CN103966486B - Low-density high specific strength Aluminium alloy structural material and preparation method thereof - Google Patents
Low-density high specific strength Aluminium alloy structural material and preparation method thereof Download PDFInfo
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Abstract
A kind of low-density high specific strength Aluminium alloy structural material, it is characterised in that this material is with aluminum for main constituent element, then adds the first constituent element magnesium, the second constituent element lithium, third element copper and the 4th constituent element titanium composition, forms Al-Mg-Li-Cu-Ti system alloy.The preparation method that the invention also discloses this Aluminium alloy structural material.Compared with prior art, it is an advantage of the current invention that: gained Aluminium alloy structural material density of the present invention is lower is equivalent to the effect of aluminium lithium alloy, the higher effect being equivalent to the superstrength alloys such as 7A04,7A09 and 7055 of intensity, realize specific strength and reach the use target of more than 235MPa/ (g/cm3) so that applicable surface is wider.
Description
Technical field
The present invention relates to a kind of aluminum alloy materials, the preparation method that the invention still further relates to aluminum alloy materials, belong to technical field of alloy.
Background technology
A key technical index in the design of equipment configuration loss of weight is specific strength Rm/ ρ, i.e. the ratio of the hot strength Rm of structural material and density p.This ratio is more big, and structure loss of weight potentiality are more big., there is urgent loss of weight requirement such as connecting rod, swing arm, knuckle, storehouse section, rocket body, the control wing, empennage, housing etc. in all kinds of load-carrying construction on ground traffic tools such as automobile, motorcycle, racing car and spacecraft such as aircraft, rocket etc..Particularly spacecraft structural articles every loss of weight 1 gram weight is with regard to the value of suitable 1 gram of gold.
Existing low density aluminum alloy, such as 5XXX system, 6XXX system Al-Mg, Al-Mg-Si class alloy, exemplary alloy such as 5A06,6061, density is less than 2.71g/cm3, specific strength is about 185MPa/ (g/cm3)；8XXX system Al-Li-Cu-Mg class alloy, exemplary alloy such as 8090,8091, CP276 etc., density is less than 2.65g/cm3, specific strength is about 190MPa/ (g/cm3)；Al-Li-Mg class alloy, exemplary alloy such as 1420,1421,1423, density can be obtained less than 2.55g/cm3Technique effect, specific strength is less than 200MPa/ (g/cm3)；Adopt ultralight UL30, UL40 aluminium lithium alloy prepared by jet deposition technology of preparing, it is possible to obtain the less about 2.50g/cm of density3Aluminium lithium alloy, the about 235MPa/ (g/cm of its specific strength3)；Obviously, above-mentioned all kinds of alloys improve specific strength by decrease in density, but because the design of intensity deficiency loss of weight is limited.
7XXX system alloy such as 7A04,7A09 and the superstrength alloys such as 7055, its specific strength about 190～230MPa/ (g/cm3), although intensity is significantly high up to 540～680MPa, but the too about 2.78～2.86g/cm of such alloy density3, it is clear that loss of weight design is not beneficial.
Usually improve intensity and the reduction density feature of aluminum alloy materials by adding the low-density alloy units such as magnesium, lithium, silicon in aluminium alloy, achieve good effect.But by the restriction of alloying, technology of preparing condition, its gain is limited.Existing low density aluminum alloy, if 5XXX system, 6XXX system Al-Mg, Al-Mg-Si class alloy are by the restriction of routine casting metallurgical technology and condition, the addition of magnesium is the highest is limited to 5.5%～9.6%；Casting class alloys magnesium addition is the highest less than 10.5%.Although high content of magnesium decrease in density amplitude is bigger again, but can produce serious coarsening compound AlxMgy(such as Al3Mg2、Al5Mg8) phase, alloy mechanical property dramatic drop-off will be caused.
Referenced patent number is ZL200610069171.5 Chinese invention patent " a kind of aluminium-silicon-copper-magnesium series deforming alloy and preparation method thereof " (Authorization Notice No. is CN100439533C), this patent prepares aluminium alloy by melting, refine, rotten, refine again, casting, hot extrusion deformation and forging, the more about 2.7g/cm3 of density of gained alloy, intensity is also low for 379MPa, its specific strength is about 147MPa/ (g/cm3), it is clear that can not meet loss of weight designing requirement.
Can also referenced patent number be the Chinese invention patent " a kind of high-strength Al alloy containing Li and preparation method thereof " (Authorization Notice No. is CN1216167C) of ZL02100830.2, the aluminium alloy specific strength of this patent disclosure has brought up to 170～200MPa/ (g/cm3), but is not enough to reach loss of weight designing requirement.
Summary of the invention
The technical problem to be solved is to provide a kind of low-density high specific strength Aluminium alloy structural material for the above-mentioned state of the art.
To be solved by this invention another technical problem is that the preparation method providing a kind of low-density high specific strength Aluminium alloy structural material for the above-mentioned state of the art.
This invention address that the technical scheme that above-mentioned technical problem adopts is: a kind of low-density high specific strength Aluminium alloy structural material, it is characterized in that this material is with aluminum for main constituent element, add the first constituent element magnesium, the second constituent element lithium, third element copper and the 4th constituent element titanium again to constitute, forming Al-Mg-Li-Cu-Ti system alloy, component and the weight proportion thereof of this material are as follows:
Mg:10.5%～17.4%；
Li:1.2%～2.2%；
Cu:0.3%～1.8%；
Ti:0.15%～0.25%；
Al: the aluminium alloy of surplus.
Further, described magnesium contains the Be accounting for total magnesium weight 0.01%～0.05%.
The preparation method of a kind of low-density high specific strength Aluminium alloy structural material, it is characterised in that comprise the steps:
1. component and weight proportion design thereof
This alloy is Al-Mg-Li-Cu-Ti system alloy, and component and the weight proportion thereof of this material are as follows:
Mg:10.5%～17.4%；
Li:1.2%～2.2%；
Cu:0.3%～1.8%；
Ti:0.15%～0.25%；
Al: the aluminium alloy of surplus；
2. mix designs
Select fine aluminium furnace charge, pure magnesium furnace charge, pure lithium furnace charge and aluminum bronze, aluminum titanium intermediate alloy furnace charge, carry out accurate weighing dispensing；
3. melting, refine and purification
During melting, aluminum, magnesium, lithium add with the form of simple metal furnace charge, and copper, titanium add with the furnace charge form of aluminum bronze, aluminum titanium intermediate alloy；Adopt intermediate frequency electromagnetic induction furnace melting；
4. jet deposition
Carrying out alloy melting, degasification and purified treatment at mid-frequency melting furnace, be poured into funnel and control water conservancy diversion, enter jet deposition nebulizer spray deposition, produce the high speed semisolid sputtering stream of high atomisation, high-speed sputtering deposits on reception chassis；
5. hot extrusion processing
Cutting stock becomes the extruded stock required, is heated to extrusion temperature, and insulation is sent in extruder extrusion molding；
6. finished product processing
Finished product processing processes cutting on semi-finished product, finished product at hot extrusion deformation, processing obtains；Or after hot extrusion deformation, carry out finished product processing；
7. heat treatment
The material processed through finished product, goods are placed in heat-treatment furnace and carry out heat treatment.
Described magnesium contains the Be accounting for total magnesium weight 0.01%～0.05%.Magnesium furnace charge is brought into Be alloy melting there is effective protective effect.
As preferably, in step 3. described in melting, refine and purification condition as follows:
It is initially charged fine aluminium furnace charge and aluminum bronze, aluminum titanium intermediate alloy furnace charge；Fusing is warmed up to 680 DEG C～720 DEG C and will be pressed in aluminum melt through the pure magnesium furnace charge containing Be0.01%0.05% that preheating temperature is 120 DEG C～150 DEG C with bell jar or pressure wooden dipper；Then the upper bell of cover, passes into argon, and argon pressure reaches 0.5～1.2Pa, and flow can be 0.2Nm3/ min carries out melting protection, then by thin seal-packed in the pure lithium furnace charge press-in stove that preheating temperature is 120 DEG C～150 DEG C with aluminum；
Alloy is warmed up to 730 DEG C～750 DEG C after all melting, adopt argon refine.Argon pressure is 0.05～0.07Pa, and the logical argon time controls at 5～10min.Quartz ampoule or graphite-pipe can be adopted in end to load onto graphite breather plug or refractory material breather plug, and the hole being drilled with 2～3mm on breather plug is multiple, and logical argon flow amount controls at 0.2～0.3Nm3/ min.After logical argon, only put 15～20min, remove oxide and gas in aluminium alloy melt；Control aluminium alloy melt temperature reaches 750 DEG C～800 DEG C and pours into a mould；
As preferably, step 4. described in jet deposition condition as follows:
Cast parameters of the guiding vane:
Pouring temperature: 750 DEG C～800 DEG C；
Metal flow: 4～8Kg/Min；
Jet deposition parameter:
Nitrogen flow: 12～25Nm3/ Min；
Nitrogen pressure: 5.0～8.5atm；
Nebulizer scanning speed: 20.9～23.3Hz；
Receive chassis rotary speed: 2.78～3.16r/s；
Receive chassis translational speed: 0.57～0.70mm/s；
Jet deposition height: 670～730mm.
As preferably, step 5. described in hot extrusion processing conditions as follows:
Squeezing parameter:
Extrusion ratio: 8～16；
Extrusion speed: 1.2～1.5m/Min；
Extruding heating technique:
Heating-up temperature: 350 DEG C～400 DEG C；
The heating and thermal insulation time: calculate as follows and obtain:
(i) when extruded stock diameter of phi or thickness δ≤50mm, temperature retention time τ=1.5 Φ or δ；(ii) when extruded stock diameter of phi or thickness δ >=100mm, temperature retention time τ=2 Φ or δ；(iii) extruded stock diameter of phi or thickness δ are when 50～100mm, and temperature retention time τ=1.5 Φ or δ+0.01 (Φ or δ-50) Φ or δ, unit of time is min.
As preferably, the 7. described heat treatment condition of step is as follows:
Solution treatment parameter:
Solid solubility temperature: 400 DEG C～430 DEG C；
Temperature retention time: 0.5～3.5h.
Ageing Treatment parameter；
Aging temp: 90 DEG C～125 DEG C
Aging time: 8～12h；
Or natrual ageing 24h.
The content of Mg is 10.5%～17.4%.The effect of magnesium is to put forward heavy alloyed hot strength by solution strengthening and precipitation strength.Magnesium maximum solid solution degree in aluminum can reach 17.4%, often increases by 1% magnesium in aluminum, and intensity can be made to improve 35MPa.But in actual casting, existing achievement in research shows that intensity reaches 420MPa containing magnesium 14.4% alloy quenching+natrual ageing state.Obviously, the linear gain of magnesium does not reach expection strengthening effect, and it is thick that this is mainly cast sturcture, and precipitated phase forming core difficulty, precipitate size causes greatly.Designing in conjunction with technical scheme, the approach that can pass through solidified structure refinement, deformation strengthening and heat treatment reinforcement obtains gain.
The content of Li is 1.2%～2.2%.The effect of lithium is precipitation strength and solution strengthening.Lithium before solid solubility limit 4.2%, often increases by 1% lithium in aluminum in aluminum, and alloy density can be made to reduce about 3%, and elastic modelling quantity can increase by 5%.By useful S (AL can be formed with the chemical combination of magnesium2MgLi) phase, and intensity and fatigue behaviour raising effect is very big.But excessive lithium easily forms segregation in aluminum, is also easily formed thick AlLi and balances the deleterious aspects such as phase, precipitate free zone, and the price of lithium is high, and melting adds difficulty, it is necessary to vacuum or melting under argon shield simultaneously.
The content of Cu is 0.3%～1.8%.Copper solid solubility in aluminum reaches 5.65%, and copper content is when 4.3%～5.5%, and the invigoration effect of aluminium alloy is reached maximum by copper, but this is totally unfavorable to dropping low-alloyed density, therefore should limit addition.
The content of Ti is 0.15%～0.25%.The effect of titanium is the precipitation Al when alloy graining3Ti phase and dissolving in α phase.Add at alloy hot and be conducive to man-hour controlling recrystallization, after solution treatment, during Precipitation, become AlxMgy(such as Al3Mg2、Al5Mg8) the nucleation core of phase, be conducive to refinement AlxMgy(such as Al3Mg2、Al5Mg8) phase, alloy intensity and fatigue strength raising effect are very big.But excessive titanium easily forms segregation in aluminum, gathers, and is also easily formed thick Al3Ti phase, forming core is unfavorable.
Above-mentioned analysis can illustrate that every kind of composition is all requisite inside the system of whole alloy, and, every kind of alloy content is excessive or crosses major general and directly affects the specific strength of product.
Compared with prior art, it is an advantage of the current invention that:
Component prescription is designed with low-density high-load alloying element magnesium, lithium, a small amount of efficiently intensified element copper, is refined into nuclear element titanium and magnesium furnace charge on a small quantity.On component prescription designs, invention density and strength prediction computational methods, it is to avoid blindness, provide new method for the development of material prescription design scienceization.
Spray deposition technique is adopted to prepare low-density high specific strength aluminium alloy metallurgy tiny, uniform, segregation-free, and the super saturated solid solution degree of alloying element can be widened greatly, coordinate the effect of the alloying element titanium of structure refinement, greatly improve the solid solubility of magnesium, metallurgy tiny, uniform, segregation-free can be prepared.Short distance Technology for Heating Processing, its technical characteristic is solution treatment+artificial or natrual ageing, make low-density high specific strength aluminium alloy of the present invention have the high intensity feature of 7A04,7A09 high strength alumin ium alloy, the low-density feature of aluminium lithium alloy and avoid the method adopting flow harden processing to complicate technology path to the high cost improving intensity, make product category feature widely.
Gained Aluminium alloy structural material density of the present invention is lower is equivalent to the effect of aluminium lithium alloy, the higher effect being equivalent to the superstrength alloys such as 7A04,7A09 and 7055 of intensity, it is achieved specific strength reaches 235MPa/ (g/cm3) and makes applicable surface wider.
Accompanying drawing explanation
Fig. 1 is jet deposition schematic diagram in embodiment 1.
Fig. 2 is the jet deposition state metallographic structure figure in embodiment 2.
Fig. 3 is extrusion process schematic diagram in embodiment 1.
Fig. 4 is the extrusion process state metallographic structure figure in embodiment 2.
Fig. 5 is heat treatment schematic diagram in embodiment 1.
Fig. 6 is the heat treatment state metallographic structure figure in embodiment 2.
Detailed description of the invention
Below in conjunction with accompanying drawing embodiment, the present invention is described in further detail.
Low-density high specific strength Aluminium alloy structural material preparation method, comprises the steps:
One, design of alloy
Density prediction calculates:
The main contributions that density p lowers includes the comprehensive function of the contribution of each constituent element element density value and addition.It is reduced to:
ρ=G/ Σ (Wi/ρi)(1)
Wherein G is component prescription total amount, for convenience of calculation in 100%；
WiPercent by weight is added for each constituent element in component prescription；
ρiDensity value for constituent element each in component prescription.
Strength prediction calculates:
Intensity RmGain mainly includes the gain of each constituent element effect of alloying, structure refinement, deformation strengthening and heat treatment reinforcement.The gain of intensity is mainly 35MPa × W with magnesium for estimation object by each constituent element of alloyingj；Intensity is had substantial gain by structure refinement, but cannot add up and determine；And the gain of deformation strengthening and heat treatment reinforcement, can be 100～300MPa according to previous experiences.It is reduced to:
Rm=35MPa/% × Wj+ 100～300MPa (2)
Wherein WjFor Mg elemental weight percent.
Low-density high specific strength Aluminium alloy structural material composition of the present invention design (weight percentage):
Al-Mg-Li-Cu-Ti system alloy:
Mg:10.5%～17.4%；
Li:1.2%～2.2%；
Cu:0.3%～1.8%；
Ti:0.15%～0.25%；
Be:0.01%～0.05%；
Al: the aluminium alloy of surplus.
Two, mix designs
Select fine aluminium furnace charge, the pure magnesium furnace charge containing Be0.01%～0.05%, pure lithium furnace charge and aluminum-50% copper and aluminum-5% titanium intermediate alloy furnace charge, carry out accurate weighing dispensing；
Three, melting, refine and purification
During melting, aluminum, magnesium, lithium add with the form of simple metal furnace charge, and copper, titanium add with aluminum-50% copper and aluminum-5% titanium intermediate alloy furnace charge form.
Adopting intermediate frequency electromagnetic induction furnace melting, batch is 120kg.
It is initially charged fine aluminium furnace charge and aluminum bronze, aluminum titanium intermediate alloy furnace charge.Fusing is warmed up to 680 DEG C～720 DEG C and will be pressed in aluminum melt through the pure magnesium furnace charge containing Be0.01%～0.05% that preheating temperature is 120 DEG C～150 DEG C with bell jar or pressure wooden dipper；Then the upper bell of cover, passes into argon, and argon pressure reaches 0.5～1.2Pa, and flow can be 0.2Nm3/ min carries out melting protection, then by thin seal-packed in the pure lithium furnace charge press-in stove that preheating temperature is 120 DEG C～150 DEG C with aluminum.
Alloy is warmed up to 730 DEG C～750 DEG C after all melting, adopt argon refine.Argon pressure is 0.05～0.07Pa, and the logical argon time controls at 5～10min.Quartz ampoule or graphite-pipe can be adopted in end to load onto graphite breather plug or refractory material breather plug, and the hole being drilled with 2～3mm on breather plug is multiple, and logical argon flow amount controls at 0.2～0.3Nm3/ min.After logical argon, only put 15～20min, remove oxide and gas in aluminium alloy melt；Control aluminium alloy melt temperature reaches 750 DEG C～800 DEG C and pours into a mould.
Four, jet deposition
Such as Fig. 1, jet deposition is the key means in the preparation of low-density high specific strength Aluminium alloy structural material.Alloy melting, degasification and purified treatment is carried out at mid-frequency melting furnace 1, it is poured into funnel 2 and controls water conservancy diversion, enter jet deposition nebulizer 3 spray deposition, under the effect of atomization gas 4, produce the high speed semisolid sputtering stream 5 of high atomisation, high-speed sputtering deposits on reception chassis 7, by the synthesis of the downward translational speed in chassis with nebulizer pivot angle, the circular ingot blank 6 of preparation diameter of phi 300mm；
Cast parameters of the guiding vane:
Pouring temperature: 750 DEG C～800 DEG C；
Metal flow: 4～8Kg/Min；
Jet deposition parameter:
Nitrogen flow: 12～25Nm3/ Min；
Nitrogen pressure: 5.0～8.5atm；
Nebulizer scanning speed: 20.9～23.3Hz；
Receive chassis rotary speed: 2.78～3.16r/s；
Receive chassis translational speed: 0.57～0.70mm/s；
Jet deposition height: 670～730mm.
Five, extrusion process
Such as Fig. 3, employing hot extrusion deformation processing.
Circular ingot blank 6 cutting stock of diameter of phi 300 is become the extruded stock of Φ 63.5 × 200mm, it is heated to extrusion temperature, temperature retention time is 105min, extruded stock is sent in the extrusion chamber 10 of recipient 9 of diameter of phi 65mm, extrusion molding diameter of phi 17mm bar under the effect of extruding plunger 8, bar is extruded from squeezing passage 11.Squeezing parameter:
Squeezing parameter:
Extrusion ratio: 8～16；
Extrusion speed: 1.2～1.5m/Min；
Extruding heating technique:
Heating-up temperature: 350 DEG C～400 DEG C；
The heating and thermal insulation time:
The extruded stock heating and thermal insulation time of diameter of phi 63.5mm calculates as follows and obtains:
Because extruded stock diameter of phi 63.5mm is in diameter 50～100mm, then temperature retention time τ=1.5 Φ+0.01 (Φ-50) Φ (min)=1.5 × 63.5+0.01 (63.5-50) × 63.5 (min) is 105min.
Six, sample processing
Sample processing directly cutting processing acquisition on extrusion process diameter of phi 17mm bar；
Finished product processing can be cut on large scale extrusion process material, be processed acquisition；
Finished product processing also can on large scale extrusion process material cutting stock, carry out thermoforming processing again, as connecting rod, swing arm, knuckle can adopt bar, heavy-gauge sheeting cutting stock, end product is obtained by normal pressures processing methods such as heating, bases, just forging, finish forging, pipe feeding can be adopted such as storehouse section, housing etc., obtain end product by normal pressures processing methods such as heating, radial forging or rotary press modellings.
Seven, heat treatment
Such as Fig. 5, short route heat treatment is another important means in the preparation of low-density high specific strength Aluminium alloy structural material, i.e. solution treatment+artificial or natrual ageing.By low-density high specific strength Aluminium alloy structural material and goods 11a or hot forming end product.It is placed in heat-treatment furnace 13 and carries out solution treatment；Then artificial aging or natural aging treatment are carried out.
Test sample adopts:
1, the circular ingot blank deposited of diameter of phi 200mm is dissected；Diameter of phi 17mm bar extruding state is dissected and is dissected after heat treatment, cuts metallographic specimen.
2, dissect after diameter of phi 17mm bar heat treatment, cut facies analysis sample；
3, dissect after diameter of phi 17mm bar heat treatment, cut circular standard Φ 6 tensile sample.
The component prescription of each embodiment is as shown in table 1.
The each embodiment chemical composition (wt%) of table 1
The mechanical property feature of each embodiment is as shown in table 2.
The each embodiment mechanical property feature of table 2
The microstructure feature of each embodiment is as shown in table 3.
The each embodiment microstructure feature of table 3
Fig. 2 is the jet deposition state metallographic structure figure in embodiment 2.Fig. 4 is the extrusion process state metallographic structure figure in embodiment 2.Fig. 6 is the heat treatment state metallographic structure figure in embodiment 2.
Make to set up separately with embodiment 2 for example and count:
Density prediction calculates:
Embodiment 2Al content is 100%-(15.0%+2.0%+1.5%+0.20%)=81.3%；
The density of Al is 2.699g/cm3；
The density of Mg is 1.74g/cm3；
The density of Li is 0.545g/cm3；
The density of Cu is 8.9g/cm3；
The density of Ti is 4.54g/cm3；
Then embodiment 2-in-1 gold density:
ρ=G/ Σ (Wi/ρi)=100/ (15.0/1.74+2.0/0.54+1.5/8.9+0.20/4.54+81.3/2.699)=2.33g/cm3
Embodiment 2-in-1 gold strength prediction calculates:
Rm=35MPa/% × Wj+ 100～300MPa >=625MPa.
Burdening calculation is done for example: melting 120kg with embodiment 2.
1) chemical composition of embodiment 2 is as follows:
Mg:15.0%；Li:2.0%；Cu:1.50%；Ti:0.20%；Al: the aluminium alloy of surplus.
2) then alloy needs each alloying element amount to be:
By shove charge 120 kg furnace charge, carry out burdening calculation, it is necessary to the weight of the alloying element of addition is:
Mg:18.0 kilogram；Li:2.4 kilogram；Cu:1.8 kilogram；Ti:0.24；Al: surplus is total algebraical sum (22.44 kilograms) of 120 kg-above-mentioned alloying element, is 97.56 kilograms.
3) because copper, titanium are that the furnace charge form adopting intermediate alloy adds.Therefore, it is necessary to each alloy adding to be converted to the addition of its intermediate alloy.Then:
1. to add 1.8 kilograms of Cu, then need add Al-50%Cu intermediate alloy furnace charge be
1.8 kilograms/50%=3.6 kilogram；To bring Al amount into is 3.6 kilograms-1.8 kilograms=1.8 kilograms.
2. to add 0.24 kilogram of Ti, then need add Al-5%Ti intermediate alloy furnace charge be
0.24 kilogram/5%=4.8 kilogram；To bring Al amount into is 4.8 kilograms-0.24 kilogram=4.56 kilograms.
4) Al that needs are added is:
It it is 97.56 kilograms because 120 kg alloy needs Al amount；
And the aluminum amount that the form of above-mentioned employing intermediate alloy adds copper, titanium is brought into is (1.8+4.56)=6.36 kilogram.
Then needing the fine aluminium supplied is 97.56 kilograms-6.36 kilograms=91.2 kilograms.
5) all furnace charges so far calculate complete, then the furnace charge that should add in stove:
Pure magnesium furnace charge is 18.0 kilograms (not considering burning problems, be theoretical addition amount)；
Pure lithium furnace charge is 2.4 kilograms (not considering burning problems, be theoretical addition amount)；
Al-50%Cu intermediate alloy furnace charge is 3.6 kilograms；
Al-5%Ti intermediate alloy furnace charge is 4.8 kilograms；
Need the pure Al furnace charge added for for 91.2 kilograms；
6) then total addition checking:
Pure magnesium furnace charge+pure lithium furnace charge+aluminum-50%Cu intermediate alloy furnace charge+aluminum-Al-5%Ti intermediate alloy furnace charge+fine aluminium furnace charge=18.0+2.4+3.6+4.8+91.2=120 kilogram.
Claims (8)
1. a low-density high specific strength Aluminium alloy structural material, it is characterized in that this material is with aluminum for main constituent element, adding the first constituent element magnesium, the second constituent element lithium, third element copper and the 4th constituent element titanium again to constitute, form Al-Mg-Li-Cu-Ti system alloy, component and the weight proportion thereof of this material are as follows:
Mg:10.5%～17.4%；
Li:1.5%～2.2%；
Cu:0.8%～1.8%；
Ti:0.15%～0.25%；
Al: the aluminium alloy of surplus.
2. low-density high specific strength Aluminium alloy structural material according to claim 1, it is characterised in that described magnesium contains the Be accounting for total magnesium weight 0.01%～0.05%.
3. the preparation method of a low-density high specific strength Aluminium alloy structural material, it is characterised in that comprise the steps:
1. component and weight proportion design thereof
This alloy is Al-Mg-Li-Cu-Ti system alloy, and component and the weight proportion thereof of this material are as follows:
Mg:10.5%～17.4%；
Li:1.5%～2.2%；
Cu:0.8%～1.8%；
Ti:0.15%～0.25%；
Al: the aluminium alloy of surplus；
2. mix designs
Select fine aluminium furnace charge, pure magnesium furnace charge, pure lithium furnace charge and aluminum bronze, aluminum titanium intermediate alloy furnace charge, carry out accurate weighing dispensing；
3. melting, refine and purification
During melting, aluminum, magnesium, lithium add with the form of simple metal furnace charge, and copper, titanium add with the furnace charge form of aluminum bronze, aluminum titanium intermediate alloy；Adopt intermediate frequency electromagnetic induction furnace melting；
4. jet deposition
Carrying out alloy melting, degasification and purified treatment at mid-frequency melting furnace, be poured into funnel and control water conservancy diversion, enter jet deposition nebulizer spray deposition, produce the high speed semisolid sputtering stream of high atomisation, high-speed sputtering deposits on reception chassis；
5. hot extrusion processing
Cutting stock becomes the extruded stock required, is heated to extrusion temperature, and insulation is sent in extruder extrusion molding；
6. finished product processing
Finished product processing processes cutting on semi-finished product, finished product at hot extrusion deformation, processing obtains；Or after hot extrusion deformation, carry out finished product processing；
7. heat treatment
The material processed through finished product, goods are placed in heat-treatment furnace and carry out heat treatment.
4. preparation method according to claim 3, it is characterised in that described magnesium contains the Be accounting for total magnesium weight 0.01%～0.05%.
5. preparation method according to claim 4, it is characterised in that step 3. described in melting, refine and purification condition as follows:
It is initially charged fine aluminium furnace charge and aluminum bronze, aluminum titanium intermediate alloy furnace charge；Fusing is warmed up to 680 DEG C～720 DEG C and will be pressed in aluminum melt through the pure magnesium furnace charge containing Be0.01%0.05% that preheating temperature is 120 DEG C～150 DEG C with bell jar or pressure wooden dipper；Then the upper bell of cover, passes into argon, and argon pressure reaches 0.5～1.2Pa, and flow is 0.2Nm3/ min carries out melting protection, then by thin seal-packed in the pure lithium furnace charge press-in stove that preheating temperature is 120 DEG C～150 DEG C with aluminum；
Alloy is warmed up to 730 DEG C～750 DEG C after all melting, adopt argon refine, argon pressure is 0.05～0.07Pa, the logical argon time controls at 5～10min, quartz ampoule or graphite-pipe is adopted to load onto graphite breather plug or refractory material breather plug in end, the hole being drilled with 2～3mm on breather plug is multiple, and logical argon flow amount controls at 0.2～0.3Nm3/ min, after logical argon, stands 15～20min, removes oxide and gas in aluminium alloy melt；Control aluminium alloy melt temperature reaches 750 DEG C～800 DEG C and pours into a mould.
6. preparation method according to claim 5, it is characterised in that step 4. described in jet deposition condition as follows:
Cast parameters of the guiding vane:
Pouring temperature: 750 DEG C～800 DEG C；
Metal flow: 4～8Kg/Min；
Jet deposition parameter:
Nitrogen flow: 12～25Nm3/ Min；
Nitrogen pressure: 5.0～8.50atm；
Nebulizer scanning speed: 20.9～23.3Hz；
Receive chassis rotary speed: 2.78～3.16r/s；
Receive chassis translational speed: 0.57～0.70mm/s；
Jet deposition height: 670～730mm.
7. preparation method according to claim 6, it is characterised in that step 5. described in hot extrusion processing conditions as follows:
Squeezing parameter:
Extrusion ratio: 8～16；
Extrusion speed: 1.2～1.5m/Min；
Extruding heating technique:
Heating-up temperature: 350 DEG C～400 DEG C；
The heating and thermal insulation time: calculate as follows and obtain:
(i) when extruded stock diameter of phi or thickness δ≤50mm, temperature retention time τ=1.5 Φ or δ；(ii) when extruded stock diameter of phi or thickness δ >=100mm, temperature retention time τ=2 Φ or δ；(iii) extruded stock diameter of phi or thickness δ are when 50～100mm, and temperature retention time τ=1.5 Φ or δ+0.01 (Φ or δ-50) Φ or δ, unit of time is min.
8. preparation method according to claim 7, it is characterised in that the 7. described heat treatment condition of step is as follows:
Solution treatment parameter:
Solid solubility temperature: 400 DEG C～430 DEG C；
Temperature retention time: 0.5～3.5h；
Ageing Treatment parameter；
Aging temp: 90 DEG C～125 DEG C；
Aging time: 8～12h；
Or natrual ageing 24h.
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| CN105345004B (en) * | 2015-10-15 | 2018-09-14 | 江苏豪然喷射成形合金有限公司 | A method of it utilizes and is injected into the standby three-dimensional big specification aluminium lithium alloy billet of shape |
| CN106702237A (en) * | 2016-12-20 | 2017-05-24 | 江苏豪然喷射成形合金有限公司 | Spray forming method for aluminum-lithium alloy |
| CN106636998B (en) * | 2016-12-20 | 2018-06-29 | 江苏豪然喷射成形合金有限公司 | A kind of gas shield device for aluminium lithium alloy production |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US6056835A (en) * | 1993-01-27 | 2000-05-02 | Toyota Jidosha Kabushiki Kaisha | Superplastic aluminum alloy and process for producing same |
| CN101457318A (en) * | 2008-12-20 | 2009-06-17 | 中国兵器工业第五二研究所 | High-silicon aluminum alloy cylinder sleeve material and preparation method thereof |
| CN103045920A (en) * | 2012-12-21 | 2013-04-17 | 中国兵器工业第五二研究所 | High-silicon aluminum alloy cylinder sleeve material and fabrication method thereof |
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| JPS552757A (en) * | 1978-06-23 | 1980-01-10 | Hitachi Ltd | Manufacture of high strength aluminum alloy material |
| CA1337747C (en) * | 1986-12-01 | 1995-12-19 | K. Sharvan Kumar | Ternary aluminium-lithium alloys |
| JPH0790460A (en) * | 1993-08-10 | 1995-04-04 | Kawasaki Steel Corp | High strength aluminum alloy sheet excellent in formability and weldability and its production |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US6056835A (en) * | 1993-01-27 | 2000-05-02 | Toyota Jidosha Kabushiki Kaisha | Superplastic aluminum alloy and process for producing same |
| CN101457318A (en) * | 2008-12-20 | 2009-06-17 | 中国兵器工业第五二研究所 | High-silicon aluminum alloy cylinder sleeve material and preparation method thereof |
| CN103045920A (en) * | 2012-12-21 | 2013-04-17 | 中国兵器工业第五二研究所 | High-silicon aluminum alloy cylinder sleeve material and fabrication method thereof |
Non-Patent Citations (2)
| Title |
|---|
| "Age-hardening of an Al–Li–Cu–Mg alloy (2091) processed by high-pressure torsion";Seungwon Lee et al.;《Materials Science and Engineering: A》;20120601;第546卷;第82-89页 * |
| "Effects of solution treatment on mechanical properties and microstructures of Al-Li-Cu-Mg-Ag alloy";YU Cheng et al.;《Journal of Central South University》;20130815;第2083-2089页 * |
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