CN108264368B - Carbon-ceramic composite material with self-lubricating and anti-oxidation functions and preparation method thereof - Google Patents
Carbon-ceramic composite material with self-lubricating and anti-oxidation functions and preparation method thereof Download PDFInfo
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- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
- C04B35/83—Carbon fibres in a carbon matrix
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/52—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbon, e.g. graphite
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
- C04B35/56—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on carbides or oxycarbides
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/64—Burning or sintering processes
- C04B35/65—Reaction sintering of free metal- or free silicon-containing compositions
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- C04B35/806—
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D69/00—Friction linings; Attachment thereof; Selection of coacting friction substances or surfaces
- F16D69/02—Compositions of linings; Methods of manufacturing
- F16D69/023—Composite materials containing carbon and carbon fibres or fibres made of carbonizable material
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2200/00—Materials; Production methods therefor
- F16D2200/0034—Materials; Production methods therefor non-metallic
- F16D2200/0039—Ceramics
- F16D2200/0047—Ceramic composite, e.g. C/C composite infiltrated with Si or B, or ceramic matrix infiltrated with metal
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
- F16D2200/00—Materials; Production methods therefor
- F16D2200/0082—Production methods therefor
Abstract
The invention relates to a carbon-ceramic composite material with self-lubricating and anti-oxidation functions and a preparation method thereof3SiC2The preparation method comprises the following steps: (1) preparing and pretreating a carbon fiber preform; (2) preparing a protective coating on the surface of the carbon fiber preform; (3) densifying the carbon fiber preform with the protective coating to prepare a porous C/C preform; (4) carrying out high-temperature heat treatment on the porous C/C prefabricated body; (5) carrying out high-temperature heat treatment on the Ti-Si alloy or the mixed powder of Ti and Si and the porous C/C preform to prepare the C/C-TiC-Ti3SiC2Carbon-ceramic composite material. The preparation method has the advantages of simple operation, low cost and short process period, and the prepared C/C-TiC-Ti3SiC2The carbon-ceramic composite material has the functions of self-lubrication and oxidation resistance, is wear-resistant, and is environment-friendly and pollution-free.
Description
Technical Field
The invention relates to a carbon-ceramic composite material with self-lubricating and anti-oxidation functions and a preparation method thereof, in particular to carbon fiber reinforced carbon, titanium carbide and Ti3SiC2A matrix carbon-ceramic composite material, a preparation method and application thereof.
Background
The carbon-ceramic composite material integrates the excellent properties of the carbon fiber and the ceramic material, has the advantages of low density, high strength, abrasion resistance, excellent oxidation resistance, good thermal shock resistance and the like, is an ideal high-performance friction braking material, and has wide application prospect in brake braking systems of industries such as aviation, aerospace, high-speed rail, automobile and the like. Carbon fiber reinforced carbon composite (C/C) and carbon fiber reinforced carbon and silicon carbide double-matrix carbon ceramic composite (C/C-SiC) are typical representatives of carbon ceramic friction braking materials, are successfully applied to brake braking systems of automobiles and airplanes at present, and show excellent friction and wear properties compared with traditional friction braking materials and powder metallurgy friction braking materials.
The C/C composite material is a carbon-based friction braking material which is most widely applied at present, has low density, large specific heat capacity and good heat resistance, can still maintain excellent friction performance under high load, and has been widely applied to aeronautic and astronautic aircraft brake pairs. However, the preparation period of the C/C composite material is long, the cost is high, the oxidation resistance is poor, the friction factor of the C/C composite material in a wet state is unstable, the requirement on the environment (cleanness and dryness) is high, and the C/C composite material is difficult to be applied to vehicles with poor use environments on a large scale.
The C/C-SiC composite material is developed from a C/C composite material, combines the advantages of carbon fiber and silicon carbide ceramic materials, has obviously improved oxidation resistance compared with the C/C composite material, is a carbon ceramic friction braking composite material with high strength, large heat capacity, excellent friction performance and good oxidation resistance, and the prepared brake pad not only has a series of advantages of a carbon disc, but also overcomes the defects of low static friction coefficient, low wet friction coefficient and large difference of friction coefficients in dry and wet states of the carbon disc, has better friction and wear performance and better oxidation resistance. The preparation method of the C/C-SiC composite material comprises a chemical vapor infiltration method, a precursor impregnation cracking method and a liquid silicon infiltration method. The chemical vapor infiltration method and the precursor impregnation pyrolysis method can prepare parts which have excellent performance and can be formed cleanly and nearly, but the preparation period is long, the cost is high, and the method is not suitable for preparing carbon ceramic friction materials. The liquid silicon infiltration method is a high-efficiency and low-cost preparation method of the C/C-SiC composite material, but the prepared composite material contains a certain amount of residual silicon, which not only influences the high-temperature resistance of the composite material, but also is unfavorable for the frictional wear performance of the C/C-SiC composite material. In addition, when the C/C-SiC composite material is rubbed with the steel disc in a dual mode, the scratch damage to the steel disc is serious at high speed, and the friction and wear performance needs to be further optimized and improved.
Disclosure of Invention
The invention aims to provide C/C-TiC-Ti3SiC2The carbon-ceramic composite material and the preparation method thereof have short preparation period and low cost, and the prepared C/C-TiC-Ti3SiC2The carbon-ceramic composite material has good friction and abrasion resistance, and has self-lubricating and anti-oxidation functions.
The invention firstly provides C/C-TiC-Ti3SiC2The carbon-ceramic composite material comprises carbon fibers, a carbon fiber protective layer, a carbon matrix, a TiC matrix and Ti3SiC2A substrate; the carbon fiber protective layer is coated on the surface of the carbon fiber, and the carbon substrate, the TiC substrate and the Ti are coated with the carbon fiber protective layer3SiC2The matrix is distributed in the composite material layer by layer, and the TiC matrix is positioned in the carbon matrix and Ti3SiC2Between the substrates.
The C/C-TiC-Ti3SiC2 carbon ceramic composite material disclosed by the invention comprises the following components in percentage by volume: 15-50% of carbon fiber, 10-50% of carbon matrix, 10-40% of TiC matrix and Ti3SiC21-40% of matrix.
Preferably, C/C-TiC-Ti3SiC2The composite material comprises the following matrix components: 20-45% of carbon fiber, 15-30% of carbon matrix, 15-30% of TiC matrix and Ti3SiC215-35% of a matrix.
The invention provides the C/C-TiC-Ti3SiC2The preparation method of the carbon-ceramic composite material comprises the following steps：
(1) Preparing and pretreating a carbon fiber preform;
(2) preparing a protective coating on the surface of the carbon fiber preform;
(3) densifying the carbon fiber preform with the protective coating to prepare a porous C/C preform;
(4) carrying out high-temperature heat treatment on the porous C/C prefabricated body;
(5) and carrying out high-temperature heat treatment on the Ti-Si alloy or the mixed powder of Ti and Si and the porous C/C prefabricated body together to obtain the composite material.
In the preparation method, the carbon fiber preform in the step (1) is prepared by preparing the carbon fiber preform with the fiber volume fraction of 10-50% by adopting a needling, carbon cloth lamination puncturing, three-dimensional weaving or multi-dimensional integral weaving mode on carbon fiber or carbon fiber cloth; the pretreatment of the step (1) is to subject the carbon fiber preform to vacuum degree of 5.0 × 10-2The Pa-3Pa temperature is 1200-1800 ℃ for 1-4 h.
The coating in the step (2) is a pyrolytic carbon coating SiC coating or a BN coating, and the thickness is 50-500 nm.
Step (3) densifying the carbon fiber preform with the protective coating by adopting a chemical vapor deposition process or a polymer impregnation cracking process to prepare a porous C/C preform; the density of the porous C/C preform is controlled to be 0.9-1.6g/cm3The porosity is controlled between 15% and 55%.
The high-temperature heat treatment method of the porous C/C preform in the step (4) is to carry out heat treatment on the porous C/C preform at 1600-2200 ℃ for 1-4h in vacuum or inert atmosphere.
The high-temperature heat treatment conditions in the step (5) are as follows: heating to 50-300 ℃ above the melting point of the Ti-Si alloy at a heating rate of 5-30 ℃/min under vacuum or inert atmosphere or heating to 1900 ℃ by adopting mixed powder of Ti and Si for reaction for 1-5 h.
The Ti-Si alloy in the step (5) is prepared by adopting an arc melting method or an induction melting method, and the raw materials are titanium ingot with the purity of more than 99.9 percent and silicon powder with the purity of more than 99.5 percent, wherein the atomic percentage is 75:25-95: 5; the mixed powder of Ti and Si is prepared by ball milling and mixing titanium powder with the purity of more than 99.5 percent and silicon powder with the purity of more than 99.5 percent, and the atomic percentage is 70:30-90: 10.
The invention provides C/C-TiC-Ti prepared by the preparation method3SiC2Carbon-ceramic composite material.
Further, the C/C-TiC-Ti prepared by the preparation method3SiC2The carbon-ceramic composite material comprises carbon fibers, a carbon fiber protective layer, a carbon matrix, a TiC matrix and Ti3SiC2A substrate; the carbon fiber protective layer is coated on the surface of the carbon fiber, and the carbon substrate, the TiC substrate and the Ti are coated with the carbon fiber protective layer3SiC2The matrix is distributed in the composite material layer by layer, and the TiC matrix is positioned in the carbon matrix and Ti3SiC2Between the substrates. The components are distributed according to the volume percentage as follows: 15-50% of carbon fiber, 10-50% of carbon matrix, 10-40% of TiC matrix and Ti3SiC21-40% of matrix. Preferably, C/C-TiC-Ti3SiC2The composite material comprises the following matrix components: 20-45% of carbon fiber, 15-30% of carbon matrix, 15-30% of TiC matrix and Ti3SiC215-35% of a matrix.
The invention provides the prepared C/C-TiC-Ti3SiC2The application of the carbon-ceramic composite material in braking.
The invention provides the prepared C/C-TiC-Ti3SiC2The application of the carbon-ceramic composite material in preparing brake fittings.
The invention has the advantages that:
(1) the C/C-TiC-Ti prepared by the invention3SiC2TiC and Ti in carbon-ceramic composite material3SiC2The TiC phase has the super-hard characteristic, the oxidation resistance of the carbon-ceramic composite material is improved by more than 2 times compared with that of a C/C composite material, and the wear resistance of the carbon-ceramic composite material is effectively improved; ti3SiC2The phase has a lamellar structure and has excellent high-temperature lubricating property, so that the carbon-ceramic composite material has good self-lubricating property.
(2) Preparation of C/C-TiC-Ti3SiC2The carbon-ceramic composite material has the advantages of short process cycle, high efficiency and low cost, and the near-net forming of the carbon-ceramic composite material is realized.
(3) The preparation method provided by the invention solves the problem that residual unreacted metal is easy to exist in the carbon-ceramic composite material prepared by the conventional metal infiltration process.
Drawings
FIG. 1 is a schematic representation of the C/C-TiC-Ti prepared in example 13SiC2XRD pattern of carbon ceramic composite material.
FIG. 2 is a schematic representation of the C/C-TiC-Ti prepared in example 13SiC2And (3) a scanning electron microscope image of the section of the carbon-ceramic composite material.
Detailed Description
The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
Unless otherwise specified, the starting materials described in the examples of the present application are all commercially available.
Example 1
The carbon fiber preform is prepared by taking continuous carbon fibers as raw materials and adopting a laid fabric lamination puncturing process, wherein the fiber volume fraction of the carbon fiber preform is 37%. The carbon fiber preform is subjected to vacuum degree of 8.0 multiplied by 10-2Heating to 1500 ℃ under Pa, and carrying out heat treatment and heat preservation for 1 h. And preparing a pyrolytic carbon protective coating on the surface of the carbon fiber preform subjected to heat treatment by adopting a chemical vapor deposition process, wherein the thickness of the pyrolytic carbon protective coating is 90 nm. Continuously depositing matrix pyrolytic carbon for subsequent reaction in the porous carbon fiber preform by adopting a chemical vapor infiltration process, densifying the porous carbon fiber preform to obtain a porous C/C composite preform, wherein the density of the porous C/C composite preform is controlled at 1.12g/cm3The porosity was 38%. And heating the porous C/C preform to 1800 ℃ in an argon atmosphere, carrying out high-temperature heat treatment and heat preservation for 1h, and improving the graphitization degree and the reaction activity of the matrix carbon. Titanium ingot with the purity of 99.9 percent and silicon powder with the purity of 99.6 percent are used as raw materials, alloy raw materials are prepared according to the atomic percentage of 86.5:13.5, and the Ti-Si alloy is prepared by adopting an electric arc melting method. Placing the prepared Ti-Si alloy and the porous C/C composite material prefabricated body subjected to high-temperature heat treatment in a graphite crucible, heating to a temperature of 100 ℃ above the melting point of the alloy at a heating rate of 15 ℃/min in an argon atmosphere, reacting for 2h, and cooling along with the furnace to prepare the C/C-TiC-Ti3SiC2A composite material.
The prepared C/C-TiC-Ti3SiC2The composite material comprises 37% of carbon fibers, a carbon fiber protective layer, 23% of a carbon matrix, 15% of a TiC matrix and 25% of a Ti3SiC2 matrix (the% are volume percentages). The carbon fiber protective layer is coated on the surface of the carbon fiber, the carbon matrix, the TiC matrix and the Ti3SiC2 matrix are distributed in the composite material in a layered mode, and the TiC matrix is located between the carbon matrix and the Ti3SiC2 matrix.
The C/C-TiC-Ti prepared in this example3SiC2The XRD pattern of the composite material is shown in figure 1, and TiC and Ti appear in figure 13SiC2Typical diffraction peaks of (A) indicate the reaction of the composite material to form TiC and Ti3SiC2And (4) phase(s). FIG. 2 is a schematic diagram of the prepared C/C-TiC-Ti3SiC2The scanning electron microscope image of the section of the composite material shows that the composite material is microcosmically compact and complete and has no obvious defects such as holes and the like. The prepared C/C-TiC-Ti is tested by adopting a friction wear testing machine3SiC2Compared with the C/C-SiC composite material prepared by the same process, the friction and wear performance of the composite material is reduced by 30%, and after the composite material is worn, a layer of lubricating mill is formed on the surface of a test sample, so that the composite material has self-lubricating property. Respectively adopts oxidation experiments to characterize the prepared C/C-TiC-Ti3SiC2The composite material and the conventional C/C and C/C-SiC composite material have oxidation resistance, and compared with the C/C and C/C-SiC composite material prepared by the same process, the prepared C/C-TiC-Ti3SiC2The oxidation resistance of the composite material is respectively improved by 230 percent and 51 percent, and the oxidation resistance is excellent.
Example 2
The carbon fiber preform is prepared by taking continuous carbon fibers as raw materials and adopting a laid fabric lamination puncturing process, wherein the fiber volume fraction of the carbon fiber preform is 35%. The carbon fiber preform is placed in a vacuum degree of 9.0X 10-2Heating to 1700 ℃ under Pa, and carrying out heat treatment and heat preservation for 1 h. And preparing a pyrolytic carbon protective coating on the surface of the carbon fiber preform subjected to heat treatment by adopting a chemical vapor deposition process, wherein the thickness of the pyrolytic carbon protective coating is 200 nm. The chemical vapor infiltration process is adopted to continueDepositing matrix pyrolytic carbon for subsequent reaction inside the porous carbon fiber preform, densifying the porous carbon fiber preform to obtain the porous C/C composite preform, wherein the density of the porous C/C composite preform is controlled to be 1.31g/cm3The porosity was 38%. And heating the porous C/C preform to 1900 ℃ in an argon atmosphere, carrying out high-temperature heat treatment and heat preservation for 2h, and improving the graphitization degree and the reaction activity of the matrix carbon. Titanium powder with the purity of 99.5 percent and silicon powder with the purity of 99.6 percent are used as raw materials, the raw materials are prepared according to the atomic percentage of 80:20, and mixed powder is prepared by adopting a ball mill to mix. Placing the prepared mixed powder and the porous C/C composite material prefabricated body subjected to high-temperature heat treatment in a graphite crucible, heating to 200 ℃ above the melting point of the alloy at a heating rate of 30 ℃/min in an argon atmosphere, reacting for 2h, and cooling along with the furnace to prepare the C/C-TiC-Ti3SiC2A composite material.
The C/C-TiC-Ti prepared in this example3SiC2The composite material comprises 30% of carbon fiber, a carbon fiber protective layer, 25% of a carbon matrix, 20% of a TiC matrix and Ti3SiC2Matrix 25% (% by volume). The carbon fiber protective layer is coated on the surface of the carbon fiber, and the carbon substrate, the TiC substrate and the Ti are coated with the carbon fiber protective layer3SiC2The matrix is distributed in the composite material layer by layer, and the TiC matrix is positioned in the carbon matrix and Ti3SiC2Between the substrates.
The C/C-TiC-Ti prepared in this example3SiC2TiC and Ti appear on the XRD pattern of the composite material3SiC2Typical diffraction peaks of (A) indicate the reaction of the composite material to form TiC and Ti3SiC2And (4) phase(s). The C/C-TiC-Ti prepared in this example3SiC2The scanning electron microscope image of the section of the composite material shows that the composite material is microcosmically compact and complete and has no obvious defects such as holes and the like. The prepared C/C-TiC-Ti is tested by adopting a friction wear testing machine3SiC2Compared with the C/C-SiC composite material prepared by the same process, the friction and wear performance of the composite material is reduced by 23%, and after the composite material is worn, a layer of lubricating mill is formed on the surface of a test sample, so that the composite material has self-lubricating property. Respectively adopts oxidation experiments to characterize the prepared C/C-TiC-Ti3SiC2The composite material and the C/C and C/C-SiC composite material prepared by the same process have the oxidation resistance, and compared with the conventional C/C and C/C-SiC composite material, the prepared C/C-TiC-Ti3SiC2The oxidation resistance of the composite material is respectively improved by 260 percent and 57 percent, and the oxidation resistance is excellent.
Although the invention has been described in detail hereinabove with respect to a general description and specific embodiments thereof, it will be apparent to those skilled in the art that modifications or improvements may be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (9)
1. C/C-TiC-Ti3SiC2The carbon-ceramic composite material is characterized by comprising carbon fibers, a carbon fiber protective coating, a carbon matrix, a TiC matrix and Ti3SiC2A substrate; the carbon fiber protective coating is coated on the surface of the carbon fiber, and the carbon substrate, the TiC substrate and the Ti are coated3SiC2The matrix is distributed in the composite material layer by layer, and the TiC matrix is positioned in the carbon matrix and Ti3SiC2Between the substrates;
the components are distributed according to the volume percentage as follows: 15-50% of carbon fiber, 10-50% of carbon matrix, 10-40% of TiC matrix and Ti3SiC21-40% of matrix.
2. The C/C-TiC-Ti of claim 13SiC2The preparation method of the carbon-ceramic composite material comprises the following steps:
(1) preparing and pretreating a carbon fiber preform;
(2) preparing a carbon fiber protective coating on the surface of the carbon fiber preform;
(3) densifying the carbon fiber preform with the protective coating to prepare a porous C/C preform;
(4) carrying out high-temperature heat treatment on the porous C/C prefabricated body;
(5) and carrying out high-temperature heat treatment on the Ti-Si alloy or the mixed powder of Ti and Si and the porous C/C prefabricated body together to obtain the composite material.
3. The preparation method according to claim 2, wherein the carbon fiber preform in the step (1) is prepared by carrying out needling, carbon cloth lamination puncturing, three-dimensional weaving or multi-dimensional integral weaving on carbon fiber or carbon fiber cloth to obtain the carbon fiber preform with the fiber volume fraction of 10-50%; the pretreatment of the step (1) is to subject the carbon fiber preform to vacuum degree of 5.0 × 10-2The Pa-3Pa temperature is 1200-1800 ℃ for 1-4 h.
4. The method according to claim 2, wherein the carbon fiber protective coating of step (2) is a pyrolytic carbon coating, a SiC coating or a BN coating, and has a thickness of 50 to 500 nm.
5. The preparation method according to claim 2, wherein the step (3) densifies the carbon fiber preform with the protective coating to obtain a porous C/C preform by using a chemical vapor deposition process or a polymer impregnation cracking process; the density of the porous C/C preform is controlled to be 0.9-1.6g/cm3The porosity is controlled between 15% and 55%.
6. The preparation method according to claim 2, wherein the porous C/C preform in the step (4) is subjected to high temperature heat treatment at 1600-2200 ℃ for 1-4h under vacuum or inert atmosphere.
7. The method according to any one of claims 2 to 6, wherein the high-temperature heat treatment conditions in the step (5) are as follows: heating to 50-300 ℃ above the melting point of the Ti-Si alloy at a heating rate of 5-30 ℃/min under vacuum or inert atmosphere or heating to 1900 ℃ by adopting mixed powder of Ti and Si for reaction for 1-5 h.
8. The preparation method according to any one of claims 2 to 6, wherein the Ti-Si alloy in the step (5) is prepared by an arc melting method or an induction melting method by using titanium ingots with the purity of more than 99.9% and silicon powders with the purity of more than 99.5% in an atomic ratio of 75:25 to 95: 5; the mixed powder of Ti and Si is prepared by ball milling and mixing titanium powder with the purity of more than 99.5 percent and silicon powder with the purity of more than 99.5 percent, and the atomic percentage is 70:30-90: 10.
9. The C/C-TiC-Ti of claim 13SiC2The application of the carbon-ceramic composite material in a brake system.
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| CN112377547B (en) * | 2020-11-12 | 2022-08-02 | 湖南世鑫新材料有限公司 | Carbon-ceramic brake disc and preparation method thereof |
| CN112830805B (en) * | 2021-01-18 | 2022-12-02 | 长沙理工大学 | Preparation method of carbon-ceramic wear-resistant composite material |
| CN114044679A (en) * | 2021-11-22 | 2022-02-15 | 湖南兴晟新材料科技有限公司 | High-toughness ultrahigh-temperature ceramic matrix composite and preparation method thereof |
| CN114685176A (en) * | 2022-03-22 | 2022-07-01 | 潍柴动力股份有限公司 | Preparation method of multilayer interface modified carbon-ceramic composite material and engine piston |
| CN115057713B (en) * | 2022-06-27 | 2023-07-25 | 中国人民解放军国防科技大学 | 1500 ℃ resistant heat-proof and heat-insulating integrated composite structural ceramic and preparation method thereof |
| CN116836002B (en) * | 2023-05-26 | 2024-04-30 | 西北工业大学 | Be used for SiCfTi-Si-C composite coating on SiC surface and preparation method thereof |
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| DE19711831C2 (en) * | 1997-03-21 | 2000-07-13 | Daimler Chrysler Ag | Melt-infiltrated fiber-reinforced composite ceramics and method for producing such |
| CN103342561B (en) * | 2013-06-26 | 2014-11-05 | 中国人民解放军国防科学技术大学 | C/ZrC composite material prepared on basis of vapor infiltration reaction, preparation method thereof and equipment for process |
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