CN113463008A - Crack expansion resistant environmental barrier coating and preparation method thereof - Google Patents

Crack expansion resistant environmental barrier coating and preparation method thereof Download PDF

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CN113463008A
CN113463008A CN202110727142.8A CN202110727142A CN113463008A CN 113463008 A CN113463008 A CN 113463008A CN 202110727142 A CN202110727142 A CN 202110727142A CN 113463008 A CN113463008 A CN 113463008A
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mosi
sio
barrier coating
environmental barrier
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钟鑫
毛枫岐
牛亚然
黄利平
郑学斌
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Shanghai Institute of Ceramics of CAS
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Shanghai Institute of Ceramics of CAS
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material

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  • Engineering & Computer Science (AREA)
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  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

The invention relates to an anti-crack-propagation environmental barrier coating and a preparation method thereof. The crack propagation resistant environmental barrier coating comprises: si bonding layer and RE deposited on the surface of the substrate in sequence2Si2O7Intermediate layer and MoSi2/RE2SiO5A composite facing; wherein RE is at least one of Y, Dy, Ho, Er, Tm, Yb and Lu; the MoSi is2/RE2SiO5MoSi in composite surface layer2In an amount of not more than 10 vol.%.

Description

Crack expansion resistant environmental barrier coating and preparation method thereof
Technical Field
The invention relates to an anti-crack-expansion environmental barrier coating and a preparation method thereof, belonging to the technical field of preparation of coatings for aircraft engines and ground gas turbines.
Background
The development of aircraft engines is oriented toward higher thrust-weight ratios, and the inlet temperature of the engine needs to be increased and the weight of the structure needs to be reduced. The ceramic matrix Composite Materials (CMCs) have the characteristics of low density, high specific strength and the like, can partially replace high-temperature alloy, and are used for hot end parts of engines. However, the ceramic matrix composite material is subjected to severe environmental corrosion in the combustion environment of the engine, resulting in a sharp decline in the material properties.
The application of the environmental barrier coating can effectively solve the problem that the substrate fails due to environmental corrosion. Researches find that the rare earth silicate has a thermal expansion coefficient matched with that of a substrate material, good phase stability and excellent water-oxygen corrosion resistance, and is an ideal environment barrier coating material. Some current structural reports on rare earth silicate environmental barrier coatings include mainly Si (bond coat) + rare earth silicates (e.g., Er)2SiO5、Yb2SiO5、Lu2SiO5And Yb2Si2O7Etc., surface layer) and Si (bonding layer) + mullite (intermediate layer) + rare earth silicate (e.g., Er)2SiO5、Yb2SiO5And Lu2SiO5Etc., a top coat), etc. However, these coating structures suffer from the disadvantage that during thermal cycling, such as thermal shock, water oxygen corrosion, and long term oxidation, the coating system develops through cracks that provide rapid diffusion paths for the oxidizing agent, accelerating the growth of the internal Thermally Grown Oxide (TGO), and ultimately leading to failure of the coating system. In addition, cracks propagating at the interface of the facing layer and the intermediate layer may also lead to rapid spalling of the facing material.
Disclosure of Invention
In order to overcome the technical problems, the invention aims to provide an environmental barrier coating resisting crack propagation and a preparation method thereof. The environmental barrier coating has the characteristics of oxidation resistance, stable coating structure, crack expansion resistance and the like, the service temperature can reach more than 1350 ℃, the service life of the environmental barrier coating is greatly prolonged, and the environmental barrier coating can be applied to the protection of hot end parts of aircraft engines.
In one aspect, the present invention provides an environmental barrier coating resistant to crack propagation comprising: sequentially deposited on the surface of the substrateSi bonding layer and RE of surface2Si2O7Intermediate layer and MoSi2/RE2SiO5A composite facing; wherein RE is at least one of Y, Dy, Ho, Er, Tm, Yb and Lu; the MoSi is2/RE2SiO5MoSi in composite surface layer2In an amount of not more than 10 vol.%.
In the present disclosure, the environmental barrier coating against crack propagation can reduce the generation and propagation of cracks, MoSi2Can consume oxidant and oxidize product SiO in subsequent service environment2Can be associated with part RE2SiO5Reaction to form RE2Si2O7，RE2Si2O7Has good phase stability, and can greatly improve the service life of the environmental barrier coating.
Preferably, the MoSi is2/RE2SiO5Composite surface layer (or called modified RE)2SiO5Surface layer) of MoSi2The content of (b) is 5vol.% to 10vol.%, more preferably 5 vol.%.
Preferably, the thickness of the Si bonding layer is 50-100 μm.
Preferably, the RE2Si2O7The thickness of the intermediate layer is 50 to 200 μm.
Preferably, the MoSi is2/RE2SiO5The thickness of the composite surface layer is 50-200 μm.
Preferably, the matrix is a ceramic matrix composite, preferably a silicon carbide-based ceramic material, and more preferably a SiC matrix or a SiC/SiC composite.
On the other hand, the invention also provides a preparation method of the crack propagation resistant environmental barrier coating, which comprises the steps of sequentially preparing the Si bonding layer and the RE on the substrate by adopting a plasma spraying technology2Si2O7Intermediate layer and MoSi2/RE2SiO5And (4) compounding the surface layer. The preparation method of the crack expansion resistant environmental barrier coating is a plasma spraying technology, and the prepared coating is compact in structure, uniform in components and good in thermal shock resistance. And the thermal and physical properties between the coating and the substrate and between the layersThe matching is good, and the thermal stress of a coating system can be effectively relieved.
Preferably, the parameters for preparing the Si bonding layer on the substrate by using the plasma spraying technology include: the vacuum degree of the tank body is 100-500 mbar, the particle size of Si powder is 1-100 microns, the plasma spraying power is 30-50 kW, the spraying distance is 100-300 mm, the current is 550-700A, the argon flow is 30-60 slm, the hydrogen flow is 5-10 slm, and the powder feeding speed is 5-20 g/min.
Preferably, the RE is prepared by plasma spraying2Si2O7Parameters of the intermediate layer include: the vacuum degree of the tank body is 100-500 mbar, RE2Si2O7The particle size range of the powder is 1-100 mu m, the plasma spraying power is 30-45 kW, the spraying distance is 100-300 mm, the current is 550-700A, the argon flow is 40-60 slm, the hydrogen flow is 5-10 slm, the powder feeding speed is 20-50 g/min, and the vacuum degree is 100-500 mbar.
Preferably, the plasma spraying technology is adopted to MoSi2/RE2SiO5The parameters of the composite surface layer comprise: the vacuum degree of the tank body is 100-500 mbar, MoSi2/RE2SiO5The particle size range of the composite powder is 1-100 mu m, the plasma spraying power is 35-50 kW, the spraying distance is 150-300 mm, the current is 500-700A, the argon flow is 40-55 slm, the hydrogen flow is 5-15 slm, and the powder feeding speed is 20-60 g/min.
Has the advantages that:
in the present invention, MoSi2Has good damage tolerance, MoSi during thermal cycling2/RE2SiO5MoSi in the top layer2The crack can be effectively prevented from expanding, so that the durability of a coating system is improved;
in the invention, in the service examination process, MoSi2Oxidation can occur, therefore MoSi2/RE2SiO5The surface layer has the performance of consuming the oxidant, so that the oxidizing substances are effectively slowed down from permeating into the coating, the TGO thickening rate in the coating is favorably slowed down, and the service life of a coating system is prolonged;
in the present invention, MoSi2SiO generated by oxidation2Monosilicate (RE) with surface layer2SiO5) Continue to useReaction, resulting pyrosilicate (RE)2Si2O7) The phase can reduce the thermal mismatch effect of the surface layer material and the system, thereby further improving the crack propagation resistance of the coating system;
the coating is sprayed by adopting a plasma technology, and the method has the advantages of low process cost, high efficiency, good repeatability, controllable coating thickness, suitability for large-scale production and the like.
Drawings
FIG. 1 is a schematic structural view of an environmental barrier coating for crack propagation resistance on the surface of a ceramic matrix composite;
FIG. 2 is a macro-topography of the crack growth resistant environmental barrier coating of example 1 before and after 40 thermal shocks;
FIG. 3 is a macro-topography of the crack growth resistant environmental barrier coating of example 2 before and after 50 thermal shocks;
FIG. 4 is a macro-topography of the crack propagation resistant environmental barrier coating before and after 500h oxidation in example 3;
FIG. 5 is a cross-sectional profile of the crack growth resistant environmental barrier coating of example 3 after 500h oxidation;
FIG. 6 is a macro-topography of the crack propagation resistant environmental barrier coating before and after 300h of water-oxygen corrosion in example 4;
FIG. 7 is the cross-sectional profile of the crack growth resistant environmental barrier coating of example 4 after water-oxygen corrosion for 300 h;
FIG. 8 is a photomicrograph of the water oxygen corrosion of the crack growth resistant environmental barrier coating of example 5 after 500 hours of oxidation;
FIG. 9 is a photomicrograph of the water oxygen corrosion of the crack growth resistant environmental barrier coating of example 6 after 500 hours of oxidation;
FIG. 10 is a macro-topography of the crack growth resistant environmental barrier coating before and after 40 thermal shocks in comparative example 1;
FIG. 11 is a macro-topography of the crack growth resistant environmental barrier coating before and after 50 thermal shocks in comparative example 2;
FIG. 12 is a cross-sectional profile of the crack growth resistant environmental barrier coating of comparative example 3 after oxidation for 500 hours;
FIG. 13 is a cross-sectional view of the crack growth resistant environmental barrier coating of comparative example 4 after 200h of water-oxygen corrosion;
FIG. 14 is the cross-sectional profile of the crack growth resistant environmental barrier coating of example 7 after 200h of water-oxygen corrosion.
Detailed Description
The present invention is further illustrated by the following examples, which are to be understood as merely illustrative and not restrictive.
In the present disclosure, an environmental barrier coating resistant to crack propagation includes: the ceramic matrix composite material comprises a substrate such as a silicon carbide-based ceramic material and the like, and a Si bonding layer and a RE which are sequentially deposited on the surface of the substrate2Si2O7Intermediate layer and MoSi2Doping of RE2SiO5Surface layer (or called MoSi)2/RE2SiO5A composite tie layer); wherein RE is at least one of Y, Dy, Ho, Er, Tm, Yb and Lu.
The following is an exemplary description of the preparation of the crack propagation resistant environmental barrier coating. For example, a vacuum plasma spray system (Sulzer Metco, Switzerland) with an F4-VB spray gun may be used to produce an environmental barrier coating that resists crack propagation.
Preparation of MoSi2/RE2SiO5And (3) composite powder. MoSi is subjected to mechanical ball milling2Powder and RE2SiO5And uniformly mixing the powder to obtain mixed powder. The MoSi is2/RE2SiO5The particle size of the composite powder can be 1-100 mu m, MoSi2The volume percentage is not more than 10%, preferably 2.5-10%, and more preferably 5-7.5 vol%. If it is MoSi2If the volume percentage is too low, no crack propagation resistance is obvious. If it is MoSi2If the volume percentage is too high, the gaseous substances which are oxidized to generate a large amount of molybdenum oxide damage the coating, and the service life of the coating is affected.
As a MoSi2/RE2SiO5An example of preparing the composite powder is first to prepare RE2O3After the powder and the Si powder are mixed according to a certain proportion, the powder suitable for spraying is prepared by adopting a mechanical mixing method, and the parameters comprise: the rotating speed is 150 rpm-200 rpm, and the mixing time is 5 h.
And preparing the Si bonding layer on the surface of the substrate by adopting a plasma spraying technology. The thickness of the Si bonding layer can be 50-100 μm. The parameters of the plasma spray technique may include: the plasma spraying power is 30-50 kW, the spraying distance is 100-300 mm, the current is 550-700A, the argon flow is 30-60 slm, the hydrogen flow is 5-10 slm, the powder feeding speed is 8-20 g/min, the vacuum degree is 100-500 mbar, and the spraying time can be 1-20 minutes.
Preparing RE on the surface of the Si bonding layer by adopting a plasma spraying technology2Si2O7An intermediate layer. The thickness of the middle layer is 50-200 mu m. The parameters of the plasma spraying technique include: the plasma spraying power is 30-45 kW, the spraying distance is 100-300 mm, the current is 550-700A, the argon flow is 40-60 slm, the hydrogen flow is 5-10 slm, the powder feeding speed is 20-50 g/min, the vacuum degree is 100-500 mbar, and the spraying time can be 1-20 minutes. RE used2Si2O7The particle size of the powder can be 1-100 μm.
By plasma spraying on RE2Si2O7Preparation of MoSi on surface of intermediate layer2/RE2SiO5And (4) compounding the surface layer. The thickness of the surface layer is 50-200 μm. The parameters of the plasma spraying technique include: the plasma spraying power is 35-50 kW, the spraying distance is 150-300 mm, the current is 500-700A, the argon flow is 40-55 slm, the hydrogen flow is 5-15 slm, the powder conveying speed is 25-60 g/min, the vacuum degree is 100-500 mbar, and the spraying time can be 1-20 minutes. RE used2SiO5The particle size of the powder can be 1-100 μm. Preferably, RE2SiO5RE and RE in the top layer2Si2O7The RE elements in the intermediate layer are the same.
The present invention will be described in detail by way of examples. It is also to be understood that the following examples are illustrative of the present invention and are not to be construed as limiting the scope of the invention, and that certain insubstantial modifications and adaptations of the invention by those skilled in the art may be made in light of the above teachings. The specific process parameters and the like of the following examples are also only one example of suitable ranges, i.e., those skilled in the art can select the appropriate ranges through the description herein, and are not limited to the specific values exemplified below.
Example 1
Step 1: carrying out sand blasting treatment on the surface of the SiC matrix, wherein the sand blasting pressure is 0.6MPa, so as to obtain a matrix with the surface being pretreated;
step 2: preparing a Si bonding layer on the surface of the pretreated substrate by adopting a plasma spraying method, wherein the parameters of the spraying process are shown in a table 1;
and step 3: by plasma spraying on Yb2O3Yb spraying on the surface of the/Si composite bonding layer2Si2O7The intermediate layer, the spraying process parameters are shown in table 2;
and 4, step 4: by vacuum plasma spraying method on Yb2Si2O7Spraying MoSi on the surface of the intermediate layer2/Yb2SiO5The surface layer and the spraying process parameters are shown in the table 3.
Table 1 shows the process parameters for vacuum plasma spraying the Si bonding layer in example 1:
plasma gas Ar 50slpm Powder carrier gas Ar 2slpm Electric current 630A
Plasma gas H2 10slpm Distance of spraying 250mm Degree of vacuum 100mbar
Spraying power 39kW Powder feeding rate 13g/min Time 2 minutes
The average thickness of the resulting Si bonding layer was 80 μm.
TABLE 2 vacuum plasma spray of Yb2Si2O7The process parameters of the intermediate layer are as follows:
plasma gas Ar 50slpm Powder carrier gas Ar 2.5slpm Electric current 650A
Plasma gas H2 8slpm Distance of spraying 200mm Degree of vacuum 200mbar
Spraying power 36kW Powder feeding rate 42g/min Time 3 minutes
Obtained Yb2Si2O7The average thickness of the intermediate layer was 80 μm.
TABLE 3 vacuum plasma spray MoSi2/Yb2SiO5Technological parameters of surface layer
Plasma gas Ar 43slpm Powder carrier gas Ar 2.5slpm Electric current 600A
Plasma gas H2 12slpm Distance of spraying 200mm Degree of vacuum 200mbar
Spraying power 40kW Powder feeding rate 50g/min Time 3 minutes
The obtained MoSi2/Yb2SiO5MoSi in the top layer2Is 5vol.% and has an average thickness of 90 μm.
The thermal shock resistance of the coating in example 1 was evaluated by a water quenching thermal shock test under the following conditions: and placing the coating system sample in an alumina crucible, placing the crucible in a tubular furnace at 1350 ℃ for heat preservation for 10 minutes, taking the crucible out of the tubular furnace, rapidly placing the coating system sample in water for quenching, and then cleaning and drying, wherein the above is a cycle. The test was stopped when the thermal shock was 40 times or the area of the coating surface peeled off exceeded 10%. The macro-topography of the coating system before and after thermal shock is shown in figure 2. When the thermal shock is finished, although the SiC matrix has a fragmentation phenomenon, the coating system on the surface of the matrix still keeps complete and does not have a shedding phenomenon.
Example 2
The differences between this example 2 and example 1 are: the coating substrate is made of SiC/SiC composite material, and the thermal shock frequency is improved to 50 times. The macro morphology of the coating system before and after 50 times of thermal shock is shown in figure 3. The coating system on the surface of the SiC/SiC composite material can still keep the structural integrity after 50 times of thermal shock.
Example 3
The differences between this example 3 and example 1 are: the oxidation resistance of the coating is checked by adopting a static oxidation method, and the conditions are as follows: placing the coating sample in a muffle furnace, heating to 1350 ℃ along with the furnace, stopping heating every 25 hours, taking out the sample for observation,recording the time of crack occurrence; the test was stopped when the oxidation time was 500h or the area of coating spalling exceeded 10%. The macro-morphology of the environmental barrier coating before and after 500h oxidation is shown in fig. 4, and the coating system remains intact after 500h oxidation. The cross-sectional morphology of the coating system after being oxidized for 500h is shown in FIG. 5, the modified surface layer has a compact structure after being oxidized for 500h, and no longitudinal crack is generated inside the modified surface layer. Yb of2Si2O7A TGO layer of about 3 μm thickness is formed at the/Si interface, the TGO layer and Yb2Si2O7And Si bonds well.
Example 4
This example 4 differs from that described in example 1 in that: the corrosion resistance of the coating obtained in example 1 was examined by a water-oxygen coupling experiment under the following conditions: placing the coating sample in an alumina tube furnace, heating to 1350 ℃ along with the furnace, and introducing 30% H2O-70% of air, the flow rate of the mixed gas is 2.5 multiplied by 10-4m/s, heating was stopped at 10-hour intervals. The test was stopped when the corrosion was 200 hours or the area of coating spalling exceeded 10%. The macroscopic morphology of the coating system after 300h of water-oxygen corrosion is shown in FIG. 6, and the coating system remains intact after 300h of water-oxygen corrosion. The cross-sectional morphology of the coating system after 300h of water-oxygen corrosion is shown in FIG. 7, and a defect with transverse cracks as the main component, Yb, appears in the surface layer2Si2O7A TGO layer of about 3 μm thickness is formed at the/Si interface, the TGO layer and Yb2Si2O7And Si bonds well.
Example 5
In this example 5, the environmental barrier coating process parameters were as described in example 1, except that: MoSi2/Yb2SiO5MoSi in composite surface layer2Is 2.5 vol.%. Referring to example 4, the obtained environmental barrier coating was subjected to the water oxygen corrosion test for the same time, and a macroscopic photograph thereof after 300h of corrosion is shown in fig. 8(a), and the sample remained intact without cracking and peeling. Referring to example 3, a macroscopic photograph of the environmental barrier coating of example 5 after being oxidized for 500 hours is shown in fig. 8(b), and the sample remains intact without cracking or peeling.
Example 6
In this example 6Environmental barrier coating process parameters refer to example 1 with the difference that: MoSi2/Yb2SiO5MoSi in composite surface layer2Is 7.5 vol.%. Referring to example 4, the obtained environmental barrier coating was subjected to the water oxygen corrosion test for the same time, and a macroscopic photograph thereof after 300h of corrosion is shown in fig. 9(a), and the sample remained intact without cracking and peeling. Referring to example 3, a macroscopic photograph of the environmental barrier coating of example 6 after being oxidized for 500 hours is shown in fig. 9(b), and the sample remains intact without cracking or peeling.
Example 7
Environmental barrier coating process parameters against crack propagation in this example 7 reference is made to example 1 with the difference that: MoSi2/Yb2SiO5MoSi in composite surface layer2Is 10 vol.%. Referring to example 4, the obtained environmental barrier coating was subjected to water-oxygen corrosion examination for the same time, and the cross-sectional morphology after 200h corrosion was shown in FIG. 12. The modified top coat exhibited a number of holes, much less so than the coating of example 4. The coating system of this example, after etching, had a thinner TGO layer thickness than the coating system of comparative example 4, as compared to comparative example 4, indicating superior performance to comparative example 4.
Comparative example 1
The environmental barrier coating process parameters in this comparative example 1 were as in example 1 except that: selecting Yb2SiO5Is a surface layer. The obtained coating was subjected to 40 thermal shock examinations, and the macro-morphology of the coating before and after 40 thermal shock examinations is shown in FIG. 10. It can be seen that the unmodified system of the SiC matrix surface partially spalled at the edge after 40 thermal shocks.
Comparative example 2
The environmental barrier coating process parameters of this comparative example 2 were as in example 1 except that: selecting Yb2SiO5Is a surface layer, the matrix is a SiC/SiC composite material, and the thermal shock times are 50 times. The thermal shock examination of the coating was performed in the same manner as in example 1. The macro-morphology of the coating system before and after 50 times of thermal shock is shown in FIG. 11, the edge of the matrix is slightly stripped after 50 times of thermal shock, and the thermal shock resistance of the coating system is not as good as that of example 2.
Comparative example 3
The environmental barrier coating process parameters of this comparative example 3 were as in example 1 except that: selecting Yb2SiO5Is a surface layer. Referring to example 3, the obtained environmental barrier coating was subjected to oxidation examination for the same time, and its cross-sectional morphology is shown in fig. 12. After 500h of oxidation, Yb2SiO5A large number of longitudinal cracks, Yb, appear in the surface layer2SiO5/Yb2Si2O7Crack generation at the interface, Yb2Si2O7There were a number of cracks in the TGO at the/Si interface, much less so than the coating in example 1.
Comparative example 4
The environmental barrier coating process parameters of this comparative example 4 were as in example 1 except that: selecting Yb2SiO5Is a surface layer. Referring to example 4, the obtained environmental barrier coating was subjected to 200h water oxygen etching, and its cross-sectional morphology is shown in FIG. 13. Yb of2SiO5A large number of longitudinal cracks, Yb, appear in the surface layer2Si2O7There were a number of cracks in the TGO at the/Si interface, much less so than the coating in example 4.

Claims (10)

1. An environmental barrier coating resistant to crack propagation comprising: si bonding layer and RE deposited on the surface of the substrate in sequence2Si2O7Intermediate layer and MoSi2/RE2SiO5A composite facing; wherein RE is at least one of Y, Dy, Ho, Er, Tm, Yb and Lu; the MoSi is2/RE2SiO5MoSi in composite surface layer2In an amount of not more than 10 vol.%.
2. The environmental barrier coating against crack propagation according to claim 1, wherein said MoSi2/RE2SiO5MoSi in composite surface layer2The content of (A) is 5-10 vol.%.
3. The environmental barrier coating against crack propagation according to claim 1 or 2, wherein the thickness of the Si bonding layer is 50 to 100 μ ι η.
4. The environmental barrier coating against crack propagation according to any one of claims 1 to 3, wherein the RE2Si2O7The thickness of the intermediate layer is 50 to 200 μm.
5. The environmental barrier coating against crack propagation according to any one of claims 1-4, wherein the MoSi is2/RE2SiO5The thickness of the composite surface layer is 50-200 μm.
6. The environmental barrier coating against crack propagation according to any one of claims 1-5, wherein the substrate is a ceramic matrix composite, preferably a silicon carbide based ceramic material, more preferably a SiC substrate or a SiC/SiC composite.
7. A method for preparing the crack propagation resistant environmental barrier coating according to any one of claims 1 to 6, wherein the Si bonding layer, the RE, and the Si adhesion layer are sequentially prepared on the substrate by using a plasma spraying technique2Si2O7Intermediate layer and MoSi2/RE2SiO5And (4) compounding the surface layer.
8. The method of claim 7, wherein the parameters for preparing the Si bonding layer on the substrate by using the plasma spraying technique comprise: the vacuum degree of the tank body is 100-500 mbar, the particle size of Si powder is 1-100 microns, the plasma spraying power is 30-50 kW, the spraying distance is 100-300 mm, the current is 550-700A, the argon flow is 30-60 slm, the hydrogen flow is 5-10 slm, and the powder feeding speed is 5-20 g/min.
9. The method according to claim 7 or 8, wherein the RE is prepared by plasma spraying2Si2O7Parameters of the intermediate layer include: the vacuum degree of the tank body is 100-500 mbar, RE2Si2O7The particle size range of the powder is 1-100 mu m, the plasma spraying power is 30-45 kW, the spraying distance is 100-300 mm, the current is 550-700A, the argon flow is 40-60 slm, the hydrogen flow is 5-10 slm, the powder feeding speed is 20-50 g/min, and the vacuum degree is 100-500 mbar.
10. Preparation method according to any one of claims 7 to 9, characterized in that the plasma spraying technique MoSi is used2/RE2SiO5The parameters of the composite surface layer comprise: the vacuum degree of the tank body is 100-500 mbar, MoSi2/RE2SiO5The particle size range of the composite powder is 1-100 mu m, the plasma spraying power is 35-50 kW, the spraying distance is 150-300 mm, the current is 500-700A, the argon flow is 40-55 slm, the hydrogen flow is 5-15 slm, and the powder feeding speed is 20-60 g/min.
CN202110727142.8A 2021-06-29 2021-06-29 Crack expansion resistant environmental barrier coating and preparation method thereof Pending CN113463008A (en)

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CN112457061A (en) * 2020-12-22 2021-03-09 中国科学院上海硅酸盐研究所 Environment barrier coating with gradient change of components and preparation method thereof

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