CN114261153A - Metal or alloy composite structure and preparation method and application thereof - Google Patents
Metal or alloy composite structure and preparation method and application thereof Download PDFInfo
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Abstract
The invention provides a metal or alloy composite structure and a preparation method and application thereof, wherein the composite structure comprises a layer A, a layer B and a layer C; the layer A and the layer C are made of high-temperature-resistant metal materials or high-temperature-resistant alloy materials; the layer B is a transition layer formed by melting a transition material with the layer A and the layer C, the transition layer is positioned between the layer A and the layer C, and the transition material is a fusible metal material or an alloy material thereof; the B layer is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer and the C layer in the forming and cooling process so as to reduce deformation. The composite structure prepared by the method is applied to the processing of equipment or components such as electronic equipment, aerospace equipment, power equipment, precision equipment or radiation-resistant equipment, and the like, has the advantages of stable processing technology, high production efficiency, short processing time, low production cost and the like, and the processed product has attractive appearance, high strength, light weight, strong corrosion resistance and radiation resistance and can meet the performance requirements of the product.
Description
Technical Field
The invention relates to the technical field of material forming, in particular to a metal or alloy composite structure and a preparation method and application thereof.
Background
The titanium alloy is an alloy formed by adding other alloy elements into titanium serving as a base material, has the advantages of low density (light weight), high specific strength, good corrosion resistance, high heat resistance, good process performance and the like, and based on the advantages, the outer frame body or the structural body of high-precision equipment such as aerospace equipment, electronic equipment, electrical equipment and the like is made of a titanium alloy material. Many mechanisms and electronic elements are generally installed in a frame or a structural body of high-precision equipment such as aerospace equipment, electronic equipment, electrical equipment and the like, so that a plurality of installation holes, installation grooves and other installation and positioning structures for installing and positioning the mechanisms and the electronic elements are generally arranged on the surface or the back surface of a titanium alloy frame or the structural body, but the titanium alloy has the characteristics of poor ductility, high hardness and the like, so that the titanium alloy is large in processing difficulty, complex in processing process and high in processing cost.
Taking a mobile phone as an example, as smart machines gradually move towards large screen, light and thin and multifunctional, the size of a mainstream screen is continuously increased, a larger screen needs a material with higher strength to support, and therefore a larger mobile phone middle frame is needed. The cost for processing the titanium alloy mobile phone middle frame by adopting the existing processing technology is more than 3 times of the cost for processing the stainless steel mobile phone middle frame. The existing processing mode is generally formed by numerical control processing of a whole metal plate or metal section, and is limited by a processing method and materials, so that the numerical control processing molding is long in time consumption, high in production cost and poor in mass production, and the existing numerical control processing method is easy to break due to the fact that the material is high in hardness and poor in plasticity and ductility; or the surface of the processed product has a few cracks, thereby causing problems such as poor appearance.
Patent document 4 with publication number CN112497864A discloses a high-temperature resistant light metal cladding material and a preparation method thereof, the cladding material is a three-layer structure, the outer layer is a high-temperature resistant metal material, the inner layer is a light metal material, and the middle layer is a slow-release isolation layer; the preparation of the cladding material is to use an outer layer high-temperature resistant metal material as a hot isostatic pressing sheath, and realize the formation of three layers of materials through hot isostatic pressing diffusion connection. Its advantages are low specific weight, and high resistance to high-temp oxidization and ablation.
As can be seen from the search, patent documents 1 to 3 mainly use a diffusion welding method to combine two layers of different materials, while patent document 4 mainly uses a hot isostatic pressing diffusion bonding method to form three layers of different materials. By adopting the existing method, the thermal expansion coefficients are different due to different materials, the generated internal stress is also different, and the deformation phenomenon is easy to occur in the forming process, or the layering problem occurs at the joint part between two layers of different materials in the later use process. Therefore, it is required to develop a composite structure having high strength and excellent machine-shaping properties, which can solve the problems of high processing cost, unstable product quality, poor mass productivity, and the like of the conventional high-strength metal material, and can satisfy the use requirements of high-precision devices such as electronic devices, aerospace devices, electric power devices, precision devices, and radiation-resistant devices.
Disclosure of Invention
In order to solve the above problems, an object of the present invention is to provide a composite structure with excellent properties, which has the advantages of stable processing technology, high production efficiency, short processing time, low production cost, etc. when being used for processing related products, and also provides a preparation method of the composite structure and an application of the composite structure, specifically a metal or alloy composite structure and a preparation method and an application thereof.
In order to achieve the purpose, the invention adopts the following technical scheme:
a metal or alloy composite structure comprising a layer a, a layer B and a layer C; the layer A and the layer C are made of high-temperature-resistant metal materials or high-temperature-resistant alloy materials; the layer B is a transition layer formed by melting a transition material with the layer A and the layer C, the transition layer is positioned between the layer A and the layer C, and the transition material is a fusible metal material or an alloy material thereof; the B layer is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer and the C layer in the forming and cooling process so as to reduce deformation.
Further, the B layers include B1 layer, B2 layer, B3 layer; wherein the content of the first and second substances,
the B1 layer comprises an alloy formed by melting a transition material and an A layer material, and an alloy formed by the A layer material, the transition material and a C layer material;
the B2 layer comprises an alloy formed by melting a transition material and an A layer material, an alloy formed by melting the A layer material, the transition material and a C layer material, and an alloy formed by melting the transition material and the C layer material;
the layer B3 includes an alloy formed from the material of layer A, the transition material, the material of layer C, and an alloy formed by melting the transition material and layer C.
Wherein the separation of the B layer into B1, B2 and B3 layers is not a well-defined interlayer structure, but is merely intended to describe an asymptotic process of melting the formed alloy with the transition layer being located near different positions of the a or C layers; in addition, because the A layer and the C layer are made of different raw materials and have different thermal expansion coefficients, the B layer is added for buffering the internal stress generated by the A layer and the C layer due to the different thermal expansion coefficients in the cooling process of the A layer and the C layer.
Further, the layer A is made of titanium or titanium alloy material; the layer C is made of zirconium or zirconium alloy; the transition material is any one or more of aluminum and alloy thereof, copper and alloy thereof, silver and alloy thereof, tin and alloy thereof, nickel and alloy thereof, niobium and alloy thereof, vanadium and alloy thereof, titanium-aluminum composite material or zirconium-aluminum composite material.
Further, the layer A is made of a titanium alloy material, and the titanium alloy material is Ti3Al alloy, Ti2AlNb alloy, Ti6Al4Any one of V alloy or titanium alloy composite material; the C layer is made of a zirconium alloy material, and the zirconium alloy material is a Zr-2 alloyAny one of Zr-4 alloy and Zr-2.5Nb alloy; the transition material is aluminum.
Furthermore, the invention also provides a preparation method of the metal or alloy composite structure, and the preparation method mainly comprises the steps of preparing a layer A and a layer C; cladding the transition material on one of the layer A and the layer C to form a cladding layer; overlapping the other one of the A layer and the C layer which is not clad with the transition material on the surface of the cladding layer to obtain a composite structure blank; placing the composite structure blank in a metal sheath for vacuum pumping treatment, and then performing hot pressing treatment; and finally removing the metal sheath to obtain the complex structure with the required shape and size.
Further, the preparation method specifically comprises the following steps:
(1) firstly, designing a metal sheath according to the shape and structure of a complex structure to be prepared, and requiring the overall dimension of the metal sheath to be 0.5-3 mm larger than the dimension of a workpiece;
(2) respectively processing corresponding high-temperature-resistant metal materials into an A layer and a C layer;
(3) cladding the transition material on one of the layer A and the layer C to form a cladding layer;
(4) stacking the other block of the non-cladding transition material on the surface of the cladding layer to obtain a composite structure blank;
(5) placing the composite structure blank in a metal sheath, and sealing the metal sheath;
(6) heating the sealed metal sheath, and simultaneously carrying out vacuum-pumping treatment in the heating process;
(7) placing the vacuumized metal sheath in a hot isostatic pressing machine for hot isostatic pressing; or placing the powder in an electromagnetic induction heater, performing electromagnetic induction heating treatment, and pressurizing by a bidirectional or unidirectional press; fusing the cladding layer with the layer A and the layer C into a whole to form a layer B;
(8) and taking the metal sheath subjected to the hot isostatic pressing treatment out of the hot isostatic pressing machine, cooling to room temperature, and removing the metal sheath to obtain the composite structure with the required shape and size.
Further, in the preparation method of the present invention, the cladding layer in step (3) is formed by cladding the transition material powder on the layer a or the layer C in a laser cladding manner; the specific process of laser cladding is that in the process that transition material powder falls on the layer A or the layer C, the transition material powder is melted by laser, and the melted transition material powder is fused on the layer A or the layer C to form a cladding layer.
Further, according to the preparation method, the particle size of the transition material powder in the step (3) is controlled within 200 microns, and the thickness of the B layer is 1-100 microns.
Further, according to the preparation method, before the composite structure blank in the step (5) is placed into the metal sheath, the prefabricated mold is used for clamping and shaping, and then the prefabricated mold clamped with the composite structure blank is placed into the metal sheath. After the prefabricated die is used for clamping and shaping, the situation that the blank deforms and displaces in the subsequent treatment process can be prevented, and meanwhile, the compounding efficiency can be improved.
Further, according to the preparation method, the metal sheath is internally provided with the release agent.
Further, according to the preparation method, the release agent is graphite, and the thickness of the release agent is 0.5-1.5 mm.
Further, in the preparation method of the present invention, in the laser cladding process in step (3), the specific laser cladding process parameters are as follows: the laser power is: 6 ~ 8KW, scanning speed is: 800-900 mm/min, and protective gas is: argon, powder feeding speed: 1-2 g/s.
Further, in the preparation method of the present invention, in the vacuum pumping treatment process in step (6), the specific vacuum degassing process parameters are as follows: the degassing temperature is 200-650 ℃, the vacuum degree is 1X 10-1X 10-3Pa, and the degassing time is 2-28 hours.
Further, in the preparation method of the present invention, in the hot isostatic pressing treatment in step (7), specific hot isostatic pressing process parameters are as follows: the hot isostatic pressing temperature is 950-1300 ℃, the pressure is 100-150 MPa, and the time of saturated temperature and saturated pressure is 3-5 hours.
Further, in the preparation method of the present invention, in the electromagnetic induction heating and pressurizing treatment in step (7), specific heating and pressurizing process parameters are as follows: the heating temperature is 950-1300 ℃, the pressure is 300-350 MPa, and the time of saturated temperature and saturated pressure is 1-2 hours.
The invention also discloses application of the metal or alloy composite structure in electronic equipment, aerospace equipment, electric power equipment, precision equipment or anti-radiation equipment.
Further, the electronic device comprises a mobile phone, a computer, a tablet computer, a watch, a camera or an intelligent wearable device, and is used for preparing a mobile phone middle frame, or a support framework of the computer, the tablet computer, the watch, the camera or the intelligent wearable device; the aerospace device comprises an aerospace structural part and is used for preparing an outer frame or a supporting framework of the aerospace structural part; the precision equipment comprises a precision measurement or detection instrument and is used for preparing an outer frame or a supporting framework of the precision measurement or detection instrument; the power equipment comprises a measuring meter and power supply equipment, and is used for preparing an outer frame of the measuring meter or a supporting framework of the power supply equipment.
Compared with the prior art, the metal or alloy composite structure and the preparation method and the application thereof have the beneficial effects that:
(1) the composite structure manufactured by the process has the advantages of light weight, high strength, good corrosion resistance, high heat resistance, good process performance, good ductility of the main processing surface, small hardness, convenient processing and capability of effectively reducing the processing cost.
(2) When the composite structure is manufactured, the layer A or the layer C is provided with the layer of transition material, the transition material forms a cladding layer in a laser cladding mode, and the cladding layer is fused between the layer A and the layer C to form a layer B in the hot isostatic pressing treatment or electromagnetic induction heating process, so that the composite fastness and the strength of the composite structure are enhanced; the existence of B layer can effectively cushion A layer and C layer because of A layer and the most internal stress that C layer thermal expansion coefficient difference produced in the cooling process for the difficult deformation or the deformation degree of taking place of composite structure are lighter.
(3) The composite structure is mainly formed by fusing a titanium alloy plate and a zirconium alloy plate with relatively similar expansion coefficients and a transition material arranged between the titanium alloy plate and the zirconium alloy, and the prepared composite structure has small internal stress, good ductility and difficult deformation or cracking; in the hot pressing process of the composite structure blank, the temperature of over 900 ℃ is adopted for processing, so that the zirconium alloy plate can generate crystal phase transformation and is transformed from alpha phase or beta phase to gamma phase, the gamma-phase zirconium alloy plate has good ductility and low hardness, is convenient to process, and can effectively reduce the processing cost.
In conclusion, the composite structure prepared by the method can be widely applied to electronic equipment, aerospace equipment, power equipment, precision equipment or radiation-resistant equipment, the composite structure is used as a base material to process related products, and the composite structure has the advantages of stable processing technology, high production efficiency, short processing time consumption, low production cost and the like.
Drawings
The present invention will be described in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic structural view of a composite structure according to the present invention;
FIG. 2 is a photograph of a product structure of a composite structure provided in example 1 of the present invention;
FIG. 3 is a photograph showing the structure of a product obtained by bending and extruding the composite structure provided in comparative example 1;
FIG. 4 is a photograph showing the structure of a product obtained by bending and extruding the composite structure provided in comparative example 1;
fig. 5 is a photograph showing the structure of the product after bending and pressing the composite structure provided in comparative example 2.
Detailed Description
The following description of the embodiments of the present invention is provided for illustrative purposes, and other advantages and effects of the present invention will become apparent to those skilled in the art from the present disclosure. The described embodiments are only some embodiments of the invention, not all 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. In addition, the hot isostatic pressing machine, the electromagnetic induction heater, the two-way press or the one-way press involved in the preparation process and the laser machine adopted by laser cladding are all universal equipment in the prior art, so long as the use requirements are met, and the specific model is not limited.
Example 1
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is a transition layer formed by melting a transition material with the A layer 1 and the C layer 3, the transition layer is positioned between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated by the difference of the thermal expansion coefficients of the A layer 1 and the C layer 3 in the forming cooling process so as to relieve deformation, and the B layer comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23; the division of the B layer 2 into B1 layers 21, B2 layers 22 and B3 layers 23 is not a well-defined interlayer structure, but is merely intended to describe an asymptotic process of melting the formed alloy with the transition layer being located close to different positions of the a layer 1 or the C layer 3; because the A layer 1 and the C layer 3 are made of different raw materials and have different thermal expansion coefficients, the transition material is added for buffering the internal stress generated by the A layer 1 and the C layer 3 due to the different thermal expansion coefficients in the cooling process of the A layer 1 and the C layer 3.
In this embodiment, the layer a 1 is a titanium plate, the layer C3 is a zirconium plate, and the transition material is aluminum.
The preparation method of the metal or alloy composite structure comprises the following steps:
(1) firstly, designing a metal sheath according to the shape and structure of a complex structure to be prepared, and requiring the overall dimension of the metal sheath to be 0.5-3 mm larger than the dimension of a workpiece;
(2) selecting a corresponding titanium plate and a corresponding zirconium plate,
(3) adopting a laser cladding mode to clad aluminum powder on the zirconium plate; the laser cladding specific process comprises the steps of melting aluminum powder by using laser in the process of dropping the aluminum powder onto a zirconium plate, and cladding the molten aluminum powder on the zirconium plate to form a cladding layer; the specific laser cladding process parameters are as follows: the laser power is: 6KW, scan speed: 800mm/min, protective gas is: argon, powder feeding speed: 1g/s, controlling the granularity of the aluminum powder within 200 mu m, and controlling the thickness of a cladding layer to be 1-20 mu m;
(4) stacking titanium plates on the surface of the cladding layer to obtain a composite structure blank;
(5) firstly, arranging a layer of graphite with the thickness of 0.5-1.0 mm in a metal sheath as a release agent, then clamping and shaping by using a prefabricated mold, then placing the prefabricated mold clamped with a composite structure blank into the metal sheath, and finally sealing the metal sheath;
(6) heating the sealed metal sheath, and simultaneously carrying out vacuum pumping treatment in the heating process, wherein the specific vacuum degassing process parameters are as follows: degassing at 200-350 deg.C under 1X10 degree of vacuum-1Pa, degassing for 2-15 hours;
(7) placing the vacuumized metal sheath in a hot isostatic pressing machine, carrying out hot isostatic pressing treatment, and fusing the cladding layer with the A layer 1 and the C layer 3 into a whole to form a B layer 2; the specific hot isostatic pressing process parameters are as follows: the hot isostatic pressing temperature is 950 ℃, the pressure is 100MPa, and the time of full temperature and full pressure is 3-5 hours;
(8) and taking the metal sheath subjected to the hot isostatic pressing treatment out of the hot isostatic pressing machine, cooling to room temperature, and removing the metal sheath to obtain the composite structure with the required shape and size.
Destructive analysis is carried out on the processed composite structure, since a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in the forming and cooling process so as to reduce deformation, and the B layer 2, the A layer 1 and the C layer 3 form an integral structure, so that the prepared composite structure is shown in FIG. 2. Through hardness detection, the Brinell hardness of the A layer 1 is 260-300 HB, the Brinell hardness of the C layer 3 is reduced to 110-150 HB, and the shear strength of the composite structure is greater than 350 MPa. Finally, through a bending extrusion test, the middle joint part does not generate the separation and delamination condition, and the condition of the product after bending extrusion is shown in fig. 3.
Example 2
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
The a layer 1, C layer 3 and transition material described in this example are the same as in example 1.
The above-described metal or alloy composite structure was prepared in substantially the same manner as in example 1, except during the hot pressing. Placing the vacuumized metal sheath in an electromagnetic induction heater, performing electromagnetic induction heating treatment, and pressurizing by a bidirectional or unidirectional press; fusing the cladding layer with the layer A and the layer C into a whole to form a layer B; the specific heating and pressurizing process parameters are as follows: the heating temperature is 950-1300 ℃, the pressure is 300-350 MPa, and the time of saturated temperature and saturated pressure is 1-2 hours.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Example 3
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
The a layer 1, C layer 3 and transition material described in this example are the same as in example 1.
The preparation method of the metal or alloy composite structure specifically comprises the following steps:
(1) firstly, designing a metal sheath according to the shape and structure of a complex structure to be prepared, and requiring the overall dimension of the metal sheath to be 0.5-3 mm larger than the dimension of a workpiece;
(2) selecting a corresponding titanium plate and a corresponding zirconium plate,
(3) adopting a laser cladding mode to clad aluminum powder on the zirconium plate; the laser cladding specific process comprises the steps of melting aluminum powder by using laser in the process of dropping the aluminum powder onto a zirconium plate, and cladding the molten aluminum powder on the zirconium plate to form a cladding layer; the specific laser cladding process parameters are as follows: the laser power is: 7KW, scan speed: 850mm/min, protective gas: argon, powder feeding speed: 1.5g/s, controlling the granularity of the aluminum powder within 200 mu m, and controlling the thickness of a cladding layer to be 20-60 mu m;
(4) stacking titanium plates on the surface of the cladding layer to obtain a composite structure blank;
(5) firstly, arranging a layer of graphite with the thickness of 0.8-1.2 mm in a metal sheath as a release agent, then clamping and shaping by using a prefabricated mold, then placing the prefabricated mold clamped with a composite structure blank into the metal sheath, and finally sealing the metal sheath;
(6) heating the sealed metal sheath, and simultaneously carrying out vacuum pumping treatment in the heating process, wherein the specific vacuum degassing process parameters are as follows: degassing at 300-450 deg.c and vacuum degree of 1X10-2Pa, degassing for 10-20 hours;
(7) placing the vacuumized metal sheath in a hot isostatic pressing machine, carrying out hot isostatic pressing treatment, and fusing the cladding layer with the A layer 1 and the C layer 3 into a whole to form a B layer; the specific hot isostatic pressing process parameters are as follows: the hot isostatic pressing temperature is 1050 ℃, the pressure is 120MPa, and the time of saturated temperature and pressure is 3-5 hours;
(8) and taking the metal sheath subjected to the hot isostatic pressing treatment out of the hot isostatic pressing machine, cooling to room temperature, and removing the metal sheath to obtain the composite structure with the required shape and size.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Example 4
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
The a layer 1, C layer 3 and transition material described in this example are the same as in example 1.
The preparation method of the metal or alloy composite structure specifically comprises the following steps:
(1) firstly, designing a metal sheath according to the shape and structure of a complex structure to be prepared, and requiring the overall dimension of the metal sheath to be 0.5-3 mm larger than the dimension of a workpiece;
(2) selecting a corresponding titanium plate and a corresponding zirconium plate,
(3) adopting a laser cladding mode to clad aluminum powder on the zirconium plate; the laser cladding specific process comprises the steps of melting aluminum powder by using laser in the process of dropping the aluminum powder onto a zirconium plate, and cladding the molten aluminum powder on the zirconium plate to form a cladding layer; the specific laser cladding process parameters are as follows: the laser power is: 8KW, scan speed: 900mm/min, protective gas is: argon, powder feeding speed: 2g/s, controlling the granularity of the aluminum powder within 200 mu m, and controlling the thickness of a cladding layer within 60-100 mu m;
(4) stacking titanium plates on the surface of the cladding layer to obtain a composite structure blank;
(5) placing the composite structure blank in a metal sheath, and sealing the metal sheath;
(6) heating the sealed metal sheath, and simultaneously carrying out vacuum pumping treatment in the heating process, wherein the specific vacuum degassing process parameters are as follows: degassing at 400-650 deg.C and vacuum degree of 1X10-3Pa, degassing for 20-28 hours;
(7) placing the vacuumized metal sheath in a hot isostatic pressing machine, carrying out hot isostatic pressing treatment, and fusing the cladding layer with the A layer 1 and the C layer 3 into a whole to form a B layer; the specific hot isostatic pressing process parameters are as follows: the hot isostatic pressing temperature is 1300 ℃, the pressure is 150MPa, and the time of full temperature and full pressure is 3-5 hours;
(8) and taking the metal sheath subjected to the hot isostatic pressing treatment out of the hot isostatic pressing machine, cooling to room temperature, and removing the metal sheath to obtain the composite structure with the required shape and size.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Example 5
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
In this example, layer A1 is Ti3The Al alloy titanium plate, the C layer 3 is a Zr-2 alloy zirconium plate, and the transition material is copper.
The method of making the metal or alloy composite structure described in this example was the same as in example 1.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Example 6
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
In this example, layer A1 is Ti3The Al alloy titanium plate, the C layer 3 is a Zr-2 alloy zirconium plate, and the transition material is copper.
The method of making the metal or alloy composite structure described in this example was the same as in example 2.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Example 7
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
In this example, layer A1 is Ti2An AlNb alloy plate, the C layer 3 being a Zr-4 alloy plate, andthe transition material is nickel.
The method of making the metal or alloy composite structure described in this example was the same as in example 3.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Example 8
As shown in fig. 1, the present embodiment provides a metal or alloy composite structure including an a layer 1, a B layer 2, and a C layer 3; the B layer 2 is formed by melting a transition material with the A layer 1 and the C layer 3, is positioned between the A layer 1 and the C layer 3, is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer 1 and the C layer 3 in a forming cooling process so as to relieve deformation, and comprises a B1 layer 21, a B2 layer 22 and a B3 layer 23.
In this example, layer A1 is Ti6Al4The C layer 3 is a Zr-2.5Nb alloy plate, and the transition material is a zirconium-aluminum composite material.
The method of making the metal or alloy composite structure described in this example was the same as in example 4.
Destructive analysis is carried out on the processed composite structure, and due to the fact that a transition layer, namely the B layer 2, is fused between the A layer 1 and the C layer 3, the B layer 2 is used for absorbing internal stress generated in the forming and cooling process due to the fact that the A layer 1 and the C layer 3 are different in thermal expansion coefficient, deformation is relieved, and an integrated structure is formed by the B layer 2, the A layer 1 and the C layer 3. Through the bending and extrusion test, the middle joint part does not generate the separation and delamination condition.
Comparative example 1
This comparative example provides a metal or alloy composite structure comprising an a layer 1 and a C layer 3.
The a layer 1, C layer 3 and transition material described in this comparative example are the same as in example 1.
The preparation method of the metal or alloy composite structure described in this comparative example uses the existing diffusion welding method to achieve the combination of the a layer 1 and the C layer 3.
Destructive analysis of the finished composite structure was performed, since there was no transition layer between the a layer 1 and the C layer 3, but the integral structure was formed directly. Through the bending extrusion test, the joint between the A layer 1 and the C layer 3 cracks, and the separation and delamination condition is generated, and the product condition is shown in figure 4. In addition, when the composite structure prepared by the comparative example is compared with the composite structure prepared by the example 1 in terms of weight, the weight of the composite structure can be reduced by 15-20% under the condition of the same thickness.
Comparative example 2
This comparative example provides a metal or alloy composite structure comprising an a layer 1 and a C layer 3.
The a layer 1, C layer 3 and transition material described in this comparative example are the same as in example 1.
The preparation method of the metal or alloy composite structure in the comparative example adopts the existing hot isostatic pressing diffusion connection mode to realize the combination of the A layer 1 and the C layer 3.
Destructive analysis of the finished composite structure was performed, since there was no transition layer between the a layer 1 and the C layer 3, but the integral structure was formed directly. Through the bending extrusion test, the joint between the A layer 1 and the C layer 3 cracks, and the separation and delamination condition is generated, and the product condition is shown in figure 5.
In conclusion, the composite structure prepared by the method has the characteristics of high strength, light weight, strong corrosion resistance and radiation resistance and the like, can be widely applied to electronic equipment, aerospace equipment, power equipment, precision equipment or radiation-resistant equipment, can realize the advantages of stable processing technology, high production efficiency, short processing time, low production cost and the like, and can meet the performance requirements of products.
It is to be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
The scope of the present invention is not limited to the technical solutions disclosed in the embodiments, and any modifications, equivalent substitutions, improvements, etc. made to the above embodiments according to the technical spirit of the present invention fall within the scope of the present invention.
Claims (17)
1. A metal or alloy composite structure characterized by: the composite structure comprises a layer A, a layer B and a layer C; the layer A and the layer C are made of high-temperature-resistant metal materials or high-temperature-resistant alloy materials; the layer B is a transition layer formed by melting a transition material with the layer A and the layer C, the transition layer is positioned between the layer A and the layer C, and the transition material is a fusible metal material or an alloy material thereof; the B layer is used for absorbing internal stress generated by different thermal expansion coefficients of the A layer and the C layer in the forming and cooling process so as to reduce deformation.
2. A metal or alloy composite structure according to claim 1 wherein: the B layers comprise a B1 layer, a B2 layer and a B3 layer; wherein the content of the first and second substances,
the B1 layer comprises an alloy formed by melting a transition material and an A layer material, and an alloy formed by the A layer material, the transition material and a C layer material;
the B2 layer comprises an alloy formed by melting a transition material and an A layer material, an alloy formed by melting the A layer material, the transition material and a C layer material, and an alloy formed by melting the transition material and the C layer material;
the layer B3 includes an alloy formed from the material of layer A, the transition material, the material of layer C, and an alloy formed by melting the transition material and layer C.
3. A metal or alloy composite structure according to claim 1 or 2, wherein: the layer A is made of titanium or titanium alloy material; the layer C is made of zirconium or zirconium alloy; the transition material is any one or more of aluminum and alloy thereof, copper and alloy thereof, silver and alloy thereof, tin and alloy thereof, nickel and alloy thereof, niobium and alloy thereof, vanadium and alloy thereof, titanium-aluminum composite material or zirconium-aluminum composite material.
4. A metal or alloy composite structure according to claim 3 wherein: the layer A is made of a titanium alloy material, and the titanium alloy material is Ti3Al alloy, Ti2AlNb alloy, Ti6Al4Any one of V alloy or titanium alloy composite material; the C layer is made of a zirconium alloy material, and the zirconium alloy material is any one of Zr-2 alloy, Zr-4 alloy or Zr-2.5Nb alloy; the transition material is aluminum.
5. A method of making a metal or alloy composite structure according to claim 1 or 2, wherein: the preparation method mainly comprises the steps of preparing a layer A and a layer C; cladding the transition material on one of the layer A and the layer C to form a cladding layer; overlapping the other one of the A layer and the C layer which is not clad with the transition material on the surface of the cladding layer to obtain a composite structure blank; placing the composite structure blank in a metal sheath for vacuum pumping treatment, and then performing hot pressing treatment; and finally removing the metal sheath to obtain the complex structure with the required shape and size.
6. The preparation method according to claim 5, characterized in that the preparation method specifically comprises the steps of:
(1) firstly, designing a metal sheath according to the shape and structure of a complex structure to be prepared, and requiring the overall dimension of the metal sheath to be 0.5-3 mm larger than the dimension of a workpiece;
(2) respectively processing corresponding high-temperature-resistant metal materials into an A layer and a C layer;
(3) cladding the transition material on one of the layer A and the layer C to form a cladding layer;
(4) stacking the other block of the non-cladding transition material on the surface of the cladding layer to obtain a composite structure blank;
(5) placing the composite structure blank in a metal sheath, and sealing the metal sheath;
(6) heating the sealed metal sheath, and simultaneously carrying out vacuum-pumping treatment in the heating process;
(7) placing the vacuumized metal sheath in a hot isostatic pressing machine for hot isostatic pressing; or placing the powder in an electromagnetic induction heater, performing electromagnetic induction heating treatment, and pressurizing by a bidirectional or unidirectional press; fusing the cladding layer with the layer A and the layer C into a whole to form a layer B;
(8) and taking the metal sheath subjected to the hot isostatic pressing treatment out of the hot isostatic pressing machine, cooling to room temperature, and removing the metal sheath to obtain the composite structure with the required shape and size.
7. The method of claim 6, wherein: the cladding layer in the step (3) is formed by cladding transition material powder on the layer A or the layer C in a laser cladding mode; the specific process of laser cladding is that in the process that transition material powder falls on the layer A or the layer C, the transition material powder is melted by laser, and the melted transition material powder is fused on the layer A or the layer C to form a cladding layer.
8. The method of claim 6, wherein: and (3) controlling the particle size of the transition material powder in the step (3) within 200 mu m, and controlling the thickness of the B layer to be 1-100 mu m.
9. The method of claim 6, wherein: and (5) before the composite structure blank is placed into the metal sheath, clamping and shaping by using a prefabricated mold, and then placing the prefabricated mold clamped with the composite structure blank into the metal sheath.
10. The method of claim 6, wherein: and a release agent is arranged in the metal sheath.
11. The method of claim 6, wherein: the release agent is graphite, and the thickness of the release agent is 0.5-1.5 mm.
12. The method of claim 6, wherein: in the laser cladding process in the step (3), the specific laser cladding process parameters are as follows: the laser power is: 6 ~ 8KW, scanning speed is: 800-900 mm/min, and protective gas is: argon, powder feeding speed: 1-2 g/s.
13. The method of claim 6, wherein: in the vacuum-pumping treatment process in the step (6), the specific vacuum degassing process parameters are as follows: degassing at 200-650 deg.C under 1X10 degree of vacuum-1～1X10-3The degassing time is 2-28 hours between Pa.
14. The method of claim 6, wherein: in the hot isostatic pressing treatment process in the step (7), specific hot isostatic pressing process parameters are as follows: the hot isostatic pressing temperature is 950-1300 ℃, the pressure is 100-150 MPa, and the time of saturated temperature and saturated pressure is 3-5 hours.
15. The method of claim 6, wherein: in the electromagnetic induction heating and pressurizing treatment in the step (7), the specific heating and pressurizing process parameters are as follows: the heating temperature is 950-1300 ℃, the pressure is 300-350 MPa, and the time of saturated temperature and saturated pressure is 1-2 hours.
16. Use of the metal or alloy composite structure according to claim 1 or 2 in electronic devices, aerospace devices, electrical devices, precision devices or radiation-resistant devices.
17. Use according to claim 16, characterized in that: the electronic equipment comprises a mobile phone, a computer, a tablet personal computer, a watch, a camera or intelligent wearable equipment, and is used for preparing a mobile phone middle frame or a support framework of the computer, the tablet personal computer, the watch, the camera or the intelligent wearable equipment; the aerospace device comprises an aerospace structural part and is used for preparing an outer frame or a supporting framework of the aerospace structural part; the precision equipment comprises a precision measurement or detection instrument and is used for preparing an outer frame or a supporting framework of the precision measurement or detection instrument; the power equipment comprises a measuring meter and power supply equipment, and is used for preparing an outer frame of the measuring meter or a supporting framework of the power supply equipment.
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