CN110666168A - Method for repairing turbine guider through laser material increase - Google Patents
Method for repairing turbine guider through laser material increase Download PDFInfo
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- CN110666168A CN110666168A CN201910893856.9A CN201910893856A CN110666168A CN 110666168 A CN110666168 A CN 110666168A CN 201910893856 A CN201910893856 A CN 201910893856A CN 110666168 A CN110666168 A CN 110666168A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
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- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
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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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/60—Treatment of workpieces or articles after build-up
- B22F10/64—Treatment of workpieces or articles after build-up by thermal means
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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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/34—Process control of powder characteristics, e.g. density, oxidation or flowability
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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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/38—Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
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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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/50—Treatment of workpieces or articles during build-up, e.g. treatments applied to fused layers during build-up
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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
- 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
- B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
- B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
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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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- 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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/32—Process control of the atmosphere, e.g. composition or pressure in a building chamber
- B22F10/322—Process control of the atmosphere, e.g. composition or pressure in a building chamber of the gas flow, e.g. rate or direction
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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
- B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
- B22F10/30—Process control
- B22F10/36—Process control of energy beam parameters
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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 method for repairing the turbine guider by laser additive comprises the following steps of S1, carrying out fluorescence detection on the damaged guider, and photographing to record the position of a defect; s2, cleaning the surface of the guider, polishing the area to be repaired, and removing a wear layer, a fatigue layer, an oxidation layer and other impurities; s3, confirming the size of the area to be repaired according to three-dimensional scanning and the drawing; s4, analyzing and confirming the material of the repair area by an alloy analyzer; s5, establishing a repairing process: confirming a repairing sequence, a tool with reasonable design, repairing parameters of laser material increase and powder types; s6, machining and quality inspection; and machining the repaired area to ensure that the size, shape precision and surface quality of the repaired area meet the technical requirements, and carrying out X-ray detection on the repaired area to detect whether defects exist. The invention has the advantages of good repairing quality, high repairing speed, high efficiency, metallurgical bonding between the repairing area and the substrate, strong bonding force and small deformation.
Description
Technical Field
The invention relates to the technical field of additive repair of thin-wall metal components, in particular to a method for repairing a turbine guider by laser additive repair.
Background
The turbine guider consists of guider blades and inner and outer rings, the working condition of the turbine guider is severe, the 1 st-stage guider is close to the outlet of the combustion chamber, the guider blades are surrounded by high-temperature gas flow, and the guider blades are one of the parts with the highest temperature in the engine, have high and uneven temperature and are easy to burn out; free oxygen and sulfur in the fuel gas have strong oxidation and corrosion effects on the surface of the blade; meanwhile, due to the fact that the working condition is constantly changed, the parts bear the cold and hot fatigue effect, fatigue cracks are prone to being generated, the direct scrapping can increase the economic cost, and the damaged parts need to be repaired and reused.
The traditional repair method mostly adopts repair welding methods such as argon arc welding, gas shielded welding and the like, and the defects of deformation of parts after repair, cracks in a repair area and the like are easy to occur.
Disclosure of Invention
The invention aims to provide a method for repairing a turbine guider through laser additive.
The invention realizes the purpose through the following technical scheme: a method of laser additive repair of a turbine vane, comprising the steps of:
s1, carrying out fluorescence detection on the damaged guider and photographing to record the defect position;
s2, cleaning the surface of the guider, polishing the area to be repaired, and removing a wear layer, a fatigue layer, an oxidation layer and other impurities;
s3, confirming the size of the area to be repaired according to three-dimensional scanning and the drawing;
s4, analyzing and confirming the material of the repair area by an alloy analyzer;
s5, establishing a repairing process: confirming a repairing sequence, a tool with reasonable design, repairing parameters of laser material increase and powder types;
s6, machining and quality inspection; and machining the repaired area to ensure that the size, shape precision and surface quality of the repaired area meet the technical requirements, and carrying out X-ray detection on the repaired area to detect whether defects exist.
Further, the step S1 is to use a fluorescence detection guide to observe the blade wear and the outer ring wear with emphasis, and take a picture to record the position of the defect.
Further, the step S2 is to remove defects with a polishing gun under a fluorescent lamp, polish off the wear layer and the oxide layer with a file and a piece of abrasive paper, then clean the wear layer and the oxide layer in an ultrasonic cleaning machine for 10 minutes, remove oil stains, polishing scraps and possibly residual fluorescent liquid which affect the repair quality, and blow-dry the fluorescent liquid with compressed air.
Further, the step S3 is specifically to measure the current size of the guide by using a three-dimensional optical scanner, and analyze the size to be repaired by combining with a drawing;
further, in the step S4, the material of the repair area is GH3536 alloy.
Further, in step S5, the repairing process includes:
s51, selecting GH3536 powder mainly comprising Ni, Cr, Fe, Mo, Co, W, Al and Ti, preparing the alloy powder by adopting a gas atomization method, wherein the powder particles are spherical and have the particle size of 53-106 mu m;
s52, specially designing a tool aiming at the characteristic that the blade tip of the blade is narrow and thin;
s53, considering the factors of size shrinkage and hole deviation caused by blade tip and positioning hole outer edge repair, repairing the blade tip, repairing the hole outer edge, filling the positioning hole according to the drawing and the deviation position, and machining;
s54, the overall repair process is laser material increase repair, the laser power is 500-800W, the spot size is 2-3mm, the protective gas flow is 8-15L/min, the powder feeding amount is 4-8g/min, the powder feeding gas flow is 4-5L/min, the repair rate is 10-15mm/S, the layer height is 0.4-1.2mm, and the lap joint amount is 1-2 mm;
s55, after laser material increase and repair, the guider is subjected to a stress-relief heat treatment system, and the temperature is kept for 2 hours at 700 ℃.
Compared with the prior art, the method for repairing the turbine guider by laser additive has the beneficial effects that: the repairing quality is good, the repairing speed is high, the efficiency is high, the interface of the repairing area and the substrate is metallurgically bonded, the bonding force is strong, and the deformation is small.
Drawings
FIG. 1 is a schematic view of a turbine nozzle.
Fig. 2 is a schematic view of the arrangement angle of the tool.
Detailed Description
Example 1
The turbine guide vane is repaired by a laser additive repair method, and the base material is GH3536 alloy.
The embodiment comprises the following steps:
after repairable assessment of the damaged part determines repairable, laser additive repair is carried out, and the following specific steps are implemented:
s1, carrying out fluorescence detection on the damaged guider and photographing to record the defect position; specifically, a fluorescence detection guider is adopted, the positions of blade abrasion and outer ring abrasion are mainly observed, and the positions of defects are photographed and recorded;
s2, cleaning the surface of the guider, removing defects by using a polishing gun under a fluorescent lamp, polishing a wear layer and an oxidation layer by using a file and abrasive paper, then putting the guider into an ultrasonic cleaning machine for cleaning for 10 minutes, removing oil stains, polishing scraps and possibly residual fluorescent liquid which influence the repair quality, and drying the guider by compressed air;
s3, measuring the current size of the guider by using a three-dimensional optical scanner, analyzing the size to be repaired by combining with a drawing, and reserving a machining allowance of 1 mm;
s4, analyzing and confirming that the repair area is made of GH3536 alloy through an alloy analyzer;
s5, formulating a repairing process, which comprises the following steps:
s51, adopting GH3536 alloy with repair powder components consistent with matrix components, wherein the main components are Ni, Cr, Fe, Mo, Co, W, Al and Ti, the alloy powder is prepared by adopting an air atomization method, the powder particles are spherical, and the particle size is 53-106 mu m;
s52, designing a special tool aiming at the characteristic that the blade tip of the blade is narrow and thin;
s53, considering the factors of size shrinkage and hole deviation caused by blade tip and positioning hole outer edge repair, repairing the blade tip, repairing the hole outer edge, filling the positioning hole according to the drawing and the deviation position, and machining;
s54, the overall repair process is laser additive repair, the laser power is 600W, the spot size is 2mm, the flow rate of protective gas Ar is 10L/min, the powder feeding amount is 4.5g/min, the flow rate of powder feeding gas He is 5L/min, the repair rate is 10mm/S, the layer height is 0.4mm, and the lap joint is 1 mm;
s55, after laser material increase and repair, preserving heat for 2h at 700 ℃ by adopting a stress-relief heat treatment system;
s6, machining and quality inspection: and machining the repaired area to ensure that the size, shape precision and surface quality of the repaired area meet the technical requirements, and carrying out X-ray detection on the repaired area to detect whether defects including cracks, air holes and the like exist.
Example 2
The turbine guide vane is repaired by a laser additive repair method, and the base material is GH3536 alloy.
The embodiment comprises the following steps:
after repairable assessment of the damaged part determines repairable, laser additive repair is carried out, and the following specific steps are implemented:
s1, carrying out fluorescence detection on the damaged guider and photographing to record the defect position; specifically, a fluorescence detection guider is adopted, the positions of blade abrasion and outer ring abrasion are mainly observed, and the positions of defects are photographed and recorded;
s2, cleaning the surface of the guider, removing defects by using a polishing gun under a fluorescent lamp, polishing a wear layer and an oxidation layer by using a file and abrasive paper, then putting the guider into an ultrasonic cleaning machine for cleaning for 10 minutes, removing oil stains, polishing scraps and possibly residual fluorescent liquid which influence the repair quality, and drying the guider by compressed air;
s3, measuring the current size of the guider by using a three-dimensional optical scanner, analyzing the size to be repaired by combining with a drawing, and reserving a machining allowance of 1.5 mm;
s4, analyzing and confirming that the repair area is made of GH3536 alloy through an alloy analyzer;
s5, formulating a repairing process, which comprises the following steps:
s51, adopting GH3536 alloy with repair powder components consistent with matrix components, wherein the main components are Ni, Cr, Fe, Mo, Co, W, Al and Ti, the alloy powder is prepared by adopting an air atomization method, the powder particles are spherical, and the particle size is 53-106 mu m;
s52, designing a special tool aiming at the characteristic that the blade tip of the blade is narrow and thin;
s53, considering the factors of size shrinkage and hole deviation caused by blade tip and positioning hole outer edge repair, repairing the blade tip, repairing the hole outer edge, filling the positioning hole according to the drawing and the deviation position, and machining;
s54, the overall repair process is laser additive repair, the laser power is 500W, the spot size is 2.5mm, the flow rate of protective gas Ar is 8L/min, the powder feeding amount is 4g/min, the flow rate of powder feeding gas He is 4.5L/min, the repair rate is 12mm/S, the layer height is 0.8mm, and the lap joint is 2 mm;
s55, after laser material increase and repair, preserving heat for 2h at 700 ℃ by adopting a stress-relief heat treatment system;
s6, machining and quality inspection: and machining the repaired area to ensure that the size, shape precision and surface quality of the repaired area meet the technical requirements, and carrying out X-ray detection on the repaired area to detect whether defects including cracks, air holes and the like exist.
Example 3
The turbine guide vane is repaired by a laser additive repair method, and the base material is GH3536 alloy.
The embodiment comprises the following steps:
after repairable assessment of the damaged part determines repairable, laser additive repair is carried out, and the following specific steps are implemented:
s1, carrying out fluorescence detection on the damaged guider and photographing to record the defect position; specifically, a fluorescence detection guider is adopted, the positions of blade abrasion and outer ring abrasion are mainly observed, and the positions of defects are photographed and recorded;
s2, cleaning the surface of the guider, removing defects by using a polishing gun under a fluorescent lamp, polishing a wear layer and an oxidation layer by using a file and abrasive paper, then putting the guider into an ultrasonic cleaning machine for cleaning for 10 minutes, removing oil stains, polishing scraps and possibly residual fluorescent liquid which influence the repair quality, and drying the guider by compressed air;
s3, measuring the current size of the guider by using a three-dimensional optical scanner, analyzing the size to be repaired by combining with a drawing, and reserving a machining allowance of 1 mm;
s4, analyzing and confirming that the repair area is made of GH3536 alloy through an alloy analyzer;
s5, formulating a repairing process, which comprises the following steps:
s51, adopting GH3536 alloy with repair powder components consistent with matrix components, wherein the main components are Ni, Cr, Fe, Mo, Co, W, Al and Ti, the alloy powder is prepared by adopting an air atomization method, the powder particles are spherical, and the particle size is 53-106 mu m;
s52, designing a special tool aiming at the characteristic that the blade tip of the blade is narrow and thin;
s53, considering the factors of size shrinkage and hole deviation caused by blade tip and positioning hole outer edge repair, repairing the blade tip, repairing the hole outer edge, filling the positioning hole according to the drawing and the deviation position, and machining;
s54, the overall repair process is laser additive repair, the laser power is 800W, the spot size is 3mm, the flow rate of protective gas Ar is 15L/min, the powder feeding amount is 8g/min, the flow rate of powder feeding gas He is 4L/min, the repair rate is 15mm/S, the layer height is 1.2mm, and the lap joint is 1 mm;
s55, after laser material increase and repair, preserving heat for 2h at 700 ℃ by adopting a stress-relief heat treatment system;
s6, machining and quality inspection: and machining the repaired area to ensure that the size, shape precision and surface quality of the repaired area meet the technical requirements, and carrying out X-ray detection on the repaired area to detect whether defects including cracks, air holes and the like exist.
The invention has the advantages of good repairing quality, high repairing speed, high efficiency, metallurgical bonding of the interface of the repairing area and the substrate, strong bonding force, small deformation and higher economic value.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (6)
1. A method of laser additive repair of a turbine vane, comprising the steps of:
s1, carrying out fluorescence detection on the damaged guider and photographing to record the defect position;
s2, cleaning the surface of the guider, polishing the area to be repaired, and removing a wear layer, a fatigue layer, an oxidation layer and other impurities;
s3, confirming the size of the area to be repaired according to three-dimensional scanning and the drawing;
s4, analyzing and confirming the material of the repair area by an alloy analyzer;
s5, establishing a repairing process: confirming a repairing sequence, a tool with reasonable design, repairing parameters of laser material increase and powder types;
s6, machining and quality inspection; and machining the repaired area to ensure that the size, shape precision and surface quality of the repaired area meet the technical requirements, and carrying out X-ray detection on the repaired area to detect whether defects exist.
2. The method of laser additive repair of a turbine vane of claim 1, wherein: and S1, specifically, a fluorescence detection guider is adopted, the worn parts of the blades and the worn parts of the outer ring are mainly observed, and the positions of the defects are photographed and recorded.
3. The method of laser additive repair of a turbine vane of claim 1, wherein: the step S2 is to remove defects with a polishing gun under a fluorescent lamp, polish off the wear layer and the oxide layer with a file and a sand paper, then clean the wear layer and the oxide layer in an ultrasonic cleaning machine for 10 minutes, remove oil stains, polishing debris and possibly residual fluorescent liquid which affect the repair quality, and blow-dry the fluorescent liquid with compressed air.
4. The method of laser additive repair of a turbine vane of claim 1, wherein: the step S3 is to measure the current size of the guide by using a three-dimensional optical scanner, and analyze the size to be repaired by combining with a drawing.
5. The method of laser additive repair of a turbine vane of claim 1, wherein: in the step S4, the repair area is made of GH3536 alloy.
6. The method of laser additive repair of a turbine vane of claim 1, wherein: in the step S5, the repairing process includes:
s51, selecting GH3536 powder mainly comprising Ni, Cr, Fe, Mo, Co, W, Al and Ti, preparing the alloy powder by adopting a gas atomization method, wherein the powder particles are spherical and have the particle size of 53-106 mu m;
s52, specially designing a tool aiming at the characteristic that the blade tip of the blade is narrow and thin;
s53, considering the factors of size shrinkage and hole deviation caused by blade tip and positioning hole outer edge repair, repairing the blade tip, repairing the hole outer edge, filling the positioning hole according to the drawing and the deviation position, and machining;
s54, the overall repair process is laser material increase repair, the laser power is 500-800W, the spot size is 2-3mm, the protective gas flow is 8-15L/min, the powder feeding amount is 4-8g/min, the powder feeding gas flow is 4-5L/min, the repair rate is 10-15mm/S, the layer height is 0.4-1.2mm, and the lap joint amount is 1-2 mm;
s55, after laser material increase and repair, the guider is subjected to a stress-relief heat treatment system, and the temperature is kept for 2 hours at 700 ℃.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112045363A (en) * | 2020-08-07 | 2020-12-08 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112276086A (en) * | 2020-11-10 | 2021-01-29 | 西安交通大学 | Additive/equal-material preparation method for blade tenon |
| CN113458605A (en) * | 2021-07-12 | 2021-10-01 | 南京航空航天大学 | Device and method based on laser-MIG composite additive repair |
| CN113478832A (en) * | 2021-07-27 | 2021-10-08 | 贵州航天天马机电科技有限公司 | Process method for post-treatment repair of SLA parts |
| 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 |
| CN114734055A (en) * | 2022-01-20 | 2022-07-12 | 航发优材(镇江)增材制造有限公司 | Laser metal deposition preparation method for boss structure of engine diffuser |
| 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 |
| CN118060862A (en) * | 2024-04-25 | 2024-05-24 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Guider additive machining method and guider |
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| CN112045363B (en) * | 2020-08-07 | 2022-03-11 | 中国人民解放军第五七一九工厂 | Integrated repairing method for turbine blade damage |
| CN112276086A (en) * | 2020-11-10 | 2021-01-29 | 西安交通大学 | Additive/equal-material preparation method for blade tenon |
| CN112276086B (en) * | 2020-11-10 | 2021-08-27 | 西安交通大学 | Additive/equal-material preparation method for blade tenon |
| CN113458605A (en) * | 2021-07-12 | 2021-10-01 | 南京航空航天大学 | Device and method based on laser-MIG composite additive repair |
| CN113478832A (en) * | 2021-07-27 | 2021-10-08 | 贵州航天天马机电科技有限公司 | Process method for post-treatment repair of SLA parts |
| CN114734055A (en) * | 2022-01-20 | 2022-07-12 | 航发优材(镇江)增材制造有限公司 | Laser metal deposition preparation method for boss structure of engine diffuser |
| CN114734055B (en) * | 2022-01-20 | 2023-07-11 | 航发优材(镇江)增材制造有限公司 | Laser metal deposition preparation method for boss structure of engine diffuser |
| 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 |
| 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 |
| CN118060862A (en) * | 2024-04-25 | 2024-05-24 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Guider additive machining method and guider |
| CN118060862B (en) * | 2024-04-25 | 2024-06-25 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Guider additive machining method and guider |
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