CN111036741B - Method for preparing multilayer metal composite material by high-temperature torsion - Google Patents
Method for preparing multilayer metal composite material by high-temperature torsion Download PDFInfo
- Publication number
- CN111036741B CN111036741B CN201911187417.2A CN201911187417A CN111036741B CN 111036741 B CN111036741 B CN 111036741B CN 201911187417 A CN201911187417 A CN 201911187417A CN 111036741 B CN111036741 B CN 111036741B
- Authority
- CN
- China
- Prior art keywords
- metal
- composite material
- torsion
- sample
- aluminum alloy
- 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D11/00—Bending not restricted to forms of material mentioned in only one of groups B21D5/00, B21D7/00, B21D9/00; Bending not provided for in groups B21D5/00 - B21D9/00; Twisting
- B21D11/14—Twisting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D39/00—Application of procedures in order to connect objects or parts, e.g. coating with sheet metal otherwise than by plating; Tube expanders
- B21D39/03—Application of procedures in order to connect objects or parts, e.g. coating with sheet metal otherwise than by plating; Tube expanders of sheet metal otherwise than by folding
- B21D39/031—Joining superposed plates by locally deforming without slitting or piercing
Abstract
The invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion. Firstly, selecting metals A and B with different deformation resistances, and alternately stacking the metals A and B, wherein the metal of the central layer is the metal B with higher deformation resistance, the initial layer and the final layer of the stacked sample are both the metal A with lower deformation resistance, and the thicknesses of the metal A and the metal B are controlled to be 1.5-3 mm; and then placing the sample on a torsion testing machine provided with a heating furnace, heating the sample, and when the temperature reaches a set value, keeping the temperature for 5-15 min, and then twisting the stacked sample at the speed of 30-120 r/min by 180-2160 degrees. The invention has reasonable design, simple and controllable preparation process, high composite yield, high tensile height of the obtained composite material, high elongation and excellent composite interface combination.
Description
Technical Field
The invention relates to a novel multilayer metal material compounding process, in particular to a method for preparing a multilayer metal composite material through high-temperature torsion, and belongs to the technical field of multilayer metal material preparation.
Background
With the continuous development and progress of modern industry and scientific technology, metal materials made of single metal or alloy are more and more difficult to meet the requirements of extreme environments due to the limitation of the inherent properties of the materials, so that novel metal composite materials are more and more valued by various industries. The metal composite material is a metal material with multiple components formed by combining two or more metals through a physical or chemical method. The material not only has the excellent performance of single component metal, but also has the excellent performance characteristics of each component, thereby showing stronger comprehensive performance. At present, the metal composite material is widely applied to the fields of aviation, aerospace, transportation and the like.
Currently, the conventional metal laminated composite materials are mainly prepared by combining different metal materials with each other by means of plastic deformation, wherein roll lamination and extrusion lamination are common. Roll cladding is a conventional cladding process in which two or more layered metals having different properties are firmly bonded to each other by a rolling force. The rolling compounding has high requirements on the quality of a rolling mill, the process is complex, and the rolled composite plate has large residual stress and is easy to have edge cracking, so the yield is low; extrusion compounding is a pressure processing technology for applying pressure to one end of a metal material placed in an extrusion container through an extrusion rod to enable a blank to deform in a closed extrusion container space, so that the blank is formed through an extrusion die hole. It can reduce the defects in the material structure and improve the compactness. It is known that rolling and extrusion lamination are carried out by controlling stress to compound different kinds of metal materials, however, in the metal lamination process, because the difference of plastic deformation resistance among different metal components is large, the deformation among the metal components is mainly concentrated in the component with small deformation resistance in the rolling or extrusion lamination forming process, and the deformation degree of the metal component with large deformation resistance is small. The deformation of the whole metal composite material is very uneven and larger interface stress exists, so that the yield is not high in the forming process, and phenomena such as deformation instability, cracking and the like are easy to occur; in addition, in the rolling compounding and extrusion compounding processes, the time for the whole deformation of the component is short, the combined action time of stress and heat on the component is not long, the interface combination between metal components is mainly simple mechanical engagement, and the interface combination between the components is weaker.
As a structural material, metal composite materials are widely used in various industries because of their excellent mechanical properties. Strength and elongation are two important mechanical property indexes of metal composite materials in engineering application. If the composite material has excellent strength and elongation at the same time, the composite material has good capability of resisting external force damage, thereby having higher safe service life.
In order to simultaneously improve the elongation and the strength of the metal composite material, the invention firstly provides a novel composite process, namely a high-temperature torsion composite process. Under the action of torsional strain, even if the metal components with larger difference of deformation resistance can still keep better deformation uniformity, thereby solving the problem of non-uniform deformation of the composite material; meanwhile, in the twisting process, the strain rate is easily and uniformly controlled, so that the yield of the twisted composite material is high; in addition, when the composite material is twisted, the metal components are subjected to high temperature and strain and have longer acting time, and the diffusion rate of each metal component is higher under the combined action of force and heat, so that the interface combination effect among the metal components is obviously improved. Experiments prove that the requirements of the composite material on the elongation and the strength can be realized by controlling the torsional deformation angle, and the composite material has higher strength under a smaller torsional angle; with the increase of the torsion angle, the elongation of the composite material is obviously improved. The elongation of the composite material prepared by the process can reach more than 90%; in addition, the process has higher controllability, can well prepare various metal plate materials, and the yield of the metal plate materials can reach more than 98 percent.
Therefore, the method for preparing the multilayer composite material by high-temperature torsion provides a brand-new way for preparing the high-quality multilayer composite metal material.
Disclosure of Invention
In order to solve the defects and shortcomings, the invention provides a preparation method and a device for preparing a multilayer metal composite material by a high-temperature torsion process for the first time.
The invention also aims to provide the multilayer metal composite material prepared by the preparation method.
In order to achieve the above object, the present invention provides a method for preparing a multilayer metal composite material by high temperature twisting, which comprises the following steps:
(1) selecting a metal A with lower deformation resistance and a metal B with higher deformation resistance, wherein the deformation resistance of the metal B is greater than that of the metal A.
(2) Stacking the metal A and the metal B selected in the step (1); obtaining a stacked sample;
(3) heating and insulating the stacked sample obtained in the step (2) and then twisting; obtaining the metal composite material.
As a preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; in the step (2), the metal A and the metal B obtained in the step (1) are alternately stacked, wherein the initial layer and the termination layer of the stacked sample are both the metal A; the central layer is metal B. As a further preferable scheme, the thicknesses of the two metals are stacked according to a set ratio in consideration of the service environment and the requirement of the materials.
In a further preferred embodiment, the volume occupied by the metal a after stacking is equal to or greater than the volume occupied by the metal B.
As a preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; the equipment used for twisting is an unsetting twisting device and a locating twisting device; wherein the non-locating means: the stacked sample obtained in step (2) was mounted in a jig (see fig. 4b), and then the jig with the sample was mounted on a torsion testing machine (see fig. 4b), followed by mounting a heating furnace, and the whole was assembled (see fig. 4 c). A positioning device: fixing the stacked sample obtained in the step (2) in a clamp with positioning holes (shown in figure (5a)) through positioning bolts, then installing the clamp with the sample installed on a torsion testing machine, then installing a heating furnace, and finally installing a positioning device (shown in figure (5b)), and integrally assembling the figure (shown in figure (5 c)).
As a preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; the temperature of the sample is controlled to be 20-550 ℃ and less than the melting points of the metal A and the metal B during twisting.
The invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; the heat preservation time in the step (3) is determined according to the thickness of the superposed samples, and is preferably 5-15 min.
As a preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; the torsion rate is 30-120 r/min.
As a preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; the twisting angle is 180-2160 degrees, preferably 1000-2160 degrees.
As a preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; the metal A is an aluminum alloy plate, and the metal B is stainless steel or copper material. More preferably, the aluminum alloy sheet is a 1-series or 6-series aluminum alloy sheet. The stainless steel is 304 stainless steel. The copper material is preferably a copper plate.
As a further preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; when the metal A is 1060 aluminum alloy plate and the metal B is 304 stainless steel plate, the thickness of the single-layer plate is preferably 1mm to 3.5mm, more preferably 1.5mm when stacked.
As a further preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; when the metal A is 1060 aluminum alloy plate and the metal B is 304 stainless steel plate, the heating temperature of the sample after stacking is 20 ℃ to 550 ℃, and more preferably 500 ℃.
As a further preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; when the metal A is 1060 aluminum alloy plate and the metal B is 304 stainless steel plate, the tensile strength of the product obtained by twisting at 1080 DEG is larger than that of the product obtained by other twisting angles, and when the product is twisted at 1440 DEG, the elongation of the product obtained is larger than that of the product obtained by other twisting angles.
As a further preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; when the metal A is 1060 aluminum alloy plate and the metal B is pure copper plate, the elongation of the obtained product is more than 60% when the product is twisted by 1080 degrees.
As a further preferred scheme, the invention relates to a preparation method for preparing a multilayer metal composite material by high-temperature torsion; when the metal A is a 6061 aluminum alloy plate and the metal B is a 304 stainless steel plate, the elongation of the composite material is more than or equal to 91% when the composite material is twisted by 1080-1800 degrees. The tensile strength of the composite material is more than 380MPa when the composite material is twisted by 1080 degrees.
The center layer of the stacked sample in the step (2) of the invention is metal B with high deformation resistance, and the invention has the advantages that:
(1) the initial layer and the final layer of the sample are both metal A, the sample is twisted at a certain temperature (20-550 ℃), good combination can be obtained, meanwhile, the high-temperature twisted sample can increase diffusion of all metal elements in the plate, and the combination performance of the alloy is improved.
(2) Through experimental research, if the metal A with smaller deformation resistance is placed on the central layer of a torsion sample, and the metal B with high deformation resistance is placed on two sides of the torsion sample, the sample can generate the phenomenon of deformation instability during torsion, and the required multilayer metal composite material cannot be obtained. Therefore, the metal B with higher deformation resistance is selected as the central layer of the torsional sample, so that the phenomenon of deformation instability of the sample during torsion is prevented.
In industrial application, the metal A and the metal B are respectively subjected to surface cleaning to remove oil stains; obtaining metal A and metal B with clean and dry surfaces; the specific operation is as follows:
first, the metal a and the metal B are washed with alcohol, respectively, to remove oil stains and the like on the metal surface.
In the industrial application process, the heating furnace is always in a heat preservation state during twisting. The metal elements have high activity in a high-temperature environment, and strong shearing force action is realized in the twisting process, so that the mutual diffusion among the elements can be better realized by the metal of each component, and the interface combination effect among the metal components is better.
The preparation method provided by the invention is simple to operate, low in cost and high in yield, and can be used for combining various metal composite plates and adjusting the volume fraction of each metal material, so that the composite material with better comprehensive performance is obtained. Meanwhile, through the trial of the invention, the performance of the obtained product is found to be superior to the theoretical value.
Drawings
FIG. 1a is a process flow diagram of an unset torsion experiment;
FIG. 1b is a process flow diagram of a positional torsion experiment;
FIG. 2a is a dimensional view of an unset torsion specimen;
FIG. 2b is a dimensional view of a positioning torsion specimen;
FIG. 3 is a testing machine for metal twisting and compounding;
FIG. 4a is an unset torsion specimen holder;
FIG. 4b is the clamping of an unset torsion specimen;
FIG. 4c is a view of the overall assembly of the unset torsion device;
FIG. 5a shows positioning and torsion specimen clamping;
FIG. 5b shows positioning device installation;
FIG. 5c illustrates the positioning and twisting device as a whole;
FIG. 6a is an unset torsion specimen;
FIG. 6b is a view of positioning a torsion specimen;
FIG. 7a is a 1060 aluminum untwisted metallographic picture;
FIG. 7b is a 1060 aluminum torsional metallographic picture;
FIG. 7c is a metallographic picture of steel untwisted;
FIG. 7d is a metallographic picture of steel torsion;
FIG. 7e is a metallographic picture of copper untwisted;
FIG. 7f is a metallographic picture of copper torsion;
FIG. 7g is a 6061 aluminum untwisted metallographic picture;
FIG. 7h is a 6061 aluminum torsional metallographic picture;
FIG. 8(a) stress-strain curves of the 1060 Al alloy/304 stainless steel layered composite without different torsion angles for 3mm thick sheet;
FIG. 8(b) stress-strain plots of the 1060 Al alloy/304 stainless steel layered composite without different torsion angles for a 1.5mm thick sheet;
FIG. 8(c) stress-strain plots of the 1060 Al alloy/304 stainless steel layered composite with different torsion angles for the 1.5mm and 3mm thick plates not positioned;
FIG. 8(d) stress-strain curves of 1060 Al alloy/Cu layered composite without different torsion angles for 3mm thick sheet;
FIG. 8(e) stress-strain curve of 6061 Al/304 stainless steel layered composite material with 3mm thickness plate positioned at different torsion angles;
FIG. 9 is a stress-strain plot of a 1060 Al alloy/304 stainless steel layered composite at different temperatures for a 3mm thick sheet;
FIG. 10 is an SEM topography at the interface of a layered composite obtained by high temperature twisting of 1060 aluminum alloy/304 stainless steel of a 3mm thick plate;
FIG. 11 is an SEM topography at the interface of a layered composite obtained by high temperature twisting of 1060 aluminum alloy/304 stainless steel of a 1.5mm thick plate;
FIG. 12 is an SEM topography of a layered composite obtained by high temperature twisting of 6061 aluminum/304 stainless steel in a 3mm thick plate;
Detailed Description
Example 1
Firstly, cutting 1060 aluminum alloy plate with thickness of 3mm and 304 stainless steel plate into torsion samples with shapes as shown in figure 2(a) by wire cutting;
secondly, placing the cut sample on a grinding machine to remove an oxide layer on the surface and expose a smooth metal layer, and then cleaning the ground plate with alcohol and wiping the cleaned plate;
thirdly, alternately stacking 2 pieces of 1060 aluminum alloy plates and 1 piece of 304 stainless steel plates which are 3mm after surface treatment, wherein the 304 stainless steel plates are arranged in the central layer;
fixing the stacked samples in a clamp, then installing the clamp with the samples on a torsion tester (shown in figure 4b), then installing a heating furnace (shown in figure 4c), heating the samples, and carrying out heat preservation treatment for 5min when the temperature of the heating furnace reaches 500 ℃;
fifthly, twisting the stacked sample after heat preservation treatment at the speed of 120r/min respectively at 1080 degrees, 1440 degrees and 1800 degrees for torsion experiments to obtain the 1060 aluminum alloy/steel torsion composite material.
In this example, the volume fraction of 1060 aluminum alloy is 66.7% and the volume fraction of 304 stainless steel is 33.3%. The mechanical properties of 1060 aluminum alloy and 304 stainless steel are measured by experiments and are as follows:
room temperature mechanical tensile property of 11060 aluminum alloy and 304 stainless steel
According to the calculation rule of the theoretical strength of the composite material:
VA+VB＝1 (1)
σ0＝σAVA+σBVB (2)
in the formula: vAAnd VBRespectively represents the volume fraction of the metal A and the metal B in the composite material, sigmaAAnd σBRespectively representing the tensile strength, σ, of the individual original plates of metal A and metal B0It represents the theoretical tensile strength of the laminated composite.
The theoretical tensile strength of the 1060 aluminum alloy/304 stainless steel torsional composite material can be calculated to be 271MPa according to equations (1) and (2).
FIG. 7 is a 1060 metallographic microstructure of an aluminum alloy before and after twisting, and FIG. 7(a) is a 1060-torsional metallographic microstructure in which the metallographic structure is generally flat and in which a part of equiaxed grain structure appears; FIG. 7(b) is a diagram of the gold phase of 1060 aluminum alloy after twisting, and it is obvious from the diagram that the crystal grains in the twisted alloy are obviously long and uniformly distributed in the alloy matrix. After twisting, the crystal grains in the alloy matrix have obvious thinning phenomenon. FIGS. 7(c) and 7(d) are the metallographic images before and after twisting of 304 stainless steel, and comparing the metallographic images with the metallographic images, it can be seen that the grain refining effect of the alloy matrix is very significant after the stainless steel is twisted.
In fig. 8(a), it can be seen that, in terms of strength, the tensile strength of the composite material at 1080 ° torsion is 330.6MP, the tensile strength of the composite material at 1440 ° torsion is 312.1MPa, and the tensile properties of the composite material at both torsion angles are higher than the theoretical tensile strength 271MP of the composite material. In terms of elongation, at a certain torsion angle, the elongation of the material increases significantly with increasing torsion angle, but when the torsion angle is too high, the elongation of the material decreases slightly. It is evident from the figure that the elongation of the twisted composite material is as high as more than 70%, which is obviously higher than that of the single metal component metal. When the material is twisted at 1440 degrees, the elongation of the material reaches 98.2 percent; it can be seen that, along with the increase of sample torsion angle, the tensile strength and the elongation of sample all have obvious decline trend, mainly because when combined material torsion angle reached a certain amount, some slight damage phenomena can appear in the material inside, along with the continuous increase of torsion angle, the inside slight damage of material can aggravate gradually, and then influences combined material's comprehensive properties for the tensile strength and the elongation of material reduce.
Example 2
Firstly, cutting 1060 aluminum alloy plate with thickness of 3mm and 304 stainless steel plate into samples with the shape of figure 2(a) by wire cutting;
secondly, placing the cut sample on a grinding machine to remove an oxide layer on the surface and expose a smooth metal layer, and then cleaning the ground plate with alcohol and wiping the cleaned plate;
thirdly, alternately stacking 2 pieces of 1060 aluminum alloy plates and 1 piece of 304 stainless steel plates which are 3mm after surface treatment, wherein the 304 stainless steel plates are arranged in the central layer;
fixing the stacked samples in a clamp, mounting the clamp with the samples on a torsion tester (shown in figure 4(b)), mounting a heating furnace (shown in figure 4(c)), heating the samples, and performing heat preservation treatment for 5min when the temperature of the heating furnace reaches the specified temperature of 200 ℃, 300 ℃ and 500 ℃ respectively;
fifthly, torsion experiments are carried out when the stacked samples subjected to heat preservation treatment are respectively twisted at 1440 degrees at the speed of 120r/min, and the 1060 aluminum alloy/steel torsion composite material is obtained.
The theoretical tensile strength of the 1060 aluminum alloy/304 stainless steel composite can be calculated to be 271MPa according to equations (1) and (2).
FIG. 9 shows that the tensile strength of the material is about 312MPa, which is significantly higher than the theoretical tensile strength of the 1060 aluminum alloy/304 stainless steel composite material of 271MPa, which indicates that the high-temperature torsional composite process can improve the mechanical properties of the material well. Along with the rise of the temperature, the tensile strength of the material is not obviously changed, which shows that the influence of the torsion temperature under the same torsion angle on the tensile strength of the composite material is smaller; however, under the same torsion angle, the elongation of the material is obviously increased along with the increase of the temperature, which shows that the temperature has a large influence on the elongation of the composite material, and when the torsion temperature reaches 500 ℃, the elongation of the torsion composite material is as high as 98.2 percent and is far higher than that of any single component metal material.
After the sample is subjected to torsion compounding treatment, the elongation of the obtained composite material is greatly improved mainly due to the stress state of the sample during torsion. When the sample is twisted, the sample is not only subjected to the action of shear stress, but also subjected to compressive stress caused by mutual extrusion among the layers of the plates. The grain refining effect of the torsion sample is enhanced, the plasticity of the material is obviously improved, and the elongation of the composite material is further improved.
FIG. 10 is an SEM topography at the interface of a layered composite obtained by high temperature twisting of 1060 aluminum alloy/304 stainless steel of a 3mm thick sheet; wherein (a) is an EDS analysis at position 1; panel (b) is EDS analysis at position 2; figure (c) elemental line scan analysis at position 3; FIG. (d) elemental line scan analysis at position 4; FIG. (e) is a partial bond interface SEM topography; graph (f) elemental plane analysis graph at interface. From the elemental analysis at both points of fig. 10(a) and 10(b), it is found that Al and Fe are both present in the elements near the bonding surface, and the phenomenon in which the elements near the bonding surface of the torsion sample diffuse into each other is explained. In the line scan elemental analysis of fig. 10(c) and 10(d), there is a tendency that the Al content gradually increases and the Fe content gradually decreases in the scanning direction, and finally the contents of both elements tend to be stable. Wherein the diffusion region width of Al and Fe is about 45 μm. Fig. 10(e) is a partially enlarged view of the SEM topography at the bonding interface, and fig. 10(f) is an elemental plane analysis corresponding to the area of fig. 10(e), from which a distinct bonding interface is seen, in which interdiffusion of elements occurs on both sides of the interface. Mainly, the time generally required by the twisting process is longer, the mutual diffusion of elements among all metal components is facilitated under the long-time combined action of high temperature, strain and compressive stress, and the element diffusion effect is more obvious along with the increase of time, so that the 1060 aluminum alloy and the 304 stainless steel have better interface combination effect.
Example 3
Firstly, processing 1060 aluminum alloy plate with thickness of 1.5mm and 304 stainless steel plate into a sample with shape as shown in figure 2 (a);
secondly, placing the cut sample on a belt type grinding machine to remove an oxide layer on the surface and expose a smooth metal layer, and then cleaning the ground plate by using alcohol;
thirdly, alternately stacking the 1060 aluminum alloy plate and the 304 stainless steel plate after surface treatment;
fixing the stacked samples in a clamp, then installing the clamp with the samples on a torsion tester (shown in figure 4b), then installing a heating furnace (shown in figure 4c), heating the samples, and performing heat preservation treatment for 5min when the temperature of the heating furnace reaches 500 ℃ respectively;
fifthly, respectively twisting the stacked samples subjected to heat preservation treatment at the speed of 60r/min for 1080 degrees and 1440 degrees to obtain the 1060 aluminum alloy plate/304 stainless steel twisted composite material.
In this example, the 1060 aluminum alloy has a volume fraction of 60% and 304 stainless steel has a volume fraction of 40%. It was calculated according to equations (1) and (2) that the theoretical tensile strength of the 1060 aluminum alloy/304 stainless steel composite was 301.9 MPa.
FIG. 8(b) is a stress-strain plot of a plate torsional composite material having a thickness of 1.5 mm. From the figure, it can be seen that the elongation of the material increases with increasing twist angle, but the strength of the composite material decreases significantly with increasing twist angle. The tensile strength of the sample is 311.5MPa when the sample is twisted at 1080 degrees, which is 271MPa higher than the theoretical tensile strength; wherein the elongation of the composite material reaches 104.1 percent when the composite material is twisted at 1440 degrees. It is apparent from FIG. 8(c) that the composite material obtained by twisting the sample having a thickness of 1.5mm has a lower strength but a slightly higher elongation than the composite material obtained by twisting the sample having a thickness of 3mm at the same twisting angle.
FIG. 11 is an SEM topography of a layered composite made from 1060 aluminum alloy/304 stainless steel of a 1.5mm thick plate. Local observations were made in fig. 11(a) and (b) at randomly chosen locations at the interfacial junctions of the inner and outer layers, respectively. The partial enlarged view of the SEM morphology picture can clearly see that the interface bonding effect is good, and no gap or other bonding defects are found. The element line scanning shows that the content change of Al and Fe along the scanning line direction can explain the phenomenon that the elements in the two alloys are diffused mutually after being twisted. The diffusion regions were measured to have a width of about 90 μm at the interface junction of either the inner or outer layer. Compared with 1060 aluminum alloy/304 stainless steel laminated composite material obtained by twisting a plate with the thickness of 3mm, the width of the bonding area is greatly improved. The material interface bonding effect obtained by twisting the plate with the thickness of 1.5mm is better.
Example 4
Firstly, processing a 1060 aluminum alloy plate with the thickness of 3mm and a pure copper plate into a torsion sample with the shape as shown in figure 2 (a);
secondly, placing the cut sample on a belt type grinding machine to remove an oxide layer on the surface and expose a smooth metal layer, and then cleaning the ground plate with alcohol and wiping the cleaned plate;
thirdly, alternately stacking 2 pieces of 1060 aluminum alloy plates and 1 piece of copper plate after surface treatment, wherein the pure copper plate is placed in the central layer;
fixing the stacked samples in a clamp, then installing the clamp with the samples on a torsion tester (shown in figure 4b), then installing a heating furnace (shown in figure 4c), heating the samples, and performing heat preservation treatment for 5min when the temperature of the heating furnace reaches 500 ℃ respectively;
fifthly, twisting the stacked sample subjected to heat preservation treatment at a speed of 30r/min for 1080 degrees to obtain the 1060 aluminum alloy/copper twisted composite material.
FIGS. 7(e) and 7(f) are the gold phase diagrams before and after twisting of pure copper, respectively. It can be seen from FIG. 7(e) that the copper grains are mostly equiaxed grains, and are larger in size, some larger-sized grains appear, and are not uniformly distributed; the grains in fig. 7(f) are significantly smaller, the distribution of the grains is relatively uniform, and a large amount of twins occur. The twisting can obviously refine the metal grains, improve the distribution of the metal internal grains, effectively improve the strength of the twisted metal and further improve the strength of the twisted material.
FIG. 8(d) is a stress-strain curve diagram of a layered composite material prepared by a 3mm thick plate which is not positioned and twisted at 1080 deg. As can be seen from the figure, the elongation of the composite material is 65%, which is higher than the elongation of the single component metals constituting the composite material. Because the sample is twisted, the deformation degree of each metal component is more uniform under the action of strain, and in addition, because the interface between each metal component has stronger compressive stress action during twisting, the combination interface between each metal component is tighter, and the elongation of the material is greatly improved.
Example 5
Firstly, processing a 6061 aluminum alloy plate and a 304 stainless steel plate with the thickness of 3mm into a torsion sample with the shape as shown in figure 2 (b);
secondly, placing the cut sample on a belt type grinding machine to remove an oxide layer on the surface and expose a smooth metal layer, and then cleaning the ground plate with alcohol and wiping the cleaned plate;
thirdly, alternately stacking 2 aluminum alloy plates 6061 subjected to surface treatment and 1 stainless steel plate 304, wherein the stainless steel plate 304 is placed in the central layer;
and fourthly, fixing the stacked samples in a clamp with positioning holes (shown in figure (5a)) through positioning bolts, then installing the clamp with the mounted samples on a torsion testing machine, then installing a heating furnace, and finally installing a positioning device (shown in figure (5b)), and integrally assembling the figure (shown in figure (5 c)).
Fifthly, after the sample is subjected to heat preservation treatment at the temperature of 500 ℃ for 5min, the sample is respectively twisted at 1080, 1440, 1800 and 2160 degrees at the speed of 120r/min to obtain the 6061 aluminum alloy/304 stainless steel twisted composite material.
The volume fraction of the 6061 aluminum alloy in the example is 66.7%, the volume fraction of the 304 stainless steel is 33.3%, and the mechanical properties of the 6061 aluminum alloy measured by experiments are as follows:
TABLE 26061 mechanical tensile Properties of aluminum alloys at Room temperature
The theoretical tensile strength of the 6061 aluminum alloy/304 stainless steel composite material obtained according to the formulas (1) and (2) is 317.3 MPa.
FIGS. 7(g) and 7(h) are the metallographic images of 6061 aluminum alloy before and after twisting. As can be seen from fig. 7(g), the grains of the 6061 aluminum alloy are substantially equiaxial and the grain size is relatively uniform in the as-received state. FIG. 7(h) is a diagram of the gold phase after the sample is twisted, and it can be seen that the grain size of the alloy is significantly reduced and the grain distribution in the matrix is more uniform. Compared with fig. 7(g), it can be found that the microstructure change in the metal after the alloy is subjected to torsion treatment is obvious, and the grain size is obviously refined, so that the strength and the elongation of the composite material are improved.
As can be seen in FIG. 8(e), the elongation of the composite material is more than 91% when the composite material is twisted at 1080-1800 degrees, and the elongation of the composite material is 73.8% when the composite material is twisted at 2160 degrees. It is shown that the elongation of the composite material increases with increasing twist angle within a certain twist angle range, and that the elongation of the sample decreases when the twist angle of the material is outside this range. The elongation of the torsional composite material is higher than that of any single metal component of 6061 aluminum alloy and 304 stainless steel; in terms of strength, the strength of the specimen decreases as the torsion angle increases. The tensile strength of the composite material is 384.6MPa when the composite material is twisted at 1080 degrees, which is higher than the theoretical tensile strength of the composite material of 317.3 MPa. In the twisting process of the composite material, under the combined action of strong shear stress and high temperature, the structure in the metal matrix can be subjected to fine-grain reinforcement, so that the mechanical property of the composite material is obviously improved; however, when the torsion angle of the material exceeds a certain critical value, the internal structure of the material is slightly damaged, and the damage is aggravated along with the continuous increase of the torsion angle, so that the elongation and the mechanical property of the composite material are reduced.
FIG. 12 is an SEM topography of a layered composite obtained by torsional recombination of 3mm thick 6061 aluminum/304 stainless steel. FIGS. 12(b) and (e) are two selected local positions in either scan of a 6061 aluminum/304 stainless steel layered composite. FIG. 12(a) is an elemental plane analysis diagram at position 1, in which a bonding interface is clearly seen, and Al and Fe are diffused into each other in the vicinity of the bonding interface; FIG. 12(b) is a SEM image of the position 1, and FIG. 12(c) is the distribution of Al and Fe content along the scanning line direction at the position 1. It can be seen that Al and Fe have a significant diffusion phenomenon at the bonding interface, with a diffusion region length of about 32.06 μm. FIG. 12(d) is an elemental plane analysis at position 2, from which it can also be seen that the bonding interface is relatively clear and that there is interdiffusion of Al and Fe near the bonding interface; FIG. 12(e) is the SEM image at position 2, and FIG. 12(f) is the distribution of Al and Fe content along the scan line at position 2. Al and Fe have significant diffusion phenomena at the bonding interface, with diffusion zone lengths of about 34.74 μm. Comparing position 1 and position 2, it can be found that the two materials of the twisted composite have a better bonding effect at the center.
Claims (6)
1. A method for preparing a multilayer metal composite material by high-temperature torsion is characterized by comprising the following steps of; the method comprises the following steps:
(1) selecting a metal A with lower deformation resistance and a metal B with higher deformation resistance, wherein the deformation resistance of the metal B is higher than that of the metal A;
(2) stacking the metal A and the metal B selected in the step (1); obtaining a stacked sample;
(3) heating and insulating the stacked sample obtained in the step (2) and then twisting; obtaining a metal composite material;
the metal A is an aluminum alloy plate, and the metal B is stainless steel or a copper material;
when the metal A is a 1060 aluminum alloy plate and the metal B is a 304 stainless steel plate, the tensile strength of the product obtained by twisting at 1080 degrees is greater than that of the product obtained by other twisting angles, and when the product is twisted at 1440 degrees, the elongation of the product obtained is greater than that of the product obtained by other twisting angles;
when the metal A is 1060 aluminum alloy plate and the metal B is pure copper plate, the elongation of the obtained product is more than 60% when the product is twisted for 1080 degrees;
when the metal A is a 6061 aluminum alloy plate and the metal B is a 304 stainless steel plate, the elongation of the composite material is more than or equal to 91% when the composite material is twisted at 1080-1800 degrees; the tensile strength of the composite material is more than 380MPa when the composite material is twisted by 1080 degrees.
2. A high temperature twist production multilayer metal composite production method according to claim 1; the method is characterized in that: in the step (2), the metal A and the metal B obtained in the step (1) are alternately stacked, wherein the initial layer and the termination layer of the stacked sample are both the metal A; the central layer is metal B.
3. A high temperature twist production multilayer metal composite production method according to claim 1; the method is characterized in that: the temperature of the sample is controlled to be 20-550 ℃ and less than the melting points of the metal A and the metal B during twisting.
4. A high temperature twist production multilayer metal composite production method according to claim 1; the method is characterized in that: the torsion rate is 30 to 120 r/min.
5. A high temperature twist production multilayer metal composite production method according to claim 1; the method is characterized in that: when the metal A is 1060 aluminum alloy plate and the metal B is 304 stainless steel plate, the thickness of the single-layer plate is preferably 1mm to 3.5mm when stacked.
6. A high temperature twist production multilayer metal composite production method according to claim 1; the method is characterized in that: when the metal A was 1060 aluminum alloy plate and the metal B was 304 stainless steel plate, the heating temperature of the sample after stacking was 20 to 550 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911187417.2A CN111036741B (en) | 2019-11-28 | 2019-11-28 | Method for preparing multilayer metal composite material by high-temperature torsion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911187417.2A CN111036741B (en) | 2019-11-28 | 2019-11-28 | Method for preparing multilayer metal composite material by high-temperature torsion |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111036741A CN111036741A (en) | 2020-04-21 |
| CN111036741B true CN111036741B (en) | 2022-03-11 |
Family
ID=70233923
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911187417.2A Active CN111036741B (en) | 2019-11-28 | 2019-11-28 | Method for preparing multilayer metal composite material by high-temperature torsion |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111036741B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113881915B (en) * | 2021-10-12 | 2023-11-17 | 西南大学 | Preparation method and preparation device of torsion coating |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU710720A1 (en) * | 1977-08-01 | 1980-01-25 | Донецкий научно-исследовательский институт черной металлургии | Method of producing bimetallic rods |
| JPS5677041A (en) * | 1979-11-30 | 1981-06-25 | Tanaka Kikinzoku Kogyo Kk | Production of composite metal wire blank material |
| CN2486233Y (en) * | 2001-02-06 | 2002-04-17 | 攀枝花钢铁有限责任公司机械制造公司 | Device for making twist iron |
| CN101795788A (en) * | 2007-10-09 | 2010-08-04 | 后藤常郎 | Manufacturing method and manufacturing apparatus for twisted flat bar |
| CN103182412A (en) * | 2013-03-18 | 2013-07-03 | 西北工业大学 | Crankling processing device for section |
| CN110421077A (en) * | 2019-07-23 | 2019-11-08 | 上海交通大学 | The combined shaping method of the component of narrow deep chamber feature is distorted with wide-angle thin-walled |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3165825A (en) * | 1963-11-27 | 1965-01-19 | Leach & Garner Co | Jeweler's patterned wire |
| DE3266710D1 (en) * | 1981-10-31 | 1985-11-07 | Vaillant Joh Gmbh & Co | Method of manufacturing a helix |
| JP4558910B2 (en) * | 2000-09-22 | 2010-10-06 | 株式会社村元工作所 | Spiral twisted shaft body and manufacturing method thereof |
| CN101216271B (en) * | 2007-01-04 | 2011-02-02 | 郭常喜 | Manufacture method of cutlery body with multiple pattern change |
| JP4593690B1 (en) * | 2009-11-13 | 2010-12-08 | 有限会社杢目金屋 | Metal body manufacturing method, apparatus and metal body |
-
2019
- 2019-11-28 CN CN201911187417.2A patent/CN111036741B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU710720A1 (en) * | 1977-08-01 | 1980-01-25 | Донецкий научно-исследовательский институт черной металлургии | Method of producing bimetallic rods |
| JPS5677041A (en) * | 1979-11-30 | 1981-06-25 | Tanaka Kikinzoku Kogyo Kk | Production of composite metal wire blank material |
| CN2486233Y (en) * | 2001-02-06 | 2002-04-17 | 攀枝花钢铁有限责任公司机械制造公司 | Device for making twist iron |
| CN101795788A (en) * | 2007-10-09 | 2010-08-04 | 后藤常郎 | Manufacturing method and manufacturing apparatus for twisted flat bar |
| CN103182412A (en) * | 2013-03-18 | 2013-07-03 | 西北工业大学 | Crankling processing device for section |
| CN110421077A (en) * | 2019-07-23 | 2019-11-08 | 上海交通大学 | The combined shaping method of the component of narrow deep chamber feature is distorted with wide-angle thin-walled |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111036741A (en) | 2020-04-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Chen et al. | Influence of multi-pass rolling and subsequent annealing on the interface microstructure and mechanical properties of the explosive welding Mg/Al composite plates | |
| Shabani et al. | Fabrication of Al/Ni/Cu composite by accumulative roll bonding and electroplating processes and investigation of its microstructure and mechanical properties | |
| Alizadeh et al. | Fabrication of Al/Cup composite by accumulative roll bonding process and investigation of mechanical properties | |
| Liu et al. | Effect of W particles on the properties of accumulatively roll-bonded Al/W composites | |
| US20080276681A1 (en) | Preparation method of laminated composite materials of different alloys | |
| JP4734578B2 (en) | Magnesium alloy sheet processing method and magnesium alloy sheet | |
| CN110695089B (en) | Rolling method of bimetal composite plate with good plate shape | |
| Karimi et al. | An alternative method for manufacturing high-strength CP Ti–SiC composites by accumulative roll bonding process | |
| CN111036741B (en) | Method for preparing multilayer metal composite material by high-temperature torsion | |
| Yu et al. | Advanced rolling technologies for producing ultrafine-grain/nanostructured alloys | |
| CN108555039B (en) | Preparation method of copper/steel laminated composite material and composite material prepared by preparation method | |
| CN111360095B (en) | Method for improving tensile plasticity of ultra-fine grain aluminum plate | |
| CA2758719C (en) | Oxide-dispersion-strengthened platinum material and method for producing the same | |
| EP1365910B1 (en) | Method of manufacturing metallic composite material | |
| CN113478063B (en) | Titanium-zirconium-molybdenum alloy vacuum diffusion bonding method taking refractory metal as intermediate layer | |
| Lei et al. | Study on microstructure evolution and fracture behavior of Al/Al/Cu multilayer composites | |
| Heydari Vini et al. | Mechanical and Bonding Properties of Bi-Metal Al/Cu Bulk Composites Produced via Apb Technique | |
| CN109082567A (en) | A kind of preparation method of aluminum alloy composite board | |
| CN112296086B (en) | Accumulative roll-stacking method for preparing high-bonding-strength copper-chromium composite material | |
| KR101568493B1 (en) | Magnesium alloys plate and method for manufacturing the same | |
| CN114807642B (en) | Segregation-free alloy and high yield preparation method thereof | |
| Shakouri et al. | Characterization of microstructure and mechanical properties of multilayer Al/Cu/Mg/Ni composite produced through accumulative roll bonding | |
| KR102534890B1 (en) | Fabrication method of aluminum alloy clad sheets and aluminum alloy clad sheets fabricated by the method | |
| CN113634597A (en) | Micro-nano layered copper/copper alloy composite board and preparation method thereof | |
| CN114148046B (en) | Aluminum alloy composite material and preparation method and application thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |