CN115338409B - SiAlON-YG8 composite welding blade and preparation method and application thereof - Google Patents
SiAlON-YG8 composite welding blade and preparation method and application thereof Download PDFInfo
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- CN115338409B CN115338409B CN202211071168.2A CN202211071168A CN115338409B CN 115338409 B CN115338409 B CN 115338409B CN 202211071168 A CN202211071168 A CN 202211071168A CN 115338409 B CN115338409 B CN 115338409B
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- 238000003466 welding Methods 0.000 title claims abstract description 48
- 239000002131 composite material Substances 0.000 title claims abstract description 42
- 238000002360 preparation method Methods 0.000 title claims abstract description 12
- 229910003564 SiAlON Inorganic materials 0.000 claims abstract description 50
- 238000005245 sintering Methods 0.000 claims abstract description 27
- 238000005219 brazing Methods 0.000 claims abstract description 25
- 239000000956 alloy Substances 0.000 claims abstract description 19
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 18
- 239000011159 matrix material Substances 0.000 claims abstract description 15
- 238000005520 cutting process Methods 0.000 claims abstract description 14
- 238000000227 grinding Methods 0.000 claims abstract description 13
- 239000011812 mixed powder Substances 0.000 claims abstract description 13
- 238000012545 processing Methods 0.000 claims abstract description 12
- 238000003754 machining Methods 0.000 claims abstract description 11
- 239000000203 mixture Substances 0.000 claims abstract description 6
- 239000000463 material Substances 0.000 claims description 32
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- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 21
- 229910018072 Al 2 O 3 Inorganic materials 0.000 claims description 18
- 238000000034 method Methods 0.000 claims description 18
- 238000010438 heat treatment Methods 0.000 claims description 17
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 12
- 238000001035 drying Methods 0.000 claims description 8
- 238000005476 soldering Methods 0.000 claims description 8
- 238000002156 mixing Methods 0.000 claims description 7
- 238000003825 pressing Methods 0.000 claims description 7
- 229910052757 nitrogen Inorganic materials 0.000 claims description 6
- 238000002490 spark plasma sintering Methods 0.000 claims description 6
- 229910052709 silver Inorganic materials 0.000 claims description 5
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 claims description 4
- 238000000576 coating method Methods 0.000 claims description 4
- 238000009694 cold isostatic pressing Methods 0.000 claims description 4
- 238000007731 hot pressing Methods 0.000 claims description 4
- 239000000843 powder Substances 0.000 claims description 4
- 238000007873 sieving Methods 0.000 claims description 4
- 239000002245 particle Substances 0.000 claims description 3
- 229910052769 Ytterbium Inorganic materials 0.000 claims description 2
- 229910052727 yttrium Inorganic materials 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims 5
- 235000011837 pasties Nutrition 0.000 claims 1
- 238000010008 shearing Methods 0.000 claims 1
- 239000000919 ceramic Substances 0.000 description 9
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- 230000004907 flux Effects 0.000 description 3
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 150000001875 compounds Chemical class 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000002994 raw material Substances 0.000 description 2
- 238000001878 scanning electron micrograph Methods 0.000 description 2
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- 229910001220 stainless steel Inorganic materials 0.000 description 2
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- 241001391944 Commicarpus scandens Species 0.000 description 1
- AFCARXCZXQIEQB-UHFFFAOYSA-N N-[3-oxo-3-(2,4,6,7-tetrahydrotriazolo[4,5-c]pyridin-5-yl)propyl]-2-[[3-(trifluoromethoxy)phenyl]methylamino]pyrimidine-5-carboxamide Chemical compound O=C(CCNC(=O)C=1C=NC(=NC=1)NCC1=CC(=CC=C1)OC(F)(F)F)N1CC2=C(CC1)NN=N2 AFCARXCZXQIEQB-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- JPNWDVUTVSTKMV-UHFFFAOYSA-N cobalt tungsten Chemical compound [Co].[W] JPNWDVUTVSTKMV-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/04—Making metallic powder or suspensions thereof using physical processes starting from solid material, e.g. by crushing, grinding or milling
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/02—Compacting only
- B22F3/04—Compacting only by applying fluid pressure, e.g. by cold isostatic pressing [CIP]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/105—Sintering only by using electric current other than for infrared radiant energy, laser radiation or plasma ; by ultrasonic bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/12—Both compacting and sintering
- B22F3/14—Both compacting and sintering simultaneously
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/04—Making metallic powder or suspensions thereof using physical processes starting from solid material, e.g. by crushing, grinding or milling
- B22F2009/043—Making metallic powder or suspensions thereof using physical processes starting from solid material, e.g. by crushing, grinding or milling by ball milling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention belongs to the technical field of workpiece machining, and discloses a SiAlON-YG8 composite welding blade, and a preparation method and application thereof. Flattening and sintering SiAlON mixed powder, obtaining SiAlON presintered blocks, processing the SiAlON presintered blocks into SiAlON cutter corners, and processing YG8 hard alloy plates into YG8 matrixes with unfilled corners by laser; and (3) the SiAlON cutter angles are consistent with the four cutter angles cut out by the YG8 matrix, then the SiAlON cutter angles are replaced with the cut-out four cutter angles to be adhered with the YG8 matrix with unfilled corners, the mixture is sintered at 800-900 ℃ by a brazing furnace to obtain a sintered blank of the cutter, and the SiAlON-YG8 composite welding blade is obtained by grinding. The composite welding blade of the cutter has higher strength and wear resistance, and can be applied to the fields of cutting, processing bearings of aerospace wear-resistant parts and the like.
Description
Technical Field
The invention belongs to the technical field of workpiece machining, and particularly relates to a SiAlON-YG8 composite welding blade, and a preparation method and application thereof.
Background
SiAlON (SiAlON) is a metal oxide of Si 3 N 4 Based on the development of a novel material having a crystal structure with Si 3 N 4 Similarly, in Si 3 N 4 Single-phase compounds formed by the metal elements Me and O in solid solution are based on Si 3 N 4 Is a generic term for ceramic compounds. Among all ceramic materials, the SiAlON ceramic has the characteristics of high hardness, high strength, high toughness, excellent dimensional stability, thermal shock resistance and the like, and is the structural ceramic with the best comprehensive performance.
Among many tool materials, sialon ceramic tools can achieve higher cutting speeds than cemented carbide tools due to excellent high temperature strength and red hardness. When cast iron and nickel-based alloys are processed, the cutting speed of the SiAlON ceramic cutter can reach tens of times of that of the traditional cutter material (such as hard alloy). Compared with an alumina-based material cutter, the SiAlON-based cutter has higher toughness and capability of bearing rapid temperature change in high-speed machining, has unique advantages in continuous cutting, and is increasingly widely applied in intermittent machining. Cemented carbide is known as an important tool material, and has excellent properties such as high strength, high wear resistance, high corrosiveness, high hardness and the like, and plays an important role in cutting tools, mining tools and petroleum exploitation tools.
The ceramic cutter obtained at present has the problems of low toughness, low overall strength and the like, is easy to break suddenly in high-speed cutting, has poor stability and is difficult to apply to high-efficiency high-quality precision machining. The hard alloy material with the brand of YG8 is a tungsten-cobalt material, has very high toughness and wear resistance, is hopeful to use the hard alloy as a matrix of a cutter, and uses SiAlON ceramic as a cutter angle of the cutter to participate in cutting, so that the composite blade with improved overall strength, toughness and wear resistance is manufactured.
Disclosure of Invention
In order to solve the defects and shortcomings of the prior art, the primary aim of the invention is to provide a preparation method of a SiAlON-YG8 composite welding blade, wherein YG8 hard alloy is used as a matrix, and SiAlON ceramic is used as a cutting angle; the welding blade has high overall strength and toughness, and the welding strength of the contact surface of the SiAlON blade angle and the YG8 hard alloy is high; and applying pressure to four corners of the sintered cutter sample by using a special welding flux and a special fixing die at high temperature to enable the welding flux which is uniformly coated on the contact surface in advance to melt and flow, filling the whole contact surface, and then cooling by a certain temperature gradient to enable the welding flux to be slowly solidified so as to achieve the aim of connecting SiAlON and hard alloy. At the same time of solder flow at high temperature, forming on the contact surface of SiAlON and solderWith TiN and Ti 5 Si 3 The strength of the connecting layer is obviously increased by the Ti concentrated layer which is mainly used.
Another object of the present invention is to provide a SiAlON-YG8 composite welding insert manufactured by the above method.
It is still another object of the present invention to provide an application of the SiAlON-YG8 composite welding insert.
The aim of the invention is achieved by the following technical scheme:
a preparation method of a SiAlON-YG8 composite welding blade comprises the following specific steps:
s1, si is mixed with 3 N 4 、Al 2 O 3 AlN, tiN and sintering aid Re 2 O 3 Mixing, si on a roller ball mill 3 N 4 The balls are grinding balls, absolute ethyl alcohol is used as a grinding medium, and mixed powder is obtained after mixing, drying and sieving; with Si 3 N 4 、Al 2 O 3 The total mass of AlN and TiN powder is 100%, and the Si 3 N 4 、Al 2 O 3 And 70-95% of AlN powder, and 5-30% of TiN powder; the Re (Re) 2 O 3 Is of the mass of Si 3 N 4 、Al 2 O 3 1 to 5 percent of the total mass of the AlN and TiN mixed powder;
s2, dry-pressing the mixed powder obtained in the step S1 into blocks, and maintaining the pressure for 250-300S under 200-250 MPa of cold isostatic pressing to obtain a blank; SPS sintering or hot-pressing sintering the blank at 1450-1650 ℃ to obtain a SiAlON presintered block;
s3, processing the hard alloy plate of the YG8 into a cuboid through laser processing, and cutting off four cutter corners of the cuboid to prepare a YG8 matrix with unfilled corners; the SiAlON pre-sintered body is manufactured into a triangular prism SiAlON knife angle with the bottom edge of an isosceles right triangle, and the triangular prism SiAlON knife angle is consistent with the shape of the four knife angles cut out by the YG8 hard alloy plate;
s4, replacing the SiAlON cutter corners with the cut four cutter corners, coating brazing material on the bottom surface of the SiAlON cutter corners of the triangular prism, and connecting the triangular prism with the YG8 matrix with unfilled corners to obtain a prefabricated cutter body; and (3) applying pressure of 10-20 Pa from four cutter angle directions of the prefabricated cutter body by using a die, fixing the prefabricated cutter body, placing the fixed prefabricated cutter body in a brazing furnace, sintering at 800-900 ℃ to obtain a cutter blank, and grinding to remove the machining allowance of the cutter blank to obtain the SiAlON-YG8 composite welding blade.
Preferably, si is as described in step S1 3 N 4 The purity of (3) is 95-100%, and the grain diameter is<5 μm; the Al is 2 O 3 The purity of (3) is 95-100%, and the grain diameter is<5 μm; the AlN has a purity of 98-100% and a particle diameter<5 μm; the purity of the TiN is 98-100%, and the grain diameter is<100nm; the Re (Re) 2 O 3 The purity of (2) is 99.999%; the Re (Re) 2 O 3 The element Re in (B) is Y, la, gd or Yb.
Preferably, the rotating speed of the mixed material in the step S1 is 90-150 r/min, and the time of the mixed material is 18-36 h; the drying temperature is 60-80 ℃, and the drying time is 12-24 h.
Preferably, the specific procedure of spark plasma sintering in step S2 is as follows: heating to 1000-1200 ℃ at a speed of 130-150 ℃/min, starting to charge nitrogen and starting to apply pressure from 0, continuously heating to 1450-1650 ℃ and simultaneously heating to 30-40 MPa; preserving heat and pressure for 3-7 min after the temperature-raising program is executed; then cooling at the speed of 80-100 ℃/min, decompressing at 1000-1200 ℃, cooling to 750-850 ℃ and then cooling with a furnace.
Preferably, the hot press sintering specific procedure in step S2 is as follows: nitrogen is filled from the temperature rise to 800-1000 ℃ at the speed of 10-14 ℃/min, pressure is applied from 0, the temperature rise is continued at the speed of 6-8 ℃/min, the temperature rise is carried out to 1450-1650 ℃, and the pressure is simultaneously raised to 30-40 MPa; preserving heat and pressure for 3-7 min after the temperature-raising program is executed; then cooling at a cooling rate of 10-12 ℃/min, decompressing at 1000-1200 ℃ and cooling with a furnace after the temperature is reduced to 750-850 ℃.
Preferably, the specific procedure of sintering in step S4 to brazing furnace sintering is as follows: vacuumizing the furnace body, heating to 800-900 ℃ at the speed of 6-15 ℃/min, and preserving heat for 2-3 h; then cooling at the speed of 3-6 ℃/min, and cooling along with the furnace after the temperature is reduced to 350-450 ℃.
Preferably, in the step S4, the brazing material is a paste mixture rich in Ag, cu and Ti, and the mass fraction of Ag in the brazing material is 60-70%, the mass fraction of Cu is 20-25%, and the mass fraction of Ti is 5-10% based on 100% of the total mass of the three elements.
A SiAlON-YG8 composite welding blade is prepared by the method.
Preferably, the shear strength of the welding layer in the composite welding blade is 180-185 MPa, the relative density is more than 98%, the surface hardness is 18-24 GPa, and the fracture toughness is 5-8 MPa m 1/2 The thermal conductivity is 80-92W/(m.K); the core hardness is 14-18 GPa, and the fracture toughness is 8-12 MPa.m 1/2 The thermal conductivity is 87-103W/(m.K).
The SiAlON-YG8 composite welding blade is applied to the preparation of the processing bearing of the aerospace wear-resistant part and the difficult-to-process material.
In the vacuum high-temperature environment of the brazing furnace, the active element Ti in the brazing material gradually diffuses and migrates to one side of the SiAlON knife angle along with the flow of the brazing material, and reacts with the N element and the Si element in the SiAlON knife angle to generate TiN and Ti 5 Si 3 . The grains of the two elements are mutually staggered and stacked, and a reaction layer (Ti concentrated layer) with the thickness of 1-5 micrometers is formed on one side of the SiAlON knife angle. During sintering, the brazing material is melted by high temperature and flows between the SiAlON cutter angle and the contact surface of the unfilled YG8 matrix; the die is fixed to contact and connect the SiAlON cutter angle and the YG8 matrix of the unfilled corner, and the prepared prefabricated cutter body applies certain pressure, so that the melted brazing material can cover the contact surface more uniformly. After the brazing material flows fully, the temperature gradually decreases to solidify the brazing material, so that the purpose of welding the SiAlON cutter angle and the unfilled YG8 matrix is achieved.
Compared with the prior art, the invention has the following beneficial effects:
1. compared with the traditional SiAlON ceramic blade and YG8 hard alloy blade, the SiAlON-YG8 composite welding blade prepared by the invention has the advantages that the overall strength, toughness and heat conductivity can be improved by about 20 percent.
2. The SiAlON-YG8 composite welding blade prepared by the invention is formed by TiN and Ti 5 Si 3 The main Ti concentrated layer is positioned on one side of the SiAlON knife angle in the whole welding layer, and the SiAlON knife angle is the first failure in the shear strength test.
Drawings
Fig. 1 is a schematic structure diagram of SiAlON cutting angle in SiAlON-YG8 composite welding blade of the present invention.
Fig. 2 is a schematic structural view of the unfilled corner YG8 cemented carbide substrate of the present invention.
Fig. 3 is an SEM image of the SiAlON-YG8 composite soldering blade soldering layer prepared in example 1.
Fig. 4 is a physical view of a stationary mold used in the present invention.
FIG. 5 is a physical diagram of a SiAlON-YG8 soldering blade in example 1-2 of the present invention.
Detailed Description
The present invention is further illustrated below in conjunction with specific examples, but should not be construed as limiting the invention. The technical means used in the examples are conventional means well known to those skilled in the art unless otherwise indicated. Unless specifically stated otherwise, the reagents, methods and apparatus employed in the present invention are those conventional in the art.
In the following examples, the weld layer elemental distribution and phase composition of the weld blade may be characterized by scanning electron microscopy and its performance by vickers hardness tester or the like.
Example 1
A preparation method of a SiAlON-YG8 composite welding blade comprises the following specific steps:
(1) With Si 3 N 4 、Al 2 O 3 AlN and TiN powder as material and rare earth oxide Gd 2 O 3 As sintering aid, si 3 N 4 The balls are grinding balls, absolute ethyl alcohol is used as a grinding medium, and mixed powder is obtained after mixing, drying and sieving; with Si 3 N 4 、Al 2 O 3 The total mass of AlN and TiN powder is 100%, si 3 N 4 、Al 2 O 3 The AlN powder has a mass percentage of 80% (83.07% Si) 3 N 4 、4.854％AlN、12.075％Al 2 O 3 ) The mass percentage of TiN powder is 20%; gd (Gd) 2 O 3 Is of the mass of Si 3 N 4 、Al 2 O 3 4% of total mass of AlN and TiN mixed powder;
the method comprises the steps of (1) processing a hard alloy plate with the brand number of YG8 into a cuboid with the size of 13.6mm multiplied by 5.76mm by laser processing by taking the hard alloy plate as a raw material, cutting off four corners of a cuboid blank, and obtaining a YG8 matrix with unfilled corners, wherein the shape of a cutter corner is a triangular prism with an isosceles right triangle with the size of 4mm multiplied by 4mm as a bottom surface;
(2) Dry-pressing the mixed powder obtained in the step (1) into a block body with the diameter of 18.2mm multiplied by 7mm by a stainless steel die, and then maintaining the pressure for 300s under the pressure of 250MPa of cold isostatic pressing to obtain a blank body to be sintered; and then sintering by using an SPS sintering furnace or a hot-pressing sintering furnace, wherein the specific process flow of sintering is to start charging nitrogen and pressurizing when the temperature rises to 1000 ℃ at the heating rate of 100 ℃/min, to heat up to 1550 ℃ and simultaneously to heat up to 40MPa, to keep the temperature and the pressure for 4min, to cool at the cooling rate of 100 ℃/min after the heat preservation is finished, to cool down to 1300 ℃ after the pressure relief is finished, and to cool down with the furnace after the temperature is reduced to 800 ℃ to obtain the SiAlON presintered block.
(3) The obtained SiAlON pre-sintered block was cut by laser to prepare a triangular prism having an isosceles right triangle of 4mm×4mm as a bottom surface, and used as a knife angle. The method comprises the steps of preparing a prefabricated cutter body by uniformly coating a special brazing material (a paste mixture rich in Ag, cu and Ti, wherein the mass fraction of Ag in the brazing material is 60-70%, the mass fraction of Cu is 20-25%, and the mass fraction of Ti is 5-10%) on a connecting surface of a prefabricated SiAlON cutter angle in contact with a YG8 matrix with a unfilled corner through screen printing, replacing the cut four cutter angles by the prefabricated SiAlON cutter angle in accordance with the shape of the four cutter angles cut out by a hard alloy plate of the YG8, preparing the prefabricated cutter body, then using a special fixing die (shown in figure 4, the special fixing die is divided into a sample disc and a clamping block, the sample disc is circular, four grooves are distributed on the circumference of a concentric circle smaller than the diameter of the sample disc at equal intervals, the four clamping blocks can be fixed through screws, and the positions of the clamping block in the radial direction can be adjusted according to the size of the sample, one end of the clamping block is in a right angle shape so as to adapt to the right angle shape of the cutter, and the prefabricated cutter body is prevented from falling off from the unfilled corner of the cutter body to the prefabricated cutter body and the cutter body is prevented from being fixed on the YG 8. And (3) placing the fixed prefabricated cutter body into a brazing furnace for high-temperature sintering, heating to 850 ℃ at a speed of 10 ℃/min in a vacuum environment, then preserving heat for 2.5 hours at 850 ℃, cooling to 400 ℃ at a speed of 5 ℃/min after the heat preservation is finished, and cooling along with the furnace to obtain a blank body of the composite welding blade. And then removing the reserved machining allowance by grinding to obtain the SiAlON-YG8 composite welding blade (shown in figure 5).
Fig. 3 is an SEM image of a soldering layer in the SiAlON-YG8 composite soldering blade manufactured in this example. As can be seen from fig. 3, the Ti concentrated layer is formed on the side of the SiAlON corner, has a thickness of 1.5 μm, is tightly adhered to the SiAlON corner, and does not see the defects of cracks and voids. The shear strength of the welding layer in the SiAlON-YG8 composite welding blade prepared in the embodiment reaches 180MPa, the relative density is 99.9%, the surface hardness is 19GPa, and the fracture toughness is 6 MPa.m 1/2 The thermal conductivity is 85W/(m.K); the core hardness was 16GPa, and the fracture toughness was 9 MPa.m 1/2 The thermal conductivity was 88W/(m.K).
Example 2
(1) With Si 3 N 4 、Al 2 O 3 AlN and TiN powder as material and RE oxide Y as material 2 O 3 As sintering aid, si 3 N 4 The balls are grinding balls, absolute ethyl alcohol is used as a grinding medium, and mixed powder is obtained after mixing, drying and sieving; with Si 3 N 4 、Al 2 O 3 The total mass of AlN and TiN powder is 100%, si 3 N 4 、Al 2 O 3 The AlN powder has a mass percentage of 90% (90.56% Si) 3 N 4 、3.42％AlN、6.02％Al 2 O 3 ) TiN powderThe mass percentage is 10%; y is Y 2 O 3 Is of the mass of Si 3 N 4 、Al 2 O 3 5% of total mass of AlN and TiN mixed powder;
the YG8 substrate with unfilled corners is prepared by using YG8 hard alloy plates with the brand number as raw materials, processing the YG8 hard alloy plates into cuboid with the size of 13.6mm multiplied by 5.76mm through laser processing, cutting off four cutter corners of a cuboid blank, wherein the cutter corners are triangular prisms with isosceles right triangles with the size of 4mm multiplied by 4mm as bottom surfaces;
(2) Dry-pressing the mixed powder obtained in the step (1) into a block body with the diameter of 18.2mm multiplied by 7mm by a stainless steel die, and then maintaining the pressure for 300s under the pressure of 250MPa of cold isostatic pressing to obtain a blank body to be sintered; then sintering by using an SPS sintering furnace or a hot-pressing sintering furnace, heating to 1000 ℃ at the speed of 100 ℃/min, starting to charge nitrogen and starting to pressurize, heating to 1550 ℃ and simultaneously heating to 40MPa, preserving heat and maintaining pressure for 4min, cooling at the speed of 100 ℃/min after the heat preservation is finished, cooling along with the furnace at the temperature of 800 ℃ after the pressure relief is finished at the speed of 1300 ℃, and obtaining the SiAlON presintered block.
(3) The structure of the SiAlON knife angle of the present invention is shown in fig. 1. The pre-sintered SiAlON block is cut by laser to prepare a triangular prism with an isosceles right triangle of 4mm multiplied by 4mm as a bottom surface, and the triangular prism is used as a SiAlON knife angle. Fig. 2 is a schematic structural diagram of the YG8 cemented carbide substrate of the present invention. And (3) uniformly coating a special brazing material (paste mixture rich in Ag, cu and Ti, wherein the total mass of the three elements is 100 percent, the mass fraction of Ag in the brazing material is 60-70 percent, the mass fraction of Cu is 20-25 percent, and the mass fraction of Ti is 5-10 percent) on a connecting surface of the manufactured SiAlON cutter angle and the YG8 matrix with unfilled corners through screen printing, enabling the prefabricated SiAlON cutter angle to be consistent with the cut four cutter angles of the YG8 hard alloy matrix, replacing the cut four cutter angles, preparing a prefabricated cutter body, brushing the brazing material, applying 20Pa pressure to the prefabricated cutter body from the direction of the four cutter angles of the prefabricated cutter body by using a special fixing die (shown in figure 4), and fixing the prefabricated cutter body, so as to prevent the prefabricated cutter angle from falling off from the YG8 matrix with the unfilled corners. And (3) placing the prefabricated cutter body fixed by the fixed die into a brazing furnace for high-temperature sintering, heating to 850 ℃ at the speed of 10 ℃/min under a vacuum environment, then preserving heat for 2.5 hours at 850 ℃, cooling with the furnace after the heat preservation is finished and reducing to 400 ℃ at the speed of 5 ℃/min, obtaining a blank of the composite welding blade, and removing machining allowance by a grinding mode to obtain the SiAlON-YG8 composite welding blade (shown in figure 5).
The shear strength of the welding layer in the SiAlON-YG8 composite welding blade prepared by the embodiment reaches 185MPa, the relative density is 99.9%, the surface hardness is 20GPa, and the fracture toughness is 7.2 MPa.m 1/2 Thermal conductivity 90W/(m.k); the core hardness was 19GPa and the fracture toughness was 10 MPa.m 1/2 The thermal conductivity is 100W/(m.K).
The shear strength of the welding layer in the SiAlON-YG8 composite welding blade is 180-185 MPa, the relative density is more than 98%, the surface hardness is 18-24 GPa, and the fracture toughness is 5-8 MPa.m 1/2 The thermal conductivity is 80-92W/(m.K); the core hardness is 14-18 GPa, and the fracture toughness is 8-12 MPa.m 1/2 The thermal conductivity is 87-103W/(m.K). The SiAlON-YG8 composite welding blade is applied to the preparation of a machining bearing for machining materials difficult to machine and aerospace wear-resistant parts.
The above examples are preferred embodiments of the present invention, but the embodiments of the present invention are not limited to the above examples, and any other changes, modifications, substitutions, combinations and simplifications that do not depart from the spirit and principle of the present invention should be made in the equivalent manner, and the embodiments are included in the protection scope of the present invention.
Claims (10)
1. The preparation method of the SiAlON-YG8 composite welding blade is characterized by comprising the following specific steps of:
s1. Si is mixed with 3 N 4 、Al 2 O 3 AlN, tiN and sintering aid Re 2 O 3 Mixing, si on a roller ball mill 3 N 4 The balls are grinding balls, absolute ethyl alcohol is used as a grinding medium, and mixed powder is obtained after mixing, drying and sieving; with Si 3 N 4 、Al 2 O 3 The total mass of AlN and TiN powder is 100%, and the Si 3 N 4 、Al 2 O 3 The total mass percentage of the AlN powder is 70-95%, and the mass percentage of the TiN powder is 5-30%; the Re (Re) 2 O 3 Is of the mass of Si 3 N 4 、Al 2 O 3 1-5% of the total mass of AlN and TiN mixed powder;
s2, dry-pressing the mixed powder obtained in the step S1 into a block, and maintaining the pressure for 250-300S under 200-250 MPa of cold isostatic pressing to obtain a blank; sintering the blank body at 1450-1650 ℃ through spark plasma sintering or hot-pressing sintering to obtain a SiAlON presintered block;
s3, processing the hard alloy plate of the YG8 into a cuboid through laser processing, and cutting off four cutter corners of the cuboid to prepare a YG8 matrix with unfilled corners; the SiAlON pre-sintered body is manufactured into a triangular prism SiAlON knife angle with the bottom edge of an isosceles right triangle, and the triangular prism SiAlON knife angle is consistent with the shape of the four knife angles cut out by the YG8 hard alloy plate;
s4, replacing the SiAlON cutter angles with the cut four cutter angles, coating brazing material on the bottom surface of the SiAlON cutter angles of the triangular prism, and connecting the base body with the YG8 base body with the unfilled angle to obtain a prefabricated cutter body; and applying pressure of 10-20 Pa from four cutter angle directions of the prefabricated cutter body by using a die, fixing the prefabricated cutter body, placing the fixed prefabricated cutter body in a brazing furnace, sintering at 800-900 ℃ to obtain a cutter blank, and grinding to remove the machining allowance of the cutter blank to obtain the SiAlON-YG8 composite welding blade.
2. The method for manufacturing a SiAlON-YG8 composite soldering tip according to claim 1, wherein the Si in step S1 3 N 4 The purity of (2) is 95-100%, and the grain diameter is<5 μm; the Al is 2 O 3 The purity of (3) is 95-100%, and the particle size is<5 mu m; the AlN has a purity of 98-100% and a particle diameter<5 mu m; the purity of the TiN is 98-100%, and the grain diameter is<100nm; the Re (Re) 2 O 3 The purity of (2) is 99.999%; the Re (Re) 2 O 3 The element Re in (B) is Y, la, gd or Yb.
3. The preparation method of the SiAlON-YG8 composite welding blade according to claim 1, wherein the rotating speed of the mixed material in the step S1 is 90-150 r/min, and the mixing time is 18-36 h; the drying temperature is 60-80 ℃, and the drying time is 12-24 hours.
4. The method for manufacturing a SiAlON-YG8 composite welding insert according to claim 1, wherein the spark plasma sintering specific procedure in step S2 is as follows: heating to 1000-1200 ℃ at a speed of 130-150 ℃/min, starting to charge nitrogen, starting to apply pressure from 0, continuously heating to 1450-1650 ℃ and heating to 30-40 MPa; after the execution of the temperature raising program is finished, preserving heat and pressure for 3-7 min; and then cooling at a speed of 80-100 ℃/min, and cooling along with the furnace after the temperature is reduced to 750-850 ℃ after the pressure is relieved at 1000-1200 ℃.
5. The method for manufacturing a SiAlON-YG8 composite soldering tip according to claim 1, wherein the hot press sintering specific procedure in step S2 is as follows: heating to 800-1000 ℃ at a speed of 10-14 ℃/min, starting to charge nitrogen, starting to apply pressure from 0, continuously heating to 1450-1650 ℃ at a speed of 6-8 ℃/min, and simultaneously heating to 30-40 MPa; after the execution of the temperature raising program is finished, preserving heat and pressure for 3-7 min; and then cooling at a cooling rate of 10-12 ℃/min, and cooling along with the furnace after the temperature is reduced to 750-850 ℃ after the pressure relief at 1000-1200 ℃ is completed.
6. The method for manufacturing a SiAlON-YG8 composite soldering blade according to claim 1, wherein the specific procedure of sintering into brazing furnace sintering in step S4 is as follows: vacuumizing the furnace body, heating to 800-900 ℃ at a speed of 6-15 ℃/min, and preserving heat for 2-3 hours; and then cooling at a speed of 3-6 ℃/min, cooling to 350-450 ℃ and then cooling along with the furnace.
7. The preparation method of the SiAlON-YG8 composite welding blade according to claim 1, wherein in the step S4, the brazing material is a pasty mixture rich in Ag, cu and Ti, and the mass fraction of Ag in the brazing material is 60-70%, the mass fraction of Cu is 20-25% and the mass fraction of Ti is 5-10% based on 100% of the total mass of the three elements Ag, cu and Ti.
8. The SiAlON-YG8 composite welding blade is characterized in that the SiAlON-YG8 composite welding blade is prepared by the method of any one of claims 1-7.
9. The SiAlON-YG8 composite welding blade according to claim 8, wherein the shearing strength of the welding layer in the composite welding blade is 180-185 mpa, the relative density is greater than 98%, the surface hardness is 18-24 gpa, and the fracture toughness is 5-8 mpa-m 1/2 The thermal conductivity is 80-92W/(m.K); the core hardness is 14-18 GPa, and the fracture toughness is 8-12 MPa m 1/2 The thermal conductivity is 87-103W/(m.K).
10. The use of the SiAlON-YG8 composite welding insert of claim 9 in the manufacture of a machined bearing for cutting difficult-to-machine materials, aerospace wear resistant parts.
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