CN112877559A - Multi-component ultrahigh-entropy light-weight refractory composite material - Google Patents
Multi-component ultrahigh-entropy light-weight refractory composite material Download PDFInfo
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- 239000002131 composite material Substances 0.000 title claims abstract description 47
- 239000000843 powder Substances 0.000 claims abstract description 24
- 238000005245 sintering Methods 0.000 claims abstract description 18
- 230000003647 oxidation Effects 0.000 claims abstract description 17
- 238000007254 oxidation reaction Methods 0.000 claims abstract description 17
- 229910052581 Si3N4 Inorganic materials 0.000 claims abstract description 14
- 229910033181 TiB2 Inorganic materials 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 12
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 11
- 229910052758 niobium Inorganic materials 0.000 claims abstract description 11
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 11
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 11
- QYEXBYZXHDUPRC-UHFFFAOYSA-N B#[Ti]#B Chemical compound B#[Ti]#B QYEXBYZXHDUPRC-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 7
- 229910020968 MoSi2 Inorganic materials 0.000 claims abstract description 6
- ZKATWMILCYLAPD-UHFFFAOYSA-N niobium pentoxide Chemical compound O=[Nb](=O)O[Nb](=O)=O ZKATWMILCYLAPD-UHFFFAOYSA-N 0.000 claims abstract description 5
- 238000000498 ball milling Methods 0.000 claims description 14
- 239000002994 raw material Substances 0.000 claims description 12
- 229910034327 TiC Inorganic materials 0.000 claims description 11
- 238000002360 preparation method Methods 0.000 claims description 7
- 230000001681 protective effect Effects 0.000 claims description 6
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical group CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 5
- 230000001590 oxidative effect Effects 0.000 claims description 5
- 238000004321 preservation Methods 0.000 claims description 5
- 229910003925 SiC 1 Inorganic materials 0.000 claims description 2
- 238000007731 hot pressing Methods 0.000 claims description 2
- 229910003465 moissanite Inorganic materials 0.000 claims description 2
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 2
- 239000000126 substance Substances 0.000 claims description 2
- 238000001291 vacuum drying Methods 0.000 claims description 2
- 238000005303 weighing Methods 0.000 claims description 2
- 239000011159 matrix material Substances 0.000 abstract description 8
- 238000002156 mixing Methods 0.000 abstract description 4
- 238000004377 microelectronic Methods 0.000 abstract description 3
- 229910052796 boron Inorganic materials 0.000 abstract description 2
- 229910052799 carbon Inorganic materials 0.000 abstract description 2
- 239000000919 ceramic Substances 0.000 abstract description 2
- 229910001234 light alloy Inorganic materials 0.000 abstract description 2
- 238000000465 moulding Methods 0.000 abstract description 2
- 229910052757 nitrogen Inorganic materials 0.000 abstract description 2
- 229910052760 oxygen Inorganic materials 0.000 abstract description 2
- 229910052681 coesite Inorganic materials 0.000 abstract 1
- 229910052906 cristobalite Inorganic materials 0.000 abstract 1
- 239000000377 silicon dioxide Substances 0.000 abstract 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 abstract 1
- 229910052682 stishovite Inorganic materials 0.000 abstract 1
- 229910052905 tridymite Inorganic materials 0.000 abstract 1
- 239000000463 material Substances 0.000 description 22
- 239000010936 titanium Substances 0.000 description 14
- 239000007789 gas Substances 0.000 description 7
- 238000002679 ablation Methods 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 3
- 239000000956 alloy Substances 0.000 description 3
- 238000001035 drying Methods 0.000 description 3
- 238000000713 high-energy ball milling Methods 0.000 description 3
- 239000011812 mixed powder Substances 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 239000011153 ceramic matrix composite Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 229910000765 intermetallic Inorganic materials 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000003870 refractory metal Substances 0.000 description 2
- 239000012720 thermal barrier coating Substances 0.000 description 2
- 229910018575 Al—Ti Inorganic materials 0.000 description 1
- 229910016006 MoSi Inorganic materials 0.000 description 1
- 229910010038 TiAl Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004100 electronic packaging Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 239000005022 packaging material Substances 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
Classifications
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
-
- 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
- B22F3/24—After-treatment of workpieces or articles
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/04—Making non-ferrous alloys by powder metallurgy
- C22C1/05—Mixtures of metal powder with non-metallic powder
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C27/00—Alloys based on rhenium or a refractory metal not mentioned in groups C22C14/00 or C22C16/00
- C22C27/04—Alloys based on tungsten or molybdenum
-
- 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
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
-
- 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
Abstract
The invention provides a multi-component ultrahigh-entropy light-weight refractory composite material, which takes four light alloy elements of Mo, Ti, Al and Nb as a matrix, and introduces nonmetallic elements of Si, C, N, B and O into the matrix, so that the composite material has TiC and TiB2、SiC、Si3N4、BC、MoSi2、Nb2O5、SiO2The high-temperature strength and the oxidation resistance of a matrix are effectively improved by the multiphase ceramics, so that the low-density, high-temperature, high-toughness and long-time oxidation resistance of the matrix are realized, the composite material is prepared by powder mixing, molding, sintering and pre-oxidation, and the oxidation resistance time of the composite material in an air environment at 800-1500 ℃ is 100-300 h; the tensile strength at room temperature is 600-1000 MPa, and the elongation is more than or equal to 10%; the density is 4.5 to 5.5g/cm3. The method is suitable for the fields of aviation, aerospace, weapons, nuclear energy, microelectronics and the like.
Description
Technical Field
The invention relates to the field of high-temperature thermal protection materials, in particular to a multi-component ultrahigh-entropy light-weight refractory composite material.
Background
With the development of advanced technologies, hot end parts of aircrafts and aeroengines put extremely high requirements on high-temperature materials. If the aircraft can cruise and repeatedly use at low altitude for Ma 0-6 long time, the large-area skin is required to resist high temperature of 800-1200 ℃, light weight, oxidation resistance and ablation resistance. If the temperature of the turbine of the new-generation aircraft engine reaches up to 2100K, the turbine blade is required to endure the high temperature of more than 1500 ℃ under the cooling effect of the cooling gas and bear high-pressure gas scouring. The high-temperature materials commonly used in aerospace, such as titanium alloy, high-temperature alloy, intermetallic compound, ceramic matrix composite, refractory metal and the like, can not meet the requirements: the titanium alloy has low density, but can only be used below 600 ℃; the high-temperature alloy can be used at 900-1100 ℃, and can be used for a long time at 1100-1300 ℃ after being coated on the surface, but on one hand, the high-temperature alloy has high density, and meanwhile, the coating can crack and peel off when the thermal barrier coating on the surface is used for a long time, so that the work of the thermal barrier coating is unstable; the TiAl intermetallic compound has low density and good high-temperature toughness at 800-900 ℃, but has large room temperature brittleness, cannot be processed and deformed to be rolled into thin plates and sheets, and meanwhile, when the temperature is higher than 1000 ℃, the toughness of the material is sharply reduced; the ceramic matrix composite has low density and good oxidation resistance, but has low high-temperature performance and poor thermal bearing performance, and has greater unreliability danger when being repeatedly used for a long time; refractory metals can be used above 1600 ℃, but require coatings with high densities, limiting their use. Meanwhile, in the fields of civil nuclear energy, microelectronic information and the like, high-temperature parts of the materials, such as plasma-oriented materials and electronic packaging materials, require high-temperature resistance, high toughness and long-time oxidation resistance, and great demands are also made on the materials.
Therefore, the development of a material integrating high-temperature, high-toughness, oxidation resistance, ablation resistance and light-weight comprehensive performance at 800-1500 ℃ is urgently needed.
Disclosure of Invention
The invention provides a multi-component ultrahigh-entropy light-weight refractory composite material, and aims to realize the comprehensive performance of high temperature, high strength and toughness, oxidation resistance and light weight of the material at 800-1500 ℃.
In order to achieve the purpose, the invention provides a multi-component ultrahigh-entropy light-weight refractory composite material, which comprises the following components in percentage by mass: 20-40% of Mo, 40-60% of Ti, 10-20% of Al, 1-5% of Nb, 1-5% of Si, 0.5-1% of C, 0.5-1% of N and 0.5-1% of O.
Preferably, the composite material comprises the following components in percentage by mass: 30-40% of Mo, 78-50% of Ti40, 15-20% of Al, 1-4% of Nb, 1-4% of Si, 0.5-1% of C, 0.5-1% of N and 0.5-1% of O.
Preferably, the composite material comprises the following components in percentage by mass: 20-30% of Mo, 50-60% of Ti, 10-15% of Al, 2-4% of Nb, 2-4% of Si, 0.5-0.8% of C, 0.5-0.8% of N and 0.8-1% of O.
Preferably, the composite material comprises the following components in percentage by mass: 25-35% of Mo, 78-55% of Ti45, 14-18% of Al, 3-4% of Nb, 3-4% of Si, 0.5-0.6% of C, 0.5-0.6% of N and 0.8-1% of O.
Preferably, the composite material comprises TiC and TiB2，SiC，Si3N4，BC，MoSi2And a simple substance Nb.
Preferably, the surface of the composite material comprises MoSi2And Nb2O5The multi-component protective film.
Preferably, the density of the composite material is 4.5-5.5 g/cm3。
The invention also provides a preparation method of the multi-component ultrahigh-entropy light-weight refractory composite material, which comprises the following steps:
s1: weighing raw materials according to the component content proportion of the multi-component ultrahigh-entropy light-weight refractory composite material;
s2: adding a medium into the raw materials weighed in the S1, carrying out mixed ball milling under a protective atmosphere, and then carrying out vacuum drying to obtain dry powder;
s3: preparing the dried powder obtained in S2 into a powder compact;
s4: sintering the powder compact obtained in the step S3 to obtain a sintered blank;
s5: and pre-oxidizing the sintered blank to obtain the multi-component ultrahigh-entropy light-weight refractory composite material.
Preferably, in S1, the raw material is Mo, Ti, Al, Nb, Si, TiC, TiB2、SiC、BC、Si3N4Powder; the weight percentage is as follows: 20-40% of Mo, 40-55% of Ti, 10-20% of Al, 1-5% of Nb, 1-5% of Si, 1-3% of TiC and TiB21～3％，SiC 1～3％，BC 1～3％，Si3N41～3％。
Preferably, in the step S2, the medium is absolute ethyl alcohol; the protective atmosphere is Ar gas and N2Gas or vacuum; the ball milling equipment is a planetary ball mill, the ball milling rotating speed is 200-500 rpm, and the ball milling time is 5-20 h.
Preferably, in the S3, the pressure is 100-300 MPa.
Preferably, the sintering mode is one of spark plasma, vacuum hot pressing and high-temperature sintering; the sintering atmosphere is Ar gas or vacuum, the sintering temperature is 1600-2000 ℃, and the heat preservation time is 2-10 h.
Preferably, the pre-oxidation temperature is 800-1200 ℃, and the time is 1-4 h.
The scheme of the invention has the following beneficial effects:
the invention takes four light alloy elements of Mo, Ti, Al and Nb as the matrix, and then introduces nonmetal elements of Si, C, N, B and O into the matrix, and the matrix of the invention fully exerts the height of MoThe temperature strength, the low density and the obdurability of Al-Ti are realized, and simultaneously, the introduced non-metallic elements react with the metallic elements to generate TiC and TiB2、SiC、Si3N4、MoSi2The ceramic can effectively improve the high-temperature strength and the oxidation resistance of the matrix, and in addition, MoSi is formed on the surface of the composite material under the pre-oxidation condition2And Nb2O5The multi-component self-protection film can further improve the long-time oxidation resistance and ablation resistance of the material.
The composite material has the oxidation resistance time of 100-300 h in an air environment at 800-1500 ℃; the tensile strength at room temperature is 600-1000 MPa, and the elongation is more than or equal to 10%; the tensile strength is more than or equal to 200MPa at 800 ℃, and the elongation is more than or equal to 50 percent; the tensile strength is more than or equal to 100MPa at 1200 ℃, and the elongation is more than or equal to 80 percent; the density is 4.5 to 5.5g/cm3。
The composite material disclosed by the invention is low in density, high in high-temperature strength and toughness and excellent in long-time oxidation resistance, is a lightweight composite material with excellent comprehensive performance, and is suitable for the fields of aerospace aircrafts, high-temperature parts of engines, weapons, nuclear energy, microelectronics and the like.
The multi-component ultrahigh-entropy light-weight refractory composite material is prepared by powder mixing, molding, sintering and pre-oxidation, the process is simple, the operation is easy, and large-scale automatic production can be realized.
Detailed Description
In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following detailed description is given with reference to specific embodiments.
Example 1
The multi-component ultrahigh-entropy light-weight refractory composite material comprises the following components in percentage by mass: 40% of Mo, 40% of Ti, 15% of Al, 1% of Nb, 1% of Si, 1% of C, 1% of N and 1% of O;
the preparation process comprises the following steps:
s1: according to the mass percentage, Mo is 40%, Ti is 38%, Al is 13%, Nb is 1%, Si is 0.5%, TiC is 1%, TiB21％，SiC 1.5％，BC 1％，Si3N43 percent of Mo, Ti, Al, Nb, Si, TiC and TiB2、SiC、BC、Si3N4Powder raw materials;
s2: the raw materials are uniformly mixed by a high-energy ball milling method to form powder.
The ball milling process parameters are as follows: the ball-material ratio is 5:1, the rotating speed is 500r/min, the ball milling time is 5 hours, absolute ethyl alcohol is used as a medium, and Ar gas is used for protection; then drying the uniformly mixed powder in a vacuum state to obtain dried powder;
s3: pressing the dried powder into a green body under the pressure of 300 MPa;
and S4, sintering the pressed and formed blank by adopting a discharge plasma method under the vacuum protection, wherein the sintering temperature is 1600 ℃, and the heat preservation time is 2 hours, so as to prepare the block material.
S5: and pre-oxidizing the block material in air at 800 ℃ for 2h to obtain the multi-component ultrahigh-entropy light-weight refractory composite material.
The density of the composite material obtained in this example was 5.5g/cm3Room temperature tensile strength of 900MPa and elongation of 12%; tensile strength of 300MPa at 800 ℃ and elongation of 55 percent; tensile strength of 160MPa at 1200 ℃ and elongation of 82 percent; the material can be used for more than 300 hours in a high-temperature air thermal impact environment of 1200-1400 ℃.
Example 2
The multi-component ultrahigh-entropy light-weight refractory composite material comprises the following components in percentage by mass: mo 30%, Ti 40%, Al 20%, Nb 4%, Si 4%, C0.5%, N0.5%, O1%;
s1: according to the mass percentage, Mo is 30 percent, Ti is 38 percent, Al is 18 percent, Nb is 4 percent, Si is 4 percent, TiC is 1 percent, and TiB21％，SiC 2％，BC 1％，Si3N41 percent of Mo, Ti, Al, Nb, Si, TiC and TiB2、SiC、BC、Si3N4Powder raw materials;
s2: uniformly mixing the raw materials by adopting a high-energy ball milling method to form powder;
the ball milling process parameters are as follows: the ball-material ratio is 5:1, the rotating speed is 200r/min, the ball milling time is 24 hours, absolute ethyl alcohol is used as a medium, and Ar gas is used for protection; then drying the uniformly mixed powder in a vacuum state to obtain dried powder;
s3: pressing the dried powder into a green body under the pressure of 100 MPa;
s4: sintering the pressed and formed blank by adopting a discharge plasma method under the vacuum protection, wherein the sintering temperature is 2000 ℃, and the heat preservation time is 2 hours, so as to prepare the block material.
S5: and pre-oxidizing the block material in air at 1200 ℃ for 1h to obtain the multi-element ultrahigh-entropy light-weight refractory composite material.
The density of the composite material obtained in this example was 5g/cm3The room temperature tensile strength is 1500MPa, and the elongation is 12%; tensile strength of 350MPa at 800 ℃ and elongation of 53 percent; tensile strength of 200MPa at 1200 ℃ and elongation of 82 percent; the material can be used for more than 320 hours in a high-temperature air thermal impact environment of 1200-1400 ℃.
Example 3
The multi-component ultrahigh-entropy light-weight refractory composite material comprises the following components in mass content: mo 20%, Ti 60%, Al 10%, Nb 4%, Si 4%, C0.5%, N0.5%, O1%;
s1: according to the mass percentage, Mo is 20%, Ti is 58%, Al is 10%, Nb is 3%, Si is 3%, TiC is 1%, TiB21％，SiC 2％，BC 1％，Si3N41 percent of Mo, Ti, Al, Nb, Si, TiC and TiB2、SiC、BC、Si3N4Powder raw materials;
s2: uniformly mixing the raw materials by adopting a high-energy ball milling method to form powder;
the ball milling process parameters are as follows: the ball-material ratio is 5:1, the rotating speed is 300r/min, the ball milling time is 16 hours, absolute ethyl alcohol is used as a medium, and Ar gas is used for protection; then drying the uniformly mixed powder in a vacuum state to obtain dried powder;
s3: pressing the dried powder into a green body under the pressure of 200 MPa;
s4: sintering the pressed and formed blank by adopting a discharge plasma method under the vacuum protection, wherein the sintering temperature is 1800 ℃, and the heat preservation time is 5 hours, so as to prepare the block material.
S5: and pre-oxidizing the block material in the air at 1000 ℃ for 2h to obtain the multi-element ultrahigh-entropy light-weight refractory composite material.
The density of the composite material obtained in this example was 4.5g/cm3The room temperature tensile strength is 1500MPa, and the elongation is 12%; tensile strength of 320MPa at 800 ℃ and elongation of 53 percent; tensile strength of 180MPa at 1200 ℃ and elongation of 82 percent; the material can be used for more than 280 hours in a high-temperature air thermal impact environment of 1200-1400 ℃.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. The multi-component ultrahigh-entropy light-weight refractory composite material is characterized by comprising the following components in percentage by mass: 20-40% of Mo, 40-60% of Ti, 10-20% of Al, 1-5% of Nb, 1-5% of Si, 0.5-1% of C, 0.5-1% of N and 0.5-1% of O.
2. The multi-component ultra-high entropy light-weight refractory composite material of claim 1, wherein the composite material comprises TiC and TiB2，SiC，Si3N4，BC，MoSi2And a simple substance Nb.
3. The multi-component ultra-high entropy light-weight refractory composite material of claim 1, wherein the surface of the composite material comprises MoSi2And Nb2O5The multi-component protective film.
4. The multi-component ultrahigh-entropy light-weight refractory composite material according to claim 1, wherein the density of the composite material is 4.5-5.5 g/cm3。
5. The preparation method of the multi-component ultrahigh-entropy light-weight refractory composite material is characterized by comprising the following steps of:
s1: weighing raw materials according to the component content proportion of the multi-element ultrahigh-entropy light-weight refractory composite material in claim 1;
s2: adding a medium into the raw materials weighed in the S1, carrying out mixed ball milling under a protective atmosphere, and then carrying out vacuum drying to obtain dry powder;
s3: preparing the dried powder obtained in S2 into a powder compact;
s4: sintering the powder compact obtained in the step S3 to obtain a sintered blank;
s5: and pre-oxidizing the sintered blank to obtain the multi-component ultrahigh-entropy light-weight refractory composite material.
6. The preparation method of the multi-component ultrahigh-entropy light-weight refractory composite material according to claim 5, wherein in S1, raw materials are Mo, Ti, Al, Nb, Si, TiC and TiB2、SiC、BC、Si3N4Powder; the weight percentage is as follows: 20-40% of Mo, 40-55% of Ti, 10-20% of Al, 1-5% of Nb, 1-5% of Si, 1-3% of TiC and TiB2 1～3％，SiC 1～3％，BC 1～3％，Si3N4 1～3％。
7. The method for preparing the multi-component ultra-high entropy light-weight refractory composite material according to claim 5, wherein in S2, the medium is absolute ethyl alcohol; the protective atmosphere is Ar gas and N2Gas or vacuum; the ball milling equipment is a planetary ball mill, the ball milling rotating speed is 200-500 rpm, and the ball milling time is 5-20 h.
8. The preparation method of the multi-element ultrahigh-entropy light-weight refractory composite material according to claim 5, wherein in S3, the pressure is 100-300 MPa.
9. The preparation method of the multi-element ultrahigh-entropy light-weight refractory composite material according to claim 5, wherein the sintering mode is one of spark plasma, vacuum hot pressing and high-temperature sintering; the sintering atmosphere is Ar gas or vacuum, the sintering temperature is 1600-2000 ℃, and the heat preservation time is 2-10 h.
10. The preparation method of the multi-element ultrahigh-entropy light-weight refractory composite material according to claim 5, wherein the pre-oxidation temperature is 800-1200 ℃ and the time is 1-4 h.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114959406A (en) * | 2022-07-05 | 2022-08-30 | 长沙理工大学 | Oscillatory pressure sintering ultrahigh-temperature medium-entropy ceramic reinforced refractory fine-grain medium-entropy alloy composite material |
| CN115386780A (en) * | 2022-09-13 | 2022-11-25 | 南京工业大学 | Light high-strength high-toughness Gao Shangchao alloy and preparation method thereof |
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| CN116065076B (en) * | 2021-11-04 | 2024-04-12 | 哈尔滨工业大学 | Low-density refractory multi-principal element alloy and preparation method and application thereof |
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| CN114959406A (en) * | 2022-07-05 | 2022-08-30 | 长沙理工大学 | Oscillatory pressure sintering ultrahigh-temperature medium-entropy ceramic reinforced refractory fine-grain medium-entropy alloy composite material |
| CN115386780A (en) * | 2022-09-13 | 2022-11-25 | 南京工业大学 | Light high-strength high-toughness Gao Shangchao alloy and preparation method thereof |
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