CN103113112A - 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 PDFInfo
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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
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 technology
Turbine blade is one of core component of aircraft engine.Turbine blade is operated in the position that in aircraft engine, environment is the most abominable, temperature is the highest, stress is the most complicated, and its design will have a direct impact the over-all properties of aircraft engine 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 the combustion chamber, fuel gas temperature is higher, and the thrust that energy utilization rate is higher, engine 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 subjected to the restriction of existing manufacture level, the manufacture difficulty of hollow turbine vane with complicated cooling structure is very large, and manufacturing cost is very high.
Can keep the high performance structural material under exploitation high temperature, to the manufacturing important in inhibiting of aircraft engine.Advanced ceramics material is subject to Materials science worker's attention owing to having the excellent high mechanical property always.Stupalith has the advantages such as intensity is high, high temperature resistant, quality is light, is the ideal material of making turbine blade.Yet stupalith is high due to hardness, fragility is large, is difficult to machine-shaping, and the surface shape of blade is complicated, and therefore, the moulding problem that solves ceramic blade is most important.
Gelcasting Technique provides a kind of new approach for the moulding of ceramic blade.Gelcasting Technique is a kind of new forming process of ceramics technology of U.S. Oak Ridge National Key Laboratory invention.This technology combines traditional ceramic preparation method with polymer chemistry, be a kind of near-net-shape technology of novel preparation complicated shape ceramic part.At first the method configures high solid phase, low viscous ceramic size, then the ceramic size of good fluidity is poured into mould under vacuum environment, and the in-situ solidifying reaction occurs under the effect of catalyzer, initiator ceramic size, forms the ceramic part base substrate.The method can be used for the manufacturing 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 metallic framework and ceramics turbo blade, obtain inner ceramics turbo blade with metallic framework, strengthened the toughness of ceramics turbo blade.
The present invention is achieved through the following technical solutions:
A kind of preparation method of Metal toughened ceramic matrix composite turbine blade comprises the following steps:
1) print by metal 3D the Metal toughened skeleton that technique prepares turbine blade, then form ceramic interfacial layers by vapour deposition on Metal toughened skeleton surface;
The Metal toughened skeleton that 2) will have a ceramic interfacial layers combines with the light-cured resin mould of turbine blade, obtains inner resin die with the Metal toughened skeleton;
3) prepare ceramic size by gel injection technique, the cast ceramics slurry to resin die, obtains ceramics turbo blade base substrate under vacuum environment;
4) remove resin die by chemical corrosion method, adopt vacuum lyophilization to remove moisture in ceramic body, to improve precision, then under protective atmosphere in 1200～1400 ℃ of sintering 3～6h, realize composite porous turbine blade prototype;
5) generate silicon carbide ceramics by chemical vapour deposition in the hole of composite turbine blade, carry out densification, realize the ceramic matrix composite turbine blade.
The metal 3D of described Metal toughened skeleton prints and comprises:
At first design the Metal toughened skeleton of desired structure form by 3D sculpting software;
Then the three-dimensional model of Metal toughened skeleton is carried out importing in the 3D PRN device after hierarchy slicing processes, obtain the Metal toughened skeleton by the precinct laser fusion metal-powder.
Described metal-powder is titanium alloy powder or powder of stainless steel;
Being set to of laser: power is 120～200W, sweep velocity 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 interfacial layer be with silane and ammonia respectively as silicon source and nitrogenous source, form ceramic interfacial layers in the vapour deposition of Metal toughened Skeleton Table surface chemistry;
Described silicon carbide ceramics interfacial layer is take trichloromethyl silane as source of the gas, and hydrogen or nitrogen are carrier gas, forms ceramic interfacial layers in the vapour deposition of Metal toughened Skeleton Table surface chemistry.
The light-cured resin mould of described turbine blade is to make the resin enclosure of the turbine blade of required structure by light-curing rapid forming equipment.
The described operation that obtains ceramics turbo blade base substrate comprises:
1) with organic monomer acrylamide and linking agent N, N '-methylene-bisacrylamide is dissolved in water according to mass ratio 20～25:1, adds stirring and dissolving after dispersion agent, is mixed with the 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 solid load by ball milling is 50～60% ceramic size, and ceramic size is fully disperseed by ball milling;
4) add catalyzer, initiator in ceramic size, be poured in resin die by type vacuum injecting and forming machine after stirring, curing reaction occurs in the organism in the porcelain slurry under the effect of catalyzer, initiator, after curing reaction is completed, obtain ceramics turbo blade base substrate.
Resin die is removed in described chemical corrosion: will put into corrosive fluid with the ceramics turbo blade base substrate of resin die, resin die is successively removed under the corrosive nature of corrosive fluid;
Described corrosive fluid is the mixing solutions of potassium hydroxide, alcohol and water, and wherein the massfraction of potassium hydroxide 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 lyophilization is removed the moisture in ceramic body comprises:
Under-30 ℃～-60 ℃, after crystal water is frozen into ice crystal in ceramic body, be vacuum lyophilization under 10～30Pa in vacuum tightness.
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 vapour 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 metallic framework surface preparation ceramic interfacial layers, then the Metal toughened skeleton is combined with the light-cured resin mould; By gel injection technique cast ceramics slurry in the resin die, ceramic size generation curing reaction obtains the turbine blade base substrate under the effect of catalyzer, initiator; Adopt the method for chemical corrosion to remove resin die, guarantee the dimensional precision of turbine blade by vacuum lyophilization; After ceramics turbo blade sintering, realize that by chemical vapour deposition silicon carbide ceramics is filled in the turbine blade internal void, realizes 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, 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, simultaneously, the thyrite that transforms preparation by precursor has intensity preferably.
The present invention is particularly useful for the manufacturing of low-pressure turbine blade, and the turbine blade by the method manufacturing not only has good hot strength and high temperature toughness, and, compare with traditional metal blade, can greatly alleviate the quality of blade, improve the thrust-weight ratio of engine.
Embodiment
The present invention is described in further detail below in conjunction with specific embodiment, and the explanation of the invention is not limited.
Embodiment 1:
A kind of preparation method of Metal toughened ceramic matrix composite turbine blade comprises the following steps:
(1) manufacturing of Metal toughened skeleton.
1) at first design the metallic framework of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) three-dimensional model of the metallic framework that obtains is carried out import in the 3D PRN device and process after hierarchy slicing processes.Metal-powder used is the high-melting-point powder, is specially titanium alloy powder, and 3D PRN 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 interfacial layer by chemical vapour deposition on the metallic framework surface.
(2) by light-curing rapid forming equipment finished parts resin enclosure, resin material is selected 19120 resins.The metallic framework of preparing is combined with the light-cured resin shell, obtain towards the resin die of complicated shape with the Metal toughened skeleton.
(3) prepare high solid phase, low viscous ceramic size by gel injection technique, the cast ceramics slurry in mould, obtains the ceramic base substrate under vacuum environment.
1) at first with organic monomer AM(acrylamide) and linking agent MBAM(N, N '-methylene-bisacrylamide) be dissolved in deionized water according to mass ratio 24:1, (common dispersants gets final product to add appropriate dispersion agent again, the dispersion agent add-on be the 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 weighing solid powder (carborundum powder, carbon dust, silica flour) of carbon dust: silica flour=40:20:35, and solid powder is stirred, mixes.
3) premixed liquid for preparing is poured in ball grinder, the solid powder that mixes is slowly joined in premixed liquid, and constantly stir, prepare solid load and be 60% ceramic size.
4) adding the corundum abrading-ball according to pellet mass ratio 1:2.5, is 360r/min with the planetary ball mill speed adjustment, and ball milling 60 ~ 90min disperses, and obtains the ceramic size of good fluidity.
5) successively add pre-configured catalyzer TEMED(Tetramethyl Ethylene Diamine in the ceramic size), initiator A PS(ammonium persulfate solution), after stirring at the type vacuum injecting and forming machine upper in resin die, remove bubble in slurry by the mode of vibration in casting process.In 5 ~ 15min, curing reaction occurs in the organism in ceramic size under the effect of catalyzer, initiator, forms ceramic body.
(4) (the shared massfraction of potassium hydroxide is 20%, ethanol: water=2:5), resin enclosure are successively removed under the corrosive nature of corrosive fluid will to put into the mixing solutions of potassium hydroxide/ethanol/water with the ceramics turbo blade of resin enclosure.
(5) ceramic body is put into the reach in freezer of-30 ℃--60 ℃, after the crystal water fully charge became ice crystal in base substrate, (vacuum tightness was 10 ~ 30Pa) to utilize vacuum freeze-drying technique to carry out drying.
(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 vapour 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 kind of preparation method of Metal toughened ceramic matrix composite turbine blade comprises the following steps:
(1) manufacturing of Metal toughened skeleton
1) at first design the metallic framework of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) three-dimensional model of the metallic framework that obtains is carried out import in the 3D PRN device and process after hierarchy slicing processes.Metal-powder used is the high-melting-point powder, is specially titanium alloy powder, and 3D PRN 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 interfacial layer by chemical vapour deposition on the metallic framework surface.
(2) by light-curing rapid forming equipment finished parts resin enclosure, resin material is selected 19120 resins.The metallic framework of preparing is combined with the light-cured resin shell, obtain towards the resin die of complicated shape with the Metal toughened skeleton.
(3) prepare high solid phase, low viscous ceramic size by gel injection technique, the cast ceramics slurry in mould, obtains the ceramic base substrate under vacuum environment.
1) at first with organic monomer AM(acrylamide) and linking agent MBAM(N, N '-methylene-bisacrylamide) be dissolved in deionized water according to mass ratio 20:1, (common dispersants gets final product to add appropriate dispersion agent again, the dispersion agent add-on be the 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 weighing solid powder (carborundum powder, carbon dust, silica flour) of carbon dust: silica flour=50:24:55, and solid powder is stirred, mixes.
3) premixed liquid for preparing is poured in ball grinder, the solid powder that mixes is slowly joined in premixed liquid, and constantly stir, prepare solid load and be 60% ceramic size.
4) adding the corundum abrading-ball according to pellet mass ratio 1:2.5, is 360r/min with the planetary ball mill speed adjustment, and ball milling 60 ~ 90min disperses, and obtains the ceramic size of good fluidity.
5) successively add pre-configured catalyzer TEMED(Tetramethyl Ethylene Diamine in the ceramic size), initiator A PS(ammonium persulfate solution), after stirring at the type vacuum injecting and forming machine upper in resin die, remove bubble in slurry by the mode of vibration in casting process.In 5 ~ 15min, curing reaction occurs in the organism in ceramic size under the effect of catalyzer, initiator, forms ceramic body.
(4) (the shared massfraction of potassium hydroxide is 35%, ethanol: water=2:8), resin enclosure are successively removed under the corrosive nature of corrosive fluid will to put into the mixing solutions of potassium hydroxide/ethanol/water with the ceramics turbo blade of resin enclosure.
(5) ceramic body is put into the reach in freezer of-30 ℃--60 ℃, after the crystal water fully charge became ice crystal in base substrate, (vacuum tightness was 10 ~ 30Pa) to utilize vacuum freeze-drying technique to carry out drying.
(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 vapour 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) manufacturing of Metal toughened skeleton
1) at first design the metallic framework of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) three-dimensional model of the metallic framework that obtains is carried out import in the 3D PRN device and process after hierarchy slicing processes.Metal-powder used is stainless steel, and 3D PRN 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 interfacial layer on metallic framework surface by chemical vapour deposition.
(2) make resin enclosure by light-curing rapid forming equipment, resin material is selected 19120 resins.The metallic framework of preparing is combined with the light-cured resin shell, obtain the resin die with the Metal toughened skeleton.
(3) xylene solution with 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, be injected in resin die after fully stirring.
(4) body drying after for some time, is put into the mixing solutions (the shared massfraction of potassium hydroxide is 20%) of potassium hydroxide/ethanol/water, and resin enclosure is successively removed under the corrosive nature of corrosive fluid.
(5) ceramic body is put into the reach in freezer of-30 ℃, after the crystal water fully charge became ice crystal in base substrate, (vacuum tightness was 10 ~ 30Pa) to utilize vacuum freeze-drying technique to carry out drying.
(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 the SiC stupalith.
(7) take trichloromethyl silane (MTS) as source of the gas, nitrogen buffer gas is converted into thyrite by chemical vapour 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) manufacturing of Metal toughened skeleton
1) at first design the metallic framework of desired structure form by 3D sculpting software (UG, Pro/E etc.).
2) three-dimensional model of the metallic framework that obtains is carried out import in the 3D PRN device and process after hierarchy slicing processes.Metal-powder used is stainless steel, and 3D PRN 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 interfacial layer on metallic framework surface by chemical vapour deposition.
(2) make resin enclosure by light-curing rapid forming equipment, resin material is selected 19120 resins.The metallic framework of preparing is combined with the light-cured resin shell, obtain the resin die with the Metal toughened skeleton.
(3) xylene solution with 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, be injected in resin die after fully stirring.
(4) body drying after for some time, is put into the mixing solutions (the shared massfraction of potassium hydroxide is 10%, methyl alcohol: the volume ratio of water is 5:6) of potassium hydroxide/methanol/water, and resin enclosure is successively removed under the corrosive nature of corrosive fluid.
(5) ceramic body is put into the reach in freezer of-30 ℃, after the crystal water fully charge became ice crystal in base substrate, (vacuum tightness was 10 ~ 30Pa) to utilize vacuum freeze-drying technique to carry out drying.
(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 ℃, and sintering 6h, Polycarbosilane cracking at this temperature generates the SiC stupalith.
(7) take trichloromethyl silane (MTS) as source of the gas, take hydrogen as carrier gas, be converted into thyrite by chemical vapour 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 (10)
1. the preparation method of a 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 prepares turbine blade, then form ceramic interfacial layers by vapour deposition on Metal toughened skeleton surface;
The Metal toughened skeleton that 2) will have a ceramic interfacial layers combines with the light-cured resin mould of turbine blade, obtains inner resin die with the Metal toughened skeleton;
3) prepare ceramic size by gel injection technique, the cast ceramics slurry to resin die, obtains ceramics turbo blade base substrate under vacuum environment;
4) remove resin die by chemical corrosion method, adopt vacuum lyophilization to remove moisture in ceramic body, then under protective atmosphere in 1200～1400 ℃ of sintering 3～6h, obtain composite porous turbine blade prototype;
5) generate silicon carbide ceramics by chemical vapour deposition in the hole of composite porous turbine blade prototype, 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:
At first design the Metal toughened skeleton of desired structure form by 3D sculpting software;
Then the three-dimensional model of Metal toughened skeleton is carried out importing in the 3D PRN device after hierarchy slicing processes, obtain the Metal toughened skeleton by the precinct laser fusion metal-powder.
3. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 2, is characterized in that, described metal-powder is titanium alloy powder or powder of stainless steel;
Being set to of laser: power is 120～200W, sweep velocity 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, is characterized in that, the material of described ceramic interfacial layers is silicon nitride or silicon carbide.
5. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 4, it is characterized in that, described silicon nitride ceramics interfacial layer be with silane and ammonia respectively as silicon source and nitrogenous source, form ceramic interfacial layers in the vapour deposition of Metal toughened Skeleton Table surface chemistry;
Described silicon carbide ceramics interfacial layer is take trichloromethyl silane as source of the gas, and hydrogen or nitrogen are carrier gas, forms ceramic interfacial layers in the vapour deposition of Metal toughened Skeleton Table surface chemistry.
6. 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 to make the resin enclosure of the turbine blade of required structure by light-curing rapid forming equipment.
7. the preparation method of Metal toughened ceramic matrix composite turbine blade as claimed in claim 1, is characterized in that, the described operation that obtains ceramics turbo blade base substrate comprises:
1) with organic monomer acrylamide and linking agent N, N '-methylene-bisacrylamide is dissolved in water according to mass ratio 20～25:1, adds stirring and dissolving after dispersion agent, is mixed with the 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 solid load by ball milling is 50～60% ceramic size, and ceramic size is fully disperseed by ball milling;
4) add catalyzer, initiator in ceramic size, be poured in resin die by type vacuum injecting and forming machine after stirring, curing reaction occurs in the organism in the porcelain slurry under the effect of catalyzer, initiator, after curing reaction is completed, obtain ceramics turbo blade base substrate;
Perhaps comprise following operation:
1) xylene solution with carborundum powder and Polycarbosilane is mixed and made into ceramic size, carborundum powder wherein: the mass ratio of Polycarbosilane is 80～90:10～20, then ceramic size is heated while stirring, after fully stirring, be poured into by type vacuum injecting and forming machine and solidify drying in resin die, obtain ceramics turbo blade base substrate.
8. 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: will put into corrosive fluid with the ceramics turbo blade base substrate of resin die, resin die is successively removed under the corrosive nature of corrosive fluid;
Described corrosive fluid is the mixing solutions of potassium hydroxide, alcohol and water, and wherein the massfraction of potassium hydroxide is 5～35%, and the volume ratio of alcohol and water is 2～5:4～8, and described alcohol is methyl alcohol or ethanol.
9. 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 lyophilization is removed the moisture in ceramic body comprises:
Under-30 ℃～-60 ℃, after crystal water is frozen into ice crystal in ceramic body, be vacuum lyophilization under 10～30Pa in vacuum tightness.
10. 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 vapour deposition, be filled in the hole of composite porous turbine blade prototype.
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