CN111334744A - Processing method for regulating and controlling micro texture on surface of thermal barrier coating bonding layer by utilizing laser impact - Google Patents
Processing method for regulating and controlling micro texture on surface of thermal barrier coating bonding layer by utilizing laser impact Download PDFInfo
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- CN111334744A CN111334744A CN202010098313.0A CN202010098313A CN111334744A CN 111334744 A CN111334744 A CN 111334744A CN 202010098313 A CN202010098313 A CN 202010098313A CN 111334744 A CN111334744 A CN 111334744A
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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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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
- C21D10/005—Modifying the physical properties by methods other than heat treatment or deformation by laser shock processing
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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
- C23C14/06—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
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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
- C23C14/28—Vacuum evaporation by wave energy or particle radiation
- C23C14/30—Vacuum evaporation by wave energy or particle radiation by electron bombardment
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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
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
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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
- C23C4/18—After-treatment
Abstract
The invention relates to a preparation process of a thermal barrier coating of an aeroengine blade, in particular to a processing method for regulating and controlling the microtexture on the surface of a bonding layer of the thermal barrier coating by utilizing laser impact. The method is characterized in that a laser impact structure is adopted to form crisscross array pit microtexture on the surface of a thermal barrier coating bonding layer, the bonding layer is processed by a laser impact method, the shape of crisscross array pit is formed by regulating and controlling the space between light spots to be 4-12mm and the laser energy to be 10-40J, different surface microtexture is formed, thus the microstructure and phase structure of the surface of the bonding layer are regulated and controlled, and the contact area between the bonding layer and a ceramic layer is increased, so that the interface mechanical binding force is improved. The residual stress field induced by laser shock can effectively counteract the tensile stress generated by the coating under high-temperature service, thereby slowing down the phenomenon of coating cracking caused by stress concentration. The preparation method has the advantages of few process flows, simple equipment and easy control.
Description
Technical Field
The invention relates to a preparation process of a thermal barrier coating of an aeroengine blade. The method is characterized in that laser impact is used for regulating and controlling the micro-texture of the surface of the bonding layer of the thermal barrier coating, and the laser impact is used for constructing the crisscross array pit micro-texture on the surface of the bonding layer of the thermal barrier coating.
Background
With the rapid development of aerospace, the thrust-weight ratio of an aero-engine is increasingly improved, the service temperature of a turbine engine is also greatly improved, and the gas temperature and the environmental pressure born by the turbine blades of the turbine engine are also continuously improved. Although several generations of high temperature alloys have been developed over the past 20 years to increase the temperature of the air intake of an aircraft turbine engine, the increase in the temperature of the air intake of an aircraft turbine engine is increasingly difficult due to limitations of the high temperature alloys such as melting point, surface corrosion, and stress cracking, which hinders the development of high efficiency high thrust weight ratio aircraft engines. For this reason, the national space agency (NASA) proposed the concept of TBCs as early as 1952, and in the 70 s of the 20 th century, TBCs were first used for protection of aircraft engine combustors and other hot end components, lowering the hot end component surface temperature, and improving engine efficiency.
The thermal barrier coating is easy to peel off from the ceramic coating and the bonding layer in the industrial application process, cracks are generated on the surface of the ceramic layer, and the like, so that the problem of early failure is solved, and the application of the thermal barrier coating is influenced to a great extent. Research shows that the failure mechanism of the thermal barrier coating material is influenced by the structure and the service environment of the thermal barrier coating material, generally considered to be caused by high-temperature oxidation, CMAS, stress, TGO and the like, and the service life of the thermal barrier coating is prolonged.
The surface micro-texture technology is proved to be a means for effectively improving the bearing capacity of the material, thereby prolonging the service life of the material. The current processing technology of the surface microtexture mainly comprises a mechanical micro-etching processing technology, a laser processing technology, an electric spark processing technology, an electrolytic processing technology and the like.
Chinese patent CN201210118555.7 discloses a method for preparing microtexture by laser lithography assisted electrochemical deposition, which obtains a surface composite plating layer with regular microtexture on the surface of a metal material, and improves the contact area of adjacent materials. However, the method is only suitable for preparing the surface texture of the metal or semiconductor material, other electrochemical reactions often occur in the deposition process, the quality of the deposited texture unit is further influenced, and the use of a large amount of electrolyte can also bring about a serious environmental pollution problem; the lie wood adopts laser multi-pass lap cladding to prepare good local reticular microtexture on the thermal barrier coating, so that the bonding force between the bonding layer and the ceramic layer is stronger, but a temperature field generated by the laser cladding can cause subsequent tensile thermal stress, and the service life of a test piece is influenced; although the bonding force between samples can be increased by adopting the circumferential groove microtexture prepared on the surface of the bonding layer by the shot blasting technology in a brilliant manner, the stress layer which can only be introduced is too small, the forming is difficult, and the production and processing requirements of high-performance parts can not be met; chinese patent CN2017110341311 discloses a surface treatment method for a laser shock regulation thermal barrier coating transition layer interface structure, wherein although the pit morphology of the structure on the surface layer of a bonding layer can improve the interface contact area of adjacent coatings, the processed microtexture is a single non-lap-joint parallel arrangement/dislocation arrangement morphology, the regulation of the depth of a shock pressure layer and the distance between light spots is difficult, and the shock effect is very small; chinese patent CN201810165047.1 discloses a preparation process of a thermal barrier coating of an aircraft engine blade, wherein a tenon-shaped staggered structure is formed on the interface of a bonding layer and a ceramic layer so as to prolong the service life of the coating, but the process of connecting a picosecond laser on the ceramic layer-bonding layer-ceramic layer to form an isosceles trapezoid structure is complex and difficult to form.
Disclosure of Invention
The invention aims to solve the technical problem that the contact area between a thermal barrier coating bonding layer and a ceramic layer is increased by constructing a cross-shaped pit microtexture, so that the mechanical binding force of an adjacent coating is increased, the thermal stress of a thermal barrier coating interface is adjusted, and the service life of the thermal barrier coating is prolonged.
The processing method for regulating and controlling the microtexture on the surface of the thermal barrier coating bonding layer by utilizing laser impact comprises the following steps:
s1, selecting a high-temperature alloy substrate material, and purifying the surface of the high-temperature alloy substrate: firstly, manually polishing the surface of a matrix by using metallographic abrasive paper to achieve the purpose of removing various oxides, impurities, rusty spots and other adhesive substances on the surface, then respectively carrying out ultrasonic cleaning in acetone and an alcohol solvent for 5min to remove surface grease, and after drying the matrix, adopting compressed air as power to form a high-speed jet beam to jet quartz sand to the surface of the matrix at a high speed.
S2, spraying the bonding layer on the high-temperature alloy matrix by adopting atmospheric plasma, wherein the spraying parameters are as follows in sequence: the power is 30 KW; the distance is 1000 mm; main gas 60L/mm; carrier gas 45L/mm; the powder feeding rate is 2 min; the moving speed of the spray gun is 200 mm/min; the thickness of the bonding layer is 80-200 μm; the bond coat is CoNiCrAlY with a composition of 38.5 Wt.% Co, 32 Wt.% Ni, 21 Wt.% Cr, 8 Wt.% Al, 0.5 Wt.% Y.
S3, processing the bonding layer in the step S2 by adopting a laser shock process, wherein the shock process parameters are as follows in sequence: selecting Nd: YAG nanosecond laser beam with pulse wavelength of 1064 nm; pulse width 15 ns; the diameter of the light spot is 4 mm; the pulse energy is 10-40J; the spot spacing is 4-12mm, the crisscross array pit surface microtexture with different pressure layer depths and different spot spacings is formed by controlling the spot spacing and the laser pulse energy, and the depth of the impacted pressure layer is 15-24 μm.
S4, depositing a ceramic layer on the surface of the bonding layer by adopting electron beam physical vapor deposition and carrying out a thermal shock test, wherein the parameters of the electron beam physical vapor deposition are as follows in sequence: acceleration voltage: -10 KV; heating current: 100-; rotation speed: 5-12 r.min-1(ii) a Vacuum chamber pressure: less than or equal to 0.02 Pa; preheating temperature of the matrix: 975 +/-50 ℃; the thickness of the deposited ceramic layer is 200-300 μm; the selected temperature of the thermal shock test is 1000 ℃, and the failure is judged when the oxidation area is stripped to 5%.
The invention has the advantages that:
1. processing the bonding layer by using a laser impact means, regulating and controlling the space (4-12mm) of light spots and the laser energy (10-40J) to construct a crisscross array pit morphology, forming different surface microtextures so as to regulate and control the microstructure and phase structure constitution of the surface of the bonding layer, and increasing the contact area of the bonding layer and the ceramic layer so as to improve the interface mechanical binding force of the bonding layer and the ceramic layer;
2. the residual stress field induced by laser shock can effectively counteract the tensile stress generated by the coating under high-temperature service, thereby slowing down the phenomenon of coating cracking caused by stress concentration;
3. the preparation method has the advantages of few process flows, simple equipment and easy control.
Drawings
Fig. 1 is a path diagram of a laser shock peening spot in an implementation example.
FIG. 2 is a cross-sectional view of the bonding layer after laser shock peening in example 1.
FIG. 3 is a cross-sectional view of the bonding layer after laser shock peening in example 2.
FIG. 4 is a cross-sectional view of the bonding layer after laser shock peening in example 3.
Wherein, 1 is an adhesive layer, 2 is an impact area, d1 is an impact pressure layer, and d2 is a light spot space.
Detailed Description
The embodiments of the present invention will now be described, but the present invention should not be construed as being limited thereto.
Example 1
The superalloy GH4169 substrate was first cut into 10mm by 3mm samples by wire cutting. The substrate is then subjected to a series of cleaning treatments: the surface of a matrix is manually polished by metallographic abrasive paper to achieve the purpose of removing various oxides, impurities, rusty spots and other adhesive substances on the surface, and then ultrasonic cleaning is carried out in acetone and alcohol solvents for 5min respectively to remove the grease on the surface. After the matrix is dried, compressed air is used as power to form a high-speed spray beam to spray the quartz sand to the surface of the matrix at a high speed, then plasma spraying CoNiCrAlY is adopted, and the spraying parameters are as follows: the power is 30 KW; the distance is 1000 mm; main gas 60L/mm; carrier gas 45L/mm; the powder feeding rate is 2 min; the moving speed of the spray gun is 200 mm/min; the thickness of the adhesive layer was 80 μm.
Strengthening by laser shockBonding layer, structured cross-shaped array pit shape, pulse wavelength: 1064 nm; pulse width 15 ns; the diameter of the light spot is 4 mm; laser shock spot spacing was set to 6mm, laser energy was set to 10J, followed by electron beam physical vapor deposition of 8% Y2O3-ZrO2The ceramic layer and the electron beam physical vapor deposition parameters are as follows in sequence: the accelerating voltage is-10 KV; heating current is 100 mA; rotation speed 5r min-1(ii) a The pressure of the vacuum chamber is less than or equal to 0.02 Pa; the preheating temperature of the substrate is 975 ℃, and the thickness of the deposited ceramic layer is 200 μm.
Thus, as shown in fig. 2, the contact area of the bonding layer and the ceramic layer of the prepared thermal barrier coating is improved by 44.6%, the depth of the pit is 18 μm, a thermal shock test is carried out at 1000 ℃, the thermal barrier coating is judged to be ineffective when the oxidation area is stripped to 5%, and the thermal shock resistance frequency is 264 on average.
Example 2:
the superalloy GH4169 substrate was first cut into 10mm by 3mm samples by wire cutting. The substrate is then subjected to a series of cleaning treatments: the surface of a matrix is manually polished by metallographic abrasive paper to achieve the purpose of removing various oxides, impurities, rusty spots and other adhesive substances on the surface, and then ultrasonic cleaning is carried out in acetone and alcohol solvents for 5min respectively to remove the grease on the surface. After the base member is dried, adopt compressed air as power to form high-speed spray beam and spray quartz sand to the base member surface at a high speed, adopt plasma spraying CoNiCrAlY tie coat afterwards, the spraying parameter is in proper order: the power is 30 KW; the distance is 1000 mm; main gas 60L/mm; carrier gas 45L/mm; the powder feeding rate is 2 min; the moving speed of the spray gun is 200 mm/min; the thickness of the adhesive layer was 80 μm.
Strengthening the bonding layer by using a laser impact method, and constructing a cross array pit shape with a pulse wavelength of 1064 nm; pulse width 15 ns; the diameter of the light spot is 4 mm; laser shock spot spacing was set to 8mm, laser energy was set to 15J, followed by electron beam physical vapor deposition of 8% Y2O3-ZrO2The ceramic layer and the electron beam physical vapor deposition parameters are as follows in sequence: the accelerating voltage is-10 KV; heating current is 100 mA; rotation speed 5r min-1(ii) a The pressure of the vacuum chamber is less than or equal to 0.02 Pa; preheating matrix at 975 deg.CThe thickness of the deposited ceramic layer was 200. mu.m.
Thus, as shown in fig. 3, the prepared thermal barrier coating has the advantages that the contact area between the bonding layer and the ceramic layer is increased by 32.1%, the depth of a pit is 19 microns, a thermal shock test is carried out at 1000 ℃, the thermal shock resistance is judged to be failure when the oxidation area is stripped to 5%, and the thermal shock resistance frequency is 250 times on average.
Example 3:
the superalloy GH4169 substrate was first cut into 10mm by 3mm samples by wire cutting. The substrate is then subjected to a series of cleaning treatments: the surface of a matrix is manually polished by metallographic abrasive paper to achieve the purpose of removing various oxides, impurities, rusty spots and other adhesive substances on the surface, and then ultrasonic cleaning is carried out in acetone and alcohol solvents for 5min respectively to remove the grease on the surface. After the base member is dried, adopt compressed air as power to form high-speed spray beam and spray quartz sand to the base member surface at a high speed, adopt plasma spraying CoNiCrAlY tie coat afterwards, the spraying parameter is in proper order: the power is 30 KW; the distance is 1000 mm; main gas 60L/mm; carrier gas 45L/mm; the powder feeding rate is 2 min; the moving speed of the spray gun is 200 mm/min; the thickness of the adhesive layer was 80 μm.
Strengthening the bonding layer by using a laser impact method, and constructing a cross array pit shape with a pulse wavelength of 1064 nm; pulse width 15 ns; the diameter of the light spot is 4 mm; laser shock spot spacing was set to 9mm, laser energy was set to 20J, followed by electron beam physical vapor deposition of 8% Y2O3-ZrO2The ceramic layer and the electron beam physical vapor deposition parameters are as follows in sequence: the accelerating voltage is-10 KV; heating current is 100 mA; rotation speed 5r min-1(ii) a The pressure of the vacuum chamber is less than or equal to 0.02 Pa; the preheating temperature of the substrate is 975 ℃, and the thickness of the deposited ceramic layer is 200 μm.
Thus, as shown in fig. 4, the contact area between the bonding layer and the ceramic layer of the prepared thermal barrier coating is increased by 25.8%, the depth of the pit is 22 μm, a thermal shock test is performed at 1000 ℃, the thermal barrier coating is judged to be ineffective when the oxidation area is stripped to 5%, and the thermal shock resistance frequency is averagely 234 times.
Claims (5)
1. The processing method for regulating and controlling the micro texture on the surface of the thermal barrier coating bonding layer by utilizing laser impact is characterized by comprising the following specific steps of:
s1, selecting a high-temperature alloy substrate material, and purifying the surface of the high-temperature alloy substrate;
s2, spraying a bonding layer on the high-temperature alloy matrix by adopting atmospheric plasma;
s3, processing the bonding layer in the step S2 by adopting a laser shock process, and forming a crisscross array pit surface microtexture with different pressure layer depths and different light spot pitches by controlling the light spot pitches and the laser pulse energy;
and S4, depositing a ceramic layer on the surface of the bonding layer by adopting electron beam physical vapor deposition and carrying out a thermal shock test.
2. The method for controlling the microtexture on the surface of the thermal barrier coating bonding layer by using laser shock as claimed in claim 1, wherein in step S1, the method for performing the cleaning treatment on the surface of the high-temperature alloy substrate comprises the following steps: firstly, manually polishing the surface of a matrix by using metallographic abrasive paper to achieve the purpose of removing various oxides, impurities, rusty spots and other adhesive substances on the surface, then respectively carrying out ultrasonic cleaning in acetone and an alcohol solvent for 5min to remove surface grease, and after drying the matrix, adopting compressed air as power to form a high-speed jet beam to jet quartz sand to the surface of the matrix at a high speed.
3. The processing method for regulating and controlling the micro-texture on the surface of the bonding layer of the thermal barrier coating by using laser shock as claimed in claim 1, wherein in the step S2, the process parameters of spraying the bonding layer are as follows in sequence: the power is 30 KW; the distance is 1000 mm; main gas 60L/mm; carrier gas 45L/mm; the powder feeding rate is 2 min; the moving speed of the spray gun is 200 mm/min; the thickness of the bonding layer is 80-200 μm; the bond coat is CoNiCrAlY with a composition of 38.5 Wt.% Co, 32 Wt.% Ni, 21 Wt.% Cr, 8 Wt.% Al, 0.5 Wt.% Y.
4. The processing method for regulating and controlling the micro-texture on the surface of the thermal barrier coating bonding layer by using laser shock as claimed in claim 1, wherein in the step S3, the laser shock process parameters are as follows in sequence: selecting Nd: YAG nanosecond laser beam with pulse wavelength of 1064 nm; pulse width 15 ns; the diameter of the light spot is 4 mm; the pulse energy is 10-40J; the distance between light spots is 4-12mm, and the depth of the impact pressure layer is 15-24 μm.
5. The processing method for regulating and controlling the microtexture of the surface of the thermal barrier coating bonding layer by utilizing the laser impact as claimed in claim 1, wherein in the step S4, the parameters of the electron beam physical vapor deposition are as follows in sequence: acceleration voltage: -10 KV; heating current: 100-; rotation speed: 5-12 r.min-1(ii) a Vacuum chamber pressure: less than or equal to 0.02 Pa; preheating temperature of the matrix: 975 +/-50 ℃; the thickness of the deposited ceramic layer is 200-300 μm; the selected temperature of the thermal shock test is 1000 ℃, and the failure is judged when the oxidation area is stripped to 5%.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112376013A (en) * | 2020-11-04 | 2021-02-19 | 苏州热工研究院有限公司 | Gamma ray shielding coating and preparation method thereof |
| CN113118631A (en) * | 2021-03-17 | 2021-07-16 | 江苏大学 | Method for removing thick coating and modifying surface of matrix based on laser shock |
| CN114807822A (en) * | 2022-03-03 | 2022-07-29 | 山东大学 | Laser microtexture modified thermal barrier coating for delaying growth of interface TGO and preparation process thereof |
| CN116462532A (en) * | 2023-03-10 | 2023-07-21 | 西安交通大学 | Ceramic matrix composite material with bionic multi-stage structure and laser preparation method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5419971A (en) * | 1993-03-03 | 1995-05-30 | General Electric Company | Enhanced thermal barrier coating system |
| CN102051615A (en) * | 2009-11-02 | 2011-05-11 | 中国科学院兰州化学物理研究所 | Preparation method of anti-creeping and anti-corrosive titanium or titanium alloy material |
| CN104451672A (en) * | 2014-12-18 | 2015-03-25 | 上海交通大学 | Laser powder deposition method for regulating and controlling interface morphology of thermal barrier coating |
| CN104593767A (en) * | 2015-01-07 | 2015-05-06 | 上海交通大学 | Method for preparing thermal barrier coating bonding layer by utilizing laser powder deposition technology |
| CN106676449A (en) * | 2015-11-04 | 2017-05-17 | 中国人民解放军装甲兵工程学院 | Method for improving bonding strength of coating |
| CN107841704A (en) * | 2017-10-30 | 2018-03-27 | 江苏大学 | Laser-impact regulates and controls the surface treatment method of thermal barrier coating transition interface structure |
-
2020
- 2020-02-18 CN CN202010098313.0A patent/CN111334744A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5419971A (en) * | 1993-03-03 | 1995-05-30 | General Electric Company | Enhanced thermal barrier coating system |
| CN102051615A (en) * | 2009-11-02 | 2011-05-11 | 中国科学院兰州化学物理研究所 | Preparation method of anti-creeping and anti-corrosive titanium or titanium alloy material |
| CN104451672A (en) * | 2014-12-18 | 2015-03-25 | 上海交通大学 | Laser powder deposition method for regulating and controlling interface morphology of thermal barrier coating |
| CN104593767A (en) * | 2015-01-07 | 2015-05-06 | 上海交通大学 | Method for preparing thermal barrier coating bonding layer by utilizing laser powder deposition technology |
| CN106676449A (en) * | 2015-11-04 | 2017-05-17 | 中国人民解放军装甲兵工程学院 | Method for improving bonding strength of coating |
| CN107841704A (en) * | 2017-10-30 | 2018-03-27 | 江苏大学 | Laser-impact regulates and controls the surface treatment method of thermal barrier coating transition interface structure |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112376013A (en) * | 2020-11-04 | 2021-02-19 | 苏州热工研究院有限公司 | Gamma ray shielding coating and preparation method thereof |
| CN112376013B (en) * | 2020-11-04 | 2023-01-10 | 苏州热工研究院有限公司 | Gamma ray shielding coating and preparation method thereof |
| CN113118631A (en) * | 2021-03-17 | 2021-07-16 | 江苏大学 | Method for removing thick coating and modifying surface of matrix based on laser shock |
| CN113118631B (en) * | 2021-03-17 | 2023-01-17 | 江苏大学 | Method for removing thick coating and modifying surface of matrix based on laser shock |
| CN114807822A (en) * | 2022-03-03 | 2022-07-29 | 山东大学 | Laser microtexture modified thermal barrier coating for delaying growth of interface TGO and preparation process thereof |
| CN116462532A (en) * | 2023-03-10 | 2023-07-21 | 西安交通大学 | Ceramic matrix composite material with bionic multi-stage structure and laser preparation method |
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