CN216941895U - Autoclave forming die for composite propeller blade of ship - Google Patents
Autoclave forming die for composite propeller blade of ship Download PDFInfo
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Abstract
The utility model 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 main body die is provided with a cavity; 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 blades with similar structures can be formed. The utility model can realize the autoclave molding process of the composite material blade of the large propeller, can improve the production efficiency and reduce the mold cost while ensuring high yield.
Description
Technical Field
The utility model relates to the technical field of ship propellers, in particular to an autoclave forming die for a composite propeller blade of a ship propeller.
Background
At present, the domestic conventional ship propeller is 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 varies from product to product, and the required mold varies. 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 products.
Chinese patent CN212888465U discloses a blade preforming mold for a split composite propeller, which comprises a preforming main body mold, wherein the preforming main body mold comprises a base, a spiral groove is formed on the base, and a chute is further formed 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 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 processed into designed specification and size and are sequentially arranged according to the laminating 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 mold loose piece design is difficult to ensure the air tightness required by the autoclave forming process and is only suitable for the mold 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.
SUMMERY OF THE UTILITY MODEL
The technical problem to be solved by the utility model is to provide the autoclave forming die for the composite propeller blades of the ships, aiming at the defects in the prior art, the autoclave forming process for the composite propeller blades of the large-scale propellers can be realized through the die, the high yield is ensured, the production efficiency can be improved, and the die cost is reduced.
The technical scheme adopted by the utility model 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.
In the scheme, the main body die, the die loose piece, the die pressing plate and the die base plate are made of one or more of conventional metal steel, cast iron and aluminum alloy.
In the scheme, the surface roughness of the blade cavity reaches or is superior to Ra6.4.
In the scheme, the surface roughness of the blade backing plate cavity and the blade root backing plate cavity reaches or is superior to Ra6.4.
The utility model has the beneficial effects that:
1. the utility model 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 the 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, and the main die is of an integrated structure, so that the airtightness of the main 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 backing plate can be designed and manufactured in a blocking mode according to needs, 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 utility model, the 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, 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.
Drawings
The utility model 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 mold assembly of the autoclave molding mold of the present invention;
fig. 9 is a sectional view of the structure 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 utility model 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 pressing plate 30 and a die backing plate 40, and 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, 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 comprises a blade backing plate 41 and a blade root backing plate 42, and the blade backing plate 41 and the blade root backing plate 42 are fixedly connected in a dovetail clamping groove mode. 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 shim plate cavity 411 and the blade shim 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 utility model 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 optimizing, 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, 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 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 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 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 base plate 40 matched with the blade blank die, 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) cleaning the main body die 10 and the die backing plate 40, and coating a release agent and release wax; (4) and finishing the preparation of the laser projection locator according to the positioning datum point of the main body die 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 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 the mold pressing plate 30 on the upper surface of the loose piece sliding groove 12, screwing the mold pressing plate 30 through the bolts to further pre-press the metal connecting piece 220, ensuring that the metal connecting piece 220 is fully contacted with the paved prepreg and ensuring the bonding performance.
S2.5, paving and sticking prepreg on the upper half side of the composite blade blank mold: and the operation is the same as S2.2, and all prepreg paving and sticking on the upper half of the composite material blade blank mold are completed in sequence.
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.
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 die:
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 die 10, and coating a release agent and release wax; (3) and finishing the preparation of the laser projection locator according to the positioning datum point of the main body die 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 mold loose piece 20 and the blank mold in the step S2.10 into the main body mold 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 pasting prepreg on the upper half of the composite material blade product mould: and the operation is the same as S2.12, and all prepreg paving and pasting on the upper half of the composite material blade are completed in sequence.
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.
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 treatment 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 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 composite material blades with similar structures, 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, paving and sticking the lower half prepreg 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 discharge 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.
And S3.4, installing a mold pressing plate 30 on the upper surface of the loose piece chute 12, and fastening and connecting the mold pressing plate 30 and the main body mold 10 so as to further pre-press the metal connecting piece 220, ensure that the metal connecting piece 220 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: and the operation is the same as S3.2, and all prepregs on the upper half of the composite blade with the similar structure are laid and attached sequentially.
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 the trimming treatment to obtain the composite material blade.
S3.9, 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 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 utility model 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 chute matched with the mould movable block, the blade cavity comprises a blade cavity and a blade root cavity which are mutually communicated, the movable block chute is arranged close to the blade root cavity, and the mould movable block is inserted into the movable block chute through an upper end opening of the movable block chute; 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 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 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 composite propeller blades of ships according to claim 2, characterized in that the blade root backing plate and the blade backing plate are fixedly connected 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 blade of the marine propeller as claimed in claim 1, wherein a plurality of composite material blade raw material paving and positioning reference points are arranged around the upper surface of the blade cavity of the main body die.
6. The autoclave molding die for the marine propeller composite blade according to claim 1, wherein the main body die is of an integral structure, and hollow-out holes are formed in all the side faces and the bottom of the main body die.
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. The autoclave molding die for the composite propeller blades of the marine ship as claimed in claim 2, wherein the main body die, the die loose piece, the die pressing plate and the die backing plate are made of one or more of conventional metal steel, cast iron and aluminum alloy.
9. The autoclave molding die for the marine propeller composite blade according to claim 1, wherein the surface roughness of the blade cavity is equal to or better than Ra6.4.
10. The autoclave molding die for the composite propeller blades of ships according to claim 2, wherein the surface roughness of the blade backing plate cavity and the blade root backing plate cavity is equal to or better than Ra6.4.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202220230614.9U CN216941895U (en) | 2022-01-27 | 2022-01-27 | Autoclave forming die for composite propeller blade of ship |
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| CN202220230614.9U CN216941895U (en) | 2022-01-27 | 2022-01-27 | Autoclave forming die for composite propeller blade of ship |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114559680A (en) * | 2022-01-27 | 2022-05-31 | 武汉海威船舶与海洋工程科技有限公司 | Autoclave forming die and forming method for ship propeller composite material blade |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114559680A (en) * | 2022-01-27 | 2022-05-31 | 武汉海威船舶与海洋工程科技有限公司 | Autoclave forming die and forming method for ship propeller composite material blade |
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