CN114672759A - Aluminum alloy wear surface size repairing method - Google Patents
Aluminum alloy wear surface size repairing method Download PDFInfo
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- CN114672759A CN114672759A CN202210367640.0A CN202210367640A CN114672759A CN 114672759 A CN114672759 A CN 114672759A CN 202210367640 A CN202210367640 A CN 202210367640A CN 114672759 A CN114672759 A CN 114672759A
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- 238000000034 method Methods 0.000 title claims abstract description 46
- 229910000838 Al alloy Inorganic materials 0.000 title claims abstract description 33
- 239000000843 powder Substances 0.000 claims abstract description 72
- 238000005488 sandblasting Methods 0.000 claims abstract description 30
- 239000010410 layer Substances 0.000 claims abstract description 25
- 238000007750 plasma spraying Methods 0.000 claims abstract description 24
- 239000011248 coating agent Substances 0.000 claims abstract description 22
- 238000000576 coating method Methods 0.000 claims abstract description 22
- 229910000789 Aluminium-silicon alloy Inorganic materials 0.000 claims abstract description 20
- 229910000943 NiAl Inorganic materials 0.000 claims abstract description 20
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 claims abstract description 20
- 239000002344 surface layer Substances 0.000 claims abstract description 11
- 230000003746 surface roughness Effects 0.000 claims abstract description 11
- 238000003754 machining Methods 0.000 claims abstract description 7
- 238000004140 cleaning Methods 0.000 claims abstract description 6
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims description 26
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 13
- 229910052782 aluminium Inorganic materials 0.000 claims description 13
- 229910052786 argon Inorganic materials 0.000 claims description 13
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims description 12
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 12
- 239000001257 hydrogen Substances 0.000 claims description 12
- 229910052739 hydrogen Inorganic materials 0.000 claims description 12
- 239000002245 particle Substances 0.000 claims description 12
- 238000005507 spraying Methods 0.000 claims description 8
- 230000007547 defect Effects 0.000 claims description 7
- 229910052759 nickel Inorganic materials 0.000 claims description 6
- 229910052710 silicon Inorganic materials 0.000 claims description 6
- 239000010703 silicon Substances 0.000 claims description 6
- 239000004820 Pressure-sensitive adhesive Substances 0.000 claims description 5
- 239000003960 organic solvent Substances 0.000 claims description 4
- 230000000873 masking effect Effects 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 2
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 description 8
- 239000007921 spray Substances 0.000 description 6
- 229910052593 corundum Inorganic materials 0.000 description 4
- 239000010431 corundum Substances 0.000 description 4
- 239000012535 impurity Substances 0.000 description 4
- 238000007689 inspection Methods 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 239000004576 sand Substances 0.000 description 4
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical group CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 3
- 238000010288 cold spraying Methods 0.000 description 3
- 238000007781 pre-processing Methods 0.000 description 3
- 238000005422 blasting Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000007788 roughening Methods 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/067—Metallic material containing free particles of non-metal elements, e.g. carbon, silicon, boron, phosphorus or arsenic
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/08—Metallic material containing only metal elements
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses a size repairing method for an aluminum alloy wear surface, relates to the field of maintenance of aero-engines, and aims to realize size repairing for the wear surface of an aluminum alloy part. The technical scheme of the invention is as follows: the method for repairing the size of the wear surface of the aluminum alloy part is used for repairing the size of the wear surface of the aluminum alloy part, and comprises the following steps: cleaning the wear surface of the part, performing shielding protection before sand blasting on the part outside the repair area, and then performing sand blasting coarsening on the repair area; carrying out plasma spraying on NiAl powder on the repair area to form a bonding bottom layer; plasma spraying AlSi powder on the bonding bottom layer to form a working surface layer; and machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements. The size repairing method of the aluminum alloy wear surface realizes the size repairing of the wear surface of the aluminum alloy part, and can be used for the size repairing of the inner ring of the bearing shell of the aero-engine.
Description
Technical Field
The invention relates to the field of maintenance of aero-engines, in particular to a method for repairing the size of an aluminum alloy wear surface in a plasma spraying mode.
Background
The bearing shell of a certain type of aircraft engine is made of cast aluminum alloy, the bearing shell is positioned between the transition speed reducer and the exhaust casing, an inner ring of the bearing shell is matched with an output shaft of the power turbine, and the output shaft provides a torque signal through rotation or deflection. After the aircraft engine is in service, the inner ring of the bearing shell is often abraded or damaged, so that the size is out of tolerance, and the assembly requirement of a product cannot be met. In order to reduce the manufacturing and processing cost of new products and shorten the complete repair cycle of the aircraft engine, the size of the worn position of the bearing shell needs to be repaired.
At present, the size repair of aluminum alloy parts mainly adopts a surfacing method and a cold spraying repair, the surfacing method mainly adopts argon arc welding and laser welding, the repair efficiency is low, the joint strength is not high, the cold spraying repair efficiency is high, the bonding strength is high, but the cold spraying process requirement is high, high-purity Ar is required to be used, the air consumption is huge, and the cost is high.
Disclosure of Invention
The invention provides a method for repairing the size of an aluminum alloy wear surface, and aims to repair the size of the wear surface of an aluminum alloy part.
The technical scheme adopted by the invention is as follows: the method for repairing the size of the wear surface of the aluminum alloy part is used for repairing the size of the wear surface of the aluminum alloy part, for example, the part is a bearing shell of an aircraft engine, and the wear surface is an inner ring surface of the bearing shell, and comprises the following steps:
s1, repairing pretreatment: cleaning the wear surface of the part, carrying out shielding protection before sand blasting on the part outside the repair area, and then carrying out sand blasting coarsening on the repair area.
Further, the method comprises the following steps: in step S1, before cleaning the wear surface of the component, the wear surface is turned or polished until the wear surface has no crack defect.
Specifically, the method comprises the following steps: in step S1, the wear surface is cleaned by an organic solvent. For example, the organic solvent is absolute ethanol or acetone.
Specifically, the method comprises the following steps: in step S1, a tool and/or a high-temperature pressure-sensitive adhesive tape is used for shielding protection before sandblasting.
Specifically, the method comprises the following steps: in step S1, the sand blasting pressure is 0.2-0.4 MPa, and the surface roughness of the repair range is 4.0-8.0 μm after sand blasting coarsening.
And S2, carrying out plasma spraying on NiAl powder on the repair area to form a bonding bottom layer.
In step S2, the NiAl powder is an atomized powder composed of 93-97% by mass of nickel and the balance of aluminum, and has a particle size of 45-90 μm.
Specifically, the method comprises the following steps: in step S2, parameters of plasma spraying NiAl powder: the argon flow is 80-120 SCFH, the hydrogen flow is 20-35 SCFH, the current is 600-640A, the powder feeding rate is 30-45% RPM, the spraying distance is 120-150 mm, and the coating thickness is 0.05-0.15 mm.
And S3, performing plasma spraying of AlSi powder on the bonding bottom layer to form a working surface layer.
In step S3, the AlSi powder is an atomized powder composed of 86 to 90% by mass of aluminum and the balance of silicon, and has a particle size of 45 to 75 μm.
Specifically, the method comprises the following steps: in step S3, parameters of the plasma sprayed AlSi powder: the argon flow is 90-130 SCFH, the hydrogen flow is 10-25 SCFH, the current is 610-630A, the spraying distance is 120-150 mm, the powder feeding rate is 65-80% RPM, and the thickness of the coating is 0.20-0.60 mm.
And S4, machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements.
The invention has the beneficial effects that: the method for repairing the size of the wear surface of the aluminum alloy realizes the size repair of the wear surface of the part made of the aluminum alloy, and has the characteristics of simple process, low cost and high repair efficiency. The invention adopts plasma spraying NiAl powder to form the bonding bottom layer, reduces the difference of the thermal expansion coefficients between the substrate and the working surface layer, and provides a foundation for the subsequent spraying of the working surface layer with larger thickness. On the basis of bonding the bottom layer, plasma spraying is carried out on AlSi powder to form a working surface layer, the working surface layer is compact and high in hardness, the bonding strength can reach more than 50MPa, and when the size repair of the wear surface is completed, the size repair cost is reduced, and the size repair efficiency is improved. After the repairing area is machined, better surface quality can be obtained, the components with repaired sizes meet the assembly requirements, the part remanufacturing cost is saved, and the mass production is favorably realized.
Drawings
FIG. 1 is a microstructure view of an aluminum alloy wear surface after dimensional restoration in accordance with the present invention.
Detailed Description
The invention relates to a size repairing method of an aluminum alloy wear surface, which is used for repairing the size of the wear surface of an aluminum alloy part. For example, the bearing shell of a certain type of aircraft engine is made of cast aluminum alloy, the inner ring surface of the bearing shell is abraded or damaged, so that the dimensional tolerance is caused, and the bearing shell can be repaired according to the dimensional repairing method of the invention to restore the diameter of the inner ring. The method for repairing the size of the wear surface of the aluminum alloy comprises the following steps:
and S1, repairing pretreatment.
The repair pretreatment is intended to prepare for subsequent plasma spraying, including cleaning of the wear surface of the component, masking protection of the part outside the repair area prior to blasting, and blasting roughening of the repair area. Considering that the surface of the parts is generally stained with oil and other impurities, the worn surface can be cleaned by an organic solvent, such as absolute ethyl alcohol or acetone.
The purpose of sand blasting is to coarsen the repair area, so as to facilitate the subsequent formation of a stable bonding bottom layer, for example, the surface roughness of the repair area is controlled to be 4.0-8.0 μm. In order to control the surface roughness in the repair range to 4.0-8.0 microns, the sand blasting pressure can be 0.2-0.4 MPa, 46-60 meshes of white corundum sand can be selected as a sand blasting medium, and the roughness test can be carried out along with a test sample. In order to avoid damage to parts outside the repair area, masking protection before sandblasting may be performed using tooling and/or high temperature pressure sensitive tape.
If the wearing surface of the part has defects such as cracks or the like, before the wearing surface of the part is cleaned, the wearing surface can be turned or polished to remove a wearing layer and a damaged layer. If necessary, the method can also carry out fluorescence penetration inspection to ensure that the wear surface has no defects such as cracks.
And S2, carrying out plasma spraying on NiAl powder on the repair area to form a bonding bottom layer.
The NiAl powder is atomized powder, and consists of 93-97% of nickel and the balance of aluminum by mass, and the particle size of the powder is 45-90 mu m. Parameters of plasma spraying NiAl powder: the argon flow is 80-120 SCFH, the hydrogen flow is 20-35 SCFH, the current is 600-640A, the powder feeding rate is 30-45% RPM, the spraying distance is 120-150 mm, and the coating thickness is 0.05-0.15 mm.
And S3, performing plasma spraying of AlSi powder on the base layer to form a working surface layer.
The AlSi powder is atomized powder, and consists of 86-90% of aluminum and the balance of silicon by mass, and the particle size of the powder is 45-75 mu m. Parameters of plasma-sprayed AlSi powder: the argon flow is 90-130 SCFH, the hydrogen flow is 10-25 SCFH, the current is 610-630A, the spraying distance is 120-150 mm, the powder feeding rate is 65-80% RPM, and the coating thickness is 0.20-0.60 mm.
And S4, machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements.
The method is used for size repair of the inner ring surface of the bearing shell, has the advantages of simple process, low spraying cost, high coating bonding strength, controllable coating thickness and the like, is more compact and higher in hardness than a sprayed aluminum coating, can finally obtain better surface quality, and realizes size repair of the diameter of the inner ring of the bearing shell of the aero-engine.
The present invention will be further described with reference to the following examples.
Example 1
The method comprises the following steps of carrying out size repair on an inner ring surface of a bearing shell of a certain type of aeroengine:
and S1, repairing and preprocessing.
Firstly, turning an inner ring surface of a bearing shell, removing a wear layer and a damaged layer, and carrying out fluorescence permeation inspection on the inner ring surface to ensure that the inner ring surface has no defects such as cracks; secondly, wiping the turned inner ring surface and the sample to be measured with acetone, and removing oil stains and impurities; thirdly, shielding and protecting the parts outside the repair area before sand blasting by adopting a tool and a high-temperature pressure-sensitive adhesive tape; and finally, carrying out sand blasting treatment on the repair area and the test sample by using 46-mesh white corundum sand to coarsen the inner ring surface of the part and the surface of the test sample, wherein the sand blasting pressure is 0.3MPa, and after the sand blasting is finished, the part is respectively blown clean by clean and dry compressed air, and the roughness of the surface of the test sample is 6.3 mu m.
And S2, carrying out plasma spraying NiAl powder on the repaired area to form a bonding bottom layer.
The NiAl powder is atomized powder and consists of 95.4% of nickel and 4.6% of aluminum by mass, and the particle size of the powder is 45-90 mu m. Parameters of plasma spraying NiAl powder: the argon flow rate was 100SCFH, the hydrogen flow rate was 27.5SCFH, the current was 620A, the spray distance was 135mm, the powder feed rate was 38% RPM, and the coating thickness was 0.10 mm.
And S3, performing plasma spraying of AlSi powder on the base layer to form a working surface layer.
The AlSi powder is atomized powder, and consists of 87.8% of aluminum and 12.2% of silicon by mass, and the particle size of the powder is 45-90 mu m. Parameters of plasma-sprayed AlSi powder: the argon flow was 110SCFH, the hydrogen flow was 17.5SCFH, the current was 620A, the spray distance was 135mm, the powder feed rate was 72% RPM, and the coating thickness was 0.54 mm.
And S4, machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements, namely completing size repair of the diameter of the inner ring of the bearing shell. The microstructure of the nickel-base superalloy wear surface after dimensional restoration according to the above procedure is shown in fig. 1.
Example 2
Carrying out size repair on an inner ring surface of a bearing shell of a certain type of aeroengine, and comprising the following steps:
and S1, repairing and preprocessing.
Firstly, turning the inner annular surface of the bearing shell, removing a wear layer and a damaged layer, and carrying out fluorescence permeation inspection on the inner annular surface to ensure that the inner annular surface has no defects such as cracks; secondly, wiping the turned inner ring surface and the tested sample with absolute ethyl alcohol, and removing oil stains and impurities; thirdly, shielding and protecting the part outside the repair area before sand blasting by adopting a high-temperature pressure-sensitive adhesive tape; and finally, carrying out sand blasting treatment on the repair area and the test sample by adopting 60-mesh white corundum sand to coarsen the inner ring surface of the part and the surface of the test sample, wherein the sand blasting pressure is 0.2MPa, the sand blasting is finished, then the sand blasting is respectively carried out by clean and dry compressed air, and the roughness of the surface of the test sample is 4.2 mu m.
And S2, carrying out plasma spraying on NiAl powder on the repair area to form a bonding bottom layer.
The NiAl powder is atomized powder and consists of 95.2% of nickel and 4.8% of aluminum by mass, and the particle size of the powder is 45-90 microns. Parameters of plasma spraying NiAl powder: the argon flow was 120SCFH, the hydrogen flow was 20SCFH, the current was 640A, the spray distance was 120mm, the powder feed rate was 45% RPM, and the coating thickness was 0.12 mm.
And S3, performing plasma spraying of AlSi powder on the base layer to form a working surface layer.
The AlSi powder is atomized powder and consists of 88.3% of aluminum and 11.7% of silicon by mass, and the particle size of the powder is 45-90 mu m. Parameters of plasma-sprayed AlSi powder: the argon flow was 130SCFH, the hydrogen flow was 10SCFH, the current was 620A, the spray distance was 120mm, the powder feed rate was 65% RPM, and the coating thickness was 0.46 mm.
And S4, machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements, namely completing the size repair of the diameter of the inner ring of the bearing shell.
Example 3
The method comprises the following steps of carrying out size repair on an inner ring surface of a bearing shell of a certain type of aeroengine:
and S1, repairing and preprocessing.
Firstly, turning the inner annular surface of the bearing shell, removing a wear layer and a damaged layer, and carrying out fluorescence permeation inspection on the inner annular surface to ensure that the inner annular surface has no defects such as cracks; secondly, wiping the turned inner ring surface and the sample to be measured with acetone, and removing oil stains and impurities; thirdly, shielding and protecting the parts outside the repair area before sand blasting by adopting a tool and a high-temperature pressure-sensitive adhesive tape; and finally, carrying out sand blasting treatment on the repair area and the test sample by adopting 60-mesh white corundum sand to coarsen the inner ring surface of the part and the surface of the test sample, wherein the sand blasting pressure is 0.4MPa, the sand blasting is finished, then the sand blasting is respectively carried out by clean and dry compressed air, and the roughness of the surface of the test sample is 7.2 mu m.
And S2, carrying out plasma spraying on NiAl powder on the repair area to form a bonding bottom layer.
The NiAl powder is atomized powder and consists of 95.1% of nickel and 4.9% of aluminum by mass, and the particle size of the powder is 45-90 mu m. Parameters of plasma spraying NiAl powder: the argon flow was 80SCFH, the hydrogen flow was 35SCFH, the current was 600A, the spray distance was 140mm, the powder feed rate was 30% RPM, and the coating thickness was 0.08 mm.
And S3, performing plasma spraying of AlSi powder on the base layer to form a working surface layer.
The AlSi powder is atomized powder and consists of 87.9% of aluminum and 12.1% of silicon by mass, and the particle size of the powder is 45-90 microns. Parameters of plasma-sprayed AlSi powder: argon flow was 90SCFH, hydrogen flow was 25SCFH, current was 610A, spray distance was 140mm, powder feed rate was 80% RPM, and coating thickness was 0.58 mm.
And S4, machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements, namely completing size repair of the diameter of the inner ring of the bearing shell.
Claims (10)
1. The aluminum alloy wear surface size repairing method is used for repairing the size of the wear surface of the aluminum alloy part and is characterized in that: the method comprises the following steps:
s1, repairing pretreatment: cleaning the wear surface of the part, performing shielding protection before sand blasting on the part outside the repair area, and then performing sand blasting coarsening on the repair area;
s2, carrying out plasma spraying on NiAl powder on the repair area to form a bonding bottom layer;
s3, performing plasma spraying of AlSi powder on the bonding bottom layer to form a working surface layer;
and S4, machining the repair area to enable the thickness and the surface roughness of the coating to meet the process requirements.
2. The method of repairing the size of an aluminum alloy wear surface of claim 1, wherein: the parts are bearing shells of aero-engines, and the wear surfaces are inner annular surfaces of the bearing shells.
3. The method of repairing the size of an aluminum alloy wear surface of claim 1, wherein: in step S1, before cleaning the wear surface of the component, the wear surface is turned or polished until the wear surface has no crack defect.
4. The method of repairing the size of an aluminum alloy wear surface of claim 1, wherein: in step S1, the wear surface is cleaned by an organic solvent.
5. The method of repairing the size of an aluminum alloy wear surface of claim 1, wherein: in step S1, masking protection before sandblasting is performed using a tool and/or a high-temperature pressure-sensitive adhesive tape.
6. The method of repairing the size of an aluminum alloy wear surface of claim 1, wherein: in step S1, in step S1, the sand blasting pressure is 0.2 to 0.4MPa, and the surface roughness of the repair range after sand blasting coarsening is 4.0 to 8.0 μm.
7. The method for repairing the size of an aluminum alloy wear surface according to any one of claims 1 to 6, wherein: in step S2, the NiAl powder is atomized powder composed of 93-97% by mass of nickel and the balance of aluminum, and has a particle size of 45-90 μm.
8. The method of repairing the size of an aluminum alloy wear surface of claim 7, wherein: in step S2, parameters of plasma spraying NiAl powder: the argon flow is 80-120 SCFH, the hydrogen flow is 20-35 SCFH, the current is 600-640A, the powder feeding rate is 30-45% RPM, the spraying distance is 120-150 mm, and the coating thickness is 0.05-0.15 mm.
9. The method for repairing the size of an aluminum alloy wear surface according to any one of claims 1 to 6, wherein: in step S3, the AlSi powder is an atomized powder composed of 86 to 90% by mass of aluminum and the balance of silicon, and has a particle size of 45 to 75 μm.
10. The method of repairing the dimensions of an aluminum alloy wear surface of claim 9, wherein: in step S3, parameters of the plasma sprayed AlSi powder: the argon flow is 90-130 SCFH, the hydrogen flow is 10-25 SCFH, the current is 610-630A, the spraying distance is 120-150 mm, the powder feeding rate is 65-80% RPM, and the coating thickness is 0.20-0.60 mm.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19711756A1 (en) * | 1997-03-21 | 1998-09-24 | Audi Ag | Coating light metal alloy workpiece |
| EP1652952A1 (en) * | 2004-10-29 | 2006-05-03 | United Technologies Corporation | Methods for repairing workpieces using microplasma spray coating |
| CN103710660A (en) * | 2013-12-24 | 2014-04-09 | 中国人民解放军装甲兵工程学院 | Method for size restoring and reinforcing of outer wall and inner wall of water-cooling cylinder sleeve of engine |
| CN105970142A (en) * | 2016-05-24 | 2016-09-28 | 中国航空工业集团公司北京航空材料研究院 | Method for aluminum-silicon abradable seal coating through explosion spraying |
| WO2017012769A1 (en) * | 2015-07-23 | 2017-01-26 | Volkswagen Aktiengesellschaft | Method for coating a cylinder barrel of a cylinder crankcase, cylinder crankcase with a coated cylinder barrel and engine |
-
2022
- 2022-04-08 CN CN202210367640.0A patent/CN114672759A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19711756A1 (en) * | 1997-03-21 | 1998-09-24 | Audi Ag | Coating light metal alloy workpiece |
| EP1652952A1 (en) * | 2004-10-29 | 2006-05-03 | United Technologies Corporation | Methods for repairing workpieces using microplasma spray coating |
| CN103710660A (en) * | 2013-12-24 | 2014-04-09 | 中国人民解放军装甲兵工程学院 | Method for size restoring and reinforcing of outer wall and inner wall of water-cooling cylinder sleeve of engine |
| WO2017012769A1 (en) * | 2015-07-23 | 2017-01-26 | Volkswagen Aktiengesellschaft | Method for coating a cylinder barrel of a cylinder crankcase, cylinder crankcase with a coated cylinder barrel and engine |
| CN105970142A (en) * | 2016-05-24 | 2016-09-28 | 中国航空工业集团公司北京航空材料研究院 | Method for aluminum-silicon abradable seal coating through explosion spraying |
Non-Patent Citations (1)
| Title |
|---|
| RADU L. ORBAN ET.AL.: "NiAl Behavior at Plasma Spray Deposition", 《MATERIALS SCIENCE FORUM》, vol. 534, pages 1545 - 1548 * |
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