CN106891006A - A kind of selective laser fusing TC4 in-situ annealings go residual stress method - Google Patents

A kind of selective laser fusing TC4 in-situ annealings go residual stress method Download PDF

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CN106891006A
CN106891006A CN201710254587.2A CN201710254587A CN106891006A CN 106891006 A CN106891006 A CN 106891006A CN 201710254587 A CN201710254587 A CN 201710254587A CN 106891006 A CN106891006 A CN 106891006A
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laser
remelting
thin
residual stress
time
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CN106891006B (en
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王森
王国玉
刘基权
王林志
陈添
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Chongqing Institute of Green and Intelligent Technology of CAS
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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
    • 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
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • 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
    • 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
    • B22F10/364—Process control of energy beam parameters for post-heating, e.g. remelting
    • 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
    • B22F10/366—Scanning parameters, e.g. hatch distance or scanning strategy
    • 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
    • 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
    • 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
    • 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
    • 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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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Automation & Control Theory (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laser Beam Processing (AREA)

Abstract

The present invention relates to a kind of method of the residual stress for reducing precinct laser fusion increasing material manufacturing TC4 thin-wall workpieces, by the energy density input, the remelting number of times that are precisely controlled remelting processing, realize the function of print procedure self annealing, reduce the residual stress of precinct laser fusion increasing material manufacturing TC4 thin-wall workpieces, realize the rapid shaping of TC4 thin-wall parts, suppress the cracking/deformation in print procedure, be conducive to popularization and application of the precinct laser fusion manufacturing technology in the manufacture of aviation field precise thin wall pieces.

Description

A kind of selective laser fusing TC4 in-situ annealings go residual stress method
Technical field
The invention belongs to precinct laser fusion material increasing field, it is related to a kind of selective laser fusing TC4 in-situ annealings to go Residual stress method.
Background technology
The appearance of precinct laser fusion increases material manufacturing technology (hereinafter referred to as SLM), reduces traditional machining mode in TC4 Waste of material in thin-wall workpiece manufacturing process, shortens the research and development of products cycle, and its excellent in mechanical performance.But it is restricted The influence such as material properties, laser parameter, scanning strategy, SLM increasing material manufacturing parts inner accumulations pole in rapid melting and solidification process Residual stress high, especially for the TC4 thin-wall parts of aviation field application, the residual stress successively accumulated is in print procedure Discharged in the way of deforming/ftractureing, cause test specimen that irreversible damage is just produced in forming process, cause high shaping to be lost Rate is lost, is greatly constrained and is prepared TC4 thin-wall parts using SLM technologies.
At present, there are two methods to tackle precinct laser thawing titanium alloy residual stress release problem, one is to enter test specimen Row stress relief annealing, how 201510508138.7 pairs eliminate residual stress and done detailed by controlling Post isothermal treatment technique Illustrate, the method is only applicable to complete the test specimen of shaping, another method is preheating printing substrate, reduces forming process Along the thermograde of powder deposition direction, weaken residual stress accumulation, but be limited to the temperature that machine internal components can bear, mesh Preceding business machine preheating temperature loading is general all at 200 DEG C or so, and TC4 needs nearly 750 DEG C and could realize stress relief annealing, institute Reduce TC4 thin-wall workpiece residual stress in manufacturing process to be badly in need of a kind of method simple to operate.
The content of the invention
The technical problems to be solved by the invention are：Reduce TC4 thin-wall workpieces residual stress accumulation in manufacturing process, Solve the cracking/deformational behavior in TC4 thin-wall part manufacturing processes.According to stress relief annealing principle, by SLM technical matters depths Enter research, propose the in-situ annealing method in SLM forming processes, i.e., to current printable layer coagulation surface input energy again, Residual stress size control is realized, reduces thin-wall workpiece residual stress accumulation in manufacturing process.
In view of this, residual stress method is gone it is an object of the invention to provide a kind of selective laser fusing TC4 in-situ annealings Above-mentioned purpose is reached, the present invention provides following technical scheme：
1. a kind of selective laser fusing TC4 in-situ annealings go residual stress method, comprise the following steps：
(1) one layer of titanium alloy powder is spread, current printing Titanium Powder last layer is melted and solidified；
(2) laser remolten is carried out to the individual layer that step (1) has melted and solidified, described remelting number of times is 1~10 time；
(3) repeat step (1)-(2) finish until TC4 thin-wall workpieces are manufactured.
Further, the process conditions of step (1) powder fusing are：Powdering 0.03~0.05mm of thickness, laser power 180~ 220W, 0.05~0.08mm of spot diameter, the μ s of time for exposure 110~130, laser spots are away from 0.07~0.08mm, sweep span The cheque board scan mode of 0.14-0.16mm, 5~10mm size.
Further, step (2) remelting condition is：150~190W of laser power, 0.14~0.5mm of spot diameter, during exposure Between 125~300 μ s, laser spots are away from 0.03~0.1mm, the cheque board scan of sweep span 0.04~0.1mm, 5~10mm size Mode, remelting energy density is more than 2.22J/mm2。
2. a kind of selective laser fusing TC4 in-situ annealings go residual stress method, comprise the following steps：
(1) one layer of titanium alloy powder is spread, current printing Titanium Powder last layer is melted and solidified；
(2) repeat step (1) 2~10 time, forms laminated titanium-alloy solidification layer；
(3) laser remolten, described remelting time are carried out to the laminated titanium-alloy solidification layer that step (2) has melted and solidified Number is 1~10 time；
(4) repeat step (1)-(3) finish until TC4 thin-wall workpieces are manufactured.
Further, the process conditions of step (1) powder fusing are：180~220W of laser power, spot diameter 0.05~ 0.08mm, the μ s of time for exposure 110~130, away from 0.07~0.08mm, 0.14-0.16mm, 5~10mm are big for sweep span for laser spots Small cheque board scan mode, 0.03~0.05mm of powdering thickness.
Further, step (3) remelting condition is：150~190W of laser power, 0.14~0.5mm of spot diameter, during exposure Between 125~300 μ s, laser spots are away from 0.03~0.1mm, the cheque board scan of sweep span 0.04~0.1mm, 5~10mm size Mode, remelting energy density is more than 2.22J/mm2。
The beneficial effects of the present invention are：TC4 thin-wall parts are prepared using selective laser melting process, are divided into the completion of two steps, The first step is that powder is melted and solidified, and second step is to having melted and solidifies single or multiple lift and carry out laser and melt again, is reduced Thermograde, reduces stress accumulation, improves microstructure, realizes annealing effect.The rapid shaping of TC4 thin-wall parts is realized, is pressed down Made the craze and transfiguration in print procedure, be conducive to precinct laser fusion manufacturing technology aviation field precise thin wall pieces manufacture in Popularization and application.
Brief description of the drawings
In order that the purpose of the present invention, technical scheme and beneficial effect are clearer, the present invention provides drawings described below and carries out Explanation：
Fig. 1 is that remelting energy density is 2.22~18J/mm2When TC4 thin-wall workpieces；
Fig. 2 is that remelting energy density is 0~1.79J/mm2When TC4 thin-wall workpieces；
Fig. 3 is TC4 thin-wall workpieces residual stress test point；
Fig. 4 is TC4 thin-wall workpiece residual stress test results.
Specific embodiment
Below in conjunction with accompanying drawing, the preferred embodiments of the present invention are described in detail.
Embodiment 1
Selective laser melting process is the process that successively powdering piles up fusing, and the present embodiment step is as follows：
(1) one layer of titanium alloy powder is spread, powdering thickness 0.05mm melts and solidify to current printing Titanium Powder last layer； The melting process of powder is：Laser power 200W, spot diameter 0.075, the μ s of time for exposure 125, laser spots are swept away from 0.075mm Retouch the cheque board scan mode of spacing 0.15mm, 5mm size；
(2) laser remolten is carried out to the individual layer that step (1) has melted and solidified, described remelting number of times is 1 time；Remelting Technique is：Laser power 190W, spot diameter 0.3mm, the μ s of time for exposure 200, laser spots are away from 0.05mm, sweep span The cheque board scan mode of 0.06mm, 5mm size, melts energy density and is set to again：0J/mm2、0.25J/mm2、0.49J/ mm2、0.60J/mm2、0.74J/mm2、1.19J/mm2、1.79J/mm2、2.22J/mm2、4.0J/mm2、7.5J/mm2、7.5J/ mm2、14J/mm2、14J/mm2、18J/mm2, melt energy again with each and print a sample, altogether 14 samples, counter sample Numbering is shown in Table 1, wherein 0J/mm2Representative does not carry out remelting, so as to Comparative result；
(3) repeat step (1)-(2) finish until TC4 thin-wall workpieces are manufactured.
The TC4 thin-wall parts of table 1 are numbered and corresponding relative energy density
Print result as depicted in figs. 1 and 2, when remelting energy density be more than 2.22J/mm2When, do not occur substantially cracking Phenomenon, when remelting energy density is less than 2.22J/mm2Or remelting is not carried out, there are different degrees of cracking behaviors.Fig. 3 is choosing The residual stress test point for taking, each sample chooses 3 test points of different zones.Test result as shown in figure 4, with do not enter The sample contrast of row remelting processing, TC4 thin-wall parts prepared by the present invention are reduced along the residual stress parallel to deposition direction 85%~97%, 81%~98% is reduced along the residual stress perpendicular to deposition direction, TC4 thin-wall parts are greatly inhibited in choosing Strain cracking behavior in area's laser melting process, greatly improves selective laser melting (SLM) molding technology and is made in Thin-walled Workpiece Make application.
Embodiment 2
Laminated titanium-alloy solidification layer can be initially formed, then laser remolten is carried out to it, the present embodiment step is as follows：
(1) one layer of titanium alloy powder is spread, powdering thickness 0.035mm melts and solidify to current printing Titanium Powder last layer； Laser power 190W, spot diameter 0.07mm, the μ s of time for exposure 110, away from 0.07mm, 0.16mm, 8mm are big for sweep span for laser spots Small cheque board scan mode；
(2) repeat step (1) 5 time, forms laminated titanium-alloy solidification layer；
(3) laser remolten, described remelting time are carried out to the laminated titanium-alloy solidification layer that step (2) has melted and solidified Number is 2 times, and remelting condition is：Laser power 160W, spot diameter 0.3mm, the μ s of time for exposure 200, laser spots are swept away from 0.06mm Retouch the cheque board scan mode of spacing 0.08mm, 8mm size, energy density 5.7J/mm2；
(4) repeat step (1)-(3) finish until TC4 thin-wall workpieces are manufactured.
Finally illustrate, preferred embodiment above is merely illustrative of the technical solution of the present invention and unrestricted, although logical Cross above preferred embodiment to be described in detail the present invention, it is to be understood by those skilled in the art that can be Various changes are made to it in form and in details, without departing from claims of the present invention limited range.

Claims (6)

1. a kind of selective laser fusing TC4 in-situ annealings go residual stress method, it is characterised in that comprise the following steps：
(1) one layer of titanium alloy powder is spread, current printing Titanium Powder last layer is melted and solidified；
(2) laser remolten is carried out to the individual layer that step (1) has melted and solidified, described remelting number of times is 1~10 time；
(3) repeat step (1)-(2) finish until TC4 thin-wall workpieces are manufactured.
2. method according to claim 1, it is characterised in that the process conditions of step (1) powder fusing are：Powdering thickness 0.03 ~0.05mm, 180~220W of laser power, 0.05~0.08mm of spot diameter, the μ s of time for exposure 110~130, laser spots away from 0.07~0.08mm, the cheque board scan mode of sweep span 0.14-0.16mm, 5~10mm size.
3. according to the method for claim 1 or 2, it is characterised in that step (2) remelting condition is：150~190W of laser power, 0.14~0.5mm of spot diameter, the μ s of time for exposure 125~300, laser spots away from 0.03~0.1mm, sweep span 0.04~ The cheque board scan mode of 0.1mm, 5~10mm size, remelting energy density is more than 2.22J/mm2。
4. a kind of selective laser fusing TC4 in-situ annealings go residual stress method, it is characterised in that comprise the following steps：
(1) one layer of titanium alloy powder is spread, current printing Titanium Powder last layer is melted and solidified；
(2) repeat step (1) 2~10 time, forms laminated titanium-alloy solidification layer；
(3) laser remolten is carried out to the laminated titanium-alloy solidification layer that step (2) has melted and solidified, described remelting number of times is 1~10 time；
(4) repeat step (1)-(3) finish until TC4 thin-wall workpieces are manufactured.
5. method according to claim 5, it is characterised in that the process conditions of step (1) powder fusing are：Powdering thickness 0.03 ~0.05mm, 180~220W of laser power, 0.05~0.08mm of spot diameter, the μ s of time for exposure 110~130, laser spots away from 0.07~0.08mm, the cheque board scan mode of sweep span 0.14-0.16mm, 5~10mm size.
6. according to the method for claim 4 or 5, it is characterised in that step (3) remelting condition is：150~190W of laser power, 0.14~0.5mm of spot diameter, the μ s of time for exposure 125~300, laser spots away from 0.03~0.1mm, sweep span 0.04~ The cheque board scan mode of 0.1mm, 5~10mm size, remelting energy density is more than 2.22J/mm2。
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Cited By (12)

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CN107900331A (en) * 2017-10-17 2018-04-13 安徽工程大学 A kind of laser 3D printing molding machine for effectively preventing metallic alloy piece from cracking
CN110405209A (en) * 2019-08-28 2019-11-05 上海工程技术大学 The method in situ for reducing precinct laser fusion preparation titanium composite material residual stress
CN110523986A (en) * 2019-09-25 2019-12-03 华南理工大学 A method of it is Fe-based amorphous based on precinct laser fusion forming agglomerate body
CN110640139A (en) * 2019-11-08 2020-01-03 黑龙江科技大学 Processing method for eliminating stress of powder-spreading type 3D printing workpiece with assistance of laser
CN110860797A (en) * 2019-11-08 2020-03-06 中国船舶重工集团公司第七二五研究所 Electric arc-laser composite additive manufacturing method
CN111266574A (en) * 2019-12-11 2020-06-12 西安航天发动机有限公司 Integral manufacturing method of pin type head interlayer shell of aerospace engine
WO2020211887A1 (en) * 2019-04-17 2020-10-22 MTU Aero Engines AG Layer building process and layer building apparatus for the additive manufacture of at least one wall of a component, as well as computer program product and storage medium
CN112008079A (en) * 2020-08-30 2020-12-01 中南大学 Method for improving mechanical property of 3D printing nickel-based superalloy through in-situ heat treatment
CN112658279A (en) * 2020-11-30 2021-04-16 华南理工大学 Method for in-situ treatment of 4D printing component
CN111455216B (en) * 2020-05-27 2021-07-23 长安大学 TC 4-like titanium alloy for laser additive manufacturing application
CN113492529A (en) * 2020-04-07 2021-10-12 中国科学院化学研究所 3D printing method and printing system with near-infrared semiconductor laser as heating source
CN114985765A (en) * 2022-08-03 2022-09-02 北京煜鼎增材制造研究院有限公司 Laser melting direct material increase method for titanium alloy blisk selected area

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CN105750543A (en) * 2016-03-03 2016-07-13 西安铂力特激光成形技术有限公司 Checkerboard-type laser scanning route planning method
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CN102120261A (en) * 2011-04-20 2011-07-13 林锦新 Method for preparing titanium product
WO2013079581A1 (en) * 2011-11-29 2013-06-06 Matthias Fockele Process for producing a shaped body by layerwise buildup from material powder
US20140034626A1 (en) * 2012-08-06 2014-02-06 Materials Solutions Additive manufacturing
CN103160825A (en) * 2013-03-18 2013-06-19 张翀昊 Method for improving metal 3D (three-dimensional) printing compactness by utilizing synchronous double-beam laser
CN104368814A (en) * 2014-11-11 2015-02-25 西安交通大学 Method for directly molding high-entropy alloy turbine engine hot end component through laser metal
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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107900331B (en) * 2017-10-17 2019-12-06 安徽工程大学 laser 3D printing forming equipment capable of effectively preventing metal alloy component from cracking
CN107900331A (en) * 2017-10-17 2018-04-13 安徽工程大学 A kind of laser 3D printing molding machine for effectively preventing metallic alloy piece from cracking
WO2020211887A1 (en) * 2019-04-17 2020-10-22 MTU Aero Engines AG Layer building process and layer building apparatus for the additive manufacture of at least one wall of a component, as well as computer program product and storage medium
CN110405209A (en) * 2019-08-28 2019-11-05 上海工程技术大学 The method in situ for reducing precinct laser fusion preparation titanium composite material residual stress
CN110523986A (en) * 2019-09-25 2019-12-03 华南理工大学 A method of it is Fe-based amorphous based on precinct laser fusion forming agglomerate body
CN110640139B (en) * 2019-11-08 2022-02-08 黑龙江科技大学 Processing method for eliminating stress of powder-spreading type 3D printing workpiece with assistance of laser
CN110640139A (en) * 2019-11-08 2020-01-03 黑龙江科技大学 Processing method for eliminating stress of powder-spreading type 3D printing workpiece with assistance of laser
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CN112008079B (en) * 2020-08-30 2022-03-29 中南大学 Method for improving mechanical property of 3D printing nickel-based superalloy through in-situ heat treatment
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