CN112939629A - Multilayer-structure environmental barrier coating for silicon carbide ceramic matrix composite and preparation method thereof - Google Patents
Multilayer-structure environmental barrier coating for silicon carbide ceramic matrix composite and preparation method thereof Download PDFInfo
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- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 title claims abstract description 71
- 229910010271 silicon carbide Inorganic materials 0.000 title claims abstract description 71
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 62
- 239000011248 coating agent Substances 0.000 title claims abstract description 55
- 238000000576 coating method Methods 0.000 title claims abstract description 55
- 230000007613 environmental effect Effects 0.000 title claims abstract description 45
- 230000004888 barrier function Effects 0.000 title claims abstract description 44
- 238000002360 preparation method Methods 0.000 title claims abstract description 19
- 239000000463 material Substances 0.000 claims abstract description 32
- 238000000034 method Methods 0.000 claims abstract description 30
- 229910052681 coesite Inorganic materials 0.000 claims abstract description 23
- 229910052906 cristobalite Inorganic materials 0.000 claims abstract description 23
- 239000000377 silicon dioxide Substances 0.000 claims abstract description 23
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims abstract description 23
- 229910052682 stishovite Inorganic materials 0.000 claims abstract description 23
- 229910052905 tridymite Inorganic materials 0.000 claims abstract description 23
- 238000007750 plasma spraying Methods 0.000 claims abstract description 18
- 239000000919 ceramic Substances 0.000 claims abstract description 9
- 238000005488 sandblasting Methods 0.000 claims abstract description 9
- 239000002131 composite material Substances 0.000 claims abstract description 8
- 238000001035 drying Methods 0.000 claims abstract description 8
- 238000004506 ultrasonic cleaning Methods 0.000 claims abstract description 8
- 238000005498 polishing Methods 0.000 claims abstract description 4
- 238000005507 spraying Methods 0.000 claims description 46
- 239000000843 powder Substances 0.000 claims description 28
- 230000008569 process Effects 0.000 claims description 16
- 239000007921 spray Substances 0.000 claims description 16
- 239000011159 matrix material Substances 0.000 claims description 13
- 239000002245 particle Substances 0.000 claims description 11
- 239000011863 silicon-based powder Substances 0.000 claims description 4
- 230000003746 surface roughness Effects 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 3
- 238000004140 cleaning Methods 0.000 claims description 3
- 239000010431 corundum Substances 0.000 claims description 3
- 229910052593 corundum Inorganic materials 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 claims description 3
- 239000004576 sand Substances 0.000 claims description 3
- 238000007517 polishing process Methods 0.000 claims description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 abstract description 2
- 239000001301 oxygen Substances 0.000 abstract description 2
- 229910052760 oxygen Inorganic materials 0.000 abstract description 2
- 230000007774 longterm Effects 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 43
- 238000005452 bending Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 6
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 238000000227 grinding Methods 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 239000000758 substrate Substances 0.000 description 3
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000011247 coating layer Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 239000012720 thermal barrier coating Substances 0.000 description 2
- 238000005229 chemical vapour deposition Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 238000005240 physical vapour deposition Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 238000004901 spalling Methods 0.000 description 1
- 230000002195 synergetic effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
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- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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Abstract
The invention relates to a multilayer-structure environmental barrier coating for a silicon carbide ceramic matrix composite and a preparation method thereof. The method comprises the following steps: carrying out sand blasting, polishing, ultrasonic cleaning and drying on the silicon carbide ceramic matrix composite; sequentially preparing a bonding layer Si and a middle first layer Yb on the surface of the pretreated silicon carbide ceramic-based composite material by utilizing an atmospheric plasma spraying method2O3‑2SiO2An intermediate second layerYb2O3‑SiO2And an outer layer La2O3‑2MgO‑11Al2O3. The multilayer structure environmental barrier coating prepared by the method is combined with the silicon carbide ceramic matrix composite material compactly, and can provide effective protection for the silicon carbide ceramic matrix composite material in an oxygen-rich high-temperature environment, and the long-term use temperature is 1350 ℃ and the time is more than 500 hours.
Description
Technical Field
The invention relates to the technical field of materials, and relates to a multilayer-structure environmental barrier coating for a silicon carbide ceramic matrix composite and a preparation method thereof.
Background
With the upgrading and upgrading of the aero-engine, the thrust-weight ratio of the aero-engine is larger and larger, and the related key technologies comprise the improvement of the gas temperature and the weight reduction of the engine. Currently, the conventional high temperature alloy cannot meet the above requirements, and a new material is urgently needed for replacing the high temperature alloy. Due to the advantages of low density, high strength, high modulus, high temperature resistance, corrosion resistance, designability and the like, the silicon carbide ceramic matrix composite becomes a hot spot for research and application of aerospace engines in recent years. With the application of the silicon carbide ceramic matrix composite material in aeroengines, the corrosion of the silicon carbide ceramic matrix composite material by Environmental factors such as water vapor and CMAS under high temperature environment is more and more concerned by people, and an Environmental Barrier Coating (EBC) is required to be prepared on the surface of a silicon carbide ceramic matrix composite material member to isolate the corrosion factors from the silicon carbide ceramic matrix composite material, so that the corrosion of the environment to the silicon carbide ceramic matrix composite material is greatly reduced, and the problem that the performance of the silicon carbide ceramic matrix composite material is sharply reduced in the service process is solved.
Through the development of many years, the double-layer structure coating and the multilayer structure coating are gradually derived from the initial single coating on the surface environmental barrier coating of the silicon carbide ceramic matrix composite, so that the application range of the silicon carbide ceramic matrix composite is wider and wider. The current environment barrier coating systems with application value comprise a YSZ system, a BSAS system, a rare earth ceramic system and the like, but the coating systems fail to work for a long time due to different degrees when the temperature is higher than 1200 ℃.
Therefore, the development of a novel high-temperature-resistant EBC coating and a coating preparation technology has very important significance for improving the service temperature of the hot-end component of the silicon carbide ceramic matrix composite aeroengine, reducing the overall quality of the aeroengine and improving the performance of the aeroengine.
Disclosure of Invention
The invention aims to provide a multilayer-structure environmental barrier coating for a silicon carbide ceramic-based composite material and a preparation method thereof, which can provide high-temperature environmental shielding protection for the silicon carbide ceramic-based composite material, so that the silicon carbide ceramic-based composite material can keep the toughening property under a high-temperature aerobic environment, and can be prevented from being embrittled and losing efficacy.
In order to solve the technical problems, the invention adopts the following technical scheme:
a preparation method of a multilayer structure environmental barrier coating for a silicon carbide ceramic matrix composite material comprises the following steps:
(1) carrying out sand blasting and polishing pretreatment on the silicon carbide ceramic matrix composite material, wherein the surface roughness of the pretreated silicon carbide ceramic matrix composite material is 3-15 mu m;
(2) carrying out ultrasonic cleaning on the pretreated silicon carbide ceramic matrix composite;
(3) preparing a bonding layer Si and a middle first layer Yb on the surface of the silicon carbide ceramic-based composite material subjected to ultrasonic cleaning in sequence by adopting an atmospheric plasma spraying process2O3-2SiO2Intermediate second layer Yb2O3-SiO2And an outer layer La2O3-2MgO-11Al2O3And obtaining the multilayer structure environmental barrier coating.
In the above preparation method, preferably, in the step (1), the sand blasting medium is 100-300 mesh corundum sand, and the compressed air pressure is 0.5-1.0 MPa.
In the above preparation method, preferably, in the step (1), the grinding medium is 500-.
In the above preparation method, preferably, in the step (2), the ultrasonic cleaning time is 10 to 30 min.
In the above preparation method, preferably, in the step (3), the particle size of the Si powder used for spraying is 20-60 μm, and the thickness of the bonding layer Si is 100-200 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 15-35kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
In the above-mentioned production method, preferably, in the step (3), Yb to be used is sprayed2O3-2SiO2The powder particle size is 35-150 μm, and the first layer Yb is2O3-2SiO2The thickness is 15-50 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 20-45kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
In the above-mentioned production method, preferably, in the step (3), Yb to be used is sprayed2O3-SiO2Powder particle size of 35-150 μm and middle second layer Yb2O3-SiO2The thickness is 10-50 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 20-40kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
In the above-mentioned preparation method, preferably, in the step (3), the La used for spraying is sprayed2O3-2MgO-11Al2O3The powder particle size is 25-150 μm, and the outer layer La2O3-2MgO-11Al2O3The thickness is 30-180 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 15-50kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
Compared with the prior art, the invention has the advantages that:
1. the invention combines the environmental barrier coating Si, Yb2O3-2SiO2、Yb2O3-SiO2La with outer layer2O3-2MgO-11Al2O3The combination of the thermal barrier coating can effectively improve the thermal protection performance of the coating, and the thermal barrier coating and the coating have synergistic effect to achieve the purpose of protecting the silicon carbide ceramic matrix composite member. Moreover, the thermal expansion coefficient of the silicon carbide ceramic matrix composite material is 4.5 multiplied by 10-6/K，Si、Yb2O3-2SiO2、Yb2O3-SiO2The coefficients are 4.7X 10 respectively-6/K、4.8×10-6/K、6.7×10-6K, and La2O3-2MgO-11Al2O3Has a coefficient of thermal expansion of 9.4X 10-6The environment barrier coating with the four-layer structure designed by the invention is from the silicon carbide ceramic matrix composite material to the outer layer La2O3-2MgO-11Al2O3The thermal expansion coefficient is increased in sequence by a small amplitude, and the problem of thermal mismatch between the environmental barrier coating and the silicon carbide ceramic matrix composite can be effectively solved. Furthermore, since Yb2O3-2SiO2、Yb2O3-SiO2For the intermediate layer of the multilayer environmental coating according to the invention, the two layers are designed in particular as thin layers (thickness of less than 50 μm each) in order to reduce the thermal stresses during service. By combining the design ideas, the thermal matching performance of the multilayer-structure environmental barrier coating and the silicon carbide ceramic matrix composite material can be improved, and the silicon carbide ceramic matrix composite material can be effectively protected.
2. The multilayer structure environmental barrier coating has good thermal shock performance, and the coating and the silicon carbide ceramic matrix composite material are well combined without failure phenomena such as stripping, bulging and the like after 500 thermal shock cycles at the temperature of 1350 ℃. Moreover, the bending strength test is carried out on the sample according to the service condition of the silicon carbide ceramic matrix composite material, and the result shows that the bending strength retention rate of the silicon carbide ceramic matrix composite material with the multilayer structure environmental barrier coating reaches more than 85 percent after the silicon carbide ceramic matrix composite material is oxidized for a long time in a high-temperature oxygen-enriched environment, the fiber toughening property of the silicon carbide ceramic matrix composite material is maintained, and the silicon carbide ceramic matrix composite material is in 'pseudo-plastic' fracture.
3. Compared with the prior art of combining low-pressure plasma spraying, chemical vapor deposition, physical vapor deposition, various preparation processes and the like, the preparation equipment and the process used in the invention are simple, the cost is low, and the industrial production and the application are easy.
Drawings
FIG. 1 is a flow chart showing a multilayer environmental barrier coating for a silicon carbide ceramic matrix composite and a method for preparing the same according to an embodiment of the present invention.
FIG. 2 is a flow chart illustrating a multilayer environmental barrier coating for a silicon carbide ceramic matrix composite and a method for preparing the same according to an embodiment of the present invention.
Figure 3 shows a photomicrograph of an environmental barrier coating of a multilayer structure according to one embodiment of the invention.
Figure 4 shows a photomicrograph of a multilayer environmental barrier coating in accordance with one embodiment of the present invention.
Fig. 5 shows a schematic structural view of a multilayer environmental barrier coating in accordance with an embodiment of the present invention.
FIG. 6 shows a force-displacement curve for a sample bending strength test in one embodiment of the present invention.
FIG. 7 shows an SEM photograph of the multilayer environmental barrier coating after 500 thermal shocks in accordance with an embodiment of the present invention.
Detailed Description
In order to better understand the present invention, the following examples are further provided to illustrate the content of the present invention, but the present invention is not limited to the following examples.
Example 1
A multilayer structure environmental barrier coating for a silicon carbide ceramic matrix composite and a preparation method thereof are disclosed, as shown in figure 1, and the method comprises the following steps:
(1) carrying out sand blasting pretreatment on the silicon carbide ceramic matrix composite, wherein the sand blasting process conditions are as follows: the pressure of corundum sand and compressed air of 100 meshes is 0.6Mpa, then a roughness meter is used for detecting, and the surface roughness of the pretreated silicon carbide ceramic matrix composite material is 13.5 mu m;
(2) ultrasonically cleaning the silicon carbide ceramic matrix composite subjected to sand blasting treatment in the step (1) in 98% alcohol for 12min, and drying at 100 ℃;
(3) preparing a bonding layer Si on the surface of the silicon carbide ceramic-based composite material subjected to ultrasonic cleaning and drying in the step (2) by adopting an atmospheric plasma spraying process, wherein the granularity of Si powder used for spraying is 20-40 mu m, and the thickness of the bonding layer Si is 110 mu m; the temperature of a substrate is 600 ℃, the power of a spray gun is 18kW, the spraying distance is 180mm, the powder feeding rate is 6%, and the spraying angle is 35 degrees;
(4) preparing a middle first layer Yb on the surface of the silicon carbide ceramic matrix composite material with the bonding layer Si prepared in the step (3)2O3-2SiO2Yb for spray coating2O3-2SiO2The powder particle size is 35-80 μm, and the first layer Yb is2O3-2SiO2The thickness is 45 μm; the temperature of a matrix is 800 ℃, the power of a spray gun is 21kW, the spraying distance is 190mm, the powder feeding rate is 7%, and the spraying angle is 40 degrees;
(5) preparing the bonding layer Si and the middle first layer Yb in the step (4)2O3-2SiO2Preparing the intermediate second layer Yb on the surface of the silicon carbide ceramic matrix composite material2O3-SiO2Yb for spray coating2O3-SiO2Powder grain size of 70-150 μm and middle second layer Yb2O3-SiO2The thickness is 10 μm; the temperature of a substrate is 700 ℃, the power of a spray gun is 20kW, the spraying distance is 100mm, the powder feeding rate is 15%, and the spraying angle is 45 degrees;
(6) preparing the bonding layer Si and the middle first layer Yb in the step (5)2O3-2SiO2And an intermediate second layer Yb2O3-SiO2Preparing outer La on the surface of the silicon carbide ceramic matrix composite material2O3-2MgO-11Al2O3La for spray coating2O3-2MgO-11Al2O3The powder particle size is 25-90 μm, and the outer layer La2O3-2MgO-11Al2O3The thickness is 50 mu m, the temperature of the matrix is 900 ℃, the power of a spray gun is 20kW, the spraying distance is 86mm, the powder feeding rate is 6%, and the spraying angle is 30 degrees, thereby finally obtaining the multilayer-structure environmental barrier coating positioned on the surface of the silicon carbide ceramic matrix composite.
Fig. 3 is a macroscopic photograph of the multi-layer environmental barrier coating of this embodiment, which shows that the multi-layer environmental barrier coating prepared in this embodiment is flat and uniform. Fig. 4 is a photomicrograph of the environmental barrier coating with a multilayer structure of this embodiment, which shows that the environmental barrier coating with a multilayer structure prepared in this embodiment has a certain roughness, which is the morphology of the coating prepared by typical atmospheric plasma spraying.
After the silicon carbide ceramic matrix composite sample with the multilayer structure environmental barrier coating in the embodiment is subjected to heat preservation for 500 hours at 1350 ℃ in a muffle furnace in an air environment, the bending strength of the sample is 349.56MPa, for comparison, the bending strength of the silicon carbide ceramic matrix composite without the coating subjected to high-temperature oxidation is 392.86MPa, and the bending strength retention rate of the coating sample after long-time high-temperature oxidation reaches 88.98%.
FIG. 6 is a force-displacement curve of the multilayer environmental barrier coating according to this embodiment, which shows that the multilayer environmental barrier coating according to this embodiment enables the SiC CMC to maintain ductile fracture characteristics after a long period of high temperature oxidation.
Example 2
A multilayer environmental barrier coating for SiC ceramic matrix composites and a method for preparing the same are disclosed, as shown in FIG. 2, comprising the following steps:
(1) polishing pretreatment is carried out on the silicon carbide ceramic matrix composite, and the polishing process conditions are as follows: the grinding medium is a 600-mesh diamond grinding wheel, the rotating speed of the grinding wheel is 120 revolutions per minute, and the surface roughness of the pretreated silicon carbide ceramic matrix composite is 5.8 mu m;
(2) ultrasonically cleaning the silicon carbide ceramic matrix composite subjected to sand blasting in the step (1) in 98% alcohol for 28min, and then drying;
(3) preparing a bonding layer Si on the surface of the silicon carbide ceramic-based composite material subjected to ultrasonic cleaning and drying in the step (2) by adopting an atmospheric plasma spraying process, wherein the granularity of Si powder used for spraying is 35-60 mu m, and the thickness of the bonding layer Si is 195 mu m; the temperature of a substrate is 700 ℃, the power of a spray gun is 32kW, the spraying distance is 60mm, the powder feeding rate is 18%, and the spraying angle is 55 degrees;
(4) preparing a middle first layer Yb on the surface of the silicon carbide ceramic matrix composite material with the bonding layer Si prepared in the step (3)2O3-2SiO2Yb for spray coating2O3-2SiO2The powder grain size is 70-150 μm, the first layer Yb2O3-2SiO2The thickness is 18 μm; the temperature of a matrix is 610 ℃, the power of a spray gun is 45kW, the spraying distance is 55mm, the powder feeding rate is 20%, and the spraying angle is 60 degrees;
(5) preparing the bonding layer Si and the middle first layer Yb in the step (4)2O3-2SiO2Preparing the intermediate second layer Yb on the surface of the silicon carbide ceramic matrix composite material2O3-SiO2Yb for spray coating2O3-SiO2The powder particle size is 35-90 μm, and the middle second layer Yb2O3-SiO2The thickness is 40 μm; the temperature of a matrix is 880 ℃, the power of a spray gun is 40kW, the spraying distance is 170mm, the powder feeding rate is 8 percent, and the spraying angle is 55 degrees;
(6) preparing the bonding layer Si and the middle first layer Yb in the step (5)2O3-2SiO2And an intermediate second layer Yb2O3-SiO2Preparing outer La on the surface of the silicon carbide ceramic matrix composite material2O3-2MgO-11Al2O3La for spray coating2O3-2MgO-11Al2O3The powder particle size is 55-150 μm, and the outer layer La2O3-2MgO-11Al2O3The thickness is 180 mu m, the matrix temperature is 780 ℃, the spray gun power is 50kW, the spraying distance is 180mm, the powder feeding rate is 20%, the spraying angle is 60 degrees, and finally the multilayer-structure environmental barrier coating positioned on the surface of the silicon carbide ceramic matrix composite is obtained.
With the silicon carbide ceramic matrix composite sample of taking multilayer structure environmental barrier coating in this embodiment, the thermal shock cycle experiment is carried out to 1350 ℃ under the air environment in the tube furnace, and specific experimentation is: the sample was placed in the furnace-hold 55 minutes-take the sample out-air cool with compressed air for 5 minutes to room temperature-place the sample in the furnace for one cycle, and so on. Fig. 7 is an SEM photograph of the multilayer structure environmental barrier coating layer of the present embodiment after 500 thermal shock cycles, which shows that the multilayer structure environmental barrier coating layer after the thermal shock cycles is well bonded to the silicon carbide ceramic matrix composite without significant spalling.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, many modifications and changes can be made without departing from the inventive concept of the present invention, and these modifications and changes are within the protection scope of the present invention.
Claims (10)
1. A multilayer structure environmental barrier coating, characterized by comprising from inside to outside in proper order: bonding layer Si, intermediate first layer Yb2O3-2SiO2Intermediate second layer Yb2O3-SiO2Outer layer La2O3-2MgO-11Al2O3。
2. The multilayer environmental barrier coating of claim 1 wherein the bonding layer Si has a thickness of 100-200 μm; middle first layer Yb2O3-2SiO2The thickness is 15-50 μm; intermediate second layer Yb2O3-SiO2The thickness is 10-50 μm; outer layer La2O3-2MgO-11Al2O3The thickness is 30-180 μm.
3. The multilayer environmental barrier coating of claim 1, wherein the multilayer environmental barrier coating is applied primarily to the surface of the silicon carbide ceramic matrix composite.
4. The method for preparing the environmental barrier coating with a multi-layer structure as defined in claim 1, wherein the bonding layer Si and the middle first Yb layer are sequentially formed on the surface of the SiC ceramic matrix composite by an atmospheric plasma spraying process2O3-2SiO2Intermediate second layer Yb2O3-SiO2And an outer layer La2O3-2MgO-11Al2O3。
5. The method of making a multilayer environmental barrier coating according to claim 4, comprising the steps of:
(1) carrying out sand blasting and polishing pretreatment on the surface of the silicon carbide ceramic matrix composite; the surface roughness of the pretreated silicon carbide ceramic matrix composite material is 3-15 mu m;
(2) cleaning and drying the pretreated silicon carbide ceramic matrix composite;
(3) preparing a bonding layer Si and a middle first layer Yb on the silicon carbide ceramic-based composite material after ultrasonic cleaning and drying by adopting an atmospheric plasma spraying process2O3-2SiO2Intermediate second layer Yb2O3-SiO2And an outer layer La2O3-2MgO-11Al2O3And obtaining the multilayer structure environmental barrier coating attached to the silicon carbide ceramic matrix composite.
6. The method for preparing the alloy material according to claim 5, wherein the sand blasting process conditions are as follows: 100-mesh 300-mesh corundum sand, and the pressure of compressed air is 0.5-1.0 MPa; the polishing process conditions are as follows: 500-.
7. The preparation method according to claim 5, characterized in that an atmospheric plasma spraying process is adopted to prepare the bonding layer Si on the surface of the silicon carbide ceramic matrix composite material after ultrasonic cleaning and drying, the granularity of the Si powder used for spraying is 20-60 μm, and the thickness of the bonding layer Si is 100-200 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 15-35kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
8. The article of claim 5The preparation method is characterized in that the atmospheric plasma spraying process is adopted to prepare the first Yb layer in the middle on the surface of the bonding layer Si2O3-2SiO2Yb for spray coating2O3-2SiO2The powder particle size is 35-150 μm, and the first layer Yb is2O3-2SiO2The thickness is 15-50 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 20-45kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
9. The method according to claim 5, wherein the first layer Yb is formed in the middle2O3-2SiO2Surface preparation of the intermediate second layer Yb2O3-SiO2Yb for spray coating2O3-SiO2Powder particle size of 35-150 μm and middle second layer Yb2O3-SiO2The thickness is 10-50 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 20-40kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
10. The method according to claim 5, wherein the second layer Yb is formed in the middle2O3-SiO2Surface preparation of outer layer La2O3-2MgO-11Al2O3La for spray coating2O3-2MgO-11Al2O3The powder particle size is 25-150 μm, and the outer layer La2O3-2MgO-11Al2O3The thickness is 30-180 μm; in the process of atmospheric plasma spraying, the temperature of a matrix is 600-900 ℃, the power of a spray gun is 15-50kW, the spraying distance is 50-200mm, the powder feeding rate is 5-20%, and the spraying angle is 30-60 degrees.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115340410A (en) * | 2022-06-20 | 2022-11-15 | 武汉理工大学 | Ceramic-based sealing coating for surface of silicon carbide fiber-reinforced silicon carbide composite material and preparation method and application thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106116702A (en) * | 2016-06-27 | 2016-11-16 | 中国科学院长春应用化学研究所 | A kind of Cfthe preparation method of/SiC ceramic matrix composite material surface high-temp oxidation-inhibited thermal barrier coating |
| CN108911791A (en) * | 2018-07-24 | 2018-11-30 | 中国人民解放军国防科技大学 | Environmental barrier coating and preparation method thereof |
| CN109336647A (en) * | 2018-11-06 | 2019-02-15 | 航天特种材料及工艺技术研究所 | A kind of heat/Environmental Barrier Coatings on Si-based Ceramics and preparation method thereof for ceramic matric composite |
| CN109516835A (en) * | 2018-12-11 | 2019-03-26 | 哈尔滨理工大学 | A kind of reaction and plasma spraying ZrB2The method of-SiC base composite coating |
| CN111334743A (en) * | 2020-03-15 | 2020-06-26 | 河北工业大学 | Preparation method of zirconium boride-zirconium carbide-silicon carbide composite coating |
| CN111848222A (en) * | 2020-07-07 | 2020-10-30 | 航天特种材料及工艺技术研究所 | Gradient environmental barrier coating formed on base material and preparation method thereof |
-
2021
- 2021-01-27 CN CN202110108060.5A patent/CN112939629A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106116702A (en) * | 2016-06-27 | 2016-11-16 | 中国科学院长春应用化学研究所 | A kind of Cfthe preparation method of/SiC ceramic matrix composite material surface high-temp oxidation-inhibited thermal barrier coating |
| CN108911791A (en) * | 2018-07-24 | 2018-11-30 | 中国人民解放军国防科技大学 | Environmental barrier coating and preparation method thereof |
| CN109336647A (en) * | 2018-11-06 | 2019-02-15 | 航天特种材料及工艺技术研究所 | A kind of heat/Environmental Barrier Coatings on Si-based Ceramics and preparation method thereof for ceramic matric composite |
| CN109516835A (en) * | 2018-12-11 | 2019-03-26 | 哈尔滨理工大学 | A kind of reaction and plasma spraying ZrB2The method of-SiC base composite coating |
| CN111334743A (en) * | 2020-03-15 | 2020-06-26 | 河北工业大学 | Preparation method of zirconium boride-zirconium carbide-silicon carbide composite coating |
| CN111848222A (en) * | 2020-07-07 | 2020-10-30 | 航天特种材料及工艺技术研究所 | Gradient environmental barrier coating formed on base material and preparation method thereof |
Non-Patent Citations (2)
| Title |
|---|
| 范文娟: ""Cf／SiC表面Yb2Si2O7／LaMgAl11Ol9热障涂层的热循环行为与失效机理研究"，范文娟，《长沙理工大学硕士论文》，第1-93页", 《长沙理工大学硕士论文》 * |
| 魏世丞: "《热喷涂技术及其在再制造中的应用》", 31 May 2019, 哈尔滨工业大学出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115340410A (en) * | 2022-06-20 | 2022-11-15 | 武汉理工大学 | Ceramic-based sealing coating for surface of silicon carbide fiber-reinforced silicon carbide composite material and preparation method and application thereof |
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