CN116770214A - High-temperature-resistant self-lubricating low-friction sealing coating material and preparation method thereof - Google Patents
High-temperature-resistant self-lubricating low-friction sealing coating material and preparation method thereof Download PDFInfo
- Publication number
- CN116770214A CN116770214A CN202310753197.5A CN202310753197A CN116770214A CN 116770214 A CN116770214 A CN 116770214A CN 202310753197 A CN202310753197 A CN 202310753197A CN 116770214 A CN116770214 A CN 116770214A
- Authority
- CN
- China
- Prior art keywords
- self
- lubricating
- spraying
- coating material
- preparing
- 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 73
- 239000011248 coating agent Substances 0.000 title claims abstract description 72
- 239000000463 material Substances 0.000 title claims abstract description 49
- 238000007789 sealing Methods 0.000 title claims abstract description 40
- 238000002360 preparation method Methods 0.000 title claims abstract description 22
- 239000000843 powder Substances 0.000 claims abstract description 52
- 238000005524 ceramic coating Methods 0.000 claims abstract description 34
- MCMNRKCIXSYSNV-UHFFFAOYSA-N Zirconium dioxide Chemical compound O=[Zr]=O MCMNRKCIXSYSNV-UHFFFAOYSA-N 0.000 claims abstract description 28
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 26
- 239000000956 alloy Substances 0.000 claims abstract description 26
- 238000007750 plasma spraying Methods 0.000 claims abstract description 19
- 229910002080 8 mol% Y2O3 fully stabilized ZrO2 Inorganic materials 0.000 claims abstract description 17
- 229910004261 CaF 2 Inorganic materials 0.000 claims abstract description 15
- 238000005516 engineering process Methods 0.000 claims abstract description 15
- 239000011159 matrix material Substances 0.000 claims abstract description 13
- 238000005328 electron beam physical vapour deposition Methods 0.000 claims abstract description 8
- 238000010285 flame spraying Methods 0.000 claims abstract description 5
- 238000005253 cladding Methods 0.000 claims abstract description 4
- 239000010410 layer Substances 0.000 claims description 30
- 238000005507 spraying Methods 0.000 claims description 27
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 14
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 14
- 238000000034 method Methods 0.000 claims description 14
- 239000002245 particle Substances 0.000 claims description 8
- 229910052786 argon Inorganic materials 0.000 claims description 7
- 229910052757 nitrogen Inorganic materials 0.000 claims description 7
- 229910000601 superalloy Inorganic materials 0.000 claims description 7
- 239000000758 substrate Substances 0.000 claims description 6
- 229910001293 incoloy Inorganic materials 0.000 claims description 4
- 238000004372 laser cladding Methods 0.000 claims description 4
- 238000010891 electric arc Methods 0.000 claims description 3
- 238000005488 sandblasting Methods 0.000 claims description 3
- 239000012790 adhesive layer Substances 0.000 claims description 2
- 238000005238 degreasing Methods 0.000 claims description 2
- 238000005461 lubrication Methods 0.000 abstract description 7
- 239000007921 spray Substances 0.000 abstract description 6
- 239000000919 ceramic Substances 0.000 description 17
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 9
- 239000007789 gas Substances 0.000 description 8
- 238000002156 mixing Methods 0.000 description 8
- 239000002131 composite material Substances 0.000 description 7
- NRTOMJZYCJJWKI-UHFFFAOYSA-N Titanium nitride Chemical compound [Ti]#N NRTOMJZYCJJWKI-UHFFFAOYSA-N 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 239000011253 protective coating Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 238000005266 casting Methods 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 239000003153 chemical reaction reagent Substances 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 229910052746 lanthanum Inorganic materials 0.000 description 2
- 229910052759 nickel Inorganic materials 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 229910052582 BN Inorganic materials 0.000 description 1
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910052688 Gadolinium Inorganic materials 0.000 description 1
- WMOHXRDWCVHXGS-UHFFFAOYSA-N [La].[Ce] Chemical compound [La].[Ce] WMOHXRDWCVHXGS-UHFFFAOYSA-N 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 230000005669 field effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 229910001938 gadolinium oxide Inorganic materials 0.000 description 1
- 229940075613 gadolinium oxide Drugs 0.000 description 1
- CMIHHWBVHJVIGI-UHFFFAOYSA-N gadolinium(iii) oxide Chemical compound [O-2].[O-2].[O-2].[Gd+3].[Gd+3] CMIHHWBVHJVIGI-UHFFFAOYSA-N 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 230000006698 induction Effects 0.000 description 1
- FZLIPJUXYLNCLC-UHFFFAOYSA-N lanthanum atom Chemical compound [La] FZLIPJUXYLNCLC-UHFFFAOYSA-N 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910044991 metal oxide Inorganic materials 0.000 description 1
- 150000004706 metal oxides Chemical class 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 229910002077 partially stabilized zirconia Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000002861 polymer material Substances 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 239000004065 semiconductor Substances 0.000 description 1
- 230000008093 supporting effect Effects 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
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame spraying
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/08—Oxides
- C23C14/083—Oxides of refractory metals or yttrium
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
- C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer at least one MCrAlX layer
-
- 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
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
-
- 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
- C23C4/04—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
-
- 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
- C23C4/131—Wire arc spraying
-
- 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)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Inorganic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The application provides a preparation method of a high-temperature-resistant self-lubricating low-friction sealing coating material, which is characterized by comprising the following preparation steps: s1, adopting plasma spraying, supersonic flame spraying and laser meltingThe coating equipment or the arc cladding equipment sprays the NiCoCrAlY alloy powder on the surface of the alloy matrix to form a Ni-based bonding layer; s2, preparing 8YSZ powder on the surface of the Ni-based bonding layer by adopting an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology to form a first ceramic coating; s3, further carrying out mass ratio of 1 by using an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology: 1:1, LCO and GZO, or a mass ratio of 10:3:7 first co-doped zirconia system, moS 2 And CaF 2 The formed second co-doped zirconia system is prepared on the surface of the first ceramic coating to form a second ceramic coating, and the prepared sealing coating has high temperature resistance, self-lubrication and low friction.
Description
Technical Field
The application relates to the technical field of composite coatings, in particular to a high-temperature-resistant self-lubricating low-friction sealing coating material and a preparation method thereof.
Background
The high-temperature alloy has wide application in the fields of gas turbines, thermal power generation, atomic energy industry and the like by virtue of excellent high-temperature mechanical property, oxidation resistance and corrosion resistance. However, with the development of aerospace engine and gas turbine technologies, higher requirements are put on the clearance seal between the tips of the blades and castings of the compressor and turbine parts. The abradable seal coating is generally used for sealing the gas path of an aircraft turbine engine, and aims to reduce the clearance between the tip of a blade and castings of a compressor and a turbine part, play roles in protecting the blade, reducing air leakage between stages and improving the efficiency of the engine, and are widely applied in the field of aviation at present. The preparation of the sealing coating is a key technology for sealing the gas path of the turbine engine.
In order to prevent the coating from falling off, the abradable seal coating not only needs to have relatively high bonding strength, but also has good comprehensive performance. The coating is hard enough to ensure the normal work under the high-temperature and high-speed airflow erosion, and the requirement is mainly realized by tightly sealing the metal phase (Al base, cu base, ni base, co base and the like) in the coating, so that the coating can provide a supporting effect. The rotor is soft enough to be worn preferentially when being worn with a rotor component, so that the blade is prevented from being scraped to be damaged, the requirement is mainly achieved by tightly sealing nonmetallic phases (graphite, boron nitride, high polymer materials and the like) and pores in the coating, the pores can effectively reduce the hardness of the coating, and the nonmetallic phases can provide lubrication.
Along with the continuous rise of the temperature of the fuel gas, the high-temperature resistance of the sealing coating is required to be higher. Meanwhile, due to the functional characteristics of the sealing coating, on one hand, the sealing coating needs to be wear-resistant, and on the other hand, the coating cannot damage friction of a turbine part, so that new and higher requirements are provided for the wear-resistant sealing coating.
Disclosure of Invention
Aiming at the problems in the prior art, the application provides a high-temperature-resistant low-friction double-layer ceramic protective coating material and a preparation method thereof, and the material and the preparation technology of a double-layer gradient composite functional coating are designed to prepare the 1300 ℃ high-temperature-resistant double-layer ceramic protective coating material (sealing coating) with high-temperature resistance, self-lubrication and low-friction performance.
The specific application comprises the following steps:
in a first aspect, the application provides a preparation method of a high-temperature-resistant, self-lubricating and low-friction sealing coating material, which comprises the following preparation steps:
s1, spraying NiCoCrAlY alloy powder on the surface of an alloy matrix by adopting plasma spraying, supersonic flame spraying, laser cladding equipment or electric arc cladding equipment to form a Ni-based bonding layer;
s2, preparing 8YSZ powder on the surface of the Ni-based bonding layer by adopting an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology to form a first ceramic coating;
s3, further carrying out mass ratio of 1 by using an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology: 1:1, LCO and GZO, or a mass ratio of 10:3:7, the first combined powder and MoS 2 And CaF 2 And preparing the formed second combined powder on the surface of the first ceramic coating to form a second ceramic coating.
Optionally, in step S1, the thickness of the Ni-based adhesive layer is 1-150 μm.
Optionally, in step S2, the particle size of the 8YSZ powder is 37-69 μm.
Optionally, in step S2, the powder feeding rate of the 8YSZ powder is 3-4 g/min.
Optionally, in step S2, the thickness of the first ceramic coating is 200-300 μm;
the microstructure of the first ceramic coating has a vertical crack structure, and the density of the vertical cracks is 2-4 channels per millimeter.
Optionally, in step S3, the first combined powder and MoS 2 And CaF 2 The particle sizes of the particles are 40-80 mu m.
Optionally, in step S3, the thickness of the second ceramic coating is 100-150 μm;
the microstructure of the second ceramic coating has a vertical crack structure, the density of the vertical cracks being 2-4 lanes per millimeter.
Optionally, the working parameters of the atmospheric laminar plasma spraying technology are as follows:
the volume ratio of nitrogen to argon is 7:3, a step of;
the working current is 120-160A;
the output power is 15-30kW;
the spraying distance is 200-300mm;
the spraying speed is 0.4-0.8m/s;
the spraying interval is 3-8mm.
Optionally, the working parameters of the atmospheric laminar plasma spraying technology are as follows:
the volume ratio of nitrogen to argon is 7:3, a step of;
the working current is 160A;
the output power is 25-26kW;
the spraying distance is 250mm;
the spraying speed is 0.4m/s;
the spraying interval was 4mm.
Optionally, the alloy substrate comprises: superalloy K456 or Incoloy M956.
Optionally, the surface of the alloy matrix is the surface of the alloy matrix subjected to degreasing and sand blasting.
In a second aspect, the present application provides a high temperature resistant, self-lubricating, low friction seal coating material obtained by the preparation method of the first aspect, where the high temperature resistant, self-lubricating, low friction seal coating material includes: the first ceramic coating and the second ceramic coating are sequentially positioned on the surface of the alloy matrix with the bonding layer.
Compared with the prior art, the application has the following advantages:
the application provides a sealing coating material which is prepared under the atmospheric condition and has high temperature resistance, self lubrication and low friction and a preparation method, wherein the sealing coating has a double-layer ceramic layer structure, the bottom ceramic layer is 8YSZ ceramic, and the top ceramic layer mainly comprises any one of the following component systems: (1) LZO+LCO+GZO co-doped zirconia system; (2) MoS (MoS) 2 、CaF 2 La, ce and Gd co-doped zirconia system. Because the top ceramic layer has high temperature resistance, self-lubrication and low friction performance, the ceramic layer has lower friction coefficient (less than 0.4) and thermal conductivity less than 1.8W/(mK) at 1000-1300 ℃, and the high temperature resistance of the sealing coating can be greatly improved. And meanwhile, when the ceramic coating is prepared, an atmospheric laminar plasma spray gun is adopted, so that the ceramic coating with a higher-density penetrating vertical crack structure can be prepared, and the thermal cycle life of the sealing coating can be remarkably prolonged.
Drawings
In order to more clearly illustrate the embodiments of the application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 shows a schematic flow chart of a preparation method of a high-temperature-resistant, self-lubricating and low-friction sealing coating material provided by the embodiment of the application;
fig. 2 shows a schematic structural diagram of a high-temperature-resistant, self-lubricating and low-friction sealing coating material provided by the embodiment of the application.
Detailed Description
The following examples are provided for a better understanding of the present application and are not limited to the preferred embodiments described herein, but are not intended to limit the scope of the application, any product which is the same or similar to the present application, whether in light of the present teachings or in combination with other prior art features, falls within the scope of the present application.
Specific experimental steps or conditions are not noted in the examples and may be performed in accordance with the operation or conditions of conventional experimental steps described in the prior art in the field. The reagents used, as well as other instruments, are conventional reagent products available commercially, without the manufacturer's knowledge. Furthermore, the drawings are merely schematic illustrations of embodiments of the application and are not necessarily drawn to scale. The same reference numerals in the drawings denote the same or similar parts, and thus a repetitive description thereof will be omitted. Some of the block diagrams shown in the figures are functional entities and do not necessarily correspond to physically or logically separate entities.
Currently, the gas temperature is close to 2000K and is significantly higher than the melting point of the superalloy (about 1300 ℃). Therefore, superalloys have not fully met the use requirements. To accommodate the harsh high temperature operating environment, superalloy surface modification is necessary. The heat-insulating wear-resistant self-sealing coating is a high-temperature-resistant wear-resistant functional coating and can meet the requirements of high temperature resistance and wear resistance. At present, ceramic materials commonly used for the sealing coating at present comprise yttria partially stabilized zirconia YSZ, gadolinium oxide doped zirconia GZO, lanthanum zirconate LZO, lanthanum cerium acid LCO and other ultrahigh-temperature rare earth ceramic materials. However, these coating materials mainly serve as heat insulation, do not have a low friction coefficient, have a high friction coefficient, have little change in friction coefficient at high temperature, and do not have the comprehensive characteristics of self-lubrication, low friction coefficient and high heat insulation.
Based on the design, the application aims to ensure that the prepared double-layer ceramic coating meets the multifunctional application requirements of high temperature resistance, self lubrication and low friction under the excitation induction of external factors through the design of the double-layer gradient composite functional coating. The specific implementation mode is as follows:
in a first aspect, the present application provides a method for preparing a high temperature resistant, self-lubricating, low friction sealing coating material, fig. 1 shows a schematic flow chart of a preparation method of a high temperature resistant, self-lubricating, low friction sealing coating material provided by an embodiment of the present application, and as shown in fig. 1, the preparation method includes the following preparation steps:
s1, spraying NiCoCrAlY alloy powder on the surface of an alloy matrix by adopting plasma spraying, supersonic flame spraying, laser cladding equipment or electric arc cladding equipment to form a Ni-based bonding layer;
s2, preparing 8YSZ powder on the surface of the Ni-based bonding layer by adopting an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology to form a first ceramic coating;
s3, further carrying out mass ratio of 1 by using an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology: 1:1, LCO and GZO, or a mass ratio of 10:3:7, the first combined powder and MoS 2 And CaF 2 And preparing the formed second combined powder on the surface of the first ceramic coating to form a second ceramic coating.
In specific implementation, the application provides a preparation method of a high-temperature-resistant self-lubricating low-friction sealing coating material, which comprises the following preparation steps:
the first step: the mass ratio of the components is 1:1:1 to obtain an LZO-LCO-GZO co-doped zirconia system or
The mass ratio of the components is 1:1:1 to obtain an LZO-LCO-GZO co-doped zirconia system, and then further adding MoS 2 And CaF 2 Forming LZO-LCO-GZO and MoS 2 And CaF 2 The mass ratio of (2) is 10:3:7, the second co-doped zirconia system is mixed uniformly by adopting a mechanical powder mixing mode.
And a second step of: deoiling and sand blasting the high-temperature alloy to obtain an alloy matrix with certain roughness, wherein the alloy matrix can be high-temperature alloy K456 or Incoloy M956.
And a third step of: preparing a NiCoCrAlYNI-based bonding layer on a high-temperature alloy substrate by adopting plasma spraying, supersonic flame spraying or laser cladding equipment, wherein the thickness of the bonding layer is 1-150 mu m;
fourth step: and (3) preparing a ceramic layer on the surface of the bonding layer prepared in the third step by adopting an atmospheric laminar plasma spraying mode, wherein the ceramic layer is 8YSZ in material composition, and preparing the 8YSZ ceramic layer with the thickness of about 200 mu m on the bonding layer by controlling spraying parameters.
Fifth step: on the basis of the 8YSZ ceramic coating prepared in the fourth step, preparing the outermost ceramic coating by using an atmospheric laminar plasma spraying mode, wherein the type of the coating is LZO-LCO-GZO co-doped zirconia system or LZO-LCO-GZO co-doped zirconia system+MoS 2 +CaF 2 The co-doped zirconia system had a coating thickness of about 100 μm.
Fig. 2 shows a schematic structural diagram of a high temperature resistant, self-lubricating, low friction sealing coating material provided by the embodiment of the application, as shown in fig. 2, the high temperature resistant, self-lubricating, low friction sealing coating material includes: the first ceramic coating 103 and the second ceramic coating 104 are sequentially positioned on the surface of the alloy substrate with the bonding layer.
The high-temperature-resistant, self-lubricating and low-friction sealing coating material coating prepared by the application has a double-layer ceramic layer composite structure, and the outermost ceramic layer has high-temperature-resistant, self-lubricating and low-friction sealing properties, so that the coating can resist higher working temperature in the service process and has excellent sealing effect. In the high-temperature-resistant, self-lubricating and low-friction sealing coating material, the first ceramic coating and the second ceramic coating both have high-density penetrability vertical crack structures, the crack density is 1-4 times per millimeter, and the penetrability vertical cracks exist, so that the stress after thermal cycle and thermal service is greatly relaxed, and the high-temperature-resistant and low-friction double-layer ceramic protective coating material can be matched and adapted to the current working temperature higher than 1000 ℃.
In addition, the application provides a novel metal oxide semiconductor field effect transistor containing MoS 2 And CaF 2 The sealing coating material of the (C) has lower friction coefficient (less than 0.4) at 1000-1300 ℃ and thermal conductivity less than 1.8W/(mK). Meets the use requirement of high temperature resistance and low friction.
In order to make the present application more clearly understood by those skilled in the art, the following examples will illustrate a high temperature resistant, self-lubricating, low friction seal coating material and a method for preparing the same.
Example 1: high-temperature alloy K456 surface spray-coating titanium nitride coating
The nickel-based superalloy K465 alloy has higher creep resistance, higher fatigue resistance and higher temperature bearing capacity.
1) Preparing a base material, and fixing the base material by a fixing and clamping device. LZO, LCO, GZO powder was mixed according to a mass ratio of 1:1: mixing uniformly in proportion of 1.
2) A base material of 8X 200mm was prepared and fixed to a base temperature control unit by a fixing and clamping device.
3) After the surface was sandblasted, a 150 μm thick bond coat was first obtained using a supersonic flame spray NiCoCrAlY coating.
4) 8YSZ powder with granularity of 37-69 mu m is adopted, and the powder feeding rate is 3-4 g/min.
5) The plasma control device and the plasma generating device are started.
6) Through the long jet control device, the working gas is adjusted to be nitrogen and argon, and the volume ratio is 7:3, working current 120A and output power of 17-18kW.
7) The spraying distance was selected to be 200mm, the scanning speed was 0.4m/s, and the interval was 3mm.
8) Starting the powder feeding device to feed out the powder.
9) The mechanical arm is controlled, and the coating with the thickness of more than 200 mu m can be obtained by circularly spraying for 30 times.
10 8YSZ ceramic powder in the powder feeder is replaced by LZO, LCO and GZO powder, the granularity of the powder is 40-80 mu m, and the steps (5) - (8) are repeated.
11 The mechanical arm is controlled, and the coating with the thickness of more than 100 mu m can be obtained by circularly spraying for 20 times.
12 The powder feeder is closed, then the plasma generator generating unit is closed, and finally the circulating water device of the plasma generator is closed.
13 Waiting for the matrix temperature control unit to cool the sample to room temperature, and taking down the sample to obtain the composite ceramic coating.
Example 2: high-temperature alloy K456 surface spray-coating titanium nitride coating
The nickel-based superalloy K465 alloy has higher creep resistance, higher fatigue resistance and higher temperature bearing capacity.
1) Preparing a base material, and fixing the base material by a fixing and clamping device. LZO, LCO, GZO powder was mixed according to a mass ratio of 1:1:1, mixing uniformly, mixing the uniformly mixed LZO, LCO, GZO powder and MoS 2 With CaF 2 The mass ratio of the powder is 10:3: and 7, uniformly mixing the materials in proportion.
2) Preparing a base materialIs fixed on the substrate temperature control unit through a fixed clamping device.
3) After the surface was sandblasted, a 150 μm thick bond coat was first obtained using a supersonic flame spray NiCoCrAlY coating.
4) 7YSZ powder with granularity of 37-69 mu m is adopted, and the powder feeding rate is 3-4 g/min.
5) The plasma control device and the plasma generating device are started.
6) Through the long jet control device, the working gas is adjusted to be nitrogen and argon, and the volume ratio is 7:3, working current 120A and output power of 17-18kW.
7) The spraying distance was selected to be 200mm, the scanning speed was 0.4m/s, and the interval was 3mm.
8) Starting the powder feeding device to feed out the powder.
9) The mechanical arm is controlled, and the coating with the thickness of more than 200 mu m can be obtained by circularly spraying for 30 times.
10 Replacement of 8YSZ ceramic powder in powder feeder to LZO, LCO, GZO, moS 2 ，CaF 2 And (3) repeating the steps (5) - (8) by using powder with the particle size of 40-80 mu m.
11 The mechanical arm is controlled, and the coating with the thickness of more than 100 mu m can be obtained by circularly spraying for 20 times.
12 The powder feeder is closed, then the plasma generator generating unit is closed, and finally the circulating water device of the plasma generator is closed.
13 Waiting for the matrix temperature control unit to cool the sample to room temperature, and taking down the sample to obtain the composite ceramic coating.
Example 3: incoloy M956 surface spray titanium nitride coating
The M956 alloy has high lasting strength and excellent oxidation and corrosion resistance at high temperature, and is widely applied as a hot end part of an advanced aeroengine at the working temperature of 1000-1200 ℃ and a heat protection part exceeding 1300 ℃ in an industrial furnace.
1) Preparing a base material, and fixing the base material by a fixing and clamping device. LZO, LCO, GZO powder was mixed according to a mass ratio of 1:1:1, mixing uniformly, mixing the uniformly mixed LZO, LCO, GZO powder and MoS 2 With CaF 2 The mass ratio of the powder is 10:3: and 7, uniformly mixing the materials in proportion.
2) Preparing a base materialIs fixed on the substrate temperature control unit through a fixed clamping device.
3) After the surface was sandblasted, a 150 μm thick bond coat was first obtained using a supersonic flame spray NiCoCrAlY coating.
4) 8YSZ powder with granularity of 37-69 mu m is adopted, and the powder feeding rate is 3-4 g/min.
5) The plasma control device and the plasma generating device are started.
6) Through the long jet control device, the working gas is adjusted to be nitrogen and argon, and the volume ratio is 7:3, working current 120A and output power of 17-18kW.
7) The spraying distance was selected to be 200mm, the scanning speed was 0.4m/s, and the interval was 3mm.
8) Starting the powder feeding device to feed out the powder.
9) The mechanical arm is controlled, and the coating with the thickness of more than 200 mu m can be obtained by circularly spraying for 30 times.
10 Replacement of 8YSZ ceramic powder in powder feeder to LZO, LCO, GZO, moS 2 ，CaF 2 And (3) repeating the steps (5) - (8) by using powder with the particle size of 40-80 mu m.
11 The mechanical arm is controlled, and the coating with the thickness of more than 100 mu m can be obtained by circularly spraying for 20 times.
12 The powder feeder is closed, then the plasma generator generating unit is closed, and finally the circulating water device of the plasma generator is closed.
13 Waiting for the matrix temperature control unit to cool the sample to room temperature, and taking down the sample to obtain the composite ceramic coating.
In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, one skilled in the art can combine and combine the different embodiments or examples described in this specification.
For the purposes of simplicity of explanation, the methodologies are shown as a series of acts, but one of ordinary skill in the art will recognize that the present application is not limited by the order of acts described, as some acts may, in accordance with the present application, occur in other orders and concurrently. Further, those skilled in the art will recognize that the embodiments described in the specification are all of the preferred embodiments, and that the acts and components referred to are not necessarily required by the present application.
The application provides a high temperature resistant, self-lubricating and low friction sealing coating material and a preparation method thereof, and specific examples are applied to illustrate the principle and the implementation mode of the application, and the illustration of the examples is only used for helping to understand the method and the core idea of the application; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present application, the present description should not be construed as limiting the present application in view of the above.
Claims (10)
1. The preparation method of the high-temperature-resistant self-lubricating low-friction sealing coating material is characterized by comprising the following preparation steps:
s1, spraying NiCoCrAlY alloy powder on the surface of an alloy matrix by adopting plasma spraying, supersonic flame spraying, laser cladding equipment or electric arc cladding equipment to form a Ni-based bonding layer;
s2, preparing 8YSZ powder on the surface of the Ni-based bonding layer by adopting an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology to form a first ceramic coating;
s3, further carrying out mass ratio of 1 by using an atmospheric laminar plasma spraying or electron beam physical vapor deposition technology: 1:1, LCO and GZO, or a mass ratio of 10:3:7, said first co-doped zirconia system, moS 2 And CaF 2 And preparing a second co-doped zirconia system on the surface of the first ceramic coating to form a second ceramic coating.
2. The method for preparing a high temperature resistant, self-lubricating, low friction seal coating material according to claim 1, wherein in step S1, the thickness of the Ni-based adhesive layer is 1-150 μm.
3. The method for preparing a high temperature resistant, self-lubricating, low friction seal coating material according to claim 1, wherein in step S2, the particle size of the 8YSZ powder is 37-69 μm;
the powder feeding speed of the 8YSZ powder is 3-4 g/min;
the thickness of the first ceramic coating is 200-300 mu m;
the microstructure of the first ceramic coating has a vertical crack structure, and the density of the vertical cracks is 2-4 channels per millimeter.
4. The preparation method of the high-temperature-resistant, self-lubricating and low-friction sealing coating material according to claim 1The method is characterized in that in the step S3, the first co-doped zirconia system, moS 2 And CaF 2 The particle sizes of the particles are 40-80 mu m.
5. The method for preparing a high temperature resistant, self-lubricating, low friction seal coating material according to claim 1, wherein in step S3, the thickness of the second ceramic coating is 100-150 μm;
the microstructure of the second ceramic coating has a vertical crack structure, the density of the vertical cracks being 2-4 lanes per millimeter.
6. The method for preparing the high temperature resistant, self-lubricating and low friction sealing coating material according to claim 1, wherein the working parameters of the atmospheric laminar plasma spraying technology are as follows:
the volume ratio of nitrogen to argon is 7:3, a step of;
the working current is 120-160A;
the output power is 15-30kW;
the spraying distance is 200-300mm;
the spraying speed is 0.4-0.8m/s;
the spraying interval is 3-8mm.
7. The method for preparing the high temperature resistant, self-lubricating and low friction sealing coating material according to claim 1, wherein the working parameters of the atmospheric laminar plasma spraying technology are as follows:
the volume ratio of nitrogen to argon is 7:3, a step of;
the working current is 160A;
the output power is 25-26kW;
the spraying distance is 250mm;
the spraying speed is 0.4m/s;
the spraying interval was 4mm.
8. The method for preparing a high temperature resistant, self-lubricating, low friction seal coating material according to claim 1, wherein the alloy substrate comprises: superalloy K456 or Incoloy M956.
9. The method for preparing the high-temperature-resistant, self-lubricating and low-friction sealing coating material according to claim 1, wherein the surface of the alloy matrix is subjected to degreasing and sand blasting.
10. A high temperature resistant, self-lubricating, low friction seal coating material obtained by the method of any one of the preceding claims 1-8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310753197.5A CN116770214A (en) | 2023-06-25 | 2023-06-25 | High-temperature-resistant self-lubricating low-friction sealing coating material and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310753197.5A CN116770214A (en) | 2023-06-25 | 2023-06-25 | High-temperature-resistant self-lubricating low-friction sealing coating material and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116770214A true CN116770214A (en) | 2023-09-19 |
Family
ID=87987530
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310753197.5A Pending CN116770214A (en) | 2023-06-25 | 2023-06-25 | High-temperature-resistant self-lubricating low-friction sealing coating material and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116770214A (en) |
-
2023
- 2023-06-25 CN CN202310753197.5A patent/CN116770214A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US11149338B2 (en) | Gas turbine engine component coating with self-healing barrier layer | |
| Hardwicke et al. | Advances in thermal spray coatings for gas turbines and energy generation: a review | |
| DeMasi-Marcin et al. | Protective coatings in the gas turbine engine | |
| EP2521802B1 (en) | Coating system for clearance control in rotating machinery | |
| CA2653270C (en) | Blade tip coatings using high purity powders | |
| US20070274837A1 (en) | Blade tip coatings | |
| CN102695818B (en) | The ceramic thermal insulation coating of nanometer and micrometer structure | |
| EP1840238A2 (en) | Oxidation-resistant coating and formation method thereof, thermal barrier coating, heat-resistant member, and gas turbine | |
| US20110171488A1 (en) | Thermal barrier coating systems | |
| US20080026160A1 (en) | Blade tip coating processes | |
| EP1908856A2 (en) | Segmented abradable coatings and process(es) for applying the same | |
| US20110048017A1 (en) | Method of depositing protective coatings on turbine combustion components | |
| US8722202B2 (en) | Method and system for enhancing heat transfer of turbine engine components | |
| Tailor et al. | Development of a new TBC system for more efficient gas turbine engine application | |
| Avci et al. | Microstructure and oxidation behavior of atmospheric plasma-sprayed thermal barrier coatings | |
| Suzuki et al. | The current status of environmental barrier coatings and future direction of thermal spray process | |
| US20190047253A1 (en) | Adhesion promoter layer for joining a high-temperature protection layer to a substrate, and method for producing same | |
| US20140112758A1 (en) | High Temperature Components With Thermal Barrier Coatings for Gas Turbine | |
| Wortman et al. | Bond coat development for thermal barrier coatings | |
| CN116770214A (en) | High-temperature-resistant self-lubricating low-friction sealing coating material and preparation method thereof | |
| EP2423347A1 (en) | Method for forming a thermal barrier coating and a turbine component with the thermal barrier coating | |
| Ying et al. | Thermal shock failure mechanism of nanostructured zirconia coating by atmospheric plasma spraying | |
| JPH09176821A (en) | Radiation shield coating member and its production | |
| Saha et al. | Application of thermal barrier coating in high temperature resistance | |
| Li et al. | Thermal barrier coating for aerial and aerospace engine |
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 |