CN104529458B - The manufacture method of high-performance SiC ceramic based composites blade of aviation engine - Google Patents
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine Download PDFInfo
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- CN104529458B CN104529458B CN201410721023.1A CN201410721023A CN104529458B CN 104529458 B CN104529458 B CN 104529458B CN 201410721023 A CN201410721023 A CN 201410721023A CN 104529458 B CN104529458 B CN 104529458B
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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
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Abstract
The present invention discloses the manufacture method of a kind of high-performance SiC ceramic based composites blade of aviation engine, 3D printing technique is used to be prepared for blade of aviation engine mould, the SiC ceramic biscuit part adding carbon fiber is prepared again by gel injection-moulding method, through freeze-drying, the techniques such as degreasing obtain porous SiC ceramics prefabricated component, the most repeatedly infiltration pyrolysis organic matter precursor, pyrolysis product is utilized to fill the hole of prefabricated component, reach preliminary densification, in order to ensure product intensity and consistency, final utilization high temperature insostatic pressing (HIP) method produces high-performance SiC ceramic based composites blade of aviation engine.The method combines multiple near-net-shape technology and overcomes the shortcomings such as SiC material processing difficulties, compared with traditional alloy vane, SiC ceramic based composites blade of aviation engine has light weight, resistant to elevated temperatures advantage, is the trend of following blade of aviation engine development.
Description
[technical field]
The invention belongs to ceramic matric composite complex parts manufacturing technology field, relate to a kind of high-performance SiC ceramic base and be combined
The manufacture method of material blade of aviation engine.
[background technology]
Blade is the critical component of aero-engine, in order to improve constantly the combination property of aero-engine, then needs to improve boat
The fuel gas temperature of empty engine, this just requires that blade has and sufficiently high holds heat energy power.Conventionally employed high temperature alloy uses temperature
Limited, and the higher (8.03-8.06g/cm of density3), constrain the further lifting of aero-engine performance.
[summary of the invention]
It is an object of the invention to provide the manufacture method of a kind of high-performance SiC ceramic based composites blade of aviation engine,
The method, based on 3D printing technique, produces high-performance SiC ceramic base composite wood through gel injection-moulding, heat and other static pressuring processes
Material blade of aviation engine, this blade is high temperature resistant and density is low, is conducive to improving the combination property of aero-engine.
To achieve these goals, the present invention adopts the following technical scheme that
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine, comprises the following steps:
1) resin die of blade of aviation engine is prepared；
2) solid phase particles finely dispersed SiC suspended nitride is prepared；
3) use type vacuum injecting and forming technology to pour in resin die by SiC suspended nitride, obtain SiC ceramic biscuit；
4) the SiC ceramic biscuit obtained is carried out freeze-drying process, remove the green compact that the crystallization water in base substrate obtains being dried；
And use liquid nitrogen to be removed by its resin die；
5) under atmosphere protection, dry green compact are carried out degreasing process, by internal for base substrate organic matter ablation, obtain porous
SiC ceramic blade；
6) by carrying out repeatedly polymer infiltration and pyrolysis technique, by the SiC ceramic blade initial densification of porous；
7) utilize isostatic pressing technology, the SiC ceramic blade of initial densification sintered, finally produce consistency more than or
SiC ceramic based composites blade equal to 95%.
Preferably, step 2) specifically include:
2.1) according to the loose monofilament short carbon fiber with PCS coating: nano SiC: premixed liquid=1:(5～15): 45
The loose monofilament short carbon fiber and nano SiC with PCS coating are joined in the middle of the premixed liquid configured by volume ratio, and
Carry out ultrasonic disperse and obtain scattered premixed liquid；
2.2) micron SiC mixed-powder is added step 2.1) scattered premixed liquid obtains mixed slurry, it is subsequently adding
In mixed slurry, the Sodium Polyacrylate of solid-phase component 0.5～2wt% is as dispersant；Then mixed slurry is inserted mechanical agitation
Stir in device, finally give solid phase particles finely dispersed SiC suspended nitride；Wherein, micron SiC mixed-powder
Addition and step 2.1) used in the volume ratio of premixed liquid be (39～49): 45；
The preparation method of described premixed liquid is: by organic monomer acrylamide and crosslinking agent N, N '-methylene-bisacrylamide,
According to mass ratio (6～24): 1 mixing, being the most at room temperature dissolved in deionized water, being configured to mass fraction is 15～25%
Premixed liquid；
The preparation method of the loose monofilament short carbon fiber of the described PCS of having coating is: by solid-state PCS grind into powder, molten
In dimethylbenzene, it is configured to the PCS/Xylene maceration extract of 20wt%～25wt% of mass fraction；By a length of 0.5～4mm
Short carbon fiber adds in maceration extract, and ultrasonic wave processes the bubble got rid of in gully, short carbon fiber surface；Take out after standing 1h,
PCS is made to react with the oxygen generation self-crosslinked oxidation in air in 140 DEG C of insulation 8h；Then the short carbon fiber of crosslinking will be completed
Ultrasonic disperse 5min in dimethylbenzene, takes out post-drying；Circulation aforesaid operations 1～2 times, must arrive surface and have uniform and light
The loose monofilament short carbon fiber of sliding PCS coating；
Micron SiC mixed-powder by thick SiC powder and thin SiC powder with mass ratio (3～5): 1 mixes, described thick SiC
The particle diameter of powder is 40～60um, and the particle diameter of thin SiC powder is 2～10 μm.
Preferably, step 3) specifically include following steps: SiC suspended nitride is inserted in type vacuum injecting and forming machine, successively adds
The catalyst of catalytic amount and initiator, start to pour into a mould suspended nitride in resin die, open shake table simultaneously after stirring,
Drain bubble in resin die；After vacuum pouring completes, stand at atmospheric environment normal temperature and be properly completed monomer crosslinked solidification
Blade biscuit after gel；Wherein, described catalyst be mass fraction be 25% tetramethylethylenediamine molten, described in draw
Send out agent be mass fraction be 30% ammonium persulfate solution, the quality of catalyst and the mass ratio of initiator are 1:6-7.
Preferably, step 4) specifically include: the blade biscuit after gel is positioned over-60 DEG C and freezes in cabinet, freezing 3～5h,
Make the complete freezing and crystallizing of the moisture in green compact；Then use liquid nitrogen to peel off resin die, then green compact are put into freeze drier
In negative pressure of vacuum cabin, persistently it is evacuated to vacuum and is maintained at 0.1Pa～10Pa so that the crystallization water in green compact distils completely
Obtain the green compact being dried.
Preferably, step 5) specifically include: dry green compact are completed degreasing process in atmosphere batch-type furnace, with argon gas is
Protective gas, degreasing heating process: with the heating rate of 5 DEG C/min from room temperature to 200 DEG C, then with 1 DEG C/min
Heating rate be warming up to 700 DEG C from 200 DEG C, be then warming up to from 700 DEG C with the heating rate of 2 DEG C/min～900 DEG C also
Insulation 1h；After degreasing, obtain the SiC ceramic blade of porous.
Preferably, step 6) specifically include: the SiC ceramic blade of the porous obtained is placed in vacuum tank, after vacuumizing
Sucking SiC/PCS/xylene dipping sizing agent, vacuum is 8 × 10-2, pressurize dipping 30min；Product after impregnating, in
It is dried 2～4h at 80 DEG C, is then warmed up to 150 DEG C and completes oxidation cross-linked；Then under Ar gas shielded, with 5 DEG C/min's
Speed is warming up to 1300 DEG C and cracks, and is incubated 1～1.5h at 1300 DEG C；Then impregnating agent is replaced by PCS/xylene
Solution, repeats above-mentioned impregnating cracking technology and obtains the SiC ceramic blade of initial densification；SiC/PCS/xylene dipping sizing agent
The mass fraction of middle SiC is 10%, and the mass fraction of PCS is 40%, and SiC is nano particle；PCS/xylene impregnates
In slurry, the mass fraction of PCS is 40%.
Preferably, step 7) specifically include: by the SiC ceramic blade of initial densification from room temperature with the intensification of 5 DEG C/min
Speed carries out being warming up to 1500 DEG C, and carries out HIP sintering, HIP sintering in 1500 DEG C of temperature retention times 1.5～2h
With argon gas as transmission medium, pressure 100MPa；HIP sintering cools to room temperature with the furnace after completing, and obtains preparing
High-performance SiC ceramic based composites blade of aviation engine.
Preferably, step 2) specifically include:
2.1) according to the loose monofilament short carbon fiber with PCS coating: premixed liquid=(5～15): the volume ratio of 45 will have
The loose monofilament short carbon fiber of PCS coating joins in the middle of the premixed liquid configured, and carries out ultrasonic disperse and obtain scattered
Premixed liquid；
2.2) again with graphite: silica flour: SiC: premixed liquid=6:14:(20～30): the volume of 45 is by graphite, silica flour and SiC
Powder adds in scattered premixed liquid and obtains mixed slurry, be subsequently adding solid-phase component 0.5～2wt% in mixed slurry point
Powder；Then stir in slurry being inserted mechanical agitator, finally give solid phase particles finely dispersed SiC suspension slurry
Material；Graphite particle diameter is 15～25um, and silica flour particle diameter is 5um, and SiC powder particle diameter is 40～60um；
The preparation method of described premixed liquid is: by organic monomer acrylamide and crosslinking agent N, N '-methylene-bisacrylamide,
According to mass ratio (6～24): 1 mixing, being the most at room temperature dissolved in deionized water, being configured to mass fraction is 15～25%
Premixed liquid；
The preparation method of the loose monofilament short carbon fiber of the described PCS of having coating is: by solid-state PCS grind into powder, molten
In dimethylbenzene, it is configured to the PCS/Xylene maceration extract of 20wt%～25wt% of mass fraction；By a length of 0.5～4mm
Short carbon fiber adds in maceration extract, and ultrasonic wave processes the bubble got rid of in gully, short carbon fiber surface；Take out after standing 1h,
PCS is made to react with the oxygen generation self-crosslinked oxidation in air in 140 DEG C of insulation 8h；Then the short carbon fiber of crosslinking will be completed
Ultrasonic disperse 5min in dimethylbenzene, takes out post-drying；Circulation aforesaid operations 1～2 times, must arrive surface and have uniform and light
The loose monofilament short carbon fiber of sliding PCS coating.
Preferably, step 1) specifically include: use 3 d modeling software to build blade of aviation engine three-dimensional prototype, then
Prototype is taken out shell and obtains blade mold, exported as stl form, then be conducted in delamination software Magics, to blade
Mold former carries out layered shaping；Magics is processed data and imports in photocureable rapid shaping machine, start program, complete
The manufacture of blade light-cured resin mould；Sweep parameter: spot size is 0.14mm, laser power is 300mw, scanning
Speed is 5500mm/s, thickness 0.1mm.
Compared with prior art, the present invention has a following useful technique effect:
The present invention provides the manufacture method of a kind of high-performance SiC ceramic based composites blade of aviation engine, uses 3D to beat
Print technology prepares photocuring blade minus mould, uses gel injection-moulding method to obtain SiC ceramic biscuit, is then passed through freezing dry
The SiC part that the techniques such as dry, degreasing obtain, but its consistency is low, it is difficult to realize SiC ceramic and start at high performance turbine
Application on machine.The present invention combines precursor infiltration and pyrolysis method and hot isostatic pressing technique overcomes the defect that its consistency is low,
Toughness, structural good, consistency high SiC ceramic base blade of aviation engine are arrived.
The SiC ceramic based composites blade of aviation engine that the present invention manufactures, uses dipping precursor (Polycarbosilane),
It is cracked to form surface complete S iC boundary layer at fiber surface, effectively prevents fiber from reacting with matrix, and improve itself and pottery
The bond strength of matrix.
[detailed description of the invention]
Below in conjunction with specific embodiment, the present invention is described in further detail, described in be explanation of the invention rather than
Limit.
It is specifically described with the preparation of blade of aviation engine in detail below.
Embodiment 1
The preparation method of a kind of high-performance SiC ceramic based composites blade of aviation engine, comprises the following steps:
1. blade of aviation engine minus Mould design and manufacturing
1.1 use 3 d modeling software (UG, ProE etc.) to build blade of aviation engine three-dimensional prototype, then to prototype
Take out shell (taking out thickness of the shell is 0.5-1.0mm) and obtain blade mold, exported as stl form, then be conducted into being layered soft
In part Magics, blade mold model is carried out layered shaping.
Magics is processed data by 1.2 to be imported in photocureable rapid shaping machine (SPS600) RP fabrication schedule, starts program,
Complete the manufacture of blade light-cured resin mould.Sweep parameter: spot size is 0.14mm, laser power is 300mw,
Sweep speed is 5500mm/s, thickness 0.1mm.
2. the preparation of slurry
The preparation of 2.1 premixed liquids
By organic monomer acrylamide AM and crosslinking agent N, N '-methylene-bisacrylamide MBAM, according to mass ratio
(6～24): 1 mixing, the most at room temperature (25 DEG C) are dissolved in deionized water, and being configured to mass fraction is 15～25%
Premixed liquid.
Prepared by 2.2 fiber coats
By solid-state PCS (Polycarbosilane) grind into powder, it is dissolved in dimethylbenzene (Xylene), is configured to mass fraction
The PCS/Xylene maceration extract of 20wt%～25wt%.A length of 0.5～4mm short carbon fiber are added in maceration extract, ultrasonic wave
Process (28Hz) 30min, to get rid of the bubble in gully, short carbon fiber surface.Stand 1h, in 140 DEG C of insulations after taking-up
8h makes PCS react with the oxygen generation self-crosslinked oxidation in air；Then the short carbon fiber completing crosslinking is surpassed in dimethylbenzene
Sound dispersion 5min, takes out post-drying.Circulation aforesaid operations 1～2 times, i.e. can get surface and has uniform and smooth PCS
The loose monofilament short carbon fiber of coating.
Prepared by 2.3 solid phase components
Solid phase composition is: prepared by step 2.2 has the loose monofilament short carbon fiber of PCS coating, nano SiC (average particle
Footpath 50nm, is shaped as spherical) and nano grade alpha-SiC mixed-powder；The wherein purity 99.8% of nano grade alpha-SiC mixed-powder,
And be made up of thick SiC and thin SiC, the particle diameter of thick SiC powder is 40～60um, the particle diameter of thin SiC powder is 2～10 μm, slightly
SiC: the mass ratio of thin SiC is (3～5): 1, mixes formation nano grade alpha-SiC mixed-powder.
2.3.1 according to the loose monofilament short carbon fiber with PCS coating: nano SiC: premixed liquid=1:(5～15): 45
Above-mentioned short carbon fiber and nano SiC are joined in the middle of the premixed liquid configured by volume ratio, and carry out the ultrasonic disperse of 5min
Obtain scattered premixed liquid.
2.3.2 micron SiC mixed-powder is added in the premixed liquid that step 2.3.1 is scattered, be subsequently adding solid-phase component
The Sodium Polyacrylate of 0.5～2wt% is as dispersant.Then stirring in slurry being inserted mechanical agitator, mixing time sets
It is 20～45min, finally gives solid phase particles finely dispersed SiC suspended nitride.The addition of micron SiC mixed-powder
It is (39～49) with the volume ratio of the premixed liquid used in step 2.3.1: 45.
3. gel casting forming
SiC suspended nitride is inserted in type vacuum injecting and forming machine (vacuum is 8 × 10-2), successively add the catalyst (matter of catalytic amount
Amount mark is the tetramethylethylenediamine solution of 25%) and initiator (mass fraction is 30% ammonium persulfate solution), continue to stir
Mix.Starting to pour into a mould suspended nitride after 1min in blade mold, open shake table simultaneously, in draining mould, bubble ensures to fill
Type is complete.After vacuum pouring completes, it is properly completed monomer crosslinked solidification at atmospheric environment normal temperature standing 30min and is coagulated
Blade biscuit after glue.Wherein, the quality of catalyst is 1:6-7 with the mass ratio of initiator.
4. freeze-drying
Blade biscuit after gel is positioned over-60 DEG C and freezes in cabinet, freezing 3～5h, make the complete freezing and crystallizing of the moisture in green compact.
Then use liquid nitrogen to be peeled off by the resin die of green compact, then put it in the negative pressure of vacuum cabin of freeze drier, persistently take out true
Empty (vacuum is maintained at 0.1Pa～10Pa) so that the crystallization water in green compact distils completely, thus reach dry purpose with
Obtain the green compact being dried.
5. vacuum degreasing
Dry green compact are completed degreasing process in atmosphere batch-type furnace, with argon gas as protective gas, degreasing heating process: room
Temperature～200 DEG C (5 DEG C/min of heating rate)；200～700 DEG C (1 DEG C/min of heating rate)；700～900 DEG C of (heating rates
2℃/min)；900 DEG C of insulation 1h.After degreasing, obtain the aperture porous SiC ceramics based composites blade at about 5um.
6. the dipping of organic matter precursor and cracking
6.1 two kinds of impregnating agent of preparation: (in slurry, the mass fraction of SiC is 10% to configuration SiC/PCS/xylene slurry, PCS
Mass fraction be 40%, SiC is nano particle) with PCS/xylene solution (mass fraction of PCS is 40%).
The porous SiC ceramics prefabricated component obtained is placed in vacuum tank by 6.2, sucks SiC/PCS/xylene dipping after vacuumizing
Slurry.Vacuum is 8 × 10-2, pressurize dipping 30min.By the product after dipping, at 80 DEG C, it is dried 2～4h, heats up
Complete oxidation cross-linked to 150 DEG C.Under Ar gas shielded, it is warming up to 1300 DEG C with the speed of 5 DEG C/min and cracks, and
It is incubated 1～1.5h at 1300 DEG C.Then impregnating agent is replaced by PCS/xylene solution, repeated impregnations-cracking technology.Wait to split
Solve technique complete after obtain the higher SiC ceramic based composites blade of aviation engine of consistency (its consistency up to
85%～90%).
7. high temperature insostatic pressing (HIP)
SiC ceramic based composites blade of aviation engine prepared by step 6.2 from room temperature with the heating rate of 5 DEG C/min
Carrying out being warming up to 1500 DEG C, and carry out HIP sintering in 1500 DEG C of temperature retention times 1.5～2h, HIP sintering is with argon
Gas is transmission medium, pressure 100MPa.HIP sintering cools to room temperature with the furnace after completing, take out exemplar, final
It is 2.75-2.82g/cm to density3, high temperature (1300 DEG C) bending strength is the SiC ceramic based composites boat of 270MPa
Empty engine blade.
Embodiment 2
The preparation method of a kind of high-performance SiC ceramic based composites blade of aviation engine, comprises the following steps:
1. identical with the step 1 of example 1；
2. the preparation of slurry
2.1. identical with example 1 step 2.1
2.2. identical with example 1 step 2.2
2.3. according to the loose monofilament short carbon fiber with PCS coating: premixed liquid=(5～15): the volume ratio of 45 is mixed
Close, and carry out the ultrasonic disperse of 5min.Again with graphite: silica flour: SiC: premixed liquid=6:14:(20～30): the body of 45
Long-pending by premixed liquid scattered for the addition of graphite, silica flour and SiC powder, it is subsequently adding whole solid-phase component 0.5～2wt%
Sodium Polyacrylate is as dispersant.Then stirring in slurry being inserted mechanical agitator, mixing time is set as 20～45min,
Finally give solid phase particles finely dispersed SiC suspended nitride.Graphite particle diameter is 15～25um, and Si powder footpath is 5um,
SiC powder particle diameter is 40～60um.
3. gel casting forming
SiC suspended nitride is inserted in type vacuum injecting and forming machine (vacuum is 8 × 10-2), successively add the catalyst (matter of catalytic amount
Amount mark is the tetramethylethylenediamine solution of 25%) and initiator (mass fraction is 30% ammonium persulfate solution), continue to stir
Mix.Starting to pour into a mould suspended nitride after 1min in blade mold, open shake table simultaneously, in draining mould, bubble is to ensure
Fill type complete.After vacuum pouring completes, it is properly completed monomer crosslinked solidification at atmospheric environment normal temperature standing 30min and obtains
Blade product after gel.Wherein, the quality of catalyst is 1:6-7 with the mass ratio of initiator.
4. freeze-drying
Blade product after gel is positioned over-60 DEG C and freezes in cabinet, freezing 3～5h, make the complete freezing and crystallizing of the moisture in green compact.
Then use liquid nitrogen to be peeled off by the resin die of green compact, then put it in the negative pressure of vacuum cabin of freeze drier, persistently take out true
Empty (vacuum is maintained at 0.1Pa～10Pa) so that the crystallization water in green compact distils completely, thus reaches dry purpose,
To obtain the green compact being dried.
5. vacuum degreasing
Degreasing process is completed in atmosphere batch-type furnace, with argon gas as protective gas, degreasing heating process: room temperature～200 DEG C of (liters
Temperature 5 DEG C/min of speed)；200～700 DEG C (1 DEG C/min of heating rate)；700～900 DEG C (2 DEG C/min of heating rate)；900℃
Insulation 1h.After degreasing, obtain the aperture porous SiC ceramics at about 5um.
6. the dipping of organic matter precursor and cracking
6.1 two kinds of impregnating agent of preparation, (in slurry, the mass fraction of SiC is 10% to configuration SiC/PCS/xylene slurry, PCS
Mass fraction be 40%, SiC is nano particle) with PCS/xylene solution (mass fraction of PCS is 40%).
The porous SiC ceramics prefabricated component obtained is placed in vacuum tank by 6.2, sucks SiC/PCS/xylene dipping after vacuumizing
Slurry.Vacuum is 8 × 10-2, pressurize dipping 30min.By the product after dipping, at 80 DEG C, it is dried 2～4h, heats up
Complete oxidation cross-linked to 150 DEG C.Under Ar gas shielded, split from room temperature to 1300 DEG C with the speed of 5 DEG C/min
Solve, and be incubated 1～1.5h at 1300 DEG C.Then impregnating agent is replaced by PCS/xylene solution, repeated impregnations-cracking technology.
The SiC ceramic matrix composite material blade that consistency is higher is obtained after cracking technology completes.
7. high temperature insostatic pressing (HIP)
SiC ceramic based composites blade of aviation engine prepared by step 6.2 from room temperature with the heating rate of 5 DEG C/min
Carrying out being warming up to 1500 DEG C, and carry out HIP sintering in 1500 DEG C of temperature retention times 1.5～2h, HIP sintering is with argon
Gas is transmission medium, pressure 100MPa.HIP sintering cools to room temperature with the furnace after completing, take out exemplar, final
It is 2.75-2.82g/cm to density3, high temperature (1300 DEG C) bending strength is the SiC ceramic based composites boat of 270MPa
Empty engine blade.
Claims (7)
1. the manufacture method of high-performance SiC ceramic based composites blade of aviation engine, it is characterised in that comprise the following steps:
1) resin die of blade of aviation engine is prepared；
2) solid phase particles finely dispersed SiC suspended nitride is prepared；
3) use type vacuum injecting and forming technology to pour in resin die by SiC suspended nitride, obtain SiC ceramic biscuit；
4) the SiC ceramic biscuit obtained is carried out freeze-drying process, remove the green compact that the crystallization water in base substrate obtains being dried；And use liquid nitrogen to be removed by its resin die；
5) under atmosphere protection, dry green compact are carried out degreasing process, by internal for base substrate organic matter ablation, obtain the SiC ceramic blade of porous；
6) by carrying out repeatedly polymer infiltration and pyrolysis technique, by the SiC ceramic blade initial densification of porous；
7) utilize isostatic pressing technology, the SiC ceramic blade of initial densification is sintered, finally produce the consistency SiC ceramic based composites blade more than or equal to 95%；
Step 3) specifically include following steps: SiC suspended nitride is inserted in type vacuum injecting and forming machine, successively add catalyst and the initiator of catalytic amount, start to pour into a mould suspended nitride after stirring in resin die, open shake table simultaneously, drain bubble in resin die；After vacuum pouring completes, stand at atmospheric environment normal temperature and be properly completed the blade biscuit after monomer crosslinked solidification obtains gel；Wherein, described catalyst be mass fraction be the tetramethylethylenediamine solution of 25%, described initiator be mass fraction be 30% ammonium persulfate solution, the quality of catalyst and the mass ratio of initiator are 1:6-7.
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine the most according to claim 1, it is characterised in that step 2) specifically include:
2.1) according to the loose monofilament short carbon fiber with PCS coating: nano SiC: premixed liquid=1:(5～15): the loose monofilament short carbon fiber and nano SiC with PCS coating are joined in the middle of the premixed liquid configured by the volume ratio of 45, and carry out ultrasonic disperse and obtain scattered premixed liquid；
2.2) micron SiC mixed-powder is added step 2.1) scattered premixed liquid obtains mixed slurry, it is subsequently adding in mixed slurry the Sodium Polyacrylate of solid-phase component 0.5～2wt% as dispersant；Then stir in mixed slurry being inserted mechanical agitator, finally give solid phase particles finely dispersed SiC suspended nitride；Wherein, the addition of micron SiC mixed-powder and step 2.1) volume ratio of scattered premixed liquid is (39～49): 45；
The preparation method of described premixed liquid is: by organic monomer acrylamide and crosslinking agent N, N '-methylene-bisacrylamide, according to mass ratio (6～24): 1 mixing, the most at room temperature it is dissolved in deionized water, is configured to the premixed liquid that mass fraction is 15～25%；
The preparation method of the loose monofilament short carbon fiber of the described PCS of having coating is: by solid-state PCS grind into powder, is dissolved in dimethylbenzene, is configured to the PCS/Xylene maceration extract of 20wt%～25wt% of mass fraction；Adding in maceration extract by a length of 0.5～4mm short carbon fiber, ultrasonic wave processes the bubble got rid of in gully, short carbon fiber surface；Take out after standing 1h, make PCS react with the oxygen generation self-crosslinked oxidation in air in 140 DEG C of insulation 8h；Then will complete short carbon fiber ultrasonic disperse 5min in dimethylbenzene of crosslinking, take out post-drying；Circulation aforesaid operations 1～2 times, must arrive surface and have the loose monofilament short carbon fiber of uniform and smooth PCS coating；
Micron SiC mixed-powder by thick SiC powder and thin SiC powder with mass ratio (3～5): 1 mixes, and the particle diameter of described thick SiC powder is 40～60 μm, and the particle diameter of thin SiC powder is 2～10 μm.
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine the most according to claim 1, it is characterized in that, step 4) specifically include: the blade biscuit after gel is positioned over-60 DEG C and freezes in cabinet, freezing 3～5h, make the complete freezing and crystallizing of the moisture in green compact；Then use liquid nitrogen to peel off resin die, then green compact are put into the negative pressure of vacuum cabin of freeze drier, be persistently evacuated to vacuum and be maintained at 0.1Pa～10Pa so that the crystallization water in green compact distils the green compact obtaining being dried completely.
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine the most according to claim 1; it is characterized in that; step 5) specifically include: dry green compact are completed degreasing process in atmosphere batch-type furnace; with argon gas as protective gas; degreasing heating process: with the heating rate of 5 DEG C/min from room temperature to 200 DEG C; then it is warming up to 700 DEG C with the heating rate of 1 DEG C/min from 200 DEG C, is then warming up to 900 DEG C with the heating rate of 2 DEG C/min from 700 DEG C and is incubated 1h；After degreasing, obtain the SiC ceramic blade of porous.
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine the most according to claim 1, it is characterized in that, step 6) specifically include: the SiC ceramic blade of the porous obtained is placed in vacuum tank, sucking SiC/PCS/xylene dipping sizing agent after vacuumizing, vacuum is 8 × 10-2, pressurize dipping 30min；By the product after dipping, at 80 DEG C, it is dried 2～4h, is then warmed up to 150 DEG C and completes oxidation cross-linked；Then under Ar gas shielded, it is warming up to 1300 DEG C with the speed of 5 DEG C/min and cracks, and be incubated 1～1.5h at 1300 DEG C；Then impregnating agent is replaced by PCS/xylene solution, repeats above-mentioned impregnating cracking technology and obtain the SiC ceramic blade of initial densification；In SiC/PCS/xylene dipping sizing agent, the mass fraction of SiC is 10%, and the mass fraction of PCS is 40%, and SiC is nano particle；In PCS/xylene dipping sizing agent, the mass fraction of PCS is 40%.
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine the most according to claim 1, it is characterized in that, step 7) specifically include: carry out being warming up to 1500 DEG C with the heating rate of 5 DEG C/min from room temperature by the SiC ceramic blade of initial densification, and carry out HIP sintering in 1500 DEG C of temperature retention times 1.5～2h, HIP sintering with argon gas as transmission medium, pressure 100MPa；HIP sintering cools to room temperature with the furnace after completing, and obtains high-performance SiC ceramic based composites blade of aviation engine to be prepared.
The manufacture method of high-performance SiC ceramic based composites blade of aviation engine the most according to claim 1, it is characterised in that step 2) specifically include:
2.1) according to the loose monofilament short carbon fiber with PCS coating: premixed liquid=(5～15): the loose monofilament short carbon fiber with PCS coating is joined in the middle of the premixed liquid configured by the volume ratio of 45, and carry out ultrasonic disperse and obtain scattered premixed liquid；
2.2) again with graphite: silica flour: SiC: premixed liquid=6:14:(20～30): the volume of 45, by obtaining mixed slurry in premixed liquid scattered for the addition of graphite, silica flour and SiC powder, is subsequently adding the dispersant of solid-phase component 0.5～2wt% in mixed slurry；Then stir in slurry being inserted mechanical agitator, finally give solid phase particles finely dispersed SiC suspended nitride；Graphite particle diameter is 15～25 μm, and silica flour particle diameter is 5 μm, and SiC powder particle diameter is 40～60 μm；
The preparation method of described premixed liquid is: by organic monomer acrylamide and crosslinking agent N, N '-methylene-bisacrylamide, according to mass ratio (6～24): 1 mixing, the most at room temperature it is dissolved in deionized water, is configured to the premixed liquid that mass fraction is 15～25%；
The preparation method of the loose monofilament short carbon fiber of the described PCS of having coating is: by solid-state PCS grind into powder, is dissolved in dimethylbenzene, is configured to the PCS/Xylene maceration extract of 20wt%～25wt% of mass fraction；Adding in maceration extract by a length of 0.5～4mm short carbon fiber, ultrasonic wave processes the bubble got rid of in gully, short carbon fiber surface；Take out after standing 1h, make PCS react with the oxygen generation self-crosslinked oxidation in air in 140 DEG C of insulation 8h；Then will complete short carbon fiber ultrasonic disperse 5min in dimethylbenzene of crosslinking, take out post-drying；Circulation aforesaid operations 1～2 times, must arrive surface and have the loose monofilament short carbon fiber of uniform and smooth PCS coating.
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