CN111285703B - Method for manufacturing low-cost double-element carbon matrix airplane carbon brake disc - Google Patents
Method for manufacturing low-cost double-element carbon matrix airplane carbon brake disc Download PDFInfo
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- CN111285703B CN111285703B CN202010243627.5A CN202010243627A CN111285703B CN 111285703 B CN111285703 B CN 111285703B CN 202010243627 A CN202010243627 A CN 202010243627A CN 111285703 B CN111285703 B CN 111285703B
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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
- C04B35/71—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
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
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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
- F16D65/00—Parts or details
- F16D65/02—Braking members; Mounting thereof
- F16D65/12—Discs; Drums for disc brakes
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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
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—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
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/614—Gas infiltration of green bodies or pre-forms
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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
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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 discloses a method for manufacturing a low-cost binary carbon matrix airplane carbon brake disc, which comprises the following steps: firstly, carrying out high-temperature pretreatment on the needled weftless carbon cloth integral carbon disc preform; secondly, carrying out isothermal vapor deposition on the needled weftless carbon cloth integral carbon disc preform subjected to high-temperature pretreatment to obtain a pyrolytic carbon matrix with a rough layer structure; thirdly, performing resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix to obtain a resin carbon-containing binary carbon matrix; and fourthly, carrying out high-temperature graphitization treatment on the binary carbon matrix to obtain the binary carbon matrix airplane carbon brake disc. The method adopts the carbon source gas mainly comprising natural gas to carry out isothermal vapor deposition, utilizes the characteristics of small natural gas molecules, large penetration depth and high gas utilization rate, improves the vapor deposition speed, shortens the production period, reduces the raw material cost and the conveying cost, improves the structural uniformity and the quality consistency of the aircraft carbon brake disc with the binary carbon matrix, and is suitable for large-batch industrial production.
Description
Technical Field
The invention belongs to the technical field of preparation of airplane carbon brake discs, and particularly relates to a method for manufacturing a low-cost double-element carbon matrix airplane carbon brake disc.
Background
With the development of carbon/carbon composite materials, the aspects of theoretical innovation, preparation process, application expansion and the like are deeply researched, the preparation technology of the materials is continuously improved, and the low cost and large batch of carbon/carbon composite material products become the future development trend.
At present, carbon matrix materials for manufacturing carbon brake discs of airplanes at home and abroad mainly comprise three types of pyrolytic carbon, resin carbon and pitch carbon. The aircraft Carbon brake discs produced by foreign major Carbon disc manufacturers such as Dunlop company in UK, Carbon industrie company in France, B.F. Goodrich company in USA and the like are all single pyrolytic Carbon substrates obtained by adopting a chemical vapor deposition method; the American ABS company adopts a single resin carbon matrix; the Russian institute of H, P, A, and T uses a single pitch matrix. The mainstream technology of the brake disc of the domestic airplane comprises two types: the first is a binary carbon matrix obtained by combining thermal gradient vapor deposition and resin impregnation-carbonization, wherein the thermal gradient vapor deposition takes propylene as a carbon source and is represented by Xian super code and Boyun new material; the second is a pure pyrolytic carbon matrix obtained by vapor deposition using natural gas as a carbon source, represented by Huaxing aviation airplane wheel company and a new material for the metallurgy of the smoke platform. The method has the common defects of long production period and high cost.
U.S. Pat. No. 5900297 discloses a method for preparing a carbon/carbon composite material by a pressure gradient CVI method, which uses a mixture of natural gas and propane to prepare a carbon/carbon composite material with a higher density in a shorter time by the pressure gradient CVI method (chemical vapor infiltration method), but the method has higher requirements on equipment and higher operation difficulty, and is not suitable for mass production.
The Chinese patent with the publication number of CN 1291173C discloses a method for manufacturing an aircraft carbon brake disc with optimized combination of a binary carbon matrix, and the method adopts a method of combining propylene thermal gradient vapor deposition and resin impregnation-carbonization to prepare the binary carbon matrix. Firstly, the method takes propylene as a carbon source gas, and has the following defects: (1) the propylene has larger molecular weight, small penetration depth and low carbon deposition efficiency; (2) the surface of the prefabricated part is easy to crust in the process of densification, and intermediate machining is needed, so that the production period is prolonged, and the production cost is increased; (3) propylene is relatively expensive and requires tank car transportation, increasing shipping costs. Secondly, the method needs to be respectively arranged in an inner thermal gradient deposition furnace and an outer thermal gradient deposition furnace according to different types of carbon disks, has higher requirement on equipment and complex process, is not beneficial to large-scale industrial production, and thus the prepared product has unstable product quality consistency and poorer structure uniformity due to process difference.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for manufacturing a low-cost double-element carbon matrix airplane carbon brake disc aiming at the defects of the prior art. The method adopts the carbon source gas mainly containing natural gas to carry out isothermal vapor deposition, utilizes the characteristics of small natural gas molecules, large penetration depth and high gas utilization rate, improves the vapor deposition speed, shortens the production period, reduces the raw material cost and the transportation cost, improves the structural uniformity and the quality consistency of the aircraft carbon brake disc with the binary carbon matrix, and is suitable for large-batch industrial production.
In order to solve the technical problems, the invention adopts the technical scheme that: a manufacturing method of a low-cost binary carbon matrix airplane carbon brake disc is characterized by comprising the following steps:
firstly, putting a needled weftless carbon cloth integral carbon disk preform into a high-temperature heat treatment furnace, and carrying out high-temperature pretreatment at the temperature of 1800-2400 ℃;
step two, putting the needled weftless carbon cloth integral carbon disk preform pretreated at high temperature in the step one into a vapor deposition furnace, adjusting the flow of carbon source gas, enabling the carbon source gas to directionally flow through the surface of the needled weftless carbon cloth integral carbon disk preform, and then carrying out isothermal vapor deposition to obtain a pyrolytic carbon matrix with a rough layer structure; the temperature of the isothermal vapor deposition is 950-1100 ℃; the mass content of the rough layer in the pyrolytic carbon matrix is 50-65%; the carbon source gas mainly comprises natural gas;
step three, performing resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix obtained in the step two to obtain a resin carbon-containing binary carbon matrix; the mass content of the resin carbon in the binary carbon matrix is 5-20%;
and step four, carrying out high-temperature graphitization treatment on the binary carbon matrix obtained in the step three at the temperature of 2000-2400 ℃ to obtain the binary carbon matrix airplane carbon brake disc.
The preparation method comprises the steps of firstly carrying out high-temperature pretreatment on a needled weftless carbon cloth integral carbon disc preform to remove metal inclusions and sizing agents on the surface of carbon fibers, then carrying out isothermal vapor deposition by adopting a carbon source gas mainly comprising natural gas, filling, depositing and compacting the carbon source gas in the needled weftless carbon cloth integral carbon disc preform subjected to the high-temperature pretreatment to obtain a pyrolytic carbon matrix with a rough layer structure, carrying out resin impregnation-carbonization compaction treatment to obtain a binary carbon matrix containing resin carbon, and carrying out high-temperature graphitization treatment to obtain the binary carbon matrix airplane carbon brake disc.
Firstly, the carbon source gas mainly comprising natural gas is adopted, and the carbon source gas has high carbon yield as gas source gas due to small natural gas molecules, large penetration depth and high gas utilization rate, so that the vapor deposition speed is improved, the surface is not easy to crust in the process of densification treatment, the number of times of intermediate machining treatment is reduced, the production period is shortened, the production cost is reduced, meanwhile, the natural gas is cheap, the pipeline conveying can be adopted, the conveying cost is reduced, and the manufacturing cost is further reduced; secondly, the method adopts isothermal vapor deposition, has low requirements on equipment, ensures that the needled weftless carbon cloth integrated carbon disc preform is always in a uniformly heated state in the deposition process, improves the uniformity of vapor deposition, thereby improving the structural uniformity and quality consistency of the binary carbon matrix aircraft carbon brake disc, solves the problems that the existing gradient vapor deposition needs to arrange a strong heat source and a strong cold source on two corresponding surfaces of the inner diameter and the outer diameter of the needled weftless carbon cloth integrated carbon disc preform respectively to form an inner thermal gradient and an outer thermal gradient, has high requirements on equipment and complex process, overcomes the problems of uneven deposition density, unstable quality consistency and poor structural uniformity of a binary carbon matrix aircraft carbon brake disc product prepared by gradient vapor deposition, has high production efficiency, and is suitable for large-batch industrial production.
According to the invention, the flow of the carbon source gas is regulated according to the total mass of the needled weftless carbon cloth integrated carbon disc preform which is put into the vapor deposition furnace and subjected to high-temperature pretreatment, the quality of a final product and the utilization rate of the decomposed carbon source gas so as to ensure the isothermal vapor deposition effect, and then according to the placing position of the needled weftless carbon cloth integrated carbon disc preform in the vapor deposition furnace, an internal gas limiting tool is adopted to limit the flow path of the carbon source gas, so that the carbon source gas is fully contacted with the surface of the needled weftless carbon cloth integrated carbon disc preform subjected to high-temperature pretreatment, the uniformity of isothermal vapor deposition is favorably improved, and the structural uniformity and the quality uniformity of the aircraft carbon brake disc with a binary carbon matrix are further improved.
The manufacturing method of the low-cost double-element carbon matrix aircraft carbon brake disc is characterized in that in the step one, the needled weftless carbon cloth integrated carbon disc preform is manufactured by radial needling after carbon fiber plain cloth or twill cloth and carbon fiber net tires are alternately layered, and the density of the needled weftless carbon cloth integrated carbon disc preform is 0.5g/cm3～0.7g/cm3. The needling non-weft carbon cloth integral carbon disc preform prepared by the optimal preparation method has carbon fiber bundles in the axial direction, so that the axial heat conductivity coefficient is obviously improved, the temperature of a friction surface is facilitated, and the friction coefficient is more stable; the content of carbon fiber in the needling non-weft carbon cloth integral carbon disc preform with the optimal density is moderate, and the carbon brake disc of the aircraft with the binary carbon matrix has higher mechanical property.
The manufacturing method of the low-cost double-element carbon matrix aircraft carbon brake disc is characterized in that the mode of loading the needle-punched weftless carbon cloth integral carbon disc preform subjected to high-temperature pretreatment into a vapor deposition furnace in the step one is a single-material column furnace loading mode or a multi-material column furnace loading mode. The method adopting isothermal vapor deposition is suitable for single-material column small equipment and multi-material column large equipment, and has high preparation efficiency and wide application range.
The manufacturing method of the low-cost double-element carbon matrix aircraft carbon brake disc is characterized in that in the second step, the carbon source gas is formed by mixing natural gas and one or more of propylene, propane, acetylene, hydrogen and nitrogen, wherein the volume percentage of the natural gas in the carbon source gas is 55-98%. The optimized carbon source gas takes micromolecular natural gas as a main component, has large penetration depth and high gas utilization rate, so that the deposition speed is high, the production period is short, the price is low, the carbon source gas is suitable for pipeline transportation, and the manufacturing cost is reduced.
The manufacturing method of the low-cost double-element carbon matrix airplane carbon brake disc is characterized in that in the step two, the carbon source gas is firstly sent into a gas preheating device outside the furnace or a gas circulating preheating device arranged at the bottom in the furnace for preheating, and then is sent into a vapor deposition furnace for isothermal vapor deposition; the preheating temperature is 950 ℃ to 1100 ℃. The carbon source gas is directly sent into the vapor deposition furnace for isothermal vapor deposition, the temperature at the air inlet is low, the carbon source gas cannot reach the decomposition temperature, the deposition densification effect of the pyrolytic carbon matrix at the bottom of the vapor deposition furnace is poor, and the consumed time is long, so that the carbon source gas is preferably preheated and then sent into the vapor deposition furnace for isothermal vapor deposition, the utilization rate of the carbon source gas is improved, the gas consumption is saved, the deposition densification effect is improved, and the deposition time is shortened.
The manufacturing method of the low-cost binary carbon matrix airplane carbon brake disc is characterized in that the isothermal vapor deposition time in the second step is 120-400 hours. The density and deposition densification effect required by preparing the pyrolytic carbon matrix can be realized within the isothermal vapor deposition time, the isothermal vapor deposition time is reduced, and the whole manufacturing period is favorably shortened.
Compared with the prior art, the invention has the following advantages:
1. the invention adopts the carbon source gas mainly comprising natural gas to carry out vapor deposition, and utilizes the characteristics of small natural gas molecules, large penetration depth and high gas utilization rate to improve the vapor deposition speed, shorten the production period and reduce the raw material cost and the transportation cost.
2. The method adopts an isothermal vapor deposition method, improves the uniformity of vapor deposition, thereby improving the structural uniformity and quality consistency of the binary carbon matrix airplane carbon brake disc, solving the problems of complex process and higher requirement on equipment in the prior art, having high production efficiency and being suitable for large-batch industrial production.
3. The aircraft carbon brake disc with the double-element carbon matrix manufactured by the invention has good structural uniformity and stable quality, exerts the characteristic of complementary advantages of the double-element carbon matrix, keeps better friction and wear performance of the aircraft carbon brake disc through the pyrolytic carbon matrix with a rough layer structure, further reduces the aperture ratio through hole filling and densification of the resin carbon, is beneficial to improving the compression, bending and shearing strength of the aircraft carbon brake disc, and simultaneously greatly reduces the hygroscopicity due to hole sealing of the resin carbon, improves the wet braking performance and ensures that the wet braking friction coefficient is not attenuated basically.
4. The invention has simple manufacturing process and good repeatability, can adopt a single material column or multi-material column mode according to deposition equipment with different sizes, and is suitable for batch production.
5. The method has the advantages of short production period and greatly reduced cost, and through estimation, compared with the process of performing gradient vapor deposition by adopting propylene in the prior art, the vapor deposition time is reduced by at least 43 percent, the total production period is reduced by at least 36 percent, the costs of material consumption, hydroelectric power, fixed asset depreciation and the like are greatly reduced, and the production cost of charging by adopting a single material column is reduced by at least 30 percent.
The technical solution of the present invention is further described in detail below with reference to the embodiments by the accompanying drawings.
Drawings
FIG. 1 is a schematic view of a single charge column furnace structure of a needled weftless carbon cloth monolithic carbon disk preform after high temperature pretreatment according to the present invention.
FIG. 2 is a schematic view of a first multi-column furnace structure of a needled weftless carbon cloth monolithic carbon disk preform after high temperature pretreatment according to the present invention.
Fig. 3 is a sectional view a-a of fig. 2.
FIG. 4 is a schematic view of a second multi-material column furnace structure of a needle-punched non-weft carbon cloth monolithic carbon disk preform after high-temperature pretreatment according to the present invention.
Description of the reference numerals
1-a graphite cover plate; 2-a heating element; 3, a gasket;
4, needling the whole carbon disk preform of the weftless carbon cloth; 5, circulating gas guiding and preheating device; 6, an air inlet pipe;
7-gas-limiting cylinder.
Detailed Description
Example 1
The embodiment comprises the following steps:
step one, setting the density to be 0.50g/cm3The needle-punched non-weft carbon cloth integral carbon disc preform is put into a high-temperature heat treatment furnace and is subjected to high-temperature pretreatment at the temperature of 1800 ℃; the needling weft-free carbon cloth integral carbon disc preform is prepared by alternately layering carbon fiber plain cloth and a carbon fiber net tire and then needling in a radial direction;
step two, putting the needled weftless carbon cloth integrated carbon disc preform subjected to high-temperature pretreatment in the step one into a vapor deposition furnace with the diameter phi of 600mm, wherein the furnace charging structure is shown in figure 1, putting the needled weftless carbon cloth integrated carbon disc preform 4 subjected to high-temperature pretreatment into a hearth of the vapor deposition furnace and surrounded by a heating body 2 to form a single material column, the top end of the single material column is provided with a graphite cover plate 1, the bottom of the single material column is provided with a circulating air guide preheating device 5, the bottom of the circulating air guide preheating device 5 is provided with an air inlet pipe 6, and a gasket 3 is laid between the adjacent needled weftless carbon cloth integrated carbon disc preforms 4; the flow rate of the carbon source gas was adjusted to 3.0m3Allowing the carbon to enter a circulating air guide preheating device 5 in the furnace through an air inlet pipe 6 to preheat to 950 ℃, allowing the carbon to flow through the surface of the needle-punched weftless carbon cloth integral carbon disk preform subjected to high-temperature pretreatment in the vapor deposition furnace from bottom to top, and performing isothermal vapor deposition at 950 ℃ for 400 hours to obtain a pyrolytic carbon substrate with a rough layer structure; the mass content of the rough layer structure in the pyrolytic carbon matrix is 65 percent; the carbon source gas is formed by mixing natural gas with the volume percentage of 55% and propylene with the volume percentage of 45%;
step three, carrying out furfuryl ketone resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix obtained in the step two to obtain a resin carbon-containing binary carbon matrix; the mass content of the resin carbon in the binary carbon matrix is 5 percent;
and step four, carrying out high-temperature graphitization treatment on the binary carbon matrix obtained in the step three at the temperature of 2000 ℃ to obtain the binary carbon matrix airplane carbon brake disc.
The carbon source gas in the present embodiment may be a mixture of natural gas other than a combination of natural gas and propylene and one or more of propylene, propane, acetylene, hydrogen, and nitrogen.
Example 2
The embodiment comprises the following steps:
step one, setting the density to be 0.70g/cm3The needle-punched weftless carbon cloth integrated carbon disk preform is put into a high-temperature heat treatment furnace and is subjected to high-temperature pretreatment at the temperature of 2400 ℃; the needling non-weft carbon cloth integral carbon disc preform is prepared by alternately layering carbon fiber twill cloth and carbon fiber net tires and then needling in a radial direction;
step two, putting the needled weftless carbon cloth integrated carbon disk preform subjected to high-temperature pretreatment in the step one into a vapor deposition furnace with the diameter phi of 650mm, putting the needled weftless carbon cloth integrated carbon disk preform 4 subjected to high-temperature pretreatment into a hearth of the vapor deposition furnace and surrounded by a heating body 2 to form a single material column, wherein a graphite cover plate 1 is arranged at the top end of the single material column, a circulating air guide preheating device 5 is arranged at the bottom of the single material column, an air inlet pipe 6 is arranged at the bottom of the circulating air guide preheating device 5, and a gasket 3 is laid between the adjacent needled weftless carbon cloth integrated carbon disk preforms 4; the flow rate of the carbon source gas is adjusted to be 3.0m3Preheating the carbon disc preform to 1100 ℃ by a gas preheating device outside the furnace, flowing the carbon disc preform through the surface of the needle-punched weftless carbon cloth integral carbon disc preform subjected to high-temperature pretreatment in a vapor deposition furnace from bottom to top, and performing isothermal vapor deposition for 120 hours at the temperature of 1100 ℃ to obtain a pyrolytic carbon substrate with a rough layer structure; the mass content of the rough layer structure in the pyrolytic carbon matrix is 50%; the carbon source gas is formed by mixing natural gas with the volume percentage of 75% and propane with the volume percentage of 25%;
step three, carrying out furfuryl ketone resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix obtained in the step two to obtain a resin carbon-containing binary carbon matrix; the mass content of the resin carbon in the binary carbon matrix is 20 percent;
and step four, carrying out high-temperature graphitization treatment on the binary carbon matrix obtained in the step three at the temperature of 2400 ℃ to obtain the binary carbon matrix airplane carbon brake disc.
The carbon source gas in the present embodiment may be a mixture of natural gas other than a combination of natural gas and propane and one or more of propylene, propane, acetylene, hydrogen, and nitrogen.
Example 3
The embodiment comprises the following steps:
step one, setting the density to be 0.65g/cm3The needle-punched non-weft carbon cloth integral carbon disc preform is put into a high-temperature heat treatment furnace and is subjected to high-temperature pretreatment at the temperature of 2000 ℃; the needling weft-free carbon cloth integral carbon disc preform is prepared by alternately layering carbon fiber plain cloth and a carbon fiber net tire and then needling in a radial direction;
step two, putting the needled weftless carbon cloth integrated carbon disk preform subjected to high-temperature pretreatment in the step one into a vapor deposition furnace with the diameter phi of 1400mm, wherein the furnace charging structure is shown in fig. 2 and 3, putting the needled weftless carbon cloth integrated carbon disk preform 4 subjected to high-temperature pretreatment into a hearth surrounded by a heating body 2 of the vapor deposition furnace to form three material columns, the top end of each material column is provided with a graphite cover plate 1, a limited air cylinder 7 is arranged around each material column in a surrounding manner, the bottom of each material column is provided with a circulating air guide preheating device 5, the bottom of each circulating air guide preheating device 5 is provided with an air inlet pipe 6, and a gasket 3 is laid between every two adjacent needled weftless carbon cloth integrated carbon disk preforms 4 in each material column; the flow rate of the carbon source gas is adjusted to 6.0m3Allowing the carbon to enter a circulating air guide preheating device 5 in the furnace through an air inlet pipe 6 to preheat to 1050 ℃, allowing the carbon to flow through the surface of the needle-punched weftless carbon cloth integral carbon disk preform subjected to high-temperature pretreatment in the vapor deposition furnace from bottom to top, and performing isothermal vapor deposition for 300 hours at 1050 ℃ to obtain a pyrolytic carbon substrate with a rough layer structure; the mass content of the rough layer in the pyrolytic carbon matrix is 62%; the carbon source gas is formed by mixing natural gas with the volume percentage of 98% and hydrogen with the volume percentage of 2%;
step three, carrying out furfuryl ketone resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix obtained in the step two to obtain a resin carbon-containing binary carbon matrix; the mass content of the resin carbon in the binary carbon matrix is 8 percent;
and step four, carrying out high-temperature graphitization treatment on the binary carbon matrix obtained in the step three at the temperature of 2300 ℃ to obtain the binary carbon matrix airplane carbon brake disc.
The carbon source gas in the present embodiment may be a mixture of natural gas other than a combination of natural gas and hydrogen and one or more of propylene, propane, acetylene, hydrogen, and nitrogen.
Example 4
The embodiment comprises the following steps:
step one, setting the density to be 0.55g/cm3The needle-punched non-weft carbon cloth integral carbon disc preform is put into a high-temperature heat treatment furnace and is subjected to high-temperature pretreatment at the temperature of 2300 ℃; the needling weftless carbon cloth integral carbon disk preform is prepared by alternately layering carbon fiber twill cloth and carbon fiber net tires and then needling the carbon fiber twill cloth and the carbon fiber net tires in a radial direction;
step two, putting the needled weftless carbon cloth integrated carbon disk preform subjected to high-temperature pretreatment in the step one into a vapor deposition furnace with the diameter phi of 1600mm, wherein the furnace charging structure is shown in fig. 4, putting the needled weftless carbon cloth integrated carbon disk preform 4 subjected to high-temperature pretreatment into a hearth of the vapor deposition furnace and surrounded by a heating body 2 to form seven material columns, the top end of each material column is provided with a graphite cover plate 1, a limited air cylinder 7 is arranged around each material column in a surrounding manner, the bottom of each material column is provided with a circulating air guide preheating device 5, the bottom of each circulating air guide preheating device 5 is provided with an air inlet pipe 6, and a gasket 3 is laid between the adjacent needled weftless carbon cloth integrated carbon disk preforms 4 in each material column; the flow rate of the carbon source gas is adjusted to 12.0m3Allowing the carbon to enter a circulating air guide preheating device 5 in the furnace through an air inlet pipe 6 to preheat to 950 ℃, allowing the carbon to flow through the surface of the needle-punched weftless carbon cloth integral carbon disk preform subjected to high-temperature pretreatment in the vapor deposition furnace from bottom to top, and performing isothermal vapor deposition at 950 ℃ for 400 hours to obtain a pyrolytic carbon substrate with a rough layer structure; the mass content of the rough layer structure in the pyrolytic carbon matrix is 55%; the carbon source gas is formed by mixing 85% of natural gas by volume percentage, 13% of acetylene by volume percentage and 2% of hydrogen by volume percentage;
step three, carrying out furfuryl ketone resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix obtained in the step two to obtain a resin carbon-containing binary carbon matrix; the mass content of the resin carbon in the binary carbon matrix is 15 percent;
and step four, carrying out high-temperature graphitization treatment on the binary carbon matrix obtained in the step three at the temperature of 2300 ℃ to obtain the binary carbon matrix airplane carbon brake disc.
The carbon source gas in this embodiment may be a mixture of natural gas other than natural gas, a combination of acetylene and hydrogen, and one or more of propylene, propane, acetylene, hydrogen, and nitrogen.
The above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention in any way. Any simple modification, change and equivalent changes of the above embodiments according to the technical essence of the invention are still within the protection scope of the technical solution of the invention.
Claims (5)
1. A manufacturing method of a low-cost binary carbon matrix airplane carbon brake disc is characterized by comprising the following steps:
firstly, putting a needled weftless carbon cloth integral carbon disk preform into a high-temperature heat treatment furnace, and carrying out high-temperature pretreatment at the temperature of 1800-2400 ℃;
step two, putting the needled weftless carbon cloth integral carbon disk preform pretreated at high temperature in the step one into a vapor deposition furnace, adjusting the flow of carbon source gas, enabling the carbon source gas to directionally flow through the surface of the needled weftless carbon cloth integral carbon disk preform, and then carrying out isothermal vapor deposition to obtain a pyrolytic carbon matrix with a rough layer structure; the temperature of the isothermal vapor deposition is 950-1100 ℃; the mass content of the rough layer structure in the pyrolytic carbon matrix is 50-65%; the carbon source gas mainly comprises natural gas, and is formed by mixing the natural gas with one or more of propylene, propane and acetylene, wherein the volume percentage of the natural gas in the carbon source gas is 55-98%;
step three, performing resin impregnation-carbonization densification treatment on the pyrolytic carbon matrix obtained in the step two to obtain a resin carbon-containing binary carbon matrix; the mass content of the resin carbon in the binary carbon matrix is 5-20%;
and step four, carrying out high-temperature graphitization treatment on the binary carbon matrix obtained in the step three at the temperature of 2000-2400 ℃ to obtain the binary carbon matrix airplane carbon brake disc.
2. The method for manufacturing a low-cost double-element carbon matrix aircraft carbon brake disc as claimed in claim 1, wherein in the step one, the needle-punched non-weft carbon cloth integrated carbon disc preform is made by carbon fiber plain cloth or twill cloth and carbon fiber net tire which are alternately layered and then subjected to radial needle punching, and the density of the needle-punched non-weft carbon cloth integrated carbon disc preform is 0.5g/cm3～0.7g/cm3。
3. The method for manufacturing a low-cost double-element carbon matrix aircraft carbon brake disc as claimed in claim 1, wherein the manner of loading the needle-punched weftless carbon cloth monolithic carbon disc preform pretreated at high temperature into the vapor deposition furnace in the step one is a single charge column loading furnace or a multi-charge column loading furnace.
4. The method for manufacturing the low-cost dual-element carbon matrix airplane carbon brake disc as claimed in claim 1, wherein in the second step, the carbon source gas is firstly sent into a gas preheating device outside the furnace or a gas circulating preheating device arranged at the bottom inside the furnace for preheating, and then is sent into a vapor deposition furnace for isothermal vapor deposition; the preheating temperature is 950 ℃ to 1100 ℃.
5. The method for manufacturing a low-cost binary carbon matrix aircraft carbon brake disc as claimed in claim 1, wherein the isothermal vapor deposition time in step two is 120-400 h.
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Citations (3)
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|---|---|---|---|---|
| US5093156A (en) * | 1989-07-27 | 1992-03-03 | Nippon Oil Company, Limited | Process for preparing carbon material |
| CN1544825A (en) * | 2003-11-24 | 2004-11-10 | 西安航天复合材料研究所 | Method for manufacturing airplane carbon brake wheel with double element carbon base optimal combination |
| CN101157564A (en) * | 2007-09-13 | 2008-04-09 | 北京航空航天大学 | Method for reinforcing charcoal/charcoal component by charcoal nano-fibre |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5093156A (en) * | 1989-07-27 | 1992-03-03 | Nippon Oil Company, Limited | Process for preparing carbon material |
| CN1544825A (en) * | 2003-11-24 | 2004-11-10 | 西安航天复合材料研究所 | Method for manufacturing airplane carbon brake wheel with double element carbon base optimal combination |
| CN101157564A (en) * | 2007-09-13 | 2008-04-09 | 北京航空航天大学 | Method for reinforcing charcoal/charcoal component by charcoal nano-fibre |
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