CN114669956B - Powder metallurgy repairing method for repairing defects of high-temperature alloy blade - Google Patents
Powder metallurgy repairing method for repairing defects of high-temperature alloy blade Download PDFInfo
- Publication number
- CN114669956B CN114669956B CN202210255276.9A CN202210255276A CN114669956B CN 114669956 B CN114669956 B CN 114669956B CN 202210255276 A CN202210255276 A CN 202210255276A CN 114669956 B CN114669956 B CN 114669956B
- Authority
- CN
- China
- Prior art keywords
- powder
- repairing
- melting
- blade
- repair
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Powder Metallurgy (AREA)
Abstract
The invention belongs to the field of research on repairing turbine blades, and provides a powder metallurgy repairing 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 under a protective atmosphere to obtain uniform mixed powder; mixing proper amount of ethanol, propanol, polyvinylpyrrolidone, polyacrylamide and stearic acid to obtain a bonding fluid; adding the obtained mixed powder into a bonding fluid, and uniformly stirring to obtain a gel repairing agent with fluidity and cohesiveness; and (3) coating the repairing agent on the defect to be repaired of the high-temperature alloy blade, and performing heat treatment in a vacuum furnace to finish the repair. The invention provides a new thought for manufacturing the turbine blade of the gas turbine by the Inconel738LC, and has the advantages of wide applicability, strong flexibility, arbitrary adjustment and optimization according to the size and shape of the defect or damaged part of the high-temperature alloy blade, and the like.
Description
Technical Field
The invention belongs to the field of research on repairing of turbine blades, and particularly provides a powder metallurgy repairing method suitable for repairing defects of a superalloy blade by repairing an Inconel738LC nickel-based superalloy.
Background
The Inconel738LC superalloy has excellent room temperature and high temperature mechanical properties, good structural stability, corrosion resistance and oxidation resistance, and is widely used for preparing long-life turbine working blades and guide blades of gas turbines. In the service process, the Inconel738LC high-temperature blade is subjected to the effects of abrasion, impact, cold and hot fatigue and the like for a long time, so that the corrosion, crack, deformation and pit defects are easy to generate, and the hidden trouble of major accidents is easy to become. The gas turbine blade manufacturing process is complex and heavy, and the raw materials for preparing the blade are expensive, so that the cost for remanufacturing the gas turbine blade is high. Therefore, if the defect and the damaged part can be repaired by adopting the repair technology, the performance of the defect and the damaged part can be recovered, the service life of the defect and the damaged part can be prolonged, and the defect repair method has great economic benefit.
The conventional repair method of the high-temperature blade of the heavy-duty gas turbine is fusion welding, brazing, diffusion welding and transient liquid phase connection repair method. Fusion welding is a method of joining materials by heating a welding wire and a region of a workpiece to be repaired 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 because the Inconel738LC superalloy contains higher content of Al and Ti elements, the gamma' phase close to the repair area is easy to change obviously, even microcracks are possibly generated, and the performance of the repaired blade is obviously reduced. In the conventional brazing, a brazing filler metal having a melting point lower than that of a base metal is generally used, and 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 melt and flow to fill a gap to be repaired, and the base metal is mutually diffused to form a metallurgical bonding diffusion layer. Conventional brazing generally pursues a low repair temperature while using a brazing filler metal having a composition greatly different from that of a base material, and the final brazing filler metal completes the repair process by temperature-variable solidification. Eventually, a very brittle eutectic structure tends to form in the welded area, resulting in reduced joint strength, hot corrosion resistance, and oxidation resistance. Diffusion welding is a technology for performing connection repair by using solid-phase diffusion, and the principle is that two solid-phase atoms on the surfaces of materials in contact with each other are used for performing solid-phase diffusion under the action of high temperature and high pressure to form a new diffusion layer at an interface, so that reliable connection is realized. However, diffusion welding has high cost and long time, and the size of repairable defects is limited.
Disclosure of Invention
The invention discloses a powder metallurgy repairing method for repairing defects of a superalloy blade, which aims to solve any one of the above and other potential problems in the prior art.
In order to achieve the above purpose, the technical scheme of the invention is as follows: a powder metallurgy repair method for repairing defects of a superalloy blade comprises the following steps,
s1) dissolving Zr-containing low-melting-point powder A and multi-principal-element alloy powder B in a solvent, and performing ball milling under a protective atmosphere to obtain uniform mixed powder;
s2) mixing proper amounts 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 repairing agent with fluidity and cohesiveness;
s4) coating the repairing agent obtained in the step S4) on the position to be repaired of the Inconel738LC nickel-based superalloy, and performing heat treatment in a vacuum furnace to finish the repair.
Further, the mass ratio of the Zr-containing low melting point powder A and the multi-component alloy powder B in the S1) is (0.1-0.3): 1.
Further, 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 atomic percentages of the components of the multi-principal alloy powder B are as follows: 8-25at.% Cr, 8-25at.% Co, 3-15at.% Al, 0.5-5at.% W, 0.5-5at.% Mo, 0.5-6at.% Ti, the balance Ni and unavoidable impurities.
Further, 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 Ni and unavoidable impurities,
the atomic percentages of the components of the multi-principal alloy powder B are as follows: 10-20at.% Cr, 10-20at.% Co, 3-10at.% Al, 1-5at.% W, 1-5at.% Mo, 1-5at.% Ti, the balance Ni and unavoidable impurities.
Further, the specific process of the heat treatment of S3) is as follows:
s3.1) in a vacuum environment, heating to 400-500 ℃ per minute at 10 ℃ and preserving heat for 1-3 hours,
s3.2) heating to 1100-1250 ℃ every minute at 5 ℃ for heat preservation for 1-3 hours, cooling to 700-900 ℃ along with furnace temperature, and then introducing argon for quick cooling.
Further, the porosity of the repaired area of the repaired Inconel738LC nickel-based superalloy is less than 0.5%, and the strength ratio between the connecting joint part and the base metal alloy is more than or equal to 65%.
Further, the particle size of the Zr-containing low melting point powder A is less than 20 mu m, and the particle size of the multi-principal alloy powder B is less than 106 mu m.
Further, the particle size of the Zr-containing low melting point powder A is 8-28 mu m, and the particle size of the multi-principal alloy powder B is 53-100 mu m.
Further, the ball milling in the step S1) takes stainless steel balls as a medium and argon as a protective atmosphere, and the mixture is mixed for 2 to 12 hours at the rotating speed of 20 to 60 revolutions per minute.
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 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.
Transient liquid phase joining (Transient liquid phase bonding, TLP) is a method of repairing by melting and wetting the filled blade during the insulation process using an intermediate layer. Compared with the conventional brazing method, the TLP method is mainly characterized in that the intermediate layer disappears in liquid phase by isothermal solidification to complete the repair process. Meanwhile, through subsequent heat treatment, the tissue of the repair area can be gradually homogenized, so that the tissue non-uniformity of the repair blade can be reduced 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, and can simultaneously connect a plurality of workpieces and a plurality of welding seams, thereby having high efficiency and low cost.
However, in the transient liquid phase connection repairing 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 element composition and microstructure. If zirconium element is added into the interlayer material, the melting point of the alloy can be effectively reduced, and the addition of a proper amount of zirconium element into the alloy can not only improve the binding force of the grain boundary to strengthen the grain boundary, but also improve the high-temperature strength of the alloy by entering a 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 tissue of the repair area. Although the intermediate layer and the base material elements in the vicinity can be homogenized by diffusion, eutectic structure and Ni that induce a gamma+gamma' phase are unavoidable 5 Zr、Ni 7 Zr 2 Intermetallic phases are generated inside the repair zone and at the repair zone/matrix interface, resulting in reduced blade performance after repair.
The powder metallurgy method is used for repairing the turbine blade, so that the defect of the transient liquid phase linking method can be effectively overcome. In the process of repairing the turbine blade by using the powder metallurgy method, a part of high-melting-point powder is used as a framework to keep solid, the other part of low-melting-point powder is melted, flows and fills the gaps of the framework, the liquid-phase dissolved framework and the surface layer of the base material are melted to finish connection, and then the structure is gradually homogenized by 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 repairing raw material in the repairing process, the repairing cost can be reduced by a powder metallurgy method, and the generation of harmful phases can be effectively reduced, so that higher strength after repairing can be obtained. In the process of repairing turbine blades by powder metallurgy, the addition of zirconium element in low melting point powder can ensure the appearance of liquid phase in the repairing process. However, if the composition of the powder raw material is improperly designed, the melting-reducing element is quickly lost in the repairing process, isothermal solidification occurs when the filling process is not completed, and finally, the repairing area has excessive pores, so that the repairing fails. Therefore, by reasonable design of repairing powder components, it is important to ensure that the liquid phase can exist for a sufficient time to complete the filling process on the premise of not increasing the harmful phase in the repairing area.
The development of high-entropy (multi-principal element) alloys in recent years has provided applicants with new ideas for repairing Inconel738LC superalloy turbine blades in a powder metallurgy process. The Inconel738LC is the brand of 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. High entropy (multi-principal element) alloys high entropy alloys, which are formed by combining three or more metal elements in equimolar ratios or near equimolar ratios, have received wide attention from various industries due to their extremely potential structural and functional applications. Particularly, the diffusion of high-entropy alloy caused by multi-principal component characteristics and serious lattice distortion needs to overcome the resistance caused by the cooperative diffusion of a plurality of components and lattice distortion. Therefore, the effective diffusion rate of the high-entropy alloy is greatly reduced compared with that of the traditional single principal element alloy. It is expected that the use of a high entropy alloy as the repair zone infusible powder skeleton may effectively reduce the diffusion rate between the liquid phase and the skeleton, thereby allowing sufficient flow of the liquid phase during repair, promoting particle rearrangement to promote densification of the repair zone. The method can reduce the consumption of low-melting-point powder to the maximum extent, so that the introduction of melting-point reducing elements in the repairing process can be reduced, thereby effectively inhibiting the precipitation of harmful phases in the repairing area and improving the mechanical properties of the repaired blade.
The invention has the advantages and beneficial effects that:
1. the invention provides a novel repair material and repair technology for repairing the surface defects of the gas turbine blade made of Inconel738LC and provides a novel thought for repairing the gas turbine blade.
2. The repairing layer is firmly combined with the matrix, and the content of the microstructure harmful phase is low. Since the low-melting powder is added in a small amount, even if a very small amount of nickel-zirconium intermetallic compound is formed, the mechanical properties of the blade, particularly the low cycle fatigue properties, are less affected.
3. The repairing material and the repairing method provided by the invention have the advantages of low cost, wide applicability and strong flexibility, and can be used for repairing most of blade defects or damages.
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 described below with reference to the accompanying drawings and specific implementation.
As shown in fig. 1, the powder metallurgy repairing method for repairing defects of a superalloy blade according to the present invention comprises the steps of,
s1) dissolving Zr-containing low-melting-point powder A and multi-principal-element alloy powder B in a solvent, and performing ball milling under a protective atmosphere to obtain uniform mixed powder;
s2) mixing proper amounts 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 repairing agent with fluidity and cohesiveness;
s4) coating the repairing agent obtained in the step S4) on the position to be repaired of the Inconel738LC nickel-based superalloy, and performing 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 alloy powder B in the S1) is (0.1-0.3): 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 atomic percentages of the components of the multi-principal alloy powder B are as follows: 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 Ni and unavoidable impurities,
the atomic percentages of the components of the multi-principal alloy powder B are as follows: 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 the diffusion of Zr-containing low-melting elements is reduced by the action of multi-principal element powder.
The specific process of the heat treatment of the S3) is as follows:
s3.1) in a vacuum environment, heating to 400-500 ℃ per minute at 10 ℃ and preserving heat for 1-3 hours,
s3.2) heating to 1100-1250 ℃ every minute at 5 ℃ for 1-3 hours, cooling to 700-900 ℃ along with furnace temperature, introducing argon gas for quick cooling, adjusting the morphology and the size of a precipitated phase, and increasing the tissue stability.
The porosity of the repaired area of the repaired Inconel738LC nickel-based superalloy is less than 0.5%, and the joint part 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 smaller than 20 mu m, and the grain diameter of the multi-principal alloy powder B is smaller than 106 mu m.
The grain size of the Zr-containing low-melting-point powder A is 8-28 mu m, and the grain size of the multi-principal alloy powder B is 53-100 mu m.
And (2) ball milling in the step (1) is carried out by taking a stainless steel ball as a medium and argon as a protective atmosphere, and mixing for 2-12 hours at the rotating speed of 20-60 r/min, so that Zr-containing low-melting-point powder A and multi-principal-element alloy powder B are uniformly mixed.
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 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:
powder A containing Ni-8wt.% Cr-4wt.% Co-1wt.% Al-2wt.% Ti-1wt.% W-1wt.% Mo-13wt.% Zr and powder B containing Ni-15at.% Cr-15at.% Co-3at.% Al-1at.% W-1at.% Mo-1at.% Ti are mixed in a mass ratio of 0.1:1 and dissolved in a proper amount of alcohol, and mixed for 8 hours under a rotation speed of 60 revolutions per minute with stainless steel balls as a medium and argon as a protective atmosphere. Adding 4wt.% PVP, 4wt.% PAM, 1wt.% SA, 45wt.% propanol and the balance 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 adhesive fluid in the repairing agent is 20:1. After the repairing agent is coated on a place where the Inconel738LC blade needs to be repaired, placing the blade in a vacuum furnace, firstly heating to 500 ℃ at 10 ℃ per minute, preserving heat for 3 hours, heating to 1120 ℃ at 5 ℃ per minute, preserving heat for 3 hours, cooling to 700 ℃ along with furnace temperature, introducing argon gas, rapidly cooling to room temperature, completing the repairing process, manufacturing the repaired repairing area into a stretched piece, measuring that the room temperature tensile strength is 683MPa, and reaching more than 65% of the base metal strength.
Example 2:
powder A containing Ni-12wt.% Cr-5wt.% Co-2wt.% Al-3wt.% Ti-2wt.% W-2wt.% Mo-10wt.% Zr and powder B containing Ni-18at.% Cr-18at.% Co-6at.% Al-2at.% W-2at.% Mo-2at.% Ti are mixed in a mass ratio of 0.15:1 and dissolved in a proper amount of alcohol, and mixed for 6 hours under a rotation speed of 50 revolutions per minute with stainless steel balls as a medium and argon as a protective atmosphere. Adding 3wt.% PVP, 2.5wt.% PAM, 0.8wt.% SA, 40wt.% propanol and the balance 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 adhesive fluid in the repairing agent is 16:1. After the repairing agent is coated on the place where the Inconel738LC blade needs to be repaired, the blade is placed in a vacuum furnace, the temperature is firstly increased to 450 ℃ per minute for 2 hours, then the temperature is increased to 1150 ℃ per minute for 2 hours, the furnace temperature is cooled to 760 ℃, argon is introduced for quick cooling to room temperature to complete the repairing process, the repaired repairing area is manufactured into a stretched piece, the room temperature tensile strength is measured to be 692MPa, and the strength of the parent metal is more than 65%.
Example 3:
powder A containing Ni-15wt.% Cr-5.5wt.% Co-3wt.% Al-3wt.% Ti-2.5wt.% W-2.5wt.% Mo-6wt.% Zr and powder B containing Ni-20at.% Cr-20at.% Co-8at.% Al-3at.% W-3at.% Mo-3at.% Ti are mixed in a mass ratio of 0.2:1 and dissolved in a proper amount of alcohol, and mixed for 4 hours at a rotation speed of 40 revolutions per minute with stainless steel balls as a medium and argon as a protective atmosphere. Adding binding fluid with the component ratio of 2wt.% PVP, 1.5wt.% PAM, 0.5wt.% SA, 40wt.% propanol and the balance 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 the place where the Inconel738LC blade needs to be repaired, the blade is placed in a vacuum furnace, the temperature is firstly increased to 480 ℃ for 3 hours at 10 ℃ per minute, then the temperature is increased to 1180 ℃ for 2 hours at 5 ℃ per minute, the repairing agent is cooled to 840 ℃ along with the furnace temperature, argon is introduced for quick cooling to room temperature, the repairing area after repairing is manufactured into a stretched piece, the room temperature tensile strength is measured to be 679MPa, and the strength of the parent metal is up to more than 65%.
Example 4:
powder A containing Ni-16wt.% Cr-6wt.% Co-3wt.% Al-3wt.% Ti-3wt.% W-3wt.% Mo-4wt.% Zr and powder B containing Ni-25at.% Cr-25at.% Co-10at.% Al-5at.% Mo-5at.% Ti are mixed in a mass ratio of 0.3:1 and dissolved in a proper amount of alcohol, and mixed for 2 hours under a rotating speed of 30 revolutions per minute with stainless steel balls as a medium and argon as a protective atmosphere. Adding binding fluid with the component ratio of 0.5wt.% PVP, 0.5wt.% PAM, 0.1wt.% SA, 30wt.% propanol and the balance 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. After the slurry is coated on a place where the Inconel738LC blade needs to be repaired, placing the blade in a vacuum furnace, heating to 500 ℃ per minute for 2 hours at first, heating to 1250 ℃ for 2 hours at first, cooling to 880 ℃ along with the furnace temperature, introducing argon gas, rapidly cooling to room temperature, completing the repair process, manufacturing the repaired repair area into a tensile piece, measuring that the room temperature tensile strength is 685MPa, and reaching more than 65% of the base metal strength.
The foregoing is a further detailed description of the invention in connection with specific preferred embodiments, and is not intended to limit the practice of the invention to such description. It will be apparent to those skilled in the art that several simple deductions and substitutions can be made without departing from the spirit of the invention, and these are considered to be within the scope of the invention.
Claims (6)
1. A powder metallurgy repair method for repairing defects of a high-temperature alloy blade is characterized by comprising the following steps of S1) dissolving Zr-containing low-melting-point powder A and multi-principal alloy powder B in a solvent, and performing ball milling under a protective atmosphere to obtain uniform mixed powder; the ball milling is carried out by taking a stainless steel ball as a medium and argon as a protective atmosphere, and mixing is carried out for 2-12 hours at the rotating speed of 20-60 r/min;
the mass ratio of the Zr-containing low-melting-point powder A to the multi-principal alloy powder B is (0.1-0.3) 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 atomic percentages of the components of the multi-principal alloy powder B are as follows: 8-25at.% Cr, 8-25at.% Co, 3-15at.% Al, 0.5-5at.% W, 0.5-5at.% Mo, 0.5-6at.% Ti, the balance Ni and unavoidable impurities;
s2) mixing proper amounts of ethanol, propanol, polyvinylpyrrolidone, polyacrylamide and stearic acid to obtain a bonding fluid;
the mass ratio of the mixed powder to the bonding fluid is (5-20) 1, and the mixing and stirring time is 3-30 minutes;
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 repairing agent with fluidity and cohesiveness;
s4) coating the repairing agent obtained in the step S4) on the defect to be repaired of the high-temperature alloy blade, and performing heat treatment in a vacuum furnace to complete the repair.
2. The method according to claim 1, wherein the Zr-containing low-melting powder a comprises the following components in mass percent: 8-16wt.% Cr, 4-6wt.% Co, 1-3wt.% Al, 1-3wt.% Ti, 1-3wt.% W, 1-2wt.% Mo, 3-13wt.% Zr, the balance Ni and unavoidable impurities,
the atomic percentages of the components of the multi-principal alloy powder B are as follows: 10-20at.% Cr, 10-20at.% Co, 3-10at.% Al, 1-5at.% W, 1-5at.% Mo, 1-5at.% Ti, the balance Ni and unavoidable impurities.
3. The method according to claim 1, wherein the specific process of the heat treatment of S3) is:
s3.1) heating to 400-500 ℃ in a vacuum environment at 10 ℃ per minute, and preserving heat for 1-3 hours;
s3.2) heating to 1100-1250 ℃ every minute at 5 ℃, preserving heat for 1-3 hours, cooling to 700-900 ℃ along with the furnace temperature, and then introducing argon for quick cooling.
4. The method of claim 1, wherein the repaired superalloy blade repair zone has a porosity of <0.5% and a strength ratio between the joint portion and the superalloy blade parent metal alloy of greater than or equal to 65%.
5. The method according to claim 1, wherein the Zr-containing low-melting powder a has a particle size of less than 20 μm and the multi-principal alloy powder B has a particle size of less than 106 μm.
6. The method of claim 1, wherein the mass percentages of the components of the bonding fluid are: 0.5-4wt.% polyvinylpyrrolidone, 0.5-4wt.% polyacrylamide, 0.1-1wt.% stearic acid, 30-45wt.% propanol, the balance being ethanol.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210255276.9A CN114669956B (en) | 2022-03-15 | 2022-03-15 | Powder metallurgy repairing method for repairing defects of high-temperature alloy blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210255276.9A CN114669956B (en) | 2022-03-15 | 2022-03-15 | Powder metallurgy repairing method for repairing defects of high-temperature alloy blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114669956A CN114669956A (en) | 2022-06-28 |
| CN114669956B true CN114669956B (en) | 2023-06-02 |
Family
ID=82073299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210255276.9A Active CN114669956B (en) | 2022-03-15 | 2022-03-15 | Powder metallurgy repairing method for repairing defects of high-temperature alloy blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114669956B (en) |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102717224B (en) * | 2011-07-18 | 2015-05-20 | 王茂才 | Method for conducting powder sintering and forming and restoring to large blade gap defects of gas turbine |
| US10967466B2 (en) * | 2017-04-20 | 2021-04-06 | Kennametal Inc. | Layered assemblies for superalloy article repair |
-
2022
- 2022-03-15 CN CN202210255276.9A patent/CN114669956B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN114669956A (en) | 2022-06-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109420862B (en) | Powder brazing filler metal for nickel-based single crystal superalloy connection and preparation method and application thereof | |
| CN109909641B (en) | Cobalt-based powder brazing filler metal for high-temperature alloy connection and preparation method and application thereof | |
| CN114703472B (en) | Method for repairing nickel-based superalloy based on isothermal solidification principle | |
| CN110355496B (en) | High-temperature-resistant solder for gamma-TiAl alloy and brazing process | |
| CN110666328B (en) | Diffusion welding method for cast high-temperature alloy and martensitic stainless steel | |
| CN112853154B (en) | Nickel-based intermediate layer alloy material, preparation method thereof, weldment, welding method and application | |
| CN114310033B (en) | Activating diffusion agent and application thereof | |
| CN114669738B (en) | Repairing material for repairing gas turbine blade and repairing method thereof | |
| CN114669820B (en) | Repairing agent and repairing process for high-temperature alloy blade | |
| CN113941798A (en) | Nickel-based alloy brazing material for high-temperature structural material and application thereof | |
| CN113857715B (en) | Preformed solder block for repairing service defects of Hastelloy X high-temperature alloy component and preparation method thereof | |
| CN114669956B (en) | Powder metallurgy repairing method for repairing defects of high-temperature alloy blade | |
| CN110900037B (en) | Brazing filler metal and method for welding molybdenum-rhenium alloy and steel | |
| CN114632990B (en) | Repair process for repairing defects of high-temperature alloy blade | |
| CN114378477B (en) | Mixed powder solder and preparation method thereof, welding interlayer and welding method | |
| CN114632991A (en) | Repair process for repairing gas turbine blade based on powder metallurgy process | |
| CN109773370A (en) | Nano particle doped titanium-base solder and preparation method thereof | |
| CN114635056A (en) | High-temperature high-strength titanium alloy and additive preparation method thereof | |
| CN114571024B (en) | Vacuum brazing process for reducing corrosion of GH3536 honeycomb and GH4738 ring assembly | |
| CN114888388B (en) | Method for brazing titanium alloy and nickel-based superalloy | |
| CN115446495B (en) | Multielement high-entropy alloy brazing material for high-temperature alloy brazing connection | |
| CN113878259B (en) | Design method of solder suitable for full-layer structure titanium-aluminum alloy, solder and welding process | |
| CN115889756A (en) | Composite high-performance activation auxiliary powder for repairing nickel-based superalloy and repairing method and application thereof | |
| CN117535573A (en) | Co-Cr-Ni-Ti-W high-entropy alloy powder, preparation and cobalt-based superalloy repair method | |
| CN117344189A (en) | Activator, repairing agent and remodeling method for defective remodeling of blade injury |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |