CN112122617A - Laser additive repair method for high-performance monocrystalline directional crystal turbine blade - Google Patents
Laser additive repair method for high-performance monocrystalline directional crystal turbine blade Download PDFInfo
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- CN112122617A CN112122617A CN202010847324.4A CN202010847324A CN112122617A CN 112122617 A CN112122617 A CN 112122617A CN 202010847324 A CN202010847324 A CN 202010847324A CN 112122617 A CN112122617 A CN 112122617A
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- 239000013078 crystal Substances 0.000 title claims abstract description 45
- 238000000034 method Methods 0.000 title claims abstract description 45
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- 230000000996 additive effect Effects 0.000 title claims abstract description 42
- 230000008439 repair process Effects 0.000 title claims abstract description 29
- 238000004519 manufacturing process Methods 0.000 claims abstract description 23
- 238000001816 cooling Methods 0.000 claims abstract description 20
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 16
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229910000601 superalloy Inorganic materials 0.000 claims abstract description 10
- 238000004140 cleaning Methods 0.000 claims abstract description 8
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 8
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 3
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- 229910052751 metal Inorganic materials 0.000 description 1
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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
- 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
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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
- B22F3/24—After-treatment of workpieces or articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B33—ADDITIVE MANUFACTURING TECHNOLOGY
- B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
- B33Y10/00—Processes of additive manufacturing
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
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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
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/248—Thermal after-treatment
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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
- 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
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- 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
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Abstract
The invention discloses a laser additive repair method for a high-performance monocrystalline directional crystal turbine blade, which comprises the following steps of: 1) removing the damaged part of the turbine blade to be repaired by adopting a mechanical processing method; 2) polishing the surface of the part to be repaired by using sand paper, and cleaning the polished surface to be repaired by using acetone; 3) fixing the turbine blade to be repaired on a base with a cooling device through a clamp; 4) remelting the surface of the part to be repaired by adopting continuous pulse laser to obtain a uniform, fine and consistent-orientation crystalline structure; 5) and repairing the turbine blade layer by adopting a laser additive manufacturing process. 6) And after the additive manufacturing is finished, performing stress relief heat treatment. The method can effectively solve the problems of cracking and incapability of obtaining continuous oriented production organization in the repair process of the single crystal and oriented crystal nickel-based superalloy blade.
Description
[ technical field ] A method for producing a semiconductor device
The invention belongs to the technical field of laser processing of metal materials, and particularly relates to a laser additive repair method for a high-performance monocrystalline directional crystal turbine blade.
[ background of the invention ]
High performance turbine blades, particularly aircraft engines and gas turbines, have a large, conservative estimate of over 200 billion dollars per year today in the repair and maintenance market. Among these, the repair of the superalloy blades, a key core component, accounts for a significant proportion. The laser additive manufacturing technology has wide application prospect in the field of manufacturing and repairing turbine blades of aeroengines and gas turbines. At present, the laser additive manufacturing technology is gradually accepted by international aircraft engine manufacturers such as GE, P & W and Rolls-Royce and is applied to repair and manufacture of various blades. However, domestic research in this aspect is still not mature enough, and due to reasons of technical secrecy and technical blockade, it is also difficult to directly obtain equipment and related processes for blade additive manufacturing, so that the repair process for the blade is difficult to meet the repair requirements.
[ summary of the invention ]
The invention mainly aims to provide a laser additive repair method for a high-performance monocrystalline oriented crystal turbine blade, which can effectively solve the problems of cracking and incapability of obtaining continuous oriented production organization in the repair process of monocrystalline and oriented crystal nickel-based superalloy blades.
The invention realizes the purpose through the following technical scheme: a laser additive repair method for a high-performance single crystal oriented crystal turbine blade comprises the following steps:
1) removing the damaged part of the turbine blade to be repaired by adopting a mechanical processing method;
2) polishing the surface of the part to be repaired by using sand paper, and cleaning the polished surface to be repaired by using acetone;
3) fixing the turbine blade to be repaired on a base with a cooling device through a clamp;
4) remelting the surface of the part to be repaired by adopting continuous pulse laser to obtain a uniform, fine and consistent-orientation crystalline structure;
5) and repairing the turbine blade layer by adopting a laser additive manufacturing process.
6) And after the additive manufacturing is finished, performing stress relief heat treatment.
Further, in the step 2), the surface roughness Ra of the part to be repaired after surface treatment is 1-8 μm.
Further, in the step 2), acetone is used for cleaning for 1-3 times, and alcohol can be mixed for cleaning when the polished surface to be repaired is cleaned.
Further, in the step 4), continuous laser is adopted in the laser remelting process, and the process parameter range is as follows: the laser power P is 400-1200W, the diameter of a laser spot is 5-10 mm, the laser scanning speed is 30-150 mm/s, and the pulse frequency is 10-100 Hz.
Further, in the step 5), the additive used in the additive repairing process is nickel-based single crystal superalloy powder, and before laser remelting repairing, the powder is dried in a drying furnace to remove moisture in the powder, wherein the drying temperature is set to be 100-150 ℃, the temperature is kept for 60-180 min, and the granularity is 50-200 meshes.
Further, in the step 5), continuous laser is adopted in the additive repair process, and the process parameter range is as follows: the laser power is 100-2000W, the diameter of a light spot is 2-8 mm, the laser scanning speed is 20-300 m/s, the powder feeding speed is 1-30 g/min, the defocusing amount is-10-30 mm, and the interlayer thickness is 0.1-0.5 mm.
Furthermore, the cooling device adopts a water cooling mode.
Compared with the prior art, the laser additive repair method for the high-performance monocrystalline directional crystal turbine blade has the beneficial effects that: integrating a laser energy regulating system and a high-speed deposition head, and providing a process technology suitable for additive manufacturing and repairing of single crystals and directional blades to realize control on metallurgical defects and directional growth of tissues; the method has the characteristics of adjustable laser energy and high deposition speed, and provides methods and processes for repairing single crystals and directional blades, controlling metallurgical defects and tissue growth and the like.
[ description of the drawings ]
Fig. 1 is a schematic structural diagram of the additive repair according to the present invention;
FIG. 2 is a crystal structure diagram of the present invention after laser cladding and before directional growth;
FIG. 3 is a crystal structure diagram of the directional growth of the present invention.
[ detailed description ] embodiments
Referring to fig. 1 to fig. 3, a laser additive repair method for a high-performance single-crystal directional crystal turbine blade includes the following steps:
1) removing the damaged part of the turbine blade to be repaired by adopting a mechanical processing method;
2) polishing the surface of the part to be repaired by using sand paper, and cleaning the polished surface to be repaired by using acetone;
3) fixing the turbine blade to be repaired on the base with the cooling device 100 through a clamp;
4) remelting the surface of the part to be repaired by adopting continuous pulse laser to obtain a uniform, fine and consistent-orientation crystalline structure;
5) and repairing the turbine blade layer by adopting a laser additive manufacturing process.
6) And after the additive manufacturing is finished, performing stress relief heat treatment.
In the step 2), the surface roughness Ra of the part to be repaired after surface treatment is 1-8 μm. And cleaning with acetone for 1-3 times. When the polished part to be repaired is cleaned, alcohol can be mixed for cleaning.
In the step 4), continuous laser is adopted in the laser remelting process, and the process parameter range is as follows: the laser power P is 400-1200W, the diameter of a laser spot is 5-10 mm, the laser scanning speed is 30-150 mm/s, and the pulse frequency is 10-100 Hz.
The corresponding laser power is 1200W, the scanning speed is 60m/s, the laser spot is 6mm, the dendrite refinement marked by the dendrite refinement of nearly two orders of magnitude under the electronic scanning mirror, the periodic distance of alloy element segregation caused by solidification of the dendrite is shortened, the amplitude is reduced, compared with the coarse dendrite, the ratio of the content of certain element interdendrium and the content of the dendrite in the segregation coefficient is closer to 1, the distribution of the alloy element tends to be more uniform, and the surface quality of the alloy fused is improved.
In the step 5), the additive used in the additive repairing process is nickel-based single crystal superalloy powder, and before laser remelting repairing, the powder is dried in a drying furnace to remove water in the powder, wherein the drying temperature is set to be 100-150 ℃, the temperature is kept for 60-180 min, and the granularity is 50-200 meshes.
In the step 5), continuous laser is adopted in the additive repairing process, and the process parameter range is as follows: the laser power is 100-2000W, the diameter of a light spot is 2-8 mm, the laser scanning speed is 20-300 m/s, the powder feeding speed is 1-30 g/min, the defocusing amount is-10-30 mm, and the interlayer thickness is 0.1-0.5 mm.
Corresponding to laser power 1400W, scanning speed 120m/s, under the water cooling result, a molten pool and a clear molten pool boundary which are mutually overlapped can be obviously seen on the lower cross section of the electronic scanning mirror, the distance between adjacent molten pools is about 20-80pm, and a clear molten pool front edge can be seen in the melting channel. The obvious laminated molten pool can be seen from the longitudinal section, the form of the molten pool also presents the characteristic of Gaussian energy distribution, and a solidification region with darker color can be found at the bottom of the molten pool to form very fine subgrain grains which are growth structures of good crystals.
The cooling method inside the cooling device 100 is water cooling.
The repair method mainly comprises a laser remelting repair technology and an additive repair technology, and mainly aims at repairing single-crystal and oriented-crystal nickel-based superalloy blades.
The single crystal and directional nickel-base superalloy blade repair technology comprises the following steps: the technology mainly aims at the problem of cracks in the additive manufacturing of the nickel-based superalloy, and provides a technical scheme and an implementation process; the method utilizes the properties of laser energy concentration and rapid cooling, combines the characteristics of a thermal process in laser cladding and a crack defect forming mechanism, and controls the laser output state in the laser remelting treatment process so as to inhibit thermal cracks and form compact continuous columnar crystals; in the continuous laser metal additive manufacturing process, the heat flow distribution is controlled in a heat preservation and cooling mode, and continuous columnar crystals without cracks are formed on a substrate; the method is simple to operate, has obvious effect, is beneficial to simultaneously ensuring the inhibition of thermal cracking and the continuous growth of columnar crystals compared with the traditional repairing method, and has high metallurgical quality, good high-temperature mechanical property and short production period.
In the embodiment, the cooling device is arranged, so that the directionally solidified alloy is forcibly cooled in the laser cladding process, and the repair quality is improved. Specifically, the service performance of the single crystal and directionally solidified nickel-based superalloy is closely related to the crystal orientation, and in order to obtain an ideal crystal orientation in the additive manufacturing and repairing, a thermal field in the solidification process needs to be reasonably controlled. According to the technology, the forced cooling device attached to the workpiece is used for increasing the cooling rate of the workpiece in the laser cladding process, so that the bottom of the workpiece is rapidly cooled in the laser cladding process, a larger temperature gradient is obtained in the expected grain growth direction, and a columnar crystal structure which is higher in proportion and better in orientation consistency and grows in a directional epitaxial mode is obtained, and excellent service performance of an additive manufacturing and repairing part is guaranteed.
Compared with the existing liquid nitrogen cooling method, the forced cooling method has the advantages that the cooling speed can be adjusted within a certain range, the directionality of the temperature field is better, the operation safety is higher, and the manufacturing and operation maintenance costs are lower.
What has been described above are merely some embodiments of the present invention. It will be apparent to those skilled in the art that various changes and modifications can be made without departing from the inventive concept thereof, and these changes and modifications can be made without departing from the spirit and scope of the invention.
Claims (7)
1. A laser additive repair method for a high-performance single crystal oriented crystal turbine blade is characterized by comprising the following steps: which comprises the following steps:
1) removing the damaged part of the turbine blade to be repaired by adopting a mechanical processing method;
2) polishing the surface of the part to be repaired by using sand paper, and cleaning the polished surface to be repaired by using acetone;
3) fixing the turbine blade to be repaired on a base with a cooling device through a clamp;
4) remelting the surface of the part to be repaired by adopting continuous pulse laser to obtain a uniform, fine and consistent-orientation crystalline structure;
5) and repairing the turbine blade layer by adopting a laser additive manufacturing process.
6) And after the additive manufacturing is finished, performing stress relief heat treatment.
2. The laser additive repair method of a high performance single crystal oriented crystal turbine blade of claim 1, wherein: in the step 2), the surface roughness Ra of the part to be repaired after surface treatment is 1-8 μm.
3. The laser additive repair method of a high performance single crystal oriented crystal turbine blade of claim 1, wherein: and in the step 2), the surface to be repaired is cleaned for 1-3 times by using acetone, and the polished surface to be repaired can be cleaned by mixing with alcohol.
4. The laser additive repair method of a high performance single crystal oriented crystal turbine blade of claim 1, wherein: in the step 4), continuous laser is adopted in the laser remelting process, and the process parameter range is as follows: the laser power P is 400-1200W, the diameter of a laser spot is 5-10 mm, the laser scanning speed is 30-150 mm/s, and the pulse frequency is 10-100 Hz.
5. The laser additive repair method of a high performance single crystal oriented crystal turbine blade of claim 1, wherein: in the step 5), the additive used in the additive repairing process is nickel-based single crystal superalloy powder, and before laser remelting repairing, the powder is dried in a drying furnace to remove moisture in the powder, wherein the drying temperature is set to be 100-150 ℃, the temperature is kept for 60-180 min, and the granularity is 50-200 meshes.
6. The laser additive repair method of a high performance single crystal oriented crystal turbine blade of claim 1, wherein: in the step 5), continuous laser is adopted in the additive repairing process, and the process parameter range is as follows: the laser power is 100-2000W, the diameter of a light spot is 2-8 mm, the laser scanning speed is 20-300 m/s, the powder feeding speed is 1-30 g/min, the defocusing amount is-10-30 mm, and the interlayer thickness is 0.1-0.5 mm.
7. The laser additive repair method of a high performance single crystal oriented crystal turbine blade of claim 1, wherein: the cooling device adopts a water cooling mode.
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Cited By (5)
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| CN112893874A (en) * | 2021-01-13 | 2021-06-04 | 华中科技大学 | 3D printing device and method for oriented crystal or single crystal high-temperature alloy and product |
| CN114406268A (en) * | 2022-03-29 | 2022-04-29 | 北京煜鼎增材制造研究院有限公司 | Method for repairing side wall of single crystal high temperature alloy turbine blade |
| CN114737185A (en) * | 2022-04-26 | 2022-07-12 | 西安交通大学 | Laser swing composite power modulation method for repairing single crystal turbine blade |
| CN114959331A (en) * | 2022-05-11 | 2022-08-30 | 南昌航空大学 | Method for preparing nickel-based single crystal superalloy based on coaxial powder feeding laser additive manufacturing |
| CN115351292A (en) * | 2022-08-02 | 2022-11-18 | 浙江工业大学 | Method for preparing high-ductility and toughness 1CrMo alloy repair layer by laser additive and post-heat treatment composite process |
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| CN112893874A (en) * | 2021-01-13 | 2021-06-04 | 华中科技大学 | 3D printing device and method for oriented crystal or single crystal high-temperature alloy and product |
| CN114406268A (en) * | 2022-03-29 | 2022-04-29 | 北京煜鼎增材制造研究院有限公司 | Method for repairing side wall of single crystal high temperature alloy turbine blade |
| CN114737185A (en) * | 2022-04-26 | 2022-07-12 | 西安交通大学 | Laser swing composite power modulation method for repairing single crystal turbine blade |
| CN114959331A (en) * | 2022-05-11 | 2022-08-30 | 南昌航空大学 | Method for preparing nickel-based single crystal superalloy based on coaxial powder feeding laser additive manufacturing |
| CN115351292A (en) * | 2022-08-02 | 2022-11-18 | 浙江工业大学 | Method for preparing high-ductility and toughness 1CrMo alloy repair layer by laser additive and post-heat treatment composite process |
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