CN114774830B

CN114774830B - Multifunctional coating, preparation method thereof and power equipment

Info

Publication number: CN114774830B
Application number: CN202210694214.8A
Authority: CN
Inventors: 于月光; 刘建明; 刘通; 林筠; 张鑫; 章德铭; 郭丹; 彭浩然; 张安琴; 原慷; 卢晓亮; 潘玥; 刘栋
Original assignee: Bgrimm Advanced Materials Science & Technology Co ltd; BGRIMM Technology Group Co Ltd; AECC Guiyang Engine Design Research Institute
Current assignee: Bgrimm Advanced Materials Science & Technology Co ltd; BGRIMM Technology Group Co Ltd; AECC Guiyang Engine Design Research Institute
Priority date: 2022-06-20
Filing date: 2022-06-20
Publication date: 2022-09-02
Anticipated expiration: 2042-06-20
Also published as: CN114774830A

Abstract

The application provides a multifunctional coating, a preparation method thereof and power equipment. The multifunctional coating comprises an abradable surface layer, a metal transition layer, a ceramic middle layer and a bonding bottom layer which are arranged in a stacked mode. The preparation method of the multifunctional coating comprises the following steps: and preparing a bonding bottom layer, a ceramic intermediate layer, a metal transition layer and an abradable surface layer on the operation surface by adopting a thermal spraying process in sequence. The power equipment comprises the multifunctional coating. The application provides a multifunctional coating has resistant marine corrosion, clearance control and prevents the triple function of titanium fire, has solved that current coating is not corrosion-resistant, can't effectively prevent titanium molten drop burn-through etc. not enough, can satisfy high performance aeroengine and gas turbine operation requirement.

Description

Multifunctional coating, preparation method thereof and power equipment

Technical Field

The application relates to the field of materials, in particular to a multifunctional coating, a preparation method thereof and power equipment.

Background

The rotor clearance in aircraft engines and gas turbines has an important influence on equipment efficiency and oil consumption, and the smaller the clearance, the higher the efficiency and the lower the oil consumption. However, if the rotor and stator clearance is too small, collision and abrasion can occur, which causes accidents, and particularly when the rotor member is made of titanium alloy, titanium fire can also be caused.

The prior art solves the problems that an abradable seal coating and a titanium fire prevention coating are coated on a stator part of an aeroengine or a gas turbine, but the reliability of the coating is insufficient, the coating is easy to corrode and peel off, titanium molten drops burn through and the like in a marine environment and a high-temperature environment, and the manufacturing requirements of high-end equipment cannot be met.

Disclosure of Invention

The present application aims to provide a multifunctional coating, a preparation method thereof and a power device, so as to solve the above problems.

In order to achieve the purpose, the following technical scheme is adopted in the application:

a multifunctional coating comprises a wearable surface layer, a metal transition layer, a ceramic middle layer and a bonding bottom layer which are arranged in a laminated manner;

the abradable surface layer comprises a skeletal material comprising one or more of copper, a copper-containing metallic material, nickel, a nickel-containing metallic material, and an abradable material comprising a non-conductive material; the metal transition layer is made of the framework material; the ceramic intermediate layer comprises zirconia-based ceramic, and cracks distributed along the thickness direction of the ceramic intermediate layer are arranged in the ceramic intermediate layer; the bonding primer layer comprises a nickel-based metallic material.

Preferably, the abradable surface layer has a thickness of 0.5mm to 3.0 mm;

the thickness of the metal transition layer is 0.02mm-0.1 mm;

the thickness of the ceramic intermediate layer is 0.5mm-1.5mm, and the density is not less than 80%;

the thickness of the bonding bottom layer is 0.05mm-0.2 mm.

Preferably, the copper-containing metal material comprises one or more of copper-aluminum alloy, copper-aluminum-iron alloy and copper/aluminum mechanical composite metal;

the nickel-containing metal material comprises one or more of nickel-chromium alloy, nickel-chromium-aluminum alloy and nickel-chromium/aluminum mechanical composite metal;

the abradable material comprises one or more of polyphenyl ester, polyurethane, boron nitride, bentonite and diatomite;

in the abradable surface layer, the content of the skeleton material is greater than or equal to 20% and less than 100%, and the content of the abradable material is less than or equal to 80%.

Preferably, the zirconia-based ceramic comprises one or more of yttria-stabilized zirconia, calcia-stabilized zirconia, dysprosia-stabilized zirconia, and ytterbia-stabilized zirconia.

Preferably, the length of the cracks is 0.1mm-1.5mm, and the distribution density of the cracks along the non-thickness direction is 0-8 strips/mm.

Preferably, the nickel-based metallic material comprises one or more of nickel, nickel-aluminum alloy, nickel/aluminum composite metal, nickel-chromium alloy, nickel-chromium/aluminum composite metal, MCrAlY; wherein M is Ni or NiCo.

The application also provides a preparation method of the multifunctional coating, which comprises the following steps:

and preparing the bonding bottom layer, the ceramic intermediate layer, the metal transition layer and the abradable surface layer on the operation surface by adopting a thermal spraying process in sequence.

Preferably, the thermal spray process comprises one or more of atmospheric plasma spraying, low pressure plasma spraying, supersonic flame spraying, conventional flame spraying, suspension plasma spraying.

Preferably, the interlayer spraying interval time between every two layers is less than or equal to 2 h.

The application also provides a power device comprising the multifunctional coating.

Compared with the prior art, the beneficial effect of this application includes:

according to the multifunctional coating provided by the application, the abradable material in the abradable surface layer is not conductive, galvanic corrosion is avoided in the environments of high humidity and high salt in the ocean, and the corrosion resistance of the coating is improved; a metal transition layer is arranged between the abradable surface layer and the ceramic intermediate layer, so that the interlayer bonding force is obviously improved; meanwhile, the components of the metal transition layer are the same as those of the framework material in the abradable surface layer, so that galvanic corrosion between dissimilar metals is avoided, and the corrosion resistance of the coating is further improved; by prefabricating cracks in the ceramic intermediate layer, the volume stress of the thick ceramic layer generated under the working condition of a cold-hot cycle is relieved, the thermal shock resistance of the coating is ensured, and meanwhile, the non-inclusive damage caused by titanium molten drops burning through the coating and then the casing can be effectively prevented from being burnt through in a high-temperature environment; the bonding bottom layer is used for tightly bonding the three layers with the coated object so as to improve the bonding strength of the coating; the coating has triple functions of marine corrosion resistance, clearance control and titanium fire prevention, overcomes the defects that the existing coating is not corrosion-resistant and cannot effectively prevent titanium molten drops from burning through, and the like, and can meet the use requirements of high-performance aeroengines and gas turbines.

According to the preparation method of the multifunctional coating, the bonding bottom layer, the ceramic middle layer, the metal transition layer and the abradable surface layer are prepared through the thermal spraying process, the operability is high, and the obtained coating is high in stability.

The application provides a power equipment has marine corrosion resistance, clearance control and prevents the titanium fire performance through setting up above-mentioned multi-functional coating, and equipment reliability is high, can adapt to marine environment and high temperature environment, can satisfy the high-end needs of equipping the manufacturing.

Drawings

To more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are required to be used in the embodiments are briefly described below, and it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope of the present application.

FIG. 1 is a schematic structural view of a multifunctional coating provided herein;

FIG. 2 is a photograph showing the appearance of the product obtained in example 1 after 30 tests of water-cooling and heat shock at 650 ℃;

FIG. 3 is a photograph of the product of example 1 before it is subjected to a neutral salt spray test for 96 hours;

FIG. 4 is a photograph of the product of example 1 after 96 hours of neutral salt spray testing;

FIG. 5 is a photo of the product obtained in example 1 showing the blocking of 5 continuous drops of titanium droplets in an air environment at 650 ℃;

FIG. 6 is a photograph showing that the product obtained in comparative example 1 is peeled off 6 times by water-cooling and thermal shock at 650 ℃;

FIG. 7 is a photograph showing that the product obtained in comparative example 3 was burned through by 5 continuous drops of titanium melt at 650 ℃ in an air atmosphere.

Reference numerals:

1-abradable surface layer; 2-a metal transition layer; 3-cracking; 4-a ceramic intermediate layer; 5-bonding a bottom layer; 6-working surface.

Detailed Description

The terms as used herein:

"prepared from … …" is synonymous with "comprising". The terms "comprises," "comprising," "includes," "including," "has," "having," "contains," "containing," or any other variation thereof, as used herein, are intended to cover a non-exclusive inclusion. For example, a composition, process, method, article, or apparatus that comprises a list of elements is not necessarily limited to only those elements but may include other elements not expressly listed or inherent to such composition, process, method, article, or apparatus.

The conjunction "consisting of … …" excludes any non-specified element, step, or component. If used in a claim, the phrase is intended to claim as closed, meaning that it does not contain materials other than those described, except for the conventional impurities associated therewith. When the phrase "consisting of … …" appears in a clause of the subject matter of the claims rather than immediately after the subject matter, it defines only the elements described in the clause; other elements are not excluded from the claims as a whole.

When an amount, concentration, or other value or parameter is expressed as a range, preferred range, or as a range of upper preferable values and lower preferable values, this is to be understood as specifically disclosing all ranges formed from any pair of any upper range limit or preferred value and any lower range limit or preferred value, regardless of whether ranges are separately disclosed. For example, when the range "1 ~ 5" is disclosed, the ranges described should be construed to include the ranges "1 ~ 4", "1 ~ 3", "1 ~ 2 and 4 ~ 5", "1 ~ 3 and 5", and the like. When a range of values is described herein, unless otherwise stated, the range is intended to include the endpoints thereof and all integers and fractions within the range.

In these examples, the parts and percentages are by mass unless otherwise indicated.

"parts by mass" means a basic unit of measure indicating a mass ratio of a plurality of components, and 1 part by mass may represent any unit mass, for example, 1g or 2.689 g. If we say that the part by mass of the component A is a part by mass and the part by mass of the component B is B part by mass, the ratio of the part by mass of the component A to the part by mass of the component B is a: b. alternatively, the mass of the A component is aK and the mass of the B component is bK (K is an arbitrary number, and represents a multiple factor). It is unmistakable that, unlike the parts by mass, the sum of the parts by mass of all the components is not limited to 100 parts.

"and/or" is used to indicate that one or both of the illustrated conditions may occur, e.g., a and/or B includes (a and B) and (a or B).

the abradable surface layer comprises a skeletal material comprising one or more of copper, a copper-containing metallic material, nickel, a nickel-containing metallic material, and an abradable material comprising a non-conductive material; the metal transition layer is made of the framework material; the ceramic intermediate layer comprises zirconia-based ceramic, and cracks distributed along the thickness direction of the ceramic intermediate layer are arranged in the ceramic intermediate layer; the bonding primer layer includes a nickel-based metallic material.

In the present application, the term "distribution in the thickness direction" means a distribution in the substantially longitudinal direction, for example, a distribution perpendicular to the plane of the coating layer or a distribution having an acute angle with the perpendicular direction, and is not strictly and absolutely aligned in the thickness direction. It is understood that the directions of the plurality of cracks are not completely uniform. Fig. 1 is merely an example, and does not constitute a limitation of "distribution in the thickness direction".

In an alternative embodiment, the abradable surface layer has a thickness of 0.5mm to 3.0 mm;

alternatively, the thickness of the abradable face layer may be any value between 0.5mm, 1.0mm, 1.5mm, 2.0mm, 2.5mm, 3.0mm, or 0.5mm-3.0 mm.

In an alternative embodiment, the thickness of the metal transition layer is 0.02mm to 0.1 mm;

optionally, the thickness of the metal transition layer may be 0.02mm, 0.03mm, 0.04mm, 0.05mm, 0.06mm, 0.07mm, 0.08mm, 0.09mm, 0.1mm, or any value between 0.02mm and 0.1 mm.

In an optional embodiment, the ceramic intermediate layer has a thickness of 0.5mm to 1.5mm and a compactness of not less than 80%;

the thickness of the ceramic intermediate layer of the existing titanium fire-proof coating is generally not more than 0.3mm, titanium molten drops cannot be effectively prevented from burning through, and the coating is peeled off due to large difference of expansion coefficients of ceramic and a metal matrix when the thickness of a ceramic layer is increased; according to the method, the cracks can be prefabricated in the ceramic interlayer, the volume stress of the thick ceramic layer generated under the cold-hot circulation working condition is relieved, and the thermal shock resistance of the coating is ensured, so that the thickness of the ceramic interlayer is increased under the condition of ensuring the bonding fastness of the coating, and the burning-through of titanium molten drops is effectively prevented.

Optionally, the thickness of the ceramic intermediate layer may be any value between 0.5mm, 1.0mm, 1.5mm or 0.5mm and 1.5mm, and the compactness may be any value of 80%, 85%, 90%, 95% or not less than 80%.

In an alternative embodiment, the bonding primer layer has a thickness of 0.05mm to 0.2 mm.

Optionally, the thickness of the adhesive bottom layer may be 0.05mm, 0.1mm, 0.15mm, 0.2mm, or any value between 0.05mm and 0.2 mm.

In an alternative embodiment, the copper-containing metallic material comprises one or more of copper aluminum alloy, copper aluminum iron alloy, copper/aluminum mechanical composite metal;

in an alternative embodiment, the nickel-containing metallic material comprises one or more of nichrome, nichrome alloy, nichrome/aluminum mechanical composite metal;

in an alternative embodiment, the abradable material comprises one or more of a polyphenyl ester, polyurethane, boron nitride, bentonite, diatomaceous earth;

in the abradable surface layer, the mass content of the skeleton material is 20% or more and less than 100%, and the mass content of the abradable material is 80% or less.

Alternatively, the content of the framework material may be 20%, 30%, 40%, 50%, 60%, 70%, 80%, 90%, 99% or any value between 20% and less than 100%, and the content of the abradable material may be 1%, 5%, 10%, 20%, 30%, 40%, 50%, 60%, 70%, 79% or any value between 80%.

In an alternative embodiment, the zirconia-based ceramic comprises one or more of yttria-stabilized zirconia, calcia-stabilized zirconia, dysprosia-stabilized zirconia, ytterbia-stabilized zirconia.

In an alternative embodiment, the length of the crack is between 0.1mm and 1.5 mm;

optionally, the length of the slit may be 0.1mm, 0.5mm, 1.0mm, 1.5mm, or any value between 0.1mm and 1.5 mm.

In an alternative embodiment, the distribution density of the cracks in the non-thickness direction is 0 to 8 strips/mm.

The "non-thickness direction" referred to herein means a length direction and a width direction extending along the coating layer on the surface of the object to be coated, in addition to the thickness direction.

The distribution density data indicates that there are situations in the ceramic interlayer: some locations have no cracks, while other locations may have 1, 2, 3, 4, 5, 6, 7, 8 cracks, calculated in units of 1 mm.

In an alternative embodiment, the nickel-based metallic material comprises one or more of nickel, nickel-aluminum alloy, nickel/aluminum composite, nickel-chromium alloy, nickel-chromium/aluminum composite, MCrAlY; wherein M is Ni or NiCo.

The nickel-based metal material should be selected on the principle that the thermal expansion coefficient of the nickel-based metal material is less different from that of the base material and the ceramic layer material, or the thermal shock test confirms that the selected nickel-based metal material meets the design requirement of thermal shock resistance of the coating.

In an alternative embodiment, the thermal spray process comprises one or more of atmospheric plasma spraying, low pressure plasma spraying, supersonic flame spraying, conventional flame spraying, suspension plasma spraying.

In an alternative embodiment, the inter-layer spraying interval time between each two layers is less than or equal to 2 h.

Embodiments of the present application will be described in detail below with reference to specific examples, but those skilled in the art will appreciate that the following examples are only illustrative of the present application and should not be construed as limiting the scope of the present application. The examples, in which specific conditions are not specified, were conducted under conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are conventional products which are not indicated by manufacturers and are commercially available.

Example 1

As shown in FIG. 1, the present embodiment provides a multifunctional coating comprising an abradable face layer 1, a metal transition layer 2, a ceramic intermediate layer 4 having cracks 3, and a primer layer 5, the primer layer 5 and an object Ti to be coated being sequentially stacked ₂ The working surface 6 of the AlNb titanium alloy matrix adjoins.

The preparation method comprises the following steps:

the method comprises the following steps: for Ti ₂ Carrying out oil removal and sand blowing pretreatment on the AlNb titanium alloy matrix, and spraying Ni/Al composite powder (brand: KF-6) by adopting a Metco Muticoat atmospheric plasma spraying system F4 to prepare a bonding bottom layer 5, wherein the thickness of the bonding bottom layer 5 is 0.1 mm;

step two: preparing a ceramic intermediate layer 4 on the surface of the bonding bottom layer 5 by spraying yttria-stabilized zirconia powder (brand: KF-230) by using atmospheric plasma, wherein the spraying process parameters are as follows: the power is 55kW, the spraying distance is 26mm, the powder feeding speed is 50g/min, the substrate linear velocity is 7m/min, and the spraying thickness is 1 mm; the cracks 3 are prefabricated in the structure of the ceramic intermediate layer 4 prepared by the process, the number of the cracks 3 is about 3-6 per mm, and the length of the cracks is not less than 0.4 mm;

step three: preparing a metal transition layer 2 on the surface of the ceramic intermediate layer 4 by spraying copper-aluminum powder (brand: KF-325) by atmospheric plasma, wherein the spraying process parameters are as follows: the power is 24kW, the spraying distance is 100mm, the powder feeding speed is 30g/min, the substrate linear velocity is 90m/min, and the spraying thickness is 0.05 mm;

step four: preparing an abradable surface layer 1 on the surface of a metal transition layer 2 by spraying composite powder mixed by copper aluminum powder (brand: KF-325) and 200-mesh polyphenyl ester powder according to a weight ratio of 9:1 by using atmospheric plasma, wherein the spraying process parameters are as follows: the power is 28kW, the spraying distance is 150mm, the powder feeding speed is 25g/min, the substrate linear speed is 90m/min, and the spraying thickness is 1.5 mm.

The spraying interval time between the first step and the fourth step is 5 min.

The product obtained by the method is good in appearance after being subjected to water cooling and thermal shock for 30 times at 650 ℃. The results are shown in FIG. 2.

The photo of the product obtained above is shown in fig. 3 before the test and in fig. 4 after the test after the 96-hour neutral salt spray test. By contrast, the coating has good corrosion resistance.

Fig. 5 is a photograph of the product obtained as described above showing the barrier of 5 continuous drops of titanium in an air atmosphere at 650 ℃. As can be seen from FIG. 5, the multifunctional coating provided by the present application can effectively prevent titanium droplets from burning through.

Example 2

Referring to fig. 1, the present embodiment provides a multifunctional coating, which comprises an abradable surface layer 1, a metal transition layer 2, a ceramic intermediate layer 4 with cracks 3, and a bonding bottom layer 5, which are sequentially stacked, wherein the bonding bottom layer 5 is adjacent to a working surface 6 of an object to be coated, GH4169 superalloy substrate.

The preparation method comprises the following steps:

the method comprises the following steps: pretreating a GH4169 high-temperature alloy substrate, and spraying NiCrAlY powder by supersonic flame to prepare a bonding bottom layer 5, wherein the thickness of the bonding bottom layer 5 is 0.12 mm;

step three: preparing a metal transition layer 2 on the surface of the ceramic intermediate layer 4 by spraying nickel-based alloy powder (brand: KF-3062) by using atmospheric plasma, wherein the spraying process parameters are as follows: the power is 32kW, the spraying distance is 120mm, the powder feeding speed is 35g/min, the substrate linear velocity is 90m/min, and the spraying thickness is 0.04 mm;

step four: the abrasion surface layer 1 is prepared on the surface of the metal transition layer 2 by spraying nickel-based boron nitride composite powder (brand: KF-125) by adopting a Metco 6P flame spraying system, and the spraying process parameters are as follows: the oxygen flow is 42lpm, the acetylene flow is 26lpm, the spraying distance is 220mm, the powder feeding speed is 50g/min, the substrate linear speed is 50m/min, and the spraying thickness is 1.5 mm.

The spraying interval time between the first step and the third step is 5min, and the interlayer spraying interval time between the fourth step and the third step is 24 min.

Example 3

Referring to fig. 1, the present embodiment provides a multifunctional coating, which comprises an abradable surface layer 1, a metal transition layer 2, a ceramic intermediate layer 4 with cracks 3, and a bonding bottom layer 5, which are sequentially stacked, wherein the bonding bottom layer 5 is adjacent to a working surface 6 of a Ti60 titanium alloy substrate to be coated.

The preparation method comprises the following steps:

the method comprises the following steps: pretreating a Ti60 titanium alloy matrix, spraying NiCr alloy powder by adopting a Metco Muticoat atmospheric plasma spraying system F4 plasma spray gun to prepare a bonding bottom layer 5, wherein the thickness of the bonding bottom layer 5 is 0.15 mm;

step three: adopting atmospheric plasma to spray CoNiCrAlY alloy powder, preparing a metal transition layer 2 on the surface of the ceramic intermediate layer 4, wherein the spraying process parameters are as follows: the power is 42kW, the spraying distance is 120mm, the powder feeding speed is 45g/min, the substrate linear velocity is 80m/min, and the spraying thickness is 0.1 mm;

step four: preparing a wearable surface layer 1 on the surface of the metal transition layer 2 by spraying CoNiCrAlY/polyphenyl ester composite powder by adopting a Metco Muticoat atmospheric plasma spraying system F4 plasma spray gun, wherein the spraying process parameters are as follows: the power is 28kW, the spraying distance is 120mm, the powder feeding speed is 40g/min, the matrix linear velocity is 80m/min, and the spraying thickness is 1.5 mm.

The spraying interval time from the first step to the fourth step is 1.5 hours.

Comparative example 1

Unlike example 1, the operation of step three was eliminated.

FIG. 6 is a photograph showing 6 times of peeling of the coating obtained in comparative example 1 by water-cooling and thermal shock at 650 ℃.

This shows that the metal transition layer 2 plays an important role in improving the interlayer bonding force and ensuring the stability of the coating.

Comparative example 2

The only difference from example 2 is step two:

preparing a ceramic intermediate layer 4 on the surface of the bonding bottom layer 5 by spraying yttria-stabilized zirconia powder (brand: KF-230) by using atmospheric plasma, wherein the spraying process parameters are as follows: the power is 45kW, the spraying distance is 120mm, the powder feeding speed is 20g/min, the linear velocity of the substrate is 5m/min, and the spraying thickness is 1 mm; the structure of the ceramic intermediate layer 4 prepared by this process is free from pre-cracks.

Comparative example 3

The only difference from example 3 is step two:

preparing a ceramic intermediate layer 4 on the surface of the bonding bottom layer 5 by spraying yttria-stabilized zirconia powder (brand: KF-230) by using atmospheric plasma, wherein the spraying process parameters are as follows: the power is 55kW, the spraying distance is 26mm, the powder feeding speed is 50g/min, the substrate linear velocity is 7m/min, and the spraying thickness is 0.15 mm.

Comparative example 3 a photograph of a coating burned through by 5 consecutive drops of titanium droplets in an air environment at 650 c is shown in fig. 7.

It is thus shown that the arrangement of the ceramic intermediate layer 4 and the selection of its thickness play an important role in ensuring that the coating effectively prevents the titanium droplets from burning through.

Comparative example 4

The only difference from example 1 is step four:

the abrasion surface layer 1 is prepared on the surface of the metal transition layer 2 by spraying nickel-based graphite composite powder (brand: KF-116) by adopting a Metco 6P flame spraying system, and the spraying process parameters are as follows: the oxygen flow is 38lpm, the acetylene flow is 246lpm, the spraying distance is 230mm, the powder feeding speed is 55g/min, the substrate linear speed is 50m/min, and the spraying thickness is 1.5 mm.

The coatings obtained in the examples and comparative examples were subjected to the performance test, and the results are shown in the following table 1:

table 1 performance test data

Sample (I)	Thermal shock resistance of coating (Water cooling thermal shock)	Coating corrosion resistance (96 h neutral salt spray corrosion)	Depth of ablation of coating (5 drops of titanium)
				Example 1	Coating integrity at 650 deg.C for 30 times	Grade	6	1.92mm
Example 2	Coating integrity at 750 ℃ for 32 times	Grade	6						1.84mm
				Example 3	600 ℃ for 35 times of coating integrity	Grade	6	1.86mm
Comparative example 1	6 times of coating peeling at 650 DEG C	Grade	5						1.96mm
				Comparative example 2	Coating peeling off at 750 ℃ for 8 times	Grade	6	1.73mm
Comparative example 3	600 ℃ for 35 times of coating integrity	Grade	6						The coating is burned through
				Comparative example 4	Coating integrity at 650 deg.C for 30 times	Stage	2	1.97mm

As can be seen from Table 1, the multifunctional coating provided by the application has good thermal shock resistance, corrosion resistance and titanium fire resistance. Finally, it should be noted that: the above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art will understand that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present application.

Moreover, those skilled in the art will appreciate that while some embodiments herein include some features included in other embodiments, rather than other features, combinations of features of different embodiments are meant to be within the scope of the application and form different embodiments. For example, in the claims above, any of the claimed embodiments may be used in any combination. The information disclosed in this background section is only for enhancement of understanding of the general background of the application and should not be taken as an acknowledgement or any form of suggestion that this information forms the prior art already known to a person skilled in the art.

Claims

1. A multifunctional coating is characterized by comprising an abradable surface layer, a metal transition layer, a ceramic middle layer and a bonding bottom layer which are sequentially stacked;

the abradable surface layer comprises a skeletal material comprising one or more of copper, a copper-containing metallic material, nickel, a nickel-containing metallic material, and an abradable material comprising a non-conductive material; the metal transition layer is made of the framework material; the ceramic intermediate layer comprises zirconia-based ceramic, and cracks distributed along the thickness direction of the ceramic intermediate layer are arranged in the ceramic intermediate layer; the bonding underlayer comprises a nickel-based metal material; the thickness of the abradable surface layer is 0.5mm-3.0 mm;

the thickness of the metal transition layer is 0.02mm-0.1 mm;

the thickness of the bonding bottom layer is 0.05mm-0.2 mm.

2. The multifunctional coating of claim 1, wherein said copper-containing metallic material comprises one or more of copper aluminum alloy, copper aluminum iron alloy, copper/aluminum mechanical composite metal;

in the abradable surface layer, the content of the skeleton material is 20% or more and less than 100%, and the content of the abradable material is 80% or less.

3. The multifunctional coating of claim 1, wherein the zirconia-based ceramic comprises one or more of yttria-stabilized zirconia, calcia-stabilized zirconia, dysprosia-stabilized zirconia, and ytterbia-stabilized zirconia.

4. The multifunctional coating of claim 1, wherein the cracks have a length of 0.1mm to 1.5mm and a distribution density of the cracks in a non-thickness direction of 0 to 8 stripes/mm.

5. The multifunctional coating of any one of claims 1 to 4, wherein the nickel-based metallic material comprises one or more of nickel, nickel-aluminum alloy, nickel/aluminum composite, nickel-chromium alloy, nickel-chromium/aluminum composite, MCrAlY; wherein M is Ni or NiCo.

6. A method of preparing the multifunctional coating of any one of claims 1 to 5, comprising:

7. The method of claim 6, wherein the thermal spray process comprises one or more of atmospheric plasma spraying, low pressure plasma spraying, high velocity flame spraying, conventional flame spraying, suspension plasma spraying.

8. The production method according to claim 6 or 7, wherein the interlayer spraying interval time between each two layers is 2 hours or less.

9. A power plant comprising the multifunctional coating of any one of claims 1 to 5.