CN113600957A - Composite interlayer and method for brazing boron carbide composite ceramic and titanium alloy - Google Patents
Composite interlayer and method for brazing boron carbide composite ceramic and titanium alloy Download PDFInfo
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- CN113600957A CN113600957A CN202110924039.2A CN202110924039A CN113600957A CN 113600957 A CN113600957 A CN 113600957A CN 202110924039 A CN202110924039 A CN 202110924039A CN 113600957 A CN113600957 A CN 113600957A
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- 238000005219 brazing Methods 0.000 title claims abstract description 100
- 239000002131 composite material Substances 0.000 title claims abstract description 93
- 239000000919 ceramic Substances 0.000 title claims abstract description 62
- 229910052580 B4C Inorganic materials 0.000 title claims abstract description 58
- INAHAJYZKVIDIZ-UHFFFAOYSA-N boron carbide Chemical compound B12B3B4C32B41 INAHAJYZKVIDIZ-UHFFFAOYSA-N 0.000 title claims abstract description 57
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 55
- 239000011229 interlayer Substances 0.000 title claims abstract description 30
- 238000000034 method Methods 0.000 title claims abstract description 18
- 229910002110 ceramic alloy Inorganic materials 0.000 title claims abstract description 14
- 229910052751 metal Inorganic materials 0.000 claims abstract description 72
- 239000002184 metal Substances 0.000 claims abstract description 72
- 239000010410 layer Substances 0.000 claims abstract description 64
- 239000000945 filler Substances 0.000 claims abstract description 51
- 229910017945 Cu—Ti Inorganic materials 0.000 claims abstract description 49
- 239000010949 copper Substances 0.000 claims abstract description 36
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 29
- 229910052802 copper Inorganic materials 0.000 claims abstract description 28
- 229910000679 solder Inorganic materials 0.000 claims description 21
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 10
- 238000001816 cooling Methods 0.000 claims description 9
- 238000004506 ultrasonic cleaning Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 7
- 239000010936 titanium Substances 0.000 claims description 6
- 230000003746 surface roughness Effects 0.000 claims description 5
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 4
- 239000002904 solvent Substances 0.000 claims description 2
- 238000005452 bending Methods 0.000 abstract description 3
- 239000010955 niobium Substances 0.000 description 11
- 238000013001 point bending Methods 0.000 description 11
- 230000000052 comparative effect Effects 0.000 description 10
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 description 9
- 229910052758 niobium Inorganic materials 0.000 description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 6
- 239000011888 foil Substances 0.000 description 6
- 229910002804 graphite Inorganic materials 0.000 description 6
- 239000010439 graphite Substances 0.000 description 6
- 229910052709 silver Inorganic materials 0.000 description 5
- 239000011889 copper foil Substances 0.000 description 4
- 239000010944 silver (metal) Substances 0.000 description 4
- 229910052719 titanium Inorganic materials 0.000 description 4
- 238000003466 welding Methods 0.000 description 4
- 238000005282 brightening Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 150000002739 metals Chemical class 0.000 description 3
- 238000005498 polishing Methods 0.000 description 3
- 238000004321 preservation Methods 0.000 description 3
- 238000005476 soldering Methods 0.000 description 3
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000001035 drying Methods 0.000 description 2
- 238000005245 sintering Methods 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 1
- 229910007948 ZrB2 Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000861 blow drying Methods 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007676 flexural strength test Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000001000 micrograph Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052575 non-oxide ceramic Inorganic materials 0.000 description 1
- 239000011225 non-oxide ceramic Substances 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
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- 238000001878 scanning electron micrograph Methods 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 238000002490 spark plasma sintering Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
- B23K1/206—Cleaning
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2103/00—Materials to be soldered, welded or cut
- B23K2103/16—Composite materials, e.g. fibre reinforced
Abstract
The invention discloses a composite interlayer and a method for brazing boron carbide composite ceramic and titanium alloy by using the same. The composite middle layer consists of an upper brazing filler metal layer, a middle metal layer and a lower brazing filler metal layer; the upper brazing filler metal layer and the lower brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal, and the middle metal layer is made of copper. The method for brazing the boron carbide composite ceramic and the titanium alloy by using the composite interlayer comprises the steps of sequentially placing the composite interlayer and the titanium alloy on the surface to be brazed of the boron carbide composite ceramic to form a workpiece to be brazed in a sandwich structure, and performing high-temperature brazing connection on the workpiece to be brazed under a vacuum condition, so that the obtained brazed joint has excellent bending strength.
Description
Technical Field
The invention belongs to the field of connection of ceramics and metals, and particularly relates to a composite interlayer and a method for brazing boron carbide composite ceramics and titanium alloy by using the same.
Background
Boron carbide as a novel non-oxide ceramic within special ceramics has very good properties: high melting point, high hardness, high elastic modulus, low density, good thermal stability, strong chemical corrosion resistance, strong neutron absorption capacity and the like. Boron carbide as one member of a superhard material family is mainly used for armors, armor shields and a plurality of industrial applications of tanks, and has wide application prospect in the fields of aerospace, nuclear engineering and the like. The boron carbide composite ceramic prepared by sintering improves the mechanical property thereof, solves the problems of poor sintering property, low fracture toughness and the like, and improves the electrical conductivity thereof by introducing the second phase, thereby solving the problem of difficult machining. The titanium alloy has high specific strength, small elastic modulus, excellent corrosion resistance and higher application temperature, and is widely applied to the aspects of aviation, aerospace, medical treatment, chemical industry, military, marine petroleum and the like.
In engineering applications, due to technical and equipment limitations or the need for realizing special functions, material connection technology is often needed to obtain ceramic matrix composite and titanium alloy connected components with large sizes or complex shapes. The advantages of both ceramics and metals can be combined to obtain the composite member with excellent performances of both ceramics and metals. The reliable connection between the boron carbide composite ceramic and the titanium alloy is realized, the application range of the boron carbide composite ceramic is expanded, but at present, few reports about connection research between the boron carbide composite ceramic and the titanium alloy are reported.
The main difficulties of the connection of the boron carbide composite ceramic and the titanium alloy are as follows: (1) the difference of the thermal physical properties of the two materials is large (particularly the expansion coefficient), so that large residual stress is generated in the joint in the process of cooling after welding, and even the joint fails; (2) boron carbide ceramics are difficult to weld. Therefore, it is highly desirable to provide a method for bonding boron carbide composite ceramics and titanium alloys.
Disclosure of Invention
Based on the technical problems, the invention provides the composite interlayer and the method for brazing the boron carbide composite ceramic and the titanium alloy by using the composite interlayer, which can realize high-performance connection of the boron carbide composite ceramic and the titanium alloy and solve the problems that the ceramic material is difficult to weld and the joint is low in strength and even cracks due to large residual stress of the joint when the boron carbide composite ceramic and the titanium alloy are brazed.
The specific technical scheme of the invention is as follows:
the invention provides a composite middle layer, which consists of an upper brazing filler metal layer, a middle metal layer and a lower brazing filler metal layer; the upper brazing filler metal layer and the lower brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal, and the middle metal layer is made of copper.
Preferably, the thickness of the intermediate metal layer is 0.3-1 mm; the thickness of the upper brazing filler metal layer is 50-80 μm; the thickness of the lower brazing filler metal layer is 50-80 μm; more preferably, the thickness of the intermediate metal layer is 0.5-0.8 mm.
Preferably, the purity of the copper is 99.00-99.95%.
Preferably, in the Ag-Cu-Ti solder, the mass fraction of Ti is 1-10%.
Preferably, in the Ag-Cu-Ti brazing filler metal, the mass fraction of Ag is 60-70%, and the mass fraction of Cu is 20-30%.
The invention also provides a method for brazing the boron carbide composite ceramic and the titanium alloy by using the composite interlayer, wherein the composite interlayer and the titanium alloy are sequentially placed on the surface to be brazed of the boron carbide composite ceramic to form a workpiece to be brazed in a sandwich structure, and the workpiece to be brazed is subjected to high-temperature brazing connection under a vacuum condition.
The composition of the boron carbide composite ceramic of the present invention is not particularly limited, and includes, but is not limited to, B4C-ZrB2-SiC composite ceramic. The type of titanium alloy described in the present invention is not particularly limited, and includes, but is not limited to, TC4, TC6, TC11, TA10, TA15, TB2, TB3, and the like.
Preferably, the high temperature brazed connection is in particular: placing the workpiece to be brazed in a vacuum furnace with the vacuum degree of less than or equal to 5 multiplied by 10- 2Pa, the brazing temperature is 790-870 ℃, the pressure is 0.01-0.05MPa, the temperature is kept for 5-30min, then the temperature is reduced to 280-300 ℃, and then the furnace is cooled to the room temperature.
Preferably, the temperature is increased from room temperature to the brazing temperature at a temperature increase rate of 5-10 ℃/min; the temperature is reduced from the brazing temperature to 280-300 ℃ at the cooling rate of 5-10 ℃/min.
Preferably, before high-temperature soldering connection, the Ag-Cu-Ti solder, the copper, the titanium alloy and the boron carbide composite ceramic are ground and polished to ensure that the surface roughness Ra of the materials is less than or equal to 5 mu m.
Preferably, before high-temperature soldering connection, the polished Ag-Cu-Ti solder, copper, titanium alloy and boron carbide composite ceramic are subjected to ultrasonic cleaning; the solvent for ultrasonic cleaning is acetone or ethanol, and the ultrasonic cleaning time is 10-20 min.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a composite interlayer for brazing boron carbide composite ceramic and titanium alloy, which consists of an upper brazing filler metal layer, a middle metal layer and a lower brazing filler metal layer; the upper brazing filler metal layer and the lower brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal, and the middle metal layer is made of copper. The joint obtained by brazing the boron carbide composite ceramic and the titanium alloy by using the composite interlayer has excellent bending strength.
The Ag-Cu-Ti brazing filler metal can wet ceramics and titanium alloy to form good interface metallurgical bonding, and the problem that boron carbide ceramics are difficult to weld is solved; the Ag-Cu-Ti brazing filler metal and the metal copper form a composite intermediate layer in a specific structure, the boron carbide composite ceramic and the titanium alloy are connected, joint stress can be slowly released through plastic deformation or viscoplastic deformation of the silver-based brazing seam layer and the copper, and the problem of large residual stress of joints of boron carbide composite ceramic and titanium alloy connectors is solved.
In the preferred scheme, the bending strength of the boron carbide composite ceramic and titanium alloy soldered joint is further enhanced by further optimizing the thickness of the Cu in the middle metal layer, the thickness of the upper layer solder layer, the thickness of the lower layer solder layer and the soldering temperature.
Drawings
FIG. 1 is a schematic structural diagram of a brazed joint of boron carbide composite ceramic and titanium alloy obtained by brazing the composite interlayer of the present invention.
FIG. 2 is a scanning electron microscope image of a brazed joint prepared in example 1 of the present invention at a low magnification.
FIG. 3 is a high-power scanning electron micrograph of a brazed joint prepared in example 1 of the present invention.
Detailed Description
Hereinafter, the technical solution of the present invention will be described in detail by specific examples, but these examples should be explicitly proposed for illustration, but should not be construed as limiting the scope of the present invention.
The boron carbide composite ceramics in the following examples and comparative examples are B prepared by spark plasma sintering4C-ZrB2-SiC composite ceramic (wherein ZrB2And SiC in a volume fraction of 18% and 24%, respectively, B4C is the balance), the size of which is 8mm × 8mm × 8 mm; the titanium alloy is TC4 titanium alloy, and the size of the titanium alloy is 8mm multiplied by 8 mm.
Example 1
A composite middle layer consists of an upper brazing filler metal layer, a middle metal layer and a lower brazing filler metal layer; the upper brazing filler metal layer and the lower brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal, and the middle metal layer is made of copper. The composite intermediate layer is expressed by Ag-Cu-Ti/Cu/Ag-Cu-Ti.
Wherein the Ag-Cu-Ti solder is a solder foil, the mass fractions of Ag, Cu and Ti in the Ag-Cu-Ti solder are respectively 68.8%, 26.7% and 4.5%, and the sizes are 8mm multiplied by 0.07 mm; the copper is copper foil, the purity of the copper is 99.95%, and the size of the copper is 8mm multiplied by 0.8 mm;
a method for brazing boron carbide composite ceramic and titanium alloy by using the composite interlayer specifically comprises the following steps:
1) polishing and brightening the to-be-welded surfaces of the boron carbide composite ceramic, the titanium alloy, the Ag-Cu-Ti brazing filler metal and the copper by using SiC abrasive paper to ensure that the surface roughness Ra of the materials is less than or equal to 5 mu m;
2) sequentially putting boron carbide composite ceramic, titanium alloy, Ag-Cu-Ti solder and copper into ethanol, performing ultrasonic cleaning for 15min, and drying for later use;
3) sequentially placing Ag-Cu-Ti/Cu/Ag-Cu-Ti and titanium alloy on the to-be-welded surface of the boron carbide composite ceramic to assemble a to-be-brazed workpiece with a sandwich structure, and then placing the to-be-brazed workpiece in a graphite mold;
4) placing the graphite mold with the workpiece to be brazed in a vacuum furnace for brazing connection, wherein the vacuum degree is 4 multiplied by 10- 2Pa, the brazing temperature is 790 ℃, the pressure is 0.02MPa, the heat preservation time is 10min, the heating rate is 10 ℃/min, the cooling rate is 5 ℃/min to 300 ℃, and then furnace cooling is carried out to room temperature, so as to obtain the boron carbide composite ceramic and titanium alloy brazing joint.
The three-point bending strength of the brazed joint obtained in this example was tested to be 63 MPa.
And (3) detecting the brazing joint by a low-power scanning electron microscope, wherein the scanning electron microscope figure of the brazing joint is shown in figure 2, and the interface connection of the brazing joint is good.
The brazing joint is detected by a high-power scanning electron microscope, the scanning electron microscope figure of the brazing joint is shown in figure 3, and it can be seen that the Ag-Cu-Ti brazing filler metal and the boron carbide composite ceramic react at a connecting interface to generate carbide and boride, so that strong interface combination is formed.
Example 2
This example is the same as example 1 except that in step 4, the brazing temperature was 810 ℃.
The three-point bending strength of the brazed joint obtained in this example was tested to be 69 MPa.
Example 3
This example is the same as example 1 except that in step 4, the brazing temperature was 830 ℃.
The three-point bending strength of the brazed joint obtained in this example was tested to be 74 MPa.
Example 4
This example is the same as example 1 except that in step 4, the brazing temperature was 850 ℃.
Tests show that the three-point bending strength of the brazing joint obtained by the embodiment can reach 68 MPa.
Example 5
This example is the same as example 3 except that the copper foil has dimensions of 8mm × 8mm × 0.5 mm.
The three-point bending strength of the braze joint obtained in the example was tested to be 62 MPa.
Example 6
This example is the same as example 3 except that in step 4, the holding time during brazing is 5 min.
The three-point bending strength of the brazed joint obtained in this example was tested to be 65 MPa.
Example 7
This example is the same as example 3 except that the copper foil has a size of 8mm × 8mm × 1 mm.
The three-point bending strength of the brazed joint obtained in this example was tested to be 63 MPa.
Comparative example 1
And brazing connection is carried out on the boron carbide composite ceramic and the titanium alloy by taking an Ag-Cu-Ti brazing filler metal foil as an intermediate layer, wherein the mass fractions of Ag, Cu and Ti in the Ag-Cu-Ti brazing filler metal foil are respectively 68.8%, 26.7% and 4.5%, and the sizes are 8mm multiplied by 0.07 mm. The specific brazing process comprises the following steps:
1) polishing and brightening the surfaces to be welded of the boron carbide composite ceramic, the titanium alloy and the Ag-Cu-Ti solder by using SiC abrasive paper, wherein the surface roughness Ra is less than or equal to 5 mu m;
2) sequentially putting the boron carbide composite ceramic, the titanium alloy and the Ag-Cu-Ti brazing filler metal into ethanol, carrying out ultrasonic cleaning for 15min, and drying for later use;
3) sequentially placing Ag-Cu-Ti solder and titanium alloy on the to-be-welded surface of the boron carbide composite ceramic to assemble a to-be-brazed workpiece, and then placing the to-be-brazed workpiece in a graphite mold;
4) and (3) placing the graphite mold with the workpiece to be welded into a vacuum furnace for braze welding connection, wherein the vacuum degree is 4 multiplied by 10 < -2 > Pa, the braze welding temperature is 830 ℃, the pressure is 0.02MPa, the heat preservation time is 10min, the heating rate is 10 ℃/min, the cooling rate is 5 ℃/min to 300 ℃, and then, furnace cooling is carried out to the room temperature, so that the boron carbide composite ceramic and titanium alloy braze welding joint is obtained.
The three-point bending strength of the brazed joint obtained in this comparative example was tested to be 23 MPa.
Comparative example 2
A composite middle layer consists of an upper brazing filler metal layer, a middle metal layer and a lower brazing filler metal layer; the upper brazing filler metal layer and the lower brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal, and the middle metal layer is made of niobium. The composite interlayer described in this comparative example is denoted as "Ag-Cu-Ti/Nb/Ag-Cu-Ti".
Wherein the Ag-Cu-Ti solder is solder foil, the mass fractions of Ag, Cu and Ti in the Ag-Cu-Ti solder foil are respectively 68.8%, 26.7% and 4.5%, and the sizes are 8mm multiplied by 0.07 mm; the niobium was a niobium foil having a purity of 99.95% and a size of 8mm × 8mm × 0.2 mm.
A method for brazing a boron carbide composite ceramic and a titanium alloy using the above composite interlayer, which was otherwise the same as in example 3 except that "Ag-Cu-Ti/Cu/Ag-Cu-Ti" was replaced with "Ag-Cu-Ti/Nb/Ag-Cu-Ti" in the composite interlayer, and "copper" in each step was replaced with "niobium".
The three-point bending strength of the brazed joint obtained in this comparative example was tested to be 28 MPa.
Comparative example 3
A composite interlayer consists of a first brazing filler metal layer, copper, a second brazing filler metal layer, niobium and a third brazing filler metal layer from top to bottom; the first brazing filler metal layer, the second brazing filler metal layer and the third brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal. The composite interlayer described in this comparative example is denoted as "Ag-Cu-Ti/Nb/Ag-Cu-Ti/Cu/Ag-Cu-Ti".
Wherein the Ag-Cu-Ti solder is a solder foil, the mass fractions of Ag, Cu and Ti in the Ag-Cu-Ti solder are respectively 68.8%, 26.7% and 4.5%, and the sizes are 8mm multiplied by 0.07 mm; the copper is copper foil, the purity of the copper is 99.95%, and the size of the copper is 8mm multiplied by 0.8 mm; the niobium was a niobium foil having a purity of 99.95% and a size of 8mm × 8mm × 0.2 mm.
A method for brazing boron carbide composite ceramic and titanium alloy by using the composite interlayer specifically comprises the following steps:
1) polishing and brightening the to-be-welded surfaces of boron carbide-based composite ceramic, titanium alloy, Ag-Cu-Ti brazing filler metal, copper and niobium by using SiC abrasive paper to ensure that the surface roughness Ra of the materials is less than or equal to 5 mu m;
2) sequentially putting boron carbide-based composite ceramic, titanium alloy, Ag-Cu-Ti brazing filler metal, copper and niobium into ethanol, carrying out ultrasonic cleaning for 15min, and blow-drying for later use;
3) sequentially placing Ag-Cu-Ti/Nb/Ag-Cu-Ti/Cu/Ag-Cu-Ti and titanium alloy on the to-be-welded surface of the boron carbide composite ceramic to assemble a to-be-brazed workpiece, and then placing the to-be-brazed workpiece in a graphite mold;
4) placing the graphite mold with the workpiece to be brazed in a vacuum furnace for brazing connection, wherein the vacuum degree is 4 multiplied by 10- 2Pa, the brazing temperature is 830 ℃, the pressure is 0.02MPa, the heat preservation time is 10min, the heating rate is 10 ℃/min, the cooling rate is 5 ℃/min to 300 ℃, and then furnace cooling is carried out to room temperature, so as to obtain the boron carbide composite ceramic and titanium alloy brazing joint.
The three-point bending strength of the brazed joint obtained in this comparative example was 40MPa, as measured.
The three-point bending strength test results of the boron carbide composite ceramic and titanium alloy brazed joint prepared in the above examples and comparative examples of the present invention are shown in table 1 below:
TABLE 1 flexural Strength test results of brazed joints
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (10)
1. A composite intermediate layer is characterized by consisting of an upper brazing filler metal layer, an intermediate metal layer and a lower brazing filler metal layer; the upper brazing filler metal layer and the lower brazing filler metal layer are made of Ag-Cu-Ti brazing filler metal, and the middle metal layer is made of copper.
2. The composite interlayer of claim 1, wherein the thickness of the intermediate metal layer is 0.3-1 mm; the thickness of the upper brazing filler metal layer is 50-80 μm; the thickness of the lower brazing filler metal layer is 50-80 μm; preferably, the thickness of the intermediate metal layer is 0.5-0.8 mm.
3. The composite interlayer of claim 1 or 2, wherein the copper has a purity of 99.00-99.95%.
4. The composite interlayer according to any one of claims 1 to 3, wherein the mass fraction of Ti in the Ag-Cu-Ti solder is 1% to 10%.
5. The composite interlayer of claim 4, wherein the mass fraction of Ag is 60-70% and the mass fraction of Cu is 20-30% in the Ag-Cu-Ti solder.
6. A method for brazing boron carbide composite ceramics and titanium alloy by using the composite interlayer as claimed in any one of claims 1 to 5, characterized in that the composite interlayer and the titanium alloy are sequentially arranged on the surface to be brazed of the boron carbide composite ceramics, and workpieces to be brazed are assembled into a sandwich structure and are subjected to high-temperature brazing connection under a vacuum condition.
7. The method for brazing the boron carbide composite ceramic and the titanium alloy by using the composite interlayer according to claim 6, wherein the high-temperature brazing connection is specifically as follows: placing the workpiece to be brazed in a vacuum furnace with the vacuum degree of less than or equal to 5 multiplied by 10-2Pa, the brazing temperature is 790-870 ℃, the pressure is 0.01-0.05MPa, the temperature is kept for 5-30min, then the temperature is reduced to 280-300 ℃, and then the furnace is cooled to the room temperature.
8. The method of brazing a boron carbide composite ceramic and titanium alloy with a composite interlayer according to claim 7, wherein the temperature is raised from room temperature to the brazing temperature at a ramp rate of 5-10 ℃/min; the temperature is reduced from the brazing temperature to 280-300 ℃ at the cooling rate of 5-10 ℃/min.
9. The method for brazing a boron carbide composite ceramic and a titanium alloy using a composite interlayer according to any one of claims 6 to 8, wherein before the high temperature brazing, the Ag-Cu-Ti solder, the copper, the titanium alloy and the boron carbide composite ceramic are polished so that the surface roughness Ra of the materials is not more than 5 μm.
10. The method for brazing the boron carbide composite ceramic and the titanium alloy with the composite interlayer according to claim 9, wherein before the high-temperature brazing connection, the polished Ag-Cu-Ti solder, copper, titanium alloy and boron carbide composite ceramic are subjected to ultrasonic cleaning; the solvent for ultrasonic cleaning is acetone or ethanol, and the ultrasonic cleaning time is 10-20 min.
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN114105669A (en) * | 2021-11-11 | 2022-03-01 | 南京理工大学 | Composite manufacturing and stress releasing method of ceramic-coated cylinder sleeve of engine |
| CN114178638A (en) * | 2021-12-03 | 2022-03-15 | 湘潭大学 | Welding method for high-strength graphite pipe and titanium alloy pipe sleeved composite component |
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| CN114105669A (en) * | 2021-11-11 | 2022-03-01 | 南京理工大学 | Composite manufacturing and stress releasing method of ceramic-coated cylinder sleeve of engine |
| CN114029571A (en) * | 2021-12-03 | 2022-02-11 | 湘潭大学 | Method for brazing graphite and titanium alloy by using NiCu porous alloy interlayer |
| CN114178638A (en) * | 2021-12-03 | 2022-03-15 | 湘潭大学 | Welding method for high-strength graphite pipe and titanium alloy pipe sleeved composite component |
| CN114951880A (en) * | 2022-06-13 | 2022-08-30 | 宁波江丰电子材料股份有限公司 | Method for welding three-layer structure ceramic target |
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| CN116283337B (en) * | 2023-03-30 | 2024-02-06 | 中国科学院上海硅酸盐研究所 | Boron carbide ceramic-metal gradient connection structure and preparation method thereof |
| CN116532740A (en) * | 2023-06-13 | 2023-08-04 | 哈尔滨工业大学 | Method for step-by-step brazing of magnesium fluoride ceramic and titanium alloy by using metal and glass solder |
| CN116532740B (en) * | 2023-06-13 | 2024-04-09 | 哈尔滨工业大学 | Method for step-by-step brazing of magnesium fluoride ceramic and titanium alloy by using metal and glass solder |
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