CN105172162A - Forming mould for composite-material fan blade of aero-engine - Google Patents
Forming mould for composite-material fan blade of aero-engine Download PDFInfo
- Publication number
- CN105172162A CN105172162A CN201510527938.3A CN201510527938A CN105172162A CN 105172162 A CN105172162 A CN 105172162A CN 201510527938 A CN201510527938 A CN 201510527938A CN 105172162 A CN105172162 A CN 105172162A
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- CN
- China
- Prior art keywords
- mould
- tenon root
- blade
- counterdie
- tenon
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a forming mould for a composite-material fan blade of an aero-engine. A blade body mould of the forming mould is an open mould; and a tenon root lower mould and a tenon root upper mould are closed moulds. A complex free curved surface which is thick in middle and thin in two sides is formed on the surface of the blade body mould by taking a direction from the blade tenon root to the blade tip as an axis; a groove for limiting the tenon root lower mould is formed in the middle of a convex section at the tail end of the blade body mould; a lug boss which is matched with the groove in the tail end of the blade body mould is arranged on the lower end surface of the tenon root lower mould; the tenon root lower mould and the blade body mould are limited and fixedly connected by flanging lining sleeves, dowel pins and bolts which are symmetrical distributed; and the tenon root upper mould and the tenon root lower mould are limited and fixedly connected by virtue of a lining sleeve, a tapered dowel pin and a bolt. The blade body mould, the tenon root lower mould and the tenon root upper mould are coaxially mounted. The forming mould is simple in structure and convenient in dismounting, and capable of being repeatedly used for many times while the production precision of the forming mould is not affected. The forming mould for the composite-material fan blade of the aero-engine not only can improve the processing efficiency of the composite-material fan blade, but also can reduce the production cost of the composite-material fan blade.
Description
Technical field
The present invention relates to aeronautical technology equipment configuration design and manufaction technical field, specifically, relate to a kind of metal die for precision manufactureing aero-engine composite material fan blade.
Background technology
At aviation industry, widely used engine mainly fanjet.Engine blade is thin-walled workpiece, and have complicated free form surface, designing requirement precision is high, lightweight.Especially, when forth generation aero-engine requires to have higher thrust-weight ratio, traditional metal material cannot meet its requirement far away, or even the lightweight metal material such as titanium alloy has also seemed unable to do what one wishes.Therefore, need badly a kind of there is good physical, the material of more lightweight of chemical property carrys out alternative current material.The day by day ripe of carbon fiber enhancement resin base composite material brings possibility for high succeeding in developing of thrust-weight ratio aero-engine.But carbon fiber enhancement resin base composite material belongs to difficult-to-machine material, if adopt the mode of numerical control cutting blank to process composite material fan blade as metal material, be not only difficult to accept on cost, the crudy of final product also cannot ensure.
In the manufacture method of existing carbon fiber enhancement resin base composite material fan blade, utilize mould laying, adopt solidification of hot-press tank moulding process to be generally acknowledged best manufacture method.Because aero-engine composite material fan blade is thin-wall construction, to have with blade tenon root to blade tip direction for the free form surface that axle is the thin complexity in thick middle both sides, and there is surface features that is curved, that turn round, plunder shape, design accuracy requires very high, especially the tenon root position be connected with leaf dish, its design accuracy requires higher.And carbon fiber enhancement resin base composite material is difficult-to-machine material, existing Computerized Numerical Control processing technology is difficult to process satisfactory aero-engine composite material fan blade; How under the prerequisite meeting design accuracy on the basis of existing processing mold experience, produce satisfactory carbon fiber enhancement resin base composite material fan blade mould, enhance productivity, reduce production cost, have very important significance in the development process of the high thrust-weight ratio aero-engine of a new generation.
Summary of the invention
In order to avoid the deficiency that prior art exists, the present invention proposes a kind of aero-engine composite material fan blade mould, this mould not only can improve the working (machining) efficiency of aero-engine composite material fan blade, and can reduce the production cost of aero-engine composite material fan blade; Forming die structure is simple, installs easy accessibility, can repeatedly use and not affect its production precision.
The technical solution adopted for the present invention to solve the technical problems is: comprise blade mould, tenon root counterdie, tenon root patrix, conical dowel pin, alignment pin, flange lining, lining, bolt,
Described blade mould is die sinking, blade mould upper surface with blade tenon root to blade tip direction for axle forms the thin complex free curved surface in thick middle both sides, blade die end convex section middle part has for the spacing groove of tenon root counterdie, and two flange linings are embedded in blade die end convex section;
Described tenon root counterdie and tenon root patrix are mold closing, there is the boss with blade die end groove fit tenon root counterdie lower surface, tenon root counterdie and blade mould spacing by symmetrical flange lining, alignment pin and bolt, be connected, two flange linings are embedded in tenon root counterdie, tenon root patrix and tenon root counterdie spacing by lining, conical dowel pin and bolt, be connected, two linings are embedded in tenon root patrix respectively;
Described blade die horizontal is fixing on the table, and blade laying is positioned at blade mould upper surface, and wherein blade mould laying tail end height is equal with blade mould laying intersection height with tenon root counterdie laying.
Tenon root counterdie, tenon root patrix and blade mould are coaxially installed.
Beneficial effect
A kind of aero-engine composite material fan blade mould that the present invention proposes, is made up of blade mould, tenon root counterdie, tenon root patrix three part; Wherein, blade mould is die sinking, and tenon root counterdie, tenon root patrix are mold closing, and the upper surface of blade forms complex free curved surface, and tenon root counterdie, tenon root patrix are mutually stacked, detachable with blade die end convex section.Tenon root counterdie, to be connected and fixed by limited impression, multiple lining, alignment pin and bolt between tenon root patrix and blade mould, and mould installing/dismounting, convenience.
Blade mould upper surface with blade tenon root to blade tip direction for axle forms the thin complex free curved surface in thick middle both sides, there is surface features that is curved, that turn round, plunder shape, meet the requirement of aeroengine fan blades to aerodynamic configuration; Tenon root counterdie and tenon root patrix further increase machining accuracy by design, and by limited impression, lining, cooperatively interacting between alignment pin and bolt, blade mould, tenon root counterdie, tenon root patrix three parts accurately can be fixed and obtain enough, uniform pressure, it not only can avoid the dislocation of tenon root, can reduce the damage of tenon root simultaneously.
Aero-engine composite material fan blade mould of the present invention, under the prerequisite meeting the accuracy of manufacture, not only can improve working (machining) efficiency and the precision of aero-engine composite material fan blade, and the production cost of aero-engine composite material fan blade can be reduced.Forming die structure is simple, easy accessibility, can repeatedly use and not affect its production precision.
Accompanying drawing explanation
Below in conjunction with drawings and embodiments, a kind of aero-engine composite material fan blade of the present invention mould 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. blade mould 2. tenon root counterdie 3. tenon root patrix 4. conical dowel pin 5. alignment pin 6. flange lining 7. lining 8. bolt 9. blade
Detailed description of the invention
The present embodiment is a kind of aero-engine composite material fan blade mould.
Consult Fig. 1, Fig. 2, aero-engine composite material fan blade mould is made up of blade mould 1, tenon root counterdie 2, tenon root patrix 3, conical dowel pin 4, alignment pin 5, flange lining 6, lining 7, bolt 8 and blade 9; Aero-engine composite material fan blade shaping mould has die sinking and mold closing two parts, and wherein, blade mould 1 is die sinking, and tenon root counterdie 2 and tenon root patrix 3 are mold closing.
Blade mould 1 surface with blade tenon root to blade tip direction for axle forms the thin complex free curved surface in thick middle both sides, blade mould 1 end convex section middle part has for the spacing groove of tenon root counterdie 2, and two flange linings 6 are embedded in blade mould 1 end convex section.There is the boss with blade mould 1 end groove fit tenon root counterdie 2 lower surface, and tenon root counterdie 2 and blade mould 1 be spacing with bolt 8 by symmetrical flange lining 6, alignment pin 5, be fixedly connected with, and two flange linings 6 are embedded in tenon root counterdie 2.Tenon root patrix 3 and tenon root counterdie 2 be spacing with bolt 8 by lining 7, conical dowel pin 4, be fixedly connected with, and two linings 7 are embedded in tenon root patrix 3 respectively.The fixed installation of blade mould 1 level on the table; Blade laying is positioned at blade mould 1 upper surface, and wherein, blade mould 1 laying tail end height is equal with blade mould 1 laying intersection height with tenon root counterdie 2 laying.
In the present embodiment, blade mould 1 is horizontally fixed on work top, when carrying out the operation of blade 9 laying, disassembled by tenon root patrix 3, tenon root counterdie 2 is tightly fixed on blade mould 1 end convex section by symmetrical flange lining 6, alignment pin 5 and bolt 8; When tight a bolt 8 time, just can ensure that blade mould 1 laying part tail end height has equal height with tenon root counterdie 2 laying part and blade mould 1 laying part intersection, can ensure that the blade part of blade 9 and tenon root divide transition that can be level and smooth.The surface of blade mould 1 laying with blade 9 tenon root to blade tip direction for axle forms the thin complex free curved surface in thick middle both sides, there is surface features that is curved, that turn round, plunder shape, meet the requirement of aeroengine fan blades 9 pairs of aerodynamic configurations.
During mould assembling, tenon root counterdie, tenon root patrix and blade mould are coaxially installed.Limited impression, four flange linings, 6, two alignment pins 5 and bolt follow closelys 8 by blade mould 1 with tenon root counterdie 2 is spacing, fix, wherein, two flange linings 6 are embedded in blade mould 1 end convex section, and two other flange lining 6 is embedded in tenon root counterdie 2; Two linings, 7, two conical dowel pins 4 and bolt 8 are by tenon root counterdie 2 and tenon root patrix 3 is spacing, fixing, two linings 7 are embedded in tenon root patrix 3 respectively.Tenon root counterdie 2 and tenon root patrix 3 improve machining accuracy by design, and by limited impression, lining 7, make tenon root counterdie 2, tenon root patrix 3 and blade mould 1 three parts accurately to fix coordinating between alignment pin 5 with bolt 8 and obtain enough uniform pressure, and the random movement of blade mould 1, tenon root counterdie 2 and tenon root patrix 3 can be prevented, avoid the dislocation of tenon root, reduce the damage of tenon root.
Claims (2)
1. an aero-engine composite material fan blade mould, is characterized in that: comprise blade mould, tenon root counterdie, tenon root patrix, conical dowel pin, alignment pin, flange lining, lining, bolt,
Described blade mould is die sinking, blade mould upper surface with blade tenon root to blade tip direction for axle forms the thin complex free curved surface in thick middle both sides, blade die end convex section middle part has for the spacing groove of tenon root counterdie, and two flange linings are embedded in blade die end convex section;
Described tenon root counterdie and tenon root patrix are mold closing, there is the boss with blade die end groove fit tenon root counterdie lower surface, tenon root counterdie and blade mould spacing by symmetrical flange lining, alignment pin and bolt, be connected, two flange linings are embedded in tenon root counterdie, tenon root patrix and tenon root counterdie spacing by lining, conical dowel pin and bolt, be connected, two linings are embedded in tenon root patrix respectively;
Described blade die horizontal is fixing on the table, and blade laying is positioned at blade mould upper surface, and wherein blade mould laying tail end height is equal with blade mould laying intersection height with tenon root counterdie laying.
2. aero-engine composite material fan blade mould according to claim 1, is characterized in that: tenon root counterdie, tenon root patrix and blade mould are coaxially installed.
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 true CN105172162A (en) | 2015-12-23 |
| CN105172162B CN105172162B (en) | 2017-08-15 |
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Family Applications (1)
| 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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| Country | Link |
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| CN (1) | CN105172162B (en) |
Cited By (6)
| 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 |
| CN109703069A (en) * | 2018-12-11 | 2019-05-03 | 惠阳航空螺旋桨有限责任公司 | A kind of blade mold jacking block localization 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 |
| CN112549381A (en) * | 2020-10-30 | 2021-03-26 | 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 |
| CN112743769A (en) * | 2021-01-13 | 2021-05-04 | 广东星联精密机械有限公司 | Apply to split type die lip of injection mould |
| CN115351950A (en) * | 2022-10-21 | 2022-11-18 | 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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| EP1216770A2 (en) * | 2000-12-22 | 2002-06-26 | ALSTOM Power N.V. | Method and device for casting a mould part used during the fabrication 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 |
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| 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 |
| EP2481559A1 (en) * | 2011-02-01 | 2012-08-01 | Siemens Aktiengesellschaft | Method of moulding a wind-turbine blade |
| 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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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| EP1216770A2 (en) * | 2000-12-22 | 2002-06-26 | ALSTOM Power N.V. | Method and device for casting a mould part used during the fabrication 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 |
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| EP2481559A1 (en) * | 2011-02-01 | 2012-08-01 | Siemens Aktiengesellschaft | Method of moulding a wind-turbine blade |
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Cited By (8)
| 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 |
| CN109703069A (en) * | 2018-12-11 | 2019-05-03 | 惠阳航空螺旋桨有限责任公司 | A kind of blade mold jacking block localization method |
| 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 |
| CN112549381A (en) * | 2020-10-30 | 2021-03-26 | 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 |
| CN112743769A (en) * | 2021-01-13 | 2021-05-04 | 广东星联精密机械有限公司 | Apply to split type die lip of injection mould |
| CN115351950A (en) * | 2022-10-21 | 2022-11-18 | 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105172162B (en) | 2017-08-15 |
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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 |