CN113718188A - Novel thermal barrier coating structure and preparation method thereof - Google Patents
Novel thermal barrier coating structure and preparation method thereof Download PDFInfo
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- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 37
- 238000002360 preparation method Methods 0.000 title claims abstract description 8
- 238000000034 method Methods 0.000 claims abstract description 41
- 230000008569 process Effects 0.000 claims abstract description 26
- 239000000919 ceramic Substances 0.000 claims abstract description 25
- 239000011159 matrix material Substances 0.000 claims abstract description 17
- 230000035939 shock Effects 0.000 claims abstract description 14
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 36
- 238000001035 drying Methods 0.000 claims description 30
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical group [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 28
- 238000005507 spraying Methods 0.000 claims description 21
- 229910045601 alloy Inorganic materials 0.000 claims description 20
- 239000000956 alloy Substances 0.000 claims description 20
- 238000004140 cleaning Methods 0.000 claims description 20
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 18
- 229910052786 argon Inorganic materials 0.000 claims description 14
- 239000013078 crystal Substances 0.000 claims description 10
- 238000000227 grinding Methods 0.000 claims description 8
- 238000005498 polishing Methods 0.000 claims description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 8
- 238000005728 strengthening Methods 0.000 claims description 7
- 238000004506 ultrasonic cleaning Methods 0.000 claims description 6
- 229910002609 Gd2Zr2O7 Inorganic materials 0.000 claims description 5
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 239000003344 environmental pollutant Substances 0.000 claims description 5
- 238000013532 laser treatment Methods 0.000 claims description 5
- 231100000719 pollutant Toxicity 0.000 claims description 5
- 238000011282 treatment Methods 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical group [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 2
- 239000011888 foil Substances 0.000 claims description 2
- 239000007921 spray Substances 0.000 abstract description 9
- 239000002184 metal Substances 0.000 abstract description 8
- 229910052751 metal Inorganic materials 0.000 abstract description 8
- 238000005516 engineering process Methods 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 43
- 238000005520 cutting process Methods 0.000 description 12
- 238000005488 sandblasting Methods 0.000 description 8
- 239000000758 substrate Substances 0.000 description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 6
- 239000001307 helium Substances 0.000 description 6
- 229910052734 helium Inorganic materials 0.000 description 6
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 6
- 239000001301 oxygen Substances 0.000 description 6
- 229910052760 oxygen Inorganic materials 0.000 description 6
- 238000004901 spalling Methods 0.000 description 6
- 239000012159 carrier gas Substances 0.000 description 5
- 238000000576 coating method Methods 0.000 description 5
- 239000011248 coating agent Substances 0.000 description 4
- 230000003647 oxidation Effects 0.000 description 4
- 238000007254 oxidation reaction Methods 0.000 description 4
- 239000002245 particle Substances 0.000 description 4
- 239000005030 aluminium foil Substances 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000007750 plasma spraying Methods 0.000 description 3
- 239000000843 powder Substances 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 239000002344 surface layer Substances 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 229910000943 NiAl Inorganic materials 0.000 description 1
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 238000004873 anchoring Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 150000001768 cations Chemical class 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
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- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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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
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- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/12—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure
- B23K26/123—Working by laser beam, e.g. welding, cutting or boring in a special atmosphere, e.g. in an enclosure in an atmosphere of particular gases
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/352—Working by laser beam, e.g. welding, cutting or boring for surface treatment
- B23K26/355—Texturing
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F3/00—Changing the physical structure of non-ferrous metals or alloys by special physical methods, e.g. treatment with neutrons
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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
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- 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
- C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
- C23C4/11—Oxides
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- 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
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- 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 invention relates to the technical field of thermal barrier coatings, in particular to a novel thermal barrier coating structure and a preparation method thereof. The method adopts laser shock to a DD6 matrix, then constructs a microstructure on the surface of the DD6 matrix through picosecond laser, and finally sprays Gd on the surface of the DD6 matrix by using a PS-PVD technology2Zr2O7The ceramic layer can effectively solve the technical problem that the metal bonding layer of the traditional thermal barrier coating is easy to lose efficacy, and the process is simplified.
Description
Technical Field
The invention relates to the technical field of thermal barrier coatings, in particular to a novel thermal barrier coating structure and a preparation method thereof.
Background
In recent years, with the continuous development of thrust-weight ratio and efficiency of aero-engines, the inlet temperature is remarkably improved and far exceeds the working limit temperature of nickel-based high-temperature alloy. At present, thermal barrier coating techniques are often employed to protect metal blades. A typical thermal barrier coating consists of three layers, a metal substrate, a bond coat and a ceramic layer. The bonding layer has two main functions, on one hand, the metal substrate can be protected from oxidation corrosion in a high-temperature environment, on the other hand, the thermal mismatch between the metal substrate and the ceramic layer can be relieved, and the interface bonding force of the metal substrate and the ceramic layer is improved. The ceramic layer mainly plays a role in heat insulation and reduces the surface temperature of the metal substrate. Nevertheless, failure of thermal barrier coatings is often caused by weak bonding forces at the ceramic layer to bond coat interface and microstructural evolution of the bond coat. Typically, the bond coat material is MCrAlY or NiAl, which has poor creep resistance at high temperatures. Under high stress and high temperature conditions, rapid creep deformation is easy to occur above the ductile-brittle transition temperature, resulting in failure of the coating.
The DD6 single crystal superalloy is a low-cost second generation single crystal superalloy independently developed in China, and has the advantages of high-temperature strength, good comprehensive performance, stable structure, good casting technological properties and the like. The using temperature is increased by about 40 ℃ compared with that of the first generation of single crystal, and the tensile property, the durability, the creep property, the fatigue resistance, the oxidation resistance and the hot corrosion resistance are greatly improved, and the working temperature is generally lower than 1150 ℃. The laser shock peening technology flexibly regulates and controls the surface appearance, refines crystal grains, introduces crystal defects such as high-density dislocation, twin crystal and the like in the material, and increases Cr3+The diffusion path of the oxide cations can quickly form a continuous and compact protective film on the surface of the material, and the high-temperature oxidation resistance and high-temperature creep resistance of the alloy can be improved.
Furthermore, sand blasting is often used industrially to improve the mechanical bonding between coatings. However, the sand blasting technique has the defects of easy crack formation and poor uniformity of particle residues, and needs to be improved. The surface texture can produce a strong mechanical anchoring effect between the coating and the substrate, and improve the adhesion of the surface coating. However, the traditional micro-texture preparation method such as acid etching has low precision and complex process, and is not suitable for preparing the surface microstructure of the high-temperature blade.
Disclosure of Invention
The invention aims to solve the technical problem of providing a novel thermal barrier coating structure and a preparation method thereof, which adopts laser impact on a DD6 matrix, constructs a microstructure on the surface of the DD6 matrix through picosecond laser, and finally sprays Gd on the surface of the DD6 matrix by using a PS-PVD technology2Zr2O7The ceramic layer can effectively solve the technical problem that the metal bonding layer of the traditional thermal barrier coating is easy to lose efficacy, and the process is simplified.
A preparation method of a novel thermal barrier coating structure comprises the following steps:
the method comprises the following steps: grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the DD6 alloy matrix to be processed;
step two: the DD6 sample after the first treatment was prepared using Nd: YAG nanosecond pulse laser carries out laser shock strengthening, wherein the absorption layer is aluminum foil, the restraint layer is water, and the process parameters are as follows: the pulse width is 10-15 ns, the energy is 1-7J, the diameter of a light spot is 3mm, the lap joint rate is 20-80%, and the impact is performed for 1-10 times.
Step three: ultrasonic cleaning the sample subjected to laser impact in acetone and alcohol in sequence to remove surface oil pollutants, and drying in a drying oven at 80 ℃ for 30 min;
step four: and (4) constructing a micro texture on the surface of the DD6 single crystal alloy subjected to laser impact by using a picosecond laser on the sample treated in the step three. The picosecond laser process parameters are as follows: the pulse width is 13ps, the repetition frequency is 100-1000 kHz, the scanning speed is 100-1000 mm/s, the repetition frequency is 1-20 times, the diameter of a light spot is 25 mu m, the laser power is 5-20W, and the processing atmosphere is argon. The obtained microtexture is specifically: the diameter of the round hole type array is 40-120 mu m, the center distance between adjacent round holes is 60-120 mu m, and the depth is 10-30 mu m; or a straight groove type array, the width of the straight groove type array is 30-100 μm, the center distance between adjacent grooves is 60-100 μm, and the depth is 10-30 μm; or an orthogonal groove array, the width of the orthogonal groove array is 30-100 mu m, the center distance between adjacent grooves is 60-100 mu m, the depth is 10-30 mu m, and the specific structure is shown in figure 1;
step five: cleaning the sample subjected to the laser treatment in the fourth picosecond step by using acetone and alcohol in sequence, and then drying the sample in a drying box at the temperature of 80 ℃ for 30 min;
step six: spraying Gd on the surface of the sample cleaned and dried in the fifth step by adopting a PS-PVD process2Zr2O7And the ceramic layer is controlled to be 300 mu m in thickness.
The invention has the advantages of
1. According to the nanosecond laser shock strengthening technology, defects such as high-density dislocation, twin crystals and the like are introduced into the surface layer of the DD6 alloy, crystal grains are refined, the oxidation resistance of the surface of the DD6 alloy is effectively improved, and compressive stress is implanted into the surface layer of the DD6 alloy, so that the thermal stress under high-temperature circulation can be favorably regulated and controlled;
2. the picosecond laser microtexture can effectively relieve the DD6 alloy and Gd2Zr2O7The thermal mismatch between the ceramics greatly improves the Gd between the DD6 alloy substrate and the surface2Zr2O7The mechanical interlocking mechanism between the ceramic layers can remarkably improve the interface bonding force of the ceramic layers. In addition, the existence of the interface microtexture can effectively inhibit the expansion of cracks, improve the toughness of the interface and readjust the distribution and the size of thermal stress;
3. the thermal barrier coating of the invention has no traditional bonding layer, reduces the complicated spraying process of the traditional bonding layer, ensures the thermal shock resistance and reduces the cost.
Drawings
In fig. 1: (a) a circular hole pattern array structure; (b) a straight slot type array structure; (c) an orthogonal slot type array structure; (d) the cross section of the coating is schematic.
Detailed Description
Embodiments of the present invention will now be described.
Example 1
Cutting the DD6 alloy matrix into a standard sample with the diameter of 25.4cm by adopting a linear cutting process, and then grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the standard sample; then adopting the following steps: YAG nanosecond pulse laser reinforces its surface, and wherein the absorption layer is the aluminium foil, and the restriction layer is water, and its technological parameter is: the pulse width is 10ns, the energy is 5J, the spot diameter is 3mm, the lap-joint rate is 40%, the impact is carried out for 5 times, and the thickness of the obtained impact strengthening layer is 40 mu m.
And sequentially placing the sample subjected to laser shock strengthening in acetone and alcohol for ultrasonic cleaning for 30min respectively to remove surface oil pollutants, and then placing the sample in a drying oven at 80 ℃ for drying for 30 min. Micro-texture is constructed on the surface of the micro-texture by using a picosecond laser. The picosecond laser process parameters are as follows: the pulse width was 13ps, the repetition frequency was 500kHz, the scanning speed was 400mm/s, the number of repetitions was 10, the spot diameter was 25 μm, the laser power was 10W, and the processing atmosphere was argon. The processed microstructure is a round hole type array, the diameter is 60 mu m, the center distance between adjacent round holes is 60 mu m, and the depth is 25 mu m.
Sequentially placing the sample subjected to picosecond laser treatment in acetone and alcohol for ultrasonic cleaning respectively, then placing the sample in a drying oven at 80 ℃ for drying for 30min, and spraying Gd on the surface of the sample by adopting PS-PVD2Zr2O7The ceramic layer is prepared by the specific process of 2600A of current, 35L/min of argon flow rate, 60L/min of helium flow rate, 2L/min of oxygen flow rate, 16L/min of carrier gas flow rate, 900mm of spraying distance, 1000mm/s of spray gun moving rate and 300 mu m of thickness.
For ease of comparison, conventional thermal barrier coatings were prepared. The specific process comprises the following steps: cutting the DD6 alloy matrix into a standard sample with the diameter of 25.4cm by adopting a linear cutting process, and then grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the standard sample; the NiCrAlY bonding layer is prepared by adopting a plasma spraying method, and the specific process comprises the steps of spraying distance of 90mm, spraying voltage of 40V, spraying current of 650A, argon flow of 60L/min, powder feeding rate of 50g/min and thickness of 80 mu m. And then carrying out surface sand blasting treatment, wherein the specific process comprises that the sand blasting working pressure is 0.2Mpa, and the diameter of the medium particles is 50 mu m. Finally, Gd is sprayed on the surface of the film by adopting PS-PVD2Zr2O7The ceramic layer is prepared by the specific processes of current 2600A, argon flow rate of 35L/min, helium flow rate of 60L/min, oxygen flow rate of 2L/min, carrier gas flow rate of 16L/min, spraying distance of 900mm, spray gun moving rate of 1000mm/s and thickness of 300 mu m. Thus obtaining the traditional DD6 alloy matrix, NiCrAlY bonding layer and Gd2Zr2O7A ceramic layer thermal barrier coating.
A thermal shock test was performed at 1150 ℃ for 5min and then water cooled to room temperature. The results show that when the spalling area of the ceramic layer of the conventional thermal barrier coating as a comparative example is more than 30%, while the spalling area of the surface of the novel thermal barrier coating prepared by the embodiment is about 8%, the novel thermal barrier coating has excellent high-temperature thermal shock resistance and stability.
Example 2
Cutting the DD6 alloy matrix into a standard sample with the diameter of 25.4cm by adopting a linear cutting process, and then grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the standard sample; then adopting the following steps: YAG nanosecond pulse laser reinforces its surface, and wherein the absorption layer is the aluminium foil, and the restriction layer is water, and its technological parameter is: the pulse width is 10ns, the energy is 5J, the spot diameter is 3mm, the lap-joint rate is 40%, the impact is carried out for 5 times, and the thickness of the obtained impact strengthening layer is 40 mu m.
And (3) ultrasonically cleaning the sample subjected to laser impact in acetone and alcohol for 30min to remove surface oil pollutants, and then drying in a drying oven at 80 ℃ for 30 min. Micro-texture is constructed on the surface of the micro-texture by using a picosecond laser. The picosecond laser process parameters are as follows: the pulse width was 13ps, the repetition frequency was 500kHz, the scanning speed was 400mm/s, the number of repetitions was 10, the spot diameter was 25 μm, the laser power was 10W, and the processing atmosphere was argon. The processed microstructure was a straight groove type array with a width of 60 μm, a center-to-center distance between adjacent grooves of 60 μm, and a depth of 25 μm.
Sequentially placing the sample subjected to picosecond laser treatment in acetone and alcohol for ultrasonic cleaning respectively, then placing the sample in a drying oven at 80 ℃ for drying for 30min, and spraying Gd on the surface of the sample by adopting PS-PVD2Zr2O7The ceramic layer is prepared by the specific processes of current 2600A, argon flow rate of 35L/min, helium flow rate of 60L/min, oxygen flow rate of 2L/min, and carrier gasThe flow speed is 16L/min, the spraying distance is 900mm, the moving speed of the spray gun is 1000mm/s, and the thickness of the spray gun is 300 mu m, thus obtaining the novel thermal barrier coating.
For ease of comparison, conventional thermal barrier coatings were prepared. The specific process comprises the following steps: cutting the DD6 alloy matrix into a standard sample with the diameter of 25.4cm by adopting a linear cutting process, and then grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the standard sample; the NiCrAlY bonding layer is prepared by adopting a plasma spraying method, and the specific process comprises the steps of spraying distance of 90mm, spraying voltage of 40V, spraying current of 650A, argon flow of 60L/min, powder feeding rate of 50g/min and thickness of 80 mu m. And then carrying out surface sand blasting treatment, wherein the specific process comprises that the sand blasting working pressure is 0.2Mpa, and the diameter of the medium particles is 50 mu m. Finally, Gd is sprayed on the surface of the film by adopting PS-PVD2Zr2O7The ceramic layer is prepared by the specific processes of current 2600A, argon flow rate of 35L/min, helium flow rate of 60L/min, oxygen flow rate of 2L/min, carrier gas flow rate of 16L/min, spraying distance of 900mm, spray gun moving rate of 1000mm/s and thickness of 300 mu m. Thus obtaining the traditional DD6 alloy matrix, NiCrAlY bonding layer and Gd2Zr2O7A ceramic layer thermal barrier coating.
A thermal shock test was performed at 1150 ℃ for 5min and then water cooled to room temperature. The results show that when the spalling area of the ceramic layer of the conventional thermal barrier coating as a comparative example is more than 30%, while the spalling area of the surface of the novel thermal barrier coating prepared by the embodiment is about 5%, the novel thermal barrier coating has excellent high-temperature thermal shock resistance and stability.
Example 3
Cutting the DD6 alloy matrix into a standard sample with the diameter of 25.4cm by adopting a linear cutting process, and then grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the standard sample; then adopting the following steps: YAG nanosecond pulse laser reinforces its surface, and wherein the absorption layer is the aluminium foil, and the restriction layer is water, and its technological parameter is: the pulse width is 10ns, the energy is 5J, the spot diameter is 3mm, the lap-joint rate is 40%, the impact is carried out for 5 times, and the thickness of the obtained impact strengthening layer is 40 mu m.
And (3) ultrasonically cleaning the sample subjected to laser impact in acetone and alcohol for 30min to remove surface oil pollutants, and then drying in a drying oven at 80 ℃ for 30 min. Micro-texture is constructed on the surface of the micro-texture by using a picosecond laser. The picosecond laser process parameters are as follows: the pulse width was 13ps, the repetition frequency was 500kHz, the scanning speed was 400mm/s, the number of repetitions was 10, the spot diameter was 25 μm, the laser power was 10W, and the processing atmosphere was argon. The microstructure processed was an orthogonal groove array with a width of 50 μm, a center-to-center distance between adjacent grooves of 60 μm and a depth of 25 μm.
Sequentially placing the sample subjected to picosecond laser treatment in acetone and alcohol for ultrasonic cleaning respectively, then placing the sample in a drying oven at 80 ℃ for drying for 30min, and spraying Gd on the surface of the sample by adopting PS-PVD2Zr2O7The ceramic layer is prepared by the specific process of 2600A of current, 35L/min of argon flow rate, 60L/min of helium flow rate, 2L/min of oxygen flow rate, 16L/min of carrier gas flow rate, 900mm of spraying distance, 1000mm/s of spray gun moving rate and 300 mu m of thickness.
For ease of comparison, conventional thermal barrier coatings were prepared. The specific process comprises the following steps: cutting the DD6 alloy matrix into a standard sample with the diameter of 25.4cm by adopting a linear cutting process, and then grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the standard sample; the NiCrAlY bonding layer is prepared by adopting a plasma spraying method, and the specific process comprises the steps of spraying distance of 90mm, spraying voltage of 40V, spraying current of 650A, argon flow of 60L/min, powder feeding rate of 50g/min and thickness of 80 mu m. And then carrying out surface sand blasting treatment, wherein the specific process comprises that the sand blasting working pressure is 0.2Mpa, and the diameter of the medium particles is 50 mu m. Finally, Gd is sprayed on the surface of the film by adopting PS-PVD2Zr2O7The ceramic layer is prepared by the specific processes of current 2600A, argon flow rate of 35L/min, helium flow rate of 60L/min, oxygen flow rate of 2L/min, carrier gas flow rate of 16L/min, spraying distance of 900mm, spray gun moving rate of 1000mm/s and thickness of 300 mu m. Thus obtaining the traditional DD6 alloy matrix, NiCrAlY bonding layer and Gd2Zr2O7A ceramic layer thermal barrier coating.
A thermal shock test was performed at 1150 ℃ for 5min and then water cooled to room temperature. The results show that when the spalling area of the ceramic layer of the conventional thermal barrier coating as a comparative example is more than 30%, while the spalling area of the surface of the novel thermal barrier coating prepared by the embodiment is about 3%, the novel thermal barrier coating has excellent high-temperature thermal shock resistance and stability.
Claims (6)
1. A preparation method of a novel thermal barrier coating structure is characterized by comprising the following steps:
the method comprises the following steps: grinding, polishing, acetone cleaning, alcohol cleaning and drying the surface of the DD6 alloy matrix to be processed;
step two: the DD6 sample after the first treatment was prepared using Nd: YAG nanosecond pulse laser is used for carrying out laser shock strengthening;
step three: ultrasonic cleaning the sample after laser impact in acetone and alcohol to eliminate surface oil pollutant, and subsequent drying;
step four: constructing a micro texture on the surface of the DD6 single crystal alloy subjected to laser impact by using a picosecond laser on the sample treated in the step three;
step five: cleaning the sample subjected to the laser treatment in the fourth picosecond step by using acetone and alcohol in sequence, and then drying;
step six: spraying Gd on the surface of the sample cleaned and dried in the fifth step by adopting a PS-PVD process2Zr2O7And (5) obtaining a novel thermal barrier coating structure by a ceramic layer.
2. The method for preparing a novel thermal barrier coating structure as claimed in claim 1, wherein in the second step, laser shock peening is performed, the absorption layer is aluminum foil, the constraint layer is water, and the process parameters are as follows: the pulse width is 10-15 ns, the energy is 1-7J, the diameter of a light spot is 3mm, the lap joint rate is 20-80%, and the impact is performed for 1-10 times.
3. The method for preparing a novel thermal barrier coating structure as claimed in claim 1, wherein in the third step, the drying means is dried in a drying oven at 80 ℃ for 30 min.
4. The method for preparing a novel thermal barrier coating structure as claimed in claim 1, wherein in step four, the picosecond laser process parameters are as follows: the pulse width is 13ps, the repetition frequency is 100-1000 kHz, the scanning speed is 100-1000 mm/s, the repetition frequency is 1-20 times, the diameter of a light spot is 25 mu m, the laser power is 5-20W, and the processing atmosphere is argon; the obtained microtexture is specifically: the diameter of the round hole type array is 40-120 mu m, the center distance between adjacent round holes is 60-120 mu m, and the depth is 10-30 mu m; or a straight groove type array, the width of the straight groove type array is 30-100 μm, the center distance between adjacent grooves is 60-100 μm, and the depth is 10-30 μm; or an orthogonal groove array, the width of the orthogonal groove array is 30-100 μm, the center distance between adjacent grooves is 60-100 μm, and the depth is 10-30 μm.
5. The method for preparing a novel thermal barrier coating structure as claimed in claim 1, wherein in the fifth step, the drying means is dried in a drying oven at 80 ℃ for 30 min.
6. The method for preparing a novel thermal barrier coating structure as claimed in claim 1, wherein in step six, Gd2Zr2O7The thickness of the ceramic layer was 300. mu.m.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115261764A (en) * | 2022-08-24 | 2022-11-01 | 昆山西诺巴精密模具有限公司 | Aircraft engine casing coating and preparation method thereof |
| CN115673556A (en) * | 2022-10-12 | 2023-02-03 | 宁夏巨能机器人股份有限公司 | Method for improving laser shock spraying efficiency |
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2021
- 2021-08-31 CN CN202111010413.4A patent/CN113718188A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115261764A (en) * | 2022-08-24 | 2022-11-01 | 昆山西诺巴精密模具有限公司 | Aircraft engine casing coating and preparation method thereof |
| CN115261764B (en) * | 2022-08-24 | 2023-08-25 | 昆山西诺巴精密模具有限公司 | Aeroengine casing coating and preparation method thereof |
| CN115673556A (en) * | 2022-10-12 | 2023-02-03 | 宁夏巨能机器人股份有限公司 | Method for improving laser shock spraying efficiency |
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