CN112277343A - Composite material blade edge covering method and structure - Google Patents
Composite material blade edge covering method and structure Download PDFInfo
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- CN112277343A CN112277343A CN202011060393.7A CN202011060393A CN112277343A CN 112277343 A CN112277343 A CN 112277343A CN 202011060393 A CN202011060393 A CN 202011060393A CN 112277343 A CN112277343 A CN 112277343A
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- 239000002131 composite material Substances 0.000 title claims abstract description 64
- 238000000034 method Methods 0.000 title claims abstract description 26
- 229910052751 metal Inorganic materials 0.000 claims abstract description 51
- 239000002184 metal Substances 0.000 claims abstract description 50
- 239000003365 glass fiber Substances 0.000 claims description 8
- 239000003292 glue Substances 0.000 claims description 7
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 6
- 238000004026 adhesive bonding Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 238000003825 pressing Methods 0.000 claims description 6
- 238000007731 hot pressing Methods 0.000 claims description 3
- 238000009957 hemming Methods 0.000 claims 2
- 238000007723 die pressing method Methods 0.000 claims 1
- 238000003780 insertion Methods 0.000 description 4
- 230000037431 insertion Effects 0.000 description 4
- 238000013461 design Methods 0.000 description 3
- 239000006185 dispersion Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 239000007769 metal material Substances 0.000 description 3
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000000805 composite resin Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 238000009991 scouring Methods 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000013585 weight reducing agent Substances 0.000 description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000032798 delamination Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229920001568 phenolic resin Polymers 0.000 description 1
- 239000005011 phenolic resin Substances 0.000 description 1
- 239000004814 polyurethane Substances 0.000 description 1
- 229920005749 polyurethane resin Polymers 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Images
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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
- B29C70/845—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined by moulding material on a relative small portion of the preformed parts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J15/00—Riveting
- B21J15/02—Riveting procedures
-
- 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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/74—Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding
- B29C70/76—Moulding on edges or extremities of the preformed part
- B29C70/763—Moulding on edges or extremities of the preformed part the edges being disposed in a substantial flat plane
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
- F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The composite material blade edge covering method and structure includes dividing the edge covering of the blade into two parts, and protecting the edge of the blade with metal covering in the front edge and composite material covering in the blade tip and the back edge. The invention adopts different edge covering modes aiming at the stress conditions of different parts of the blade, adopts metal edge covering at the front edge of the blade, and adopts composite material edge covering at the blade tip and the rear edge of the blade, thereby better adapting to the use environment of the blade, and improving the operation efficiency compared with the metal edge covering of the whole blade.
Description
Technical Field
The invention designs a wrapping method and a structure, and particularly relates to a composite material blade wrapping method and a composite material blade wrapping structure.
Background
For a turbine fan, a remarkable weight reduction effect can be obtained by adopting the composite material blade. Most of the existing composite material blades adopt a prepreg integral molding structure. In the process of rapid rotation of the blade, the blade is impacted and corroded by water drops and sand dust, and physical defects such as pores and delamination of prepreg easily occur at the edge of the blade, so that the weak point of strength is formed. Therefore, composite blades generally need to have a covered edge designed to protect the blade edge. The traditional composite material blade edge covering mostly adopts the integral structure design of metal materials, however, the thermal expansion coefficient difference of metal and composite material is large, internal stress is easily generated in the process of high and low temperature environment change, and meanwhile, the impact energy born by the metal edge covering cannot be well dispersed, so that the reliability of the edge covering is weakened. In addition, the front edge of the blade is subjected to larger external force impact, so the front edge has higher tolerance requirements than the blade tip and the rear edge, and the front edge needs to be subjected to edge wrapping design with stronger impact resistance.
For example, application No. 201710372747.3, entitled "hybrid structure aircraft engine fan blade", discloses a hybrid structure aircraft engine fan blade that includes a metal leading edge panel and a composite portion that are integrally combined in an interfacing manner. The hybrid structure aircraft engine fan blade can effectively give consideration to the strength performance and the weight reduction effect, reduces the difficulty of the processing technology of the traditional composite material fan blade, and is a development direction with light weight and large bypass ratio and very promising than the fan blade.
As another example, application No. 201620774541.4, entitled "a resin-based composite material fan stator blade structure", discloses a resin-based composite material fan stator blade structure, in which an upper edge plate, a blade body, and a lower edge plate are integrally formed, the upper edge plate, the blade body, and the lower edge plate are all made of composite material, the upper edge plate is provided with two insertion pieces, the axes of the insertion pieces and the axis of the blade body are parallel to each other, and the insertion pieces are connected with a clamping groove of an engine central shaft through the insertion pieces; two ends of the lower edge plate are provided with two-stage step-shaped bulges which are connected with corresponding sockets on the engine case; the blade body surface covering is made of glass fiber composite materials, the front edge of the blade body is glued with a titanium alloy wrapping structure, the inside of the blade body is formed by pressing carbon fiber composite material laminated plates, and the heights of the carbon fiber composite material laminated plates are sequentially and symmetrically reduced from inside to outside. The utility model provides an engine metal blade weight big, the poor scheduling problem of fatigue resistance ability. The loss of the blade caused by aerodynamic shape change in the working state is reduced, and therefore the overall efficiency of the engine is improved.
In the scheme, only the front edge part of the blade is covered, and other edge parts have no extra protective measures, so that the covering scheme needs to be improved in order to protect the blade edge in an all-round manner.
Disclosure of Invention
The invention provides a composite material blade edge covering method and a composite material blade edge covering structure aiming at the problem that the existing composite material blade edge covering method and structure cannot provide good protection for the blade edge.
The technical means adopted by the invention to solve the problems are as follows: the composite material blade edge covering method includes the steps of dividing the edge covering of the blade into two parts, and protecting the edge of the blade in the mode of metal edge covering at the front edge part of the blade and composite material edge covering at the blade tip and the rear edge part of the blade.
Further, the metal edge of the front edge part of the blade is connected with the blade in a mode of combining gluing and riveting.
Furthermore, the edge of the metal edge cover adopts a fan blade-shaped structure.
Furthermore, the composite material wrapping edges of the blade tip and the blade trailing edge are connected with the composite material blade in an integrated forming mode by pre-paving the prepreg in a die cavity.
A composite material blade edge covering structure comprises a metal edge covering at the front edge of a blade, a blade tip and a composite material edge covering at the rear edge of the blade.
Furthermore, the edge of the metal edge cover adopts a fan blade-shaped structure.
Furthermore, the length of each fan blade is 30mm-80mm, and the maximum interval between the fan blades is 1mm-8 mm.
Furthermore, the metal wrapping edge is connected with the blade in a mode of combining gluing and riveting.
Further, the gluing adopts a vacuum bag pressing process.
Further, the width of the metal edge cover is 20mm-100 mm.
Furthermore, the metal wrapping material is titanium alloy, and is formed through a hot pressing process.
Furthermore, the rivets for riveting the metal edge cover are uniformly distributed, and the interval between the rivets is 30mm-200 mm.
Further, the rivet is located in the middle of the fan blade and is 10mm-50mm away from the edge of the metal wrapping edge.
Furthermore, the composite material edge covers are formed integrally with the blades by pre-paving and sticking prepreg in a die cavity.
Furthermore, the composite material wrapping material is a double-shaft glass fiber prepreg, and the composite material wrapping material is formed through a mould pressing process.
Furthermore, the composite material edge covering adopts a 2-6-layer prepreg lap joint structure.
Furthermore, the width of the innermost layer of the composite material wrapping edge is 20-50mm, the width of the outermost layer of the composite material wrapping edge is 30-100mm, and the difference between the overlapping edges of the two adjacent layers is 5-20 mm.
The invention has the beneficial effects that:
1. the invention adopts different edge covering modes aiming at the stress conditions of different parts of the blade, adopts metal edge covering at the front edge of the blade, and adopts composite material edge covering at the blade tip and the rear edge of the blade, thereby better adapting to the use environment of the blade, and improving the operation efficiency compared with the metal edge covering of the whole blade.
2. The metal wrapping edge at the front edge of the blade adopts a fan blade shape, so that the structure greatly reduces the internal stress between the metal wrapping edge and the composite material blade, is more favorable for the dispersion of the impact force of the wrapping edge, improves the anti-scouring capability of the blade, and greatly improves the safety of the blade.
3. According to the invention, the metal wrapping edge is bonded by gluing and riveting, so that the bonding force between the metal wrapping edge and the blade is improved, and the quality of the wrapping edge is ensured; the composite material edge is integrally formed by adopting a die, so that the operation is simple, safe and reliable.
Drawings
FIG. 1 is a schematic view of a blade configuration;
FIG. 2 is a schematic view of a structure of a covering edge on a blade according to an embodiment;
FIG. 3 is a schematic view of a metal covering structure;
FIG. 4 is a partially enlarged schematic view of FIG. 3;
1. the blade comprises a blade, 11 parts of a blade leading edge, 12 parts of a blade tip, 13 parts of a blade trailing edge, 14 parts of a blade root, 2 parts of a metal wrapping edge, 3 parts of a composite material wrapping edge and 4 parts of rivets.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
In the present invention, as shown in fig. 1, the blade leading edge 11 refers to the windward side edge of the blade 1 when the blade rotates; the blade trailing edge 13 refers to the leeward side edge when the blade 1 rotates; the blade root 14 refers to the part of the blade 1 connected with the rotating shaft; the blade tip 12 refers to the edge on the opposite side of the blade root 14.
Example one
A composite material blade edge covering structure is shown in figure 2 and comprises a metal edge covering 2 at the front edge 11 of a blade, a blade tip 12 and a composite material edge covering 3 at the rear edge 13 of the blade.
As shown in figure 3, the edge of the metal binding 2 adopts a fan blade-shaped structure, and the width W of the metal binding 2 of the blade front edge 11 is 20-100 mm. By adopting the fan blade-shaped structure, the internal stress between the metal wrapping edge 2 and the composite material blade 1 is greatly reduced, the dispersion of the impact force of the metal wrapping edge 2 is more facilitated, the anti-scouring capability of the blade 1 is improved, and the safety performance of the blade 1 is greatly improved. As shown in FIG. 4, the length L of each fan blade is 30-80mm, and the maximum distance D between two adjacent fan blades is 1-8 mm. By reasonably selecting the shape of the metal wrapping edge 2, the internal stress dispersion effect of the blade 1 is optimal, and meanwhile, the energy can be better dispersed when external impact is resisted.
The metal wrapping 2 is made of titanium alloy and is formed through a hot pressing process. And the metal edge cover 2 and the blade front edge 11 are connected into a whole by adopting a fixing mode of combining glue joint and riveting joint. Wherein, the glue joint adopts epoxy structure glue and adopts vacuum bag pressing process to improve the glue joint quality. And when riveting, the titanium alloy rivet 4 is selected and fixed by adopting a pulling rivet process. As shown in figure 3, the rivets 4 are uniformly distributed on the metal wrapping edge 2, the interval between the rivets is 30mm-200mm, and as shown in figure 3, the rivets 4 are positioned in the middle of the fan-blade shape of the metal wrapping edge 2 and are 10-50mm away from the edge of the metal wrapping edge 2. The combination quality of the metal wrapping 2 and the blade 1 is improved by reasonably selecting the position of the rivet.
The composite material wrapping 3 is made of a double-shaft glass fiber prepreg and is formed by adopting a mould pressing process. And the composite material bordures 3 and the combination mode of blade and adopts the mould integrated into one piece, namely lay the glass fibre prepreg of biax in advance in the mould die cavity of blade 1 in the position that blade trailing edge 13 and apex 12 need bordure, combine directly in the shaping process of blade 1. The composite material wrapping edge 3 is of a 2-6-layer double-shaft glass fiber prepreg lap joint structure, the width of the innermost layer is 20-50mm, the width of the outermost layer is 30-100mm, the difference between the lap joint edges of the two adjacent layers is 5-20mm, the bonding quality between each layer and the blade 1 is guaranteed, and the edge of the blade tip 12 and the edge of the blade trailing edge 13 is protected to the maximum. The integrally-formed mode is simple to operate, safe and reliable, and improves the edge covering efficiency and quality of the blade 1.
Example two
In this embodiment, the metal covering edge 2 may be made of other metal materials such as stainless steel.
EXAMPLE III
In this embodiment, other adhesives such as polyurethane and phenolic resin may be used for the adhesive bonding.
Example four
In this embodiment, the riveting method may adopt other methods such as stamping.
The embodiment also relates to a composite material blade edge covering method, wherein the edge covering of the front edge 11, the blade tip 12 and the rear edge 13 of the blade is carried out in two different modes, wherein the front edge 11 of the blade is made of metal such as titanium alloy and stainless steel, the edge covering 2 is made of metal, and the blade tip 12 and the rear edge 13 of the blade are made of composite material of biaxial glass fiber prepreg, and the edge covering 4 is made of composite material. The metal wrapping 2 is connected to the front edge 11 of the blade in a mode of combining glue joint and riveting, and the composite material wrapping 3 is arranged at the blade tip 12 and the rear edge 13 of the blade in a mode of laying double-shaft glass fiber prepreg in a mold cavity and integrally forming with the blade 1. According to the different conditions of different external forces borne by different parts of the blade 1, different edge covering modes are adopted, so that the whole blade 1 is effectively protected, and the edge covering operation efficiency is improved.
The above embodiments are provided for illustrative purposes only and not for limiting the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and therefore all equivalent technical solutions should fall within the scope of the present invention, and the scope of the present invention should be defined by the claims.
Claims (10)
1. A composite material blade edge covering method is characterized in that: the edge of the blade (1) is divided into two parts, the metal edge (2) is adopted at the front edge (11) of the blade, and the composite material edge (3) is adopted at the blade tip (12) and the rear edge (13) of the blade to protect the edge of the blade (1).
2. A method of hemming a composite blade according to claim 1 wherein: the metal wrapping edges (2) of the front edge (11) of the blade are connected with the blade (1) in a mode of combining glue joint and riveting;
the composite material covered edge (3) of the blade tip (12) and the blade trailing edge (13) is connected with the composite material blade (1) in an integrated forming mode by pre-paving and sticking prepreg in a die cavity.
3. A method of hemming a composite blade according to claim 1 wherein: the edge of the metal wrapping (2) adopts a fan blade structure.
4. The utility model provides a combined material blade structure of borduring which characterized in that: comprises a metal edge covering (2) at the front edge (11) of the blade, a blade tip (12) and a composite material edge covering (3) at the rear edge (13) of the blade.
5. The composite blade edge banding structure of claim 4, wherein: the edge of the metal wrapping (2) adopts a fan-blade-shaped structure;
the length of each fan blade is 30mm-80mm, and the maximum interval between the fan blades is 1mm-8 mm.
6. The composite blade edge banding structure of claim 5, wherein: the metal wrapping (2) is connected with the blade (1) in a mode of combining glue joint and riveting;
the composite material edge (3) is formed by pre-paving and sticking a prepreg in a die cavity in advance and integrally forming with the blade (1).
7. The composite blade edge banding structure of claim 6 wherein: the gluing adopts a vacuum bag pressing process;
the composite material edge covering (3) adopts a 2-6-layer prepreg lap joint structure.
8. The composite blade edge banding structure of claim 6 wherein: rivets (4) for riveting the metal wrapping edges (2) are uniformly distributed, and the interval between the rivets (4) is 30-200 mm;
the rivet (4) is positioned in the middle of the fan blade and is 10mm-50mm away from the edge of the metal wrapping edge (2).
9. The composite blade edge banding structure of claim 4, wherein: the width of the metal wrapping (2) is 20mm-100 mm;
the width of the innermost layer of the composite material wrapping edge (3) is 20-50mm, the width of the outermost layer is 30-100mm, and the difference of the overlapped edges of the two adjacent layers is 5-20 mm.
10. The composite blade edge banding structure of claim 4, wherein: the metal wrapping (2) is made of titanium alloy and is formed by a hot pressing process;
the composite material wrapping (3) is made of a biaxial glass fiber prepreg and is formed through a die pressing process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011060393.7A CN112277343A (en) | 2020-09-30 | 2020-09-30 | Composite material blade edge covering method and structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011060393.7A CN112277343A (en) | 2020-09-30 | 2020-09-30 | Composite material blade edge covering method and structure |
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| CN112277343A true CN112277343A (en) | 2021-01-29 |
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| CN202011060393.7A Pending CN112277343A (en) | 2020-09-30 | 2020-09-30 | Composite material blade edge covering method and structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415003A (en) * | 2021-06-30 | 2021-09-21 | 中国航空制造技术研究院 | Woven composite material fan blade and forming method thereof |
| CN113843933A (en) * | 2021-08-24 | 2021-12-28 | 株洲时代新材料科技股份有限公司 | Manufacturing method of edge covering for composite material blade, product and composite material blade |
| CN113858652A (en) * | 2021-08-26 | 2021-12-31 | 中航复合材料有限责任公司 | Edge covering structure and process without folds for composite material skirt board of railway vehicle equipment compartment |
| CN114131945A (en) * | 2021-11-05 | 2022-03-04 | 湖南弘辉科技有限公司 | Metal edge covering method and device for high-speed fan blade |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109989938A (en) * | 2019-03-22 | 2019-07-09 | 中国科学院工程热物理研究所 | A kind of fan blade of aero-engine and preparation method thereof |
-
2020
- 2020-09-30 CN CN202011060393.7A patent/CN112277343A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109989938A (en) * | 2019-03-22 | 2019-07-09 | 中国科学院工程热物理研究所 | A kind of fan blade of aero-engine and preparation method thereof |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415003A (en) * | 2021-06-30 | 2021-09-21 | 中国航空制造技术研究院 | Woven composite material fan blade and forming method thereof |
| CN113415003B (en) * | 2021-06-30 | 2022-11-11 | 中国航空制造技术研究院 | Woven composite material fan blade and forming method thereof |
| CN113843933A (en) * | 2021-08-24 | 2021-12-28 | 株洲时代新材料科技股份有限公司 | Manufacturing method of edge covering for composite material blade, product and composite material blade |
| CN113858652A (en) * | 2021-08-26 | 2021-12-31 | 中航复合材料有限责任公司 | Edge covering structure and process without folds for composite material skirt board of railway vehicle equipment compartment |
| CN113858652B (en) * | 2021-08-26 | 2023-06-16 | 中航复合材料有限责任公司 | Non-fold edge wrapping structure and process for composite material apron board of equipment compartment of railway vehicle |
| CN114131945A (en) * | 2021-11-05 | 2022-03-04 | 湖南弘辉科技有限公司 | Metal edge covering method and device for high-speed fan blade |
| CN114131945B (en) * | 2021-11-05 | 2023-07-25 | 湖南弘辉科技有限公司 | High-speed fan blade metal edge-covering and edge-covering method and edge-covering device |
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