CN112249285B - Propeller and forming method - Google Patents
Propeller and forming method Download PDFInfo
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- CN112249285B CN112249285B CN202010965716.0A CN202010965716A CN112249285B CN 112249285 B CN112249285 B CN 112249285B CN 202010965716 A CN202010965716 A CN 202010965716A CN 112249285 B CN112249285 B CN 112249285B
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- propeller
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H1/00—Propulsive elements directly acting on water
- B63H1/02—Propulsive elements directly acting on water of rotary type
- B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
- B63H1/14—Propellers
- B63H1/26—Blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B73/00—Building or assembling vessels or marine structures, e.g. hulls or offshore platforms
- B63B73/20—Building or assembling prefabricated vessel modules or parts other than hull blocks, e.g. engine rooms, rudders, propellers, superstructures, berths, holds or tanks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B73/00—Building or assembling vessels or marine structures, e.g. hulls or offshore platforms
- B63B73/50—Building or assembling vessels or marine structures, e.g. hulls or offshore platforms characterised by forming methods, e.g. manufacturing of curved blocks
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B73/00—Building or assembling vessels or marine structures, e.g. hulls or offshore platforms
- B63B73/70—Building or assembling vessels or marine structures, e.g. hulls or offshore platforms characterised by using moulds; Moulds or plugs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63H—MARINE PROPULSION OR STEERING
- B63H1/00—Propulsive elements directly acting on water
- B63H1/02—Propulsive elements directly acting on water of rotary type
- B63H1/12—Propulsive elements directly acting on water of rotary type with rotation axis substantially in propulsive direction
- B63H1/14—Propellers
- B63H1/20—Hubs; Blade connections
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Combustion & Propulsion (AREA)
- Ocean & Marine Engineering (AREA)
- Architecture (AREA)
- Structural Engineering (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Moulding By Coating Moulds (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a propeller and a forming method in the technical field of propellers, and the propeller comprises a metal propeller hub and a plurality of composite material blades solidified on the metal propeller hub, wherein each composite material blade comprises a structural layer and a protective layer coated outside the structural layer; one ends of the structural layers of the composite material blades are uniformly arranged around the circumferential direction of the metal hub and are wound on the metal hub in an overlapping mode towards the same direction. The blade is solidified on the propeller hub, so that the problem of difficult assembly of the blade and the propeller hub is solved, and the problem of corrosion of a connecting propeller hub part caused by a gap between the combined blade and the propeller hub is solved.
Description
Technical Field
The invention belongs to the technical field of propellers, and particularly relates to a propeller and a forming method.
Background
The propeller is a main component of an underwater vehicle propulsion device of ships, naval vessels and the like, is mainly prepared by metal materials such as NAB alloy and the like at present, and has the defects of poor corrosion resistance, large vibration and the like. Composite propellers can effectively ameliorate these disadvantages and provide better stealth performance. The existing composite material propeller mainly comprises an integral propeller and a combined propeller, wherein the integral propeller is generally formed by adopting a mould pressing method and an RTM (resin transfer molding) method, the combined propeller also adopts an injection molding process, and the produced propeller blades and a propeller hub are assembled by adopting a bolt connection mode or an ear-inserting screw connection mode and the like. The disadvantages of the above-mentioned several preparation methods are: firstly, the connection matching of the composite material blade and the metal hub is difficult to operate, so that the blade root of the propeller is damaged in a fatigue way; and secondly, a gap exists between the combined blade and the hub, so that the part connected with the hub is seriously corroded.
Disclosure of Invention
In order to solve the defects in the prior art, the invention aims to provide a propeller and a forming method, wherein blades are solidified on a propeller hub, so that the problem of difficult assembly of the blades and the propeller hub is solved, and the problem of corrosion of a connecting propeller hub part caused by a gap between a combined blade and the propeller hub is also solved.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows: a propeller comprises a metal hub and a plurality of composite material blades solidified on the metal hub, wherein each composite material blade comprises a structural layer and a protective layer coated outside the structural layer; one ends of the structural layers of the composite material blades are uniformly arranged around the circumferential direction of the metal hub and are wound on the metal hub in an overlapping mode towards the same direction.
Further, the structural layer comprises one or more of a carbon fiber prepreg fabric, a carbon fiber unidirectional prepreg tape, an aramid fiber fabric prepreg tape, a glass fiber prepreg fabric and a glass fiber unidirectional prepreg tape.
Further, the structural layer is made of carbon fiber prepreg fabric and/or glass fiber prepreg fabric, and the mass content of resin in the carbon fiber prepreg fabric and the glass fiber prepreg fabric is 40-50%.
Furthermore, the structural layer adopts a carbon fiber unidirectional prepreg tape and/or a glass fiber unidirectional prepreg tape, and the mass content of resin in the carbon fiber unidirectional prepreg tape and the glass fiber unidirectional prepreg tape is 25-40%.
Furthermore, the structural layer adopts carbon fibers, glass fibers and aramid fibers, the layering proportion ranges of the carbon fibers, the glass fibers and the aramid fibers are 40-60%, 20-30% and 10-40%, the carbon fibers refer to carbon fiber prepreg fabrics and/or carbon fiber unidirectional prepreg tapes, the glass fibers refer to glass fiber prepreg fabrics and/or glass fiber unidirectional prepreg tapes, and the aramid fibers refer to aramid fiber fabric prepreg and/or aramid fiber fabric prepreg tapes.
Further, the protective layer includes one or both of polyurethane and tetrafluoroethylene.
A propeller forming method comprising:
designing a lower die block, wherein the edge of a cavity of the lower die block extends outwards for a set width and is used for arranging a positioning pin;
designing a metal hub, processing a key groove on the metal hub along the axial direction, uniformly arranging one end of a structural layer of a plurality of composite material blades around the circumferential direction of the metal hub, overlapping and winding the structural layer on the metal hub towards the same direction, winding the structural layer to a set thickness, fixing the metal hub on a positioning flange of a lower module, and respectively placing the other end of the structural layer of the composite material blades in a cavity of the lower module;
manufacturing a paddle, cutting a plurality of unidirectional prepreg tapes and prepreg cloth, and paving the unidirectional prepreg tapes and the prepreg cloth into a cavity of a lower module layer by layer according to a designed paving sequence;
prepressing the blade in the cavity of the lower module into a designed shape through a shaping mould;
laying auxiliary materials, and laying release cloth and an isolating film;
closing the die, buckling the semi-rigid upper die and the lower die block, and extracting air in the die through the first air extraction hole and the second air extraction hole;
curing, namely heating to a set temperature and then applying a set pressure to cure;
demoulding, removing vacuum, removing the semi-rigid upper mould and the lower mould block, and carrying out surface finishing;
and (4) spraying, wherein a protective coating is sprayed on the surface to form a protective layer, so as to obtain the composite material propeller.
Further, the edge of the cavity of the lower die block extends outwards by 10-20 mm.
Further, the set pressure is 0.03MPa to 0.06 MPa.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the propeller and the propeller forming method, the structural layer of the composite material propeller blade is wound and solidified on the metal propeller hub, so that the connection performance between the metal propeller hub and the composite material propeller blade is effectively improved, the requirement on strength is met, and the problem that the part connected with the propeller hub is corroded due to the clearance between the combined propeller blade and the propeller hub is solved;
(2) according to the propeller, the propeller blades are manufactured by adopting the prepreg fabric, the prepreg tape and the like as raw materials, so that the power performance of the propeller can be stabilized, and the qualification rate of products is improved;
(3) the propeller adopts a coating technology, and the protective layer is coated outside the structural layer of the composite propeller, so that the surface quality of the propeller is effectively improved, and the cavitation corrosion resistance of the propeller is improved;
(4) in the propeller forming method, the semi-rigid upper die is used to transfer pressure more easily, the manufacturing process performance of the propeller is improved, and the prepared propeller has better surface quality and can effectively resist cavitation corrosion.
Drawings
Fig. 1 is a schematic perspective view of a lower module of a propeller forming mold according to a third embodiment of the present invention;
fig. 2 is a schematic perspective view of a semi-rigid upper mold of a propeller forming mold according to a third embodiment of the present invention;
FIG. 3 is a schematic view of a laminated structure of a metal hub and a composite blade of a propeller according to an embodiment of the present invention;
fig. 4 is a schematic cross-sectional view of a metal hub of a propeller according to an embodiment of the present invention.
Detailed Description
The invention is further described below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and the protection scope of the present invention is not limited thereby.
The first embodiment is as follows:
as shown in fig. 3 and 4, a propeller comprises a metal hub 1 and 4 composite material blades solidified on the metal hub 1, wherein each composite material blade comprises a structural layer 21 and a protective layer 22 coated outside the structural layer; one ends of the structural layers 21 of the 4 composite material blades are uniformly arranged around the circumferential direction of the metal hub 1 and are wound on the metal hub 1 in an overlapping manner towards the same direction; the other end of the structural layer 21 constitutes a part of the composite blade. The metal hub 1 is provided with a key groove 11 along the axial direction, and the key groove 11 is used for connecting a transmission shaft of a driving blade. In this embodiment, the structural layer 21 may be one or a combination of a plurality of carbon fiber prepreg fabrics, carbon fiber unidirectional prepreg tapes, aramid fiber fabric prepreg tapes, glass fiber prepreg fabrics, and glass fiber unidirectional prepreg tapes; the composite material paddle has the advantages that the structural layers 21 of the composite material paddle are overlapped, wound and solidified on the metal paddle hub 1, the paddle and the paddle hub are of an integrated structure, no connecting gap exists, the connecting performance between the metal paddle hub 1 and the composite material paddle is effectively improved, the requirement of strength is met, and meanwhile the problem of corrosion of the connecting paddle hub position due to the fact that a gap exists between the combined paddle and the paddle hub is solved. The protective layer 22 can be one or the combination of polyurethane and tetrafluoroethylene, and a coating technology is adopted, so that the protective layer 22 is coated outside the structural layer 21 of the composite propeller to form a blade surface 221 and a blade back 222 which are wrapped outside the structural layer 21 of the blade, the surface quality of the propeller is effectively improved, and the cavitation erosion resistance of the propeller is improved.
Example two:
the difference between the embodiment and the first embodiment is that the embodiment provides three specific composition modes of the structural layer which can stabilize the power performance of the propeller and improve the yield of products.
The method I comprises the following steps: the structural layer adopts carbon fiber pre-impregnated fabric and/or glass fiber pre-impregnated fabric, and the mass content of resin in the carbon fiber pre-impregnated fabric and the glass fiber pre-impregnated fabric is 40-50%.
The second method comprises the following steps: the structural layer adopts a carbon fiber unidirectional prepreg tape and/or a glass fiber unidirectional prepreg tape, and the mass content of resin in the carbon fiber unidirectional prepreg tape and the glass fiber unidirectional prepreg tape is 25-40%.
The third method comprises the following steps: the structural layer adopts carbon fibers, glass fibers and aramid fibers, the layering proportion ranges of the carbon fibers, the glass fibers and the aramid fibers are 40-60%, 20-30% and 10-40%, wherein the carbon fibers refer to carbon fiber prepreg fabrics and/or carbon fiber unidirectional prepreg tapes, the glass fibers refer to glass fiber prepreg fabrics and/or glass fiber unidirectional prepreg tapes, and the aramid fibers refer to aramid fiber fabric prepreg and/or aramid fiber fabric prepreg tapes.
Example three:
as shown in fig. 1 and 2, a propeller forming mold includes: the lower die block is provided with a first sealing groove 31 at a parting surface, the edge of a cavity of the lower die block extends outwards (in the direction of the first sealing groove) by 10-20 mm in width for mounting a conical rotatable positioning pin, meanwhile, the contact area between the lower die block and the semi-rigid upper die is increased, the sealing performance at the parting surface is improved, a plurality of positioning pins are positioned between the cavity of the lower die block and the first sealing groove 31, and a positioning flange 32 for fixing a hub is arranged at the center of the cavity of the lower die block; the semi-rigid upper die is formed by laminating an elastomer material, a glass fiber fabric and carbon fibers, a positioning hole matched with the positioning pin and a first sealing piece matched with the first sealing groove are formed in the parting surface of the semi-rigid upper die, a first air suction hole penetrating through the semi-rigid upper die is formed in the semi-rigid upper die, and the first air suction hole is communicated with the cavity; the lower module and the semi-rigid upper module are assembled from the parting surface to form a cavity matched with the appearance of the propeller to be molded, air in the cavity is pumped out through the first air pumping hole, and the semi-rigid upper module and the lower module are pressed together under the action of atmospheric pressure.
Example four:
the difference between the present embodiment and the third embodiment is that a second seal groove is further provided on the outer side of the first seal groove 31 on the parting surface of the lower die block; a second sealing element matched with the second sealing groove is arranged on the semi-rigid upper die; the semi-rigid upper die is also provided with a second air suction hole penetrating through the semi-rigid upper die, and the second air suction hole is communicated with an annular area between the first sealing element and the second sealing element and is used for sucking air between the two sealing elements after die assembly; in the embodiment, after die assembly, air in the cavity is pumped out through the first air pumping hole, the semi-rigid upper die and the lower die block are pressed together under the action of atmospheric pressure, meanwhile, air in an annular area between the first sealing piece and the second sealing piece is pumped out through the second air pumping hole, and the die is further locked through vacuum pressure.
Example five:
this embodiment differs from the third or fourth embodiment in that several specific compositions of the semi-rigid upper mold are given in this embodiment.
The method comprises the following steps: adopting silicone rubber (elastomer material) and 100g/m 2 Glass fiber fabric of 200g/m 2 Glass fiber fabric, 240g/m 2 The carbon fiber laminate obtained a semi-rigid upper mold.
The composition is two: respectively adopting nitrile butadiene rubber (elastomer material) and 100g/m 2 Glass fiber fabric of 200g/m 2 Glass fiber fabric, 240g/m 2 The carbon fiber laminate obtained a semi-rigid upper mold.
The composition is as follows: respectively adopting fluororubber (elastomer material) and 100g/m 2 Glass fiber fabric of 200g/m 2 Glass fiber fabric, 240g/m 2 The carbon fiber laminate yields a semi-rigid upper mold.
In this embodiment, the elastomer material may also be an elastomer material other than silicone rubber, nitrile rubber, or fluororubber, which has a long-term service temperature of not less than 120 ℃.
Example six:
this embodiment is different from the fifth embodiment in that SiO is used for the cavity surface of the semi-rigid upper mold 2 /Al 2 O 3 Carbon black reinforced rubber composition, SiO in rubber composition 2 /Al 2 O 3 The content of carbon black is respectively 30g/m 2 ～60g/m 2 . In this example, SiO in the rubber mixture 2 Has a content of 30g/m 2 ，Al 2 O 3 Has a content of 40g/m 2 The content of carbon black is 55g/m 2 The propeller forming die is used for manufacturing the composite propeller by utilizing the designed single-side semi-rigid upper die, and the semi-rigid die is easier to transmit pressure under the pressure state, so that the manufacturing manufacturability of the large-blade propeller is greatly improved; by using SiO in the surface layer of the upper mold 2 /Al 2 O 3 The carbon black reinforced rubber mixture improves the surface hardness, so that the prepared product has better surface quality.
The quality ratio of the product processed using the semi-rigid upper mold of the present embodiment to the product processed using the conventional mold is shown in table 1.
Table 1 comparison of the effects
| Item | Traditional rigid mould | Silicone rubber | Nitrile rubber | Fluororubber |
| Flatness of product surface | Preferably less than or equal to 0.1mm | ≤0.2mm | 0.2mm～0.3mm | ≤0.2mm |
| Internal mass | Difference (D) | Superior food | Youyou (an instant noodle) | Youyou (an instant noodle) |
| Convenience of operation | Difference (D) | Youyou (an instant noodle) | Youyou (an instant noodle) | Superior food |
As can be seen from table 1, the internal quality of the product processed by the semi-rigid upper die of the present embodiment is far better than that of the conventional rigid die, and the surface flatness is better.
Example seven:
a propeller forming method for manufacturing a composite propeller by adopting the propeller forming die comprises the following steps:
1) designing a lower die block, wherein the edge of a cavity of the lower die block extends outwards for 10-20 mm in width and is used for arranging a conical rotatable positioning pin;
2) designing a metal hub, processing a key groove on the metal hub along the axial direction, uniformly arranging one end of a structural layer of a plurality of composite material blades around the circumferential direction of the metal hub, overlapping and winding the structural layer of the composite material blades on the metal hub in the same direction, wherein the winding thickness is 5-10 mm, in the embodiment, the winding thickness is selected to be 5mm, fixing the metal hub on a positioning flange of a lower module, and respectively placing the other end of the structural layer of the composite material blade in a cavity of the lower module; in the embodiment, the structural layer adopts glass fiber prepreg cloth/carbon fiber prepreg cloth;
3) manufacturing a blade, cutting a plurality of unidirectional prepreg tapes and prepreg cloths, and laying the unidirectional prepreg tapes and the prepreg cloths into a cavity of a lower module layer by layer according to a designed laying sequence, wherein the prepreg tapes and the prepreg cloths form a part of a structural layer so as to meet the requirements of the shape and the strength of the blade;
4) prepressing, namely prepressing the blade in the cavity of the lower die block into a designed shape through a shaping die;
5) laying auxiliary materials, laying release cloth and an isolation film, and facilitating subsequent release;
6) closing the die, and buckling the semi-rigid upper die and the lower die block; vacuumizing and assembling the die through the first air exhaust hole and/or the second air exhaust hole; the semi-rigid upper die and the lower die block are tightly attached together under the action of atmospheric pressure, a first sealing element and a second sealing element double-layer sealing structure is adopted, and air in an annular area surrounded by the two sealing elements is pumped out through a second air pumping hole, so that the die assembly effect of the semi-rigid upper die and the lower die block is improved, and the vacuum degree in a die cavity is ensured;
7) curing, namely heating to 135 ℃, and then applying pressure of 0.03-0.06 MPa, wherein in the embodiment, the pressure of 0.043MPa is selected to be applied for curing for 4 hours;
8) demoulding, cooling and removing vacuum, removing the semi-rigid upper mould and the lower mould block, and carrying out surface finishing;
9) and (4) spraying, wherein a protective coating is sprayed on the surface to form a protective layer, so that the cavitation erosion resistance of the surface is improved, and the composite propeller is obtained.
Example eight:
the difference between the embodiment and the seventh embodiment is that the paving material sheet is cut by a sample plate or a digital-analog expansion pattern type and is laid according to the paving method shown in fig. 3. The prepreg is wound on the metal hub and placed on the positioning device, and the laying position is determined by selecting laser projection positioning or positioning clamping plates, so that the positioning precision of laying is improved.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (5)
1. A propeller is characterized by comprising a metal propeller hub and a plurality of composite material blades solidified on the metal propeller hub, wherein each composite material blade comprises a structural layer and a protective layer coated outside the structural layer; one ends of the structural layers of the composite material blades are uniformly arranged around the circumferential direction of the metal hub and are wound on the metal hub in an overlapping mode towards the same direction;
the structural layer comprises one or more of a carbon fiber prepreg fabric, a carbon fiber unidirectional prepreg tape, an aramid fiber fabric prepreg tape, a glass fiber prepreg fabric and a glass fiber unidirectional prepreg tape;
or the structural layer adopts a carbon fiber prepreg fabric and/or a glass fiber prepreg fabric, and the mass content of resin in the carbon fiber prepreg fabric and the glass fiber prepreg fabric is 40-50%;
or the structural layer adopts a carbon fiber unidirectional prepreg tape and/or a glass fiber unidirectional prepreg tape, and the mass content of resin in the carbon fiber unidirectional prepreg tape and the glass fiber unidirectional prepreg tape is 25-40%;
or the structural layer adopts carbon fibers, glass fibers and aramid fibers, and the layering proportion ranges from 40-60% of the carbon fibers, 20-30% of the glass fibers and 10-40% of the aramid fibers, wherein the carbon fibers refer to carbon fiber prepreg fabrics and/or carbon fiber unidirectional prepreg tapes, the glass fibers refer to glass fiber prepreg fabrics and/or glass fiber unidirectional prepreg tapes, and the aramid fibers refer to aramid fiber fabric prepreg fabrics and/or aramid fiber fabric prepreg tapes.
2. The propeller of claim 1 wherein said protective layer comprises one or both of polyurethane and tetrafluoroethylene.
3. A method of forming a propeller, wherein the propeller is as claimed in claim 1 or claim 2, the method comprising:
designing a lower die block, wherein the edge of a cavity of the lower die block extends outwards for a set width and is used for arranging a positioning pin;
designing a metal propeller hub, machining a key groove on the metal propeller hub along the axial direction, uniformly arranging one ends of the structural layers of a plurality of composite material blades around the circumferential direction of the metal propeller hub, overlapping and winding the structural layers on the metal propeller hub in the same direction, winding the structural layers to a set thickness, fixing the metal propeller hub on a positioning flange of a lower module, and respectively placing the other ends of the structural layers of the composite material blades in a cavity of the lower module;
manufacturing a paddle, cutting a plurality of unidirectional prepreg tapes and prepreg cloth, and paving the unidirectional prepreg tapes and the prepreg cloth into a cavity of a lower module layer by layer according to a designed paving sequence;
prepressing, namely prepressing the blade in the cavity of the lower die block into a designed shape through a shaping die;
laying auxiliary materials, and laying release cloth and an isolating film;
closing the die, buckling the semi-rigid upper die and the lower die block, and extracting air in the die through the first air extraction hole and the second air extraction hole;
curing, namely heating to a set temperature and then applying a set pressure to cure;
demolding, removing vacuum, removing the semi-rigid upper mold and the lower mold block, and performing surface finishing;
and spraying, namely spraying a protective coating on the surface to form a protective layer to obtain the composite propeller.
4. The propeller forming method of claim 3, wherein the edge of the cavity of the lower mold block extends outward by 10mm to 20 mm.
5. A method for forming a propeller as claimed in claim 3, wherein the predetermined pressure is 0.03MPa to 0.06 MPa.
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| CN202010965716.0A CN112249285B (en) | 2020-09-15 | 2020-09-15 | Propeller and forming method |
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| CN202010965716.0A CN112249285B (en) | 2020-09-15 | 2020-09-15 | Propeller and forming method |
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| CN112937819B (en) * | 2021-03-30 | 2024-05-14 | 大连海事大学 | Corrosion-resistant impact-resistant marine hybrid fiber composite propeller blade and preparation method thereof |
| 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 |
| 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 |
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| GB2456566B (en) * | 2008-01-18 | 2012-03-07 | Gkn Aerospace Services Ltd | A method of manufacturing a polymer matrix composite forming tool |
| CN101704302B (en) * | 2009-11-17 | 2011-09-14 | 哈尔滨工业大学 | Integrally forming mould of composite propeller and manufacture method thereof |
| CN106965457A (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 compound propeller blade burst shaping is studied with transition Joining Technology |
| CN106965456A (en) * | 2016-11-11 | 2017-07-21 | 武汉海威船舶与海洋工程科技有限公司 | A kind of leafy composite propeller forming method |
| CN107599443B (en) * | 2017-09-05 | 2019-10-11 | 中国船舶重工集团公司第七二五研究所 | A kind of continuous fiber reinforced composite materials propeller Lay up design and preparation method |
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2020
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