CN106863848B - The forming method of the composite material blade of aero-engine - Google Patents
The forming method of the composite material blade of aero-engine Download PDFInfo
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- CN106863848B CN106863848B CN201710085405.3A CN201710085405A CN106863848B CN 106863848 B CN106863848 B CN 106863848B CN 201710085405 A CN201710085405 A CN 201710085405A CN 106863848 B CN106863848 B CN 106863848B
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- 239000002131 composite material Substances 0.000 title claims abstract description 38
- 238000000034 method Methods 0.000 title claims abstract description 34
- 239000000835 fiber Substances 0.000 claims abstract description 49
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 42
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 42
- 239000004744 fabric Substances 0.000 claims abstract description 25
- 238000010438 heat treatment Methods 0.000 claims abstract description 19
- 238000000465 moulding Methods 0.000 claims abstract description 16
- 238000005516 engineering process Methods 0.000 claims abstract description 11
- 229920005992 thermoplastic resin Polymers 0.000 claims abstract description 9
- 238000007598 dipping method Methods 0.000 claims abstract description 5
- 238000001035 drying Methods 0.000 claims description 6
- 239000003822 epoxy resin Substances 0.000 claims description 5
- 229920000647 polyepoxide Polymers 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 3
- 239000007924 injection Substances 0.000 claims description 3
- 230000006872 improvement Effects 0.000 description 7
- 239000000243 solution Substances 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000009941 weaving Methods 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- 239000002023 wood Substances 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 229930185605 Bisphenol Natural products 0.000 description 1
- 229920000271 Kevlar® Polymers 0.000 description 1
- 229920003368 Kevlar® 29 Polymers 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- ITZGNPZZAICLKA-UHFFFAOYSA-N bis(oxiran-2-ylmethyl) 7-oxabicyclo[4.1.0]heptane-3,4-dicarboxylate Chemical compound C1C2OC2CC(C(=O)OCC2OC2)C1C(=O)OCC1CO1 ITZGNPZZAICLKA-UHFFFAOYSA-N 0.000 description 1
- IISBACLAFKSPIT-UHFFFAOYSA-N bisphenol A Chemical compound C=1C=C(O)C=CC=1C(C)(C)C1=CC=C(O)C=C1 IISBACLAFKSPIT-UHFFFAOYSA-N 0.000 description 1
- 238000009954 braiding Methods 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000004033 diameter control Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 229920013657 polymer matrix composite Polymers 0.000 description 1
- 239000011160 polymer matrix composite Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 229920001169 thermoplastic Polymers 0.000 description 1
- 239000004416 thermosoftening plastic Substances 0.000 description 1
- 238000002604 ultrasonography Methods 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B13/00—Conditioning or physical treatment of the material to be shaped
- B29B13/02—Conditioning or physical treatment of the material to be shaped by heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
- B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
- B29B15/14—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length of filaments or wires
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Reinforced Plastic Materials (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a kind of forming methods of the composite material blade of aero-engine, comprising the following steps: carbon fibre tow is unfolded, using the carbon fibre tow after the dipping expansion of thermoplastic resin mud, obtains intermediate tow；Dry intermediate tow；Intermediate tow is heated by the way of ultrasonic vibration heating, the intermediate tow after heating is carried out by layer-by-layer laying using the method for dry-laid silk, forms blade precast body after laying；The carbon fibre fabric set in the outer cover of blade precast body carries out edge suture with internal blade precast body to carbon fibre fabric set using the method for three-dimensional suture；Blade precast body after suture is put into RTM mold with carbon fibre fabric set, using RTM technology by blade precast body and carbon fibre fabric set die closing and curing molding, obtains composite material blade；This invention ensures that the ratio and precise positioning of axis fiber, to improve the globality and impact resistance of composite material blade.
Description
Technical field
The invention belongs to composite material automatic forming field more particularly to a kind of composite material blades of aero-engine
Forming method.
Background technique
Polymer matrix composites heat-resisting ability is lower, but its light-weight, specific strength and specific modulus height, endurance and corrosion resistant
Corrosion is good, damping characteristic is good, and designability is strong in addition and moulding process comparative maturity, in aero-engine cold end component
(mainly there are the outer culvert casing, stator blade, rotor blade of engine to contain casing and engine nacelle, thrust reverser etc.
Component) widely applied, can substantially reduced engine weight, reduce the development cost of engine, greatly increase hair
The performance of motivation.
It experienced the development of many decades, the manufacturing process of forth generation aero-engine composite material blade is mainly three at present
Dimension braiding and RTM technology, wherein RTM forming technology has the advantages that good surface quality；Can prepare it is complex-shaped,
Accurate in size product；It can be with strict control fiber volume fraction；Structure, function integration can be achieved, be therefore particularly suited for
The manufacture of engine composite material rotor blade, can be significantly reduced manufacturing cost.
The molding of the precast body of the blade of random appearance may be implemented using three dimensional weaving technique, but in order to improve big fly
The bypass ratio and efficiency of the engine of machine, it is necessary to use larger sized fan, its centrifugal load is far longer than small size at this time
Aero-engine composite material fan blade, therefore axial rigidity to composite material blade and intensity propose higher want
It asks.The ratio of its axial direction fibre can not be further increased using three dimensional weaving technique, and is unavoidably being saved in 3 D weaving
The reduction that fibre property is caused at point, is easy to happen damage.Therefore, for the RTM of large-scale composite material engine blower blade
Moulding process, the moulding process of prefabricated component it is necessary to ensure that axis fiber ratio and precise positioning, and keep overall structure
Damage tolerance.
Summary of the invention
The technical problem to be solved by the present invention is to provide a kind of aero-engine in view of the above shortcomings of the prior art
The forming method of composite material blade, the forming method of the composite material blade of this aero-engine ensure that the ratio of axis fiber
Example and precise positioning, improve the globality and impact resistance of molding composite material blade.
To realize the above-mentioned technical purpose, the technical scheme adopted by the invention is as follows:
A kind of forming method of the composite material blade of aero-engine, comprising the following steps:
(1) carbon fibre tow is unfolded, using the carbon fibre tow after the dipping expansion of thermoplastic resin mud, obtains centre
Body tow；
(2) intermediate tow is dried；
(3) intermediate tow is heated by the way of ultrasonic vibration heating, will be heated using the method for dry-laid silk
Intermediate tow afterwards carries out layer-by-layer laying, forms blade precast body after laying；
(4) the carbon fibre fabric set in the outer cover of blade precast body, using the method for three-dimensional suture to carbon fibre fabric
Set carries out edge suture with internal blade precast body；
(5) by after suture blade precast body and carbon fibre fabric set be put into RTM mold, using RTM technology by blade
Precast body and carbon fibre fabric set die closing and curing molding, obtain composite material blade.
Technical solution as a further improvement of that present invention, it is described to be unfolded to include leading to carbon fibre tow by carbon fibre tow
Carbon fibre tow after crossing the expansion of exhibition yarn roller and being unfolded has certain width.
Technical solution as a further improvement of that present invention, the drying intermediate tow include using drying tunnel by intermediate
Tow is dried.
Technical solution as a further improvement of that present invention, the step (3) include:
Intermediate tow is heated using ultrasonic vibration heating head, using laying pressure roller according to preset track will in
Mesosome tow is laid in the surface of laying mold and layer-by-layer laying, blade precast body is formed after laying, from the surface of laying mold
Remove blade precast body.
Technical solution as a further improvement of that present invention, the ultrasonic vibration frequency of the ultrasonic vibration heating head when heated
Rate is 20kHz, and amplitude 0.15, the laying rate of the laying pressure roller is 15m/min.
Technical solution as a further improvement of that present invention, the RTM mold include RTM formpiston and RTM former.
Technical solution as a further improvement of that present invention, the step (5) include:
Blade precast body after suture and carbon fibre fabric set are put between RTM formpiston and RTM former；
RTM formpiston and RTM former are molded, injection epoxy resin and curing molding obtain composite material after demoulding
Blade.
The present invention carries out heating to intermediate tow by the way of ultrasonic vibration heating to reduce intermediate tow
Intermediate tow is laid in the surface of laying mold using laying pressure roller by the viscosity of middle thermoplastic resin according to preset track
The ratio for realizing accurate positioning and axis fiber of the intermediate tow on laying mold, in upper one layer of intermediate tow
Layer-by-layer laying intermediate tow also achieves accurate positioning and forms very big interface bond strength again on surface；It is prefabricated in blade
Carbon fibre fabric set in the outer cover of body improves the globality and impact resistance of composite material blade after molding, anti-to stop loss
Wound；The molding that composite material blade is realized using RTM technology, ensure that the shape geometric dimension and precision of composite material blade；
Compared with blade in the prior art, the present invention molding composite wood in such a way that the method and RTM technology of dry-laid silk combine
Expect blade, 1 times of axial strength can be improved under the premise of identical weight, 1.5 times of modulus is improved, so as to prepare bigger ruler
Very little composite material blade, to meet the requirement of higher bypass ratio.
Detailed description of the invention
Fig. 1 is the preparation flow structural schematic diagram of intermediate tow of the invention.
Fig. 2 is the preparation flow structural schematic diagram of composite material blade of the invention.
Specific embodiment
A specific embodiment of the invention is further illustrated below according to Fig. 1 and Fig. 2:
Referring to Fig. 1 and Fig. 2, a kind of forming method of the composite material blade of aero-engine, comprising the following steps:
(1) carbon fibre tow is unfolded, using the carbon fibre tow after the dipping expansion of thermoplastic resin mud 4, is obtained
Mesosome tow 9；
(2) intermediate tow 9 is dried；
(3) intermediate tow 9 is heated by the way of ultrasonic vibration heating, will be heated using the method for dry-laid silk
Intermediate tow 9 afterwards carries out layer-by-layer laying, forms blade precast body 13 after laying；
(4) the carbon fibre fabric set 14 in the outer cover of blade precast body 13, using the method for three-dimensional suture to carbon fiber
Fabric sleeve 14 and internal blade precast body 13 carry out edge suture；
(5) the blade precast body 13 after suture is put into RTM mold with carbon fibre fabric set 14, it will using RTM technology
Blade precast body 13 and carbon fibre fabric cover 14 die closings and curing molding, obtain composite material blade.
Further, the forming method of the composite material blade of this aero-engine is included the steps that in detail below:
(1) referring to Fig. 1, carbon fibre tow is pulled out under the action of feeding roller 2 from the first closed reel 1, is used
Opening up the carbon fibre tow after carbon fibre tow is unfolded and is unfolded by yarn roller 3 has certain width, after making expansion by feeding roller 2
Carbon fibre tow by filling the glue groove 5 of thermoplastic resin mud 4, wherein thermoplastic resin mud 4 is powder mud, thermoplastic
The diameter control of property toner is 10µM is obtained after dipping hereinafter, thermoplastic resin mud 4 impregnates carbon fibre tow
Intermediate tow 9 containing lower resin content；
(2) intermediate tow 9 passes through drying tunnel 6 under the action of feeding roller 2, and drying tunnel 6 dries intermediate tow 9,
Intermediate tow 9 after drying is got up under the action of feeding roller 2 by the winding of the second closed reel 7；
(3) referring to fig. 2, after the winding for completing intermediate tow 9, to intermediate tow by the way of ultrasonic vibration heating
9 are heated, and ultrasonic vibration heating head 11 can be used and heat to intermediate tow 9, in ultrasonic vibration heating head 11
The viscosity of thermoplastic resin in intermediate tow 9 is reduced under heat effect, wherein ultrasonic vibration heating head 11 is when heated
Ultrasonic vibration frequency is 20kHz, then amplitude 0.15 is carried out the intermediate tow 9 after heating using the method for dry-laid silk
Layer-by-layer laying forms blade precast body after laying；Wherein use the method for dry-laid silk are as follows: using laying pressure roller 8 according to preset
By 9 automatic placement of intermediate tow after heating on the surface of laying mold 10, the laying rate of laying pressure roller 8 is 15m/ for track
Min, and in the surface of upper one layer of intermediate tow layer-by-layer laying intermediate tow again, the prepegged strands 12 in laying are formed, when
After the completion of laying, blade precast body 13 is formed, blade precast body 13 is removed from the surface of laying mold 10；It is shaken using ultrasound
The mode of dynamic heating and the method for dry-laid silk can carry out intermediate tow 9 to be accurately positioned to carry out accurate layer-by-layer laying, and
The intermediate tow 9 of layer-by-layer laying has certain interface bond strength, wherein if the material of blade precast body 13 is different, by
The number of plies of the intermediate tow 9 of layer laying is different；
(4) carbon fibre fabric set 14, carbon fiber in the outer cover for the blade precast body 13 that the method using dry-laid silk is formed
Dimension fabric sleeve 14 improves the globality and shock resistance of blade precast body 13, then using the three-dimensional method sutured and utilizes edge sealing
Kevlar suture 15 carries out edge sealing suture, suture ginseng to the edge of carbon fibre fabric set 14 and internal blade precast body 13
Number is Kevlar29(1500 denier), sewing density is 3 × 3；
(5) the blade precast body 13 after suture is put into RTM mold with carbon fibre fabric set 14, RTM mold includes RTM
Formpiston 17 and RTM former 16, blade precast body 13 and carbon fibre fabric set 14 are adopted between RTM formpiston 17 and RTM former 16
With RTM technology by blade precast body and carbon fibre fabric set die closing and curing molding, composite material blade is obtained, wherein RTM skill
Art are as follows: RTM formpiston 17 and RTM former 16 are molded, epoxy resin is injected from the injection orifice of RTM formpiston 17, has injected
RTM mold is put into baking oven afterwards and carries out curing molding operation, after be down to room temperature with baking oven and demoulded, take out and obtain composite wood
Expect blade；Obtaining composite material blade using RTM technology ensure that the shape geometric dimension and precision of composite material blade；Wherein
It is 180 DEG C that baking oven, which carries out cured temperature, and TDE-85 bisphenol f type epoxy resin can be used by solidifying the epoxy resin used.
Protection scope of the present invention includes but is not limited to embodiment of above, and protection scope of the present invention is with claims
Subject to, replacement, deformation, the improvement that those skilled in the art that any pair of this technology is made is readily apparent that each fall within of the invention
Protection scope.
Claims (5)
1. a kind of forming method of the composite material blade of aero-engine, which comprises the following steps:
(1) carbon fibre tow is unfolded, using the carbon fibre tow after the dipping expansion of thermoplastic resin mud, obtains intermediate silk
Beam；
(2) intermediate tow is dried；
(3) intermediate tow is heated by the way of ultrasonic vibration heating, it will be after heating using the method for dry-laid silk
Intermediate tow carries out layer-by-layer laying, forms blade precast body after laying；
(4) the carbon fibre fabric set in the outer cover of blade precast body, using three-dimensional suture method to carbon fibre fabric set with
Internal blade precast body carries out edge suture；
(5) the blade precast body after suture is put into RTM mold with carbon fibre fabric set, it is using RTM technology that blade is prefabricated
Body and carbon fibre fabric set die closing and curing molding, obtain composite material blade；
The step (3) includes: to be heated using ultrasonic vibration heating head to intermediate tow, using laying pressure roller according to pre-
If track by intermediate tow be laid in laying mold surface and layer-by-layer laying, blade precast body is formed after laying, from paving
Remove blade precast body in the surface for putting mold；
The step (5) include: by after suture blade precast body and carbon fibre fabric set be put into RTM formpiston and RTM former it
Between；
RTM formpiston and RTM former are molded, injection epoxy resin and curing molding obtain composite material blade after demoulding.
2. the forming method of the composite material blade of aero-engine according to claim 1, it is characterised in that: described to incite somebody to action
Carbon fibre tow expansion includes that the carbon fibre tow after carbon fibre tow to be passed through to the expansion of exhibition yarn roller and is unfolded has fixed width
Degree.
3. the forming method of the composite material blade of aero-engine according to claim 2, it is characterised in that: the baking
Dry intermediate tow includes being dried intermediate tow using drying tunnel.
4. the forming method of the composite material blade of aero-engine according to claim 1, it is characterised in that: described super
The ultrasonic vibration frequency of acoustic vibration heating head when heated is 20kHz, and the laying rate of amplitude 0.15, the laying pressure roller is
15m/min。
5. the forming method of the composite material blade of aero-engine according to claim 1, it is characterised in that: described
RTM mold includes RTM formpiston and RTM former.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710085405.3A CN106863848B (en) | 2017-02-17 | 2017-02-17 | The forming method of the composite material blade of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710085405.3A CN106863848B (en) | 2017-02-17 | 2017-02-17 | The forming method of the composite material blade of aero-engine |
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| Publication Number | Publication Date |
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| CN106863848A CN106863848A (en) | 2017-06-20 |
| CN106863848B true CN106863848B (en) | 2019-10-01 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107521123B (en) * | 2017-07-26 | 2020-08-04 | 青岛理工大学 | Embedded co-curing sewing damping film composite material and manufacturing process thereof |
| CN107521116A (en) * | 2017-08-30 | 2017-12-29 | 航天长征睿特科技有限公司 | A kind of leading edge bonding angle sewing method |
| WO2019110939A1 (en) * | 2017-12-06 | 2019-06-13 | Safran Aircraft Engines | Method for manufacturing an ordered network of acoustic channels made of abradable material |
| CN108099317A (en) * | 2017-12-15 | 2018-06-01 | 武汉理工大学 | A kind of high endurance composite material automobile leaf spring and preparation method thereof |
| GB201803802D0 (en) * | 2018-03-09 | 2018-04-25 | Rolls Royce Plc | Composite fan blade and manufacturing method thereof |
| CN110315775B (en) * | 2019-07-05 | 2020-06-23 | 常州市宏发纵横新材料科技股份有限公司 | Wind power blade girder laying system and control method thereof |
| CN114434890A (en) * | 2021-12-20 | 2022-05-06 | 东华大学 | Preparation method of composite carbon fiber tape for automatic laying liquid forming |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH044107A (en) * | 1990-04-20 | 1992-01-08 | Nec Corp | Prepreg sheet of carbon fiber reinforced composite material |
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| CN101698326A (en) * | 2009-10-28 | 2010-04-28 | 中国人民解放军国防科学技术大学 | Fiber reinforced preform for resin transfer molding (RTM) process, and composite material member and preparation method thereof |
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| CN102700151A (en) * | 2012-05-15 | 2012-10-03 | 上海飞机制造有限公司 | Method and device for laying pre-soaking silks automatically |
| CN103407171A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integral forming method for sewing enhanced cross connector made of fiber reinforced resin matrix composite |
| CN104260367A (en) * | 2014-08-22 | 2015-01-07 | 北京卫星制造厂 | A moulding method of a light composite material structural connecting part |
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