CN107699844B - Thermal barrier ablation-resistant composite coating and preparation method thereof - Google Patents

Thermal barrier ablation-resistant composite coating and preparation method thereof Download PDF

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CN107699844B
CN107699844B CN201710717196.XA CN201710717196A CN107699844B CN 107699844 B CN107699844 B CN 107699844B CN 201710717196 A CN201710717196 A CN 201710717196A CN 107699844 B CN107699844 B CN 107699844B
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thermal barrier
powder
coating
layer
ablation
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CN107699844A (en
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周武平
王铁军
刘国辉
张保红
林冰涛
唐亮亮
张丹华
甘乐
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Aetna Tianlong (Beijing) tungsten molybdenum Technology Co.,Ltd.
Advanced Technology and Materials Co Ltd
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Advanced Technology and Materials Co Ltd
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    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • 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
    • 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
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention belongs to the field of refractory metals and composite materials thereof, and discloses a thermal barrier ablation-resistant composite coating which is arranged on a metal substrate and sequentially comprises a bonding layer and a thermal barrier layer from the surface of the metal substrate to the outside, wherein the thermal barrier layer is made of composite powder of heat-insulating ceramic and tungsten and/or molybdenum. The thermal barrier ablation-resistant composite coating has good high-temperature resistance, ablation resistance, oxidation resistance, scouring resistance and stripping resistance, and is particularly suitable for being used in an environment with strong airflow; in addition, the invention has low cost. The thermal barrier ablation-resistant composite coating can be applied to the surfaces of components working under high-temperature conditions such as ship engines, ground gas turbines, wings, empennages and rudder blades of aircrafts and the like so as to carry out thermal protection on the components, thereby prolonging the service life of a metal matrix. By changing the component content and the coating structure of the thermal barrier layer, the thermal barrier layer can be used in different working environments or can meet certain special use requirements.

Description

Thermal barrier ablation-resistant composite coating and preparation method thereof
The application is a divisional application of a patent application with the application date of 2015, 06, 19 and the application number of 201510346596.5 and the name of 'a thermal barrier ablation-resistant composite coating and a preparation method thereof'.
Technical Field
The invention belongs to the field of refractory metals and composite materials thereof, and relates to a thermal barrier ablation-resistant composite coating and a preparation method thereof.
Background
The thermal barrier coating combines the ceramic and the metal matrix in a coating mode by utilizing the high temperature resistance, corrosion resistance, low heat conduction and other properties of the ceramic material, so that the service temperature of the metal hot end component is improved, and the high temperature oxidation resistance of the hot end component is enhanced. The service life of the hot end component is prolonged, and the efficiency of the heat engine is improved. Can be used for ship engines, ground gas turbines, rockets, missile engines and the like.
The existing thermal barrier composite coating has a double-layer structure, a multi-layer structure, a gradient structure and the like.
The thermal barrier coating with the double-layer structure consists of a bonding layer and low-heat-conductivity ceramics, the alloy bonding layer plays a role in enabling the ceramic layer to be tightly combined with the substrate, and the low-heat-conductivity ceramics mainly plays a role in heat insulation. In a typical two-layer thermal barrier coating, a MCrAlY coating and a Pt modified aluminized coating are generally used as bonding layers, and yttria-stabilized zirconia is used as a thermal insulation layer.
The thermal barrier coating with a multilayer structure generally comprises a bonding layer, a low-thermal-conductivity ceramic layer, an oxygen barrier layer and a surface sealing layer, wherein the bonding layer usually adopts an MCrAlY coating and a Pt modified aluminized coating. The low heat conduction ceramic layer, the oxygen barrier layer and the sealing layer are all composed of different oxide ceramic layers. Each layer has a specific function, and the outer sealing layer is mainly used for preventing the corrosion of fuel gas corrosion products; the low-thermal-conductivity ceramic is used for blocking heat transmission to the alloy matrix, and the oxygen barrier layer is used for reducing diffusion of oxygen to the inside of the coating and improving the oxidation resistance of the coating. However, such a multi-layer thermal barrier coating has not been practically applied.
The thermal barrier coating with the gradient structure is usually provided with a transition coating with stress and functional gradient between the bonding layer and the low-thermal-conductivity ceramic surface layer, so that the stress generated due to the larger thermal expansion coefficient of the metal material and the ceramic material is reduced, the bonding strength and the thermal shock resistance of the coating are improved, and the service life of the coating is prolonged.
At present, the existing thermal barrier coating is applied more in a static environment, and the thermal shock resistance and the high-temperature resistance pneumatic ablation resistance of the ceramic coating are poorer in an environment with airflow impact at a high temperature, so that the development of a novel composite coating and the improvement of the comprehensive performances of the coating such as high temperature resistance, ablation resistance, oxidation resistance, scouring resistance, stripping resistance and the like are new problems faced at present.
Disclosure of Invention
In view of the shortcomings of the prior art, the invention aims to provide a thermal barrier ablation-resistant composite coating.
The invention also aims to provide a preparation method of the thermal barrier ablation-resistant composite coating.
The invention adopts the coating prepared from the composite powder of metal and ceramic as the thermal barrier layer, optimizes the performance matching between the coating and the metal matrix and between the coating and the coating through multilayer compounding, further improves the bonding strength of the functional gradient coating, and effectively prevents the coating from peeling off. From the perspective of service performance, the composite coating not only has the effect of protecting the thermal barrier of the metal matrix, but also improves the high-temperature resistance, ablation resistance and erosion resistance of the coating so as to adapt to wider high-temperature working environment. Provides a new scheme for a novel multipurpose thermal barrier ablation-resistant coating.
In order to achieve the purpose, the invention adopts the following technical scheme:
the thermal barrier ablation-resistant composite coating is arranged on a metal substrate, and comprises a bonding layer and a thermal barrier layer from the surface of the metal substrate to the outside in sequence, wherein the thermal barrier layer is made of composite powder of heat-insulating ceramic and tungsten and/or molybdenum.
As a preferred embodiment, the material of the bonding layer is tungsten powder, molybdenum powder, tungsten-molybdenum composite powder, or MCrAlY powder, where M is one or two of Co or Ni.
As a preferred embodiment, in the composite powder of the thermal insulation ceramic and tungsten and/or molybdenum, the thermal insulation ceramic is 30 to 90% by mass, and the tungsten and/or molybdenum is: 10-70%; preferably, the heat insulation ceramic is yttria-stabilized zirconia or alumina, wherein the yttria-stabilized zirconia contains 0-15% of yttria by mass.
As a preferred embodiment, the thermal barrier layer is composed of a single layer or more than two sub-layers, preferably, the thermal barrier layer is composed of a heat insulation sub-layer and a transition sub-layer in sequence from the surface of the bonding layer to the outside in the two or more sub-layers, the composite powder adopted in the heat insulation sub-layer contains 60-90% by mass of the heat insulation ceramic, and the composite powder adopted in the transition sub-layer contains 30-70% by mass of the heat insulation ceramic.
As a preferred embodiment, the thermal barrier ablation-resistant composite coating is 0.2-2 mm thick.
As a preferred embodiment, the thermal barrier ablation-resistant composite coating further comprises a protective layer, wherein the protective layer is arranged on the surface of the thermal barrier layer and is made of tungsten powder, molybdenum powder, tungsten-molybdenum composite powder, or composite powder of the thermal insulation ceramic and tungsten and/or molybdenum; preferably, the thickness of the protective layer is 0.5-3.0 mm.
As a preferred embodiment, the thermal barrier ablation-resistant composite coating is prepared by adopting a spray granulation process to prepare the composite powder of the heat-insulating ceramic and tungsten and/or molybdenum; preferably, the parameters of the spray granulation process are as follows: the inlet temperature is 200-300 ℃, the outlet temperature is 60-130 ℃, the pressure in the tower is-0.03-0.06 MPa, and the roasting temperature is 1200-1400 ℃.
The preparation method of the thermal barrier ablation-resistant composite coating adopts a plasma spraying process to spray the thermal barrier ablation-resistant composite coating on the surface of the metal substrate.
In the above preparation method, as a preferred embodiment, the following steps are included:
a sand blasting and cleaning treatment step, wherein the sand blasting treatment is carried out on the surface of the metal matrix, and then residual stains or dust on the surface of the metal matrix are cleaned;
and spraying, namely spraying corresponding coating material powder serving as a raw material on the surface of the cleaned metal substrate layer by adopting a plasma spraying process to form the composite coating.
In the above production method, as a preferred embodiment, in the spraying step, when each layer of the composite coating layer is sprayed, the formed coating layers are ground and measured to ensure the dimensional accuracy of each coating layer.
The technical scheme of the invention has the following process principle: the spraying method is adopted to spray a coating with certain heat insulation and ablation resistance on the surface of the metal substrate.
The invention has the advantages that:
1) the plasma spraying method is adopted, is not limited by the shape of a matrix, and can realize the spraying of products with various structural shapes.
2) The matching performance of the coating material and the matrix material is good: tungsten, molybdenum and titanium in the metal matrix are infinite solid solutions and can form compounds with iron and nickel. The bonding layer material adopted by the invention can form infinite solid solution or compound components with a conventional metal matrix, so that the matrix and the coating have good compatibility. Furthermore, when thermal spraying, the metal powder is in a molten or semi-molten state, which makes it easy for the sprayed powder to metallurgically bond with the base material when deposited on the base material. The fused or semi-fused spray powder is beneficial to forming good combination between the coating and the substrate and between the coating, and internal stress between the coating and the substrate and between the coating is reduced. The defects of coating material peeling, cracking, holes and the like are avoided.
3) The thermal barrier ablation-resistant composite coating has good high-temperature resistance, ablation resistance, oxidation resistance, scouring resistance and spalling resistance, the temperature of an ablation point is more than 2000 ℃, and particularly, as the thermal barrier ablation-resistant composite coating adopts the composite powder of the heat-insulating ceramic and the tungsten and/or the molybdenum as the thermal barrier, the thermal barrier ablation-resistant composite coating has stronger heat-insulating effect, is particularly suitable for being used in the environment with strong airflow and has good scouring resistance; in addition, the invention has low cost.
4) The thermal barrier ablation-resistant composite coating can be applied to the surfaces of components working under high-temperature conditions such as ship engines, ground gas turbines, wings, empennages and rudder blades of aircrafts and the like so as to carry out thermal protection on the components, thereby prolonging the service life of a metal matrix.
5) By changing the component content and the coating structure of the thermal barrier layer, the thermal barrier layer can be used in different working environments or can meet certain special use requirements.
Drawings
FIG. 1 is a schematic structural view of a metal substrate coated with a thermal barrier ablation-resistant composite coating according to the present invention;
FIG. 2 is an enlarged view of the composite coating of FIG. 1;
FIG. 3 is a microscopic morphology of the sprayed composite powder used in example 1 of the present invention;
FIG. 4 is a microstructure diagram of a composite coating of example 1 prepared according to the present invention.
Wherein, in the attached drawings, 1, a metal substrate; 2. a bonding layer; 3. a thermal barrier layer; 4. protective layer
Detailed Description
In order to more clearly explain the technical features and effects of the present invention, the present invention will be described in detail with reference to the following embodiments in conjunction with the accompanying drawings.
The thermal barrier ablation-resistant composite coating disclosed by the invention is arranged on or coated on a metal substrate 1, and comprises a bonding layer 2, a thermal barrier layer 3 and a protective layer 4 from the surface of the metal substrate 1 to the outside in sequence, wherein the thermal barrier layer 3 is made of composite powder of heat-insulating ceramic and tungsten and/or molybdenum, namely the thermal barrier layer 3 is made of composite powder of heat-insulating ceramic and tungsten, composite powder of heat-insulating ceramic and molybdenum or composite powder of heat-insulating ceramic and tungsten and molybdenum.
The design of the material and the components of the composite coating mainly takes the melting point, the strength, the thermal conductivity, the thermal expansion coefficient and the like of the material into consideration.
The thermal barrier ablation-resistant composite coating can be applied to the surfaces of components working under high-temperature conditions such as ship engines, ground gas turbines, wings, empennages and rudder blades of aircrafts and the like so as to protect the components from heat insulation, oxidation, erosion and the like. Therefore, the metal substrate in the present invention may be a titanium alloy, a high temperature alloy or alloy steel, an aluminum alloy, or the like.
The material of the bonding layer can be any material which has good bonding property with the metal matrix and has a melting point of more than 1500 ℃, has a high melting point, and can be well bonded with the matrix and other coatings, so that the interface bonding strength of the coating and the matrix is improved. Preferably, the bonding layer is made of tungsten powder, molybdenum powder, tungsten-molybdenum composite powder (the mixing ratio of the molybdenum powder and the tungsten powder can be any ratio, and the mixing ratio can be manufactured by mechanical mixing, ball milling or spray granulation, etc.) or MCrAlY (M specifically refers to one or two of Ni or Co, wherein the MCrAlY alloy comprises 0-75% of Ni, 0-70% of Co, 15-25% of Cr, 5-15% of Al, 0.5-2.0% of Y, and the mass percentage content of Ni and Co is not zero at the same time, and the thickness of the bonding layer is preferably 0.05-0.15 mm (such as 0.06mm, 0.08mm, 0.10mm, 0.12mm, 0.13mm and 0.14mm) so as to ensure good bonding strength and ablation resistance.
The material of the thermal barrier layer needs to have good heat insulation and high-temperature ablation resistance at the same time so as to prevent high temperature from being transmitted to the metal matrix from the outside, and the thermal barrier layer has relatively high melting point, low thermal conductivity and proper thermal expansion coefficient. The material of the thermal barrier layer is composite powder of heat-insulating ceramic and tungsten and/or molybdenum; preferably, in the composite powder of the heat-insulating ceramic and tungsten and/or molybdenum, the mass percent of the heat-insulating ceramic is 30-90%, and the mass percent of the tungsten and/or molybdenum is: 10-70%;
more preferably, the thermal insulation ceramic is yttria-stabilized zirconia or alumina, wherein the yttria-stabilized zirconia contains 0-15% by mass (e.g., 0%, 2%, 4%, 6%, 7%, 8%, 9%), that is, when the content is zero, the yttria-stabilized zirconia is pure zirconia. The thickness of the heat-insulating ablation-resistant layer is preferably 0.2-2 mm (such as 0.3mm, 0.4mm, 0.6mm, 0.7mm, 0.8mm, 0.9mm, 1.0mm, 1.2mm, 1.3mm, 1.4mm, 1.5mm, 1.6mm, 1.8mm and 1.9mm), so that the heat barrier layer has a good thermal barrier effect and a good ablation resistance.
The composite powder of the heat-insulating ceramic and the tungsten and/or the molybdenum can be prepared by adopting a mechanical mixing method, a spray granulation method, a wet ball milling process and other processes, and is preferably prepared by adopting a spray granulation process; the parameters of the spray granulation process are as follows: the inlet temperature is 200-300 deg.C (such as 210 deg.C, 230 deg.C, 250 deg.C, 260 deg.C, 280 deg.C, 290 deg.C), the outlet temperature is 60-130 deg.C (such as 70 deg.C, 90 deg.C, 100 deg.C, 110 deg.C, 120 deg.C, 125 deg.C), the tower internal pressure is-0.03-0.06 MPa (such as-0.04 MPa, -0.05MPa, -0.055MPa), and the roasting temperature is 1200-1400 deg.C (such as 1210 deg.C, 1260 deg.C, 1300 deg.C, 1330.
The heat barrier layer can be a single layer or consists of more than two sublayers, and in each sublayer, the use amount of the heat insulation ceramic in the composite powder adopted by each sublayer is gradually reduced from the surface of the bonding layer to the outside; preferably, the thermal barrier layer is composed of an insulating sublayer and a transition sublayer in sequence from the bonding layer surface to the outside, wherein the insulating sublayer is composed of 60 to 90% by mass (for example, 65%, 70%, 75%, 80%, 85%) of the insulating ceramic in the composite powder used, and the transition sublayer is composed of 30 to 70% by mass (for example, 35%, 40%, 45%, 50%, 55%, 65%) of the insulating ceramic in the composite powder used. The function of the heat insulation sublayer is heat insulation, so that the service life of the metal matrix is prolonged. The transition sub-layer has the main functions of not only playing a role in heat insulation, but also improving the heat matching performance between the coatings, improving the bonding strength of the coatings and improving the ablation resistance of the coatings. The thermal barrier layer structure has good heat insulation effect and also has strong anti-scouring and anti-ablation properties.
The protective layer is arranged on the surface of the thermal barrier layer and is made of the tungsten powder, the molybdenum powder, the tungsten-molybdenum composite powder or the composite powder of the heat-insulating ceramic and tungsten and/or molybdenum; preferably, the thickness of the protective layer is 0.5-3.0 mm (such as 0.6mm, 0.8mm, 1.2mm, 1.5mm, 1.8mm, 2.2mm, 2.5mm, 2.8 mm). Characteristics of the protective layer material: has high melting point, and can resist severe ablation and scouring of high-temperature and high-speed gas flow, thereby protecting the thermal barrier layer and prolonging the service life of the thermal barrier layer.
The preparation method of the thermal barrier ablation-resistant composite coating adopts a plasma spraying process to spray the composite coating on the surface of the metal substrate.
Preferably, the preparation method comprises the following steps:
a sand blasting and cleaning treatment step, wherein the sand blasting treatment is carried out on the surface of the metal matrix, and then residual stains or dust on the surface of the metal matrix are cleaned;
specifically, the metal matrix is subjected to sand blasting before spraying, and the color of each part of the surface of the matrix subjected to sand blasting is uniform and consistent without a region which can be seen by naked eyes and is uneven. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material. The specific conditions of sand blasting are as follows: the pressure is 0.4-1.0 MPa (such as 0.5MPa, 0.6MPa, 0.7MPa, 0.8MPa and 0.9MPa), the sand blasting distance is 20-60 cm (such as 21cm, 25cm, 35cm, 45cm and 55cm), and the angle is 30-70 degrees (such as 32 degrees, 40 degrees, 45 degrees, 50 degrees, 55 degrees, 60 degrees and 65 degrees). The blasting equipment used for blasting is equipment commonly used in the art.
And spraying, namely spraying corresponding coating material powder serving as a raw material on the surface of the cleaned metal substrate layer by adopting a plasma spraying process to form the composite coating. The equipment adopted in the plasma spraying process is the equipment commonly used in the field.
Specifically, according to different spraying requirements, proper metal powder or composite powder is selected as spraying powder to be sequentially sprayed on the surface of the metal matrix according to the material and raw material ratio of each layer in the composite coating, so as to form the required composite coating.
The yttria-stabilized zirconia contains 0-15% yttria, and is a commercially available product.
In the spraying step, the specific process parameters of the spraying are preferably as follows: the arc current is 700-900A (such as 710A, 750A, 800A, 850A, 880A), the voltage is 20-50V (such as 22V, 30V, 35V, 40V, 45V), the helium flow SCFH 20-90 (such as SCFH22, SCFH35, SCFH40, SCFH50, SCFH60, SCFH70, SCFH80, SCFH85), the argon flow SCFH 80-100 (such as SCFH85, SCFH90, SCFH95, SCFH98), the powder feeding amount RPM is 1.0-3.0 (such as RPM1.2, RPM1.5, RPM2, RPM2.5, RPM2.8), and the distance is 60-100 mm (such as 65mm, 70mm, 80mm, 90mm, 95 mm). When each layer in the composite coating is sprayed, the formed layers are polished and measured to ensure the dimensional accuracy of each coating.
During the spraying process, if necessary, a suitable working gas is selected, for example, helium, hydrogen, nitrogen, argon, or the like can be selected.
The thermal barrier ablation-resistant composite coating and the preparation method thereof of the present invention are explained in detail by using specific examples below.
Example 1:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the bonding layer is 0.10 +/-0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of the thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters of the spray granulation are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. Wherein, the content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 62 wt%, tungsten content: 38 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.40 +/-0.1 mm, the thickness of the transition sublayer coating is 0.40 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 0.80 +/-0.2 mm. Fig. 3 is a microscopic morphology of the sprayed composite powder used in this step.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of a thermal barrier coating, namely a transition sub-layer, by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 1.50 +/-0.2 mm. FIG. 4 is a microstructure diagram of the composite coating after spraying.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier anti-ablation coatings on 5 titanium alloy substrates respectively, the test is carried out under the condition of plasma flame simulation working conditions (temperature and flow rate), the ejection port of plasma flame is directly aligned to the titanium alloy substrate coated with the thermal barrier anti-ablation coatings, wherein the vertical distance from the ejection port of the plasma flame to the surface of the titanium alloy substrate is 50mm, an infrared thermometer is adopted to measure the temperature of the plasma flame reaching the surface of the titanium alloy substrate, a laser Doppler velocimeter is adopted to measure the flow rate of the plasma flame, the test is carried out under the conditions that the surface temperature of the titanium alloy substrate is 1600 ℃ and the flow rate of the plasma flame is 1400m/s, and a stopwatch is used to record the test time. The test time is about 50s, the stripping area of the coating reaches about 10%, and the total time for completely stripping the coating is 62 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 2:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 62 wt%, tungsten content: 38 wt%. And (2) sequentially spraying the composite powder to the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.60 +/-0.1 mm, the thickness of the transition sublayer coating is 0.80 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 1.40 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 1.50 +/-0.2 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 55s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 69 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 3:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 62 wt%, tungsten content: 38 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.40 +/-0.1 mm, the thickness of the transition sublayer coating is 0.40 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 0.80 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 2.0 +/-0.2 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 58s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 73 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 4:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 62 wt%, tungsten content: 38 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat-insulating sublayer coating is 0.80 +/-0.1 mm, the thickness of the transition sublayer coating is 1.0 +/-0.1 mm, and the total thickness of the heat-insulating ablation-resistant layer coating is 1.80 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 3.0 +/-0.2 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare the thermal barrier ablation-resistant coating on 5 titanium alloy substrates, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 68s, the stripping area of the coating reaches about 10%, and the total time for completely stripping the coating is 86 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 5:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the transition sublayer was: 50 wt%, the content of tungsten is: 50 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.60 +/-0.1 mm, the thickness of the transition sublayer coating is 0.70 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 1.30 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 2.80 +/-0.2 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 55s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 71 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 6:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer is a single layer, composite powder is used as spraying powder, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the thermal barrier layer is as follows: 90 wt%, the content of tungsten is: 10 wt%. And spraying the composite powder to the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the thermal barrier layer coating is 0.60 +/-0.1 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 1.30 +/-0.1 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 40s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 57 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 7:
(1) carrying out sand blasting treatment on a high-temperature alloy (GH 4169) base body, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the high-temperature alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 70 wt%, the content of tungsten is: 30 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat-insulating sublayer coating is 0.50 +/-0.1 mm, the thickness of the transition sublayer coating is 0.60 +/-0.1 mm, and the total thickness of the heat-insulating ablation-resistant layer coating is 1.10 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 0.6 +/-0.1 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 36s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 54 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 8:
(1) carrying out sand blasting treatment on an alloy steel (with the trademark of 1Cr18Ni9Ti) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal tungsten powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal tungsten powder to the surface of the alloy steel matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the thermal barrier sublayer was: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the transition sublayer was: 62 wt%, tungsten content: 38 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.60 +/-0.1 mm, the thickness of the transition sublayer coating is 0.70 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 1.30 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 2.0 +/-0.1 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 38s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 53 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 9:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal molybdenum powder (the purity is 99.9%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal molybdenum powder to the surface of the titanium alloy matrix subjected to sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 700A, voltage 20V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 200 ℃, the outlet temperature is 60 ℃, the pressure in the tower is-0.03 MPa, and the roasting temperature is 1300 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and contains a composite powder of yttria-stabilized zirconia and molybdenum, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 90 wt%, molybdenum content: 10 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 50 wt%, molybdenum content: 50 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 750A, voltage 25V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.60 +/-0.1 mm, the thickness of the transition sublayer coating is 0.70 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 1.30 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal molybdenum powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal molybdenum powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 700A, voltage 20V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 1.10 +/-0.1 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 35s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 49 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 10:
(1) carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: NiCrAlY powder with the granularity of-200 meshes to +325 meshes (commercially available, specific components are as follows: 66.0 wt% of Ni, 22.0 wt% of Cr, 11.0 wt% of Al and 1.0 wt% of Y) is selected as bonding layer spraying powder, and the metal NiCrAlY powder is sprayed on the surface of the titanium alloy matrix after sand blasting by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 720A, voltage 25V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 250 ℃, the outlet temperature is 100 ℃, the pressure in the tower is-0.04 MPa, and the roasting temperature is 1200 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and contains a composite powder of aluminum oxide and tungsten as a component. The content of alumina in the composite powder adopted by the heat insulation sublayer is as follows: 62 wt%, tungsten content: 38 wt%; the content of alumina in the composite powder adopted by the transition sub-layer is as follows: 50 wt%, the content of tungsten is: 50 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 750A, voltage 30V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 0.40 +/-0.1 mm, the thickness of the transition sublayer coating is 0.50 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 0.90 +/-0.2 mm.
(4) Spraying a protective layer: selecting metal tungsten powder with the granularity of-200 meshes to +325 meshes as protective layer spraying powder, and spraying the metal tungsten powder to the surface of the thermal barrier coating by adopting a plasma spraying method, wherein the process parameters of the plasma spraying are as follows: arc current 900A, voltage 50V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the protective layer coating is 1.60 +/-0.1 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 35s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 52 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Example 11
(1) Carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal CoCrAlY powder (the content of the specific components is as follows, Co is 65.4 wt%, Cr is 23.0 wt%, Al is 11.0 wt%, and Y is 0.6 wt%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal CoCrAlY powder to the surface of the titanium alloy matrix after sand blasting by adopting a plasma spraying method, wherein the technological parameters of the plasma spraying are as follows: arc current 730A, voltage 20V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer comprises two sublayers: the coating layer adjacent to the bonding layer, i.e. at the outer surface of the bonding layer, is referred to as the thermal barrier sublayer and the coating layer at the outer surface of the thermal barrier sublayer is referred to as the transition sublayer. The composite powder is used as spraying powder of a thermal barrier layer, the composite powder is obtained by adopting a spray granulation process, and the specific process parameters are as follows: the inlet temperature is 300 ℃, the outlet temperature is 130 ℃, the pressure in the tower is-0.06 MPa, and the roasting temperature is 1400 ℃. The composite powder has a (d50) particle size of 50 to 100 μm and comprises a composite powder of yttria-stabilized zirconia and tungsten, wherein the yttria-stabilized zirconia contains 6 wt% of yttria. The content of yttria-stabilized zirconia in the composite powder adopted by the heat insulation sublayer is as follows: 80 wt%, the content of tungsten is: 20 wt%; the content of yttria-stabilized zirconia in the composite powder used for the transition sublayer was: 50 wt%, the content of tungsten is: 50 wt%. And (2) sequentially spraying the composite powder on the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the heat insulation sublayer coating is 1.0 +/-0.1 mm, the thickness of the transition sublayer coating is 1.50 +/-0.1 mm, and the total thickness of the heat barrier layer coating is 2.5 +/-0.2 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the embodiment is adopted to prepare thermal barrier ablation-resistant coatings on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the embodiment 1, the test time is about 40s, the stripping area of the coatings reaches about 10%, and the total time for completely stripping the coatings is 53 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.
Comparative example 1
(1) Carrying out sand blasting treatment on a titanium alloy (with the trademark of TC4) substrate, wherein corundum is used as a sand blasting medium, the mesh number of the corundum is 10-100 meshes, and the conditions of the sand blasting treatment are as follows: the pressure is 0.7 +/-0.3 MPa, the sand blasting distance is 40 +/-20 cm, and the angle is 50 +/-20 degrees.
The color of each part of the surface of the matrix after sand blasting is uniform and consistent, and no uneven area can be seen by naked eyes. And (4) wiping the material after the sand blasting is finished by using alcohol if stains or dust remain on the surface of the material.
(2) And (3) spraying a bonding layer: selecting metal CoCrAlY powder (the content of the specific components is as follows, Co is 65.4 wt%, Cr is 23.0 wt%, Al is 11.0 wt%, and Y is 0.6 wt%) with the granularity of-200 meshes to +325 meshes as bonding layer spraying powder, and spraying the metal CoCrAlY powder to the surface of the titanium alloy matrix after sand blasting by adopting a plasma spraying method, wherein the technological parameters of the plasma spraying are as follows: arc current 730A, voltage 20V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The thickness of the coating is 0.10 plus or minus 0.05 mm.
(3) Thermal barrier coating: the thermal barrier layer is a single yttria-stabilized zirconia layer: adjacent to the bonding layer, i.e. at the outer surface of the bonding layer. Wherein, the content of the yttrium oxide in the yttrium oxide stabilized zirconium oxide is 6 wt%. And spraying the yttria-stabilized zirconia powder to the surface of the bonding layer by adopting a plasma spraying method, wherein the plasma spraying process parameters are as follows: arc current 800A, voltage 40V, helium flow SCFH70 + -20, argon flow SCFH80 + -20, powder delivery RPM2.0 + -1.0, and distance 80 + -20 mm. The total thickness of the thermal barrier coating is 2.5 +/-0.2 mm.
The thickness of each coating was measured using a vernier caliper.
The method of the comparative example is adopted to prepare the thermal barrier ablation-resistant coating on 5 titanium alloy substrates respectively, the performance test is carried out by adopting the method of the example 1, the test time is about 30s, the stripping area of the coating reaches about 10 percent, and the total time for completely stripping the coating is 47 s. The above test result data are all average values of the test results of the above 5 titanium alloy substrates.

Claims (8)

1. A thermal barrier ablation-resistant composite coating is characterized in that: the composite coating is arranged on a metal matrix and sequentially comprises a bonding layer and a thermal barrier layer from the surface of the metal matrix to the outside, wherein the thermal barrier layer is made of composite powder of heat-insulating ceramic and tungsten and/or molybdenum; the heat barrier layer consists of more than two sub-layers, and in the more than two sub-layers, from the surface of the bonding layer to the outside, the heat barrier layer sequentially consists of a heat insulation sub-layer and a transition sub-layer, wherein in the composite powder adopted by the heat insulation sub-layer, the mass percent of the heat insulation ceramic is 60-90%, and in the composite powder adopted by the transition sub-layer, the mass percent of the heat insulation ceramic is 30-70%; the usage amount of the heat insulation ceramic in the composite powder adopted by the heat insulation sublayer and the transition sublayer is sequentially reduced; the composite coating further comprises a protective layer, wherein the protective layer is arranged on the surface of the thermal barrier layer and is made of tungsten powder, molybdenum powder, tungsten-molybdenum composite powder or composite powder of the heat-insulating ceramic and tungsten and/or molybdenum.
2. The thermal barrier ablation-resistant composite coating of claim 1, wherein: the bonding layer is made of tungsten powder, molybdenum powder, tungsten-molybdenum composite powder or MCrAlY powder, wherein M is one or two of Co or Ni.
3. The thermal barrier ablation-resistant composite coating of claim 1, wherein: the heat insulation ceramic is yttria-stabilized zirconia or alumina, wherein the mass percentage of yttria in the yttria-stabilized zirconia is 0-15%.
4. The thermal barrier ablation-resistant composite coating of claim 1, wherein: the thickness of the thermal barrier layer is 0.2-2 mm.
5. The thermal barrier ablation-resistant composite coating of claim 1, wherein: the thickness of the protective layer is 0.5-3.0 mm.
6. The thermal barrier ablation-resistant composite coating as claimed in any one of claims 1 to 5, wherein: the composite powder of the heat-insulating ceramic and the tungsten and/or the molybdenum is prepared by adopting a spray granulation process.
7. The thermal barrier ablation-resistant composite coating of claim 6, wherein: the parameters of the spray granulation process are as follows: the inlet temperature is 200-300 ℃, the outlet temperature is 60-130 ℃, the pressure in the tower is-0.03-0.06 MPa, and the roasting temperature is 1200-1400 ℃.
8. The method for preparing the thermal barrier ablation-resistant composite coating as claimed in any one of claims 1 to 7, characterized in that: and spraying a thermal barrier ablation-resistant composite coating on the surface of the metal matrix by adopting a plasma spraying process.
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