CN114669956A - Powder metallurgy repair method for repairing defects of high-temperature alloy blade - Google Patents
Powder metallurgy repair method for repairing defects of high-temperature alloy blade Download PDFInfo
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Abstract
The invention belongs to the field of research on repair of turbine blades, and provides a powder metallurgy repair method for repairing defects of high-temperature alloy blades, which comprises the following steps of dissolving Zr-containing low-melting-point powder A and multi-principal-element alloy powder B in a solvent, and performing ball milling in a protective atmosphere to obtain uniformly mixed powder; mixing a proper amount of ethanol, propanol, polyvinylpyrrolidone, polyacrylamide and stearic acid to obtain a bonding fluid; adding the obtained mixed powder into the binding fluid and uniformly stirring to obtain a gel-state repairing agent with fluidity and binding property; and coating the obtained repairing agent on the to-be-repaired defect of the high-temperature alloy blade, and placing the high-temperature alloy blade in a vacuum furnace for heat treatment to finish repairing. The invention provides a new idea for manufacturing the gas turbine blade made of Inconel738LC, and has the advantages of wide method applicability, strong flexibility, capability of being adjusted and optimized randomly according to the size and the shape of the defect or the damaged part of the high-temperature alloy blade and the like.
Description
Technical Field
The invention belongs to the field of research on repair of turbine blades, and particularly provides a powder metallurgy repair method for repairing defects of a high-temperature alloy blade, which is suitable for repairing Inconel738LC nickel-based high-temperature alloy.
Background
The Inconel738LC high-temperature alloy has excellent room-temperature and high-temperature mechanical properties and good structure stability, corrosion resistance and oxidation resistance, so the Inconel738LC high-temperature alloy is widely applied to preparation of long-life turbine working blades and guide blades of gas turbines. In the service process, the Inconel738LC high-temperature blade is easily corroded, cracked, deformed and pitted under the actions of abrasion, impact, cold and hot fatigue and the like for a long time, and is easily a hidden trouble of major accidents. Gas turbine blades are complex and cumbersome to manufacture, and the raw materials used to fabricate the blades are expensive, making the remanufacturing of gas turbine blades expensive. Therefore, if the repair technology can be adopted to repair the defects and the damaged parts, the performance of the composite material is recovered, the service life of the composite material is prolonged, and great economic benefits are achieved.
The conventional repairing method of the heavy-duty gas turbine high-temperature blade comprises a fusion welding, brazing, diffusion welding and instantaneous liquid phase connection repairing method. Fusion welding is a method of joining materials by heating a welding wire and a region to be repaired of a workpiece together to a molten state and then relying on the melting. The method has the advantages of high heat source temperature, concentrated heat and simpler operation, but the Inconel738LC high-temperature alloy contains higher Al and Ti elements, so that the gamma' phase close to a repair area is easy to change remarkably, even microcracks are possibly generated, and the performance of the repaired blade is remarkably reduced. The traditional brazing method generally uses brazing filler metal with a melting point lower than that of a base metal, when the brazing filler metal and the base metal are heated together to a temperature higher than the melting point of the brazing filler metal but lower than the melting point of the base metal, the brazing filler metal will be melted, flow and fill gaps needing to be repaired, and the base metal is mutually diffused to form a metallurgical bonding diffusion layer. In the traditional brazing, a brazing filler metal with a composition greatly different from that of a base material is used generally after pursuing low repair temperature, and finally the brazing filler metal is solidified at variable temperature to finish the repair process. Eventually, very much brittle eutectic structure tends to form in the weld area, resulting in reduced joint strength, hot corrosion resistance, and oxidation resistance. Diffusion welding is a technology for connection repair by utilizing solid phase diffusion, and the principle is that two solid phase atoms on the surfaces of materials which are contacted with each other are utilized to carry out solid phase diffusion under the action of high temperature and high pressure, and a new diffusion layer is formed at an interface, so that reliable connection is realized. However, diffusion welding costs are high, the required time is long, and the repairable defect size is limited.
Disclosure of Invention
The invention discloses a powder metallurgy repair method for repairing defects of a high-temperature alloy blade, which aims to solve any one of the above and other potential problems in the prior art.
In order to achieve the purpose, the technical scheme of the invention is as follows: a powder metallurgy repair method for repairing superalloy blade defects, the method comprising the steps of,
s1) dissolving the Zr-containing low-melting-point powder A and the multi-principal-element alloy powder B in a solvent, and performing ball milling in a protective atmosphere to obtain uniform mixed powder;
s2) mixing a proper amount of ethanol, propanol, polyvinylpyrrolidone, polyacrylamide and stearic acid to obtain a bonding fluid;
s3) adding the bonding fluid obtained in the step S2) into the mixed powder obtained in the step S1) and stirring to obtain the gel-state repairing agent with fluidity and bonding property;
s4) coating the repairing agent obtained in the step S4) on the part to be repaired of the Inconel738LC nickel-based superalloy, and carrying out heat treatment in a vacuum furnace to finish the repair.
Further, the mass ratio of the Zr-containing low melting point powder A to the multi-element alloy powder B in S1) is (0.1-0.3): 1.
Further, the mass percentages of the components in the Zr-containing low-melting-point powder A are as follows: 6-18wt.% Cr, 3-8wt.% Co, 1-8wt.% Al, 1-8wt.% Ti, 0.5-5wt.% W, 0.5-4wt.% Mo, 3-15wt.% Zr,
The multi-principal element alloy powder B comprises the following components in percentage by atom: 8-25at.% Cr, 8-25at.% Co, 3-15at.% Al, 0.5-5at.% W, 0.5-5at.% Mo, 0.5-6at.% Ti, the balance being Ni and unavoidable impurities.
Further, the mass percentages of the components in the Zr-containing low-melting-point powder A are as follows: 8-16wt.% Cr, 4-6wt.% Co, 1-3wt.% Al, 1-3wt.% Ti, 1-3wt.% W, 1-2wt.% Mo, 3-13wt.% Zr, the balance being Ni and unavoidable impurities,
the multi-principal element alloy powder B comprises the following components in percentage by atom: 10-20at.% Cr, 10-20at.% Co, 3-10at.% Al, 1-5at.% W, 1-5at.% Mo, 1-5at.% Ti, the balance being Ni and unavoidable impurities.
Further, the specific process of the heat treatment of S3) is as follows:
s3.1) heating to 400-500 ℃ per minute at 10 ℃ in a vacuum environment, preserving the heat for 1-3 hours,
s3.2) heating to 1100-.
Furthermore, the porosity of the repaired area of the repaired Inconel738LC nickel-based high-temperature alloy is less than 0.5%, and the strength ratio between the connecting joint part and the base metal alloy is not less than 65%.
Further, the Zr-containing low melting point powder A has a particle size of less than 20 μm, and the multi-principal component alloy powder B has a particle size of less than 106 μm.
Further, the Zr-containing low-melting-point powder A has a particle diameter of 8 to 28 μm, and the multi-principal-element alloy powder B has a particle diameter of 53 to 100 μm.
Further, in the S1), the ball milling is carried out, stainless steel balls are used as a medium, argon is used as a protective atmosphere, and the mixture is mixed for 2-12 hours at the rotating speed of 20-60 r/min.
Further, the mass ratio of the mixed powder to the binding fluid in the step S2) is (5-20):1, and the mixing and stirring time is 3-30 minutes.
Further, the mass percentages of the components of the binding fluid are as follows: 0.5-4wt.% polyvinylpyrrolidone, 0.5-4wt.% polyacrylamide, 0.1-1wt.% stearic acid, 30-45wt.% propanol and the balance ethanol.
Transient liquid phase bonding (TLP) is a method of completing repairs using an intermediate layer to melt and wet the filler blades during the incubation process. The TLP process is mainly characterized by the elimination of the liquid phase by isothermal solidification of the interlayer to complete the repair process, compared to the conventional brazing process. Meanwhile, through subsequent heat treatment, tissues in the repair area can be gradually homogenized so as to reduce the tissue nonuniformity of the repair blade as much as possible. The TLP technology combines the advantages of simple and convenient high-temperature brazing process and high strength of solid diffusion connection, can simultaneously connect a plurality of workpieces and a plurality of welding seams, and has high efficiency and low cost.
However, in the transient liquid phase connection repair process, in order to ensure that the intermediate layer can be completely liquefied at a lower temperature, more melting-reducing elements must be added, i.e., the intermediate layer and the base material have larger difference in elemental composition and microstructure. If the zirconium element is added into the intermediate layer material, the melting point of the zirconium element can be effectively reduced, and the addition of a proper amount of the zirconium element into the alloy can not only improve the grain boundary bonding force and strengthen the grain boundary, but also improve the high-temperature strength of the alloy by entering the gamma' phase. However, in order to meet the melting reduction requirement, more zirconium element must be added into the interlayer material, and the introduction of excessive zirconium element has adverse effect on the tissues of the repair area. Although the intermediate layer and the base material elements in the vicinity can be uniformized by diffusion, it is inevitable to induce a eutectic structure of γ + γ' phase and Ni5Zr、Ni7Zr2Intermetallic phases are formed inside the repair zone and at the repair zone/substrate interface, resulting in reduced performance of the repaired blade.
The defects of the transient liquid phase linking method can be effectively improved by using a powder metallurgy method to repair the turbine blade. In the process of repairing the turbine blade by the powder metallurgy method, one part of high-melting-point powder is used as a framework to keep a solid state, the other part of low-melting-point powder is melted, flows and fills gaps of the framework, the liquid phase dissolves the surface layers of the framework and the base material to complete connection, and then the tissues are gradually homogenized through isothermal solidification and high-temperature diffusion, so that the repairing process is completed. Because only part of low-melting-point powder is used as a repair raw material in the repair process, the repair cost of the turbine blade repaired by the powder metallurgy method can be reduced, and the generation of harmful phases can be effectively reduced, so that higher strength after repair is obtained. In the powder metallurgy repair of turbine blades, the addition of zirconium element to the low melting point powder ensures the presence of a liquid phase during repair. However, if the component of the powder raw material is improperly designed, the melting-reducing element can be rapidly lost in the repair process, isothermal solidification occurs when the filling process is not completed, and finally, the repair area has too many pores to cause repair failure. Therefore, through reasonable repair powder component design, the liquid phase can be ensured to exist for enough time and the filling process is completed on the premise of not increasing harmful phases in a repair area.
The development of high entropy (multi-principal element) alloy in recent years provides a new idea for the applicant to repair Inconel738LC high temperature alloy turbine blades by a powder metallurgy method. The Inconel738LC is the grade of the nickel-based superalloy, and the nickel-based superalloy comprises the following components in percentage by mass: 0.11C, 15.84Cr, 8.5Co, 2.48W, 1.88Mo, 0.07Fe, 0.92Nb, 3.46Al, 3.4Ti, 1.69Ta, 0.001S, 0.04Zr, 0.012B and the balance Ni. The high-entropy (multi-principal element) alloy is formed by combining three or more metal elements in an equal molar ratio or a nearly equal molar ratio, and is widely concerned by various industries due to the extremely potential structural and functional applications. In particular, the diffusion of the high-entropy alloy caused by the characteristics of multiple principal elements and serious lattice distortion needs to overcome the resistance caused by the cooperative diffusion of multiple elements and the lattice distortion. Therefore, compared with the traditional single-principal-element alloy, the effective diffusion rate of the high-entropy alloy is greatly reduced. It can be expected that the diffusion rate between the liquid phase and the framework can be effectively reduced by using the high-entropy alloy as the infusible powder framework of the repair region, so that the liquid phase can flow sufficiently in the repair process, and the particle rearrangement is promoted to improve the compactness of the repair region. The method can reduce the use amount of low-melting-point powder to the maximum extent, so that the introduction of melting-reducing elements in the repair process can be reduced, the precipitation of harmful phases in the repair area is effectively inhibited, and the mechanical property of the repaired blade is improved.
The invention has the advantages and beneficial effects that:
1. the invention provides a novel repair material and a repair process for repairing the surface defects of the Inconel738LC gas turbine blade, and provides a new idea for repairing the gas turbine blade.
2. The repairing layer is firmly combined with the matrix, and the harmful phase content of the microstructure is less. Since the addition amount of the low-melting-point powder is small, even if a very small amount of the intermetallic nickel-zirconium compound is formed, the influence on the mechanical properties of the blade, particularly the low cycle fatigue properties, is small.
3. The repair material and the repair method provided by the invention have the advantages of low cost, wide applicability and strong flexibility, and can meet the repair requirements of most of defects or damages of the blades.
Drawings
FIG. 1 is a flow chart of a powder metallurgy repair method for repairing superalloy blade defects according to the present invention.
Detailed Description
The technical scheme of the invention is further explained by combining the attached drawings and concrete implementation.
Referring to fig. 1, a powder metallurgy repair method for repairing a superalloy blade defect according to the present invention includes the steps of,
s1) dissolving the Zr-containing low-melting-point powder A and the multi-principal-element alloy powder B in a solvent, and carrying out ball milling in a protective atmosphere to obtain uniform mixed powder;
S2) mixing a proper amount of ethanol, propanol, polyvinylpyrrolidone, polyacrylamide and stearic acid to obtain a bonding fluid;
s3) adding the bonding fluid obtained in the step S2) into the mixed powder obtained in the step S1) and stirring to obtain the gel-state repairing agent with fluidity and bonding property;
s4) coating the repairing agent obtained in the step S4) on the part to be repaired of the Inconel738LC nickel-based superalloy, and carrying out heat treatment in a vacuum furnace to finish the repair.
The mass ratio of the Zr-containing low-melting-point powder A to the multi-principal-element alloy powder B in S1) (0.1-0.3) is 1.
The Zr-containing low-melting-point powder A comprises the following components in percentage by mass: 6-18wt.% Cr, 3-8wt.% Co, 1-8wt.% Al, 1-8wt.% Ti, 0.5-5wt.% W, 0.5-4wt.% Mo, 3-15wt.% Zr,
the multi-principal component alloy powder B comprises the following components in atomic percentage: 8-25at.% Cr, 8-25at.% Co, 3-15at.% Al, 0.5-5at.% W, 0.5-5at.% Mo, 0.5-6) at.% Ti, the balance being Ni and unavoidable impurities.
The Zr-containing low-melting-point powder A comprises the following components in percentage by mass: 8-16wt.% Cr, 4-6wt.% Co, 1-3wt.% Al, 1-3wt.% Ti, 1-3wt.% W, 1-2wt.% Mo, 3-13wt.% Zr, the balance being Ni and unavoidable impurities,
the multi-principal component alloy powder B comprises the following components in atomic percentage: 10-20at.% Cr, 10-20at.% Co, 3-10at.% Al, 1-5at.% W, 1-5at.% Mo, 1-5at.% Ti, and the balance Ni and unavoidable impurities, and functions as a multi-principal-element powder to reduce diffusion of low-melting-point elements containing Zr.
The specific process of the heat treatment of S3) is as follows:
s3.1) heating to 400-500 ℃ per minute at 10 ℃ in a vacuum environment, preserving the heat for 1-3 hours,
s3.2) heating to 1100-.
The porosity of the repaired area of the repaired Inconel738LC nickel-based superalloy is less than 0.5%, and a joint part and the repaired area are connected
The strength ratio between the base metal alloys is more than or equal to 65 percent.
The grain diameter of the Zr-containing low-melting-point powder A is less than 20 mu m, and the grain diameter of the multi-principal-element alloy powder B is less than 106 mu m.
The grain diameter of the Zr-containing low-melting-point powder A is 8-28 mu m, and the grain diameter of the multi-principal-element alloy powder B is 53-100 mu m.
And in the S1), ball milling, taking a stainless steel ball as a medium and argon as a protective atmosphere, and mixing for 2-12 hours at a rotating speed of 20-60 r/min to uniformly mix Zr-containing low-melting-point powder A and multi-principal-element alloy powder B.
The mass ratio of the mixed powder to the binding fluid in the step S2) is (5-20):1, and the mixing and stirring time is 3-30 minutes. The binding fluid has good wettability with the powder, is easy to remove at low temperature, and has almost no residue.
The mass percentages of the components of the bonding fluid are as follows: 0.5-4wt.% polyvinylpyrrolidone, 0.5-4wt.% polyacrylamide, 0.1-1wt.% stearic acid, 30-45wt.% propanol, and the balance ethanol.
Example 1:
mixing a powder A with the components of Ni-8wt.% Cr-4wt.% Co-1wt.% Al-2wt.% Ti-1wt.% W-1wt.% Mo-13wt.% Zr and a powder B with the components of Ni-15at.% Cr-15at.% Co-3at.% Al-1at.% W-1at.% Mo-1at.% Ti according to the mass ratio of 0.1:1, dissolving in a proper amount of alcohol, mixing at a rotation speed of 60 revolutions per minute for 8 hours by using a stainless steel ball as a medium and argon as a protective atmosphere. Adding a binding fluid which comprises 4wt.% of PVP, 4wt.% of PAM, 1wt.% of SA, 45wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 30 minutes to obtain the repairing agent, wherein the mass ratio of the mixed powder to the binding fluid in the repairing agent is 20: 1. Coating the repairing agent on a required repairing part of the Inconel738LC blade, placing the blade in a vacuum furnace, heating to 500 ℃ at 10 ℃ per minute for 3 hours, heating to 1120 ℃ at 5 ℃ per minute for 3 hours, cooling to 700 ℃ along with the temperature of the furnace, introducing argon gas, rapidly cooling to room temperature to complete the repairing process, manufacturing the repaired repairing area into a tensile member, and measuring the tensile strength at the room temperature to be 683MPa to reach more than 65% of the strength of the base material.
Example 2:
mixing a powder A with the components of Ni-12wt.% Cr-5wt.% Co-2wt.% Al-3wt.% Ti-2wt.% W-2wt.% Mo-10wt.% Zr and a powder B with the components of Ni-18at.% Cr-18at.% Co-6at.% Al-2at.% W-2at.% Mo-2at.% Ti according to the mass ratio of 0.15:1, dissolving in a proper amount of alcohol, mixing at a rotation speed of 50 revolutions per minute for 6 hours by using a stainless steel ball as a medium and argon as a protective atmosphere. Adding a binding fluid which comprises 3wt.% of PVP, 2.5wt.% of PAM, 0.8wt.% of SA, 40wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 30 minutes to obtain the repairing agent, wherein the mass ratio of the mixed powder to the binding fluid in the repairing agent is 16: 1. After the repairing agent is coated on a required repairing part of the Inconel738LC blade, the blade is placed in a vacuum furnace, the temperature is increased to 450 ℃ per minute at 10 ℃ and is preserved for 2 hours, then the temperature is increased to 1150 ℃ per minute at 5 ℃ and is preserved for 2 hours, the blade is cooled to 760 ℃ along with the temperature of the furnace, then argon is introduced to rapidly cool the blade to room temperature to complete the repairing process, the repaired repairing area is made into a tensile piece, the tensile strength at the room temperature is 692MPa, and the tensile strength reaches more than 65% of the strength of a base material.
Example 3:
mixing a powder A with the components of Ni-15wt.% Cr-5.5wt.% Co-3wt.% Al-3wt.% Ti-2.5wt.% W-2.5wt.% Mo-6wt.% Zr and a powder B with the components of Ni-20at.% Cr-20at.% Co-8at.% Al-3at.% W-3at.% Mo-3at.% Ti according to the mass ratio of 0.2:1, dissolving in a proper amount of alcohol, mixing with a stainless steel ball as a medium and argon as a protective atmosphere at a rotating speed of 40 revolutions per minute for 4 hours. Adding a binding fluid which comprises 2wt.% of PVP, 1.5wt.% of PAM, 0.5wt.% of SA, 40wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 10 minutes to obtain the repairing agent, wherein the mass ratio of the mixed powder to the binding fluid in the repairing agent is 12: 1. After the repairing agent is coated on a part, needing to be repaired, of an Inconel738LC blade, the blade is placed in a vacuum furnace, the temperature is increased to 480 ℃ at 10 ℃ per minute and is preserved for 3 hours, then the temperature is increased to 1180 ℃ at 5 ℃ per minute and is preserved for 2 hours, the temperature is cooled to 840 ℃ along with the temperature of the furnace, then argon is introduced to rapidly cool the blade to room temperature, the repairing process is completed, the repaired repairing area is made into a tensile piece, the tensile strength at the room temperature is 679MPa, and the tensile strength reaches more than 65% of the strength of a base material.
Example 4:
mixing a powder A with the composition of Ni-16wt.% Cr-6wt.% Co-3wt.% Al-3wt.% Ti-3wt.% W-3wt.% Mo-4wt.% Zr and a powder B with the composition of Ni-25at.% Cr-25at.% Co-10at.% Al-5at.% W-5at.% Mo-5at.% Ti in a mass ratio of 0.3:1, dissolving in an appropriate amount of alcohol, mixing at a rotation speed of 30 revolutions per minute for 2 hours by using a stainless steel ball as a medium and argon as a protective atmosphere. Adding a binding fluid with the component ratio of 0.5wt.% of PVP, 0.5wt.% of PAM, 0.1wt.% of SA, 30wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 3 minutes to obtain the repairing agent, wherein the mass ratio of the mixed powder to the binding fluid in the repairing agent is 5: 1. Coating the slurry on a required repair part of the Inconel738LC blade, placing the blade in a vacuum furnace, heating to 500 ℃ at 5 ℃ per minute, preserving heat for 2 hours, heating to 1250 ℃ and preserving heat for 2 hours, cooling to 880 ℃ along with the furnace temperature, introducing argon, quickly cooling to room temperature to complete the repair process, manufacturing the repaired repair area into a tensile piece, and measuring the tensile strength at room temperature to be 685MPa to reach more than 65% of the strength of the base material.
The foregoing is a further detailed description of the present invention in connection with specific preferred embodiments thereof, and it is not intended to limit the invention to the specific embodiments thereof. For those skilled in the art to which the invention pertains, numerous and varied simplifications or substitutions may be made without departing from the spirit of the invention, which should be construed as falling within the scope of the invention.
Claims (10)
1. A powder metallurgy repair method for repairing superalloy blade defects, comprising the steps of,
s1) dissolving the Zr-containing low-melting-point powder A and the multi-principal-element alloy powder B in a solvent, and performing ball milling in a protective atmosphere to obtain uniform mixed powder;
s2) mixing a proper amount of ethanol, propanol, polyvinylpyrrolidone, polyacrylamide and stearic acid to obtain a bonding fluid;
s3) adding the bonding fluid obtained in the step S2) into the mixed powder obtained in the step S1) and stirring to obtain the gel-state repairing agent with fluidity and bonding property;
s4) coating the repairing agent obtained in the step S4) on the to-be-repaired defect of the high-temperature alloy blade, and carrying out heat treatment in a vacuum furnace to finish the repair.
2. The method according to claim 1, wherein the mass ratio of the Zr-containing low-melting-point powder A and the multi-principal-element alloy powder B in S1) is (0.1-0.3): 1.
3. The method according to claim 2, wherein the mass percentages of the respective components in the Zr-containing low-melting-point powder a are: 6-18wt.% Cr, 3-8wt.% Co, 1-8wt.% Al, 1-8wt.% Ti, 0.5-5wt.% W, 0.5-4wt.% Mo, 3-15wt.% Zr,
the multi-principal component alloy powder B comprises the following components in atomic percentage: 8-25at.% Cr, 8-25at.% Co, 3-15at.% Al, 0.5-5at.% W, 0.5-5at.% Mo, 0.5-6at.% Ti, the balance being Ni and unavoidable impurities.
4. The method according to claim 2, wherein the mass percentages of the respective components in the Zr-containing low-melting-point powder a are: 8-16wt.% Cr, 4-6wt.% Co, 1-3wt.% Al, 1-3wt.% Ti, 1-3wt.% W, 1-2wt.% Mo, 3-13wt.% Zr, the balance being Ni and unavoidable impurities,
the multi-principal component alloy powder B comprises the following components in atomic percentage: 10-20at.% Cr, 10-20at.% Co, 3-10at.% Al, 1-5at.% W, 1-5at.% Mo, 1-5at.% Ti, the balance being Ni and unavoidable impurities.
5. The method as claimed in claim 1, wherein the specific process of the heat treatment of S3) is as follows:
s3.1) heating to 400-500 ℃ per minute at 10 ℃ in a vacuum environment, preserving the heat for 1-3 hours,
s3.2) heating to 1100-.
6. The method of claim 1, wherein the porosity of the repaired superalloy blade repair area is less than 0.5%, and the strength ratio between the base alloy connecting the joint portion and the superalloy blade is greater than or equal to 65%.
7. The method according to claim 3, wherein the Zr containing low melting point powder A has a particle size of less than 20 μm and the multi-principal element alloy powder B has a particle size of less than 106 μm.
8. The method as claimed in claim 1, wherein the ball milling in S1) is carried out in a stainless steel ball medium under a protective atmosphere of argon gas at 20-60 rpm for 2-12 hours.
9. The method according to claim 1, wherein the mass ratio of the mixed powder to the binding fluid in S2) is (5-20):1, and the mixing and stirring time is 3-30 minutes.
10. The method according to claim 9, wherein the bonding fluid comprises the following components in percentage by mass: 0.5-4wt.% polyvinylpyrrolidone, 0.5-4wt.% polyacrylamide, 0.1-1wt.% stearic acid, 30-45wt.% propanol and the balance ethanol.
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| CN103042338A (en) * | 2011-10-12 | 2013-04-17 | 河北农业大学 | Reaction nitrogen arc fusion covering wear-resistant coating manufacture process based on part remanufacture repairing |
| US20180304420A1 (en) * | 2017-04-20 | 2018-10-25 | Kennametal Inc. | Layered assemblies for superalloy article repair |
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