CN113857603A - Method for assisting in brazing ceramic matrix composite material and metal - Google Patents
Method for assisting in brazing ceramic matrix composite material and metal Download PDFInfo
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- CN113857603A CN113857603A CN202111148966.6A CN202111148966A CN113857603A CN 113857603 A CN113857603 A CN 113857603A CN 202111148966 A CN202111148966 A CN 202111148966A CN 113857603 A CN113857603 A CN 113857603A
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- 238000005219 brazing Methods 0.000 title claims abstract description 68
- 239000002184 metal Substances 0.000 title claims abstract description 58
- 229910052751 metal Inorganic materials 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims abstract description 34
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 28
- 239000000463 material Substances 0.000 title claims description 21
- 239000002131 composite material Substances 0.000 claims abstract description 45
- 239000000835 fiber Substances 0.000 claims abstract description 38
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 22
- 229910021389 graphene Inorganic materials 0.000 claims abstract description 22
- 239000000945 filler Substances 0.000 claims description 26
- 239000011888 foil Substances 0.000 claims description 26
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 15
- 229910052681 coesite Inorganic materials 0.000 claims description 11
- 229910052906 cristobalite Inorganic materials 0.000 claims description 11
- 239000000377 silicon dioxide Substances 0.000 claims description 11
- 229910052682 stishovite Inorganic materials 0.000 claims description 11
- 229910052905 tridymite Inorganic materials 0.000 claims description 11
- 239000003054 catalyst Substances 0.000 claims description 8
- 238000010438 heat treatment Methods 0.000 claims description 8
- 238000000623 plasma-assisted chemical vapour deposition Methods 0.000 claims description 6
- 229910017693 AgCuTi Inorganic materials 0.000 claims description 5
- 239000011208 reinforced composite material Substances 0.000 claims description 5
- 229910000679 solder Inorganic materials 0.000 claims description 5
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 3
- 238000000137 annealing Methods 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 3
- 239000005350 fused silica glass Substances 0.000 claims description 3
- 239000012535 impurity Substances 0.000 claims description 3
- 239000007788 liquid Substances 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 3
- 238000002791 soaking Methods 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 2
- 229910052593 corundum Inorganic materials 0.000 claims description 2
- VCJMYUPGQJHHFU-UHFFFAOYSA-N iron(III) nitrate Inorganic materials [Fe+3].[O-][N+]([O-])=O.[O-][N+]([O-])=O.[O-][N+]([O-])=O VCJMYUPGQJHHFU-UHFFFAOYSA-N 0.000 claims description 2
- 229910001960 metal nitrate Inorganic materials 0.000 claims description 2
- 229910001845 yogo sapphire Inorganic materials 0.000 claims description 2
- 150000002739 metals Chemical class 0.000 claims 6
- 238000003466 welding Methods 0.000 abstract description 6
- 239000000919 ceramic Substances 0.000 abstract description 5
- 239000011229 interlayer Substances 0.000 abstract description 5
- 230000003014 reinforcing effect Effects 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 13
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- 238000001035 drying Methods 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000002245 particle Substances 0.000 description 2
- 239000011226 reinforced ceramic Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000007740 vapor deposition Methods 0.000 description 2
- 238000009941 weaving Methods 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 229920002134 Carboxymethyl cellulose Polymers 0.000 description 1
- 229920002430 Fibre-reinforced plastic Polymers 0.000 description 1
- 229910021538 borax Inorganic materials 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 235000010948 carboxy methyl cellulose Nutrition 0.000 description 1
- 229920006184 cellulose methylcellulose Polymers 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 238000012710 chemistry, manufacturing and control Methods 0.000 description 1
- 239000012459 cleaning agent Substances 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
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- 239000003733 fiber-reinforced composite Substances 0.000 description 1
- 239000011151 fibre-reinforced plastic Substances 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 239000002241 glass-ceramic Substances 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- -1 graphite alkene Chemical class 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 150000004767 nitrides Chemical class 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 239000004328 sodium tetraborate Substances 0.000 description 1
- 235000010339 sodium tetraborate Nutrition 0.000 description 1
- 238000005019 vapor deposition process Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
- C04B35/14—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on silica
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
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- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
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- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
- C04B41/5001—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials with carbon or carbonisable materials
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- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
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- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
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- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
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- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
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Abstract
The invention discloses a method for assisting brazing of a ceramic matrix composite and metal, which is characterized in that a graphene reinforced short fiber is introduced to be woven in a three-dimensional mode, and a ceramic matrix composite interlayer in a loose and porous structure assists in brazing connection of the composite and the metal. Therefore, the problems that the residual stress of the brazed joint is too high, the introduced amount of a ceramic reinforcing phase is small and the brittleness of a welding seam is aggravated due to the fact that the coefficient of thermal expansion of the existing ceramic and metal is not matched greatly are solved.
Description
Technical Field
The invention relates to a method for auxiliary brazing of an interlayer. The invention relates to the technical field of composite materials, in particular to a method for assisting brazing of a ceramic matrix composite material and metal.
Background
The ceramic matrix composites (CMCs for short) have excellent performances of high temperature resistance, oxidation resistance, corrosion resistance, high strength, high rigidity, low density and the like, and have wide application prospects in the fields of aerospace, machinery, automobiles and the like.
To date, development and application of ceramic matrix composites has been a 60 year history: fiber reinforced plastic → alumina ceramic → glass-ceramics → quartz ceramic → nitride ceramic, evolving to date continuous fiber reinforced ceramic matrix wave-transparent composites. Continuous fiber reinforced ceramic matrix composites are considered potential materials for advanced aircraft engines, spaces, and fusion power reactors by virtue of their high surface strength at high temperatures and high fracture toughness. However, the fiber-reinforced composite material has poor workability, and is difficult to be prepared into a large-sized structural member having a complicated shape, and thus the composite material needs to be connected with metal to achieve wide application.
When the ceramic matrix composite and the metal are connected by adopting an active brazing method, the thermal expansion coefficient of the composite and the metal or the active brazing filler metal is not matched, so that large residual stress is generated in the joint, and the strength of the joint is reduced. At present, researchers have found out the residual stress of the braze joint formed by the ceramic matrix composite and the metal: the residual stress can be relieved by adding the nanoparticle phase into the brazing filler metal, but the addition amount of the nanoparticle phase is very limited (< 6-8 wt.%), however, the addition amount is too large, and the nanoparticle phase can be agglomerated in a welding line, so that the residual stress relief by adding the nanoparticle phase is very limited. The researchers also introduce the ceramic material woven by short fibers as the middle layer to meet the requirement that the short fibers are added into the brazing filler metal in a large amount, but in the brazing process, the short fibers and the active brazing filler metal are subjected to excessive reaction to cause the collapse of the three-dimensional woven structure of the composite material, the segregation of compound particle phases formed by the reaction occurs, and the joint strength is reduced.
Disclosure of Invention
The embodiment of the application provides a method for assisting brazing of ceramic matrix composite and metal, the adoption is loose, porous structure's graphite alkene strengthens short fiber woven materials as the intermediate level, supplementary brazing, can make a large amount of short fibers dispersion in the welding seam, and the intermediate level can keep complete woven structure, thereby it is too high to solve current pottery and the great brazing joint residual stress that leads to of metal thermal expansion coefficient mismatching degree, the leading-in volume of ceramic reinforcing phase is few, and make the problem of welding seam fragility aggravation, effectively alleviate brazing residual stress, improve the brazing strength, realize the high quality of combined material and metal and be connected.
The embodiment of the application provides a method for assisting in brazing ceramic matrix composite and metal, the graphene-reinforced short fiber woven composite is used as an intermediate layer to assist in brazing, and the method comprises the following specific steps:
the method comprises the following steps: immersing three-dimensional braided short fiber into liquid fused quartz, wherein the short fiber is SiO2Fibres or Al2O3Standing the fiber for 5-20 min, then carrying out vacuum annealing at the temperature of 400-800 ℃ for 2-5 h, and repeating the above processes for 2-5 times to obtain an annealed short fiber woven composite material; cutting a composite material woven by short fibers into a sheet with the thickness of 50-200 mu m, and preferably cutting the composite material woven by the short fibers by using a diamond wire cutting machine;
step two: soaking the flaky composite material in a catalyst solution with the concentration of 0.01-0.2 mol/L, wherein the catalyst is a metal nitrate solution, drying the catalyst in air, and then carrying out vapor deposition by adopting a PECVD method, and further, in the vapor deposition process, the heating temperature is 500-800 ℃, the pressure is set at 400-1000 Pa under the heating temperature, the radio frequency is started, the radio frequency time is 10-60 min, and Ar and CH are subjected to heat treatment4The gas flow ratio of the graphene/the carbon fiber composite material is 2-20, and the radio frequency power is 100-200W, so that the graphene reinforced short fiber woven composite material is obtained; the pecvd (plasma Enhanced Chemical Vapor deposition) refers to a Vapor deposition method of plasma Enhanced Chemical;
step three: and polishing the metal to be welded, the ceramic matrix composite to be welded and the brazing filler metal foil by using sand paper, further cleaning the metal to be welded, the ceramic matrix composite to be welded and the brazing filler metal foil by using a chemical cleaning agent to further remove surface impurities, sequentially stacking the composite to be welded, the brazing filler metal foil and the prepared graphene reinforced composite intermediate layer, the brazing filler metal foil and the metal to be welded in sequence, brazing in a vacuum furnace at the brazing temperature of 550-1300 ℃ for 5-30 min, and finally cooling along with the furnace to finish welding.
Preferably, in the step one, the thickness of the composite material intermediate layer is 50 to 200 μm, and the thickness is 25 μm as a unit.
Preferably, in step two, the catalyst solution is Ni (NO)3)2、Fe(NO3)3Or Cu (NO)3)2Any one of them.
Preferably, in the second step, the concentration of the catalyst is 0.05 mol/L-0.2 mol/L.
Preferably, in the second step, the heating temperature is 600 ℃.
Preferably, in the second step, the radio frequency time is 10-40 min.
Preferably, in the third step, the brazing filler metal foil is AgCuTi brazing filler metal foil, AgCu brazing filler metal foil, tizronicu brazing filler metal foil, BNi2 brazing filler metal foil, BNi5 brazing filler metal foil or AlSi12 brazing filler metal foil.
Preferably, in the third step, the thickness of the solder foil is preferably 100 μm.
Preferably, in the third step, the brazing temperature is 600-1140 ℃.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
according to the method for assisting brazing of the ceramic matrix composite and the metal, the composite material which is formed by weaving the short graphene reinforced fibers in a loose and porous structure is prepared by three-dimensionally weaving the short graphene reinforced fibers, and the short graphene reinforced fiber woven composite material is used as the middle layer for assisting brazing, so that the method is simple, efficient and obvious in effect;
in the prior art methods of interlayer assisted brazing,the method is characterized in that nano-particle-phase borax or graphene is added into the brazing filler metal, and a nano-particle-phase compound is formed in the brazing process to relieve residual stress, however, the addition amount of the nano-particle phase is very limited, the effect of relieving the residual stress is also very limited, although short fibers can be added into the brazing filler metal in a large amount, the short fibers and the active brazing filler metal excessively cause the middle layer to react and collapse, and the joint strength is not high; the graphene reinforced short fiber three-dimensional woven material is adopted as the middle layer for auxiliary brazing, the advantages of the graphene reinforced short fiber three-dimensional woven material and the middle layer can be integrated, a large amount of short fibers can be ensured to be added, the condition that a large amount of short fibers are dispersed and distributed in a welding seam is met, and therefore a good thermal expansion coefficient gradient transition is formed in a joint, specifically metal (12-17 multiplied by 10)-6K-1) Brazing filler metal (5-8 x 10)-6K-1) And a composite material (1-2X 10)-6K-1) The coefficient of thermal expansion among the three has a good gradient transition, and the intermediate layer has a complete structure, so that the residual stress of the joint is effectively relieved, the strength of the joint is improved, and the high-quality connection of the composite material and the metal is realized.
Drawings
FIG. 1 shows SiO in the first embodiment of the present application2f/SiO2Growing the microscopic morphology of graphene on the surface of the composite material;
FIG. 2 shows SiO in the first embodiment of the present application2f/SiO2Composite to TC4 joint microstructures;
FIG. 3 shows SiO in comparative example one of the present application2f/SiO2Composite to TC4 joint microstructures;
FIG. 4 is a schematic view showing the stacking sequence of brazing materials according to the first example and the first comparative example of the present application.
Detailed Description
In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the detailed description.
The technical solution of the present invention is not limited to the specific embodiments listed below, and includes any combination of the specific embodiments.
Example one
The method for assisting in brazing the ceramic matrix composite material and the metal in the embodiment is specifically performed according to the following steps:
step one, immersing three-dimensionally woven short fibers into liquid fused quartz, standing for 5-20 min, then carrying out vacuum annealing at the temperature of 400-800 ℃ for 2-5 h, and repeating the above processes for 2-5 times to obtain the annealed short fiber woven ceramic matrix composite; placing the annealed composite material on a diamond wire cutting machine, processing the composite material into a flaky composite material with the thickness of 5mm multiplied by 100 mu m to obtain SiO2A middle layer of ceramic matrix composite material woven by short fiber.
Step two, soaking the flaky composite material in Cu (NO) with the concentration of 0.1mol/L3)2Drying in air, heating in a PECVD furnace at 600 deg.C under 1000Pa, starting radio frequency for 10min, and collecting Ar and CH4The gas flow ratio of (a) is 4, and the radio frequency power is 200W, so that the graphene reinforced composite material intermediate layer is obtained.
Step three, using sand paper to carry out the treatment on TC4 and SiO2f/SiO2Polishing the surfaces of the composite material and the AgCuTi brazing filler metal foil, chemically cleaning to remove surface impurities, and then carrying out SiO treatment2f/SiO2The composite material/AgCuTi solder foil/graphene reinforced short fiber woven composite material interlayer/AgCuTi solder foil/TC 4 are placed in a vacuum furnace for brazing, the brazing temperature is 860 ℃, the heat preservation time is 10min, and finally the temperature is reduced along with the furnace, and the joint strength reaches 40 MPa.
Comparative example 1
As shown in FIG. 4, the difference from the first example is only that in the first comparative example, SiO is assisted by the composite material interlayer which is woven by adding short fiber2f/SiO2The brazing of the composite material to TC4 was carried out in the same manner as in example one, except that the joint strength obtained was less than 5 MPa.
The microstructure of the surface of the intermediate layer of the graphene reinforced composite material in the first embodiment is shown in fig. 1, and it can be seen from fig. 1 that the graphene grown on the surface of the composite material is well formed.
SiO obtained in example one2f/SiO2The microstructure of the composite material and TC4 joint is shown in FIG. 2. from FIG. 2, it can be seen that a large number of short fibers and a particle phase obtained by reacting the short fibers with the reactive filler metal are dispersed in the weld.
SiO obtained in comparative example 12f/SiO2The microstructure of the composite and TC4 joint is shown in fig. 3, and it can be seen from fig. 3 that the middle layer is biased.
Claims (9)
1. A method for assisting in brazing ceramic matrix composite materials to metals, comprising the steps of:
the method comprises the following steps: immersing three-dimensional braided short fiber into liquid fused quartz, wherein the three-dimensional braided short fiber is SiO2Fiber and Al2O3Standing the fiber for 5-20 min, then, repeating the process for 2-5 times at the temperature of 400-800 ℃ for 2-5 h in vacuum annealing to obtain an annealed short fiber braided composite material, and processing the blocky ceramic matrix composite material into a sheet shape;
step two: growing graphene on the surface of the flaky short fiber braided composite material obtained in the step one by adopting a PECVD method to obtain a graphene reinforced composite material;
step three: and taking the graphene reinforced composite material as an intermediate layer for auxiliary brazing, sequentially stacking the composite material to be brazed, the brazing filler metal foil, the graphene reinforced intermediate layer, the brazing filler metal foil and the metal to be brazed in sequence in the brazing process, placing the stack in a vacuum furnace for brazing, and finally cooling the stack along with the furnace.
2. The method for assisting in brazing ceramic matrix composites to metal of claim 1 wherein in step one, the laminar composite has a thickness in the range of 50 to 200 μm.
3. The method of claim 1, wherein the brazing of the ceramic matrix composite material to the metal is assisted by brazingCharacterized in that the second step specifically comprises the following operations: soaking a flaky composite material in a catalyst solution with the concentration of 0.01-0.2 mol/L, wherein the catalyst is a metal nitrate solution, airing the flaky composite material in air, placing the dried flaky composite material in a PECVD (plasma enhanced chemical vapor deposition) furnace for heating at the temperature of 500-800 ℃, setting the pressure at the heating temperature, the pressure value is 400-1000 Pa, starting radio frequency, the radio frequency time is 10-60 min, and Ar and CH are subjected to heat treatment4The gas flow ratio of the graphene oxide/graphene oxide composite material is 2-20, and the radio frequency power is 100-200W, so that the graphene reinforced composite material intermediate layer is obtained.
4. The method of assisting in brazing of a ceramic matrix composite material to a metal of claim 1, wherein step three further comprises: and (3) polishing the metal to be welded, the composite material to be welded and the brazing filler metal foil by using abrasive paper, chemically cleaning to remove surface impurities, and then stacking and placing in a vacuum furnace for brazing.
5. The method for assisting in brazing ceramic matrix composite materials to metals according to claim 1, wherein the brazing temperature in step three is 550 to 1300 ℃ and the holding time is 5 to 30 min.
6. The method for assisting in brazing ceramic matrix composite materials to metals of claim 3 wherein said catalyst solution is Ni (NO)3)2、Fe(NO3)3Or Cu (NO)3)2Any one of them.
7. The method for assisting in brazing ceramic matrix composite materials to metals of claim 1 wherein said braze foil of step three is AgCuTi braze foil, AgCu braze foil, TiZrNiCu braze foil, BNi2Brazing filler metal foil, BNi5Solder foil or AlSi12Any one of solder foils.
8. The method for assisting in the brazing of ceramic matrix composite materials to metals according to claim 1, wherein in step three, the brazing filler metal foil is preferably 100 μm thick.
9. The method for assisting in brazing ceramic matrix composite materials to metals of claim 1 wherein in step three, said brazing temperature is 860 ℃ and holding time is 10 min.
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