CN106180719B - IN718 component, system, heat treatment method and the device of selective laser fusing increasing material manufacturing - Google Patents
IN718 component, system, heat treatment method and the device of selective laser fusing increasing material manufacturing Download PDFInfo
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- CN106180719B CN106180719B CN201610856349.4A CN201610856349A CN106180719B CN 106180719 B CN106180719 B CN 106180719B CN 201610856349 A CN201610856349 A CN 201610856349A CN 106180719 B CN106180719 B CN 106180719B
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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
- B22F10/20—Direct sintering or melting
- B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
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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
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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
- B22F10/30—Process control
- B22F10/36—Process control of energy beam parameters
- B22F10/366—Scanning parameters, e.g. hatch distance or scanning strategy
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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
- 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
- B22F3/003—Apparatus, e.g. furnaces
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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
- 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
- B33Y30/00—Apparatus for additive manufacturing; Details thereof or accessories therefor
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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
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt 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
- B22F12/00—Apparatus or devices specially adapted for additive manufacturing; Auxiliary means for additive manufacturing; Combinations of additive manufacturing apparatus or devices with other processing apparatus or devices
- B22F12/60—Planarisation devices; Compression devices
- B22F12/67—Blades
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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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- 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
- B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
- B22F2998/10—Processes characterised by the sequence of their steps
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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
- B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
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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
Abstract
The present invention relates to IN718 component, system, heat treatment method and the devices of a kind of fusing increasing material manufacturing of selective laser.IN718 component laser power when selective laser is melted and shaped is 275-800W, spot diameter 0.1-0.2mm, scanning speed 900-1400mm/s, and powdering thickness is 0.04-0.08mm.The heat treatment method is comprising steps of be placed in progress vacuum annealing heat treatment in vacuum heat treatment furnace for the IN718 component of forming.The annealing device includes vacuum heat treatment furnace.The system of selective laser fusing increasing material manufacturing IN718 comprising 3D printer further includes the vacuum heat treatment furnace after the 3D printer process.The residual stress generated in print procedure the invention enables IN718 alloy components is eliminated, and tissue is obviously homogenized, and promotes its corrosion resistance, obdurability etc. very well, can meet requirement of the Aerospace Products to IN718 alloy structure part.
Description
Technical field
The invention mainly relates to metal material increasing fields more particularly to a kind of selective laser to melt increasing material manufacturing
IN718 component, system, heat treatment method and device.
Background technique
Nickel base superalloy has excellent anti-oxidant, corrosion-resistant and high temperature resistance, can be widely applied to aeroplane engine
Machine turbo blade, petrochemical industry and ship need anti-corrosion critical component.In718 nickel base superalloy is a kind of ageing strengthening type nickel
Based high-temperature alloy is with higher strong within the scope of -253 DEG C -650 DEG C using nickel as matrix (content is generally higher than 50% or more)
Degree, plasticity and good anti-oxidant, anticorrosive, Weldability, therefore have extensively in the fields such as aerospace, nuclear energy, petroleum
Using there is the laudatory title of " omnipotent alloy ".
The main intensified element of In718 high temperature alloy is Nb, accounts for about the left and right 5% (wt) of total specific gravity, the reinforcing in alloy
Organize main γ ' precipitated phase (Ni3(Al, Ti, Nb) face-centered cubic) and γ " phase (Ni3Nb body-centered tetragonal), MC carbonization is precipitated in crystal boundary
Object and δ phase.
These main hardening constituents in IN718 alloy are precipitated slowly, by casting or the alloy substrate γ of high temperature forging
Mutually have little time to be precipitated γ ' in cooling procedure mutually with γ ' ' phase, material mechanical performance at this time is poor, needs at heat appropriate
Reason, make to be precipitated in crystal grain equally distributed γ ' mutually with γ ' ' phase, to achieve the purpose that industrial application.In solid solution and ageing treatment
In the process, the parameters such as cooling rate, temperature, time can all influence the precipitation of hardening constituent in matrix, to influence the mechanics of material
Performance.IN718 alloy is a kind of precipitation strength type ferronickel based high-temperature alloy, can control alloy by adjusting heat treating regime
Grain size, it is most important that control γ ' precipitated phase (Ni3(Al, Ti, Nb) face-centered cubic) and γ " phase (Ni3Nb body-centered tetragonal), it is brilliant
Pattern, distribution and the quantity that MC carbide and δ phase is precipitated in boundary are answered to obtain the mechanical property of different stage with meeting difference
Needs.Currently, international and domestic general IN718 alloy heat treating regime has two classes (when solid solution+two-stage time effect or twin-stage
Effect).
Increasing material manufacturing is a kind of high-new manufacturing technology based on material stacking method, a kind of no longer to need traditional cutter, folder
Tool and lathe can make any shape.It collects mechanical engineering, CAD, reverse Engineering Technology, Layered Manufacturing Technology, numerical control
Design philosophy, can automatically, directly, quickly and accurately be changed into one by technology, material science, laser technology
Determine the prototype or direct manufacturing parts of function.
Selective laser fusing is as one of common three kinds of modes of current metal increasing material manufacturing, it can be achieved that high-precision, high surface
Finish, complex component is integrally formed, has complicated inner cavity structure, thin-wall construction, grid Lightened structure especially suitable for manufacture
Difficult machining titanium alloy, the parts such as high temperature alloy, states such as GE, Air Passenger, Sai Feng, Air China's industry, space flight section work, middle ship heavy industry at present
Inside and outside enterprise has started even batch and has used selective laser fusing forming IN718 nickel base superalloy product.
When laser residence is in powder, metal powder temperature rises suddenly and is more than the fusing point formation molten bath of metal, at this point,
Molten metal is in liquid equilibrium, and metallic atom can move freely, and alloying element is uniformly distributed；After laser is mobile, due to
The disappearance of heat source, molten bath solidify (about 10 at a terrific speed3-105K/S).In the process, metallic atom and alloying element
Diffusion it is mobile restricted, it is suppressed that the segregation of crystal grain grown up with alloying element, the metal structure crystal grain after solidification is tiny, alloy
Elemental redistribution is uniform, can greatly improve the intensity and toughness of material.Therefore, the metal parts tool that selective laser is melted and molded
There are the advantages such as consistency is high, crystal grain is tiny, even tissue, mechanical property are excellent.
Since the quick thermodynamics of solidification and kinetic character of precinct laser fusion forming are different from coagulating under usual conditions
Gu causing quickly to solidify along with strong nonequilibrium effect.The forming temperature of usual precinct laser fusion forming IN718 exists
2000 DEG C or more, and environment substrate temperature is often in 200 DEG C hereinafter, liquid phase false set under high supercooling degree state, solidified
Journey be it is non-equilibrium, matrix γ is in hypersaturated state, and melt tank edge is different from center portion crystallite dimension and institutional framework, whole group
It knits that state is very unstable, causes IN718 component strength lower and component inside has very big residual stress, it must be by subsequent
Heat treatment process improve its structure property.
Therefore, in order to obtain with the IN718 component of excellent properties, forming IN718 material is melted for selective laser
Process characteristic, in order to discharge the residual stress of IN718 component of selective laser fusing increasing material manufacturing method forming, tissue is obtained
Homogenization obtains good obdurability matching, corrosion-resistant, high temperature resistance, to meet Aerospace Products to IN718 alloy knot
The requirement of component, it is necessary to propose that IN718 component and the manufacture system of the forming of increasing material manufacturing method are melted in a kind of suitable selective laser
System, heat treatment method and its device.
Summary of the invention
In view of the above-mentioned problems, the object of the present invention is to provide a kind of IN718 component of selective laser fusing increasing material manufacturing, being
System, heat treatment method and device, to obtain the IN718 component with excellent properties, and were printing IN718 alloy components
The residual stress generated in journey is eliminated, and tissue is obviously homogenized, and mentions its corrosion resistance, obdurability etc. very well
It rises, requirement of the Aerospace Products to IN718 alloy structure part can be met.
The present invention provides a kind of IN718 component of selective laser fusing increasing material forming, and the IN718 component is in selective laser
Laser power is 275-800W, spot diameter 0.1-0.2mm, scanning speed 900-1400mm/s, powdering when fusing forming
Thickness is 0.04-0.08mm.
The present invention provides the heat treatment method of selective laser fusing increasing material manufacturing IN718 a kind of, the method includes the steps:
The IN718 component of forming is placed in progress vacuum annealing heat treatment in vacuum heat treatment furnace.
Above-mentioned method, the vacuum annealing heat treatment includes: that temperature in vacuum heat treatment furnace is warming up to 600-700 DEG C
After keep the temperature 20-40min.
Above-mentioned method, the vacuum annealing heat treatment includes: that temperature in vacuum heat treatment furnace is warming up to 950-1050
2-4h is kept the temperature after DEG C.
Above-mentioned method, the vacuum annealing heat treatment includes: that vacuum heat treatment furnace is evacuated down to 10-3-10-4Pa；It will
It is heated up in vacuum heat treatment furnace with the speed of 5-10 DEG C/min.
Above-mentioned method, the vacuum annealing heat treatment include: described in the forming board companion by the IN718 component
Vacuum annealing is heat-treated IN718 component together；Cool to IN718 component with the furnace room temperature.
Above-mentioned method, the vacuum annealing heat treatment are that single track is annealed.
Above-mentioned method, IN718 component intensity after vacuum annealing is heat-treated are reached in 1100MPa or more, elongation percentage
To 20% or more, hardness is greater than 42HRC.
The present invention provides the annealing device of selective laser fusing increasing material manufacturing IN718 a kind of, and described device includes vacuum
Heat-treatment furnace.
The present invention also provides the systems of selective laser fusing increasing material manufacturing IN718 a kind of comprising 3D printer further includes
Vacuum heat treatment furnace after the 3D printer process.
Technical solution of the present invention, the IN718 alloy components after above-mentioned heat treatment, what component generated in print procedure
Residual stress is eliminated, tissue obviously homogenized, the second phased soln into austenitic matrix after it is uniform in the cold process of furnace
It is precipitated, promotes its corrosion resistance very well；Its room temperature tensile intensity reaches not less than 1100MPa simultaneously, extends at the same time
Rate reaches 20% or more, and hardness can be greater than 42HRC, thus it is resistance to IN718 alloy structure part to meet some Aerospace Products
The requirement of burn into high intensity, high rigidity and high-ductility.
Detailed description of the invention
Fig. 1 is IN718 alloy components heat treatment process schematic diagram of the present invention；
Fig. 2 is the structural schematic diagram of vacuum heat treatment furnace of the present invention.
Specific embodiment
Below in conjunction with drawings and examples, a specific embodiment of the invention is described in more details, so as to energy
The advantages of enough more fully understanding the solution of the present invention and its various aspects.However, specific embodiments described below and reality
It applies example to be for illustrative purposes only, rather than limiting the invention.
The system of fusing increasing material manufacturing IN718 in selective laser provided by the invention comprising at 3D printer and Vacuum Heat
Manage furnace.Vacuum heat treatment furnace, can be separately as IN718 production technology for being heat-treated to the IN718 component after forming
Annealing device.
3D printer mainly includes laser, optical system, processing platform system and powder powdering system etc..
The 3D printing method of IN718 component is as follows: after the completion of the design of IN718 component and auxiliary support structure design, by three
Dimension mould and Auxiliary support hierarchy slicing, after importing former, the scraper of selective laser melting appartus is first very thin one
Layer metal powder is equably layered on substrate, and high energy laser beam is selectively melted according to the data information of three-dimensional digital-to-analogue current layer
Change the powder on substrate, shapes the shape of part current layer, then scraper repaves one layer of metal in manufactured level
Powder, high energy beam laser carry out selection fusing according to next layer data information of digital-to-analogue, so on circulate until entire part
Complete manufacture.
IN718 alloy precinct laser fusion technological parameter are as follows: laser power 275-800W, spot diameter 0.1-
0.2mm, scanning speed 900-1400mm/s, powdering thickness are 0.04-0.08mm.
The IN718 component completed is manufactured followed by heat treatment.
Since the quick thermodynamics of solidification and kinetic character of selective laser fusing forming are different from coagulating under usual conditions
Gu causing quickly to solidify along with strong nonequilibrium effect.
The forming temperature of usual precinct laser fusion forming IN718 is at 2000 DEG C or more, and environment temperature is often in 200 DEG C
Hereinafter, liquid phase false set under high supercooling degree state, process of setting is non-equilibrium, so that at the matrix γ in IN718 tissue
In hypersaturated state, and melt tank edge is different from center portion crystallite dimension and phase constitution, and structural state is very unstable, causes
The intensity of IN718 component is lower and component inside has very big residual stress, therefore must be improved by subsequent heat treatment process
Its structure property.
The present invention is in view of the above-mentioned problems, specially have developed the heat treatment side of selective laser fusing increasing material manufacturing IN718 a kind of
Method, comprising: first clean out the powder on the IN718 component and forming board of forming；It then can be by substrate and component together
It is put into vacuum heat treatment furnace, IN718 component only can also be put into vacuum heat treatment furnace certainly, but because part and substrate segmentation can
Part Auxiliary support can be caused to fail, lead to part deformation, thermal effectiveness may be without carrying out hot place in company with one piece of substrate
It manages.And heat-treatment furnace is evacuated down to 10-3-10-4Pa is then warming up to 600-700 DEG C of heat preservation with the speed of 5-10 DEG C/min
20-40min then continues to make IN718 component cool to room temperature with the furnace after being warming up to 900-1000 DEG C of heat preservation 2-4h, so far at heat
Reason process is completed.Burner hearth is then unloaded into vacuum to atmospheric pressure again, takes out workpiece.
The complex art that vacuum heat treatment, that is, vacuum technique is combined with two professions of heat treatment, refers to heat treatment process
All carried out under vacuum conditions with part.Vacuum heat treatment furnace is to obtain the advanced heat treatment of large development in recent years to set
Standby, workpiece is heated and is cooled down in super hypobaric space.It has high-quality, energy saving, safety and pollutes few etc.
Advantage.
Vacuum heat treatment furnace thermal efficiency it is high, it can be achieved that be rapidly heated and cool down, it can be achieved that non-oxidation, without decarburization, without carburizing,
The phosphorus bits of workpiece surface can be removed, and have the effects of degreasing degasification, to achieve the effect that surface-brightening purifies.In general,
Processed workpiece heats slowly in furnace, and the interior hot temperature difference is smaller, and thermal stress is small, thus deforms small, product qualification rate height.
Further, vacuum heat treatment can reduce cost, there is getter action, to improve the mechanical performance of work and make
Use the service life.Its working environment is good, safe operation, does not pollute and public hazards.Processed workpiece does not have hydrogen embrittlement dangerous, at Vacuum Heat
The stability of science and engineering skill and reproducible.It, can high degree thus for the aerospace of the invention being directed to is with material IN718
Ground ensures its physicochemical characteristic and surface cleanliness, reduces processing cost, improves processing efficiency.
Above-mentioned heat treatment process schematic diagram is as shown in Figure 1.Wherein " FC " represents furnace cooling.
The structure of vacuum heat treatment furnace is as shown in Figure 2.
The main structure of vacuum heat treatment furnace is furnace body 1, is stamped bell 2 above furnace body, vacuum heat treatment furnace further includes furnace
The pillar 3 of 1 lower section of body, the calandria 4 in furnace body 1 for being heated to furnace interior, and it is true for being taken out to vacuum heat treatment furnace
Empty molecular pump 5.
IN718 alloy components after above-mentioned process, the thermal stress occurred in print procedure are substantially eliminated, are organized
To obvious homogenization, the second phased soln is then uniformly precipitated during furnace is cold into austenitic matrix, obtains corrosion resistance very
It is good to be promoted；Its intensity reaches not less than 1100MPa, and elongation percentage reaches 20% or more at the same time, and hardness is greater than 42HRC, can expire
The some Aerospace Products of foot are corrosion-resistant to IN718 alloy structure part, high-intensitive, high rigidity and high-ductility requirement.
Embodiment 1
The manufacture system using the manufacture IN718 alloy components in embodiment of the invention to IN718 alloy components at
Shape, IN718 alloy precinct laser fusion technological parameter are as follows: laser power 275W, spot diameter 0.10mm, scanning speed are
800mm/s, powdering thickness are 0.04mm.
The IN718 component that manufacture is completed is heat-treated.
First IN718 component is placed in vacuum heat treatment furnace, heat-treatment furnace is evacuated down to 10-3Pa, then with 10 DEG C/
The speed of min is warming up to 600 DEG C or so heat preservation 20min, then continues to make after being warming up to 950 DEG C or so heat preservation 2h with aforementioned speed
IN718 component cools to room temperature with the furnace, and so far heat treatment process is completed.Burner hearth is then unloaded into vacuum to atmospheric pressure again, takes out work
Part.
IN718 alloy components after above-mentioned process, the thermal stress occurred in print procedure are substantially eliminated, are organized
To obvious homogenization, the second phased soln is then uniformly precipitated during furnace is cold into austenitic matrix, obtains corrosion resistance very
It is good to be promoted；Its intensity reaches not less than 1100MPa, and elongation percentage reaches 20% or more at the same time, and hardness can reach 43HRC, can
Meet that some Aerospace Products are corrosion-resistant to IN718 alloy structure part, requirement of high-intensitive, high rigidity and high-ductility.
Embodiment 2
The manufacture system using the manufacture IN718 alloy components in embodiment of the invention to IN718 alloy components at
Shape, IN718 alloy precinct laser fusion technological parameter are as follows: laser power 800W, spot diameter 0.2mm, scanning speed are
1400mm/s, powdering thickness are 0.08mm.
The IN718 component that manufacture is completed is heat-treated.
First IN718 component is placed in vacuum heat treatment furnace, heat-treatment furnace is evacuated down to 10-4Pa, then with 5 DEG C/min
Speed be warming up to 700 DEG C or so heat preservation 40min, then continue to be warming up to make after 1050 DEG C or so heat preservation 4h IN718 component with
Furnace is cooled to room temperature, and so far heat treatment process is completed.Burner hearth is then unloaded into vacuum to atmospheric pressure again, takes out workpiece.
IN718 alloy components after above-mentioned process, the thermal stress occurred in print procedure are substantially eliminated, are organized
To obvious homogenization, the second phased soln is then uniformly precipitated during furnace is cold into austenitic matrix, obtains corrosion resistance very
It is good to be promoted；Its intensity reaches not less than 1100MPa, and elongation percentage reaches 20% or more at the same time, and hardness can expire up to 44HRC
The some Aerospace Products of foot are corrosion-resistant to IN718 alloy structure part, high-intensitive, high rigidity and high-ductility requirement.
Embodiment 3
The manufacture system using the manufacture IN718 alloy components in embodiment of the invention to IN718 alloy components at
Shape, IN718 alloy precinct laser fusion technological parameter are as follows: laser power 540W, spot diameter 0.15mm, scanning speed are
1200mm/s, powdering thickness are 0.06mm.
The IN718 component that manufacture is completed is heat-treated.
First IN718 component is placed in vacuum heat treatment furnace, heat-treatment furnace is evacuated down to 5x10-4Pa, then with 7.5
DEG C/speed of min is warming up to 650 DEG C or so heat preservation 30min, it then continues to make IN718 after being warming up to 1000 DEG C or so heat preservation 3h
Component cools to room temperature with the furnace, and so far heat treatment process is completed.Burner hearth is then unloaded into vacuum to atmospheric pressure again, takes out workpiece.
IN718 alloy components after above-mentioned process, the thermal stress occurred in print procedure are substantially eliminated, are organized
To obvious homogenization, the second phased soln is then uniformly precipitated during furnace is cold into austenitic matrix, obtains corrosion resistance very
It is good to be promoted；Its intensity reaches not less than 1100MPa, and elongation percentage reaches 20% or more at the same time, and hardness can reach 43HRC, can
Meet that some Aerospace Products are corrosion-resistant to IN718 alloy structure part, requirement of high-intensitive, high rigidity and high-ductility.
Finally, it should be noted that obviously, the above embodiment is merely an example for clearly illustrating the present invention, and simultaneously
The non-restriction to embodiment.For those of ordinary skill in the art, it can also do on the basis of the above description
Other various forms of variations or variation out.There is no necessity and possibility to exhaust all the enbodiments.And thus drawn
The obvious changes or variations that Shen goes out are still in the protection scope of this invention.
Claims (3)
1. a kind of heat treatment method of selective laser fusing increasing material manufacturing IN718, which is characterized in that the method includes the steps:
The IN718 component of forming is placed in progress vacuum annealing heat treatment in vacuum heat treatment furnace；
Firstly, vacuum heat treatment furnace is evacuated down to 10-3-10-4Pa；
Then, 20-40min is kept the temperature after 600-700 DEG C being warming up in vacuum heat treatment furnace with the speed of 5-10 DEG C/min；
Then, 2-4h is kept the temperature after temperature in vacuum heat treatment furnace being warming up to 950-1050 DEG C；
Then, IN718 component is cooled to room temperature with vacuum heat treatment furnace；
Finally, vacuum heat treatment furnace is unloaded vacuum to atmospheric pressure, IN718 component is taken out.
2. the method as described in claim 1, which is characterized in that the vacuum annealing heat treatment is that single track is annealed.
3. the method as described in claim 1, which is characterized in that IN718 component room temperature after vacuum annealing is heat-treated is anti-
Tensile strength is in 1100MPa or more, and elongation percentage reaches 20% or more, and hardness is greater than 42HRC.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610856349.4A CN106180719B (en) | 2016-09-27 | 2016-09-27 | IN718 component, system, heat treatment method and the device of selective laser fusing increasing material manufacturing |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610856349.4A CN106180719B (en) | 2016-09-27 | 2016-09-27 | IN718 component, system, heat treatment method and the device of selective laser fusing increasing material manufacturing |
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| Publication Number | Publication Date |
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| CN106180719A CN106180719A (en) | 2016-12-07 |
| CN106180719B true CN106180719B (en) | 2019-01-18 |
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