CN117512491A - Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating - Google Patents
Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating Download PDFInfo
- Publication number
- CN117512491A CN117512491A CN202311533980.7A CN202311533980A CN117512491A CN 117512491 A CN117512491 A CN 117512491A CN 202311533980 A CN202311533980 A CN 202311533980A CN 117512491 A CN117512491 A CN 117512491A
- Authority
- CN
- China
- Prior art keywords
- chromium
- aluminum
- spraying
- yttrium
- nickel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000576 coating method Methods 0.000 title claims abstract description 71
- 239000011248 coating agent Substances 0.000 title claims abstract description 70
- -1 nickel-chromium-aluminum-yttrium Chemical compound 0.000 title claims abstract description 42
- 230000004888 barrier function Effects 0.000 title claims abstract description 18
- 238000002360 preparation method Methods 0.000 title claims abstract description 10
- 238000005507 spraying Methods 0.000 claims abstract description 59
- 238000000034 method Methods 0.000 claims abstract description 24
- 239000010410 layer Substances 0.000 claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 16
- 230000008569 process Effects 0.000 claims abstract description 14
- 239000002344 surface layer Substances 0.000 claims abstract description 13
- 239000000843 powder Substances 0.000 claims description 27
- 239000002245 particle Substances 0.000 claims description 17
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 14
- 238000001035 drying Methods 0.000 claims description 10
- 229910000831 Steel Inorganic materials 0.000 claims description 5
- 238000007689 inspection Methods 0.000 claims description 5
- 239000010977 jade Substances 0.000 claims description 5
- 238000005498 polishing Methods 0.000 claims description 5
- 239000011148 porous material Substances 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 239000010959 steel Substances 0.000 claims description 5
- 238000007664 blowing Methods 0.000 claims description 4
- 238000004140 cleaning Methods 0.000 claims description 4
- 239000004576 sand Substances 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 3
- 239000007921 spray Substances 0.000 claims description 3
- 238000003892 spreading Methods 0.000 claims description 2
- 230000007480 spreading Effects 0.000 claims description 2
- 238000005554 pickling Methods 0.000 claims 1
- 238000005260 corrosion Methods 0.000 abstract description 6
- 230000007797 corrosion Effects 0.000 abstract description 6
- 239000000758 substrate Substances 0.000 abstract description 4
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 239000012720 thermal barrier coating Substances 0.000 description 13
- 239000000919 ceramic Substances 0.000 description 7
- 238000009826 distribution Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 238000005187 foaming Methods 0.000 description 4
- OTSDRZDDXSWTNV-UHFFFAOYSA-N [La].[Sm].[Gd] Chemical compound [La].[Sm].[Gd] OTSDRZDDXSWTNV-UHFFFAOYSA-N 0.000 description 3
- 238000000227 grinding Methods 0.000 description 3
- 238000009413 insulation Methods 0.000 description 3
- 238000002310 reflectometry Methods 0.000 description 3
- 238000005488 sandblasting Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000011109 contamination Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 229910002080 8 mol% Y2O3 fully stabilized ZrO2 Inorganic materials 0.000 description 1
- 235000015842 Hesperis Nutrition 0.000 description 1
- 235000012633 Iberis amara Nutrition 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000005328 electron beam physical vapour deposition Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000002329 infrared spectrum Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000000643 oven drying Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000007747 plating Methods 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 229910002076 stabilized zirconia Inorganic materials 0.000 description 1
- 229910001233 yttria-stabilized zirconia Inorganic materials 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- 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
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
A preparation method of a high temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating belongs to the technical field of high temperature resistant corrosion coating materials. According to the invention, the Amdry962 bottom layer is firstly sprayed on the surface of a substrate, then an intermittent spraying mode is adopted, and a method of spraying nickel-chromium-aluminum-yttrium surface layer is adopted, wherein each spraying is carried out for 10 times at intervals of 5-10min, meanwhile, the surface temperature of a part in the spraying process is controlled to be 300+/-10 ℃, the finally prepared coating is more uniform and compact, the surface layer/bottom layer interface pollution of the coating is less than 20%, no macroscopic crack exists, the porosity is less than 15%, and the holes are not more than 30 mu m; the hardness is improved by 20%, and the service life of parts is prolonged by 30%.
Description
Technical Field
The invention belongs to the technical field of high-temperature corrosion resistant coating materials, and particularly relates to a preparation method of a high-temperature heat barrier resistant nickel-chromium-aluminum-yttrium coating.
Background
The high-temperature alloy is a metal material which is based on iron, nickel and cobalt, can work for a long time under the action of high temperature above 600 ℃ and certain stress, has higher high-temperature strength, good oxidation resistance and corrosion resistance, good comprehensive properties such as fatigue property, fracture toughness and the like, is also called as super alloy, and is mainly applied to the aerospace field and the energy field. In the use process, the blade and the surface of the casing part are easy to be damaged because the blade and the casing part are in a high-temperature and high-pressure working environment for a long time. The thermal barrier coating (Thermal Barrier Coatings) is deposited on the surface of high-temperature resistant metal or superalloy, plays a role in heat insulation for a substrate material, reduces the temperature of the substrate, enables devices (such as engine turbine blades) manufactured by the thermal barrier coating to operate at high temperature, and can improve the thermal efficiency of the devices (such as engines and the like) by more than 60 percent. In order to ensure the safe and stable service of the high-temperature component and prolong the life cycle of the heavy-duty gas turbine, a thermal barrier coating is required to be prepared on the surface of the high-temperature component so as to play the roles of heat insulation, corrosion resistance, erosion resistance and the like, and the high-temperature component is provided with heat protection, so that the temperature of the high-temperature component is in a reasonable range.
Patent CN116988010A relates to a lanthanum gadolinium samarium ternary medium entropy thermal barrier coating material and a preparation method thereof, wherein the thermal expansion coefficient of the thermal barrier coating material is close to that of YSZ, and the thermal barrier coating material has lower thermal conductivity, and meanwhile, the lanthanum gadolinium samarium ternary medium entropy thermal barrier coating is prepared by utilizing an electron beam physical vapor deposition technology, so that the lanthanum gadolinium samarium ternary medium entropy thermal barrier coating has a unique columnar crystal structure; meanwhile, the NiCrAlHfTa is prepared by the vacuum arc plating equipment and used as a metal bottom layer of the thermal barrier coating, so that the overall matching property of the coating material is improved. The patent CN116752071A provides a low-heat-conductivity high-reflectivity composite coating and a preparation method thereof, the composite coating system is provided with a double-layer ceramic layer structure, the bottom ceramic layer is 8YSZ ceramic, the top ceramic layer is ceramic with larger reflectivity to the infrared spectrum of heat radiation, and the outermost ceramic layer has higher infrared reflectivity, so that the heat insulation performance of the thermal barrier coating can be greatly improved. However, the above ceramic thermal barrier coating is affected by the brittle characteristics of the material itself, and it is difficult to stably function for a long period of time. The nickel-chromium-aluminum-yttrium coating technology can better solve the problem of short service life of parts of blades and cases caused by high-temperature and high-pressure working environments.
Disclosure of Invention
The invention aims to obtain a preparation process of a nickel-chromium-aluminum-yttrium coating with stable and excellent performance by researching an automatic nickel-chromium-aluminum-yttrium coating spraying technology, thereby improving the production efficiency and solving the problems of unstable quality and the like.
The core point of the invention is the structure, performance and preparation mode of the coating. The spray process was optimized based on analysis of the texture and performance of the sprayed nickel-chromium-aluminum-yttrium stabilized zirconia, alumina, and yttria coatings. The main technological parameters include spraying distance, powder feeding rate, etc. The coating properties include metallographic structure, HV0.3 microhardness, thermal shock, bonding strength, and the like.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
a preparation method of a high-temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating comprises the following steps:
step 1, appearance inspection samples or parts;
step 2, drying nickel-chromium-aluminum-yttrium spraying powder;
step 3, detecting the powder feeding speed and the electrode voltage of the spray gun;
step 4, immersing alloy samples or parts in acetone, and blowing sand;
step 5, spraying an Amdry962 bottom layer and spraying a nickel-chromium-aluminum-yttrium surface layer;
step 6, cleaning after spraying to obtain a high-temperature-resistant heat barrier nickel-chromium-aluminum-yttrium coating;
wherein, the nickel-chromium-aluminum-yttrium surface layer spraying process is carried out in an intermittent spraying mode.
In the step 2, the drying step is as follows: spreading the powder on a stainless steel plate with thickness not more than 28mm, and oven drying at 90-110deg.C for not less than 2 hr; wherein the time from the end of powder drying to the start of spraying is not more than 1 hour;
the particle size of the powder is 21-98 μm and the ratio is more than 97.5%.
In the step 3, the powder feeding speed is 18+/-5 g/min; the electrode voltage is 70-80V;
in the step 4, the acetone soaking time is 15-20 min;
the sand blowing process parameters are as follows: 60 mesh white steel jade with pressure of 0.2Mpa;
in the step 5, the bottom layer is an Amdry962 coating with the thickness of 0.05 mm-0.10 mm;
the spraying technology of the nickel-chromium-aluminum-yttrium coating comprises the following steps: spraying is carried out for 10 times every spraying at intervals of 5-10 min; in the spraying process, the surface temperature of the part is 300+/-10 ℃.
In the step 6, the cleaning mode after spraying is as follows: and (5) manually polishing and removing redundant coating materials.
The high-temperature-resistant heat barrier nickel-chromium-aluminum-yttrium coating has the thickness of 0.25-0.35 mm and is uniformly and continuously distributed; the surface layer/bottom layer interface pollution of the coating is less than 20%, and no macroscopic crack exists; porosity is less than 15%, and pores are not more than 30 μm; the content of undeformed or unmelted particles in the coating is less than 15%, and the particle size of the undeformed or unmelted particles is not more than 30 mu m; microhardness: HV 0.1-0.3350-360 MIN.
The coating and the substrate have no crack or tilting, and the coating has no peeling and foaming phenomena.
Compared with the prior art, the invention has the beneficial effects that:
1. the invention adopts a spraying mode that each spraying is performed for 10 times at intervals of 5-10 min; in the spraying process, the surface temperature of the part is controlled to be 300+/-10 ℃, so that the coating is more uniform and compact, the hardness is improved by 20%, and the service life of the part is prolonged by 30%.
2. The nickel-chromium-aluminum-yttrium coating prepared by the method has the characteristics of excellent high-temperature corrosion resistance, reliable quality and stable production, can be used for resisting high-temperature corrosion at the working temperature of more than 600 ℃ and the working time of more than 1000 hours on an aeroengine, can be also applied to thermal barrier coatings of various engines and rockets, greatly prolongs the service life of parts, has wide market prospect, is easy to popularize to equipment and facilities such as civil gas turbines, prolongs the service life of the equipment and facilities, and has remarkable economic and social benefits.
Drawings
FIG. 1 is a nickel chromium aluminum yttrium powder morphology of example 1;
FIG. 2 is a microstructure of the nickel-chromium-aluminum-yttrium coating of example 1.
Detailed Description
The invention will be further described with reference to the drawings and specific examples.
Example 1
1. Appearance inspection is carried out on the engine case (the base material is 1Cr17Ni 2);
2. the nickel-chromium-aluminum-yttrium spraying powder is spread on a stainless steel plate with the thickness of 25mm, and is dried in a baking oven at the temperature of 100 ℃ for 2 hours, and the time from the end of powder drying to the beginning of spraying is 1 hour; wherein the powder particle size distribution range is 21-98 μm with 97.5%. Wherein, the morphology of the nickel-chromium-aluminum-yttrium powder is shown in figure 1.
3. Checking that the powder feeding speed is 18g/min; the electrode voltage was 70V;
4. after the engine case is immersed in an acetone solution for 20min, carrying out sand blasting treatment on the engine case by using 60-mesh white steel jade under the condition that the pressure is 0.2Mpa;
5. firstly spraying an Amdry962 coating with the thickness of 0.06mm on the surface of the casing as a bottom layer, then spraying a nickel-chromium-aluminum-yttrium surface layer by adopting a spraying mode of 10 times of spraying every 6 minutes until the total thickness of the coating is 0.28mm, and stopping spraying. In the spraying process, the surface temperature of the case needs to be maintained at 300+/-10 ℃.
6. And manually polishing and grinding to remove superfluous coating materials on the surface of the casing.
The coating prepared by the scheme is uniform and continuous in distribution, has an off-white appearance, has a microstructure shown in figure 2, has 18% of surface layer/bottom layer interface pollution, has 10% of undeformed or unmelted particles, and has a particle size of 30 mu m. The coating and the engine case have no cracks or tilting, and the coating has no peeling, foaming and other phenomena. The coating was tested for porosity with a final porosity of 12% and a maximum pore size of 30 μm. The microhardness of the coating is HV 0.1-0.3 360MIN.
Example 2
1. Appearance inspection is carried out on the engine case (the base material is 1Cr17Ni 2);
2. the nickel-chromium-aluminum-yttrium spraying powder is spread on a stainless steel plate with the thickness of 25mm, and is dried in a baking oven at the temperature of 100 ℃ for 2 hours, and the time from the end of powder drying to the beginning of spraying is 1 hour; wherein the powder particle size distribution range is 21-98 μm with 98% of the ratio.
3. Checking that the powder feeding speed is 17g/min; the electrode voltage was 75V;
4. after the engine case is immersed in an acetone solution for 20min, carrying out sand blasting treatment on the engine case by using 60-mesh white steel jade under the condition that the pressure is 0.2Mpa;
5. firstly spraying an Amdry962 coating with the thickness of 0.8mm on the surface of the casing as a bottom layer, then spraying a nickel-chromium-aluminum-yttrium surface layer by adopting a spraying mode of 10 times of spraying every 6 minutes until the total thickness of the coating is 0.30mm, and stopping spraying. In the spraying process, the surface temperature of the case needs to be maintained at 300+/-10 ℃.
6. And manually polishing and grinding to remove superfluous coating materials on the surface of the casing.
The coating prepared by the scheme is uniformly and continuously distributed and has an off-white appearance. The surface/bottom layer interface contamination of the coating was 18%, the undeformed or unmelted particles were 12% and the maximum particle size was 30 μm. The coating and the engine case have no cracks or tilting, and the coating has no peeling, foaming and other phenomena. The coating was tested for porosity with a final porosity of 14% and a maximum pore size of 25 μm. The microhardness of the coating is HV 0.1-0.3350 MIN.
Example 3
1. Appearance inspection is carried out on the engine case (the base material is 1Cr17Ni 2);
2. the nickel-chromium-aluminum-yttrium spraying powder is spread on a stainless steel plate with the thickness of 25mm, and is dried in a baking oven at the temperature of 100 ℃ for 2 hours, and the time from the end of powder drying to the beginning of spraying is 1 hour; wherein the powder particle size distribution range is 21-98 μm with 98% of the ratio.
3. Checking that the powder feeding speed is 19g/min; the electrode voltage was 75V;
4. after the engine case is immersed in an acetone solution for 20min, carrying out sand blasting treatment on the engine case by using 60-mesh white steel jade under the condition that the pressure is 0.2Mpa;
5. firstly spraying an Amdry962 coating with the thickness of 0.07mm on the surface of the casing as a bottom layer, then spraying a nickel-chromium-aluminum-yttrium surface layer by adopting a spraying mode of 10 times of spraying every 6 minutes until the total thickness of the coating is 0.28mm, and stopping spraying. In the spraying process, the surface temperature of the case needs to be maintained at 300+/-10 ℃.
6. And manually polishing and grinding to remove superfluous coating materials on the surface of the casing.
The coating prepared by the scheme is uniformly and continuously distributed and has an off-white appearance. The surface/bottom layer interface contamination of the coating was 15%, the undeformed or unmelted particles were 12% and the particle size was 25 μm. The coating and the engine case have no cracks or tilting, and the coating has no peeling, foaming and other phenomena. The coating was tested for porosity with a final porosity of 12% and a maximum pore size of 22 μm. The microhardness of the coating is HV 0.1-0.3350 MIN.
Claims (9)
1. The preparation method of the high-temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating is characterized by comprising the following steps of:
step 1, appearance inspection samples or parts;
step 2, drying nickel-chromium-aluminum-yttrium spraying powder;
step 3, detecting the powder feeding speed and the electrode voltage of the spray gun;
step 4, immersing alloy samples or parts in acetone, and blowing sand;
step 5, spraying an Amdry962 bottom layer and spraying a nickel-chromium-aluminum-yttrium surface layer;
step 6, cleaning after spraying to obtain a high-temperature-resistant heat barrier nickel-chromium-aluminum-yttrium coating;
wherein, the nickel-chromium-aluminum-yttrium surface layer spraying process is carried out in an intermittent spraying mode.
2. The method for preparing the high temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein in the step 2, the drying step is as follows: spreading the powder on a stainless steel plate, wherein the thickness is not more than 28mm, and drying in an oven at 90-110 ℃ for not less than 2 hours; wherein the time from the end of powder drying to the start of spraying is not more than 1 hour.
3. The method for preparing the high-temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein the particle size of the nickel-chromium-aluminum-yttrium spraying powder is more than 97.5% in the range of 21-98 μm.
4. The method for preparing a high temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein in the step 3, the powder feeding speed is 18+ -5 g/min; the electrode voltage is 70-80V.
5. The method for preparing the high-temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein in the step 4, the acetone pickling time is 15-20 min;
the sand blowing process parameters are as follows: 60 mesh white steel jade with pressure of 0.2Mpa.
6. The method for preparing the high-temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein in the step 5, the bottom layer is an Amdry962 coating, and the thickness is 0.05 mm-0.10 mm; in the spraying process, the surface temperature of the part is 300+/-10 ℃.
7. The method for preparing the high-temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein the spraying process of the nickel-chromium-aluminum-yttrium surface layer is as follows: the spraying mode is adopted when spraying, wherein each spraying time is 10 times, and the interval is 5-10 min.
8. The method for preparing the high temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein in the step 6, the cleaning mode after spraying is as follows: and (5) manually polishing and removing redundant coating materials.
9. The method for preparing the high temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating according to claim 1, wherein the high temperature resistant thermal barrier nickel-chromium-aluminum-yttrium coating has a thickness of 0.25 mm-0.35 mm and is uniformly and continuously distributed; the surface layer/bottom layer interface pollution of the coating is less than 20%, and no macroscopic crack exists; porosity is less than 15%, and pores are not more than 30 μm; the content of undeformed or unmelted particles in the coating is less than 15%, and the particle size of the undeformed or unmelted particles is not more than 30 mu m; microhardness: HV 0.1-0.3 MIN 350-360 MIN.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311533980.7A CN117512491A (en) | 2023-11-17 | 2023-11-17 | Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311533980.7A CN117512491A (en) | 2023-11-17 | 2023-11-17 | Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117512491A true CN117512491A (en) | 2024-02-06 |
Family
ID=89754598
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311533980.7A Pending CN117512491A (en) | 2023-11-17 | 2023-11-17 | Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117512491A (en) |
-
2023
- 2023-11-17 CN CN202311533980.7A patent/CN117512491A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4861618A (en) | Thermal barrier coating system | |
| CN109628929B (en) | Thermal barrier coating, preparation method and application thereof, and aeroengine turbine blade | |
| US6875464B2 (en) | In-situ method and composition for repairing a thermal barrier coating | |
| CN111004990B (en) | MAX phase coating for thermal barrier coating anti-melting CMAS corrosion and thermal spraying preparation method | |
| CN109440046B (en) | Thermal barrier coating for blades of aero-engine and gas turbine and preparation method thereof | |
| CN108118190B (en) | A kind of environment resistant deposit corrosion thermal barrier coating and preparation method thereof | |
| CN103668191A (en) | Preparation method for thermal-barrier coating | |
| CN110093579B (en) | Preparation method of corrosion-resistant and ablation-resistant composite coating | |
| US20100028711A1 (en) | Thermal barrier coatings and methods of producing same | |
| US12085039B2 (en) | Composite coating, piston, engine and vehicle | |
| CN113584419B (en) | Thermal barrier coating for TiAl alloy surface and preparation method thereof | |
| CN112176275B (en) | Thermal barrier coating and preparation method and application thereof | |
| CA1330638C (en) | Thermal barrier coating system | |
| CN113151772A (en) | Novel high-temperature corrosion-resistant thermal barrier coating with double ceramic layer structure and preparation method thereof | |
| CN107254652A (en) | A kind of multilayer thermal barrier coating and preparation method thereof | |
| CN105463453A (en) | Thermal barrier coating with stable interface and manufacturing method of thermal barrier coating | |
| CN108004543A (en) | A kind of thermal barrier coating of anti-CMAS corrosion and preparation method thereof | |
| CN111962028A (en) | EB-PVD/APS composite structure double-ceramic-layer thermal barrier coating and preparation method thereof | |
| CN109930102A (en) | A kind of novel thermal barrier coating preparation process | |
| CN110387520B (en) | Crack-stopping anti-stripping bionic dam structure gradient coating and preparation method thereof | |
| CN113249676A (en) | Abradable seal coating structure with low friction coefficient and high wear rate and preparation method thereof | |
| CN112481577B (en) | Thermal shock resistant thermal barrier coating material and preparation method thereof | |
| CN117512491A (en) | Preparation method of high-temperature-resistant thermal barrier nickel-chromium-aluminum-yttrium coating | |
| CN117107311A (en) | Pt modified blade tip protective coating and preparation method thereof | |
| CN114592164B (en) | DVC thermal barrier coating and preparation method and application thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |