross-sectional view of a large composite blade formed in stages by an autoclave forming die of the present invention.
In the figure: 10. a main body mold; 11. blade cavity; 111. a blade cavity; 112. a blade root cavity; 12. a movable block chute; 13. a platen positioning hole; 14. paving and pasting a positioning datum point on the raw materials; 15. hollow open holes; 16. hoisting the bolt holes;
20. A die movable block; 21. blade root mounting groove; 22. blade root locating holes; 23. demoulding bolt holes;
30. A mold pressing plate; 31. round holes matched with the demoulding bolt holes; 32. bolt holes connected with the main body mould;
40. a die backing plate; 41. blade pad plate; 411. blade pad plate cavity; 42. a blade root backing plate; 43. positioning slot screw holes.
210. Composite material paddles; 211. a composite blade; 212. a composite blade root; 220. a metal connector; 230. a sandwich structure; 240. blank mold skin; 250. and (5) product mold covering.
Detailed Description
For a clearer understanding of technical features, objects and effects of the present invention, a detailed description of embodiments of the present invention will be made with reference to the accompanying drawings.
The invention provides an autoclave forming die for a composite material blade of a ship propeller, which is a single-piece die, wherein the structure of a composite material blade 210 to be manufactured is shown in fig. 1, the blade root of the blade is a metal connecting piece 220, the surface of the metal connecting piece 220 is coated with a composite material outer skin, and the composite material outer skin comprises a composite material blade 211 and a composite material blade root 212.
As shown in fig. 2 to 8, the autoclave molding die comprises a main body die 10, a die loose piece 20, a die pressing plate 30 and a die backing plate 40, wherein the main body die 10, the die loose piece 20, the die pressing plate 30 and the die backing plate 40 are made of one or more of conventional metal steel, cast iron and aluminum alloy. Referring to fig. 2, a main body mold 10 is provided with a blade cavity 11 matched with a blade type value and a movable block chute 12 matched with a mold movable block 20; wherein the blade cavity 11 comprises a blade cavity 111 and a blade root cavity 112 which are communicated with each other, and the surface roughness of the blade cavity 11 is up to or better than Ra6.4; the loose-leaf chute 12 is disposed adjacent the root cavity 112 and the mold loose-leaf 20 is inserted into the loose-leaf chute 12 through the upper opening of the loose-leaf chute 12. Referring to fig. 4, the main structure of the die block 20 is determined according to the structure of the metal connection piece 220, the die block 20 is provided with a blade root installation groove 21 matched with the metal connection piece 220, and the metal connection piece 220 is inserted into the blade root installation groove 21 from the upper end opening of the blade root installation groove 21; the blade root mounting slot 21 is open to the side of the blade cavity 11 so that the projecting end of the metal connector 220 is connected to the composite blade. The upper end of the die loose piece 20 is provided with a demoulding bolt hole 23. Referring to fig. 5, the die platen 30 is sized by the specific configuration of the die shoe 20 to cover the upper opening of the shoe runner 12 and to be securely connected to the body die 10 so that a compressive force is applied during the manufacturing process and the pre-compression forces the article to be clamped in place. A round hole 31 matched with the demoulding bolt hole is arranged on the mould pressing plate 30; the die pressing plate 30 is also provided with a bolt hole 32 connected with the main die, and the periphery of the upper surface of the movable block chute 12 of the main die 10 is provided with a corresponding pressing plate positioning hole 13 and matched with a corresponding bolt.
Referring to fig. 6, the autoclave molding die further includes a die pad 40 for molding large composite blades in separate steps or for making composite blades of similar structure. The die pad 40 comprises a blade pad 41 and a blade root pad 42, and the blade pad 41 is fixedly connected with the blade root pad 42 through a dovetail clamping groove. The bottom surface shape value of the blade pad 41 is conformal with the blade cavity 111 shape value so as to be installed in the blade cavity 111, the surface of the blade pad 41 is provided with a blade pad cavity 411, and the blade pad cavity 411 is matched with the blade structure of the composite material blade blank mold formed in a dividing mode or is matched with the blade structure of the composite material blade with a similar structure. The bottom surface shape value of the blade root backing plate 42 is shaped along with the shape value of the blade root cavity 112 so as to be installed in the blade root cavity 112, the surface of the blade root backing plate 42 is provided with a blade root backing plate cavity (not shown), and the blade root backing plate cavity is matched with the blade root structure of the composite material blade blank mold formed in a split mode or is matched with the blade root structure of a composite material blade with a similar structure. The surface roughness of the blade pad cavity 411 and the blade root pad cavity is equal to or better than Ra6.4. The periphery of the die cushion plate 40 is provided with a plurality of positioning clamping groove screw holes 43, and the die cushion plate 40 is fixed in the corresponding cavity of the main die 10 through positioning clamping groove bolts during molding. When the composite material blade needs to be molded in a divided mode, the die cushion plate 40 can be adopted to mold a blade preformed body firstly, then the die cushion plate 40 is removed, and a product (generally, a composite material blade with larger size and thickness is specified) is molded on the main die 10; a similar structure of composite blade may also be formed using die pad 40. There is no need to remanufacture the main body mold 10, saving mold costs.
Further optimizing, the main body die 10 is of an integral structure, and hollow openings are formed in all sides and the bottom of the die, so that the integral efficient heat transfer of the die is facilitated, the uniformity of temperature rise and temperature reduction is good, the quality of products is ensured, and meanwhile, the production efficiency can be improved.
Further preferably, a plurality of composite material blade raw material paving positioning reference points are arranged around the upper surface of the blade cavity 11 of the main body die 10, and the number of the positioning reference points is preferably 4 to 12.
Further optimizing, the periphery of the main body die 10 is provided with a plurality of hoisting bolt holes, so that the main body die 10 is convenient to hoist.
Further preferably, the blade root mounting groove 21 is provided with a blade root positioning hole 22 for fixing and positioning the metal connecting piece 220. The blade root positioning hole 22 penetrates through the other side of the die loose piece 20; the blade root locating holes 22 are bolt holes or pin holes.
Further optimizing, to reduce mold tooling costs, blade pad 41 may be segmented.
The molding die of the autoclave for the composite material blade of the ship propeller can be used for molding the composite material blade matched with the blade cavity 11, and the molding process comprises the following steps:
S1.1, completing related preparation work, including: (1) The prepreg lay-up design, engineering drawing conversion, cutting and numbering for the composite material blade are completed by utilizing professional CAD software, and a laser projection positioning data file is formed at the same time; (2) Completing the preparation of a laser projection positioner according to the positioning datum point of the main body mould 10 and the laser projection positioning data file; (3) Cleaning a main body die, and coating a release agent and release wax;
S1.2, paving and pasting prepreg at the lower half of the composite blade: directly paving the first prepreg layer into a blade cavity 11 of the main body die 10 according to the laser projection positioning contour line on the main body die 10; when a certain number of layering layers (1-20 layers) are finished, precompaction and bubble removal treatment are carried out in a vacuumizing mode; and then sequentially completing the prepreg paving of all paving numbers on the lower half of the composite material blade. According to the actual thickness requirement, when the thickness is thicker, the half forming times can be divided into a plurality of times.
S1.3, the metal connector 220 is installed in the blade root installation groove 21 of the die loose piece 20, and the die loose piece 20 is integrally assembled into the loose piece chute 12 of the main body die 10.
S1.4, mounting a die pressing plate 30 on the upper surface of the movable block chute 12, and further pre-pressing the metal connecting piece 220 by screwing a bolt, so that the metal connecting piece 220 is fully contacted with the laid prepreg, and the bonding performance is ensured.
S1.5, repeating the step S1.2, and finishing the paving and pasting of the prepreg on the upper half of the composite material blade.
S1.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; and then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state. The temperature-resistant molding auxiliary consumable material comprises a demolding cloth, a separation film, a blank mold upper surface conformal soft board and an air felt which are sequentially paved on the surface of a product, a vacuum bag film applied to the surface of the body mold.
S1.7, the whole main body die 10 is placed in an autoclave for heating, pressurizing and curing, and the curing system is specifically set according to the prepreg performance, the layering thickness and the die structure size. For example, the curing may be accomplished by a gradient of elevated temperature and pressure, as detailed in the following table:
S1.8, moving the cured composite material blade out of the autoclave along with the die, demoulding, and trimming to obtain the composite material blade.
S1.9, further polishing and smoothly transiting the non-mould surface of the composite material blade to finish the shape modification treatment; still further, wrap 1 to 10 layers of prepreg on the whole composite material paddle surface to accomplish the solidification shaping, improve composite material paddle's overall shape value, intensity and pleasing to the eye effect.
The molding die of the autoclave for the composite material blade of the ship propeller can be used for molding the large composite material blade in a divided mode, and the large composite material blade is firstly split into N blank molds and one product mold structurally, wherein N is more than or equal to 1. Taking a blank mold and a product mold as an example, as shown in fig. 9, a sandwich structure 230 is arranged in the middle of a blade of a large composite blade, the root of the sandwich structure 230 is assembled and connected with a metal connecting piece 220 to form an assembly, and the outer surface of the assembly is sequentially coated with a blank mold skin 240 and a product mold skin 250. The forming process of the large composite material blade comprises the following steps:
First, blank mold forming:
s2.1, completing related preparation work, including: (1) The prepreg lay-up design, engineering drawing conversion, cutting and numbering for the composite material blade blank mold are completed by utilizing professional CAD software, and a laser projection positioning data file is formed at the same time; (2) Preparing a die cushion plate 40 which is matched with a blade blank die, and respectively installing a blade cushion plate 41 and a blade root cushion plate 42 of the die cushion plate 40 in a blade cavity 111 and a blade root cavity 112; (3) Completing cleaning of the main body die 10 and the die pad 40, and coating release agent and release wax; (4) Laser projection locator preparation is accomplished based on the body mold 10 positioning reference points and the laser projection positioning data file.
S2.2, paving and pasting prepreg at the lower half of the blank mold of the composite blade: the first prepreg layer is laid according to the laser projection positioning contour line on the die cushion plate 40; when a certain number of layering layers (1-20 layers) are finished, precompaction and bubble removal treatment are carried out in a vacuumizing mode; and (5) sequentially completing the prepreg paving of all paving numbers on the lower half side of the composite material blade blank mold.
S2.3, after the metal connecting piece 220 and the sandwich structure 230 are assembled, the metal connecting piece 220 is installed in the blade root installation groove 21 of the die loose piece 20, and the die loose piece 20 is integrally assembled in the loose piece sliding groove 12 of the main body die 10.
S2.4, mounting a die pressing plate 30 on the upper surface of the movable block chute 12, and tightening the die pressing plate 30 through bolts so as to further pre-press the metal connecting piece 220, so that the metal connecting piece 220 is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured.
S2.5, paving and pasting the prepreg at the upper half of the blank mold of the composite blade: and S2.2, sequentially finishing the paving and pasting of all the prepregs on the upper half side of the blank mold of the composite material blade.
S1.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; and then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state. The temperature-resistant molding auxiliary consumable material comprises a demolding cloth, a separation film, a blank mold upper surface conformal soft board and an air felt which are sequentially paved on the surface of a product, a vacuum bag film applied to the surface of the body mold.
S2.7, the whole main body die 10 is placed in an autoclave for heating, pressurizing and curing, and the curing system is specifically set according to the prepreg performance, the layering thickness and the die structure size. For example, the curing may be accomplished by a gradient of elevated temperature and pressure, as detailed in the following table:
s2.8, demolding the cured product to obtain the blank mold.
Secondly, molding the product:
S2.10, polishing the surface of the integral composite material of the blank mould to be rough (the mesh number of the selected sand paper is more than 80 meshes), and cleaning the surface for later use.
S2.11, removing the die pad 40 and completing the associated preparation work, including: (1) The prepreg lay-up design, engineering drawing conversion, cutting and numbering for the composite material blade product mould are completed by utilizing professional CAD software, and a laser projection positioning data file is formed at the same time; (2) Finishing the cleaning of the main body die 10, and coating a release agent and release wax; (3) Laser projection locator preparation is accomplished based on the body mold 10 positioning reference points and the laser projection positioning data file.
S2.12, paving and pasting prepreg at the lower half of the composite blade product mould: the first layer of prepreg is paved according to the laser projection positioning contour line on the die main body; when a certain number of layering layers (1-20 layers) are finished, precompaction and bubble removal treatment are carried out in a vacuumizing mode; and (5) sequentially completing the prepreg paving of all paving numbers on the lower half side of the composite material blade product die.
S2.13, installing the die loose piece 20 and the blank die which are standby in the step S2.10 into the main die 10.
S2.14, installing a die pressing plate 30 on the upper surface of the movable block chute 12, and further pre-pressing the metal connecting piece 220 by screwing bolts, so that the full contact between the whole blank die and the laid prepreg is ensured, and the bonding performance is ensured.
S2.15, paving and pasting prepreg on the upper half of the composite material blade product mould: and (2) the operation is the same as that of S2.12, and all prepregs on the upper half of the composite material blade are sequentially paved and pasted.
S1.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; and then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state. The temperature-resistant molding auxiliary consumable material comprises a demolding cloth, a separation film, a blank mold upper surface conformal soft board and an air felt which are sequentially paved on the surface of a product, a vacuum bag film applied to the surface of the body mold.
S2.17, the whole main body die 10 is placed in an autoclave for heating, pressurizing and curing, and the curing system is specifically set according to the prepreg performance, the layering thickness and the die structure size. For example, the curing may be accomplished by a gradient of elevated temperature and pressure, as detailed in the following table:
s2.18, demolding the cured product to obtain a finished product mold, and finishing trimming to obtain the composite material blade.
S2.19, further, polishing, smoothing, transitional and other processing treatments on the non-mould surface of the composite material blade to finish the shape modification treatment; still further, wrap 1 to 10 layers of prepreg on the whole composite material paddle surface to accomplish the solidification shaping, improve composite material paddle's overall shape value, intensity and pleasing to the eye effect.
The molding die of the autoclave for the composite material blade of the ship propeller can also be used for molding composite material blades with similar structures, and the molding process comprises the following steps:
S3.1, completing related preparation work, including: (1) The prepreg layering design, engineering drawing conversion, cutting and numbering for the composite material blade with the similar structure are completed, and a laser projection positioning data file is formed at the same time; (2) Preparing a die backing plate 40 which is matched with the composite material blade with similar structure, and respectively installing a blade backing plate 41 and a blade root backing plate 42 of the die backing plate 40 in a blade cavity 111 and a blade root cavity 112; (3) Completing the preparation of a laser projection positioner according to the positioning datum point of the main body mould 10 and the laser projection positioning data file; (4) And (3) cleaning the main body die and the backing plate, and coating a release agent and release wax.
S3.2, paving and pasting prepreg at the lower half of the blade made of the composite material with the similar structure: the first prepreg layer is laid according to the laser projection positioning contour line on the die cushion plate 40; when a certain number of layering layers (1-20 layers) are finished, precompaction and bubble removal treatment are carried out in a vacuumizing mode; and (5) sequentially completing the prepreg paving of all paving numbers on the lower half of the composite material blade with the similar structure.
S3.3, the metal connector 220 is installed in the blade root installation groove 21 of the die loose piece 20, and the die loose piece 20 is integrally assembled in the loose piece chute 12 of the main body die 10.
And S3.4, mounting a die pressing plate 30 on the upper surface of the movable block chute 12, and fastening and connecting the die pressing plate 30 with the main die 10 to further pre-press the metal connecting piece 220, so that the metal connecting piece 220 is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured.
S3.5, paving and pasting prepreg on the upper half of the blade made of the composite material with the similar structure: and (3) operating the same as the step (S3.2) to sequentially finish the paving and pasting of all the prepregs on the upper half of the composite material blade with the similar structure.
S1.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; and then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state. The temperature-resistant molding auxiliary consumable material comprises a demolding cloth, a separation film, a blank mold upper surface conformal soft board and an air felt which are sequentially paved on the surface of a product, a vacuum bag film applied to the surface of the body mold.
S3.7, placing the main body die 10 in an autoclave for heating, pressurizing and curing, wherein the curing system is specifically set according to the prepreg performance, the layering thickness and the die structure size.
S3.8, demolding the cured product to obtain the composite material blade with the similar structure; and finishing trimming treatment to obtain the composite material blade.
S3.9, further, polishing, smoothing, transitional and other processing treatments on the non-mould surface of the composite material blade to finish the shape modification treatment; still further, wrap 1 to 10 layers of prepreg on the whole composite material paddle surface to accomplish the solidification shaping, improve composite material paddle's overall shape value, intensity and pleasing to the eye effect.
The manufacturing process of the composite material blade is simple to operate, and the quality (the model value, the strength, the noise performance and the hydrodynamic performance) of the finished product of the prepared composite material blade meets the structural design requirement, so that the anti-corrosion effect is good; each composite blade is independently formed, thereby being beneficial to maintenance and replacement.
The embodiments of the present invention have been described above with reference to the accompanying drawings, but the present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present invention and the scope of the claims, which are to be protected by the present invention.
Claims (8)
1. A molding die for an autoclave of a composite material blade of a ship propeller is characterized in that,
The autoclave forming die is a single-piece die, the blade root of the composite material blade to be manufactured is a metal connecting piece, and the surface of the metal connecting piece is coated with the composite material outer skin;
The autoclave forming die comprises a main die, a die movable block and a die pressing plate; the main body die is provided with a blade cavity matched with the blade type value and a movable block chute matched with the die movable block, the blade cavity comprises a blade cavity and a blade root cavity which are communicated with each other, the movable block chute is arranged close to the blade root cavity, and the die movable block is inserted into the movable block chute through an upper end opening of the movable block chute; the main body die is of an integral structure, and hollow open holes are formed in all sides and the bottom; the die loose piece is provided with a blade root mounting groove matched with the metal connecting piece, and one side of the blade root mounting groove, which faces the blade cavity, is provided with an opening so as to connect the metal connecting piece with the composite material blade; the die pressing plate is used for covering the upper end opening of the movable block chute and is fixedly connected with the main die, so that pre-pressing force is applied in the manufacturing process to promote the product to be clamped in place;
The forming die further comprises a die backing plate, wherein the die backing plate comprises a blade backing plate and a blade root backing plate; the bottom surface shape value of the blade pad is conformal with the blade cavity shape value so as to be conveniently installed in the blade cavity, the surface of the blade pad is provided with the blade pad cavity, and the blade pad cavity is matched with the blade structure of the composite material blade blank mold formed in a dividing mode or is matched with the blade structure of the composite material blade with a similar structure; the bottom surface type value of the blade root backing plate and the blade root cavity type value follow-up shape so as to be installed in the blade root cavity, the surface of the blade root backing plate is provided with the blade root backing plate cavity, and the blade root backing plate cavity is matched with the blade root structure of the composite material blade blank mold formed in a dividing mode or is matched with the blade root structure of the composite material blade with a similar structure.
2. The molding die for the autoclave of the composite material blade of the ship propeller of claim 1, wherein the blade root pad and the blade pad are fixedly connected in a detachable manner.
3. The molding die for the autoclave of the composite propeller blade of the ship according to claim 1, wherein a plurality of positioning clamping groove bolts are arranged on the periphery of the die backing plate, and the die backing plate is fixed in the corresponding cavity of the main die through the positioning clamping groove bolts.
4. The molding die for the composite material blade autoclave of the ship propeller of claim 1, wherein a plurality of composite material blade raw material paving positioning datum points are arranged around the upper surface of the blade cavity of the main body die.
5. The molding die for the autoclave of the composite material blade of the ship propeller of claim 1, wherein a blade root positioning hole is arranged in the blade root mounting groove.
6. A process for molding a composite material blade autoclave of a ship propeller, which is characterized in that a composite material blade matched with the blade cavity is molded by adopting the molding die of the composite material blade autoclave of the ship propeller in claim 1, and the process comprises the following steps:
S1.1, completing related preparation work, including: the prepreg layering design, engineering drawing conversion, cutting and numbering for the composite material blade are completed, and a laser projection positioning data file is formed at the same time; completing the preparation of a laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
S1.2, paving and pasting prepreg at the lower half of the composite blade: directly paving the first layer of prepreg in a blade cavity of the main body die according to a laser projection positioning contour line on the main body die; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; then sequentially completing the prepreg paving of all paving numbers on the lower half of the composite material blade;
s1.3, loading the metal connecting piece into a blade root mounting groove of a die loose piece, and integrally assembling the die loose piece into a loose piece chute of a main body die;
S1.4, mounting a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the metal connecting piece is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured;
S1.5, repeating the step S1.2 to finish the paving of the prepreg on the upper half of the composite material blade;
S1.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
S1.7, placing the whole body die which is subjected to prepreg paving and integral sealing in an autoclave, heating, pressurizing and curing, wherein a curing system is specifically set according to prepreg performance, layering thickness and die structure size;
S1.8, moving the cured composite material blade out of the autoclave along with the die, demoulding, and trimming to obtain the composite material blade.
7. The molding process of the autoclave for the large-scale ship propeller composite material blade is characterized in that the molding die of the autoclave for the ship propeller composite material blade is adopted to mold the large-scale composite material blade in a divided mode, the large-scale composite material blade is firstly split into N blank molds and one product mold from the structure, and N is more than or equal to 1; the molding process comprises the following steps:
Step one, blank mold forming:
S2.1, completing related preparation work, including: preparing a die backing plate matched with the first layer of blade blank die, and respectively installing a blade backing plate and a blade root backing plate of the die backing plate in a blade cavity and a blade root cavity; the prepreg layer design, engineering drawing conversion, cutting and numbering for the composite material blade blank mold are completed, a laser projection positioning data file is formed at the same time, and the preparation of a laser projection positioning instrument is completed according to the main body mold positioning reference point and the laser projection positioning data file;
S2.2, paving and pasting prepreg at the lower half of the blank mold of the composite blade: the first layer of prepreg is paved according to the laser projection positioning contour line on the die backing plate; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; sequentially completing the prepreg paving of all paving numbers on the lower half side of the composite material blade blank mold;
s2.3, loading the metal connecting piece into a blade root mounting groove of the die loose piece, and integrally assembling the die loose piece into a loose piece chute of the main body die;
S2.4, mounting a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the metal connecting piece is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured;
S2.5, paving and pasting the prepreg at the upper half of the blank mold of the composite blade: s2.2, sequentially finishing the paving and pasting of all prepregs on the upper half side of the blank mold of the composite material blade;
s2.6, finishing laying of the temperature-resistant molding auxiliary consumable materials, and finishing sealing by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
s2.7, placing the whole main body die in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the prepreg performance, the layering thickness and the structural size of the die;
s2.8, demolding the cured product to obtain a first layer of blade blank mold;
s2.9, when N is more than 1, repeating the steps S2.1-S2.8 to sequentially finish the manufacture of the Nth layer of blade blank mould, wherein after the lower half prepreg of the Nth layer of blade blank mould is paved, the Nth-1 layer of blade blank mould is arranged in a mould backing plate of the Nth layer of blade blank mould;
Secondly, molding the product:
S2.10, polishing the surface of the integral composite material of the blank mold to be rough, and cleaning for standby;
S2.11, removing the die backing plate and completing related preparation work, wherein the method comprises the following steps: the prepreg lay-up design, engineering drawing conversion, cutting and numbering for the composite material blade product mould are completed, and a laser projection positioning data file is formed at the same time; completing the preparation of a laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
S2.12, paving and pasting prepreg at the lower half of the composite blade product mould: the first layer of prepreg is paved according to the laser projection positioning contour line on the die main body; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; sequentially completing prepreg paving of all paving numbers on the lower half side of the composite material blade product mould;
s2.13, installing the die loose piece and the blank die which are standby in the step S2.10 into a main die;
S2.14, installing a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the whole blank die is fully contacted with the laid prepreg, and the bonding performance is ensured;
S2.15, paving and pasting prepreg on the upper half of the composite material blade product mould: s2.12, sequentially finishing the paving of all the prepregs on the upper half of the composite material blade;
S2.16, laying of the temperature-resistant molding auxiliary consumable materials is completed, and sealing is completed by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
S2.17, placing the whole main body die in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the prepreg performance, the layering thickness and the structural size of the die;
s2.18, demolding the cured product to obtain a finished product mold, and finishing trimming to obtain the composite propeller blade.
8. The molding process of the autoclave for the large-scale ship propeller composite material blade is characterized in that the molding die for the autoclave for the ship propeller composite material blade is adopted to mold the composite material blade with similar structure, and the molding process comprises the following steps:
S3.1, completing related preparation work, including: preparing a die backing plate matched with the composite material blade with the similar structure, and respectively installing a blade backing plate and a blade root backing plate of the die backing plate in a blade cavity and a blade root cavity; the prepreg ply design, engineering drawing conversion, cutting and numbering for the composite material blade with the similar structure are completed, a laser projection positioning data file is formed at the same time, and the preparation of the laser projection positioning instrument is completed according to the main body mold positioning reference point and the laser projection positioning data file;
s3.2, paving and pasting prepreg at the lower half of the blade made of the composite material with the similar structure: the first layer of prepreg is paved according to the laser projection positioning contour line on the die backing plate; when a certain number of layering layers are completed, precompaction and bubble removal treatment are carried out in a vacuumizing mode; sequentially completing prepreg paving of all paving numbers of the lower half of the composite material blade with the similar structure;
S3.3, loading the metal connecting piece into a blade root mounting groove of the die loose piece, and integrally assembling the die loose piece into a loose piece chute of the main body die;
s3.4, mounting a die pressing plate on the upper surface of the movable block chute, and fastening and connecting the die pressing plate with a main die to further pre-press the metal connecting piece, so that the metal connecting piece is ensured to be fully contacted with the laid prepreg, and the bonding performance is ensured;
S3.5, paving and pasting prepreg on the upper half of the blade made of the composite material with the similar structure: s3.2, sequentially finishing the paving and pasting of all prepregs on the upper half of the composite material blade with the similar structure;
S3.6, laying of the temperature-resistant molding auxiliary consumable materials is completed, and sealing is completed by using a temperature-resistant sealing adhesive tape; then carrying out vacuumizing leak detection to ensure that the main body die is in a sealing state;
S3.7, placing the material into an autoclave, heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of the layer and the structural size of the die;
And S3.8, demolding the cured product to obtain the composite material blade with the similar structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210103719.2A CN114559680B (en) | 2022-01-27 | 2022-01-27 | Forming die and forming method for ship propeller composite material blade autoclave |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210103719.2A CN114559680B (en) | 2022-01-27 | 2022-01-27 | Forming die and forming method for ship propeller composite material blade autoclave |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114559680A CN114559680A (en) | 2022-05-31 |
| CN114559680B true CN114559680B (en) | 2024-08-13 |
Family
ID=81713708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210103719.2A Active CN114559680B (en) | 2022-01-27 | 2022-01-27 | Forming die and forming method for ship propeller composite material blade autoclave |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114559680B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115351950B (en) * | 2022-10-21 | 2023-02-17 | 北京玻钢院复合材料有限公司 | Mold for preparing composite material fan blade and preparation method of composite material fan blade |
| CN115847868B (en) * | 2023-02-27 | 2023-05-09 | 江苏新扬新材料股份有限公司 | Manufacturing method of carbon fiber composite low-temperature blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB871066A (en) * | 1957-07-20 | 1961-06-21 | Vasiljevic C | Improvements in or relating to a method for the production of impeller and like blades, and a blade produced in accordance with this method |
| CN102166824A (en) * | 2010-12-29 | 2011-08-31 | 江西昌河航空工业有限公司 | Method for positioning composite material metal insert |
| CN109228397A (en) * | 2018-08-03 | 2019-01-18 | 武汉源海博创科技有限公司 | A kind of Composite propulsor molding die and products thereof |
| CN216941895U (en) * | 2022-01-27 | 2022-07-12 | 武汉海威船舶与海洋工程科技有限公司 | Autoclave forming die for composite propeller blade of ship |
Family Cites Families (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4902458A (en) * | 1987-05-12 | 1990-02-20 | Trimble Brent J | Method of molding composite bicycle frames |
| CN101501132A (en) * | 2006-06-30 | 2009-08-05 | 东丽株式会社 | Epoxy resin composition, prepreg, and fiber-reinforced composite material |
| CN101704302B (en) * | 2009-11-17 | 2011-09-14 | 哈尔滨工业大学 | Integrally forming mould of composite propeller and manufacture method thereof |
| DK2524134T3 (en) * | 2010-01-14 | 2014-08-11 | Neptco Inc | Rotor blade components for a wind turbine and methods for making them |
| FR3050957A1 (en) * | 2016-03-04 | 2017-11-10 | Inst De Rech Tech Jules Verne | METHOD AND DEVICE FOR MANUFACTURING A HOLLOW PIECE OF COMPOSITE MATERIAL AND PROPELLER BLADE OBTAINED BY SUCH A METHOD |
| CN205835753U (en) * | 2016-06-28 | 2016-12-28 | 北京航天新风机械设备有限责任公司 | A kind of change size cavity composite element compression molding die |
| CN106346800B (en) * | 2016-09-30 | 2019-05-10 | 咸宁海威复合材料制品有限公司 | A kind of preparation method of propeller blade |
| CN106965456A (en) * | 2016-11-11 | 2017-07-21 | 武汉海威船舶与海洋工程科技有限公司 | A kind of leafy composite propeller forming method |
| CN107599443B (en) * | 2017-09-05 | 2019-10-11 | 中国船舶重工集团公司第七二五研究所 | A kind of continuous fiber reinforced composite materials propeller Lay up design and preparation method |
| KR102084764B1 (en) * | 2017-10-20 | 2020-04-23 | 코리아터빈(주) | Manufacturng for propeller of ship using composite materials |
| CN109249627B (en) * | 2018-08-17 | 2020-07-10 | 武汉源海博创科技有限公司 | Compression molding process for carbon fiber composite propeller |
| WO2020083472A1 (en) * | 2018-10-23 | 2020-04-30 | Wärtsilä Netherlands B.V. | A method of manufacturing a propeller blade assembly |
| EP3647033A1 (en) * | 2018-10-31 | 2020-05-06 | The Boeing Company | Composite structure and method for barely visible impact damage detection |
| CN110439630B (en) * | 2019-08-12 | 2022-07-29 | 航天材料及工艺研究所 | Variable-thickness composite stator blade and forming method thereof |
| CN110789155A (en) * | 2019-11-08 | 2020-02-14 | 江苏科技大学 | Automatic forming equipment and laying process method for carbon fibers of offshore wind power blade |
| CN211442519U (en) * | 2019-11-13 | 2020-09-08 | 合肥工业大学 | Formula car hollow wing piece |
| CN110815859B (en) * | 2019-11-29 | 2022-03-29 | 株洲时代新材料科技股份有限公司 | Design and manufacturing method of composite material blade and composite material blade |
| CN212889040U (en) * | 2020-07-17 | 2021-04-06 | 东莞皓宇智能复合材料有限公司 | Blade forming die of split type composite material propeller |
| CN212888465U (en) * | 2020-07-17 | 2021-04-06 | 东莞皓宇智能复合材料有限公司 | Blade preforming mould of split type combined material screw |
| CN112249285B (en) * | 2020-09-15 | 2022-09-06 | 江苏恒神股份有限公司 | Propeller and forming method |
| CN112277343A (en) * | 2020-09-30 | 2021-01-29 | 株洲时代新材料科技股份有限公司 | Composite material blade edge covering method and structure |
| CN112519996A (en) * | 2020-12-10 | 2021-03-19 | 武汉理工大学 | Composite material propeller for underwater dynamic strain measurement and preparation method thereof |
| CN215152021U (en) * | 2021-07-19 | 2021-12-14 | 威海光威复合材料股份有限公司 | Composite material propeller blade forming die |
-
2022
- 2022-01-27 CN CN202210103719.2A patent/CN114559680B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB871066A (en) * | 1957-07-20 | 1961-06-21 | Vasiljevic C | Improvements in or relating to a method for the production of impeller and like blades, and a blade produced in accordance with this method |
| CN102166824A (en) * | 2010-12-29 | 2011-08-31 | 江西昌河航空工业有限公司 | Method for positioning composite material metal insert |
| CN109228397A (en) * | 2018-08-03 | 2019-01-18 | 武汉源海博创科技有限公司 | A kind of Composite propulsor molding die and products thereof |
| CN216941895U (en) * | 2022-01-27 | 2022-07-12 | 武汉海威船舶与海洋工程科技有限公司 | Autoclave forming die for composite propeller blade of ship |
Non-Patent Citations (1)
| Title |
|---|
| 大厚度船用复合材料螺旋桨桨叶设计与成型工艺;周鑫;《船舶工程》;20220930;第44卷(第9期);24-28 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114559680A (en) | 2022-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114559680B (en) | Forming die and forming method for ship propeller composite material blade autoclave | |
| CN110103487B (en) | Process method for forming composite material part with Z-shaped section | |
| CN113681937B (en) | Composite material cap-shaped stringer wallboard structure and preparation method | |
| CA2721318A1 (en) | Method and shaping device for producing a composite fibre component for air and space travel | |
| CN113771388B (en) | Forming method of special-shaped composite material reinforced grid rib and special-shaped skin cabin section thereof | |
| CN216941895U (en) | Autoclave forming die for composite propeller blade of ship | |
| CN111716761A (en) | Special-shaped curved surface aramid fiber paper honeycomb simple pre-setting die and manufacturing method thereof | |
| CN111085661A (en) | Investment mold and method for manufacturing blade with complex cavity | |
| CN106985413A (en) | A kind of forming frock for foam core filled composite material structure winglet | |
| CN117774375A (en) | Composite material ring frame and forming method and device thereof | |
| CN107901448B (en) | Large-diameter composite skirt compression curing method | |
| CN110815853A (en) | Forming method and application of air bag die for forming composite J-shaped beam | |
| CN209775592U (en) | Overall forming tool for composite fuselage skin | |
| CN110303693A (en) | A kind of compression-moulding methods of small-sized aerofoil Composite Sandwich part | |
| CN112721238B (en) | Preparation method of variable-thickness composite material workpiece | |
| CN115596748A (en) | One-time glue joint curing molding method for mosaic structure and shell assembly | |
| CN212331566U (en) | Be used for hollow bow-shaped undercarriage solidification moulding frock of unmanned aerial vehicle combined material | |
| CN212350289U (en) | Precoated sand splicing model suitable for large parts | |
| CN113665037A (en) | Carbon fiber composite material magazine forming tool for aviation, magazine and forming method of magazine | |
| CN110654039B (en) | Manufacturing method of non-equal-diameter closed square tubular carbon fiber beam of unmanned aerial vehicle | |
| CN215849776U (en) | Fiber reinforced composite material forming die for automobile body covering part product | |
| CN111716601A (en) | Preparation method of large-scale main load-bearing composite material structure and forming die used in preparation method | |
| CN111604469A (en) | Precoated sand splicing model suitable for large parts | |
| CN2736099Y (en) | Die for drawing, milling and cutting | |
| CN220534991U (en) | Pre-curing forming tool for foam reinforcing rib of rotor blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |