CN104741865A - Laser repairing method for die - Google Patents

Laser repairing method for die Download PDF

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Publication number
CN104741865A
CN104741865A CN201510183200.XA CN201510183200A CN104741865A CN 104741865 A CN104741865 A CN 104741865A CN 201510183200 A CN201510183200 A CN 201510183200A CN 104741865 A CN104741865 A CN 104741865A
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CN
China
Prior art keywords
overlay cladding
laser
die
flaring die
adopts
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Pending
Application number
CN201510183200.XA
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Chinese (zh)
Inventor
唐全林
张智明
高云飞
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Suzhou Tangshi Machinery Manufacturing Co Ltd
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Suzhou Tangshi Machinery Manufacturing Co Ltd
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Publication of CN104741865A publication Critical patent/CN104741865A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B23K35/3053—Fe as the principal constituent
    • B23K35/308—Fe as the principal constituent with Cr as next major constituent
    • B23K35/3086—Fe as the principal constituent with Cr as next major constituent containing Ni or Mn
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/02—Ferrous alloys, e.g. steel alloys containing silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/22—Ferrous alloys, e.g. steel alloys containing chromium with molybdenum or tungsten
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/24—Ferrous alloys, e.g. steel alloys containing chromium with vanadium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/32—Ferrous alloys, e.g. steel alloys containing chromium with boron
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/34—Ferrous alloys, e.g. steel alloys containing chromium with more than 1.5% by weight of silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C22C38/38—Ferrous alloys, e.g. steel alloys containing chromium with more than 1.5% by weight of manganese
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/20—Tools

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Laser Beam Processing (AREA)

Abstract

The invention relates to a laser repairing method for a die. The method includes the steps: treating, detecting and analyzing the surface of a flaring die to be repaired, and removing a fatigue layer of an abrasion portion; surfacing the abrasion portion to form a first surfacing layer, then surfacing on the first surfacing layer to form a second surfacing layer, performing surfacing in a preset powder feeding manner, continuously overlapping and scanning the die by taking a fast-transverse-flow carbon dioxide laser as a light source. The thickness of the first surfacing layer ranges from 2mm to 3mm, the thickness of the second surfacing layer ranges from 2mm to 3mm, laser cladding of the surface of the flaring die is performed, and the hardness of the surface of the flaring die and the size of the abrasion portion can meet use requirements.

Description

A kind of laser repair method of mould
The application is the applying date is on June 29th, 2013, and application number is 201310267075.1, and denomination of invention is the divisional application of " laser repair method of flaring die ".
Technical field
The present invention relates to a kind of laser cladding method, especially a kind of laser melting coating restorative procedure of die surface.
Background technology
Punching press is at room temperature, utilizes the diel be arranged on forcing press to apply pressure to material, makes it produce separation or plastic deformation, thus obtains a kind of pressure processing method of required part.Diel is requisite technological equipment in punching production, is technology-intensive product.The quality of stamping parts, production efficiency and production cost etc., have direct relation with Design of Dies and manufacture.Diel is divided into blanking die, perforating die, bending die, Drawing Die, flaring die etc. according to technological property, these diels are are all inevitably worn and torn in the course of the work, but because each mould role is different, stressing conditions during punching press is different, and the degree of wear in the course of work and wearing character are also different.Carry out die surface reparation by common overlaying method, the shortcomings such as deflection is large, hardness is not enough, easy to crack can be brought.And different moulds should select more suitable renovation technique according to its characteristic, otherwise the mold use life-span cannot be protected, and can have a strong impact on mold use precision, cause produced product quality to decline.
Laser melting coating refers to and is made it to melt with matrix surface skim through laser irradiation by coating material cladding matrix surface placed by selecting with different adding material modes simultaneously, and it is extremely low to form dilution factor after rapid solidification, the face coat of metallurgical binding is become with matrix, the remarkable process improving the wear-resisting, anti-corrosion, heat-resisting, anti-oxidant of substrate surface and electrical characteristic, thus reach the object of surface modification or reparation.With built-up welding, spraying, plating and gas phase sedimentary facies ratio, laser melting coating has that dilution factor is little, dense structure, coating and matrix is combined, be applicable to that cladding material is many, granularity and the feature such as changes of contents is large.How laser melting and coating technique being effectively applied to the reparation of flaring die, is the problem that those skilled in the art needs to solve.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of surface to flaring die and carries out laser melting coating, makes the size of its case hardness and abrading section reach the laser repair method of the flaring die of instructions for use.
In order to solve the problems of the technologies described above, the invention provides a kind of laser repair method of flaring die, comprise following concrete steps:
The first step, the surface of flaring die to be repaired to be processed;
Second step, carry out detection analyze, determine abrading section and wear extent thereof;
The fatigue layer of the 3rd step, removal abrading section;
4th step, detection analysis result according to flaring die, programme to the die cavity of abrading section, formulates technological parameter;
5th step, built-up welding is carried out to abrading section form the first overlay cladding, then at ground floor overlay cladding enterprising windrow weldering formation second overlay cladding, the thickness of described first overlay cladding is 2mm to 3mm, the thickness of described second overlay cladding is 2mm to 3mm, in weld deposit process, constantly evenly knock mould alloy cladding layer, built-up welding adopts the mode of preset powder feeding, be that light source carries out lap connection scanning to mould with fast-transverse-flow CO2 laser, laser power is 1200W to 1400W, spot size is 12mm × 1.8mm, laser instrument is 255mm to 265mm from the distance between agent, sweep speed is 110mm/min to 130mm/min, amount of lap is 4.5mm, powder sending quantity is 12g/min to 15g/min, the component of the alloy powder that the first overlay cladding adopts and weight percent content are C≤0.1%, Cr:15% to 19%, B:1.5% to 2.5%, Si:1% to 2%, Mo:0.8% to 1%, Mn:2% to 5%, all the other are Fe, the component of the alloy powder that the second overlay cladding adopts and weight percent content are C≤0.1%, Cr:6% to 8%, B:1.5% to 2.5%, Si:1% to 2%, Mo:0.8% to 1%, Mn:5% to 7%, W:2% to 4%, V: 2% to 6%, TiO 2: 5% to 10%, all the other are Fe,
6th step, detection case hardness and deflection, carry out machining, penetrant inspection to the flaring die after repairing.
The mass percentage content of the Mn in the alloy powder that above-mentioned second overlay cladding adopts is 5.6% to 6.6%.
The mass percentage content of the W in the alloy powder that above-mentioned second overlay cladding adopts is 2.8% to 3.5%.
The mass percentage content of the V in the alloy powder that above-mentioned second overlay cladding adopts is 4.2% to 5.8%.
TiO in the alloy powder that above-mentioned second overlay cladding adopts 2mass percentage content be 6.3% to 8.7%.
The beneficial effect that the present invention brings is: the laser repair method of flaring die of the present invention is lower according to the wearing character of flaring die first built-up welding one deck hardness, wearability generally organizes the first comparatively fine and close, uniformity is good overlay cladding, higher, good second overlay cladding of wearability of built-up welding one deck hardness on the first overlay cladding again, during the second overlay cladding built-up welding, the first overlay cladding does not still cool, and both all have selected suitable alloy powder and carry out built-up welding, wetability between two overlay claddings is good, in conjunction with tightr.The content of the strict control C of the alloy powder of the second overlay cladding, be conducive to the wetability improving cladding layer, prevent from cracking in cladding process and pore, add appropriate B, Si and make alloy form matrix based on austenite after solidification, utilize appropriate Cr, Mn, W, Mo, V, TiO 2carry out alloy strengthening to ferrous alloy, even if C content is lower, the hardness of cladding layer also can reach more than 55.5HRC, fully meets the hardness requirement that mould uses, and has very high wearability.Adopt the mode of preset powder feeding in addition, strictly control powder sending quantity, and laser power, sweep speed, amount of lap etc. are optimized, such that the structural homogenity of cladding layer is good, thickness and hardness even.The method did not need to carry out preheating to mould before built-up welding, without the need to annealing to mould after built-up welding, effectively can control the distortion of mould, and heat can be avoided to concentrate generation thermal stress by carrying out laser melting coating in an orderly manner everywhere, be conducive to reducing distortion further, improve hardness and the wearability of mould.
Detailed description of the invention
Embodiment 1
The concrete steps of the laser repair method of the flaring die of the present embodiment are as follows:
The first step, the surface of flaring die to be repaired to be processed, by removings such as the dust on flaring die, greasy dirt, corrosions.
Second step, carry out detection and analyze, original service condition, hardness and the mechanical property parameters of record flaring die, detects the size at each position of flaring die, determines abrading section and wear extent thereof.
3rd step, remove the right angle of abrading section by polishing, remove the fatigue layer of abrading section, and clean.
4th step, detection analysis result according to flaring die, programme (numerical control machining simulation system that programming can use Mitsubishi) to the die cavity of abrading section, formulate technological parameter.
5th step, built-up welding is carried out to abrading section form the first overlay cladding, then at ground floor overlay cladding enterprising windrow weldering formation second overlay cladding, the thickness of described first overlay cladding is 3mm, the thickness of described second overlay cladding is 3mm, in weld deposit process, constantly evenly knock mould alloy cladding layer with mallet.Built-up welding adopts the mode of preset powder feeding, is that light source carries out lap connection scanning to mould with fast-transverse-flow CO2 laser.Laser power is 1400W, and spot size is 12mm × 1.8mm, and laser instrument is 265mm from the distance between agent, and sweep speed is 120mm/min, and amount of lap is 4.5mm, and powder sending quantity is 12g/min.The component of the alloy powder that the first overlay cladding adopts and weight percent content are C:0.07%, Cr:15.4%, B:2.2%, Si:1.4%, Mo:0.8%, Mn:2.5%, and all the other are Fe.The component of the alloy powder that the second overlay cladding adopts and weight percent content are C:0.08%, Cr:7.2%, B:2%, Si:1.5%, Mo:1%, Mn:6.5%, V: 4.5%, W:3.2%, TiO 2: 8.1%, all the other are Fe.
6th step, detection case hardness and deflection, carry out machining, penetrant inspection to the flaring die after repairing.
Mean value through the case hardness of the flaring die of the laser repair method reparation of the flaring die of the present embodiment reaches 57.1HRC, and the hardness minimum in all test points is 55.9HRC.
Embodiment 2
The remainder of the laser repair method of the flaring die of the present embodiment is identical with embodiment 1, difference is: laser power is 1200W, spot size is 12mm × 1.8mm, laser instrument is 255mm from the distance between agent, sweep speed is 110mm/min, amount of lap is 4.5mm, and powder sending quantity is 13g/min.The component of the alloy powder that the first overlay cladding adopts and weight percent content are C:0.09%, Cr:17.5%, B:1.7%, Si:1.1%, Mo:0.9%, Mn:3.4%, and all the other are Fe.The component of the alloy powder that the second overlay cladding adopts and weight percent content are C:0.06%, Cr:6.6%, B:1.8%, Si:1.2%, Mo:0.9%, Mn:5.8%, V:5.3%, W:3.4%, TiO 2: 7.6%, all the other are Fe.
Mean value through the case hardness of the flaring die of the laser repair method reparation of the flaring die of the present embodiment reaches 57.2HRC, and the hardness minimum in all test points is 55.8HRC.
Embodiment 3
The remainder of the laser repair method of the flaring die of the present embodiment is identical with embodiment 1, difference is: laser power is 1300W, spot size is 12mm × 1.8mm, laser instrument is 260mm from the distance between agent, sweep speed is 130mm/min, amount of lap is 4.5mm, and powder sending quantity is 15g/min.The component of the alloy powder that the first overlay cladding adopts and weight percent content are C:0.05%, Cr:16.5%, B:2%, Si:1.3%, Mo:0.8%, Mn:3.6%, and all the other are Fe.The component of the alloy powder that the second overlay cladding adopts and weight percent content are C:0.09%, Cr:7.6%, B:2.2%, Si:1.8%, Mo:0.8%, Mn:5.9%, V: 4.8%, W:2.9%, TiO 2: 6.7%, all the other are Fe.
Mean value through the case hardness of the flaring die of the laser repair method reparation of the flaring die of the present embodiment reaches 57.4 HRC, and the hardness minimum in all test points is 55.7HRC.
Obviously, above-described embodiment is only for example of the present invention is clearly described, and is not the restriction to embodiments of the present invention.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all embodiments.And these belong to spirit institute's apparent change of extending out of the present invention or change and are still among protection scope of the present invention.

Claims (3)

1. a laser repair method for mould, comprises following concrete steps:
The first step, the surface of flaring die to be repaired to be processed, the dust on flaring die, greasy dirt, corrosion are removed;
Second step, carry out detection analyze, determine abrading section and wear extent thereof;
The fatigue layer of the 3rd step, removal abrading section;
4th step, detection analysis result according to flaring die, programme to the die cavity of abrading section, formulates technological parameter;
5th step, built-up welding is carried out to abrading section form the first overlay cladding, then at ground floor overlay cladding enterprising windrow weldering formation second overlay cladding, the thickness of described first overlay cladding is 2mm to 3mm, the thickness of described second overlay cladding is 2mm to 3mm, in weld deposit process, constantly evenly knock mould alloy cladding layer, built-up welding adopts the mode of preset powder feeding, be that light source carries out lap connection scanning to mould with fast-transverse-flow CO2 laser, laser power is 1200W to 1400W, spot size is 12mm × 1.8mm, laser instrument is 255mm to 265mm from the distance between agent, sweep speed is 110mm/min to 130mm/min, amount of lap is 4.5mm, powder sending quantity is 12g/min to 15g/min, the component of the alloy powder that the first overlay cladding adopts and weight percent content are C≤0.1%, Cr:15% to 19%, B:1.5% to 2.5%, Si:1% to 2%, Mo:0.8% to 1%, Mn:2% to 5%, all the other are Fe, the component of the alloy powder that the second overlay cladding adopts and weight percent content are C≤0.1%, Cr:6% to 8%, B:1.5% to 2.5%, Si:1% to 2%, Mo:0.8% to 1%, Mn:5% to 7%, W:2.8% to 3.5%, V: 2% to 6%, TiO 2: 6.3% to 8.7%, all the other are Fe,
6th step, detection case hardness and deflection, carry out machining, penetrant inspection to the flaring die after repairing.
2. the laser repair method of a kind of mould according to claim 1, is characterized in that: the mass percentage content of the Mn in the alloy powder that the second overlay cladding adopts is 5.6% to 6.6%.
3. the laser repair method of a kind of mould according to claim 1, is characterized in that: the mass percentage content of the V in the alloy powder that the second overlay cladding adopts is 4.2% to 5.8%.
CN201510183200.XA 2013-06-29 2013-06-29 Laser repairing method for die Pending CN104741865A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201310267075.1A CN103343338B (en) 2013-06-29 2013-06-29 Laser restoration method of flaring die

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Application Number Title Priority Date Filing Date
CN201310267075.1A Expired - Fee Related CN103343338B (en) 2013-06-29 2013-06-29 Laser restoration method of flaring die
CN201510183179.3A Pending CN104746070A (en) 2013-06-29 2013-06-29 Laser repair method
CN201510183096.4A Pending CN104827188A (en) 2013-06-29 2013-06-29 Laser repairing method for flaring die
CN201510183178.9A Pending CN104746069A (en) 2013-06-29 2013-06-29 Laser repair method
CN201510183097.9A Pending CN104762617A (en) 2013-06-29 2013-06-29 Laser repairing method for die
CN201510183200.XA Pending CN104741865A (en) 2013-06-29 2013-06-29 Laser repairing method for die

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CN201310267075.1A Expired - Fee Related CN103343338B (en) 2013-06-29 2013-06-29 Laser restoration method of flaring die
CN201510183179.3A Pending CN104746070A (en) 2013-06-29 2013-06-29 Laser repair method
CN201510183096.4A Pending CN104827188A (en) 2013-06-29 2013-06-29 Laser repairing method for flaring die
CN201510183178.9A Pending CN104746069A (en) 2013-06-29 2013-06-29 Laser repair method
CN201510183097.9A Pending CN104762617A (en) 2013-06-29 2013-06-29 Laser repairing method for die

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CN105252203A (en) * 2015-10-19 2016-01-20 浙江大学宁波理工学院 Restoration method for mold fractures
FR3058345A1 (en) * 2016-11-08 2018-05-11 Peugeot Citroen Automobiles Sa CENTER FOR MACHINING AND METALLURGICAL TREATMENT FOR TOOLS FOR AUTOMOTIVE FITTING
CN109554704A (en) * 2018-12-24 2019-04-02 广东省新材料研究所 A method of remanufacturing cable forming mold
CN109664024A (en) * 2019-02-20 2019-04-23 丁二纲 Repair the method for laser welding of base material surface or internal flaw
CN111633519A (en) * 2020-06-16 2020-09-08 姚政 Shaft type die surface flaw detection repairing device and using method

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CN110709206A (en) * 2017-06-07 2020-01-17 住友电工烧结合金株式会社 Method for manufacturing mold member and mold member
CN108118335B (en) * 2017-12-28 2020-02-21 沈阳大陆激光技术有限公司 Laser repairing method for high-pressure water descaling header
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CN1674408A (en) * 2004-03-26 2005-09-28 沈阳大陆激光技术有限公司 Electric power generator, steam turbine rotor spindle repaired by laser and repairing method thereof
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CN105252203A (en) * 2015-10-19 2016-01-20 浙江大学宁波理工学院 Restoration method for mold fractures
FR3058345A1 (en) * 2016-11-08 2018-05-11 Peugeot Citroen Automobiles Sa CENTER FOR MACHINING AND METALLURGICAL TREATMENT FOR TOOLS FOR AUTOMOTIVE FITTING
CN109554704A (en) * 2018-12-24 2019-04-02 广东省新材料研究所 A method of remanufacturing cable forming mold
CN109664024A (en) * 2019-02-20 2019-04-23 丁二纲 Repair the method for laser welding of base material surface or internal flaw
CN111633519A (en) * 2020-06-16 2020-09-08 姚政 Shaft type die surface flaw detection repairing device and using method

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CN104746070A (en) 2015-07-01
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CN104827188A (en) 2015-08-12
CN103343338A (en) 2013-10-09

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Application publication date: 20150701