CN106079474B - A kind of naval vessel composite propeller blade preform and preparation method thereof - Google Patents
A kind of naval vessel composite propeller blade preform and preparation method thereof Download PDFInfo
- Publication number
- CN106079474B CN106079474B CN201610408962.XA CN201610408962A CN106079474B CN 106079474 B CN106079474 B CN 106079474B CN 201610408962 A CN201610408962 A CN 201610408962A CN 106079474 B CN106079474 B CN 106079474B
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- Prior art keywords
- fibre sleeving
- equal thickness
- propeller blade
- thickness
- blade
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- 239000002131 composite material Substances 0.000 title claims abstract description 28
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 239000000835 fiber Substances 0.000 claims abstract description 73
- 238000013461 design Methods 0.000 claims abstract description 28
- 238000009954 braiding Methods 0.000 claims abstract description 9
- 239000011162 core material Substances 0.000 claims description 36
- 238000000034 method Methods 0.000 claims description 15
- 238000009826 distribution Methods 0.000 claims description 14
- 239000004744 fabric Substances 0.000 claims description 13
- 239000006260 foam Substances 0.000 claims description 10
- 239000000463 material Substances 0.000 claims description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 7
- 239000004917 carbon fiber Substances 0.000 claims description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 7
- 238000005520 cutting process Methods 0.000 claims description 3
- 239000011521 glass Substances 0.000 claims description 3
- 238000004364 calculation method Methods 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims description 2
- 238000009833 condensation Methods 0.000 claims 1
- 230000005494 condensation Effects 0.000 claims 1
- 230000032798 delamination Effects 0.000 abstract description 5
- 238000005260 corrosion Methods 0.000 abstract description 4
- 230000007797 corrosion Effects 0.000 abstract description 4
- 210000003934 vacuole Anatomy 0.000 abstract description 4
- 229910052751 metal Inorganic materials 0.000 abstract description 2
- 239000002184 metal Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 239000011152 fibreglass Substances 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 238000000465 moulding Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 208000020442 loss of weight Diseases 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000009941 weaving Methods 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002386 leaching Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- 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
- 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
- B63H1/265—Blades each blade being constituted by a surface enclosing an empty space, e.g. forming a closed loop
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/087—Propellers
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Composite Materials (AREA)
- Combustion & Propulsion (AREA)
- Ocean & Marine Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention relates to a kind of naval vessel composite propeller blade preforms and preparation method thereof, the composite propeller preform is compared to metal airscrew, composite propeller blade has light-weight, good corrosion resistance, hydrodynamic performance is superior, it can postpone the generation of vacuole, reduce the corrosion of vacuole, and acoustic characteristic is excellent, reduce propeller noise, is conducive to the Stealth Fighter for improving naval vessels.Fibre sleeving is main load carrier in the present invention, fibre sleeving equal thickness designs and covers entire blade, utilize the quasi- two dimensionization of the invention for effectively realizing complex three-dimensional braiding, present invention effectively prevents the delamination stripping problems at original blade guide margin and lagging edge, it not only reduces the difficulty of braiding, reduces cost, the dead weight of propeller blade can also be greatly reduced, improve the form accuracy of propeller blade.
Description
Technical field
The present invention relates to ship equipment design field more particularly to a kind of naval vessel composite propeller blade preforms
And preparation method thereof.
Background technology
Currently, the preparation process of existing composite propeller is frequently with compression molding and RTM Shooting Techniques.But it is molded
There is interlaminar strength in composite propeller prepared by moulding process, permanent military service is lower easily to cause blade guide margin and lagging edge
The delamination at place is removed, and working efficiency, or even failure are reduced.RTM Shooting Techniques frequently with fiber cloth laying or weaving method into
The making of row preform, according to laying mode equally will produce lead, the delamination problems at lagging edge, and due to being molded
Journey can make laying that subtle mobile variation occur, it is also difficult to ensure that all blade internal structures prepared by same mold are completely the same
So as to cause vibration noise problem；In addition three-dimensional for this complex contour of marine propeller and the higher product of required precision
The difficulty for weaving preform is larger, and cost is higher.
Invention content
The applicant is directed to above-mentioned existing issue, has carried out Improvement, provides a kind of naval vessel composite propeller leaf
Piece preform and preparation method thereof not only avoids the delamination stripping problem of guide margin, lagging edge, also substantially reduces the difficulty of establishment
Degree, reduces cost, and propeller blade dead weight is greatly reduced.
The technical solution adopted in the present invention is as follows：
A kind of naval vessel composite propeller blade preform and preparation method thereof, includes the following steps：
The first step：Equal thickness fibre sleeving, the equal thickness fibre sleeving are designed according to the work loading conditions of propeller blade
For the main load bearing component of composite propeller blade preform；
Second step：It is designed according to the thickness of equal thickness fibre sleeving obtained by the first step and makes core model；
Third walks：Equal thickness fibre sleeving is woven based on core model using braider；
4th step：It cuts prepreg synusia and is pasted on the outer surface of equal thickness fibre sleeving and is modified, make described pre-
Leaching material is corrected to identical as propeller blade shape.
Its further technical solution is：
The equal thickness fibre sleeving thickness distribution is consistent；The design of the equal thickness fibre sleeving includes thickness design and fiber
The design of angle design, the equal thickness fibre sleeving needs the intensity for meeting propeller blade and deformation requirements；
Normal direction offset is born in the blade face of propeller blade and blade back by the core model design method along its surface respectively；
The offset distance is identical as fibre sleeving thickness；
The braiding of the fibre sleeving needs the design requirement for reaching fibre sleeving, and the design requirement of the fibre sleeving includes fiber
Thickness requirement and the fiber angles requirement of set；
In the 4th step, the thickness distribution of propeller is calculated according to propeller blade shape offset, utilizes three-dimensional modeling
Prepreg cloth, is cut into the region shape of equal thickness distribution curve, each equal thickness by Software on Drawing blade equal thickness distribution curve
Region prepreg piece quantity is obtained according to the area thickness and prepreg cloth THICKNESS CALCULATION of equal thickness distribution curve, prepreg
The paving of piece should be consistent to angle with the paving of fibre sleeving to angle；
Composite propeller blade preform includes that inside is used to support the composite core film of establishment and is wrapped in
The equal thickness fibre sleeving of the composite core film is also bonded prepreg in the periphery of the equal thickness fibre sleeving；
The fiber cover material is made of high intensity carbon fiber material, and the prepreg cloth presoaks for high-strength carbon fiber
Expect cloth；
The core model is by numerical control cutting foam core material and is laid in one layer of glass laying of the foam core material outer surface
Composition；
Beneficial effects of the present invention are as follows：
Compared to metal airscrew, composite propeller blade has light-weight, good corrosion resistance, hydrodynamic performance excellent
More, the generation that can postpone vacuole reduces the corrosion of vacuole, and acoustic characteristic is excellent, reduces propeller noise, is conducive to carry
The Stealth Fighter of high naval vessels.Fibre sleeving is main load carrier in the present invention, and fibre sleeving equal thickness designs and cover entire blade,
Using the quasi- two dimensionization of the invention for effectively realizing complex three-dimensional braiding, present invention effectively prevents original blade guide margin and lagging edges
The delamination stripping problem at place not only reduces the difficulty of braiding, reduces cost, moreover it is possible to propeller blade be greatly reduced
Dead weight, improves the form accuracy of propeller blade.
Description of the drawings
Fig. 1 is the structural schematic diagram of preform in the present invention.
Fig. 2 is the structural schematic diagram in preform cross section in the present invention.
Wherein：1, equal thickness fibre sleeving；2, core model；3, prepreg.
Specific implementation mode
Below in conjunction with the accompanying drawings, illustrate the specific implementation mode of the present invention.
As shown in Figure 1 and Figure 2, a kind of naval vessel composite propeller blade preform includes that inside is used to support braiding
Composite material core model 2 and be wrapped in the equal thickness fibre sleeving 1 of composite material core model, it is also viscous in the periphery of equal thickness fibre sleeving 1
Connect prepreg 3.The material of equal thickness fibre sleeving 1 is made of high intensity modules carbon fibre material.Core model 2 is by numerical control cutting foam
Core material simultaneously lays one layer of glass laying in foam core material outer surface.
Embodiment 1：
As shown in Figure 1 and Figure 2, a kind of naval vessel composite propeller blade preform preparation method includes the following steps：
The first step：Calculate the hydrodynamic load under design conditions of propeller blade using CFD software, and then design etc.
The thickness of thickness fibre sleeving 1, above-mentioned equal thickness fibre sleeving 1 is 5mm, and fiber angles are [0/30/0/30] s.Through finite element software
It checks, the design of the equal thickness fibre sleeving 1 meets the intensity and deformation requirements of propeller blade.
Second step：Core model is designed and makes according to the thickness of uniform thickness fibre sleeving 1 obtained by the first step, core model design method is profit
With 3D sculpting software by propeller blade blade face and blade back respectively along negative normal direction offset 5mm (offset distance with it is above-mentioned
The thickness of fibre sleeving 1 is identical), the shape (such as appearance schematic diagram of Fig. 1 core moulds 2) of core model 2 is obtained, and using outside foam core
The method for applying fiberglass covering makes the core model 2, which is PVC foams, and the fiberglass covering of external application is thick
Spend 0.5mm.
Third walks：Equal thickness fibre sleeving is woven using braider on the basis of core model 2, material is carbon fiber T700.Deng
It is [0/ that the braiding of thickness fibre sleeving, which needs the design requirement for reaching fibre sleeving, i.e. equal thickness fibre sleeving thickness 5mm, fiber angles,
30/0/30]s。
4th step：First according to propeller blade shape offset in the step, blade three is drawn using 3D sculpting software
Dimension module obtains the equal thickness distribution curve of 0.5mm, 1mm, 1.5mm, 2mm, 2.5mm, 3mm, 3.5mm, 4mm, 4.5mm, 5mm,
Carbon fiber prepreg cloth is cut into the region shape of the equal thickness distribution curve, each equal thickness region prepreg piece quantity
It is calculated and is obtained according to the thickness 0.5mm of the area thickness combination prepreg cloth, respectively 1~10 layer.The paving of synusia should be with to angle
The paving of fibre sleeving is consistent to angle, namely [0/30/0/30] s.Each synusia is pasted onto to the outer surface of fibre sleeving in sequence, is utilized
Prepreg synusia amendment preform shape is extremely identical as propeller blade shape, completes preforming making.
The preform of completion has carried out profile measurement and strength test after RTM technique curing moldings.After testing, leaf
Piece shape meets 2 grades of tolerances of marine propeller geometric dimension, and intensity and deformation are also met the requirements.And compared to aluminium alloy spiral
The dead weight of paddle single blade 4.8kg, composite propeller single blade dead weight 2.8kg, loss of weight 42%, and simple for process, production
Efficiency is higher.
Embodiment 2 (Design of Propeller for being directed to diameter 500mm)：
As shown in Figure 1 and Figure 2, a kind of naval vessel composite propeller blade preform preparation method includes the following steps：
The first step：Calculate the hydrodynamic load under design conditions of propeller blade using CFD software, and then design etc.
The thickness of thickness fibre sleeving 1, above-mentioned equal thickness fibre sleeving 1 is 3mm, and fiber angles are [- 30/0/45/-30/0/45] s.Through having
It limits meta software to check, the design of the equal thickness fibre sleeving 1 meets the intensity and deformation requirements of propeller blade.
Second step：Core model is designed and makes according to the thickness of uniform thickness fibre sleeving 1 obtained by the first step, core model design method is profit
With 3D sculpting software by propeller blade blade face and blade back respectively along negative normal direction offset 3mm (offset distance with it is above-mentioned
The thickness of fibre sleeving 1 is identical), the shape (such as appearance schematic diagram of Fig. 1 core moulds 2) of core model 2 is obtained, and using outside foam core
The method for applying fiberglass covering makes the core model 2, which is PVC foams, and the fiberglass covering of external application is thick
Spend 0.1mm.
Third walks：Equal thickness fibre sleeving is woven using braider on the basis of core model 2, material is carbon fiber T300.Deng
The braiding of thickness fibre sleeving needs the design requirement for reaching fibre sleeving, i.e. equal thickness fibre sleeving thickness 3mm, fiber angles be [-
30/0/45/-30/0/45]s。
4th step：First according to propeller blade shape offset in the step, blade three is drawn using 3D sculpting software
Dimension module obtains the equal thickness distribution curve of 0.5mm, 1mm, 1.5mm, 2mm, 2.5mm, 3mm, prepreg cloth is cut into described
The region shape of equal thickness distribution curve, each equal thickness region number of lamina amount is according to the thickness of the area thickness combination prepreg cloth
0.5mm, which is calculated, to be obtained, respectively 1~6 layer.The paving of synusia should be consistent to angle with the paving of fibre sleeving to angle, namely [- 30/0/45/-
30/0/45]s.Each synusia is pasted onto to the outer surface of fibre sleeving in sequence, is corrected outside preform using the prepreg synusia
Shape is extremely identical as propeller blade shape, completes preforming making.
The preform of completion has carried out profile measurement and strength test after RTM technique curing moldings.After testing, leaf
Piece shape meets 2 grades of tolerances of marine propeller geometric dimension, and intensity and deformation are also met the requirements.And compared to aluminium alloy spiral
The dead weight of paddle single blade 3.2kg, composite propeller single blade dead weight 1.7kg, loss of weight 47%, and simple for process, production
Efficiency is higher.
Above description is explanation of the invention, is not the restriction to invention, limited range of the present invention is referring to right
It is required that without prejudice to the basic structure of the present invention, the present invention can make any type of modification.
Claims (4)
1. a kind of preparation method of naval vessel composite propeller blade preform, it is characterised in that include the following steps：
The first step：Equal thickness fibre sleeving is designed according to the work loading conditions of propeller blade, the equal thickness fibre sleeving is multiple
The main load bearing component of condensation material propeller blade preform；The equal thickness fibre sleeving thickness distribution is consistent；The equal thickness
The design of fibre sleeving includes that thickness design and fiber angles design, the design of the equal thickness fibre sleeving need to meet screw blade
The intensity and deformation requirements of piece；
Second step：It is designed according to the thickness of equal thickness fibre sleeving obtained by the first step and makes core model；The core model design method is
The blade face of propeller blade and blade back are born into normal direction offset, the offset distance and fibre sleeving thickness phase along its surface respectively
Together；
Third walks：Equal thickness fibre sleeving is woven based on core model using braider；The braiding needs of the fibre sleeving reach fine
The design requirement of set is tieed up, the design requirement of the fibre sleeving includes thickness requirement and the fiber angles requirement of fibre sleeving；
4th step：It cuts prepreg synusia and is pasted on the outer surface of equal thickness fibre sleeving and is modified, make the prepreg
It corrects to identical as propeller blade shape；The thickness distribution of propeller is calculated according to propeller blade shape offset, is utilized
3D sculpting software draws blade equal thickness distribution curve, and prepreg cloth is cut into the region shape of equal thickness distribution curve,
Each equal thickness region prepreg piece quantity is obtained according to the area thickness and prepreg cloth THICKNESS CALCULATION of equal thickness distribution curve,
The paving of prepreg synusia should be consistent to angle with the paving of fibre sleeving to angle.
2. composite propeller blade preform prepared by method as described in claim 1, it is characterised in that：Including inside
It is used to support the composite core film (2) of establishment and is wrapped in the equal thickness fibre sleeving (1) of the composite core film, in described
The periphery of equal thickness fibre sleeving (1) is also bonded prepreg (3).
3. composite propeller blade preform as claimed in claim 2, it is characterised in that：The fiber cover material is adopted
It is made of high intensity carbon fiber material, the prepreg cloth is high-strength carbon fiber prepreg cloth.
4. composite propeller blade preform as claimed in claim 2, it is characterised in that：The core model is by numerical control cutting
The one layer of glass laying composition cut foam core material and be laid in the foam core material outer surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610408962.XA CN106079474B (en) | 2016-06-12 | 2016-06-12 | A kind of naval vessel composite propeller blade preform and preparation method thereof |
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| CN201610408962.XA CN106079474B (en) | 2016-06-12 | 2016-06-12 | A kind of naval vessel composite propeller blade preform and preparation method thereof |
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| CN106079474B true CN106079474B (en) | 2018-08-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| RU2797954C1 (en) * | 2022-07-18 | 2023-06-13 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Method for manufacturing aerodynamic controls for unmanned aerial vehicles |
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| CN106584883B (en) * | 2016-12-07 | 2019-06-18 | 中国人民解放军海军工程大学 | Underwater lightweight buoyancy offset-type composite material solid core crashworthiness endergonic structure unit |
| CN108192201B (en) * | 2017-12-25 | 2021-04-09 | 中广核俊尔新材料有限公司 | Continuous fiber reinforced thermoplastic resin composite material paddle blade and preparation method thereof |
| CN108466686B (en) * | 2018-03-29 | 2020-09-29 | 哈尔滨工业大学（威海） | Marine propeller blade with piezoelectric damping and preparation method |
| CN110815859B (en) * | 2019-11-29 | 2022-03-29 | 株洲时代新材料科技股份有限公司 | Design and manufacturing method of composite material blade and composite material blade |
| 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 |
| 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 |
| CN114889153A (en) * | 2022-03-15 | 2022-08-12 | 云路复合材料(上海)有限公司 | Carbon fiber composite material unmanned aerial vehicle propeller preforming body weaving forming method |
| CN114889786B (en) * | 2022-05-17 | 2023-03-28 | 中国人民解放军海军工程大学 | Composite propeller blade |
| CN115258122B (en) * | 2022-07-07 | 2023-09-08 | 中国船舶重工集团公司第七一五研究所 | Light high-strength composite alloy solid rudder plate and preparation method thereof |
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| CN101579955B (en) * | 2008-05-16 | 2013-01-30 | 比亚迪股份有限公司 | Carbon fiber product and manufacturing method thereof |
| US9457435B2 (en) * | 2012-01-25 | 2016-10-04 | Snecma | Method for producing a propeller blade from a composite material |
| CN104743087B (en) * | 2015-03-26 | 2017-09-26 | 北京勤达远致新材料科技股份有限公司 | A kind of ship D braided composites propeller blade and preparation method thereof |
| CN104743099B (en) * | 2015-03-26 | 2017-09-12 | 北京勤达远致新材料科技股份有限公司 | A kind of aircraft D braided composites propeller blade and preparation method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| RU2797954C1 (en) * | 2022-07-18 | 2023-06-13 | Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации | Method for manufacturing aerodynamic controls for unmanned aerial vehicles |
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