CN106676515B - A kind of gas turbine turbine cylinder split laser sealing coating material - Google Patents
A kind of gas turbine turbine cylinder split laser sealing coating material Download PDFInfo
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- CN106676515B CN106676515B CN201510763690.0A CN201510763690A CN106676515B CN 106676515 B CN106676515 B CN 106676515B CN 201510763690 A CN201510763690 A CN 201510763690A CN 106676515 B CN106676515 B CN 106676515B
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- coating material
- gas turbine
- turbine
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
- C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
- C23C24/106—Coating with metal alloys or metal elements only
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Laser Beam Processing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The present invention discloses a kind of gas turbine turbine cylinder split laser sealing coating material, and composition has Ni, Cr, Mo, Fe, Cu, B, Si, C, wherein the percentage of each component are as follows: C:0.2~0.5%；Cr:18~24%；Cu:24~30%；Mo:3~7%；Fe:1.0~1.4%；B:0.4~0.9%；Si:0.2~0.6%；Ni: surplus.The present invention passes through selected alloy substrate intensified element, crystal grain refinement boundary-strengthening element, and the degree of preferably each component, alloy powder is set to obtain superior comprehensive performance, alloy powder is especially realized while with good drawability, anti-oxidant, corrosion-resistant and erosive wear resistant performance is increased again, meets property requirement of the gas turbine split to cladding layer high temperature resistant, corrosion resistance and erosion resistance abrasion and good drawability and sealing performance etc..
Description
Technical field
The present invention relates to a kind of alloy powder materials for being suitable for laser melting coating, are used for gas turbine more particularly to one kind
The laser of turbine cylinder split reparation obturages nickel-base alloy powder powder material.
Background technique
Gas turbine cylinder split leads to block distortion, split combination is not tight, gap width since long period uses
Maximum can reach 1mm, minimum 0.2mm.Solve the problems, such as that this conventional method seals for gluing, but often sealing does not live, and causes to leak
Gas.Through preliminary surveying, combustion turbine power decline 1%-2% or so will cause, while bringing temperature between gas turbine engine excessively high,
Blower burden lotus is overweight between turbine, also considerably increases energy consumption.
Laser melting coating recovery technique has obtained rapid popularization in recent years and has answered extensively as a kind of advanced re-manufacturing technology
With.
Laser melting coating is to obtain and high property the defects of pore-free, crackle in conjunction with matrix strong metallurgical in metal surface
Can surface coating advanced re-manufacturing technology, it can by dystectic alloy material cladding low melting point substrate surface,
High performance surface covering can be prepared on low-cost substrates, to replace a large amount of advanced, high performance integral materials, saved
Precious metal reduces components cost.
Laser melting and coating technique solves the insurmountable material of the conventional repairings method such as vibratory weld, argon arc welding, spraying, coating
The contradiction that limitation, technical process thermal stress, thermal deformation, material grains be coarse, basis material bond strength is difficult to ensure is selected,
A kind of new approach is provided for the reparation of product remanufacturing and failure components.
Currently, not having the dedicated alloy powder material of laser melting coating to sell on domestic and international market, majority is using thermal spraying
Or the metal powder of surfacing, or on the basis of existing metal powder by heterogeneity proportion, take powder mixing machine mode system
Alloy powder material needed for standby laser melting coating.
On as this cast iron member of gas turbine turbine cylinder split, it can be repaired using laser melting and coating process,
The alloy powder for being suitable for laser melting coating can be made, retrieves and investigates through the applicant: there is no the correlation of this respect both at home and abroad
Report.
Summary of the invention
It is an object of the invention to solve the above problem of the existing technology, after repetition test and research, one is provided
The dedicated gas turbine turbine cylinder split laser sealing coating material of kind, makes it combine laser melting and coating technique, can be effectively
For repairing gas turbine turbine cylinder split, using laser seal coating, in the case where not damaging substrate performance, Neng Gouyou
Effect solves cylinder split leakage problem.On the one hand it can be improved gas turbine unit power 1%-2% or so, while also solving
The excessively high problem of gas turbine work room temperature.
The gas turbine turbine cylinder split laser sealing coating material is led on the component base of existing pure nickel electrode
The high temperature oxidation resistance that addition element Cr, Mo improve cladding region is crossed, coating drawability is improved by addition element Cu,
Alloy substrate reinforcing is carried out by addition B, Si etc. elements and improve cladding performance, make the powder that there is higher hardness, intensity
Meanwhile and there is good toughness and high temperature oxidation resistance, white structure is not formed with cast iron effect, crack tendence is minimum
The characteristics of.The Co-based alloy powder on the turbine cylinder split of gas leakage, is formed anti-by the processing method cladding of laser melting coating
Oxidation, corrosion resistance and erosion resistance abrasion, the seal line with certain drawability and cladding superior performance, to solve turbine
The technical problem of cylinder split gas leakage.
The technical solution that the present invention provides is: this gas turbine turbine cylinder split laser sealing coating material, group
At including Ni, Cr, Mo, Fe, its main feature is that further including having Cu, B, Si, C, wherein (quality) percentage of each component is.
C:0.2~0.5%；Cr:18~24%；Cu:24~30%；Mo:3~7%；Fe:1.0~1.4%；B:0.4~
0.9；Si:0.2~0.6；Ni: surplus.
The present invention is by largely testing and creative work, selected alloy substrate intensified element, crystal grain refinement crystal boundary
Intensified element, and the degree of preferably each component, make alloy powder obtain superior comprehensive performance, especially realize
Alloy powder increases anti-oxidant, corrosion-resistant and erosive wear resistant performance while with good drawability.Meet
Gas turbine split is to cladding layer high temperature resistant, corrosion resistance and erosion resistance abrasion and good drawability and sealing performance etc.
Property requirement.
The combustion engine turbine cylinder split laser sealing coating material that the present invention provides is by vacuum melting, vacuum aerosol
What the processes such as change, screening were prepared meticulously, granularity is -100+270 mesh.
The combustion engine turbine cylinder split laser sealing coating material that the present invention provides, using complete solid in practical cladding operation
The technological parameter of state 1KW laser, the dusty material described in combustion engine turbine cylinder split laser melting coating is: power: 1000~
1200W, spot diameter: 1~2mm, scanning speed: 50~100mm/min sets powder thickness: 0.3~1.0mm.
Compared with prior art, the beneficial effects of the invention are as follows.
1. the gas turbine turbine cylinder split laser sealing coating material is on the basis of nickel chromium triangle copper alloy, addition is closed
Auri body intensified element, crystal grain refinement and boundary-strengthening element, and adjust the degree of each element.Pass through a variety of reinforcing hands
Section, reinforced alloys matrix, and grain boundary quality is improved, so that alloy is obtained good comprehensive performance.Having to realize alloy
While having good drawability, and increase anti-oxidant, corrosion-resistant and erosive wear resistant performance.It meets in gas turbine and divides
In face of the property requirement of cladding layer high temperature resistant, corrosion resistance and erosion resistance abrasion and good drawability and sealing performance etc..
2. the gas turbine turbine cylinder split laser sealing coating material is molten suitable for combustion engine turbine cylinder split laser
It covers, by the cladding alloy powder material, so that gas turbine turbine cylinder split is avoided gas leakage, improve efficiency, effectively solve
Problem is repaired in combustion engine of having determined turbine cylinder split gas leakage.
Specific embodiment
Embodiment 1.
With all solid state 1KW laser, laser melting coating is carried out to combustion engine turbine cylinder split.The sealing coating material of design closes
The mass percent of gold element is.
C: 0.3%； Cr: 18%；Cu:26%；Mo:4%；Fe:1.1%；B:0.5%；Si:0.4%；
Ni: surplus.
Its melting and coating process parameter is: power: 1200W, spot diameter: 2mm, scanning speed: 75mm/min sets powder thickness:
0.8mm。
Its granularity is -100+270 mesh.
This gas turbine turbine cylinder split laser sealing coating material that the present invention provides, can satisfy following want
It asks: 1) performance of flushing of resistance to gas: to guarantee that laser obturages cylinder body air tight, sealing coating material in an overhaul time (4 years)
There must be preferable scour resistance, therefore laser obturages material in the case where meeting other performance condition, should select as far as possible high hard
Coating material is spent, improves the scour resistance of coating, coating hardness cannot be below 100HV；2) seal coating drawability: due to
Deformation and local corrosion of the cylinder body split in longtime running, split gap is 0.2-0.8mm when no seal coating, and not
Energy precise measurement, to guarantee that laser obturages the sealing performance of cylinder body, sealing coating material must have preferable drawability, pressure
When prolonging deflection and reaching 30%, coating does not crack；3) high-temperature behavior of sealing coating material: cylinder body actual motion temperature is 400-
600 degrees Celsius, sealing coating material cannot soften at this temperature, and coating material passes through 400-600 degrees Celsius, anneal within 24 hours
Hardness decline afterwards is no more than 30HV.
Embodiment 2.
With all solid state 1KW laser, laser melting coating is carried out to combustion engine turbine cylinder split.The sealing coating material of design closes
The mass percent of gold element is.
C: 0.2%； Cr: 20%；Cu:28%；Mo:5%；Fe:1.3%；B:0.4%；Si:0.5%；
Ni: surplus.
Its melting and coating process parameter is: power: 1200W, spot diameter: 2mm, scanning speed: 75mm/min sets powder thickness:
0.8mm。
Its granularity is -100+270 mesh.
This gas turbine turbine cylinder split laser sealing coating material that the present invention provides, can satisfy following want
It asks: 1) performance of flushing of resistance to gas: to guarantee that laser obturages cylinder body air tight, sealing coating material in an overhaul time (4 years)
There must be preferable scour resistance, therefore laser obturages material in the case where meeting other performance condition, should select as far as possible high hard
Coating material is spent, improves the scour resistance of coating, coating hardness cannot be below 100HV；2) seal coating drawability: due to
Deformation and local corrosion of the cylinder body split in longtime running, split gap is 0.2-0.8mm when no seal coating, and not
Energy precise measurement, to guarantee that laser obturages the sealing performance of cylinder body, sealing coating material must have preferable drawability, pressure
When prolonging deflection and reaching 30%, coating does not crack；3) high-temperature behavior of sealing coating material: cylinder body actual motion temperature is 400-
600 degrees Celsius, sealing coating material cannot soften at this temperature, and coating material passes through 400-600 degrees Celsius, anneal within 24 hours
Hardness decline afterwards is no more than 30HV.
Embodiment 3.
With all solid state 1KW laser, laser melting coating is carried out to combustion engine turbine cylinder split.The sealing coating material of design closes
The mass percent of gold element is.
C: 0.4%； Cr: 22%；Cu:25%；Mo:3%；Fe:1.2%；B:0.6%；Si:0.2%.
Ni: surplus.
Its melting and coating process parameter is: power: 1200W, spot diameter: 2mm, scanning speed: 75mm/min sets powder thickness:
0.8mm。
Its granularity is -100+270 mesh.
This gas turbine turbine cylinder split laser sealing coating material that the present invention provides, can satisfy following want
It asks: 1) performance of flushing of resistance to gas: to guarantee that laser obturages cylinder body air tight, sealing coating material in an overhaul time (4 years)
There must be preferable scour resistance, therefore laser obturages material in the case where meeting other performance condition, should select as far as possible high hard
Coating material is spent, improves the scour resistance of coating, coating hardness cannot be below 100HV；2) seal coating drawability: due to
Deformation and local corrosion of the cylinder body split in longtime running, split gap is 0.2-0.8mm when no seal coating, and not
Energy precise measurement, to guarantee that laser obturages the sealing performance of cylinder body, sealing coating material must have preferable drawability, pressure
When prolonging deflection and reaching 30%, coating does not crack；3) high-temperature behavior of sealing coating material: cylinder body actual motion temperature is 400-
600 degrees Celsius, sealing coating material cannot soften at this temperature, and coating material passes through 400-600 degrees Celsius, anneal within 24 hours
Hardness decline afterwards is no more than 30HV.
Claims (2)
1. a kind of gas turbine turbine cylinder split laser sealing coating material, composition includes Ni, Cr, Mo, Fe, feature
It is to further include having Cu, B, Si, C, wherein the mass percent of each component are as follows:
C:0.2%, Cr:20%, Cu:28%, Mo:5%, Fe:1.3%, B:0.4%,
Si:0.5%, Ni: surplus.
2. a kind of gas turbine turbine cylinder split laser sealing coating material, composition includes Ni, Cr, Mo, Fe, feature
It is to further include having Cu, B, Si, C, wherein the mass percent of each component are as follows:
C:0.4%, Cr:22%, Cu:25%, Mo:3%, Fe:1.2%, B:0.6%,
Si:0.2%, Ni: surplus.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510763690.0A CN106676515B (en) | 2015-11-11 | 2015-11-11 | A kind of gas turbine turbine cylinder split laser sealing coating material |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510763690.0A CN106676515B (en) | 2015-11-11 | 2015-11-11 | A kind of gas turbine turbine cylinder split laser sealing coating material |
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| CN106676515A CN106676515A (en) | 2017-05-17 |
| CN106676515B true CN106676515B (en) | 2019-03-15 |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111041472A (en) * | 2019-11-28 | 2020-04-21 | 上海大陆天瑞激光表面工程有限公司 | Laser replication process method for mortise of hub of ground gas turbine |
| CN112795212A (en) * | 2020-12-29 | 2021-05-14 | 北京科技大学广州新材料研究院 | High-performance corrosion-resistant coating and preparation method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102021564A (en) * | 2009-09-17 | 2011-04-20 | 沈阳大陆激光技术有限公司 | Anticorrosive coating nickel-based alloy powder for laser cladding |
| CN103981518A (en) * | 2014-05-16 | 2014-08-13 | 杭州大冶激光科技有限公司 | Laser cladding method for improving abrasion resistance of mechanical seal sleeve for pump |
| CN106636754A (en) * | 2015-11-03 | 2017-05-10 | 上海闸电燃气轮机发电有限公司 | Split face laser seal coating process in gas turbine cylinder |
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2015
- 2015-11-11 CN CN201510763690.0A patent/CN106676515B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102021564A (en) * | 2009-09-17 | 2011-04-20 | 沈阳大陆激光技术有限公司 | Anticorrosive coating nickel-based alloy powder for laser cladding |
| CN103981518A (en) * | 2014-05-16 | 2014-08-13 | 杭州大冶激光科技有限公司 | Laser cladding method for improving abrasion resistance of mechanical seal sleeve for pump |
| CN106636754A (en) * | 2015-11-03 | 2017-05-10 | 上海闸电燃气轮机发电有限公司 | Split face laser seal coating process in gas turbine cylinder |
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