CN116377374A - Multilayer composite thermal barrier coating - Google Patents
Multilayer composite thermal barrier coating Download PDFInfo
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- CN116377374A CN116377374A CN202310375516.3A CN202310375516A CN116377374A CN 116377374 A CN116377374 A CN 116377374A CN 202310375516 A CN202310375516 A CN 202310375516A CN 116377374 A CN116377374 A CN 116377374A
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- 239000012720 thermal barrier coating Substances 0.000 title claims abstract description 71
- 239000002131 composite material Substances 0.000 title claims abstract description 42
- 239000000843 powder Substances 0.000 claims abstract description 34
- 239000000919 ceramic Substances 0.000 claims abstract description 30
- 239000000956 alloy Substances 0.000 claims abstract description 26
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 26
- 239000002994 raw material Substances 0.000 claims abstract description 21
- 239000011863 silicon-based powder Substances 0.000 claims abstract description 18
- 230000003647 oxidation Effects 0.000 claims abstract description 17
- 238000007254 oxidation reaction Methods 0.000 claims abstract description 17
- 238000000576 coating method Methods 0.000 claims abstract description 16
- 239000011248 coating agent Substances 0.000 claims abstract description 15
- 239000003381 stabilizer Substances 0.000 claims abstract description 12
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical group [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims abstract description 6
- 239000001301 oxygen Substances 0.000 claims abstract description 6
- 229910052760 oxygen Inorganic materials 0.000 claims abstract description 6
- 150000001768 cations Chemical class 0.000 claims abstract description 3
- 239000011159 matrix material Substances 0.000 claims description 47
- 238000007750 plasma spraying Methods 0.000 claims description 21
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 14
- 239000000758 substrate Substances 0.000 claims description 14
- 238000002360 preparation method Methods 0.000 claims description 13
- 239000007921 spray Substances 0.000 claims description 13
- 238000012360 testing method Methods 0.000 claims description 12
- 238000002474 experimental method Methods 0.000 claims description 11
- 238000004140 cleaning Methods 0.000 claims description 10
- 238000005488 sandblasting Methods 0.000 claims description 9
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 7
- 239000011259 mixed solution Substances 0.000 claims description 7
- 239000004576 sand Substances 0.000 claims description 7
- 238000005507 spraying Methods 0.000 claims description 7
- 238000005516 engineering process Methods 0.000 claims description 6
- 239000002245 particle Substances 0.000 claims description 6
- 244000137852 Petrea volubilis Species 0.000 claims description 5
- 238000002441 X-ray diffraction Methods 0.000 claims description 5
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- 238000005520 cutting process Methods 0.000 claims description 5
- 238000001035 drying Methods 0.000 claims description 5
- 230000002708 enhancing effect Effects 0.000 claims description 5
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- 238000000034 method Methods 0.000 claims description 5
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- 238000005498 polishing Methods 0.000 claims description 5
- 239000011148 porous material Substances 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 5
- 238000012545 processing Methods 0.000 claims description 5
- 239000010935 stainless steel Substances 0.000 claims description 5
- 229910001220 stainless steel Inorganic materials 0.000 claims description 5
- 238000003756 stirring Methods 0.000 claims description 5
- 230000003746 surface roughness Effects 0.000 claims description 5
- 238000003466 welding Methods 0.000 claims description 5
- 239000012159 carrier gas Substances 0.000 claims description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims 1
- 239000010410 layer Substances 0.000 abstract 6
- 239000012790 adhesive layer Substances 0.000 abstract 2
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- 239000000463 material Substances 0.000 description 6
- 230000000052 comparative effect Effects 0.000 description 3
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- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- 239000010431 corundum Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005328 electron beam physical vapour deposition Methods 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
- 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
- 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
- C23C4/04—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
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a multilayer composite thermal barrier coating, which belongs to the technical field of high-temperature oxidation resistance, and comprises a ceramic layer, a thermally grown oxide layer and a bonding layer, wherein the bonding layer is composed of the following raw materials in percentage by weight: 90-98 wt.% of NiCrCoAlY alloy powder and 2-8 wt.% of Si powder; the ceramic layer is composed of the following raw materials in percentage by weight: zrO (ZrO) 2 90～92％、Y 2 O 3 8-10% and the balance stabilizer, wherein the NiCrCoAlY alloy powder and Y 2 O 3 Y in the adhesive layer is oxygen sensitive element with the element content of 0.2-1 wt.%, and the stabilizer contains trivalent and tetravalent cations, so that the invention can ensure that the Cr element content on the surface of the adhesive layer is the highest and the generated Cr is generated 2 O 3 Film and method for producing the sameThe multilayer composite thermal barrier coating is more compact, has minimum roughness, improves the high-temperature performance of the multilayer composite thermal barrier coating, can obtain the optimal tissue structure on the surface of the bonding layer, improves the wear resistance of the multilayer composite thermal barrier coating, can prevent oxygen from diffusing into the coating, and improves the oxidation resistance of the multilayer composite thermal barrier coating.
Description
Technical Field
The invention relates to the technical field of high-temperature oxidation resistance, in particular to a multilayer composite thermal barrier coating.
Background
The thermal barrier coating, TBC for short, is widely applied to turbine blade parts of aeroengines due to excellent heat insulation performance, the traditional thermal barrier coating generally comprises a surface ceramic layer and a bonding layer, in the service process of the thermal barrier coating, a layer of oxide is generated at the joint of the surface ceramic layer and the bonding layer under the influence of the components of the bonding layer materials, which is generally called as thermal growth oxide, at present, MCrAlY (M=Ni, co or Ni+Co) is generally selected as the bonding layer, and 8wt% Y2O3 stable ZrO2 is generally selected as the surface ceramic layer material.
With further improvement of the turbine inlet air temperature of the aeroengine, the selection requirement of the high-temperature protective coating material is further improved, namely the selected material must have lower heat conductivity and better heat stability, if the thermal barrier coating on the surface of the turbine blade is peeled off during the service process of the aeroengine, the internal high-temperature alloy is exposed to high temperature to be dangerous, and the peeling area of the thermal barrier coating on the surface of the turbine blade mainly occurs between the ceramic layer and the thermally grown oxide layer or between the thermally grown oxide layer and the bonding layer, so that the improvement of the adhesiveness among the ceramic layer, the thermally grown oxide layer and the bonding layer and the heat stability are very critical.
Through retrieval, chinese patent number CN111363998B discloses a preparation method of a porous metal-ceramic nano composite thermal barrier coating, although effective control of the porosity of the coating can be realized by adjusting the amount of pore-forming agent, the porosity is obviously improved, so that the heat insulation performance of the coating is also improved, various defects existing in the preparation of the thermal barrier coating by an electron beam physical vapor deposition technology and a thermal spraying technology in the prior art are overcome, but the high temperature performance, the wear resistance and the oxidation resistance of the coating cannot be improved.
Disclosure of Invention
The invention aims to solve the defects in the prior art and provides a multilayer composite thermal barrier coating.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the multilayer composite thermal barrier coating comprises a ceramic layer, a thermally grown oxide layer and a bonding layer, wherein the bonding layer is composed of the following raw materials in percentage by weight: 90-98 wt.% of NiCrCoAlY alloy powder and 2-8 wt.% of Si powder; the ceramic layer is composed of the following raw materials in percentage by weight: zrO (ZrO) 2 90～92％、Y 2 O 3 8-10%, and the balance of stabilizer.
Further, the NiCrCoAlY alloy powder and Y 2 O 3 Y in (2) is an oxygen-sensitive element, the element content of which is 0.2 to 1wt.%, and the stabilizer contains trivalent and tetravalent cations.
Further, the thickness of the ceramic layer is 100-500 μm, the thickness of the bonding layer is 80-120 μm, the alloy powder particle size of the NiCrCoAlY alloy powder is 45-75 μm, the purity of Si powder is 99.9%, the powder particle size is 25 μm, and the powder particle size of the ceramic layer raw material is 25-85 μm.
Further, the preparation method of the multilayer composite thermal barrier coating comprises the following specific steps:
step one: selecting raw materials and equipment: the NiCrCoAlY alloy powder produced by the company of California Jin Jiang, the Si powder produced by the company of Mecanum Biochemical technology, and the 8%Y produced by the company of California Jin Jiang are selected 2 O 3 Stabilized ZrO 2 The powder is prepared by selecting DH-2080 type plasma spraying device, selecting TRULASER CELL 7040 disc type laser of TRUMPF company, and simultaneously performing processing by matching with high-flexibility KUKA KR60L30HA robot, wherein the model of the laser welding head is YW 52;
step two: pretreatment of a substrate: selecting 310S stainless steel, cutting into square samples with the length of 15 multiplied by 5mm, polishing the cut samples to 800# by using SiC sand paper to form a matrix, performing sand blasting on the matrix to remove impurities on the surface of the matrix, enhancing the surface roughness of the matrix, enabling the matrix to be better combined with a coating, placing the sand blasted matrix into an absolute ethyl alcohol and acetone mixed solution, ultrasonically cleaning for 20min, cleaning the surface of the matrix, and drying to finish the pretreatment of the matrix;
step three: plasma spraying: mechanically mixing NiCrCoAlY alloy powder and Si powder uniformly for later use, automatically controlling a DH-2080 type plasma spraying device through a plasma spraying control cabinet, and controlling a mechanical arm to spray the substrate in the second step, so as to realize the spray preparation of a bonding layer and a ceramic layer and form a prefabricated thermal barrier coating;
step four: laser remelting: scanning a high-energy laser beam of a TRULASER CELL 7040 disc laser on the prefabricated thermal barrier coating to form a molten pool, and under the convection and stirring of the molten pool, enabling the components of the prefabricated thermal barrier coating to be more uniform, the grains to be more refined, the pores and the cracks to be eliminated, simultaneously realizing metallurgical bonding between the prefabricated thermal barrier coating and a matrix, and finally rapidly cooling to obtain the multi-layer composite thermal barrier coating;
step five: post-treatment: and carrying out constant-temperature oxidation experiments, thermal cycle experiments, X-ray diffraction analysis, roughness tests and microhardness tests on the multilayer composite thermal barrier coating.
Further, sand grains selected in the sand blasting treatment in the step two are 24# brown corundum, the sand blasting pressure is 0.6-0.75 MPa, and the ratio of absolute ethyl alcohol to acetone in the mixed solution is 3:1.
Further, in the third step, the mechanical arm is translated and sprayed for one pass, a coating with the thickness of 12-15 μm is deposited on the surface of the substrate, the coating to be deposited is cooled, spraying is continued in the same way, and the process is repeated until a bonding layer with the thickness of about 100 μm and a ceramic top layer with the thickness of about 200 μm are prepared on the surface of the substrate.
Further, parameters of the DH-2080 type plasma spraying device in the third step are as follows: 500-530A of current, 70-75V of voltage, 38-40L/M of main air flow, 8-10L/M of secondary air flow, 2.5-3L/M of carrier gas flow, 100mm of spraying distance, 35-40 kw of spray gun power and 30rad/M of rotating speed; and in the fourth step, rated output power of the TRULASER CELL 7040 disc laser is 5000W, and laser beam wavelength is 1030nm.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the invention, as the mass fraction of Si is increased, the surface of the bonding layer has the tendency of reducing average roughness, more and more fully melted powder, and the defects of air holes, microcracks and the like continuously reduce, and when the mass fraction of Si element reaches 6 wt%, the surface of the bonding layer obtains the optimal tissue structure, so that the wear resistance of the multilayer composite thermal barrier coating is improved.
2. After isothermal oxidation for 20 hours at 1100 ℃, complex oxidation products in the shapes of ellipsoids and flowers are generated on the surface of the bonding layer, the bonding layer presents a triangle layered structure under high power, and the oxide component is Cr through XRD and EDS tests 2 O 3 When the Si element content is 6wt.%, the Cr element content on the surface of the bonding layer is highest, and the generated Cr 2 O 3 The film is more compact, the roughness is minimum, and the high-temperature performance of the multilayer composite thermal barrier coating is improved.
3. The bonding layer material mainly comprises a light gray matrix phase and an acicular reinforcing phase, ni elements are uniformly distributed in the light gray matrix phase of the bonding layer before oxidation, cr and Si elements are widely distributed in the whole bonding layer, and the bonding layer material rapidly diffuses to form an oxide film after oxidation, so that oxygen is prevented from diffusing into the coating, and the oxidation resistance of the multilayer composite thermal barrier coating is improved.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention.
FIG. 1 is a schematic diagram of a preparation flow of a multilayer composite thermal barrier coating according to the present invention;
FIG. 2 shows the cross-sectional morphology of original coatings with different Si contents of a multilayer composite thermal barrier coating provided by the invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments.
In the description of the present invention, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "top," "bottom," "inner," "outer," and the like indicate or are based on the orientation or positional relationship shown in the drawings, merely to facilitate description of the present invention and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Example 1:
referring to fig. 1, the present invention provides a technical solution: the multilayer composite thermal barrier coating comprises a ceramic layer, a thermally grown oxide layer and a bonding layer, wherein the bonding layer is composed of the following raw materials in percentage by weight: 96wt.% of NiCrCoAlY alloy powder and 4wt.% of Si powder; the ceramic layer is composed of the following raw materials in percentage by weight: zrO (ZrO) 2 90％、Y 2 O 3 8 percent of stabilizer and the balance of stabilizer, the preparation method of the multilayer composite thermal barrier coating comprises the following specific steps:
step one: selecting raw materials and equipment: the NiCrCoAlY alloy powder produced by the company of California Jin Jiang, the Si powder produced by the company of Mecanum Biochemical technology, and the 8%Y produced by the company of California Jin Jiang are selected 2 O 3 Stabilized ZrO 2 The powder is prepared by selecting DH-2080 type plasma spraying device, selecting TRULASER CELL 7040 disc type laser of TRUMPF company, and simultaneously performing processing by matching with high-flexibility KUKA KR60L30HA robot, wherein the model of the laser welding head is YW 52;
step two: pretreatment of a substrate: selecting 310S stainless steel, cutting into square samples with the length of 15 multiplied by 5mm, polishing the cut samples to 800# by using SiC sand paper to form a matrix, performing sand blasting on the matrix to remove impurities on the surface of the matrix, enhancing the surface roughness of the matrix, enabling the matrix to be better combined with a coating, placing the sand blasted matrix into an absolute ethyl alcohol and acetone mixed solution, ultrasonically cleaning for 20min, cleaning the surface of the matrix, and drying to finish the pretreatment of the matrix;
step three: plasma spraying: mechanically mixing NiCrCoAlY alloy powder and Si powder uniformly for later use, automatically controlling a DH-2080 type plasma spraying device through a plasma spraying control cabinet, and controlling a mechanical arm to spray the substrate in the second step, so as to realize the spray preparation of a bonding layer and a ceramic layer and form a prefabricated thermal barrier coating;
step four: laser remelting: scanning a high-energy laser beam of a TRULASER CELL 7040 disc laser on the prefabricated thermal barrier coating to form a molten pool, and under the convection and stirring of the molten pool, enabling the components of the prefabricated thermal barrier coating to be more uniform, the grains to be more refined, the pores and the cracks to be eliminated, simultaneously realizing metallurgical bonding between the prefabricated thermal barrier coating and a matrix, and finally rapidly cooling to obtain the multi-layer composite thermal barrier coating;
step five: post-treatment: and carrying out constant-temperature oxidation experiments, thermal cycle experiments, X-ray diffraction analysis, roughness tests and microhardness tests on the multilayer composite thermal barrier coating.
Example 2:
referring to fig. 1, the present invention provides a technical solution: the multilayer composite thermal barrier coating comprises a ceramic layer, a thermally grown oxide layer and a bonding layer, wherein the bonding layer is composed of the following raw materials in percentage by weight: 94wt.% of NiCrCoAlY alloy powder and 6wt.% of Si powder; the ceramic layer is composed of the following raw materials in percentage by weight: zrO (ZrO) 2 92％、Y 2 O 3 8 percent of stabilizer and the balance of stabilizer, the preparation method of the multilayer composite thermal barrier coating comprises the following specific steps:
step one: selecting raw materials and equipment: the NiCrCoAlY alloy powder produced by the company of California Jin Jiang, the Si powder produced by the company of Mecanum Biochemical technology, and the 8%Y produced by the company of California Jin Jiang are selected 2 O 3 Stabilized ZrO 2 The powder is prepared by selecting DH-2080 type plasma spraying device, selecting TRULASER CELL 7040 disc type laser of TRUMPF company, and simultaneously performing processing by matching with high-flexibility KUKA KR60L30HA robot, wherein the model of the laser welding head is YW 52;
step two: pretreatment of a substrate: selecting 310S stainless steel, cutting into square samples with the length of 15 multiplied by 5mm, polishing the cut samples to 800# by using SiC sand paper to form a matrix, performing sand blasting on the matrix to remove impurities on the surface of the matrix, enhancing the surface roughness of the matrix, enabling the matrix to be better combined with a coating, placing the sand blasted matrix into an absolute ethyl alcohol and acetone mixed solution, ultrasonically cleaning for 20min, cleaning the surface of the matrix, and drying to finish the pretreatment of the matrix;
step three: plasma spraying: mechanically mixing NiCrCoAlY alloy powder and Si powder uniformly for later use, automatically controlling a DH-2080 type plasma spraying device through a plasma spraying control cabinet, and controlling a mechanical arm to spray the substrate in the second step, so as to realize the spray preparation of a bonding layer and a ceramic layer and form a prefabricated thermal barrier coating;
step four: laser remelting: scanning a high-energy laser beam of a TRULASER CELL 7040 disc laser on the prefabricated thermal barrier coating to form a molten pool, and under the convection and stirring of the molten pool, enabling the components of the prefabricated thermal barrier coating to be more uniform, the grains to be more refined, the pores and the cracks to be eliminated, simultaneously realizing metallurgical bonding between the prefabricated thermal barrier coating and a matrix, and finally rapidly cooling to obtain the multi-layer composite thermal barrier coating;
step five: post-treatment: and carrying out constant-temperature oxidation experiments, thermal cycle experiments, X-ray diffraction analysis, roughness tests and microhardness tests on the multilayer composite thermal barrier coating.
Example 3:
referring to fig. 1, the present invention provides a technical solution: the multilayer composite thermal barrier coating comprises a ceramic layer, a thermally grown oxide layer and a bonding layer, wherein the bonding layer is composed of the following raw materials in percentage by weight: 92wt.% of NiCrCoAlY alloy powder and 8wt.% of Si powder; the ceramic layer is composed of the following raw materials in percentage by weight: zrO (ZrO) 2 92％、Y 2 O 3 8 percent of stabilizer and the balance of stabilizer, the preparation method of the multilayer composite thermal barrier coating comprises the following specific steps:
step one: selecting raw materials and equipment: niCrCoAlY alloy powder manufactured by Male Jin Jiang spraying Material Co., ltdThe Si powder is 8%Y manufactured by the company Jin Jiang spraying material Co., ltd 2 O 3 Stabilized ZrO 2 The powder is prepared by selecting DH-2080 type plasma spraying device, selecting TRULASER CELL 7040 disc type laser of TRUMPF company, and simultaneously performing processing by matching with high-flexibility KUKA KR60L30HA robot, wherein the model of the laser welding head is YW 52;
step two: pretreatment of a substrate: selecting 310S stainless steel, cutting into square samples with the length of 15 multiplied by 5mm, polishing the cut samples to 800# by using SiC sand paper to form a matrix, performing sand blasting on the matrix to remove impurities on the surface of the matrix, enhancing the surface roughness of the matrix, enabling the matrix to be better combined with a coating, placing the sand blasted matrix into an absolute ethyl alcohol and acetone mixed solution, ultrasonically cleaning for 20min, cleaning the surface of the matrix, and drying to finish the pretreatment of the matrix;
step three: plasma spraying: mechanically mixing NiCrCoAlY alloy powder and Si powder uniformly for later use, automatically controlling a DH-2080 type plasma spraying device through a plasma spraying control cabinet, and controlling a mechanical arm to spray the substrate in the second step, so as to realize the spray preparation of a bonding layer and a ceramic layer and form a prefabricated thermal barrier coating;
step four: laser remelting: scanning a high-energy laser beam of a TRULASER CELL 7040 disc laser on the prefabricated thermal barrier coating to form a molten pool, and under the convection and stirring of the molten pool, enabling the components of the prefabricated thermal barrier coating to be more uniform, the grains to be more refined, the pores and the cracks to be eliminated, simultaneously realizing metallurgical bonding between the prefabricated thermal barrier coating and a matrix, and finally rapidly cooling to obtain the multi-layer composite thermal barrier coating;
step five: post-treatment: and carrying out constant-temperature oxidation experiments, thermal cycle experiments, X-ray diffraction analysis, roughness tests and microhardness tests on the multilayer composite thermal barrier coating.
Comparative example 1:
the raw material of the bonding layer adopts MCrAlY (M=Ni, co or Ni+Co), and the raw material of the ceramic layer adopts 8wt% of ZrO 2O3 stable 2 The other steps are the same as in example 2.
From examples 1 to 32 parts of the multi-layer composite thermal barrier coating are respectively extracted and marked as A 1 、A 2 、B 1 、B 2 、C 1 And C 2 Then with 2 parts of the thermal barrier coating of comparative example 1, denoted as E 1 And E is 2 An isothermal oxidation experiment at 1100 ℃ was performed and the following results were obtained:
TABLE 1
As can be seen by comparison, the oxide composition is Cr by XRD and EDS tests 2 O 3 When the Si element content is 6wt.%, the Cr element content on the surface of the bonding layer is highest, and the generated Cr 2 O 3 The film is more compact and has minimal roughness.
Table 2, bonding layers with different Si content isothermal oxidation at 1100 ℃ for 20h surface element content (wt.%)
As is clear from comparison, the multi-layer composite thermal barrier coating prepared in the embodiment 2 has Cr and Si elements widely distributed on the whole bonding layer, and the Cr and Si elements rapidly diffuse to generate an oxide film after oxidation, so that oxygen is prevented from diffusing into the coating.
As shown in FIG. 2, the surface structure of the bonding layer of comparative example 1 without Si element addition is rough and rough, the whole body is in a loose and porous structure, a large amount of unmelted spherical particles appear in a local area, the bonding layer of example 2 with 6wt.% Si element addition is shown in the graph (g, h), the large-area continuous and smooth structure of the bonding layer surface can be seen, defects such as air holes and micro cracks are obviously reduced, good macroscopic quality is shown, the bonding layer of example 3 with 8wt.% Si element addition is shown in the graph (i, j), the defects such as air holes and micro cracks on the bonding layer surface are increased, the formed low alloy cannot be fully covered, a large amount of micro holes are generated in the liquid alloy shrinkage process of the local area, and fine cracks are observed in the area of the flat structure of the bonding layer under high power, so that the bonding layer surface shows a trend of average roughness reduction, full powder melting, continuous defects such as air holes and micro cracks are seen, and the like with the increase of Si element mass fraction reaching 6wt.% and the best structure of the bonding layer surface is obtained.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art, who is within the scope of the present invention, should make equivalent substitutions or modifications according to the technical scheme of the present invention and the inventive concept thereof, and should be covered by the scope of the present invention.
Claims (7)
1. The multilayer composite thermal barrier coating is characterized by comprising a ceramic layer, a thermally grown oxide layer and a bonding layer, wherein the bonding layer is composed of the following raw materials in percentage by weight: 90-98 wt.% of NiCrCoAlY alloy powder and 2-8 wt.% of Si powder; the ceramic layer is composed of the following raw materials in percentage by weight: zrO (ZrO) 2 90～92％、Y 2 O 3 8-10%, and the balance of stabilizer.
2. The multilayer composite thermal barrier coating of claim 1, wherein the NiCrCoAlY alloy powder and Y 2 O 3 Y in (2) is an oxygen-sensitive element, the element content of which is 0.2 to 1wt.%, and the stabilizer contains trivalent and tetravalent cations.
3. The multilayer composite thermal barrier coating according to claim 1, wherein the thickness of the ceramic layer is 100-500 μm, the thickness of the bonding layer is 80-120 μm, the alloy powder particle size of the NiCrCoAlY alloy powder is 45-75 μm, the Si powder purity is 99.9%, the powder particle size is 25 μm, and the powder particle size of the ceramic layer raw material is 25-85 μm.
4. The multilayer composite thermal barrier coating according to claim 1, wherein the preparation method of the multilayer composite thermal barrier coating comprises the following specific steps:
step one: selecting raw materials and equipment: the NiCrCoAlY alloy powder produced by the company of California Jin Jiang, the Si powder produced by the company of Mecanum Biochemical technology, and the 8%Y produced by the company of California Jin Jiang are selected 2 O 3 Stabilized ZrO 2 The powder is prepared by selecting DH-2080 type plasma spraying device, selecting TRULASER CELL 7040 disc type laser of TRUMPF company, and simultaneously performing processing by matching with high-flexibility KUKA KR60L30HA robot, wherein the model of the laser welding head is YW 52;
step two: pretreatment of a substrate: selecting 310S stainless steel, cutting into square samples with the length of 15 multiplied by 5mm, polishing the cut samples to 800# by using SiC sand paper to form a matrix, performing sand blasting on the matrix to remove impurities on the surface of the matrix, enhancing the surface roughness of the matrix, enabling the matrix to be better combined with a coating, placing the sand blasted matrix into an absolute ethyl alcohol and acetone mixed solution, ultrasonically cleaning for 20min, cleaning the surface of the matrix, and drying to finish the pretreatment of the matrix;
step three: plasma spraying: mechanically mixing NiCrCoAlY alloy powder and Si powder uniformly for later use, automatically controlling a DH-2080 type plasma spraying device through a plasma spraying control cabinet, and controlling a mechanical arm to spray the substrate in the second step, so as to realize the spray preparation of a bonding layer and a ceramic layer and form a prefabricated thermal barrier coating;
step four: laser remelting: scanning a high-energy laser beam of a TRULASER CELL 7040 disc laser on the prefabricated thermal barrier coating to form a molten pool, and under the convection and stirring of the molten pool, enabling the components of the prefabricated thermal barrier coating to be more uniform, the grains to be more refined, the pores and the cracks to be eliminated, simultaneously realizing metallurgical bonding between the prefabricated thermal barrier coating and a matrix, and finally rapidly cooling to obtain the multi-layer composite thermal barrier coating;
step five: post-treatment: and carrying out constant-temperature oxidation experiments, thermal cycle experiments, X-ray diffraction analysis, roughness tests and microhardness tests on the multilayer composite thermal barrier coating.
5. The multilayer composite thermal barrier coating according to claim 4, wherein sand grains selected for sand blasting in the second step are 24# brown alumina, the sand blasting pressure is 0.6-0.75 MPa, and the ratio of absolute ethyl alcohol to acetone in the mixed solution is 3:1.
6. The multilayer composite thermal barrier coating of claim 4, wherein in step three the robot arm translates the spray coating one pass to deposit a 12-15 μm coating on the substrate surface, the coating to be deposited cools, and the spray coating is continued in the same manner, and the process is repeated until an approximately 100 μm bond coat and an approximately 200 μm ceramic top layer are prepared on the substrate surface.
7. The multilayer composite thermal barrier coating of claim 4, wherein the DH-2080 type plasma spray device in step three has parameters of: 500-530A of current, 70-75V of voltage, 38-40L/M of main air flow, 8-10L/M of secondary air flow, 2.5-3L/M of carrier gas flow, 100mm of spraying distance, 35-40 kw of spray gun power and 30rad/M of rotating speed; and in the fourth step, rated output power of the TRULASER CELL 7040 disc laser is 5000W, and laser beam wavelength is 1030nm.
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