CN114559680A - Autoclave forming die and forming method for ship propeller composite material blade - Google Patents
Autoclave forming die and forming method for ship propeller composite material blade Download PDFInfo
- Publication number
- CN114559680A CN114559680A CN202210103719.2A CN202210103719A CN114559680A CN 114559680 A CN114559680 A CN 114559680A CN 202210103719 A CN202210103719 A CN 202210103719A CN 114559680 A CN114559680 A CN 114559680A
- Authority
- CN
- China
- Prior art keywords
- blade
- composite material
- die
- mold
- prepreg
- 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.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 185
- 238000000034 method Methods 0.000 title claims abstract description 45
- 229910052751 metal Inorganic materials 0.000 claims abstract description 54
- 239000002184 metal Substances 0.000 claims abstract description 54
- 238000000465 moulding Methods 0.000 claims abstract description 52
- 230000008569 process Effects 0.000 claims abstract description 39
- 238000009434 installation Methods 0.000 claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 claims abstract description 17
- 238000007723 die pressing method Methods 0.000 claims abstract description 8
- 238000003825 pressing Methods 0.000 claims description 33
- 238000007789 sealing Methods 0.000 claims description 31
- 238000002360 preparation method Methods 0.000 claims description 25
- 238000013461 design Methods 0.000 claims description 18
- 238000005086 pumping Methods 0.000 claims description 18
- 238000006243 chemical reaction Methods 0.000 claims description 12
- 238000005056 compaction Methods 0.000 claims description 12
- 238000005520 cutting process Methods 0.000 claims description 12
- 238000010438 heat treatment Methods 0.000 claims description 10
- 239000002994 raw material Substances 0.000 claims description 9
- 238000001514 detection method Methods 0.000 claims description 8
- 238000004140 cleaning Methods 0.000 claims description 7
- 238000009966 trimming Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 238000005498 polishing Methods 0.000 claims description 6
- 101100134058 Caenorhabditis elegans nth-1 gene Proteins 0.000 claims description 2
- 230000003044 adaptive effect Effects 0.000 claims description 2
- 208000028659 discharge Diseases 0.000 claims 2
- 230000000694 effects Effects 0.000 description 8
- 239000004744 fabric Substances 0.000 description 8
- 239000011248 coating agent Substances 0.000 description 7
- 238000000576 coating method Methods 0.000 description 7
- 238000012546 transfer Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 4
- 239000003795 chemical substances by application Substances 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 238000009745 resin transfer moulding Methods 0.000 description 4
- 238000012545 processing Methods 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000012423 maintenance 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
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
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
Abstract
The invention relates to a ship propeller composite material blade autoclave forming die which comprises a main body die, a die movable block and a die pressing plate, wherein the die movable block is arranged on the main body die; the main body mould is provided with a blade cavity matched with a blade type value and a movable block sliding groove matched with a mould movable block, the blade cavity comprises a blade cavity and a blade root cavity, the movable block sliding groove is arranged close to the blade root cavity, and the mould movable block is inserted into the movable block sliding groove through an upper end opening of the movable block sliding groove; the mould loose piece is provided with a blade root installation groove matched with the metal connecting piece, and one side of the mould loose piece facing to the blade cavity is provided with an opening; the die pressing plate covers an opening at the upper end of the loose piece sliding chute, is fixedly connected with the main die and is used for applying pre-tightening pressure to enable a product to be closed in place; the requirement of forming large-scale blades in multiple times can be met by additionally arranging the die base plate, and other blades with similar structures can be formed. The invention can realize the autoclave molding process of the large propeller composite material blade, ensure high yield, improve production efficiency and reduce mold cost.
Description
Technical Field
The invention relates to the technical field of ship propellers, in particular to a ship propeller composite material blade autoclave forming die and a forming method.
Background
At present, domestic conventional ship propellers are basically made of metal. With the higher requirements of the 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 an extremely complex structure shape and has high quality and size requirements. Such as very high curvature of the blade, high requirement and different forms of connection of the blade root, large thickness of the blade root, very thin blade tip and easy deformation, etc. 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 mold is expected to be heated up quickly to promote the solidification of products, cooled down quickly and demolded, so that the whole production efficiency is improved, and the mold cost can be reduced. Therefore, the mold is very important as an important tool for producing the composite material blade.
For conventional composite blades, alternative manufacturing processes include RTM processes, mold pressing processes and autoclave processes. The RTM process and the mould pressing process both need a double-mould die, the cost of the die is high, when the large-size complex composite material paddle is formed, the size and the thickness of the double-mould die of the mould pressing process are large, the heat transfer efficiency is low, complex heat transfer pipelines need to be arranged in the die, the technical difficulty is very high, and the cost control is not facilitated; although the autoclave process only needs a single mold, the molding of the large-size complex composite material blade also has great technical difficulty and high process cost.
In addition, the formation of composite articles is often somewhat 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 are not beneficial to cost control because multiple sets of moulds are generally required to be prepared for the fractional molding of large-scale products.
Chinese patent CN212888465U discloses a blade preforming mold of a split type composite propeller, which comprises a preforming main body mold, wherein the preforming main body mold comprises a base, a spiral groove is formed in the base, and a sliding groove is formed in one side, located on the spiral groove, of the base; 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 recessed part and the spiral groove are enclosed to form an accommodating cavity matched with the outer contour of the paddle. In the pre-forming process, the material sheets are firstly made into the designed specification and size and are sequentially arranged according to the attaching sequence; and moving the sliding block away from the sliding groove, paving the material sheets in the spiral groove of the preforming mold, paving the material sheets in the concave part of the sliding block, then inserting the sliding block into the sliding groove to be butted with the spiral groove, and paving the material sheets in the spiral concave part to form the blade preform. The mold design has the following disadvantages: (1) the open type transverse moving die loose piece design is difficult to ensure the air tightness required by the autoclave forming process and is only suitable for the mould pressing process; (2) the mould is only suitable for manufacturing the blade with the blade root formed by prepreg, and is not suitable for the blade with the blade root as a metal connecting piece; (3) the blade root of the large-scale complex structure composite material blade is very thick at the corner position, the whole blade is difficult to complete at one time, the blade root is completed at one time, and meanwhile, compared with a patent mold, the large-scale complex structure composite material blade is only suitable for forming a small-scale blade in combination with the patent CN 111873449A; (4) the mold can not meet the requirement of fractional molding of the large-scale propeller blade.
Disclosure of Invention
The invention aims to solve the technical problem of providing a mould and a method for molding the autoclave of the composite propeller blade of the ship, aiming at the defects of the prior art.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a ship propeller composite material blade autoclave forming die is a single-piece die, the blade root of a composite material blade to be manufactured is a metal connecting piece, and the surface of the metal connecting piece is coated with a composite material outer skin;
the autoclave forming die comprises a main die, a die loose piece and a die pressing plate; the main body mould is provided with a blade cavity matched with a blade type value and a movable block sliding groove matched with the mould movable block, the blade cavity comprises a blade cavity and a blade root cavity which are communicated with each other, the movable block sliding groove is arranged close to the blade root cavity, and the mould movable block is inserted into the movable block sliding groove through an upper end opening of the movable block sliding groove; the mould loose piece is provided with a blade root installation groove matched with the metal connecting piece, and one side of the blade root installation groove, facing to the blade cavity, is provided with an opening so that the metal connecting piece can be conveniently connected with the composite material blade; the die pressing plate is used for covering the upper end opening of the loose piece sliding groove and is fixedly connected with the main body die, so that pre-tightening pressure is applied to enable a product to be closed in place in the manufacturing process.
In the above scheme, the forming die further comprises a die backing plate, and the die backing plate comprises a blade backing plate and a blade root backing plate; the bottom surface shape value of the blade backing plate follows the shape value of the blade cavity so as to be conveniently arranged in the blade cavity, the surface of the blade backing plate is provided with a blade backing plate cavity, and the blade backing plate cavity is matched with the blade structure of a composite material blade blank mold formed in a grading way or matched with the blade structure of a composite material blade with a similar structure; the bottom surface model value of the blade root base plate follows the shape of the blade root cavity model value so as to be conveniently installed in the blade root cavity, the surface of the blade root base plate is provided with the blade root base plate cavity, and the blade root base plate cavity is matched with the blade root structure of a composite material blade blank mold formed in a grading way or matched with the blade root structure of a composite material blade with a similar structure.
In the above scheme, the blade root base plate and the blade base plate are fixedly connected in a detachable mode.
In the scheme, the periphery of the die base plate is provided with a plurality of positioning clamping groove bolts, and the die base plate is fixed in the corresponding cavity of the main body die through the positioning clamping groove bolts.
In the scheme, a plurality of composite material blade raw material paving and 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-out holes are formed in all the side faces and the bottom.
In the above scheme, the blade root mounting groove is internally provided with a blade root positioning hole.
The invention also provides a process for molding the autoclave of the composite material blade of the ship propeller, which adopts the autoclave molding die for molding the composite material blade of the ship propeller, and the autoclave molding die is matched with the blade cavity, and comprises the following steps:
s1.1, completing related preparation work, including: finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for the composite material blade, and simultaneously forming a laser projection positioning data file; completing the preparation of the laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
s1.2, laying and sticking prepreg on the lower half side of the composite material blade: directly paving a first layer of prepreg in a blade cavity of a main body mould according to a laser projection positioning profile on the main body mould; when a certain number of layers of the layers are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; then sequentially finishing the laying of all the layers of the prepreg with the serial numbers on the lower half of the composite material blade;
S1.3, installing a metal connecting piece into a blade root installation groove of a mold loose piece, and integrally assembling the mold loose piece into a loose piece sliding groove of a main body mold;
s1.4, installing a mold pressing plate on the upper surface of the loose piece chute, and fixedly connecting the mold pressing plate with a main body mold so as to further pre-press a metal connecting piece, ensure that the metal connecting piece is fully contacted with the paved prepreg and ensure the bonding performance;
s1.5, repeating the step S1.2 to finish the laying and the sticking of the upper lateral prepreg of the composite material blade;
s1.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then vacuumizing and detecting leakage to ensure that the main body mould is in a sealed state;
s1.7, placing the whole main body mould which finishes the laying and the integral sealing of the prepreg in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of a laid layer and the structural size of the mould;
and S1.8, moving the cured composite material blade out of the autoclave along with the mold, demolding, and finishing trimming to obtain the composite material blade.
The invention also provides a process for molding the autoclave of the composite material blade of the large ship propeller, which comprises the steps of molding the large composite material blade by the autoclave molding die of the composite material blade of the large ship propeller in batches, splitting the large composite material blade into N blank dies and one product die 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 base plate matched with the first layer of blade blank die, and respectively installing a blade base plate and a blade root base plate of the die base plate in a blade cavity and a blade root cavity; finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for a composite material blade blank mold, simultaneously forming a laser projection positioning data file, and finishing preparation of a laser projection positioning instrument according to a main body mold positioning datum point and the laser projection positioning data file;
s2.2, paving and sticking the lower half prepreg of the composite blade blank mold: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the die backing plate; when a certain number of layers of the layers are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; sequentially finishing the laying of all layers of the prepreg with the serial numbers on the lower half of the composite material blade blank mold;
s2.3, installing the metal connecting piece into a blade root installation groove of the die loose piece, and integrally assembling the die loose piece into a loose piece sliding groove of the main body die;
s2.4, installing a mold pressing plate on the upper surface of the loose piece sliding chute, and fixedly connecting the mold pressing plate with the main body mold so as to further pre-press the metal connecting piece, ensure that the metal connecting piece is fully contacted with the paved prepreg and ensure the bonding performance;
S2.5, paving and sticking prepreg on the upper half side of the composite blade blank mold: the operation is the same as S2.2, and all prepreg paving and sticking on the upper half side of the composite material blade blank mold are completed in sequence;
s2.6, paving the temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then carrying out vacuum pumping leak detection to ensure that the main body mould is in a sealed state;
s2.7, placing the whole main body mold in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mold;
s2.8, demolding the cured product to obtain a first layer of blade blank mold;
s2.9, when N is larger than 1, repeating the steps S2.1-S2.8 to sequentially complete the manufacture of the blade blank mold of the Nth layer, wherein after the prepreg of the lower half side of the blade blank mold of the Nth layer is paved, the blade blank mold of the Nth-1 layer is installed in a mold base plate of the blade blank mold of the Nth layer;
step two, product mold forming:
s2.10, polishing the surface of the blank mold integral composite material to be rough, and cleaning for later use;
s2.11, removing the die base plate and completing related preparation work, wherein the method comprises the following steps: finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for a composite material blade product mold, and simultaneously forming a laser projection positioning data file; completing the preparation of the laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
S2.12, paving and sticking the lower half prepreg of the composite material blade product mould: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the mould main body; when a certain number of layers of the layers are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; sequentially finishing the laying of all the layers of the prepreg with the serial numbers on the lower half of the composite material blade product mold;
s2.13, installing the spare die loose block and blank die in the step S2.10 into a main body die;
s2.14, installing a mold pressing plate on the upper surface of the loose piece chute, and fixedly connecting the mold pressing plate with the main body mold so as to further pre-press the metal connecting piece, so that the whole blank mold is ensured to be 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: the operation is the same as S2.12, and all prepreg paving and sticking on the upper half side of the composite material blade are sequentially completed;
s2.16, paving the temperature-resistant forming auxiliary consumable material, and sealing by using a temperature-resistant sealing rubber strip; then carrying out vacuum pumping leak detection to ensure that the main body mould is in a sealed state;
s2.17, placing the whole main body mould in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mould;
And S2.18, demolding the cured product to obtain a finished product mold, and finishing trimming treatment to obtain the composite material propeller blade.
The invention also provides a process for molding the autoclave of the composite material blade of the large ship propeller, which adopts the autoclave molding die for molding the composite material blade of the ship propeller with a similar structure, and comprises the following steps:
s3.1, completing related preparation work, including: preparing a die base plate adaptive to the composite material blade with the similar structure, and respectively installing a blade base plate and a blade root base plate of the die base plate in a blade cavity and a blade root cavity; finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for composite material blades with similar structures, simultaneously forming a laser projection positioning data file, and finishing preparation of a laser projection positioning instrument according to a main body die positioning datum point and the laser projection positioning data file;
s3.2, laying and sticking prepreg on the lower half of the composite material blade with the similar structure: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the die backing plate; when a certain number of layers of the layers are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; sequentially finishing the laying and pasting of all the layers of the lower half of the composite material blade with the similar structure;
S3.3, installing the metal connecting piece into a blade root installation groove of the movable block of the die, and integrally assembling the movable block of the die into a movable block sliding groove of the main body die;
s3.4, installing a mold pressing plate on the upper surface of the loose piece chute, and fixedly connecting the mold pressing plate with the main body mold so as to further pre-press the metal connecting piece, ensure that the metal connecting piece is fully contacted with the paved prepreg and ensure the bonding performance;
s3.5, paving and pasting prepreg on upper half sides of composite material blades with similar structures: the operation is the same as S3.2, and all prepreg paving and sticking on the upper half side of the composite material blade with the similar structure are sequentially completed;
s3.6, paving the temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then carrying out vacuum pumping leak detection to ensure that the main body mould is in a sealed state;
s3.7, placing the prepreg in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of a laying layer and the structural size of a mould;
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 mould loose piece and the mould pressing plate on the basis of the main mould, installs the metal connecting piece at the root of the blade through the mould loose piece, and applies a certain pressure in the manufacturing process through the mould pressing plate, and prepressing promotes the metal connecting piece and the prepreg to be matched in place. In the mold closing process, the mold loose piece is vertically closed downwards by the main body mold guide groove, and the accuracy of in-place mold closing is ensured by taking the mold guide groove and the bottom plane as references; the vacuum bag film is laid and pasted on the upper surface of the whole main body die, the die loose piece and the die pressing plate, and sealing is completed by using a temperature-resistant sealing rubber strip along the upper edge of the periphery of the main body die, so that the integral sealing performance of the main body die can be ensured, the subsequent autoclave process forming is facilitated, and the autoclave process forming of large-size blades can be realized.
2. The whole die is made of metal materials, and the main body die is of an integrated structure, so that the airtightness of the main body die, and the high-temperature resistance and pressure resistance of the whole die are guaranteed; the bottom and the side of the main body mold are both provided with hollowed-out holes, so that the integral efficient heat transfer of the mold is facilitated, the heating and cooling uniformity is good, the product quality is ensured, the production efficiency can be improved, and the main body mold is particularly suitable for autoclave molding technology and also particularly suitable for large-size paddle molding.
3. The innovative design of the die backing plate is very beneficial to realizing the autoclave process, so that the requirement of molding the composite material blade of the large propeller by times can be met, other composite material blades with similar structures can be molded, and the die cost is further reduced; the die base plate can be designed and manufactured in blocks according to requirements, and the manufacturing cost of the die is further reduced. The RTM process and the mold pressing process are difficult to realize the design of the mold pad, and are not favorable for the realization of the molding process, so that a plurality of sets of molds need to be prepared during the molding process.
4. In the manufacturing of large-scale paddle, because the size of raw materials is limited, and the size, position and shape of the raw materials in the paving process are constantly changed, how to position the raw materials is a great difficulty. According to the invention, the plurality of composite material paddle raw material paving and positioning datum points are arranged around the upper surface of the paddle 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 and positioning of the raw materials can be accurately realized.
5. The mould adopts a single-piece mould structure form, is beneficial to heat transfer in the forming process of the composite material blade and demoulding of a formed product, particularly for forming the composite material blade of the propeller of a large ship, and has particularly obvious advantages of process simplicity and mould cost.
6. According to the forming process designed by the forming die, the manufacturing process of the composite material blade is simple to operate, 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, and the anti-corrosion effect is good; each composite material blade is independently formed, and maintenance and replacement are facilitated.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic structural view of a composite blade to be manufactured by the autoclave molding die of the present invention;
FIG. 2 is a schematic structural view of a main body mold of the autoclave molding mold according to the present invention;
FIG. 3 is a schematic view of another angle configuration of the body mold of FIG. 2;
FIG. 4 is a schematic structural view of a mold loose piece of the autoclave molding mold of the present invention;
FIG. 5 is a schematic view of the construction of the mold platen of the autoclave molding mold of the present invention;
FIG. 6 is a schematic view of the construction of the die pad of the autoclave molding die of the present invention;
FIG. 7 is a schematic view of the mold closing process of the autoclave molding mold according to the present invention;
FIG. 8 is a schematic view of the closing of the autoclave molding die of the present invention;
fig. 9 is a structural sectional view of a large composite blade molded in several stages by the autoclave molding die of the present invention.
In the figure: 10. a main body mold; 11. a blade cavity; 111. a blade cavity; 112. a blade root cavity; 12. a loose piece chute; 13. a press plate positioning hole; 14. paving and positioning datum points on the raw materials; 15. hollowing out and opening holes; 16. hoisting the bolt holes;
20. a mould loose piece; 21. a blade root mounting groove; 22. a blade root positioning hole; 23. demolding the bolt hole;
30. pressing a mold plate; 31. a circular hole matched with the demoulding bolt hole; 32. a bolt hole connected with the main body die;
40. a die backing plate; 41. a blade backing plate; 411. a blade backing plate cavity; 42. a blade root backing plate; 43. and positioning clamping groove screw holes.
210. A composite blade; 211. a composite blade; 212. a composite blade root; 220. a metal connecting member; 230. a sandwich structure; 240. covering the blank mold; 250. and (5) product mold covering.
Detailed Description
For a more clear understanding of the technical features, objects and effects of the present invention, embodiments of the present invention will now be described in detail 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 composite material blade 210 to be manufactured has the structure shown in figure 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 includes a main body die 10, a die loose piece 20, a die press plate 30 and a die pad plate 40, and the main body die 10, the die loose piece 20, the die press plate 30 and the die pad plate 40 are made of one or more of conventional metal steel, cast iron and aluminum alloy. Referring to fig. 2, the main body mold 10 is provided with a blade cavity 11 matched with a blade profile value and a loose piece chute 12 matched with a mold loose piece 20; 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 reaches or is superior to Ra6.4; the loose piece slide channel 12 is disposed proximate the blade root cavity 112 and the mold loose piece 20 is inserted into the loose piece slide channel 12 through an upper end opening of the loose piece slide channel 12. Referring to fig. 4, the main structure of the mold loose piece 20 is determined according to the structure of the metal connecting piece 220, the mold loose piece 20 is provided with a blade root installation groove 21 matched with the metal connecting piece 220, and the metal connecting 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 groove 21 is provided with an opening towards the side of the blade cavity 11 for the protruding end of the metal connector 220 to be connected to the composite blade. The upper end of the mold loose piece 20 is provided with a demolding bolt hole 23. Referring to fig. 5, the mold platen 30 is sized and configured to cover the upper end opening of the slide channel 12 and to be securely attached to the body mold 10, as determined by the particular configuration of the mold slide 20, so that during the manufacturing process, a certain pressure is applied and pre-compression urges the product into position. A round hole 31 matched with the demoulding bolt hole is arranged on the mould pressing plate 30; the die pressing plate 30 is further provided with bolt holes 32 connected with the main body die, and corresponding pressing plate positioning holes 13 are arranged around the upper surface of the loose piece sliding groove 12 of the main body die 10 and are matched with corresponding bolts.
Referring to fig. 6, the autoclave molding mold further includes a mold backing plate 40 for molding a large composite blade in multiple steps or manufacturing a composite blade having a similar structure. The die backing plate 40 includes a blade backing plate 41 and a root backing plate 42, and the blade backing plate 41 and the root backing plate 42 are fixedly connected through a dovetail slot form. The bottom surface shape value of the blade backing plate 41 follows the shape value of the blade cavity 111 so as to be conveniently installed in the blade cavity 111, the surface of the blade backing plate 41 is provided with a blade backing plate cavity 411, and the blade backing plate cavity 411 is matched with the blade structure of a composite material blade blank mold formed in a grading manner or matched with the blade structure of a composite material blade with a similar structure. The bottom surface profile of the blade root pad 42 follows the profile of the blade root cavity 112 for installation in the blade root cavity 112, the surface of the blade root pad 42 is provided with a blade root pad cavity (not shown), and the blade root pad cavity is adapted to the blade root structure of the composite blade blank mold formed in separate times or the blade root structure of the composite blade with similar structure. The surface roughness of the blade pad plate cavity 411 and the blade pad plate cavity is equal to or better than Ra6.4. The periphery of the die backing plate 40 is provided with a plurality of positioning slot screw holes 43, and during molding, the die backing plate 40 is fixed in a corresponding cavity of the main body die 10 through positioning slot bolts. The invention adds the die backing plate 40, when the composite material blade needs to be formed in several times, the die backing plate 40 can be adopted to form a blade preformed body firstly, then the die backing plate 40 is removed, and a product (generally, the composite material blade with larger size and thickness) is formed on the main body die 10; a similarly configured composite blade may also be formed using the die pad 40. The main body mold 10 does not need to be manufactured again, and the mold cost is saved.
Further optimize, main part mould 10 is whole integral structure to set up the fretwork trompil in all sides of mould and bottom, do benefit to the holistic high-efficient heat transfer of mould, and rise, the cooling homogeneity is good, when guaranteeing the goods quality, can improve production efficiency.
Further preferably, a plurality of composite material blade raw material paving and positioning datum points are arranged around the upper surface of the blade cavity 11 of the main body die 10, and the number of the positioning datum points is preferably 4 to 12.
Further optimize, the peripheral periphery of main part mould 10 sets up a plurality of hoist and mount bolt holes, the hoist and mount of main part mould 10 of being convenient for.
Further preferably, a blade root positioning hole 22 is disposed in the blade root mounting groove 21 for fixing and positioning the metal connecting element 220. The blade root positioning hole 22 penetrates to the other side of the mold loose piece 20; the blade root positioning holes 22 are bolt holes or pin holes.
Further optimization, in order to reduce the mold processing cost, the blade backing plate 41 can be designed in blocks.
The autoclave forming die for the composite material blade of the ship propeller can form the composite material blade matched with the blade cavity 11, and the forming process comprises the following steps:
s1.1, completing related preparation work, including: (1) utilizing professional CAD software to complete prepreg laying design, engineering drawing conversion, cutting and numbering for the composite material blade, and simultaneously forming a laser projection positioning data file; (2) finishing the preparation of the laser projection locator according to the positioning datum point of the main body mould 10 and the laser projection positioning data file; (3) cleaning a main body mould, and coating a release agent and release wax;
S1.2, paving and sticking prepreg on the lower half of the composite material blade: directly paving a first layer of prepreg in a blade cavity 11 of a main body mould 10 according to a laser projection positioning contour line on the main body mould 10; when a certain number of layers (1-20 layers) are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; and then sequentially finishing the laying of all the layers of the prepreg with the serial numbers on the lower half of the composite material blade. According to the actual forming thickness requirement, when the thickness is thicker, the half-edge forming times can be formed for a plurality of times.
S1.3, the metal connecting piece 220 is arranged in the blade root installation groove 21 of the mold loose piece 20, and the mold loose piece 20 is integrally assembled in the loose piece sliding groove 12 of the main body mold 10.
S1.4, installing a mold pressing plate 30 on the upper surface of the loose piece chute 12, and screwing down through bolts to further pre-press the metal connecting piece 220, so that the metal connecting piece 220 is ensured to be fully contacted with the paved prepreg, and the bonding performance is ensured.
S1.5, repeating the step S1.2, and finishing the laying of the upper lateral prepreg of the composite material blade.
S1.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then, vacuumizing leak detection is carried out, and the main body die is ensured to be in a sealing state. The temperature-resistant forming auxiliary consumable comprises demoulding cloth, an isolating film, a blank mould upper surface conformal soft board, an air-permeable felt and a vacuum bag film, wherein the demoulding cloth, the isolating film, the blank mould upper surface conformal soft board and the air-permeable felt are sequentially paved on the surface of a product, and the vacuum bag film is paved on the surface of a main body mould.
S1.7, the whole main body mould 10 is placed in an autoclave to be heated, pressurized and cured, and a curing system is specifically set according to the performance of the prepreg, the thickness of a laying layer and the structural size of the mould. For example, the pressure may be increased by a gradient of temperature and pressure and the cure completed, as detailed in the following table:
and S1.8, moving the cured composite material blade out of the autoclave along with the mold, demolding, and finishing trimming to obtain the composite material blade.
S1.9, further, polishing the non-mold surface of the composite material blade for smooth transition to finish the shape modification treatment; and further, coating 1-10 layers of prepreg on the surface of the whole composite material blade, and completing curing molding, so that the overall shape value, the strength and the attractive effect of the composite material blade are improved.
The autoclave forming die for the composite material blade of the ship propeller can also be used for forming large composite material blades in batches, the large composite material blade is firstly structurally split into N blank dies and a product die, and 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 material blade, the root of the sandwich structure 230 is assembled and connected with a metal connecting piece 220 to form an assembly part, and the outer surface of the assembly part is sequentially coated with a blank mold skin 240 and a product mold skin 250. The large composite material blade forming process comprises the following steps:
Step one, blank mold forming:
s2.1, completing related preparation work, including: (1) utilizing professional CAD software to complete prepreg laying design, engineering drawing conversion, cutting and numbering for the composite material blade blank mold, and simultaneously forming a laser projection positioning data file; (2) preparing a die cushion plate 40 matched with the 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) cleaning the main body mold 10 and the mold backing plate 40, and coating a release agent and release wax; (4) and finishing the preparation of the laser projection positioner according to the positioning datum point of the main body mould 10 and the laser projection positioning data file.
S2.2, paving and sticking the lower half prepreg of the composite blade blank mold: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the die backing plate 40; when a certain number of layers (1-20 layers) are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; and sequentially finishing the laying of all the layers of the prepreg with the serial numbers on the lower half 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 mold loose piece 20, and the mold loose piece 20 is integrally assembled in the loose piece sliding groove 12 of the main body mold 10.
S2.4, installing a mold pressing plate 30 on the upper surface of the loose piece chute 12, and screwing the mold pressing plate 30 through bolts to further pre-press the metal connecting piece 220, so that the metal connecting piece 220 is ensured to be fully contacted with the paved prepreg, and the bonding performance is ensured.
S2.5, paving and sticking the upper half prepreg of the composite blade blank mold: and the operation is the same as S2.2, and all the prepregs on the upper half of the composite material blade blank mold are laid and attached sequentially.
S1.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; and then vacuumizing and detecting leakage to ensure that the main body mould is in a sealed state. The temperature-resistant forming auxiliary consumable comprises demoulding cloth, an isolating film, a blank mould upper surface conformal soft board, an air-permeable felt and a vacuum bag film, wherein the demoulding cloth, the isolating film, the blank mould upper surface conformal soft board and the air-permeable felt are sequentially paved on the surface of a product, and the vacuum bag film is paved on the surface of a main body mould.
S2.7, the whole main body mould 10 is placed in an autoclave to be heated, pressurized and cured, and a curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mould. For example, the pressure may be increased by a gradient of temperature and pressure and the cure completed, as detailed in the following table:
and S2.8, demolding the cured product to obtain a blank mold.
Step two, molding a product mold:
and S2.10, polishing the surface of the blank mold integral composite material to be rough (the mesh number of selected sand paper is more than 80 meshes), and cleaning for later use.
S2.11, removing the die backing plate 40 and completing related preparation work, wherein the preparation work comprises the following steps: (1) utilizing professional CAD software to complete prepreg laying design, engineering drawing conversion, cutting and numbering for a composite material blade product mold, and simultaneously forming a laser projection positioning data file; (2) cleaning the main body mold 10, and coating a release agent and a release wax; (3) and finishing the preparation of the laser projection positioner according to the positioning datum point of the main body mould 10 and the laser projection positioning data file.
S2.12, paving and sticking the lower half prepreg of the composite material blade product mould: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the mould main body; when a certain number of layers (1-20 layers) are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; and sequentially finishing the laying of all the layers under the composite material blade product mold.
S2.13, installing the spare die loose piece 20 and the blank die in the step S2.10 into the main body die 10.
S2.14, installing a mold pressing plate 30 on the upper surface of the loose piece chute 12, and screwing down through bolts to further pre-press the metal connecting piece 220, so that the whole blank mold is ensured to be fully contacted with the paved prepreg, and the bonding performance is ensured.
S2.15, paving and sticking prepreg on the upper half of the composite material blade product mould: and the operation is the same as S2.12, and all the prepregs on the upper half of the composite material blade are laid and attached sequentially.
S1.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; and then vacuumizing and detecting leakage to ensure that the main body mould is in a sealed state. The temperature-resistant forming auxiliary consumable comprises demoulding cloth, an isolating film, a blank mould upper surface conformal soft board, an air-permeable felt and a vacuum bag film, wherein the demoulding cloth, the isolating film, the blank mould upper surface conformal soft board and the air-permeable felt are sequentially paved on the surface of a product, and the vacuum bag film is paved on the surface of a main body mould.
S2.17, the whole main body mould 10 is placed in an autoclave to be heated, pressurized and cured, and a curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mould. For example, the pressure may be increased by a gradient of temperature and pressure and the cure completed, as detailed in the following table:
and 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 the non-mold surface of the composite material blade, performing processing treatment such as smooth transition and the like, and finishing shape modification treatment; and further, coating 1-10 layers of prepreg on the surface of the whole composite material blade, and completing curing molding, so that the overall shape value, the strength and the attractive effect of the composite material blade are improved.
The autoclave forming die for the composite material blade of the ship propeller can also form the composite material blade with a similar structure, and the forming process comprises the following steps:
s3.1, completing related preparation work, including: (1) finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for composite material blades with similar structures, and simultaneously forming a laser projection positioning data file; (2) preparing a die base plate 40 matched with the composite material blade with the similar structure, and respectively installing a blade base plate 41 and a blade root base plate 42 of the die base plate 40 in a blade cavity 111 and a blade root cavity 112; (3) finishing the preparation of the laser projection locator according to the positioning datum point of the main body mould 10 and the laser projection positioning data file; (4) and finishing the cleaning of the main body mold and the backing plate, and coating a release agent and release wax.
S3.2, laying and sticking prepreg on the lower half of the composite material blade with the similar structure: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the die backing plate 40; when a certain number of layers (1-20 layers) are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; and sequentially finishing the laying of all the layers of the prepreg with the serial numbers on the lower half of the composite material blade with the similar structure.
And S3.3, installing the metal connecting piece 220 into the blade root installation groove 21 of the mold loose piece 20, and integrally assembling the mold loose piece 20 into the loose piece sliding groove 12 of the main body mold 10.
S3.4, installing the mold pressing plate 30 on the upper surface of the loose piece chute 12, and fixedly connecting the mold pressing plate 30 with the main body mold 10 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.
S3.5, paving and pasting prepreg on upper half sides of composite material blades with similar structures: and the operation is the same as S3.2, and all prepreg paving and pasting on the upper half side of the composite material blade with the similar structure are sequentially completed.
S1.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then, vacuumizing leak detection is carried out, and the main body die is ensured to be in a sealing state. The temperature-resistant forming auxiliary consumable comprises demoulding cloth, an isolating film, a blank mould upper surface conformal soft board, an air-permeable felt and a vacuum bag film, wherein the demoulding cloth, the isolating film, the blank mould upper surface conformal soft board and the air-permeable felt are sequentially paved on the surface of a product, and the vacuum bag film is paved on the surface of a main body mould.
And S3.7, placing the main body mould 10 in an autoclave for heating, pressurizing and curing, wherein the curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mould.
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 the non-mold surface of the composite material blade, performing processing such as smooth transition and the like, and finishing shape modification; and further, coating 1-10 layers of prepreg on the surface of the whole composite material blade, and completing curing molding, so that the overall shape value, the strength and the attractive effect of the composite material blade are improved.
The manufacturing process of the composite material blade is simple to operate, 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, and the anti-corrosion effect is good; each composite material blade is independently formed, and maintenance and replacement are facilitated.
While the present invention has been described with reference to the embodiments shown in the drawings, the present invention is not limited to the embodiments, which are illustrative and not restrictive, and it will be apparent to those skilled in the art that various changes and modifications can be made therein without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. A ship propeller composite material blade autoclave molding die, which 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 a composite material outer skin;
The autoclave forming die comprises a main die, a die loose piece and a die pressing plate; the main body mould is provided with a blade cavity matched with a blade type value and a movable block sliding groove matched with the mould movable block, the blade cavity comprises a blade cavity and a blade root cavity which are communicated with each other, the movable block sliding groove is arranged close to the blade root cavity, and the mould movable block is inserted into the movable block sliding groove through an upper end opening of the movable block sliding groove; the mould loose piece is provided with a blade root installation groove matched with the metal connecting piece, and one side of the blade root installation groove facing to the blade cavity is provided with an opening so as to facilitate the connection of the metal connecting piece and the composite material blade; the die pressing plate is used for covering the upper end opening of the loose piece sliding groove and is fixedly connected with the main body die, so that pre-tightening pressure is applied to enable a product to be closed in place in the manufacturing process.
2. The autoclave molding die for the marine propeller composite blade according to claim 1, further comprising 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 backing plate follows the shape value of the blade cavity so as to be conveniently arranged in the blade cavity, the surface of the blade backing plate is provided with a blade backing plate cavity, and the blade backing plate cavity is matched with the blade structure of a composite material blade blank mold formed in a grading way or matched with the blade structure of a composite material blade with a similar structure; the bottom surface model value of the blade root base plate follows the shape of the blade root cavity model value so as to be conveniently installed in the blade root cavity, the surface of the blade root base plate is provided with the blade root base plate cavity, and the blade root base plate cavity is matched with the blade root structure of a composite material blade blank mold formed in a grading way or matched with the blade root structure of a composite material blade with a similar structure.
3. The autoclave molding die for the marine propeller composite blade according to claim 2, wherein the blade root base plate is fixedly connected with the blade base plate in a detachable manner.
4. The autoclave molding die for the composite propeller blades of the ship as claimed in claim 2, wherein a plurality of positioning slot bolts are arranged on the periphery of the die base plate, and the die base plate is fixed in the corresponding cavity of the main body die through the positioning slot bolts.
5. The autoclave molding die for the composite material blades of the ship propellers according to claim 1, wherein a plurality of raw material paving and positioning datum points for the composite material blades are arranged around the upper surface of the blade cavity of the main body die.
6. The autoclave molding die for the composite propeller blades of the marine craft as claimed in claim 1, wherein the main body die is of an integral structure and is provided with hollowed-out openings on all sides and at the bottom.
7. The autoclave molding die for the composite propeller blades of ships according to claim 1, wherein blade root positioning holes are formed in the blade root mounting grooves.
8. A ship propeller composite material blade autoclave molding process is characterized in that the ship propeller composite material blade autoclave molding die of claim 1 is adopted to mold the composite material blade matched with the blade cavity, and the process comprises the following steps:
S1.1, completing related preparation work, including: finishing prepreg laying design, engineering drawing conversion, cutting and numbering for the composite material blades, and simultaneously forming a laser projection positioning data file; finishing the preparation of the laser projection locator according to the main body mould positioning datum point and the laser projection positioning data file;
s1.2, paving and sticking prepreg on the lower half of the composite material blade: directly paving a first layer of prepreg in a blade cavity of a main body mould according to a laser projection positioning profile on the main body mould; when a certain number of layers are laid, pre-compaction and bubble discharge treatment are performed in a vacuum pumping mode; then sequentially finishing the laying and pasting of all the layers of the lower half of the composite material blade;
s1.3, installing a metal connecting piece into a blade root installation groove of a mold loose piece, and integrally assembling the mold loose piece into a loose piece sliding groove of a main body mold;
s1.4, installing a mold pressing plate on the upper surface of the loose piece chute, and fixedly connecting the mold pressing plate with a main body mold so as to further pre-press a metal connecting piece, ensure that the metal connecting piece is fully contacted with the paved prepreg and ensure the bonding performance;
s1.5, repeating the step S1.2 to finish laying and pasting the upper lateral prepreg of the composite material blade;
S1.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then vacuumizing and detecting leakage to ensure that the main body mould is in a sealed state;
s1.7, placing the whole main body mould which finishes the laying and the integral sealing of the prepreg in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of a laid layer and the structural size of the mould;
and S1.8, moving the cured composite material blade out of the autoclave along with the mold, demolding, and finishing trimming to obtain the composite material blade.
9. A large ship propeller composite material blade autoclave molding process is characterized in that the large composite material blade is molded by the ship propeller composite material blade autoclave molding die of claim 2 in multiple times, the large composite material blade is firstly structurally split into N blank dies and a product die, 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 base plate matched with the first layer of blade blank die, and respectively installing a blade base plate and a blade root base plate of the die base plate in a blade cavity and a blade root cavity; finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for a composite material blade blank mold, simultaneously forming a laser projection positioning data file, and finishing preparation of a laser projection positioning instrument according to a main body mold positioning datum point and the laser projection positioning data file;
S2.2, paving and sticking the lower half prepreg of the composite material blade blank mold: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the die backing plate; when a certain number of layers are laid, pre-compaction and bubble discharge treatment are performed in a vacuum pumping mode; sequentially finishing the laying and pasting of all the layers numbered on the lower half of the composite material blade blank mold;
s2.3, installing the metal connecting piece into a blade root installation groove of the die loose piece, and integrally assembling the die loose piece into a loose piece sliding groove of the main body die;
s2.4, installing a mold pressing plate on the upper surface of the loose piece sliding chute, and fixedly connecting the mold pressing plate with the main body mold so as to further pre-press the metal connecting piece, ensure that the metal connecting piece is fully contacted with the paved prepreg and ensure the bonding performance;
s2.5, paving and sticking the upper half prepreg of the composite blade blank mold: the operation is the same as S2.2, and all prepreg paving and sticking on the upper half side of the composite material blade blank mold are completed in sequence;
s2.6, paving temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then carrying out vacuum pumping leak detection to ensure that the main body mould is in a sealed state;
s2.7, placing the whole main body mold in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mold;
S2.8, demolding the cured product to obtain a first layer of blade blank mold;
s2.9, when N is larger than 1, repeating the steps S2.1-S2.8 to sequentially complete the manufacture of the blade blank mold of the Nth layer, wherein after the prepreg of the lower half side of the blade blank mold of the Nth layer is paved, the blade blank mold of the Nth-1 layer is installed in a mold base plate of the blade blank mold of the Nth layer;
step two, product mold forming:
s2.10, polishing the surface of the blank mold integral composite material to be rough, and cleaning for later use;
s2.11, removing the die base plate and completing related preparation work, wherein the method comprises the following steps: finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for a composite material blade product mold, and simultaneously forming a laser projection positioning data file; completing the preparation of the laser projection positioning instrument according to the main body mold positioning datum point and the laser projection positioning data file;
s2.12, paving and sticking the lower half prepreg of the composite material blade product mould: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the mould main body; when a certain number of layers of the layers are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; sequentially finishing the laying of all the layers of the prepreg with the serial numbers on the lower half of the composite material blade product mold;
S2.13, installing the spare die loose block and blank die in the step S2.10 into a main body die;
s2.14, installing a mold pressing plate on the upper surface of the loose piece chute, and fixedly connecting the mold pressing plate with the main body mold so as to further pre-press the metal connecting piece, so that the whole blank mold is ensured to be 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: the operation is the same as S2.12, and all prepreg paving and sticking on the upper half side of the composite material blade are sequentially completed;
s2.16, paving the temperature-resistant forming auxiliary consumable material, and sealing by using a temperature-resistant sealing rubber strip; then carrying out vacuum pumping leak detection to ensure that the main body mould is in a sealed state;
s2.17, placing the whole main body mould in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of the laying layer and the structural size of the mould;
s2.18, demolding the cured product to obtain a finished product mold, and finishing trimming to obtain the composite material propeller blade.
10. A large-scale ship propeller composite material paddle autoclave molding process is characterized in that the ship propeller composite material paddle autoclave molding die of claim 2 is adopted to mold composite material paddles with similar structures, and the process comprises the following steps:
S3.1, completing related preparation work, including: preparing a die base plate adaptive to the composite material blade with the similar structure, and respectively installing a blade base plate and a blade root base plate of the die base plate in a blade cavity and a blade root cavity; finishing prepreg laying layer design, engineering drawing conversion, cutting and numbering for composite material blades with similar structures, simultaneously forming a laser projection positioning data file, and finishing preparation of a laser projection positioning instrument according to a main body die positioning datum point and the laser projection positioning data file;
s3.2, laying and sticking prepreg on the lower half of the composite material blade with the similar structure: paving and pasting the first layer of prepreg according to the laser projection positioning contour line on the die backing plate; when a certain number of layers of the layers are laid, pre-compaction and bubble removal treatment are performed in a vacuum pumping mode; sequentially finishing the laying and pasting of all the layers of the lower half of the composite material blade with the similar structure;
s3.3, installing the metal connecting piece into a blade root installation groove of the die loose piece, and integrally assembling the die loose piece into a loose piece sliding groove of the main body die;
s3.4, installing a mold pressing plate on the upper surface of the loose piece chute, and fixedly connecting the mold pressing plate with the main body mold so as to further pre-press the metal connecting piece, ensure that the metal connecting piece is fully contacted with the paved prepreg and ensure the bonding performance;
S3.5, paving and pasting prepreg on upper half sides of composite material blades with similar structures: the operation is the same as S3.2, and all prepreg paving and sticking on the upper half side of the composite material blade with the similar structure are sequentially completed;
s3.6, paving the temperature-resistant forming auxiliary consumables, and sealing by using a temperature-resistant sealing rubber strip; then carrying out vacuum pumping leak detection to ensure that the main body mould is in a sealed state;
s3.7, placing the prepreg in an autoclave for heating, pressurizing and curing, wherein a curing system is specifically set according to the performance of the prepreg, the thickness of a laying layer and the structural size of a mould;
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 CN114559680A (en) | 2022-01-27 | 2022-01-27 | Autoclave forming die and forming method for ship propeller composite material blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210103719.2A CN114559680A (en) | 2022-01-27 | 2022-01-27 | Autoclave forming die and forming method for ship propeller composite material blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114559680A true CN114559680A (en) | 2022-05-31 |
Family
ID=81713708
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210103719.2A Pending CN114559680A (en) | 2022-01-27 | 2022-01-27 | Autoclave forming die and forming method for ship propeller composite material blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114559680A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115351950A (en) * | 2022-10-21 | 2022-11-18 | 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 |
| CN115847868A (en) * | 2023-02-27 | 2023-03-28 | 江苏新扬新材料股份有限公司 | Manufacturing method of carbon fiber composite low-temperature blade |
Citations (21)
| 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 |
| CN101501132A (en) * | 2006-06-30 | 2009-08-05 | 东丽株式会社 | Epoxy resin composition, prepreg, and fiber-reinforced composite material |
| CN101704302A (en) * | 2009-11-17 | 2010-05-12 | 哈尔滨工业大学 | Integrally forming mould of composite propeller and manufacture method thereof |
| 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 |
| US20140023514A1 (en) * | 2010-01-14 | 2014-01-23 | Neptco, Inc. | Wind Turbine Rotor Blade Components And Methods Of Making Same |
| 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 |
| WO2017149166A1 (en) * | 2016-03-04 | 2017-09-08 | Institut De Recherche Et De Technologie Jules Verne | Method and device for manufacturing a hollow part made of a composite material and turbine blade produced by this method |
| CN107599443A (en) * | 2017-09-05 | 2018-01-19 | 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 |
| 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 |
| CN109249627A (en) * | 2018-08-17 | 2019-01-22 | 武汉源海博创科技有限公司 | A kind of carbon fibre composite propeller die press technology for forming |
| KR20190044176A (en) * | 2017-10-20 | 2019-04-30 | 코리아터빈(주) | Propeller of ship using composite materials and manufacturng of the same |
| CN110439630A (en) * | 2019-08-12 | 2019-11-12 | 航天材料及工艺研究所 | A kind of Varying-thickness composite material stator blade and its forming method |
| CN110815859A (en) * | 2019-11-29 | 2020-02-21 | 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 |
| WO2020083472A1 (en) * | 2018-10-23 | 2020-04-30 | Wärtsilä Netherlands B.V. | A method of manufacturing a propeller blade assembly |
| CN111114743A (en) * | 2018-10-31 | 2020-05-08 | 波音公司 | Composite structure, aircraft and method for nearly invisible impact damage detection |
| CN112249285A (en) * | 2020-09-15 | 2021-01-22 | 江苏恒神股份有限公司 | Propeller and forming method |
| 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 |
| 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 |
| 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 |
| 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 |
| 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 |
-
2022
- 2022-01-27 CN CN202210103719.2A patent/CN114559680A/en active Pending
Patent Citations (21)
| 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 |
| CN101501132A (en) * | 2006-06-30 | 2009-08-05 | 东丽株式会社 | Epoxy resin composition, prepreg, and fiber-reinforced composite material |
| CN101704302A (en) * | 2009-11-17 | 2010-05-12 | 哈尔滨工业大学 | Integrally forming mould of composite propeller and manufacture method thereof |
| US20140023514A1 (en) * | 2010-01-14 | 2014-01-23 | Neptco, Inc. | Wind Turbine Rotor Blade Components And Methods Of Making Same |
| 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 |
| WO2017149166A1 (en) * | 2016-03-04 | 2017-09-08 | Institut De Recherche Et De Technologie Jules Verne | Method and device for manufacturing a hollow part made of a composite material and turbine blade produced by this method |
| 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 |
| CN107599443A (en) * | 2017-09-05 | 2018-01-19 | 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 |
| KR20190044176A (en) * | 2017-10-20 | 2019-04-30 | 코리아터빈(주) | Propeller of ship using composite materials and manufacturng of the same |
| 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 |
| CN109249627A (en) * | 2018-08-17 | 2019-01-22 | 武汉源海博创科技有限公司 | A kind of carbon fibre composite propeller die press technology for forming |
| WO2020083472A1 (en) * | 2018-10-23 | 2020-04-30 | Wärtsilä Netherlands B.V. | A method of manufacturing a propeller blade assembly |
| CN111114743A (en) * | 2018-10-31 | 2020-05-08 | 波音公司 | Composite structure, aircraft and method for nearly invisible impact damage detection |
| CN110439630A (en) * | 2019-08-12 | 2019-11-12 | 航天材料及工艺研究所 | A kind of Varying-thickness composite material stator blade and its forming method |
| CN110815859A (en) * | 2019-11-29 | 2020-02-21 | 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 |
| 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 |
| 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 |
| CN112249285A (en) * | 2020-09-15 | 2021-01-22 | 江苏恒神股份有限公司 | Propeller and forming method |
| 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 |
| 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 |
|---|
| 周鑫: "大厚度船用复合材料螺旋桨桨叶设计与成型工艺", 《船舶工程》, vol. 44, no. 9, 30 September 2022 (2022-09-30), pages 24 - 28 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115351950A (en) * | 2022-10-21 | 2022-11-18 | 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 |
| 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 |
| CN115847868A (en) * | 2023-02-27 | 2023-03-28 | 江苏新扬新材料股份有限公司 | Manufacturing method of carbon fiber composite low-temperature blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114559680A (en) | Autoclave forming die and forming method for ship propeller composite material blade | |
| CN110815856A (en) | Soft die manufacturing method for forming I-beam composite material part and application thereof | |
| CN104589670B (en) | A kind of gas path design method of composite cavity structure air bag shaping | |
| CN110103487B (en) | Process method for forming composite material part with Z-shaped section | |
| CN104290336A (en) | Method for forming J-shaped beam structure composite workpiece by open type soft tooling | |
| CN104494166A (en) | Air bag forming method of composite material part with T-shaped reinforced web structure | |
| CN112406135B (en) | Method for assisting forming of composite propeller blade by air bag blowing | |
| CN216941895U (en) | Autoclave forming die for composite propeller blade of ship | |
| CN113681937B (en) | Composite material cap-shaped stringer wallboard structure and preparation method | |
| CN104290337A (en) | Method for realization of co-cementing of reinforcing rib web composite produced part by accurate positioning soft tooling | |
| CN112238551B (en) | Multi-part integrated forming assembly die and forming assembly method for composite wing | |
| CN108016054A (en) | Carbon fibre composite is molded membranous disc manufacturing process | |
| CN110815854A (en) | Manufacturing method and application of flexible tool for molding longitudinal and transverse T-shaped reinforcing rib workpieces | |
| CN202702639U (en) | Molding device of aircraft wing-shaped member pelvic fin | |
| CN111716761A (en) | Special-shaped curved surface aramid fiber paper honeycomb simple pre-setting die and manufacturing method thereof | |
| CN107901448B (en) | Large-diameter composite skirt compression curing method | |
| CN209775592U (en) | Overall forming tool for composite fuselage skin | |
| CN109353024B (en) | Composite material forming method for J-shaped rib of airplane aileron | |
| CN215849776U (en) | Fiber reinforced composite material forming die for automobile body covering part product | |
| CN110815853A (en) | Forming method and application of air bag die for forming composite J-shaped beam | |
| CN111604469A (en) | Precoated sand splicing model suitable for large parts | |
| CN111716601A (en) | Preparation method of large-scale main load-bearing composite material structure and forming die used in preparation method | |
| CN112123811A (en) | Forming method of split tooling composite material bracket | |
| CN114474779B (en) | Progressive forming method of fiber reinforced composite material preform | |
| CN214821039U (en) | PMI foam mold for composite material molding |
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 |