CN106278335B - A kind of manufacturing method of fiber alignment toughening ceramic based composites turbo blade - Google Patents
A kind of manufacturing method of fiber alignment toughening ceramic based composites turbo blade Download PDFInfo
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- CN106278335B CN106278335B CN201610639427.5A CN201610639427A CN106278335B CN 106278335 B CN106278335 B CN 106278335B CN 201610639427 A CN201610639427 A CN 201610639427A CN 106278335 B CN106278335 B CN 106278335B
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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
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/622—Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/64—Burning or sintering processes
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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
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
- C04B2235/602—Making the green bodies or pre-forms by moulding
- C04B2235/6023—Gel casting
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Abstract
A kind of manufacturing method of fiber alignment toughening ceramic based composites turbo blade, the following steps are included: 1) stress according to turbo blade at work, design fiber moves towards arrangement in blade interior first, establish fibre preforms body three-dimensional models, then fiber preform is prepared by FDM fusion sediment method, blade resin shape is prepared by SLA Stereolithography method again, fiber preform and blade resin profile integration are assembled；2) it prepares the ceramic slurry for meeting casting requirement and completes to be poured, turbo blade biscuit is obtained after ceramic slurry curing；3) solvent and organic matter of removal turbo blade biscuit inside and fiber surface, obtains blade porous body；4) the ceramic matrix composite turbine blade of fiber alignment toughening is obtained by CVD/CVI chemical vapor deposition/osmosis.The present invention can orient toughening ceramic based composites turbo blade, improve the mechanical property of part and use temperature.
Description
Technical field
The present invention relates to a kind of processing methods of composite turbine blade, and in particular to a kind of fiber alignment toughening ceramic
The manufacturing method of based composites turbo blade.
Background technique
Hot end key component of the turbo blade as gas-turbine unit, operating condition is severe, needs in high temperature, height
Safe and reliable work, temperature capability directly decide engine performance under pressure, high revolving speed bring complexity load.
Nickel base superalloy is the material that current gas-turbine unit hot end components mainly use, and density is about
8.03-9.20g/cm3, currently holding the warm upper limit is about 1150 DEG C, and its fusion temperature is at 1350 DEG C or so.
Compared with nickel base superalloy, ceramic matric composite has lightweight, high temperature resistant, corrosion-resistant, high than strong and high ratio
The advantages that mould, it is considered to be it is the ideal material of following high-performance enginer hot end components (turbo blade, combustion chamber etc.),
The high-technology fields such as aerospace, defence and military have boundless application prospect, but ceramic material brittleness is big, reliability
It is poor, it needs to introduce toughening and mutually improves toughness of material, and need to explore a kind of holding fiber in blade interior oriented formation
Method.
Summary of the invention
It is an object of the invention to be directed to above-mentioned problem in the prior art, it is compound to provide a kind of fiber alignment toughening ceramic base
The manufacturing method of material turbo blade effectively improves the mechanical property of part and uses temperature.
To achieve the goals above, the technical solution adopted by the present invention the following steps are included:
1) stress according to turbo blade at work, first design fiber move towards arrangement blade interior, establish fine
Prefabricated body three-dimensional models are tieed up, fiber preform are then prepared by FDM fusion sediment method, then pass through SLA Stereolithography legal system
Fiber preform and blade resin shape are combined assembly by standby blade resin shape；
2) it prepares the ceramic slurry for meeting casting requirement and completes to be poured, turbo blade element is obtained after ceramic slurry curing
Base；
3) solvent and organic matter of removal turbo blade biscuit inside and fiber surface, obtains blade porous body；
4) ceramic matrix composite turbine of fiber alignment toughening is obtained by CVD/CVI chemical vapor deposition/osmosis
Blade.
The concrete operations of fiber preform are prepared in the step 1) are as follows: binding material is melted first and is wrapped in continuous
Then fiber surface carries out continuous fiber printing according to the forming path layering of design, sets in the upper and lower ends of fiber preform
It sets for connecting, supporting each layer and provide the technical support mount structure of each layer deposition initial position, continuous fiber is overlapped on technique
On supporting structure, obtain orienting the fiber preform continuously arranged along blade principal stress after adjusting fiber spacing.
The technical support mount structure includes the support body of several technique interlayers and connection all technique interlayers both ends,
Adjustment fiber spacing include adjust fiber sparse degree and technique interlayer layer away from.
Binding material and fiber are passed through heating nozzle to melt, binding material is wrapped in continuous fiber surface and sprays from printing
Mouth squeezes out.
The fiber preform is made of core reinforcing material and external binding material, and core reinforcing material is carbon fiber
Dimension, silicon carbide fibre or alumina fibre, external binding material be thermoplastic material or thermoplastic material and staple fiber group at
Mixing material.
The technique of removal turbo blade biscuit inside and fiber surface solvent and organic matter includes in the step 3)
Dry and pyrolysis, the binding material charring ablative on fiber preform surface is made by pyrolytic process, forms gap.
Ceramic powders in the ceramic slurry are one of silicon carbide, silicon nitride, boron carbide, zirconium boride or aluminium oxide
Or mixture made of multiple combinations.
The ceramic slurry passes through three-level gradation, and solid concentration is 20vol%~65vol%, and slurry viscosity is less than
1Pa.s, the particle size range of particle are 0.5 μm~50 μm.
Being cast in type vacuum injecting and forming machine for ceramic slurry is completed in the step 2).
One layer is deposited to blade porous body by CVD/CVI chemical vapor deposition/osmosis first in the step 4)
Pyrocarbon coating, then redeposited silicon carbide realizes matrix densification, finally obtains fiber alignment toughening ceramic based composites
Turbo blade.
Compared with prior art, present invention tool prepares fiber preform by FDM fusion sediment method, the fiber edge prepared
Principal direction of stress when turbo blade works continuously is arranged, and can orient toughening ceramic based composites according to part time job demand
Turbo blade.In addition, carrying out part densification by CVD/CVI chemical vapor deposition/osmosis, both realized in lower temperature
The lower manufacture for completing high performance ceramic base composite turbine blade of degree, while one layer of uniform deposition is prepared in fiber surface
Object effectively increases the mechanical property of part and uses temperature.Compared to fibrage and laying, the FDM that the present invention uses is molten
Thaw collapse area method can make the fiber preform being prepared have certain shapes precision, meet the requirement of labyrinth, and fine
Dimension moves towards arrangement along the principal direction of stress of turbo blade blade, and pore structure is controllable between fiber and fiber.SLA is light-cured into
The characteristics of type method is that forming accuracy is high, the surface quality of manufacture part is good, particularly suitable for making containing complicated fine structure
Blade resin shape has been provided using this advantageous feature to customize manufacture three-dimensional mould with the forming of Muller's fibers precast body
Sharp condition.
Further, the present invention is provided in the upper and lower ends of fiber preform for connecting when preparing fiber preform
It connects, support each layer and the technical support mount structure of each layer deposition initial position is provided, and technical support mount structure includes several
Technique interlayer and the support body for connecting all technique interlayers both ends, the purpose that support body and technique interlayer are introduced in structure are
In order to control the hole between fiber and fiber, in casting process, ceramic particle is able to enter in these holes, finally
The uniform formation that ceramic particle wraps up fiber from outside to inside is obtained, this facilitates the promotion of Blade Properties.
Further, the present invention selects multistage gradation when preparing ceramic slurry, and grain diameter is from 0.5 μm to 50 μm, slurry
Expect that viscosity control within 1Pa.s, ensure that the mold-filling capacity of slurry, also can effectively fill particularly with the lesser structure of hole
Type.
Further, ceramic slurry is silicon carbide, silicon nitride, boron carbide, zirconium boride or oxidation in casting process of the present invention
Mixture made of one of aluminium or multiple combinations is selected with the use temperature of turbo blade is corresponding to performance requirement.
Further, the present invention is during using CVD/CVI chemical deposition/osmosis process, first by blade porous body
Chemical vapor deposition is quickly carried out under cryogenic, and it is fine can to deposit one layer of uniform pyrolytic carbon protection in fiber surface
Dimension, then slowly carries out the deposition and infiltration of silicon carbide again, which deposits two layers of coatings (pyrolytic carbon, carbonization in fiber surface
Silicon) so that blade at work, extends crack propagation path, a large amount of energy to failure is consumed to improve blade mechanical property
Energy.
Detailed description of the invention
The process flow chart of Fig. 1 manufacturing method of the present invention；
Fig. 2 fiber preform and blade resin profile integration installation diagram；
The structural schematic diagram of Fig. 3 fiber preform of the present invention；
Continuous fiber reinforcement formable layer path profile in Fig. 4 (a) fiber preform；
Technique interlayer forming path figure in Fig. 4 (b) fiber preform；
In attached drawing: 1- fiber preform；2- blade resin shape；3- support body；4- technique interlayer；5- molding is initial/whole
Stop bit is set.
Specific embodiment
Present invention will be described in further detail below with reference to the accompanying drawings, described to be explanation of the invention rather than limit
It is fixed.
The manufacturing method of fiber alignment toughening ceramic based composites turbo blade of the present invention, comprising the following steps:
(1) fiber preform is manufactured；
Principal direction of stress when being worked according to turbo blade determines fiber in the arrangement of blade interior.It is made using UG three-dimensional
The threedimensional model of type software design blade interior fiber preform 1.Rapid shaping lift height is considered in design process, makes to be sliced
Forming path after layered shaping is consistent with design, is controlled by the density or adding technology interlayer 4 that design directional fiber vertical
To and lateral spacing finally obtain as shown in figures 3 and 4 and orient the fibre preforms body Model continuously arranged along blade principal stress.
Stl file is exported, model slice layering is carried out using rapid shaping the poster processing soft Magics, by data after processing
File imports fused glass pellet device fabrication fiber preform 1, post-treated to be used for subsequent technique.
(2) blade resin die is manufactured；
2 mold of blade resin shape is designed using 3D sculpting software, resin die includes blade profile shell, precast body
Location structure and ceramic slurry running gate system.Then STL format is converted by threedimensional model, and using the poster processing soft to three
Dimension module carries out layered shaping and addition support, and data file after processing is imported light-curing rapid forming equipment and is manufactured.
(3) gel casting forming；
1) assembly fiber preform 1 is combined with blade resin shape 2, as shown in Figure 2.
2) it prepares and meets the ceramic slurry that casting requires: by organic monomer acrylamide AM and crosslinking agent N, N '-methylene
Bisacrylamide MBAM is (6~24) according to mass ratio: 1 mixing, then (25 DEG C) are dissolved into deionized water at room temperature,
It is configured to the premixed liquid that mass fraction is 15%~25%.Micron SiC mixed-powder is added in scattered premixed liquid, then
The Sodium Polyacrylate of solid-phase component 0.5wt%~2wt% is added as dispersing agent.Then slurry is placed in mechanical agitator and is stirred
It mixes, mixing time is set as 20min~45min, finally obtains the finely dispersed SiC suspended nitride of solid phase particles.Micron SiC is mixed
The volume ratio of the additional amount and premixed liquid of closing powder is (39~49): 45.
3) SiC suspended nitride is placed in type vacuum injecting and forming machine, suitable catalyst and initiator is successively added, stirs evenly
After start to be poured suspended nitride into resin die, and the bubble in slurry is drained in resin die.It is completed to vacuum pouring
Afterwards, room temperature is stood under atmospheric environment, completes the monomer crosslinked blade biscuit solidified after obtaining gel；
Wherein, the catalyst is the tetramethylethylenediamine solution that mass fraction is 25%, and initiator is that mass fraction is
30% ammonium persulfate solution, the quality of catalyst and the mass ratio of initiator are 1:(6~7).
(4) it is freeze-dried；
Blade biscuit after gel is placed in -60 DEG C of jelly cabinet, 3h~5h is freezed, keeps the moisture in biscuit completely cold
Freeze crystalline substance.Then the resin die of biscuit is removed using liquid nitrogen, and removes part of the fiber preform other than blade, then will
It is put into the negative pressure of vacuum cabin of freeze drier, persistently vacuumizes (vacuum degree is maintained at 0.1Pa~10Pa), so that in green compact
The crystallization water distil completely, to obtain dry blade biscuit.
(5) degreasing；
Dry biscuit is subjected to degreasing in atmosphere batch-type furnace, using argon gas as protective gas, (is risen with room temperature~200 DEG C
Warm rate is 5 DEG C/min), 200~700 DEG C (heating rate is 1 DEG C/min), 700~900 DEG C (heating rate is 2 DEG C/min),
900 DEG C of heat preservation 1h are as heating process parameter.The organic matter that biscuit inside and fiber surface are removed after the completion of degreasing, obtains hole
SiC ceramic blade porous body of the diameter at 5 μm or so.
(6) chemical vapor deposition/infiltration；
Blade porous body in step (5) is placed in chemical vapor deposition/infiltration furnace, using propylene as air-born substances, hydrogen
As carrier gas, hydrogen flowing quantity 300ml/min, in-furnace temperature is 900-1100 DEG C, fast deposition pyrolytic carbon, sedimentation time 2~
8h.Then using trichloromethyl silane (MTS) as air-born substances, hydrogen is as carrier gas, and argon gas is as carrier gas, depositing temperature
1100~1300 DEG C, atmosphere pressures 3kPa, 200~400ml/min of argon flow, hydrogen flowing quantity 300ml/min, sedimentation time
100h。
Silicon carbide chemical vapor deposition/infiltration is carried out to hole by gas diffusion, obtains continuous fiber orientation toughening
Ceramic matrix composite turbine blade.
Claims (10)
1. a kind of manufacturing method of fiber alignment toughening ceramic based composites turbo blade, which is characterized in that including following step
It is rapid:
1) stress according to turbo blade at work, first design fiber move towards arrangement blade interior, and it is pre- to establish fiber
Then body three-dimensional models processed are prepared fiber preform (1) by FDM fusion sediment method, then prepared by SLA Stereolithography method
Fiber preform (1) and blade resin shape (2) are combined assembly by blade resin shape (2)；
2) it prepares the ceramic slurry for meeting casting requirement and completes to be poured, turbo blade biscuit is obtained after ceramic slurry curing；
3) solvent and organic matter of removal turbo blade biscuit inside and fiber surface, obtains blade porous body；
4) the ceramic matrix composite turbine blade of fiber alignment toughening is obtained by CVD/CVI chemical vapor deposition/osmosis.
2. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 1
In preparing the concrete operations of fiber preform (1) in the step 1) are as follows: first melt binding material and be wrapped in continuous fibre
Then dimension table face carries out continuous fiber printing according to the forming path layering of design, sets in the upper and lower ends of fiber preform (1)
It sets for connecting, supporting each layer and provide the technical support mount structure of each layer deposition initial position, continuous fiber is overlapped on technique
On supporting structure, obtain orienting the fiber preform (1) continuously arranged along blade principal stress after adjusting fiber spacing.
3. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 2
In: the technical support mount structure includes the support body of several technique interlayers (4) and all technique interlayer (4) both ends of connection
(3), adjustment fiber spacing include adjust fiber sparse degree and technique interlayer (4) layer away from.
4. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 2
In: binding material and fiber are passed through heating nozzle and melted, binding material is wrapped in continuous fiber surface and squeezes from printing nozzle
Out.
5. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 2
Be made of in: the fiber preform (1) core reinforcing material and external binding material, core reinforcing material be carbon fiber,
Silicon carbide fibre or alumina fibre, external binding material be thermoplastic material or thermoplastic material and staple fiber group at it is mixed
Condensation material.
6. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 2
In: in the step 3) inside removal turbo blade biscuit and the technique of fiber surface solvent and organic matter include it is dry and
Pyrolysis makes the binding material charring ablative on fiber preform (1) surface by pyrolytic process, forms gap.
7. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 1
In: ceramic powders in the ceramic slurry be one of silicon carbide, silicon nitride, boron carbide, zirconium boride or aluminium oxide or more
The mixture that kind is composed.
8. according to claim 1 or the manufacturing method of the 7 fiber alignment toughening ceramic based composites turbo blades, feature
Be: the ceramic slurry passes through three-level gradation, and solid concentration is 20vol%~65vol%, and slurry viscosity is less than 1Pa.s,
The particle size range of grain is 0.5 μm~50 μm.
9. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 1
In: being cast in type vacuum injecting and forming machine for ceramic slurry is completed in the step 2).
10. the manufacturing method of fiber alignment toughening ceramic based composites turbo blade, feature exist according to claim 1
In: one layer of pyrolytic carbon is deposited to blade porous body by CVD/CVI chemical vapor deposition/osmosis first in the step 4)
Coating, then redeposited silicon carbide realizes matrix densification, finally obtains fiber alignment toughening ceramic based composites turbine leaf
Piece.
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| CN114105663B (en) * | 2021-11-19 | 2022-08-23 | 西北工业大学 | Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity |
| CN114292115A (en) * | 2021-12-31 | 2022-04-08 | 华中科技大学 | Reinforced SiC composite material preparation method based on robot laser additive manufacturing |
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