CN114799158A - 713C-AlN-TiC multilayer embedded composite material and preparation method thereof - Google Patents
713C-AlN-TiC multilayer embedded composite material and preparation method thereof Download PDFInfo
- Publication number
- CN114799158A CN114799158A CN202210293061.6A CN202210293061A CN114799158A CN 114799158 A CN114799158 A CN 114799158A CN 202210293061 A CN202210293061 A CN 202210293061A CN 114799158 A CN114799158 A CN 114799158A
- Authority
- CN
- China
- Prior art keywords
- aln
- tic
- powder
- layer
- composite material
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 41
- 238000002360 preparation method Methods 0.000 title abstract description 9
- 238000005245 sintering Methods 0.000 claims abstract description 32
- 239000002245 particle Substances 0.000 claims abstract description 31
- 238000005238 degreasing Methods 0.000 claims abstract description 21
- 239000000843 powder Substances 0.000 claims description 47
- 238000000034 method Methods 0.000 claims description 22
- 238000002347 injection Methods 0.000 claims description 19
- 239000007924 injection Substances 0.000 claims description 19
- 239000000463 material Substances 0.000 claims description 13
- 230000003197 catalytic effect Effects 0.000 claims description 9
- 239000000203 mixture Substances 0.000 claims description 9
- 239000011230 binding agent Substances 0.000 claims description 6
- 238000002156 mixing Methods 0.000 claims description 6
- 229920006324 polyoxymethylene Polymers 0.000 claims description 6
- 235000021355 Stearic acid Nutrition 0.000 claims description 5
- 239000000853 adhesive Substances 0.000 claims description 5
- 230000001070 adhesive effect Effects 0.000 claims description 5
- 210000001161 mammalian embryo Anatomy 0.000 claims description 5
- QIQXTHQIDYTFRH-UHFFFAOYSA-N octadecanoic acid Chemical compound CCCCCCCCCCCCCCCCCC(O)=O QIQXTHQIDYTFRH-UHFFFAOYSA-N 0.000 claims description 5
- OQCDKBAXFALNLD-UHFFFAOYSA-N octadecanoic acid Natural products CCCCCCCC(C)CCCCCCCCC(O)=O OQCDKBAXFALNLD-UHFFFAOYSA-N 0.000 claims description 5
- 229920002037 poly(vinyl butyral) polymer Polymers 0.000 claims description 5
- 239000008117 stearic acid Substances 0.000 claims description 5
- 239000002253 acid Substances 0.000 claims description 4
- 229910052804 chromium Inorganic materials 0.000 claims description 4
- 229910052750 molybdenum Inorganic materials 0.000 claims description 4
- 239000012188 paraffin wax Substances 0.000 claims description 4
- 229920000193 polymethacrylate Polymers 0.000 claims description 4
- 238000000465 moulding Methods 0.000 claims description 2
- 229930040373 Paraformaldehyde Natural products 0.000 claims 1
- -1 polyoxymethylene Polymers 0.000 claims 1
- 238000005728 strengthening Methods 0.000 abstract description 6
- 230000002349 favourable effect Effects 0.000 abstract description 4
- 239000011185 multilayer composite material Substances 0.000 abstract 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 8
- 238000012360 testing method Methods 0.000 description 6
- 239000000956 alloy Substances 0.000 description 5
- 229910045601 alloy Inorganic materials 0.000 description 5
- 230000000052 comparative effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 229910052759 nickel Inorganic materials 0.000 description 4
- 238000005336 cracking Methods 0.000 description 3
- 230000001965 increasing effect Effects 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000001746 injection moulding Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 239000008188 pellet Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 239000006104 solid solution Substances 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 238000009736 wetting Methods 0.000 description 2
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000013329 compounding Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000005469 granulation Methods 0.000 description 1
- 230000003179 granulation Effects 0.000 description 1
- 238000001192 hot extrusion Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000004881 precipitation hardening Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Images
Classifications
-
- 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
- B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
- B22F1/10—Metallic powder containing lubricating or binding agents; Metallic powder containing organic material
- B22F1/103—Metallic powder containing lubricating or binding agents; Metallic powder containing organic material containing an organic binding agent comprising a mixture of, or obtained by reaction of, two or more components other than a solvent or a lubricating agent
-
- 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
- B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
- B22F1/10—Metallic powder containing lubricating or binding agents; Metallic powder containing organic material
- B22F1/107—Metallic powder containing lubricating or binding agents; Metallic powder containing organic material containing organic material comprising solvents, e.g. for slip casting
-
- 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
- B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
- B22F1/12—Metallic powder containing non-metallic particles
-
- 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
- B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
- B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Ceramic Products (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a 713C-AlN-TiC multilayer embedded composite material and a preparation method thereof, belonging to the technical field of multilayer composite materials, wherein a circulating unit with a cross-sectional structure obtained by sequentially carrying out the steps of banburying, granulating, injecting, degreasing and sintering is as follows: the embedded laminated structure is favorable for relieving the expansion of microcracks, and improves the toughness, hardness and wear resistance of the composite material; and the fine AlN and TiC particles play a role in strengthening the second phase at the same time, so that the mechanical property of the composite material is improved.
Description
Technical Field
The invention relates to the technical field of multilayer alloy composite materials, in particular to a 713C-AlN-TiC multilayer embedded composite material and a preparation method thereof.
Background
713C is a nickel-based precipitation-hardening type equiaxed superalloy, which is generally used at temperatures below 900 ℃. The alloy has high creep strength, cold and hot fatigue resistance and oxidation resistance. The method is widely used for manufacturing aviation, ground and offshore gas turbine working blades, guide blades and cast turbines, cast turbine rotors and guides of engines for space missiles, supercharged turbines of diesel engines and gasoline engines and hot extrusion dies, but the base body of the method is low in hardness, poor in abrasion resistance, long-term friction and abrasion, and prone to causing material failure and fracture.
The Chinese patent with publication number CN113618060A discloses a nickel-based alloy powder, which is used for wrapping ceramic particles to solve the cracking tendency of the nickel-based alloy, but the method has the advantages of complex operation and higher cost, is only suitable for modifying the nickel-based alloy powder, and has smaller application range.
Disclosure of Invention
In order to overcome the defects of the prior art, the technical problems to be solved by the invention are as follows: how to provide a 713C material with a high degree of wear resistance and mechanical properties and a method for its preparation.
In order to solve the technical problems, the invention adopts the technical scheme that: A713C-AlN-TiC multilayer embedded composite material is characterized in that a circulating unit of a cross-sectional structure of the 713C-AlN-TiC multilayer embedded composite material is as follows: 713C-AlN-713C-TiC.
Wherein the thickness of the 713C layer is 1.8-2.2mm, and the thickness of the AlN layer and the thickness of the TiC layer are both 0.7-1.3 mm.
The other technical scheme adopted by the invention is as follows: a preparation method of the 713C-AlN-TiC multilayer embedded composite material comprises the following steps:
s1, banburying: respectively mixing 713C powder, AlN powder and TiC powder with an adhesive to obtain three mixtures, and banburying the three mixtures respectively;
s2, granulating: granulating the internally mixed materials to obtain three feeding particles;
s3, injection: sequentially injecting and molding the three types of feeding particles to obtain a circulating unit with a cross-sectional structure as follows: a 713C layer-AlN layer-713C layer-TiC layer multilayer embedded green body;
s4, degreasing: putting the multilayer embedded green body into a catalytic degreasing furnace for catalytic degreasing to obtain a brown blank;
s5, sintering: and sintering the brown blank to obtain the composite material.
Wherein the particle size of the 713C powder is D50:6-7 μm;
the 713C powder comprises, in mass percent, C: 0.08-0.16%, Cr: 11.5-13.5%, Mo: 3.8-4.8%, Al: 4.3-5.3%, Ti: 2.0-2.8%, Nb: 1.8-2.5%, B: 0.008-0.02, Zr: 0.06-0.15 percent, Mn <0.05 percent, Si <0.015 percent and P <0.015 percent.
The particle sizes of the AlN powder and the TiC powder are D50:2-3 μm, and the purities of the AlN powder and the TiC powder are both more than or equal to 99.99%.
Wherein the shrinkage feed ratio of the three feed particles is the same and is 1.18-1.19.
The adhesive is composed of polyformaldehyde, polymethacrylate, polyvinyl butyral, paraffin and stearic acid.
Wherein the mass ratio of the 713C powder, the AlN powder and the TiC powder to the binder is 80-85: 15-20.
Wherein, the sintering temperature is 1240-1320 ℃, and the sintering time is 170-190 min.
Wherein the acid removal rate of the defatted brown embryo is more than or equal to 7.7 percent.
The invention has the beneficial effects that: the circulation unit adopting the circulation multilayer embedded injection mode to obtain the cross-section structure is as follows: the embedded laminated structure is favorable for relieving the expansion of microcracks and improving the toughness, hardness and wear resistance of the composite material; and the fine AlN and TiC particles play a role in strengthening the second phase at the same time, so that the mechanical property of the composite material is improved.
Drawings
FIG. 1 is a schematic cross-sectional view of a 713C-AlN-TiC multilayer chimeric composite material in first to third embodiments of the present invention.
Description of reference numerals: 1. a first 713C layer; 2. an AlN layer; 3. a second 713C layer; 4. and a TiC layer.
Detailed Description
In order to explain technical contents, achieved objects, and effects of the present invention in detail, the following description is made with reference to the accompanying drawings in combination with the embodiments.
The most key concept of the invention is as follows: the circulation unit adopting the circulation multilayer embedded injection mode to obtain the cross-section structure is as follows: the embedded laminated structure is favorable for relieving the expansion of microcracks and improving the toughness, hardness and wear resistance of the composite material; and the fine AlN and TiC particles play a role in strengthening the second phase at the same time, so that the mechanical property of the composite material is improved.
Referring to fig. 1, the circulation unit of the cross-sectional structure of the 713C-AlN-TiC multilayer embedded composite material of the present invention is: 713C-AlN-713C-TiC.
From the above description, the beneficial effects of the present invention are:
the circulation unit of the cross-sectional structure is: the embedded laminated structure is beneficial to relieving the expansion of microcracks and improving the toughness, hardness and wear resistance of the composite material; the thermal expansion coefficients of 713C, AlN and TiC are different, so that the dislocation density is increased, the slippage of dislocation is hindered, and higher strength is provided for the material;
and fine AlN and TiC particles exist in a second phase, so that the plastic deformation of 713C can be inhibited, the hardness is improved, the tissues can be obviously refined by adding TiC and AlN, and the movement and the expansion of dislocation are hindered, so that the microhardness is improved, the second phase strengthening effect is realized, and the mechanical property of the composite material is improved.
Furthermore, the thickness of the 713C layer is 1.8-2.2mm, and the thickness of the AlN layer and the TiC layer are 0.7-1.3 mm.
From the above description, the thickness of the base material 713C layer is much greater than that of the AlN layer and the TiC layer, which is beneficial to enhancing the mechanical properties of the material, and simultaneously maintains the creep strength, the cold and hot fatigue resistance, and the oxidation resistance of the 713C layer.
A preparation method of a 713C-AlN-TiC multilayer embedded composite material comprises the following steps:
s1, banburying: mixing the 713C powder, the AlN powder and the TiC powder with an adhesive respectively to obtain three mixtures, and banburying the three mixtures respectively; the banburying temperature is 192-;
s2, granulating: granulating the internally mixed materials to obtain three feeding particles;
s3, injection: three kinds of feeding particlesThe pellets are sequentially injection molded, and the circulation unit for obtaining the section structure is as follows: a 713C layer-AlN layer-713C layer-TiC layer multilayer embedded green body; the injection temperature is 180 ℃ and 220 ℃, the injection pressure is 58-62MPa, and the injection speed is 9-11cm 3 The pressure maintaining time is 1.4-1.6 s;
s4, degreasing: putting the multilayer embedded green body into a catalytic degreasing furnace for catalytic degreasing to obtain a brown blank;
s5, sintering: and sintering the brown blank to obtain the composite material.
As can be seen from the above description, the circulation unit capable of obtaining the cross-sectional structure by the above-described circulation multilayer insert injection method is: the embedded laminated structure is favorable for relieving the expansion of microcracks and improving the toughness, hardness and wear resistance of the composite material; and the fine AlN and TiC particles play a role in strengthening the second phase at the same time, so that the mechanical property of the composite material is improved.
Further, the particle size of the 713C powder is D50:6-7 μm;
the 713C powder comprises, by mass percent, C: 0.08-0.16%, Cr: 11.5-13.5%, Mo: 3.8-4.8%, Al: 4.3-5.3%, Ti: 2.0-2.8%, Nb: 1.8-2.5%, B: 0.008-0.02, Zr: 0.06-0.15 percent, Mn <0.05 percent, Si <0.015 percent and P <0.015 percent.
From the above description, it can be seen that in the above composition, when 713C contains 4.3-5.3% Al and 2.0-2.8% Ti, it is advantageous to reduce the wetting angle with AlN and TiC during sintering, and to facilitate the tight bonding of the mosaic laminated structure.
Furthermore, the particle diameters of the AlN powder and the TiC powder are D50:2-3 μm, and the purities of the AlN powder and the TiC powder are both more than or equal to 99.99%.
From the above description, the fine AlN and TiC particles act as a second phase reinforcement to improve the mechanical properties of the composite material.
Further, the shrinkage feed ratios of the three feed pellets were the same and were all 1.18-1.19.
As can be seen from the above description, the shrinkage ratios of the three feeding particles are kept consistent, which is beneficial to reducing the problem of thermal stress concentration in the injection process; on the other hand, the consistent feeding shrinkage rate can improve the uniform and orderly opening of the degreasing channel in the green blank degreasing process, avoid the larger internal pressure of the product and reduce the deformation and cracking in the degreasing sintering process.
Further, the adhesive is composed of 85% of polyformaldehyde, 6% of polymethacrylate, 5% of polyvinyl butyral, 3% of paraffin and 1% of stearic acid in percentage by mass.
Furthermore, the mass ratio of the 713C powder, the AlN powder and the TiC powder to the binder is 80-85: 15-20.
Furthermore, the sintering temperature is 1240-1320 ℃, and the sintering time is 170-190 min.
As is apparent from the above description, the solid solution effect of Ti atoms increases microhardness by deforming a lattice structure, pinning dislocations, and hindering movement of dislocations during sintering, and particles precipitated after sintering (such as precipitated large TiC and AlN particles) strongly hinder movement of dislocations, and accordingly increase microhardness.
Further, the acid removal rate of the defatted brown embryo is more than or equal to 7.7 percent.
Referring to fig. 1, a first embodiment of the present invention is:
A713C-AlN-TiC multilayer embedded composite material has a cross-sectional structure from top to bottom as follows: 713C-AlN-713C-TiC.
The preparation method of the 713C-AlN-TiC multilayer embedded composite material comprises the following steps:
s1, powder preparation: the particle size of the 713C powder was: d50:6-7 μm, wherein the 713C powder comprises C: 0.08-0.16%, Cr: 11.5-13.5%, Mo: 3.8-4.8%, Al: 4.3-5.3%, Ti: 2.0-2.8%, Nb: 1.8-2.5%, B: 0.008-0.02, Zr: 0.06-0.15 percent, Mn is less than 0.05 percent, Si is less than 0.015 percent, and P is less than 0.015 percent; the particle size of AlN and TiN powder is as follows: d50 is 2-3 μm, and the purity is: 99.99 percent;
s2, banburying: mixing 713C powder, AlN powder and TiC powder with a binder (the binder consists of 85% of Polyformaldehyde (POM), 6% of Polymethacrylate (PMMA), 5% of polyvinyl butyral (PVB), 3% of Paraffin (PW) and 1% of Stearic Acid (SA) in percentage by mass) according to a mass ratio of 85:15 to obtain three mixtures, wherein the three feeding shrinkage ratios are guaranteed as follows: 1.185 of the total weight of the powder; putting the three mixtures into a preheated internal mixer respectively, and internally mixing for 30min at the internal mixing temperature of 195 ℃ and the screw rotation speed of 30 r/min;
s3, granulation: granulating the internally mixed materials to obtain three feeding particles;
s4, injection: sequentially putting the three feeding particles into a co-injection molding machine for injection molding, wherein the circulating unit of the obtained cross-section structure is as follows: a 713C layer-AlN layer-713C layer-TiC layer multilayer embedded green body;
wherein the thickness of the base 713C layer is 2mm, and the thickness of the AlN and TiC layers is 1 mm;
the injection parameters were: the injection temperature is 200 ℃, the injection pressure is 60MPa, and the injection speed is 10cm 3 The pressure maintaining time is 1.5 s;
s5, degreasing: putting the raw embryo into a catalytic degreasing furnace to remove polyformaldehyde, wherein the acid removal rate of the brown embryo after catalytic degreasing is more than 7.7%;
s6, sintering: sintering the brown blank subjected to catalytic degreasing at the sintering temperature of 1240 ℃ for 180min to obtain a composite material;
the sintering process comprises the following steps: increasing the sintering temperature from 50 ℃ to 600 ℃ at a heating rate of 3 ℃/min; raising the sintering temperature from 600 ℃ to 1240 ℃ at the temperature raising rate of 2 ℃/min; keeping the temperature at 1240 ℃ for 180 min; reducing the sintering temperature from 1240 ℃ to 1100 ℃ at the heating rate of 5 ℃/min; the temperature is kept at 1100 ℃ for 2h and nitrogen protection is introduced, and then the temperature is brought to room temperature at 5 ℃/min.
The difference between the second embodiment of the present invention and the first embodiment is: the sintering temperature was 1320 ℃.
The difference between the third embodiment of the present invention and the first embodiment is: the sintering temperature was 1280 ℃.
The fourth embodiment of the present invention is different from the first embodiment in that: A713C-AlN-TiC multilayer embedded composite material has a cross-sectional structure from top to bottom as follows: 713C layer-AlN layer-713C layer-TiC layer-713C layer-AlN layer-713C layer-TiC layer.
The comparative example one differs from the example one in that: the substrate was a single 713C material, and the thickness of the injected sample remained the same as in the example, and was 6 mm.
The comparative example two differs from the example one in that: the injection green body embedded structures are different, and the section structure of the comparative example II is as follows: 713C-TiC-AlN-713C, the circulating unit is 713C-TiC-AlN, wherein the base 713C layer is 2mm, and the AlN and TiC layers are 1 mm.
And (3) performance testing:
the heat-treated standard tensile member is tested on a universal testing universal tester according to GB/T228.1-2010 to test the tensile strength, the yield strength and the elongation;
the heat treated workpieces were subjected to a frictional wear test with reference to GBT12444-2006, where the inverse of the wear rate may be indicative of wear resistance, with smaller values giving higher wear resistance.
The mechanical properties (GB/T228.1-2010) and the wear resistance (test standard GBT12444-2006) of the first to third examples and the first and second comparative examples were measured, respectively, and the test results are shown in Table 1.
TABLE 1
As can be seen from the above table, compared with the first example, the toughness and hardness of the material are improved, especially the wear resistance is greatly improved, compared with the single 713C substrate after co-injection multilayer embedded compounding; comparing the comparative example with the example I, it can be known that the composite material with the embedded layer structure of 713C-TiC-AlN-713C has lower performance than the composite material with the structure of 713C-AlN-713C-TiC, and the embedded structure of AlN and TiC circularly and alternately embedded with the 713C material is most reasonable and effective.
In summary, the circulation unit of the cross-sectional structure obtained by banburying, granulating, injecting, degreasing and sintering the 713C powder, the AlN powder and the TiC powder is as follows: the embedded laminated structure is beneficial to relieving the expansion of microcracks and improving the toughness, hardness and wear resistance of the composite material; the thermal expansion coefficients of 713C, AlN and TiC are different, so that the dislocation density is increased, the slippage of dislocation is hindered, and higher strength is provided for the material;
the fine AlN and TiC particles exist in a second phase, so that the plastic deformation of 713C can be inhibited, the hardness is improved, the TiC and the AlN are added, meanwhile, the structure can be obviously refined, and the movement and the expansion of dislocation are hindered, so that the microhardness is improved, the second phase strengthening effect is realized, and the mechanical property of the composite material is improved;
during feeding, the feeding shrinkage ratios of the three feeding particles are kept consistent, so that the problem of thermal stress concentration in the injection process is reduced; on the other hand, the consistent feeding shrinkage rate can improve the uniform and orderly opening of the degreasing channel in the green blank degreasing process, avoid the larger internal pressure of the product and reduce the deformation and cracking in the degreasing sintering process.
In the sintering process, the 713C contains 4.3-5.3% of Al and 2.0-2.8% of Ti, which is beneficial to reducing wetting angles with AlN and TiC in the sintering process and is beneficial to the tight combination of a mosaic laminated structure; the solid solution effect of Ti atoms increases microhardness by deforming the lattice structure, pinning dislocations, and hindering dislocation movement, and the particles precipitated after sintering (e.g., large precipitated TiC particles) also strongly hinder dislocation movement and accordingly increase microhardness.
The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all equivalent changes made by using the contents of the present specification and the drawings, or applied directly or indirectly to the related technical fields, are included in the scope of the present invention.
Claims (10)
1. A713C-AlN-TiC multilayer embedded composite material is characterized in that a circulating unit of a cross-sectional structure of the 713C-AlN-TiC multilayer embedded composite material is as follows: 713C layer-AlN layer-713C layer-TiC layer.
2. The 713C-AlN-TiC multilayer chimeric composite of claim 1, wherein the thickness of the 713C layer is 1.8-2.2mm, and the thickness of both the AlN layer and the TiC layer is 0.7-1.3 mm.
3. A method for preparing a 713C-AlN-TiC multilayer chimeric composite material according to claim 1, comprising the steps of:
s1, banburying: respectively mixing 713C powder, AlN powder and TiC powder with an adhesive to obtain three mixtures, and banburying the three mixtures respectively;
s2, granulating: granulating the internally mixed materials to obtain three feeding particles;
s3, injection: sequentially injecting and molding the three types of feeding particles to obtain a circulating unit with a cross-sectional structure as follows: a 713C layer-AlN layer-713C layer-TiC layer multilayer embedded green body;
s4, degreasing: putting the multilayer embedded green body into a catalytic degreasing furnace for catalytic degreasing to obtain a brown blank;
s5, sintering: and sintering the brown blank to obtain the composite material.
4. The method of claim 3, wherein the 713C-AlN-TiC multilayer chimeric composite material has a particle size of D50:6-7 μm;
the 713C powder comprises, in mass percent, C: 0.08-0.16%, Cr: 11.5-13.5%, Mo: 3.8-4.8%, Al: 4.3-5.3%, Ti: 2.0-2.8%, Nb: 1.8-2.5%, B: 0.008-0.02, Zr: 0.06-0.15 percent, Mn <0.05 percent, Si <0.015 percent and P <0.015 percent.
5. The method of claim 3, wherein the particle size of the AlN powder and the TiC powder is D50:2-3 μm, and the purities of the AlN powder and the TiC powder are both greater than or equal to 99.99%.
6. The method for preparing 713C-AlN-TiC multilayer chimeric composite material of claim 3, wherein the feeding shrinkage ratios of the three feeding particles are the same and all are 1.18-1.19.
7. The method of claim 3, wherein the binder is selected from the group consisting of polyoxymethylene, polymethacrylate, polyvinylbutyral, paraffin wax, and stearic acid.
8. The method of claim 3, wherein the mass ratio of the 713C powder, the AlN powder and the TiC powder to the binder is 80-85: 15-20.
9. The method for preparing 713C-AlN-TiC multilayer mosaic composite material as claimed in claim 3, characterized in that, during sintering, the sintering temperature is 1240-1320 ℃, and the sintering time is 170-190 min.
10. The method for preparing 713C-AlN-TiC multilayer chimeric composite material of claim 3, wherein the acid removal rate of the defatted brown embryo is greater than or equal to 7.7%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210293061.6A CN114799158B (en) | 2022-03-23 | 2022-03-23 | 713C-AlN-TiC multilayer embedded composite material and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210293061.6A CN114799158B (en) | 2022-03-23 | 2022-03-23 | 713C-AlN-TiC multilayer embedded composite material and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114799158A true CN114799158A (en) | 2022-07-29 |
| CN114799158B CN114799158B (en) | 2023-07-18 |
Family
ID=82531749
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210293061.6A Active CN114799158B (en) | 2022-03-23 | 2022-03-23 | 713C-AlN-TiC multilayer embedded composite material and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114799158B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4818635A (en) * | 1984-04-06 | 1989-04-04 | Santrade Ltd. | Nitride-based ceramic material |
| KR101659700B1 (en) * | 2015-12-24 | 2016-09-23 | 영남대학교 산학협력단 | A novel method for the production of aluminum nitride and aluminum nitride-based composite substances |
| CN107074665A (en) * | 2014-10-23 | 2017-08-18 | 住友电气工业株式会社 | Sintered body |
| CN108380889A (en) * | 2018-03-12 | 2018-08-10 | 淮海工学院 | TiC/316L composite material and preparation methods |
| EP3372329A1 (en) * | 2017-03-06 | 2018-09-12 | Seiko Epson Corporation | Compound for metal powder injection molding, metal powder molded body, method for producing sintered body, and sintered body |
| US20180297901A1 (en) * | 2015-10-05 | 2018-10-18 | Safran Aircraft Engines | Process for manufacturing a ceramic composite material part by pressurized injection of a loaded slurry into a porous mould |
| JP6526889B1 (en) * | 2018-08-01 | 2019-06-05 | Ｊｘ金属株式会社 | Laminate of ceramic layer and sintered body of copper powder paste |
| CN112961998A (en) * | 2020-12-27 | 2021-06-15 | 湖南英捷高科技有限责任公司 | Powder metallurgy preparation method for step-by-step forming cemented carbide hard alloy/steel double-layer structure composite material |
| CN113319284A (en) * | 2021-05-31 | 2021-08-31 | 中南大学 | Preparation method of co-injection multilayer structure part |
| CN113732292A (en) * | 2020-05-28 | 2021-12-03 | 华为机器有限公司 | Composite material, preparation method thereof, rotating mechanism and electronic equipment |
-
2022
- 2022-03-23 CN CN202210293061.6A patent/CN114799158B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4818635A (en) * | 1984-04-06 | 1989-04-04 | Santrade Ltd. | Nitride-based ceramic material |
| CN107074665A (en) * | 2014-10-23 | 2017-08-18 | 住友电气工业株式会社 | Sintered body |
| US20180297901A1 (en) * | 2015-10-05 | 2018-10-18 | Safran Aircraft Engines | Process for manufacturing a ceramic composite material part by pressurized injection of a loaded slurry into a porous mould |
| KR101659700B1 (en) * | 2015-12-24 | 2016-09-23 | 영남대학교 산학협력단 | A novel method for the production of aluminum nitride and aluminum nitride-based composite substances |
| EP3372329A1 (en) * | 2017-03-06 | 2018-09-12 | Seiko Epson Corporation | Compound for metal powder injection molding, metal powder molded body, method for producing sintered body, and sintered body |
| CN108380889A (en) * | 2018-03-12 | 2018-08-10 | 淮海工学院 | TiC/316L composite material and preparation methods |
| JP6526889B1 (en) * | 2018-08-01 | 2019-06-05 | Ｊｘ金属株式会社 | Laminate of ceramic layer and sintered body of copper powder paste |
| CN113732292A (en) * | 2020-05-28 | 2021-12-03 | 华为机器有限公司 | Composite material, preparation method thereof, rotating mechanism and electronic equipment |
| CN112961998A (en) * | 2020-12-27 | 2021-06-15 | 湖南英捷高科技有限责任公司 | Powder metallurgy preparation method for step-by-step forming cemented carbide hard alloy/steel double-layer structure composite material |
| CN113319284A (en) * | 2021-05-31 | 2021-08-31 | 中南大学 | Preparation method of co-injection multilayer structure part |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114799158B (en) | 2023-07-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109811165B (en) | Method for regulating interface structure of Ti/beta-titanium alloy layered composite material | |
| CN101618617B (en) | Metal/ceramic three-layer composite material and preparation method thereof | |
| JPS63501883A (en) | Aluminum-lithium alloy and method of manufacturing the same | |
| CN108315598A (en) | A kind of preparation method of IN713C nickel base superalloys | |
| CN114086017A (en) | Preparation method of SiCp/Al silicon carbide particle reinforced aluminum matrix composite | |
| CN110093524B (en) | Alterant for high-silicon aluminum alloy and use method thereof | |
| CN114150238A (en) | Ti-Al-Nb-based composite material and preparation method thereof | |
| US5066626A (en) | Ceramic materials for use in insert-casting and processes for producing the same | |
| CN109513930B (en) | High-strength turbocharger nozzle ring blade and preparation method thereof | |
| CN113025844B (en) | High-temperature titanium alloy and preparation method thereof | |
| CN114799158A (en) | 713C-AlN-TiC multilayer embedded composite material and preparation method thereof | |
| US5705280A (en) | Composite materials and methods of manufacture and use | |
| CN113560604A (en) | Selective laser melting nickel-based gradient nanocomposite material, and preparation method and application thereof | |
| CN101457317B (en) | Turbo material of AlTi basal body pressure booster and preparation method thereof | |
| CN114934211B (en) | Nickel-base superalloy, nickel-base superalloy powder, and nickel-base superalloy component | |
| CN111114044A (en) | Medium-temperature high-strength aluminum alloy plate and preparation method thereof | |
| CN109536781A (en) | A kind of high-purity is low to be mingled with Ni-base P/M Superalloy and its preparation method and application | |
| CN112522530B (en) | High-strength Ti-ZrO2-B4Preparation method of C-system composite material | |
| CN105821232B (en) | One kind is by adding nanometer Y2O3The method for improving Ti 48Al 2Cr 2Nb Alloy At Room Temperature tensile properties | |
| CN114368969A (en) | TiSi2Gd-doped2Zr2O7Ceramic material, preparation method and thermal barrier coating | |
| CN112941397A (en) | Light medium-entropy alloy with excellent high-temperature mechanical properties and processing technology thereof | |
| CN112756610B (en) | Turbine blade for high-performance gasoline engine and preparation method thereof | |
| Zhang et al. | Study on Mechanical and Thermal Expansion Properties of Oxide Coated Magnesium Borate Whiskers Reinforced Aluminum-based Composite | |
| CN114082985B (en) | Sc/Zr modified high-modulus high-strength aluminum-lithium alloy and laser forming method thereof | |
| US20230193432A1 (en) | Aluminum alloy workpiece and preparation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |