A high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material and its preparation method

Abstract

This application relates to a high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material and its preparation method. The composite material includes carbon fiber cloth and a resin paste impregnated on the carbon fiber cloth and cured. An interface modification layer is formed on the surface of the carbon fiber cloth by a modifier selected from one or more of epoxy resin, hexamethyldisilazane, polydopamine, KH550, and boron-zirconium hybrid polysilazane. The resin paste comprises the following components in parts by weight: 25-35 parts of methyl vinyl polysilazane resin, 20-25 parts of reinforcing filler, 1-5 parts of organosilicon modifier, 2.5-5 parts of thickener, 0.01-2.5 parts of curing agent, and 0.1-5 parts of release agent. This application achieves a synergistic improvement in high-temperature resistance, corrosion resistance, anti-coking, and mechanical properties by chemically matching the surface modification layer of the carbon fiber cloth with the polysilazane body in the resin paste, enabling copolymerization and crosslinking during high-temperature ceramization to form a component gradient transition interface.

Description

Technical Field

[0001] This application relates to the petrochemical field, and in particular to a high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material and its preparation method. Background Technology

[0002] In the fields of petroleum refining, coal chemical industry, and fine chemical industry, the internal components of core equipment such as fractionation towers, absorption towers, and stripping towers (including trays, packing, support devices, distributors, etc.) are subjected to harsh conditions of high temperature, strong corrosion, and easy scaling and coking. For example, in scenarios such as acetic acid units, PTA acetic acid dehydration towers, DMC dehydrogenation towers, and vinyl acetate units, the internal components need to withstand high temperatures exceeding 500°C, corrosion from multiple corrosive media such as hydrogen sulfide, sulfur dioxide, hydrogen chloride, organic acids, and strong alkalis, and face the problems of coking, scaling, and erosion wear caused by easily polymerizable components or solid particles in the materials. Currently, to meet the above-mentioned extreme operating conditions, the materials widely used for tower internal components in industry are mainly special metals and their alloys, such as zirconium, titanium, Hastelloy, duplex stainless steel, and Monel alloy.

[0003] However, the aforementioned special metal materials face significant technical bottlenecks in practical applications. Firstly, their corrosion resistance is a weakness: zirconium performs excellently in reducing media but is sensitive to fluoride ions and some chloride media; titanium reacts violently in hydrofluoric acid and strong oxidizing media; Hastelloy lacks stability in high-temperature fluoride environments; duplex stainless steel exhibits a mid-temperature brittleness zone, and its service temperature is typically strictly limited to below 250℃; Monel alloys have poor corrosion resistance in oxidizing acids. Secondly, the high density and cost of these materials result in a large self-weight of the tower internals, increasing the tower's load and significantly raising equipment investment and maintenance costs. Furthermore, the limited surface hardness of the metal materials makes them prone to wear under high-speed gas-liquid erosion or solid particle impact, further exacerbating localized corrosion. The metal surfaces also readily adsorb organic matter or catalyze coking reactions, causing scaling and blockage of the tower internals. Although surface modification technologies such as thermal spray ceramic coatings can be used, the bonding strength between the coating and the substrate, resistance to thermal cycling and spalling, and the coating's own density remain technical bottlenecks, making it susceptible to failure due to localized defects. On the other hand, although some non-metallic materials such as engineering ceramics (such as alumina, silicon carbide, silicon nitride, etc.) have excellent temperature resistance and chemical corrosion resistance, their inherent high brittleness, difficulty in processing, poor thermal shock resistance, and poor compatibility with metal tower bodies seriously restrict their large-scale application in the internal components of large towers.

[0004] In summary, current technologies lack a tower internals material that simultaneously possesses excellent high-temperature mechanical properties, long-term resistance to corrosion in complex media, good resistance to coking and erosion wear, as well as machinability, lightweight design, and overall economic efficiency. Therefore, developing a novel high-temperature resistant, corrosion-resistant, and coking-resistant lightweight high-strength composite material to overcome the current technological limitations of metallic and non-metallic materials and meet the evolving needs of modern petrochemical industries for higher parameters, longer operating cycles, and safer and more stable operation has become an urgent technical problem to be solved in this field. Summary of the Invention

[0005] In order to achieve a comprehensive improvement in the performance of petrochemical tower internals under high temperature, strong corrosion and easy coking conditions, including high temperature resistance, corrosion resistance, coking resistance, lightweight and high strength, this application provides a high temperature resistant, corrosion resistant, coking resistant, lightweight and high strength carbon fiber ceramic matrix composite material and its preparation method.

[0006] In a first aspect, this application provides a high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material, which adopts the following technical solution: A high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material, comprising carbon fiber cloth and a resin paste impregnated on the carbon fiber cloth and cured; the surface of the carbon fiber cloth is modified by a modifier to form an interface modification layer, the modifier being selected from one or more of epoxy resin, hexamethyldisilazane, polydopamine, KH550, and boron-zirconium hybrid polysilazane; the resin paste comprises the following components in parts by weight: 25-35 parts of methyl vinyl polysilazane resin, 20-25 parts of reinforcing filler, 1-5 parts of organosilicon modifier, 2.5-5 parts of thickener, 0.01-2.5 parts of curing agent, and 0.1-5 parts of release agent.

[0007] The inventors discovered that by using a chemically matched interface modification layer and a polysilazane alkyl body resin paste, and by anchoring modifiers containing active functional groups (such as KH550 and boron-zirconium hybrid polysilazane) to the carbon fiber surface, the silicon-nitrogen bonds and silicon-hydrogen bonds in the modification layer and the methyl vinyl polysilazane in the resin paste undergo in-situ copolymerization and crosslinking during high-temperature ceramization, forming a compositional gradient transition interface from the fiber surface to the matrix. This interface, combined with the micro-nano particles of reinforcing filler and the multi-level reinforcement-barrier structure constructed by carbon fiber cloth, unexpectedly achieved a synergistic improvement in high temperature resistance, corrosion resistance, and coking resistance while maintaining lightweight and high strength.

[0008] Specifically, during high-temperature service, the composite material, due to the homologous copolymerization of the interface modification layer and the matrix resin, has the same ceramization temperature range and a gradually changing coefficient of thermal expansion, avoiding microcracks and delamination caused by thermal mismatch in traditional heterogeneous interfaces. Even if local micro-damage occurs in the matrix, the gradually changing composition structure of the gradient transition layer can effectively transfer the load and prevent crack propagation, thus maintaining excellent mechanical stability at high temperatures and achieving high-temperature resistance.

[0009] The composite material also benefits from the combination of hydrophobic ceramic phases (such as B-Zr-Si-CN ceramics converted from boron-zirconium hybrid polysilazane) in the interface modification layer with the dense resin paste ceramic matrix, forming a low-surface-energy, highly dense inert barrier on the material surface. This barrier, on the one hand, blocks the penetration path of corrosive media (H⁺, OH⁻, Cl⁻, etc.) into the material interior, and on the other hand, makes it difficult for coking precursors to be adsorbed and deposited on the surface, unexpectedly achieving excellent anti-corrosion and anti-coking properties simultaneously. Even with slight surface wear, the internal gradient interface layer remains intact, preventing the diffusion of corrosive media along the fiber-matrix interface, thus eliminating interface corrosion and coking adhesion at the structural root.

[0010] Furthermore, carbon fiber fabric forms a continuous three-dimensional reinforcing skeleton in the composite material, endowing the material with extremely high specific strength and specific modulus, achieving lightweight and high strength. On the other hand, the fibers and the reinforcing fillers (silicon carbide, silicon nitride, alumina, and other micro powders) in the resin paste constitute a micron-nano multi-level interface. When subjected to external forces, the micro-nano fillers absorb fracture energy through pinning effect and microcrack deflection mechanism, while the carbon fibers bear the main load through pull-out work and bridging effect. The synergy between the two enables the material to maintain high strength while also possessing good impact resistance. During the ceramization process, the reinforcing fillers also inhibit matrix shrinkage and reduce porosity through in-situ reaction, further improving density and strength retention.

[0011] This application achieves a synergistic improvement in comprehensive performance, including high temperature resistance, corrosion resistance, coking resistance, lightweight, and high strength, by matching the chemical structure of the carbon fiber surface interface modification layer with the polysiloxane alkyl ester resin paste, combined with the physical reinforcement-barrier coupling network of carbon fiber cloth and micro / nano fillers, without the need for complex processes and while maintaining lightweight and high strength.

[0012] In one specific implementation, the modifier comprises KH550 and boron-zirconium hybrid polysilazane, wherein the weight ratio of KH550 to boron-zirconium hybrid polysilazane is 1:(2-4).

[0013] The inventors discovered that when KH550 and boron-zirconium hybrid polysilazane are compounded in the above-mentioned ratio for carbon fiber surface modification, a significant synergistic effect is achieved. KH550 forms silanols through hydrolysis, which then undergo a condensation reaction with the hydroxyl groups on the carbon fiber surface, anchoring the amino and silane segments to the carbon fiber surface. The boron-zirconium hybrid polysilazane, with its abundant silicon-hydrogen bonds and boron-zirconium hybrid structure, crosslinks with the amino groups of KH550 to form a covalently bonded composite interface layer. Furthermore, the polysilazane structure in its molecular chain is highly compatible with methyl vinyl polysilazane resin paste, enabling simultaneous crosslinking, cyclization, and inorganic transformation during high-temperature ceramization. Simultaneously, the silane segments of KH550 significantly improve the initial wettability of the carbon fiber and resin paste, preventing dry spots or bubbles during layup.

[0014] Extensive testing revealed that when the weight ratio of the two components is controlled within the aforementioned compounding range, the proportion of KH550 in the interface layer is sufficient to achieve adequate activation and initial bonding of the fiber surface, without causing porosity due to the high-temperature decomposition of excessive KH550. The proportion of boron-zirconium hybrid polysilazane ensures that the interface layer forms a continuous and dense B-Zr-Si-CN ceramic transition phase after ceramization. This transition phase forms a chemical bond with the carbon fiber surface and a compositional gradient with the outer polysilazane ceramic matrix, perfectly eliminating the abrupt change in the thermal expansion coefficient of traditional heterogeneous interfaces. Compared to situations where using KH550 alone leads to interface failure due to high-temperature decomposition, or where using boron-zirconium hybrid polysilazane alone results in poor initial wettability and numerous interface defects, the compounding scheme employed in this application unexpectedly achieves a synergistic leap in high-temperature stability, corrosion resistance, and anti-coking properties.

[0015] In one specific implementation, the organosilicon modifier is selected from one or more of polyborosiloxane resin, methylphenyl vinyl silicone oil, silicone resin, KH550, hexamethyldisilazane, boron-zirconium hybrid silicone resin, and boron-zirconium hybrid polysilazane; preferably, the organosilicon modifier is KH550.

[0016] By employing the above technical solutions, organosilicon modifiers play multiple chemical bonding roles in resin pastes. Taking KH550 as an example: First, the triethoxysilane groups in the KH550 molecule are pre-hydrolyzed in the system to generate silanols. Silanols can undergo condensation reactions with the hydroxyl groups on the surface of reinforcing fillers (such as silicon carbide, silicon nitride, alumina, etc.) to form Si-O-filler covalent bonds, thereby chemically anchoring the amino and siloxane segments to the filler surface, significantly improving the interfacial compatibility and stress transfer efficiency between the filler and the resin matrix. Second, the amino groups in KH550 undergo addition reactions with the vinyl groups in the methyl vinyl polysilazane resin molecular chains or undergo ammonolysis reactions with the silane bonds, thereby forming effective chemical crosslinking points, grafting KH550 onto the polysilazane molecular chains in a covalent manner. This grafting structure increases the crosslinking density of the resin system, improving the high-temperature dimensional stability of the preform after hot pressing and curing; on the other hand, the introduced siloxane segments reduce the surface tension of the resin paste, improving its wettability and layup uniformity of the carbon fiber cloth. In addition, when other boron-zirconium hybrid silicone resins or polysilazanes are selected as organosilicon modifiers, the BO, Zr-O or Si-N bonds in their molecules can also copolymerize or coordinate crosslink with polysilazane resins to form an organic-inorganic hybrid network with higher heat resistance.

[0017] Therefore, this application constructs a multi-level interfacial bonding system of filler-matrix-reinforcing fiber from the inside of the resin paste through the chemical grafting and cross-linking effect of organosilicon modifier. This system forms an internal and external synergy with the interfacial modification layer on the surface of carbon fiber cloth, jointly endowing the composite material with excellent comprehensive performance under high temperature, strong corrosion and easy coking conditions.

[0018] In one specific implementation, the reinforcing filler is selected from one or more of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder, and boron nitride micro powder; preferably, the reinforcing filler includes silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder, and boron nitride micro powder, and the weight ratio of the silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder, and boron nitride micro powder is (6-10):(3-7):(2-4):(2-4):1.

[0019] The inventors discovered that when five micro powders—silicon carbide, silicon nitride, alumina, zirconium oxide, and boron nitride—are combined as reinforcing fillers, a significant synergistic effect is generated among the components.

[0020] Among them, silicon carbide and silicon nitride micropowders possess high hardness, high thermal conductivity, and excellent chemical inertness. During the pyrolysis and ceramization process of polysilazane, they act as physical fillers to inhibit matrix shrinkage and reduce cracks. Furthermore, the silanol groups on their surfaces can form interfacial bonds with the SiO2 phase generated by the decomposition of polysilazane, forming a dense SiC / Si3N4-SiO2 composite ceramic framework, significantly improving the material's high-temperature strength and thermal shock resistance. Alumina micropowder can react with amorphous SiO2 derived from polysilazane at high temperatures to generate mullite or aluminosilicate glass, filling micropores and strengthening the matrix. Simultaneously, alumina itself exhibits good corrosion resistance in acidic media, further enhancing the composite material's acid corrosion barrier. Zirconia micropowder utilizes its unique martensitic transformation toughening mechanism. When the matrix is ​​subjected to thermal stress or external impact, the tetragonal zirconia transforms into a monoclinic phase accompanied by volume expansion, absorbing fracture energy and blunting crack tips, thereby significantly improving the fracture toughness of the composite material and compensating for the inherent brittleness of the ceramic matrix. Boron nitride micro powder has a layered hexagonal structure. As a solid lubricant, it can reduce the surface energy of materials and reduce the adhesion of coking products. At the same time, its good thermal conductivity and chemical stability help to alleviate local thermal stress at high temperatures and prevent matrix cracking.

[0021] By blending the above five fillers in a ratio of silicon carbide:silicon nitride:alumina:zirconia:boron nitride = (6-10):(3-7):(2-4):(2-4):1, complementary matching of each component in terms of particle size distribution, surface chemical activity, and thermophysical properties can be achieved. Silicon carbide and silicon nitride constitute the main phase of a high-strength ceramic framework, alumina and zirconia synergistically fill and densify the structure and introduce a toughening mechanism, and boron nitride provides a lubricating and anti-coking surface. Beyond this range, if the proportion of silicon carbide or silicon nitride is too low, the framework strength will be insufficient; if it is too high, the density will decrease. Too much zirconia will lead to phase transformation stress concentration, while too little will result in an insignificant toughening effect. Excessive boron nitride will reduce the interfacial bonding strength. This specific blending ratio allows the filler to form a multi-synergistic structure of "framework reinforcement - micropore filling - phase transformation toughening - surface lubrication" in the ceramicized matrix, achieving a balance of high density, high flexural strength, high impact toughness, and excellent anti-coking performance, significantly superior to single-filler solutions.

[0022] In one specific implementation scheme, the thickener is selected from one or more of polyamide wax, organobentonite, precipitated silica, and fumed silica; preferably, the thickener is fumed silica.

[0023] Thickeners in resin pastes primarily function as rheological regulators and prevent sedimentation. Taking fumed silica (French silica) as an example, it possesses nanoscale particle size, extremely high specific surface area, and abundant silanol groups. During mechanical stirring and dispersion, the silanol groups on the surface of the fumed silica form a hydrogen bond network with polysilazane molecules and organosilicon modifiers in the resin paste, thereby constructing a three-dimensional thixotropic structure within the resin paste. This structure endows the resin paste with significant shear-thinning properties: at high shear rates (such as during stirring or coating), the hydrogen bond network is disrupted, the viscosity of the resin paste decreases sharply, and its fluidity increases, facilitating the wetting of carbon fiber cloth and filling the voids between reinforcing fillers; when the shear force is removed (such as during layup settling or the initial stage of hot pressing), the hydrogen bond network rapidly recovers, the viscosity of the resin paste rebounds, effectively preventing sedimentation of the reinforcing fillers due to density differences and ensuring uniform component distribution. Simultaneously, the nano-effect of fumed silica can also act as a micro-filler, further reducing the porosity of the cured preform.

[0024] Compared to polyamide waxes or organobentonite, fumed silica exhibits superior thermal stability. It can be converted into silica during high-temperature ceramization, is compatible with the matrix, and does not introduce volatile organic compounds, thus avoiding pores or impurities caused by thickener decomposition during pyrolysis. Furthermore, its surface silanol groups can undergo condensation reactions with the silanium-hydrogen bonds of polysilazanes or the hydroxyl groups of reinforcing fillers, forming chemical bonds and enhancing the overall cohesive strength of the resin paste.

[0025] Therefore, this application selects fumed silica as a thickener, which not only ensures the excellent processability of the resin paste, but also further improves the density of the composite material after curing and the interfacial bonding quality after high-temperature ceramization.

[0026] In one specific implementation, the curing agent is selected from one or more of N,N-dimethylbenzylamine, 1,1-di-tert-butylperoxycyclohexane, dicumyl peroxide, and (2,5-dimethyl-2,5-di-tert-butylperoxy)hexane; preferably, the curing agent is dicumyl peroxide.

[0027] The curing agent initiates the cross-linking and curing of methyl vinyl polysilazane resin during the hot pressing stage, transforming linear or oligomeric resin molecules into a three-dimensional network structure, thereby forming a preform with certain mechanical strength and dimensional stability, laying the foundation for subsequent high-temperature ceramicization.

[0028] Taking dicumyl peroxide as a preferred example, it homolytically cleaves under heating conditions (decomposition half-life temperature is approximately 120~140℃) to generate highly reactive cumyloxy radicals. These radicals can abstract α-hydrogen from the vinyl groups in polysilazane molecules or directly undergo addition reactions with silane bonds to generate silicon radicals or carbon radicals. Subsequently, these radicals couple with each other or undergo chain addition with the vinyl groups of another molecule, gradually forming crosslinking points and ultimately constructing a dense three-dimensional network structure. As a radical initiator, dicumyl peroxide has advantages such as moderate decomposition temperature, suitable half-life, no induction period, fewer byproducts (isocumyl alcohol, acetophenone, etc.) and easy volatilization, which are highly compatible with the temperature windows of the first stage (120~140℃) and the second stage (150~180℃) in the three-stage hot pressing molding process of this invention. Compared to amine curing agents (such as N,N-dimethylbenzylamine), dicumyl peroxide does not introduce alkaline impurities, avoiding excessive crosslinking or bubble generation of polysilazane during high-temperature ceramization. Compared to peroxy ketal curing agents, its thermal decomposition behavior is milder, less likely to generate violent exothermic reactions leading to internal defects in the preform. Simultaneously, dicumyl peroxide exhibits good compatibility with other components in the resin paste (such as organosilicon modifiers and thickeners), without affecting the storage stability and layup operation of the resin paste. Through the aforementioned free radical crosslinking mechanism, the preform after hot-press curing possesses sufficient green strength, maintaining its shape integrity during demolding and transfer. Furthermore, the silicon-carbon-nitrogen bonds in the crosslinking network act as "inorganic precursors" during subsequent ceramization at 1400–1750℃, facilitating the formation of a uniform, dense, and crack-free SiCN ceramic matrix.

[0029] Therefore, this application achieves a seamless integration of hot-press crosslinking and high-temperature ceramicization processes by preferentially using dicumyl peroxide as a curing agent, thus ensuring the overall density and mechanical properties of the composite material.

[0030] In one specific implementation, the release agent is selected from one or more of calcium stearate, magnesium stearate, and zinc stearate; the release agent is zinc stearate.

[0031] During the hot pressing process, the release agent forms a dense isolation film between the mold and the resin paste, effectively reducing the adhesion between the composite preform and the mold surface, ensuring smooth demolding after molding, and avoiding cracking or surface damage of the preform due to demolding difficulties.

[0032] Taking zinc stearate as an example, its molecule is composed of long-chain hydrophobic alkyl groups and metal-philic zinc ions. During the first stage of hot pressing, when the temperature rises to 120-140°C, zinc stearate gradually melts and spreads uniformly. Its polar zinc carboxylate end undergoes physical adsorption or weak chemical coordination with the metal surface of the mold (iron, chromium, etc.), while the non-polar long-chain alkyl group faces the resin paste side, thus forming a lubricating isolation layer on the mold surface. This isolation layer significantly reduces demolding resistance and prevents active components in the resin paste (such as polysilazane, fillers, etc.) from directly contacting the mold and causing chemical adhesion. Compared to calcium stearate and magnesium stearate, zinc stearate has a lower melting point (approximately 120-130°C) and superior film uniformity. In the three-stage hot pressing process of this application, it can quickly complete melting and spreading in the first stage and will not decompose and volatilize prematurely in the second stage (150-180°C) and the third stage (190-210°C), continuously providing an effective demolding effect. Furthermore, the thermal decomposition temperature of zinc stearate is above 300°C, while the highest temperature of the hot pressing molding of this invention is only around 210°C. Therefore, the release agent does not decompose during the molding stage, avoiding the generation of volatile gases that could lead to porosity inside the preform. During the subsequent high-temperature ceramization process (1400~1750°C), the remaining zinc stearate completely decomposes into zinc oxide, carbon dioxide, and water vapor. The zinc oxide can react with silica or alumina in the matrix to form zinc spinel or zinc silicate, participating in the formation of the ceramic phase without introducing impurities or reducing material properties. The addition amount is controlled within the range of 0.1~5 parts, which ensures sufficient release effect without causing the release agent to agglomerate in the resin paste or affect the interfacial bonding strength due to excessive amount. Therefore, by preferentially using zinc stearate as the release agent, this application ensures high yield and feasibility of large-scale compression molding without negatively impacting the final performance of the composite material, achieving a balance between processability and material properties.

[0033] Secondly, this application provides a method for preparing a high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material, which adopts the following technical solution: A method for preparing a high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material includes the following steps: S1. Mix and disperse methyl vinyl polysilazane resin, reinforcing filler and organosilicon modifier to obtain a mixed resin liquid; S2. Add thickener, curing agent and release agent to the mixed resin liquid obtained in step S1, and disperse to obtain resin paste; S3. The carbon fiber cloth is subjected to desizing and oxidation treatment and surface modification treatment with a modifier in sequence to form an interface modification layer on the surface of the carbon fiber cloth. S4. The resin paste obtained in step S2 and the carbon fiber cloth obtained in step S3 are alternately layered and laid, and the preform is obtained by hot pressing in a three-stage process. S5. The preform obtained in step S4 is ceramicized under inert gas protection to obtain the composite material.

[0034] The composite material prepared by the above steps exhibits in-situ copolymerization and crosslinking between the interface-modified layer on the carbon fiber cloth surface and the polysiloxane alkyl body in the resin paste during high-temperature ceramization. This forms a compositional gradient transition interface from the fiber surface to the matrix, effectively eliminating the thermal expansion coefficient mismatch and microcrack tendency of traditional heterogeneous interfaces. Simultaneously, the reinforcing filler constructs a multi-synergistic structure within the ceramized matrix, encompassing "skeleton reinforcement, micropore filling, phase transformation toughening, and surface lubrication." Thickeners and curing agents ensure the process stability and crosslinking density of the resin paste, while release agents guarantee a high yield of molded products. Thus, while maintaining lightweight and high strength, the composite material unexpectedly achieves a synergistic improvement in high-temperature resistance, corrosion resistance, and coking resistance, enabling long-term stable service under the high-temperature, highly corrosive, and easily coking conditions of petrochemical tower internals.

[0035] In a specific feasible implementation, the three-stage process of hot pressing in step S3 includes: the first stage: heating from room temperature to 120-140℃, pressure of 10-15MPa, and holding pressure for 20-30 minutes; the second stage: heating to 150-180℃, pressure of 10-15MPa, and holding pressure for 20-30 minutes; and the third stage: heating to 190℃-210℃, pressure of 10-15MPa, and holding temperature for 25-35 minutes.

[0036] The three-stage hot pressing process is matched with the decomposition behavior of the curing agent in the resin paste and the crosslinking characteristics of the polysilazane resin, achieving precise control over the crosslinking reaction rate, volatile matter emission, and internal stress release.

[0037] Specifically, during the first stage of heating to 120-140℃ and holding under pressure for 20-30 minutes, the curing agent (such as dicumyl peroxide) undergoes homogeneous cracking upon heating, generating free radicals that initiate a preliminary cross-linking reaction between the vinyl groups and silane bonds in the polysilazane resin. The temperature during this stage is controlled within a suitable range corresponding to the decomposition half-life of the curing agent, ensuring the cross-linking reaction proceeds at a mild and controllable rate, avoiding localized overheating or the generation of large amounts of volatiles (such as low-molecular-weight byproducts and residual solvents) due to excessive reaction. Simultaneously, the pressure holding operation allows the resin paste to flow fully, filling the gaps in the carbon fiber cloth, and promotes the discharge of air bubbles and low-molecular-weight volatiles from the system under conditions where the resin viscosity is still relatively low, reducing the porosity inside the preform.

[0038] During the second stage of heating to 150-180℃ and holding under pressure for 20-30 minutes, the crosslinking reaction enters the deep curing stage. As the temperature increases, the crosslinking density of the resin system significantly increases, forming a more complete three-dimensional network structure. The pressure holding operation in this stage serves two purposes: firstly, to maintain pressure and suppress microcracks caused by crosslinking shrinkage; and secondly, to ensure that the remaining small amount of volatile matter continues to escape. Simultaneously, this temperature window further promotes the grafting reaction between the organosilicon modifier and the polysilazane, and enhances the chemical bonding between the filler surface and the resin matrix, thereby strengthening the interfacial adhesion.

[0039] During the third stage of heating to 190-210℃ and holding for 25-35 minutes, the preform enters the post-curing stage. At this temperature, unreacted active groups in the resin system (such as residual vinyl groups, silane bonds, or amino groups) are fully consumed, and the cross-linking network tends to be complete. The heat preservation treatment ensures a uniform temperature distribution inside the preform, eliminates internal stress caused by uneven curing, and prevents warping or cracking after demolding. Simultaneously, the high cross-linking density preform formed in this stage exhibits high green strength and high-temperature dimensional stability, enabling it to withstand subsequent demolding and mechanical handling during transfer to the atmosphere oven.

[0040] If a one-stage hot-pressing process with direct heating to 200℃ is used, the cross-linking reaction may be too rapid, leading to insufficient volatile matter to escape and resulting in porosity defects, or the preform may crack due to internal stress concentration. If the heat preservation time is too long or the temperature is too high, it may cause premature pyrolysis of the resin and destruction of the cross-linking network.

[0041] The three-stage hot pressing molding process described in this application achieves a gradual control of the crosslinking reaction from "slow initiation - fast growth - complete post-curing" by controlling the temperature and pressure in stages. While ensuring the high density and defect-free nature of the preform, it provides a precursor with uniform structure and excellent mechanical properties for subsequent high-temperature ceramization at 1400-1750℃, thereby ensuring that the final composite material has excellent comprehensive performance.

[0042] In summary, this application includes at least one of the following beneficial technical effects: 1. This application adopts a chemical structure matching design between the carbon fiber cloth surface interface modification layer and the methyl vinyl polysilazane alkyl body in the resin paste, so that the two undergo in-situ copolymerization and cross-linking during the high-temperature ceramicization process, forming a composition gradient transition interface. This effectively eliminates microcracks and interface delamination caused by the mismatch of thermal expansion coefficients, and unexpectedly achieves a synergistic improvement in high temperature resistance, corrosion resistance, and anti-coking performance. The composite material maintains excellent mechanical stability after high-temperature treatment at 1000℃, and its appearance remains intact and its weight loss rate is extremely low after long-term immersion in strong acid and strong alkali media. Moreover, the low surface energy characteristics of the surface significantly inhibit coking adhesion.

[0043] 2. This application uses five micro powders—silicon carbide, silicon nitride, alumina, zirconium oxide, and boron nitride—mixed in a specific weight ratio as reinforcing fillers to construct a multi-synergistic structure of "skeleton reinforcement, micropore filling, phase transformation toughening, and surface lubrication" in a ceramic matrix. This significantly improves the density, flexural strength, impact toughness, and coking resistance of the composite material, with an apparent porosity of less than 3%. This overcomes the technical challenge of achieving both high strength and high toughness with a single filler or simple mixing.

[0044] 3. This application employs a three-stage hot-pressing molding process, which matches the decomposition behavior of the curing agent in the resin paste and the crosslinking characteristics of polysilazane. This achieves a gradual control of the crosslinking reaction from "slow initiation to rapid growth to complete post-curing," effectively eliminating volatiles, releasing internal stress, and avoiding pore and crack defects. This ensures the high density and structural uniformity of the preform, providing an excellent precursor for subsequent high-temperature ceramization, thereby ensuring that the final composite material has stable and reliable comprehensive performance. Detailed Implementation

[0045] The present application will be further described in detail below with reference to embodiments and comparative examples: Some of the raw materials used in the examples and comparative examples: Methyl vinyl polysilazane ceramic resin (model: ANTICORO-M10, from Shanghai Hanfu Industrial Development Co., Ltd.). Silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder, each with a particle size of 10μm, were all purchased from Suzhou Sailon Nano New Materials Industry Co., Ltd. KH550, namely γ-aminopropyltriethoxysilane, CAS: 919-30-2; Fumed silica, model: AEROSIL R812S, brand: Evonik, Germany; Carbon fiber cloth, single layer thickness 1.5mm, model: T300, purchased from Shanghai Lishuo Composite Materials Technology Co., Ltd.

[0046] Unless otherwise specified, all raw materials used in the examples and comparative examples are commercially available products.

[0047] Preparation Example 1 The preparation of boron-zirconium hybrid polysilazane is as follows: Ten parts by weight of zirconium tetrachloride were added to a three-necked flask equipped with a stirrer, a constant pressure funnel, and a distillation apparatus. The flask was evacuated and purged with dry nitrogen three times, and the reactor was pre-cooled to -15°C. Under the protection of dry nitrogen, 8.8 parts by weight of boron trichloride and 10.2 parts by weight of trichlorosilane were dissolved in anhydrous n-hexane and injected into the three-necked flask. Then, 117.3 parts by weight of heptamethyldisilazane were placed in a constant pressure funnel and added dropwise to the three-necked flask while stirring. After the addition was complete, the reactor was heated to 270°C at a heating rate of 0.5°C / min and polymerized at this temperature for 10 hours. After the reaction was completed, the reactor temperature was lowered to 120°C and vacuum distilled to remove low molecular weight fractions. The mixture was then cooled to room temperature to obtain boron-zirconium hybrid polysilazane. Example Example 1

[0048] The composite material is prepared as follows: S1. Add 30 parts by weight of methyl vinyl polysilazane resin, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) and 2 parts by weight of KH550 into a high-speed disperser and disperse by mechanical stirring at 2000 rpm for 2 hours to obtain a uniform mixed resin liquid. S2. Add 3 parts by weight of fumed silica, 0.5 parts by weight of dicumyl peroxide and 0.5 parts by weight of zinc stearate to the mixed resin liquid obtained in step S1, and continue to disperse at a high speed of 3000 rpm for 1.5 hours to obtain a resin paste with good thixotropy and leveling properties. S3. First, desizing and oxidizing the carbon fiber cloth: immerse it in acetone at 70°C for 36 hours under reflux, rinse it with deionized water until neutral, and vacuum dry it at 80°C for 2 hours; then place it in a muffle furnace and oxidize it at 450°C at 3°C / min under air atmosphere for 45 minutes, and cool it with the furnace; then ultrasonically clean it with deionized water and anhydrous ethanol for 20 minutes in sequence, and dry it at 80°C for 2 hours. Then, surface modification treatment is carried out: the desized and oxidized carbon fiber cloth is immersed in a modifier solution (the modifier is a compound of KH550 and boron zirconium hybrid polysilazane, with a weight ratio of 1:3, anhydrous ethanol as solvent, and a total mass fraction of 5% of the modifier), immersed for 20 minutes, and then dried at 100℃ to form an interface modification layer on the surface of the carbon fiber cloth. S4. Using the hand lay-up method, the resin paste obtained in step S2 and the carbon fiber cloth obtained in step S3 are alternately layered and laid (a total of 8 layers of carbon fiber cloth are laid, and the resin paste is evenly coated between each layer), and then dried in a vacuum oven at 60°C for 2 hours. The dried prepreg is placed into a hot press mold and subjected to three-stage hot pressing: First stage: Increase from room temperature to 130℃, pressure 12MPa, and maintain pressure for 25 minutes; Second stage: Heat to 165℃, pressure 12MPa, hold pressure for 25 minutes; Third stage: Heat to 200℃, pressure 12MPa, hold for 30 minutes; After naturally cooling to room temperature, demold to obtain the preform; S5. Place the preform obtained in step S4 in a furnace under a high-purity argon atmosphere, raise the temperature to 1500℃ at a rate of 5℃ / min, hold for 120 minutes, and maintain an argon flow rate of 50mL / min throughout the process. After pyrolysis, cool the preform in the furnace to below 200℃ and remove it to obtain the composite material. Example 2

[0049] The difference between Example 2 and Example 1 is only that in step S3 of Example 2, the modifier solution (the modifier is a compound combination of KH550 and the boron-zirconium hybrid polysilazane prepared in Preparation Example 1, with a weight ratio of 1:3, using anhydrous ethanol as solvent, and a total mass fraction of 5% modifier) ​​is replaced with the modifier solution (the modifier is KH550, using anhydrous ethanol as solvent, and a total mass fraction of 5% modifier). Example 3

[0050] The difference between Example 3 and Example 1 is only that in step S3 of Example 3, the modifier solution (the modifier is a compound combination of KH550 and the boron-zirconium hybrid polysilazane prepared in Preparation Example 1, with a weight ratio of 1:3, using anhydrous ethanol as solvent, and a total mass fraction of 5% modifier) ​​is replaced with the modifier solution (the modifier is a compound combination of boron-zirconium hybrid polysilazane prepared in Preparation Example 1, using anhydrous ethanol as solvent, and a total mass fraction of 5% modifier). Example 4

[0051] The difference between Example 4 and Example 1 is only that in step S3 of Example 4, the modifier solution (the modifier is a compound combination of KH550 and the boron-zirconium hybrid polysilazane prepared in Preparation Example 1, with a weight ratio of 1:3, using anhydrous ethanol as solvent, and the total mass fraction of the modifier is 5%) is replaced with the modifier solution (the modifier is a compound combination of KH550 and the boron-zirconium hybrid polysilazane prepared in Preparation Example 1, with a weight ratio of 1:1, using anhydrous ethanol as solvent, and the total mass fraction of the modifier is 5%). Example 5

[0052] The difference between Example 5 and Example 1 is only that in step S3 of Example 5, the modifier solution (the modifier is a compound combination of KH550 and the boron-zirconium hybrid polysilazane prepared in Preparation Example 1, with a weight ratio of 1:3, using anhydrous ethanol as solvent, and the total mass fraction of the modifier is 5%) is replaced with the modifier solution (the modifier is a compound combination of KH550 and the boron-zirconium hybrid polysilazane prepared in Preparation Example 1, with a weight ratio of 1:5, using anhydrous ethanol as solvent, and the total mass fraction of the modifier is 5%). Example 6

[0053] The difference between Example 6 and Example 1 is that in step S1 of Example 6, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) is replaced with 22 parts by weight of silicon carbide micro powder. Example 7

[0054] The difference between Example 7 and Example 1 is that in step S1 of Example 7, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) is replaced with 22 parts by weight of silicon nitride micro powder. Example 8

[0055] The difference between Example 8 and Example 1 is that in step S1 of Example 8, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) is replaced with 22 parts by weight of alumina micro powder. Example 9

[0056] The difference between Example 9 and Example 1 is that in step S1 of Example 9, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) is replaced with 22 parts by weight of zirconium oxide micro powder. Example 10

[0057] The difference between Example 10 and Example 1 is that in step S1 of Example 10, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) is replaced with 22 parts by weight of boron nitride micro powder.

[0058] Comparative Example 1 The only difference between Comparative Example 1 and Example 1 is that in step S3 of Comparative Example 1, the carbon fiber cloth does not undergo desizing oxidation treatment and surface modification treatment with a modifier. Its preparation steps are as follows: S1. Add 30 parts by weight of methyl vinyl polysilazane resin, 22 parts by weight of reinforcing filler (the reinforcing filler is composed of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder in a weight ratio of 8:5:3:3:1) and 2 parts by weight of KH550 into a high-speed disperser and disperse by mechanical stirring at 2000 rpm for 2 hours to obtain a uniform mixed resin liquid. S2. Add 3 parts by weight of fumed silica, 0.5 parts by weight of dicumyl peroxide and 0.5 parts by weight of zinc stearate to the mixed resin liquid obtained in step S1, and continue to disperse at a high speed of 3000 rpm for 1.5 hours to obtain a resin paste with good thixotropy and leveling properties. S3. Using the hand lay-up method, the resin paste obtained in step S2 is alternately layered with carbon fiber cloth (a total of 8 layers of carbon fiber cloth are laid, with resin paste evenly coated between each layer), and then dried in a vacuum oven at 60°C for 2 hours. The dried prepreg is placed into a hot press mold and subjected to three-stage hot pressing: First stage: Increase from room temperature to 130℃, pressure 12MPa, and maintain pressure for 25 minutes; Second stage: Heat to 165℃, pressure 12MPa, hold pressure for 25 minutes; Third stage: Heat to 200℃, pressure 12MPa, hold for 30 minutes; After naturally cooling to room temperature, demold to obtain the preform; S4. Place the preform obtained in step S4 in a furnace under a high-purity argon atmosphere, raise the temperature to 1500℃ at a rate of 5℃ / min, hold for 120 minutes, and maintain an argon flow rate of 50mL / min throughout the process. After pyrolysis, cool the preform in the furnace to below 200℃ and remove it to obtain the composite material.

[0059] Comparative Example 2 The only difference between Comparative Example 2 and Example 1 is that in step S4 of Comparative Example 2, the dried prepreg is placed into a hot press mold for three-stage hot pressing: First stage: Increase from room temperature to 130℃, pressure 12MPa, and maintain pressure for 25 minutes; Second stage: Heat to 165℃, pressure 12MPa, hold pressure for 25 minutes; Third stage: Heat to 200℃, pressure 12MPa, hold for 30 minutes; After naturally cooling to room temperature, demold to obtain the preform; Replace with, The dried prepreg is placed in a hot press mold, heated directly from room temperature to 200°C, pressure 12MPa, held for 80 minutes, and then naturally cooled to room temperature before demolding to obtain the preform.

[0060] The composite materials obtained in each embodiment and comparative example were made into 80mm×15mm×3mm plate samples. At least 5 parallel samples were tested in each group, and the average value of the test results was taken. 1. Basic physical property testing and room temperature mechanical property testing: The apparent density (g / cm³) of each plate sample was determined according to GB / T 1463-2005, and the percentage of the material density that reached the theoretical density was calculated, i.e., the density (%). The apparent porosity (%) of each plate sample was determined according to GB / T 1966-1996, the flexural strength (MPa) of each plate sample was determined according to GB / T 9341-2008, and the impact strength (kJ / m²) of each plate sample was determined according to GB / T229-2020. The ceramic yield (wt%) of the composite material after impregnation-pyrolysis in each example and comparative example was recorded.

[0061] The test data above are summarized in Table 1 below: Table 1. Test data of basic physical properties and mechanical properties at room temperature for each plate sample

[0062] 2. High temperature resistance test: The samples were first kept at 1000℃ in an argon atmosphere for 2 hours, and then cooled to room temperature in the furnace. The bending strength (MPa) of each plate sample was determined according to GB / T 9341-2008, and the impact strength (kJ / m²) of each plate sample was determined according to GB / T 229-2020. The linear shrinkage rate (%) was measured and calculated based on the changes in sample length / thickness from the preform to ceramization at 1500℃ in each example and comparative example.

[0063] The test data above are summarized in Table 2 below: Table 2. High-temperature resistance test data of each plate sample

[0064] 3. Corrosion resistance test: 3.1 After soaking each sample in 42wt% H2SO4 solution at 120℃ for different number of days, the flexural strength (MPa) was determined according to GB / T 9341-2008 and the impact strength (kJ / m²) was determined according to GB / T 229-2020. The test data above are summarized in Table 3 below: Table 3. Test data on acid corrosion resistance of each plate sample

[0065] 3.2 After soaking each sample in 30% NaOH solution at 120℃ for different number of days, the flexural strength (MPa) was determined according to GB / T 9341-2008 and the impact strength (kJ / m²) was determined according to GB / T 229-2020. The test data above are summarized in Table 4 below: Table 4. Test data on alkali corrosion resistance of each plate sample

[0066] Based on Examples 1-10 and Tables 1-4, it can be seen that when the carbon fiber cloth surface modifier is KH550 combined with boron-zirconium hybrid polysilazane in a preferred weight ratio, and the reinforcing filler is composed of five micro powders—silicon carbide, silicon nitride, alumina, zirconium oxide, and boron nitride—in a predetermined ratio, the composite material exhibits the highest density and lowest apparent porosity. Its flexural strength and impact strength at both room and high temperatures are significantly superior to other examples. Examples 2-5 show that using KH550 alone, or boron-zirconium hybrid polysilazane alone, or deviating from the preferred ratio, leads to decreased density, increased porosity, and a significant reduction in mechanical retention and acid / alkali corrosion resistance after high-temperature treatment. Examples 6-10 further demonstrate that using a single reinforcing filler cannot form a multi-component synergistic filling-toughening-densification network, and its performance is inferior to the five-filler compound scheme. The above comparison fully demonstrates that the combination design of the interface modifier (KH550 + boron-zirconium hybrid polysilazane) and the multi-component combination of the reinforcing filler (synergistic effect of five micro powders) are mutually coupled, which is the key to achieving high density, high strength, high temperature resistance and corrosion resistance of the material.

[0067] Combining Example 1 and Comparative Examples 1-2, and referring to Tables 1-4, it can be seen that Comparative Example 1, without desizing, oxidation, and surface modification treatment of the carbon fiber cloth, exhibits poor density, high porosity, and significantly inferior mechanical properties at room temperature, strength retention at high temperatures, and acid and alkali corrosion resistance compared to Example 1. This indicates that carbon fibers and polysiloxane alkyl bodies without interface regulation are highly susceptible to interfacial failure under high temperature and corrosive environments. Comparative Example 2, employing a one-stage hot pressing process instead of a three-stage hot pressing process, also shows significantly lower density and overall performance than Example 1. This demonstrates that three-stage hot pressing facilitates stable crosslinking reactions, sufficient volatile matter removal, and internal stress release, serving as a crucial process guarantee for obtaining defect-free preforms.

[0068] This application constructs a gradient interface layer containing KH550 and boron-zirconium hybrid polysilazane on the fiber surface by sequentially desizing, oxidizing and surface modifying carbon fiber cloth; at the same time, it introduces five kinds of micro powders compounded in a specific ratio as reinforcing fillers into the resin paste, and combines three-stage hot pressing molding and high-temperature ceramicization process, so that the composite material can achieve a synergistic improvement of multiple properties such as high temperature resistance, strong corrosion resistance and anti-coking while maintaining lightweight and high strength. The comprehensive performance far exceeds that of the unmodified or improperly processed comparison scheme.

[0069] This specific embodiment is merely an explanation of this application and is not intended to limit it. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but such modifications are protected by patent law as long as they fall within the scope of the claims of this application.

Claims

1. A high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material, characterized in that, The composite material includes carbon fiber cloth and a resin paste impregnated on the carbon fiber cloth and cured; the surface of the carbon fiber cloth is modified with a modifier to form an interface modification layer, the modifier being selected from one or more of epoxy resin, hexamethyldisilazane, polydopamine, KH550, and boron-zirconium hybrid polysilazane; the resin paste includes the following components in parts by weight: 25-35 parts of methyl vinyl polysilazane resin, 20-25 parts of reinforcing filler, 1-5 parts of organosilicon modifier, 2.5-5 parts of thickener, 0.01-2.5 parts of curing agent, and 0.1-5 parts of release agent.

2. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The modifier includes KH550 and boron-zirconium hybrid polysilazane, wherein the weight ratio of KH550 to boron-zirconium hybrid polysilazane is 1:(2-4).

3. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The organosilicon modifier is selected from one or more of the following: polyborosiloxane resin, methylphenyl vinyl silicone oil, silicone resin, KH550, hexamethyldisilazane, boron-zirconium hybrid silicone resin, and boron-zirconium hybrid polysilazane.

4. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The reinforcing filler is selected from one or more of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder, and boron nitride micro powder.

5. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 4, characterized in that, The reinforcing filler includes silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder, wherein the weight ratio of silicon carbide micro powder, silicon nitride micro powder, alumina micro powder, zirconium oxide micro powder and boron nitride micro powder is (6-10):(3-7):(2-4):(2-4):

1.

6. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The thickener is selected from one or more of polyamide wax, organobentonite, precipitated silica, and fumed silica.

7. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The curing agent is selected from one or more of N,N-dimethylbenzylamine, 1,1-di-tert-butylperoxycyclohexane, dicumyl peroxide, and (2,5-dimethyl-2,5-di-tert-butylperoxy)hexane.

8. The high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The release agent is selected from one or more of calcium stearate, magnesium stearate, and zinc stearate.

9. A method for preparing a high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to any one of claims 1-8, characterized in that, Includes the following steps: S1. Mix and disperse methyl vinyl polysilazane resin, reinforcing filler and organosilicon modifier to obtain a mixed resin liquid; S2. Add thickener, curing agent and release agent to the mixed resin liquid obtained in step S1, and disperse to obtain resin paste; S3. The carbon fiber cloth is subjected to desizing and oxidation treatment and surface modification treatment with a modifier in sequence to form an interface modification layer on the surface of the carbon fiber cloth. S4. The resin paste obtained in step S2 and the carbon fiber cloth obtained in step S3 are alternately layered and laid, and the preform is obtained by hot pressing in a three-stage process. S5. The preform obtained in step S4 is ceramicized under inert gas protection to obtain the composite material.

10. The preparation method of the high-temperature resistant, corrosion-resistant, anti-coking, lightweight, high-strength carbon fiber ceramic matrix composite material according to claim 1, characterized in that, The three-stage hot pressing process in step S3 includes: the first stage: heating from room temperature to 120-140℃, pressure of 10-15MPa, and holding pressure for 20-30 minutes; the second stage: heating to 150-180℃, pressure of 10-15MPa, and holding pressure for 20-30 minutes; and the third stage: heating to 190℃-210℃, pressure of 10-15MPa, and holding temperature for 25-35 minutes.

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