CN114030203A - Tooling for manufacturing aeroengine composite material fan blade body characteristic part - Google Patents
Tooling for manufacturing aeroengine composite material fan blade body characteristic part Download PDFInfo
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- CN114030203A CN114030203A CN202111311429.9A CN202111311429A CN114030203A CN 114030203 A CN114030203 A CN 114030203A CN 202111311429 A CN202111311429 A CN 202111311429A CN 114030203 A CN114030203 A CN 114030203A
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- tooling
- tool
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- fan blade
- positioning
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- 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
- B29L2031/082—Blades, e.g. for helicopters
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention relates to a tool for manufacturing a composite material fan blade body characteristic part of an aero-engine, which comprises a tool main body and a butt joint component, wherein the tool main body comprises a tool profile and a tool supporting frame, the center part of the tool profile is a part paving area, a surplus area is arranged on the periphery of the part paving area, and the tool profile is arranged on the upper surface of the tool supporting frame. The invention can realize the application of the automatic filament laying process in the manufacturing of the composite material fan blade body, improves the manufacturing efficiency and the contour precision of parts, and can promote the realization of the automation of the manufacturing process of the composite material fan blade body.
Description
Technical Field
The invention belongs to the field of manufacturing of aero-engines, and particularly relates to a tool for manufacturing a composite material fan blade body characteristic part of an aero-engine, which can be used for laying layers of the composite material fan blade body characteristic part in an automatic silk laying process, combining and pasting a vacuum bag and an auxiliary material before an autoclave curing process, curing the vacuum bag and the auxiliary material in the autoclave along with parts, and finally realizing the primary manufacturing of the composite material fan blade body.
Background
The aircraft engine is a heart-type component of the aircraft, provides power required by the aircraft for flying, and is a decisive component for the reliability, durability and economy of the aircraft. According to statistics, the mass of the fan section accounts for about 30% -35% of the total mass of the engine, and reducing the mass of the fan section is a key means for reducing the overall mass of the engine and improving the efficiency of the engine. Therefore, in order to meet the performance requirements of high thrust-weight ratio, low oil consumption rate, light weight and the like of the aircraft engine, the carbon fiber reinforced resin matrix composite material with the advantages of high specific strength, small thermal expansion coefficient, easiness in molding and the like has gradually become an ideal material for manufacturing the aircraft engine fan blade instead of titanium alloy.
In the existing manufacturing technology of the carbon fiber reinforced resin matrix composite aircraft engine fan blade, the common prepreg is formed by autoclave or die pressing after being manually laid. However, the manual operation of laying layer positioning is determined according to a laser projection system and naked eyes, manual compaction is needed, and vacuumizing compaction processing is needed for each certain number of laying layers, so that the deviation of the shape, the thickness and the design size of the final part is easily caused.
At present, the existing forming tool for fan blades made of similar composite materials in China has the following problems:
1. the design only faces to the manual layering/autoclave forming process;
2. the device cannot be directly butted with a positioning device of an automatic filament paving machine;
3. if the automatic fiber spreading machine with the existing model is directly used for spreading on the molded surface, the concave area of the automatic fiber spreading machine is easy to interfere with the fiber spreading head;
4. there is no design on the profile for positioning of the automatic filament spreading machine, and it is generally not suitable for the automatic filament spreading process to lay the fan blades.
In recent years, the gradually developed Automatic Fiber Placement (AFP) technology is widely applied to the manufacturing process of composite parts by means of an efficient and automatic placement operation flow.
Aiming at the defects of the existing similar tool in China at present, the tool for forming the aero-engine composite material fan blade body sample facing the automatic fiber laying process is designed based on the requirements on the assembly size of the butt joint device of the automatic fiber laying machine, the appearance characteristics of the fiber laying head and the understanding of the automatic fiber laying process flow, is used for evaluating the process feasibility of tool manufacturing and the structural integrity of composite material blades manufactured by the automatic fiber laying process, and has important significance for realizing the manufacturing automation of the composite material fan blade body.
Disclosure of Invention
The invention aims to solve the problem that the existing composite material fan blade forming tool cannot be directly applied to an automatic filament spreading process, and designs a set of tool facing an automatic filament spreading machine, so that the design size of a tool interface is matched with the size of the automatic filament spreading machine, meanwhile, the profile of the tool is not interfered with a filament spreading head, and a related design for positioning of the automatic filament spreading machine is arranged, so that a blade body characteristic part can be manufactured by using an automatic filament spreading/autoclave process, and the process feasibility of automatic filament spreading manufacturing and the structural integrity of a composite material blade body are evaluated.
In order to ensure that the tool is matched with the automatic filament paving machine in size, the blade body characteristic part tool provided by the invention has the following characteristics:
1) the tool is of a metal frame type structure.
2) The molded surface of the tool is a male mold of a full-area outward-protruding type, and different curved surfaces are continuously connected by adopting a tangent line, so that the problem of interference with the molded surface of the tool caused by overlarge size of a thread laying head of an automatic thread laying machine is avoided to the greatest extent.
3) The profile of the tool is provided with a target ball jack which can be used for inserting a target ball, the automatic wire laying machine is specially used for positioning the tool, and the interface component can be directly matched with the automatic wire laying machine.
4) The tool is provided with a margin area of 150 plus 300mm, and is used for laying the wire laying margin needing subsequent numerical control machining and simultaneously used for sticking the vacuum bag.
5) The tool can also be used for manual laying operation so as to compare the quality of parts in a manual laying process and an automatic wire laying process.
According to the above thought, the invention provides a tooling for manufacturing a composite fan blade feature part of an aero-engine, which comprises a tooling main body and butt joint parts facing an automatic wire laying process, wherein the left side and the right side of the tooling main body are respectively connected with the butt joint parts, and the two butt joint parts are used for integrally erecting the tooling on an automatic wire laying machine; the frock main part includes frock profile and frock braced frame, the central part of frock profile is the part and lays the district, and the surplus district sets up and lays the district periphery at the part, the frock profile sets up frock braced frame's upper surface.
Furthermore, the molding surface of the tool is a male die which is convex in the whole area, and different curved surfaces are continuously connected by adopting a tangent line.
Further, the tool supporting frame comprises an assembly part consisting of a steel plate and a bottom plate, and the assembly part is arranged on the bottom plate; the assembly is of a grid type structure and is formed by assembling a plurality of supporting steel plates with holes through cross mortise-tenon joints, and the top of the assembly is set to be in a shape matched with the curved surface shape of the tool molded surface.
In order to enable the tool and the part prefabricated body to have good heat transfer efficiency and temperature distribution uniformity in an autoclave environment and small deformation after heating, the tool main body is designed in a metal frame mode and made of InVar steel (InVar steel).
Further, the top heat dissipation holes are formed in the positions, close to the top, where the supporting steel plate with holes is connected with the molded surface of the tool, and the side face of the supporting steel plate with holes is provided with the side face heat dissipation holes.
Furthermore, a plurality of target ball jacks are uniformly distributed at the edge of the molded surface of the tool and used for assembling the target balls for positioning of the wire laying machine.
Furthermore, the main part one end of butt joint part is provided with flange fixed disc, positioning channel and location accessory, and is a plurality of positioning channel is the radiation state and evenly sets up on the flange fixed disc, the location accessory sets up in the positioning channel. The positioning accessory is used for playing a positioning role in the positioning clamping groove and setting the butt joint component on the automatic wire laying machine.
Furthermore, the positioning accessory (2-3) comprises a central part and four positioning sliding blocks, the central part is used for positioning the central position of a flange plate of the positioning device of the automatic wire laying machine, and the four positioning sliding blocks are matched with the circumferential groove in the central part and the positioning clamping grooves (2-2) to realize circumferential positioning of the flange fixing disc (2-1).
Optionally, a rib plate for enhancing the connection strength between the main body and the flange fixing disc is arranged on the main body of the butt joint component, and a hanging ring hanging hole for connecting the first hanging ring is formed in the rib plate. The first lifting ring is used for lifting the tool to an automatic wire laying machine.
Furthermore, the other end of the main body of the butt joint component is provided with a flange fixing plate for connecting the tool main body, the flange fixing plate is connected with a hoisting column, and the hoisting column is provided with a hoisting ring jack for inserting a circular hoisting ring. The circular hanging ring is used for hoisting the tool to an automatic filament paving machine.
The invention has the beneficial effects that:
the invention relates to a tool for manufacturing a composite material fan blade body characteristic part of an aeroengine, which is compared with the prior art,
1. the butt joint parts are arranged on the two sides of the tool main body, the butt joint parts and the positioning device of the automatic wire laying machine are used for positioning the assembling position, and then the positioning device is fixedly connected with a flange through a bolt, so that the tool can be conveniently erected on the automatic wire laying machine, and the automatic wire laying of the composite material fan blade body characteristic part of the aircraft engine can be realized;
2. designing a tool molded surface based on a pressure surface curved surface of a blade feature part, and ensuring that the tool molded surface is a male die which is convex in the whole area through reasonable edge curve design and curved surface connection design treatment, so that the interference between the tool molded surface and a filament spreading head is avoided;
3. a plurality of target ball jacks are formed in the tool profile and used for assembling target balls for positioning of the wire laying machine, so that the tool profile can be positioned on the automatic wire laying machine;
4. the tool supporting frame is of a grid structure and is provided with top radiating holes and side radiating holes, so that the tool and the part prefabricated body have good heat transfer efficiency and temperature distribution uniformity in an autoclave environment, and deformation after heating is small. The 8 perforated support steel plates are assembled into a nine-grid support structure in a cross-shaped tenon-and-mortise mode, so that uniform support force is provided for the profile of the tool, the rigidity of the profile is ensured, and the thermal deformation of the tool in an autoclave is reduced.
The invention can realize the application of the automatic filament laying process in the manufacturing of the composite material fan blade body, improves the manufacturing efficiency and the contour precision of parts, and can promote the realization of the automation of the manufacturing process of the composite material fan blade body.
Drawings
FIG. 1 is a three-dimensional perspective view of a tooling of the present invention for manufacturing an aircraft engine composite fan blade feature;
FIG. 2 is a top view of the tooling of the present invention for manufacturing an aircraft engine composite fan blade feature;
FIG. 3 is a schematic three-dimensional exploded view of the tooling body of the present invention;
FIG. 4 is a three-dimensional perspective view of the tooling support frame of the present invention;
FIG. 5 is a schematic front view of the perforated support plate of the tool support frame of the present invention;
fig. 6 is a three-dimensional exploded view of the docking component of the present invention.
In the drawings:
1, a tool main body; 2, butting parts;
1-1 tooling profile; 1-2 parts paving area; 1-3 balance area; 1-4 target ball insertion holes; 1-5 tool support frames; 1-6 lifting lugs are provided with pore plates; 1-7 lifting lugs;
1-8 supporting steel plates with holes; 1-9 bottom plates; 1-10 side heat dissipation holes; 1-11 top heat dissipation holes; 1-12 assembling a slot;
2-1, fixing a disc by a flange; 2-2, positioning the clamping groove; 2-3 positioning fittings; 2-4 a first lifting ring; 2-5 hanging ring hanging holes; 2-6 hoisting ring jacks; 2-7 of a circular hanging ring; 2-8 flange fixing plates.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Referring to fig. 1 and 2, the tooling for manufacturing the blade body characteristic part of the composite material fan of the aero-engine, provided by the invention, can be used for forming the blade body characteristic part of the composite material fan of the aero-engine by an automatic fiber laying process, and is formed by connecting a tooling main body 1 facing the automatic fiber laying process and two butt joint parts 2 through flanges. The butt joint component 2 is used for connecting the tool main body 1 and the automatic wire laying machine.
Designing a tool profile 1-1 based on a pressure surface curved surface of a blade feature piece:
firstly, extracting a curved surface of a pressure surface of a blade feature part, and performing extrapolation extension on the boundary of the curved surface by 30mm to obtain a part paving area 1-2 containing a part wire paving allowance curved surface; then based on the boundary curved surface and the curve curvature change trend of the margin area 1-3, tool boundary curve design is carried out on the front, back, left and right side planes of the tool main body, the part overlaying area 1-2 curved surface and the four tool boundaries are filled by using curved surfaces in sequence, the margin area curved surface with continuous tangent lines and without large-angle inward recess is obtained by continuously adjusting the curvature of the tool boundary curve, and finally, the complete tool profile curved surface is obtained.
The fixture molded surface 1-1 is manufactured by using a whole invar steel plate, the central part of the fixture molded surface is a part paving area 1-2, and the boundary dimension of the fixture molded surface is the final dimension of the part. And margin areas 1-3 are arranged around the tool molded surface 1-1 and used for laying margin of the boundary and assembling a vacuum bag. The curved surfaces of the part paving area 1-2 and the allowance area 1-3 are continuously connected by a tangent. 8 target ball jacks 1-4 are uniformly distributed on the edge of the tool molded surface 1-1 and used for assembling target balls used for positioning of the wire laying machine. The tool supporting frame 1-5 is composed of 8 supporting steel plates with holes 1-8, and lifting lug mounting hole plates 1-6 are arranged on two sides and used for assembling the lifting lugs 1-7.
Through design experience and multi-posture statics simulation verification of common composite material component tools, the tool supporting frames 1-5 are designed to be of a grid type structure and are formed by assembling 8 supporting steel plates with holes 1-8 in a cross mortise-tenon mode and then welding the supporting steel plates with holes and bottom plates 1-9. And 1-10 side radiating holes and 1-11 top radiating holes are distributed on 1-8 each perforated support steel plate and are used for improving the temperature distribution uniformity of the tool profile 1-1 in the autoclave. The assembling slots 1-12 in the middle are used for assembling the cross mortise and tenon joints, are used for realizing a grid type structure, provide uniform supporting force for the molded surface of the tool, ensure the rigidity of the molded surface and reduce the thermal deformation of the tool in an autoclave. The tool main body 1 is made of InVar steel, so that the tool and a part prefabricated body have good heat transfer efficiency and temperature distribution uniformity in an autoclave environment, the deformation of the tool and the part prefabricated body is small after the tool and the part prefabricated body are heated, and meanwhile, the metal frame type structure has the advantages of reducing the overall weight of the tool and ensuring the rigidity of the molded surface of the tool.
One end of the butt joint part 2 is provided with a flange fixing disc 2-1, a positioning clamping groove 2-2 and a hanging ring hanging hole 2-5, and the other end is provided with a hanging ring jack 2-6 and a flange fixing plate 2-8 welded and assembled with the tool. The positioning fittings 2-3 are used for positioning in the positioning clamping grooves 2-2, the central parts of the positioning fittings are used for positioning the central positions of the flange plates of the positioning devices of the automatic wire spreading machine, and the four positioning slide blocks around the positioning fittings are used for circumferentially positioning the flange plates, so that the assembly and positioning of the butt joint device and the positioning devices of the automatic wire spreading machine are completed. The first hanging ring 2-4 and the circular hanging ring 2-7 are respectively assembled in the hanging ring hanging hole 2-5 and the hanging ring insertion hole 2-6.
Referring to fig. 3 to 6, in order to enable the tool and the part preform to have good heat transfer efficiency and temperature distribution uniformity in an autoclave environment and to have small deformation after heating, the tool main body 1 is designed in a metal frame type, is made of InVar steel, and comprises a tool profile 1-1 and a tool supporting frame 1-5. The tool supporting frame 1-5 is formed by assembling 8 supporting steel plates with holes 1-8 crossed mortise-tenon joints and welding the assembled supporting steel plates with the holes with the bottom plates 1-9, and the structure has the advantages of reducing the overall weight of the tool and ensuring the rigidity of the molded surface of the tool. And after the integral welding is finished, the tool profile 1-1 is welded and connected, and finally, lifting lug mounting hole plates 1-6 are welded on two sides. The butt joint part 2 is used for connecting the tool and the positioning device of the automatic filament paving machine, one end of the butt joint part is provided with a flange fixing disc 2-1, a positioning clamping groove 2-2 and a hanging ring hanging hole 2-5, and the other end of the butt joint part is provided with a hanging ring jack 2-6 and a flange fixing plate 2-8 welded and assembled with the tool. The first lifting rings 2-4 and the circular lifting rings 2-7 are respectively assembled in lifting ring hanging holes 2-5 and lifting ring insertion holes 2-6, and lifting lugs 1-7 are connected with lifting lug mounting hole plates 1-6 on two sides of the tool main body 1 through flanges.
Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The tooling for manufacturing the fan blade body characteristic part made of the composite material of the aero-engine is characterized by comprising a tooling main body (1) and butt joint parts (2), wherein the left side and the right side of the tooling main body (1) are respectively connected with one butt joint part (2), and the two butt joint parts (2) are jointly used for integrally erecting the tooling on an automatic wire laying machine; the tool main body (1) comprises a tool profile (1-1) and a tool supporting frame (1-5), the central part of the tool profile (1-1) is a part paving area (1-2), the surplus area (1-3) is arranged on the periphery of the part paving area (1-2), and the tool profile (1-1) is arranged on the upper surface of the tool supporting frame (1-5).
2. The tooling for manufacturing the composite fan blade body characteristic part of the aircraft engine according to claim 1, wherein the molding surface (1-1) of the tooling is a male mold with a full-area convex type, and different curved surfaces are continuously connected by adopting a tangent line.
3. The tooling for manufacturing composite fan blade body features for aircraft engines according to claim 2, characterized in that the tooling support frame (1-5) comprises an assembly of steel plates and a base plate (1-9), the assembly being arranged on the base plate (1-9); the assembly is of a grid type structure and is formed by assembling a plurality of supporting steel plates (1-8) with holes through cross mortise and tenon joints, and the top of the assembly is set to be in a shape which is adaptive to the curved surface shape of the tool profile (1-1).
4. The tooling for manufacturing composite fan blade body features of aircraft engines according to claim 3, characterized in that top heat dissipation holes (1-11) are arranged near the top where the perforated support steel plates (1-8) are connected with the tooling profile (1-1), and side heat dissipation holes (1-10) are arranged on the side of the perforated support steel plates (1-8).
5. The tooling for manufacturing an aircraft engine composite fan blade feature of claim 4, wherein the perforated support steel plates (1-8) are invar steel plates.
6. The tooling for manufacturing the composite fan blade body feature of the aircraft engine according to claim 1, wherein a plurality of target ball insertion holes (1-4) are uniformly distributed on the edge of the profile (1-1) of the tooling and used for assembling target balls used for positioning of a thread laying machine.
7. The tooling for manufacturing the composite fan blade body characteristic part of the aero-engine according to claim 1, wherein one end of a main body of the butt joint part (2) is provided with a flange fixing disc (2-1), a positioning clamping groove (2-2) and a positioning accessory (2-3), the plurality of positioning clamping grooves (2-2) are uniformly arranged on the flange fixing disc (2-1) in a radiation state, and the positioning accessory (2-3) is arranged in the positioning clamping groove (2-2).
8. The tooling for manufacturing the composite fan blade body characteristic part of the aero-engine as claimed in claim 7, wherein the positioning fitting (2-3) comprises a central part and four positioning sliding blocks, the central part is used for being positioned to a central position of a flange plate of an automatic filament spreading machine positioning device, and the four positioning sliding blocks are matched with a circumferential groove on the central part and the positioning clamping grooves (2-2) to realize circumferential positioning of the flange fixing disc (2-1).
9. The tooling for manufacturing the composite fan blade body characteristic part of the aircraft engine according to claim 7, wherein a rib plate for enhancing the connection strength of the main body and the flange fixing disc (2-1) is arranged on the main body of the butt joint part (2), and a hanging ring hanging hole (2-5) for connecting the first hanging ring (2-4) is arranged on the rib plate.
10. The tooling for manufacturing the composite fan blade body characteristic part of the aircraft engine according to claim 7, wherein a flange fixing plate (2-8) for connecting the tooling body (1) is arranged at the other end of the main body of the butt joint part (2), a hoisting column is connected to the flange fixing plate (2-8), and a hoisting ring insertion hole (2-6) for inserting the circular hoisting ring (2-7) is arranged on the hoisting column.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111311429.9A CN114030203A (en) | 2021-11-08 | 2021-11-08 | Tooling for manufacturing aeroengine composite material fan blade body characteristic part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111311429.9A CN114030203A (en) | 2021-11-08 | 2021-11-08 | Tooling for manufacturing aeroengine composite material fan blade body characteristic part |
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| Publication Number | Publication Date |
|---|---|
| CN114030203A true CN114030203A (en) | 2022-02-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111311429.9A Pending CN114030203A (en) | 2021-11-08 | 2021-11-08 | Tooling for manufacturing aeroengine composite material fan blade body characteristic part |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103338914A (en) * | 2010-12-07 | 2013-10-02 | 吉凯恩航空服务有限公司 | Method of forming a composite structure comprising a flange |
| CN104401013A (en) * | 2014-10-23 | 2015-03-11 | 西安爱生技术集团公司 | Framework type tooling for molding composite material product autoclave |
| CN205889647U (en) * | 2016-07-07 | 2017-01-18 | 上海卫星装备研究所 | Satellite combined material load tube formwork utensil based on automatic fiber placement forming technology |
| CN108466437A (en) * | 2018-03-28 | 2018-08-31 | 中国航发北京航空材料研究院 | Preparation and its application for the two dimension multidirectional prepreg cloth with flange for containing casing |
-
2021
- 2021-11-08 CN CN202111311429.9A patent/CN114030203A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103338914A (en) * | 2010-12-07 | 2013-10-02 | 吉凯恩航空服务有限公司 | Method of forming a composite structure comprising a flange |
| CN104401013A (en) * | 2014-10-23 | 2015-03-11 | 西安爱生技术集团公司 | Framework type tooling for molding composite material product autoclave |
| CN205889647U (en) * | 2016-07-07 | 2017-01-18 | 上海卫星装备研究所 | Satellite combined material load tube formwork utensil based on automatic fiber placement forming technology |
| CN108466437A (en) * | 2018-03-28 | 2018-08-31 | 中国航发北京航空材料研究院 | Preparation and its application for the two dimension multidirectional prepreg cloth with flange for containing casing |
Non-Patent Citations (2)
| Title |
|---|
| 石林: "自动铺丝束在航空工业中的应用现状", 《航空制造工程》 * |
| 谢富原: "《先进复合材料制造技术》", 30 September 2017, 航空工业出版社 * |
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Application publication date: 20220211 |