CN106278335A - A kind of manufacture method of fiber alignment toughening ceramic based composites turbo blade - Google Patents
A kind of manufacture method of fiber alignment toughening ceramic based composites turbo blade Download PDFInfo
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- CN106278335A CN106278335A CN201610639427.5A CN201610639427A CN106278335A CN 106278335 A CN106278335 A CN 106278335A CN 201610639427 A CN201610639427 A CN 201610639427A CN 106278335 A CN106278335 A CN 106278335A
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- fiber
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- turbo blade
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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
Abstract
A kind of manufacture method of fiber alignment toughening ceramic based composites turbo blade, comprise the following steps: 1) according to turbo blade stress operationally, first design fiber blade interior move towards arrangement, set up fibre preforms body three-dimensional models, then fiber preform is prepared by FDM fusion sediment method, prepare blade resin profile by SLA Stereolithography method again, fiber preform is assembled with blade resin profile integration；2) preparation meets the ceramic size of cast requirement and completes cast, obtains turbo blade biscuit after ceramic slurry curing；3) remove turbo blade biscuit inside and the solvent of fiber surface and Organic substance, obtain blade porous body；4) obtain, by CVD/CVI chemical gaseous phase deposition/osmosis, the ceramic matrix composite turbine blade that fiber alignment is toughness reinforcing.The present invention can orient toughening ceramic based composites turbo blade, improves mechanical property and the use temperature of part.
Description
Technical field
The processing method that the present invention relates to a kind of composite turbine blade, is specifically related to a kind of fiber alignment toughening ceramic
The manufacture method of based composites turbo blade.
Background technology
Turbo blade is as the hot junction key component of gas-turbine unit, and its working condition is severe, needs at high temperature, height
Work safe and reliable under the complicated load that pressure, high rotating speed bring, its temperature capability directly decides engine performance.
Nickel base superalloy is the material that current gas-turbine unit hot junction parts mainly use, and its density is about
8.03-9.20g/cm3, currently hold the temperature upper limit and be about 1150 DEG C, and its fusion temperature is at about 1350 DEG C.
Compared with nickel base superalloy, ceramic matric composite has lightweight, high temperature resistant, corrosion-resistant, high than strong and high ratio
The advantages such as mould it is considered to be the ideal material of following high-performance enginer hot junction parts (turbo blade, combustor etc.),
The high-technology field such as Aero-Space, defence and military has boundless application prospect, but ceramic material fragility is big, reliability
Poor, need to introduce toughness reinforcing phase and improve toughness of material, and need to explore and a kind of keep fiber at blade interior oriented formation
Method.
Summary of the invention
Present invention aims to problem in above-mentioned prior art, it is provided that a kind of fiber alignment toughening ceramic base is combined
The manufacture method of material turbo blade, is effectively improved mechanical property and the use temperature of part.
To achieve these goals, the technical solution used in the present invention comprises the following steps:
1) according to turbo blade stress operationally, first design fiber moves towards arrangement in blade interior, sets up fibre
Dimension precast body threedimensional model, then prepares fiber preform by FDM fusion sediment method, then by SLA Stereolithography legal system
Standby blade resin profile, is combined assembling by fiber preform and blade resin profile；
2) preparation meets the ceramic size of cast requirement and completes cast, obtains turbo blade element after ceramic slurry curing
Base；
3) remove turbo blade biscuit inside and the solvent of fiber surface and Organic substance, obtain blade porous body；
4) obtain, by CVD/CVI chemical gaseous phase deposition/osmosis, the ceramic matrix composite turbine that fiber alignment is toughness reinforcing
Blade.
Described step 1) in prepare the concrete operations of fiber preform and be: first binding material melted and be wrapped in continuously
Fiber surface, then according to the forming path layering of design carries out continuous fiber printing, sets at the two ends up and down of fiber preform
Putting for connecting, support each layer and providing the technical support mount structure of each layer deposition original position, continuous fiber is overlapped on technique
On supporting structure, after adjusting fiber spacing, i.e. obtain the fiber preform along the arrangement continuously of blade principal stress orientation.
Described technical support mount structure includes several technique interlayers and connects the stake body at all technique interlayer two ends,
Adjust fiber spacing include the layer adjusting the sparse degree of fiber and technique interlayer away from.
Binding material and fiber being passed through heating shower nozzle melt, binding material is wrapped in continuous fiber surface and from printing spray
Mouth is extruded.
Described fiber preform is made up of with outside binding material core reinforcing material, and core reinforcing material is that carbon is fine
Dimension, silicon carbide fibre or alumina fibre, outside binding material is thermoplastic or thermoplastic forms with chopped fiber
Mixing material.
Described step 3) middle removal turbo blade biscuit is internal and fiber surface solvent includes with organic technique
It is dried and pyrolysis, makes the binding material charring ablative of fibre preforms surface through pyrolytic process, form gap.
Ceramic powders in described ceramic size is the one in carborundum, silicon nitride, boron carbide, zirconium boride or aluminium oxide
Or the mixture of multiple combination.
Described ceramic size is through three grades of gratings, and solid concentration is 20vol%～65vol%, and slurry viscosity is less than
1Pa.s, the particle size range of granule is 0.5um～50um.
Described step 2) in ceramic size be cast in type vacuum injecting and forming machine in complete.
Described step 4) in first pass through CVD/CVI chemical gaseous phase deposition/osmosis to blade porous body deposit one layer
Pyrocarbon coating, then redeposited carborundum realizes matrix densification, finally gives 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 during turbo blade work is arranged continuously, it is possible to orient toughening ceramic based composites according to part time job demand
Turbo blade.Additionally, carry out part densification by CVD/CVI chemical gaseous phase deposition/osmosis, both achieved in relatively low temperature
Complete the manufacture of high performance ceramic base composite turbine blade under degree, prepare one layer of uniform deposition at fiber surface simultaneously
Thing, is effectively increased mechanical property and the use temperature of part.Compared to fibrage and lay, the FDM that the present invention uses melts
Thaw collapse area method can make the fiber preform prepared have definite shape precision, meets the requirement of labyrinth, and fine
Dimension moves towards the principal direction of stress along turbo blade blade of arranging, and between fiber and fiber, pore structure is controlled.SLA is light-cured into
The feature of type method is that forming accuracy surface quality high, manufacture part is good, is particularly suitable for making containing complicated fine structure
Blade resin profile, utilizes this advantageous feature to provide with the shaping of Muller's fibers precast body for customizing manufacture three-dimensional mould
Profit condition.
Further, the present invention, when preparing fiber preform, is provided with at the two ends up and down of fiber preform for even
Connect, support each layer and the technical support mount structure of each layer deposition original position is provided, and technical support mount structure includes several
Technique interlayer and connect the stake body at all technique interlayer two ends, the purpose structurally introducing stake body and technique interlayer is
In order to control the hole between fiber and fiber, in casting process, ceramic particle can enter in the middle of these holes, finally
Obtaining ceramic particle and wrap up the uniform formation of fiber from outside to inside, this contributes to the lifting of Blade Properties.
Further, the present invention selects multistage grating when preparing ceramic size, and grain diameter, from 0.5um to 50um, is starched
Material viscosity controls within 1Pa.s, it is ensured that the mold-filling capacity of slurry, the structure less particularly with hole also can effectively be filled
Type.
Further, in casting process of the present invention, ceramic size is carborundum, silicon nitride, boron carbide, zirconium boride or oxidation
The mixture that one or more in aluminum combine, selects 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
The most quickly carry out chemical gaseous phase deposition, it is possible to deposit one layer of uniform pyrolytic carbon protection fibre at fiber surface
Dimension, the most slowly carries out deposition and the infiltration of carborundum, and this technique deposits two layers of coatings (pyrolytic carbon, carbonization at fiber surface
Silicon) so that blade operationally, extends crack propagation path, consumes substantial amounts of energy to failure thus improves blade mechanical property
Energy.
Accompanying drawing explanation
The process chart of Fig. 1 manufacture method of the present invention；
Fig. 2 fiber preform and blade resin profile integration installation diagram；
The structural representation of Fig. 3 fiber preform of the present invention；
Continuous lod formable layer pathway figure in Fig. 4 (a) fiber preform；
Technique interlayer forming path figure in Fig. 4 (b) fiber preform；
In accompanying drawing: 1-fiber preform；2-blade resin profile；3-stake body；4-technique interlayer；5-molding is initial/whole
Stop bit is put.
Detailed description of the invention
The present invention is described in further detail below in conjunction with the accompanying drawings, described in be explanation of the invention rather than limit
Fixed.
The manufacture method of fiber alignment toughening ceramic based composites turbo blade of the present invention, comprises the following steps:
(1) fiber preform is manufactured；
Principal direction of stress when working according to turbo blade, determines the fiber arrangement in blade interior.UG three-dimensional is used to make
The threedimensional model of type software design blade interior fiber preform 1.Design process considers rapid shaping lift height, makes section
Forming path after layered shaping is consistent with design, and density or adding technology interlayer 4 by design directional fiber control vertical
To and horizontal spacing, such as Fig. 3, shown in 4, finally give the fibre preforms body Model along the arrangement continuously of blade principal stress orientation.
Output stl file, uses rapid shaping the poster processing soft Magics to carry out model slice layering, data after processing
File imports fused glass pellet device fabrication fiber preform 1, post-treated for subsequent technique.
(2) blade resin die is manufactured；
Using 3D sculpting software design blade resin profile 2 mould, resin die includes blade profile shell, precast body
Location structure, and ceramic size running gate system.Then threedimensional model is converted into STL form, and uses the poster processing soft to three
Dimension module carries out layered shaping and adds support, data file after process is imported light-curing rapid forming equipment and manufactures.
(3) gel casting forming；
1) fiber preform 1 and blade resin profile 2 are combined assembling, as shown in Figure 2.
2) preparation meets the ceramic size that cast requires: by organic monomer acrylamide AM and cross-linking agent N, N '-methylene
Bisacrylamide MBAM, is (6～24) according to mass ratio: 1 mixing, and the most at room temperature (25 DEG C) are dissolved in deionized water,
It is configured to the premixed liquid that mass fraction is 15%～25%.Micron SiC mixed-powder is added in scattered premixed liquid, then
Add the sodium polyacrylate of solid-phase component 0.5wt%～2wt% as dispersant.Then stir in slurry being inserted mechanical agitator
Mixing, mixing time is set as 20min～45min, finally gives solid phase particles finely dispersed SiC suspended nitride.Micron SiC is mixed
Closing the addition of powder with the volume ratio of premixed liquid is (39～49): 45.
3) SiC suspended nitride is inserted in type vacuum injecting and forming machine, successively add appropriate catalyst and initiator, stir
Suspended nitride is poured into a mould in rear beginning in resin die, and drains the bubble in slurry in resin die.Treat that vacuum pouring completes
After, under atmospheric environment, room temperature stands, and completes the blade biscuit after monomer crosslinked solidification obtains gel；
Wherein, described catalyst be mass fraction be the tetramethylethylenediamine solution of 25%, 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) lyophilization；
Blade biscuit after gel is positioned over-60 DEG C freeze in cabinet, freezing 3h～5h, make the moisture in biscuit the coldest
Freeze crystalline substance.Then use liquid nitrogen to be peeled off by the resin die of biscuit, and remove fiber preform part beyond blade, then will
It puts into the negative pressure of vacuum cabin of freezer dryer, continues evacuation (vacuum is maintained at 0.1Pa～10Pa) so that in green compact
Water of crystallization distil completely, thus obtain the blade biscuit being dried.
(5) defat；
Dry biscuit is carried out in atmosphere batch-type furnace defat, with argon as protective gas, (rises with room temperature～200 DEG C
Temperature speed be 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 insulation 1h are as heating process parameter.Biscuit inside and the Organic substance of fiber surface are removed in defat after completing, obtain hole
Footpath is at the SiC ceramic blade porous body of about 5um.
(6) chemical gaseous phase deposition/infiltration；
Step (5) Leaf porous body is placed on chemical gaseous phase and deposits/permeate in stove, with 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 is as carrier gas, depositing temperature
1100～1300 DEG C, atmosphere pressures 3kPa, argon flow amount 200～400ml/min, hydrogen flowing quantity 300ml/min, sedimentation time
100h。
Carry out carborundum chemistry vapour deposition/infiltration by gas diffusion couple hole, obtain continuous fiber orientation toughness reinforcing
Ceramic matrix composite turbine blade.
Claims (10)
1. the manufacture method of a fiber alignment toughening ceramic based composites turbo blade, it is characterised in that include following step
Rapid:
1) according to turbo blade stress operationally, first design fiber moves towards arrangement in blade interior, sets up fiber pre-
Body three-dimensional models processed, is then prepared fiber preform (1) by FDM fusion sediment method, then is prepared by SLA Stereolithography method
Blade resin profile (2), is combined assembling by fiber preform (1) and blade resin profile (2)；
2) preparation meets the ceramic size of cast requirement and completes cast, obtains turbo blade biscuit after ceramic slurry curing；
3) remove turbo blade biscuit inside and the solvent of fiber surface and Organic substance, obtain blade porous body；
4) obtain, by CVD/CVI chemical gaseous phase deposition/osmosis, the ceramic matrix composite turbine blade that fiber alignment is toughness reinforcing.
The most according to claim 1, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In, described step 1) in prepare the concrete operations of fiber preform (1) and be: first binding material melted and be wrapped in continuous fibre
Dimension table face, then according to the forming path layering of design carries out continuous fiber printing, sets at the two ends up and down of fiber preform (1)
Putting for connecting, support each layer and providing the technical support mount structure of each layer deposition original position, continuous fiber is overlapped on technique
On supporting structure, after adjusting fiber spacing, i.e. obtain the fiber preform (1) along the arrangement continuously of blade principal stress orientation.
The most according to claim 2, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In: described technical support mount structure includes several technique interlayers (4) and connects the stake body at all technique interlayer (4) two ends
(3), adjust fiber spacing include the layer adjusting the sparse degree of fiber and technique interlayer (4) away from.
The most according to claim 2, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In: binding material and fiber being passed through heating shower nozzle and melts, binding material is wrapped in continuous fiber surface and squeezes from printing nozzle
Go out.
The most according to claim 2, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
Be made up of with outside binding material core reinforcing material in: described fiber preform (1), core reinforcing material be carbon fiber,
Silicon carbide fibre or alumina fibre, what outside binding material was thermoplastic or thermoplastic with chopped fiber composition is mixed
Condensation material.
The most according to claim 2, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In described step 3) in remove that turbo blade biscuit is internal and fiber surface solvent and organic technique include being dried and
Pyrolysis, makes the binding material charring ablative on fiber preform (1) surface through pyrolytic process, forms gap.
The most according to claim 1, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In: the ceramic powders in described ceramic size is the one in carborundum, silicon nitride, boron carbide, zirconium boride or aluminium oxide or many
Plant the mixture combined.
8. according to the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature described in claim 1 or 7
Being: described ceramic size is through three grades of gratings, and solid concentration is 20vol%～65vol%, slurry viscosity is less than 1Pa.s,
The particle size range of grain is 0.5um～50um.
The most according to claim 1, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In described step 2) in ceramic size be cast in type vacuum injecting and forming machine in complete.
The most according to claim 1, the manufacture method of fiber alignment toughening ceramic based composites turbo blade, its feature exists
In described step 4) in first pass through CVD/CVI chemical gaseous phase deposition/osmosis blade porous body deposited one layer of pyrolytic carbon
Coating, then redeposited carborundum realizes matrix densification, finally gives fiber alignment toughening ceramic based composites turbine leaf
Sheet.
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Cited By (10)
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| CN106946571A (en) * | 2017-03-27 | 2017-07-14 | 安徽陶普新材科技有限公司 | A kind of fiber reinforced silicon carbide ceramic impeller and its gel casting forming preparation method |
| CN108033802A (en) * | 2017-12-15 | 2018-05-15 | 天津大学 | Fiber reinforced ceramic profiled piece forming method based on gel injection-moulding 3D printing |
| CN109482886A (en) * | 2019-01-07 | 2019-03-19 | 吉林大学 | A kind of preparation method of 3D printing ceramics and fiber composite enhancing alumina-base material |
| CN110229012A (en) * | 2019-06-27 | 2019-09-13 | 西安交通大学 | A kind of continuous fiber combines short carbon fiber toughened ceramic matric composite forming method |
| CN112898038A (en) * | 2021-03-22 | 2021-06-04 | 河海大学 | Preparation method of silicon nitride-based fiber monolithic ceramic wave-transmitting material |
| JP2022509125A (en) * | 2018-11-20 | 2022-01-20 | ユーティー－バットル，リミティド ライアビリティ カンパニー | Additional manufacturing of complex objects using refractory matrix materials |
| CN114013069A (en) * | 2021-10-22 | 2022-02-08 | 华中科技大学 | Automatic laying and fused deposition compounding process of fiber reinforced thermoplastic material |
| CN114105663A (en) * | 2021-11-19 | 2022-03-01 | 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 |
| CN115650755A (en) * | 2022-11-03 | 2023-01-31 | 西北工业大学 | Method for preparing continuous fiber toughened silicon carbide ceramic matrix composite material through 3D printing |
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| CN106946571B (en) * | 2017-03-27 | 2018-07-24 | 安徽陶普新材科技有限公司 | A kind of fiber reinforced silicon carbide ceramic impeller and its gel casting forming preparation method |
| CN106946571A (en) * | 2017-03-27 | 2017-07-14 | 安徽陶普新材科技有限公司 | A kind of fiber reinforced silicon carbide ceramic impeller and its gel casting forming preparation method |
| CN108033802A (en) * | 2017-12-15 | 2018-05-15 | 天津大学 | Fiber reinforced ceramic profiled piece forming method based on gel injection-moulding 3D printing |
| JP2022509125A (en) * | 2018-11-20 | 2022-01-20 | ユーティー－バットル，リミティド ライアビリティ カンパニー | Additional manufacturing of complex objects using refractory matrix materials |
| JP7197696B2 (en) | 2018-11-20 | 2022-12-27 | ユーティー－バットル，リミティド ライアビリティ カンパニー | Integral nuclear fuel element and manufacturing method thereof |
| CN109482886A (en) * | 2019-01-07 | 2019-03-19 | 吉林大学 | A kind of preparation method of 3D printing ceramics and fiber composite enhancing alumina-base material |
| CN110229012A (en) * | 2019-06-27 | 2019-09-13 | 西安交通大学 | A kind of continuous fiber combines short carbon fiber toughened ceramic matric composite forming method |
| CN112898038A (en) * | 2021-03-22 | 2021-06-04 | 河海大学 | Preparation method of silicon nitride-based fiber monolithic ceramic wave-transmitting material |
| CN112898038B (en) * | 2021-03-22 | 2022-06-10 | 河海大学 | Preparation method of silicon nitride-based fiber monolithic ceramic wave-transmitting material |
| CN114013069A (en) * | 2021-10-22 | 2022-02-08 | 华中科技大学 | Automatic laying and fused deposition compounding process of fiber reinforced thermoplastic material |
| CN114013069B (en) * | 2021-10-22 | 2022-12-02 | 华中科技大学 | Automatic laying and fused deposition compounding process of fiber reinforced thermoplastic material |
| CN114105663A (en) * | 2021-11-19 | 2022-03-01 | 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 |
| CN115650755A (en) * | 2022-11-03 | 2023-01-31 | 西北工业大学 | Method for preparing continuous fiber toughened silicon carbide ceramic matrix composite material through 3D printing |
| CN115650755B (en) * | 2022-11-03 | 2023-08-18 | 西北工业大学 | Method for preparing continuous fiber toughened silicon carbide ceramic matrix composite material through 3D printing |
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