CN114457307A - CMAS bonding-resistant bionic thermal barrier coating and preparation method thereof - Google Patents

CMAS bonding-resistant bionic thermal barrier coating and preparation method thereof Download PDF

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CN114457307A
CN114457307A CN202210060115.4A CN202210060115A CN114457307A CN 114457307 A CN114457307 A CN 114457307A CN 202210060115 A CN202210060115 A CN 202210060115A CN 114457307 A CN114457307 A CN 114457307A
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cmas
coating
thermal barrier
barrier coating
preparation
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CN114457307B (en
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宋文佳
郭洪波
徐惠彬
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Beihang University
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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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/24—Vacuum evaporation
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/02—Pretreatment of the material to be coated
    • C23C14/028—Physical treatment to alter the texture of the substrate surface, e.g. grinding, polishing
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/0605—Carbon
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • C23C14/083—Oxides of refractory metals or yttrium
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/24—Vacuum evaporation
    • C23C14/28—Vacuum evaporation by wave energy or particle radiation
    • C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/58—After-treatment
    • C23C14/5806—Thermal treatment
    • C23C14/5813—Thermal treatment using lasers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention discloses a CMAS bonding resistant bionic thermal barrier coating and a preparation method thereof, wherein the preparation method comprises the following steps: carrying out sand blasting treatment on the surface of the ceramic matrix; preparing yttria-stabilized zirconia target and powder, wherein Y2O3At 8 wt.%; preparing an yttria-stabilized zirconia coating with a columnar crystal structure on the surface of a substrate by adopting electron beam physical vapor deposition (EB-PVD); scanning the surface of the yttria-stabilized zirconia coating by using femtosecond laser; using a carbon evaporation coating instrument to perform the coating on the surfaceAnd carrying out carbon spraying treatment on the yttria-stabilized zirconia coating after the femtosecond laser treatment. According to the method, the surface structure of the ceramic coating is changed into a lotus-shaped micro-nano structure through laser modification, and the carbon layer is sprayed, so that the adhesion and wettability of CMAS on the ceramic coating are reduced, CMAS particles with different particle sizes can not wet the coating and permeate into the surface of the coating, and the CMAS corrosion resistance is good.

Description

CMAS bonding-resistant bionic thermal barrier coating and preparation method thereof
Background
Dust in the atmosphere (including sand, dust and volcanic ash, etc., whose main composition is CaO-MgO-Al)2O3-SiO2CMAS for short) presents the greatest challenge to aviation safety in terms of its destructive effects on the aircraft engineAnd (6) sounding. The melting point of the CMAS particles is about 1100 ℃, which is far lower than the flame temperature (2000 ℃) of a combustion chamber in an aircraft engine. Therefore, when entering the combustion chamber of the aircraft engine along with compressed air, the foreign particles can be rapidly melted in the hot engine and adhere to the surface of the hot end component, thereby blocking surface air film cooling holes, affecting cooling, reducing the thermodynamic performance and mechanical performance of the coating, even causing early peeling failure of Thermal Barrier Coatings (TBCs), and seriously threatening the service safety and service life of the aircraft engine. As turbine engines get higher thrust-to-weight ratios and turbine forward inlet temperatures get higher and higher, the CMAS problem becomes more severe.
Thermal Barrier Coatings (TBCs) applied to hot end components of aircraft engines are a surface protection technology for compounding ceramic materials with metal substrates in the form of coatings, and are used for blocking heat and protecting bottom high-temperature alloys. The structure is generally composed of a ceramic topcoat that provides thermal insulation, a metallic bond coat that resists oxidation, and a thermally grown oxide layer formed on the bond coat due to oxidation. Wherein the ceramic layer material is YSZ (6-8 wt.% Y)2O3Partially stabilized ZrO2). At present, the technologies for preparing the thermal barrier coating mainly comprise electron beam-vapor deposition (EB-PVD for short) and atmospheric plasma spraying (APS for short).
The failure of TBCs under the action of CMAS is mainly reflected in two aspects, one is that the thermochemical reaction between TBCs and CMAS causes the reduction of high-temperature stability and the premature phase transition instability of TBCs and CMAS, such as SiO in CMAS2Will dissolve Y in YSZ2O3And CaO replaces Y2O3As ZrO2The stabilizer of (1). Secondly, the physical thermal stress between the TBCs and the CMAS is not matched, for example, the CMAS particle infiltration and the thermal stress cause the TBCs ceramic layer delamination and the CMAS particle densification on the coating surface generates the shrinkage stress, so that the internal thermal stress of the ceramic layer is increased in the thermal cycle process, and finally the coating delamination cracks and the layer-by-layer peeling failure are caused.
On the basis of clear correlation failure mechanism, domestic and foreign scholars try to develop different TBCs coatings to protect against CMAS. Currently, there are three main ways CMAS corrosion protection measures:
(1) physical isolation CMAS melt infiltration prevention method: by adding an inert, dense impermeable coating that is non-reactive with CMAS, the CMAS melt is directly isolated from the thermal barrier coating by the physical properties of the material, thereby blocking CMAS melt penetration. The method comprises the following steps: inert blocking layer design (metal Pd-Ag protective coating), coating surface layer densification, namely surface preparation of a-Al2O3The compact protective layer plays a physical role in blocking the attachment and infiltration of CMAS particles. The technical problems exist that the thermal expansion coefficients of the system are not matched, so that microcracks and pores of the coating are enlarged, cracking and peeling are easily caused due to large thermal stress in the service process, and the protection effect is poor;
(2) chemical reaction CMAS melt infiltration prevention method: by coating one or more layers of novel thermal barrier coatings or doping different elements into the existing YSZ coatings, and by changing the phase composition of CMAS permeating into the surface layer of the coatings, the rapid crystallization of CMAS melt is promoted, and the continuous permeation of the subsequent CMAS is delayed. The chemical coating comprises: perovskite (SrZrO)3Or BaZrO3) Rare earth zirconates (Gd)2Zr2O7And La2Zr2O7) And rare earth phosphates (RePO)4And Re ═ rare earth element). The technical problem is that during the reaction of the chemical protective layer, part of the molten CMAS melt can still permeate into the coating through cracks and holes, and meanwhile, as the thickness of the CMAS melt is continuously increased, the thermal stress is enhanced, so that the service life of the coating is reduced;
(3) coating structure modification CMAS melt infiltration prevention method: by changing the microstructure of the TBCs surface layer, the contact area of the CMAS melt and the coating surface is reduced, and the cohesiveness of the CMAS melt is reduced; by changing the microstructure of YSZ columnar crystal on the surface layer, the time for CMAS to permeate inwards is prolonged, and the goal of delaying or inhibiting the CMAS melt permeation behavior is achieved. The coating structure modification method comprises the following steps: laser machining and plasma physical vapor deposition. The technical problem is that the CMAS melt is still adhered to the surface of the coating, and the thermal stress is continuously increased along with the increase of the penetration depth, so that the service life of the coating is reduced;
however, whatever the mechanism of the physical and chemical reaction between the trigger coating and the CMAS melt, the CMAS melt has adhered to and penetrated into the TBCs coating and continues to cause destructive effects. Therefore, the CMAS melt adhesion on the TBCs surface is simply and economically reduced, the CMAS melt resistance of the thermal barrier coating is greatly improved, and the CMAS melt adhesion prevention method has important significance on coating development and safe flight in the whole aviation industry, but no related report on preparation of the lotus leaf bionic coating and a CMAS melt complete non-adhesion function is provided at present.
Disclosure of Invention
The invention provides a coating material with a lotus leaf bionic structure and a preparation method aiming at the defects of the prior art, and provides a thermal barrier coating (ZrO) prepared by using femtosecond laser surface modification EB-PVD (electron beam-physical vapor deposition)2+8wt.％Y2O3) The surface is prepared to have a micro-nano structure similar to lotus leaves, and the coating has good CMAS melt adhesion resistance through carbon spraying treatment, so that the problem of corrosion of the CMAS melt in the coating is fundamentally solved. The invention adopts the following technical scheme:
a preparation method of a CMAS bonding resistant bionic thermal barrier coating comprises the following steps:
step 1: carrying out sand blasting treatment on the surface of the ceramic matrix;
step 2: preparing a yttria-stabilized zirconia target, wherein Y2O38 wt.%;
and step 3: preparing an yttria-stabilized zirconia coating with a columnar crystal structure on the surface of a substrate by adopting electron beam physical vapor deposition (EB-PVD);
and 4, step 4: scanning the surface of the yttria-stabilized zirconia coating by using femtosecond laser;
and 5: and carrying out carbon spraying treatment on the yttria-stabilized zirconia coating subjected to the femtosecond laser treatment by using a carbon evaporation coating instrument.
Further, in the step 1, the sand blasting treatment specifically includes: the sand blasting medium is 100-sand 200-mesh white corundum, the sand blasting pressure is 0.15-0.4 MPa, and the sand blasting distance is 70-100 mm.
Further, the step 2 specifically comprises: 8 wt.% Y2O3And ZrO2According toMixing the components in a mass ratio, and synthesizing the yttria-stabilized zirconia target material with the mass fraction of 8 wt% by a high-temperature solid phase method, wherein the synthesis temperature is 1400-1600 ℃.
Further, in the step 3, the process parameters of the EB-PVD are as follows: the pressure of the vacuum chamber in the deposition process is less than 1.0 x 10-2Pa, the heating current of the target material is 1-1.5A, the voltage of an electron gun is 18-60 kV, the heating temperature of the workpiece is 950-1000 ℃, and the rotating speed of the sample is 12-20 rpm.
Further, in the step 4, the femtosecond laser processing parameters are as follows: the femtosecond laser wavelength is 800nm, the pulse width is 65fs, the repetition frequency is 1kHz, and the single pulse energy is 2-5J/cm2The spot focusing diameter is 42 μm, the processing path is a broken line type, the transverse scanning speed is 400-12000 μm/s, the coincidence degree of the corresponding transverse axis adjacent spots is 50-100%, the longitudinal scanning speed is a fixed value 25000 μm/s, and the coincidence degree of the longitudinal axis adjacent spots is 0, as shown in fig. 1. The contact ratio of adjacent light spots is an important process parameter, the larger the contact ratio of the light spots is, the larger the energy absorbed by the coating in unit time and space is, the surface of the coating can be quickly gasified to form a micron-sized convex structure equivalent to a lotus leaf, and meanwhile, nanoparticles are generated in the gasification process, as shown in fig. 2.
Further, the step 5 specifically includes: the sample chamber was flushed with argon, 1.0X 10-2Under the mbar pressure, the carbon filament is evaporated and a carbon film with the thickness of 10-100nm is deposited on the coating surface of the micron-sized protrusions and the nano-particles obtained after the laser surface treatment, and after carbon spraying, the lotus-leaf-shaped micro-nano structure is not affected at all, the activation energy of the coating surface can be reduced, and the CMAS-resistant adhesive property of the coating is enhanced.
The CMAS bonding resistant bionic thermal barrier coating is prepared by the preparation method.
Further, the surface of the thermal barrier coating is of a lotus leaf bionic micro-nano structure.
Further, the thermal barrier coating has resistance to adhesion of millimeter-sized CMAS particles and resistance to wetting by micron-sized CMAS particles.
Compared with the prior art, the invention has the advantages that:
according to the invention, the surface structure of the ceramic coating is changed into a lotus-shaped micro-nano structure through laser modification, and the carbon layer is sprayed, so that the cohesiveness and wettability of CMAS on the ceramic coating are reduced, CMAS particles with different particle sizes can not wet the coating and permeate the surface of the coating, the CMAS coating has good CMAS corrosion resistance, and the specific advantages are as follows:
(1) according to the invention, femtosecond laser modification is utilized, and a lotus-leaf-like micro-nano structure is obtained on the surface of the coating by controlling the contact ratio of adjacent light spots of the laser, so that the adhesion and wettability of the CMAS-resistant particles are improved;
(2) according to the invention, on the basis of obtaining the lotus-like micro-nano structure, the carbon layer is sprayed on the surface, and due to the layered microstructure of the carbon, Van der Waals bonds with smaller interfacial energy further reduce the surface activation energy of the coating, and improve the adhesion and wettability of the CMAS-resistant particles;
(3) the bionic thermal barrier coating provided by the invention is simple in preparation process, easy to prepare and high in repeatability. The prepared bionic thermal barrier coating has excellent millimeter-level CMAS particle adhesion resistance and micron-level CMAS particle wettability resistance.
Drawings
Fig. 1 is a schematic diagram of coincidence degree of a scanning path and a light spot in a femtosecond laser processing process.
FIG. 2 is a schematic diagram of the generation of a coating micro-nano structure in the femtosecond laser processing process.
FIG. 3 shows the original Al2O3The micro-morphology of the cross section of the YSZ thermal barrier coating prepared by EB-PVD on the surface.
FIG. 4 shows the surface micro-and nano-structures of the EB-PVD thermal barrier coating after femtosecond laser processing in example 1.
FIG. 5 shows the surface non-wettability and non-caking property of the EB-PVD thermal barrier coating after femtosecond laser processing and carbon spraying of the macro-millimeter CMAS particles in example 1.
FIG. 6 shows the surface structure and the wettability of millimeter CMAS particles for the green EB-PVD thermal barrier coating of example 1.
FIG. 7 shows the surface non-wettability of the EB-PVD thermal barrier coating after femtosecond laser processing of the micro-scale CMAS particles in example 2.
FIG. 8 shows the surface wettability of the micro-scale CMAS particles on the original EB-PVD thermal barrier coating in example 2.
Detailed Description
The invention is described in further detail below with reference to the figures and examples of the specification.
Example 1
(1) Taking Al2O3The plate (10X 12X 1.5mm) had a purity of 99.7% and was subjected to sand blasting. Wherein the sand blasting medium is 150 meshes of white corundum, the sand blasting pressure is 0.2MPa, and the sand blasting distance is 90 mm.
(2) Al after sand blasting2O3Preparing yttria partially stabilized zirconia (ZrO) on plate by adopting electron beam physical vapor deposition2+8wt.％Y2O3) Thermal barrier coating, the pressure of vacuum chamber in the deposition process is less than 1.0 x 10-2Pa, the heating current of the target material is 1.5A, the voltage of the electron gun is 40kV, the heating temperature of the workpiece is 1000 ℃, the rotating speed of the sample is 12rpm, and the thickness of the obtained thermal barrier coating is 450 mu m, as shown in figure 3.
(3) And carrying out ultrasonic cleaning on the prepared thermal barrier coating to remove surface stains and impurities.
(4) Femtosecond laser irradiation: for thermal barrier coating (ZrO)2+8wt.％Y2O3) The surface of the sample is subjected to surface laser modification by adopting a Ti sapphire laser with the rated power of 28mW, the femtosecond laser wavelength is 800nm, the pulse width is 65fs, the repetition frequency is 1kHz, the spot size is 42 mu m, and the single pulse energy is 4.09J/cm2And adopting a broken line type processing path, wherein the transverse scanning speed is 400 mu m/s, the contact ratio of adjacent light spots on the transverse axis is 98%, the longitudinal scanning speed is 25000 mu m/s, and the contact ratio of adjacent light spots on the longitudinal axis is 0.
(5) The treated EB-PVD thermal barrier coating had a pyramidal shape with an average width of 18.75 μm, an average height of 28 μm and a surface distribution of nano-spheres with an average particle size of 235nm as shown in FIG. 4.
(6) The sample chamber was flushed with argon at 1.0X 10-2And spraying a carbon layer with the thickness of 20nm on the surface of the thermal barrier coating by using a carbon evaporation coating instrument under the pressure of mbar.
(7) Melting CMAS powder (volcanic ash directly produced after spraying of 2010 Islands in Africa and Fidelia volcanic) at 1600 deg.C,Cooling, cutting into cubes with volume of 1mm × 1mm × 1mm, placing on the surface of the coating after laser treatment and carbon spraying, placing the whole sample in a vacuum high-temperature tube furnace, and vacuumizing until the vacuum degree is less than 10-3After mbar, the CMAS sample was heated to 1200 ℃ at a heating rate of 5K/min and incubated for 1h, after which heating was stopped and allowed to cool to room temperature. As shown in fig. 5, CMAS changed to glass beads with a contact angle of 160 °, spreading did not occur, and the beads could be easily separated from the coating with tweezers and were not sticky. Namely showing non-infiltration and non-bonding to the CMAS sample and having good CMAS bonding resistance.
(8) For comparison, step 7 was repeated on the surface of the coating that was not treated with the laser and sprayed with the carbon layer, as shown in FIG. 6, with the CMAS of the green surface fully spread.
Example 2
(1) Taking Al2O3The plate (10X 12X 1.5mm) had a purity of 99.7% and was subjected to sand blasting. Wherein the sand blasting medium is 150 meshes of white corundum, the sand blasting pressure is 0.2MPa, and the sand blasting distance is 90 mm.
(2) Al after sand blasting2O3Preparing yttria partially stabilized zirconia (ZrO) on plate by adopting electron beam physical vapor deposition2+8wt.％Y2O3) Thermal barrier coating, the pressure of vacuum chamber in the deposition process is less than 1.0 x 10-2Pa, the heating current of the target material is 1.5A, the voltage of the electron gun is 40kV, the heating temperature of the workpiece is 1000 ℃, the rotating speed of the sample is 12rpm, and the thickness of the obtained thermal barrier coating is 450 mu m, as shown in figure 3.
(3) And carrying out ultrasonic cleaning on the prepared thermal barrier coating to remove surface stains and impurities.
(4) Femtosecond laser irradiation: for thermal barrier coating (ZrO)2+8wt.％Y2O3) Surface laser modification is carried out on the surface of a sample, a Ti sapphire laser with the rated power of 28mW is adopted, the femtosecond laser wavelength is 800nm, the pulse width is 65fs, the repetition frequency is 1kHz, the spot size is 42 mu m, and the single pulse energy is 4.09J/cm2Adopting a broken line type processing path, wherein the transverse scanning speed is 400 μm/s, the overlap ratio of adjacent light spots on the transverse axis is 98%, and the longitudinal scanning speed is 25000 μmm/s, and the coincidence degree of the adjacent light spots on the vertical axis is 0.
(5) The treated EB-PVD thermal barrier coating had a pyramidal shape with an average width of 18.75 μm, an average height of 28 μm and a surface distribution of nano-spheres with an average particle size of 235nm as shown in FIG. 4.
(6) The sample chamber was flushed with argon at 1.0X 10-2And spraying a carbon layer with the thickness of 20nm on the surface of the thermal barrier coating by using a carbon evaporation coating instrument under the pressure of mbar.
(7) Directly dispersing CMAS powder (volcanic ash directly collected from 2010 Islands in Africa, Fidelia and volcano) with average particle size of less than 30 μm on the surface of the coating after laser treatment and carbon spraying, placing the whole sample in a vacuum high-temperature tube furnace, and vacuumizing until the vacuum degree is less than 10-3After mbar, the CMAS sample was heated to 1200 ℃ at a heating rate of 5K/min and incubated for 1h, after which heating was stopped and allowed to cool to room temperature. As shown in FIG. 7, the micron-sized CMAS particles become micron-sized molten spheres and do not spread, i.e., the micron-sized CMAS particles are non-wetting and have good CMAS adhesion resistance.
(8) For comparison, step (7) was repeated on the coated surface which had not been treated with the laser and the sprayed carbon layer, and as shown in FIG. 8, the CMAS of the unprocessed surface was completely spread.
The above embodiments are only used for illustrating the design idea and features of the present invention, and the purpose of the present invention is to enable those skilled in the art to understand the content of the present invention and implement the present invention accordingly, and the protection scope of the present invention is not limited to the above embodiments. Therefore, all equivalent changes and modifications made in accordance with the principles and concepts disclosed herein are intended to be included within the scope of the present invention.

Claims (9)

1. A preparation method of a CMAS bonding resistant bionic thermal barrier coating is characterized by comprising the following steps:
step 1: carrying out sand blasting treatment on the surface of the ceramic matrix;
step 2: preparing a yttria-stabilized zirconia target, wherein Y2O38 wt.%;
and 3, step 3: preparing an yttria-stabilized zirconia coating with a columnar crystal structure on the surface of a substrate by adopting electron beam physical vapor deposition (EB-PVD);
and 4, step 4: scanning the surface of the yttria-stabilized zirconia coating by using femtosecond laser;
and 5: and carrying out carbon spraying treatment on the yttria-stabilized zirconia coating subjected to the femtosecond laser treatment by using a carbon evaporation coating instrument.
2. The preparation method of the anti-CMAS bonding biomimetic thermal barrier coating according to claim 1, wherein the sand blasting treatment in step 1 is specifically: the sand blasting medium is 100-sand 200-mesh white corundum, the sand blasting pressure is 0.15-0.4 MPa, and the sand blasting distance is 70-100 mm.
3. The preparation method of the anti-CMAS bonding biomimetic thermal barrier coating according to claim 1, wherein the step 2 specifically comprises: 8 wt.% Y2O3And ZrO2Mixing according to the mass ratio, and synthesizing the yttria-stabilized zirconia target material with the mass fraction of 8 wt.% by a high-temperature solid phase method, wherein the synthesis temperature is 1400-1600 ℃.
4. The preparation method of the CMAS-bonding-resistant bionic thermal barrier coating according to claim 1, wherein the EB-PVD of the step 3 has the following process parameters: the pressure of the vacuum chamber in the deposition process is less than 1.0 x 10-2Pa, the heating current of the target material is 1-1.5A, the voltage of an electron gun is 18-60 kV, the heating temperature of the workpiece is 950-1000 ℃, and the rotating speed of the sample is 12-20 rpm.
5. The preparation method of the CMAS-bonding-resistant bionic thermal barrier coating according to claim 1, wherein in the step 4, femtosecond laser processing parameters are as follows: the femtosecond laser wavelength is 800nm, the pulse width is 65fs, the repetition frequency is 1kHz, and the single pulse energy is 2-5J/cm2The focusing diameter of the light spot is 42 μm, the processing path is a broken line type, wherein the transverse scanning speed is 400-12000 μm/s, the overlapping ratio of the adjacent light spots on the transverse axis is 50-100%, the longitudinal scanning speed is 25000 μm/s, and the overlapping ratio of the adjacent light spots on the longitudinal axis is 0.
6. The preparation method of the anti-CMAS bonding biomimetic thermal barrier coating according to claim 1, wherein the step 5 specifically comprises: the sample chamber was flushed with argon at 1.0X 10-2The carbon filament is evaporated and a carbon film with a thickness of 10-100nm is deposited under mbar pressure.
7. A CMAS bond resistant biomimetic thermal barrier coating, characterized in that it is prepared by the preparation method of any of claims 1-6.
8. The CMAS-bond-resistant biomimetic thermal barrier coating of claim 7, wherein the surface of the thermal barrier coating is a lotus leaf biomimetic micro-nano structure.
9. The CMAS bond-resistant biomimetic thermal barrier coating of claim 7 or 8, wherein the thermal barrier coating has millimeter-scale CMAS particle bond resistance and micron-scale CMAS particle wettability resistance.
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