CN106906389A - Almag aircraft housing and preparation method thereof - Google Patents

Almag aircraft housing and preparation method thereof Download PDF

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Publication number
CN106906389A
CN106906389A CN201710116473.1A CN201710116473A CN106906389A CN 106906389 A CN106906389 A CN 106906389A CN 201710116473 A CN201710116473 A CN 201710116473A CN 106906389 A CN106906389 A CN 106906389A
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almag
aircraft housing
mass percent
aircraft
housing
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李子俊
陈湘
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Guangdong Runsheng Technology Materials Co Ltd
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Guangdong Runsheng Technology Materials Co Ltd
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/026—Alloys based on aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/03—Making non-ferrous alloys by melting using master alloys
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Heat Treatment Of Articles (AREA)

Abstract

The present invention relates to a kind of almag aircraft housing and the preparation method of almag aircraft housing, the preparation method of the almag aircraft housing and almag aircraft housing, the almag aircraft housing adds Si by almag aircraft housing, Fe, Cu, Mn, Zn and Ca, and by designing Si, Fe, Cu, Mn, Zn, Ca, the rational proportion of Mg and Al, traditional almag aircraft housing creep-resistant property is taken, strength character and the undesirable problem of toughness, with preferable creep-resistant property, strength character and toughness, and then can preferably meet demand of the aircraft of new generation to alloy material property.

Description

Almag aircraft housing and preparation method thereof
Technical field
The present invention relates to metal alloy compositions technical field, more particularly to a kind of almag aircraft housing and its preparation Method.
Background technology
Due to the fast development of aerospace industry, lightweight, the application of the alloy material on aircraft of new generation of high intensity Increasingly extensive, consumption and premium properties of the alloy material on aircraft of new generation have turned into the advanced important finger of aircraft of new generation One of mark.At present, almag is due to good intensity, hardness, thermal diffusivity and crushing resistance, by industrial circle and academia Close attention, be expected to be widely used in the various aspects of aerospace field.
However, there is the situation of thermodynamic instability in traditional almag, intensity in the working environment more than 120 DEG C And creep-resistant property drastically declines, meanwhile, the toughness and strength character of traditional almag are relatively poor, and traditional magnalium is closed The creep-resistant property of aircraft housing, strength character and toughness prepared by gold is undesirable, it is impossible to meet aircraft of new generation to aircraft shell The demand of the creep-resistant property, strength character and toughness of body.
The content of the invention
Based on this, it is necessary to the creep-resistant property of the aircraft housing prepared for traditional almag, strength character and Toughness is undesirable, it is impossible to meet skill of the aircraft of new generation to the demand of the creep-resistant property, strength character and toughness of aircraft housing A kind of art problem, there is provided almag aircraft housing and preparation method thereof.
A kind of almag aircraft housing, it is characterised in that each component including following mass percent：Mg：2.3%~ 3%；Si：1%~1.5%；Fe：0.2%~0.3%；Cu：0.009%~0.02%；Mn：0.05%~0.07%；Zn： 0.007%~0.012%；Ca：0.01%~0.02%；Balance of Al.
Wherein in one embodiment, including following mass percent each component：Mg：2.6%~2.7%；Si： 1.21%~1.34%；Fe：0.22%~0.23%；Cu：0.011%~0.013%；Mn：0.057~0.06%；Zn： 0.009%~0.01%；Ca：0.012%~0.013%；Balance of Al.
Wherein in one embodiment, including following mass percent each component：Mg：2.6%；Si：1.3%；Fe： 0.22%；Cu：0.013%；Mn：0.059%；Zn：0.008%；Ca：0.014%；Balance of Al.
Wherein in one embodiment, also including Cr that mass percent is 0.2%~0.3%.
Wherein in one embodiment, also including Cr that mass percent is 0.25%.
Wherein in one embodiment, also including Sc that mass percent is 0.01%~0.02%.
Wherein in one embodiment, also including Sc that mass percent is 0.016%.
A kind of preparation method of almag aircraft housing, comprises the following steps：
The each component of the almag aircraft housing described in any of the above-described embodiment is carried out into high temperature melt, raw material is obtained Liquid；
The material liquid is poured, almag ingot is obtained；
Carry out hot rolling and cold rolling, acquisition almag blank successively to the almag ingot；
The almag blank is annealed successively, pickling, anode oxidation coloration and drying, obtain almag and fly Casing body.
It is described to carry out hot rolling and cold rolling, including following step successively to the almag ingot wherein in one embodiment Suddenly：
Multiple hot rolling is carried out to the almag ingot, almag primary blank is obtained；
Repeatedly cold rolling, acquisition almag blank is carried out to almag primary blank.
Wherein in one embodiment, the temperature of the annealing is 350 DEG C~410 DEG C.
The preparation method of above-mentioned almag aircraft housing and almag aircraft housing, the almag aircraft housing By in almag aircraft housing add Si, Fe, Cu, Mn, Zn and Ca, and by design Si, Fe, Cu, Mn, Zn, Ca, The rational proportion of Mg and Al, has taken traditional almag aircraft housing creep-resistant property, strength character and toughness undesirable Problem, with preferable creep-resistant property, strength character and toughness, and then can preferably meet aircraft of new generation to alloy material Expect the demand of performance.
Brief description of the drawings
Fig. 1 is the flow chart of the preparation method of an embodiment of the present invention almag aircraft housing.
Specific embodiment
To enable the above objects, features and advantages of the present invention more obvious understandable, below in conjunction with the accompanying drawings to the present invention Specific embodiment be described in detail.Elaborate many details in order to fully understand this hair in the following description It is bright.But the present invention can be implemented with being much different from other manner described here, and those skilled in the art can be not Similar improvement is done in the case of running counter to intension of the present invention, therefore the present invention is not limited by following public specific embodiment.
In the description of the invention, it is to be understood that term " first ", " second " are only used for describing purpose, and can not It is interpreted as indicating or implying relative importance or the implicit quantity for indicating indicated technical characteristic.Thus, define " the One ", at least one this feature can be expressed or be implicitly included to the feature of " second ".In the description of the invention, " multiple " It is meant that at least two, such as two, three etc., unless otherwise expressly limited specifically.
It should be noted that Mg is one of most light structural metallic materials, the density of Mg is only 1.74g/cm3, it is lighter than Al About 36%, thus, traditional almag turns into the preferred material that aircraft of new generation mitigates deadweight.However, traditional magnalium is closed The creep-resistant property of aircraft housing, strength character and toughness prepared by gold is undesirable, it is impossible to meet aircraft of new generation to aircraft shell The demand of the creep-resistant property, strength character and toughness of body.
In order to solve the above problems, in an implementation method, a kind of almag aircraft housing, including following mass percent Each component：Mg：2.3%~3%；Si：1%~1.5%；Fe：0.2%~0.3%；Cu：0.009%~0.02%；Mn： 0.05%~0.07%；Zn：0.007%~0.012%；Ca：0.01%~0.02%；Balance of Al.
It is appreciated that in almag aircraft housing, when the too high levels of Mg, Mg and Al is easily formed Mg8Al5Phase And Mg3Al2Phase, so, it will reduce the elongation of almag aircraft housing, and then reduce the tough of almag aircraft housing Property.In the present embodiment, the mass percent of Mg is 2.3%~3%.When the mass percent of Mg is less than 2.3%, magnalium The density of alloy aircraft housing is larger, it is impossible to the demand that aircraft of new generation mitigates deadweight is met, when the mass percent of Mg is more than When 3%, it will the elongation of reduction almag aircraft housing, and then the toughness of almag aircraft housing is reduced, when Mg's When mass percent is 2.3%~3%, the demand that aircraft of new generation mitigates deadweight can either be met, can preferably improved again The toughness of almag aircraft housing.And for example, the mass percent of Mg is 2.35%~2.45%.And for example, the quality percentage of Mg Than being 2.39%~2.8%.And for example, the mass percent of Mg is 2.4%.When the mass percent of Mg is less than 2.3%, magnalium The density of alloy aircraft housing is larger, it is impossible to the demand that aircraft of new generation mitigates deadweight is met, when the mass percent of Mg is more than When 3%, it will the elongation of reduction almag aircraft housing, and then the toughness of almag aircraft housing is reduced, when Mg's When mass percent is 2.3%~3%, the demand that aircraft of new generation mitigates deadweight can either be met, can preferably improved again The toughness of almag aircraft housing.
In order that obtaining almag aircraft housing has preferable strength character, almag aircraft housing is further improved Toughness, in the present embodiment, for example, in almag aircraft housing, the mass percent of Mg is 2.3%~3%, Si Mass percent for 1%~1.5%, Mn mass percent for 0.05%~0.07%, Fe mass percent be 0.2% The mass percent of~0.3%, Cu is 0.009%~0.02%.By adding quality percentage in almag aircraft housing Than the Mg for 2.3%~3%, mass percent is 0.2%~0.3% Fe, and mass percent is 0.009%~0.02% Cu, preferably improves the strength character of almag aircraft housing, by adding quality hundred in almag aircraft housing Divide than the Si for 1%~1.5%, mass percent is 0.05%~0.07% Mn, both preferably improve almag and flown The strength character of casing body, further improves the toughness of almag aircraft housing.
Specifically, Si, Mg and Si reaction generation Mg are added in almag aircraft housing2Si, in such manner, it is possible to preferably The intensity of almag aircraft housing is improved, almag aircraft housing especially can be preferably improved in the case of a high temperature Intensity.However, when the percentage composition of Mg is excessive with the ratio of the percentage composition of Si, it will cause almag aircraft housing Toughness declines, and in order to preferably improve the intensity of almag aircraft housing, and is not easily caused almag aircraft shell The toughness of body declines, and and for example, in almag aircraft housing, the mass percent of Mg is the quality of 2.5%~2.9%, Si Percentage is 1.1%~1.4%.So, Si is added in almag aircraft housing, can either preferably improves almag The intensity of aircraft housing, and the toughness decline of almag aircraft housing is not easily caused.
Fe is added in almag aircraft housing, Fe can either preferably improve the intensity of almag aircraft housing, The situation that can preferably avoid almag aircraft housing that reaction vessel is adhered in preparation process again occurs.However, working as When Fe contents in almag aircraft housing are excessive, Fe easily with alloy in Al and Si generate needle-like intermediate compound, this Sample, the strength character for being easily caused almag aircraft housing declines.In order to preferably improve almag aircraft shell The intensity of body, is prevented from almag aircraft housing and occurs the situation for adhering to reaction vessel in preparation process again, moreover it is possible to Al and Si in Fe and alloy is enough avoided to generate the intermediate compound of needle-like, and for example, in almag aircraft housing, the matter of Fe Amount percentage is 0.21%~0.24%.So, Fe is added in almag aircraft housing, can either preferably improves magnalium The intensity of alloy aircraft housing, is prevented from almag aircraft housing and occurs adhering to reaction vessel in preparation process again Situation, additionally it is possible to avoid Al and Si in Fe and alloy from generating the intermediate compound of needle-like such that it is able to strengthen almag and fly The intensity of casing body.
Cu, Cu and Al reaction generation CuAl are added in almag aircraft housing2, preferably improve almag and fly The intensity of casing body, however, when the Cu contents in almag aircraft housing are excessive, it is easy to cause almag aircraft housing Toughness decline, in order to preferably improve the intensity of almag aircraft housing, can avoid again almag fly The toughness of casing body declines, and and for example, in almag aircraft housing, the mass percent of Cu is 0.01%~0.015%.This Sample, can either preferably improve the intensity of almag aircraft housing, and the toughness of almag aircraft housing can be avoided again Decline.
Mn is added in almag aircraft housing, Mn reacts with Al, Si and the Fe in almag aircraft housing, shape Into Al15(FeMn)3Si2, the intensity of almag aircraft housing can not only be improved, additionally it is possible to reduce Al in Fe and alloy and The probability of the intermediate compound of Si generation needle-likes.In order to preferably improve the intensity of almag aircraft housing, and energy The probability of the intermediate compound of enough Al and Si the generation needle-like preferably reduced in Fe and alloy, and for example, in almag aircraft In housing, the mass percent of Mn is 0.056%~0.067%.So, almag aircraft housing can either preferably be improved Intensity, the probability of the intermediate compound of Al and Si generation needle-like in Fe and alloy can be preferably reduced again.
Thus, it is contemplated that in almag aircraft housing, interacting between Mg, Al, Si, Fe, Mn and Cu, in order to Strength character and all good almag aircraft housing of toughness are obtained, for example, in almag aircraft housing, the quality hundred of Mg Point than the mass percent for 2.5%~2.9%, Si for 1.1%~1.4%, Fe mass percent for 0.21%~ The mass percent of 0.24%, Cu is 0.056%~0.067% for the mass percent of 0.01%~0.015%, Mn.And for example, In almag aircraft housing, the mass percent of Mg for 2.6%~2.7%, Si mass percent for 1.21%~ The mass percent of 1.34%, Fe is the matter of 0.011%~0.013%, Mn for the mass percent of 0.22%~0.23%, Cu Amount percentage is 0.057~0.06%.And for example, in almag aircraft housing, the mass percent of Mg for 2.65%~ The mass percent of 2.87%, Si is the matter of 0.224%~0.234%, Cu for the mass percent of 1.31%~1.38%, Fe Amount percentage is 0.058%~0.065% for the mass percent of 0.012%~0.014%, Mn.And for example, fly in almag In casing body, the mass percent of Mg for 2.6%, Si mass percent for the mass percent of 1.3%, Fe be 0.22%, The mass percent of Cu is 0.059% for the mass percent of 0.013%, Mn.So, by Mg, Al, Si, Fe, Mn and Cu Content in almag aircraft housing is selected so that the trend profit that interacts between Mg, Al, Si, Fe, Mn and Cu Strength character and the direction of toughness in enhancing almag aircraft housing, and then enable that almag aircraft housing has concurrently Good strength character and toughness.
Even if it should be noted that metal material can also occur slowly in certain temperature range under relatively low stress The phenomenon of plastic deformation is referred to as creep.There is the situation of thermodynamic instability in traditional almag aircraft housing, 120 DEG C with On working environment in creep-resistant property drastically decline, so as to aero-engine part cannot be applied to and machine gearbox is gone straight up to Deng in heat-resistant part.
In order that obtaining almag aircraft housing on the basis of with good strength character and toughness, also possess good Creep-resistant property, in the present embodiment, in almag aircraft housing, the mass percent of Ca for 0.01%~ 0.02%, Ca generate Al with the Al reactions in almag aircraft housing2Mg reaction lifes in Ca, with almag aircraft housing Into Mg2Ca, Al2Ca and Mg2Ca is heat-resisting phase, and so, the high temperature that almag aircraft housing is improve to a certain extent resists Croop property so that almag aircraft housing can be applied in 120 DEG C~200 DEG C of working environment.
Further, in almag aircraft housing, increasing for Ca contents can also cause that almag aircraft housing is deposited In the defect such as hot tearing and sticking to mould, in order to avoid the almag aircraft caused by adding Ca in almag aircraft housing There is the defects such as hot tearing and sticking to mould in housing, for example, in almag aircraft housing, the mass percent of Ca for 0.01%~ 0.015%.
In order to further improve the high-temperature creep resistance of almag aircraft housing, in the present embodiment, in magnalium In alloy aircraft housing, the mass percent of Zn is 0.007%~0.012%, in micro Zn and almag aircraft housing Al, Mg reaction generation better heat stability MgZn and Mg32(Al, Zn)49, Zn also can with almag aircraft housing in The Mg and Cu reaction heat-resisting phases of generation.So, the high-temperature creep resistance of almag aircraft housing is further increased.
To sum up, in order to overcome traditional almag aircraft housing creep-resistant property, intensity and toughness undesirable, Jin Erwu Method meets problem of the aircraft of new generation to the demand of alloy material property, while considering Mg, Al, Si, Fe, Mn, Cu, Ca and Zn Influence each other, for example, a kind of almag aircraft housing, including following mass percent each component：Mg：2.5%~ 2.9%；Si：1.1%~1.4%；Fe：0.21%~0.24%；Cu：0.01%~0.015%；Mn：0.056%~ 0.067%；Zn：0.007%~0.012%；Ca：0.01%~0.015%；Balance of Al.
Further, it is contemplated that Cu and Al reaction generations CuAl2, preferably improve the strong of almag aircraft housing Degree, however, when the Cu contents in almag aircraft housing are excessive, it is easy under causing the toughness of almag aircraft housing Drop, in order that the proportioning for obtaining Cu and Al is more reasonable, further enhances the intensity and toughness of almag aircraft housing, and for example, A kind of almag aircraft housing, including following mass percent each component：Mg：2.6%~2.7%；Si：1.21%~ 1.34%；Fe：0.22%~0.23%；Cu：0.011%~0.013%；Mn：0.057~0.06%；Zn：0.009%~ 0.01%；Ca：0.012%~0.013%；Balance of Al.In such manner, it is possible to further enhance the intensity of almag aircraft housing And toughness.
In view of Al, Si and Fe reaction in Mn and almag aircraft housing, Al is formed15(FeMn)3Si2, not only The intensity of almag aircraft housing can be improved, additionally it is possible to reduce the middle chemical combination that Al and Si in Fe and alloy generate needle-like The probability of thing.In order that the proportioning for obtaining Mn, Al, Si and Fe is more reasonable, the intensity of almag aircraft housing is further enhanced, And for example, a kind of each component of almag aircraft housing, including following mass percent：Mg：2.65%~2.87%；Si： 1.31%~1.38%；Fe：0.224%~0.234%；Cu：0.012%~0.014%；Mn：0.058%~0.065%； Zn：0.008%~0.011%；Ca：0.011%~0.014%；Balance of Al.And for example, a kind of almag aircraft housing, bag Include each component of following mass percent：Mg：2.6%；Si：1.3%；Fe：0.22%；Cu：0.013%；Mn：0.059%； Zn：0.008%；Ca：0.014%；Balance of Al.In such manner, it is possible to further enhance the intensity of almag aircraft housing.
So, selected by the content to Mg, Al, Si, Fe, Mn, Cu, Ca and Zn in almag aircraft housing Select so that interacting between Mg, Al, Si, Fe, Mn, Cu, Ca and Zn tends to the height beneficial to enhancing almag aircraft housing The direction of warm creep-resistant property, strength character and toughness, and then enable that almag aircraft housing has high temperature and creep resistance Performance, preferable strength character and preferable toughness, overcome traditional almag aircraft housing creep-resistant property, intensity and Toughness is undesirable, and then cannot meet problem of the aircraft of new generation to the demand of alloy material property.
The preparation method of above-mentioned almag aircraft housing and almag aircraft housing, the almag aircraft housing By in almag aircraft housing add Si, Fe, Cu, Mn, Zn and Ca, and by design Si, Fe, Cu, Mn, Zn, Ca, The rational proportion of Mg and Al, has taken traditional almag aircraft housing creep-resistant property, strength character and toughness undesirable Problem, with preferable creep-resistant property, strength character and toughness, and then can preferably meet aircraft of new generation to alloy material Expect the demand of performance.
It should be noted that the resistance to stress and erosion-resisting ability of traditional almag aircraft housing are preferably, however, passing The ability of the stress corrosion dehiscence resistant of the almag aircraft housing of system has much room for improvement, in other words, when traditional almag flies Component prepared by casing body is also easy to produce stress corrosion cracking in the collective effect of mechanical stress and corrosive medium.
In one embodiment, in order to improve the ability of the stress corrosion dehiscence resistant of almag aircraft housing, for example, In almag aircraft housing, also including Cr, and for example, the mass percent of Cr is 0.2%~0.3%.And for example, the quality hundred of Cr Divide than being 0.21%~0.26%.The mass percent of Cr is 0.24%~0.29%.The mass percent of Cr is 0.25%. In almag aircraft housing, appropriate Cr and Al, micro Fe and micro Mn generations (CrFe) Al17(CrMn) Al12, (CrFe)Al17(CrMn) Al12Deng can preferably improve the ability of the stress corrosion dehiscence resistant of almag aircraft housing.
It should be noted that in the fracture failure of aircraft component of machine, by the fatigue failure of alloy material is led The fatigue fracture of cause occupies larger proportion, and almag aircraft housing also has that anti-fatigue performance is poor.It is real one In applying mode, in order to improve the anti-fatigue performance of almag aircraft housing, for example, in almag aircraft housing, also wrapping Sc is included, and for example, the mass percent of Sc is 0.01%~0.02%.And for example, the mass percent of Sc be 0.012%~ 0.15%.And for example, the mass percent of Sc is 0.013%~0.18%.And for example, the mass percent of Sc is 0.016%.Pass through Sc is added in almag aircraft housing so that the plane strain fracture toughness of almag aircraft housing is significantly increased, The probability reduction of fatigue crack initiation, so as to improve the anti-fatigue performance of almag aircraft housing.
It is appreciated that those skilled in the art has certain experimental ability, but, in almag aircraft housing Magnalium outside element selection, and these elements mass ratio, it is assumed that with the 0.001% of Cu or Zn as one-level, Ca Or the 0.01% of Mn etc. is one-level, is calculated by 90 kinds of metallic elements, takes around 9.64 × 1020Experiment side can obtain.
Present invention additionally comprises a kind of preparation method of almag aircraft housing, as shown in figure 1, almag aircraft housing Preparation method comprise the following steps：
S110, high temperature melt is carried out by each component of almag aircraft housing described in any of the above-described embodiment respectively, is obtained Obtain material liquid.
For example, S110 specifically includes following steps：
Al is carried out into high temperature melt, aluminium water is obtained；To sequentially added in aluminium water MgSi alloys, MgFe alloys, MgMn alloys, MgCu alloys, MgCa alloys, MgZn alloys, Cr and Sc, wherein, in almag aircraft housing, the mass percent of Mg is The mass percent of 2.5%~2.9%, Si is 0.21%~0.24%, Cu's for the mass percent of 1.1%~1.4%, Fe Mass percent is the mass percent of 0.01%~0.015%, Mn for the mass percent of 0.056%~0.067%, Zn is The mass percent of 0.007%~0.012%, Ca for 0.01%~0.015%, Cr mass percent for 0.2%~ The mass percent of 0.3%, Sc is 0.01%~0.02%, balance of Al.
For example, the temperature of high temperature melt is 650 DEG C~750 DEG C, and for example, the temperature of high temperature melt is 660 DEG C~700 DEG C, And for example, the temperature of high temperature melt is 680 DEG C~740 DEG C, and and for example, the temperature of high temperature melt is 710 DEG C.When the temperature of high temperature melt It is too low, less than 650 DEG C, it is unfavorable for the thorough thawing of each component in almag aircraft housing, when the temperature of high temperature melt is too high, Higher than 750 DEG C, it is unfavorable for energy saving.When the temperature of high temperature melt is 650 DEG C~750 DEG C, can either cause that almag flies The thorough thawing of each component in casing body, again being capable of energy saving.
S120, the material liquid is poured, and obtains almag ingot.
For example, material liquid is transferred in watering appliance standing, almag ingot is obtained.
S130, hot rolling and cold rolling, acquisition almag blank are carried out to the almag ingot successively.
For example, S130 specifically includes following steps：
Multiple hot rolling is carried out to the almag ingot, almag primary blank is obtained；
Repeatedly cold rolling, acquisition almag blank is carried out to almag primary blank.
And for example, the scope of almag primary sotck thinkness is 9mm~11mm.And for example, the model of almag sotck thinkness It is 2mm~4mm to enclose.
S140, the almag blank is annealed successively, pickling, anode oxidation coloration and drying, obtain magnalium Alloy aircraft housing.
In order to ensure the almag aircraft housing obtained by follow-up preparation have preferable creep-resistant property, strength character and Toughness, for example, the temperature of annealing is 300 DEG C~410 DEG C.And for example, the temperature of annealing is 320 DEG C~370 DEG C.And for example, annealing Temperature is 350 DEG C~400 DEG C.And for example, the temperature of annealing is 400 DEG C.And for example, the time of annealing is 0.8h~1.4h, and for example, is moved back The time of fire is 1h~1.2h, and and for example, the time of annealing is 0.9h~1.3h, and and for example, the time of annealing is 1h.In such manner, it is possible to Ensure that the almag aircraft housing obtained by follow-up preparation has preferable creep-resistant property, strength character and toughness.
For example, after an annealing process, before acid cleaning process, also including Sheet Metal Forming Technology, the almag after to annealing Blank carries out punching press, after punching press in the case of flawless, proceeds acid cleaning process, reduces the magnalium obtained by follow-up preparation Fraction defective of the alloy aircraft housing caused by strength character is not up to standard.
It is below specific embodiment
Embodiment 1
Al is carried out into high temperature melt, aluminium water is obtained；To sequentially added in aluminium water MgSi alloys, MgFe alloys, MgMn alloys, MgCu alloys, MgCa alloys, MgZn alloys, Cr and Sc, wherein, in almag aircraft housing, the mass percent of Mg is The mass percent of 2.5%, Si is 0.01%, Mn for the mass percent that the mass percent of 1.1%, Fe is 0.21%, Cu Mass percent for 0.056%, Zn mass percent for 0.007%, Ca mass percent be 0.01%, it is balance of Al.Wherein, the temperature of high temperature melt is 710 DEG C.
Material liquid is transferred in watering appliance and is stood, obtain almag ingot.
5 hot rollings are carried out to almag ingot, almag primary blank is obtained, thickness is 10mm.Then, magnalium is closed Golden primary blank carries out 6 cold rolling, acquisition almag blanks, and thickness is 3mm.
At a temperature of 320 DEG C, almag blank is annealed, annealing time is 0.8h, then, after annealing Almag blank carries out punching press, and after punching press in the case of flawless, continuation carries out acid cleaning process anode oxidation coloration successively And drying, obtain almag aircraft housing.
Embodiment 2
Al is carried out into high temperature melt, aluminium water is obtained；To sequentially added in aluminium water MgSi alloys, MgFe alloys, MgMn alloys, MgCu alloys, MgCa alloys, MgZn alloys, Cr and Sc, wherein, in almag aircraft housing, the mass percent of Mg is The mass percent of 2.9%, Si is 0.015%, Mn for the mass percent that the mass percent of 1.4%, Fe is 0.24%, Cu Mass percent for 0.067%, Zn mass percent for 0.012%, Ca mass percent be 0.015%, it is balance of Al.Wherein, the temperature of high temperature melt is 740 DEG C.
Material liquid is transferred in watering appliance and is stood, obtain almag ingot.
4 hot rollings are carried out to almag ingot, almag primary blank is obtained, thickness is 9mm.Then, magnalium is closed Golden primary blank carries out 5 cold rolling, acquisition almag blanks, and thickness is 3.3mm.
At a temperature of 370 DEG C, almag blank is annealed, annealing time is 1.4h, then, after annealing Almag blank carries out punching press, and after punching press in the case of flawless, continuation carries out acid cleaning process anode oxidation coloration successively And drying, obtain almag aircraft housing.
Embodiment 3
Al is carried out into high temperature melt, aluminium water is obtained；To sequentially added in aluminium water MgSi alloys, MgFe alloys, MgMn alloys, MgCu alloys, MgCa alloys, MgZn alloys, Cr and Sc, wherein, in almag aircraft housing, the mass percent of Mg is The mass percent of 2.6%, Si is 0.011% for the mass percent that the mass percent of 1.21%, Fe is 0.22%, Cu, The mass percent of Mn is 0.012%, surplus for the mass percent that the mass percent of 0.057%, Zn is 0.009%, Ca It is Al.Wherein, the temperature of high temperature melt is 680 DEG C.
Material liquid is transferred in watering appliance and is stood, obtain almag ingot.
6 hot rollings are carried out to almag ingot, almag primary blank is obtained, thickness is 11mm.Then, magnalium is closed Golden primary blank carries out 2 cold rolling, acquisition almag blanks, and thickness is 4mm.
At a temperature of 350 DEG C, almag blank is annealed, annealing time is 1h, then, to the aluminium after annealing Magnesium alloy blank carries out punching press, after punching press in the case of flawless, continuation carry out successively acid cleaning process anode oxidation coloration and Drying, obtains almag aircraft housing.
Embodiment 4
Al is carried out into high temperature melt, aluminium water is obtained；To sequentially added in aluminium water MgSi alloys, MgFe alloys, MgMn alloys, MgCu alloys, MgCa alloys, MgZn alloys, Cr and Sc, wherein, in almag aircraft housing, the mass percent of Mg is The mass percent of 2.65%, Si is the mass percent of 1.31%, Fe for the mass percent of 0.224%, Cu is The mass percent of 0.011%, Mn is the mass percent of 0.057%, Zn for the mass percent of 0.009%, Ca is The mass percent of 0.011%, Cr for 0.2%, Sc mass percent be 0.01%, balance of Al, wherein, high temperature melt Temperature is 650 DEG C.
Material liquid is transferred in watering appliance and is stood, obtain almag ingot.
3 hot rollings are carried out to almag ingot, almag primary blank is obtained, thickness is 11mm.Then, magnalium is closed Golden primary blank carries out 5 cold rolling, acquisition almag blanks, and thickness is 2.5mm.
At a temperature of 350 DEG C, almag blank is annealed, annealing time is 0.9h, then, after annealing Almag blank carries out punching press, and after punching press in the case of flawless, continuation carries out acid cleaning process anode oxidation coloration successively And drying, obtain almag aircraft housing.
Embodiment 5
Al is carried out into high temperature melt, aluminium water is obtained；To sequentially added in aluminium water MgSi alloys, MgFe alloys, MgMn alloys, MgCu alloys, MgCa alloys, MgZn alloys, Cr and Sc, wherein, in almag aircraft housing, the mass percent of Mg is The mass percent of 2.6%, Si is 0.013%, Mn for the mass percent that the mass percent of 1.3%, Fe is 0.22%, Cu Mass percent for 0.059%, Zn mass percent for 0.008%, Ca mass percent for 0.014%, Cr matter Amount percentage is 0.02%, balance of Al for the mass percent of 0.3%, Sc.Wherein, the temperature of high temperature melt is 750 DEG C.
Material liquid is transferred in watering appliance and is stood, obtain almag ingot.
6 hot rollings are carried out to almag ingot, almag primary blank is obtained, thickness is 10mm.Then, magnalium is closed Golden primary blank carries out 3 cold rolling, acquisition almag blanks, and thickness is 2mm.
At a temperature of 410 DEG C, almag blank is annealed, annealing time is 1h, then, to the aluminium after annealing Magnesium alloy blank carries out punching press, after punching press in the case of flawless, continuation carry out successively acid cleaning process anode oxidation coloration and Drying, obtains almag aircraft housing.
Sample 1, sample 2, sample 3, sample 4, sample 5 and comparative example to being obtained in embodiment 1 to embodiment 5 are entered respectively The test of row strength test, toughness test and Properties of High Temperature Creep, wherein, strength test includes that tensile strength test and surrender are strong Degree test, toughness test is tested including test of elongation rate, and Properties of High Temperature Creep test includes the test of total creep elongation percentage, always The test temperature of creep extension is 175 DEG C, and pressure is 70MPa.Test result is as shown in table 1 below：
Tensile strength (MPa) Yield strength (MPa) Elongation (%) Total creep elongation percentage (%)
Sample 1 330 223 9 3.12
Sample 2 345.64 223.4 10.65 2.043
Sample 3 320.45 201.38 9.12 2.56
Sample 4 331.2 199.8 8.99 3.42
Sample 5 350.4 202.98 8.89 3.67
Comparative example 200.12 191.32 7.1 7.2
Table 1
Knowable to the test result in table 1, the tensile strength of sample 1, sample 2, sample 3, sample 4 and sample 5 is all higher than 330MPa, elongation is all higher than 6.5%, meets requirement of the complex parts to alloy strength and toughness on aircraft.Further, from Test result in table 1 understands that the total creep elongation percentage of sample 1, sample 2, sample 3, sample 4 and sample 5 is 2%~3.7% Between, far smaller than in comparative example 7.2%, show that there is the almag aircraft housing obtained by preparing preferable high temperature to resist compacted Become performance.
Each technical characteristic of embodiment described above can be combined arbitrarily, to make description succinct, not to above-mentioned reality Apply all possible combination of each technical characteristic in example to be all described, as long as however, the combination of these technical characteristics is not deposited In contradiction, the scope of this specification record is all considered to be.
Embodiment described above only expresses several embodiments of the invention, and its description is more specific and detailed, but simultaneously Can not therefore be construed as limiting the scope of the patent.It should be pointed out that coming for one of ordinary skill in the art Say, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to protection of the invention Scope.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.

Claims (10)

1. a kind of almag aircraft housing, it is characterised in that each component including following mass percent：
2. almag aircraft housing according to claim 1, it is characterised in that each group including following mass percent Point：
3. almag aircraft housing according to claim 1, it is characterised in that each group including following mass percent Point：
4. almag aircraft housing according to claim 1, it is characterised in that also including mass percent be 0.2% ~0.3% Cr.
5. almag aircraft housing according to claim 4, it is characterised in that also including mass percent be 0.25% Cr.
6. almag aircraft housing according to claim 1, it is characterised in that also including mass percent be 0.01% ~0.02% Sc.
7. almag aircraft housing according to claim 6, it is characterised in that be also including mass percent 0.016% Sc.
8. a kind of preparation method of almag aircraft housing, it is characterised in that comprise the following steps：
The each component of the almag aircraft housing as any one of claim 1 to 7 is carried out into high temperature melt, obtains former Feed liquid；
The material liquid is poured, almag ingot is obtained；
Carry out hot rolling and cold rolling, acquisition almag blank successively to the almag ingot；
The almag blank is annealed successively, pickling, anode oxidation coloration and drying, obtain almag aircraft shell Body.
9. almag aircraft housing according to claim 8, it is characterised in that it is described to the almag ingot successively Hot rolling and cold rolling is carried out, is comprised the following steps：
Multiple hot rolling is carried out to the almag ingot, almag primary blank is obtained；
Repeatedly cold rolling, acquisition almag blank is carried out to almag primary blank.
10. almag aircraft housing according to claim 8, it is characterised in that the temperature of the annealing is 350 DEG C~ 410℃。
CN201710116473.1A 2017-02-28 2017-02-28 Almag aircraft housing and preparation method thereof Pending CN106906389A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021126665A1 (en) * 2019-12-17 2021-06-24 Novelis Inc. Suppression of stress corrosion cracking in high magnesium alloys through the addition of calcium

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1443123A1 (en) * 2003-01-28 2004-08-04 Hydro Aluminium Deutschland GmbH Aluminum alloy for the production of can end sheet for cans
JP2004292899A (en) * 2003-03-27 2004-10-21 Kobe Steel Ltd Al-Mg-Si-BASED ALLOY SHEET HAVING EXCELLENT SURFACE PROPERTY, PRODUCTION METHOD THEREFOR, AND PRODUCTION INTERMEDIATE MATERIAL THEREOF
CN102352457A (en) * 2011-11-02 2012-02-15 永鑫精密材料（无锡）有限公司 Preparation method of aluminium alloy strip for stamping and stretch forming of cell phone shell
CN104789825A (en) * 2015-05-15 2015-07-22 朱岳群 Die-castable alloy containing aluminum, magnesium, silicon, manganese and rare earth

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1443123A1 (en) * 2003-01-28 2004-08-04 Hydro Aluminium Deutschland GmbH Aluminum alloy for the production of can end sheet for cans
JP2004292899A (en) * 2003-03-27 2004-10-21 Kobe Steel Ltd Al-Mg-Si-BASED ALLOY SHEET HAVING EXCELLENT SURFACE PROPERTY, PRODUCTION METHOD THEREFOR, AND PRODUCTION INTERMEDIATE MATERIAL THEREOF
CN102352457A (en) * 2011-11-02 2012-02-15 永鑫精密材料（无锡）有限公司 Preparation method of aluminium alloy strip for stamping and stretch forming of cell phone shell
CN104789825A (en) * 2015-05-15 2015-07-22 朱岳群 Die-castable alloy containing aluminum, magnesium, silicon, manganese and rare earth

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021126665A1 (en) * 2019-12-17 2021-06-24 Novelis Inc. Suppression of stress corrosion cracking in high magnesium alloys through the addition of calcium

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Application publication date: 20170630