CN113263250A - Composite manufacturing method of metal reinforcing edge of aircraft engine fan blade - Google Patents
Composite manufacturing method of metal reinforcing edge of aircraft engine fan blade Download PDFInfo
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- CN113263250A CN113263250A CN202110426921.4A CN202110426921A CN113263250A CN 113263250 A CN113263250 A CN 113263250A CN 202110426921 A CN202110426921 A CN 202110426921A CN 113263250 A CN113263250 A CN 113263250A
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- fan blade
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- prefabricated part
- metal reinforcing
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- 229910052751 metal Inorganic materials 0.000 title claims abstract description 42
- 239000002184 metal Substances 0.000 title claims abstract description 42
- 230000003014 reinforcing effect Effects 0.000 title claims abstract description 37
- 239000002131 composite material Substances 0.000 title claims abstract description 24
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 23
- 238000009792 diffusion process Methods 0.000 claims abstract description 32
- 238000003466 welding Methods 0.000 claims abstract description 30
- 238000005520 cutting process Methods 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims abstract description 8
- 230000002787 reinforcement Effects 0.000 claims description 6
- 229910045601 alloy Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 4
- 239000010935 stainless steel Substances 0.000 claims description 4
- 229910001220 stainless steel Inorganic materials 0.000 claims description 4
- 238000007731 hot pressing Methods 0.000 claims description 3
- 229910000679 solder Inorganic materials 0.000 claims description 3
- 238000005452 bending Methods 0.000 claims 1
- 238000012545 processing Methods 0.000 abstract description 8
- 238000004904 shortening Methods 0.000 abstract 1
- 238000000034 method Methods 0.000 description 10
- 238000007789 sealing Methods 0.000 description 7
- 230000000903 blocking effect Effects 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 238000000638 solvent extraction Methods 0.000 description 4
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 208000025274 Lightning injury Diseases 0.000 description 1
- 230000003044 adaptive effect Effects 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000003856 thermoforming Methods 0.000 description 1
- 229920001169 thermoplastic Polymers 0.000 description 1
- 239000004416 thermosoftening plastic Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/02—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by means of a press ; Diffusion bonding
- B23K20/023—Thermo-compression bonding
- B23K20/026—Thermo-compression bonding with diffusion of soldering material
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
本发明涉及一种航空发动机风扇叶片金属加强边的复合制造方法，包括根据风扇叶片形状确定金属加强边的几何形状模型，然后将几何形状模型的两端进行延伸，并将延伸后的几何模型划分为第一预制件模型和第二预制件模型，得到第一预制件和第二预制件；将风扇叶片形状的两端进行延伸得到芯模模型，然后将芯模模型划分为多个分块模型，制作分块件和芯模；将第一预制件和第二预制件贴合在芯模的两侧，芯模与第一预制件和第二预制件通过销钉进行固定，形成整体结构；将整体结构放置到真空扩散焊炉中进行扩散焊接；切除焊接后整体结构两端具有销钉的延伸部分。与现有技术相比，本发明具有提高材料利用率、缩短加工周期，大幅降低切削加工的难度等优点。
The invention relates to a composite manufacturing method for a metal reinforcing edge of an aero-engine fan blade. For the first prefabricated part model and the second prefabricated part model, the first prefabricated part and the second prefabricated part are obtained; the two ends of the fan blade shape are extended to obtain the core model model, and then the core model model is divided into multiple block models , make the divided parts and the core mold; the first preform and the second preform are attached to both sides of the core mold, and the core mold and the first preform and the second preform are fixed by pins to form an integral structure; The integral structure is placed in a vacuum diffusion welding furnace for diffusion welding; after welding, the extended parts with pins at both ends of the integral structure are cut off. Compared with the prior art, the present invention has the advantages of improving the utilization rate of materials, shortening the processing cycle, and greatly reducing the difficulty of cutting.
Description
Technical Field
The invention relates to the field of manufacturing of thin-wall deep-cavity reinforcing edges, in particular to a composite manufacturing method of a metal reinforcing edge of a fan blade of an aero-engine.
Background
The carbon fiber composite fan blade has the advantages of light weight, low noise, strong anti-flutter performance and the like, and becomes the mainstream choice of commercial aircraft engines. However, the front edge of the composite material blade has the defects of impact resistance, compression resistance, lightning stroke resistance and the like compared with the metal blade, and the overall performance of the composite material blade can be obviously improved by adding the titanium alloy wrapping edge on the front edge of the composite material blade.
In order to adapt to the shape of the front edge of the composite fan blade, the titanium alloy reinforcing edge is often provided with a complex deep-cavity thin-wall special-shaped structure. If the whole reinforcing edge is machined by a cutting method, the material utilization rate is low, the machining time is long, and a cutter with a small diameter is easy to be unstable in the process of machining a deep cavity structure, so that the rejection rate is high.
For example, the invention patent with the publication number of CN109483183B discloses a method for manufacturing a metal reinforcing edge of a composite fan blade of an aeroengine. Firstly, cutting and processing two prefabricated parts, then directly welding two sides of the prefabricated parts, welding two ends of the prefabricated parts through sealing parts to obtain a hollow structure, arranging a core mold which is only used as a support in an inner cavity formed by the prefabricated parts, and then carrying out integral welding reinforcement through a high-temperature pressure maintaining device; and finally, taking down the sealing parts at the two ends, cutting off one unnecessary side, and taking out the core mold to obtain the metal reinforcing side. However, this method has the following disadvantages: 1. the steps are tedious and require first initial welding and subsequent welding reinforcement. Meanwhile, the prefabricated member needs to be welded with a sealing structure through argon arc welding, the sealing structure comprises two prefabricated members, a core mold, two sealing members and the like, and the core mold, the prefabricated members and the sealing members are made of different materials, so that the argon arc welding is difficult. 2. The welding reinforcement is carried out through the vent pipe and the high-temperature pressure maintaining device of the sealing element, the welding reinforcement is difficult to realize basically, and the quality of a connecting interface cannot be guaranteed. 3. It cannot be used to manufacture metal reinforcing edges with large length and deep thin-wall and deep cavities.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a composite manufacturing method of a metal reinforcing edge of an aircraft engine fan blade.
The purpose of the invention can be realized by the following technical scheme:
a composite manufacturing method of a metal reinforcing edge of an aircraft engine fan blade is characterized in that the metal reinforcing edge is of a special-shaped metal thin-wall structure with a narrow deep cavity, and the composite manufacturing method comprises the following steps:
determining a geometric shape model of the metal reinforcing edge according to the shape of the fan blade, extending two ends of the geometric shape model, and dividing the extended geometric shape model into a first prefabricated part model and a second prefabricated part model;
cutting a material plate according to the first prefabricated part model and the second prefabricated part model to obtain a blank piece, and carrying out hot pressing on the blank piece to obtain a first prefabricated part and a second prefabricated part;
extending two ends of the fan blade shape to obtain a core mold model, and dividing the core mold model into a plurality of block models;
manufacturing a partitioning piece according to the partitioning model, and then splicing the partitioning piece to obtain a core mold;
attaching the first prefabricated member and the second prefabricated member to two sides of a core mold, and fixing the core mold, the first prefabricated member and the second prefabricated member through pins to form an integral structure;
placing the integral structure into a vacuum diffusion welding furnace for diffusion welding;
and cutting off the extending part with the pins at two ends of the welded integral structure, and taking out the core mold to obtain the metal reinforcing edge.
Furthermore, the blocking pieces of the core mould are connected through a chimeric structure.
Further, each piece outer layer of the core mold is coated with a solder resist.
And the shape of the inner cavity of the diffusion connection module is consistent with the outer surface profile of the metal reinforcing edge after the two ends of the metal reinforcing edge extend, and the integral structure is placed into the inner cavity of the diffusion connection module and then placed into a vacuum diffusion welding furnace for diffusion welding.
Further, the core mold has at least three pieces of the divided pieces.
Further, the partition of the core mold is a bent portion, a portion of which the circumferential dimension changes, or a set length portion of the fan blade shape.
Further, the lengths of the first preform and the second preform are less than or equal to the length of the core mold.
Further, the core mold is made of heat-resistant stainless steel or high-temperature alloy.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention simplifies the manufacturing process of the metal reinforcing edge of the fan blade, adopts a composite method of thermoplastic processing and diffusion welding, can obviously improve the material utilization rate, shorten the processing period, greatly reduce the difficulty of cutting processing, and has obvious cost and efficiency advantages.
2. According to the invention, the two prefabricated parts and the partitioned core mold form an integral structure, and the integral structure can be directly placed into a vacuum diffusion welding furnace mature in the prior art for diffusion welding, so that the two prefabricated parts form the integral structure, a heating and pressurizing device is not required to be additionally arranged, only one welding procedure is required, the operation is convenient, and the processing effect is good.
3. The integral structure can be arranged in a diffusion connection die and then placed in a vacuum diffusion welding furnace, so that the forming precision of the outer surface of the metal reinforcing edge is improved.
4. The core mold is of a structure of a partitioning piece and is connected with the prefabricated piece through a pin, after welding is completed, the core mold can be conveniently taken out only by cutting redundant extension parts on two sides of the integral structure, a finished product of the metal reinforcing edge is obtained, and production efficiency is high. The blocking pieces can be directly made into fan blade shapes and are mutually embedded and connected, the fan blade shape cutting device is suitable for metal reinforcing edges with large length, cutting processing only relates to the blocking pieces at two ends, the blocking pieces in the middle can be repeatedly used, and the material utilization rate is high.
5. The core mold is made of heat-resistant stainless steel or high-temperature alloy, so that deformation in the diffusion connection process is avoided, and the forming precision of the inner cavity of the metal reinforcing edge is ensured.
Drawings
FIG. 1 is a view of the construction of a complex narrow deep cavity profiled thin wall of the metal reinforcing rim of this example.
FIG. 2 is a schematic representation of the shape of the preform of this example.
FIG. 3 is a schematic of the preform thermoforming process.
Fig. 4 is a schematic structural view of the core mold.
FIG. 5 is a schematic view of the overall structure of the preform and core die assembly.
Fig. 6 is a schematic view of the structure of the integrated structure in the diffusion bonding mold.
Reference numerals: 1. metal reinforcing edge, 11, inner cavity, 2, first prefabricated part, 3, second prefabricated part, 4, 41, blocking part, 5, diffusion bonding mould.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments. The present embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation manner and a specific operation process are given, but the scope of the present invention is not limited to the following embodiments.
In order to ensure the aerodynamic performance, the composite material fan blade of the aircraft engine generally has a complex streamline shape, so as shown in fig. 1, the metal reinforcing edge 1 of the fan blade also needs to have a complex space geometry and is generally in a narrow deep-cavity special-shaped thin-wall structure. The fan blades of the composite material are tightly connected with the inner cavity 11 of the metal reinforcing edge 1 in a gluing mode and the like. The process of manufacturing the metal reinforcing flange 1 of the present invention will be described in detail.
Firstly, determining a geometric shape model of the metal reinforcing edge 1 according to the shape of the adaptive fan blade, then extending two ends of the geometric shape model, and dividing the extended geometric shape model into a first prefabricated part 2 model and a second prefabricated part 3 model. Meanwhile, the core mold model is obtained by extending both ends of the fan blade shape, and then the core mold model is divided into a plurality of block models. The block models have a jogged structure between them, and the segment is generally selected at the bend of the shape, the change of the circumferential dimension or the set length. The number of the blocks is generally equal to or greater than three, and three are preferred in the embodiment. Pin holes are arranged at two ends of the core model. This step may employ, but is not limited to, computer-aided CAD design.
And secondly, cutting a material plate according to the model of the first prefabricated part 2 and the model of the second prefabricated part 3 to obtain a first blank part and a second blank part, and performing hot pressing on the blank parts to obtain the first prefabricated part 2 and the second prefabricated part 3, wherein the shape of the blank parts is as close to that of the prefabricated parts as possible on the premise of easy forming. Then, hot press forming is performed through a mold, and finally, a first preform 2 and a second preform 3 are obtained, as shown in fig. 2 and 3.
Third, as shown in fig. 4, the block pieces 4 are manufactured according to the block model, and then the block pieces 41 are assembled to obtain the core mold 4. The core mold 4 is made of heat-resistant stainless steel or high-temperature alloy, and can prevent deformation in subsequent processing. And meanwhile, the outer layer of each block piece 41 is coated with solder resist, so that the block pieces are prevented from being welded with the prefabricated member.
And fourthly, as shown in fig. 5, attaching the first preform 2 and the second preform 3 to both sides of the core mold 4, and fixing the core mold 4 and the first preform 2 and the second preform 3 by pins to form an integral structure. The first preform and the second preform generally have a length less than or equal to the length of the core mold, which in this embodiment is the same.
And fifthly, placing the integral structure into an existing vacuum diffusion welding furnace for diffusion welding. The core mold 4 not only supports the first preform 2 and the second preform 3, but also shapes both preforms and ensures the accuracy and quality of the inner surfaces thereof.
And sixthly, cutting off the extending part with the pin at the two ends of the integral structure. After the diffusion bonding is completed, the entire structure is taken out, the extending portions at both ends are cut off, the core mold 4 is taken out, and the metal reinforcing flange 11 is finally obtained. The cutting-off is not limited, and wire cutting is preferably used.
In another embodiment, as shown in fig. 6, a diffusion bonding mold 5 may be designed during the manufacturing process, and the mold has a top and bottom mold structure, and the top and bottom molds form a cavity shape after being closed. The shape of the inner cavity is consistent with the outline of the outer surface of the metal reinforcing edge 1 after the two ends extend. The integral structure formed by splicing the prefabricated member and the core mold 4 is placed into an inner cavity of the diffusion connection module and then placed into a vacuum diffusion welding furnace for diffusion welding. The diffusion bonding mold 5 applies pressure to the first preform 2 and the second preform 3 to complete the diffusion bonding process, and shapes the two preforms and ensures the accuracy and quality of the outer surfaces thereof.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110426921.4A CN113263250B (en) | 2021-04-20 | 2021-04-20 | Composite manufacturing method of metal reinforced edge of aircraft engine fan blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110426921.4A CN113263250B (en) | 2021-04-20 | 2021-04-20 | Composite manufacturing method of metal reinforced edge of aircraft engine fan blade |
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| CN113263250A true CN113263250A (en) | 2021-08-17 |
| CN113263250B CN113263250B (en) | 2022-07-19 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113751976A (en) * | 2021-09-29 | 2021-12-07 | 上海交通大学 | Manufacturing method of titanium alloy reinforcing edge of leading edge of composite fan blade of aero-engine |
| CN114535935A (en) * | 2022-02-23 | 2022-05-27 | 上海涵鲲科技有限公司 | Metal edge sealing of fan blade and processing method thereof |
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| US20090246446A1 (en) * | 2008-03-28 | 2009-10-01 | Rolls-Royce Plc | Article formed from a composite material |
| US20120255176A1 (en) * | 2009-12-23 | 2012-10-11 | Snecma | Method for producing a metal reinforcement for a turbine engine blade |
| CN103429780A (en) * | 2011-03-01 | 2013-12-04 | 斯奈克玛 | Method for producing a metal component such as a turbomachine blade reinforcement |
| CN104364031A (en) * | 2012-06-01 | 2015-02-18 | 斯奈克玛 | Method of producing a metal reinforcement for a turbine engine blade |
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| CN109723671A (en) * | 2017-10-27 | 2019-05-07 | 中国航发商用航空发动机有限责任公司 | A kind of composite material fan blade metal reinforces the manufacturing method on side |
| CN110439623A (en) * | 2019-08-14 | 2019-11-12 | 上海两擎机电科技合伙企业(有限合伙) | Aircraft engine fan blade metal hemming edge, processing tool and processing method |
| CN111037938A (en) * | 2018-10-15 | 2020-04-21 | 中国航发商用航空发动机有限责任公司 | Hybrid structure blade, manufacturing method and sewing positioning clamp |
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2021
- 2021-04-20 CN CN202110426921.4A patent/CN113263250B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090246446A1 (en) * | 2008-03-28 | 2009-10-01 | Rolls-Royce Plc | Article formed from a composite material |
| CN101418811A (en) * | 2008-09-03 | 2009-04-29 | 中国航空工业第一集团公司北京航空材料研究院 | Hollow fan blade for aircraft engine |
| US20120255176A1 (en) * | 2009-12-23 | 2012-10-11 | Snecma | Method for producing a metal reinforcement for a turbine engine blade |
| CN103429780A (en) * | 2011-03-01 | 2013-12-04 | 斯奈克玛 | Method for producing a metal component such as a turbomachine blade reinforcement |
| CN104364031A (en) * | 2012-06-01 | 2015-02-18 | 斯奈克玛 | Method of producing a metal reinforcement for a turbine engine blade |
| CN206796414U (en) * | 2017-06-05 | 2017-12-26 | 山东帅信电气有限公司 | Splice type pressure injection particular manufacturing craft |
| CN109723671A (en) * | 2017-10-27 | 2019-05-07 | 中国航发商用航空发动机有限责任公司 | A kind of composite material fan blade metal reinforces the manufacturing method on side |
| CN111037938A (en) * | 2018-10-15 | 2020-04-21 | 中国航发商用航空发动机有限责任公司 | Hybrid structure blade, manufacturing method and sewing positioning clamp |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113751976A (en) * | 2021-09-29 | 2021-12-07 | 上海交通大学 | Manufacturing method of titanium alloy reinforcing edge of leading edge of composite fan blade of aero-engine |
| CN114535935A (en) * | 2022-02-23 | 2022-05-27 | 上海涵鲲科技有限公司 | Metal edge sealing of fan blade and processing method thereof |
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| CN113263250B (en) | 2022-07-19 |
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