CN106513675A - Laser additive manufacturing forming method of titanium alloy thin-walled component - Google Patents
Laser additive manufacturing forming method of titanium alloy thin-walled component Download PDFInfo
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- CN106513675A CN106513675A CN201610986062.3A CN201610986062A CN106513675A CN 106513675 A CN106513675 A CN 106513675A CN 201610986062 A CN201610986062 A CN 201610986062A CN 106513675 A CN106513675 A CN 106513675A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
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- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/64—Treatment of workpieces or articles after build-up by thermal means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/36—Process control of energy beam parameters
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/40—Structures for supporting workpieces or articles during manufacture and removed afterwards
- B22F10/47—Structures for supporting workpieces or articles during manufacture and removed afterwards characterised by structural features
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/10—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
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Abstract
The invention relates to a laser additive manufacturing forming method of a titanium alloy thin-walled component, in particular to a preparing method of a multi-branch thin-walled titanium alloy structure and belongs to the technical field of titanium alloy structural machining and molding. The preparing method is the structural preparing method based on a selective laser melting forming and laser cladding technology. According to the thin wall, the titanium alloy structure with the thickness of the titanium alloy not larger than 5mm and particularly the wall thickness ranging from 2 mm to 4 mm is formed. The titanium alloy complex thin-walled component obtained through the method has the 4mm wall thickness, and the 0.1mm/100mm size precision, and the manufacturing period is shortened by 50%.
Description
Technical field
The present invention relates to a kind of titanium alloy thin wall component laser gain material manufacture manufacturing process, more particularly to a kind of multiple-limb,
The preparation method of thin-wall titanium alloy structure, is the structure preparation method that shaping and laser melting and coating technique are melted based on selective laser,
Described thin-walled refers to that the thickness of titanium alloy is not more than 5mm, is particularly suited for the shaping of the titanium alloy structure that wall thickness is 2-4mm,
Belong to titanium alloy structure shapes technical field.
Background technology
The thin-wall light-weighted titanium alloy of large amount of complex time load-carrying construction part is employed on spacecraft, main feature includes：It is thin
Wall construction, complex contour, wide variety, dimensional stability and mechanical property requirements are high, product mounting surface space angle equidimension
Required precision is high.
At present, typically using conventional fabrication processes " casting+machining ", casting quality is wayward, the quick titanium alloy of star
The 4-6 month casting cycle of supporting construction, after the completion of casting, Jing measurements, 1 axis of support tube and 0.8 ° of X-axis angular deviation, equipment
0.8 ° of 1 axis of support tube and Y-axis angular deviation, 0.23 ° of 1 axis of equipment support tube and Z axis angular deviation (drawing requirement ±
0.05 °), other two support tubes are qualified with 3 reference axis angles.By the overproof physical dimension change for causing of angle all
" eating " has fallen casting surplus, causes product rejection.(precision relies on made allowance, machining additionally, Ti alloy casting limited precision
Ensure), casting section thickness have to be larger than 5mm, and subsequent mechanical processing capacity is big, due to exist cannot machining region (branch chamber
Body madial wall), cause product meet weight demands.
The content of the invention
The technical problem to be solved is：Overcome that conventional fabrication processes casting quality is wayward, the lead time
It is long, the shortcomings of casting accuracy is limited, there is provided a kind of titanium alloy thin wall component laser gain material manufactures manufacturing process, and the method can be solved
Certainly dimensional stability problems.
The present invention technical solution be：
A kind of titanium alloy thin wall component laser gain material manufactures manufacturing process, and described titanium alloy thin wall component includes three circles
Support tube and the bottom bracket of platy structure that cylinder is combined into, first to support tube using selective laser fusing shaping, to bottom
Support using selective laser fusing shaping, then by laser cladding method support tube and bottom bracket be connected in repeatedly one it is whole
Body；
The step of the method, includes：
(1) the method contoured bottom support of shaping is melted using selective laser, technological parameter during shaping is：Laser power
For 300-370W, spot diameter is 0.05-0.1mm, and sweep speed is 1000-1500mm/s, and powdering thickness is 0.02-
0.05mm, shaping are obtained after terminating with substrate and the bottom bracket for supporting；
(2) the method forming support cylinder of shaping is melted using selective laser, technological parameter during shaping is：Laser power is
300-370W, spot diameter are 0.05-0.1mm, and sweep speed is 1000-1500mm/s, and powdering thickness is 0.02-0.05mm,
Shaping is obtained after terminating with substrate and the support tube for supporting；
(3) step (1) is obtained with substrate and support bottom bracket and step (2) obtain with substrate and
The support tube of support is heat-treated simultaneously, and process of thermal treatment parameter is：Temperature is 780-820 DEG C, and temperature retention time is 2-4h, work
Make pressure and be not more than 6.7 × 10-2Pa, insulation terminate rear along with the furnace cooling；
(4) bottom bracket and support tube after step (3) heat treatment is carried out into wire cutting, removes substrate, only carried
The bottom bracket and support tube of support；
(5) support of bottom bracket and support tube is removed, bottom bracket and support tube is obtained, and to bottom bracket and support
Cylinder surface carries out polishing, blasting treatment；
(6) bottom bracket and support tube are first mechanically fixed using frock, are then entered using the method for laser melting coating
Row connects, and the technological parameter of laser melting coating is：Laser power is 400-500W, and spot diameter is 0.05-0.2mm, sweep speed
For 1000-1800mm/min, the frock adopted when being mechanically connected is removed after terminating by thickness 0.05-0.1mm, laser melting coating again,
Obtain titanium alloy integrated member.
Present invention advantage compared with prior art is：
(1), using " casting+machining ", the manufacturing cycle, casting quality was not easily-controllable up to 4-6 month for conventional fabrication processes
System, the percent defective (defect rate) of part is higher, and casting section thickness have to be larger than 5mm, and subsequent mechanical processing capacity is big.The present invention takes
After above-mentioned technical proposal, the alloy complex thin-wall member wall thickness of acquisition reaches 4mm, and dimensional accuracy reaches 0.1mm, manufacturing cycle
Shorten 50%；
(2) Complex Thin Shell structural member high accuracy, high-performance manufacture demand can be met using above-mentioned manufacturing technology.
Description of the drawings
Fig. 1 is the structural representation of support tube in titanium alloy member；
Fig. 2 is the structural representation of bottom bracket in titanium alloy member；
Fig. 3 is the structural representation of the titanium alloy integrated member that support tube is connected into bottom bracket.
Specific embodiment
A kind of titanium alloy thin wall component laser gain material manufactures manufacturing process, and described titanium alloy thin wall component includes three circles
Support tube and the bottom bracket of platy structure that cylinder is combined into.First to support tube using selective laser fusing shaping, to bottom
Support using selective laser fusing shaping, then by laser cladding method support tube and bottom bracket be connected as one it is whole
Body.
The step of the method, includes：
(1) the method contoured bottom support of shaping is melted using selective laser, technological parameter during shaping is：Laser power
For 300-370W, spot diameter is 0.05-0.1mm, and sweep speed is 1000-1500mm/s, and powdering thickness is 0.02-
0.05mm, shaping are obtained after terminating with substrate and the bottom bracket for supporting；
(2) the method forming support cylinder of shaping is melted using selective laser, technological parameter during shaping is：Laser power is
300-370W, spot diameter are 0.05-0.1mm, and sweep speed is 1000-1500mm/s, and powdering thickness is 0.02-0.05mm,
Shaping is obtained after terminating with substrate and the support tube for supporting；
(3) step (1) is obtained with substrate and support bottom bracket and step (2) obtain with substrate and
The support tube of support is heat-treated simultaneously, and process of thermal treatment parameter is：Temperature is 780-820 DEG C, and temperature retention time is 2-4h, work
Make pressure and be not more than 6.7 × 10-2Pa, insulation terminate rear along with the furnace cooling；
(4) bottom bracket and support tube after step (3) heat treatment is carried out into wire cutting, removes substrate, only carried
The bottom bracket and support tube of support；
(5) support of bottom bracket and support tube is removed, bottom bracket and support tube is obtained, and to bottom bracket and support
Cylinder surface carries out polishing, blasting treatment；
(6) bottom bracket and support tube are first mechanically fixed using frock, are then entered using the method for laser melting coating
Row connects, and the technological parameter of laser melting coating is：Laser power is 400-500W, and spot diameter is 0.05-0.2mm, sweep speed
For 1000-1800mm/min, the frock adopted when being mechanically connected is removed after terminating by thickness 0.05-0.1mm, laser melting coating again,
Obtain titanium alloy integrated member.
The invention will be further described with reference to the accompanying drawings and examples.
Embodiment 1
A kind of titanium alloy thin wall component laser gain material manufactures manufacturing process, as shown in Figures 1 to 3, described titanium alloy thin wall
The step of component includes the bottom bracket of the support tube that three cylinders are combined into and platy structure, the method includes：
(1) method for melting shaping using selective laser is formed separately bottom bracket and support tube, technique ginseng during shaping
Number is：Laser power is 350W, and spot diameter is 0.08mm, and sweep speed is 1100mm/s, and powdering thickness is 0.03mm；
(2) to being heat-treated with substrate and the bottom bracket for supporting and the support tube with substrate and support simultaneously,
Process of thermal treatment parameter is：Temperature is 800 DEG C, and temperature retention time is 2.5h, operating pressure 1 × 10-3Pa, is incubated after terminating with stove
Cooling；
(3) bottom bracket and support tube after heat treatment is carried out into wire cutting, removes substrate, obtained only with the bottom for supporting
Portion's support and support tube；
(4) support of bottom bracket and support tube is removed, bottom bracket and support tube is obtained, and to bottom bracket and support
Cylinder surface carries out polishing, blasting treatment；
(5) bottom bracket and support tube are first mechanically fixed using frock, are then entered using the method for laser melting coating
Row connects, and the technological parameter of laser melting coating is：Laser power is 420W, and spot diameter is 0.12mm, and sweep speed is 1400mm/
The frock adopted when being mechanically connected is removed after terminating by min, thickness 0.06mm, laser melting coating again, obtains titanium alloy integrated member.
Titanium alloy member to obtaining carries out measuring mechanical property, and which is surveyed according to GB/T228.1-2010 with stove coupon
Try, test result is：Tensile strength reaches 1140MPa；Hardness test detected according to GB/T231.1-2009, test structure
For 365HV；Surface roughness testing result is Ra4.62；The accuracy of manufacture reaches 0.1mm/100mm.
Embodiment 2
(1) method for melting shaping using selective laser is formed separately bottom bracket and support tube, technique ginseng during shaping
Number is：Laser power is 360W, and spot diameter is 0.07mm, and sweep speed is 1200mm/s, and powdering thickness is 0.04mm；
(2) to being heat-treated with substrate and the bottom bracket for supporting and the support tube with substrate and support simultaneously,
Process of thermal treatment parameter is：Temperature is 810 DEG C, and temperature retention time is 2h, operating pressure 1 × 10-3Pa, insulation are cold with stove after terminating
But；
(3) bottom bracket and support tube after heat treatment is carried out into wire cutting, removes substrate, obtained only with the bottom for supporting
Portion's support and support tube；
(4) support of bottom bracket and support tube is removed, bottom bracket and support tube is obtained, and to bottom bracket and support
Cylinder surface carries out polishing, blasting treatment；
(5) bottom bracket and support tube are first mechanically fixed using frock, are then entered using the method for laser melting coating
Row connects, and the technological parameter of laser melting coating is：Laser power is 430W, and spot diameter is 0.13mm, and sweep speed is 1450mm/
The frock adopted when being mechanically connected is removed after terminating by min, thickness 0.07mm, laser melting coating again, obtains titanium alloy integrated member.
Titanium alloy member to obtaining carries out measuring mechanical property, and which is surveyed according to GB/T228.1-2010 with stove coupon
Try, test result is：The tensile strength of titanium alloy member reaches 1150MPa；Hardness test is carried out according to GB/T231.1-2009
Detection, test structure is 369HV；Surface roughness testing result is Ra4.12；The accuracy of manufacture reaches 0.1mm/100mm.
Claims (1)
1. a kind of titanium alloy thin wall component laser gain material manufactures manufacturing process, it is characterised in that：Described titanium alloy thin wall component
The step of support tube being combined into including three cylinders and the bottom bracket of platy structure, the method, includes：
(1) the method contoured bottom support of shaping is melted using selective laser, technological parameter during shaping is：Laser power is
300-370W, spot diameter are 0.05-0.1mm, and sweep speed is 1000-1500mm/s, and powdering thickness is 0.02-0.05mm,
Shaping is obtained after terminating with substrate and the bottom bracket for supporting；
(2) the method forming support cylinder of shaping is melted using selective laser, technological parameter during shaping is：Laser power is 300-
370W, spot diameter are 0.05-0.1mm, and sweep speed is 1000-1500mm/s, and powdering thickness is 0.02-0.05mm, is shaped
Obtain after end with substrate and the support tube for supporting；
(3) step (1) is obtained with substrate and support bottom bracket and step (2) obtain with substrate and support
Support tube is heat-treated simultaneously, and process of thermal treatment parameter is：Temperature is 780-820 DEG C, and temperature retention time is 2-4h, work pressure
It is strong to be not more than 6.7 × 10-2Pa, insulation terminate rear along with the furnace cooling；
(4) bottom bracket and support tube after step (3) heat treatment is carried out into wire cutting, removes substrate, obtained only with support
Bottom bracket and support tube；
(5) support of bottom bracket and support tube is removed, bottom bracket and support tube is obtained, and to bottom bracket and support tube table
Face carries out polishing, blasting treatment；
(6) bottom bracket and support tube are first mechanically fixed using frock, are then connected using the method for laser melting coating
Connect, the technological parameter of laser melting coating is：Laser power is 400-500W, and spot diameter is 0.05-0.2mm, and sweep speed is
The frock adopted when being mechanically connected is removed after terminating by 1000-1800mm/min, thickness 0.05-0.1mm, laser melting coating again, is obtained
To titanium alloy integrated member.
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| CN201610986062.3A CN106513675A (en) | 2016-11-09 | 2016-11-09 | Laser additive manufacturing forming method of titanium alloy thin-walled component |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107511481A (en) * | 2017-07-14 | 2017-12-26 | 广州雄俊智能科技有限公司 | A kind of 3D printing of overlength metalwork, heat treatment integral processing method |
| CN107876770A (en) * | 2017-12-05 | 2018-04-06 | 北京卫星制造厂 | A kind of increasing material manufacturing method of the part with thin-wall construction based on SLM techniques |
| CN109277567A (en) * | 2018-10-16 | 2019-01-29 | 北京星航机电装备有限公司 | A kind of laser near-net-shape method of abnormity deep-cavity thin-wall cabin |
| CN109506081A (en) * | 2018-09-14 | 2019-03-22 | 上海空间推进研究所 | Rack components based on selective laser fusing forming technique |
| CN110666452A (en) * | 2019-09-19 | 2020-01-10 | 西安成立航空制造有限公司 | Machining method for replacing casting fuel nozzle shell through 3D printing |
| CN112548106A (en) * | 2021-02-26 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Method for repairing ultrathin structure by additive manufacturing |
| CN114210999A (en) * | 2021-11-29 | 2022-03-22 | 西安航天发动机有限公司 | Integral manufacturing method for multilayer thin-wall streamline structure valve shell |
| CN116117177A (en) * | 2022-12-29 | 2023-05-16 | 北京卫星制造厂有限公司 | Titanium/aluminum heterogeneous alloy swing pulse laser fuse additive equipment and method |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107511481A (en) * | 2017-07-14 | 2017-12-26 | 广州雄俊智能科技有限公司 | A kind of 3D printing of overlength metalwork, heat treatment integral processing method |
| CN107876770A (en) * | 2017-12-05 | 2018-04-06 | 北京卫星制造厂 | A kind of increasing material manufacturing method of the part with thin-wall construction based on SLM techniques |
| CN107876770B (en) * | 2017-12-05 | 2019-08-09 | 北京卫星制造厂 | A kind of increasing material manufacturing method of the part with thin-wall construction based on SLM technique |
| CN109506081A (en) * | 2018-09-14 | 2019-03-22 | 上海空间推进研究所 | Rack components based on selective laser fusing forming technique |
| CN109277567A (en) * | 2018-10-16 | 2019-01-29 | 北京星航机电装备有限公司 | A kind of laser near-net-shape method of abnormity deep-cavity thin-wall cabin |
| CN110666452A (en) * | 2019-09-19 | 2020-01-10 | 西安成立航空制造有限公司 | Machining method for replacing casting fuel nozzle shell through 3D printing |
| CN112548106A (en) * | 2021-02-26 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Method for repairing ultrathin structure by additive manufacturing |
| CN114210999A (en) * | 2021-11-29 | 2022-03-22 | 西安航天发动机有限公司 | Integral manufacturing method for multilayer thin-wall streamline structure valve shell |
| CN114210999B (en) * | 2021-11-29 | 2023-04-14 | 西安航天发动机有限公司 | Integral manufacturing method of multilayer thin-wall streamline structure valve shell |
| WO2023093906A1 (en) * | 2021-11-29 | 2023-06-01 | 西安航天发动机有限公司 | Multi-layer thin-wall streamline structure valve housing integral manufacturing method |
| CN116117177A (en) * | 2022-12-29 | 2023-05-16 | 北京卫星制造厂有限公司 | Titanium/aluminum heterogeneous alloy swing pulse laser fuse additive equipment and method |
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