CN109020589A - A kind of crash-proof fuel kernel cladding tubes and preparation method - Google Patents
A kind of crash-proof fuel kernel cladding tubes and preparation method Download PDFInfo
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Abstract
The present invention relates to a kind of crash-proof fuel kernel cladding tubes and preparation method, crash-proof fuel kernel cladding tubes are superimposed according to the design needs by continuous SiC fiber toughening SiC ceramic based composites and high melting metal layer and form sandwich multilayered structure.The multilayered structure is with continuous SiC fiber toughening SiC ceramic based composites for interior tube layer, is intermediate tube layer and continuous SiC fiber toughening SiC ceramic based composites for external tube layer using high melting metal layer.In the multilayered structure, continuous SiC fiber toughening SiC ceramic based composites layer primarily serves support bearing effect, and high melting metal layer primarily serves sealing antiseep effect.Crash-proof fuel kernel cladding tubes of the invention may be implemented in stress when crackle extends in the composite, to keep the air-tightness of core cladding tubes beyond ceramic matric composite regime of elastic deformation.
Description
Technical field
The present invention relates to a kind of crash-proof fuel kernel cladding tubes and preparation methods, and in particular to a kind of multilayer SiCf/ SiC pottery
The preparation method of the porcelain based composites core cladding tubes mutually compound with refractory metal, this seed nucleus cladding tubes are mainly used for forth generation gas
The molding and protection of nuclear fuel rod in cold fast neutron nuclear reaction heap.The crash-proof fuel kernel cladding tubes of this method preparation can also be used
In other nuclear reactors, such as the cold fast neutron reactor of pressurized water reactor, boiling water reactor, sodium.
Background technique
Ceramic matric composite is because of its low-density, Gao Biqiang, Gao Bimo, anti-oxidant, antifatigue creep, and not to crackle
The excellent properties of catastrophic damage etc. do not occur and are concerned for sensitivity.In addition ceramic matric composite is in neutron irradiation
With under hot environment still have good mechanical performance, thermal shock resistance still ensured that especially after losing coolant
The integrality of cladding tubes structure improves crash-proof ability.This has ceramic matric composite also greatly in nuclear defence field
Application prospect, become nuclear fuel element and command bundle rods for nuclear reactors cladding ideal candidates material.
However, core is faced with the critical bottleneck problem of poor air-tightness with ceramic matric composite.Therefore, these materials are uncomfortable
Cooperation is that pressure vessel or pressure pipeline use, and can not be used as cladding nuclear fuels or heat exchanger tube.Nuclear fuel covering material is resistance
The first barrier of gear radiation product diffusion, simple ceramic matric composite are not appropriate for as cladding nuclear fuels material.
Ceramic matric composite is emphasis as the problem of core cladding tubes poor air-tightness.Currently, ceramic matric composite
(SiCf/ SiC ceramic matrix composite material) breaking strength be about 300MPa, but its elastic deformation stage is very short, flexible deformation intensity
About 80MPa, elastic strain about 0.09%.When stress is greater than elastic strength, ceramic matric composite enters matrix fine fisssure
The line spreading fracture stage causes a large amount of crackle holes to generate.This fracture mode can be such that ceramic matric composite undertakes more
Stress, but deflection needed for core cladding materials is about 0.2% to 0.5% in practical applications, and intensity is about
100MPa, design strength need to reach 200MPa under extreme conditions.Obviously, ceramic matric composite is not able to satisfy core involucrum structure
Part air-tightness safety requirements.
Currently, having done a few thing about the air-tightness for improving ceramic matric composite both at home and abroad.Holger
H.Streckert(Holger H.Streckert et al.,“Hermetic ceramic composite
Structures ", US005681511A) it is vapor-deposited one layer of SiC dense coating in ceramic matric composite surface chemistry, it can be
The leakage of the gases such as helium is successfully prevented at a temperature of 1000 DEG C.Feinroth(Feinroth et al.,"Multi-layered
ceramic tube for fuel containment barrier and other applications in nuclear
2006/0039524 A1 of and fossil power plants ", US) SiC painting is prepared between two-layer ceramic based composites
Layer forms a kind of sandwich structure, effectively increases the air-tightness of core cladding tubes.But above-mentioned material is only applicable in its elasticity
It is used in deformation range, once stress is greater than its elastic strength, crackle will extend in the base, and the air-tightness of material is deteriorated,
And the elastic strength of ceramic matric composite is typically small as seen from the above.On the other hand, it prepares on core cladding tubes and uniformly causes
Close SiC coating is highly difficult.
Refractory metal can not only keep intensity at high temperature, but also have good plasticity, but refractory metal be not easy with
Nuclear fuel directly contacts, in order to avoid be etched.So the present invention combines existing work, a kind of two-layer ceramic based composites are invented
The sandwich multi-layer ceramics based composites cladding nuclear fuels pipe structure of one layer of refractory metal of sandwich, ceramic matric composite
Mechanical strength is kept outside and protects refractory metal from corroding, air-tightness of the high melting metal layer in interior holding member.Compared to
Previous invention, the present invention may be implemented in stress beyond ceramic matric composite regime of elastic deformation, and crackle is in composite wood
When extending in material, the air-tightness of holding member is remained to.
High melting metal layer will have the compatibility (lesser neutron cross section) of (1) and irradiation and in high dose of radiation (in thermography
Greater than 50dpa, greater than the mechanical strength kept under 100dpa) in reactor scope of design in fast spectrum；(2) with the compatibility of high temperature
(high-melting-point converts without allotrope, keeps certain mechanical strength)；(3) with the heat chemistry of the CMC material of inner and outer tubes
Compatibility；(4) convenient for welding.Subsequent technique will prepare ceramic matric composite in metal tube layer, so metal tube layer needs to select
With the refractory metal that can bear outer layer ceramic matric composite preparation condition, (outer layer ceramic matric composite preparation temperature is 1000
DEG C or so).Therefore selecting the metal tube layer material for meeting above-mentioned condition is Nb, Ta, W, Mo etc. and its alloy, such as Nb-1Zr, W-
Re etc..The multilayered structure is suitable for the nuclear fuel coating comprising nuclear fuel and the fission gas discharged under irradiation, therefore gold
Belong to the thickness of tube layer preferably between 50 microns to 200 microns.
Acutely diffusion and chemical reaction can occur under high temperature and radiation parameter with ceramic matrix for refractory metal, generate brittleness
Carbide or silicide, not only will form new hole can also reduce the mechanical performance of cladding tubes.The present invention is also multiple in ceramic base
One layer is prepared between condensation material layer and high melting metal layer and reacts barrier, and reaction barrier can be the expansion of aluminium oxide, pyrolytic carbon or rhenium
Dissipate potential barrier etc..On the other hand, this layer can also not alleviate the thermal expansion coefficient between ceramic matric composite and refractory metal not
With problem.
Summary of the invention
Technical problems to be solved
In order to avoid the shortcomings of the prior art, the present invention proposes a kind of crash-proof fuel kernel cladding tubes and preparation side
Method.
Technical solution
A kind of crash-proof fuel kernel cladding tubes, it is characterised in that including two layers of SiC/SiC composite layer and refractory metal
Layer, interior tube layer and external tube layer are SiC/SiC composite layer, and interlayer is that high melting metal layer constitutes sandwich multilayer knot between two layers
Structure；The interface of the SiC/SiC composite layer is the interface pyrolytic carbon PyC；The refractory metal layer material are as follows: Nb, Ta, W,
Any one in Mo, Zr and its alloy；Said inner tube thickness degree 0.2-0.5mm；Described 50-200 μm of high melting metal layer thickness；
The external tube layer 0.3-1mm.
Al is equipped between two layers2O3Buffer layer or PyC buffer layer.
The buffer layer is aluminium oxide Al2O3Or pyrolytic carbon PyC.
A method of preparing the crash-proof fuel kernel cladding tubes, it is characterised in that steps are as follows:
Step 1: SiC fiber preform is prepared on hollow plumbago pipe, then using CVI technique in SiC fiber preform
The interface upper preparation pyrolytic carbon PyC, then using CVI to progress SiC matrix densification；The SiC/SiC composite material inner tube thickness
Spend 0.2-0.5mm；
Step 2: in SiC/SiC composite material in tube layer, using Metal Organic Chemical Vapor Deposition MOCVD,
Vacuum plasma spray coating VPS or magnetron sputtering technique directly prepare high melting metal layer on interior tube layer surface；The high melting metal layer
With a thickness of 50-200 μm；
Step 3: using basketry, one layer of SiC fiber preform is worked out outside high melting metal layer, is then used
CVI technique prepares the interface pyrolytic carbon PyC on SiC fiber preform, then using CVI to progress SiC matrix densification；It is described
SiC/SiC composite material external tube layer 0.3-1mm；
Step 4: sloughing hollow plumbago pipe, complete the preparation of multilayer crash-proof fuel kernel cladding tubes.
Al between two layers of the preparation2O3The method of buffer layer is, outside SiC/SiC composite material prepared by polishing step 1
The surface of high melting metal layer prepared by surface or step 2, material is placed in magnetron sputtering stove, is prepared using magnetron sputtering
Al2O3Buffer layer, technological parameter are as follows: target uses single Al2O3Target, sputter temperature are 300-600 DEG C, sputtering power 80-
110W, air pressure is 0.1-0.55Pa in furnace, sputters 2-5h, prepares the Al of 50-100nm2O3Buffer layer.
The method of PyC buffer layer between two layers of the preparation is, outside SiC/SiC composite material prepared by polishing step 1
The surface of high melting metal layer prepared by surface or step 2, material is hung in cvd furnace, is buffered using CVD process deposits PyC
Layer, the technological parameter of deposition: precursor gas source uses propylene C3H6, depositing temperature is 800-900 DEG C, deposition pressure 2-5kPa,
10-20h is deposited, the PyC buffer layer of 50-100nm thickness is deposited.
The technique for preparing the interface pyrolytic carbon PyC on SiC fiber preform using CVI technique of the step 1 and step 3
Are as follows: obtained SiC fiber preform is hung on the mating sample frame of vacuum drying oven, precast body is in isothermal region centre bit in furnace
It sets, the interface PyC is deposited on above-mentioned SiC fiber using CVI technique.The technological parameter of deposition: precursor gas source uses propylene
C3H6, depositing temperature is 800-900 DEG C, deposition pressure 2-5kPa, deposits 20-50h, deposits PyC circle of 100-300nm thickness
Face.
The step 1 and step 3 use CVI to the technique for carrying out SiC matrix densification are as follows: deposited the pre- of the interface PyC
Body processed is hung in cvd furnace, is passed through trichloromethyl silane CH3SiCl3, MTS, hydrogen H2With diluent gas argon Ar, wherein H2
Mole mixture ratio with MTS is 10:1；Holding furnace pressure is 2-5kPa, and SiC base is deposited in 900-1000 DEG C of temperature range
Body, sedimentation time 150-400h.
The step 2 prepares high melting metal layer using technique in interior tube layer: using cold rolling, hot rolling or extrusion process system
It is standby with the matched refractory metal tube layer of interior tube layer size, then using cold drawing or hot-drawn process sleeve outside interior tube layer.
Beneficial effect
A kind of crash-proof fuel kernel cladding tubes proposed by the present invention and preparation method, crash-proof fuel kernel cladding tubes are by continuous
The fiber reinforced SiC ceramic based composites of SiC and high melting metal layer are superimposed according to the design needs forms sandwich multilayer knot
Structure.The multilayered structure is with continuous SiC fiber toughening SiC ceramic based composites for interior tube layer, is centre with high melting metal layer
Tube layer and continuous SiC fiber toughening SiC ceramic based composites are external tube layer.In the multilayered structure, continuous SiC fiber
Toughening SiC ceramic based composites layer primarily serves support bearing effect, and high melting metal layer primarily serves sealing antiseep effect.
Crash-proof fuel kernel cladding tubes of the invention may be implemented in stress beyond ceramic matric composite regime of elastic deformation, and crackle is
When extending in the composite, the air-tightness of core cladding tubes is kept.
Present invention has the main advantage that sandwich structure core of (1) ceramic matric composite of the present invention in conjunction with metal phase
On the one hand fuel tube overcomes the shortcomings that catastrophic failure easily occurs for conventional seals metallic nuclear fuel cladding tubes；On the other hand
Compared to pure ceramic core cladding tubes, the air-tightness of cladding tubes is still ensured that after regime of elastic deformation of the stress beyond material.(2)
The introducing of buffer layer not only effectively prevents metal layer and the interfacial reaction of ceramic matric composite at high temperature, but also effectively slow
The thermal expansion coefficient solved between two kinds of materials mismatches.
Detailed description of the invention
Fig. 1 is the process flow chart of the method for the present invention.
Fig. 2 is the multilayered structure schematic diagram of multilayer core fuel tube in the present invention.
Fig. 3 is the photo of prepared multilayer core fuel tube.
Specific embodiment
Now in conjunction with embodiment, attached drawing, the invention will be further described:
Crash-proof fuel kernel cladding tubes mainly include three parts, a refractory metal tube layer and two ceramic matric composites
Tube layer.Inner ceramic based composites tube layer is located at the internal layer of refractory metal tube layer, and outer layer ceramic matric composite tube layer is located at
A kind of sandwich structure is collectively formed in the outer layer of refractory metal tube layer.
Its preparation characteristic is to include the following steps:
(1) tube layer in preparing.
The selection criteria of the composition material of inner tube is identical in terms of irradiation and high temperature compatibility as metal tube layer, and heat chemistry
Compatibility will consider the chemical reaction of inner tube Yu nuclear fuel and fission product.Inner tube layer material selects SiCf/ SiC ceramic matrix composite material,
Interface is the interface pyrolytic carbon (PyC).Inner tube is with a thickness of 0.2-0.5mm.
Step 1: preparing tubulose SiC fiber preform.
Step 2: the interface PyC is deposited on fiber preform prepared by step 1.Obtained SiC fiber preform is hung
In on the mating sample frame of vacuum drying oven, precast body is in isothermal region center in furnace, using CVI technique on above-mentioned SiC fiber
Deposit the interface PyC.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature is 800-900 DEG C, deposition pressure
Power is 2-5kPa, deposits 20-50h, deposits the interface PyC of 100-300nm thickness.
Step 3: SiC matrix is deposited on the precast body that deposited the interface PyC using CVI technique.It is passed through three chloromethanes simultaneously
Base silane (CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.
Holding furnace pressure is 2-5kPa, and SiC matrix, sedimentation time 150-400h are deposited in 900-1000 DEG C of temperature range.
(2) buffer layer is prepared.
To form reaction, diffusing barrier between different tube layer and alleviating the thermodynamics having between different expansion materials
Compatibility need to prepare buffer layer between tube layer.
Step 1: using tube layer outer surface in coreless grinding technology polishing, reducing roughness.
Step 2: using the methods of chemical vapor deposition (CVD) or Metal Organic Chemical Vapor Deposition (MOCVD)
Buffer layer is prepared in outer surface.
(3) metal tube layer is prepared.
Using the preparation of the techniques such as cold rolling, hot rolling, extruding and the matched refractory metal tube layer of interior tube layer size, then using cold
It draws or the process sleeves such as hot-drawn is outside inner tube.
Metal Organic Chemical Vapor Deposition (MOCVD), vacuum plasma spray coating (VPS), magnetic control can also be used
The techniques such as sputtering directly prepare high melting metal layer in interior pipe surface.
Metal layer thickness is controlled at 50-200 μm.
(4) buffer layer is prepared.
To form reaction, diffusing barrier between different tube layer and alleviating the thermodynamics having between different expansion materials
Compatibility need to prepare buffer layer between tube layer.
Step 1: using coreless grinding technology polishing metal tube layer outer surface, reducing roughness.
Step 2: using the methods of chemical vapor deposition (CVD) or Metal Organic Chemical Vapor Deposition (MOCVD)
Buffer layer is prepared in metal layer outer surface.
(5) external tube layer is prepared
The selection criteria of the composition material of outer tube is identical in terms of irradiation and high temperature compatibility as metal tube layer, and heat chemistry
Compatibility will consider the chemical reaction of outer tube and coolant and its impurity.External tube layer material selection SiCf/ SiC ceramic matrix composite material, boundary
Face is the interface PyC.Outer tube is with a thickness of 0.3-1mm.
Step 1: using basketry, one layer of SiC fiber preform is worked out outside metal tube layer.
Step 2: the interface PyC is deposited on fiber preform prepared by step 1.Obtained SiC fiber preform is hung
In on the mating sample frame of vacuum drying oven, precast body is in isothermal region center in furnace, using CVI technique on above-mentioned SiC fiber
Deposit the interface PyC.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature is 800-900 DEG C, deposition pressure
Power is 2-5kPa, deposits 20-50h, deposits the interface PyC of 100-300nm thickness.
Step 3: SiC matrix is deposited on the precast body that deposited the interface PyC using CVI technique.It is passed through three chloromethanes simultaneously
Base silane (CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.
Holding furnace pressure is 2-5kPa, and SiC matrix, sedimentation time 150-400h are deposited in 900-1000 DEG C of temperature range.
Specific embodiment
Embodiment 1
(1) 400 μm of SiC fiber preforms of thickness are woven outside diameter 9mm hollow plumbago pipe.Then by obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 800
DEG C, deposition pressure 2kPa deposits 20h, deposits the interface PyC of 100nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 400h are deposited in 1000 DEG C of temperature ranges.
(2) using tube layer outer surface in coreless grinding technology polishing, roughness is to 1 μm.Including magnetron sputtering technique
Tube outer surface prepares aluminium oxide (Al2O3) coating 100nm.
(3) by 100 μm of cold rolling niobium (Nb) pipe sleeves outside pipe.
(4) using coreless grinding technology polishing Nb tube outer surface, roughness is to 1 μm.It is managed using magnetron sputtering technique in Nb
Outer surface prepares aluminium oxide (Al2O3) coating 100nm.
(5) basketry is used, 500 μm of SiC fiber preforms of thickness are worked out outside metal tube layer.By obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 800
DEG C, deposition pressure 2kPa deposits 20h, deposits the interface PyC of 100nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 400h are deposited in 1000 DEG C of temperature ranges.Hollow plumbago pipe is sloughed, is completed
Multilayer cladding control is standby.
Embodiment 2
(1) 300 μm of SiC fiber preforms of thickness are woven outside diameter 9mm hollow plumbago pipe.Then by obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 900
DEG C, deposition pressure 2kPa deposits 30h, deposits the interface PyC of 200nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 300h are deposited in 900 DEG C of temperature ranges.
(2) using tube layer outer surface in coreless grinding technology polishing, roughness is to 1 μm.Using chemical vapor deposition process
Pyrolytic carbon (PyC) coating 100nm is prepared in inner tube outer surface.
(3) 200 μm of niobium (Nb) metal layers are prepared outside pipe using magnetron sputtering technique.
(4) using coreless grinding technology polishing Nb tube outer surface, roughness is to 1 μm.Including chemical vapor deposition process
Tube outer surface prepares pyrolytic carbon (PyC) coating 100nm.
(5) basketry is used, 500 μm of SiC fiber preforms of thickness are worked out outside metal tube layer.By obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 900
DEG C, deposition pressure 2kPa deposits 30h, deposits the interface PyC of 200nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 300h are deposited in 900 DEG C of temperature ranges.Hollow plumbago pipe is sloughed, is completed
Multilayer cladding control is standby.
Embodiment 3
(1) 300 μm of SiC fiber preforms of thickness are woven outside diameter 9mm hollow plumbago pipe.Then by obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 800
DEG C, deposition pressure 2kPa deposits 20h, deposits the interface PyC of 100nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 400h are deposited in 1000 DEG C of temperature ranges.
(2) using tube layer outer surface in coreless grinding technology polishing, roughness is to 1 μm.Using MOCVD technique outside inner tube
Surface prepares aluminium oxide (Al2O3) coating 100nm.
(3) 200 μm of tantalum (Ta) metal layers are prepared outside pipe using MOCVD technique.
(4) using coreless grinding technology polishing Ta tube outer surface, roughness is to 1 μm.Using MOCVD technique in Ta metal tube
Outer surface prepares aluminium oxide (Al2O3) coating 100nm.
(5) basketry is used, 600 μm of SiC fiber preforms of thickness are worked out outside metal tube layer.By obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 800
DEG C, deposition pressure 2kPa deposits 20h, deposits the interface PyC of 100nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 400h are deposited in 1000 DEG C of temperature ranges.Hollow plumbago pipe is sloughed, is completed
Multilayer cladding control is standby.
Embodiment 4
(1) 200 μm of SiC fiber preforms of thickness are woven outside diameter 9mm hollow plumbago pipe.Then by obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 900
DEG C, deposition pressure 2kPa deposits 20h, deposits the interface PyC of 100nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 400h are deposited in 1000 DEG C of temperature ranges.
(2) using tube layer outer surface in coreless grinding technology polishing, roughness is to 1 μm.Using CVD technique in inner tube appearance
Wheat flour is for PyC coating 100nm.
(3) 200 μm of tungsten (W) metal layers are prepared outside pipe using vacuum ionic spraying (VPS) technique.
(4) using coreless grinding technology polishing tungsten tube outer surface, roughness is to 1 μm.Using CVD technique in inner tube outer surface
Prepare PyC coating 100nm.
(5) basketry is used, 500 μm of SiC fiber preforms of thickness are worked out outside metal tube layer.By obtained SiC fibre
Dimension precast body is hung on the mating sample frame of vacuum drying oven, and precast body is in isothermal region center in furnace, using CVI technique upper
State the deposition interface PyC on SiC fiber.The technological parameter of deposition: precursor gas source uses propylene (C3H6), depositing temperature 900
DEG C, deposition pressure 2kPa deposits 20h, deposits the interface PyC of 100nm thickness.It is last to be passed through trichloromethyl silane simultaneously
(CH3SiCl3, MTS), hydrogen (H2) and diluent gas argon gas (Ar), wherein H2Mole mixture ratio with MTS is 10:1.Keep furnace
Interior pressure is 2kPa, and SiC matrix, sedimentation time 400h are deposited in 1000 DEG C of temperature ranges.Hollow plumbago pipe is sloughed, is completed
Multilayer cladding control is standby.
Claims (9)
1. a kind of crash-proof fuel kernel cladding tubes, it is characterised in that including two layers of SiC/SiC composite layer and high melting metal layer,
Interior tube layer and external tube layer are SiC/SiC composite layer, and interlayer is that high melting metal layer constitutes sandwich multilayered structure between two layers；
The interface of the SiC/SiC composite layer is the interface pyrolytic carbon PyC；The refractory metal layer material are as follows: Nb, Ta, W, Mo, Zr
And its any one in alloy；Said inner tube thickness degree 0.2-0.5mm；Described 50-200 μm of high melting metal layer thickness；It is described
External tube layer 0.3-1mm.
2. crash-proof fuel kernel cladding tubes according to claim 1, it is characterised in that: be equipped with Al between two layers2O3Buffer layer or
PyC buffer layer.
3. crash-proof fuel kernel cladding tubes according to claim 2, it is characterised in that: the buffer layer is aluminium oxide Al2O3Or
Pyrolytic carbon PyC.
4. a kind of method for preparing any one crash-proof fuel kernel cladding tubes described in claims 1 to 3, it is characterised in that step is such as
Under:
Step 1: preparing SiC fiber preform on hollow plumbago pipe, then made on SiC fiber preform using CVI technique
The standby interface pyrolytic carbon PyC, then using CVI to progress SiC matrix densification；The SiC/SiC composite material inner tube thickness degree
0.2-0.5mm；
Step 2: in SiC/SiC composite material in tube layer, using Metal Organic Chemical Vapor Deposition MOCVD, vacuum
Plasma spraying VPS or magnetron sputtering technique directly prepare high melting metal layer on interior tube layer surface；The high melting metal layer thickness
It is 50-200 μm；
Step 3: using basketry, one layer of SiC fiber preform is worked out outside high melting metal layer, then uses CVI work
Skill prepares the interface pyrolytic carbon PyC on SiC fiber preform, then using CVI to progress SiC matrix densification；The SiC/SiC
Composite material external tube layer 0.3-1mm；
Step 4: sloughing hollow plumbago pipe, complete the preparation of multilayer crash-proof fuel kernel cladding tubes.
5. according to the method described in claim 4, it is characterized by: the Al prepared between two layers2O3The method of buffer layer
For material is put on the surface of high melting metal layer prepared by SiC/SiC composite material outer surface or step 2 prepared by polishing step 1
It is placed in magnetron sputtering stove, Al is prepared using magnetron sputtering2O3Buffer layer, technological parameter are as follows: target uses single Al2O3Target,
Sputter temperature is 300-600 DEG C, sputtering power 80-110W, and air pressure is 0.1-0.55Pa in furnace, sputters 2-5h, prepares 50-
The Al of 100nm2O3Buffer layer.
6. according to the method described in claim 4, it is characterized by: the method for PyC buffer layer between two layers of the preparation is,
The surface of high melting metal layer prepared by SiC/SiC composite material outer surface or step 2 prepared by step 1 of polishing, material is hung
In cvd furnace, using CVD process deposits PyC buffer layer, the technological parameter of deposition: precursor gas source uses propylene C3H6, deposition
Temperature is 800-900 DEG C, deposition pressure 2-5kPa, deposits 10-20h, deposits the PyC buffer layer of 50-100nm thickness.
7. method according to claim 4, it is characterised in that: the use CVI technique of the step 1 and step 3 is in SiC fiber
The technique at the interface pyrolytic carbon PyC is prepared on precast body are as follows: obtained SiC fiber preform is hung on into the mating sample frame of vacuum drying oven
On, precast body is in isothermal region center in furnace, and the interface PyC is deposited on above-mentioned SiC fiber using CVI technique.Deposition
Technological parameter: precursor gas source uses propylene C3H6, depositing temperature is 800-900 DEG C, deposition pressure 2-5kPa, deposits 20-
50h deposits the interface PyC of 100-300nm thickness.
8. according to the method described in claim 4, it is characterized by: the step 1 and step 3 are using CVI to progress SiC matrix
The technique of densification are as follows: the precast body that deposited the interface PyC is hung in cvd furnace, is passed through trichloromethyl silane CH3SiCl3,
MTS, hydrogen H2With diluent gas argon Ar, wherein H2Mole mixture ratio with MTS is 10:1；Holding furnace pressure is 2-5kPa,
SiC matrix, sedimentation time 150-400h are deposited in 900-1000 DEG C of temperature range.
9. method according to claim 4, it is characterised in that: the step 2 prepares high melting metal layer in interior tube layer and adopts
With technique: using cold rolling, hot rolling or extrusion process preparation and the matched refractory metal tube layer of interior tube layer size, then using cold drawing
Or hot-drawn process sleeve is outside interior tube layer.
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|---|---|---|---|---|
| CN111250712A (en) * | 2020-01-20 | 2020-06-09 | 西北工业大学 | Hollow shaft made of SiC fiber reinforced titanium-based composite material and preparation method |
| CN111326265A (en) * | 2020-02-28 | 2020-06-23 | 中国工程物理研究院材料研究所 | Uranium dioxide-carbide composite fuel pellet and preparation method thereof |
| CN111584100A (en) * | 2020-04-23 | 2020-08-25 | 清华大学 | Coated fuel particle containing carbide-refractory metal coating and preparation method thereof |
| CN113481479A (en) * | 2021-07-02 | 2021-10-08 | 吉林大学 | SiC fiber reinforced refractory alloy composite material and preparation method and application thereof |
| CN113571209A (en) * | 2021-08-02 | 2021-10-29 | 西北工业大学 | Multilayer cladding tube and preparation method thereof |
| CN114121307A (en) * | 2021-11-23 | 2022-03-01 | 中国核动力研究设计院 | Composite cladding tube with internal buffer layer and fuel rod formed by composite cladding tube |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103732388A (en) * | 2011-08-01 | 2014-04-16 | 原子能和替代能源委员会 | Improved multilayer tube made from ceramic-matrix composite material, the resulting nuclear fuel cladding and associated production methods |
| CN103818056A (en) * | 2013-12-27 | 2014-05-28 | 西北工业大学 | Multilayer structure of SiC/SiC (silicon carbide) composite cladding tube and preparation method thereof |
-
2018
- 2018-07-30 CN CN201810851217.1A patent/CN109020589A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103732388A (en) * | 2011-08-01 | 2014-04-16 | 原子能和替代能源委员会 | Improved multilayer tube made from ceramic-matrix composite material, the resulting nuclear fuel cladding and associated production methods |
| CN103818056A (en) * | 2013-12-27 | 2014-05-28 | 西北工业大学 | Multilayer structure of SiC/SiC (silicon carbide) composite cladding tube and preparation method thereof |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN111326265A (en) * | 2020-02-28 | 2020-06-23 | 中国工程物理研究院材料研究所 | Uranium dioxide-carbide composite fuel pellet and preparation method thereof |
| CN111326265B (en) * | 2020-02-28 | 2023-05-02 | 中国工程物理研究院材料研究所 | Uranium dioxide-carbide composite fuel pellet and preparation method thereof |
| CN111584100A (en) * | 2020-04-23 | 2020-08-25 | 清华大学 | Coated fuel particle containing carbide-refractory metal coating and preparation method thereof |
| CN111584100B (en) * | 2020-04-23 | 2022-01-28 | 清华大学 | Coated fuel particle containing carbide-refractory metal coating and preparation method thereof |
| CN113481479A (en) * | 2021-07-02 | 2021-10-08 | 吉林大学 | SiC fiber reinforced refractory alloy composite material and preparation method and application thereof |
| CN113481479B (en) * | 2021-07-02 | 2022-08-05 | 吉林大学 | SiC fiber reinforced refractory alloy composite material and preparation method and application thereof |
| CN113571209A (en) * | 2021-08-02 | 2021-10-29 | 西北工业大学 | Multilayer cladding tube and preparation method thereof |
| CN113571209B (en) * | 2021-08-02 | 2023-10-24 | 西北工业大学 | Multilayer cladding tube and preparation method thereof |
| CN114121307A (en) * | 2021-11-23 | 2022-03-01 | 中国核动力研究设计院 | Composite cladding tube with internal buffer layer and fuel rod formed by composite cladding tube |
| CN115650751A (en) * | 2022-10-13 | 2023-01-31 | 广东核电合营有限公司 | Fiber toughened silicon carbide cladding and preparation method thereof |
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