CN116462525B - Continuous carbon fiber reinforced ultrahigh-temperature ceramic matrix composite material and preparation method thereof - Google Patents
Continuous carbon fiber reinforced ultrahigh-temperature ceramic matrix composite material and preparation method thereof Download PDFInfo
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- CN116462525B CN116462525B CN202310721162.3A CN202310721162A CN116462525B CN 116462525 B CN116462525 B CN 116462525B CN 202310721162 A CN202310721162 A CN 202310721162A CN 116462525 B CN116462525 B CN 116462525B
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- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 112
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 112
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 92
- 239000000463 material Substances 0.000 title claims description 33
- 239000011216 ultra-high temperature ceramic matrix composite Substances 0.000 title claims description 26
- 238000002360 preparation method Methods 0.000 title description 8
- 239000000835 fiber Substances 0.000 claims abstract description 324
- 229910052751 metal Inorganic materials 0.000 claims abstract description 70
- 239000002184 metal Substances 0.000 claims abstract description 70
- 239000002131 composite material Substances 0.000 claims abstract description 35
- 238000002844 melting Methods 0.000 claims abstract description 32
- 230000008018 melting Effects 0.000 claims abstract description 27
- 239000011215 ultra-high-temperature ceramic Substances 0.000 claims abstract description 25
- 239000011159 matrix material Substances 0.000 claims abstract description 12
- 230000002787 reinforcement Effects 0.000 claims abstract description 11
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 4
- 239000000956 alloy Substances 0.000 claims abstract description 4
- 238000000034 method Methods 0.000 claims description 55
- 239000010410 layer Substances 0.000 claims description 34
- 239000012784 inorganic fiber Substances 0.000 claims description 25
- 239000003575 carbonaceous material Substances 0.000 claims description 22
- 239000011253 protective coating Substances 0.000 claims description 21
- 239000000919 ceramic Substances 0.000 claims description 20
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 19
- 229910052799 carbon Inorganic materials 0.000 claims description 19
- 229910052758 niobium Inorganic materials 0.000 claims description 16
- 239000010955 niobium Substances 0.000 claims description 16
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 16
- 229910052715 tantalum Inorganic materials 0.000 claims description 16
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 claims description 16
- 229910021332 silicide Inorganic materials 0.000 claims description 14
- FVBUAEGBCNSCDD-UHFFFAOYSA-N silicide(4-) Chemical compound [Si-4] FVBUAEGBCNSCDD-UHFFFAOYSA-N 0.000 claims description 14
- 238000009954 braiding Methods 0.000 claims description 13
- 238000005336 cracking Methods 0.000 claims description 12
- 238000000151 deposition Methods 0.000 claims description 12
- 238000005470 impregnation Methods 0.000 claims description 12
- 230000008595 infiltration Effects 0.000 claims description 12
- 238000001764 infiltration Methods 0.000 claims description 12
- 230000008021 deposition Effects 0.000 claims description 10
- 238000003763 carbonization Methods 0.000 claims description 9
- 238000006243 chemical reaction Methods 0.000 claims description 9
- 238000000280 densification Methods 0.000 claims description 8
- 239000002002 slurry Substances 0.000 claims description 8
- 239000011229 interlayer Substances 0.000 claims description 7
- 230000008569 process Effects 0.000 claims description 7
- 239000000126 substance Substances 0.000 claims description 7
- 229910001182 Mo alloy Inorganic materials 0.000 claims description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 6
- 229910001257 Nb alloy Inorganic materials 0.000 claims description 6
- 229910001362 Ta alloys Inorganic materials 0.000 claims description 6
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 6
- YXTPWUNVHCYOSP-UHFFFAOYSA-N bis($l^{2}-silanylidene)molybdenum Chemical compound [Si]=[Mo]=[Si] YXTPWUNVHCYOSP-UHFFFAOYSA-N 0.000 claims description 6
- 238000007598 dipping method Methods 0.000 claims description 6
- 229910052750 molybdenum Inorganic materials 0.000 claims description 6
- 239000011733 molybdenum Substances 0.000 claims description 6
- 229910021344 molybdenum silicide Inorganic materials 0.000 claims description 6
- 239000000843 powder Substances 0.000 claims description 6
- 239000002243 precursor Substances 0.000 claims description 6
- 239000010453 quartz Substances 0.000 claims description 6
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 6
- 229910052726 zirconium Inorganic materials 0.000 claims description 6
- 229910052735 hafnium Inorganic materials 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 5
- 239000011148 porous material Substances 0.000 claims description 5
- 239000007787 solid Substances 0.000 claims description 5
- -1 zirconium alkoxide Chemical class 0.000 claims description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 4
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 4
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 4
- 239000004744 fabric Substances 0.000 claims description 4
- 239000002904 solvent Substances 0.000 claims description 4
- 238000011049 filling Methods 0.000 claims description 3
- 239000000155 melt Substances 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 230000035515 penetration Effects 0.000 claims description 3
- 229920003257 polycarbosilane Polymers 0.000 claims description 3
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 3
- 239000002344 surface layer Substances 0.000 claims description 3
- WIEXMPDBTYDSQF-UHFFFAOYSA-N 1,3-bis(furan-2-yl)propan-2-one Chemical compound C=1C=COC=1CC(=O)CC1=CC=CO1 WIEXMPDBTYDSQF-UHFFFAOYSA-N 0.000 claims description 2
- KXGFMDJXCMQABM-UHFFFAOYSA-N 2-methoxy-6-methylphenol Chemical compound [CH]OC1=CC=CC([CH])=C1O KXGFMDJXCMQABM-UHFFFAOYSA-N 0.000 claims description 2
- 229920002748 Basalt fiber Polymers 0.000 claims description 2
- CTQNGGLPUBDAKN-UHFFFAOYSA-N O-Xylene Chemical compound CC1=CC=CC=C1C CTQNGGLPUBDAKN-UHFFFAOYSA-N 0.000 claims description 2
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims description 2
- 229910026551 ZrC Inorganic materials 0.000 claims description 2
- LRTTZMZPZHBOPO-UHFFFAOYSA-N [B].[B].[Hf] Chemical compound [B].[B].[Hf] LRTTZMZPZHBOPO-UHFFFAOYSA-N 0.000 claims description 2
- OTCHGXYCWNXDOA-UHFFFAOYSA-N [C].[Zr] Chemical compound [C].[Zr] OTCHGXYCWNXDOA-UHFFFAOYSA-N 0.000 claims description 2
- 238000000498 ball milling Methods 0.000 claims description 2
- 239000012159 carrier gas Substances 0.000 claims description 2
- 239000012700 ceramic precursor Substances 0.000 claims description 2
- KZHJGOXRZJKJNY-UHFFFAOYSA-N dioxosilane;oxo(oxoalumanyloxy)alumane Chemical compound O=[Si]=O.O=[Si]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O.O=[Al]O[Al]=O KZHJGOXRZJKJNY-UHFFFAOYSA-N 0.000 claims description 2
- 238000001035 drying Methods 0.000 claims description 2
- 239000003365 glass fiber Substances 0.000 claims description 2
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 claims description 2
- WHJFNYXPKGDKBB-UHFFFAOYSA-N hafnium;methane Chemical compound C.[Hf] WHJFNYXPKGDKBB-UHFFFAOYSA-N 0.000 claims description 2
- UNASZPQZIFZUSI-UHFFFAOYSA-N methylidyneniobium Chemical compound [Nb]#C UNASZPQZIFZUSI-UHFFFAOYSA-N 0.000 claims description 2
- NFFIWVVINABMKP-UHFFFAOYSA-N methylidynetantalum Chemical compound [Ta]#C NFFIWVVINABMKP-UHFFFAOYSA-N 0.000 claims description 2
- 229910052863 mullite Inorganic materials 0.000 claims description 2
- 229910052757 nitrogen Inorganic materials 0.000 claims description 2
- 239000003960 organic solvent Substances 0.000 claims description 2
- 239000005011 phenolic resin Substances 0.000 claims description 2
- 229920001568 phenolic resin Polymers 0.000 claims description 2
- QQONPFPTGQHPMA-UHFFFAOYSA-N propylene Natural products CC=C QQONPFPTGQHPMA-UHFFFAOYSA-N 0.000 claims description 2
- 125000004805 propylene group Chemical group [H]C([H])([H])C([H])([*:1])C([H])([H])[*:2] 0.000 claims description 2
- 238000000197 pyrolysis Methods 0.000 claims description 2
- 229920005989 resin Polymers 0.000 claims description 2
- 239000011347 resin Substances 0.000 claims description 2
- 229910052710 silicon Inorganic materials 0.000 claims description 2
- 239000010703 silicon Substances 0.000 claims description 2
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 2
- 229910003468 tantalcarbide Inorganic materials 0.000 claims description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 2
- 239000008096 xylene Substances 0.000 claims description 2
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims 2
- 241000588731 Hafnia Species 0.000 claims 1
- 239000011153 ceramic matrix composite Substances 0.000 claims 1
- CETPSERCERDGAM-UHFFFAOYSA-N ceric oxide Chemical compound O=[Ce]=O CETPSERCERDGAM-UHFFFAOYSA-N 0.000 claims 1
- 229910000422 cerium(IV) oxide Inorganic materials 0.000 claims 1
- CJNBYAVZURUTKZ-UHFFFAOYSA-N hafnium(IV) oxide Inorganic materials O=[Hf]=O CJNBYAVZURUTKZ-UHFFFAOYSA-N 0.000 claims 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 claims 1
- 238000002679 ablation Methods 0.000 abstract description 13
- 238000009940 knitting Methods 0.000 description 8
- 230000003647 oxidation Effects 0.000 description 7
- 238000007254 oxidation reaction Methods 0.000 description 7
- 230000008901 benefit Effects 0.000 description 6
- 239000011248 coating agent Substances 0.000 description 6
- 238000000576 coating method Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 229910010293 ceramic material Inorganic materials 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000000052 comparative effect Effects 0.000 description 2
- 238000011010 flushing procedure Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- 230000002829 reductive effect Effects 0.000 description 2
- 239000011214 refractory ceramic Substances 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000003064 anti-oxidating effect Effects 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 239000010426 asphalt Substances 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 229910000420 cerium oxide Inorganic materials 0.000 description 1
- 230000002860 competitive effect Effects 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 229910000449 hafnium oxide Inorganic materials 0.000 description 1
- WIHZLLGSGQNAGK-UHFFFAOYSA-N hafnium(4+);oxygen(2-) Chemical compound [O-2].[O-2].[Hf+4] WIHZLLGSGQNAGK-UHFFFAOYSA-N 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000011259 mixed solution Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- BMMGVYCKOGBVEV-UHFFFAOYSA-N oxo(oxoceriooxy)cerium Chemical compound [Ce]=O.O=[Ce]=O BMMGVYCKOGBVEV-UHFFFAOYSA-N 0.000 description 1
- SIWVEOZUMHYXCS-UHFFFAOYSA-N oxo(oxoyttriooxy)yttrium Chemical compound O=[Y]O[Y]=O SIWVEOZUMHYXCS-UHFFFAOYSA-N 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- RVTZCBVAJQQJTK-UHFFFAOYSA-N oxygen(2-);zirconium(4+) Chemical compound [O-2].[O-2].[Zr+4] RVTZCBVAJQQJTK-UHFFFAOYSA-N 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000011226 reinforced ceramic Substances 0.000 description 1
- 238000009991 scouring Methods 0.000 description 1
- 238000009958 sewing Methods 0.000 description 1
- 229910001928 zirconium oxide Inorganic materials 0.000 description 1
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Abstract
The composite material takes mixed continuous fibers of continuous carbon fibers and low-melting-point continuous oxide fibers as a reinforcement body and takes an ultrahigh-temperature ceramic phase as a matrix; the low-melting-point continuous oxide fiber refers to a continuous oxide fiber with a melting point lower than that of a continuous carbon fiber, and the reinforcement further comprises: continuous metal fibers; the continuous metal fiber is refractory continuous metal fiber or refractory continuous alloy fiber; the volume fraction of the low-melting-point continuous oxide fiber is 5-70%, and the volume fraction of the continuous metal fiber is 10-20%; the layer of continuous carbon fiber is separated by at most 1 layer. The composite material provided by the application has good toughness and ablation resistance.
Description
Technical Field
The application relates to the technical field of composite materials, in particular to a continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite material and a preparation method thereof.
Background
The ultra-high temperature ceramic material has high melting point (higher than 3000 ℃), high strength and high rigidity, light weight (low density) and excellent corrosion resistance compared with the metal material, and has the potential of being applied to extreme environments. However, the ultrahigh-temperature ceramic material has the fatal weaknesses of high brittleness and poor thermal shock resistance, and high-strength and high-elasticity continuous carbon fibers (reinforcing phases) and ultrahigh-temperature ceramic (matrixes) are often compounded to prepare a composite material so as to improve the brittleness and the thermal shock resistance. The continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite has been widely applied to solid/liquid rocket engine nozzles, hypersonic aircraft nose cones, scramjet engine combustors and the like.
The working environments of the solid/liquid rocket engine spray pipe, the hypersonic aircraft nose cone, the scramjet engine combustion chamber and the like have the characteristics of high temperature, strong oxidation, high-speed flushing and the like, and have high requirements on materials. As weaponry develops toward high performance, the requirements for materials become more stringent, and how to further improve the toughness and ablation resistance of the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite becomes a goal of competitive pursuits in various army countries.
The existing method for improving the toughness of the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite material can be divided into two directions. The first direction is to optimize the formulation and preparation process of the ceramic matrix material, and practice shows that the method can improve the toughness to a certain extent, but the method belongs to the category of ceramic materials after all, the nature of the material with high brittleness cannot be changed, and therefore, the improvement effect is limited. The second direction is to optimize the carbon fiber preform structure. However, the carbon fiber itself has low elongation at break and poor toughness, and optimizing the carbon fiber preform structure is not large for improving the toughness.
The method for improving the ablation resistance of the continuous carbon fiber reinforced ultrahigh temperature ceramic matrix composite is commonly used at present: optimizing the formula of the ceramic matrix material, introducing refractory ceramic components, and adding an antioxidant coating on the surface of the material. The method has obvious effect of improving the ablation resistance aiming at the application environment of weak oxidation (low oxygen partial pressure) and low-speed flow flushing. However, the application environments of the solid/liquid rocket engine spray pipe, the hypersonic aircraft nose cone, the scramjet engine combustion chamber and the like have the characteristics of high temperature, strong oxidation, strong scouring action and the like, and in the application scenes, the designed antioxidation coating and the oxide protection film formed by the refractory ceramic through oxidation are easy to be scoured, so that the improvement effect of the method is not obvious.
The method for improving the toughness and the ablation resistance of the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite material is based on optimizing the formula of a ceramic matrix, the preparation process, the structure of a carbon fiber preform and designing an oxidation-resistant coating, and has shown a certain limitation at present. In addition, the existing method for improving the toughness of the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite material and the method for improving the ablation resistance are almost independent from each other, and no method for simultaneously improving the toughness and the ablation resistance of the material by one measure exists.
Disclosure of Invention
The application aims to solve the technical problem of overcoming the defects of the prior art, and provides a continuous carbon fiber reinforced ultrahigh-temperature ceramic matrix composite material and a preparation method thereof, which can improve the toughness and ablation resistance of the material through one measure.
The technical proposal of the application is that the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite material is prepared by continuous carbon fiber and low melting pointOxide compoundThe mixed continuous fiber of the fiber is used as a reinforcement body and an ultra-high temperature ceramic phase is used as a matrix; the volume ratio of the reinforcement to the matrix is 0.1-10;
the low-melting-point continuous oxide fiber is a continuous oxide fiber with a melting point lower than that of the continuous carbon fiber, the breaking elongation of the continuous oxide fiber is 1-10%, and the melting point is 500-3000 ℃;
the reinforcement further comprises: continuous metal fibers; the continuous metal fiber is refractory continuous metal fiber or refractory continuous alloy fiber; wherein refractory means that the melting point of the continuous metal fiber is higher than 1650 ℃;
in the hybrid continuous fiber, the volume fraction of the low-melting-point continuous oxide fiber is 5-70%, and the volume fraction of the continuous metal fiber is 10-20%;
the continuous metal fiber comprises at least one of continuous molybdenum fiber, continuous tantalum fiber, continuous niobium fiber, continuous molybdenum alloy fiber, continuous tantalum alloy fiber and continuous niobium alloy fiber;
the surface layer of the continuous metal fiber is provided with a protective coating;
when the continuous metal fiber is a continuous molybdenum fiber, the protective coating is molybdenum silicide;
when the continuous metal fiber is a continuous tantalum fiber, the protective coating is a silicide of tantalum;
when the continuous metal fiber is a continuous niobium fiber, the protective coating is a silicide of niobium;
when the continuous metal fiber is a continuous molybdenum alloy fiber, the protective coating is molybdenum silicide;
when the continuous metal fiber is a continuous tantalum alloy fiber, the protective coating is silicide of tantalum;
when the continuous metal fiber is a continuous niobium alloy fiber, the protective coating is a silicide of niobium;
wherein the hybrid continuous fiber is of a layered structure or a three-dimensional woven structure; the layer of continuous carbon fiber is separated by at most 1 layer.
The application also provides a preparation method of the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite, which comprises the following steps:
s1, preparing a hybrid continuous fiber preform of continuous carbon fibers, low-melting-point continuous oxide fibers and continuous metal fibers;
s2, densifying the hybrid continuous fiber preform by using carbon to obtain a porous carbon fiber/inorganic fiber/carbon material; wherein the inorganic fibers comprise low-melting-point continuous oxide fibers and continuous metal fibers;
s3, introducing the ultra-high temperature ceramic phase into the porous carbon fiber/inorganic fiber/carbon material to obtain the target continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite.
Compared with the prior art, the application has the advantages that:
1. according to the application, other continuous oxide fibers with lower melting points are mixed in the continuous carbon fibers, and in a high-temperature use environment, the low-melting-point continuous oxide fibers are melted and softened, so that the internal gaps of the composite material can be filled, the self-healing property of the composite material is endowed, meanwhile, the penetration of oxidizing components in the environment is prevented, the oxidation of the composite material can be delayed, and the ablation resistance of the composite material is improved.
2. Compared with the single continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite, the hybrid preform reinforced ultra-high temperature ceramic matrix composite which is composed of the continuous carbon fiber and the low-melting point continuous oxide fiber is beneficial to increasing the toughness of the composite because the continuous oxide fiber with relatively good toughness is introduced.
3. The continuous carbon fiber reinforced ceramic matrix composite has poor normal temperature toughness, especially poor normal temperature impact toughness (large modulus and no plastic deformation stage), so that the normal temperature toughness needs to be enhanced, the ceramic matrix is gradually softened along with the increase of service temperature, certain plasticity is shown, the toughness of the material in a high temperature area is better, and even if the toughness of the material is not toughened by oxide fibers, the toughness of the material is also high. In addition, the oxide fiber is filled in the gap after being melted to play a certain role in buffering and toughening.
4. According to the scheme, the carbon fiber and the oxide fiber are directly mixed, the original state of the fiber is reserved to the greatest extent, the surface structure is not damaged, and the original performance (strength) of the fiber is reserved. In addition, multilayer or three-dimensional continuous (long) fibers have a greater effect on improving the strength of the material than do short fibers.
5. The performance of the ultra-high temperature ceramic matrix composite can be regulated and controlled by adjusting the proportion and the combination mode of the hybrid fiber preform, and the designability of the performance is enhanced.
6. Other oxide fibers are introduced into the continuous fiber preform, so that the consumption of expensive carbon fibers is reduced, and the cost is reduced.
Drawings
These and/or other aspects and advantages of the present application will become more apparent and more readily appreciated from the following detailed description of the embodiments of the application, taken in conjunction with the accompanying drawings, wherein:
FIG. 1 is a schematic illustration of non-90 degree weave forming of a continuous fiber bundle;
FIG. 2 is a schematic view of a hybrid continuous fiber preform formed by hybrid braiding of two types of fiber bundles;
FIG. 3 is a schematic view of a hybrid continuous fiber preform woven from bundles of composite fibers
FIG. 4 is a schematic illustration of a hybrid continuous fiber preform in a two-type fiber lay-up configuration;
FIG. 5 is a schematic illustration of a hybrid continuous fiber preform in a two-type fiber lay-up configuration with a chopped strand mat interposed between the two types of fibers;
fig. 6 is a schematic view of a hybrid continuous fiber preform in a two-type fiber lay-up configuration with a chopped strand mat interposed between the two types of fibers and with the addition of interlaminar bonding fibers.
Detailed Description
The present application will be described in further detail below with reference to the drawings and detailed description for the purpose of enabling those skilled in the art to understand the application better.
In one embodiment, a continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite is provided with hybrid continuous fibers of continuous carbon fibers and low melting point continuous oxide fibers as reinforcements and an ultra-high temperature ceramic phase as matrix; the volume ratio of the reinforcement to the matrix is 0.1-10;
the low-melting-point continuous oxide fiber is a continuous oxide fiber with a melting point lower than that of the continuous carbon fiber, the breaking elongation of the continuous oxide fiber is 1-10%, and the melting point is 500-3000 ℃;
the reinforcement further comprises: continuous metal fibers; the continuous metal fiber is refractory continuous metal fiber or refractory continuous alloy fiber; wherein refractory means that the melting point of the continuous metal fiber is higher than 1650 ℃;
in the hybrid continuous fiber, the volume fraction of the low-melting-point continuous oxide fiber is 5-70%, and the volume fraction of the continuous metal fiber is 10-20%;
the continuous metal fiber comprises at least one of continuous molybdenum fiber, continuous tantalum fiber, continuous niobium fiber, continuous molybdenum alloy fiber, continuous tantalum alloy fiber and continuous niobium alloy fiber;
the surface layer of the continuous metal fiber is provided with a protective coating;
when the continuous metal fiber is a continuous molybdenum fiber, the protective coating is molybdenum silicide;
when the continuous metal fiber is a continuous tantalum fiber, the protective coating is a silicide of tantalum;
when the continuous metal fiber is a continuous niobium fiber, the protective coating is a silicide of niobium;
when the continuous metal fiber is a continuous molybdenum alloy fiber, the protective coating is molybdenum silicide;
when the continuous metal fiber is a continuous tantalum alloy fiber, the protective coating is silicide of tantalum;
when the continuous metal fiber is a continuous niobium alloy fiber, the protective coating is a silicide of niobium;
wherein the hybrid continuous fiber is of a layered structure or a three-dimensional woven structure; the layer of continuous carbon fiber is separated by at most 1 layer. As shown in table 1, a comparison of carbon fiber to other inorganic fiber parameters is provided.
Table 1 comparison of carbon fiber with other inorganic fiber parameters
The hybrid continuous fiber is a layered structure or a three-dimensional woven structure. The present solution does not require a layering/stacking sequence of fibers, and only requires preparation of an integrally homogeneous material. And whether in a three-dimensional woven structure or a layered structure, the scheme uses hybrid fibers in layers and between layers.
The application aims to utilize the characteristics of high strength, high rigidity and high melting point of carbon fibers, and simultaneously consider the advantages of low melting point, high Wen Ziyu property and high toughness of other oxide fibers, and the carbon fibers and other oxide fibers are compounded to prepare the hybrid preform for reinforcing the ultrahigh-temperature ceramic base material, so that the advantages of the carbon fibers and the other oxide fibers are complementary to obtain the ultrahigh-temperature ceramic base composite material with excellent comprehensive performance.
On one hand, the hybrid preform combines the strength advantage of the carbon fiber and the toughness advantage of other oxide fibers, and improves the toughness on the premise of ensuring that the material has certain strength; on the other hand, other oxide fibers with relatively low melting points are introduced into the carbon fiber reinforced phase and distributed in the material, when the material is applied to a high-temperature service environment, the melting of the oxide fibers with low melting points in the interior is beneficial to filling pores (self-healing property) and prevents oxidizing components in the service environment from penetrating into the interior erosion material, so that the problem of aggravation of ablation after the oxidation-resistant coating on the surface of the material is washed away is solved to a certain extent. That is, the application provides an opportunity to improve both toughness and ablation resistance of the material. In addition, the scheme is beneficial to reducing the consumption of the carbon fiber with higher price, and reduces the material cost while increasing the designability of the material performance. In addition, the application introduces continuous metal fiber, and on the basis of overcoming technical prejudice, good material toughness and ablation resistance are still obtained.
Further, the low-melting-point continuous oxide fiber comprises at least one of glass fiber, quartz fiber, alumina fiber, mullite fiber, cerium oxide fiber, yttrium oxide fiber, hafnium oxide fiber, zirconium oxide fiber or basalt fiber;
the ultra-high temperature ceramic phase comprises a precursor: a ceramic phase formed by pyrolysis of one or more substances selected from polycarbosilane, zirconium alkoxide and hafnium alkoxide,
or a ceramic phase generated by the reaction of a melt containing one or more elements of silicon, zirconium, hafnium, niobium and tantalum after penetrating into a porous carbonaceous material,
or a solid ceramic powder comprising one or more of directly incorporated silicon carbide, zirconium carbide, hafnium carbide, tantalum carbide, niobium carbide, zirconium boride, hafnium boride.
Further, the knitting units of the three-dimensional knitting structure are single bundles of continuous fibers, and the knitting mode is orthogonal knitting or non-90-degree knitting. As shown in fig. 1, a schematic representation of a continuous fiber bundle non-90 degree weave formation is provided.
The single continuous fiber is a single continuous fiber bundle of continuous carbon fiber, low-melting point continuous oxide fiber or continuous metal fiber, that is, before braiding, each continuous fiber bundle only comprises one fiber, and after braiding with at least 3 continuous fiber bundles (including carbon fiber bundles), a hybrid continuous fiber preform with a three-dimensional structure is obtained, as shown in fig. 2, and a schematic diagram of the hybrid continuous fiber preform when two types of fiber bundles are mixed-braided is provided. Wherein, the continuous carbon fiber is parallel to the y-axis direction, the low-melting-point continuous oxide fiber is parallel to the z-axis direction, and the continuous metal fiber is parallel to the x-axis direction;
or a composite continuous fiber bundle of continuous carbon fibers and at least one other low-melting point continuous oxide fiber,
or a composite continuous fiber bundle of continuous carbon fibers, at least one other low melting point continuous oxide fiber, and at least one continuous metal fiber; i.e. each continuous fiber bundle comprises at least two fibers prior to braiding, a composite continuous fiber bundle can be obtained by co-twisting. As shown in fig. 3, a schematic diagram of the hybrid continuous fiber preform when woven and molded as a composite fiber bundle is provided.
The single-bundle fiber is used as a knitting unit, so that the knitting efficiency is high, the cost is low, and the damage of the fiber in the knitting process is less. Compared with the single fiber bundle braiding and forming and the composite fiber bundle braiding and forming, the uniformity of the single fiber bundle braiding and forming is better, and after high-temperature service, the fibers can be well adhered into a whole in the bundle and among the bundles, and the single fiber bundle braiding and forming has better deformation resistance on the premise of ensuring excellent ablation resistance.
The continuous fiber layer of the layered structure is a single continuous fiber layer of continuous carbon fiber, low-melting-point continuous oxide fiber or continuous metal fiber,
or a composite fiber layer of continuous carbon fibers and at least one other low melting point continuous oxide fiber,
or a composite continuous fiber layer of continuous carbon fibers, at least one other low melting point continuous oxide fiber, and at least one continuous metal fiber;
the continuous fiber layer is continuous fiber laid cloth or continuous fiber woven cloth; a chopped strand mat is inserted between adjacent continuous fiber layers; the chopped strand mat is a chopped carbon fiber mat, a chopped low-melting-point oxide fiber mat, or a mixed mat of chopped carbon fibers and chopped low-melting-point oxide fibers.
The units of the lay-up are also individual fibers.
As shown in fig. 4, a schematic diagram of a hybrid continuous fiber preform is provided when the two types of fiber lay-up structures are provided, wherein the a layer is a continuous carbon fiber, a low-melting-point continuous oxide fiber and a continuous metal fiber can be hybrid therein, and the b layer is one or more low-melting-point continuous oxide fibers, and a continuous carbon fiber and a continuous metal fiber can also be hybrid therein.
As shown in fig. 5, a schematic diagram is provided in which the hybrid continuous fiber preform is a two-type fiber lay-up structure with a chopped strand mat interposed between the two-type fiber layers.
Further, an interlayer connecting fiber introduced by a needling or sewing process is contained between the continuous fiber layer and the chopped strand mat;
the interlayer connecting fiber is carbon fiber, at least one low-melting-point oxide fiber or at least one metal fiber; or a hybrid fiber of carbon fiber and low-melting-point oxide fiber, or a hybrid fiber of carbon fiber, low-melting-point oxide fiber, and metal fiber.
The interlayer connecting fiber may be a continuous fiber, a chopped fiber, a mixed fiber of a continuous fiber and a chopped fiber, or a metal fiber.
By introducing connecting fibers between layers through a needling or stitching process, the bonding force between layers can be enhanced, and the toughness of the composite material can be improved. As shown in fig. 6, a schematic diagram is provided in which a hybrid continuous fiber preform is a two-type fiber lay-up structure with a chopped strand mat interposed between the two-type fibers and with the addition of interlaminar bonding fibers.
In one embodiment, a method for preparing a continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite is provided, comprising the steps of:
s1, preparing a hybrid continuous fiber preform of continuous carbon fibers, low-melting-point continuous oxide fibers and continuous metal fibers;
s2, densifying the hybrid continuous fiber preform by using carbon to obtain a porous carbon fiber/inorganic fiber/carbon material; wherein the inorganic fibers comprise low-melting-point continuous oxide fibers and continuous metal fibers;
s3, introducing the ultra-high temperature ceramic phase into the porous carbon fiber/inorganic fiber/carbon material to obtain the target continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite.
Further, in step S2, the densification method is one of the following methods:
the method comprises the steps of firstly, chemical vapor infiltration and carbon deposition densification; the step of densifying by chemical vapor infiltration deposition comprises: taking methane or propylene as a carbon source, taking nitrogen as a carrier gas, and carrying out deposition at a deposition pressure of not higher than 15KPa and a deposition temperature of 800-1200 ℃, and densifying the deposited carbon of the hybrid continuous fiber preform to obtain a porous carbon fiber/inorganic fiber/carbon material with a porosity of 20-80%;
the second method is to impregnate cracking carbon for densification; the steps of densification using dip cracking include: impregnating the hybrid continuous fiber preform into a vacuum-pressure impregnation tank containing pitch, phenolic resin or furfuryl ketone resin; the impregnation pressure is not higher than 15kPa, and the impregnation temperature is 60-100 ℃; curing after impregnation, setting the curing temperature to be 80-200 ℃, and finally completing carbonization in a carbonization furnace, wherein the carbonization temperature is set to be 600-1300 ℃, so as to obtain the porous carbon fiber/inorganic fiber/carbon material with the porosity of 20-80%.
Further, in step S3, the method for introducing the ultra-high temperature ceramic phase is one of the following methods:
the method comprises the steps of firstly, a precursor dipping cracking method; the step of introducing the ultra-high temperature ceramic phase by adopting a precursor dipping and cracking method comprises the following steps:
impregnating the ceramic precursor solution into porous carbon fiber/inorganic fiber/carbon material, and then cracking to ensure that the porosity of the composite material is lower than 15%;
a second method, a reaction infiltration method; the step of introducing the ultra-high temperature ceramic phase by adopting the reaction infiltration method comprises the following steps:
impregnating porous carbon fiber/inorganic fiber/carbon material into metal melt, reacting carbon in the porous material with the metal melt to generate ceramic phase, filling pores so that the porosity of the composite material is lower than 10%, and completing the introduction of the ultra-high temperature ceramic phase; wherein the temperature of the reaction infiltration process is set to 1500-2300 ℃, the pressure is not higher than 10kPa, and the time is 1-10 hours;
a third method, a slurry permeation method; the step of introducing the ultra-high temperature ceramic phase by adopting a slurry permeation method comprises the following steps:
mixing ceramic powder and a solvent, ball milling to obtain uniform ceramic slurry, then penetrating the ceramic slurry into a hybrid continuous fiber preform by using a vacuum tank, and finally drying and heat treating to obtain an initial composite material, wherein the primary or secondary penetration is performed until the porosity of the composite material is lower than 15%; wherein the solvent is water, ethanol, xylene or other organic solvents.
Example 1:
in the first step, a layer fiber preform is prepared, wherein the bottom layer is a hybrid fiber of continuous carbon fibers and continuous quartz fibers, the middle layer is a chopped carbon fiber layer, and the upper layer is a hybrid fiber of continuous carbon fibers and continuous quartz fibers, so that the layers are periodically laminated. And the interlayer connection carbon fiber is introduced by adopting a needling process, so that the interlayer binding force is enhanced. In the hybrid continuous fiber layer, the proportion of continuous quartz fibers is 8%, and the porosity of the preform is 85%;
secondly, preparing porous carbon fiber/inorganic fiber/carbon material, depositing carbon in the prefabricated body by adopting a chemical vapor infiltration method, and depositing the carbon in the prefabricated body for 100 hours at the temperature of 1000-1200 ℃ by utilizing methane as a carbon source, wherein the porosity of the obtained porous carbon fiber/inorganic fiber/carbon material is 65%;
thirdly, introducing an ultrahigh-temperature ceramic phase, uniformly mixing Si-containing powder and Zr-containing powder, introducing a melt into a porous carbon fiber/inorganic fiber/carbon material by adopting a reaction infiltration method, and generating a ZrC-SiC ceramic phase in situ to ensure that the porosity of the final material is lower than 10%. The sample was obtained and marked as S1-8.
The proportion of continuous quartz fibers in the first step above was adjusted to 65%, and the other steps and parameters were kept unchanged. The resulting sample was labeled S1-65.
Example 2:
in a first step, the lay-up preform of the first step in example 1 was replaced with a three-dimensional woven preform as shown in fig. 2, in which the proportion of continuous alumina fibers was 50% and the porosity of the preform was 60%;
secondly, preparing porous carbon fiber/inorganic fiber/carbon material, and densifying by adopting impregnation cracking carbon: dipping the hybrid continuous fiber preform into a vacuum-pressure dipping tank filled with asphalt; the impregnation pressure is not higher than 15kPa, and the impregnation temperature is 60-100 ℃; curing after impregnation, setting the curing temperature to 120-200 ℃, and finally completing carbonization in a carbonization furnace, wherein the carbonization temperature is set to 600-1000 ℃ to obtain porous carbon fiber/inorganic fiber/carbon material with the porosity of 50%;
thirdly, introducing an ultra-high temperature ceramic phase, immersing the mixed solution containing polycarbosilane and alkoxy hafnium into the porous carbon fiber/inorganic fiber/carbon material, and then cracking to ensure that the porosity of the material is lower than 15%. The resulting sample was labeled S2-50.
The preform in the above first step was changed to the structure shown in fig. 3 in which the proportion of the continuous alumina fibers in the composite fiber bundle was 5%, and the other steps and parameters were kept unchanged. The resulting sample was labeled as S2-5-FH.
The preform in the above first step was changed to the structure shown in fig. 3 in which the proportion of the continuous alumina fibers in the composite fiber bundle was 50%, and the other steps and parameters were kept unchanged. The resulting sample was labeled S2-50-FH.
The preform in the above first step was changed to the structure shown in fig. 3, in which the proportion of the continuous alumina fibers in the composite fiber bundle was 70%, and the other steps and parameters were kept unchanged. The resulting sample was labeled S2-70-FH.
Example 3:
10% of the continuous carbon fibers in S1-8 of example 1 were replaced with continuous tantalum fibers with a silicide coating of tantalum, with the other steps unchanged. The resulting sample is labeled S3.
Example 4:
the other steps were unchanged by replacing 20% of the continuous carbon fibers in S1-8 of example 1 with continuous niobium fibers with a silicide coating of niobium. The resulting sample is labeled S4.
Comparative example 1
The procedure of example 1 was repeated except that the low-melting-point continuous oxide fiber introduced in example 1 was changed to a carbon fiber, and the preform was changed to a needled carbon fiber preform. The resulting sample is labeled S1.
Comparative example 2
The procedure of example 2 was repeated except that the low-melting-point continuous oxide fiber introduced in example 2 was changed to a carbon fiber, and the preform was changed to a three-dimensional carbon fiber preform. The resulting sample is labeled S2.
Table 2 comparison of material properties
The foregoing description of embodiments of the application has been presented for purposes of illustration and description, and is not intended to be exhaustive or limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the various embodiments described. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.
Claims (7)
1. The continuous carbon fiber reinforced superhigh temperature ceramic matrix composite material is characterized in that mixed continuous fiber of continuous carbon fiber and low melting point continuous oxide fiber is used as a reinforcement, and superhigh temperature ceramic phase is used as a matrix; the volume ratio of the reinforcement to the matrix is 0.1-10;
the low-melting-point continuous oxide fiber is a continuous oxide fiber with a melting point lower than that of the continuous carbon fiber, the breaking elongation of the continuous oxide fiber is 1-10%, and the melting point is 500-3000 ℃;
the reinforcement further comprises: continuous metal fibers; the continuous metal fiber is refractory continuous metal fiber or refractory continuous alloy fiber; wherein refractory means that the melting point of the continuous metal fiber is higher than 1650 ℃;
in the hybrid continuous fiber, the volume fraction of the low-melting-point continuous oxide fiber is 5-70%, and the volume fraction of the continuous metal fiber is 10-20%;
the continuous metal fiber comprises at least one of a continuous molybdenum fiber, a continuous tantalum fiber, a continuous niobium fiber, a continuous molybdenum alloy fiber, a continuous tantalum alloy fiber and a continuous niobium alloy fiber;
the surface layer of the continuous metal fiber is provided with a protective coating;
when the continuous metal fiber is a continuous molybdenum fiber, the protective coating is molybdenum silicide;
when the continuous metal fiber is a continuous tantalum fiber, the protective coating is silicide of tantalum;
when the continuous metal fiber is a continuous niobium fiber, the protective coating is a silicide of niobium;
when the continuous metal fiber is a continuous molybdenum alloy fiber, the protective coating is molybdenum silicide;
when the continuous metal fiber is a continuous tantalum alloy fiber, the protective coating is silicide of tantalum;
when the continuous metal fiber is a continuous niobium alloy fiber, the protective coating is a silicide of niobium;
wherein the hybrid continuous fiber is of a layered structure or a three-dimensional woven structure; the layer of continuous carbon fiber is separated by at most 1 layer.
2. The continuous carbon fiber-reinforced ultra-high temperature ceramic matrix composite of claim 1, wherein the low melting point continuous oxide fibers comprise at least one of glass fibers, quartz fibers, alumina fibers, mullite fibers, ceria fibers, yttria fibers, hafnia fibers, zirconia fibers, or basalt fibers;
the ultra-high temperature ceramic phase comprises a precursor: a ceramic phase formed by pyrolysis of one or more substances selected from polycarbosilane, zirconium alkoxide and hafnium alkoxide,
or a ceramic phase generated by the reaction of a melt containing one or more elements of silicon, zirconium, hafnium, niobium and tantalum after penetrating into a porous carbonaceous material,
or a solid ceramic powder comprising one or more of directly incorporated silicon carbide, zirconium carbide, hafnium carbide, tantalum carbide, niobium carbide, zirconium boride, hafnium boride.
3. The continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite according to claim 1, wherein the braiding units of the three-dimensional braiding structure are single bundles of continuous fibers, and the braiding mode is orthogonal braiding or non-90 ° braiding;
the single continuous fiber is a single continuous fiber bundle of continuous carbon fiber, low-melting-point continuous oxide fiber or continuous metal fiber,
or a composite continuous fiber bundle of continuous carbon fibers and at least one other low-melting point continuous oxide fiber,
or a composite continuous fiber bundle of continuous carbon fibers, at least one other low melting point continuous oxide fiber, and at least one continuous metal fiber;
the continuous fiber layer of the layered structure is a single continuous fiber layer of continuous carbon fiber, low-melting-point continuous oxide fiber or continuous metal fiber,
or a composite fiber layer of continuous carbon fibers and at least one other low melting point continuous oxide fiber,
or a composite continuous fiber layer of continuous carbon fibers, at least one other low melting point continuous oxide fiber, and at least one continuous metal fiber;
the continuous fiber layer is continuous fiber laid cloth or continuous fiber woven cloth; a chopped strand mat is inserted between adjacent continuous fiber layers; the chopped fiber mat is a chopped carbon fiber mat, a chopped low-melting-point oxide fiber mat or a mixed mat of chopped carbon fibers and chopped low-melting-point oxide fibers.
4. The continuous carbon fiber-reinforced ultra-high temperature ceramic matrix composite according to claim 3, wherein interlayer connecting fibers introduced by a needling or stitching process are included between the continuous fiber layer and the chopped strand mat;
the interlayer connecting fiber is carbon fiber, at least one low-melting-point oxide fiber or at least one metal fiber;
or a hybrid fiber of carbon fiber and low-melting point oxide fiber,
or hybrid fibers of carbon fibers, low-melting-point oxide fibers, and metal fibers.
5. The method for preparing the continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite according to claim 1, comprising the steps of:
s1, preparing a hybrid continuous fiber preform of continuous carbon fibers, low-melting-point continuous oxide fibers and continuous metal fibers;
s2, densifying the hybrid continuous fiber preform by using carbon to obtain a porous carbon fiber/inorganic fiber/carbon material; wherein the inorganic fibers comprise low-melting-point continuous oxide fibers and continuous metal fibers;
s3, introducing the ultra-high temperature ceramic phase into the porous carbon fiber/inorganic fiber/carbon material to obtain the target continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite.
6. The method for preparing a continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite according to claim 5, wherein in the step S2, the densification method is one of the following methods:
the method comprises the steps of firstly, chemical vapor infiltration and carbon deposition densification; the step of densifying by chemical vapor infiltration deposition comprises:
taking methane or propylene as a carbon source, taking nitrogen as a carrier gas, and carrying out deposition at a deposition pressure of not higher than 15KPa and a deposition temperature of 800-1200 ℃, and densifying the deposited carbon of the hybrid continuous fiber preform to obtain a porous carbon fiber/inorganic fiber/carbon material with a porosity of 20-80%;
the second method is to impregnate cracking carbon for densification; the steps of densification using dip cracking include:
impregnating the hybrid continuous fiber preform into a vacuum-pressure impregnation tank containing pitch, phenolic resin or furfuryl ketone resin; the impregnation pressure is not higher than 15kPa, and the impregnation temperature is 60-100 ℃; curing after impregnation, setting the curing temperature to be 80-200 ℃, and finally completing carbonization in a carbonization furnace, wherein the carbonization temperature is set to be 600-1300 ℃, so as to obtain the porous carbon fiber/inorganic fiber/carbon material with the porosity of 20-80%.
7. The method for preparing a continuous carbon fiber reinforced ultra-high temperature ceramic matrix composite according to claim 5, wherein in the step S3, the method for introducing the ultra-high temperature ceramic phase is one of the following methods:
the method comprises the steps of firstly, a precursor dipping cracking method; the step of introducing the ultra-high temperature ceramic phase by adopting a precursor dipping and cracking method comprises the following steps:
impregnating the ceramic precursor solution into porous carbon fiber/inorganic fiber/carbon material, and then cracking to ensure that the porosity of the composite material is lower than 15%;
a second method, a reaction infiltration method; the step of introducing the ultra-high temperature ceramic phase by adopting the reaction infiltration method comprises the following steps:
impregnating porous carbon fiber/inorganic fiber/carbon material into metal melt, reacting carbon in the porous material with the metal melt to generate ceramic phase, filling pores so that the porosity of the composite material is lower than 10%, and completing the introduction of the ultra-high temperature ceramic phase; wherein the temperature of the reaction infiltration process is set to 1500-2300 ℃, the pressure is not higher than 10kPa, and the time is 1-10 hours;
a third method, a slurry permeation method; the step of introducing the ultra-high temperature ceramic phase by adopting a slurry permeation method comprises the following steps:
mixing ceramic powder and a solvent, ball milling to obtain uniform ceramic slurry, then penetrating the ceramic slurry into a hybrid continuous fiber preform by using a vacuum tank, and finally drying and heat treating to obtain an initial composite material, wherein the primary or secondary penetration is performed until the porosity of the composite material is lower than 15%; the solvent is water, ethanol, xylene or other organic solvents.
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Citations (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2430720A1 (en) * | 1974-06-26 | 1976-01-22 | Diethelm Dipl Chem Dr Bitzer | Carbon contg. matrix reinforced with short fibres - by sedimentation of mixture then drying has improved orientation |
| US4321042A (en) * | 1976-03-16 | 1982-03-23 | Hans Scheicher | Ceramic dental implant |
| CN1288874A (en) * | 1999-09-16 | 2001-03-28 | Sgl技术有限公司 | Fiber-reinforced ceramic substrate composite material |
| JP2003040685A (en) * | 2001-07-31 | 2003-02-13 | Ngk Insulators Ltd | Oxide fiber composite material and method of manufacturing the same |
| CN102164736A (en) * | 2008-07-23 | 2011-08-24 | 西格里碳素欧洲公司 | Method for producing a fiber-clutch reinforced composite material and fiber clutch reinforced composite material, and use thereof |
| CN102596564A (en) * | 2009-11-23 | 2012-07-18 | 应用纳米结构方案公司 | Ceramic composite materials containing carbon nanotube-infused fiber materials and methods for production thereof |
| CA2859007A1 (en) * | 2011-12-26 | 2013-07-04 | Toray Industries, Inc. | Carbon fiber base, prepreg and carbon-fiber-reinforced composite material |
| CN103724030A (en) * | 2013-05-28 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Carbon fiber-reinforced porous composite material and preparation method thereof |
| CN103724028A (en) * | 2013-07-23 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Metal ceramic matrix composite material used at temperature less than 1,600 DEG C for long time |
| CN103951453A (en) * | 2013-07-23 | 2014-07-30 | 太仓派欧技术咨询服务有限公司 | Metal ceramic matrix composite used at temperature of below 2000 DEG C for long term |
| CN103964881A (en) * | 2013-07-23 | 2014-08-06 | 太仓派欧技术咨询服务有限公司 | Metal whisker strengthening-toughening self-healing ceramic-based composite material |
| CN204702909U (en) * | 2015-04-01 | 2015-10-14 | 赵晓明 | Continuous decentralized filament fiber Nomex |
| CN105237020A (en) * | 2015-08-31 | 2016-01-13 | 中国人民解放军国防科学技术大学 | Carbon fiber-enhanced ZrB2-ZrN composite ceramic-based composite material and preparation method thereof |
| CN106830964A (en) * | 2016-12-29 | 2017-06-13 | 广州凯耀资产管理有限公司 | A kind of lightweight carbon fibre composite and its preparation technology |
| CN107073877A (en) * | 2014-11-13 | 2017-08-18 | 贝克休斯公司 | Strengthen composite, manufacture method and its product |
| CN108033803A (en) * | 2018-01-04 | 2018-05-15 | 中国人民解放军国防科技大学 | Three-dimensional silicon carbide fiber reinforced alumina-zirconia composite material and preparation method thereof |
| CN109400195A (en) * | 2018-11-15 | 2019-03-01 | 福建省德化明英华陶瓷有限公司 | A kind of Wear-resistant corrosion-resistant braiding ceramic composite and forming method, braiding ceramic |
| CN110372390A (en) * | 2019-07-26 | 2019-10-25 | 华中科技大学 | Continuous fiber reinforced SiC part preparation method and product based on increasing material manufacturing |
| CN112876273A (en) * | 2021-03-17 | 2021-06-01 | 中南大学 | High-temperature-resistant wave-absorbing structure integrated ceramic matrix composite and preparation method thereof |
| CN113233909A (en) * | 2021-05-18 | 2021-08-10 | 中国科学院宁波材料技术与工程研究所 | Novel fiber-toughened ceramic-based composite material, and preparation method and application thereof |
| WO2022007377A1 (en) * | 2020-07-09 | 2022-01-13 | 南京航空航天大学 | Composite material enhanced by mixed woven fiber preform and preparation method therefor |
| CN114014678A (en) * | 2021-12-20 | 2022-02-08 | 中南大学 | Quartz fiber/carbon fiber reinforced carbon-based composite flat plate and preparation method thereof |
| CN114560714A (en) * | 2022-03-14 | 2022-05-31 | 宁波杭州湾新材料研究院 | Fiber-toughened ceramic-based composite material and preparation method and application thereof |
| CN114773066A (en) * | 2022-05-19 | 2022-07-22 | 醴陵市凯德特种陶瓷有限公司 | Manufacturing method of toughened silicon carbide ceramic kiln furniture flat plate |
| CN115215670A (en) * | 2022-04-12 | 2022-10-21 | 湖北瑞宇空天高新技术有限公司 | Interlaminar-enhanced ultrahigh-temperature-resistant antioxidant ceramic matrix composite and preparation method thereof |
-
2023
- 2023-06-19 CN CN202310721162.3A patent/CN116462525B/en active Active
Patent Citations (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2430720A1 (en) * | 1974-06-26 | 1976-01-22 | Diethelm Dipl Chem Dr Bitzer | Carbon contg. matrix reinforced with short fibres - by sedimentation of mixture then drying has improved orientation |
| US4321042A (en) * | 1976-03-16 | 1982-03-23 | Hans Scheicher | Ceramic dental implant |
| CN1288874A (en) * | 1999-09-16 | 2001-03-28 | Sgl技术有限公司 | Fiber-reinforced ceramic substrate composite material |
| JP2003040685A (en) * | 2001-07-31 | 2003-02-13 | Ngk Insulators Ltd | Oxide fiber composite material and method of manufacturing the same |
| CN102164736A (en) * | 2008-07-23 | 2011-08-24 | 西格里碳素欧洲公司 | Method for producing a fiber-clutch reinforced composite material and fiber clutch reinforced composite material, and use thereof |
| CN102596564A (en) * | 2009-11-23 | 2012-07-18 | 应用纳米结构方案公司 | Ceramic composite materials containing carbon nanotube-infused fiber materials and methods for production thereof |
| CA2859007A1 (en) * | 2011-12-26 | 2013-07-04 | Toray Industries, Inc. | Carbon fiber base, prepreg and carbon-fiber-reinforced composite material |
| CN103724030A (en) * | 2013-05-28 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Carbon fiber-reinforced porous composite material and preparation method thereof |
| CN103724028A (en) * | 2013-07-23 | 2014-04-16 | 太仓派欧技术咨询服务有限公司 | Metal ceramic matrix composite material used at temperature less than 1,600 DEG C for long time |
| CN103951453A (en) * | 2013-07-23 | 2014-07-30 | 太仓派欧技术咨询服务有限公司 | Metal ceramic matrix composite used at temperature of below 2000 DEG C for long term |
| CN103964881A (en) * | 2013-07-23 | 2014-08-06 | 太仓派欧技术咨询服务有限公司 | Metal whisker strengthening-toughening self-healing ceramic-based composite material |
| CN107073877A (en) * | 2014-11-13 | 2017-08-18 | 贝克休斯公司 | Strengthen composite, manufacture method and its product |
| CN204702909U (en) * | 2015-04-01 | 2015-10-14 | 赵晓明 | Continuous decentralized filament fiber Nomex |
| CN105237020A (en) * | 2015-08-31 | 2016-01-13 | 中国人民解放军国防科学技术大学 | Carbon fiber-enhanced ZrB2-ZrN composite ceramic-based composite material and preparation method thereof |
| CN106830964A (en) * | 2016-12-29 | 2017-06-13 | 广州凯耀资产管理有限公司 | A kind of lightweight carbon fibre composite and its preparation technology |
| CN108033803A (en) * | 2018-01-04 | 2018-05-15 | 中国人民解放军国防科技大学 | Three-dimensional silicon carbide fiber reinforced alumina-zirconia composite material and preparation method thereof |
| CN109400195A (en) * | 2018-11-15 | 2019-03-01 | 福建省德化明英华陶瓷有限公司 | A kind of Wear-resistant corrosion-resistant braiding ceramic composite and forming method, braiding ceramic |
| CN110372390A (en) * | 2019-07-26 | 2019-10-25 | 华中科技大学 | Continuous fiber reinforced SiC part preparation method and product based on increasing material manufacturing |
| WO2022007377A1 (en) * | 2020-07-09 | 2022-01-13 | 南京航空航天大学 | Composite material enhanced by mixed woven fiber preform and preparation method therefor |
| CN112876273A (en) * | 2021-03-17 | 2021-06-01 | 中南大学 | High-temperature-resistant wave-absorbing structure integrated ceramic matrix composite and preparation method thereof |
| CN113233909A (en) * | 2021-05-18 | 2021-08-10 | 中国科学院宁波材料技术与工程研究所 | Novel fiber-toughened ceramic-based composite material, and preparation method and application thereof |
| CN114014678A (en) * | 2021-12-20 | 2022-02-08 | 中南大学 | Quartz fiber/carbon fiber reinforced carbon-based composite flat plate and preparation method thereof |
| CN114560714A (en) * | 2022-03-14 | 2022-05-31 | 宁波杭州湾新材料研究院 | Fiber-toughened ceramic-based composite material and preparation method and application thereof |
| CN115215670A (en) * | 2022-04-12 | 2022-10-21 | 湖北瑞宇空天高新技术有限公司 | Interlaminar-enhanced ultrahigh-temperature-resistant antioxidant ceramic matrix composite and preparation method thereof |
| CN114773066A (en) * | 2022-05-19 | 2022-07-22 | 醴陵市凯德特种陶瓷有限公司 | Manufacturing method of toughened silicon carbide ceramic kiln furniture flat plate |
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