CN104588649B - The technique of Laser Direct Deposition cantilever design metal parts - Google Patents
The technique of Laser Direct Deposition cantilever design metal parts Download PDFInfo
- Publication number
- CN104588649B CN104588649B CN201410747722.3A CN201410747722A CN104588649B CN 104588649 B CN104588649 B CN 104588649B CN 201410747722 A CN201410747722 A CN 201410747722A CN 104588649 B CN104588649 B CN 104588649B
- Authority
- CN
- China
- Prior art keywords
- powder
- cantilever design
- cantilever
- layer
- metal parts
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Classifications
-
- 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
Abstract
The technique that the invention discloses a kind of Laser Direct Deposition cantilever design metal parts, it is characterised in that when part model does not exists cantilever design, according to normal process cladding.When being shaped to cantilever layer, provide by one of following three kinds of methods and support: being 1. filled into around part by metal dust, and struck off by powder, be compacted, cladding layer current with part is concordant；2. metal fine-structure mesh is tiled on formed part；3. the thin slice that powder is pressed into is placed in the concordant place of current cladding layer.The corresponding different forming technology of support of one layer of different modes of cantilever: 1., reducing laser power and close powder feeder, the metal dust overhead after striking off, being compacted sweeps one layer；2., first scanning profile, metal fine-structure mesh is molten on formed part base solid, then reduces laser power, fill scanning one layer；3., directly shape according to normal process.Utilize the support that preceding layer provides, follow-up can shape according to normal process.
Description
Technical field
The present invention relates to laser gain material manufacturing technology, particularly to Laser Direct Deposition utilizes powder,
The thin slice that metal fine-structure mesh, powder are pressed into provides and supports, with the method shaping cantilever design part, main
It is used for solving insurmountable cantilever design part forming in three axles (even five axles) laser system to ask
Topic.
Background technology
Laser Direct Deposition be grow up early 1990s merged Rapid Prototyping technique and
The advanced manufacturing technology of laser melting and coating technique.It is based on " discrete-to pile up " Forming Theory, first
The three-dimensional CAD physical model of systematic function part the most in a computer；Then by the three-dimensional shaped of part
Shape information slicing delamination, is converted to a series of two-dimensional silhouette information, and aspect geological information merges shaping
Parameter generates scanning pattern numerical control code, under digital control system control, uses synchronous powder feeding system laser melting coating
Method according to scanning track successively cladding pile up, ultimately form Three-dimensional Entity Components.As overturning biography
Unite manufacturing new technique, it is possible to realize high-performance labyrinth metal parts without mould, quickly,
Complete fine and close near-net-shape, is considered the third time industrial revolution, has worldwide started research and has answered
Upsurge.It is particularly suited for special material or special shape metal parts that traditional method is difficult to manufacture,
Widely should have in fields such as Aero-Space, auto industry, Mould design and manufacturing, biomedicines
Use prospect.
Actual equipment for spraying type Laser Direct Deposition can not shape arbitrarily complicated metal parts.
As a example by the former of three-shaft linkage, for overstepping the extreme limit angle of inclination and there is the zero of cantilever design
Part, needs to add supporting and could shape, thus reduces forming efficiency, and part supports and removes difficulty
Even cannot remove.The former of five-axle linkage can overcome the problem at bigger angle of inclination, but
Cantilever design for some complexity still cannot shape (the such as one-tenth at aero engine turbine blades top
Shape).Visible complicated cantilever design limits the extensive application of Laser Direct Deposition technology.
Summary of the invention
For existing Laser Direct Deposition technology cannot shape the problem of cantilever design metal parts, this
The purpose of invention is to provide and a kind of uses fore-put powder, metal fine-structure mesh, the method for thin slice, for follow-up molten
Cover shaping and support is provided, to shape the technique containing cantilever design metal parts.
For reaching object above, the present invention adopts the following technical scheme that and is achieved:
The technique of a kind of Laser Direct Deposition cantilever design metal parts, it is characterised in that include following
Step:
(1) when metal parts does not exists cantilever design, by the direct deposited metals of laser forming common process
Powder；
(2), when cladding is to a layer of cantilever design, provides by one of following three kinds of methods and support:
1., metal dust is filled into around part, and powder is compacted, and work as front end with part
Face is concordant；
2., metal fine-structure mesh is laid in part and works as front end face；
3., by prefabricated powder thin slice it is laid in part and works as front end face, chip shape and cantilever part
Identical；
(3) cantilever layer is according to the support of step (2) different modes, corresponding following different shaping work
Skill:
1., to step (2) support 1., reduce laser power and also close powder feeder, with
Part is when pressing cantilever profile scan on the concordant metal dust of front end face；Make the fusing of powder part be formed to burn
Knot layer；
2., to step (2) support 2., first press cantilever profile scan, metal fine-structure mesh is melted
Front end face is worked as to part；Reduce laser power, refill scanning one layer；
3., to step (2) support 3., directly continue to shape according to common process；
(4) follow-up shaping only need to continue cladding by normal process, if running into cantilever design again, the most again
It is back to step (2).
In above-mentioned technique, the described supporting form to step (2) preset metal dust 2., cantilever is tied
After composition shape terminates, need the metal dust that clearing and retrieving is filled.
Forming metallic powder size is 40～60 μm.Can the selection of material be preferentially Ti-6Al-4V, also
I.e. TC4 powder.
The present invention in Laser Direct Deposition, select sintering one layer of powder, the fine-structure mesh of same metal,
The thin slice that powder is pressed into supports, and can complete the shaping of cantilever design, solves cantilever design gold
The problem belonging to part Laser Direct Deposition difficulty.The present invention has used for reference selective laser sintering technology (SLM)
In, the cantilever part of threedimensional model utilizes metal dust to support, and need not be model buildings entity again
Support.Arbitrarily complicated entity component can be shaped in theory, and due to Laser Direct Deposition part
Feature, its intensity is higher than selective laser sintering.Owing to there is not unnecessary solid support, can be
Limits improves forming efficiency, saves powder.
The present invention can quickly manufacture and have under the laser metal forming appointed condition of three kinematic axiss
The metal parts of cantilever design, it is adaptable to the shaping of the labyrinth such as blade of aviation engine, inner flow passage.
Accompanying drawing explanation
Fig. 1 is Laser Direct Deposition system schematic.In figure: 1, laser beam；2, carrier gas powder；3
Atmosphere protection cover；4, numerical control table, NC table；5, powder-feeding nozzle；6, substrate.
Fig. 2 is an example of Laser Direct Deposition cantilever part of the present invention.Wherein: (a) metal zero
The part part without cantilever design, direct forming on substrate；B () burns on preset metal dust
Tie one layer；(c) final Prototyping Metal Parts.In figure: 6, substrate；7, there is no cantilever design part
Part；8, preset metal dust；9, a layer sintered on fore-put powder；10, powder holds
Device；11, the final metal parts shaped.
Fig. 3 is the pattern photo of another example of Laser Direct Deposition cantilever part of the present invention.Wherein:
A () utilizes wire netting to support；B TC4 cantilever design part that () finally shapes.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in further detail.
Seeing Fig. 1, Laser Direct Deposition system of the present invention includes laser instrument, computer, three number of coordinates
Control workbench 4, protection gas and powder feeder, powder-feeding nozzle 5, atmosphere protection cover 3 etc., laser instrument produces
And conduct laser beam 1 to machining area, three coordinate numerical control table, NC tables realize laser beam with shape sample it
Between relative motion, carrier gas powder 2 is transferred to four road powder-feeding nozzles by powder feeder, make powder stream with swash
Light beam overlaps, and atmosphere protection cover 3 ensures that the oxygen content of working chamber reaches processing request.
Embodiment one
(1) Laser Direct Deposition cantilever design metal parts the selection of material: the metal powder used in experiment
Conventional Ti-6Al-4V (TC4) powder in end, powder size is 40～60 μm, and the material of substrate 6 is
TC4 substrate.
(2) front being placed in vacuum drying oven by powder of experiment is heated to 150 DEG C, is incubated 24h, to go
Moisture removal also strengthens powder flowbility；After TC4 substrate surface is polished with fine sandpaper, go with acetone soln
Except substrate surface oils and fats and spot, finally substrate surface ethanol solution is cleaned up.
(3), in forming process, normally shape on TC4 substrate when height is less than 3cm, main
Technological parameter is laser power 200W, scanning speed 10mm/s, and powder sending quantity is 4g/min, and Z axis promotes
Amount is 0.1mm, and overlapping spacing between twice is 0.30mm.
(4), when height is 3cm, parts profile is shaped as rectangular surfaces, and the mid portion of rectangular surfaces does not has
There is support, it is impossible to direct forming [Fig. 2 (a)].Therefore upper metal dust 8, pressure will be filled around part
Strike off after reality, make powder concordant with part upper surface, close powder feeder when shaping cantilever layer, prevent from sending
The powder of compacting is dispelled by powder nozzle.Reduction laser power is to 150W, so that the fusing of powder part,
Link together (on fore-put powder one layer 9 of sintering), provides for next layer and supports [Fig. 2 (b)].
(5), when height is more than 3mm, shape according to normal process parameter: open powder feeder,
Improve laser power to 200W.Clearing and retrieving powder after shaping, final forming titanium alloy part
As shown in Fig. 2 (c).
Embodiment two
(1), when forming height is less than 3cm, same process is used with example one；Being formed into height is
Titanium net is used to replace powder to support [Fig. 3 (a)] during 3cm.
(2) when titanium shapes on the net, first according to normal power scanning profile, it is molten to become by titanium net
On shape part base solid.Then reduction laser power is to 100W, opens powder feeder, fills scanning one
Layer.
(3) in the support of formed a layer, can shape according to normal process, final formation of parts
As shown in Fig. 3 (b).
This making an excessive case more excessive example utilize serve as with the metal fine-structure mesh of metal dust same element support can also be follow-up become
Shape provides and supports.Compared with doing support with metal dust, during metal fine-structure mesh cladding, bottom cantilever layer, there is no volume
Outer viscous powder, thus there is higher forming accuracy.
Embodiment three
With the metal fine-structure mesh in prefabricated powder thin slice alternate embodiment two, it is laid in part and works as front end face, thin
Plate shape is same with cantilever portion split-phase, directly can shape according to normal process on thin slice.
Claims (4)
1. the technique of a Laser Direct Deposition cantilever design metal parts, it is characterised in that under including
State step:
(1) when metal parts does not exists cantilever design, by the direct deposited metals of laser forming common process
Powder；
(2), when cladding is to a layer of cantilever design, support is provided by the following method: filled out by metal dust
It is charged to around part, and powder is compacted, and concordant when front end face with part；
(3) support to step (2), reduces laser power and also closes powder feeder, with part
When pressing cantilever profile scan on the metal dust that front end face is concordant；The fusing of powder part is made to form sinter layer；
(4) follow-up shaping only need to continue cladding by normal process, if running into cantilever design again, the most again
It is back to step (2).
2. the technique of Laser Direct Deposition cantilever design metal parts as claimed in claim 1, it is special
Levying and be, the supporting form of the described preset metal dust to step (2), cantilever design shapes and terminates
After, need the metal dust that clearing and retrieving is filled.
3. the technique of Laser Direct Deposition cantilever design metal parts as claimed in claim 1, it is special
Levying and be, forming metallic powder size is 40～60 μm.
4. the technique of Laser Direct Deposition cantilever design metal parts as claimed in claim 1, it is special
Levying and be, forming metallic powder the selection of material is Ti-6Al-4V, namely TC4 powder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410747722.3A CN104588649B (en) | 2014-12-08 | 2014-12-08 | The technique of Laser Direct Deposition cantilever design metal parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410747722.3A CN104588649B (en) | 2014-12-08 | 2014-12-08 | The technique of Laser Direct Deposition cantilever design metal parts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104588649A CN104588649A (en) | 2015-05-06 |
| CN104588649B true CN104588649B (en) | 2016-11-23 |
Family
ID=53114897
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410747722.3A Expired - Fee Related CN104588649B (en) | 2014-12-08 | 2014-12-08 | The technique of Laser Direct Deposition cantilever design metal parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104588649B (en) |
Families Citing this family (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106541133B (en) * | 2015-09-22 | 2018-08-21 | 首都航天机械公司 | A kind of method of in-situ preparation auxiliary support structure |
| CN105108144B (en) * | 2015-09-28 | 2017-03-29 | 苏州大学 | One kind is without matrix without support metal parts laser melting coating free forming method |
| CN105252145B (en) * | 2015-10-19 | 2017-10-20 | 华南理工大学 | A kind of method and apparatus of sheet metal superposition manufacture complicated shape part |
| CN105170974A (en) * | 2015-10-19 | 2015-12-23 | 无锡清杨机械制造有限公司 | Quick forming method |
| 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 |
| CN105252003B (en) * | 2015-11-09 | 2017-05-10 | 华中科技大学 | Additive manufacturing method for aircraft wing spar components |
| CN106041075B (en) * | 2016-06-22 | 2018-03-02 | 西北工业大学 | A kind of high energy beam increasing material manufacturing method of metal parts hanging structure |
| CN106392071A (en) * | 2016-09-18 | 2017-02-15 | 四川大学 | Method used for improving manufacturing efficiency and precision of additive formed through powder bed fusion |
| CN107282924B (en) * | 2017-07-10 | 2019-01-04 | 香港生产力促进局 | A kind of 3D printing device and method |
| CN110064759B (en) * | 2018-01-22 | 2024-03-15 | 深圳唯创技术发展有限公司 | Laminated compacted powder sintering 3D forming cylinder and forming method |
| CN109676123B (en) * | 2018-12-20 | 2021-03-02 | 西安铂力特增材技术股份有限公司 | Scanning method for photocuring formed metal, alloy and ceramic parts |
| CN110238395B (en) * | 2019-06-27 | 2020-04-24 | 南京工业大学 | Method for additive manufacturing of printed metal parts by means of prefabricated sand moulds |
| CN111069777A (en) * | 2019-08-23 | 2020-04-28 | 上海微电子装备（集团）股份有限公司 | Additive manufacturing method and additive manufacturing equipment |
| CN112548106B (en) * | 2021-02-26 | 2021-05-18 | 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 |
| CN113477923B (en) * | 2021-06-29 | 2022-09-27 | 吉林大学重庆研究院 | Preparation and sintering method of titanium alloy slurry for 3D printing |
| CN113909631B (en) * | 2021-09-30 | 2023-08-22 | 江苏烁石焊接科技有限公司 | Suspended structure material adding process with auxiliary device at tail end of robot |
| CN114131050B (en) * | 2021-12-13 | 2022-07-08 | 深圳市华阳新材料科技有限公司 | Unsupported 3D printing method |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7540996B2 (en) * | 2003-11-21 | 2009-06-02 | The Boeing Company | Laser sintered titanium alloy and direct metal fabrication method of making the same |
| GB0819935D0 (en) * | 2008-10-30 | 2008-12-10 | Mtt Technologies Ltd | Additive manufacturing apparatus and method |
| DE102010041461B4 (en) * | 2010-09-27 | 2016-03-17 | Siemens Aktiengesellschaft | Test method for an additive manufacturing process |
| US9429023B2 (en) * | 2013-01-14 | 2016-08-30 | Honeywell International Inc. | Gas turbine engine components and methods for their manufacture using additive manufacturing techniques |
| CN103394693B (en) * | 2013-08-15 | 2016-03-23 | 石家庄铁道大学 | A kind of laser multidimensional print device and method manufacturing large-angle cantilever structure workpiece |
| CN103920877B (en) * | 2014-04-12 | 2016-01-13 | 北京工业大学 | A kind of SLM manufactures metal parts and easily removes support structure designs method |
-
2014
- 2014-12-08 CN CN201410747722.3A patent/CN104588649B/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN104588649A (en) | 2015-05-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104588649B (en) | The technique of Laser Direct Deposition cantilever design metal parts | |
| EP2962836B1 (en) | An additive manufacturing system and method of additive manufacture utilizing layer-by-layer thermo-mechanical analysis | |
| CN107130124B (en) | A kind of method of increases material manufacturing technology forming high-entropy alloy | |
| CN104759623B (en) | Using the increasing material manufacturing device of electron beam laser compound scanning | |
| CN106001568B (en) | A kind of functionally gradient material (FGM) metal die 3D printing integral preparation method | |
| CN104368814B (en) | A kind of method of metal laser direct-forming high-entropy alloy turbogenerator hot-end component | |
| CN102941343B (en) | Quick manufacturing method of titanium-aluminum alloy composite part | |
| CN103495731B (en) | A kind of selective laser melting prepares the method for pure titanium loose structure | |
| CN205798442U (en) | A kind of metallic composite rapid shaping power spreading device | |
| CN103143706A (en) | 3D (three dimensional) printing manufacturing method of seal | |
| CN107243633A (en) | Laser increases and decreases material composite manufacturing device and method | |
| CN101391302A (en) | Entirety quick manufacture method of hot isostatic pressing metal wrapps | |
| CN104353833A (en) | 3D (3-dimnesional) printing manufacturing method for PDC (primary domain controller) drill bit body | |
| CN103949646A (en) | Preparation method for Nb-Si base ultra-temperature alloy turbine vane | |
| RU2004110911A (en) | METHOD FOR PRODUCING A HOLLOW OF MECHANICAL DETAILS BY USING DIFFUSION WELDING AND SUPERPLASTIC FORMING | |
| CN105386037A (en) | Method for forming functional graded part through selective laser melting | |
| CN111451505A (en) | Selective laser melting preparation process of variable density gradient material with metal lattice structure | |
| CN104708003B (en) | A kind of picosecond laser Compound Machining SLM device and laser fast forming method | |
| CN111570793A (en) | Selective laser melting preparation method of variable-density gradient metal material with porous structure | |
| CN109202081A (en) | Copper alloy based on the forming of electron beam powdering increases the preparation method of material | |
| CN105312563B (en) | A kind of manufacture method of Ni-based double-alloy blisk | |
| CN110714199A (en) | Method for preparing coating by using 3D printing and lapping electron beam | |
| CN107866569A (en) | A kind of method that fine copper tool-electrode is prepared based on selective laser smelting technology | |
| CN108015286A (en) | High-entropy alloy droplet ejection increasing material manufacturing apparatus and method | |
| CN101417338B (en) | Manufacturing process of metal parts capable of performing shape follow-up annealing heat treatment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161123 Termination date: 20201208 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |