CN115433934A - Alloy powder for laser cladding, coating, preparation method and application thereof - Google Patents
Alloy powder for laser cladding, coating, preparation method and application thereof Download PDFInfo
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Images
Classifications
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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
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/07—Alloys based on nickel or cobalt based on cobalt
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
- C22C30/02—Alloys containing less than 50% by weight of each constituent containing copper
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
- C22C32/0047—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with carbides, nitrides, borides or silicides as the main non-metallic constituents
-
- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention discloses alloy powder for laser cladding, a coating, a preparation method and application thereof. The alloy powder for laser cladding comprises stellite3 and titanium silicon carbide, and a coating prepared by combining the alloy powder for laser cladding with a laser cladding technology has excellent high-temperature wear resistance and oxidation resistance and good hardness, wherein the microhardness of a C1, C2 and C3 composite coating prepared by using the alloy powder for laser cladding is 676.62HV 63 0.5 、528.76HV 0.5 And 490.57HV 0.5 About IN718 alloy base (262.7 HV) 0.5 ) 1.88-2.58 times of the alloy material surface protection agent, and can be widely applied to alloy material surface protection.
Description
Technical Field
The invention relates to the technical field related to composite coatings, in particular to alloy powder for laser cladding, a coating, and a preparation method and application thereof.
Background
The brush type seal turbine rotor shaft is used as a common core component structure of an aircraft engine, and Inconel718 (IN 718) high-temperature alloy is one of common materials for manufacturing moving parts such as the brush type seal turbine rotor shaft and the like, and is IN service for a long time IN severe environments such as high rotating speed, high-temperature gas, strong molten salt corrosion, strong thermal cycle and the like.
In order to meet the harsh wear condition of brush seal and prolong the service life, a multifunctional wear-resistant antifriction and antioxidant composite coating is usually coated on the surface of a brush seal turbine rotor shaft, and in the related technology, the technology commonly used for preparing the composite coating mainly comprises spraying, vapor deposition, plasma cladding, laser cladding and the like, wherein the laser cladding has the advantages of controllable energy supply, wide material selection range, high condensation speed, metallurgical bonding with a matrix, accurate strengthening of the surface of a part and the like. However, the coating prepared by the existing method still has the problems of insufficient heat resistance and wear resistance, poor high-temperature oxidation resistance and the like due to the limit of the performance of the coating material.
The influence of the laser cladding coating on the wear-resisting and friction-reducing performance of the surface of the IN718 alloy is reported IN the related technology, and research shows that the hardness of the NiCo alloy coating prepared on the surface of the IN718 alloy by adopting the pulse laser cladding technology can reach 427.82HV 0.1 21.1% higher than IN718 base, improved wear resistance, 15.5% lower friction factor and 27.5% lower abrasion loss (1.176 mm base abrasion loss) 3 ). However, the high-temperature wear-resistant antifriction and oxidation-resistant performances of the composite material are still insufficient.
Therefore, an alloy powder for laser cladding, which can improve the high-temperature wear-resistant antifriction performance and oxidation resistance of the base material, and an alloy coating prepared from the alloy powder are still needed.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides the alloy powder for laser cladding, and the alloy powder can effectively improve the high-temperature wear resistance and oxidation resistance of the alloy coating when being applied to the alloy coating.
The invention also provides an alloy coating.
The invention also provides a preparation method of the alloy coating.
The invention also provides application of the alloy powder for laser cladding in surface modification of nickel-based alloy.
An alloy powder for laser cladding according to an embodiment of the first aspect of the present invention includes stellite3 and silicon titanocarbide.
In some embodiments of the invention, at least the following benefits are achieved: according to the invention, stellite3 (Stellite 3) is self-fluxing Co-based powder, has excellent deoxidation and slagging capacity and good thermal stability and high-temperature oxidation resistance, and has high carbon content (2.4 wt.%) based on Stellite3 alloy, so that the volume fraction of carbide of the Stellite3 alloy is high (about 30%), and the Stellite3 alloy is used as a toughening phase in a coating system, has the characteristics of large amorphous forming capacity, high hardness, good wear resistance and good corrosion resistance, and the like.
Titanium silicon carbide (Ti) 3 SiC 2 ) The ceramic is a typical ternary laminated MAX phase ceramic, and has the excellent characteristics of electrical conductivity, thermal conductivity and high toughness of metal, high thermal stability, high melting point, high yield strength and the like of the ceramic. The titanium silicon carbide is easy to slide between layers at high temperature so as to generate lubricating performance, and an oxidation film can be formed at high temperature to play a role in lubrication and protection.
According to some embodiments of the invention, the alloy powder for laser cladding comprises 80-95% of the stellite3 and 5-10% of silicon titanium carbide in terms of mass fraction.
According to some embodiments of the present invention, the alloy powder for laser cladding comprises, by mass fraction, 85% to 95% of the stellite3 and 5% to 10% of silicon titanium carbide.
The stellite3 is a Co-based powder, and since the wettability of silicon titanocarbide with the Co-based powder is poor, the addition of excessive silicon titanocarbide tends to cause the surface quality of the coating to be deteriorated.
According to some embodiments of the invention, the particle size of the sertraline 3 is from 40 μm to 60 μm.
According to some embodiments of the invention, the particle size of the sertraline 3 is 50 μm.
According to some embodiments of the invention, the setolit 3 comprises the following chemical elements, in weight percent: 2% to 3%C, 30% to 32% Cr, 0.5% to 1.5% Si, 12% to 13% W, 2% to 4% Fe, 2% to 4% Ni, 0.5% to 1.5% Mn and the balance Co.
According to some embodiments of the invention, the setolit 3 comprises the following chemical elements, in weight percent: 2.4% Cr, 31% Si, 12.5% W, 3% Fe, 3% Ni, 1% Mn and the balance Co.
According to some embodiments of the invention, the iron silicon carbide has a particle size of 50 μm to 80 μm.
According to some embodiments of the invention, the iron silicon carbide has a particle size of 65 μm.
According to some embodiments of the invention, the alloy powder for laser cladding further comprises copper powder.
The addition of copper powder into the alloy powder for laser cladding in the invention has the following advantages:
(1) The copper powder has a lower melting point and a higher heat conductivity coefficient, so that the penetration and metallurgical bonding capacity of the coating can be effectively improved in the cladding process, and the copper is used as a soft metal, so that the plastic deformation resistance of the coating material can be effectively improved.
(2) Copper reacts with oxygen at high temperature to form an oxide film, and the viscosity of the oxide film changes to a certain extent, so that the oxide film bears partial lubrication effect in the abrasion process, and the abrasion resistance is improved.
(3) Copper has better thermal conductivity and can accelerate the heat dissipation rate of the coating.
According to some embodiments of the invention, the mass fraction of the copper powder in the alloy powder for laser cladding is 8% to 12%.
Preferably, the mass fraction of the copper powder in the alloy powder for laser cladding is 10%.
The wear resistance of the coating is improved by adjusting the content of the copper powder, and the hardness of the coating is further reduced by excessively adjusting the content of the copper powder, so that the overall performance of the coating is influenced; and too low a copper powder content may result in insufficient lubrication of the soft metal copper.
According to some embodiments of the invention, the copper powder has a particle size of 20 μm to 50 μm.
According to some embodiments of the invention, the copper powder has a particle size of 35 μm.
According to some embodiments of the present invention, the alloy powder for laser cladding is suitable for surface modification of a nickel-based alloy.
The invention provides an alloy coating, which comprises the alloy powder for laser cladding.
The third aspect of the invention provides a preparation method of an alloy coating, which comprises the steps of mixing the alloy powder for laser cladding and then preparing the alloy coating by adopting a laser cladding process.
In some embodiments of the invention, at least the following benefits are achieved: the composite coating prepared on the surface of the IN718 high-temperature alloy by adopting a laser cladding technology and taking the stellite3, the titanium silicon carbide and the Cu powder as raw materials has excellent wear resistance and oxidation resistance. The method is simple and convenient to operate, has the advantages of controllable energy supply, wide material selection range, high condensation speed, metallurgical bonding with the matrix, accurate strengthening of the surfaces of the parts and the like, and can ensure the original use function of the base material and economically and efficiently prolong the use time of the base material. In addition, the high-temperature alloy composite coating prepared by the method has the advantages of good adhesiveness and difficult cracking and deformation.
According to some embodiments of the invention, the power of the laser cladding process is 0.7kW to 0.9kW.
According to some embodiments of the invention, the power of the laser cladding process is 0.8kW.
According to some embodiments of the invention, the laser beam output spot of the laser cladding process is
According to some embodiments of the invention, the scanning speed of the laser cladding process is between 4mm/s and 6mm/s.
According to some embodiments of the invention, the scanning speed of the laser cladding process is 5mm/s.
According to some embodiments of the invention, the powder feeding rate of the laser cladding process is 12g/min to 15g/min.
According to some embodiments of the invention, the powder feeding rate of the laser cladding process is 13.5g/min.
According to some embodiments of the invention, the number of laser irradiation cladding treatments of the laser cladding process is 8-12.
According to some embodiments of the invention, the laser irradiation cladding process comprises 10 laser irradiation cladding treatments.
According to some embodiments of the invention, the laser cladding process has an overlap ratio of 40% to 60%.
According to some embodiments of the invention, the laser cladding process has a lap joint ratio of 50%.
The fourth aspect of the invention provides application of the alloy powder for laser cladding in surface modification of nickel-based alloy.
In some embodiments of the invention, at least the following benefits are achieved: the coating prepared on the surface of the nickel alloy by adopting the alloy powder for laser cladding has excellent high-temperature wear resistance and oxidation resistance.
According to some embodiments of the invention, the nickel-based alloy is an IN718 alloy.
According to some embodiments of the invention, the nickel-based alloy surface modification comprises mixing the alloy powder, conveying the powder by using laser in a synchronous powder feeding method, and performing laser irradiation cladding treatment on the powder.
According to some embodiments of the invention, the laser has a power of 0.7kW to 0.9kW.
According to some embodiments of the invention, the laser has a power of 0.8kW.
According to some embodiments of the invention, the laser beam output spot of the laser is
According to some embodiments of the invention, the laser has a scanning speed of 4mm/s to 6mm/s.
According to some embodiments of the invention, the laser has a scanning speed of 5mm/s.
According to some embodiments of the invention, the powder feeding rate of the synchronous powder feeding method is 12g/min to 15g/min.
According to some embodiments of the invention, the powder feeding rate of the synchronous powder feeding method is 13.5g/min.
According to some embodiments of the invention, the number of laser irradiation cladding treatments is 8-12.
According to some embodiments of the invention, the number of laser irradiation cladding processes is 10.
According to some embodiments of the invention, the laser irradiation cladding treatment has an overlap ratio of 40% to 60%.
According to some embodiments of the invention, the laser irradiation cladding process has an overlap ratio of 50%.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
FIG. 1 is a cross-sectional profile of a composite coating in accordance with an embodiment of the present invention.
Fig. 2 is an XRD pattern of the composite coating of the example of the invention.
FIG. 3 is a microhardness curve of a composite coating according to an embodiment of the present invention.
FIG. 4 is a graph of the friction factor of the substrate and the composite coating at room temperature in accordance with the embodiments of the present invention.
FIG. 5 is a graph of the friction factor of a substrate and a composite coating at 600 ℃ in accordance with an embodiment of the present invention.
FIG. 6 is a graph showing the wear rate of the substrate and coating at different temperatures for examples of the present invention.
FIG. 7 is a graphical representation of the wear surface and swarf topography of a substrate and coating according to an embodiment of the present invention at room temperature.
FIG. 8 is a graphical representation of the wear surface and swarf profile of a substrate and coating at 600 deg.C in accordance with an embodiment of the present invention.
FIG. 9 is an XRD pattern of the oxidized surfaces of the substrate and coating in an example of the invention.
FIG. 10 is a graph of the oxidation kinetics of oxidized surfaces of substrates and coatings in accordance with an example of the invention.
FIG. 11 is a graph of the surface oxidation profiles of the substrate and the composite coating in an embodiment of the invention.
Detailed Description
The idea of the invention and the resulting technical effects will be clearly and completely described below in connection with the embodiments, so that the objects, features and effects of the invention can be fully understood. It is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and those skilled in the art can obtain other embodiments without inventive effort based on the embodiments of the present invention, and all embodiments are within the protection scope of the present invention.
In the description of the present invention, reference to the description of the terms "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The examples, in which specific conditions are not specified, were carried out according to 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.
IN the embodiment mode of the invention, the nickel-based alloy is an IN718 alloy, which is purchased from Shenzhen Shensheng Yi Sheng metal materials GmbH.
In the example embodiment of the present invention, the main chemical components of the Stellite3 alloy powder (Stellite 3 powder) are shown in table 1.
TABLE 1 Stellite3 Main chemistry (wt.%)
In an embodiment of the invention, the average particle size of the preparation starting material sertoli 3 (Stellite 3) is 50 μm.
Silicon titanium carbide (Ti) 3 SiC 2 ) Has an average particle size of 65 μm.
The average particle size of the copper powder (Cu) was 35 μm.
In an embodiment mode of the invention, the Room Temperature (RT) is 25 ℃. + -. 5 ℃.
Specific examples of the present invention are described in detail below.
Example 1
An alloy powder for laser cladding, which consists of stellite3 alloy powder and titanium silicon carbide.
According to the mass fraction, the stellite3 alloy powder accounts for 95 percent, and the silicon titanium carbide accounts for 5 percent.
A composite coating (marked as C1) prepared from the alloy powder for laser cladding comprises the following steps:
step S1: firstly, weighing the Stellite3 alloy powder and the silicon titanium carbide in the mass ratio by using an electronic balance, placing the mixed powder into a ball mill (DECO Deke, model DECO-PBM-V-0.4L) for ball milling for 2h, adjusting the rotating speed to 600r/min, and then drying the uniformly mixed powder for 4h at constant temperature for later use.
Step S2: the IN718 alloy matrix was ground using 200, 400 and 800 mesh sandpaper, respectively, to remove surface impurities.
And step S3: the composite coating is cladded by adopting an optical fiber laser (IPG, the model is YLS-3000) in a synchronous powder feeding mode, wherein the output power is 800W, and the output spot of a laser beam is
The scanning speed is 5mm/s, the defocusing amount is-20 mm, and the powder feeding speed is 13.5g/min.
And step S4: and performing 10-pass continuous laser scanning, wherein the lap joint rate in the laser cladding process is 50%.
Example 2
An alloy powder for laser cladding, which consists of stellite3 alloy powder and titanium silicon carbide.
According to the mass fraction, the stellite3 alloy powder accounts for 90%, and the silicon titanium carbide accounts for 10%.
A composite coating (marked as C2) prepared from the alloy powder for laser cladding comprises the following steps:
step S1: firstly, weighing the Stellite3 alloy powder and the silicon titanium carbide in the mass ratio by using an electronic balance, placing the mixed powder into a ball mill (DECO Deke, model DECO-PBM-V-0.4L) for ball milling for 2h, adjusting the rotating speed to 600r/min, and then drying the uniformly mixed powder for 4h at constant temperature for later use.
Step S2: the IN718 alloy matrix was ground using 200, 400 and 800 mesh sandpaper, respectively, to remove surface impurities.
And step S3: adopts an optical fiber laser (IPG, the model is YLS-3000) to clad the composite coating in a synchronous powder feeding mode, wherein the output power is 800W, and the output light spot of a laser beam is
The scanning speed is 5mm/s, the defocusing amount is-20 mm, and the powder feeding rate isIt was 13.5g/min.
And step S4: and performing 10-pass continuous laser scanning, wherein the lap joint rate in the laser cladding process is 50%.
Example 3
An alloy powder for laser cladding, which consists of stellite3 alloy powder, titanium silicon carbide and copper powder.
According to the mass fraction, the stellite3 alloy powder accounts for 85%, the silicon titanium carbide accounts for 5%, and the copper powder accounts for 10%.
A composite coating (marked as C3) prepared from the alloy powder for laser cladding comprises the following steps:
step S1: firstly, weighing the Stellite3 alloy powder and the silicon titanium carbide in the mass ratio by using an electronic balance, placing the mixed powder into a ball mill (DECO Deke, model DECO-PBM-V-0.4L) for ball milling for 2h, adjusting the rotating speed to 600r/min, and then drying the uniformly mixed powder for 4h at constant temperature for later use.
Step S2: the IN718 alloy matrix was ground using 200, 400 and 800 mesh sandpaper, respectively, to remove surface impurities.
And step S3: the composite coating is cladded by adopting an optical fiber laser (IPG, the model is YLS-3000) in a synchronous powder feeding mode, wherein the output power is 800W, and the output spot of a laser beam is
The scanning speed is 5mm/s, the defocusing amount is-20 mm, and the powder feeding speed is 13.5g/min.
And step S4: and performing 10 times of continuous laser scanning, wherein the lapping rate in the laser cladding process is 50 percent.
Comparative example 1
The comparative example is different in the power of the laser from example 3, and the power of the laser is 400W in the comparative example.
Comparative example 2
The comparative example is different in the power of the laser from example 3, and the power of the laser is 600W in the comparative example.
Comparative example 3
The comparative example is different in the power of the laser from example 3, and the power of the laser is 1000W in the comparative example.
Comparative example 4
The comparative example is different in the power of the laser from example 3, and the power of the laser is 1200W in the comparative example.
Detection example 1: appearance inspection of coatings
In the detection example, the appearances of the coatings in the example 3 and the comparative examples 1 to 4 are respectively detected, and the specific detection method refers to GB/T36591-2018, and the detection result shows that the coating prepared by the example 3 has better adhesive force compared with the coatings prepared by the comparative examples 1 to 4, and the fusion surface is not easy to have defects such as balling, holes and the like.
Compared with example 3, the composite coatings prepared by using comparative examples 1 and 2 are more prone to peeling, pilling, and voids, which are mainly related to the low laser power.
The composite coatings prepared using comparative examples 3 and 4 are more susceptible to deformation and cracking than example 3, which is mainly associated with excessive laser power.
Therefore, by adopting the preparation method of the alloy composite coating in the embodiment 3 of the invention, namely, the power of the laser is adjusted to 800W in the laser cladding process, which is beneficial to forming the composite coating with excellent surface quality, and when the power of the laser is too low, as shown in comparative examples 1 and 2, the coating is peeled off in different degrees, and the cladding surface has the phenomena of balling and voiding; when the power of the laser is too high, the coatings prepared therefrom are prone to deformation and cracking, as shown in comparative examples 3 and 4.
Detection example 2: micro-topography characterization of composite coatings
In this test example, the alloy composite coatings prepared in examples 1 to 3 were subjected to microscopic morphology characterization and physical phase analysis, respectively.
1. Cross-sectional topography Observation of coatings
The cross-sectional morphologies of the alloy composite coatings prepared in examples 1 to 3 were observed by an electron microscope, and the results are shown in fig. 1, in which (a) in fig. 1 is a cross-sectional morphology of the alloy composite coating prepared in example 1; FIG. 1 (b) is a cross-sectional profile of the alloy composite coating prepared in example 2; FIG. 1 (c) is a cross-sectional profile of the alloy composite coating prepared in example 3.
From fig. 1 (a), it can be seen that the weld lines between the alloy composite coating (coating layer) and the IN718 alloy Substrate layer (Substrate) are wavy lines, which indicates that the coating prepared by the present invention is heated uniformly, and the coating and the IN718 alloy Substrate form good metallurgical bonding.
Secondly, the coating in fig. 1 (a) and fig. 1 (b) has no obvious defects such as macrocracks and holes inside, while the coating in fig. 1 (c) has a small amount of air holes, because the heat conductivity of Cu is good, the heat dissipation rate of the coating is accelerated, so that the gas in the coating cannot escape in time, and thus, the micro-holes are formed.
2. XRD pattern analysis of composite coatings
The alloy composite coatings obtained in examples 1 to 3 were subjected to X-ray diffraction, respectively, to obtain XRD patterns as shown in fig. 2. In FIG. 2, C1 represents the content of the alloy composite coating (Stellite 3-5% Ti) obtained in example 1 3 SiC 2 ) (ii) a C2 is the alloy composite coating obtained in example 2 (Stellite 3-10% 3 SiC 2 ) (ii) a C3 is the alloy composite coating obtained in example 3 (Stellite 3-5% 3 SiC 2 -10％Cu)。
From FIG. 2, it can be seen that the main phases of the C1 and C2 composite coatings are solid solutions of gamma-Co, (Fe, ni), and hard phase carbide WC x 、Cr 7 C 3 TiC, ceramic phase Ti 3 SiC 2 And intermetallic compound Cr 2 Ni 3 (ii) a In addition, a diffraction peak of Cu was additionally detected in the C3 composite coating layer. Therefore, the target alloy composite coating can be obtained by adopting the preparation method of the invention.
Detection example 3: microhardness test
The hardness of the alloy composite coatings prepared in examples 1 to 3 was respectively characterized in this test example.
The specific detection method comprises the following steps: the test starts from the top of the cladding layer, and dots are punched every 100 μm in the longitudinal direction (i.e., depth direction) of the coating layer until reaching the substrate, and 5 dots are punched again to calculate the substrate hardness. The transverse direction is measured for three times at intervals of 100 mu m, and then the average value is taken to obtain the longitudinal microhardness value.
The results of the micro-hardness profile of the coating obtained are shown in FIG. 3, where C1 in FIG. 3 is the alloy composite coating obtained in example 1 (Stellite 3-5% Ti) 3 SiC 2 ) (ii) a C2 is the alloy composite coating obtained in example 2 (Stellite 3-10%) 3 SiC 2 ) (ii) a C3 is the alloy composite coating obtained in example 3 (Stellite 3-5% 3 SiC 2 -10% cu); substrate is an IN718 alloy Substrate.
By calculating the average values for each point in the coating area in FIG. 3, the microhardness of the C1, C2 and C3 composite coatings was 676.62HV 0.5 、528.76HV 0.5 And 490.57HV 0.5 About IN718 alloy base (262.7 HV) 0.5 ) 1.88 to 2.58 times of the alloy powder for laser cladding, and the alloy coating prepared by the alloy powder for laser cladding can effectively improve the hardness of a matrix.
The hardness of the coating of the invention is improved to different degrees, which can be attributed to the following three aspects: one is the hard phase WC in the coating due to strong convection in the bath x 、Cr 7 C 3 And TiC and intermetallic compound Cr 2 Ni 3 Uniformly distributed in the cladding layer to generate dispersion strengthening; secondly, the condensation speed of the molten pool is high, metal elements such as Co, fe, ni and the like cannot react in time, and are dissolved into a continuous matrix to form solid solution strengthening, and meanwhile, the large supercooling degree inhibits the growth of crystal grains to generate fine crystal strengthening; thirdly, an added solid lubricant Ti 3 SiC 2 And Cu improves the properties of the coating.
Detection example 4: wear rate of composite coating
In order to test the tribological properties of the alloy composite coatings prepared in examples 1 to 3, the tribological properties of the alloy composite coatings prepared in the present invention were tested using a ball-and-disc type high temperature friction and wear tester (HT-1000, kaikaya Hua technology development Co., ltd., lanzhou), the test parameters of which are shown in Table 2.
TABLE 2 parameters of frictional wear
| Load carrier | Temperature of | Experiment time | Rotating radius | Linear velocity |
| 5N | RT，600℃ | 30min | 3mm | 10.17m/min |
Specific friction factor data are shown in table 3.
TABLE 3 average friction factor of substrate and composite coating
| IN718 | Example 1 (C1) | Example 2 (C2) | Example 3 (C3) | |
| RT | 0.687 | 0.546 | 0.672 | 0.718 |
| 600℃ | 0.671 | 0.656 | 0.678 | 0.580 |
The friction factor curves of the alloy composite coatings prepared in examples 1 to 3 at different temperatures are shown in fig. 4 and 5, wherein fig. 4 is the friction factor curve obtained at room temperature, and fig. 5 is the friction factor curve obtained at 600 ℃.
From the data obtained above, it can be seen that: the friction coefficient curve of the coating of the composite coating prepared by the alloy powder is more stable than that of the matrix, and the mechanical abrasion damage of the matrix can be effectively reduced. Next, stellite3 and Ti were added at room temperature 3 SiC 2 The C1 and C2 composite coating of the alloy powder can effectively improve the antifriction performance of the IN718 alloy matrix; while at high temperature, stellite3-Ti is added 3 SiC 2 C3 composite coating of-Cu powder versus addition of Ti alone 3 SiC 2 And the friction reducing performance of the C1 and C2 composite coating of Stellite3 is more excellent.
Further, the wear surface profile and the wear volume were measured by an M-500 probe wear scar measuring instrument, and the wear rate value calculated by the formula is shown in table 4. Wherein, the concrete formula is:
wherein W is the wear rate (mm) 3 N m), F is the load (N), d is the sliding distance (m), and V is the wear volume (mm) 3 )。
TABLE 4 abrasion ratio of matrix to composite coating (unit: mm) 3 /N·m)
| IN718 | Example 1 (C1) | Example 2 (C2) | Example 3 (C3) | |
| RT | 38.4×10 -5 | 5.51×10 -5 | 6.24×10 -5 | 1.37×10 -5 |
| 600℃ | 29.8×10 -5 | 6.75×10 -5 | 6.09×10 -5 | 9.93×10 -5 |
As can be seen from Table 4, the composites made using the alloy powder for laser cladding of the present inventionThe coating can reduce the wear rate of the substrate. The specific comparison graph of the abrasion rates of the substrate and the three coatings at room temperature and 600 ℃ is shown in FIG. 6, and according to the data analysis, the abrasion resistance of the three composite coatings is obviously improved at room temperature, but along with Ti 3 SiC 2 The content is increased, the hardness of the coating is reduced due to the reduction of the carbide content of the composite coating, and the wear resistance of the coating is gradually reduced along with the reduction of the hardness of the coating. After the Cu element is added, the wear-resistant composite coating can be quickly adapted to the wear surface of a grinding ball to avoid more mechanical damage due to good ductility, and hard phases such as TiC and the like are dispersed on the surface layer of the coating due to low density, play a supporting role on Cu in the coating, resist the embedding of the grinding ball and reduce wear together, so that the wear rate of the C3 composite coating is reduced. At high temperature (600 ℃), as Cu becomes softer with the increase of temperature and is easy to be extruded, the overall continuity of the coating is reduced, so that the wear rate of the coating is improved relative to that of C1 and C2 composite coatings, but the overall wear rate of the three composite coatings is lower than that of a matrix layer.
Detection example 5: characterization of coating abrasion and abrasive dust morphology
IN order to observe the excellent wear resistance of the alloy composite coating provided by the invention more intuitively, the detection example respectively performs wear and abrasion appearance characterization on the IN718 alloy matrix and the alloy composite coatings prepared IN the examples 1 to 3 under different temperature conditions.
1. Wear of alloy composite coating at room temperature and appearance characterization of abrasive dust
The wear and abrasion appearance of the IN718 alloy substrate and the alloy composite coatings prepared IN examples 1-3 were respectively characterized at room temperature.
The specific method comprises the following steps: after the sliding friction test, the abrasive dust of the composite coating and the matrix is collected by using a conductive adhesive tape, and the specific shapes of the abrasion surface and the abrasive dust are represented by using a scanning electron microscope (SEM, TESCAN MIRA 4) and an energy spectrum analyzer (EDS, xplore 30.Aztec one) carried by the scanning electron microscope in time.
The wear and swarf topography results at room temperature are shown IN fig. 7, wherein (a 1) - (a 3) IN fig. 7 are wear and swarf topography maps of the IN718 alloy matrix;
in FIG. 7, (b 1) to (b 3) are graphs of the wear and abrasion debris morphology of the alloy composite coating (C1) prepared in example 1;
FIGS. 7 (C1) to (C3) are graphs of the wear and abrasion debris profiles of the alloy composite coating (C2) obtained in example 2;
in fig. 7, (d 1) to (d 3) are the wear and abrasion wear profile maps of the alloy composite coating (C3) obtained in example 3.
As can be seen IN fig. 7, the wear surface of the IN718 alloy substrate exhibited severe gouging, severe plastic deformation, and partial pitting, and the swarf was IN the form of chips. Because the hardness of the matrix is low, the friction surface and the instantaneous high temperature generated on the grinding ball cause the surface to be peeled off under the continuous action of the friction pressure to form pitting pits, and the peeled-off abrasive dust exists between the grinding ball and the abrasion surface to form three-body abrasive wear together.
Compared with an IN718 alloy matrix, the micro-cutting and plastic deformation of the surfaces of the three composite coatings prepared IN examples 1-3 can be improved to different degrees, because the coatings have higher microhardness, and the damage to the surfaces of materials IN the friction process can be reduced. Wherein, stellite3 alloy powder and solid lubricant Ti are added into the C1 and C2 composite coating 3 SiC 2 Solid solutions, carbides and intermetallic compounds with high hardness are generated, and abrasive wear can be resisted to a certain degree.
The treated surface of the C1 composite coating has partial layering and peeling phenomena, but the wear condition of the surface of the C1 composite coating is better compared with that of an IN718 alloy matrix, and the main reason of the phenomenon of the surface of the C1 composite coating is that a large amount of heat is accumulated on the surface of the coating IN the friction process, and the friction heating promotes active metal atoms IN the wear surface and oxygen IN the surrounding environment to continuously generate an oxide film, but the oxide film is thin and not dense, the interface bonding strength between a newly generated oxide film and the coating is low, and the friction surface has microcracks along with the prolonging of the wear time and gradually expands along the friction direction to finally cause the peeling of the oxide film.
Fracture and fine abrasive dust can be observed on the surface of the treated C2 composite coating, which is mainly caused by the fact that the toughness of the C2 composite coating is reduced, the hard composite coating is easy to peel off to generate abrasive grains and peeling pits, and the surface is extruded and scraped under friction pressure to generate furrows and delamination, but the abrasion condition of the whole body is improved compared with that of an IN718 alloy matrix. The C3 composite coating has few chipping particles on the surface because the soft metal Cu has good ductility, the toughness of the coating surface is improved, and the hard phase dispersed on the coating surface plays a supporting role relative to the Cu, resists the embedding of a grinding ball and reduces the abrasion.
2. Abrasion of alloy composite coating at 600 ℃ and appearance characterization of abrasive dust
The wear and abrasion appearance of the IN718 alloy matrix and the alloy composite coatings prepared IN examples 1-3 were respectively characterized at 600 ℃.
The specific treatment method comprises the following steps: after the sliding friction test, after the temperature is cooled to the room temperature, the conductive adhesive tape is used for collecting abrasive dust of the composite coating and the matrix, and a scanning electron microscope (SEM, TESCAN MIRA 4) and an energy spectrum analyzer (EDS, xplore 30.Aztec one) thereof are used for representing the specific shapes of the abrasion surface and the abrasive dust in time.
The wear and abrasive dust topography result at 600 ℃ is shown IN FIG. 8, wherein (a 1) to (a 3) IN FIG. 8 are wear and abrasive dust topography maps of the IN718 alloy matrix;
in FIG. 8, (b 1) to (b 3) are graphs of the wear and abrasion debris morphology of the alloy composite coating (C1) prepared in example 1;
in fig. 8, (C1) to (C3) are graphs of the wear and abrasion debris morphology of the alloy composite coating (C2) prepared in example 2;
in fig. 8, (d 1) to (d 3) are graphs of the wear and abrasion wear patterns of the alloy composite coating (C3) prepared in example 3.
As can be seen from fig. 8, at 600 ℃, a large amount of abrasive dust was present on the surface of the IN718 alloy substrate, and the low hardness substrate did not provide a reliable attachment point for the hard phase. As the grinding balls continue to grind, the wear surface develops furrow cracks and spalling pits. In the C1 and C2 composite coating, because the solid lubricant Ti is added into the composite coating 3 SiC 2 At high temperature Ti 3 SiC 2 The mechanical property of the material still has anisotropy, the normal bearing force is far better than the tangential direction, so the shearing resistance is poor, the lattice slippage is easy to occur in the abrasion process,plays a role of lubrication, and reduces the wear rate of the coating.
In addition, the C1 composite coating has less surface abrasive dust and shallow furrow traces. The C2 composite coating has a layer of oxide along the abrasion track, the oxide continuously exists on the surface of the coating, the effects of fixing and supporting are achieved, direct contact between the grinding ball and the interior is isolated, and material loss is reduced. The surface of the C3 composite coating has adhesion traces and plastic flow, and the abrasive dust is powdery and small blocks. Meanwhile, the soft metal Cu has high ductility at high temperature, and can play a certain role in lubrication, so that the wear rate of the coating is reduced.
Detection example 6: test for Oxidation resistance
The oxidation resistance of the IN718 alloy substrate and the alloy composite coatings prepared IN examples 1-3 was tested IN this test example using a Korotkoff single temperature zone tube furnace (OTF-1200X), wherein the test temperature was 800 ℃.
The specific test method comprises the following steps: the test procedure was carried out strictly according to the oxidation weight gain method of the standard "test methods for measuring oxidation resistance of steel and high temperature alloys". And placing the prepared test block in a quartz boat, then placing the quartz boat in a Kouchi single-temperature-zone tube furnace, setting the temperature at 800 ℃, and carrying out a high-temperature oxidation experiment on the sample for 50 hours, wherein the heating rate is 10 ℃/min. And respectively recording the weight increment of the substrate and the composite coating at 1h, 4h, 7h, 10h, 20h, 30h, 40h and 50h in the constant-temperature oxidation process by using an electronic balance instrument with the accuracy of 0.0001. After the oxidation test was completed, the oxidation products of the substrate and the C2 composite coating having the best oxidation resistance were examined using an X-ray diffractometer (XRD, smartlab SE, japan), and the surface oxidation micro-morphology and the element distribution were analyzed using a scanning electron microscope (SEM, TESCAN MIRA 4) and an energy spectrum analyzer (EDS, xpore 30.Aztec one).
The results are shown IN FIG. 9, where FIG. 9 is the XRD pattern of the oxidized surface of the IN718 alloy substrate and the coating prepared IN example 2, from which it can be seen that the surface of the coating is mainly formed of TiO 2 、SiO 2 、Cr 2 O 3 、NiCr 2 O 4 And FeCr 2 O 4 。
The quality of the matrix, the C1 and the C2 composite coatings before and after the treatment is carried outThe detection results are shown in FIG. 10, and the results show that the weight of the matrix, the C1 composite coating and the C2 composite coating are increased by 26.56mg/cm within 50h of high-temperature oxidation time 2 And 22.03mg/cm 2 、14.14mg/cm 2 。
Further, the oxidation rate constant K is calculated by the formula p And the square of the correlation coefficient, the calculation formula is Deltam 2 ＝K p t, wherein Δ m is weight gain unit area (mg/cm) 2 ) And t is oxidation time (h). The oxidation rates and correlation coefficients for specific substrates and coatings are shown in Table 5, where the correlation coefficient R is 2 The closer to 1, the better the fitting accuracy of the experimental data to the fitted curve.
TABLE 5 Oxidation rates and correlation coefficients for substrates and coatings
| Material | K p (mg 2 ·cm -4 ·h -1 ) | R 2 | Time range H(h) |
| IN718 | 9.5483 | 0.97864 | 20-50 |
| C1 | 8.396 | 0.98287 | 20-50 |
| C2 | 2.7065 | 0.97793 | 20-50 |
By plotting the oxidation kinetics and combining with fig. 10, it can be seen that the high temperature oxidation process of the substrate and coating is roughly divided into two stages: a rapid oxidation and a relatively stable oxidation stage. In the early stage of oxidation (within the first 10 h), the substrate and the coating surface are in contact with oxygen at zero intervals, and oxide is rapidly generated, so that the curve grows faster. After 20h, the substrate and the coating enter a relatively stable oxidation stage, the reaction of oxygen and the interior is slowed down by the oxidation film, and the oxidation rate is obviously reduced.
Further, the surface oxidation topography of the substrate and the composite coating is observed, and the result is shown in fig. 11, wherein (a) in fig. 11 is a surface oxidation topography map of the substrate; FIG. 11 (b) is an oxidation profile of the surface of the composite coating (C1) prepared in example 1; fig. 11 (C) is an oxidation profile of the surface of the composite coating (C2) prepared in example 2.
From the XRD results, it is presumed that the external oxide film is mainly composed of Cr 2 O 3 Composition of and Cr 2 O 3 Has a considerable growth stress (PBR 2.07) which may promote peeling of the oxide film. As the oxidation time increases, nickel and iron diffuse to form spinel NiCr 2 O 4 And FeCr 2 O 4 The formation of spinel may prevent further diffusion of oxygen into the interior and thus act as a protective coating. SiO generation on the coating surface 2 And TiO 2 Mixed oxide of (2), wherein, siO 2 Can compensate for porous TiO 2 The porous defect of (2) prevents oxygen from diffusing to the interior, and the oxidation resistance of the C1 and C2 composite coating is obviously improved.
In conclusion, the coating prepared by the alloy powder has excellent wear resistance and oxidation resistance, wherein the Stellite3 alloy powder has excellent deoxidation and slagging capacity, good thermal stability and high-temperature oxidation resistance as self-fluxing Co-based powder.
Secondly, the invention adopts the laser cladding technology, and adopts the Stellite3 alloy and Ti 3 SiC 2 The ceramic is used as a raw material, the wear-resistant and oxidation-resistant composite coating is prepared on the surface of the IN718 high-temperature alloy, the phase, the microstructure, the tribological performance and the wear mechanism of the coating at room temperature and 600 ℃ and the oxidation resistance at 800 ℃ are systematically researched, and the coating material and the preparation process reference are provided for the long-term application of the IN718 high-temperature alloy as a key moving part under the severe working condition.
While the embodiments of the present invention have been described in detail with reference to the specific embodiments, the present invention is not limited to the embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art. Furthermore, the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict.
Claims (10)
1. An alloy powder for laser cladding, which is characterized in that: including sertraline 3 and silicon titanocarbide.
2. The alloy powder for laser cladding as set forth in claim 1, wherein: according to the mass fraction, the paste comprises 80-95% of the sertraline 3 and 5-10% of silicon titanium carbide.
3. The alloy powder for laser cladding as claimed in claim 1, wherein: the particle size of the sertraline 3 is 40-60 mu m.
4. The alloy powder for laser cladding as set forth in claim 1, wherein: the grain diameter of the titanium silicon carbide is 50-80 μm.
5. An alloy powder for laser cladding as set forth in any one of claims 1 to 4, wherein: the alloy powder for laser cladding also comprises copper powder.
6. The alloy powder for laser cladding as set forth in claim 5, wherein: the mass fraction of the copper powder is 8-12%.
7. An alloy coating characterized by: the alloy powder for laser cladding, which comprises the alloy powder for laser cladding as defined in any one of claims 1 to 6.
8. A method of preparing the alloy coating of claim 7, wherein: the alloy powder for laser cladding is mixed and then prepared by adopting a laser cladding process;
preferably, the power of the laser cladding process is 0.7 kW-0.9 kW;
preferably, the output light spot of the laser beam of the laser cladding process is
Preferably, the scanning speed of the laser cladding process is 4-6 mm/s;
preferably, the powder feeding speed of the laser cladding process is 12 g/min-15 g/min.
9. The method of claim 8, wherein: the laser irradiation cladding treatment times of the laser cladding process are 8-12 times;
preferably, the lapping rate of the laser cladding process is 40-60%.
10. Use of the alloy powder for laser cladding as defined in any one of claims 1 to 6 for surface modification of nickel-base alloys.
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| CH335198A (en) * | 1952-09-30 | 1958-12-31 | Sintercast Corp America | Process for the production of a tool used for deforming metals and a tool produced according to this process |
| US4957561A (en) * | 1986-01-25 | 1990-09-18 | Nippon Hybrid Technologies Co., Ltd. | Composition for metallizing a surface of ceramics, a method for metallizing, and metallized ceramics |
| CN1070431A (en) * | 1991-08-27 | 1993-03-31 | 福田金属箔粉工业株式会社 | Make case-hardened croloy |
| CN109416200A (en) * | 2016-07-15 | 2019-03-01 | 通用电器技术有限公司 | The metal-ceramic coatings of Tube Sheet of Heat Exchanger and preparation method thereof for central solar receiver |
| CN106544672A (en) * | 2017-01-13 | 2017-03-29 | 山东建筑大学 | A kind of method by laser machining preparation quasi-crystalline substance composite |
| CN108707894A (en) * | 2018-06-09 | 2018-10-26 | 沈阳工业大学 | Powder and process used in a kind of laser melting coating self-lubricating abrasion-resistant cobalt-base alloys |
| CN109385500A (en) * | 2018-10-08 | 2019-02-26 | 宁国市开源电力耐磨材料有限公司 | A kind of power shovel multi-alloy wear-resisting cast steel bucket tooth and preparation method thereof |
| CN109609811A (en) * | 2019-02-22 | 2019-04-12 | 上海中洲特种合金材料股份有限公司 | A kind of preparation method of cobalt-base alloys casting |
| CN112645698A (en) * | 2021-01-15 | 2021-04-13 | 北京瑞尔非金属材料有限公司 | Aluminum titanium silicon carbide composite refractory castable for iron-making blast furnace |
| CN112795919A (en) * | 2021-03-17 | 2021-05-14 | 中南林业科技大学 | Composite coating material for improving friction performance of TC4 alloy and preparation method thereof |
| CN113862602A (en) * | 2021-09-29 | 2021-12-31 | 重庆川仪调节阀有限公司 | Method for spraying Stellite20 alloy on surface of workpiece |
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