CN103113112B - Preparation method of metal toughened ceramic-based composite material turbine blade - Google Patents

Preparation method of metal toughened ceramic-based composite material turbine blade Download PDF

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CN103113112B
CN103113112B CN201310044604.1A CN201310044604A CN103113112B CN 103113112 B CN103113112 B CN 103113112B CN 201310044604 A CN201310044604 A CN 201310044604A CN 103113112 B CN103113112 B CN 103113112B
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ceramic
turbine blade
metal
metal toughened
skeleton
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CN201310044604.1A
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CN103113112A (en
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鲁中良
李涤尘
刘涛
荆慧
卢秉恒
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西安交通大学
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Abstract

The invention discloses a preparation method of a metal toughened ceramic-based composite material turbine blade. According to the preparation method, the metal 3D (three dimensional) printing technology, the stereolithography rapid molding technology, the chemical vapor deposition technology and the gel-casting molding technology are combined, a metal toughened skeleton with desired structural type is manufactured by the 3D printing technology, and the metal toughened skeleton is embedded into a ceramic product to enhance the toughness of the ceramic turbine blade. By utilizing the preparation method, the metal toughened skeleton is embedded into a ceramic product to greatly improve the toughness of the ceramic product, and a silicon carbide ceramic material prepared by transforming a precursor has high strength. Compared with the conventional metal blade, by utilizing the metal toughened ceramic-based composite material turbine blade, the quality of the blade can be greatly lightened, and the thrust-weight ratio of an engine can be greatly improved.

Description

A kind of preparation method of Metal toughened ceramic matrix composite turbine blade
Technical field
The invention belongs to turbine blade manufacturing technology field, relate to a kind of preparation method of Metal toughened ceramic matrix composite turbine blade.
Background technique
Turbine blade is one of core component of aeroengine.Turbine blade is operated in the position that in aeroengine, environment is the most severe, temperature is the highest, stress is the most complicated, and its design has a direct impact the combination property to aeroengine with manufacture level.The manufacturing representative of blade of aviation engine manufacturing highest level, has become to a certain extent the important symbol of weighing a national manufacture level.The operating ambient temperature of blade of aviation engine is generally more than 1000 ℃, and in firing chamber, fuel gas temperature is higher, and the thrust that energy utilization rate is higher, motor produces is larger.Due to the restriction of melting point metal, the fuel gas temperature limit that alloy can bear that reached a high temperature before turbine.Improve blade cooling structure and can improve to a certain extent the warm ability of holding of blade, but the complicated of blade cooling structure had higher requirement to manufacture level, be subject to the restriction of existing manufacture level, the manufacture difficulty of hollow turbine vane with complicated cooling structure is very large, and manufacture cost is very high.
Under exploitation high temperature, can keep high performance structural material, to the manufacture important in inhibiting of aeroengine.Advanced ceramics material, owing to having excellent high mechanical property, is subject to materials science worker's attention always.Stupalith has the advantages such as intensity is high, high temperature resistant, quality is light, is the ideal material of manufacturing turbine blade.But stupalith, because hardness is high, fragility is large, is difficult to machine shaping, and the surface configuration complexity of blade, therefore, the moulding problem that solves ceramic blade is most important.
The moulding that Gelcasting Technique is ceramic blade provides a kind of new approach.Gelcasting Technique is a kind of new forming process of ceramics technology of Oak Ridge National Key Laboratory of U.S. invention.This technology combines traditional ceramic preparation method with polymer chemistry, be a kind of novel near-net-shape technology of preparing complicated shape ceramic part.First the method configures high solid phase, low viscous ceramic size, then the ceramic size of good fluidity is poured in mould under vacuum environment, and in-situ solidifying reaction occurs ceramic size under the effect of catalyzer, initator, forms ceramic part base substrate.The method can be used for the manufacture of ceramic blade, has successfully solved the problem of ceramic blade difficult forming.
Summary of the invention
The problem that the present invention solves is to provide a kind of preparation method of Metal toughened ceramic matrix composite turbine blade, make combining of metal frame and ceramics turbo blade, obtain the inner ceramics turbo blade with metal frame, strengthened the toughness of ceramics turbo blade.
The present invention is achieved through the following technical solutions:
A preparation method for Metal toughened ceramic matrix composite turbine blade, comprises the following steps:
1) print by metal 3D the Metal toughened skeleton that technique is prepared turbine blade, then form ceramic interfacial layers by vapor deposition on Metal toughened skeleton surface;
2) will there is the Metal toughened skeleton of ceramic interfacial layers and the light-cured resin mould of turbine blade combines, obtain the inner resin die with Metal toughened skeleton;
3) prepare ceramic size by gel injection-moulding technique, under vacuum environment, cast ceramics slurry, to resin die, obtains ceramics turbo blade base substrate;
4) remove resin die by chemical corrosion method, adopt vacuum freezing drying to remove the moisture in ceramic body, to improve precision, then under shielding gas atmosphere in 1200~1400 ℃ of sintering 3~6h, realize composite porous turbine blade prototype;
5) in the hole of composite turbine blade, generate silicon carbide ceramics by chemical vapor deposition, carry out densification, realize ceramic matrix composite turbine blade.
The metal 3D of described Metal toughened skeleton prints and comprises:
First design the Metal toughened skeleton of desired structure form by 3D sculpting software;
Then the threedimensional model of Metal toughened skeleton is carried out after hierarchy slicing processing, import in 3D printing device, obtain Metal toughened skeleton by precinct laser fusion metallic dust.
Described metallic dust is titanium alloy powder or powder of stainless steel;
Being set to of laser: power is 120~200W, sweep rate 50~100mm/s, sweep span 0.05~0.1mm, bed thickness 0.05~0.1mm.
The material of described ceramic interfacial layers is silicon nitride or silicon carbide.
Described silicon nitride ceramics interface layer be with silane and ammonia respectively as silicon source and nitrogenous source, form ceramic interfacial layers in the vapor deposition of Metal toughened Skeleton Table surface chemistry;
Described silicon carbide ceramics interface layer is take trichloromethyl silane as source of the gas, and hydrogen or nitrogen are carrier gas, forms ceramic interfacial layers in the vapor deposition of Metal toughened Skeleton Table surface chemistry.
The light-cured resin mould of described turbine blade is the resin enclosure of manufacturing the turbine blade of required structure by light-curing rapid forming equipment.
The described operation that obtains ceramics turbo blade base substrate comprises:
1) by organic monomer acrylamide and crosslinking agent N, N '-methylene-bisacrylamide, is dissolved in water according to mass ratio 20~25:1, adds stirring and dissolving after dispersing agent, is mixed with solid phase mass concentration and is 10~20% premixed liquid;
2) according to carborundum powder: carbon dust: silica flour=(20~60): (12~24): the mass ratio of (28~56) fully mixes silicon carbide, carbon and Si powder, obtains solid powder;
3) premixed liquid and solid powder fully being made to solid concentration by ball milling is 50~60% ceramic size, and ceramic size is fully disperseed by ball milling;
4) in ceramic size, add catalyzer, initator, after stirring, be poured in resin die by type vacuum injecting and forming machine, there is curing reaction in the organic substance in porcelain slurry, after curing reaction completes, obtain ceramics turbo blade base substrate under the effect of catalyzer, initator.
Resin die is removed in described chemical corrosion: the ceramics turbo blade base substrate with resin die is put into corrosive liquid, and resin die is successively removed under the corrosive action of corrosive liquid;
Described corrosive liquid is the mixed solution of caustic potoash, alcohol and water, and wherein the mass fraction of caustic potoash is 5~35%, and the volume ratio of alcohol and water is 2~5:4~8, and described alcohol is methyl alcohol or ethanol.
The operation that described vacuum freezing drying is removed the moisture in ceramic body comprises:
At-30 ℃~-60 ℃, be frozen into after ice crystal until water of crystallization in ceramic body, be vacuum freezing drying under 10~30Pa in degree of vacuum.
Described silicon carbide densification is take trichloromethyl silane as source of the gas, take hydrogen or nitrogen as carrier gas, is converted into thyrite by chemical vapor deposition, is filled in the hole of composite turbine blade.
Compared with prior art, the present invention has following useful technique effect:
The preparation method of Metal toughened ceramic matrix composite turbine blade provided by the invention, metal 3D printing technique, Introduction To Stereolithography, chemical vapour deposition technique, Gelcasting Technique are combined, concrete: adopt gas phase deposition technology in metal frame surface preparation ceramic interfacial layers, then Metal toughened skeleton is combined with light-cured resin mould; By gel injection-moulding technique, to cast ceramics slurry in resin die, under the effect of catalyzer, initator, ceramic size generation curing reaction obtains turbine blade base substrate; Adopt the method for chemical corrosion to remove resin die, guarantee the dimensional accuracy of turbine blade by vacuum freezing drying; After ceramics turbo blade sintering, realize silicon carbide ceramics by chemical vapor deposition and be filled in turbine blade internal void, realize the preparation of compact silicon carbide ceramic blade.So just produce the Metal toughened skeleton of desired structure form by metal 3D printing technique, realize the toughness reinforcing skeleton of implanted metal in ceramic products, strengthened the toughness of ceramics turbo blade.
The preparation method of Metal toughened ceramic matrix composite turbine blade provided by the invention, the toughness reinforcing skeleton of implanted metal in ceramic objects, greatly improved the toughness of ceramic objects, meanwhile, the thyrite that transforms preparation by pioneer has good intensity.
The present invention is particularly useful for the manufacture of low-pressure turbine blade, and the turbine blade of manufacturing by the method not only has good hot strength and high temperature toughness, and, compared with traditional metal blade, can greatly alleviate the quality of blade, improve the thrust weight ratio of motor.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in further detail, and the explanation of the invention is not limited.
Embodiment 1:
A preparation method for Metal toughened ceramic matrix composite turbine blade, comprises the following steps:
(1) manufacture of Metal toughened skeleton.
1) first design the metal frame of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) threedimensional model of the metal frame obtaining is carried out after hierarchy slicing processing, import in 3D printing device and process.Metallic dust used is high-melting-point powder, is specially titanium alloy powder, and 3D printing device design parameter is as follows, laser power 150W, laser scanning speed 50mm/s-100mm/s, sweep span 0.05mm-0.1mm, bed thickness 0.05mm-0.1mm.
3) with silane and ammonia respectively as silicon source and nitrogenous source, form one deck silicon nitride ceramics interface layer by chemical vapor deposition on metal frame surface.
(2) by light-curing rapid forming equipment finished parts resin enclosure, resin material is selected 19120 resins.The metal frame of preparing is combined with light-cured resin shell, obtain the resin die with Metal toughened skeleton towards complex parts.
(3) prepare high solid phase, low viscous ceramic size by gel injection-moulding technique, under vacuum environment, cast ceramics slurry, in mould, obtains ceramic products base substrate.
1) first by organic monomer AM(acrylamide) and crosslinking agent MBAM(N, N '-methylene-bisacrylamide) be dissolved in deionized water according to mass ratio 24:1, add again appropriate dispersing agent (common dispersants, dispersing agent addition be solid powder quality 2%), stirring and dissolving, is mixed with organic concentration and is 15% premixed liquid.
2) according to carborundum powder: the mass ratio of carbon dust: silica flour=40:20:35 weighs solid powder (carborundum powder, carbon dust, silica flour), and solid powder is stirred, mixed.
3) premixed liquid preparing is poured in ball grinding drum, the solid powder mixing is slowly joined in premixed liquid, and constantly stir, prepare solid concentration and be 60% ceramic size.
4) adding corundum abrading-ball according to pellet mass ratio 1:2.5, is 360r/min by planetary ball mill rotational speed regulation, and ball milling 60 ~ 90min, disperses, and obtains the ceramic size of good fluidity.
5) to successively adding pre-configured catalyzer TEMED(tetramethylethylenediamine in ceramic size), initiator A PS(ammonium persulfate solution), after stirring at type vacuum injecting and forming machine upper in resin die, in casting process by vibration mode remove the bubble in slurry.In 5 ~ 15min, there is curing reaction in the organic substance in ceramic size under the effect of catalyzer, initator, forms ceramic body.
(4) the ceramics turbo blade with resin enclosure is put into the mixed solution (the shared mass fraction of caustic potoash is 20%, ethanol: water=2:5) of caustic potoash/ethanol/water, resin enclosure is successively removed under the corrosive action of corrosive liquid.
(5) ceramic body is put into the reach in freezer of-30 ℃--60 ℃, become after ice crystal until water of crystallization fully charge in base substrate, utilize vacuum freeze-drying technique to be dried (degree of vacuum is 10 ~ 30Pa).
(6) dried ceramic blade base substrate is put into the high temperature sintering furnace sintering that is connected with argon shield, 1400 ℃ of sintering temperatures.
(7) take trichloromethyl silane (MTS) as source of the gas, with hydrogen (H 2) be carrier gas, be converted into thyrite by chemical vapor deposition, fill the space of turbine blade inside, realize the preparation of compact silicon carbide ceramic body material, obtain Metal toughened ceramic matrix composite turbine blade.
Embodiment 2:
A preparation method for Metal toughened ceramic matrix composite turbine blade, comprises the following steps:
(1) manufacture of Metal toughened skeleton
1) first design the metal frame of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) threedimensional model of the metal frame obtaining is carried out after hierarchy slicing processing, import in 3D printing device and process.Metallic dust used is high-melting-point powder, is specially titanium alloy powder, and 3D printing device design parameter is as follows, laser power 200W, laser scanning speed 60mm/s-80mm/s, sweep span 0.05mm-0.08mm, bed thickness 0.05mm-0.08mm.
3) with silane and ammonia respectively as silicon source and nitrogenous source, form one deck silicon nitride ceramics interface layer by chemical vapor deposition on metal frame surface.
(2) by light-curing rapid forming equipment finished parts resin enclosure, resin material is selected 19120 resins.The metal frame of preparing is combined with light-cured resin shell, obtain the resin die with Metal toughened skeleton towards complex parts.
(3) prepare high solid phase, low viscous ceramic size by gel injection-moulding technique, under vacuum environment, cast ceramics slurry, in mould, obtains ceramic products base substrate.
1) first by organic monomer AM(acrylamide) and crosslinking agent MBAM(N, N '-methylene-bisacrylamide) be dissolved in deionized water according to mass ratio 20:1, add again appropriate dispersing agent (common dispersants, dispersing agent addition be solid powder quality 2%), stirring and dissolving, is mixed with organic concentration and is 15% premixed liquid.
2) according to carborundum powder: the mass ratio of carbon dust: silica flour=50:24:55 weighs solid powder (carborundum powder, carbon dust, silica flour), and solid powder is stirred, mixed.
3) premixed liquid preparing is poured in ball grinding drum, the solid powder mixing is slowly joined in premixed liquid, and constantly stir, prepare solid concentration and be 60% ceramic size.
4) adding corundum abrading-ball according to pellet mass ratio 1:2.5, is 360r/min by planetary ball mill rotational speed regulation, and ball milling 60 ~ 90min, disperses, and obtains the ceramic size of good fluidity.
5) to successively adding pre-configured catalyzer TEMED(tetramethylethylenediamine in ceramic size), initiator A PS(ammonium persulfate solution), after stirring at type vacuum injecting and forming machine upper in resin die, in casting process by vibration mode remove the bubble in slurry.In 5 ~ 15min, there is curing reaction in the organic substance in ceramic size under the effect of catalyzer, initator, forms ceramic body.
(4) the ceramics turbo blade with resin enclosure is put into the mixed solution (the shared mass fraction of caustic potoash is 35%, ethanol: water=2:8) of caustic potoash/ethanol/water, resin enclosure is successively removed under the corrosive action of corrosive liquid.
(5) ceramic body is put into the reach in freezer of-30 ℃--60 ℃, become after ice crystal until water of crystallization fully charge in base substrate, utilize vacuum freeze-drying technique to be dried (degree of vacuum is 10 ~ 30Pa).
(6) dried ceramic blade base substrate is put into the high temperature sintering furnace sintering that is connected with argon shield, 1200 ℃ of sintering temperatures, sintering 4.5h.
(7) take trichloromethyl silane (MTS) as source of the gas, with hydrogen (H 2) be carrier gas, be converted into thyrite by chemical vapor deposition, fill the space of turbine blade inside, realize the preparation of compact silicon carbide ceramic body material, obtain Metal toughened ceramic matrix composite turbine blade.
Embodiment 3:
The preparation method of Metal toughened ceramic matrix composite turbine blade, comprises the following steps:
(1) manufacture of Metal toughened skeleton
1) first design the metal frame of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) threedimensional model of the metal frame obtaining is carried out after hierarchy slicing processing, import in 3D printing device and process.Metallic dust used is stainless steel, and 3D printing device design parameter is as follows, laser power 120W, laser scanning speed 60mm/s-80mm/s, sweep span 0.75mm-0.09mm, bed thickness 0.75mm-0.09mm.
3) take trichloromethyl silane as source of the gas, nitrogen is carrier gas, forms one deck silicon nitride ceramics interface layer by chemical vapor deposition on metal frame surface.
(2) manufacture resin enclosure by light-curing rapid forming equipment, resin material is selected 19120 resins.The metal frame of preparing is combined with light-cured resin shell, obtain the resin die with Metal toughened skeleton.
(3) xylene solution of SiC micro mist and Polycarbosilane (PCS) is mixed and made into ceramic size, wherein PCS content accounts for the 10wt% of PCS and SiC powder quality sum, then slurry is heated while stirring and remove solvent (solvent reclaims after condensation), after fully stirring, be injected in resin die.
(4) after body drying a period of time, put into the mixed solution (the shared mass fraction of caustic potoash is 20%) of caustic potoash/ethanol/water, resin enclosure is successively removed under the corrosive action of corrosive liquid.
(5) ceramic body is put into the reach in freezer of-30 ℃, become after ice crystal until water of crystallization fully charge in base substrate, utilize vacuum freeze-drying technique to be dried (degree of vacuum is 10 ~ 30Pa).
(6) dried ceramic blade base substrate is put into the high temperature sintering furnace sintering that is connected with nitrogen protection, sintering temperature is 1300 ℃, and Polycarbosilane cracking at this temperature generates SiC stupalith.
(7) take trichloromethyl silane (MTS) as source of the gas, nitrogen buffer gas, is converted into thyrite by chemical vapor deposition, fills the space of turbine blade inside, realize the preparation of compact silicon carbide ceramic body material, obtain high performance ceramics turbo blade.
Embodiment 4:
The preparation method of Metal toughened ceramic matrix composite turbine blade, comprises the following steps:
(1) manufacture of Metal toughened skeleton
1) first design the metal frame of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) threedimensional model of the metal frame obtaining is carried out after hierarchy slicing processing, import in 3D printing device and process.Metallic dust used is stainless steel, and 3D printing device design parameter is as follows, laser power 120W, laser scanning speed 60mm/s-80mm/s, sweep span 0.7mm-0.85mm, bed thickness 0.7mm-0.85mm.
3) take trichloromethyl silane as source of the gas, nitrogen is carrier gas, forms one deck silicon nitride ceramics interface layer by chemical vapor deposition on metal frame surface.
(2) manufacture resin enclosure by light-curing rapid forming equipment, resin material is selected 19120 resins.The metal frame of preparing is combined with light-cured resin shell, obtain the resin die with Metal toughened skeleton.
(3) xylene solution of SiC micro mist and Polycarbosilane (PCS) is mixed and made into ceramic size, wherein PCS content accounts for the 20wt% of PCS and SiC powder quality sum, then slurry is heated while stirring and remove solvent (solvent reclaims after condensation), after fully stirring, be injected in resin die.
(4) after body drying a period of time, put into the mixed solution (the shared mass fraction of caustic potoash is 10%, methyl alcohol: the volume ratio of water is 5:6) of caustic potoash/methanol/water, resin enclosure is successively removed under the corrosive action of corrosive liquid.
(5) ceramic body is put into the reach in freezer of-30 ℃, become after ice crystal until water of crystallization fully charge in base substrate, utilize vacuum freeze-drying technique to be dried (degree of vacuum is 10 ~ 30Pa).
(6) dried ceramic blade base substrate is put into the high temperature sintering furnace sintering that is connected with nitrogen protection, sintering temperature is 1350 ℃, sintering 6h, and Polycarbosilane cracking at this temperature generates SiC stupalith.
(7) take trichloromethyl silane (MTS) as source of the gas, take hydrogen as carrier gas, be converted into thyrite by chemical vapor deposition, fill the space of turbine blade inside, realize the preparation of compact silicon carbide ceramic body material, obtain high performance ceramics turbo blade.

Claims (9)

1. a preparation method for Metal toughened ceramic matrix composite turbine blade, is characterized in that, comprises the following steps:
1) print by metal 3D the Metal toughened skeleton that technique is prepared turbine blade, then form ceramic interfacial layers by vapor deposition on Metal toughened skeleton surface; Described Metal toughened skeleton is made up of titanium alloy powder or powder of stainless steel; The material of described ceramic interfacial layers is silicon nitride or silicon carbide;
2) will there is the Metal toughened skeleton of ceramic interfacial layers and the light-cured resin mould of turbine blade combines, obtain the inner resin die with Metal toughened skeleton;
3) prepare ceramic size by gel injection-moulding technique, under vacuum environment, cast ceramics slurry, to resin die, obtains ceramics turbo blade base substrate;
4) remove resin die by chemical corrosion method, adopt vacuum freezing drying to remove the moisture in ceramic body, then under shielding gas atmosphere in 1200~1400 ℃ of sintering 3~6h, obtain composite porous turbine blade prototype;
5) in the hole of composite porous turbine blade prototype, generate silicon carbide ceramics by chemical vapor deposition, carry out densification, obtain the ceramic matrix composite turbine blade of Metal toughened.
2. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, is characterized in that, the metal 3D of described Metal toughened skeleton prints and comprises:
First design the Metal toughened skeleton of desired structure form by 3D sculpting software;
Then the threedimensional model of Metal toughened skeleton is carried out after hierarchy slicing processing, import in 3D printing device, obtain Metal toughened skeleton by precinct laser fusion metallic dust.
3. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 2, is characterized in that, being set to of laser: power is 120~200W, sweep rate 50~100mm/s, sweep span 0.05~0.1mm, bed thickness 0.05~0.1mm.
4. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, it is characterized in that, described silicon nitride ceramics interface layer be with silane and ammonia respectively as silicon source and nitrogenous source, form ceramic interfacial layers in the vapor deposition of Metal toughened Skeleton Table surface chemistry;
Described silicon carbide ceramics interface layer is take trichloromethyl silane as source of the gas, and hydrogen or nitrogen are carrier gas, forms ceramic interfacial layers in the vapor deposition of Metal toughened Skeleton Table surface chemistry.
5. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, it is characterized in that, the light-cured resin mould of described turbine blade is the resin enclosure of manufacturing the turbine blade of required structure by light-curing rapid forming equipment.
6. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, is characterized in that, described in obtain ceramics turbo blade base substrate operation comprise:
1) by organic monomer acrylamide and crosslinking agent N, N '-methylene-bisacrylamide, is dissolved in water according to mass ratio 20~25:1, adds stirring and dissolving after dispersing agent, is mixed with solid phase mass concentration and is 10~20% premixed liquid;
2) according to carborundum powder: carbon dust: silica flour=(20~60): (12~24): the mass ratio of (28~56) fully mixes silicon carbide, carbon and Si powder, obtains solid powder;
3) premixed liquid and solid powder fully being made to solid concentration by ball milling is 50~60% ceramic size, and ceramic size is fully disperseed by ball milling;
4) in ceramic size, add catalyzer, initator, after stirring, be poured in resin die by type vacuum injecting and forming machine, there is curing reaction in the organic substance in porcelain slurry, after curing reaction completes, obtain ceramics turbo blade base substrate under the effect of catalyzer, initator;
Or comprise following operation:
1) xylene solution of carborundum powder and Polycarbosilane is mixed and made into ceramic size, wherein carborundum powder: the mass ratio of Polycarbosilane is 80~90:10~20, then ceramic size is heated while stirring, after fully stirring, be poured in resin die and solidify and be dried by type vacuum injecting and forming machine, obtain ceramics turbo blade base substrate.
7. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, it is characterized in that, resin die is removed in described chemical corrosion: the ceramics turbo blade base substrate with resin die is put into corrosive liquid, and resin die is successively removed under the corrosive action of corrosive liquid;
Described corrosive liquid is the mixed solution of caustic potoash, alcohol and water, and wherein the mass fraction of caustic potoash is 5~35%, and the volume ratio of alcohol and water is 2~5:4~8, and described alcohol is methyl alcohol or ethanol.
8. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, is characterized in that, the operation that described vacuum freezing drying is removed the moisture in ceramic body comprises:
At-30 ℃~-60 ℃, be frozen into after ice crystal until water of crystallization in ceramic body, be vacuum freezing drying under 10~30Pa in degree of vacuum.
9. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, it is characterized in that, described silicon carbide densification is take trichloromethyl silane as source of the gas, take hydrogen or nitrogen as carrier gas, be converted into thyrite by chemical vapor deposition, be filled in the hole of composite porous turbine blade prototype.
CN201310044604.1A 2013-02-04 2013-02-04 Preparation method of metal toughened ceramic-based composite material turbine blade CN103113112B (en)

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