CN100557053C - High-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy - Google Patents

High-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy Download PDF

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CN100557053C
CN100557053C CNB2006101369038A CN200610136903A CN100557053C CN 100557053 C CN100557053 C CN 100557053C CN B2006101369038 A CNB2006101369038 A CN B2006101369038A CN 200610136903 A CN200610136903 A CN 200610136903A CN 100557053 C CN100557053 C CN 100557053C
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alloy
add
pure
purity
rafifinal
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CN101205578A (en
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陈康华
方华婵
张茁
祝昌军
黄兰萍
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中南大学
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Abstract

The invention discloses a kind of high-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy,, add proper C r simultaneously by in Al-Zn-Mg-(Cu) alloy, adding Zr; Or when adding Zr, add Cr and rare earth element er or Yb.The present invention is behind the above-mentioned element of compound interpolation, can improve Al-Zn-Mg-(Cu) alloy recrystallization drag, improve intensity, fracture toughness property and the anti-stress corrosion performance of alloy simultaneously, and microalloy such as Zr, Cr and rare earth metal Er or Yb price are relatively cheap, are more suitable for suitability for industrialized production.

Description

High-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy
Technical field
The present invention relates to the metal alloy preparation, belong to high-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy field especially.
Background technology
Forming fine coherence disperse phase by microalloying, suppress recrystallize and grain growth, maintenance deformation-recovery tissue effectively, is the approach that improves high-strength, superduralumin alloy strength and stress corrosion resistance simultaneously.In early days, form non-coherence aluminide disperse phase by adding trace Cr, Mn.After change into and add Zr, form metastable L1 2Type Al 3Zr coherence disperse phase has improved the drag that suppresses recrystallize like this, has improved stress corrosion resistance, but metastable L1 2Type Al 3When growing at high temperature, Zr can change the stable DO of non-coherence in homogenizing and the solution treatment into 23Type Al 3Zr disperse phase, therefore, the effect that suppresses recrystallize can decrease.Add micro alloying element Sc and suppress recrystallize effect best bet at present, it can form the fine Al with the matrix coherence 3Sc disperse phase particle can improve the toughness and the anti-stress corrosion performance of alloy when improving intensity; Also can use Zr instead of part Sc, form Al 3(Zr, Sc) phase, effect are more remarkable.But owing to costing an arm and a leg of Sc, the market price is about 40,000 yuans/kilogram at present, therefore, is difficult to be actually used in the production of commercial aluminum alloy.
Summary of the invention
The objective of the invention is in aluminium alloy, to add low-cost micro alloying element, replace Sc, Al 3Zr carries out alloying, to form new and effective polynary coherence disperse phase.By in Al-Zn-Mg-(Cu) alloy, when adding Zr, add proper C r substitute for Al 3Part A l among the Zr, or compound interpolation Cr and rare earth element (Er, Yb) replace Al 3Part A l among the Zr and Zr adjust Al 3The lattice types of Zr and parameter make and stablize DO 23Or metastable L1 2Type structure Al 3Zr changes stable L1 into 2Structure (Al, Cr) 3(Zr, Re) (Re=Er or Yb) effectively suppresses recrystallize, keeps the deformation recovery tissue, improves intensity, fracture toughness property and the anti-stress corrosion performance of Al-Zn-Mg-(Cu) alloy.
Detailed technology scheme of the present invention is: a kind of high-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy, comprise main alloying element Al, Zn, Mg or Al, Zn, Mg, Cu, also adding total content, to account for alloy mass per-cent be 0.1~1.2% microalloy element Zr and Cr.
Among the present invention, except that adding microalloy element Zr and Cr, also can add rare earth element er or Yb, concrete several combinations: Zr-Cr, Zr-Cr-Er, the Zr-Cr-Yb of comprising; Add-on accounts for 0.1~1.2% of alloy mass per-cent.
Alloy as claimed in claim 1 or 2 is characterized in that: the content of Zn, Mg, Cu is: Zn:3.5~9.2wt%; Mg:1.0~2.9wt%; Cu:0~2.2wt%.
Alloy as claimed in claim 1 or 2 is characterized in that: the content of Zr and Cr is: Zr:0.05~0.2wt%; Cr:0.05~0.3wt%.
Alloy as claimed in claim 2 is characterized in that: the content of Er or Yb is: Er:0.05~0.5wt%; Yb:0.05~0.4wt%.
The present invention adds in Al-Zn-Mg-(Cu) alloy in the Zr, compound interpolation Cr and rare earth element (Er or Yb), part substitute for Al respectively 3Al among the Zr and Zr adjust Al 3The lattice types of Zr and parameter make and stablize DO 23Or metastable L1 2Type structure Al 3Zr changes stable L1 into 2Structure (Al, Cr) 3(Zr, Re) (Re=Er or Yb) effectively suppresses recrystallize, keeps the deformation recovery tissue, improves intensity, fracture toughness property and the stress corrosion resistance of Al-Zn-Mg-(Cu) alloys peak aging state and three grades of aging states.And microalloy such as Zr, Cr and rare earth metal Er or Yb price are relatively cheap, are suitable for suitability for industrialized production.Al-Zn-Mg-(Cu) alloy is widely used in fields such as space flight and aviation, vehicle, building at present, therefore, adopt the present invention can develop a series of Zr of containing and Cr, or contain high-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy of Zr and Cr and rare earth element (Er or Yb), and may be used on every field.
Description of drawings
Fig. 1: the alloy crack growth rate v-stress intensity factor graphic representation of Comparative Examples 1, embodiment 1~3 in the 3.5%NaCl aqueous solution under the T6 aging state;
Fig. 2: the alloy crack growth rate v-stress intensity factor graphic representation of Comparative Examples 2, embodiment 4~6 in the 3.5%NaCl aqueous solution under the T6 aging state;
Fig. 3: the alloy crack growth rate v-stress intensity factor graphic representation of Comparative Examples 3, embodiment 7~9 in the 3.5%NaCl aqueous solution under the T6 aging state;
Fig. 4: the alloy crack growth rate v-stress intensity factor graphic representation of Comparative Examples 4, embodiment 7~9 in the 3.5%NaCl aqueous solution under the T6 aging state;
Fig. 5: the alloy crack growth rate v-stress intensity factor graphic representation of Comparative Examples 5, embodiment 10~11 in the 3.5%NaCl aqueous solution under the T6 aging state;
Fig. 6: the alloy crack growth rate v-stress intensity factor graphic representation of Comparative Examples 6, embodiment 12 in the 3.5%NaCl aqueous solution under the T77 aging state.
Wherein, each curve is corresponding as follows with each embodiment and Comparative Examples:
A-1 Comparative Examples 1; A-10 Comparative Examples 4;
A-2 embodiment 1; A-11 embodiment 7;
A-3 embodiment 2; A-12 embodiment 8;
A-4 embodiment 3; A-13 embodiment 9;
A-5 Comparative Examples 2; B-1 Comparative Examples 5;
A-6 embodiment 4; B-2 embodiment 10;
A-7 embodiment 5; B-3 embodiment 11;
A-8 embodiment 6; C-1 Comparative Examples 6;
A-9 Comparative Examples 3; C-2 embodiment 12.
Embodiment
Comparative Examples 1: adopt the ingot metallurgy legal system to be equipped with Al-8.6%Zn-2.5%Mg-2.2%Cu-0.08%Zr (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cu, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Comparative Examples 2: preparation Al-8.6%Zn-2.5%Mg-1.0%Cu-0.16%Zr (wt%) alloy.The preparation method is as described in the Comparative Examples 1.
Comparative Examples 3: preparation Al-9.2%Zn-2.9%Mg-2.2%Cu-0.16%Zr (wt%) alloy.The preparation method is as described in the Comparative Examples 1.
Comparative Examples 4: preparation Al-9.2%Zn-2.9%Mg-2.2%Cu-0.16%Zr-0.25%Sc (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Sc master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cu, Al-Zr, Al-Sc master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Comparative Examples 5: preparation Al-4.0%Zn-1.8%Mg-0.2%Zr (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Zr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add the Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Comparative Examples 6: preparation Al-8.6%Zn-2.5%Mg-2.2%Cu-0.16%Zr (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cu, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 1: preparation Al-8.6%Zn-2.5%Mg-2.2%Cu-0.08%Zr-0.1%Cr alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 2: preparation Al-8.6%Zn-2.5%Mg-2.2%Cu-0.08%Zr-0.1%Cr-0.1Yb% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Yb master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Yb, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 3: preparation Al-8.6%Zn-2.5%Mg-2.2%Cu-0.08%Zr-0.1%Cr-0.1Er% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Er master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Er, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 4: preparation Al-8.6%Zn-2.5%Mg-1.0%Cu-0.16%Zr-0.2%Cr alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 5: preparation Al-8.6%Zn-2.5%Mg-1.0%Cu-0.16%Zr-0.2%Cr-0.3Yb% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Yb master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Yb, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 6: preparation Al-8.6%Zn-2.5%Mg-1.0%Cu-0.16%Zr-0.2%Cr-0.4Er% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Er master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Er, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 7: preparation Al-9.2%Zn-2.9%Mg-2.2%Cu-0.16%Zr-0.2%Cr alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 8: preparation Al-9.2%Zn-2.9%Mg-2.2%Cu-0.16%Zr-0.2%Cr-0.3Yb% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Yb master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Yb, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 9: preparation Al-9.2%Zn-2.9%Mg-2.2%Cu-0.16%Zr-0.2%Cr-0.4Er% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Er master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Er, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Embodiment 10: preparation Al-4.0%Zn-1.8%Mg-0.2%Zr-0.28%Cr (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Zr master alloy, Al-Cr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage, the cooling back demoulding gets alloy.
Embodiment 11: preparation Al-4.0%Zn-1.8%Mg-0.2%Zr-0.28%Cr-0.45%Er (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Zr master alloy, Al-Er master alloy, Al-Cr master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Er, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage, the cooling back demoulding gets alloy.
Embodiment 12: preparation Al-8.6%Zn-2.5%Mg-2.2%Cu-0.16%Zr-0.2%Cr-0.3Yb% (wt%) alloy.Raw materials used is rafifinal (purity is 99.99%), technical pure Mg (purity is 99.9%), technical pure Zn (purity is 99.9%), Al-Cu master alloy, Al-Zr master alloy, Al-Cr master alloy, Al-Yb master alloy.At first rafifinal is joined the graphite clay crucible, melting in electrical crucible, smelting temperature is 780 ℃, after the rafifinal fusing, add Al-Yb, Al-Cu, Al-Cr, Al-Zr master alloy, reduce to 760 ℃, add technical pure Zn, fusing also stirs the back and adds technical pure Mg, remove surperficial slag after, add 0.2%~0.4% hexachloroethane (C 2Cl 6) degasification of refining agent deslagging, left standstill 10~15 minutes, pour in the swage cooling back demoulding.
Table 1 is the composition of Al-Zn-Mg-(Cu) alloy.A-1 alloy, A-2 alloy, A-3 alloy, A-4 alloy, A-5 alloy, A-6 alloy, A-7 alloy, A-8, A-9 alloy, A-10 alloy, A-11 alloy, A-12 alloy, A-13 alloy cast ingot are behind 465 ℃/24h homogenizing annealing, carry out hot extrusion at 410 ℃-430 ℃ again, extrusion ratio is 12.2, carry out solution treatment afterwards, the solid solution system is as follows: 450 ℃ are incubated 1 hour, be warming up to 470 ℃ of insulations 1 hour, continue to be warming up to 480 ℃ of insulations 2 hours, cold-water quench, T6 timeliness (130 ℃ are incubated 24 hours).
B-1 alloy, B-2 alloy, B-3 alloy cast ingot carry out hot extrusion at 410 ℃-430 ℃ again behind 465 ℃/24h homogenizing annealing, extrusion ratio is 12.2, carry out solution treatment afterwards, solid solubility temperature is 475 ℃, cold-water quench, T6 timeliness (130 ℃ are incubated 24 hours).
C-1, C-2 alloy cast ingot are behind 465 ℃/24h homogenizing annealing, carry out hot extrusion at 410 ℃-430 ℃ again, extrusion ratio is 12.2, carry out solution treatment afterwards, solid solubility temperature is 475 ℃, cold-water quench, 130 ℃ of insulations of T77 timeliness (three grades of timeliness) were warming up to 173 ℃ of insulations 3 hours after 24 hours, were cooled to 130 ℃ of insulations 24 hours at last.
Table 2 is under the T6 state, microalloying Al-Zn-Mg-(Cu) hardness of alloy, mechanical property and stress intensity factor data sheet.As can be seen from Table 2, hardness, mechanical property and the stress corrosion performance that adds A-2, A-3, the A-4 alloy aging attitude of Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-8.6Zn-2.5Mg-2.2Cu alloy all is better than the A-1 alloy in the Comparative Examples 1; Hardness, mechanical property and the stress corrosion performance that adds A-6, A-7, the A-8 alloy aging attitude of Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-8.6Zn-2.5Mg-1.0Cu alloy all is better than the A-5# alloy in the Comparative Examples 2; The hardness, mechanical property and the stress corrosion performance that add A-11, A-12, the A-13 alloy aging attitude of Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-9.2Zn-2.9Mg-2.2Cu alloy all are better than Comparative Examples 3 and add the A-9 alloy of Zr and the A-10 alloy that Comparative Examples 4 is added Zr-Sc; Hardness, mechanical property and the stress corrosion performance that adds B-2, the B-3 alloy aging attitude of Zr-Cr, Zr-Cr-Er in the Al-4.0Zn-1.8Mg alloy all is better than the B-1 alloy in the Comparative Examples 5.
Table 3 is T77 aging states, microalloying Al-Zn-Mg-(Cu) hardness of alloy, mechanical property and stress intensity factor data sheet.As can be seen from Table 3, hardness, mechanical property and the stress corrosion performance that adds the C-2 alloy T77 aging state of Zr-Cr-Yb in the Al-8.6Zn-2.5Mg-2.2Cu alloy all is better than the C-1 alloy that only adds Zr in the Comparative Examples 6.
Table 4 is under the T6 aging state, and test medium is the 3%NaCl aqueous solution, and when stress in bending was 522MPa and 580MPa, microalloying was to Al-Zn-Mg-(Cu) alloy stress etching crack germinating resistance effect.As can be seen from Table 4, add A-2, the A-3 of Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er, the stress corrosion resistance that the A-4 alloy can improve the Al-8.6Zn-2.5Mg-2.2Cu alloy in the Al-8.6Zn-2.5Mg-2.2Cu alloy, and performance all is better than only adding in the Comparative Examples 1 the A-1 alloy of Zr; The stress corrosion resistance that adds A-6, A-7, the A-8 alloy of Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-8.6Zn-2.5Mg-1.0Cu alloy all is better than the A-5 alloy in the Comparative Examples 3; A-11, the A-12, the A-13 alloy stress corrosion resistance that add Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-9.2Zn-2.9Mg-2.2Cu alloy all are better than Comparative Examples 3 and add the A-9 alloy of Zr and the A-10 alloy that Comparative Examples 4 is added Zr-Sc.
As shown in Figure 1, A-2, A-3, the A-4 alloy stress corrosive nature of adding Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-8.6%Zn-2.5%Mg-2.2%Cu alloy all is better than the A-1 alloy that Comparative Examples 1 only contains Zr.
As shown in Figure 2, A-6, A-7, the A-8 alloy stress corrosive nature of adding Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-8.6%Zn-2.5%Mg-1.0%Cu alloy all is better than the A-5 alloy that Comparative Examples 2 only contains Zr.
As shown in Figure 3, A-11, A-12, the A-13 alloy stress corrosive nature of adding Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-9.2%Zn-2.9%Mg-2.2%Cu alloy all is better than the A-9 alloy that Comparative Examples 3 only contains Zr.
As shown in Figure 4, A-11, A-12, the A-13 alloy stress corrosive nature of adding Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er in the Al-9.2%Zn-2.9%Mg-2.2%Cu alloy all is better than the A-10 alloy that Comparative Examples 4 contains Zr-Sc.
As shown in Figure 5, B-2, the B-3 alloy stress corrosive nature of adding Zr-Cr, Zr-Cr-Er in the Al-4.0%Zn-1.8%Mg alloy all is better than the B-1 alloy that Comparative Examples 5 contains Zr.
As shown in Figure 6, add the C-1 alloy that stress corrosion performance under the C-2 alloy T77 aging state of Zr-Cr-Yb is better than the interpolation Zr of Comparative Examples 6 in the Al-8.6%Zn-2.5%Mg-2.2%Cu alloy.
Illustrate add Zr-Cr, Zr-Cr-Yb, Zr-Cr-Er after, when improving Al-Zn-Mg-(Cu) ultra-high-strength aluminum alloy peak value timeliness and three grades of aging state intensity, plasticity and fracture toughness propertyes, improve the alloy anti-stress corrosion performance.
Table 1 Al-Zn-Mg-(Cu) alloying constituent (mass percent, wt%)
Microalloying Al-Zn-Mg-(Cu) hardness of alloy, mechanical property and stress intensity factor under the table 2 T6 aging state
Annotate: K ICDirection of crack propagation is the direction of extrusion during test; Institution of prescription: 130 ℃/24h
Table 3 T77 aging state, microalloying Al-Zn-Mg-(Cu) hardness of alloy, mechanical property and stress intensity factor
Annotate: K ICDirection of crack propagation is the direction of extrusion during test; Institution of prescription: 130 ℃/24h+173 ℃/3h+130 ℃/24h
Under the table 4T6 aging state, microalloying Al-Zn-Mg-(Cu) the alloy stress etching crack germinating time
Annotate: stress corrosion cracking germinating direction is the S-direction; Institution of prescription: 130 ℃/24h

Claims (2)

1. a high-strength high-ductility corrosion A1-Zn-Mg-Cu alloy comprises main alloying element A1, Zn, Mg or Al, Zn, Mg, Cu, and microalloy element Zr and Cr, it is characterized in that: also comprise rare earth element er or Yb; It is 0.1~1.2% that Zr-Cr-Er or Zr-Cr-Yb total content account for alloy mass per-cent; The content of Er or Yb is: Er:0.05~0.5wt%; Yb:0.05~0.4wt%; The content of Zn, Mg, Cu is: Zn:3.5~9.2wt%; Mg:1.0~2.9wt%; Cu:0~2.2wt%; Surplus is Al.
2. alloy as claimed in claim 1 is characterized in that: the content of Zr and Cr is: Zr:0.05~0.2wt%; Cr:0.05~0.3wt%.
CNB2006101369038A 2006-12-19 2006-12-19 High-strength high-ductility corrosion Al-Zn-Mg-(Cu) alloy CN100557053C (en)

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US8017072B2 (en) 2008-04-18 2011-09-13 United Technologies Corporation Dispersion strengthened L12 aluminum alloys
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US9194027B2 (en) 2009-10-14 2015-11-24 United Technologies Corporation Method of forming high strength aluminum alloy parts containing L12 intermetallic dispersoids by ring rolling
US8409497B2 (en) 2009-10-16 2013-04-02 United Technologies Corporation Hot and cold rolling high strength L12 aluminum alloys
CN101724797B (en) * 2009-12-01 2011-07-13 中南大学 Solid solution heat treatment method of Al-Zn-Mg-Cu alloy and aluminum alloy treated by using same
CN102465223A (en) * 2010-11-17 2012-05-23 北京有色金属研究总院 Aluminum alloy material with ultrahigh strength, high toughness and wear resistance and preparation method thereof
CN102586706B (en) * 2012-03-07 2015-10-14 中国第一汽车股份有限公司 A kind of heat treating method making aluminium alloy obtain high-dimensional stability
CN104651672B (en) * 2015-01-30 2017-10-13 北京工业大学 The aluminium alloy and its Technology for Heating Processing of a kind of anti-corrosion reinforcings of Al Yb Zr
CN106381424A (en) * 2016-11-24 2017-02-08 苏州华意铭铄激光科技有限公司 High-performance composite aluminum-based metal product
CN106702235B (en) * 2017-02-15 2018-12-04 苏州慧金新材料科技有限公司 A kind of high-strength high-fracture toughness aluminium alloy

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