CN114101706A - Laser additive manufacturing method for heterogeneous metal - Google Patents
Laser additive manufacturing method for heterogeneous metal Download PDFInfo
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- CN114101706A CN114101706A CN202111434932.3A CN202111434932A CN114101706A CN 114101706 A CN114101706 A CN 114101706A CN 202111434932 A CN202111434932 A CN 202111434932A CN 114101706 A CN114101706 A CN 114101706A
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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
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/64—Treatment of workpieces or articles after build-up by thermal means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/66—Treatment of workpieces or articles after build-up by mechanical means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
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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
- B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
- B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
- B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
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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
- B33Y40/00—Auxiliary operations or equipment, e.g. for material handling
- B33Y40/20—Post-treatment, e.g. curing, coating or polishing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y80/00—Products made by additive manufacturing
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- 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
According to the laser additive manufacturing method for the dissimilar metal, provided by the invention, after the first metal component is prepared, the first metal component is subjected to stress removal, texturing and other treatments, so that a brittle intermetallic compound generated at a joint in the process of additive manufacturing of a dissimilar metal composite structure can be effectively avoided, the comprehensive mechanical property of the member of the dissimilar metal composite structure is effectively improved, and high-quality laser additive manufacturing of the dissimilar alloy is realized.
Description
Technical Field
The invention relates to the field of laser additive manufacturing, in particular to a laser additive manufacturing method for heterogeneous metal.
Background
With the advent of high power lasers, laser additive technology has been rapidly developed. Compared with the traditional method, the laser additive material direction is very flexible, the omnidirectional directional growth of a complex structure can be carried out, the microstructure additive material manufacturing can be carried out, the deformation of a heat affected zone is small, the forming quality is good, and in addition, refractory materials such as: titanium, tungsten alloys, and the like.
In order to meet the development requirements of light structure, structural function integration and low-cost design and manufacture, the performance advantages of different materials are comprehensively utilized, and materials with different characteristics are combined for use, so that more and more attention is paid. For example, titanium alloys are relatively strong and resistant to high temperatures, but are relatively expensive. Aluminum alloys are low density and relatively inexpensive, and therefore, when desired for special applications, aluminum/titanium composite structures may be used. In the aspect of aerospace, the American NASA YF-12 fighter wing adopts a honeycomb sandwich structure, a titanium alloy skin is connected with an aluminum alloy honeycomb sandwich in a wing box, and a radiating fin of an engine room is assembled on a titanium alloy pipe through a 3003 aluminum alloy blade. The airbus adopts a titanium plate and aluminum rib composite structure to connect the airplane seat guide rail and an area which is easy to corrode, so that the weight of the airplane body is reduced, the manufacturing cost is reduced, and the corrosion resistance is improved. In the automotive industry, Titan, Germany, has developed an automotive titanium/aluminum exhaust system that is 40% lighter in weight than a steel exhaust system. The system can withstand high temperatures above 800 ℃, and this material is suitable for the processing of all exhaust components after the catalytic converter. Therefore, the combined use of aluminum alloys and titanium alloys has become a trend in the aerospace industry and the automobile manufacturing industry. The traditional two metal combinations are mostly connected by bolts, riveted joints or glued joints, the joint strength is low, and the combination effect cannot be exerted.
Because the physical and chemical properties of the two materials are greatly different, if the melting welding is directly adopted, the brittle intermetallic compound which is easily formed on the bonding interface increases the risks of crack generation on the alloy bonding surface and integral cracking of parts, and reduces the bonding strength, so that the reduction of the precipitation of the brittle phase of the bonding surface has important significance for improving the strength of the composite structure of the laser additive manufacturing aluminum/titanium under the condition of ensuring the heat input.
Disclosure of Invention
The invention aims to provide a laser additive manufacturing method for a heterogeneous metal, which can reduce the precipitation of a brittle phase on a joint surface and further improve the composite structure strength of laser additive.
In order to achieve the purpose, the invention provides the following scheme:
a method of laser additive manufacturing of a dissimilar metal, comprising:
performing laser additive manufacturing on the first metal on the preprocessed substrate by adopting a laser according to a preset digital-analog track to obtain a first metal component, and performing stress relief processing on the first metal component;
texturing the first metal component, and coating the pretreated second metal powder on the textured first metal component according to a set thickness; the melting point of the second metal powder is lower than the melting point of the first metal;
after a set condition is met, placing the roughened first metal component coated with the second metal powder in a vacuum heat treatment furnace for heating for a preset time to obtain a second metal component; the heating temperature of the vacuum heat treatment furnace is set to be higher than the melting point of the second metal powder and lower than the melting point of the first metal;
continuously depositing second metal powder on the second metal component by using a laser additive technology to obtain a third metal component; the third metal component is the laser additive structure obtained by preparation.
Preferably, the laser is adopted to perform laser additive manufacturing on the pretreated substrate according to a preset digital-analog trajectory, and the method further includes:
polishing the substrate, and removing stains on the polished substrate by using an organic solvent to obtain a pretreated substrate;
and after the position of the pretreated substrate is adjusted, fixing the substrate after the position adjustment by using a clamp.
Preferably, the organic solvent is absolute ethanol.
Preferably, the first metal is a metal powder dried under a vacuum environment.
Preferably, the first metal is a titanium alloy powder.
Preferably, the process of pretreating the second metal powder comprises:
immersing the second metal powder in a volatilizable solvent, and taking out settled powder after the second metal powder is completely settled at the bottom of the volatilizable solvent; and the settled powder is the pretreated second metal powder.
Preferably, the second metal powder is an aluminum alloy powder.
Preferably, the set condition is that the volatilizable solvent carried in the pretreated second metal powder is completely volatilized.
Preferably, the set thickness is 0.1mm to 1 mm.
Preferably, the preset time is 5min-20 min.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
according to the laser additive manufacturing method for the dissimilar metal, provided by the invention, after the first metal component is prepared, the first metal component is subjected to stress removal, texturing and other treatments, so that a brittle intermetallic compound generated at a joint in the process of additive manufacturing of a dissimilar metal composite structure can be effectively avoided, the comprehensive mechanical property of the member of the dissimilar metal composite structure is effectively improved, and high-quality laser additive manufacturing of the dissimilar alloy is realized.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without inventive exercise.
Fig. 1 is a flow chart of a laser additive manufacturing method for a dissimilar metal provided by the invention;
fig. 2 is an overall implementation architecture diagram of a laser additive manufacturing method for a dissimilar metal according to an embodiment of the present invention;
FIG. 3 is a schematic view of a titanium-aluminum alloy composite structure thin-wall component manufactured by a heterogeneous metal laser additive manufacturing method according to an embodiment of the present invention;
FIG. 4 is a schematic view of an aluminum alloy powder preset according to an embodiment of the present invention;
FIG. 5 is a schematic structural diagram of a component prepared with aluminum alloy powder and placed in a vacuum heat treatment furnace to be melted according to an embodiment of the present invention;
fig. 6 is a schematic view of a thin-walled component manufactured by continuously performing laser additive manufacturing on an aluminum alloy metal layer according to an embodiment of the present invention.
Description of the symbols:
the method comprises the following steps of 1-aluminum alloy thin wall, 2-aluminum alloy preset layer, 3-titanium alloy thin wall, 4-titanium alloy substrate and 5-preset aluminum alloy powder.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide a laser additive manufacturing method for a heterogeneous metal, which can reduce the precipitation of a brittle phase on a joint surface and further improve the composite structure strength of laser additive.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
As shown in fig. 1, the method for laser additive manufacturing of a dissimilar metal provided by the present invention includes:
step 100: and performing laser additive manufacturing on the first metal on the pretreated substrate by adopting a laser according to a preset digital-analog track to obtain a first metal component, and performing stress relief treatment on the first metal component. The pretreatment process of the substrate comprises the following steps: polishing the substrate, and removing stains on the polished substrate by using an organic solvent (such as absolute ethyl alcohol) to obtain a pretreated substrate. And after the position of the pretreated substrate is adjusted, fixing the substrate after the position adjustment by using a clamp. For example, the first metal is titanium alloy powder dried under a vacuum environment.
Step 101: and texturing the first metal component, and coating the pretreated second metal powder on the textured first metal component according to a set thickness. The melting point of the second metal powder is lower than the melting point of the first metal. Wherein the process of pre-treating the second metal powder comprises:
and immersing the second metal powder in the volatilizable solvent, and taking out the settled powder after the second metal powder is completely settled at the bottom of the volatilizable solvent. And the settled powder is the pretreated second metal powder. For example, the second metal powder is an aluminum alloy powder.
In the present invention, the set thickness may be 0.1mm to 1mm, but is not limited thereto.
Step 102: and after the set conditions are met, placing the roughened first metal component coated with the second metal powder in a vacuum heat treatment furnace for heating for a preset time to obtain a second metal component. The heating temperature of the vacuum heat treatment furnace is set to be higher than the melting point of the second metal powder and lower than the melting point of the first metal. The setting condition can be that the volatilizable solvent carried in the pretreated second metal powder is completely volatilized, or the second metal powder can be placed for a specific time according to practical experience. In the present invention, the preset time may be in the range of 5min to 20min, but is not limited thereto.
Step 103: and continuously depositing second metal powder on the second metal component by using a laser additive technology to obtain a third metal component. The third metal component is the laser additive structure obtained by preparation.
Based on the above, it can be obtained that the present invention is mainly obtained by presetting a layer of low melting point metal B powder (i.e., second metal powder) on the surface of high melting point metal a (i.e., first metal member) that has completed additive manufacturing to obtain C, then heating through a heat treatment furnace to melt and spread it on the surface of high melting point metal a to obtain C1 (i.e., second metal member), and then continuing laser additive manufacturing of low melting point metal B on the preset metal layer of low melting point B to obtain D (i.e., third metal member). Compared with the prior art that the low-melting-point metal B is directly manufactured on the surface of the high-melting-point metal A in an additive laser mode, the method can effectively avoid intermetallic brittleness caused by easy metallurgical bonding during the laser additive manufacturing of the dissimilar metal, improves the connection strength of the bonding interface of the laser additive manufacturing composite structure of the dissimilar metal, and realizes high-quality laser additive manufacturing of the dissimilar alloy.
The following describes a specific implementation process of the laser additive manufacturing method for a heterogeneous metal according to the present invention, by taking the implementation architecture shown in fig. 2 as an example.
As shown in fig. 2, the specific implementation process is as follows:
step 1: preparation before laser additive manufacturing of high-melting-point metal A
Drying metal powder used in an experiment in a vacuum environment, polishing the surface of a substrate to be smooth, removing surface stains by using absolute ethyl alcohol and alcohol cotton, adjusting the position of the substrate to enable a laser to be free from interference with other components during manufacturing, and fixing the substrate by using a tool clamp. The laser is then mounted on an industrial robot and adjusted to the initial position for laser additive manufacturing.
Step 2: laser additive manufacturing of high melting point metal A
And setting the manufacturing parameters of the laser and starting a laser additive manufacturing system to enable the laser to perform laser additive manufacturing on the high-melting-point metal A (namely the first metal) along the designed digital-analog track. After completion, a formed structural member (i.e., a first metal member) of the high melting point metal a is obtained and subjected to a stress relieving treatment.
And step 3: high melting point metal A surface treatment for laser additive manufacturing
The bonding regions of the high melting point metal A and the low melting point metal B are treated. The method comprises the steps of texturing the surface of high-melting-point metal A (namely a first metal component) so that the high-melting-point metal A is easy to wet with low-melting-point metal B, immersing powder of the low-melting-point metal B (namely second metal powder) in a volatilizable solvent for sufficient wetting, taking out settled powder after the powder is settled to the bottom of a solution, uniformly coating the settled powder on the surface of the formed metal A, shaping the powder by using a scraper, and standing at room temperature to completely volatilize the solvent, wherein the thickness of the powder is about 0.1-1 mm according to design requirements. Or a layer of low-melting-point metal B is preset on the surface of the high-melting-point metal A by a spraying method, and the thickness is about 0.1-1 mm according to the design requirement.
And 4, step 4: melting of pre-positioned low melting point metal B powder
And putting the whole part preset with the low-melting-point metal B powder into a vacuum heat treatment furnace, setting the temperature to be higher than the melting point of the metal B, lower than the melting point of the metal A and lower than the phase transition temperature of the metal A, and keeping for a period of time so that the low-melting-point metal B powder is completely melted and can be completely spread on the surface of the high-melting-point metal A.
For example, if the high-melting-point metal is titanium alloy and the low-melting-point metal is aluminum alloy, the heating temperature is 680 ℃, the holding time is 5-20 minutes, and then cooling is performed. A good bonding of metal a and metal B, crack-free C1 (i.e., the second metal member) was obtained.
And 5: laser additive manufacturing of low-melting-point metal B
According to the part model, C1 obtained in step 4, continuously depositing low-melting-point metal B on the low-melting-point metal B metal layer by using an additive technology, and finally obtaining a metal a and metal B composite structural member (i.e. a third metal member) manufactured by laser additive.
Examples
The TC4 titanium alloy and 5B06 aluminum alloy composite structure thin-wall component is prepared by laser additive manufacturing and a preset intermediate metal layer method, and the size is 30mm multiplied by 80mm multiplied by 30mm, as shown in figure 3.
(1) Polishing the surface of the titanium alloy substrate 4 to be smooth, clean, removing surface stains by using absolute ethyl alcohol and alcohol cotton, then adjusting the position of the substrate 4 to ensure that the laser cannot interfere with other components during manufacturing, and finally fixing the substrate by using a tool clamp. The laser is then mounted on an industrial robot and adjusted to the initial position for laser additive manufacturing.
(2) Preparing a titanium alloy part component in a pure argon environment in a short-side one-way reciprocating scanning mode by adopting the technological parameters of 2400W laser power, 10mm/s scanning speed and 2.3mm scanning distance, wherein the size is 30mm multiplied by 80mm multiplied by 15mm, cooling a to-be-formed part to room temperature after the short-side one-way reciprocating scanning is finished, taking down the to-be-formed part, putting the to-be-formed part into a vacuum heat treatment furnace for annealing, setting the temperature to be 600 ℃, preserving the heat for 4 hours, and cooling the to-be-formed part along with the furnace to remove residual stress.
(3) Roughening the upper surface of the titanium alloy thin-wall component 3 obtained in the step (2), immersing aluminum alloy powder in acetone, and fully wetting, wherein the volume ratio of the powder to the acetone is 1: and 10, taking out the powder after the powder is settled to the bottom of the solution, uniformly coating the powder on the upper surface of the titanium alloy thin-wall component 3, and shaping the powder by using a scraper, wherein the thickness is controlled to be about 1mm (as shown in figure 4).
(4) After acetone is completely volatilized, the titanium alloy thin-wall component 3 and the preset aluminum alloy powder 5 are placed into a vacuum heat treatment furnace, the temperature in the furnace is set to be 600 ℃ according to the melting points of TC4 titanium alloy and 5B06 aluminum alloy of 1400 ℃ and 652 ℃ and the phase transition temperature of TC4 titanium alloy of 998 ℃, the vacuum heat treatment furnace is closed after the temperature is kept for 10 minutes, the component in the furnace is cooled to the room temperature along with the furnace, and the obtained structure is shown in figure 5.
(5) And continuously performing laser additive manufacturing on the obtained TC4 titanium alloy 3 and the preset aluminum alloy metal layer 2 to obtain an aluminum alloy part member 1, wherein the setting parameters are as follows: the laser power is 2000W, the scanning speed is 8mm/s, the scanning interval is 2.0mm, and the thin-wall member of the TC4 titanium alloy and 5B06 aluminum alloy composite structure is finally obtained, wherein the length, the width and the height of the thin-wall member are respectively 30mm, 80mm and 30mm, and the thin-wall member is shown in figures 3 and 6.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (10)
1. A method for laser additive manufacturing of a dissimilar metal, comprising:
performing laser additive manufacturing on the first metal on the preprocessed substrate by adopting a laser according to a preset digital-analog track to obtain a first metal component, and performing stress relief processing on the first metal component;
texturing the first metal component, and coating the pretreated second metal powder on the textured first metal component according to a set thickness; the melting point of the second metal powder is lower than the melting point of the first metal;
after a set condition is met, placing the roughened first metal component coated with the second metal powder in a vacuum heat treatment furnace for heating for a preset time to obtain a second metal component; the heating temperature of the vacuum heat treatment furnace is set to be higher than the melting point of the second metal powder and lower than the melting point of the first metal;
continuously depositing second metal powder on the second metal component by using a laser additive technology to obtain a third metal component; the third metal component is the laser additive structure obtained by preparation.
2. A method according to claim 1, wherein the laser additive manufacturing is performed on the first metal on the pre-processed substrate according to a predetermined digital-to-analog trajectory by using a laser, and the method further comprises:
polishing the substrate, and removing stains on the polished substrate by using an organic solvent to obtain a pretreated substrate;
and after the position of the pretreated substrate is adjusted, fixing the substrate after the position adjustment by using a clamp.
3. The laser additive manufacturing method of claim 1, wherein the organic solvent is absolute ethanol.
4. A method according to claim 1, wherein the first metal is a metal powder that is baked in a vacuum environment.
5. A method of laser additive manufacturing of dissimilar metals according to claim 4, wherein the first metal is a titanium alloy powder.
6. A method according to claim 1, wherein the pre-treating the second metal powder comprises:
immersing the second metal powder in a volatilizable solvent, and taking out settled powder after the second metal powder is completely settled at the bottom of the volatilizable solvent; and the settled powder is the pretreated second metal powder.
7. A method according to claim 6, wherein the second metal powder is an aluminium alloy powder.
8. A method according to claim 6, wherein the predetermined condition is that the volatilizable solvent carried in the pretreated second metal powder is completely volatilized.
9. A method according to claim 1, wherein the set thickness is 0.1mm-1 mm.
10. A method according to claim 1, wherein the predetermined time is 5-20 min.
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