CN107675167A - A kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure - Google Patents
A kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure Download PDFInfo
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- CN107675167A CN107675167A CN201710785359.8A CN201710785359A CN107675167A CN 107675167 A CN107675167 A CN 107675167A CN 201710785359 A CN201710785359 A CN 201710785359A CN 107675167 A CN107675167 A CN 107675167A
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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
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
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Abstract
The invention belongs to technical field of laser processing, is related to a kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure, is mainly used in the reparation of aircraft unimach component surface burn into micro-crack equivalent damage.Early stage uses same " deposited metals impact flexibility >=420KJ/m2, temperature-room type plasticity >=10.8%, mechanical properties >=1400MPa " reparation metal dust; carried out Direct Laser cladding reparation and ultrasonic impact auxiliary laser cladding repairing test on 30CrMnSiNi2A unimach undercarriage semiaxis matrixes, and room temperature tensile, room temperature impact and the microhardness performance in both reparation areas be tested respectively.Draw：The average tensile strength of Direct Laser cladding reparation is 1428.6MPa, and average elongation 11.8%, average impact toughness is 471KJ/m2, it is 474.3HV to repair metal average microhardness；The average tensile strength of ultrasonic impact auxiliary laser cladding reparation is 1436.2MPa, and average elongation 14.8%, average impact toughness is 643KJ/m2, it is 490.7HV to repair metal average microhardness.
Description
Technical field
The invention belongs to technical field of laser processing, is related to a kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding
Restorative procedure, it is mainly used in the reparation of aircraft unimach component surface burn into micro-crack equivalent damage.
Background technology
At present, aircraft finds that superhigh intensity steel member has the damage such as surface corrosion, micro-crack afterwards under arms when overhauling
Wound, when maintenance factory is repaired using conventional argon arc welding method, the weld seam and its heat affected area surface that find reparation easily go out
Now new weld crack, and then cause component to be scrapped.And when using laser cladding method progress renovation technique exploitation, find to repair
Still easily there is postwelding crackle in formed metal surfaces, through analyzing surface, the producing cause of the crackle be mainly residual stress into
Caused ductility-dip crack under shape high temperature.Therefore, to solve the problems, such as that single laser melting coating reparation easily causes ductility-dip crack, compel to be essential
Seek the recovery technique for seeking or inventing a kind of new aircraft unimach component surface damage.
The content of the invention
It is an object of the invention to provide a kind of superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure.
The particular content of technical solution of the present invention is：
(1) laser repairing material, room temperature impact toughness >=420KJ/m2, temperature-room type plasticity >=10.8, mechanical properties
≥1400MPa；The material is globular metallic powder, it is desirable to which powder size is 45 μm~150 μm, and powder sphericity >=90% is empty
Heart powder rate≤0.1%, inclusion rates≤5/200g, size≤100 μm；
(2) removing surface before repairing, under fluorescent light, polishing remove crack defect, and visual inspection unstressed configuration is shown, is removed
After crackle, 90 ° of gap opened angle=, with wire wheel polishing grinding surface, finally cleaned with acetone；
(3) ultrasonic impact auxiliary laser cladding reparation, recover to lack using ultrasonic impact+Process of Powder Feeding Laser Cladding complex method
Fall into the size of position, i.e., in laser melting coating repair process, molten bath solidification moment, by ultrasonic impact device to solidifying weld seam table
The surface ultrasonic implement treatment that face synchronizes；After cladding terminates, visual inspection gap position fills up, laser melting coating
Technological parameter is：Laser power 400W~700W, 0.3~0.8mm of spot diameter, 400~600mm/min of speed, powder feeding rate
0.8~2.0rpm, 5~10L/min of powder feeding gas, 10~15L/min of protective gas；Ultrasonic impact technological parameter：Dash current 1A
~3A, impact speed, 6~30cm/min, frequency 20kHz~50kHz, amplitude are 30 μm~50 μm, striker pin diameter Ф
3.0mm；Laser melting coating uses multilayer cladding, and thickness in monolayer is controlled between 0.1~0.5mm, in repair process, using contact
Hand-held temperature measurer, control repair position matrix temperature rise nearby within 150 DEG C；
(4) polishing processing, restoring area is processed using the mode of repairing is thrown by hand, recovers accessory size；
(5) Non-Destructive Testing, using fluorescent penetrating inspection method, check repairing position；It is required that flawless defect；
(6) stress relief annealing, using crawler type ceramic heat band, local destressing annealing is carried out to laser repairing region,
Restoring area residual stress is eliminated, heat treating regime is：230 DEG C × 2h, air cooling；
(7) bead, laser repairing region is handled using blasting technology, strengthens and repairs surface；
(8) refine, thrown by hand using oilstone and repair laser repairing region, improve surface roughness.
The present invention has the advantage that and beneficial effect,
Ultrasonic impact auxiliary laser cladding is a kind of new compound increasing material manufacturing restorative procedure, both inherits laser melting coating
The heating of method, cooling velocity are fast, and matrix heat affected area is small, repair the advantages that deformation is small.Meanwhile aid in the ultrasonic impact repaired
Processing, which has, alleviates welding stress effect, reduces weld seam and its cracking of heat affecting in welding process to a certain extent and inclines
To., can be with especially when welding and repairing the superhigh intensity steel member such as 300M, 30CrMnSiNi2A with strong crack sensitivity
Weld preheating is avoided, is favorably improved remediation efficiency.
Based on the advantage of ultrasonic impact auxiliary laser cladding recovery technique, early stage using it is same " deposited metals impact it is tough
Property >=420KJ/m2, temperature-room type plasticity >=10.8%, mechanical properties >=1400MPa " reparation metal dust,
Direct Laser cladding reparation has been carried out on 30CrMnSiNi2A unimach undercarriage semiaxis matrixes and ultrasonic impact auxiliary swashs
Light cladding repairing test, and room temperature tensile, room temperature impact and the microhardness performance in both reparation areas are surveyed respectively
Examination.Draw：The average tensile strength of Direct Laser cladding reparation is 1428.6MPa, average elongation 11.8%, average impact
Toughness is 471KJ/m2, it is 474.3HV to repair metal average microhardness；The average drawing of ultrasonic impact auxiliary laser cladding reparation
It is 1436.2MPa to stretch intensity, and average elongation 14.8%, average impact toughness is 643KJ/m2, it is average micro- to repair metal
Hardness is 490.7HV.As can be seen here, superhigh intensity steel member is repaired using ultrasonic impact auxiliary laser melting and coating technique can significantly carry
Height repairs the temperature-room type plasticity and impact flexibility in area, and greatly improving with temperature-room type plasticity and impact flexibility, it will help drop
Tearing tendency during low military service, fatigue strength is improved, so as to improve the extension service life after repairing.
The achievement of the invention can be directly used for the reparation of the defects of undercarriage semiaxis crackle, corrosion, be overhauled for aircraft
It is cost-effective, also provide technical support to occur Similar Problems on aircraft.
Embodiment
Technical solution of the present invention is described in further detail below with reference to example：
According to the installation position of superhigh intensity steel member to be repaired, analysis need to repair the force-bearing situation and cracks at position
And reason, confirm component materials composition, manufacturing process and structure composition, clearly require the repair materials of selection, divide more than
Analysis and confirmation, implement step in detail below：
(1) laser repairing material, room temperature impact toughness >=420KJ/m2, temperature-room type plasticity >=10.8%, room temperature tensile is strong
Degree >=1400MPa；The material is globular metallic powder, it is desirable to powder size is 45 μm~150 μm, powder sphericity >=90%,
Hollow powder rate≤0.1%, inclusion rates≤5/200g, size≤100 μm；
(2) removing surface before repairing, under fluorescent light, polishing remove crack defect, and visual inspection unstressed configuration is shown, is removed
After crackle, 90 ° of gap opened angle=, with wire wheel polishing grinding surface, finally cleaned with acetone；
(3) ultrasonic impact auxiliary laser cladding reparation, recover to lack using ultrasonic impact+Process of Powder Feeding Laser Cladding complex method
Fall into the size of position, i.e., in laser melting coating repair process, molten bath solidification moment, by ultrasonic impact device to solidifying weld seam table
The surface ultrasonic implement treatment that face synchronizes；After cladding terminates, visual inspection gap position fills up, laser melting coating
Technological parameter is：Laser power 400W~700W, 0.3~0.8mm of spot diameter, 400~600mm/min of speed, powder feeding rate
0.8~2.0rpm, 5~10L/min of powder feeding gas, 10~15L/min of protective gas；Ultrasonic impact technological parameter：Dash current 1A
~3A, impact speed, 6~30cm/min, frequency 20kHz~50kHz, amplitude are 30 μm~50 μm, striker pin diameter Ф
3.0mm；Laser melting coating uses multilayer cladding, and thickness in monolayer is controlled between 0.1~0.5mm, in repair process, using contact
Hand-held temperature measurer, control repair position matrix temperature rise nearby within 150 DEG C；
(4) polishing processing, restoring area is processed using the mode of repairing is thrown by hand, recovers accessory size；
(5) Non-Destructive Testing, using fluorescent penetrating inspection method, check repairing position；It is required that flawless defect；
(6) stress relief annealing, using crawler type ceramic heat band, local destressing annealing is carried out to laser repairing region,
Restoring area residual stress is eliminated, heat treating regime is：230 DEG C × 2h, air cooling；
(7) bead, laser repairing region is handled using blasting technology, strengthens and repairs surface；
(8) refine, thrown by hand using oilstone and repair laser repairing region, improve surface roughness.
Instantiation one
Certain type undercarriage semiaxis crack defect is repaired using ultrasonic impact auxiliary laser melting and coating technique
1. undercarriage semiaxis cracks confirm
Aircraft undercarriage semiaxis, material is 30CrMnSiNi2A unimach, in semiaxis thrust bolt mounting groove
There is long 30mm, deep 0.2mm crackle,
2. repair process and inspection
(1) impact flexibility and weldability is selected to be repaiied better than the unimach material metal dust of half shaft material as laser
Multiple material, powder indices meet to require.
(2) removing surface before repairing, under fluorescent light, crack defect is removed using hand-held electric rifle polishing, visually inspects nothing
Fluorescence display, after removing crackle, gap opened angle is about 80 °, deep 0.3mm, with wire wheel polishing grinding surface, finally with third
Ketone is cleaned；
(3) ultrasonic impact auxiliary laser cladding reparation, the chi of powder melting technology recovery defective locations is dosed using laser
Very little, visual inspection gap position has welded completely, and leaves about 0.2mm processing capacity, and the technological parameter of laser repairing is：Laser power
600W, spot diameter 0.8mm, speed 500mm/min, powder feeding rate 1.2rpm, powder feeding gas 5L/min, protective gas 15L/min；
Ultrasonic impact technological parameter：Dash current 1.5A, impact speed, 20cm/min, frequency 30kHz, amplitude are 30 μm, and striker pin is straight
Footpath Ф 3.0mm；Laser repairing uses multilayer cladding, and thickness in monolayer is controlled between 0.1~0.5mm, and in repair process, control is repaiied
Reset puts matrix temperature rise nearby within 150 DEG C.
(4) polishing processing, restoring area is processed using the mode of repairing is thrown by hand, removes and repairs surplus, recover accessory size；
(5) Non-Destructive Testing, using fluorescent penetrating inspection method, laser repairing region is checked, flawless defect；
(6) stress relief annealing, using crawler type ceramic heat band, local destressing annealing is carried out to laser repairing region,
Restoring area residual stress is eliminated, heat treating regime is：230 DEG C × 2h, air cooling；
(7) bead, laser repairing region is handled using blasting technology, strengthens and repairs surface；
(8) refine, thrown by hand using oilstone and repair laser repairing region, surface roughness is tested to be Ra1.6.
Compared with prior art, using the undercarriage semiaxis flawless defect of technical solution of the present invention reparation, assembling is met
It is required that installation checking has been carried out, and process operation is convenient, process stabilizing is reproducible, technology maturation.It can be widely popularized.
Claims (1)
- A kind of 1. superhigh intensity steel member ultrasonic impact auxiliary laser cladding restorative procedure, it is characterised in that：The step of this method It is：(1) laser repairing material, room temperature impact toughness >=420KJ/m2, temperature-room type plasticity >=10.8%, mechanical properties >= 1400MPa；The material is globular metallic powder, it is desirable to which powder size is 45 μm~150 μm, and powder sphericity >=90% is hollow Powder rate≤0.1%, inclusion rates≤5/200g, size≤100 μm；(2) removing surface before repairing, under fluorescent light, polishing remove crack defect, and visual inspection unstressed configuration is shown, removes crackle Afterwards, 90 ° of gap opened angle=, with wire wheel polishing grinding surface, finally cleaned with acetone；(3) ultrasonic impact auxiliary laser cladding reparation, defective bit is recovered using ultrasonic impact+Process of Powder Feeding Laser Cladding complex method The size put, i.e., in laser melting coating repair process, molten bath solidification moment, solidification face of weld is entered by ultrasonic impact device The synchronous surface ultrasonic implement treatment of row；After cladding terminates, visual inspection gap position fills up, the technique of laser melting coating Parameter is：Laser power 400W~700W, 0.3~0.8mm of spot diameter, 400~600mm/min of speed, powder feeding rate 0.8~ 2.0rpm, 5~10L/min of powder feeding gas, 10~15L/min of protective gas；Ultrasonic impact technological parameter：Dash current 1A~3A, Impact speed, 6~30cm/min, frequency 20kHz~50kHz, amplitude are 30 μm~50 μm, striker pin diameter Ф 3.0mm；Laser Cladding uses multilayer cladding, and thickness in monolayer is controlled between 0.1~0.5mm, and in repair process, thermometric is held using contact Instrument, control repair position matrix temperature rise nearby within 150 DEG C；(4) polishing processing, restoring area is processed using the mode of repairing is thrown by hand, recovers accessory size；(5) Non-Destructive Testing, using fluorescent penetrating inspection method, check repairing position；It is required that flawless defect；(6) stress relief annealing, using crawler type ceramic heat band, local destressing annealing is carried out to laser repairing region, eliminated Restoring area residual stress, heat treating regime are：230 DEG C × 2h, air cooling；(7) bead, laser repairing region is handled using blasting technology, strengthens and repairs surface；(8) refine, thrown by hand using oilstone and repair laser repairing region, improve surface roughness.
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109226761A (en) * | 2018-10-31 | 2019-01-18 | 南京理工大学 | A kind of device of the compound increasing material manufacturing of electron beam-supersonic synergic |
| CN109443916A (en) * | 2018-09-04 | 2019-03-08 | 北京航空航天大学 | The research method of metal bath Free Surface process of setting information |
| CN110552005A (en) * | 2019-09-26 | 2019-12-10 | 航发优材(镇江)增材制造有限公司 | Valve body multi-surface continuous abrasion fixing device and laser repairing method |
| CN110860808A (en) * | 2019-12-06 | 2020-03-06 | 大连理工大学 | Inductively coupled ultrasonic-assisted pulse laser welding device and method |
| CN111069371A (en) * | 2019-12-30 | 2020-04-28 | 安徽机电职业技术学院 | Heavy plate composite processing method and heavy plate |
| CN111593343A (en) * | 2020-06-10 | 2020-08-28 | 中国航发北京航空材料研究院 | Process method for repairing flap slide rail chromium plating surface chipping defect by laser cladding |
| CN111745159A (en) * | 2020-06-10 | 2020-10-09 | 中国航发北京航空材料研究院 | Laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance |
| CN112853346A (en) * | 2021-01-08 | 2021-05-28 | 中车青岛四方机车车辆股份有限公司 | Laser cladding remanufacturing device and remanufacturing method for railway vehicle axle |
| CN113718246A (en) * | 2021-09-09 | 2021-11-30 | 南通大学 | Maritime work platform pile leg laser composite repairing method capable of eliminating cladding layer interface |
| CN113878119A (en) * | 2021-09-18 | 2022-01-04 | 航发优材(镇江)增材制造有限公司 | Laser direct deposition repair method for abrasion of tight-lock coupler for high-speed rail |
| CN113878120A (en) * | 2021-09-18 | 2022-01-04 | 航发优材(镇江)增材制造有限公司 | Laser direct deposition repair process method for abrasion of roller groove tip for airplane |
| WO2023056663A1 (en) * | 2021-10-09 | 2023-04-13 | 华南理工大学 | Method for repairing crack on surface of steel structure by additive manufacturing |
| WO2023077606A1 (en) * | 2021-11-05 | 2023-05-11 | 中车株洲电机有限公司 | Method for repairing surface cracks of shaft parts |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102747364A (en) * | 2012-06-14 | 2012-10-24 | 燕山大学 | Method for restoring inner bore of gear coupling |
| CN105821408A (en) * | 2016-05-03 | 2016-08-03 | 中国航空工业集团公司北京航空材料研究院 | Method for adopting laser cladding to repair TC4-DT titanium alloys |
-
2017
- 2017-09-04 CN CN201710785359.8A patent/CN107675167A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102747364A (en) * | 2012-06-14 | 2012-10-24 | 燕山大学 | Method for restoring inner bore of gear coupling |
| CN105821408A (en) * | 2016-05-03 | 2016-08-03 | 中国航空工业集团公司北京航空材料研究院 | Method for adopting laser cladding to repair TC4-DT titanium alloys |
Non-Patent Citations (2)
| Title |
|---|
| 张颖等: "超声冲击激光熔覆层的应力场数值模拟", 《应用激光》 * |
| 戚永爱: "基于超声冲击的激光快速成形镍基高温合金强化技术研究", <<硕士学位论文>> * |
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| CN109443916B (en) * | 2018-09-04 | 2020-11-17 | 北京航空航天大学 | Research method of solidification process information of free surface of metal melt |
| CN109443916A (en) * | 2018-09-04 | 2019-03-08 | 北京航空航天大学 | The research method of metal bath Free Surface process of setting information |
| CN109226761A (en) * | 2018-10-31 | 2019-01-18 | 南京理工大学 | A kind of device of the compound increasing material manufacturing of electron beam-supersonic synergic |
| CN110552005A (en) * | 2019-09-26 | 2019-12-10 | 航发优材(镇江)增材制造有限公司 | Valve body multi-surface continuous abrasion fixing device and laser repairing method |
| CN110860808A (en) * | 2019-12-06 | 2020-03-06 | 大连理工大学 | Inductively coupled ultrasonic-assisted pulse laser welding device and method |
| CN110860808B (en) * | 2019-12-06 | 2021-04-20 | 大连理工大学 | Inductively coupled ultrasonic-assisted pulse laser welding device and method |
| CN111069371A (en) * | 2019-12-30 | 2020-04-28 | 安徽机电职业技术学院 | Heavy plate composite processing method and heavy plate |
| CN111745159A (en) * | 2020-06-10 | 2020-10-09 | 中国航发北京航空材料研究院 | Laser additive repair method for titanium alloy undercarriage upper stay bar fit out-of-tolerance |
| CN111593343A (en) * | 2020-06-10 | 2020-08-28 | 中国航发北京航空材料研究院 | Process method for repairing flap slide rail chromium plating surface chipping defect by laser cladding |
| CN111593343B (en) * | 2020-06-10 | 2022-03-15 | 中国航发北京航空材料研究院 | Process method for repairing flap slide rail chromium plating surface chipping defect by laser cladding |
| CN112853346A (en) * | 2021-01-08 | 2021-05-28 | 中车青岛四方机车车辆股份有限公司 | Laser cladding remanufacturing device and remanufacturing method for railway vehicle axle |
| CN113718246A (en) * | 2021-09-09 | 2021-11-30 | 南通大学 | Maritime work platform pile leg laser composite repairing method capable of eliminating cladding layer interface |
| CN113878119A (en) * | 2021-09-18 | 2022-01-04 | 航发优材(镇江)增材制造有限公司 | Laser direct deposition repair method for abrasion of tight-lock coupler for high-speed rail |
| CN113878120A (en) * | 2021-09-18 | 2022-01-04 | 航发优材(镇江)增材制造有限公司 | Laser direct deposition repair process method for abrasion of roller groove tip for airplane |
| WO2023056663A1 (en) * | 2021-10-09 | 2023-04-13 | 华南理工大学 | Method for repairing crack on surface of steel structure by additive manufacturing |
| WO2023077606A1 (en) * | 2021-11-05 | 2023-05-11 | 中车株洲电机有限公司 | Method for repairing surface cracks of shaft parts |
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