CN104529458B - The manufacture method of high-performance SiC ceramic based composites blade of aviation engine - Google Patents

Abstract

The invention discloses a method for manufacturing a high-performance SiC ceramic-based composite material aero-engine blade. The aero-engine blade mold is prepared by using 3D printing technology, and then a SiC ceramic blank with carbon fiber is prepared by gel injection molding. After freezing Porous SiC ceramic preforms are obtained by drying, degreasing and other processes, and then the organic precursor is impregnated and cracked multiple times, and the cracked products are used to fill the pores of the preforms to achieve initial densification. In order to ensure the strength and density of the parts, hot isostatic High-performance SiC ceramic matrix composite aeroengine blades were manufactured by pressing method. This method combines a variety of near-net shape technologies to overcome the shortcomings of SiC material processing difficulties. Compared with traditional alloy blades, SiC ceramic matrix composite aero-engine blades have the advantages of light weight and high temperature resistance, and are the future development of aero-engine blades. trend.

Description

Manufacturing method of high-performance SiC ceramic matrix composite aeroengine blade

【Technical field】

The invention belongs to the technical field of manufacturing complex parts of ceramic matrix composite materials, and relates to a method for manufacturing high-performance SiC ceramic matrix composite material aeroengine blades.

【Background technique】

Blades are the key components of aero-engines. In order to continuously improve the overall performance of aero-engines, it is necessary to increase the gas temperature of aero-engines, which requires the blades to have a high enough heat-bearing capacity. Traditionally used superalloys have limited service temperature and high density (8.03-8.06g/cm ³ ), which restricts the further improvement of aero-engine performance.

【Content of invention】

The purpose of the present invention is to provide a method for manufacturing high-performance SiC ceramic matrix composite aeroengine blades. The method is based on 3D printing technology and produces high-performance SiC ceramic matrix composite aviation Engine blades, which are high-temperature-resistant and low-density, are conducive to improving the overall performance of the aero-engine.

In order to achieve the above object, the present invention adopts the following technical solutions:

A method for manufacturing a high-performance SiC ceramic matrix composite aeroengine blade, comprising the following steps:

1) Prepare a resin mold for an aeroengine blade;

2) preparing a SiC suspension slurry in which the solid phase particles are uniformly dispersed;

3) Pouring the SiC suspension slurry into the resin mold by vacuum injection molding technology to obtain the SiC ceramic green body;

4) subjecting the obtained SiC ceramic green body to freeze-drying treatment, removing crystal water in the green body to obtain a dried green body; and using liquid nitrogen to remove the resin mold;

5) Degreasing the dried green body under the protection of the atmosphere, ablation of the organic matter inside the green body to obtain porous SiC ceramic blades;

6) Preliminary densification of porous SiC ceramic blades by performing multiple precursor dipping and cracking processes;

7) Using isostatic pressing technology to sinter the pre-densified SiC ceramic blade, and finally manufacture a SiC ceramic matrix composite material blade with a density greater than or equal to 95%.

Preferably, step 2) specifically includes:

2.1) Add the loose monofilament short carbon fiber with PCS coating and nano SiC to the configured Among the premixed liquids, ultrasonic dispersion is carried out to obtain dispersed premixed liquids;

2.2) Add the micron SiC mixed powder into the dispersed premix in step 2.1) to obtain a mixed slurry, then add sodium polyacrylate with a solid phase content of 0.5 to 2wt% in the mixed slurry as a dispersant; then put the mixed slurry into Stir evenly in a mechanical stirrer, and finally obtain a SiC suspension slurry with uniformly dispersed solid phase particles; wherein, the volume ratio of the added amount of micron SiC mixed powder to the premixed liquid used in step 2.1) is (39-49):45 ;

The preparation method of the premixed solution is as follows: the organic monomer acrylamide and the crosslinking agent N,N'-methylenebisacrylamide are mixed according to the mass ratio (6-24): 1, and then dissolved at room temperature until In deionized water, prepare a premix solution with a mass fraction of 15-25%;

The preparation method of the loose monofilament short carbon fiber with PCS coating is: solid PCS is ground into powder, is dissolved in xylene, is mixed with the PCS/Xylene dipping liquid of 20wt%～25wt% of mass fraction; 0.5-4mm short carbon fibers are added to the impregnating solution, and the air bubbles in the surface grooves of the short carbon fibers are removed by ultrasonic treatment; they are taken out after standing for 1 hour, and kept at 140°C for 8 hours to allow the oxidation and self-crosslinking reaction of PCS and oxygen in the air to occur; then the crosslinking is completed The combined short carbon fibers were ultrasonically dispersed in xylene for 5 minutes, taken out and then dried; the above operation was repeated 1 to 2 times to obtain loose monofilament short carbon fibers with a uniform and smooth PCS coating on the surface;

The micron SiC mixed powder is formed by mixing coarse SiC powder and fine SiC powder at a mass ratio (3-5): 1, the particle size of the coarse SiC powder is 40-60um, and the particle size of the fine SiC powder is 2-10μm.

Preferably, step 3) specifically includes the following steps: placing the SiC suspension slurry into a vacuum injection molding machine, adding catalytic amounts of catalyst and initiator successively, stirring evenly and starting to pour the suspension slurry into the resin mold, and simultaneously starting the vibration platform to exhaust the air bubbles in the resin mold; after the vacuum pouring is completed, stand at room temperature in the atmospheric environment to completely complete the monomer cross-linking and solidification to obtain the green blade green body after the gel; wherein the catalyst is 25% four Methylethylenediamine is dissolved, the initiator is ammonium persulfate solution with a mass fraction of 30%, and the mass ratio of the catalyst mass to the initiator is 1:6-7.

Preferably, step 4) specifically includes: placing the gelled blade blank in a freezer at -60°C, freezing for 3 to 5 hours, so that the water in the green blank is completely frozen and crystallized; then using liquid nitrogen to peel off the resin mold, and then Put the green body into the vacuum negative pressure chamber of the freeze dryer, and continue to vacuum until the vacuum degree is kept at 0.1Pa-10Pa, so that the crystal water in the green body is completely sublimated to obtain a dried green body.

Preferably, step 5) specifically includes: completing the degreasing process of the dried green body in an atmosphere box furnace, using argon as a protective gas, and the degreasing and heating process: raising the temperature from room temperature to 200 °C at a heating rate of 5 °C/min, Then the temperature was raised from 200°C to 700°C at a heating rate of 1°C/min, and then from 700°C to ~900°C at a heating rate of 2°C/min and kept for 1 hour; after degreasing, porous SiC ceramic blades were obtained.

Preferably, step 6) specifically includes: placing the obtained porous SiC ceramic blade in a vacuum tank, sucking in the SiC/PCS/xylene impregnation slurry after vacuuming, with a vacuum degree of 8×10 ^-2 , and impregnating for 30 minutes under pressure; The impregnated parts are dried at 80°C for 2 to 4 hours, and then heated to 150°C to complete oxidative cross-linking; then under the protection of Ar gas, the temperature is raised to 1300°C at a speed of 5°C/min for cracking, and at 1300°C Insulate for 1 to 1.5 hours; then replace the impregnating agent with PCS/xylene solution, repeat the above dipping and cracking process to obtain a preliminary densified SiC ceramic blade; the mass fraction of SiC in the SiC/PCS/xylene impregnating slurry is 10%, and the The mass fraction is 40%, and SiC is nanoparticles; the mass fraction of PCS in the PCS/xylene impregnation slurry is 40%.

Preferably, step 7) specifically includes: heating the pre-densified SiC ceramic blade from room temperature to 1500°C at a heating rate of 5°C/min, and performing hot isostatic pressing sintering at 1500°C for 1.5-2 hours. The isostatic sintering uses argon as the pressure transmission medium, and the pressure is 100 MPa; after the hot isostatic sintering is completed, it is cooled to room temperature with the furnace to obtain the high-performance SiC ceramic matrix composite aero-engine blade to be prepared.

Preferably, step 2) specifically includes:

2.1) According to the volume ratio of loose monofilament short carbon fiber with PCS coating: premix solution = (5 ~ 15): 45, add loose monofilament short carbon fiber with PCS coating into the prepared premix solution, and perform ultrasonic Disperse to obtain a dispersed premix;

2.2) Then add graphite, silicon powder and SiC powder into the dispersed premix with the volume of graphite: silicon powder: SiC: premix = 6: 14: (20-30): 45 to obtain a mixed slurry, then add and mix A dispersant with 0.5-2wt% solid phase component in the slurry; then put the slurry into a mechanical stirrer and stir evenly, and finally obtain a SiC suspension slurry with uniformly dispersed solid phase particles; graphite particle size is 15-25um, silicon powder The particle size is 5um, and the SiC powder particle size is 40-60um;

The preparation method of the premixed solution is as follows: the organic monomer acrylamide and the crosslinking agent N,N'-methylenebisacrylamide are mixed according to the mass ratio (6-24): 1, and then dissolved at room temperature until In deionized water, prepare a premix solution with a mass fraction of 15-25%;

The preparation method of the loose monofilament short carbon fiber with PCS coating is: solid PCS is ground into powder, is dissolved in xylene, is mixed with the PCS/Xylene dipping liquid of 20wt%～25wt% of mass fraction; 0.5-4mm short carbon fibers are added to the impregnating solution, and the air bubbles in the surface grooves of the short carbon fibers are removed by ultrasonic treatment; they are taken out after standing for 1 hour, and kept at 140°C for 8 hours to allow the oxidation and self-crosslinking reaction of PCS and oxygen in the air to occur; then the crosslinking is completed The linked short carbon fibers were ultrasonically dispersed in xylene for 5 minutes, taken out and then dried; the above operation was repeated 1 to 2 times to obtain loose monofilament short carbon fibers with a uniform and smooth PCS coating on the surface.

Preferably, step 1) specifically includes: using 3D modeling software to build a 3D prototype of an aeroengine blade, then extracting the shell of the prototype to obtain a blade mold, exporting it to stl format, and then importing it into the layered software Magics, and then performing the blade mold The model is layered and processed; the Magics processing data is imported into the light-cured rapid prototyping machine, and the program is started to complete the manufacture of the blade light-cured resin mold; scanning parameters: the spot size is 0.14mm, the laser power is 300mw, and the scanning speed is 5500mm/s , layer thickness 0.1mm.

Compared with the prior art, the present invention has the following beneficial technical effects:

The invention provides a method for manufacturing a high-performance SiC ceramic-based composite material aeroengine blade, which uses 3D printing technology to prepare a light-cured blade negative mold, uses a gel injection molding method to obtain a SiC ceramic green body, and then undergoes freeze-drying, degreasing, etc. However, the SiC parts obtained by the process have low density, which makes it difficult to realize the application of SiC ceramics in high-performance aero-engines. The invention combines the precursor impregnation cracking method and the hot isostatic pressing technology to overcome the defect of low density, and obtains SiC ceramic-based aeroengine blades with good toughness and structure and high density.

The SiC ceramic matrix composite aero-engine blade manufactured by the present invention adopts the impregnated precursor (polycarbosilane) to crack and generate a complete SiC interface layer on the surface of the fiber, effectively preventing the fiber from reacting with the matrix, and improving its bonding with the ceramic matrix strength.

【detailed description】

The present invention will be further described in detail below in conjunction with specific embodiments, which are explanations of the present invention rather than limitations.

The preparation of an aeroengine blade will be specifically described below.

Example 1

A method for preparing a high-performance SiC ceramic matrix composite material aeroengine blade, comprising the following steps:

1. Design and manufacture of aero-engine blade negative mold

1.1 Use 3D modeling software (UG, ProE, etc.) to build a 3D prototype of an aero-engine blade, then shell the prototype (the thickness of the shell is 0.5-1.0mm) to get the blade mold, export it to stl format, and then import it into the In the layer software Magics, the blade mold model is layered.

1.2 Import the Magics processing data into the RP manufacturing program of the light-curing rapid prototyping machine (SPS600), start the program, and complete the manufacture of the blade light-curing resin mold. Scanning parameters: the spot size is 0.14mm, the laser power is 300mw, the scanning speed is 5500mm/s, and the layer thickness is 0.1mm.

2. Preparation of Slurry

2.1 Preparation of master mix

The organic monomer acrylamide AM and the crosslinking agent N,N'-methylenebisacrylamide MBAM are mixed according to the mass ratio (6~24): 1, and then dissolved in deionized water at room temperature (25°C), Prepare a premix solution with a mass fraction of 15-25%.

2.2 Fiber coating preparation

Solid PCS (polycarbosilane) is ground into powder, dissolved in xylene (Xylene), and prepared into a PCS/Xylene impregnating solution with a mass fraction of 20wt%-25wt%. Add short carbon fibers with a length of 0.5 to 4 mm into the impregnation solution, and perform ultrasonic treatment (28Hz) for 30 minutes to remove air bubbles in the grooves on the surface of the short carbon fibers. Let it stand for 1 hour, take it out and keep it warm at 140°C for 8 hours to make PCS oxidize and self-crosslink with the oxygen in the air; then ultrasonically disperse the crosslinked short carbon fiber in xylene for 5 minutes, take it out and dry it. By repeating the above operation for 1-2 times, the loose monofilament short carbon fiber with a uniform and smooth PCS coating on the surface can be obtained.

2.3 Preparation of solid phase components

The solid phase components are: the loose monofilament short carbon fiber with PCS coating prepared in step 2.2, nano-SiC (average particle diameter 50nm, spherical shape) and micron α-SiC mixed powder; wherein the micron α-SiC mixed powder The purity is 99.8%, and it is composed of coarse SiC and fine SiC. The particle size of coarse SiC powder is 40-60um, the particle size of fine SiC powder is 2-10μm, and the mass ratio of coarse SiC: fine SiC is (3-5): 1. Mix evenly to form micron-sized α-SiC mixed powder.

2.3.1 According to the volume ratio of PCS-coated loose monofilament short carbon fiber: nano-SiC: premix solution = 1: (5-15): 45, add the above-mentioned short carbon fiber and nano-SiC into the prepared premix solution, and Ultrasonic dispersion was carried out for 5 min to obtain a well-dispersed premix.

2.3.2 Add the micron SiC mixed powder into the premix solution dispersed in step 2.3.1, and then add 0.5-2 wt% sodium polyacrylate as a dispersant in the solid phase. Then put the slurry into a mechanical stirrer and stir, the stirring time is set at 20-45min, and finally obtain the SiC suspension slurry with uniformly dispersed solid phase particles. The volume ratio of the added amount of micron SiC mixed powder to the premix solution used in step 2.3.1 is (39-49):45.

3. Gel injection molding

Put the SiC suspension slurry into a vacuum injection molding machine (vacuum degree is 8×10 ^-2 ), and add a catalytic amount of catalyst (a solution of tetramethylethylenediamine with a mass fraction of 25%) and an initiator (mass fraction 30% ammonium persulfate solution), continue stirring. After 1 minute, start pouring the suspension slurry into the blade mold, and at the same time turn on the vibrating table to exhaust the air bubbles in the mold to ensure the complete filling. After the vacuum pouring is completed, stand still at room temperature in the atmosphere for 30 minutes to completely complete the monomer cross-linking and solidification to obtain the green blade green body after gelation. Wherein, the mass ratio of the mass of the catalyst to the initiator is 1:6-7.

4. Freeze drying

Place the gelled leaf green body in a freezer at -60°C for 3-5 hours, so that the moisture in the green body is completely frozen and crystallized. Then use liquid nitrogen to peel off the resin mold of the green body, then put it into the vacuum negative pressure chamber of the freeze dryer, and keep vacuuming (the vacuum degree is kept at 0.1Pa ~ 10Pa), so that the crystal water in the green body is completely sublimated , so as to achieve the purpose of drying to obtain a dry green body.

5. Vacuum degreasing

Complete the degreasing process of the dried green body in the atmosphere box furnace, using argon as the protective gas, degreasing and heating process: room temperature ~ 200 ° C (heating rate 5 ° C / min); 200 ~ 700 ° C (heating rate 1 ° C / min ); 700～900°C (heating rate 2°C/min); keep at 900°C for 1h. After degreasing, a porous SiC ceramic matrix composite material blade with a pore diameter of about 5um is obtained.

6. Impregnation and pyrolysis of organic precursors

6.1 Prepare two kinds of impregnating agents: configure SiC/PCS/xylene slurry (the mass fraction of SiC in the slurry is 10%, the mass fraction of PCS is 40%, and SiC is nanoparticles) and PCS/xylene solution (the mass fraction of PCS is 40%).

6.2 Place the obtained porous SiC ceramic preform in a vacuum tank, and suck the SiC/PCS/xylene impregnation slurry after vacuuming. The vacuum degree is 8×10 ^-2 , and the impregnation is held for 30 minutes. Dry the impregnated article at 80°C for 2-4 hours, then raise the temperature to 150°C to complete oxidative cross-linking. Under the protection of Ar gas, the temperature was raised to 1300°C at a rate of 5°C/min for cracking, and the temperature was kept at 1300°C for 1-1.5h. Then the impregnating agent was replaced with PCS/xylene solution, and the impregnating-cracking process was repeated. After the cracking process is completed, a SiC ceramic matrix composite material aero-engine blade with higher density (the density can reach 85% to 90%) is obtained.

7. Hot isostatic pressing

Heat the SiC ceramic matrix composite aero-engine blade prepared in step 6.2 from room temperature to 1500°C at a heating rate of 5°C/min, and conduct hot isostatic pressing sintering at 1500°C for 1.5 to 2 hours. Argon is used as the pressure transmission medium, and the pressure is 100MPa. After the hot isostatic pressing sintering is completed, the furnace is cooled to room temperature, and the sample is taken out to obtain a SiC ceramic matrix composite aero-engine blade with a density of 2.75-2.82g/cm ³ and a high-temperature (1300°C) bending strength of 270MPa.

Example 2

A method for preparing a high-performance SiC ceramic matrix composite material aeroengine blade, comprising the following steps:

1. Same as Step 1 of Example 1;

2. Preparation of slurry

2.1. Same as Step 2.1 of Example 1

2.2. Same as Step 2.2 of Example 1

2.3. Mix them according to the volume ratio of loose monofilament short carbon fibers with PCS coating: premix solution = (5-15): 45, and perform ultrasonic dispersion for 5 minutes. Then add graphite, silicon powder and SiC powder into the dispersed premix with the volume of graphite: silicon powder: SiC: premix = 6:14: (20-30): 45, and then add 0.5-2wt of the entire solid phase component % sodium polyacrylate as a dispersant. Then put the slurry into a mechanical stirrer and stir, the stirring time is set at 20-45min, and finally obtain the SiC suspension slurry with uniformly dispersed solid phase particles. The graphite particle size is 15-25um, the Si powder particle size is 5um, and the SiC powder particle size is 40-60um.

3. Gel injection molding

Put the SiC suspension slurry into a vacuum injection molding machine (vacuum degree is 8×10 ^-2 ), add a catalytic amount of catalyst (a solution of tetramethylethylenediamine with a mass fraction of 25%) and an initiator (mass fraction 30% ammonium persulfate solution), continue stirring. After 1 minute, start pouring the suspension slurry into the blade mold, and at the same time turn on the vibrating table to exhaust the air bubbles in the mold to ensure the complete filling. After the vacuum pouring is completed, let it stand at room temperature in the atmosphere for 30 minutes to completely complete the monomer cross-linking and solidification to obtain the gelled blade parts. Wherein, the mass ratio of the mass of the catalyst to the initiator is 1:6-7.

4. Freeze drying

Place the gelled leaf parts in a -60°C freezer and freeze for 3 to 5 hours to completely freeze and crystallize the moisture in the green body. Then use liquid nitrogen to peel off the resin mold of the green body, then put it into the vacuum negative pressure chamber of the freeze dryer, and keep vacuuming (the vacuum degree is kept at 0.1Pa ~ 10Pa), so that the crystal water in the green body is completely sublimated , so as to achieve the purpose of drying to obtain a dry green body.

5. Vacuum degreasing

The degreasing process is completed in the atmosphere box furnace, with argon as the protective gas, and the degreasing heating process: room temperature ~ 200 ° C (heating rate 5 ° C / min); 200 ~ 700 ° C (heating rate 1 ° C / min); 700 ~ 900 °C (heating rate 2 °C/min); keep at 900 °C for 1 h. After degreasing, a porous SiC ceramic with a pore size of about 5um is obtained.

6. Impregnation and pyrolysis of organic precursors

6.1 Prepare two kinds of impregnating agents, configure SiC/PCS/xylene slurry (the mass fraction of SiC in the slurry is 10%, the mass fraction of PCS is 40%, and SiC is nanoparticles) and PCS/xylene solution (the mass fraction of PCS is 40%).

6.2 Place the obtained porous SiC ceramic preform in a vacuum tank, and suck the SiC/PCS/xylene impregnation slurry after vacuuming. The vacuum degree is 8×10 ^-2 , and the impregnation is held for 30 minutes. Dry the impregnated article at 80°C for 2-4 hours, then raise the temperature to 150°C to complete oxidative cross-linking. Under the protection of Ar gas, the temperature was raised from room temperature to 1300°C at a rate of 5°C/min for cracking, and kept at 1300°C for 1-1.5h. Then the impregnating agent was replaced with PCS/xylene solution, and the impregnating-cracking process was repeated. After the cracking process is completed, a SiC composite material blade with higher density is obtained.

7. Hot isostatic pressing

Heat the SiC ceramic matrix composite aero-engine blade prepared in step 6.2 from room temperature to 1500°C at a heating rate of 5°C/min, and conduct hot isostatic pressing sintering at 1500°C for 1.5 to 2 hours. Argon is used as the pressure transmission medium, and the pressure is 100MPa. After the hot isostatic pressing sintering is completed, the furnace is cooled to room temperature, and the sample is taken out to obtain a SiC ceramic matrix composite aero-engine blade with a density of 2.75-2.82g/cm ³ and a high-temperature (1300°C) bending strength of 270MPa.

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.