CN109678549A - The ceramic matric composite pin preparation method uniformly carried - Google Patents
The ceramic matric composite pin preparation method uniformly carried Download PDFInfo
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- CN109678549A CN109678549A CN201910139555.7A CN201910139555A CN109678549A CN 109678549 A CN109678549 A CN 109678549A CN 201910139555 A CN201910139555 A CN 201910139555A CN 109678549 A CN109678549 A CN 109678549A
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- 238000002360 preparation method Methods 0.000 title claims abstract description 32
- 239000002131 composite material Substances 0.000 title claims abstract description 22
- 239000000919 ceramic Substances 0.000 title claims abstract description 14
- HPNSNYBUADCFDR-UHFFFAOYSA-N chromafenozide Chemical compound CC1=CC(C)=CC(C(=O)N(NC(=O)C=2C(=C3CCCOC3=CC=2)C)C(C)(C)C)=C1 HPNSNYBUADCFDR-UHFFFAOYSA-N 0.000 title claims abstract description 11
- 239000000835 fiber Substances 0.000 claims abstract description 83
- 238000000034 method Methods 0.000 claims abstract description 34
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 24
- 230000001054 cortical effect Effects 0.000 claims abstract description 14
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 13
- 239000011248 coating agent Substances 0.000 claims abstract description 8
- 238000000576 coating method Methods 0.000 claims abstract description 8
- 230000008595 infiltration Effects 0.000 claims abstract description 8
- 238000001764 infiltration Methods 0.000 claims abstract description 8
- 239000000126 substance Substances 0.000 claims abstract description 8
- 238000004804 winding Methods 0.000 claims abstract description 6
- 239000007789 gas Substances 0.000 claims description 35
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 20
- 239000000463 material Substances 0.000 claims description 12
- 238000004062 sedimentation Methods 0.000 claims description 12
- 229910002804 graphite Inorganic materials 0.000 claims description 11
- 239000010439 graphite Substances 0.000 claims description 11
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 10
- 229910052786 argon Inorganic materials 0.000 claims description 10
- 239000001257 hydrogen Substances 0.000 claims description 10
- 229910052739 hydrogen Inorganic materials 0.000 claims description 10
- DWAWYEUJUWLESO-UHFFFAOYSA-N trichloromethylsilane Chemical compound [SiH3]C(Cl)(Cl)Cl DWAWYEUJUWLESO-UHFFFAOYSA-N 0.000 claims description 10
- 230000005587 bubbling Effects 0.000 claims description 5
- 238000006243 chemical reaction Methods 0.000 claims description 5
- 239000003085 diluting agent Substances 0.000 claims description 5
- 239000000203 mixture Substances 0.000 claims description 5
- 239000002296 pyrolytic carbon Substances 0.000 claims description 5
- 238000010792 warming Methods 0.000 claims description 5
- 238000000151 deposition Methods 0.000 claims description 2
- 238000000280 densification Methods 0.000 abstract description 7
- 238000000197 pyrolysis Methods 0.000 abstract description 3
- 229910010271 silicon carbide Inorganic materials 0.000 description 12
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 11
- 239000011204 carbon fibre-reinforced silicon carbide Substances 0.000 description 6
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 239000006185 dispersion Substances 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 239000012783 reinforcing fiber Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000005520 cutting process Methods 0.000 description 2
- 239000004744 fabric Substances 0.000 description 2
- 238000003475 lamination Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 206010021703 Indifference Diseases 0.000 description 1
- 229910003978 SiClx Inorganic materials 0.000 description 1
- 239000011184 SiC–SiC matrix composite Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000011153 ceramic matrix composite Substances 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Classifications
-
- C04B35/806—
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B15/00—Nails; Staples
-
- 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/48—Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
-
- 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/30—Constituents and secondary phases not being of a fibrous nature
- C04B2235/48—Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins
- C04B2235/483—Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes
-
- 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
-
- 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
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
-
- 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
- C04B2235/608—Green bodies or pre-forms with well-defined density
-
- 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
- C04B2235/70—Aspects relating to sintered or melt-casted ceramic products
- C04B2235/96—Properties of ceramic products, e.g. mechanical properties such as strength, toughness, wear resistance
Abstract
The invention discloses the ceramic matric composite pin preparation method that uniformly carries of one kind, the technical issues of for solving the composite material pin intensity difference of existing method preparation.Technical solution is pin precast body cortex determining first and core fibers beam quantity, further according to cortex and core fibers beam quantity, adjust cortex and core fibers ingot number, then fiber is imported on the fiber ingot of braider, core fibers spindle position is set constant, Cortical fiber ingot forms skin-core structure pin precast body around core fibers beam cross winding, prepares pyrolysis carbon boundary layer in pin precast body.Densification preparation is carried out to pin precast body using chemical vapor infiltration technique, pin blank is processed, inoxidzable coating is deposited to the pin surface after processing, completes pin preparation.The skin-core structure pin of the method for the present invention preparation, preparation process is simple, and densification degree is high, and room temperature shear strength is increased to 130~230MPa by 80~100MPa of background technique.
Description
Technical field
The present invention relates to a kind of composite material pin preparation method, in particular to a kind of ceramic base composite wood uniformly carried
Expect pin preparation method.
Background technique
Ceramic matric composite is widely used in aerospace field, with the reusable aerospace vehicle of high-performance
Development, large complicated ceramic matrix composite material structure part become the principal mode of the following high-performance application, and ceramic base is compound
The integrated of material components is assembled into critical process.
As construction standard part, ceramic matric composite pin generallys use the preparation of C/SiC or SiC/SiC composite material,
Major function is connection, fixed, support and transmitting load.
Referring to Fig. 6.Document " Chinese invention patent that application publication number is 105835455 A of CN " discloses a kind of two dimension
Carbon/silico-carbo SiClx composite material pin preparation method.Pin precast body disclosed in this method is a kind of two-dimentional (2D) lamination carbon fiber
2D precast body is clamped and is formed using graphite planar by Wei Bu, and CVI technique prepares boundary layer, and RMI technique prepares SiC ceramic base
Body；Blank material is cut into squarely strip when processing, then rounding is finally cut into pin finished product at column.Prepared pin
The room temperature shear strength for following closely material is 80~100MPa.The invention pin precast body is using two-dimentional (2D) lamination precast body, from Fig. 6
As can be seen that the composite material pin of literature method preparation has typical 2D laying fiber cloth structure.Obviously, when pin section
Suffered shearing load direction and the angle of its carbon cloth laying change, and the bearing capacity of the pin will change correspondingly, this
It is the big reason of existing pin strength decentralization in engineer application.Data shows shear-type load direction and pin laying
Pin intensity (S when direction is parallel∥), with pin intensity (S when shear-type load and vertical pin laying direction⊥) difference is very
Greatly, average intensity value deviation is at 1~1.5 times or more.In addition only 50% fiber (pin axial direction fibre) joins in 2D precast body
It is carried with shear-type load, therefore pin intensity need to be improved.
Summary of the invention
In order to overcome the shortcomings of the composite material pin intensity difference of existing method preparation, the present invention provides a kind of uniformly carrying
Ceramic matric composite pin preparation method.This method determines pin precast body cortex and core fibers beam quantity first, then
According to cortex and core fibers beam quantity, cortex and core fibers ingot number are adjusted, then fiber is imported into the fibre of braider
Tie up ingot on, core fibers spindle position set it is constant, Cortical fiber ingot around core fibers beam cross winding formed skin-core structure pin it is pre-
Body processed prepares pyrolysis carbon boundary layer in pin precast body.Pin precast body is densified using chemical vapor infiltration technique
Preparation, processes pin blank, deposits inoxidzable coating to the pin surface after processing, completes pin preparation.The present invention
" skin-core " structure pin of method preparation, manufacturing procedure is few, and processing capacity is small, and process time is short；Preparation process is without complicated auxiliary
Tooling, densification cycle are short, and densification degree is high, and sedimentation time is short；Room temperature shear strength by background technique 80~100MPa
It is increased to 130~230MPa；And there is the design of cutting performance isotropism, the shear strength dispersibility with batch pin is less than
5%.
The technical solution adopted by the present invention to solve the technical problems: the ceramic matric composite pin that one kind uniformly carries
Preparation method, its main feature is that the following steps are included:
Step 1: determining pin diameter, it is therefore an objective to determine cortex and core fibers beam quantity.As pin diameter≤3mm,
Core fibers beam quantity and Cortical fiber beam ratio of number are 10~20；As pin diameter >=3mm, core fibers beam quantity with
Cortical fiber beam ratio of number is 5~10.
Step 2: adjusting cortex and core fibers ingot number according to cortex and core fibers beam quantity, then leading fiber
Enter onto the fiber ingot of braider, core fibers spindle position is set constant, and Cortical fiber ingot is formed around core fibers beam cross winding
Skin-core structure pin precast body.
Step 3: pin precast body is wound on graphite frame, it is placed in cvd furnace, keeps vacuum 10-3Pa is warming up to
700~800 DEG C, CH3Gas is as carbon source, CH3Volumetric flow of gas is 500ml/min, 40~60h of sedimentation time, pyrolytic carbon circle
Surface thickness is 30~100 μm.
It is prepared Step 4: being densified using chemical vapor infiltration technique to pin precast body.Air pressure is maintained in cvd furnace
10-2Pa, for trichloromethyl silane as SiC presoma, hydrogen and argon gas are diluent gas, and the volumetric mixture ratio of hydrogen and argon gas is
Trichloromethyl silane gas is imported reaction zone in cvd furnace by way of bubbling by 10:1, gas flow 1000ml/min, is sunk
800~1000 DEG C of in-furnace temperature of product, 20~40h of sedimentation time.
Step 5: step 4 is repeated, as pin blank material density >=2.0g/cm3After, by pin blank from graphite frame
On remove, be cut into straight section according to length of pin, by pin blank rounding, reach required diameter, complete pin processing.
Step 6: depositing 60~100 μm of SiC inoxidzable coating on pin surface, ceramic matric composite pin is completed
Preparation.
The beneficial effects of the present invention are: this method determines pin precast body cortex and core fibers beam quantity, then root first
According to cortex and core fibers beam quantity, cortex and core fibers ingot number are adjusted, then fiber is imported into the fiber of braider
On ingot, core fibers spindle position set it is constant, Cortical fiber ingot around core fibers beam cross winding formed skin-core structure pin it is prefabricated
Body prepares pyrolysis carbon boundary layer in pin precast body.Densification system is carried out to pin precast body using chemical vapor infiltration technique
It is standby, pin blank is processed, inoxidzable coating is deposited to the pin surface after processing, completes pin preparation.Side of the present invention
" skin-core " structure pin of method preparation, manufacturing procedure is few, and processing capacity is small, and process time is short；Preparation process is not necessarily to complicated backman
Dress, densification cycle are short, and densification degree is high, and sedimentation time is short；Room temperature shear strength is mentioned by 80~100MPa of background technique
Height is to 130~230MPa；And there is the design of cutting performance isotropism, the shear strength dispersibility with batch pin is less than
5%.
It elaborates with reference to the accompanying drawings and detailed description to the present invention.
Detailed description of the invention
Fig. 1 is the flow chart for the ceramic matric composite pin preparation method that the present invention uniformly carries.
Fig. 2 is status diagram before composite material pin prepared by embodiment of the present invention method 1 is processed.
Fig. 3 is composite material pin section microstructural photographs prepared by embodiment of the present invention method 1.
Fig. 4 is that composite material pin prepared by embodiment of the present invention method 1 destroys front and back photo.
Fig. 5 is the composite material pin cross-sectional view of the method for the present invention preparation.
Fig. 6 is the composite material pin cross-sectional view of background technique method preparation.
Specific embodiment
Following embodiment referring to Fig.1-6.
Embodiment 1:
(1) use carbon fiber for reinforcing fiber, according to core fibers beam quantity: Cortical fiber beam quantity=11:1 ratio,
Design preform diameter 3.5mm.According to cortex and core fibers beam quantity, cortex and core fibers ingot number are adjusted, then will
Fiber is imported on the fiber ingot of braider, core fibers spindle position set it is constant, Cortical fiber ingot around core fibers beam intersection twines
Around formation skin-core structure pin precast body.
(2) pin precast body is wound on graphite frame, is fixed in boundary layer cvd furnace, deposited and be pyrolyzed in fiber surface
Carbon boundary layer；Keep vacuum 10-3Pa is warming up to 700 DEG C, CH3Gas is as carbon source, CH3Volumetric flow of gas is 500ml/
Min, sedimentation time 40h, pyrolytic carbon interfacial layer thickness are 30 μm.
(3) pin precast body is densified using chemical vapor infiltration technique and is prepared.Air pressure is maintained at 10 in cvd furnace- 2Pa, for trichloromethyl silane as SiC presoma, hydrogen and argon gas are diluent gas, and the volumetric mixture ratio of hydrogen and argon gas is
Trichloromethyl silane gas is imported reaction zone in cvd furnace by way of bubbling by 10:1, gas flow 1000ml/min, is sunk
800 DEG C of in-furnace temperature of product, sedimentation time 20h.
(4) step (3) are repeated, as pin blank material density >=2.0g/cm3After, by pin blank from graphite frame
It removes, pin blank is divided into section, every section of 20cm.
(5) blank pin refines, diameter to 3mm, circularity 0.05.
(6) the SiC inoxidzable coating that 60 μm are deposited on pin surface completes the preparation of Φ 3mm-C/SiC pin.
It is 130MPa that this example, which obtains Φ 3mm-C/SiC pin shear strength, and the intensity coefficient of dispersion is 3%.
It can be observed from fig. 2 that cylindric, the pin easy to process at circular cross-section is presented in blank material of the present invention.
As seen from Figure 3, inventive pin rivet fibers direction is axially parallel with pin, and circumferential shear-type load can be with indifference
Uniformly carrying.
From fig. 4 it can be seen that material body is not layered, removes after the clipped destruction of pin of the present invention, also without obvious
Situations such as bending deformation, occurs.
It is seen from fig 5 that inventive pin rivet fibers precast body is in typical " skin-core " structure, cortex construction has d type function
Can, sandwich layer is main bearing structure.
Embodiment 2:
(1) use carbon fiber for reinforcing fiber, according to core fibers beam quantity: Cortical fiber beam quantity=8:1 ratio, if
Count preform diameter 4.5mm.According to cortex and core fibers beam quantity, cortex and core fibers ingot number are adjusted, it then will be fine
Dimension imported on the fiber ingot of braider, core fibers spindle position set it is constant, Cortical fiber ingot surround core fibers beam cross winding
Form skin-core structure pin precast body.
(2) pin precast body is wound on graphite frame, is fixed in boundary layer cvd furnace, deposited and be pyrolyzed in fiber surface
Carbon boundary layer；Keep vacuum 10-3Pa is warming up to 800 DEG C, CH3Gas is as carbon source, CH3Volumetric flow of gas is 500ml/
Min, sedimentation time 50h, pyrolytic carbon interfacial layer thickness are 70 μm.
(3) pin precast body is densified using chemical vapor infiltration technique and is prepared.Air pressure is maintained at 10 in cvd furnace- 2Pa, for trichloromethyl silane as SiC presoma, hydrogen and argon gas are diluent gas, and the volumetric mixture ratio of hydrogen and argon gas is
Trichloromethyl silane gas is imported reaction zone in cvd furnace by way of bubbling by 10:1, gas flow 1000ml/min, is sunk
1000 DEG C of in-furnace temperature of product, sedimentation time 30h.
(4) step (3) are repeated, as pin blank material density >=2.0g/cm3After, by pin blank from graphite frame
It removes, pin blank is divided into section, every section of 20cm.
(5) blank pin refines, diameter to 4mm, circularity 0.05.
(6) the SiC inoxidzable coating that 80 μm are deposited on pin surface completes the preparation of Φ 4mm-C/SiC pin.
The Φ 4mm-C/SiC pin shear strength that this example obtains is 150MPa, and the intensity coefficient of dispersion is 2.5%.
Embodiment 3:
(1) use silicon carbide fibre for reinforcing fiber, according to core fibers beam quantity: Cortical fiber beam quantity=6:1 ratio
Example designs preform diameter 5.5mm.According to cortex and core fibers beam quantity, cortex and core fibers ingot number are adjusted, then
Fiber is imported on the fiber ingot of braider, core fibers spindle position set it is constant, Cortical fiber ingot around core fibers beam intersect
It is wound skin-core structure pin precast body.
(2) pin precast body is wound on graphite frame, is fixed in boundary layer cvd furnace, deposited and be pyrolyzed in fiber surface
Carbon boundary layer；Keep vacuum 10-3Pa is warming up to 800 DEG C, CH3Gas is as carbon source, CH3Volumetric flow of gas is 500ml/
Min, sedimentation time 60h, pyrolytic carbon interfacial layer thickness are 100 μm.
(3) pin precast body is densified using chemical vapor infiltration technique and is prepared.Air pressure is maintained at 10 in cvd furnace- 2Pa, for trichloromethyl silane as SiC presoma, hydrogen and argon gas are diluent gas, and the volumetric mixture ratio of hydrogen and argon gas is
Trichloromethyl silane gas is imported reaction zone in cvd furnace by way of bubbling by 10:1, gas flow 1000ml/min, is sunk
900 DEG C of in-furnace temperature of product, sedimentation time 40h.
(4) step (3) are repeated, as pin blank material density >=2.0g/cm3After, by pin blank from graphite frame
It removes, pin blank is divided into section, every section of 20cm.
(5) blank pin refines, diameter to 5mm, circularity 0.05.
(6) the SiC inoxidzable coating that 100 μm are deposited on pin surface completes the preparation of Φ 5mm-C/SiC pin.
The Φ 5mm-SiC/SiC pin shear strength that this example obtains is 230MPa, and the intensity coefficient of dispersion is 2.5%.
Claims (1)
1. the ceramic matric composite pin preparation method that one kind uniformly carries, it is characterised in that the following steps are included:
Step 1: determining pin diameter, it is therefore an objective to determine cortex and core fibers beam quantity；As pin diameter≤3mm, sandwich layer
Fibre bundle quantity and Cortical fiber beam ratio of number are 10~20；As pin diameter >=3mm, core fibers beam quantity and cortex
Fibre bundle ratio of number is 5~10；
Step 2: adjusting cortex and core fibers ingot number according to cortex and core fibers beam quantity, then importeding into fiber
On the fiber ingot of braider, core fibers spindle position set it is constant, Cortical fiber ingot around core fibers beam cross winding formed skin-core
Structure pin precast body；
Step 3: pin precast body is wound on graphite frame, it is placed in cvd furnace, keeps vacuum 10-3Pa is warming up to 700
~800 DEG C, CH3Gas is as carbon source, CH3Volumetric flow of gas is 500ml/min, 40~60h of sedimentation time, pyrolytic carbon interface
Layer is with a thickness of 30~100 μm；
It is prepared Step 4: being densified using chemical vapor infiltration technique to pin precast body；Air pressure is maintained at 10 in cvd furnace- 2Pa, for trichloromethyl silane as SiC presoma, hydrogen and argon gas are diluent gas, and the volumetric mixture ratio of hydrogen and argon gas is
Trichloromethyl silane gas is imported reaction zone in cvd furnace by way of bubbling by 10:1, gas flow 1000ml/min, is sunk
800~1000 DEG C of in-furnace temperature of product, 20~40h of sedimentation time；
Step 5: step 4 is repeated, as pin blank material density >=2.0g/cm3After, pin blank is taken from graphite frame
Under, it is cut into straight section according to length of pin, by pin blank rounding, reaches required diameter, completes pin processing；
Step 6: depositing 60~100 μm of SiC inoxidzable coating on pin surface, the preparation of ceramic matric composite pin is completed.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110240489A (en) * | 2019-06-20 | 2019-09-17 | 西北工业大学 | Refractory ceramics based composites torque tube preparation method |
| CN113603495A (en) * | 2021-07-29 | 2021-11-05 | 西北工业大学 | Method for preparing ceramic matrix composite bolt and pin based on long rod-shaped prefabricated body structure |
| CN113666762A (en) * | 2021-07-29 | 2021-11-19 | 西北工业大学 | High-length-diameter-ratio rodlike preform and preparation method thereof |
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| CN105835455A (en) * | 2015-12-15 | 2016-08-10 | 西安鑫垚陶瓷复合材料有限公司 | 2D carbon/silicon-silicon carbide composite material pin preparation method and preparation method and structure of 2D carbon/silicon-silicon carbide composite material pin preform |
| CN106565261A (en) * | 2016-11-01 | 2017-04-19 | 中国航空工业集团公司基础技术研究院 | Method for manufacturing SiC/SiC composite material pin with precursor infiltration and pyrolysis method |
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| CN113666762A (en) * | 2021-07-29 | 2021-11-19 | 西北工业大学 | High-length-diameter-ratio rodlike preform and preparation method thereof |
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