CN109468568A - A kind of the rare earth silicate environment barrier coating and preparation method of resistance to crack extension - Google Patents
A kind of the rare earth silicate environment barrier coating and preparation method of resistance to crack extension Download PDFInfo
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- CN109468568A CN109468568A CN201710801357.3A CN201710801357A CN109468568A CN 109468568 A CN109468568 A CN 109468568A CN 201710801357 A CN201710801357 A CN 201710801357A CN 109468568 A CN109468568 A CN 109468568A
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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
- C23C4/04—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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- 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
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Abstract
The present invention relates to the rare earth silicate environment barrier coating and preparation method of a kind of resistance to crack extension, the rare earth silicate environment barrier coating successively includes matrix, the adhesive layer positioned at described matrix surface, surface layer and the middle layer between the adhesive layer and surface layer；The adhesive layer is Si layers, and the middle layer is Yb2Si2O7Layer, the surface layer are rare earth monosilicate Re2SiO5.The coating that the present invention designs uses Yb2Si2O7It is the structure of superficial layer for middle layer and rare earth silicate, there is significant resistance to crack extension ability and excellent thermal shock resistance.
Description
Technical field
The present invention relates to the rare earth silicate environment barrier coatings and preparation method of a kind of resistance to crack extension, belong to coating neck
Domain.
Background technique
High thrust ratio is the distinctive marks of high-performance aeroengine.It improves the inlet temperature of combustion gas and reduces architecture quality
It is the key that realize that aero-engine develops to high thrust ratio, high efficiency direction.Silicon-based ceramic material, including SiC, Si3N4、
C/SiC and SiC/SiC etc., just gradually substitutes high temperature alloy, is applied to high thrust ratio aero-engine hot-end component.But it is navigating
During empty engine is on active service for a long time, silicon-based ceramic material will receive vapor, corrosive impurity in combustion gas environment
Threat, cause material property sharply to decline.Current most viable, most effective solution is exactly on silicon-based ceramic material surface
Depositional environment Barrier Coatings (Environmental Barrier Coating, EBC), form one between matrix and combustion gas environment
Road barrier hinders the corrosion of corrosive goods confrontation basis material, thus the service life of elongate member.
The study found that rare earth silicate generally has lower thermal expansion coefficient and good phase stability and excellent
Vapour resistant corrosive power is most potential environment barrier coating material.It is some about rare earth silicate Environment Obstacles at present
The report of coating material system mainly includes Si (adhesive layer)+rare earth silicate (surface layer, such as Er2SiO5、Yb2SiO5And
Lu2SiO5、Yb2Si2O7Deng) and Si (adhesive layer)+mullite (middle layer)+rare earth silicate (surface layer, such as Er2SiO5、
Yb2SiO5And Lu2SiO5Deng) [1K.N.Lee, D.S.Fox, N.P.Bansal, Rare earth silicate
environmental barrier coatings for SiC/SiC composites and Si3N4ceramics,
J.Eur.Ceram.Soc.2005,25(10):1705-1715.2B.T.Richards,H.N.G.Wadley,Plasma spray
deposition of tri-layer environmental barrier coatings.J.Eur.Ceram.Soc.,2014,
34(12):3069-3083.].But some researches show that since thermal expansion coefficient differs larger, Si/ rare earth silicate coating material
Material, which ties up in Thermal Cycling, can generate the crackle through rare earth silicate coating, and being corroded property of Si adhesive layer is medium oxidizing,
Finally make coating failure [1K.N.Lee, D.S.Fox, N.P.Bansal, Rare earth silicate
environmental barrier coatings for SiC/SiC composites and Si3N4ceramics,
J.Eur.Ceram.Soc.2005,25(10):1705-1715.3B.T.Richards,K.A.Young,
F.D.Francqueville,S.Sehr,M.R.Begley,H.N.G.Wadley,Response of ytterbium
disilicate-silicon environmental barrier coatings to thermal cycling in water
vapor,Acta Mater.,2016,106:1-14.]；And for Si/ mullite/rare earth silicate coating material system, in heat
In cyclic process, penetration of cracks superficial layer and mullite layer [4B.T.Richards, S.Sehr, F.de are found
Franqueville,M.R.Begley,H.N.G.Wadley,Fracture mechanisms of ytterbium
monosilicate environmental barrier coatings during cyclic thermal exposure,
Acta Materialia,vol.103,pp.448-460,2016.5B.T.Richards,M.R.Begley,and
H.N.G.Wadley,Mechanisms of ytterbium monosilicate/mullite/silicon coating
failure during thermal cycling in water vapor,J.Am.Ceram.Soc.,2015,98(12):
4066-4075.】。
Meanwhile the mullite coating of using plasma spraying technology preparation has following deficiency: (1) plasma spraying does not come
Stone coating contains more amorphous phase, and the hot environment of military service can make the amorphous phase crystallization (crystallization temperature about 1000 in coating
DEG C), to generate biggish volume change, cause to crack inside mullite coating, under the stability for leading to coating system
Drop；(2) there are decomposing phenomenons in spraying process for mullite, generate Al2O3Phase, and Al2O3Exist with mullite thermal expansion coefficient
Difference (mullite: 5-6 × 10-6K-1, Al2O3: 7.2 × 10-6K-1), it is concentrated in Thermal Cycling floating coat internal stress, corrosion
Property substance may be permeated by crackle coat inside, cause the destruction of coating system, the same stability for influencing coating system
【2B.T.Richards,H.N.G.Wadley,Plasma spray deposition of tri-layer
environmental barrier coatings.J.Eur.Ceram.Soc.,2014,34(12):3069-
3083.5B.T.Richards,M.R.Begley,and H.N.G.Wadley,Mechanisms of ytterbium
monosilicate/mullite/silicon coating failure during thermal cycling in water
vapor,J.Am.Ceram.Soc.,2015,98(12):4066-4075.6K.N.Lee,R.A.Miller,and
N.S.Jabocson,New generation of plasma-sprayed mullite coatings on silicon-
carbide,J.Am.Ceram.Soc.,1995,78(3):705-710】。
Summary of the invention
In view of the above-mentioned problems, the purpose of the present invention is to provide a kind of paintings of the rare earth silicate Environment Obstacles of resistance to crack extension
Layer and preparation method thereof.
On the one hand, the present invention provides a kind of rare earth silicate environment barrier coating, the rare earth silicate Environment Obstacles
Coating successively includes matrix, the adhesive layer positioned at described matrix surface, surface layer and between the adhesive layer and surface layer
Middle layer；The adhesive layer is Si layers, and the middle layer is Yb2Si2O7Layer, the surface layer are rare earth monosilicate Re2SiO5。
In the material system of rare earth silicate environment barrier coating provided by the invention, using Si as adhesive layer, (heat is swollen
Swollen coefficient is 3.5-4.5 × 10-6K-1), Yb2Si2O7As middle layer (3.7-4.5 × 10-6K-1), select thermal expansion coefficient to be higher than
The rare earth silicate Re of adhesive layer and middle layer2SiO5As main component as surface layer.Wherein Si adhesive layer and Yb2Si2O7In
The thermal expansion coefficient of interbed is less than basis material, by compression stress, and surface layer (rare earth monosilicate Re2SiO5) thermal expansion
Coefficient is larger, is stretched stress, this extend through coating system will not in Thermal Cycling in the crackle that surface layer generates
Yb2Si2O7Middle layer.Yb can be made full use of2Si2O7Thermal expansion coefficient is lower, has the advantages that high-temp plastic and rare earth silicic acid
Salt (Re2SiO5) excellent resistance to vapor corrosion performance combines, so that this system has good resistance to crack extension and anti-thermal shock
The characteristics of performance, can be further improved the protective performance of coating system.In addition, Si has high-temp plastic, and and rare earth silicon
The physical chemistry compatibility of hydrochlorate and silicon-based ceramic material is preferable, and the knot of rare earth silicate and silicon-based ceramic material can be improved
It closes.
Preferably, the rare earth monosilicate Re2SiO5Selected from Y2SiO5、Sc2SiO5、Gd2SiO5、Er2SiO5、Tm2SiO5、
Yb2SiO5、Lu2SiO5At least one of, preferably Yb2SiO5.The present invention is with Y2SiO5、Sc2SiO5、Gd2SiO5、Er2SiO5、
Tm2SiO5、Yb2SiO5、Lu2SiO5At least one of as main component be used as surface layer, selection rare earth monosilicate Re2SiO5
Thermal expansion coefficient is larger, especially Yb2SiO5With Yb2Si2O7Chemical composition it is similar, the two chemical compatibility is good, in conjunction with more causing
It is close.Therefore, with Yb2Si2O7Coating can be alleviated as intermediate layer material and apply the thermal stress between interlayer and coating and matrix
(concentrating that is, slowing down stress of the coat inside in Thermal Cycling), improves the resistance to crack extension ability of environment barrier coating
(that is, preventing through-wall crack in the propagation of middle layer), to finally improve its thermal shock resistance and service life.
Preferably, the adhesive layer with a thickness of 10~200 μm, preferably 10~100 μm.
Preferably, the middle layer with a thickness of 10~200 μm, in order to guarantee that there is coating system excellent anti-crack to expand
Malleability energy and thermal shock performance, preferably 30~200 μm.
Preferably, the surface layer with a thickness of 10~200 μm, preferably 30~200 μm.
Preferably, the overall thickness of the rare earth silicate Barrier Coatings is greater than 100 μm, preferably 100~500 μm.
Preferably, described matrix is SiC matrix, Si3N4Matrix, C/SiC matrices of composite material and SiC/SiC composite material
One of matrix.
On the other hand, the present invention provides a kind of preparation methods such as above-mentioned rare earth silicate Barrier Coatings, comprising:
(1) Si powder is sprayed on substrate material surface, obtains adhesive layer by using plasma spray coating method；
(2) using plasma spray coating method, by Yb2Si2O7Powder is sprayed on the matrix with adhesive layer, forms middle layer；
(3) using plasma spray coating method, by rare earth monosilicate Re2SiO5Powder is sprayed on adhesive layer and middle layer
On matrix, the rare earth silicate Barrier Coatings are obtained.
Preferably, the partial size of the Si powder is 20~100 μm, the Yb2Si2O7The partial size of powder is 20~100 μm, institute
State Yb2SiO5The partial size of powder is 20~100 μm.
Preferably, matrix is pre-processed, the pretreatment is that sandblasting is roughened, and blasting pressure is 0.1~0.6MPa.
Preferably, the parameter of the plasma spraying method includes: plasma gas Ar:35~55slpm, preferably 35
~48slpm；Powder carrier gas Ar:2~7slpm；Plasma gas H2: 5~15slpm, preferably 5~13slpm；Spraying away from
From: 90~200mm；Spray power: 30~50kw, preferably 30~45kw；Powder feeding rate: 10~35r/min.
Environment barrier coating of the invention have it is following the utility model has the advantages that
1. the coating that the present invention designs uses Yb2Si2O7It is the structure of superficial layer for middle layer and rare earth silicate, and it is existing
Single rare earth silicate coating is compared with rare earth silicate/mullite double ceramic coating system, has significant resistance to crack extension
Ability and excellent thermal shock resistance；
2. the Yb of plasma spray process preparation2Si2O7Coating as middle layer, have thermal expansion coefficient is low, amorphous phase is few,
The feature that objectionable impurities mutually lacks and high temperature stability performance is good；
3. it is uniform to spray state coating microstructure, it is well combined between each layer, no through-wall crack exists；
4. the present invention has simultaneously, simple process, at low cost, high-efficient, favorable repeatability, coating layer thickness are controllable, are suitble to scale
The advantages that production.
Detailed description of the invention
Fig. 1 is the Si/Yb prepared in embodiment 12Si2O7/Yb2SiO5The Cross Section Morphology figure of coating；
Fig. 2 is the Si/Yb prepared in embodiment 12Si2O7/Yb2SiO5Coating initial surface photomacrograph (a), thermal shock 40 times (b)
Surface photomacrograph；
Fig. 3 is the Si/Yb prepared in embodiment 12Si2O7/Yb2SiO5Coating thermal shock 40 times Cross Section Morphology figures；
Fig. 4 is the Si/Yb prepared in embodiment 22Si2O7/Yb2SiO5Coating initial surface photomacrograph (a), thermal shock 20 times
(b), the surface photomacrograph of thermal shock 30 times (c) and thermal shock 40 times (d)；
Fig. 5 is the Si/Yb prepared in embodiment 22Si2O7/Yb2SiO5Coating thermal shock 20 times Cross Section Morphology figures；
Fig. 6 is the Si/Yb prepared in embodiment 32Si2O7/Yb2SiO5Coating initial surface photomacrograph (a), thermal shock 20 times
(b), 30 times (c) and 40 times (d) surface photomacrographs；
Fig. 7 is the Si/Yb prepared in embodiment 42Si2O7/Y2SiO5Coating initial surface photomacrograph (a), thermal shock 20 times (b),
30 times (c) and 40 times (d) surface photomacrographs；
Fig. 8 is the Si/Yb prepared in embodiment 52Si2O7/Er2SiO5Coating initial surface photomacrograph (a), thermal shock 20 times
(b), 30 times (c) and 40 times (d) surface photomacrographs；
Fig. 9 is the Si/Yb prepared in embodiment 62Si2O7/Gd2SiO5Coating initial surface photomacrograph (a), thermal shock 20 times
(b), 30 times (c) and 40 times (d) surface photomacrographs；
Figure 10 is the Si/Yb prepared in comparative example 12SiO5Coating initial surface photomacrograph (a), thermal shock 35 (b) and thermal shocks
40 times (c) surface photomacrographs；
Figure 11 is the Si/Yb prepared in comparative example 12SiO5Coating thermal shock 40 times Cross Section Morphology figures.
Specific embodiment
The present invention is further illustrated below by way of following embodiments, it should be appreciated that following embodiments are merely to illustrate this
Invention, is not intended to limit the present invention.
Rare earth silicate environment barrier coating (environment barrier coating) compact structure of the invention, between coating and coating
It is good with the binding performance of matrix, there is significant resistance to crack extension performance.The environment barrier coating includes viscous in addition to matrix
Layer, middle layer and surface layer three-decker are tied, referring to Fig. 1.Wherein, the adhesive layer of the environment barrier coating refers to direct with matrix
One layer of contact, the middle layer refer to one layer directly contacted with adhesive layer, and surface layer refers to one farthest with adhesive layer distance
Layer.The environment barrier coating is suitable for SiC matrix, Si3N4Matrix, C/SiC matrices of composite material or SiC/SiC composite material base
Body.This system is with Yb2Si2O7As middle layer, Yb can be made full use of2Si2O7Lower (3.7-4.5 × 10 of thermal expansion coefficient-6K-1), have the advantages that high-temp plastic so that this system has the characteristics that resistance to crack extension；Meanwhile with rare earth monosilicate
(Re2SiO5, such as: Y2SiO5、Sc2SiO5、Gd2SiO5、Er2SiO5、Tm2SiO5、Yb2SiO5、Lu2SiO5In it is at least one kind of) make
For outer layer, it can be further improved the high-temperature resistant water steam corrosion performance of coating system, prolong the service life.
In the present invention, bonding layer material Si, intermediate layer material Yb2Si2O7, surface material is rare earth monosilicate
((Re2SiO5, such as: Y2SiO5、Sc2SiO5、Gd2SiO5、Er2SiO5、Tm2SiO5、Yb2SiO5、Lu2SiO5At least one of)
Powder.Yb in the present invention2Si2O7Thermal expansion coefficient (3.7-4.5 × 10-6K-1) and (3.5-4.5 × 10 adhesive layer Si-6K-1) connect
Closely, and it is slightly less than thermal expansion coefficient (4.5-5.5 × 10 of the basis materials such as SiC, SiC/SiC-6K-1), it is substantially less than simultaneously
Rare earth monosilicate (Re2SiO5, such as: Y2SiO5(5-6×10-6K-1)、Sc2SiO5(5-6×10-6K-1)、Gd2SiO5(7-11
×10-6K-1)、Er2SiO5(7-8×10-6K-1)、Tm2SiO5(7-8×10-6K-1)、Yb2SiO5(7-8×10-6K-1)、Lu2SiO5
(5-7×10-6K-1) etc.) and thermal expansion coefficient.When the thermal expansion coefficient of coating is lower than basis material, in Thermal Cycling,
Coating is by compression stress；Conversely, when the thermal expansion coefficient of coating is higher than when basis material, in Thermal Cycling, coating
It is stretched stress.The thickness of every layer of material of the rare earth silicate environment barrier coating structure can be 10~200 μm.Institute
The overall thickness for applying rare earth silicate environment barrier coating is stated greater than 100 μm, further preferably 100 μm~500 μm.Wherein, it glues
The thickness for tying layer (Si layers) is preferably 10~100 μm.The thickness of the middle layer of environment barrier coating is preferably 30~200 μm.Ring
The thickness of the surface layer of border Barrier Coatings is preferably 30~200 μm.
Coating in the present invention, including adhesive layer, middle layer and surface layer are prepared by plasma spray technology.Below
Illustratively illustrate the preparation method of rare earth silicate environment barrier coating provided by the invention.
The preparation of powder: by Si powder, Yb2Si2O7Powder and rare earth monosilicate Re2SiO5Powder carries out at sieving respectively
Reason, obtains the powder of appropriate particle size, each layer powder is prepared respectively.The Si powder, Yb2Si2O7Powder and rare earth monosilicate
Re2SiO5The partial size of powder can be 20~100 μm.
The pretreatment of matrix, that is, spraying pretreatment.Specifically, matrix surface is pre-processed, sandblasting roughening.Institute
It states matrix and is selected from SiC, Si3N4, C/SiC or SiC/SiC composite material.Wherein, pre-treatment step includes: sandblasting roughening, sandblasting pressure
Power is 0.1~0.6MPa.
The preparation of adhesive layer in environment barrier coating.Specifically, using plasma spray coating method, in substrate material surface
Prepare adhesive layer (for example, Si layers).Prepare adhesive layer, the parameter of the plasma spray process can include: plasma gas
Body Ar:35~48slpm；Powder carrier gas Ar:2~7slpm；Plasma gas H2: 5~13slpm；Spray distance: 90~
200mm；Spray power: 30~45kw；Powder feeding rate: 10~35r/min.
The preparation of middle layer in environment barrier coating.Using plasma spray coating method, by Yb obtained2Si2O7Powder spraying
On the matrix with adhesive layer (for example, Si layers).Wherein, the parameter of plasma spray process can include: plasma gas
Body Ar:35~55slpm；Powder carrier gas Ar:2~7slpm；Plasma gas H2: 5~15slpm；Spray distance: 90~
200mm；Spray power: 30~50kw；Powder feeding rate: 10~35r/min.
The preparation of surface layer in environment barrier coating.Using plasma spray coating method, by rare earth monosilicate powder obtained
It is sprayed on adhesive layer (Si layers) and middle layer (Yb2Si2O7Layer) matrix on, that is, obtain the environment barrier coating.Wherein,
The parameter of plasma spray process includes: plasma gas Ar:35~55slpm；Powder carrier gas Ar:2~7slpm；Deng from
Daughter gas H2: 5~15slpm；Spray distance: 90~200mm；Spray power: 30~50kw；Powder feeding rate: 10~35r/
min。
The present invention passes through the environment barrier coating material system for rationally designing and preparing new construction, can alleviate coating and apply
Thermal stress between interlayer and coating and matrix, improves the resistance to crack extension ability of environment barrier coating, and it is anti-finally to improve it
Thermal shock performance and service life.
Enumerate embodiment further below with the present invention will be described in detail.It will similarly be understood that following embodiment is served only for this
Invention is further described, and should not be understood as limiting the scope of the invention, those skilled in the art is according to this hair
Some nonessential modifications and adaptations that bright above content is made all belong to the scope of protection of the present invention.Following examples are specific
Technological parameter etc. is also only an example in OK range, i.e. those skilled in the art can be done properly by the explanation of this paper
In the range of select, and do not really want to be defined in hereafter exemplary specific value.
Embodiment 1:
Si/Yb is prepared in SiC matrix2Si2O7/Yb2SiO5Coating structure, the coating structure are made of 3 layer materials, from internal layer
To outer layer, its composition is respectively as follows: adhesive layer: Si；Middle layer: Yb2Si2O7；Surface layer: Yb2SiO5。
The step of prepared by coating is as follows:
Step 1: by Si, Yb2Si2O7And Yb2SiO5Powder carries out sieving processing respectively, selects 20~100 μm of partial size of powder,
Each layer powder is prepared respectively；
Step 2: sandblasting pretreatment, blasting pressure 0.5MPa are carried out to SiC matrix surface；
Step 3: using plasma spray system (A-2000, Sulzer Metco AG, Switzerland), above-mentioned partial size is closed
Suitable Si powder is sprayed on pretreated matrix, and spraying parameter is shown in Table 1.The coating layer thickness is 50 μm；
Table 1 is atmospheric plasma spraying Si coating process parameter:
| Plasma gas Ar | 40slpm | Powder carrier gas Ar | 4slpm |
| Plasma gas H2 | 7slpm | Spray distance | 130mm |
| Spray power | 37kw | Powder feeding rate | 20rpm |
* slpm: standard liter/min；
Step 4: using plasma spray system (A-2000, Sulzer Metco AG, Switzerland), above-mentioned partial size is closed
Suitable Yb2Si2O7Powder is sprayed on the basis material with Si adhesive layer, and spraying parameter is shown in Table 2.The coating layer thickness
It is 100 μm；
Step 5: using plasma spray system (A-2000, Sulzer Metco AG, Switzerland), above-mentioned partial size is closed
Suitable Yb2SiO5Powder is sprayed on Si adhesive layer and Yb2Si2O7On the basis material of middle layer, spraying parameter is shown in Table
2.The coating layer thickness is 100 μm；
Table 2 is plasma spray coating Yb2Si2O7With Yb2SiO5 coating process parameter:
| Plasma gas Ar | 43slpm | Powder carrier gas Ar | 5slpm |
| Plasma gas H2 | 12slpm | Spray distance | 130mm |
| Spray power | 45kw | Powder feeding rate | 15rpm |
* slpm: standard liter/min；
Preparation gained coating cross sections pattern is as shown in Figure 1, coating is the layer structure of typical plasma spray coating, microstructure
Uniformly, interlayer is applied to be tightly combined.
Water quenching thermal shock method is taken to examine coating, condition are as follows: sample keeps the temperature 20min in 1400 DEG C of tube furnaces,
It is then placed in chilling in 25 DEG C or so of water.Fig. 2 is before sample thermal shock (in Fig. 2 (a)) and after thermal shock 40 times (in Fig. 2 (b))
Macro morphology.It can be seen that, although fracture occurs in matrix, coating keeps complete, sample surfaces after 40 thermal shocks experiment
Do not occur peeling phenomenon.Fig. 3 is the Cross Section Morphology after sample thermal shock 40 times, it can be seen that the longitudinal crack generated during thermal shock
Although running through Yb2SiO5Surface layer, but terminate at Yb2Si2O7Middle layer；And Yb2SiO5Surface layer and Yb2Si2O7Middle layer combines
Well, illustrate in coating system designed by the present invention, Yb2Si2O7It is ideal intermediate layer material, coating has good anti-
Crack propagation performance and thermal shock resistance.
Embodiment 2:
The difference of the present embodiment and coating described in embodiment 1 is: matrix used material is C/SiC matrices of composite material.Its
Remaining same embodiment 1.
As can be seen that coating keeps complete, and sample surfaces do not peel off after 40 thermal shocks experiment (T=1400 DEG C)
Phenomenon (in Fig. 4 (d)).Fig. 5 is the Cross Section Morphology after sample thermal shock 20 times, it can be seen that the longitudinal crack generated during thermal shock
Although running through Yb2SiO5Surface layer, but terminate at Yb2Si2O7Middle layer；And Yb2SiO5Surface layer and Yb2Si2O7Middle layer combines
Well, illustrate in coating system designed by the present invention, Yb2Si2O7It is ideal intermediate layer material, coating has good anti-
Crack propagation performance and thermal shock resistance.
Embodiment 3:
The difference of the present embodiment and coating described in embodiment 1 is: matrix used material is SiC/SiC matrices of composite material.
Remaining is the same as embodiment 1.
As shown in Figure 6, it can be seen that after 40 thermal shocks experiment (T=1400 DEG C), coating keeps complete, and sample surfaces are not
Occur peeling phenomenon (in Fig. 6 (d)).The longitudinal crack generated during thermal shock terminates at Yb2Si2O7Middle layer.Illustrate the present invention
Designed coating system has good resistance to crack extension performance and thermal shock resistance.
Embodiment 4:
The difference of the present embodiment and coating described in embodiment 1 is: matrix used material is C/SiC matrices of composite material, face
Layer material is Y2SiO5.Si/Yb is prepared on C/SiC matrix2Si2O7/Y2SiO5Coating.
As shown in Figure 7, it can be seen that after 40 thermal shocks experiment (T=1400 DEG C), coating keeps complete, and sample surfaces are not
Occur peeling phenomenon (in Fig. 7 (d)).The longitudinal crack generated during thermal shock terminates at Yb2Si2O7Middle layer.Illustrate the present invention
Designed coating system has good resistance to crack extension performance and thermal shock resistance.
Embodiment 5:
The difference of the present embodiment and coating described in embodiment 4 is: surface material Er2SiO5.Made on C/SiC matrix
Standby Si/Yb2Si2O7/Er2SiO5Coating.
As shown in Figure 8, it can be seen that after 40 thermal shocks experiment (T=1400 DEG C), coating keeps complete, and sample surfaces are not
Occur peeling phenomenon (in Fig. 8 (d)).The longitudinal crack generated during thermal shock terminates at Yb2Si2O7Middle layer.Illustrate the present invention
Designed coating system has good resistance to crack extension performance and thermal shock resistance.
Embodiment 6:
The difference of the present embodiment and coating described in embodiment 4 is: surface material Gd2SiO5.Made on C/SiC matrix
Standby Si/Yb2Si2O7/Gd2SiO5Coating.
As shown in Figure 9, it can be seen that after 40 thermal shocks experiment (T=1400 DEG C), coating keeps complete, and sample surfaces are not
Occur peeling phenomenon (in Fig. 9 (d)).The longitudinal crack generated during thermal shock terminates at Yb2Si2O7Middle layer.Illustrate the present invention
Designed coating system has good resistance to crack extension performance and thermal shock resistance.
Comparative example 1:
Using plasma spray coating process condition identical in embodiment 1, Si/Yb is prepared in SiC matrix2SiO5Coating structure: i.e.
Si is sprayed as adhesive layer, then sprays single Y b2SiO5Coating, with a thickness of 100 μm.
The thermal shock experiment of the same terms is carried out to gained coating.It can be seen that 35 times (in Figure 10 after (b), coating goes out for thermal shock
Existing obscission.After thermal shock 40 times (in Figure 10 (c)), coating has falling off for larger area.After Figure 11 is sample thermal shock 40 times
Cross Section Morphology, it can be seen that the longitudinal crack generated during thermal shock runs through Yb2SiO5Layer, and Si adhesive layer and Yb2SiO5It applies
Crackle is also produced between layer.The coating performance can not show a candle to Si/Yb obtained in embodiment 12Si2O7/Yb2SiO5Coating.
Claims (11)
1. a kind of rare earth silicate environment barrier coating, which is characterized in that the rare earth silicate environment barrier coating successively wraps
Include matrix, the adhesive layer positioned at described matrix surface, surface layer and the middle layer between the adhesive layer and surface layer；
The adhesive layer is Si layers, and the middle layer is Yb2Si2O7Layer, the surface layer are rare earth monosilicate Re2SiO5。
2. rare earth silicate Barrier Coatings according to claim 1, which is characterized in that the rare earth monosilicate Re2SiO5
Selected from Y2SiO5、Sc2SiO5、Gd2SiO5、Er2SiO5、Tm2SiO5、Yb2SiO5、Lu2SiO5At least one of, preferably
Yb2SiO5。
3. rare earth silicate Barrier Coatings according to claim 1 or 2, which is characterized in that the adhesive layer with a thickness of
10~200 μm, preferably 10~100 μm.
4. rare earth silicate Barrier Coatings according to any one of claim 1-3, which is characterized in that the middle layer
With a thickness of 10~300 μm, preferably 30~200 μm.
5. rare earth silicate Barrier Coatings described in any one of -4 according to claim 1, which is characterized in that the thickness of the surface layer
Degree is 10~300 μm, preferably 30~200 μm.
6. rare earth silicate Barrier Coatings according to any one of claims 1-5, which is characterized in that the rare earth silicic acid
The overall thickness of salt Barrier Coatings is greater than 100 μm, preferably 100~500 μm.
7. rare earth silicate Barrier Coatings according to claim 1 to 6, which is characterized in that described matrix is
SiC matrix, Si3N4One of matrix, C/SiC matrices of composite material and SiC/SiC matrices of composite material.
8. a kind of preparation method of the rare earth silicate Barrier Coatings as described in any one of claim 1-7, which is characterized in that packet
It includes:
(1) Si powder is sprayed on substrate material surface, obtains adhesive layer by using plasma spray coating method；
(2) using plasma spray coating method, by Yb2Si2O7Powder is sprayed on the matrix with adhesive layer, forms middle layer；
(3) using plasma spray coating method, by rare earth monosilicate Re2SiO5Powder is sprayed on adhesive layer and middle layer
On matrix, the rare earth silicate Barrier Coatings are obtained.
9. preparation method according to claim 8, which is characterized in that the partial size of the transition zone raw material Si powder be 20~
100 μm, middle layer raw material Yb2Si2O7The partial size of powder is 20~100 μm, surface layer raw material rare earth monosilicate
Re2SiO5The partial size of powder is 20~100 μm.
10. preparation method according to claim 8 or claim 9, which is characterized in that pre-process matrix, the pretreatment
For sandblasting roughening, blasting pressure is 0.1~0.6 MPa.
11. the preparation method according to any one of claim 8-10, which is characterized in that the ginseng of the plasma spraying method
Number includes: the slpm of plasma gas Ar:35~55, preferably 35~48slpm；Powder carrier gas Ar:2~7 slpm；Deng
Plasma gas H2: 5~15 slpm, preferably 5~13slpm；Spray distance: 90~200 mm；Spray power: 30~50
Kw, preferably 30~45kw；Powder feeding rate: 10~35 r/min.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110330353A (en) * | 2019-08-15 | 2019-10-15 | 中南大学 | A kind of SiCf/ SiC ceramic matrix composite material burner inner liner and its automation preparation method |
| CN111233498A (en) * | 2020-03-06 | 2020-06-05 | 中南大学 | Environmental barrier coating and preparation method and application thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030138641A1 (en) * | 2001-12-28 | 2003-07-24 | Kyocera Corporation | Corrosion-resistant ceramics |
| US20050112381A1 (en) * | 2003-11-21 | 2005-05-26 | Honeywell International Inc. | Oxidation barrier coatings for silicon based ceramics |
| CN101024324A (en) * | 2005-12-09 | 2007-08-29 | 通用电气公司 | Environment barrier coating for a component and method for fabricating the same |
| JP2007254219A (en) * | 2006-03-24 | 2007-10-04 | Kyocera Corp | Corrosion-resistant ceramic member |
| CN106435443A (en) * | 2016-09-30 | 2017-02-22 | 广东省新材料研究所 | Preparation method of environmental barrier coating layer |
| CN106966762A (en) * | 2016-06-03 | 2017-07-21 | 北京航空航天大学 | A kind of preparation method of aero-engine hot junction component Environmental Barrier Coatings on Si-based Ceramics |
-
2017
- 2017-09-07 CN CN201710801357.3A patent/CN109468568B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030138641A1 (en) * | 2001-12-28 | 2003-07-24 | Kyocera Corporation | Corrosion-resistant ceramics |
| US20050112381A1 (en) * | 2003-11-21 | 2005-05-26 | Honeywell International Inc. | Oxidation barrier coatings for silicon based ceramics |
| CN101024324A (en) * | 2005-12-09 | 2007-08-29 | 通用电气公司 | Environment barrier coating for a component and method for fabricating the same |
| JP2007254219A (en) * | 2006-03-24 | 2007-10-04 | Kyocera Corp | Corrosion-resistant ceramic member |
| CN106966762A (en) * | 2016-06-03 | 2017-07-21 | 北京航空航天大学 | A kind of preparation method of aero-engine hot junction component Environmental Barrier Coatings on Si-based Ceramics |
| CN106435443A (en) * | 2016-09-30 | 2017-02-22 | 广东省新材料研究所 | Preparation method of environmental barrier coating layer |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110330353A (en) * | 2019-08-15 | 2019-10-15 | 中南大学 | A kind of SiCf/ SiC ceramic matrix composite material burner inner liner and its automation preparation method |
| US11591267B2 (en) | 2019-08-15 | 2023-02-28 | Central South University | Automated preparation method of a SiCf/SiC composite flame tube |
| CN111233498A (en) * | 2020-03-06 | 2020-06-05 | 中南大学 | Environmental barrier coating and preparation method and application thereof |
| 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 |
| CN114763598A (en) * | 2021-01-13 | 2022-07-19 | 中国科学院上海硅酸盐研究所 | Long-life environmental barrier coating and preparation method thereof |
| CN114763598B (en) * | 2021-01-13 | 2024-03-08 | 中国科学院上海硅酸盐研究所 | Long-life environmental barrier coating and preparation method thereof |
| CN113278909A (en) * | 2021-05-25 | 2021-08-20 | 广东省科学院新材料研究所 | Thermal-environmental barrier coating and preparation method and application thereof |
| CN113278909B (en) * | 2021-05-25 | 2023-02-17 | 广东省科学院新材料研究所 | Thermal-environmental barrier coating and preparation method and application thereof |
| CN113463008A (en) * | 2021-06-29 | 2021-10-01 | 中国科学院上海硅酸盐研究所 | Crack expansion resistant environmental barrier coating and preparation method thereof |
| CN114276169A (en) * | 2021-12-30 | 2022-04-05 | 广东省科学院新材料研究所 | Self-healing high-density environmental barrier coating and preparation method and application thereof |
| CN115369348A (en) * | 2022-08-03 | 2022-11-22 | 中国科学院上海硅酸盐研究所 | Environmental barrier coating with good high-temperature stability and preparation method thereof |
| CN115386823A (en) * | 2022-08-03 | 2022-11-25 | 中国科学院上海硅酸盐研究所 | High-temperature steam corrosion and CMAS corrosion resistant environmental barrier coating and preparation method thereof |
| CN115369348B (en) * | 2022-08-03 | 2024-02-06 | 中国科学院上海硅酸盐研究所 | Environment barrier coating with good high-temperature stability and preparation method thereof |
| CN115386823B (en) * | 2022-08-03 | 2024-03-08 | 中国科学院上海硅酸盐研究所 | Environmental barrier coating capable of resisting high-temperature vapor corrosion and CMAS corrosion and preparation method thereof |
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