CN109207900B - Composite coating and preparation method thereof, titanium alloy surface treatment method and application - Google Patents

Composite coating and preparation method thereof, titanium alloy surface treatment method and application Download PDF

Info

Publication number
CN109207900B
CN109207900B CN201811341016.3A CN201811341016A CN109207900B CN 109207900 B CN109207900 B CN 109207900B CN 201811341016 A CN201811341016 A CN 201811341016A CN 109207900 B CN109207900 B CN 109207900B
Authority
CN
China
Prior art keywords
layer
spraying
titanium alloy
composite coating
nicraly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201811341016.3A
Other languages
Chinese (zh)
Other versions
CN109207900A (en
Inventor
吴护林
陈汉宾
李忠盛
赵子鹏
宋凯强
张隆平
易同斌
杨九州
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
No 59 Research Institute of China Ordnance Industry
Original Assignee
No 59 Research Institute of China Ordnance Industry
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by No 59 Research Institute of China Ordnance Industry filed Critical No 59 Research Institute of China Ordnance Industry
Priority to CN202010649676.9A priority Critical patent/CN111826599B/en
Priority to CN201811341016.3A priority patent/CN109207900B/en
Publication of CN109207900A publication Critical patent/CN109207900A/en
Application granted granted Critical
Publication of CN109207900B publication Critical patent/CN109207900B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B1/00—Processes of grinding or polishing; Use of auxiliary equipment in connection with such processes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/14—Metallic material, boron or silicon
    • C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
    • C23C14/165—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon by cathodic sputtering
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/34—Sputtering
    • C23C14/35—Sputtering by application of a magnetic field, e.g. magnetron sputtering
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C23C28/022—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer with at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/027—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal matrix material comprising a mixture of at least two metals or metal phases or metal matrix composites, e.g. metal matrix with embedded inorganic hard particles, CERMET, MMC.
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/134—Plasma spraying
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment

Abstract

The invention provides a composite coating and a preparation method thereof, a titanium alloy surface treatment method and application, and relates to the technical field of titanium alloy surface engineering. The composite coating comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer comprises NiCrAlY, the intermediate layer comprises NiCrAlY/Si, and the surface layer comprises 25NiCrTa-75Cr3C2Or 14CoCrTa-86WC, and the substrate layer, the intermediate layer and the surface layer with the specific components are selected to be cooperatively matched, so that the obtained composite coating has good performance of preventing titanium fire combustion and resisting high-temperature flame ablation. The preparation method of the composite coating provided by the invention is simple, the process is easy to control, and the cost is low. The invention also provides a titanium alloy surface treatment method, which is to spray the composite coating on the pretreated titanium alloy surface; or, the surface of the pretreated titanium alloy is treated by adopting the preparation method of the composite coating.

Description

Composite coating and preparation method thereof, titanium alloy surface treatment method and application
Technical Field
The invention relates to the technical field of titanium alloy surface engineering, in particular to a composite coating and a preparation method thereof, a titanium alloy surface treatment method and application.
Background
The titanium alloy has the advantages of low density, high mechanical strength, good heat resistance, good corrosion resistance and the like, and has been widely applied to hot end parts of equipment power systems of aviation, aerospace, weapons and the like, such as rotors, casings, rocket combustion chambers and the like of aircraft engines as lightweight materials. However, titanium alloy is sensitive to combustion environment and is easy to ignite and burn under high temperature, high pressure or violent impact, which is commonly called titanium fire, so that hot end parts are burnt, fused and burnt through, and equipment failure and even safety accidents are caused.
The titanium alloy is active metal, the oxide produced by oxidation at high temperature has low density and the oxide film is not compact, and can not play a role in protecting the matrix, and in addition, the combustion released heat is far greater than the heat dissipation speed, so that the temperature of the metal is increased, and the combustion is accelerated. The problem of flame retardance and ablation resistance of titanium alloy is the primary problem limiting the application of titanium alloy to hot end parts. The titanium alloy used as the hot end component is required to bear high-temperature and high-speed gas scouring, and the problems of flame retardance and erosion resistance of the titanium alloy are mainly solved. At present, the flame retardant problem is mainly solved from two aspects, namely, the development of flame retardant titanium alloy and the development of surface coating technology. The main purpose of developing flame-retardant titanium alloy is to increase the application temperature range of titanium alloy. The flame-retardant titanium alloy needs to be added with a large amount of expensive alloy elements, is expensive and has high research and development cost. In addition, the flame-retardant titanium alloy only solves the problem of flame retardance, but cannot solve the problem of erosion and ablation of high-speed airflow. The coating technology has become the main technology for the application of the titanium alloy hot end component due to good protection effect and low cost.
The coating technology is applied to solve the problems of flame retardance and ablation of the titanium alloy hot end part, and the designed and prepared coating needs to have the following conditions: firstly, the coating needs to be flame retardant; secondly, the coating has the function of isolating fuel gas; thirdly, the surface of the coating has the function of resisting gas scouring; fourthly, the coating also has high bonding strength with the substrate, and fifthly, the difference between the thermal expansion coefficients of the coating and the substrate is small. The coating in the prior art is poor in flame retardance and ablation resistance, and cannot meet the use requirements of titanium alloy hot-end components.
In view of the above, the present invention is particularly proposed to solve at least one of the above technical problems.
Disclosure of Invention
A first object of the present invention is to provide a composite coating having good resistance to fire burning of titanium and high temperature flame ablation.
The second purpose of the invention is to provide a preparation method of the composite coating.
The third purpose of the invention is to provide a titanium alloy surface treatment method.
The fourth purpose of the invention is to provide a composite coating, a preparation method of the composite coating or an application of a titanium alloy surface treatment method.
In order to achieve the above purpose of the present invention, the following technical solutions are adopted:
the invention provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of a titanium alloy, the surface layer is arranged on one side of the substrate layer, which is far away from the surface of the titanium alloy, and the intermediate layer is positioned between the substrate layer and the surface layer;
wherein the components of the basal layer are NiCrAlY, the components of the intermediate layer are NiCrAlY/Si, and the components of the surface layer are 25NiCrTa-75Cr3C2Or 14CoCrTa-86 WC.
Further, on the basis of the technical scheme of the invention, the addition amount of Si in the intermediate layer accounts for 5-10% of the mass fraction of NiCrAlY;
and/or, when the composition of the surface layer is 25NiCrTa-75Cr3C2When the mass ratio of Ta to Ni and Cr is (0.3-1):1:1, or when the composition of the surface layer is 14CoCrTa-86WC, the mass ratio of Ta to Co and Cr is (0.3-1):1: 1.
Further, on the basis of the technical scheme of the invention, the thickness of the substrate layer is 100-200 μm;
and/or the thickness of the intermediate layer is 200-300 μm;
and/or the thickness of the surface layer is 100-300 mu m.
The invention also provides a preparation method of the composite coating, which comprises the following steps:
providing NiCrAlY spray powder, NiCrAlY/Si spray powder and 25NiCrTa-75Cr3C2Spraying powder or 14CoCrTa-86WC spraying powder;
spraying NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer;
spraying NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer;
spraying 25NiCrTa-75Cr on the surface of the intermediate layer3C2And spraying powder or 14CoCrTa-86WC spraying powder is used as a surface layer to obtain the composite coating.
Further, on the basis of the technical scheme of the invention, NiCrAlY spraying powder, NiCrAlY/Si spraying powder and 25NiCrTa-75Cr spraying powder are added3C2Before the spraying powder or the 14CoCrTa-86WC spraying powder is sprayed, the method also comprises the step of independently drying the spraying powder or the 14CoCrTa-86WC spraying powder respectively;
preferably, the drying temperature is 60-120 ℃ and the drying time is 0.5-1.5 h.
Further, on the basis of the technical scheme of the invention, when NiCrAlY spraying powder is sprayed on the surface of the titanium alloy to form a base layer, the spraying distance of a spray gun is 100-130 mm, the scanning speed is 130-180 mm/s, the power is 25-35 kW, the scanning interval is 2-6 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 1-3 times;
and/or when NiCrAlY/Si spraying powder is sprayed on the surface of the substrate layer to form an intermediate layer, the distance between spray guns is 100-130 mm, the scanning speed is 130-180 mm/s, the power is 25-35 kW, the scanning interval is 2-6 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 2-3 times;
and/or spraying 25NiCrTa-75Cr on the surface of the intermediate layer3C2When the spraying powder or the 14CoCrTa-86WC spraying powder forms a surface layer, the distance of a spray gun is 100-130 mm, the scanning speed is 100-150 mm/s, the power is 30-40 kW, the scanning interval is 4-10 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 1-3 times.
The invention also provides a titanium alloy surface treatment method, which is to spray the composite coating on the pretreated titanium alloy surface; or, the surface of the pretreated titanium alloy is treated by adopting the preparation method of the composite coating.
Further, on the basis of the technical scheme of the invention, the pretreatment comprises the steps of cleaning and sand blasting the surface of the titanium alloy; preferably, cleaning the surface of the titanium alloy by using an organic solvent, and blasting sand after surface drying; further preferably, the sand blasting adopts carborundum with the grain diameter of 60-100 meshes, and the sand blasting pressure is 0.2-0.3 MPa;
and/or after the composite coating is sprayed on the surface of the titanium alloy, grinding the surface of the composite coating; preferably, grinding the surface of the composite coating by using a diamond grinding head; further preferably, the grinding rotating speed is 1500-.
Further, on the basis of the technical scheme of the invention, the titanium alloy surface treatment method comprises the following steps:
carrying out pretreatment of cleaning and sand blasting on the surface of the titanium alloy;
spraying NiCrAlY powder, NiCrAlY/Si powder and 25NiCrTa-75Cr3C2Respectively and independently drying the spray powder or the 14CoCrTa-86WC spray powder at the drying temperature of 60-120 ℃ for 0.5-1.5 h;
spraying dried NiCrAlY spraying powder on the surface of the pretreated titanium alloy to serve as a substrate layer, wherein the thickness of the substrate layer is 100-200 mu m; spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the addition amount of Si accounts for 5-10% of the mass fraction of NiCrAlY, and the thickness of the intermediate layer is 200-300 mu m; spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Taking the spraying powder as a surface layer, wherein the mass ratio of Ta to Ni and Cr is 1:1:1, and the thickness of the surface layer is 300 mu m, or taking the dried 14CoCrTa-86WC spraying powder as a surface layer, wherein the mass ratio of Ta to Co and Cr is 1:1:1, and the thickness of the surface layer is 100-;
and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 1500-2000r/min, and the grinding amount is 50-100 mu m.
The invention also provides a heat insulation product, which comprises the composite coating;
preferably, the insulation product comprises at least two layers of the composite coating, and at least two layers of the composite coating are alternately arranged in a layer.
The invention also provides the composite coating, a preparation method of the composite coating or application of the titanium alloy surface treatment method in titanium alloy surface engineering.
Compared with the prior art, the composite coating, the preparation method of the composite coating and the titanium alloy surface treatment method provided by the invention have the following beneficial effects:
(1) the invention provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer comprises NiCrAlY, the intermediate layer comprises NiCrAlY/Si, and the surface layer comprises 25NiCrTa-75Cr3C2Or 14CoCrTa-86 WC; the NiCrAlY alloy component selected by the substrate layer has a low expansion coefficient and is close to the substrate, the bonding strength with the substrate is high after spraying, a thicker compact coating can be formed, and the flame retardant effect is good; the middle layer is a transition layer provided between the substrate layer and the surface layer, the main component of the middle layer is NiCrAlY/Si, and the middle layer can form a glass state substance after high-temperature oxidation to seal the pore gaps and prevent high-temperature gas, particularly oxygen, from contacting with the bottom layer, so that the flame retardant property is further improved; the composition of the surface layer is 25NiCrTa-75Cr3C2Or 14CoCrTa-86WC, the surface layer has a porous compact structure, has a deformation space during thermal expansion, ensures that the deformation process does not crack by utilizing pore adjustment, and has the capability of resisting scouring particles so as to improve the ablation resistance of the surface; by selecting the substrate layer, the middle layer and the surface layer with the specific components to cooperate, the obtained composite coating has good performance of preventing titanium fire combustion and high-temperature flame ablation resistance, and the flame retardant and ablation problems of the titanium alloy hot-end component can be effectively improved by applying the composite coating to the surface of the titanium alloy.
(2) The invention provides a preparation method of a composite coating, which is simple, easy in process control, low in cost and excellent in effect.
(3) The invention provides a titanium alloy surface treatment method, which comprises the steps of spraying the composite coating on the surface of a pretreated titanium alloy; or, the surface of the pretreated titanium alloy is treated by adopting the preparation method of the composite coating. In view of the advantages of the composite coating or the preparation method of the composite coating, the composite coating is sprayed on the surface of the titanium alloy, so that the performances of titanium flame burning prevention and high-temperature flame ablation resistance on the surface of the titanium alloy can be effectively improved, the use requirements are met, and the use reliability of the titanium alloy hot-end component is improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic structural diagram of a composite coating according to the present invention;
FIG. 2 is a cross-sectional view of a titanium alloy surface treated with a composite coating according to example 11 of the present invention;
FIG. 3 shows the surface topography of the composite coating provided in example 11 of the present invention.
Reference numerals:
10-titanium alloy surface; 20-a base layer; 30-an intermediate layer; 40-surface layer.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to examples, but it will be understood by those skilled in the art that the following examples are only illustrative of the present invention and should not be construed as limiting the scope of the present invention. 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 not indicated by the manufacturer, and are all conventional products available commercially.
According to a first aspect of the present invention, there is provided a composite coating, as particularly shown in fig. 1. The composite coating comprises a substrate layer 20, an intermediate layer 30 and a surface layer 40, wherein the substrate layer 20 is arranged on the titanium alloy surface 10, the surface layer 40 is arranged on one side of the substrate layer 20 far away from the titanium alloy surface 10, and the intermediate layer 30 is arranged between the substrate layer 20 and the surface layer 40;
wherein the substrate comprises NiCrAlY, the intermediate layer comprises NiCrAlY/Si, and the surface layer comprises 25NiCrTa-75Cr3C2Or 14CoCrTa-86 WC.
Specifically, the NiCrAlY alloy in the substrate layer has good high-temperature oxidation resistance and hot corrosion resistance, the thermal expansion coefficient of the NiCrAlY alloy is low and is close to that of the substrate, and the peeling of the coating caused by inconsistent expansion of the substrate and the coating when the substrate is heated can be avoided; after spraying, the coating has high bonding strength with a matrix, can form a thicker compact coating for isolating gas from contacting the surface of the titanium alloy, and has good flame retardant effect, namely, the coating does not burn in a combustion environment or in the corrosion of the gas. The specific contents of the elements in the substrate layer NiCrAlY alloy are not limited.
The intermediate layer is a transition layer provided between the substrate layer and the surface layer, and the composition of the intermediate layer is NiCrAlY/Si, and NiCrAlY/Si means that Si and NiCrAlY are mixed or doped. The preparation method of the specific NiCrAlY/Si spray powder is not limited, and preferably, a certain proportion of Si is added into NiCrAlY powder, the mixture is mixed by ball milling, and then the NiCrAlY/Si spray powder is prepared by adopting an atomization granulation method. NiCrAlY/Si can form a glass state substance after being oxidized at high temperature to seal the pore gaps, so that high-temperature gas, particularly oxygen, is prevented from contacting with the bottom layer, and the flame retardant property is further improved.
The composition of the surface layer is 25NiCrTa-75Cr3C2Or 14CoCrTa-86 WC. 25NiCrTa-75Cr3C2Refers to Ta and NiCr-Cr3C2Mixed or doped, 14CoCrTa-86WC means that Ta is mixed or doped with CoCr-WC. 25NiCrTa-75Cr3C2Or the specific preparation method of 14CoCrTa-86WC is not limited, preferably, Ta powder with a certain proportion is added into NiCr-Cr3C2Or in CoCr-WC, mixing by ball milling, and preparing 25NiCrTa-75Cr by adopting an atomization granulation method3C2Spraying powder or 14CoCrTa-86WC spraying powder;
the surface layer adopts specific 25NiCrTa-75Cr3C2Or 14CoCrTa-86WC, so that the surface layer has a porous compact structure, the porous compact structure ensures that the surface layer has a deformation space during thermal expansion, the deformation process is prevented from cracking by utilizing pore adjustment, and the surface layer also has the capability of resisting scouring particles and improves the surface ablation resistance.
The composite coating provided by the invention has the advantages that the substrate layer, the middle layer and the surface layer which are made of the specific components are cooperatively matched, so that the obtained composite coating can effectively solve the problems of flame retardance and ablation of a titanium alloy hot end part.
As an alternative embodiment of the invention, the Si added in the intermediate layer is present in a mass fraction of 5-10% of the NiCrAlY, typically but not limited to 5%, 6%, 7%, 8%, 9% or 10% by mass fraction.
The addition amount of Si cannot be too high, if the addition amount is too high, a large amount of liquid oxide is easily formed at high temperature, the bonding strength between layers is reduced, and if the addition amount of Si is too low, the liquid formed after high-temperature oxidation cannot play a role in sealing the gap. Therefore, the amount of Si added to the intermediate layer NiCrAlY/Si is preferably kept within a specific range.
As an alternative embodiment of the invention, when the composition of the surface layer is 25NiCrTa-75Cr3C2The mass ratio of Ta to Ni, Cr is (0.3-1):1:1, preferably (0.5-1):1:1, more preferably (0.6-1):1:1, most preferably 1:1:1, typical but not limiting mass ratios of Ta to Ni, Cr are 0.3:1:1, 0.4:1:1, 0.5:1:1, 0.6:1:1, 0.7:1:1, 0.8:1:1, 0.9:1:1 or 1:1: 1;
or, when the component of the surface layer is 14CoCrTa-86WC, the mass ratio of Ta to Co, Cr is (0.3-1):1:1, preferably (0.5-1):1:1, more preferably (0.6-1):1:1, most preferably 1:1:1, and typically, but not limited to, the mass ratio of Ta to Co, Cr is 0.3:1:1, 0.4:1:1, 0.5:1:1, 0.6:1:1, 0.7:1:1, 0.8:1:1, 0.9:1:1 or 1:1: 1.
In addition, the alloy is prepared in a range of 25NiCrTa to 75Cr3C2Or, Ta is generally not more than 35% by mass based on the total mass of Ni, Cr and Ta, and once the mass fraction of Ta exceeds 35%, the high-temperature oxidation resistance is deteriorated, but when T is exceededWhen the mass fraction of a is too low (less than about 13%), the ablation resistance is not exhibited.
In 14CoCrTa-86WC, Ta generally does not exceed 35% by mass based on the total mass of Co, Cr and Ta, and when the mass fraction of Ta exceeds 35%, the high-temperature oxidation resistance is deteriorated, but when the mass fraction of Ta is too low (less than about 13%), the effect of ablation resistance is not exerted.
As an alternative embodiment of the present invention, the thickness of the substrate layer is 100-200 μm, preferably 110-190 μm, and more preferably 120-180 μm, and the typical but non-limiting thickness of the substrate layer is 100 μm, 110 μm, 120 μm, 130 μm, 140 μm, 150 μm, 160 μm, 170 μm, 180 μm, 190 μm or 200 μm;
as an alternative embodiment of the present invention, the thickness of the intermediate layer is 200-300 μm, preferably 210-290 μm, and more preferably 220-280 μm, and the typical but non-limiting thickness of the intermediate layer is 200 μm, 210 μm, 220 μm, 230 μm, 240 μm, 250 μm, 260 μm, 280 μm, 290 μm or 300 μm;
as an alternative embodiment of the present invention, the thickness of the surface layer is 100-300 μm, preferably 110-290 μm, and more preferably 120-280 μm, and the typical but non-limiting thickness of the surface layer is 100 μm, 110 μm, 120 μm, 140 μm, 150 μm, 160 μm, 180 μm, 200 μm, 220 μm, 240 μm, 250 μm, 260 μm, 280 μm, 290 μm, or 300 μm.
The thickness of each layer can meet the appropriate thickness requirement by limiting the thickness of the substrate layer, the intermediate layer and the surface layer.
According to the second aspect of the present invention, there is also provided a method for preparing a composite coating, comprising the steps of:
providing NiCrAlY spray powder, NiCrAlY/Si spray powder and 25NiCrTa-75Cr3C2Spraying powder or 14CoCrTa-86WC spraying powder;
spraying NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer;
spraying NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer;
spraying 25NiCrTa-75Cr on the surface of the intermediate layer3C2Spray powder or 14CAnd taking the oCrTa-86WC spraying powder as a surface layer to obtain the composite coating.
Specifically, the spraying manner of each layer is not particularly limited, and the spraying manner commonly used in the art can be adopted, for example, the preparation of the substrate layer NiCrAlY can adopt supersonic flame spraying, low-ion spraying, thermal spraying, magnetron sputtering methods and the like; intermediate layer NiCrAlY/Si and surface layer 25NiCrTa-75Cr3C2Or the surface layer 14CoCrTa-86WC can be prepared by adopting a thermal spraying method and the like.
The preparation method of the composite coating is simple, low in cost and suitable for industrial production.
The methods of preparing the substrate layer, intermediate layer, and surface layer may also affect the structure of the composite coating. Therefore, a suitable coating preparation method should be selected. In an alternative embodiment of the present invention, the substrate layer, the intermediate layer and the surface layer are all prepared by a thermal spraying method.
Thermal spraying is to heat and melt a coating material, atomize the coating material into ultrafine particles by a high-speed airflow, and spray the ultrafine particles onto the surface of a workpiece at a high speed to form a coating. The preparation method is flexible and convenient, is not limited by the shape of a workpiece, is convenient to construct and has wide application range.
As an alternative embodiment of the invention, NiCrAlY spray powder, NiCrAlY/Si spray powder and 25NiCrTa-75Cr are sprayed3C2Before spraying the spray powder or the 14CoCrTa-86WC spray powder, the method also comprises the step of independently drying the spray powder respectively. The dryness of the individual spray powders directly influences the spray quality. Once the spraying powder is moist or the environmental humidity is large, the spraying powder is inevitably promoted to agglomerate in a large quantity, so that a spray gun and other related spraying powder conveying equipment are blocked, and the spraying quality is influenced.
As an optional embodiment of the invention, the drying temperature is 60-120 ℃ and the drying time is 0.5-1.5 h. Typical but not limiting drying temperatures are 60 ℃, 70 ℃, 80 ℃, 90 ℃, 100 ℃, 110 ℃ or 120 ℃, typical but not limiting drying times are 0.5h, 1.0h or 1.5 h. By limiting the drying temperature and the drying time, each spraying powder is in proper dryness, which is favorable for smooth spraying.
As an optional embodiment of the invention, when NiCrAlY spraying powder is sprayed on the surface of the titanium alloy to form a base layer, the spraying distance of a spray gun is 100-130 mm, the scanning speed is 130-180 mm/s, the power is 25-35 kW, the scanning interval is 2-6 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 1-3 times;
typical but non-limiting spray distances of the spray gun are for example 100mm, 105mm, 110mm, 115mm, 120mm, 125mm or 130 mm; typical but non-limiting scan speeds are 130mm/s, 140mm/s, 150mm/s, 160mm/s, 170mm/s or 180 mm/s; typical but non-limiting power is 25kW, 26kW, 28kW, 30kW, 32kW, 34kW, or 35 kW; typical but non-limiting scan pitches are 2mm, 3mm, 4mm, 5mm or 6 mm; typical but non-limiting carrier gas pressures are 0.3MPa, 0.35MPa, 0.4MPa, 0.45MPa or 0.5 MPa; typical but non-limiting spray passes are 1, 2 or 3.
As an optional embodiment of the invention, when NiCrAlY/Si spraying powder is sprayed on the surface of a substrate layer to form an intermediate layer, the distance between spray guns is 100-130 mm, the scanning speed is 130-180 mm/s, the power is 25-35 kW, the scanning interval is 2-6 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 2 times or 3 times;
typical but non-limiting spray distances of the spray gun are for example 100mm, 105mm, 110mm, 115mm, 120mm, 125mm or 130 mm; typical but non-limiting scan speeds are 130mm/s, 140mm/s, 150mm/s, 160mm/s, 170mm/s or 180 mm/s; typical but non-limiting power is 25kW, 26kW, 28kW, 30kW, 32kW, 34kW, or 35 kW; typical but non-limiting scan pitches are 2mm, 3mm, 4mm, 5mm or 6 mm; typical but non-limiting carrier gas pressures are 0.3MPa, 0.35MPa, 0.4MPa, 0.45MPa or 0.5 MPa; typical but non-limiting spray passes are 2 or 3.
As an alternative embodiment of the invention, 25NiCrTa-75Cr is sprayed on the surface of the interlayer3C2When the spraying powder or the 14CoCrTa-86WC spraying powder forms a surface layer, the distance of a spray gun is 100-130 mm, the scanning speed is 100-150 mm/s, the power is 30-40 kW, the scanning interval is 4-10 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 1-3 times；
Typical but non-limiting spray distances of the spray gun are for example 100mm, 105mm, 110mm, 115mm, 120mm, 125mm or 130 mm; typical but non-limiting scan speeds are 100mm/s, 110mm/s, 120mm/s, 130mm/s, 140mm/s or 150 mm/s; typical but non-limiting power is 30kW, 32kW, 34kW, 35kW, 36kW, 38kW or 40 kW; typical but non-limiting scan pitches are 4mm, 5mm, 6mm, 8mm or 10 mm; typical but non-limiting carrier gas pressures are 0.3MPa, 0.35MPa, 0.4MPa, 0.45MPa or 0.5 MPa; typical but non-limiting spray passes are 1, 2 or 3.
Through the limitation of each process parameter in the spraying process, the spraying quality of the substrate layer, the middle layer and the surface layer reaches a better level.
According to the third aspect of the invention, the invention also provides a titanium alloy surface treatment method, the composite coating is sprayed on the pretreated titanium alloy surface; or, the surface of the pretreated titanium alloy is treated by adopting the preparation method of the composite coating.
In view of the advantages of the composite coating or the preparation method of the composite coating, the composite coating is sprayed on the surface of the titanium alloy, so that the performances of titanium flame burning prevention and high-temperature flame ablation resistance on the surface of the titanium alloy can be effectively improved, the use requirements are met, and the use reliability of the titanium alloy hot-end component is improved.
As an alternative embodiment of the invention, the pretreatment comprises the steps of cleaning and sandblasting the titanium alloy surface;
after the titanium alloy is processed, cast or manufactured and formed, some dirt is adhered to the surface of the titanium alloy, so that the surface of the titanium alloy needs to be cleaned. As an optional implementation mode of the invention, the titanium alloy surface is cleaned by an organic solvent, and sand blasting is carried out after surface drying; further preferably, the sand blasting adopts carborundum with the grain diameter of 60-100 meshes, and the sand blasting pressure is 0.2-0.3 MPa;
the organic solvent is not particularly limited, and a non-oily volatile organic solvent such as ethyl acetate, acetone, or alcohol may be used. After cleaning with an organic solvent, sandblasting with emery having a certain grain size, typically but not limited to 60 mesh, 80 mesh or 100 mesh, and typically but not limited to 0.2MPa, 0.25MPa or 0.3 MPa.
In the sand blasting process, the sand blasting pressure is not too large or too small. If the pressure is too high, carborundum sand grains impact the surface of the titanium alloy to generate violent sparks, the temperature rise can harden with the surface of the titanium alloy to form secondary pollution, the surface quality of the titanium alloy is influenced, and if the pressure is too low, a good sand blasting effect cannot be achieved.
And after the composite coating is sprayed, finish machining the sprayed surface by diamond grinding. As an optional embodiment of the invention, after the composite coating is sprayed on the surface of the titanium alloy, the surface of the composite coating is ground; preferably, grinding the surface of the composite coating by using a diamond grinding head; further preferably, the grinding rotating speed is 1500-. Typical but non-limiting grinding speeds are 1500r/min, 1600r/min, 1700r/min, 1800r/min, 1900r/min or 2000r/min, typical but non-limiting grinding amounts are 50 μm, 60 μm, 70 μm, 80 μm, 90 μm or 100 μm.
The grinding rotating speed and the grinding amount in the grinding process are limited, so that the bonding force between the composite coating and the titanium alloy surface is influenced, and meanwhile, higher smoothness can be obtained.
As an alternative embodiment of the present invention, a titanium alloy surface treatment method includes the steps of:
carrying out pretreatment of cleaning and sand blasting on the surface of the titanium alloy;
spraying NiCrAlY powder, NiCrAlY/Si powder and 25NiCrTa-75Cr3C2Respectively and independently drying the spray powder or the 14CoCrTa-86WC spray powder at the drying temperature of 60-120 ℃ for 0.5-1.5 h;
spraying dried NiCrAlY spraying powder on the surface of the pretreated titanium alloy to serve as a substrate layer, wherein the thickness of the substrate layer is 100-200 mu m; spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein Si accounts for 5-10% of the mass fraction of NiCrAlY, and the thickness of the intermediate layer is 200-300 mu m; spraying dry on the surface of the intermediate layerDried 25NiCrTa-75Cr3C2Taking the spraying powder as a surface layer, wherein the mass ratio of Ta to Ni and Cr is 1:1:1, and the thickness of the surface layer is 300 mu m, or taking the dried 14CoCrTa-86WC spraying powder as a surface layer, wherein the mass ratio of Ta to Co and Cr is 1:1:1, and the thickness of the surface layer is 100-;
and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 1500-2000r/min, and the grinding amount is 50-100 mu m.
The steps of the titanium alloy surface treatment method are limited, so that the titanium alloy surface can achieve good effects of preventing titanium fire combustion and resisting high-temperature flame ablation, a foundation is laid for the application of the titanium alloy to hot end parts, and the application field of the titanium alloy is widened.
According to the fourth aspect of the invention, the composite coating, the preparation method of the composite coating or the application of the titanium alloy surface treatment method in titanium alloy surface engineering are also provided.
The titanium alloy treated by the composite coating, the preparation method of the composite coating or the titanium alloy surface treatment method has excellent performance of preventing titanium fire combustion and resisting high-temperature flame ablation, meets the use requirement of the titanium alloy hot-end component, achieves the aim of reliably using the titanium alloy hot-end component in a high-temperature and high-speed gas flame environment, and lays a technical foundation for expanding the use range of the titanium alloy.
The present invention will be further described with reference to specific examples and comparative examples.
Example 1
The embodiment provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of a titanium alloy, the surface layer is arranged on one side of the substrate layer, which is far away from the surface of the titanium alloy, and the intermediate layer is arranged between the substrate layer and the surface layer;
wherein the component of the basal layer is NiCrAlY, and the thickness is 100 μm; the intermediate layer is made of NiCrAlY/Si with the thickness of 200 mu m, and Si accounts for 5 percent of the mass of the NiCrAlY; the composition of the surface layer is 25NiCrTa-75Cr3C2The thickness is 100 μm, and the mass ratio of Ta to Ni and Cr is1:1:1。
The preparation method of the composite coating comprises the following steps:
(a) spraying NiCrAlY powder, NiCrAlY/Si powder and 25NiCrTa-75Cr3C2Drying the spray powder in an oven at 120 ℃ for 0.5 h;
(b) spraying dried NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer, wherein the distance between spray guns is 130mm, the scanning speed is 180mm/s, the power is 25kW, the scanning distance is 6mm, the carrier gas pressure is 0.5MPa, and the spraying pass is 1 time;
spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the distance between spray guns is 130mm, the scanning speed is 180mm/s, the power is 25kW, the scanning distance is 6mm, the carrier gas pressure is 0.5MPa, and the spraying passes are carried out for 2 times;
spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Spraying powder as a surface layer, wherein the distance between a spray gun and the surface layer is 130mm, the scanning speed is 150mm/s, the power is 30kW, the scanning distance is 10mm, the carrier gas pressure is 0.5MPa, and the spraying passes are 1 time to obtain a composite coating;
(c) and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 1500r/min, and the grinding amount is 50 microns.
Example 2
The embodiment provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of a titanium alloy, the surface layer is arranged on one side of the substrate layer, which is far away from the surface of the titanium alloy, and the intermediate layer is arranged between the substrate layer and the surface layer;
wherein the component of the basal layer is NiCrAlY, and the thickness is 200 μm; the intermediate layer is made of NiCrAlY/Si, the thickness of the intermediate layer is 300 mu m, and the Si accounts for 10 percent of the mass of the NiCrAlY; the surface layer comprises 14CoCrTa-86WC with the thickness of 300 μm and the mass ratio of Ta to Co and Cr is 1:1: 1.
The preparation method of the composite coating comprises the following steps:
(a) drying the NiCrAlY spraying powder, the NiCrAlY/Si spraying powder and the 14CoCrTa-86WC spraying powder in an oven at the drying temperature of 60 ℃ for 1.5 h;
(b) spraying dried NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer, wherein the distance between spray guns is 100mm, the scanning speed is 130/s, the power is 35kW, the scanning distance is 2mm, the carrier gas pressure is 0.3MPa, and the spraying pass is performed for 2 times;
spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the distance between spray guns is 130mm, the scanning speed is 180mm/s, the power is 25kW, the scanning distance is 6mm, the carrier gas pressure is 0.5MPa, and the spraying passes are carried out for 3 times;
spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Spraying powder as a surface layer, wherein the distance between a spray gun and the surface layer is 100mm, the scanning speed is 100mm/s, the power is 40kW, the scanning distance is 4mm, the carrier gas pressure is 0.3MPa, and the spraying passes are performed for 3 times to obtain a composite coating;
(c) and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 2000r/min, and the grinding amount is 100 mu m.
Example 3
The embodiment provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of a titanium alloy, the surface layer is arranged on one side of the substrate layer, which is far away from the surface of the titanium alloy, and the intermediate layer is arranged between the substrate layer and the surface layer;
wherein the component of the basal layer is NiCrAlY, and the thickness is 200 μm; the middle layer is made of NiCrAlY/Si with the thickness of 200 mu m, and Si accounts for 8 percent of the mass fraction of the NiCrAlY; the composition of the surface layer is 25NiCrTa-75Cr3C2The thickness is 200 μm, and the mass ratio of Ta to Ni and Cr is 1:1: 1.
The preparation method of the composite coating comprises the following steps:
(a) drying NiCrAlY spray coating powder, NiCrAlY/Si spray coating powder and 14CoCrTa-86WC spray coating powder in an oven at the drying temperature of 80 ℃ for 1.0 h;
(b) spraying dried NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer, wherein the distance between spray guns is 150mm, the scanning speed is 150/s, the power is 30kW, the scanning distance is 4mm, the carrier gas pressure is 0.4MPa, and the spraying pass is carried out for 2 times;
spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the distance between spray guns is 130mm, the scanning speed is 180mm/s, the power is 25kW, the scanning distance is 6mm, the carrier gas pressure is 0.5MPa, and the spraying passes are carried out for 2 times;
spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Spraying powder as a surface layer, wherein the distance between a spray gun and the surface layer is 120mm, the scanning speed is 130mm/s, the power is 35kW, the scanning distance is 8mm, the carrier gas pressure is 0.4MPa, and the spraying passes are performed for 2 times to obtain a composite coating;
(c) and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding speed is 1800r/min, and the grinding quantity is 50 microns.
Example 4
The embodiment provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of a titanium alloy, the surface layer is arranged on one side of the substrate layer, which is far away from the surface of the titanium alloy, and the intermediate layer is arranged between the substrate layer and the surface layer;
wherein the component of the basal layer is NiCrAlY, and the thickness is 100 μm; the middle layer is made of NiCrAlY/Si with the thickness of 200 mu m, and Si accounts for 8 percent of the mass fraction of the NiCrAlY; the surface layer comprises 14CoCrTa-86WC with a thickness of 200 μm and a mass ratio of Ta to Co to Cr of 1:1: 1.
The preparation method of the composite coating comprises the following steps:
(a) drying NiCrAlY spray coating powder, NiCrAlY/Si spray coating powder and 14CoCrTa-86WC spray coating powder in an oven at the drying temperature of 80 ℃ for 1.0 h;
(b) spraying dried NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer, wherein the distance between spray guns is 120mm, the scanning speed is 140mm/s, the power is 30kW, the scanning distance is 5mm, the carrier gas pressure is 0.4MPa, and the spraying pass is 1 time;
spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the distance between spray guns is 120mm, the scanning speed is 140mm/s, the power is 30kW, the scanning distance is 5mm, the carrier gas pressure is 0.4MPa, and the spraying passes are carried out for 2 times;
spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Spraying powder as surface layer, with a distance of 110mm, a scanning speed of 130mm/s, a power of 35kW, a scanning interval of 5mm, a carrier gas pressure of 0.4MPa, and 2 times of spraying passes to obtain a compositeCombining the coating;
(c) and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 1600r/min, and the grinding quantity is 100 mu m.
Example 5
The embodiment provides a composite coating, which comprises a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of a titanium alloy, the surface layer is arranged on one side of the substrate layer, which is far away from the surface of the titanium alloy, and the intermediate layer is arranged between the substrate layer and the surface layer;
wherein the component of the basal layer is NiCrAlY, and the thickness is 150 μm; the intermediate layer is made of NiCrAlY/Si with the thickness of 30 mu m, and Si accounts for 7 percent of the mass of the NiCrAlY; the surface layer had a composition of 14CoCrTa-86WC with a thickness of 150 μm and a mass ratio of Ta to Co, Cr of 0.3:1: 1.
The preparation method of the composite coating comprises the following steps:
(a) drying NiCrAlY spray coating powder, NiCrAlY/Si spray coating powder and 14CoCrTa-86WC spray coating powder in an oven at the drying temperature of 100 ℃ for 0.75 h;
(b) spraying dried NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer, wherein the distance between spray guns is 120mm, the scanning speed is 140mm/s, the power is 30kW, the scanning distance is 5mm, the carrier gas pressure is 0.4MPa, and the spraying pass is 1 time;
spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the distance between spray guns is 110mm, the scanning speed is 140mm/s, the power is 30kW, the scanning distance is 5mm, the carrier gas pressure is 0.4MPa, and the spraying passes are carried out for 2 times;
spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Spraying powder as a surface layer, wherein the distance between a spray gun and the surface layer is 110mm, the scanning speed is 130mm/s, the power is 35kW, the scanning distance is 5mm, the carrier gas pressure is 0.4MPa, and the spraying passes are performed for 2 times to obtain a composite coating;
(c) and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 1600r/min, and the grinding quantity is 100 mu m.
Example 6
This example provides a composite coating having a composition of 25NiCrTa-75Cr except for the surface layer3C2The mass ratio of Ta to Ni to Cr is 0.3:1:1, and the parameters and preparation method of the rest of the composite coating are the same as those of example 5.
Example 7
This example provides a composite coating having a composition of 25NiCrTa-75Cr except for the surface layer3C2The mass ratio of Ta to Ni and Cr is 1.2:1:1, and the parameters and preparation method of the rest of the composite coating are the same as those of example 1.
Example 8
This example provides a composite coating, except that the composition of the surface layer is 14CoCrTa-86WC, the mass ratio of Ta to Co, Cr is 1.2:1:1, and the parameters and preparation method of the other composite coatings are the same as those of example 2.
Example 9
This example provides a composite coating, except that the intermediate layer has a 12% Si content in NiCrAlY by mass, and the parameters and preparation method of the composite coating are the same as those of example 1.
Example 10
This example provides a composite coating, except that the intermediate layer has 3% Si by mass of NiCrAlY, and the parameters and preparation method of the composite coating are the same as those of example 1.
Comparative example 1
This comparative example provides a composite coating comprising a substrate layer and an intermediate layer, without a skin layer, the parameters of the substrate layer and the intermediate layer being the same as in example 1.
The composite coating of this example was prepared by the same procedure as in example 1, except that only the base layer and the intermediate layer were sprayed in step (b) and the surface layer was not sprayed.
Comparative example 2
This comparative example provides a composite coating comprising a substrate layer and a skin layer, without an intermediate layer, the parameters of the substrate layer and the skin layer being the same as in example 1.
The composite coating of this example was prepared by the same procedure as in example 1, except that only the base layer and the surface layer were sprayed in step (b) and the intermediate layer was not sprayed.
Comparative example 3
This comparative example provides a composite coating comprising an intermediate layer and a surface layer, without a substrate layer, the parameters of the intermediate layer and the surface layer being the same as in example 1.
Example 11
The embodiment provides a titanium alloy surface treatment method, which comprises the following steps:
(a) designing a spraying tool according to the structure of the workpiece and the requirement of a spraying part, and machining the tool by using a common 45 steel machine;
(b) cleaning the surface of the titanium alloy by using ethyl acetate, drying the surface of the titanium alloy, and then blasting sand, wherein carborundum with the particle size of 60 meshes is used, and the blasting pressure is 0.3 MPa;
(c) the composite coating is sprayed on the surface of the titanium alloy by adopting the preparation method of the composite coating provided by the embodiment 1.
Example 12
The embodiment provides a titanium alloy surface treatment method, which comprises the following steps:
(a) designing a spraying tool according to the structure of the workpiece and the requirement of a spraying part, and machining the tool by using a common 45 steel machine;
(b) cleaning the surface of the titanium alloy by using ethyl acetate, drying the surface of the titanium alloy, and then blasting sand, wherein carborundum with the particle size of 60 meshes is used, and the blasting pressure is 0.2 MPa;
(c) the composite coating is sprayed on the surface of the titanium alloy by adopting the preparation method of the composite coating provided by the embodiment 2.
Example 13
The embodiment provides a titanium alloy surface treatment method, which comprises the following steps:
(a) designing a spraying tool according to the structure of the workpiece and the requirement of a spraying part, and machining the tool by using a common 45 steel machine;
(b) cleaning the surface of the titanium alloy by using ethyl acetate, drying the surface of the titanium alloy, and then blasting sand, wherein carborundum with the particle size of 60 meshes is used, and the blasting pressure is 0.4 MPa;
(c) the composite coating is sprayed on the surface of the titanium alloy by the preparation method of the composite coating provided by the embodiment 3.
Example 14
The embodiment provides a titanium alloy surface treatment method, which comprises the following steps:
(a) designing a spraying tool according to the structure of the workpiece and the requirement of a spraying part, and machining the tool by using a common 45 steel machine;
(b) cleaning the surface of the titanium alloy by using ethyl acetate, drying the surface of the titanium alloy, and then blasting sand, wherein carborundum with the particle size of 60 meshes is used, and the blasting pressure is 0.4 MPa;
(c) the composite coating is sprayed on the surface of the titanium alloy by the preparation method of the composite coating provided in the embodiment 4.
Example 15
The embodiment provides a titanium alloy surface treatment method, which comprises the following steps:
(a) designing a spraying tool according to the structure of the workpiece and the requirement of a spraying part, and machining the tool by using a common 45 steel machine;
(b) cleaning the surface of the titanium alloy by using ethyl acetate, drying the surface of the titanium alloy, and then blasting sand, wherein carborundum with the particle size of 80 meshes is used, and the blasting pressure is 0.4 MPa;
(c) the composite coating is sprayed on the surface of the titanium alloy by the preparation method of the composite coating provided in the embodiment 5.
Example 16
This example provides a method for treating a surface of a titanium alloy, which comprises the same steps as in example 15, except that the method for preparing a composite coating layer provided in example 6 is used to spray a composite coating layer on a surface of a titanium alloy in step (c).
Example 17
This example provides a method for treating a surface of a titanium alloy, which comprises the same steps as in example 11, except that the method for preparing a composite coating layer provided in example 7 is used to spray a composite coating layer on a surface of a titanium alloy in step (c).
Example 18
This example provides a method for treating a surface of a titanium alloy, which comprises the same steps as in example 12, except that the method for preparing a composite coating layer provided in example 8 is used to spray a composite coating layer on a surface of a titanium alloy in step (c).
Example 19
This example provides a method for treating a surface of a titanium alloy, which comprises the same steps as in example 11, except that the method for preparing a composite coating layer provided in example 9 is used to spray a composite coating layer on a surface of a titanium alloy in step (c).
Example 20
This example provides a method for treating a surface of a titanium alloy, which comprises the same steps as in example 11, except that the method for preparing a composite coating layer provided in example 10 is used to spray a composite coating layer on a surface of a titanium alloy in step (c).
Comparative example 4
This comparative example provides a titanium alloy surface treatment method, which is the same as example 11 except that the composite coating is sprayed on the titanium alloy surface in step (c) using the method for preparing the composite coating provided in comparative example 1.
Comparative example 5
This comparative example provides a titanium alloy surface treatment method, which is the same as example 11 except that the composite coating is sprayed on the titanium alloy surface in step (c) using the method for preparing the composite coating provided in comparative example 2.
Comparative example 6
This comparative example provides a titanium alloy surface treatment method, which is the same as example 11 except that the composite coating is sprayed on the titanium alloy surface in step (c) using the method for preparing the composite coating provided in comparative example 3.
A series of practical verifications were carried out on the composite coatings of examples 11 to 20 and comparative examples 4 to 6, wherein fig. 2 is an SEM image of the composite coating on the surface of the titanium alloy of example 11, and fig. 3 is a surface topography image of the composite coating provided by example 11. As can be seen from fig. 2, there are a base layer, an intermediate layer and a surface layer with distinct interfaces on the surface of the titanium alloy.
From the practical application result, the performances of titanium flame burning prevention and high-temperature flame ablation resistance of the composite coating provided by the embodiment of the invention are obviously superior to those of the composite coating provided by the comparative example, so that the composite coating and the titanium alloy surface treatment method provided by the invention can achieve good technical effects and meet the use requirements of titanium alloy hot-end components.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art 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 invention.

Claims (9)

1. The composite coating is characterized by comprising a substrate layer, an intermediate layer and a surface layer, wherein the substrate layer is arranged on the surface of the titanium alloy, the surface layer is arranged on one side of the substrate layer away from the surface of the titanium alloy, and the intermediate layer is positioned between the substrate layer and the surface layer; wherein the components of the basal layer are NiCrAlY, the components of the intermediate layer are NiCrAlY/Si, and the components of the surface layer are 25NiCrTa-75Cr3C2Or 14CoCrTa-86 WC;
the mass fraction of Si in the intermediate layer accounting for NiCrAlY is 5-10%;
and/or, when the composition of the surface layer is 25NiCrTa-75Cr3C2When the mass ratio of Ta to Ni and Cr is (0.3-1):1:1, or when the composition of the surface layer is 14CoCrTa-86WC, the mass ratio of Ta to Co and Cr is (0.3-1):1: 1.
2. The composite coating according to claim 1, wherein the thickness of the substrate layer is 100-200 μm;
and/or the thickness of the intermediate layer is 200-300 μm;
and/or the thickness of the surface layer is 100-300 mu m.
3. A method for preparing a composite coating according to claim 1 or 2, characterized in that it comprises the following steps:
providing NiCrAlY spray powder, NiCrAlY/Si spray powder and 25NiCrTa-75Cr3C2Spraying powder or 14CoCrTa-86WC spraying powder;
spraying NiCrAlY spraying powder on the surface of the titanium alloy to serve as a substrate layer;
spraying NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer;
spraying 25NiCrTa-75Cr on the surface of the intermediate layer3C2And spraying powder or 14CoCrTa-86WC spraying powder is used as a surface layer to obtain the composite coating.
4. The method of claim 3, wherein the spraying powder of NiCrAlY, NiCrAlY/Si, and 25NiCrTa-75Cr are mixed3C2Before the spraying powder or the 14CoCrTa-86WC spraying powder is sprayed, the method also comprises the step of independently drying the spraying powder or the 14CoCrTa-86WC spraying powder respectively;
the drying temperature is 60-120 ℃, and the drying time is 0.5-1.5 h.
5. The preparation method of the composite coating according to claim 3 or 4, characterized in that when NiCrAlY spraying powder is sprayed on the surface of the titanium alloy to form a base layer, the spraying distance of a spray gun is 100-130 mm, the scanning speed is 130-180 mm/s, the power is 25-35 kW, the scanning interval is 2-6 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying passes are 1-3 times;
and/or when NiCrAlY/Si spraying powder is sprayed on the surface of the substrate layer to form an intermediate layer, the distance between spray guns is 100-130 mm, the scanning speed is 130-180 mm/s, the power is 25-35 kW, the scanning interval is 2-6 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 2-3 times;
and/or spraying 25NiCrTa-75Cr on the surface of the intermediate layer3C2When the spraying powder or the 14CoCrTa-86WC spraying powder forms a surface layer, the distance of a spray gun is 100-130 mm, the scanning speed is 100-150 mm/s, the power is 30-40 kW, the scanning interval is 4-10 mm, the carrier gas pressure is 0.3-0.5 MPa, and the spraying pass is 1-3 times.
6. A titanium alloy surface treatment method, characterized in that the composite coating of claim 1 or 2 is sprayed on the pretreated titanium alloy surface; or, the surface of the pretreated titanium alloy is treated by the preparation method of the composite coating layer as claimed in any one of claims 3 to 5.
7. The titanium alloy surface treatment method according to claim 6, wherein the pretreatment comprises a step of cleaning and blasting the titanium alloy surface; specifically, cleaning the surface of the titanium alloy by using an organic solvent, and blasting sand after surface drying; the sand blasting adopts carborundum with the grain diameter of 60-100 meshes, and the sand blasting pressure is 0.2-0.3 MPa;
and/or after the composite coating is sprayed on the surface of the titanium alloy, grinding the surface of the composite coating; specifically, grinding the surface of the composite coating by using a diamond grinding head; the grinding rotating speed is 1500-2000r/min, and the grinding amount is 50-100 μm.
8. The titanium alloy surface treatment method according to claim 6 or 7, characterized by comprising the steps of:
carrying out pretreatment of cleaning and sand blasting on the surface of the titanium alloy;
spraying NiCrAlY powder, NiCrAlY/Si powder and 25NiCrTa-75Cr3C2Respectively and independently drying the spray powder or the 14CoCrTa-86WC spray powder at the drying temperature of 60-120 ℃ for 0.5-1.5 h;
spraying dried NiCrAlY spraying powder on the surface of the pretreated titanium alloy to serve as a substrate layer, wherein the thickness of the substrate layer is 100-200 mu m; spraying dried NiCrAlY/Si spraying powder on the surface of the substrate layer to serve as an intermediate layer, wherein the addition amount of Si accounts for 5-10% of the mass fraction of NiCrAlY, and the thickness of the intermediate layer is 200-300 mu m; spraying dried 25NiCrTa-75Cr on the surface of the intermediate layer3C2Taking the spraying powder as a surface layer, wherein the mass ratio of Ta to Ni and Cr is 1:1:1, and the thickness of the surface layer is 300 mu m, or taking the dried 14CoCrTa-86WC spraying powder as a surface layer, wherein the mass ratio of Ta to Co and Cr is 1:1:1, and the thickness of the surface layer is 100-;
and grinding the surface of the composite coating by using a diamond grinding head, wherein the grinding rotating speed is 1500-2000r/min, and the grinding amount is 50-100 mu m.
9. Use of the composite coating according to claim 1 or 2, the method for the preparation of the composite coating according to any one of claims 3 to 5 or the method for the surface treatment of a titanium alloy according to any one of claims 6 to 8 in the surface engineering of titanium alloys.
CN201811341016.3A 2018-11-12 2018-11-12 Composite coating and preparation method thereof, titanium alloy surface treatment method and application Active CN109207900B (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN202010649676.9A CN111826599B (en) 2018-11-12 2018-11-12 High-performance composite coating suitable for titanium alloy and preparation method thereof
CN201811341016.3A CN109207900B (en) 2018-11-12 2018-11-12 Composite coating and preparation method thereof, titanium alloy surface treatment method and application

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201811341016.3A CN109207900B (en) 2018-11-12 2018-11-12 Composite coating and preparation method thereof, titanium alloy surface treatment method and application

Related Child Applications (1)

Application Number Title Priority Date Filing Date
CN202010649676.9A Division CN111826599B (en) 2018-11-12 2018-11-12 High-performance composite coating suitable for titanium alloy and preparation method thereof

Publications (2)

Publication Number Publication Date
CN109207900A CN109207900A (en) 2019-01-15
CN109207900B true CN109207900B (en) 2020-06-16

Family

ID=64996326

Family Applications (2)

Application Number Title Priority Date Filing Date
CN201811341016.3A Active CN109207900B (en) 2018-11-12 2018-11-12 Composite coating and preparation method thereof, titanium alloy surface treatment method and application
CN202010649676.9A Active CN111826599B (en) 2018-11-12 2018-11-12 High-performance composite coating suitable for titanium alloy and preparation method thereof

Family Applications After (1)

Application Number Title Priority Date Filing Date
CN202010649676.9A Active CN111826599B (en) 2018-11-12 2018-11-12 High-performance composite coating suitable for titanium alloy and preparation method thereof

Country Status (1)

Country Link
CN (2) CN109207900B (en)

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4639399A (en) * 1985-11-26 1987-01-27 The United States Of America As Represented By The Secretary Of The Navy Nickel oxide, ceramic insulated, high temperature coating
JPH1088368A (en) * 1996-09-19 1998-04-07 Toshiba Corp Thermal insulation coating member and its production
US6177200B1 (en) * 1996-12-12 2001-01-23 United Technologies Corporation Thermal barrier coating systems and materials
US5891267A (en) * 1997-01-16 1999-04-06 General Electric Company Thermal barrier coating system and method therefor
JP3522588B2 (en) * 1999-05-26 2004-04-26 トーカロ株式会社 Chromium carbide cermet sprayed coating member excellent in high-temperature hardness and method for producing the same
US7842402B2 (en) * 2006-03-31 2010-11-30 General Electric Company Machine components and methods of fabricating
US20100226783A1 (en) * 2009-03-06 2010-09-09 General Electric Company Erosion and Corrosion Resistant Turbine Compressor Airfoil and Method of Making the Same
FI123710B (en) * 2011-03-28 2013-09-30 Teknologian Tutkimuskeskus Vtt Thermally sprayed coating
CN103184399A (en) * 2011-12-31 2013-07-03 江苏太阳宝新能源有限公司 Solar photo-thermal power generation high temperature protective coating and preparation method thereof
CN105441860A (en) * 2015-11-12 2016-03-30 广东电网有限责任公司电力科学研究院 Novel SiC whisker reinforced gas turbine blade composite coating and preparation method thereof
CN105463359B (en) * 2015-12-07 2018-05-29 水利部杭州机械设计研究所 Heat resistant and wear resistant damages nickel chromium triangle-chromium carbide compounded powder of anticorrosive anti-cavitation, coating and preparation method thereof
CN105951030B (en) * 2016-04-28 2018-12-21 中国农业机械化科学研究院 Single crystal alloy surface double-layer structure adhesive layer and preparation method thereof
CN107236331B (en) * 2017-06-16 2019-07-16 国电科学技术研究院武汉电力技术分院 High-temperature corrosion resistance coating and preparation method thereof and high-temperature corrosion resistance coating and preparation method thereof
CN108441804B (en) * 2018-02-06 2020-08-18 广东正德材料表面科技有限公司 High-performance metal ceramic composite coating for lithium electric compression roller and preparation method thereof

Also Published As

Publication number Publication date
CN111826599B (en) 2022-03-15
CN111826599A (en) 2020-10-27
CN109207900A (en) 2019-01-15

Similar Documents

Publication Publication Date Title
US4645716A (en) Flame spray material
CA2444917A1 (en) Cold sprayed copper for rocket engine applications
EP3107673B1 (en) Method of applying a thermal barrier coating
CN105648296B (en) A kind of high temperature resistance tungsten carbide-base metal-ceramic composite powder end, coating and its preparation process containing Re
CN111005018B (en) Preparation method for spraying metal powder to form metal coating on surface of ceramic substrate
CN111848220B (en) MB 2 Ultrahigh-temperature-based ceramic coating and preparation method thereof
CN110976893B (en) Preparation method of composite metal layer on surface of ceramic substrate
EP2113582B1 (en) Process for forming an improved durability thick ceramic coating
CN106011721B (en) A method of laminated coating is prepared using hot spray process
CN113151772A (en) Novel high-temperature corrosion-resistant thermal barrier coating with double ceramic layer structure and preparation method thereof
CN108715987B (en) Method for improving bonding strength of thermal barrier coating
US20090223756A1 (en) Method for producing friction surfaces or friction layers of a carbon-ceramic brake disk as well as a carbon-ceramic brake disk provided with such friction surfaces or friction layers
CN112831747A (en) Thermal protection coating and preparation method thereof
CN103774082A (en) Preparation method of thermal barrier coating
CN111962028A (en) EB-PVD/APS composite structure double-ceramic-layer thermal barrier coating and preparation method thereof
US20080131612A1 (en) Method for making an environment-resistant and thermal barrier coating system on a component
CN109207900B (en) Composite coating and preparation method thereof, titanium alloy surface treatment method and application
Verstak et al. AC-HVAF sprayed tungsten carbide: properties and applications
CN112457061A (en) Environment barrier coating with gradient change of components and preparation method thereof
CN110872713B (en) Y/Y2O3Cold spraying preparation method of metal ceramic protective coating
WO2018047523A1 (en) Coating method, coating film, and turbine shroud
CN110404751B (en) Method for forming anti-ablation coating on surface of resin-based composite material
CN114086102A (en) Ba (Mg)1/3Ta2/3)O3-YSZ double-ceramic-layer thermal barrier coating and preparation method thereof
CN110273122B (en) Preparation method of long-life heat-insulation coating of polyimide composite material outer adjusting sheet
CN112226723A (en) Preparation method of aluminum-containing alloy coating in atmospheric atmosphere

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant