CN105172162B - A kind of aero-engine composite material fan blade mould - Google Patents
A kind of aero-engine composite material fan blade mould Download PDFInfo
- Publication number
- CN105172162B CN105172162B CN201510527938.3A CN201510527938A CN105172162B CN 105172162 B CN105172162 B CN 105172162B CN 201510527938 A CN201510527938 A CN 201510527938A CN 105172162 B CN105172162 B CN 105172162B
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- China
- Prior art keywords
- mould
- blade
- tenon root
- under
- root
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Classifications
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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
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
-
- 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
Abstract
The invention discloses a kind of aero-engine composite material fan blade mould.Its blade mould is molds, and mould and mould on tenon root are mold closing under tenon root.Blade die surface is using blade tenon root to blade tip direction as the complex free curved surface that axle formation thick middle both sides are thin, there is the groove spacing for mould under tenon root in the middle of blade die end convex section, there is the boss coordinated with blade die end groove mould lower surface under tenon root, mould and blade mould are spacing, connected by symmetrical flange bushing, alignment pin and bolt under tenon root, and mould and mould under tenon root are spacing, connected by bushing, conical dowel pin and bolt on tenon root.Blade mould is co-axially mounted with mould on mould under tenon root, tenon root；Mould structure is simple, convenient disassembly, can be used for multiple times without influenceing it to produce precision.Aero-engine composite material fan blade mould, can not only improve the processing efficiency of composite material fan blade, and can reduce the production cost of composite material fan blade.
Description
Technical field
The present invention relates to the design of aeronautical technology equipment configuration and manufacturing technology field, specifically, it is related to a kind of for essence
The metal die of close manufacture aero-engine composite material fan blade.
Background technology
In aviation industry, widely used engine is mainly fanjet.Engine blade is thin-wall construction
Part, with complicated free form surface, design requirement precision is high, lightweight.Especially when the requirement of forth generation aero-engine has
During higher thrust-weight ratio, traditional metal material can not much meet its requirement, the even lightweight metal material such as titanium alloy
Also seemed unable to do what one wishes.Therefore, a kind of material with good physical, the more lightweight of chemical property is needed badly existing to substitute
Material.The increasingly ripe of carbon fiber enhancement resin base composite material succeeds in developing that bring can for high thrust-weight ratio aero-engine
Energy.But carbon fiber enhancement resin base composite material belongs to difficult-to-machine material, if using numerical control cutting hair as metal material
The mode of blank processes composite material fan blade, is not only difficult to receive in cost, the crudy of final product also without
Method ensures.
In the manufacture method of existing carbon fiber enhancement resin base composite material fan blade, using mould laying, use
Solidification of hot-press tank moulding process is to generally acknowledge best manufacture method.Because aero-engine composite material fan blade is thin-walled knot
Structure, be using blade tenon root to blade tip direction axle in the thin complicated free form surface in thick middle both sides, and with it is curved, turn round, plunder
The surface features of shape, design accuracy requires very high, the tenon root position being especially connected with leaf dish, and the requirement of its design accuracy is more
It is high.And carbon fiber enhancement resin base composite material is difficult-to-machine material, and existing Computerized Numerical Control processing technology is difficult to process to meet
It is required that aero-engine composite material fan blade；How on the premise of design accuracy is met in existing processing mold experience
On the basis of, satisfactory carbon fiber enhancement resin base composite material fan blade die is produced, production efficiency, drop is improved
Low production cost, has very important significance in the development process of high thrust-weight ratio aero-engine of new generation.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention propose a kind of aero-engine composite material fan blade into
Pattern has, and the mould can not only improve the processing efficiency of aero-engine composite material fan blade, and can reduce boat
The production cost of empty engine composite material fan blade；Forming die structure is simple, installs convenient disassembly, can be used for multiple times and
It is not influenceed to produce precision.
The technical solution adopted for the present invention to solve the technical problems is:Including on mould under blade mould, tenon root, tenon root
Mould, conical dowel pin, alignment pin, flange bushing, bushing, bolt,
The blade mould is die sinking, and blade mould upper surface is using blade tenon root to blade tip direction as axle formation thick middle two
There is the groove spacing for mould under tenon root the thin complex free curved surface in side, blade die end convex section middle part, and two are turned over
Side bushing is embedded in blade die end convex section；
Mould is that mould lower surface has under mold closing, tenon root and blade die end groove coordinates on mould and tenon root under the tenon root
Mould and blade mould are spacing, connected by symmetrical flange bushing, alignment pin and bolt under boss, tenon root, two flange
Bushing is embedded under tenon root in mould, and mould and mould under tenon root are spacing, connected by bushing, conical dowel pin and bolt on tenon root, and two
Individual bushing is respectively embedded on tenon root in mould；
The blade die horizontal is fixed on the table, and blade laying is located at blade mould upper surface, wherein blade mould
Has laying tail end height highly equal with mould laying under tenon root and blade mould laying intersection.
Mould under tenon root, mould and blade mould are co-axially mounted on tenon root.
Beneficial effect
A kind of aero-engine composite material fan blade mould proposed by the present invention, under blade mould, tenon root
The part of mould three is constituted on mould, tenon root；Wherein, blade mould is die sinking, and mould under tenon root, mould is mold closing, the upper table of blade on tenon root
Face forms mould under complex free curved surface, tenon root, mould is mutually laminated, detachably with blade die end convex section on tenon root.Under tenon root
Fixed on mould, tenon root between mould and blade mould by limited impression, multiple bushings, alignment pin and bolt connection, and shaping mould
Has installing/dismounting, conveniently.
Blade mould upper surface forms the thin complex free curved surface in thick middle both sides using blade tenon root to blade tip direction as axle,
Surface features with curved, torsion, sweep, meet requirement of the aeroengine fan blades to aerodynamic configuration；Mould and tenon under tenon root
Mould further increases machining accuracy by design on root, and passes through the phase between limited impression, bushing, alignment pin and bolt
Mutually coordinate so that mould under blade mould, tenon root, three parts of mould can accurately be fixed and obtain enough, uniform pressure on tenon root
Power, it is not only avoided that the dislocation of tenon root, while can reduce the damage of tenon root.
Aero-engine composite material fan blade mould of the present invention, on the premise of the accuracy of manufacture is met, not only
The processing efficiency and precision of aero-engine composite material fan blade can be improved, and aero-engine composite can be reduced
The production cost of fan blade.Forming die structure is simple, convenient disassembly, can be used for multiple times without influenceing it to produce precision.
Brief description of the drawings
Below in conjunction with the accompanying drawings with embodiment to a kind of aero-engine composite material fan blade mould of the invention
It is described in further detail.
Fig. 1 is composite material fan blade forming die structure schematic diagram of the present invention.
Fig. 2 is composite material fan blade mould right view of the present invention.
In figure:
1. the flange bushing 7. of 4. conical dowel pin of mould, 5. alignment pin 6. on the tenon root of mould 3. under the tenon root of blade mould 2.
The blade of 8. bolt of bushing 9.
Embodiment
The present embodiment is a kind of aero-engine composite material fan blade mould.
Refering to Fig. 1, Fig. 2, aero-engine composite material fan blade mould under blade mould 1, tenon root mould 2,
Mould 3, conical dowel pin 4, alignment pin 5, flange bushing 6, bushing 7, bolt 8 and blade 9 are constituted on tenon root；Aero-engine is combined
Material fan blade shaping mould has die sinking and mold closing two parts, wherein, blade mould 1 is die sinking, under tenon root mould 2 with tenon root
Mould 3 is mold closing.
The surface of blade mould 1 forms the thin complex free curved surface in thick middle both sides using blade tenon root to blade tip direction as axle,
There is the groove spacing for mould 2 under tenon root the end convex section middle part of blade mould 1, and two flange bushings 6 are embedded in blade
In the end convex section of mould 1.Under tenon root the lower surface of mould 2 have under the boss coordinated with the end groove of blade mould 1, tenon root mould 2 with
Blade mould 1 is by symmetrical flange bushing 6, alignment pin 5 is spacing with bolt 8, be fixedly connected, and two flange bushings 6 are embedding
Enter under tenon root in mould 2.On tenon root under mould 3 and tenon root mould 2 by bushing 7, conical dowel pin 4 and bolt 8 are spacing, fixed connect
Connect, two bushings 7 are respectively embedded on tenon root in mould 3.The level of blade mould 1 is fixedly mounted on the table；Blade laying position
In the upper surface of blade mould 1, wherein, the laying tail end of blade mould 1 height is handed over the laying of mould 2 under tenon root and the laying of blade mould 1
It is highly equal at boundary.
In the present embodiment, blade mould 1 is horizontally fixed on work top, when carrying out the operation of the laying of blade 9, by tenon root
Upper mould 3 is disassembled, and mould 2 is tightly secured in blade by symmetrical flange bushing 6, alignment pin 5 and bolt 8 under tenon root
On the end convex section of mould 1；When tightening bolt 8, the laying part tail end height of blade mould 1 and mould under tenon root can be ensured just
2 laying parts and the laying part intersection of blade mould 1 have equal height, it is ensured that the blade portion of blade 9 and tenon root
Part can be smooth transition.The surface of the laying of blade mould 1 is using the tenon root of blade 9 to blade tip direction as axle formation thick middle both sides
Thin complex free curved surface, the surface features with curved, torsion, sweep, meets aeroengine fan blades 9 to aerodynamic configuration
It is required that.
When mould is assembled, mould under tenon root, mould and blade mould are co-axially mounted on tenon root.Limited impression, four flange
Bushing 6, two alignment pins 5 are spacing, fixed by mould 2 under blade mould 1 and tenon root with bolt nail 8, wherein, two flange bushings 6
It is embedded in the end convex section of blade mould 1, two other flange bushing 6 is embedded under tenon root in mould 2；Two bushings 7, two
Conical dowel pin 4 is spacing, fixed by mould 3 on mould 2 under tenon root and tenon root with bolt 8, and two bushings 7 are embedded in mould on tenon root respectively
In 3.Mould 2 improves machining accuracy with mould 3 on tenon root by design under tenon root, and passes through limited impression, bushing 7, alignment pin 5
Cooperation between bolt 8 enable mould 2 under tenon root, mould 3 and 1 three parts of blade mould are accurately fixed on tenon root and obtain foot
Enough uniform pressure, and the random movement of mould 3 on mould 2 and tenon root under blade mould 1, tenon root can be prevented, it is to avoid the dislocation of tenon root,
Reduce the damage of tenon root.
Claims (2)
1. a kind of aero-engine composite material fan blade mould, it is characterised in that:Including under blade mould, tenon root
Mould, conical dowel pin, alignment pin, flange bushing, bushing, bolt on mould, tenon root,
The blade mould is die sinking, and blade mould upper surface is thin as axle formation thick middle both sides using blade tenon root to blade tip direction
Complex free curved surface, there is a groove spacing for mould under tenon root blade die end convex section middle part, two flange linings
Set is embedded in blade die end convex section；
Under the tenon root on mould and tenon root mould be under mold closing, tenon root mould lower surface have with blade die end groove coordinate it is convex
Mould and blade mould are spacing, connected by symmetrical flange bushing, alignment pin and bolt under platform, tenon root, two flange linings
Set is embedded under tenon root in mould, and mould and mould under tenon root are spacing, connected by bushing, conical dowel pin and bolt on tenon root, two
Bushing is respectively embedded on tenon root in mould；
The blade die horizontal is fixed on the table, and blade laying is located at blade mould upper surface, and wherein blade mould is spread
Layer tail end height is highly equal with mould laying under tenon root and blade mould laying intersection.
2. aero-engine composite material fan blade mould according to claim 1, it is characterised in that:Under tenon root
Mould and blade mould are co-axially mounted on mould, tenon root.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510527938.3A CN105172162B (en) | 2015-08-25 | 2015-08-25 | A kind of aero-engine composite material fan blade mould |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510527938.3A CN105172162B (en) | 2015-08-25 | 2015-08-25 | A kind of aero-engine composite material fan blade mould |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105172162A CN105172162A (en) | 2015-12-23 |
| CN105172162B true CN105172162B (en) | 2017-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510527938.3A Active CN105172162B (en) | 2015-08-25 | 2015-08-25 | A kind of aero-engine composite material fan blade mould |
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| CN (1) | CN105172162B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108907277A (en) * | 2018-06-28 | 2018-11-30 | 中国直升机设计研究所 | A kind of unmanned plane composite material blade boring device and method for boring hole |
| CN109703069B (en) * | 2018-12-11 | 2024-02-13 | 惠阳航空螺旋桨有限责任公司 | Blade mold ejector block positioning method |
| CN111231199A (en) * | 2019-12-03 | 2020-06-05 | 惠阳航空螺旋桨有限责任公司 | Positioning mechanism of unmanned aerial vehicle blade preparation mould |
| CN112549381B (en) * | 2020-10-30 | 2022-07-12 | 哈尔滨飞机工业集团有限责任公司 | Detachable lining assembly of composite material mold and mounting and replacing method |
| 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 |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10064268A1 (en) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Tool and method for casting a molded part for the manufacture of a turbine blade |
| CN201249502Y (en) * | 2008-09-27 | 2009-06-03 | 哈尔滨玻璃钢研究院 | Fiber reinforcement resin group composite material wing panel shaping module |
| CN201329637Y (en) * | 2008-12-12 | 2009-10-21 | 江西昌河航空工业有限公司 | Positioning mechanism of helicopter composite material blade forming mould |
| CN201685365U (en) * | 2010-01-15 | 2010-12-29 | 上海玻璃钢研究院有限公司 | Axial mould-assembling and positioning mechanism of wind electricity-generating blade forming mould |
| DK2481559T3 (en) * | 2011-02-01 | 2019-07-29 | Siemens Gamesa Renewable Energy As | Preparing a wind turbine blade for proper positioning in a subsequent assembly step |
| CN203267009U (en) * | 2013-03-05 | 2013-11-06 | 连云港中复连众复合材料集团有限公司 | Manufacturing mode for wind power generation blade with baffle ring at root |
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| Publication number | Publication date |
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| CN105172162A (en) | 2015-12-23 |
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Effective date of registration: 20210209 Address after: Room 21011, block B, innovation and technology building, xigongda, 127 Youyi West Road, Xi'an, Shaanxi 710072 Patentee after: Shaanxi daobo New Material Technology Co., Ltd Address before: 710072 No. 127 Youyi West Road, Shaanxi, Xi'an Patentee before: Northwestern Polytechnical University |
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