CN114669738A - Repair material for repairing gas turbine blade and repair method thereof - Google Patents

Repair material for repairing gas turbine blade and repair method thereof Download PDF

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Publication number
CN114669738A
CN114669738A CN202210255259.5A CN202210255259A CN114669738A CN 114669738 A CN114669738 A CN 114669738A CN 202210255259 A CN202210255259 A CN 202210255259A CN 114669738 A CN114669738 A CN 114669738A
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powder
repair
repairing
repair material
nickel
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CN114669738B (en
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刘烨
权方凯
章林
王天剑
高振桓
李清松
陈旭
曲选辉
秦明礼
陈刚
张百成
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University of Science and Technology Beijing USTB
Xiangtan University
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University of Science and Technology Beijing USTB
Xiangtan University
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    • 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
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/1035—Liquid phase sintering
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • 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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • 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
    • C22C19/007—Alloys based on nickel or cobalt with a light metal (alkali metal Li, Na, K, Rb, Cs; earth alkali metal Be, Mg, Ca, Sr, Ba, Al Ga, Ge, Ti) or B, Si, Zr, Hf, Sc, Y, lanthanides, actinides, as the next major constituent
    • 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
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • 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
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
    • 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
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • 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
    • 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
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • B22F7/062—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts
    • B22F2007/068—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools involving the connection or repairing of preformed parts repairing articles

Abstract

The invention belongs to the research field of nickel-based superalloy blade repair, and relates to a repair material for repairing a gas turbine blade and a repair method thereof, wherein the repair material comprises the following components: the mass ratio is as follows: 5-20:1 of Hf-containing mixed powder and binding fluid, wherein the mixed powder comprises the following components in percentage by mass: 0.1-0.1:1 of Hf-containing low-melting-point powder and high-entropy alloy powder; coating the repairing material on the repairing position of the blade, and placing the blade in a vacuum furnace to complete the repairing process through heat treatment; the repair material provided by the invention not only improves the bonding firmness of the repair layer and the matrix, but also has few pores in the repair area, does not contain harmful phases with the size larger than 1 micron, has less influence on mechanical properties, can realize near-equal-strength or even equal-strength repair, has the advantages of low cost, wide applicability and strong flexibility, and can be adjusted and optimized randomly according to the size and the shape of the defect or the damaged part of the blade so as to achieve the purpose of efficiently repairing the blade of the heavy gas turbine.

Description

Repair material for repairing gas turbine blade and repair method thereof
Technical Field
The invention belongs to the field of research on turbine blade repair, and particularly provides a repair material for repairing a gas turbine blade and a repair method thereof, wherein the repair material is suitable for Mar-M247 alloy.
Background
The Mar-M247 high-temperature alloy has good high-temperature strength, oxidation resistance and corrosion resistance, excellent fatigue resistance and creep resistance, excellent fracture property and excellent structure stability, and is widely used for manufacturing hot-end parts such as high-temperature blades of heavy-duty gas turbines in recent decades. The high-temperature blade of the heavy-duty gas turbine is easy to generate corrosion, cracks, deformation and pit defects under the actions of abrasion, impact, high-temperature gas, cold and hot fatigue and the like for a long time, the manufacturing process of the gas turbine blade is complex and heavy, the raw material for preparing the blade is expensive, and the cost for manufacturing the gas turbine blade again is high. 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 repair method of the high-temperature blade of the heavy-duty gas turbine mainly comprises a welding method and an instantaneous liquid phase connection repair method. The Mar-M247 high-temperature alloy contains more Al and Ti, and when the Mar-M247 high-temperature alloy is repaired by a welding method, a welding seam and a heat affected zone are easy to generate hot cracks, so that the weldability of the alloy is poor, and the repairing effect by the welding method is poor. And the Transient liquid phase bonding (TLP) method uses the intermediate layer to melt and wet the surface of the filling blade to be repaired in the heat preservation process. In the process of contacting with the parent metal, the middle layer liquid phase melts part of the parent metal to complete connection, and finally the liquid phase disappears through isothermal solidification, and the tissues of the repair area are gradually homogenized to complete the repair process. The instantaneous liquid phase connection technology integrates the advantages of simplicity and convenience of a high-temperature brazing method and high strength of solid diffusion connection, can simultaneously connect a plurality of workpieces and a plurality of welding seams, and is high in efficiency and low in cost.
However, in the transient liquid phase connection repair process, in order to ensure that the intermediate layer can be completely in a liquid phase at a lower temperature, more melting-reducing elements must be added, namely, the intermediate layer and the base material have larger difference in elemental composition and microstructure. If hafnium element is added into the intermediate layer material, the melting point of the alloy can be effectively reduced, and the mechanical property of the alloy can be effectively improved by adding a proper amount of hafnium element into the alloy. However, in order to meet the melting reduction requirement, more hafnium element must be added into the interlayer material, and the introduction of excessive hafnium 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 Ni7Hf2Intermetallic phases are formed at the repair zone and at the repair interface, resulting in reduced performance of the repaired blade. In addition, hafnium is expensive, and excessive use of hafnium will greatly increase repair costs.
Disclosure of Invention
The present invention is directed to a repair material for repairing a gas turbine blade and a repair method thereof to solve any of the above technical problems and other potential problems of the prior art.
In order to achieve the purpose, the invention adopts the technical scheme that: a repair material for repairing a gas turbine blade, the repair material comprising: hf-containing mixed powder and a binding fluid; the Hf-containing mixed powder comprises Hf-containing metal powder and nickel-based high-entropy alloy powder, the high-nickel-based high-entropy alloy powder is used as a framework to keep a solid state, a liquid phase formed by melting the Hf-containing metal powder is filled into a gap of the framework by using a bonding fluid as a carrier, and the framework is connected and combined with a base material on the surface of a Mar-M247 gas turbine blade to form a whole;
The mass ratio of the Hf-containing mixed powder to the binding fluid is as follows: (5-20):1.
Further, the mass ratio of the Hf-containing metal powder to the high-entropy alloy powder is as follows: (0.1-0.3):1.
Further, the mass percentages of the components in the Hf-containing metal powder are as follows: cr: 3-15wt.%, Co: 5-15wt.%, Al: 2-10wt.%, Ta: 1-8wt.%, Hf: 6-25) wt.%, the balance being Ni and unavoidable impurities;
the nickel-based high-entropy alloy powder comprises the following components in atomic percentage: 8-25at.% Cr, 8-25at.% Co, 8-20at.% Al, 1-10at.% W, 1-4at.% Ta, with the balance being Ni and unavoidable impurities.
Further, the mass percentages of the components of the Hf-containing metal powder are as follows: cr: 3-6wt.%, Co: 7-12wt.%, Al: 2-5wt.%, Ta: 1-3wt.%, Hf: 12-20wt.%, the balance Ni and unavoidable impurities;
the nickel-based high-entropy alloy powder comprises the following components in atomic percentage: cr: 10-20at.%, Co: 10-20at.%, Al: 10-15at.%, W: 1-6at.%, Ta: 1-2at.%, the balance being Ni and unavoidable impurities.
Further, the mass percentages of the components of the bonding fluid are as follows: 0.5-8wt.% polyvinylpyrrolidone, 0.1-1wt.% stearic acid, 0.1-1wt.% triethanolamine, 30-45wt.% propanol, and the balance ethanol.
Furthermore, the particle diameter of the Hf-containing metal powder is 53-106 μm, and the powder particle diameter of the nickel-based high-entropy alloy powder is 53-106 μm.
Another object of the present invention is to provide a repair method for repairing a gas turbine blade using the above repair material, the method specifically including the steps of:
s1) respectively weighing Hf-containing metal powder and nickel-based high-entropy alloy powder, and uniformly mixing the Hf-containing metal powder and the nickel-based high-entropy alloy powder to obtain mixed powder for later use;
s2) preparing a bonding fluid;
s3) uniformly mixing the mixed powder of S1) and the bonding fluid obtained from S2) to obtain a gelled repair material, coating the gelled repair material on the to-be-repaired position of the gas turbine blade, and placing the gas turbine blade in a vacuum furnace to be subjected to heat treatment to finish repairing.
Further, the step S1) includes the following steps:
s1.1) respectively calling Hf-containing metal powder and nickel-based high-entropy alloy powder,
s1.2) dissolving Hf-containing metal powder A and high-entropy alloy powder B in alcohol according to the mass ratio of (0.1-0.3) to 1, and mixing for 2-12 hours at the rotating speed of 20-60 r/min by taking a stainless steel ball as a medium and argon as a protective atmosphere to obtain uniformly mixed powder.
Further, the specific steps of S3) are:
S3.1) mixing and stirring the Hf-containing mixed powder and the binding fluid according to the mass ratio of (5-20) to 1 for 3-30 minutes to obtain the binding fluid, adding the mixed powder and stirring to obtain the gelled repair material,
s3.2) placing the nickel-based superalloy blade coated with the gelled repair material in a vacuum degree of 1 x 10-3Under Pa, firstly heating to 400-500 ℃, and preserving heat for 1-3 hours;
then heating to 1000-1250 ℃, preserving the heat for 1-3 hours, cooling to 700-900 ℃ along with the furnace temperature, and then introducing argon to rapidly cool to the room temperature.
Furthermore, the porosity of the repaired area of the repaired gas turbine blade is less than 0.5%, and the strength ratio between the connecting joint part and the base metal alloy is not less than 65%.
The defect of the transient liquid phase linking method can be effectively improved by repairing the turbine blade by using the powder metallurgy method. 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 repairing process is completed through isothermal solidification and gradual homogenization of high-temperature diffusion tissues. 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 process of repairing the turbine blade by the powder metallurgy method, the addition of hafnium element in the low-melting point powder can ensure the appearance of liquid phase in the repairing process. 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 the high-entropy alloy in recent years provides a new idea for repairing Mar-M247 high-temperature alloy turbine blades by a powder metallurgy method. High entropy alloys composed of three or more metal elements in equimolar or near equimolar combinations have received wide attention from various industries due to their 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 component alloy, the effective diffusion rate of the high-entropy alloy is greatly reduced. Therefore, the patent provides a material and a method for repairing the turbine blade of the heavy-duty gas turbine, wherein the material comprises the following components: the high-entropy alloy powder is used as high-melting-point component powder in the repair turbine blade by a powder metallurgy method, the diffusion of low-melting-point elements in a liquid phase is delayed through reasonable component design, the flowing time of the liquid phase is increased, the introduction of melting-point elements in the repair process is reduced, the precipitation of harmful phases in the repair area is effectively inhibited, and the mechanical property of the repair turbine blade is improved.
Mar-M247 is a mark of nickel-based superalloy, and the mark comprises the following components in percentage by mass: 0.15wt.% C, 8.0 wt.% Cr, 0.6 wt.% Mo, 1 wt.% Ti, 10.0wt.% Co, 10.0wt.% W, 3.0wt.% Ta, 5.5wt.% Al, 1.5wt.% Hf, 0.015wt.% B, 0.03 wt.% Zr, the balance being Ni.
The invention has the advantages and beneficial effects that:
1. the invention provides a novel repair material and a repair method for repairing the surface defects of the Mar-M247 gas turbine blade, and provides a new idea for the near and equal strength repair of the blade;
2. the repairing layer and the substrate are combined firmly, the pores of the repairing area are few, harmful phases with the size larger than 1 micron are not contained, the influence on the mechanical property is less, and near-equal-strength or even equal-strength repairing can be realized. The cost is low;
3. the repair material and the repair method provided by the invention have wide applicability and strong flexibility, and can be adjusted and optimized randomly according to the size and the shape of the defect or the damaged part of the blade so as to achieve the aim of efficiently repairing the blade of the heavy-duty gas turbine.
Drawings
FIG. 1 is a block flow diagram of a method of repairing a repair material for superalloy blade repair in accordance with the present invention.
FIG. 2 is a microstructure diagram of a repaired area repaired by the repair material and the repair method of the present invention.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings and specific embodiments.
The present invention is a repair material for repairing a gas turbine blade, the repair material comprising: hf-containing mixed powder and a binding fluid; the Hf-containing mixed powder comprises Hf-containing metal powder and nickel-based high-entropy alloy powder, the high-nickel-based high-entropy alloy powder is used as a framework to keep a solid state, a liquid phase formed by melting the Hf-containing metal powder is filled into a gap of the framework by using a bonding fluid as a carrier, and the framework is connected and combined with a base material on the surface of a Mar-M247 gas turbine blade to form a whole;
the mass ratio of the Hf-containing mixed powder to the binding fluid is as follows: (5-20):1.
The mass ratio of the Hf-containing metal powder to the high-entropy alloy powder is as follows: (0.1-0.3):1.
Further, the mass percentages of the components in the Hf-containing metal powder are as follows: cr: 3-15wt.%, Co: 5-15wt.%, Al: 2-10wt.%, Ta: 1-8wt.%, 6-25wt.% of Hf, and the balance of Ni and unavoidable impurities;
the nickel-based high-entropy alloy powder comprises the following components in atomic percentage: 8-25at.% Cr, 8-25at.% Co, 8-20at.% Al, 1-10at.% W, 1-4at.% Ta, with the balance being Ni and unavoidable impurities.
The mass percentages of all components of the Hf-containing metal powder are as follows: cr: 3-6wt.%, Co: 7-12wt.%, Al: 2-5wt.%, Ta: 1-3wt.%, Hf: 12-20wt.%, the balance Ni and unavoidable impurities;
the nickel-based high-entropy alloy powder comprises the following components in atomic percentage: cr: 10-20at.%, Co: 10-20at.%, Al: 10-15at.%, W: 1-6at.%, Ta: 1-2at.%, the balance being Ni and unavoidable impurities.
The mass percentages of the components of the bonding fluid are as follows: 0.5-8wt.% polyvinylpyrrolidone, 0.1-1wt.% stearic acid, 0.1-1wt.% triethanolamine, 30-45wt.% propanol, and the balance ethanol.
The particle size of the Hf-containing metal powder is 53-106 mu m, and the powder particle size of the nickel-based high-entropy alloy powder is 53-106 mu m.
Another object of the present invention is to provide a repair method for repairing a gas turbine blade using the above repair material, the method specifically including the steps of:
s1) respectively weighing Hf-containing metal powder and nickel-based high-entropy alloy powder, and uniformly mixing the Hf-containing metal powder and the nickel-based high-entropy alloy powder to obtain mixed powder for later use;
s2) preparing a bonding fluid;
s3) uniformly mixing the mixed powder of S1) and the bonding fluid obtained from S2) to obtain a gelled repair material, coating the gelled repair material on the to-be-repaired position of the gas turbine blade, and placing the gas turbine blade in a vacuum furnace to be subjected to heat treatment to finish repairing.
The S1) obtaining specific steps comprises:
s1.1) respectively weighing Hf-containing metal powder and nickel-based high-entropy alloy powder,
s1.2) dissolving Hf-containing metal powder A and high-entropy alloy powder B in alcohol according to the mass ratio of (0.1-0.3) to 1, and mixing for 2-12 hours at the rotating speed of 20-60 r/min by taking a stainless steel ball as a medium and argon as a protective atmosphere to obtain uniformly mixed powder.
The S3) comprises the following specific steps:
s3.1) mixing and stirring the Hf-containing mixed powder and the binding fluid according to the mass ratio of (5-20) to 1 for 3-30 minutes to obtain the binding fluid, adding the mixed powder and stirring to obtain the gelled repair material,
s3.2) placing the nickel-based superalloy blade coated with the gelled repair material in a vacuum degree of 1 x 10-3Under Pa, firstly heating to 400-500 ℃, and preserving heat for 1-3 hours;
then heating to 1000-1250 ℃, preserving the heat for 1-3 hours, cooling to 700-900 ℃ along with the furnace temperature, and then introducing argon to rapidly cool to the room temperature.
The porosity of the repaired area of the repaired gas turbine blade is less than 0.5%, and the strength ratio between the connecting joint part and the base metal alloy is not less than 65%.
Example 1:
mixing a powder A with the components of Ni-4wt.% Cr-8wt.% Co-2wt.% Al-1wt.% Ta-12wt.% Hf and a powder B with the components of Ni-20at.% Cr-20at.% Co-20at.% Al-1.5at.% W-1at.% Ta in a mass ratio of 0.3:1, dissolving in an appropriate amount of alcohol, mixing with a stainless steel ball as a medium and argon as a protective atmosphere at a rotating speed of 60 revolutions per minute for 12 hours. Adding a binding fluid with the component ratio of 0.5wt.% of PVP, 0.1wt.% of SA, 0.1wt.% of TEOA, 45wt.% of propyl alcohol and the balance of ethanol into the mixed powder, and stirring for 3 minutes to obtain the repairing material, wherein the mass ratio of the mixed powder to the binding fluid in the repairing material is 5: 1. After the repairing material is coated on a Mar-M247 blade to be repaired, the blade is placed in a vacuum furnace, heat preservation is carried out for 3 hours at 450 ℃, then heat preservation is carried out for 3 hours at 1250 ℃, argon is introduced into the furnace to cool the blade to 900 ℃ along with the furnace temperature, the blade is cooled to room temperature to complete the repairing process, as shown in a repairing area microstructure diagram shown in figure 2, the grain boundary of a repairing area is clean, no obvious tissue non-uniformity phenomenon exists, the repaired repairing area is made into a tensile member, the tensile strength at room temperature is 551MPa, and the tensile strength reaches more than 65% of the strength of a base material.
Example 2:
mixing a powder A with the components of Ni-6wt.% Cr-10wt.% Co-3wt.% Al-1.5wt.% Ta-14wt.% Hf and a powder B with the components of Ni-25at.% Cr-10at.% Co-20at.% Al-10at.% W-1.5at.% Ta in a mass ratio of 0.25:1, dissolving in an appropriate amount of alcohol, mixing at a rotation speed of 60 revolutions per minute for 4 hours by using a stainless steel ball as a medium and argon as a protective atmosphere. Adding a binding fluid which comprises 2wt.% of PVP, 0.3wt.% of SA, 0.4wt.% of TEOA, 40wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 10 minutes to obtain the repairing material, wherein the mass ratio of the mixed powder to the binding fluid in the repairing material is 9: 1. After the repairing material is coated on a position, needing to be repaired, of the Mar-M247 blade, the blade is placed in a vacuum furnace, the temperature is kept for 1 hour at 500 ℃, then the temperature is kept for 2 hours at 1200 ℃, the repairing material is cooled to 850 ℃ along with the temperature of the furnace, then argon is introduced to rapidly cool the repairing material 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 563MPa, and the tensile strength reaches more than 70% of the strength of a base material.
Example 3:
mixing a powder A with the components of Ni-9wt.% Cr-12wt.% Co-4wt.% Al-2wt.% Ta-16wt.% Hf and a powder B with the components of Ni-15at.% Cr-20at.% Co-20at.% Al-6at.% W-1.8wt.% Ta in a 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 6 hours. Adding a binding fluid which comprises 4wt.% of PVP, 0.6wt.% of SA, 0.8wt.% of TEOA, 40wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 15 minutes to obtain the repairing material, wherein the mass ratio of the mixed powder to the binding fluid in the repairing material is 12: 1. After the repairing material is coated on a position, needing to be repaired, of the Mar-M247 blade, the blade is placed in a vacuum furnace, the temperature is kept for 2 hours at 500 ℃, then the temperature is kept for 2 hours at 1230 ℃, the repairing material is cooled to 870 ℃ along with the temperature of the furnace, then argon is introduced to the furnace to rapidly cool the repairing material to room temperature, the repairing area after repairing is manufactured into a tensile piece, the tensile strength at the room temperature is measured to be 589MPa, and the tensile strength reaches more than 70% of the strength of a base material.
Example 4:
mixing powder A with the components of Ni-10wt.% of Cr-14wt.% of Co-5wt.% of Al-3wt.% of Ta-20wt.% of Hf and powder B with the components of Ni-18at.% of Cr-18at.% of Co-18at.% of Al-8at.% of W-2at.% of Ta in a mass ratio of 0.1:1, dissolving the mixture in an appropriate amount of alcohol, and mixing the mixture for 12 hours at a rotation speed of 20 revolutions per minute by using a stainless steel ball as a medium and argon as a protective atmosphere. Adding a binding fluid which comprises 8wt.% of PVP, 1wt.% of SA, 1wt.% of TEOA, 45wt.% of propanol and the balance of ethanol into the mixed powder, and stirring for 30 minutes to obtain a repairing material, wherein the mass ratio of the mixed powder to the binding fluid in the repairing material is 20: 1. Coating the repairing material on a position of a Mar-M247 blade to be repaired, placing the blade in a vacuum furnace, preserving heat for 3 hours at 500 ℃, then preserving heat for 3 hours at 1080 ℃, cooling to 700 ℃ along with the temperature of the furnace, introducing argon, and rapidly cooling to room temperature to finish the repairing process, manufacturing a repaired repairing area into a tensile piece, and measuring the tensile strength at the room temperature to be 524MPa and reach more than 65% of the strength of a 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 repair material for repairing a gas turbine blade, the repair material comprising: hf-containing mixed powder and a binding fluid; the Hf-containing mixed powder comprises Hf-containing metal powder and nickel-based high-entropy alloy powder, the high-nickel-based high-entropy alloy powder is used as a framework to keep a solid state, a liquid phase formed by melting the Hf-containing metal powder is filled into a gap of the framework by using a bonding fluid as a carrier, and the framework is connected and combined with a base material on the surface of a Mar-M247 gas turbine blade to form a whole;
the mass ratio of the Hf-containing mixed powder to the binding fluid is (5-20): 1.
2. The repair material according to claim 1, wherein the mass ratio between the Hf-containing metal powder and the nickel-based high-entropy alloy powder is (0.1-0.3): 1.
3. The repair material of claim 2, wherein the mass percentages of the components in the Hf-containing metal powder are: cr: 3-15wt.%, Co: 5-15wt.%, Al: 2-10wt.%, Ta: 1-8wt.%, Hf: 6-25) wt.%, the balance being Ni and unavoidable impurities;
the nickel-based high-entropy alloy powder comprises the following components in atomic percentage: 8-25at.% Cr, 8-25at.% Co, 8-20at.% Al, 1-10at.% W, 1-4at.% Ta, with the balance being Ni and unavoidable impurities.
4. The repair material of claim 2, wherein the mass percentages of the components of the Hf-containing metal powder are: cr: 3-6wt.%, Co: 7-12wt.%, Al: 2-5wt.%, Ta: 1-3wt.%, Hf: 12-20wt.%, the balance Ni and unavoidable impurities;
the nickel-based high-entropy alloy powder comprises the following components in atomic percentage: cr: 10-20at.%, Co: 10-20at.%, Al: 10-15at.%, W: 1-6at.%, Ta: 1-2at.%, the balance being Ni and unavoidable impurities.
5. The repair material of claim 1, wherein the adhesive fluid comprises the following components in percentage by mass: 0.5-8wt.% polyvinylpyrrolidone, 0.1-1wt.% stearic acid, 0.1-1wt.% triethanolamine, 30-45wt.% propanol, and the balance ethanol.
6. The repair material according to claim 2, wherein the particle size of the Hf-containing metal powder A is 53-106 μm, and the powder particle size of the high-entropy alloy powder B is 53-106 μm.
7. A method for repairing a gas turbine blade using the repair material according to any one of claims 1 to 6, said method comprising in particular the steps of:
s1) respectively weighing Hf-containing metal powder and nickel-based high-entropy alloy powder, and uniformly mixing the Hf-containing metal powder and the nickel-based high-entropy alloy powder to obtain mixed powder for later use;
S2) preparing a bonding fluid;
s3) uniformly mixing the mixed powder of S1) and the bonding fluid obtained from S2) to obtain a gelled repair material, coating the gelled repair material on the to-be-repaired position of the gas turbine blade, and placing the gas turbine blade in a vacuum furnace to be subjected to heat treatment to finish repairing.
8. The method as claimed in claim 7, wherein the step of S1) is as follows:
s1.1) respectively calling Hf-containing metal powder and nickel-based high-entropy alloy powder,
s1.2) dissolving Hf-containing metal powder and nickel-based high-entropy alloy powder in an alcohol according to the mass ratio of (0.1-0.3) to 1, mixing for 2-12 hours at the rotating speed of 20-60 r/min by taking a stainless steel ball as a medium and argon as a protective atmosphere to obtain uniformly mixed powder.
9. The method as claimed in claim 7, wherein the specific steps of S3) are:
s3.1) mixing and stirring the Hf-containing mixed powder and the binding fluid according to the mass ratio of (5-20) to 1 for 3-30 minutes to obtain the binding fluid, adding the mixed powder and stirring to obtain the gelled repair material,
s3.2) placing the nickel-based superalloy blade coated with the gelled repair material in a vacuum degree of 1 x 10-3Under Pa, firstly heating to 400-500 ℃, and preserving heat for 1-3 hours;
Then heated to 1000-1250 ℃ and insulated for 1-3 hours, cooled to 700-900 ℃ along with the furnace temperature, and then quickly cooled to room temperature by introducing argon.
10. The method of claim 7, wherein the repaired gas turbine blade has a repair zone porosity of <0.5% and a strength ratio between the connection joint and the base metal alloy of 65% or more.
CN202210255259.5A 2022-03-15 2022-03-15 Repairing material for repairing gas turbine blade and repairing method thereof Active CN114669738B (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116043066A (en) * 2022-12-21 2023-05-02 东方电气集团东方汽轮机有限公司 Low-diffusivity activation auxiliary agent, application thereof, repairing agent and preparation method and alloy repairing method thereof

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110423933A (en) * 2019-09-06 2019-11-08 中国航空制造技术研究院 A kind of bio-medical Ti-Zr-Hf-Nb-Ta system's high-entropy alloy and preparation method
KR102248760B1 (en) * 2019-11-27 2021-05-04 서울시립대학교 산학협력단 Bonding composition and bonding method using the same
KR102303704B1 (en) * 2020-04-03 2021-09-16 서울시립대학교 산학협력단 Lead free solder compositions and manufacturing method of the same

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110423933A (en) * 2019-09-06 2019-11-08 中国航空制造技术研究院 A kind of bio-medical Ti-Zr-Hf-Nb-Ta system's high-entropy alloy and preparation method
KR102248760B1 (en) * 2019-11-27 2021-05-04 서울시립대학교 산학협력단 Bonding composition and bonding method using the same
KR102303704B1 (en) * 2020-04-03 2021-09-16 서울시립대학교 산학협력단 Lead free solder compositions and manufacturing method of the same

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
张杰;王茂才;翟玉春;: "先进的燃气轮机叶片粉末冶金修复技术", 材料导报, no. 03, pages 110 - 113 *
聂丽萍;杨功显;巩秀芳;: "高温合金叶片修复技术的应用与发展", 东方汽轮机, no. 04, pages 55 - 59 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116043066A (en) * 2022-12-21 2023-05-02 东方电气集团东方汽轮机有限公司 Low-diffusivity activation auxiliary agent, application thereof, repairing agent and preparation method and alloy repairing method thereof

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