CN103302292A - Laser direct forming process for titanium alloy part - Google Patents
Laser direct forming process for titanium alloy part Download PDFInfo
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- CN103302292A CN103302292A CN2012100642945A CN201210064294A CN103302292A CN 103302292 A CN103302292 A CN 103302292A CN 2012100642945 A CN2012100642945 A CN 2012100642945A CN 201210064294 A CN201210064294 A CN 201210064294A CN 103302292 A CN103302292 A CN 103302292A
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Abstract
The invention discloses a laser direct forming process for a titanium alloy part, and relates to a laser rapid forming technology for metal powder. The process mainly comprises the following steps of determining basic process parameters of the titanium alloy part, and disclosing a new laser scanning path and a method for controlling an internal defect of a laser formed part, i.e. firstly determining a process parameter range of spherical TA15 powder by a basic process experiment, and transforming processing process parameters of different layers of the laser formed part to form the titanium alloy part by adopting the laser scanning path and the related internal defect control method, namely by adopting an optimal scanning interval. The part formed by the process has the advantages of high forming efficiency, low cost, high internal quality, high automation degree, easiness in operation and the like. The process can be used for directly forming the titanium alloy part at an industrial application level, and a novel way for the production of a titanium alloy structural part is provided.
Description
Technical field
The present invention relates to the metal powder laser RP technique, be specially a kind of process of Laser Direct Deposition titanium alloy component.
Background technology
The direct RP technique of laser metal is an advanced manufacturing technology that grows up in conjunction with synchronous coaxial feeding laser melting and coating technique on the rapid prototyping technology basis that occurs the latter stage eighties.It relates to the key technology in the fields such as machinery, laser, CAD, computer-aided manufacturing, computer numerical control (CNC), material science.It has broken through the limitation of traditional fast forming process and moulding material, is most study in all multi-methods of present Quick-forming, the most rising new manufacture.
And titanium alloy is because density is little, specific strength is high, high temperature performance is excellent, becomes the indispensable structural material of war industry.Titanium alloy structure spare consumption has accounted for 41% of main body mechanism gross weight among the U.S. four generations opportunity of combat F-22, China's new fighter titanium alloy structure spare consumption also will reach more than 25%, and the height of titanium alloy structure spare consumption has become one of important symbol of weighing the defence equipment technical advances such as aircraft.Adopt and forge the manufacturing such as the conventional art that adds machining large titanium alloy structural member, not only need large-scale heavy equip forging industry equipment, and manufacturing process is various, complex process, part machinery allowance is very large.Stock utilization low (being generally less than 5～10%), the digital control processing time is long, manufacturing cost is high, has seriously restricted the extensive use of large titanium alloy structural member in advanced industry and defence equipment.And the distinct advantages of Laser Rapid Prototyping Technique provides a new way for overcoming the above-mentioned manufacturing technology shortcoming of large titanium alloy structural member, and the titanium alloy Laser Rapid Prototyping Technique has widely practicality to advanced defence equipment R﹠D and production.
But in titanium alloy laser fast forming manufacture process, formation of parts often occurs that internal soundness is poor, distortion and problems of crack are to hinder it to expand the biggest obstacle of using.And cause the underlying cause of these problems to be that titanium alloy laser fast forming machine reason is undistinct, lack practical titanium alloy laser fast forming technique, therefore, study a kind of processing technology that adopts laser fast forming method direct forming to go out titanium alloy component, the technical barrier that solves the titanium alloy Laser Rapid Prototyping Technique has very important significance.
Summary of the invention
In above-mentioned titanium alloy laser fast forming manufacture process, often occur that internal soundness is poor, distortion and problems of crack, the object of the invention is to provide that a kind of forming quality is good, stock utilization, shortening manufacturing cycle and reduce the Laser Direct Deposition titanium alloy component process of relevant manufacturing cost.
For realizing purpose of the present invention, technical scheme of the present invention is:
Determine titanium alloy component basic technology parameter, by the technological experiment on basis, adopt the sized spherical titanium powder moulding material, determine the forming parameters scope of sized spherical titanium powder;
Propose new laser beam scan path, propose simultaneously laser forming inside parts defect control method, the method adopts optimizes sweep span, working process parameter between conversion laser forming part different layers;
Sweep span according to new laser beam scan path, optimization reaches working process parameter between the conversion laser forming part different layers of determining, the whole process of titanium alloy component is carried out numerical control programming, by its whole process of computer control, realize disposable near-net-shape again.
Determine titanium alloy component basic technology parameter, adopt orthogonal experiment method, what obtained comprising each Process Parameters on Laser Quick-forming layer pattern of laser power, sweep speed, powder feeding rate, sweep span, lift height and size affects rule and then the forming parameters scope of definite sized spherical titanium powder.
The forming parameters scope of determined sized spherical titanium powder: laser power is that 1500～2200W, sweep speed are that 1～7mm/s, powder feeding rate are that 0.4～7g/min, sweep span are that 1～2mm, lift height are 0.3～0.9mm.
Proposing new laser beam scan path, is to adopt the filled type scan mode, namely during odd-level, carries out first the scanning of the outline of laser forming titanium alloy component, carries out its inner filling again; During even level, carry out first the inside of laser forming titanium alloy component and fill, carry out again the scanning of its outline.
The present invention compared with prior art has following advantage:
(1) forming efficiency is high, and cost is low
The inventive method is mainly determined titanium alloy component basic technology parameter, proposes new laser beam scan path and laser forming inside parts defect control method; The titanium alloy formation of parts that adopts forming technology of the present invention to process can greatly improve stock utilization, the shortening manufacturing cycle of titanium alloy component and reduce relevant manufacturing cost; The processing cost that the forging of elimination tradition adds the machining titanium alloy component is very high, manufacturing process is various, complex process, the defective that part machinery allowance is very large.
(2) the formation of parts internal soundness is good
The present invention utilizes the laser forming inside parts defect control method of proposition, make the internal flaw of titanium alloy component of shaping less, substantially solved that internal soundness is poor, distortion and problems of crack, and the mechanical property test such as stretched finds that its relevant mechanical performance index has has met or exceeded the level of titanium alloy forging spare.Find by the inside metallographic of analyzing the titanium alloy formation of parts, the interior tissue of formation of parts presents the net shape, and the crystal grain state is preferably equiaxed crystal of mechanical property, so that the titanium alloy component that the present invention is shaped has possessed the level of practical application in industry substantially.
(3) automaticity is high, and is easy to operate
The former that the present invention adopts is take the 5000W carbon dioxide laser as core, is aided with dust feeder, vacuum protector and mobile device.Former integrated automation level is high, can omnidistancely realize computer control.And the process that the present invention proposes, operating procedure is simple, is easy to realize.
Description of drawings
Fig. 1 is three kinds of traditional laser beam scan path schematic diagrames.
There is the photo in kind of defective in Fig. 2 for the titanium alloy laser fast forming part of tradition processing.
Fig. 3 is Laser Direct Deposition titanium alloy component process method flow chart of the present invention.
Fig. 4 is laser beam scan path schematic diagram of the present invention.
Fig. 5 is the photo in kind that the inside forming quality of formation of parts of the present invention improves.
Fig. 6 is titanium alloy laser fast forming part of the present invention photo in kind.
The specific embodiment
Below in conjunction with drawings and Examples the solution of the present invention is described in further detail:
Example 1:
As shown in Figure 3, be Laser Direct Deposition titanium alloy component process method flow chart of the present invention.The present invention is a kind of process of Laser Direct Deposition titanium alloy component, comprises its processing step:
Determine titanium alloy component basic technology parameter, by the technological experiment on basis, adopt the sized spherical titanium powder moulding material, determine the forming parameters scope of sized spherical titanium powder;
Propose new laser beam scan path, propose simultaneously laser forming inside parts defect control method, the method adopts optimizes sweep span, working process parameter between conversion laser forming part different layers;
Sweep span according to new laser beam scan path, optimization reaches working process parameter between the conversion laser forming part different layers of determining, the whole process of titanium alloy component is carried out numerical control programming, by its whole process of computer control, realize disposable near-net-shape again.
As shown in Figure 1, be three kinds of traditional laser beam scan path schematic diagrames.Laser Rapid Prototyping Technique has a variety of laser beam scan paths, and what wherein commonly use the most is: the scanning of long limit, minor face scanning, interlacing.But by the related process experimental verification, find that these the three kinds of traditional scan modes among Fig. 1 all exist such or such defective workmanship, wherein modal defective workmanship is the phenomenon of formation of parts collapsing of the edges, and this has had a strong impact on the laser fast forming crudy.
As shown in Figure 4, be laser beam scan path schematic diagram of the present invention.The present invention is directed to the phenomenon of formation of parts collapsing of the edges, proposed a kind of new laser beam scan path, this scan mode adopts the scan mode of filled type, namely during odd-level, carry out first the scanning of the outline of laser forming titanium alloy component, carry out again its inner filling; During even level, carry out first its inner filling, carry out again the scanning of the outline of laser forming titanium alloy component.Use the problem that this kind scan mode can solve formation of parts collapsing of the edges phenomenon well, obtain preferably forming quality.
The forming parameters scope of determined sized spherical titanium powder: laser power is that 1500～2200W, sweep speed are that 1～7mm/s, powder feeding rate are that 0.4～7g/min, sweep span are that 1～2mm, lift height are 0.3～0.9mm.
Optimize the technological experiment of the basic technological parameter of titanium alloy, adopt orthogonal experiment method, what obtained comprising each Process Parameters on Laser Quick-forming layer pattern of laser power, sweep speed, powder feeding rate, sweep span, lift height and size affects rule and then the process parameters range of the concrete shaping of definite sized spherical titanium powder.
The shaping sized spherical titanium powder material that the present invention adopts is: the TA15 sized spherical titanium powder, concrete composition is as shown in table 1.
Table 1 moulding material composition
| The trade mark | Specification | Al | Mo | V | Zr | Fe | Si | C | 0 | N | H |
| TA15 | The 100+200 order | 6.4％ | 1.4％ | 1.5％ | 1.9％ | 0.12％ | 0.02％ | 0.02％ | 0.07％ | ＜0.01 | ＜0.001 |
The present invention is by the experiment of a large amount of fundamental technology, determined sized spherical titanium powder TA15 spherical powder the forming parameters scope, specifically as shown in table 2.
The forming parameters scope of table 2TA15 spherical powder
| Experiment parameter | Scope |
| Laser power | 1500～2200W |
| Sweep speed | 1～7mm/s |
| Powder feeding rate | 0.4～7g/min |
| Lift height | 0.3～0.9mm |
| Sweep span | 1～2mm |
As shown in Figure 2, the photo in kind that has defective for the titanium alloy laser fast forming part of tradition processing.In the processing of titanium alloy laser fast forming, formation of parts pore, crackle often occur and merges the internal flaws such as bad, for these defectives, the present invention at first analyzes the reason that these defectives produce, and the temperature distributing disproportionation in the discovery shaping process spares and layer upper residual powder that be shaped is the main cause that affects the laser fast forming quality.
As shown in Figure 5, the photo in kind that improves for the inside forming quality of formation of parts of the present invention.The present invention adopts and optimizes sweep span, the new laser beam scan path of utilization proposition, and the measures such as working process parameter between conversion formation of parts different layers make the forming quality of laser fast forming part obtain very large improvement.
As shown in Figure 6, the pictorial diagram of formation of parts of the present invention.Adopt correlation technique corrective measure of the present invention, the present invention's three kinds of laser fast forming parts that have been shaped, the crudy of formation of parts, interior tissue and relevant mechanical property all can reach the commercial Application level of titanium alloy forging part.
The below illustrates:
Blade is the most one of core and crucial part of aero-engine, is described as " heart in the heart ".Adopt the mode shaping blade of laser fast forming, have that the part material utilization rate is high, the manufacturing cycle is short and the advantage such as relevant low cost of manufacture.The present invention processes the forming technology of certain model blade, and formation of parts is shown in Fig. 6 (a).
The filled type scan mode that blade part adopts the present invention to propose, adopt the related process parameter in the process parameters range of table 2, namely this embodiment adopting process parameter is: laser power 1900～2000W, sweep speed 5～6mm/s, powder feeding rate 1～3g/min, sweep span 1.1～1.5mm, lift height 0.6～0.8mm.In order to improve the drip molding interior tissue, in the process of processing, by adopting the different sweep span of optimizing, change the technological measures such as working process parameter of its laser forming part interlayer, improved the quality of formation of parts.
The former that the present invention adopts is take the 5000W carbon dioxide laser as core, by dust feeder, vacuum protector and mobile device this part is carried out processing and forming.Here whole process is carried out numerical control programming, by the whole process of computer control, realize disposable near-net-shape.
Example 2:
The present invention has also carried out the processing that is shaped to connector commonly used in the space flight and aviation and angle box, and formation of parts is shown in Fig. 6 (b) and Fig. 6 (c).The filled type scan mode that these two kinds of parts adopt the present invention to propose, form processing, the related process parameter that adopts is in table 2 technological parameter, and namely this embodiment adopting process parameter is: laser power 2000～2100W, sweep speed 3～5mm/s, powder feeding rate 0.5～0.9g/min, sweep span 1.1～1.5mm, lift height 0.6～0.8mm.In order to improve the interior tissue of formation of parts, by having adopted the sweep span of optimizing and having changed technological measures such as working process parameter mode between different layers, obtained preferably effect here, other processing technology is same as described above.
Claims (4)
1. the process of a Laser Direct Deposition titanium alloy component is characterized in that: comprise its processing step:
Determine titanium alloy component basic technology parameter, by the technological experiment on basis, adopt the sized spherical titanium powder moulding material, determine the forming parameters scope of sized spherical titanium powder;
Propose new laser beam scan path, propose simultaneously laser forming inside parts defect control method, the method adopts optimizes sweep span, working process parameter between conversion laser forming part different layers;
Sweep span according to new laser beam scan path, optimization reaches working process parameter between the conversion laser forming part different layers of determining, the whole process of titanium alloy component is carried out numerical control programming, by its whole process of computer control, realize disposable near-net-shape again.
2. according to the process of a kind of Laser Direct Deposition titanium alloy component claimed in claim 1, it is characterized in that: determine titanium alloy component basic technology parameter, adopt orthogonal experiment method, what obtain comprising the Process Parameters on Laser Quick-forming layer pattern of laser power, sweep speed, powder feeding rate, sweep span, lift height and size affects rule and then the forming parameters scope of definite sized spherical titanium powder.
3. according to the process of claim 1 or 2 described a kind of Laser Direct Deposition titanium alloy components, it is characterized in that: the forming parameters scope of determined sized spherical titanium powder: laser power is that 1500～2200W, sweep speed are that 1～7mm/s, powder feeding rate are that 0.4～7g/min, sweep span are that 1～2mm, lift height are 0.3～0.9mm.
4. according to the process of claim 1 or 2 described a kind of Laser Direct Deposition titanium alloy components, it is characterized in that: propose new laser beam scan path, to adopt the filled type scan mode, when being odd-level, carry out first the scanning of the outline of laser forming titanium alloy component, carry out again its inner filling; During even level, carry out first the inside of laser forming titanium alloy component and fill, carry out again the scanning of its outline.
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103962556A (en) * | 2014-04-16 | 2014-08-06 | 广州中国科学院先进技术研究所 | Pure titanium powder forming method based on selected area laser melting technology |
| CN104084584A (en) * | 2014-07-28 | 2014-10-08 | 中国科学院重庆绿色智能技术研究院 | Laser scanning method used for fast forming high-temperature alloy structural member |
| CN104899345A (en) * | 2015-03-09 | 2015-09-09 | 上海交通大学 | Method for determining laser peening forming process parameter of complex curved-surface-shaped workpiece |
| CN105397086A (en) * | 2015-10-28 | 2016-03-16 | 西安铂力特激光成形技术有限公司 | Laser precise forming method for titanium alloy hollow blade |
| CN105665704A (en) * | 2016-03-11 | 2016-06-15 | 上海拓宝机电科技有限公司 | Metal laser selective melting method |
| CN105689711A (en) * | 2016-02-04 | 2016-06-22 | 大连理工大学 | Process for laser rapid forming for nickel-based alloy parts through electromagnetic stirring assistance |
| CN106756649A (en) * | 2016-11-28 | 2017-05-31 | 中国科学院金属研究所 | A kind of continuous SiC fiber strengthens the laser gain material manufacture method of titanium matrix composite |
| CN107486522A (en) * | 2017-09-08 | 2017-12-19 | 国网湖北省电力公司检修公司 | Super extra high voltage line instrument laser formation method |
| CN107848013A (en) * | 2015-03-13 | 2018-03-27 | 奥科宁克公司 | The method of forging product of the production with inner passage |
| CN111974998A (en) * | 2020-08-13 | 2020-11-24 | 飞而康快速制造科技有限责任公司 | Additive manufacturing method for titanium alloy thin-wall part |
| CN112548119A (en) * | 2020-12-02 | 2021-03-26 | 中国科学院金属研究所 | Method for regulating and controlling selective laser melting forming titanium alloy process based on defect form |
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| CN116079075A (en) * | 2023-04-13 | 2023-05-09 | 太原理工大学 | SLM additive manufacturing invar alloy method based on differential spatial energy strategy |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1800700A2 (en) * | 2005-12-06 | 2007-06-27 | Howmedica Osteonics Corp. | Implant with laser-produced porous surface |
| CN101185970A (en) * | 2007-12-12 | 2008-05-28 | 沈阳航空工业学院 | Composite fast molding method based on laser deposition molding and reducing type molding |
| CN101607311A (en) * | 2009-07-22 | 2009-12-23 | 华中科技大学 | A kind of fusion of metal powder of three beams of laser compound scanning quick forming method |
| CN101899662A (en) * | 2010-07-22 | 2010-12-01 | 西安交通大学 | Method for improving surface evenness of laser metal forming part |
-
2012
- 2012-03-12 CN CN201210064294.5A patent/CN103302292B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1800700A2 (en) * | 2005-12-06 | 2007-06-27 | Howmedica Osteonics Corp. | Implant with laser-produced porous surface |
| CN101185970A (en) * | 2007-12-12 | 2008-05-28 | 沈阳航空工业学院 | Composite fast molding method based on laser deposition molding and reducing type molding |
| CN101607311A (en) * | 2009-07-22 | 2009-12-23 | 华中科技大学 | A kind of fusion of metal powder of three beams of laser compound scanning quick forming method |
| CN101899662A (en) * | 2010-07-22 | 2010-12-01 | 西安交通大学 | Method for improving surface evenness of laser metal forming part |
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| CN112869855A (en) * | 2014-04-11 | 2021-06-01 | 史密夫和内修有限公司 | DMLS orthopedic intramedullary devices and methods of manufacture |
| CN103962556A (en) * | 2014-04-16 | 2014-08-06 | 广州中国科学院先进技术研究所 | Pure titanium powder forming method based on selected area laser melting technology |
| CN104084584A (en) * | 2014-07-28 | 2014-10-08 | 中国科学院重庆绿色智能技术研究院 | Laser scanning method used for fast forming high-temperature alloy structural member |
| CN104899345B (en) * | 2015-03-09 | 2018-03-23 | 上海交通大学 | Method for determining complex-curved shape workpiece laser shot forming technological parameter |
| CN104899345A (en) * | 2015-03-09 | 2015-09-09 | 上海交通大学 | Method for determining laser peening forming process parameter of complex curved-surface-shaped workpiece |
| CN107848013A (en) * | 2015-03-13 | 2018-03-27 | 奥科宁克公司 | The method of forging product of the production with inner passage |
| CN105397086A (en) * | 2015-10-28 | 2016-03-16 | 西安铂力特激光成形技术有限公司 | Laser precise forming method for titanium alloy hollow blade |
| CN105397086B (en) * | 2015-10-28 | 2018-01-23 | 西安铂力特增材技术股份有限公司 | A kind of titanium alloy hollow blade laser accurate manufacturing process |
| CN105689711A (en) * | 2016-02-04 | 2016-06-22 | 大连理工大学 | Process for laser rapid forming for nickel-based alloy parts through electromagnetic stirring assistance |
| CN105665704A (en) * | 2016-03-11 | 2016-06-15 | 上海拓宝机电科技有限公司 | Metal laser selective melting method |
| CN106756649A (en) * | 2016-11-28 | 2017-05-31 | 中国科学院金属研究所 | A kind of continuous SiC fiber strengthens the laser gain material manufacture method of titanium matrix composite |
| CN107486522A (en) * | 2017-09-08 | 2017-12-19 | 国网湖北省电力公司检修公司 | Super extra high voltage line instrument laser formation method |
| CN111974998A (en) * | 2020-08-13 | 2020-11-24 | 飞而康快速制造科技有限责任公司 | Additive manufacturing method for titanium alloy thin-wall part |
| CN111974998B (en) * | 2020-08-13 | 2022-04-12 | 飞而康快速制造科技有限责任公司 | Additive manufacturing method for titanium alloy thin-wall part |
| CN112548119A (en) * | 2020-12-02 | 2021-03-26 | 中国科学院金属研究所 | Method for regulating and controlling selective laser melting forming titanium alloy process based on defect form |
| CN115740500A (en) * | 2022-12-06 | 2023-03-07 | 上海祉元社企业管理合伙企业(有限合伙) | Method for manufacturing high-strength titanium alloy containing easily segregated elements through 3D printing |
| CN115740500B (en) * | 2022-12-06 | 2023-10-24 | 上海祉元社企业管理合伙企业(有限合伙) | Method for manufacturing high-strength titanium alloy containing easily segregated elements through 3D printing |
| CN116079075A (en) * | 2023-04-13 | 2023-05-09 | 太原理工大学 | SLM additive manufacturing invar alloy method based on differential spatial energy strategy |
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