CN117051348A - Na-resistant 2 SO 4 +V 2 O 5 Corrosion gas turbine thermal barrier coating and preparation method thereof - Google Patents

Na-resistant 2 SO 4 +V 2 O 5 Corrosion gas turbine thermal barrier coating and preparation method thereof Download PDF

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Publication number
CN117051348A
CN117051348A CN202311040874.5A CN202311040874A CN117051348A CN 117051348 A CN117051348 A CN 117051348A CN 202311040874 A CN202311040874 A CN 202311040874A CN 117051348 A CN117051348 A CN 117051348A
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China
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thermal barrier
barrier coating
gas turbine
resistant
spraying
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Inventor
于海原
孙健
颜开
郭宇威
刘广华
邬雅靓
孟庆颜
应宇茜
李振瑞
余志勇
李占青
刘伟
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Beijing Beiye Functional Materials Corp
China United Heavy Gas Turbine Technology Co Ltd
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Beijing Beiye Functional Materials Corp
China United Heavy Gas Turbine Technology Co Ltd
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Priority to CN202311040874.5A priority Critical patent/CN117051348A/en
Publication of CN117051348A publication Critical patent/CN117051348A/en
Pending legal-status Critical Current

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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
    • C23C4/11—Oxides
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)

Abstract

The embodiment of the invention discloses a Na-resistant alloy 2 SO 4 +V 2 O 5 A thermal barrier coating of a corroded gas turbine and a preparation method thereof. The thermal barrier coating of the gas turbine comprises a bonding layer, an inner ceramic layer and an alkaline surface layer from inside to outside, wherein the bonding layer is arranged on the surface of a substrate, the alkaline surface layer is made of 8YSZ and alkaline oxide in a mass ratio of 1-4:1, and the alkaline oxide is selected from Gd 2 O 3 、Nd 2 O 3 、La 2 O 3 、TiO 2 One or more of the following. The invention has the advantages of easily obtained coating raw materials, simple operation in the preparation process and high flexibility, and can effectively solve the Na of the thermal barrier coating of the combustion engine 2 SO 4 +V 2 O 5 Corrosion problems.

Description

Na-resistant 2 SO 4 +V 2 O 5 Corrosion gas turbine thermal barrier coating and preparation method thereof
Technical Field
The embodiment of the invention relates to the technical field of thermal barrier coatings, in particular to a Na-resistant coating 2 SO 4 +V 2 O 5 A thermal barrier coating of a corroded gas turbine and a preparation method thereof.
Background
Thermal Barrier Coatings (TBCs) have been widely used in high temperature components of gas turbines to isolate the metal substrate from the high temperature gas, which can significantly increase the service temperature and thermal efficiency of hot side components of the gas turbine. The thermal barrier coating mainly comprises a metal bonding layer and a ceramic layer, wherein the ceramic layer plays a role of a thermal barrier. 8YSZ (8%Y) 2 O 3 -ZrO 2 ) Due to its advantagesThe material has the advantages of different high melting points, low thermal conductivity, compatibility with the thermal expansion coefficient of the metal bonding layer and excellent thermal performance and mechanical performance, and is the most widely used thermal barrier coating material of the gas turbine at present.
However 8YSZ is less resistant to the corrosive salts containing V, na and S and can severely degrade in hot corrosive environments, especially in marine environments and in service environments with poor fuel quality. The ocean atmosphere and the inferior fuel contain a large amount of Na 2 SO 4 +V 2 O 5 And salt impurities, molten salt can permeate into the coating to chemically react with the coating, so that the performance of the coating is degraded and the coating is accelerated to fail. The reaction mechanism is NaVO in a molten state 3 Penetrate into the interior through the internal voids of the ceramic and preferentially interact with stabilizer Y in 8YSZ 2 O 3 React to generate YVO 4 Precipitation of Y element in lattice, zrO 2 Destabilization from t' phase to m phase, this process is accompanied by a 3% -5% volume expansion, resulting in a transition of the coating stress state to initiate cracks and eventually flaking. Peeling of the coating can cause the metal substrate to lose heat protection and be directly exposed to a high-temperature gas environment, so that irreversible damage is caused to the hot end component.
The main preparation process of the thermal barrier coating of the gas turbine is Air-plasma Spraying (APS), and certain pores and microcracks exist in the coating prepared by the process. This structure is advantageous in reducing the thermal conductivity of the coating, but on the other hand also increases penetration of corrosive molten salts into the interior of the coating. The degree of hot corrosion of the coating is related to the penetration depth of the molten salt, so that the penetration of the molten salt into the ceramic layer is suppressed by improving the Na resistance thereof 2 SO 4 +V 2 O 5 An important direction of corrosion.
At present, the Na resistance of the thermal barrier coating is relieved 2 SO 4 +V 2 O 5 The main method of corrosion is to use Na 2 SO 4 +V 2 O 5 Inert ceramic materials with lower reaction rates (e.g. Gd 2 Zr 2 O 7 ，LaPO 4 ，Sm 2 Zr 2 O 7 Etc.) as a ceramic layer or protective layer. Although the following are providedHowever, this approach can reduce the degradation rate of the coating to some extent, but has limited ability to inhibit penetration of corrosive molten salts into the coating due to the pore structure characteristics of the thermal barrier coating. Meanwhile, the problem that the thermal expansion coefficient of the inert ceramic materials is lower than 8YSZ can aggravate the thermal stress mismatch between the coating and the bonding layer, so that the service life of the coating is shortened, and the large-scale industrial application of the inert ceramic materials is limited.
Disclosure of Invention
Therefore, the embodiment of the invention provides a Na-resistant alloy 2 SO 4 +V 2 O 5 A thermal barrier coating of a corroded gas turbine and a preparation method thereof.
In order to achieve the above object, the embodiment of the present invention provides the following technical solutions:
according to a first aspect of an embodiment of the present invention, there is provided a Na-resistant 2 SO 4 +V 2 O 5 The thermal barrier coating of the corroded gas turbine comprises a bonding layer, an inner ceramic layer and an alkaline surface layer from inside to outside, wherein the bonding layer is arranged on the surface of a substrate, the alkaline surface layer is prepared from 8YSZ and alkaline oxide in a mass ratio of 1-4:1, and the alkaline oxide is selected from Gd 2 O 3 、Nd 2 O 3 、La 2 O 3 、TiO 2 One or more of the following.
Further, the thickness of the alkaline surface layer is 200-300 micrometers, and the porosity is 5% -10%.
Further, the raw material of the inner ceramic layer is 8YSZ; and/or the number of the groups of groups,
the thickness of the inner ceramic layer is 100-300 micrometers, and the void ratio is 10% -20%.
Further, the bonding layer is MCrAlY, wherein M is Ni or Co; and/or the number of the groups of groups,
the thickness of the bonding layer is 150-250 micrometers.
Further, the raw material of the matrix is nickel-based alloy.
According to a second aspect of embodiments of the present invention, there is provided a Na-resistant alloy as described above 2 SO 4 +V 2 O 5 The preparation method of the corroded thermal barrier coating of the gas turbine comprises the following steps:
(1) Pretreating a matrix;
(2) Preparing a bonding layer on the surface of a substrate by adopting atmospheric plasma spraying;
(3) Preparing an inner ceramic layer on the surface of the bonding layer by adopting atmospheric plasma spraying;
(4) And preparing an alkaline surface layer on the surface of the inner ceramic layer by adopting atmospheric plasma spraying.
Further, in the step (2), the process parameters of the atmospheric plasma spraying are as follows: spraying voltage of 50-65V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, and the spraying distance is 90-110 mm.
Further, in the step (3), the process parameters of the atmospheric plasma spraying are as follows: spraying voltage of 50-65V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, and the spraying distance is 90-110 mm.
Further, in the step (4), the process parameters of the atmospheric plasma spraying are as follows: spraying voltage of 70-85V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, and the spraying distance is 90-110 mm.
Further, the method further comprises: in the step (2), the prepared substrate with the bonding layer is placed in an environment of 1000-1100 ℃ for vacuum heat treatment for 3-8 h.
The embodiment of the invention has the following advantages:
(1) Gd is selected from alkaline oxide in alkaline surface layer 2 O 3 、Nd 2 O 3 、La 2 O 3 、TiO 2 The alkaline oxide itself has excellent high temperature stability, and is alkaline than Y 2 O 3 The alkaline surface layer has a compact structure, can prevent corrosive melting from penetrating into the coating, and plays a role in protecting 8YSZBlocking the effect of permeation. The coupling effect of the two aspects ensures that the corrosion reaction is only carried out on the surface layer, thereby effectively relieving the problem of thermal corrosion failure of the thermal barrier coating.
(2) The alkaline surface layer of the invention takes 8YSZ and alkaline oxide with the mass ratio of 1-4:1 as raw materials, and 8YSZ as a toughening agent, so that the problem of low alkaline oxidative thermal expansion coefficient is solved, the component difference between the surface layer and the inner ceramic layer is smaller, the interlayer thermal stress is relieved, and the service life of the coating is prolonged.
(3) The invention has the advantages of easily obtained coating raw materials, simple operation in the preparation process and high flexibility, and can effectively solve the Na of the thermal barrier coating of the combustion engine 2 SO 4 +V 2 O 5 Corrosion problems.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It will be apparent to those of ordinary skill in the art that the drawings in the following description are exemplary only and that other implementations can be obtained from the extensions of the drawings provided without inventive effort.
FIG. 1 shows the Na-resistance of the present invention 2 SO 4 +V 2 O 5 Schematic of the structure of a thermal barrier coating for a corrosive gas turbine.
Detailed Description
Other advantages and advantages of the present invention will become apparent to those skilled in the art from the following detailed description, which, by way of illustration, is to be read in connection with certain specific embodiments, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in FIG. 1, the present embodiment provides Na resistance 2 SO 4 +V 2 O 5 The thermal barrier coating of the corroded gas turbine comprises from inside to outsideThe adhesive layer is arranged on the surface of the substrate. Wherein, the material of the bonding layer is MCrAlY, wherein M is Ni or Co; the material of the inner ceramic layer is 8YSZ; the alkaline surface layer is made of 8YSZ and alkaline oxide (Gd) with the mass ratio of 1-4:1 2 O 3 、Nd 2 O 3 、La 2 O 3 、TiO 2 One or more of the above). The matrix material is nickel-based alloy material such as DZ125, GH4169, etc.
The preparation method of the thermal barrier coating of the gas turbine comprises the following steps:
a) And (3) preparing alkaline surface layer powder. Considering the ingredient matching property between the alkaline surface layer and the inner ceramic layer, the alkaline surface layer takes 8YSZ and alkaline oxide with the mass ratio of 1-4:1 as raw materials, wherein 8YSZ has the function of a toughening agent, and researches show that when the alkaline oxidizing content is higher than the range, the problem of insufficient toughness is caused, and when the alkaline oxidizing content is lower than the range, the corrosion resistance effect cannot be ensured. Placing commercial 8YSZ and alkaline oxide with the mass ratio of 1-4:1 into a planet grinder, fully mixing for 20-30 min at 100-300 rpm to obtain alkaline surface layer powder, and then carrying out spray granulation on the powder to improve the fluidity. Before spraying, sieving with a 65-80 micron sieve to remove unground particles and impurities and ensure uniformity of powder particle size. And then placing the powder in a vacuum drying oven at 180-200 ℃ for 10-15 h to fully dry the powder.
b) And (5) treating the matrix. The high-temperature nickel-based alloy has better high-temperature strength, oxidation resistance and hot corrosion resistance, and is suitable for manufacturing the base materials of turbine rotating parts and bearing parts of gas turbine engines. To improve the adhesion between the coating and the substrate, a certain treatment of the substrate is required before the coating is prepared. The specific mode of matrix treatment is as follows: sequentially using acetone, alcohol and water to wash away greasy dirt on the surface of the matrix, polishing the surface of the matrix after the surface is dried to increase the roughness of the surface, washing with water again, and drying for later use.
c) An adhesive layer was prepared. The MCrAlY bonding layer is prepared by adopting atmospheric plasma spraying, and the specific technological parameters are as follows: spraying voltage 50-65V, current 550-700A and Ar flow 35 ultra-high50L/min，H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, the spraying distance is 90-110 mm, and the spraying thickness is 150-250 mu m. After the spraying is finished, the substrate with the bonding layer is placed in an environment of 1000-1100 ℃ for vacuum heat treatment for 3-8 hours to eliminate residual stress.
d) And (3) preparing an inner ceramic layer. The 8YSZ inner ceramic layer is prepared by adopting atmospheric plasma spraying, and the specific technological parameters are as follows: spraying voltage of 50-65V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, the spraying distance is 90-110 mm, and the spraying thickness is 100-300 mu m. The ceramic layer prepared by the process has 10-20% of porosity and good adhesion with the bonding layer.
e) Preparation of an alkaline surface layer. An alkaline surface layer is prepared by adopting atmospheric plasma spraying, and the higher power spraying rate is used for improving the structural density of the layer to block the penetration of corrosive molten salt, and the specific technological parameters are as follows: spraying voltage of 70-85V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, the spraying distance is 90-110 mm, and the spraying thickness is 200-300 mu m. The alkaline surface layer prepared by the process has 5-10% of porosity, on one hand, the relatively dense surface layer can slow down the penetration rate of corrosive molten salt into the alkaline surface layer, and on the other hand, the surface layer maintains a certain porosity, so that the thermal barrier performance and the strain tolerance of the alkaline surface layer can be improved.
Example 1
The present embodiment provides a Na-resistant material 2 SO 4 +V 2 O 5 The preparation method of the thermal barrier coating of the corroded gas turbine comprises the following steps:
a) And (3) preparing alkaline surface layer powder. Mixing commercial 8YSZ and basic oxide Gd with the mass ratio of 4:1 2 O 3 Placing in a star grinder, mixing at 200rpm for 30min, spray granulating, sieving with 80 μm sieve, and placing in a vacuum drying oven at 200deg.C for 12 hr.
b) And (5) treating the matrix. The nickel-based alloy matrix DZ125 sample (with the size of phi 25.4mm multiplied by 3.5 mm) is washed sequentially by acetone, alcohol and water, and is treated by borax after being dried, and is washed and dried again for use.
c) An adhesive layer was prepared. The NiCoCrAlY bonding layer is prepared by adopting atmospheric plasma spraying, and the specific technological parameters are as follows: spraying voltage 50V, current 700A, ar flow 50L/min, H 2 The flow is 10L/min, the powder feeding speed is 10g/min, the spraying distance is 110mm, the spraying thickness is 200 mu m, and then the powder is placed in a 1080 ℃ environment for vacuum heat treatment for 4 hours.
d) And (3) preparing an inner ceramic layer. The 8YSZ inner ceramic layer is prepared by adopting atmospheric plasma spraying, and the specific technological parameters are as follows: spraying voltage 50V, current 570A, ar flow 40L/min, H 2 The flow is 10L/min, the powder feeding speed is 20g/min, the spraying distance is 110mm, the spraying thickness is 200 mu m, and the void ratio is 15%.
e) Preparation of an alkaline surface layer. The alkaline surface layer is prepared by adopting atmospheric plasma spraying, and the specific technological parameters are as follows: spraying voltage 70V, current 650A, ar flow 40L/min, H 2 The flow is 10L/min, the powder feeding speed is 20g/min, the spraying distance is 110mm, the spraying thickness is 200 mu m, and the void ratio is 8%.
Comparative example 1
This comparative example provides a Na-resistant 2 SO 4 +V 2 O 5 The differences between the method for preparing the thermal barrier coating of the corroded gas turbine and the method in the embodiment 1 are that: the alkaline surface layer was not used and the thickness of the 8YSZ ceramic layer was 400 μm.
Comparative example 2
This comparative example provides a Na-resistant 2 SO 4 +V 2 O 5 The differences between the method for preparing the thermal barrier coating of the corroded gas turbine and the method in the embodiment 1 are that: the inner ceramic layer was not used and the thickness of the alkaline surface layer was 400 μm.
Test example 1
At Na (Na) 2 SO 4 +V 2 O 5 Thermal corrosion experiments were carried out on the thermal barrier coatings of example 1 and comparative examples 1-2 in a molten salt environment at 1000 ℃ and the coating surface was covered with Na 2 SO 4 +V 2 O 5 Salt concentration of 10mg/cm 2 The coating was inspected at 1h intervals. When the coating spalling area is greater than 20% of the total area, the coating is considered to fail and the total hot corrosion time is noted as hot corrosion life.
As a result of the experiment, the thermal corrosion life of the thermal barrier coating of the embodiment 1 of the invention is 25h, the thermal corrosion life of the thermal barrier coating of the comparative example 1 is 10h, the thermal corrosion life of the thermal barrier coating of the comparative example 2 is 20h, and the thermal barrier coating of the embodiment 1 shows longer corrosion life than the thermal barrier coatings of the comparative examples 1 and 2. The above shows that the improved alkaline surface layer can effectively prevent corrosive molten salt from penetrating into the coating, and has a good protection effect on the inner 8YSZ coating.
While the invention has been described in detail in the foregoing general description and specific examples, it will be apparent to those skilled in the art that modifications and improvements can be made thereto. Accordingly, such modifications or improvements may be made without departing from the spirit of the invention and are intended to be within the scope of the invention as claimed.

Claims (10)

1. Na-resistant 2 SO 4 +V 2 O 5 The corroded thermal barrier coating of the gas turbine is characterized by comprising a bonding layer, an inner ceramic layer and an alkaline surface layer from inside to outside, wherein the bonding layer is arranged on the surface of a substrate, the alkaline surface layer is prepared from 8YSZ and alkaline oxide in a mass ratio of 1-4:1, and the alkaline oxide is selected from Gd 2 O 3 、Nd 2 O 3 、La 2 O 3 、TiO 2 One or more of the following.
2. The Na-resistant of claim 1 2 SO 4 +V 2 O 5 A thermal barrier coating for a corroded gas turbine is characterized in that,
the preparation method of the raw materials of the alkaline surface layer comprises the following steps: placing 8YSZ and alkaline oxide powder into a planet grinder, fully mixing for 20-30 min at 100-300 rpm, then spraying and granulating, sieving with a 65-80 micron screen, placing into a vacuum drying oven, and drying at 180-200 ℃ for 10-15 h;
the thickness of the alkaline surface layer is 200-300 micrometers, and the porosity is 5% -10%.
3. The Na-resistant of claim 1 2 SO 4 +V 2 O 5 The corroded thermal barrier coating of the gas turbine is characterized in that the raw material of the inner ceramic layer is 8YSZ; and/or the number of the groups of groups,
the thickness of the inner ceramic layer is 100-300 micrometers, and the void ratio is 10% -20%.
4. The Na-resistant of claim 1 2 SO 4 +V 2 O 5 The corroded thermal barrier coating of the gas turbine is characterized in that the raw material of the bonding layer is MCrAlY, wherein M is Ni or Co; and/or the number of the groups of groups,
the thickness of the bonding layer is 150-250 micrometers.
5. The Na-resistant of claim 1 2 SO 4 +V 2 O 5 The corroded thermal barrier coating of the gas turbine is characterized in that the substrate is nickel-based alloy.
6. The Na-resistant composition of claim 1 2 SO 4 +V 2 O 5 The preparation method of the corroded thermal barrier coating of the gas turbine is characterized by comprising the following steps of:
(1) Pretreating a matrix;
(2) Preparing a bonding layer on the surface of a substrate by adopting atmospheric plasma spraying;
(3) Preparing an inner ceramic layer on the surface of the bonding layer by adopting atmospheric plasma spraying;
(4) And preparing an alkaline surface layer on the surface of the inner ceramic layer by adopting atmospheric plasma spraying.
7. The Na-resistant of claim 6 2 SO 4 +V 2 O 5 The preparation method of the thermal barrier coating of the corroded gas turbine is characterized in that in the step (2), the technological parameters of atmospheric plasma spraying are as follows: spraying voltage of 50-65V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, and the spraying distance is 90-110 mm.
8. The Na-resistant of claim 6 2 SO 4 +V 2 O 5 The preparation method of the thermal barrier coating of the corroded gas turbine is characterized in that in the step (3), the technological parameters of atmospheric plasma spraying are as follows: spraying voltage of 50-65V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, and the spraying distance is 90-110 mm.
9. The Na-resistant of claim 6 2 SO 4 +V 2 O 5 The preparation method of the thermal barrier coating of the corroded gas turbine is characterized in that in the step (4), the technological parameters of atmospheric plasma spraying are as follows: spraying voltage of 70-85V, current of 550-700A, ar flow of 35-50L/min, H 2 The flow is 8-12L/min, the powder feeding speed is 10-20 g/min, and the spraying distance is 90-110 mm.
10. The Na-resistant of claim 6 2 SO 4 +V 2 O 5 A method of preparing a thermal barrier coating for a corrosive gas turbine, the method further comprising:
in the step (2), the prepared substrate with the bonding layer is placed in an environment of 1000-1100 ℃ for vacuum heat treatment for 3-8 h.
CN202311040874.5A 2023-08-17 2023-08-17 Na-resistant 2 SO 4 +V 2 O 5 Corrosion gas turbine thermal barrier coating and preparation method thereof Pending CN117051348A (en)

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CN202311040874.5A CN117051348A (en) 2023-08-17 2023-08-17 Na-resistant 2 SO 4 +V 2 O 5 Corrosion gas turbine thermal barrier coating and preparation method thereof

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Application Number Priority Date Filing Date Title
CN202311040874.5A CN117051348A (en) 2023-08-17 2023-08-17 Na-resistant 2 SO 4 +V 2 O 5 Corrosion gas turbine thermal barrier coating and preparation method thereof

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