CN1629352A - Magnesium alloy laser surface reinforced repairing method - Google Patents
Magnesium alloy laser surface reinforced repairing method Download PDFInfo
- Publication number
- CN1629352A CN1629352A CN 200410020853 CN200410020853A CN1629352A CN 1629352 A CN1629352 A CN 1629352A CN 200410020853 CN200410020853 CN 200410020853 CN 200410020853 A CN200410020853 A CN 200410020853A CN 1629352 A CN1629352 A CN 1629352A
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- Prior art keywords
- magnesium alloy
- laser
- repair materials
- repair
- reparation
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Links
- 229910000861 Mg alloy Inorganic materials 0.000 title claims abstract description 85
- 238000000034 method Methods 0.000 title claims abstract description 14
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 claims abstract description 26
- 229910052786 argon Inorganic materials 0.000 claims abstract description 13
- 239000007789 gas Substances 0.000 claims abstract description 11
- 239000001307 helium Substances 0.000 claims abstract description 9
- 229910052734 helium Inorganic materials 0.000 claims abstract description 9
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract description 9
- 230000008439 repair process Effects 0.000 claims description 43
- 239000000463 material Substances 0.000 claims description 37
- 238000005728 strengthening Methods 0.000 claims description 18
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 claims description 15
- 230000002950 deficient Effects 0.000 claims description 7
- 229910002092 carbon dioxide Inorganic materials 0.000 claims description 5
- 235000011089 carbon dioxide Nutrition 0.000 claims description 5
- 239000001569 carbon dioxide Substances 0.000 claims description 5
- 230000009471 action Effects 0.000 claims description 4
- 239000000956 alloy Substances 0.000 abstract description 6
- 230000008901 benefit Effects 0.000 abstract description 2
- 230000006378 damage Effects 0.000 abstract description 2
- 230000003014 reinforcing effect Effects 0.000 abstract description 2
- 238000005266 casting Methods 0.000 description 10
- 239000011248 coating agent Substances 0.000 description 7
- 238000000576 coating method Methods 0.000 description 7
- 238000005498 polishing Methods 0.000 description 7
- 230000007797 corrosion Effects 0.000 description 6
- 238000005260 corrosion Methods 0.000 description 6
- 230000002787 reinforcement Effects 0.000 description 4
- 208000037656 Respiratory Sounds Diseases 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910001297 Zn alloy Inorganic materials 0.000 description 2
- PGTXKIZLOWULDJ-UHFFFAOYSA-N [Mg].[Zn] Chemical compound [Mg].[Zn] PGTXKIZLOWULDJ-UHFFFAOYSA-N 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- SNAAJJQQZSMGQD-UHFFFAOYSA-N aluminum magnesium Chemical compound [Mg].[Al] SNAAJJQQZSMGQD-UHFFFAOYSA-N 0.000 description 2
- 238000005282 brightening Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000011148 porous material Substances 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 238000003672 processing method Methods 0.000 description 2
- 229910052761 rare earth metal Inorganic materials 0.000 description 2
- 238000005067 remediation Methods 0.000 description 2
- 238000005275 alloying Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000003685 thermal hair damage Effects 0.000 description 1
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- Laser Beam Processing (AREA)
Abstract
The invention provides a magnesium alloy surface laser reinforcing and repairing method which comprises, using magnesium alloy material and laser beam, under atmospheric condition, protecting by using argon (or the mixed gas of helium, argon), and carrying out magnesium alloy reinforced restoring. The advantages of the invention includes, no complex apparatus such as vacuum chamber is needed, and no heat damage to magnesium alloy.
Description
Technical field
The invention belongs to the metallic surface restorative procedure, be specially the laser surface intensified restorative procedure of a kind of magnesium alloy.
Background technology
Magnesium alloy is because chemically reactive is big, in casting, machine-shaping process, be easy to defectives (because the production method of magnesium alloy is casting and is out of shape two kinds) such as generation is loose, pore, crackle, shrinkage cavity, thereby cause product percent of pass to reduce, production cost is increased, and cause in time being delivered for use of key parts such as aerospace, military affairs sometimes.
Because magnesium alloy is not corrosion-resistant, thereby makes magnesium alloy in use produce corrosion pit on magnesium alloy, thereby has a strong impact on the safe reliability of whole aircraft.Because employed magnesium alloy mostly is thin-wall part on aerospace, the guided missile, be again finished parts simultaneously, can not use argon arc welding to repair, in order to guarantee flight safety, in the past have to be because of slight corrosion pit " very reluctantly " do and scrap processing, and that the magnesium alloy member that uses on the aircraft generally all compares is expensive.
Equally,, in processing, transportation, can cause damage or scratch, and in the course of processing on its surface because magnesium alloy is not wear-resisting, operate careless slightly, just might be on magnesium alloy the multi-processing configuration that goes out a hole or do not wish when designing to occur.If can not carry out size restoration to it, whole part will be scrapped.
Summary of the invention
The present invention is directed to above problem, provide a kind of magnesium alloy laser surface intensified restorative procedure, magnesium alloy is strengthened reparation, it can " be come back to life ", can continue to use thereby can save magnesium alloy.
Technical scheme of the present invention is to realize like this, the magnesium alloy parts shape that aerospace, guided missile, automobile etc. use is various, also there is very big difference at the position that defective occurs, the invention is characterized in can be to the magnesium alloy of the various trades mark of present navigation mark defined, and the magnesium alloy of the external close trade mark, carry out the laser surface remediation intensification, hardness is higher than body material, strengthening layer and matrix are metallurgical binding, and the employed material of strengthening layer is identical or close with body material.Its processing method is:
1, the position of strengthening reparation according to the trade mark and the needs of magnesium alloy, adopt corresponding magnesium alloy repair materials, the magnesium alloy repair materials that uses is the magnesium alloy materials of the various trades mark of existing navigation mark defined, and the magnesium alloy of the external close trade mark, make corresponding magnesium alloy repair materials, because easy oxidation of magnesium alloy and burning, this repair materials is not suitable for adopting powder, can be tabular or block or strip, repair materials is covered on the defective, and tectum exceeds this surface imperfection 0.1～10mm, and the cover layer edges line is 0.1～5mm beyond the respective edges line of this surface imperfection, utilize laser to come irradiation, thereby obtain needed reinforcement repair layer.This is that the present invention is different from the notable attribute that powder is used in other laser reinforcing reparations.
2, the modes of emplacement of repair materials: adopt mechanical clamp (as instruments such as tweezers) clamping/location or directly placement, utilize laser irradiation then.
3, repair materials kind: be the various magnesium alloy materials of existing navigation mark defined, because each state all formulates the magnesium alloy standard of oneself, press the magnesium alloy trade mark, standard control table, close external magnesium alloy is also passable.
4, laser irradiation: adopt pulsed laser or carbon dioxide laser, wherein:
The pulsed laser wavelength is 1.06 microns, and average laser power is 400W-600W, the energy 10～60J of each pulse action, and pulse width is 0.5～15ms, scanning focused beam spot diameter, 0.2～2mm, pulse-repetition is 1～20Hz, sweep velocity 1-10mm/s;
Carbonic acid gas light laser wavelength is 10.6 microns, power density 10
3～10
6W/cm
2, output rating is 500～5000W, scanning focused beam spot diameter, 1～5mm, sweep velocity 3-20mm/s.
With the tectal edge line of laser alignment repair materials, begin scanning then, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.
5, do not need to carry out preheating before the surface strengthening reparation, reinforcement does not need anneal after repairing.
6, strengthening material for repairing at first needs to carry out descaling, carries out mechanical workout then.Need carry out clean to restoring area, descaling makes its surface-brightening.
Advantage of the present invention:
1, the present invention is by adopting magnesium alloy materials; use laser beam; processing method is simple; processing ease; do not need complex apparatus such as vacuum chamber; under atmospheric condition, it is just passable only to need to use argon gas (or mixed gas of helium or argon gas, helium) to protect, and defective such as loose, the pore of magnesium alloy, crackle, shrinkage cavity, corrosion pit and misrun, dimension overproof etc. are strengthened reparation.
2, the present invention does not produce thermal damage to magnesium alloy, and can carry out repeatedly remediation intensification, and is restricted to the soldering number of times unlike argon arc welding, and the heat affected zone is narrow or do not have a heat affected zone; Can only strengthen reparation to blank unlike argon arc welding, this method not only can be carried out intensive treatment to blank, all can strengthen reparation to finished parts and thin-wall part; And this method need not to strengthen preceding preheating and the anneal of strengthening after repairing.Through using, find that result of use is all well and good, not only save magnesium alloy member, and saved a large amount of funds, repaired multiple magnesium alloy parts.
Description of drawings
Because it is three major types that magnesium alloy can be divided into magnesium-aluminum alloy system, magnesium-zinc alloy system and magnesium-rare earth by alloying element, so metallograph provides ZM5 (magnesium-aluminum alloy system), ZM2 (magnesium-zinc alloy system), three kinds of alloys of ZM6 (magnesium-rare earth system) the most commonly used by above criteria for classification.
Fig. 1 is low power (50 *) metallograph of ZM5 Mg alloy surface laser repairing.
Fig. 2 is low power (100 *) metallograph of ZM2 Mg alloy surface laser repairing.
Fig. 3 is low power (50 *) metallograph of ZM6 Mg alloy surface laser repairing.
Embodiment
Embodiment 1
ZM5 Mg alloy surface laser repairing adopts same magnesium alloy repair materials to be covered on the defective, and concrete steps are as follows:
1, tectum exceeds this surface imperfection 0.6～10mm, and the cover layer edges line is 0.1～5mm beyond the respective edges line of this surface imperfection, utilizes laser to come irradiation, thereby obtains needed reinforcement repair layer.
2, the modes of emplacement of repair materials: adopt mechanical clamp (as instruments such as tweezers) clamping/location or directly placement, utilize laser irradiation then.
3, laser irradiation: adopt pulsed laser, the pulsed laser wavelength is 1.06 microns, and average laser power is 400W, the energy 30J of each pulse action, pulse width is 1-5ms, scanning focused beam spot diameter, 1mm, pulse-repetition is 10Hz, sweep velocity 3-5mm/s; Under argon shield, with laser alignment repair materials tectal edge line, begin scanning then, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.
4, the surface strengthening reparation does not need to carry out preheating, and reinforcement does not need anneal after repairing.
5, strengthening material for repairing at first needs to carry out descaling, carries out mechanical workout then.Need carry out clean to restoring area, descaling makes its surface-brightening.
Be illustrated in figure 1 as low power (50 *) metallograph of ZM5 Mg alloy surface laser repairing, repairing effect is all well and good, has not only saved magnesium alloy member, and has saved a large amount of funds.Use this method that the accessory drive gearbox of the engine charge machine casing of certain aircraft casting and aircraft engine loose carried out strengthening and repair, twice (3-10) kgf/cm that stood factory
2To suppress examination oil-proof, stood outfield subject flight examination, no abnormal.
Embodiment 2
Difference from Example 1 is:
ZM2 Mg alloy surface laser repairing, adopt same magnesium alloy repair materials, repair materials directly is placed on the reparation surface, and pulsed laser is adopted in laser irradiation, and the pulsed laser wavelength is 1.06 microns, average laser power is 500W, the energy 15J of each pulse action, pulse width is 3-5ms, scanning focused beam spot diameter, 0.5mm, pulse-repetition is 3Hz, sweep velocity 4-6mm/s; Under argon shield, with laser alignment repair materials tectal edge line, begin scanning then, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.
Be illustrated in figure 2 as low power (100 *) metallograph of ZM2 Mg alloy surface laser repairing.
We to certain aircraft before support housing repair because of the galvanic corrosion that pad causes, use through factory installation, no abnormal.
Embodiment 3
Difference from Example 1 is:
ZM6 Mg alloy surface laser repairing, adopt same magnesium alloy repair materials, repair materials directly is placed on the reparation surface, pulsed laser is adopted in laser irradiation, and the pulsed laser wavelength is 1.06 microns, and average output power is 400W, scanning focused beam spot diameter, 2mm, sweep velocity 5mm/s, pulse-repetition is 4Hz, pulse width 2-6ms.Under helium protection, with the tectal edge line of repair materials, begin scanning with laser alignment then, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.
Be illustrated in figure 3 as low power (50 *) metallograph of ZM6 Mg alloy surface laser repairing.
The surface tear that we adopt the aircraft rear portion reduction box housing (ZM6) that this method repairs is the checking by the military.Aircraft magnesium alloy MJI10 and MJI9 (Russian magnesium alloy standard to Russian import, according to the magnesium alloy trade mark, standard control table, these two kinds of alloys are close with homemade ZM6 magnesium alloy, so we have adopted the ZM6 magnesium alloy as repair materials) the atomospheric corrosion defective of annex carried out strengthening and repaired, and is through the operation in 2 years no abnormal.The concentrated shrinkage cavity of the ZM6 magnesium alloy of homemade certain missile component of repairing has been passed through the examination of relevant departments and has been delivered for use.And workman's misoperation causes the ZM6 magnesium alloy to get out the problem of a pilot hole more in the course of processing, carries out size restoration through adopting present method, is resolved.
Embodiment 4
Difference from Example 1 is:
ZM3 Mg alloy surface laser repairing adopts same magnesium alloy repair materials, repair materials directly is placed on repairs the surface, and carbon dioxide laser is adopted in laser irradiation, and carbonic acid gas light laser wavelength is 10.6 microns, power density 10
3W/cm
2, output rating is 900W, scanning focused beam spot diameter, 1mm, sweep velocity 6mm/s.Under helium protection, with the tectal edge line of laser alignment repair materials, begin scanning then, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.Now repaired the engine compressor casing and added the crackle that causes because of carelessness man-hour, the use of having installed now.
Embodiment 5
Difference from Example 1 is:
ZM1 Mg alloy surface laser repairing, the ZM2 magnesium alloy that adopts the close trade mark is as repair materials, this is that the thermal crack because of the ZM1 magnesium alloy, loose susceptibility are bigger, the material of repairing directly is placed on the reparation surface, carbon dioxide laser is adopted in laser irradiation, carbonic acid gas light laser wavelength is 10.6 microns, power density 10
5W/cm
2, output rating is 1500W, scanning focused beam spot diameter, 3mm, sweep velocity 15mm/s.Down with the tectal edge line of laser alignment repair materials, begin scanning then the mixed gas protected of argon gas, helium, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.After at present ZM1 magnesium alloy discard being repaired after testing workpiece do not have distortion.
Embodiment 6
Difference from Example 1 is:
MB3 Mg alloy surface laser repairing, adopt MB3 or MB2 magnesium alloy as repair materials, this is because MB3 is close with the chemical ingredients and the mechanical property of MB2 magnesium alloy, magnesium alloy for the close trade mark, the material of repairing directly is placed on the reparation surface, carbon dioxide laser is adopted in laser irradiation, and carbonic acid gas light laser wavelength is 10.6 microns, power density 10
5W/cm
2, output rating is 1000W, scanning focused beam spot diameter, 3.5mm, sweep velocity 10mm/s.Down with the tectal edge line of laser alignment repair materials, begin scanning then the mixed gas protected of argon gas, helium, light beam is irradiation repeatedly, forms laser melt-casting coating, grind afterwards repair, detect, operation such as polishing finishes the magnesium alloy surface strengthening reparation.After at present the part of MB3 magnesium alloy interior of aircraft annex being repaired after testing workpiece do not have distortion.
Claims (3)
1, the laser surface intensified restorative procedure of magnesium alloy is characterized in that concrete steps are as follows:
(1) material and the defective according to magnesium alloy adopts corresponding magnesium alloy repair materials to strengthen, and the repair materials modes of emplacement is for adopting mechanical system clamping/location or directly placing;
(2) argon gas or helium or argon gas, helium mixed gas protected down, use pulsed laser or carbon dioxide laser to carry out laser irradiation;
Pulsed laser carries out the processing parameter of laser irradiation:
Wavelength is 1.06 microns;
Average laser power is 400-600W;
Energy 10～the 60J of each pulse action;
Pulse width is 0.5～15ms;
Scanning focused beam spot diameter, is 0.2～2mm;
Pulse-repetition is 1～20Hz;
Sweep velocity 1-10mm/s;
The carbonic acid gas light laser carries out the processing parameter of laser irradiation:
Wavelength is 10.6 microns;
Power density 10
3～10
6W/cm
2
Output rating is 500～5000W;
Scanning focused beam spot diameter, 1～5mm;
Sweep velocity 3-20mm/s.
2, according to the laser surface intensified restorative procedure of the described magnesium alloy of claim 1, it is characterized in that: before the reparation, carry out the descaling processing earlier strengthening restoring area, make its light, repair then, need carry out descaling equally to the repair materials that is adopted and handle, make its light.
3, according to the laser surface intensified restorative procedure of right 1 described magnesium alloy, it is characterized in that: the material of reparation adopts the magnesium alloy of identical or the close trade mark; Perhaps, adopt close external magnesium alloy according to the magnesium alloy trade mark, standard control table.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100208538A CN1298880C (en) | 2004-06-30 | 2004-06-30 | Magnesium alloy laser surface reinforced repairing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100208538A CN1298880C (en) | 2004-06-30 | 2004-06-30 | Magnesium alloy laser surface reinforced repairing method |
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| Publication Number | Publication Date |
|---|---|
| CN1629352A true CN1629352A (en) | 2005-06-22 |
| CN1298880C CN1298880C (en) | 2007-02-07 |
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ID=34845690
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004100208538A Expired - Fee Related CN1298880C (en) | 2004-06-30 | 2004-06-30 | Magnesium alloy laser surface reinforced repairing method |
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| CN (1) | CN1298880C (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101985751A (en) * | 2010-12-10 | 2011-03-16 | 云南昆钢联合激光技术有限公司 | Motor mandrel surface strengthening layer compound technology |
| CN102764990A (en) * | 2011-05-04 | 2012-11-07 | 通用汽车环球科技运作有限责任公司 | System and method for manufacturing magnesium body panels with improved corrosion resistance |
| CN105479007A (en) * | 2014-09-17 | 2016-04-13 | 沈阳金研激光再制造技术开发有限公司 | Defect mending method for casting Ti3A1-type alloy plate disk by laser beam welding |
| CN109662251A (en) * | 2019-03-01 | 2019-04-23 | 四川光友薯业有限公司 | A kind of potato convenient rice flour noodles and its processing method |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2128251Y (en) * | 1992-06-30 | 1993-03-17 | 沈阳工业学院 | Die cast ram through laser surface treatment |
| CN1056549C (en) * | 1997-05-17 | 2000-09-20 | 中国科学院金属腐蚀与防护研究所 | Laser repairing and reconstructing process method for damaged area of high-temperature high-speed wheel disc |
| CN1164794C (en) * | 2001-02-21 | 2004-09-01 | 中国科学院金属研究所 | Technology method for laser direct forming copper base alloy valve holder on car engine cylinder cover |
-
2004
- 2004-06-30 CN CNB2004100208538A patent/CN1298880C/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101985751A (en) * | 2010-12-10 | 2011-03-16 | 云南昆钢联合激光技术有限公司 | Motor mandrel surface strengthening layer compound technology |
| CN102764990A (en) * | 2011-05-04 | 2012-11-07 | 通用汽车环球科技运作有限责任公司 | System and method for manufacturing magnesium body panels with improved corrosion resistance |
| CN102764990B (en) * | 2011-05-04 | 2014-12-17 | 通用汽车环球科技运作有限责任公司 | System and method for manufacturing magnesium body panels with improved corrosion resistance |
| CN105479007A (en) * | 2014-09-17 | 2016-04-13 | 沈阳金研激光再制造技术开发有限公司 | Defect mending method for casting Ti3A1-type alloy plate disk by laser beam welding |
| CN109662251A (en) * | 2019-03-01 | 2019-04-23 | 四川光友薯业有限公司 | A kind of potato convenient rice flour noodles and its processing method |
| CN109662251B (en) * | 2019-03-01 | 2022-11-18 | 四川光友薯业有限公司 | Potato instant rice noodles and processing method thereof |
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| Publication number | Publication date |
|---|---|
| CN1298880C (en) | 2007-02-07 |
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