CN110157977A - A kind of laser remanufacturing reparation iron(-)base powder and the preparation method and application thereof - Google Patents
A kind of laser remanufacturing reparation iron(-)base powder and the preparation method and application thereof Download PDFInfo
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- 239000000843 powder Substances 0.000 title claims abstract description 158
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 title claims abstract description 121
- 229910052742 iron Inorganic materials 0.000 title claims abstract description 55
- 238000002360 preparation method Methods 0.000 title claims abstract description 12
- 238000005253 cladding Methods 0.000 claims abstract description 56
- 239000011651 chromium Substances 0.000 claims abstract description 37
- 239000011572 manganese Substances 0.000 claims abstract description 27
- 229910052796 boron Inorganic materials 0.000 claims abstract description 20
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims abstract description 19
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 17
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 17
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 16
- 238000000034 method Methods 0.000 claims abstract description 16
- 239000010703 silicon Substances 0.000 claims abstract description 16
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 15
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims abstract description 15
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 15
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 12
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 12
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 12
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 12
- 239000011733 molybdenum Substances 0.000 claims abstract description 12
- 239000000463 material Substances 0.000 claims abstract description 6
- 239000010410 layer Substances 0.000 claims description 53
- 239000012159 carrier gas Substances 0.000 claims description 19
- 239000007789 gas Substances 0.000 claims description 18
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 12
- 238000005520 cutting process Methods 0.000 claims description 7
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 6
- 229910052786 argon Inorganic materials 0.000 claims description 6
- 238000012387 aerosolization Methods 0.000 claims description 5
- 238000002844 melting Methods 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 239000000428 dust Substances 0.000 claims description 4
- 239000000155 melt Substances 0.000 claims description 4
- 230000001681 protective effect Effects 0.000 claims description 4
- 238000005202 decontamination Methods 0.000 claims description 3
- 230000003588 decontaminative effect Effects 0.000 claims description 3
- 238000001035 drying Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 239000002994 raw material Substances 0.000 claims description 3
- 238000003723 Smelting Methods 0.000 claims description 2
- 230000008859 change Effects 0.000 claims description 2
- 238000004140 cleaning Methods 0.000 claims description 2
- 239000011229 interlayer Substances 0.000 claims description 2
- 230000003287 optical effect Effects 0.000 claims description 2
- 239000002356 single layer Substances 0.000 claims description 2
- 238000001816 cooling Methods 0.000 claims 1
- 229910045601 alloy Inorganic materials 0.000 abstract description 37
- 239000000956 alloy Substances 0.000 abstract description 37
- 230000008439 repair process Effects 0.000 abstract description 11
- 230000007547 defect Effects 0.000 abstract description 10
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- 230000004907 flux Effects 0.000 description 17
- 239000011248 coating agent Substances 0.000 description 10
- 238000000576 coating method Methods 0.000 description 10
- 239000002245 particle Substances 0.000 description 10
- 208000037656 Respiratory Sounds Diseases 0.000 description 8
- 238000003466 welding Methods 0.000 description 7
- 238000004364 calculation method Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 5
- 239000000203 mixture Substances 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 4
- 229920001296 polysiloxane Polymers 0.000 description 4
- 239000002893 slag Substances 0.000 description 4
- 238000012360 testing method Methods 0.000 description 4
- 238000005275 alloying Methods 0.000 description 3
- 238000002149 energy-dispersive X-ray emission spectroscopy Methods 0.000 description 3
- 238000007689 inspection Methods 0.000 description 3
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
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- 239000001301 oxygen Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 238000009418 renovation Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 229910000851 Alloy steel Inorganic materials 0.000 description 1
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 229910000906 Bronze Inorganic materials 0.000 description 1
- CWYNVVGOOAEACU-UHFFFAOYSA-N Fe2+ Chemical compound [Fe+2] CWYNVVGOOAEACU-UHFFFAOYSA-N 0.000 description 1
- 238000007545 Vickers hardness test Methods 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000010974 bronze Substances 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
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Classifications
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- B22F1/0003—
-
- 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
- C22C38/04—Ferrous alloys, e.g. steel alloys containing manganese
-
- 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
- C22C38/32—Ferrous alloys, e.g. steel alloys containing chromium with boron
-
- 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
Abstract
The present invention provides a kind of laser remanufacturing reparation iron(-)base powders and the preparation method and application thereof, the alloy powder consists of the following components in percentage by mass: carbon C:0.01~0.04%, chromium Cr:1.0~1.2%, silicon Si:0.5~0.8%, boron: 0.4%~0.7%, manganese Mn:0.4~0.6%, molybdenum Mo:0.4~0.6%, surplus Fe；Using the alloy powder and its application method, it can be obtained under wide in range technological parameter and contain specific alloy elements, pore-free crack defect, cladding layer of good performance, two layers laser remanufacturing can be achieved and repair the Cr content of layer surface close to alloy powder ingredient, and laser remanufacturing reparation operating process is flexible, it is repeated consistent, it is high-efficient, there is big advantage compared to traditional technology, can be used for low pressure (being also applied for other high Cr ultra supercritical rotor materials) rotor journal laser remanufacturing reparation.
Description
(1) technical field
The present invention relates to laser remanufacturing recovery technique fields, and in particular to one kind is suitable for low-pressure turbine rotor journal
Low Cr iron(-)base powder of laser remanufacturing reparation and the preparation method and application thereof.
(2) background technique
Submerged arc overlay welding, Brush Plating, thermal spraying are generally used at present, or carefully the technological means such as galleting tile are come again by axle journal vehicle
Repair the abrading section of low-pressure turbine rotor journal.But above-mentioned technological means there are heat inputs big, low efficiency, coating and base
Body combines the problems such as insecure, coating consistency is low, and carefully the technological means of galleting tile then changes original design size to vehicle again, needs
Again spare part, and can not be thin without limitation vehicle, it is limited to repair number.
Laser remanufacturing reparation is used as one kind is advanced to remanufacture recovery technique, compared to the above conventional repair techniques, tool
Have that heat input is few, heat affected area is small, matrix deformation is small, dilution is low, metallurgical interface combines, coating consistency is high, remediation efficiency
Not the advantages that height does not change the original size of rotor journal, is not necessarily to galleting tile spare part again.Therefore, tradition can be substituted by the technology
Technology, the abrasion reparation for low-pressure turbine rotor journal position.
It is steel alloy due to needing the turbine rotor repaired, ferrous alloy is not only close because of ingredient and matrix composition,
Interface cohesion is secured, and is compared to for Ni-based and cobalt-base alloys, at low cost, easily studied and popularization and application.Therefore, it grinds
Turbine rotor laser remanufacturing processed, which repairs special-purpose iron-base alloy powder, has very big value.Currently, used iron-based conjunction
Mainly there are two sources at bronze end: directly iron(-)base powder used in purchase hot spray-welding, or related using laser melting coating
The laser melting coating special-purpose iron-base alloy powder that research institution and manufacturer develop, but all continue to use hot spray-welding substantially from powdered ingredients
Powder material system, containing a large amount of alloying element and higher Si, B, C, this way is unscientific.Since laser is molten
It covers with hot spray-welding to alloy powder performance requirement used there are biggish gap, causes using existing hot spray-welding with from flux system
Cladding layer is easy to produce crackle when alloy powder carries out laser remanufacturing reparation, cladding layer hardness requirement when high this phenomenon it is special
Obviously.It can be seen that invent a kind of moderate cost, application effect it is significant, containing specific alloy elements, be suitable for low-pressure turbine
The iron(-)base powder of rotor journal laser remanufacturing reparation, is extremely necessary.
(3) summary of the invention
The present invention is intended to provide a kind of significant, high-efficient, applicable containing specific alloy elements, moderate cost, application effect
It is low to solve in the iron(-)base powder and the preparation method and application thereof of the turbine rotor shaft neck laser remanufacturing reparation of low pressure
Steam turbine rotor shaft is pressed to wear reparation problem.
Technical scheme is as follows:
A kind of laser remanufacturing reparation iron(-)base powder, consists of the following components in percentage by mass:
Carbon C:0.01~0.04%, chromium Cr:1.0~1.2%, silicon Si:0.5~0.8%, boron: 0.4%~0.7%, manganese
Mn:0.4~0.6%, molybdenum Mo:0.4~0.6%, surplus Fe.
Preferably, the laser remanufacturing reparation is consisted of the following components in percentage by mass with iron(-)base powder:
Carbon C:0.01%, chromium Cr:1.0%, silicon Si:0.51%, boron: 0.41%, manganese Mn:0.4%, molybdenum Mo:0.4%, iron
Fe:97.27%.
It is also preferred that the laser remanufacturing reparation iron(-)base powder is grouped by the group of following mass percent
At:
Carbon C:0.04%, chromium Cr:1.2%, silicon Si:0.8%, boron: 0.7%, manganese Mn:0.6%, molybdenum Mo:0.6%, iron
Fe:96.06%.
Iron(-)base powder ingredient design principle of the present invention are as follows:
Carbon C:0.01%~0.04%
Carbon can form carbide hard phase with other alloying elements.Carbide is easy to assemble in grain boundaries, and carbon content is excessively high,
The carbide of precipitation increases, the enhancing of re-melt deposit welding sensibility.Simultaneously in view of the hardness of cladding layer should be close with matrix hardness,
Therefore, carbon content is set as 0.01%~0.04%.
Chromium Cr:1.0%~1.2%
In order to obtain low Cr laser remanufacturing repair layer, Cr content is set as 1.0%~1.2%, it is too low to will affect
Laser remanufacturing repairs cladding layer processing performance, excessively high to be difficult to achieve the purpose that reduce cladding layer Cr content.
Silicon Si:0.5%~0.8%
In laser remanufacturing reparation, silicon can reduce the fusing point of alloy powder, improve the mobility in molten bath and to matrix
Wetability, and form borosilicate in conjunction with oxygen and boron and be covered in weld pool surface, play the role of deoxidation slag making, to avoid molten
The oxidation of coating.Silicone content is too low, does not have the effect of deoxidation slag making, and remaining silicone content increases in excessively high then cladding layer, cladding
Layer crack sensitivity enhancing, mechanical degradation, while the effect of silicon and boron is to be mutually related, silicone content will combine boron content
Setting.Therefore, as a kind of laser remanufacturing reparation alloy powder, silicone content is set as 0.5%~0.8%.
Boron: 0.4%~0.7%
In laser remanufacturing repair process, boron is combined with silicon plays the role of deoxidation slag making, meanwhile, boron can be improved molten
Coating hardness.But boron content is too high to significantly reduce cladding layer toughness, the too low effect for not having deoxidation slag making, it is contemplated that silicon
Content, set boron content as 0.4%~0.7%.
Manganese Mn:0.4%~0.6%
Manganese can properly increase the intensity and hardness of cladding layer, but manganese content is excessively high, during laser remanufacturing easily with
Oxygen combination forms oxide and is trapped in cladding layer, reduces the mechanical property of cladding layer.Therefore, set manganese content 0.4%~
0.6%.
Molybdenum Mo:0.4%~0.6%
Mo atomic binding energy power is strong, is easy to form compound hardening constituent with alloying elements such as C, in addition, the thermal expansion system of Mo
Number is small, and thermal conductivity is good, is added in cladding layer, and the intensity, toughness of cladding layer, heat resistance can be made to increase substantially.
The granularity of iron(-)base powder of the present invention is between -80~+325 mesh, the hollow powder based on areal calculation
Rate is lower than 1%, the restriction foundation of the hollow powder rate are as follows:
It, i.e., can be if the gas in hollow powder particles cannot overflow molten bath completely in laser remanufacturing repair process
" bringing into property " stomata is formed in cladding layer, can also crack defect because of stomata when serious, influences the compactness, continuous of cladding layer
Property, mechanical property, corrosion resistance etc..
It finds, when the hollow powder rate based on areal calculation is higher than 1%, can gradually go out in cladding layer in practical applications
Existing gas hole defect, adjusting process parameter are difficult to completely eliminate, therefore iron(-)base powder described herein is based on areal calculation
Hollow powder rate highest is limited to 1%.
Wherein: hollow powder rate is defined as: the sum of powder particle cross section " hole " area is total with all powder cross section
Area ratio need to inlay powder, grinding and polishing before the computation, obtain powder particle cross-sectional picture, miss to reduce measurement
Difference knows method for distinguishing analysis treated picture specimen page using pixel by photo handling software:
In formula (1), Pixhallow,iFor the pixel of powder particle cross section i-th " hole ", PixpowderIt indicates to include " empty
The total pixel in powder particle cross section including hole ".
Alloy powder hollow powder rate PixavIt is defined as the average value of the limited cross section hollow powder rate of alloy powder, it may be assumed that
M indicates selected for counting the number of alloy powder cross section in formula (2), herein alloy powder cross section with
Machine selects 3 positions, by calculating the average value of 3 cross section hollow powder rates as alloy powder hollow powder rate.
Iron(-)base powder of the present invention the preparation method comprises the following steps:
According to formula, each component raw material is mixed, after heating melting, carries out aerosolization in vacuum atomizing room, it is atomized
Powder, is utilized respectively 140 mesh (109 μm) later and 320 mesh (45 μm) series standard sieve sieves atomized powder, obtain-
Finished product iron(-)base powder between 80~+325 mesh；
The technological parameter of the aerosolization are as follows: atomizing medium N2, 1600 DEG C of smelting temperature, 150 DEG C of the degree of superheat, holding temperature
1300 DEG C, gas pressure 7MPa.
The present invention also provides application of the iron(-)base powder in the reparation of turbine rotor shaft neck laser remanufacturing.
Specifically, the method for the application includes the following steps:
(a) it by rotor journal entire surface to be repaired cutting (cutting depth is 0.2~1.5mm, preferably 0.5mm), uses
Rotor journal after acetone cleaning cutting, decontamination of deoiling；The rotor journal material to be repaired is, for example, 30Cr；
(b) iron(-)base powder is placed in baking oven, in 100~200 DEG C of heat preservations until drying；
(c) rotor journal to be repaired is preheated to 100~300 DEG C (preferably 150 DEG C), is placed under laser, uses load
Gas dust feeder is uniformly sent into the iron(-)base powder to rotor journal surface to be repaired, the irradiation of laser outgoing laser beam in
The iron(-)base powder is simultaneously melted in rotor journal surface, according to desired guiding trajectory so that the continuous cladding of the iron(-)base powder in
Rotor journal surface to be repaired forms cladding layer；
The laser optical shape of spot is the hot spot of diameter 5mm, and laser energy is uniformly distributed, and the laser power is answered
2000~4000W, laser scanning speed are 200~600mm/min, and laser head protective gas is argon gas；
The powder feeding gas that the carrier gas dust feeder uses is that (99.99%) Ar, purity are greater than argon gas, protective gas is also
Argon gas, powder feeding rate are 5~17g/min, and automatic powder feeding system is to synchronize coaxial conveying；
The cladding layer thickness in monolayer is between 0.5~1.5mm (preferably 0.8~1.2mm), taking between cladding passage
Connecing rate is 40%~60% (preferably 50%), and when continuous cladding, cladding interlayer temperature should be controlled within 300 DEG C；
(d) after the continuous cladding for completing preset range workpiece surface, workpiece is kept the temperature in 100~300 DEG C (preferably 200 DEG C)
Cooled to room temperature after 2 hours, finally by its turning to target size.
Compared with prior art, beneficial effect of the present invention is mainly reflected in:
Using the alloy powder and its application method, can be obtained under wide in range technological parameter containing particular alloy member
Element, pore-free crack defect, cladding layer of good performance are, it can be achieved that the Cr content that two layers of laser remanufacturing repairs layer surface approaches
Alloy powder ingredient, and laser remanufacturing reparation operating process is flexible, repeatability is consistent, and it is high-efficient, compared to submerged arc overlay welding etc.
Traditional technology has big advantage, is fully available for low pressure (being also applied for other high Cr ultra supercritical rotor materials) armature spindle
Neck laser remanufacturing reparation.
(4) Detailed description of the invention
Fig. 1 is the powder morphology (light microscopic and SEM) of iron(-)base powder described in embodiment 1；
Fig. 2 is the powder morphology (light microscopic and SEM) of iron(-)base powder described in embodiment 2；
Fig. 3 is the powder morphology (light microscopic and SEM) of iron(-)base powder described in embodiment 3；
Fig. 4 is the powder morphology (light microscopic and SEM) of iron(-)base powder described in embodiment 4；
Fig. 5 a laser power is to 2000W, scanning speed 400mm/min, powder sending quantity 11g/min, powder feeding carrier gas flux
For 600L/h, protection air-flow amount is 10L/min, and overlapping rate is the cladding layer metallograph under the conditions of 50%；
Fig. 5 b laser power is to 2000W, scanning speed 200mm/min, powder sending quantity 5.0g/min, powder feeding carrier gas flux
For 600L/h, protection air-flow amount is 10L/min, and overlapping rate is the cladding layer metallograph under the conditions of 50%；
Fig. 5 c laser power is to 3000W, scanning speed 400mm/min, powder sending quantity 11g/min, powder feeding carrier gas flux
For 600L/h, protection air-flow amount is 10L/min, and overlapping rate is the cladding layer metallograph under the conditions of 50%；
Fig. 5 d laser power is to 4000W, scanning speed 600mm/min, powder sending quantity 17g/min, powder feeding carrier gas flux
For 600L/h, protection air-flow amount is 10L/min, and overlapping rate is the cladding layer metallograph under the conditions of 50%；
Fig. 6 is 6 cladding layer micro-hardness testing of embodiment；
Stomata when Fig. 7 is hollow powder rate 1.1% of 8 alloy powder of embodiment based on quantitative aspects in representativeness cladding layer
And crack defect picture.
(5) specific embodiment
The present invention will be described in detail combined with specific embodiments below, and embodiment is merely to illustrate the present invention, but this hair
Bright protection scope is not limited thereto.
Embodiment 1 is used for the iron(-)base powder of low-pressure turbine rotor journal laser remanufacturing reparation
The present embodiment laser remanufacturing repairing alloy powder quality percentage is by carbon C:0.01%, chromium Cr:1.0%, silicon Si:
0.51%, boron: 0.41%, manganese Mn:0.4%, molybdenum Mo:0.4%, iron Fe:97.27% composition, the hollow powder based on areal calculation
Rate 0.1%, particle size range are -80~+325 mesh.
The preparation method comprises the following steps:
According to formula, each component raw material is mixed, after heating melting, carries out aerosolization in vacuum atomizing room, it is atomized
Powder, is utilized respectively 140 mesh (109 μm) later and 320 mesh (45 μm) series standard sieve sieves atomized powder, obtain-
Final alloy powder between 80~+325 mesh.Alloy powder atomization process parameter is shown in Table 1:
1 alloy powder atomization process parameter of table
Embodiment 2 is used for the iron(-)base powder of low-pressure turbine rotor journal laser remanufacturing reparation
The present embodiment laser remanufacturing repairing alloy powder quality percentage is by carbon C:0.04%, chromium Cr:1.2%, silicon Si:
0.8%, boron: 0.7%, manganese Mn:0.6%, molybdenum Mo:0.6%, iron Fe:96.06% composition, based on area in terms of hollow powder rate
1.0%, particle size range is -80~+325 mesh.
The preparation method is the same as that of Example 1.
Embodiment 3 is used for the iron(-)base powder of low-pressure turbine rotor journal laser remanufacturing reparation
The present embodiment laser remanufacturing repairing alloy powder quality percentage is by carbon C:0.02%, chromium Cr:1.02%, silicon
Si:0.75%, boron: 0.55%, manganese Mn:0.51%, molybdenum Mo:0.53%, iron Fe:96.62% composition, based on areal calculation
Hollow powder rate 0.5%, particle size range are -80~+325 mesh.
The preparation method is the same as that of Example 1.
Embodiment 4 is used for the iron(-)base powder of low-pressure turbine rotor journal laser remanufacturing reparation
The present embodiment laser remanufacturing repairing alloy powder quality percentage is by carbon C:0.02%, chromium Cr:1.08%, silicon
Si:0.63%, boron: 0.59%, manganese Mn:0.55%, molybdenum Mo:0.57%, iron Fe:96.56% composition, based on areal calculation
Hollow powder rate 1.1%, particle size range are -80~+325 mesh.
The preparation method is the same as that of Example 1.
Application of the iron(-)base powder described in embodiment 1 of embodiment 5 in laser remanufacturing reparation
Using the iron(-)base powder described in embodiment 1 for the laser remanufacturing reparation of low-pressure turbine rotor journal,
For the laser hot spot used for the hot spot of diameter 5mm, the automatic powder feeding system of alloy powder is to synchronize coaxial conveying.
(1) whole turnery processing is carried out to rotor journal position, turning depth is unilateral 0.5mm, cleans cutting with acetone
Rotor journal afterwards, decontamination of deoiling；
(2) rotor journal to be repaired after whole cutting is preheated to 150 DEG C to be placed under laser, adjusts laser position
It sets to region to be processed；
(3) by the iron(-)base powder described in embodiment 1 for being used for low-pressure turbine rotor journal laser remanufacturing reparation
100 DEG C~200 DEG C are placed in baking oven heat preservation until being put into powder feeder after drying；
(4) laser technical parameters are set as follows:
A) laser power is to 2000W, scanning speed 200mm/min, powder sending quantity 5.0g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
B) laser power is to 3000W, scanning speed 400mm/min, powder sending quantity 11g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
C) laser power is to 4000W, scanning speed 600mm/min, powder sending quantity 17g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
(5) cladding multilayer is repeated according to actual needs to being more than target size and there are machining allowance, and surplus is preferred
1.0mm；
(6) cooled to room temperature after keeping the temperature 2 hours for 200 DEG C of workpiece, finally by its turning to target size.
Have no that crackle images through dye penetrant inspection, microstructure of surface cladding layer is fine and close, pore-free, be mingled with, crackle the defects of.To cladding layer
Carry out EDS analysis, when element before not considering atomic number 8, the Cr content of the cladding layer second layer down to 1.03%, melts
Element at the top of coating is substantially close to the primitive component of designed alloy powder.
After having carried out a large number of experiments, preferentially selection laser remanufacturing renovation technique parameter is as described in Table 2, swashs described in table 2
Light, which remanufactures, can get satisfied cladding layer under renovation technique parameter, cladding layer pattern is as shown in Figure 5.
Application of the iron(-)base powder as described in example 2 of embodiment 6 in laser remanufacturing reparation
The powder that the present embodiment uses is 2 alloy powder of embodiment, step (1)~(3), (5)~(6) and embodiment 5
Identical, the adjustment of step (4) laser technical parameters is as follows:
A) laser power is to 2250W, scanning speed 250mm/min, powder sending quantity 6.5g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
B) laser power is to 2750W, scanning speed 350mm/min, powder sending quantity 9.5g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
C) laser power is to 3250W, scanning speed 450mm/min, powder sending quantity 12.5g/min, powder feeding carrier gas flux
For 600L/h, protection air-flow amount is 10L/min, overlapping rate 50%.
D) laser power is to 3750W, scanning speed 550mm/min, powder sending quantity 15.5g/min, powder feeding carrier gas flux
For 600L/h, protection air-flow amount is 10L/min, overlapping rate 50%.
Have no that crackle images through dye penetrant inspection, microstructure of surface cladding layer is fine and close, pore-free, be mingled with, crackle the defects of.To cladding layer
Carry out EDS analysis, when element before not considering atomic number 8, the Cr content of the cladding layer second layer down to 1.24%, melts
Element at the top of coating is substantially close to the primitive component of designed alloy powder.
Using Hv-1000 type micro Vickers, cladding layer hardness test is carried out, test method is according to " GB/T
4340.1-2009 Vickers Hardness Test part 1: test method ", test pressure be 300gf (2.942N), point away from
0.15mm protects and carries the time as 10s, tests altogether at 25 points, test result is shown in Fig. 6.Cladding layer bottom maximum hardness is 350Hv0.3, with
The number of plies increase, hardness has a downward trend, and hardness is just almost unchanged after two layers, and hardness is minimum at the top of cladding layer is down to
230Hv0.3。
Application of the iron(-)base powder described in embodiment 3 of embodiment 7 in laser remanufacturing reparation
The powder that the present embodiment uses is 2 alloy powder of embodiment, step (1)~(3), (5)~(6) and embodiment 5
Identical, the adjustment of step (4) laser technical parameters is as follows:
A) laser power is to 2500W, scanning speed 300mm/min, powder sending quantity 8g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
B) laser power is to 3500W, scanning speed 500mm/min, powder sending quantity 14g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
Have no that crackle images through dye penetrant inspection, microstructure of surface cladding layer is fine and close, pore-free, be mingled with, crackle the defects of.To cladding layer
Carry out EDS analysis, when element before not considering atomic number 8, the Cr content of the cladding layer second layer down to 1.03%, melts
Element at the top of coating is substantially close to the primitive component of designed alloy powder.
Above embodiments can obtain dense structure for the preferable embodiment of the present invention, and pore-free is mingled with, crackle etc.
The cladding layer of defect, while the number of clad layers can be reduced, after two layers, cladding layer Cr content is substantially close to designed alloyed powder
The primitive component at end, can significantly save working hour and material, improve rotor journal surface modification efficiency, have and preferably answer
Use prospect.
Application of the iron(-)base powder as described in example 4 of embodiment 8 in laser remanufacturing reparation
The powder that the present embodiment uses is 4 alloy powder of embodiment, step (1)~(3), (5)~(6) and embodiment 5
Identical, the adjustment of step (4) laser technical parameters is as follows:
A) laser power is to 2000W, scanning speed 200mm/min, powder sending quantity 5.0g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
B) laser power is to 3000W, scanning speed 400mm/min, powder sending quantity 11g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
C) laser power is to 4000W, scanning speed 600mm/min, powder sending quantity 17g/min, powder feeding carrier gas flux
600L/h, protection air-flow amount are 10L/min, overlapping rate 50%.
4 alloy powder of embodiment has been higher than 1% based on the hollow powder rate in terms of area, the gas in hollow powder particles
Molten bath cannot be overflowed completely, form stomata in cladding layer, can also crack defect when serious because of stomata, as shown in Figure 7.
The above describes the embodiments of the present invention in detail, but protection scope of the present invention is not limited to this, any
Those skilled in the art are in technical scope disclosed by the invention, the variation readily occurred in, made any modification,
Equivalent replacement etc., should be covered by the protection scope of the present invention, such as: laser remanufacturing reparation alloyed powder of the invention
End can also be used for that other high Cr are overcritical and the laser remanufacturing of ultra-supercritical steam turbine rotor axle journal is repaired.
2 laser remanufacturing of table repairs optimum technological parameters
Claims (6)
1. a kind of laser remanufacturing reparation iron(-)base powder, which is characterized in that consist of the following components in percentage by mass:
Carbon C:0.01~0.04%, chromium Cr:1.0~1.2%, silicon Si:0.5~0.8%, boron: 0.4%~0.7%, manganese Mn:
0.4~0.6%, molybdenum Mo:0.4~0.6%, surplus Fe.
2. laser remanufacturing reparation iron(-)base powder as described in claim 1, which is characterized in that the laser remanufacturing
Reparation is consisted of the following components in percentage by mass with iron(-)base powder:
Carbon C:0.01%, chromium Cr:1.0%, silicon Si:0.51%, boron: 0.41%, manganese Mn:0.4%, molybdenum Mo:0.4%, iron Fe:
97.27%.
3. laser remanufacturing reparation iron(-)base powder as described in claim 1, which is characterized in that the laser remanufacturing
Reparation is consisted of the following components in percentage by mass with iron(-)base powder:
Carbon C:0.04%, chromium Cr:1.2%, silicon Si:0.8%, boron: 0.7%, manganese Mn:0.6%, molybdenum Mo:0.6%, iron Fe:
96.06%.
4. the preparation method of laser remanufacturing reparation iron(-)base powder as described in claim 1, which is characterized in that described
The preparation method comprises the following steps:
According to formula, each component raw material is mixed, after heating melting, vacuum atomizing room carry out aerosolization, atomized powder,
Be utilized respectively later 140 mesh and 320 mesh series standards sieve atomized powder is sieved, obtain -80~+325 mesh between at
Product iron(-)base powder；
The technological parameter of the aerosolization are as follows: atomizing medium N2, 1600 DEG C of smelting temperature, 150 DEG C of the degree of superheat, holding temperature 1300
DEG C, gas pressure 7MPa.
5. laser remanufacturing reparation iron(-)base powder as described in claim 1 is in turbine rotor shaft neck laser remanufacturing
Application in reparation.
6. application as claimed in claim 5, which is characterized in that the method for the application includes the following steps:
(a) rotor journal entire surface to be repaired is cut, cutting depth is 0.2~1.5mm, after acetone cleaning cutting
Rotor journal, decontamination of deoiling；The rotor journal material to be repaired is 30Cr；
(b) iron(-)base powder is placed in baking oven, in 100~200 DEG C of heat preservations until drying；
(c) rotor journal to be repaired is preheated to 100~300 DEG C, be placed under laser, using carrier gas dust feeder to be repaired
The iron(-)base powder is uniformly sent on multiple rotor journal surface, and the irradiation of laser outgoing laser beam is in rotor journal surface and melts
Change the iron(-)base powder, according to desired guiding trajectory, so that the continuous cladding of the iron(-)base powder is in rotor journal table to be repaired
Face forms cladding layer；
The laser optical shape of spot is the hot spot of diameter 5mm, and laser energy is uniformly distributed, the laser power answers 2000~
4000W, laser scanning speed are 200~600mm/min, and laser head protective gas is argon gas；
The powder feeding gas that the carrier gas dust feeder uses is argon gas, and protective gas is also argon gas, and powder feeding rate is 5~17g/
Min, automatic powder feeding system are to synchronize coaxial conveying；
The cladding layer thickness in monolayer is between 0.5~1.5mm, and the overlapping rate between cladding passage is 40%~60%, even
When continuous cladding, cladding interlayer temperature is controlled within 300 DEG C；
(d) after the continuous cladding for completing preset range workpiece surface, natural cooling after workpiece is kept the temperature 2 hours in 100~300 DEG C
To room temperature, finally by its turning to target size.
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| CN113529071A (en) * | 2021-07-13 | 2021-10-22 | 熔创金属表面科技(常州)有限公司 | Laser cladding layer of sealing surface of track ball valve and preparation method thereof |
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Application publication date: 20190823 |