CN105712746A - Method of preparing Si-Mo-Cr coating with excellent heat shock resistance on surface of C/C composite material - Google Patents
Method of preparing Si-Mo-Cr coating with excellent heat shock resistance on surface of C/C composite material Download PDFInfo
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- CN105712746A CN105712746A CN201610031502.XA CN201610031502A CN105712746A CN 105712746 A CN105712746 A CN 105712746A CN 201610031502 A CN201610031502 A CN 201610031502A CN 105712746 A CN105712746 A CN 105712746A
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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
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/52—Multiple coating or impregnating multiple coating or impregnating with the same composition or with compositions only differing in the concentration of the constituents, is classified as single coating or impregnation
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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
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
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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
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/89—Coating or impregnation for obtaining at least two superposed coatings having different compositions
Abstract
The invention relates to a method of preparing Si-Mo-Cr coating with excellent heat shock resistance on the surface of a C/C composite material. The method includes: ablating the C/C composite material; preparing SiC nanowires; preparing the Si-Mo-Cr ceramic coating on the C/C composite material through an embedding method. The method particularly includes: cleaning and drying the C/C composite material for standby use; adjusting flow of oxygen and acetylene, fully mixing and lighting, and ablating the C/C composite material to quickly and efficiently obtain the C/C composite material comprising a porous surface layer; adopting a chemical gas-phase deposition method to prepare the SiC nanowires; adopting the embedding method to prepare the Si-Mo-Cr ceramic coating on the surface of the C/C composite material. The method has the advantages that compared with a Si-Mo-Cr ceramic coating sample prepared without through treatment and provided with a planar interface, binding strength between the coating and a matrix is improved by 40-70%; after going through 20 times of heat shock in oxyacetylene ablation environment from 160 DEG C to room temperature, weight loss ratio of the sample is lowered by 50-70%.
Description
Technical field
The method that the invention belongs to prepare coating at C/C composite material surface, is specifically related to a kind of C/C composite table
The method of the superior Si-Mo-Cr coating of thermal shock resistance is prepared in face.
Background technology
Carbon/carbon (C/C) composite is as reinforcing material with carbon (or graphite) fiber and fabric thereof, with carbon (or stone
Ink) it is matrix, the full carbonaceous composite made by processed and carbonization treatment.Due to C/C composite
Being made up of with enhanced carbon fiber carbon base body, carbon the most easily aoxidizes, and causes various performance to be decreased obviously.At table
The military service stability that ORC can be effectively improved under C/C composite high temperature is prepared in face.Silicon based ceramic coating,
Such as Si-Mo-Cr coating, at high temperature can react with oxygen that generation has self-healing capability, oxygen permeability is relatively low, uniformly connect
Continuous fine and close SiO2Glassy state protective film, can realize the isolation of C/C matrix and oxygen.Although having with C/C composite
Have the good chemical compatibility, when by from the thermal shock of room temperature to high temperature time, between Si-Mo-Cr coating and C/C matrix because of
The thermal stress that thermal expansion mismatch produces can cause coating cracking to peel off.
At present, add SiC nanowire and carry out activeness and quietness silicon based ceramic coating, can effectively suppress the cracking trend of coating,
Improve the oxidation resistance of coating.Document one " Chu Y, Li H, Li L, et al.Oxidation protection of C/C
composites by ultra-long SiC nanowire-reinforced SiC–Si coating[J].Corrosion Science,
2014,84 (3): 204-208. " in SiC Si coating, introduce SiC nanowire, effectively inhibit the extension of crackle in coating,
After 1500 DEG C of oxidation 160h, the weight-loss ratio of sample is only 0.44%.The studies above introduces SiC nanowire in the coating,
But coating is effectively improved not yet with the interface fine structure of C/C matrix, the flaky problem of coating still exists.
For coating and basal body interface bonding state, document two " Shan Y, Fu Q, Wen S, et al.Improvement in
thermal fatigue behavior of Si–Mo–Cr coated C/C composites through modification of the
C/C-coating interface [J] .Surface and Coatings Technology, 2014,258:114-120. " use pre-oxygen
The way changed is in C/C composite (density 1.75g/cm3) surface structure porous layer, then use embedding method of impregnation to exist
C/C matrix and Mo Si Cr painting interlayer construct and inlay interfacial structure so that coating C/C composite is standing 15
Secondary after the thermal cycle of 1773K to room temperature strength retention reached 82.97%.This research uses the way head of pre-oxidation
First construct coarse and porous surface structure, react more difficult control.And oxidization time is longer, can be to a certain degree
The mechanical property of upper damage C/C composite.
Summary of the invention
Solve the technical problem that
In place of the deficiencies in the prior art, the present invention proposes a kind of C/C composite material surface and prepares thermal shock resistance
The method of Si-Mo-Cr coating that can be superior, improves Si-Mo-Cr coating thermal shock resistance in high/low temperature alternation environment
Can, it is that a kind of structure C/C-Si-Mo-Cr inlays boundary layer and introducing SiC nanowire combines and improves Si-Mo-Cr
The method of thermal shock performance of coatings.
Technical scheme
A kind of C/C composite material surface prepares the method for the superior Si-Mo-Cr coating of thermal shock resistance, it is characterised in that
Step is as follows:
Step 1, pretreatment C/C composite: C/C composite heat gradient chemical gaseous phase permeation method made surpasses
Sound cleans post-drying；
Step 2, C/C composite material surface construct porous layer: oxy-acetylene rifle is pretreated with 90 ° of angular alignments
C/C composite carries out ablation, and ablation uses ultrasonic cleaning after terminating, and dries；
Described oxy-acetylene rifle is 8～12mm with the distance of C/C composite, and the ablation time is 25～50s；
Step 3, prepare SiC nanowire porous layer at C/C composite material surface:
Weighing the Si powder that mass percent is 10～20%, mass percent is 15～the C powder of 30% and percent mass
Than the SiO being 55～75%2Powder, puts into mixed powder bottom graphite crucible after ball-milling treatment；Again prepared by step 2
The C/C composite containing porous surface layer with charcoal rope binding rear-mounted powder in crucible above；By graphite earthenware
Crucible is put in the vacuum response stove of graphite heater, and after vacuum drying oven is carried out application of vacuum, logical argon is to normal pressure, then
With 5～10 DEG C/min programming rate, furnace temperature is risen to 1500～1700 DEG C from room temperature, be incubated 1～3 hour；Close subsequently
Close power supply and naturally cool to room temperature, omnidistance argon shield；
Step 4, embedding method of impregnation prepare Si-Mo-Cr coating；Weighing mass percent respectively is 45 60%Si powder,
Mass percent is 25 30%MoSi2Powder, mass percent is 5 15%Cr powder and mass percent is 8 15%C
Powder, is placed in powder in monkey after ball milling mixed processing, then C/C composite embedment powder step 3 obtained
In, one is placed in embedding in stove, be passed through the argon heating rate with 4～8 DEG C/min embedding stove is warmed up to 1900～
2300 DEG C, it is incubated 1～4h, obtains, at C/C composite material surface, the Si-Mo-Cr ceramic coating that thermal shock resistance is superior.
The density of described C/C composite is 1.65～1.75g/cm3。
The drying temperature of described step 1 is 70～90 DEG C.
Described oxy-acetylene muzzle internal diameter is 2～4mm, and oxygen flow is 0.88～1.51m3/ h, acetylene flow be 0.65～
1.12m3/h。
The drying temperature of described step 2 is 70～90 DEG C.
It is 2～4 hours that described step 3 and step 4 prepare the ball milling mixed processing time of powder.
Described step 1 and step 2 ultrasonic cleaning use distilled water.
Beneficial effect
A kind of C/C composite material surface that the present invention proposes prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, by preparing at C/C composite C/C composite ablation processes-preparation SiC nanowire-investment
Si-Mo-Cr ceramic coating.Detailed process is: C/C composite is cleaned post-drying standby；Regulation oxygen and acetylene
Flow, is sufficiently mixed after lighting and C/C composite carries out ablation processes, obtains containing porous surface layer quickly and efficiently
C/C composite；Chemical vapour deposition technique prepares SiC nanowire；Use investment at C/C composite material surface
Preparation Si-Mo-Cr ceramic coating.
Beneficial effects of the present invention: use and build porous layer at C/C composite material surface under oxyacetylene torch, then exist
SiC nanowire is prepared on porous layer surface, then uses investment to prepare Si-Mo-Cr coating.The present invention will build
C/C-Si-Mo-Cr inlays boundary layer and introducing SiC nanowire combines, and improves while toughness reinforcing Si-Mo-Cr coating
Interface fine structure between Si-Mo-Cr coating and C/C composite, effectively alleviates the thermal expansion between coating and matrix
Coefficient does not mates, and then improves the thermal shock resistance of Si-Mo-Cr coating.With unprocessed preparation there is straight interface
Si-Mo-Cr ceramic coating sample compare, the bond strength between coating and matrix improves 40%～70%.Work as experience
After thermal shock under the oxyacetylene ablation environment of 20 1600 to room temperatures, sample weight-loss ratio reduces 50～70%.
Accompanying drawing explanation
Fig. 1 is present invention process flow chart
Fig. 2 is the C/C composite micrograph through ablation processes rear surface
Fig. 3 is the micrograph of Si-Mo-Cr nano wire porous layer prepared by the present invention
Fig. 4 is the cross-section photograph of Si-Mo-Cr coating prepared by the present invention
Detailed description of the invention
In conjunction with embodiment, accompanying drawing, the invention will be further described:
The detailed process of the present invention is:
Step 1, pretreatment C/C composite sample；Choose the C/C composite wood that heat gradient chemical gaseous phase permeation method is made
Material, density is 1.65～1.75g/cm3, it is processed into a size ofPolish after cylinder, with steaming
Distilled water ultrasonic cleaning, after to put into drying in oven standby, drying temperature is 70～90 DEG C；
Step 2, constructs porous layer at C/C composite material surface；Detailed process is:
1) oxygen and the gas flow of acetylene in regulation oxyacetylene torch；Oxy-acetylene muzzle internal diameter is 2～4mm, oxygen
Flow is 0.88～1.51m3/ h, acetylene flow is 0.65～1.12m3/h.Light after oxygen and acetylene are sufficiently mixed；
2) ablation processes structured surface porous layer；The C/C sample processed is positioned over sample bench, by oxy-acetylene rifle with
90 ° of angular alignment C/C samples carry out ablation, and oxy-acetylene rifle is 8～12mm with the distance of sample, the ablation time be 25～
50s.After ablation terminates, sample is used distilled water ultrasonic cleaning.Being finally putting into drying in oven standby, drying temperature is
70～90 DEG C；
Step 3, prepares SiC nanowire porous layer at C/C composite material surface；Weighing mass percent is 10～20%
Si powder, mass percent is the C powder of 15～30%, and mass percent is the SiO of 55～75%2Powder, is placed in ball
In grinding jar, ball-milling treatment 2～after 4 hours, powder is sufficiently mixed；The mixed powder of preparation is put into bottom graphite crucible.
Again by step 2) the C/C composite charcoal rope containing porous surface layer prepared binding rear-mounted powder in crucible
Above material；Graphite crucible is put in the vacuum response stove of graphite heater, after vacuum drying oven is carried out application of vacuum, logical
Argon to normal pressure, after with 5～10 DEG C/min programming rate, furnace temperature is risen to 1500～1700 DEG C from room temperature, be incubated 1～3
Hour；It is then turned off power supply and naturally cools to room temperature, omnidistance argon shield；
Step 4, embedding method of impregnation prepares Si-Mo-Cr coating；Weighing mass percent respectively is 45 60%Si powder,
Mass percent is 25 30%MoSi2Powder, mass percent is 5 15%Cr powder and mass percent is 8 15%C
Powder, is placed in Colophonium ball grinder, ball milling mixed processing 2～4 hours one-tenth mixed powders；Ceramic powder is placed in monkey
In, then by step 3) in the C/C sample that obtains embedment powder, one is placed in embedding in stove, is passed through argon with 4～8 DEG C
Embedding stove is warmed up to 1900～2300 DEG C by the heating rate of/min, is incubated 1～4h, obtains at C/C composite material surface
To Si-Mo-Cr ceramic coating.
Embodiment one
The present embodiment is a kind of method improving C/C composite material surface Si-Mo-Cr thermal shock performance of coatings.
Step 1, is 1.7g/cm by density3C/C composite sample with after distilled water ultrasonic cleaning 25min, put into baking
Case is in 80 DEG C of dry for standby.
Step 2, ablation processes structured surface porous layer；C/C sample is positioned over sample bench, regulation oxygen and acetylene stream
Amount is 0.88m3/ h and 0.65m3/ h, lights after being sufficiently mixed.Oxy-acetylene rifle is carried out ablation with 90 ° of angular alignment C/C samples,
Oxy-acetylene rifle is 10mm with the distance of sample, and the ablation time is 45s.After ablation terminates, by ultrasonic for sample distilled water
Clean.Being finally putting into drying in oven standby, drying temperature is 80 DEG C, thus prepares the C/C containing porous surface layer
Composite.
Step 3, prepares SiC nanowire porous layer at C/C composite material surface；Weighing mass percent respectively is 15%
Si powder, mass percent is the C powder of 20%, and mass percent is the SiO of 65%2Powder, is placed in ball grinder,
Ball milling mixed processing becomes mixed powder in 2 hours；The mixed powder of preparation is put in graphite crucible.Again by step 2)
The C/C composite containing porous surface layer of preparation charcoal rope bundlees above rear-mounted powder in crucible；By stone
Ink crucible is put in the vacuum response stove of graphite heater, after vacuum drying oven is carried out application of vacuum, logical argon to normal pressure,
After with 5 DEG C/min programming rate, furnace temperature is risen to 1600 DEG C from room temperature, be incubated 2 hours；It is then turned off power supply the coldest
But to room temperature, omnidistance argon shield；
Step 4, embedding method of impregnation prepares Si-Mo-Cr coating；Weighing mass percent respectively is 45%Si powder, matter
Amount percentage ratio is 30%MoSi2Powder, mass percent is 15%Cr powder and mass percent is 10%C powder, is placed in
In Colophonium ball grinder, ball milling mixed processing becomes mixed powder in 2 hours；Ceramic powder is placed in monkey, then will step
Rapid 3), in the C/C sample embedment powder obtained, one is placed in embedding in stove, is passed through the argon intensification with 5 DEG C/min
Embedding stove is warmed up to 2100 DEG C by speed, is incubated 2h, obtains Si-Mo-Cr ceramic coating at C/C composite material surface；
The Si-Mo-Cr coating C/C composite that the present embodiment obtains is compared with the undressed Si-Mo-Cr under same process
Bond strength between coating C/C composite coating and matrix improves 40%.
Embodiment two
Step 1, is 1.7g/cm by density3C/C composite with after distilled water ultrasonic cleaning 20min, put into baking oven in
80 DEG C of dry for standby.
Step 2, ablation processes structured surface porous layer；C/C sample is positioned over sample bench, regulation oxygen and acetylene stream
Amount is 1.12m3/ h and 0.83m3/ h, lights after being sufficiently mixed.Oxy-acetylene rifle is carried out ablation with 90 ° of angular alignment C/C samples,
Oxy-acetylene rifle is 10mm with the distance of sample, and the ablation time is 30s.After ablation terminates, by ultrasonic for sample distilled water
Clean.Being finally putting into drying in oven standby, drying temperature is 90 DEG C, thus prepares the C/C containing porous surface layer
Composite.
Step 3, prepares SiC nanowire porous layer at C/C composite material surface；Weighing mass percent respectively is 15%
Si powder, mass percent is the C powder of 20%, and mass percent is the SiO of 65%2Powder, is placed in Colophonium ball grinder
In, ball milling mixed processing becomes mixed powder in 2 hours；The mixed powder of preparation is put in graphite crucible.Again by step
2) above the binding rear-mounted powder in crucible of the C/C composite charcoal rope containing porous surface layer prepared；
Being put into by graphite crucible in the vacuum response stove that graphite is heater, after vacuum drying oven is carried out application of vacuum, logical argon is extremely
Normal pressure, after with 4 DEG C/min programming rate, furnace temperature is risen to 1600 DEG C from room temperature, be incubated 1.5 hours；It is then turned off electricity
Source naturally cools to room temperature, omnidistance argon shield；
Step 4, embedding method of impregnation prepares Si-Mo-Cr coating；Weighing mass percent is 50%Si powder, quality hundred
Proportion by subtraction is 30%MoSi2Powder, mass percent is 15%Cr powder and mass percent is 5%C powder, is placed in Colophonium
In ball grinder, ball milling mixed processing becomes mixed powder in 2 hours；Ceramic powder is placed in monkey, then by step 3)
In the C/C sample embedment powder obtained, one is placed in embedding in stove, is passed through argon and incites somebody to action with the heating rate of 5 DEG C/min
Embedding stove is warmed up to 2300 DEG C, is incubated 2h, obtains Si-Mo-Cr ceramic coating at C/C composite material surface；
When experience oxyacetylene torch lower 20 times 1600 DEG C to after the thermal cycle of room temperature, the present embodiment obtains Si-Mo-Cr and is coated with
Layer C/C composite reduces compared with the weight-loss ratio of the unprocessed Si-Mo-Cr coating C/C composite under same process
50%.
Embodiment three
Step 1, is 1.65g/cm by density3C/C composite with after distilled water ultrasonic cleaning 20min, put into baking oven
In 80 DEG C of dry for standby.
Step 2, ablation processes structured surface porous layer；C/C sample is positioned over sample bench, regulation oxygen and acetylene stream
Amount is 1.51m3/ h and 1.12m3/ h, lights after being sufficiently mixed.Oxy-acetylene rifle is carried out ablation with 90 ° of angular alignment C/C samples,
Oxy-acetylene rifle is 10mm with the distance of sample, and the ablation time is 30s.After ablation terminates, by ultrasonic for sample distilled water
Clean.Being finally putting into drying in oven standby, drying temperature is 90 DEG C, thus prepares the C/C containing porous surface layer
Composite.
Step 3, prepares SiC nanowire porous layer at C/C composite material surface；Weighing mass percent respectively is 15%
Si powder, mass percent is the C powder of 20%, and mass percent is the SiO of 65%2Powder, is placed in Colophonium ball grinder
In, ball milling mixed processing becomes mixed powder in 2 hours；The mixed powder of preparation is put in graphite crucible.Again by step
2) above the binding rear-mounted powder in crucible of the C/C composite charcoal rope containing porous surface layer prepared；
Being put into by graphite crucible in the vacuum response stove that graphite is heater, after vacuum drying oven is carried out application of vacuum, logical argon is extremely
Normal pressure, after with 4 DEG C/min programming rate, furnace temperature is risen to 1600 DEG C from room temperature, be incubated 1.5 hours；It is then turned off electricity
Source naturally cools to room temperature, omnidistance argon shield；
Step 4, embedding method of impregnation prepares Si-Mo-Cr coating；Weighing mass percent is 60%Si powder, quality hundred
Proportion by subtraction is 25%MoSi2Powder, mass percent is 5%Cr powder and mass percent is 10%C powder, is placed in Colophonium
In ball grinder, ball milling mixed processing becomes mixed powder in 2 hours；Ceramic powder is placed in monkey, then by step 3)
In the C/C sample embedment powder obtained, one is placed in embedding in stove, is passed through argon and incites somebody to action with the heating rate of 5 DEG C/min
Embedding stove is warmed up to 2300 DEG C, is incubated 2h, obtains Si-Mo-Cr ceramic coating at C/C composite material surface；
When experience oxyacetylene torch lower 20 times 1600 DEG C to after the thermal cycle of room temperature, the present embodiment obtains Si-Mo-Cr
Coating C/C composite drops compared with the weight-loss ratio of the unprocessed Si-Mo-Cr coating C/C composite under same process
Low by 60%.
Claims (7)
1. the method that a C/C composite material surface prepares the superior Si-Mo-Cr coating of thermal shock resistance, it is characterised in that
Step is as follows:
Step 1, pretreatment C/C composite: C/C composite heat gradient chemical gaseous phase permeation method made surpasses
Sound cleans post-drying；
Step 2, C/C composite material surface construct porous layer: oxy-acetylene rifle is pretreated with 90 ° of angular alignments
C/C composite carries out ablation, and ablation uses ultrasonic cleaning after terminating, and dries；
Described oxy-acetylene rifle is 8～12mm with the distance of C/C composite, and the ablation time is 25～50s；
Step 3, prepare SiC nanowire porous layer at C/C composite material surface:
Weighing the Si powder that mass percent is 10～20%, mass percent is 15～the C powder of 30% and percent mass
Than the SiO being 55～75%2Powder, puts into mixed powder bottom graphite crucible after ball-milling treatment；Again prepared by step 2
The C/C composite containing porous surface layer with charcoal rope binding rear-mounted powder in crucible above；By graphite earthenware
Crucible is put in the vacuum response stove of graphite heater, and after vacuum drying oven is carried out application of vacuum, logical argon is to normal pressure, then
With 5～10 DEG C/min programming rate, furnace temperature is risen to 1500～1700 DEG C from room temperature, be incubated 1～3 hour；Close subsequently
Close power supply and naturally cool to room temperature, omnidistance argon shield；
Step 4, embedding method of impregnation prepare Si-Mo-Cr coating；Weighing mass percent respectively is 45 60%Si powder,
Mass percent is 25 30%MoSi2Powder, mass percent is 5 15%Cr powder and mass percent is 8 15%C
Powder, is placed in powder in monkey after ball milling mixed processing, then C/C composite embedment powder step 3 obtained
In, one is placed in embedding in stove, be passed through the argon heating rate with 4～8 DEG C/min embedding stove is warmed up to 1900～
2300 DEG C, it is incubated 1～4h, obtains, at C/C composite material surface, the Si-Mo-Cr ceramic coating that thermal shock resistance is superior.
The most according to claim 1, C/C composite material surface prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, it is characterised in that: the density of described C/C composite is 1.65～1.75g/cm3。
The most according to claim 1, C/C composite material surface prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, it is characterised in that: the drying temperature of described step 1 is 70～90 DEG C.
The most according to claim 1, C/C composite material surface prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, it is characterised in that: described oxy-acetylene muzzle internal diameter is 2～4mm, and oxygen flow is 0.88～1.51m3/ h,
Acetylene flow is 0.65～1.12m3/h。
The most according to claim 1, C/C composite material surface prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, it is characterised in that: the drying temperature of described step 2 is 70～90 DEG C.
The most according to claim 1, C/C composite material surface prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, it is characterised in that: it is 2～4 hours that described step 3 and step 4 prepare the ball milling mixed processing time of powder.
The most according to claim 1, C/C composite material surface prepares the side of the superior Si-Mo-Cr coating of thermal shock resistance
Method, it is characterised in that: described step 1 and step 2 ultrasonic cleaning use distilled water.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109354506A (en) * | 2018-10-22 | 2019-02-19 | 湖南国科碳陶新材料科技有限公司 | A kind of high-temperature oxidation resistant carbon ceramic composite material and preparation method thereof |
| CN113831155A (en) * | 2021-09-29 | 2021-12-24 | 湖北瑞宇空天高新技术有限公司 | Improved high-temperature oxidation-resistant composite coating with adjustable oxygen partial pressure technology and preparation method and application thereof |
| CN114853507A (en) * | 2022-07-06 | 2022-08-05 | 湖南泰坦未来科技有限公司 | Composite carbon material and preparation method and application thereof |
| CN115784776A (en) * | 2022-03-22 | 2023-03-14 | 西北工业大学 | MoSi-rich material uniformly distributed on surface of carbon/carbon composite material in large range 2 -ZrB 2 Oxidation resistant coating and preparation method thereof |
| CN116178040A (en) * | 2023-02-20 | 2023-05-30 | 西安工业大学 | Preparation method of interface-reinforced C/C-Al composite material |
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| YUCAI SHAN等: "Improvement in thermal fatigue behavior of Si-Mo-Cr coated C/C composites through modification of the C/C-coating interface", 《SURFACE & COATINGS TECHNOLOGY》 * |
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| CN116178040A (en) * | 2023-02-20 | 2023-05-30 | 西安工业大学 | Preparation method of interface-reinforced C/C-Al composite material |
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