CN104674231B - The surface reinforcing method of aluminium alloy and its composite material - Google Patents
The surface reinforcing method of aluminium alloy and its composite material Download PDFInfo
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- CN104674231B CN104674231B CN201310629089.3A CN201310629089A CN104674231B CN 104674231 B CN104674231 B CN 104674231B CN 201310629089 A CN201310629089 A CN 201310629089A CN 104674231 B CN104674231 B CN 104674231B
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Abstract
The present invention relates to a kind of aluminium alloy and its surface reinforcing method of composite material parts, belong to metal surface enhanced technical field.First, blasting treatment is carried out to aluminium alloy and its composite material parts, sand particle diameter is 70~200 μm, cleaning surface lubricant, pollution impurity and fold defect；Secondly, corrosion treatment is carried out to aluminium alloy and its composite material parts, is first placed into sodium hydrate aqueous solution and soaks, then clear water rinses, and places into salpeter solution and soaks, and clear water rinses, and finally dries up, and removes surface sand-blasting trace：Finally, bead is carried out to aluminium alloy and its composite material parts, bullet uses spherical glass ball, and particle diameter is 70~200 μm, forms compressive stress layer.Aluminium alloy and its composite material parts can significantly improve the mechanical performances such as anti-fatigue performance, the wear-resisting property of material after this method is handled.
Description
Technical field
The invention belongs to metal surface enhanced technical field, the surface of more particularly to a kind of aluminium alloy and its composite material is strong
Change method.
Background technology
Aluminium alloy and its composite material have density is small, specific strength is high, specific stiffness is high, antifatigue and croop property is good,
It is corrosion-resistant to wait excellent performance, through the lightweight structure materials application frequently as first choice in fields such as aerospace, auto industrys.
Shot peening strengthening is a kind of important means that can effectively improve parts anti-fatigue performance, it can be in metal surface
A residual compressive stress layer is formed, can prevent germinating and extension with delay fatigue crackle, improves the fatigue life of parts.Separately
Outer surface residual compressive stress can also strengthen parts wear-resisting property, can effectively prevent stress corrosion, improve its corrosion
Fatigue life.
Aluminium alloy and its composite material are as a kind of aerospace key construction part, its surface quality is to its fatigue
Aging effects are very sensitive.Traditional method for surface hardening is only that the parts Jing Guo Plastic Forming are directly sprayed
Ball processing, the middle processing without any link.But actually parts terminate rear surface in Plastic Forming can remain very much
Lubricant (such as graphite), and the other impurity (such as iron filings) introduced in Plastic Forming link, if parts shape is answered
It is miscellaneous then there may be forging defects such as many folding, pits, only can not fully erased above-mentioned impurity by single bead
And defect, or even some impurity can be pressed into forging top layer, provide supremacy clause, the tired longevity of forging for the germinating of fatigue crack
Life can decrease.Therefore, obtain a cleaning, have it is particularly important that surface peening layer of residual compressive stress.
The content of the invention
It is an object of the invention to provide a kind of aluminium alloy and its surface reinforcing method of composite material parts, the surface
Intensifying method strengthening layer is cleaner, cost is low, production efficiency is high, can significantly improve anti-fatigue performance, the wearability of material
The mechanical performances such as energy.
A kind of surface reinforcing method of aluminium alloy and its composite material parts, comprises the following steps：
(1) blasting treatment is carried out to aluminium alloy and its composite material parts, sand particle diameter is 70~200 μm, clears up table
Face lubricant, pollution impurity and fold defect etc.；
(2) corrosion treatment is carried out to aluminium alloy and its composite material parts, is first placed into sodium hydrate aqueous solution and soaks
Bubble, then clear water flushing, places into salpeter solution and soaks, and clear water rinses, and finally dries up, and removes surface sand-blasting trace：
(3) bead is carried out to aluminium alloy and its composite material parts, bullet uses spherical glass ball, particle diameter 70
~200 μm, form compressive stress layer.
For load assembly, component surface quality can significantly affect its fatigue life, surface quality is good,
There are compression strengthening layer, then its fatigue life is longer, so obtaining a cleaning, having the surface peening layer of residual compressive stress outstanding
To be important.
In the present invention, blasting treatment is carried out to aluminium alloy and its composite material parts first, is preferably cut using sand
Ability is cut to clear up the lubricant that surface is introduced in the Plastic Forming stage, pollution impurity or fold defect etc., sand particle diameter is 70
~200 μm, jet length is 10~40cm, 0.2~1MPa of gas pressure, the too small or too big sand cutting energy force difference of particle diameter,
Sandblasting efficiency is low.
Then, corrosion treatment is carried out to aluminium alloy and its composite material parts, be first placed into mass concentration for 10%~
20%th, temperature is to be soaked in 50~80 DEG C of sodium hydrate aqueous solution, and clear water rinses after soaking time is 5~15min, Ran Houfang
Entering and soaked in the salpeter solution that mass concentration is 5%~10%, temperature is room temperature, clear water rinses after soaking time is 1~3min, then
Drying；Remove surface sand-blasting trace.After blasting treatment, material surface can produce short cut that many sands leave (see Fig. 2
(a)), this surface is very beneficial for fatigue crack initiation, can greatly reduce the service life of parts, so using price
Sodium hydroxide solution cheap, easy to operate is corroded removing, then using in salpeter solution and remaining sodium hydroxide solution,
Finally obtain a smooth, clean surface.
Finally, bead is carried out to aluminium alloy and its composite material parts, produces a clean compressive stress layer, bullet
Ball selects spherical glass ball, and particle diameter is 70~200 μm, and jet length is 10~40cm, 0.2~1MPa of gas pressure.
The surface reinforcing method of the present invention can be widely applied to the casting of 2XXX systems and 6XXX line aluminium alloys and its composite material
Part and forging part.
The present invention aluminium alloy and its composite material parts surface reinforcing method the advantages of be：This method cost is low,
The surface peening layer that production efficiency is high, can obtain a cleaning, have residual compressive stress, has that strengthening layer is cleaner, cost is low
And production efficiency it is high the characteristics of, the mechanical performances such as anti-fatigue performance, the wear-resisting property of material can be significantly improved.
Below by embodiment and attached drawing, the present invention will be further described, but does not mean that and the present invention is protected
The limitation of scope.
Brief description of the drawings
Fig. 1 is the surface intensified technique general flow chart of aluminium alloy and its composite material parts.
Fig. 2 (a) is 15vol.%SiCpMicrostructure picture (Hitachi's S-4800 types after/2009Al composite material forging sandblastings
Cold field emission scanning electron microscope, amplifies 400 times).
Fig. 2 (b) is 15vol.%SiCpMicrostructure picture (Hitachi's S-4800 types after the corrosion of/2009Al composite materials forging
Cold field emission scanning electron microscope, amplifies 400 times).
Fig. 2 (c) is 15vol.%SiCpMicrostructure picture (Hitachi's S-4800 types after/2009Al composite material forging shot-peenings
Cold field emission scanning electron microscope, amplifies 400 times).
Embodiment
As shown in Figure 1, be the letter of the surface intensified technique flow of aluminium alloy of the present invention and its composite material parts, including it is right
Parts carry out blasting treatment, three steps of corrosion treatment and bead.First to aluminium alloy and its composite material parts
Blasting treatment is carried out, surface lubricant, pollution impurity or fold defect etc. are cleared up using the preferable cutting power of sand；Then
Corrosion treatment is carried out, removes surface sand-blasting trace；Bead is finally carried out, material surface is produced a clean compression
Layer, so as to significantly improve the mechanical performances such as the anti-fatigue performance of material, wear-resisting property.
Embodiment 1：
The experiment material of the present embodiment is 15vol.%SiCp/ 2009Al composite material forging.Specific implementation method：First
Step, carries out composite material forging blasting treatment, cleaning surface lubricant, pollution impurity or fold defect etc., and sand particle diameter is
150 μm, jet length 10cm, gas pressure 1MPa；Second step, carries out corrosion treatment to composite material forging, removes surface
Sandblasting trace：Clear water after soaking 10min is first placed into the sodium hydrate aqueous solution that mass concentration is 10%, temperature is 70 DEG C to rush
Wash, be then placed in the salpeter solution that mass concentration is 5%, temperature is room temperature clear water after soaking 3min and rinse, then dry up；3rd
Step, bead is carried out to composite material forging, produces compressive stress layer, and bullet selects spherical glass ball, and particle diameter is 70 μm, injection
Distance is 20cm, gas pressure 1MPa.
Fig. 2 is 15vol.%SiCp/ 2009Al composite materials forging surface microscopic tissue after blasting treatment, by spray
After sand processing (Fig. 2 (a)), forging surface has been covered with short cut, these cuts can bring adverse effect, institute to forging fatigue behaviour
That must be removed.After sodium hydroxide solution corrodes (Fig. 2 (b)), the remaining short cut of sandblasting is cleaned out, forging table
Face is smooth, has one layer of SiC particulate exposed outside.After bead (Fig. 2 (c)), exposed SiC particulate is knocked de-
Fall, produce to form one layer of uniform ball hole on forging surface.After tested, forging hardness is 160HB before shot-peening, is after shot-peening
180HB, improves 12.5%.Drawing-pulling shaft shows to testing fatigue, and when loading stress is 380MPa, the circulation cycle of material is by spraying
2 × 10 before ball5Improve to 3 × 106。
Embodiment 2：
The experiment material of the present embodiment is 2024Al plates.Specific implementation method：The first step, sprays 2024Al plates
Sand processing, cleaning surface lubricant, pollution impurity or fold defect etc., sand particle diameter is 100 μm, jet length 20cm, gas
Body pressure 0.5MPa；Second step, carries out corrosion treatment to 2024Al plates, removes surface sand-blasting trace：It is dense to be first placed into quality
Spend and rinsed to soak clear water after 5min in sodium hydrate aqueous solution that 15%, temperature is 60 DEG C, be then placed in mass concentration for 10%,
Temperature is rinsed to soak clear water after 1min in the salpeter solution of room temperature, then is dried up；3rd step, carries out at shot-peening 2024Al plates
Reason, produces compressive stress layer, and bullet selects spherical glass ball, and particle diameter is 150 μm, jet length 40cm, gas pressure 0.5MPa.
After tested, material hardness is 125HB before shot-peening, is 140HB after shot-peening, improves 12%.Drawing-pulling shaft shows to testing fatigue, adds
When load stress is 300MPa, the circulation cycle of material is by 5 × 10 before shot-peening5Improve to 1 × 106。
Embodiment 3：
The experiment material of the present embodiment is 6061Al bars.Specific implementation method：The first step, sprays 6061Al bars
Sand processing, cleaning surface lubricant, pollution impurity or fold defect etc., sand particle diameter is 200 μm, jet length 30cm, gas
Body pressure 0.2MPa；Second step, carries out corrosion treatment to 6061Al bars, removes surface sand-blasting trace：It is dense to be first placed into quality
Spend and rinsed to soak clear water after 5min in sodium hydrate aqueous solution that 20%, temperature is 50 DEG C, be then placed in mass concentration for 10%,
Temperature is rinsed to soak clear water after 2min in the salpeter solution of room temperature, then is dried up；3rd step, carries out at shot-peening 6061Al bars
Reason, produces compressive stress layer, and bullet selects spherical glass ball, and particle diameter is 200 μm, jet length 30cm, gas pressure 0.2MPa.
After tested, Tensile strength is 240MPa before shot-peening, is 260MPa after shot-peening.Drawing-pulling shaft shows that loading should to testing fatigue
When power is 120MPa, the circulation cycle of material is by 7 × 10 before shot-peening4Improve to 8 × 105。
Cost of the present invention is low, production efficiency is high, can obtain a cleaning, have the surface peening layer of residual compressive stress, can be with
Significantly improve the mechanical performances such as anti-fatigue performance, the wear-resisting property of material.
Claims (3)
1. the surface reinforcing method of a kind of aluminium alloy and its composite material parts, comprises the following steps：
(1) blasting treatment is carried out to aluminium alloy and its composite material parts, sand particle diameter is 70~200 μm, and jet length is
10~40cm, 0.2~1MPa of gas pressure, cleaning surface lubricant, pollution impurity and fold defect；
(2) corrosion treatment is carried out to aluminium alloy and its composite material parts, is first placed into sodium hydrate aqueous solution and soaks, so
Clear water rinses afterwards, places into salpeter solution and soaks, and clear water rinses, and finally dries up, and removes surface sand-blasting trace：
(3) aluminium alloy and its composite material parts are carried out with bead, bullet use spherical glass ball, and particle diameter is 70~
200 μm, jet length is 10~40cm, 0.2~1MPa of gas pressure, forms compressive stress layer.
2. the surface reinforcing method of aluminium alloy according to claim 1 and its composite material parts, it is characterised in that：Institute
The mass concentration for the sodium hydrate aqueous solution stated is 10%~20%, and temperature is 50~80 DEG C, and soaking time is 5~15min.
3. the surface reinforcing method of aluminium alloy according to claim 1 and its composite material parts, it is characterised in that：Institute
The mass concentration for the salpeter solution stated is 5%~10%, and soaking time is 1~3min.
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| CN110453054A (en) * | 2018-05-07 | 2019-11-15 | 南京晶质新型复合材料科技有限公司 | A kind of nanocomposite steel substrate surface processing method |
| CN111136588A (en) * | 2018-11-06 | 2020-05-12 | 有研工程技术研究院有限公司 | Method for improving surface quality of aluminum matrix composite |
| CN113936906B (en) * | 2021-09-30 | 2023-08-11 | 安徽瑞德磁电科技有限公司 | Sphericizing preparation method of broken sendust magnetic powder particles |
| CN116005049B (en) * | 2023-01-06 | 2023-07-18 | 山东国泰铝业有限公司 | Corrosion-resistant aluminum alloy profile and preparation method thereof |
| CN116162873B (en) * | 2023-04-26 | 2023-06-27 | 中北大学 | 2024 aluminum alloy and surface treatment method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101020946A (en) * | 2007-02-14 | 2007-08-22 | 大连交通大学 | Composite shot blasting reinforcement process to raise fatigue strength of titanium metal |
| CN101709476A (en) * | 2009-10-30 | 2010-05-19 | 南南铝业股份有限公司 | Production method and equipment for deburring aluminum workpieces by continuously alkali washing |
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| CN101275177A (en) * | 2007-11-30 | 2008-10-01 | 江苏大学 | Anti-fatigue controlled laser shot peening method and device therefor |
| CN101676439A (en) * | 2008-09-18 | 2010-03-24 | 浙江帝龙新材料股份有限公司 | Aluminum strip continuous anodic oxidation automatic production line |
| CN101530985A (en) * | 2009-04-09 | 2009-09-16 | 上海交通大学 | Method for processing composite shot blasting considering both surface peening and polishing |
| CN102051640B (en) * | 2010-11-17 | 2012-10-31 | 昆明理工大学 | Preparation method of Al-based Pb-ZrO2-CeO2 composite anode material for zinc electrodepositing |
| CN103014769A (en) * | 2012-11-26 | 2013-04-03 | 中国铝业股份有限公司 | Alloy inert anode for aluminium electrolysis and preparation method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101020946A (en) * | 2007-02-14 | 2007-08-22 | 大连交通大学 | Composite shot blasting reinforcement process to raise fatigue strength of titanium metal |
| CN101709476A (en) * | 2009-10-30 | 2010-05-19 | 南南铝业股份有限公司 | Production method and equipment for deburring aluminum workpieces by continuously alkali washing |
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Effective date of registration: 20210602 Address after: 101407 No.11, Xingke East Street, Yanqi Economic and Technological Development Zone, Huairou District, Beijing Patentee after: Youyan metal composite technology Co.,Ltd. Address before: 101407 No. 11 Xingke East Street, Yanqi Economic Development Zone, Huairou District, Beijing Patentee before: YOUYAN ENGINEERING TECHNOLOGY RESEARCH INSTITUTE Co.,Ltd. |
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