CN115449790B - Wear-resistant corrosion-resistant high-entropy alloy cladding layer for remanufacturing of propeller and preparation method - Google Patents
Wear-resistant corrosion-resistant high-entropy alloy cladding layer for remanufacturing of propeller and preparation method Download PDFInfo
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- CN115449790B CN115449790B CN202211263180.3A CN202211263180A CN115449790B CN 115449790 B CN115449790 B CN 115449790B CN 202211263180 A CN202211263180 A CN 202211263180A CN 115449790 B CN115449790 B CN 115449790B
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- 238000005253 cladding Methods 0.000 title claims abstract description 102
- 239000000956 alloy Substances 0.000 title claims abstract description 73
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 72
- 238000005260 corrosion Methods 0.000 title claims abstract description 25
- 230000007797 corrosion Effects 0.000 title claims abstract description 25
- 238000002360 preparation method Methods 0.000 title claims abstract description 19
- 239000000758 substrate Substances 0.000 claims abstract description 21
- 230000007547 defect Effects 0.000 claims abstract description 7
- 238000004140 cleaning Methods 0.000 claims abstract description 5
- 238000005498 polishing Methods 0.000 claims abstract description 5
- 239000000843 powder Substances 0.000 claims description 46
- 238000001035 drying Methods 0.000 claims description 18
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 14
- 229910052751 metal Inorganic materials 0.000 claims description 13
- 239000002184 metal Substances 0.000 claims description 13
- 239000000463 material Substances 0.000 claims description 12
- 229910000906 Bronze Inorganic materials 0.000 claims description 10
- 239000010974 bronze Substances 0.000 claims description 10
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 claims description 10
- 239000007789 gas Substances 0.000 claims description 10
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 8
- 229910000943 NiAl Inorganic materials 0.000 claims description 5
- 239000002245 particle Substances 0.000 claims description 5
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 4
- 244000137852 Petrea volubilis Species 0.000 claims description 4
- 229910052786 argon Inorganic materials 0.000 claims description 4
- 238000000889 atomisation Methods 0.000 claims description 4
- 239000011324 bead Substances 0.000 claims description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 238000011068 loading method Methods 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 4
- 239000000155 melt Substances 0.000 claims description 2
- 229910005347 FeSi Inorganic materials 0.000 claims 2
- 238000001856 aerosol method Methods 0.000 claims 1
- 238000011065 in-situ storage Methods 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 claims 1
- 238000003541 multi-stage reaction Methods 0.000 claims 1
- 229910052710 silicon Inorganic materials 0.000 claims 1
- 239000010703 silicon Substances 0.000 claims 1
- 239000011159 matrix material Substances 0.000 abstract description 8
- 238000005516 engineering process Methods 0.000 abstract description 5
- 230000000052 comparative effect Effects 0.000 description 9
- 238000005299 abrasion Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000010287 polarization Effects 0.000 description 3
- 239000007921 spray Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 2
- 235000007516 Chrysanthemum Nutrition 0.000 description 1
- 244000189548 Chrysanthemum x morifolium Species 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000004925 denaturation Methods 0.000 description 1
- 230000036425 denaturation Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010891 electric arc Methods 0.000 description 1
- 238000013213 extrapolation Methods 0.000 description 1
- 238000010285 flame spraying Methods 0.000 description 1
- 238000004372 laser cladding Methods 0.000 description 1
- 238000002161 passivation Methods 0.000 description 1
- 239000013535 sea water Substances 0.000 description 1
- 239000011863 silicon-based powder Substances 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
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
- C23C24/106—Coating with metal alloys or metal elements only
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F9/00—Making metallic powder or suspensions thereof
- B22F9/02—Making metallic powder or suspensions thereof using physical processes
- B22F9/06—Making metallic powder or suspensions thereof using physical processes starting from liquid material
- B22F9/08—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying
- B22F9/082—Making metallic powder or suspensions thereof using physical processes starting from liquid material by casting, e.g. through sieves or in water, by atomising or spraying atomising using a fluid
-
- 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
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Coating By Spraying Or Casting (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention discloses a wear-resistant corrosion-resistant high-entropy alloy cladding layer for remanufacturing a propeller and a preparation method thereof, wherein the high-entropy alloy material for cladding comprises the following components: feCoNiCrMnAl x Si y After polishing and cleaning the surface of the substrate to be clad, preparing a high-entropy alloy cladding layer on the surface of the substrate by adopting plasma cladding equipment; the high-entropy alloy cladding layer prepared by adopting the plasma cladding technology has no defects such as holes, cracks and the like, the cladding layer and the matrix are well metallurgically bonded, and the cladding layer has compact and uniform structure; the hardness, wear resistance and corrosion resistance of the cladding layer are obviously improved relative to the matrix, and the requirements of the remanufacturing of the propeller on wear resistance and corrosion resistance can be met.
Description
Technical Field
The invention relates to the field of remanufacturing, in particular to a wear-resistant corrosion-resistant high-entropy alloy cladding layer for repairing a propeller and a plasma preparation method thereof.
Background
The propeller is one of core components of a ship power system, and is subjected to cavitation corrosion caused by high-speed operation and seawater corrosion because the propeller works under the working conditions of high load, high corrosion and high abrasion all the year round. The surface of the propeller is worn and corroded, and the service life of the propeller is greatly reduced. Therefore, the method has important significance for repairing and remanufacturing the propeller.
Firstly, the service environment of the propeller is harsh, so that the repair material is required to have excellent corrosion resistance and wear resistance; the high-entropy alloy is a novel alloy which appears in recent years, has excellent performances such as high strength, high hardness, high wear resistance, corrosion resistance and the like, and has potential engineering application prospect. Secondly, considering that the propeller is a large key part, a high-efficiency repairing method is needed; however, the cladding layer obtained by flame spraying, electric arc spraying and other modes at the present stage still has the defects of low bonding strength, high porosity of the repair layer, concentrated stress of the repair layer, large surface roughness of the repair layer, material denaturation caused by high temperature and the like, the cost of laser cladding is higher, the efficiency is lower, the nickel-aluminum bronze matrix has a reflection effect on laser, and certain difficulty exists in the cladding process. In contrast, the plasma cladding technology has the advantages of low cost, high working efficiency, good metallurgical bonding performance and the like, so that the wear-resistant corrosion-resistant high-entropy alloy cladding layer is prepared by adopting the plasma cladding technology to repair the propeller.
Disclosure of Invention
The invention aims to solve the problems in the background technology and provide the wear-resistant corrosion-resistant high-entropy alloy cladding layer for remanufacturing the propeller and the plasma preparation method thereof, the prepared high-entropy alloy cladding layer has no defects, the cladding layer and a matrix are well metallurgically bonded, and the cladding layer has compact and uniform structure.
In order to achieve the purpose, the invention adopts the following technical scheme that the preparation method of the wear-resistant corrosion-resistant high-entropy alloy cladding layer for remanufacturing of the propeller comprises the following steps:
1) Powder preparation: the utility model provides a wear-resisting corrosion-resistant high entropy alloy cladding layer for screw remanufacturing which characterized in that: the composition and atomic ratio are as follows: feCoNiCrMnAl x Si y WhereinX is more than or equal to 0.4 and less than 1, y is more than or equal to 0 and less than or equal to 0.6; feCoNiCrMnAl is prepared by adopting an air atomization method x Si y In the preparation process, firstly, metal Co, metal Mn, metal Cr, feSi alloy and NiAl alloy are smelted into alloy blocks according to a certain proportion, then the alloy melt is impacted by high-speed airflow, the kinetic energy of the air is converted into the surface energy of the metal melt by collision, the molten metal flow is crushed into tiny droplets, and then the droplets are rapidly cooled and solidified in the airflow atmosphere to form powder with the particle size of 30-80 mu m; then FeCoNiCrMnAl is added x Si y Placing the powder into a baking oven for baking treatment, setting the drying temperature to be 60-80 ℃ and the time to be 6-8h;
2) And (3) treating a base material: polishing the surface of the nickel-aluminum bronze substrate by using sand paper, cleaning the surface by using alcohol, and drying the substrate; wherein the drying temperature is 60-80 ℃ and the drying time is 2-4h;
3) Preparing a cladding layer: feCoNiCrMnAl is added x Si y Loading alloy powder into a powder feeder of plasma cladding equipment, fixing a base material by using a clamp, opening the cladding equipment for cladding, and naturally cooling in air after cladding is completed to obtain a high-entropy alloy cladding layer; wherein, the gases used in the cladding process are all argon, and the technological parameters of cladding are as follows: cladding current is 100-105A, cladding speed is 150-180 mm.min -1 The flow rate of the plasma is 2-4 L.min -1 Protecting air flow of 10-20 L.min -1 The distance between the spray gun and the substrate is 7-10mm, and the powder feeding gas flow is 2-10 L.min -1 Powder feeding speed is 20-30 r.min -1 Welding bead overlap joint 2-10mm;
the beneficial effects of the invention are as follows:
1) The high-entropy alloy cladding layer prepared by the method has no defects such as cracks, holes and the like, has uniform and compact structure, and generates good metallurgical bonding with a matrix.
2) The high-entropy alloy cladding layer with excellent comprehensive performance is prepared by adopting a plasma cladding technology, so that the surface hardness, wear resistance and corrosion resistance of the propeller are effectively improved.
3) The cladding layer obtained by the method has good quality, can meet the requirements of repairing and remanufacturing the propeller, and has low cost and high working efficiency.
Drawings
FIG. 1 shows a cladding layer surface and cross-sectional microstructure of an embodiment.
Figure 2 shows the XRD phase composition of the powder of the example.
FIG. 3 is a graph showing the potentiodynamic polarization of a substrate and cladding layer according to one embodiment.
Detailed Description
The present invention will be described in further detail below with reference to specific embodiments and drawings for the understanding of those skilled in the art.
The example high entropy alloy powder consists of Fe, co, ni, cr, mn, al, si powder, wherein the molar ratio of Fe, co, ni, cr, mn, al, si is: 1:1:1:1:1:0.5:0.5.
FeCoNiCrMnAl in this example 0.5 Si 0.5 The preparation method of the high-entropy alloy cladding layer comprises the following steps:
1) Powder preparation: feCoNiCrMnAl is prepared by adopting an air atomization method 0.5 Si 0.5 In the preparation process, firstly, metal Co, metal Mn, metal Cr, feSi alloy and NiAl alloy are smelted into alloy blocks according to a certain proportion, then the alloy blocks melt is impacted by high-speed air flow, the kinetic energy of the air is converted into the surface energy of the melt by collision, the molten metal flow is broken into tiny droplets, and then the droplets are rapidly cooled and solidified in the air flow atmosphere to form powder, wherein the particle size of the prepared powder is 30-80 mu m; then FeCoNiCrMnAl is added 0.5 Si 0.5 Drying the powder, wherein the drying temperature is set to 80 ℃ and the time is 8 hours;
2) And (3) treating a base material: polishing the surface of the nickel-aluminum bronze substrate by using sand paper, cleaning the surface by using alcohol, and drying the substrate; wherein the drying temperature is 60 ℃ and the drying time is 2 hours;
3) Preparing a cladding layer: feCoNiCrMnAl is added 0.5 Si 0.5 Loading alloy powder into a powder feeder of plasma cladding equipment, fixing a base material by using a clamp, opening the cladding equipment for cladding, and naturally cooling in air after cladding is completed to obtain a high-entropy alloy cladding layer; wherein, in the cladding processThe gases used are argon, and the technological parameters of cladding are as follows: cladding current 103A, cladding speed 175 mm.min -1 Plasma gas flow rate 3 L.min -1 Protecting air flow 15 L.min -1 The distance between the spray gun and the substrate is 8mm, and the powder feeding gas flow is 5 L.min -1 Powder feeding speed 23 r.min -1 Welding bead overlap joint 4mm;
FeCoNiCrMnAl obtained in this example 0.5 Si 0.5 The high-entropy alloy cladding layer has good quality and no defects such as cracks, air holes and the like.
The example shows that FeCoNiCrMnAl is obtained 0.5 Si 0.5 The microstructure of the high-entropy alloy cladding layer was studied and the results are shown in FIG. 1. From FIG. 1 (a), it can be seen that FeCoNiCrMnAl 0.5 Si 0.5 The microstructure of the high-entropy alloy cladding layer is dendritic, the shape of the high-entropy alloy cladding layer is chrysanthemum, the grain size is 10-20 mu m, and the microstructure is uniformly distributed. FIG. 1 (b) shows the cross-sectional structure of the cladding layer, and it can be seen that the bonding site of the cladding layer and the substrate interface has no obvious cracks or holes, and the interface line is in zigzag metallurgical bonding, which proves that the cladding layer is fully bonded with the substrate.
The present example is directed to FeCoNiCrMnAl 0.5 Si 0.5 The phases of the high-entropy alloy powder were analyzed and the results are shown in fig. 2. It can be shown that: feCoNiCrMnAl 0.5 Si 0.5 The high entropy alloy powder phase is a simple single FCC solid solution structure.
The present example is directed to FeCoNiCrMnAl 0.5 Si 0.5 The corrosion resistance of the high-entropy alloy cladding layer was tested and the results are shown in fig. 3. FIG. 3 shows the potentiodynamic polarization curve of the substrate and cladding layer, calculated by Tafel extrapolation 0.5 Si 0.5 The corrosion current densities of the cladding layer and the nickel-aluminum bronze substrate were 2.35×10, respectively -6 A/cm 2 And 4.7X10 -6 A/cm 2 It can be seen that the corrosion current density of the cladding layer is smaller than that of the substrate, and the polarization curve of the cladding layer has obvious inflection points, which indicates that passivation is generated, and the result shows that the corrosion resistance of the cladding layer is superior to that of the substrate.
The present example is directed to FeCoNiCrMnAl 0.5 Si 0.5 The friction and wear performance of the high-entropy alloy cladding layer is tested, and the result shows that the wear mechanism of the nickel-aluminum bronze matrix is mainly adhesive wear, and the wear mechanism of the high-entropy alloy cladding layer is mainly abrasive particle wear; the mass abrasion amount of the matrix is about 4 times of that of the cladding layer, which shows that FeCoNiCrMnAl 0.5 Si 0.5 The wear resistance of the high-entropy alloy cladding layer is superior to that of the nickel-aluminum bronze matrix.
Comparative example 1
To further illustrate the beneficial properties of the high entropy alloy powders described in the examples, a comparative powder was prepared.
Comparative example 1 the molar ratio of Fe, co, ni, cr, mn, al, si in the high entropy alloy powder is: 1:1:1:1:1:0.5:0.
FeCoNiCrMnAl in this example 0.5 The preparation method of the high-entropy alloy cladding layer comprises the following specific steps:
1) Powder preparation: the FeCoNiCrMnAl is prepared by adopting an air atomization method 0.5 The shape of the powder is spherical powder with the particle size of 30-80 mu m; and then FeCoNiCrMnAl is added 0.5 Drying the powder, wherein the drying temperature is set to 80 ℃ and the time is 8 hours;
2) And (3) treating a base material: polishing the surface of the nickel-aluminum bronze substrate by using sand paper, cleaning the surface by using alcohol, and drying the substrate; wherein the drying temperature is 60 ℃ and the drying time is 2 hours;
3) Preparing a cladding layer: feCoNiCrMnAl is added 0.5 Loading alloy powder into a powder feeder of plasma cladding equipment, fixing a base material by using a clamp, opening the cladding equipment for cladding, and naturally cooling in air after cladding is completed to obtain a high-entropy alloy cladding layer; wherein, the gases used in the cladding process are all argon, and the technological parameters of cladding are as follows: cladding current 103A, cladding speed 175 mm.min -1 Plasma gas flow rate 3 L.min -1 Protecting air flow 15 L.min -1 The distance between the spray gun and the substrate is 8mm, and the powder feeding gas flow is 5 L.min -1 Powder feeding speed 23 r.min -1 Welding bead overlap joint 4mm;
the method changes the component proportion of the alloy powder, and the prepared FeCoNiCrMnAl alloy powder 0.5 The mass abrasion loss of the high-entropy alloy cladding layer is about 6.5 times of the abrasion loss of the nickel-aluminum bronze substrate, and FeCoNiCrMnAl is known 0.5 The wear resistance of the high-entropy alloy cladding layer is inferior to that of FeCoNiCrMnAl in the specific embodiment 0.5 Si 0.5 A high-entropy alloy cladding layer.
Comparative example 2
To further illustrate the beneficial properties of the high entropy alloy powders described in the examples, a comparative powder was prepared.
Comparative example 2 the molar ratio of Fe, co, ni, cr, mn, al, si in the high entropy alloy powder is: 1:1:1:1:1:0.5:1.
FeCoNiCrMnSiAl in this comparative example 0.5 The preparation method of the high-entropy alloy cladding layer is the same as in comparative example 1.
FeCoNiCrMnSiAl prepared in this comparative example 0.5 The high-entropy alloy cladding layer has poor surface quality, and the cladding layer has defects of cracks, air holes and the like.
Claims (6)
1. A preparation method of a wear-resistant corrosion-resistant high-entropy alloy cladding layer for remanufacturing a propeller is characterized by comprising the following steps of: the high-entropy alloy cladding layer comprises the following components in atomic ratio: feCoNiCrMnAl x Si y Wherein x is more than or equal to 0.4 and less than 1, y is more than or equal to 0 and less than or equal to 0.6, and the preparation method comprises the following steps:
(1) Powder preparation: feCoNiCrMnAl is prepared by adopting an air atomization method x Si y A powder; drying the powder at 60-80deg.C for 6-8 hr;
(2) And (3) treating a base material: polishing the surface of the nickel-aluminum bronze substrate by using sand paper, cleaning the surface by using alcohol, and drying the substrate; the drying temperature is 60-80 ℃ and the drying time is 2-4h;
(3) Preparing a cladding layer: feCoNiCrMnAl is added x Si y Loading alloy powder into a powder feeder of plasma cladding equipment, fixing a base material by using a clamp, opening the cladding equipment for cladding, and naturally cooling in air after cladding is completed to obtain a high-entropy alloy cladding layer; wherein the gases used in the cladding process are argon, and the cladding process parameter is thatThe number is as follows: cladding current is 100-105A, cladding speed is 150-180 mm.min -1 The flow rate of the plasma is 2-4 L.min -1 Protecting air flow of 10-20 L.min -1 The distance between the nozzle and the base material is 7-10mm, and the flow rate of the powder feeding gas is 2-10 L.min -1 Powder feeding speed is 20-30 r.min -1 The welding bead is overlapped by 2-10mm.
2. The method for producing a wear-resistant and corrosion-resistant high-entropy alloy cladding layer according to claim 1, wherein the step (1) employs an aerosol method for producing FeCoNiCrMnAl x Si y In the preparation process, metal Co, metal Mn, metal Cr, feSi alloy and NiAl alloy are firstly smelted into alloy blocks according to a certain proportion, then the alloy blocks are impacted into alloy block melt by high-speed airflow, the kinetic energy of the air is converted into the surface energy of the melt by collision, so that the molten metal flow is broken into tiny droplets, and then the fine droplets are rapidly cooled and solidified in the airflow atmosphere to form powder.
3. The FeSi alloy and NiAl alloy according to claim 2, wherein the FeSi alloy contains 50% silicon and the NiAl alloy has an atomic ratio of 1:1.
4. the FeCoNiCrMnAl of claim 2 x Si y The high-entropy alloy powder is characterized in that the particle size of the powder is 30-80 mu m.
5. The method for preparing the wear-resistant corrosion-resistant high-entropy alloy cladding layer according to claim 1, wherein the high-entropy alloy cladding layer prepared by the method is good in quality, compact in cladding layer structure and free of defects such as cracks and holes.
6. The method for preparing the wear-resistant and corrosion-resistant high-entropy alloy cladding layer according to claim 1, wherein in the preparation process, feCoNiCrMnAl x Si y Alloy powder and nickel aluminum bronze base material undergo in-situ composite reaction, and the formed cladding layer has good wear resistance and corrosion resistance and can be applied toThe method is used for repairing and remanufacturing the propeller.
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