EP2714954A2 - Alliages d'aluminium - Google Patents

Alliages d'aluminium

Info

Publication number
EP2714954A2
EP2714954A2 EP12789530.8A EP12789530A EP2714954A2 EP 2714954 A2 EP2714954 A2 EP 2714954A2 EP 12789530 A EP12789530 A EP 12789530A EP 2714954 A2 EP2714954 A2 EP 2714954A2
Authority
EP
European Patent Office
Prior art keywords
alloy
hours
heating
temperature
holding
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12789530.8A
Other languages
German (de)
English (en)
Other versions
EP2714954A4 (fr
Inventor
Abhijeet Misra
James A. Wright
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Questek Innovations LLC
Original Assignee
Questek Innovations LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Questek Innovations LLC filed Critical Questek Innovations LLC
Publication of EP2714954A2 publication Critical patent/EP2714954A2/fr
Publication of EP2714954A4 publication Critical patent/EP2714954A4/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent
    • 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
    • C22F1/053—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 zinc as the next major constituent

Definitions

  • N00014-09-M-0400 and N00014-1 l-C-0080 may have certain rights in the invention.
  • Aluminum alloys such as the 7XXX Al-Zn-based alloys, are commonly used in structural applications demanding high specific strength.
  • the commercial aluminum alloy 7050 is widely used for aerospace applications. When aged to near the peak of strength, commercial aluminum alloys are susceptible to stress-corrosion cracking (SCC). Thus, there has developed a need for aluminum alloys which show a high strength and yet are resistant to SCC.
  • the disclosure relates to an alloy comprising, by weight, about 5.8% to about 6.8%) zinc, about 2.5% to about 3.0% magnesium, about 1.5% to about 2.3% copper, 0% to about 0.2%) scandium, 0% to about 0.2% zirconium, and optionally less than about 0.50% silver, the balance essentially aluminum and incidental elements and impurities.
  • the alloy has a stress-corrosion cracking threshold stress of at least about 240 MPa using an ASTM G47 short-transverse test specimen and a yield strength of at least about 510 MPa using an ASTM E8 longitudinal test specimen.
  • the disclosure relates to a method for producing an alloy, the method comprising preparing a melt that includes, by weight, about 5.8% to about 6.8% zinc, about 2.5% to about 3.0% magnesium, about 1.5% to about 2.3% copper, 0% to about 0.2% scandium, 0% to about 0.2% zirconium, and optionally less than about 0.50% silver, the balance essentially aluminum and incidental elements and impurities.
  • the melt can be cooled to room temperature.
  • the alloy is homogenized by heating it from room temperature to 400°C at 1°C per minute, holding it at 400°C for 12 hours, heating it from 400°C at 1°C per minute, and holding it at 460°C-480°C for 24-48 hours.
  • the disclosure relates to a method for producing an alloy that comprises an aluminum matrix.
  • the SCC index of the alloy is less than or equal to 1.6.
  • Fig. 1 is a graph plotting short-transverse SCC threshold stress and typical longitudinal yield strength of some embodiments of alloys in comparison to conventional aluminum alloys.
  • Fig. 2 is a graph plotting maximum applied stress as a function of life (cycles to failure) of one of the embodiments of Fig. 1 in comparison to a conventional aluminum alloy.
  • stress-corrosion-cracking resistance include definitions that are generally known in the art such as those found in ASM MATERIALS ENGINEERING DICTIONARY (J.R. Davis ed., ASM
  • Homogenizing refers to a process in which high-temperature soaking is used at a suitable temperature for a suitable dwell time to reduce chemical or metallurgical segregation, which occurs as a natural result of solidification in some alloys. In some embodiments, the high-temperature soaking is conducted for a dwell time of about 8 hours to about 48 hours.
  • Extrusion or “extruding” as used herein refers to a conversion of a metal ingot or billet into lengths of uniform cross section by forcing the metal to flow plastically through a die orifice.
  • Aging temperature refers to an elevated temperature at which an alloy is kept for heat treatment. Such heat treatment may suitably induce a precipitation reaction. In some embodiments, the heat treatment may be conducted at two distinct temperatures for two distinct times.
  • Yield strength refers to the stress level at which plastic deformation begins. [0016] Any recited range described herein is to be understood to encompass and include all values within that range, without the necessity for an explicit recitation.
  • aspects of the disclosure relate to aluminum alloys which show acceptably high strength and yet are resistant to SCC. Without being necessarily limited by any mechanism or mode of operation, it may be that segregation of zinc to grain boundaries in aluminum alloys can make the alloy susceptible to SCC. According to one aspect, the disclosed alloys can minimize the elemental segregation of zinc to the grain boundaries, and thereby reduce the susceptibility of the alloy to SCC. It is contemplated that segregation of zinc to the grain boundaries in Al-Zn-based alloys can be prevented by using the zinc to instead form the MgZn 2 phase. The MgZn 2 phase forms both within the grain and at the grain boundary, as either discrete or linked particles.
  • SCC index 2xwpZn + wpMg - wpCu [1] where wpZn, wpMg, and wpCu are the weight percentages of Zn, Mg, and Cu, respectively, in solution in the matrix of the alloy.
  • the SCC index is calculated at the aging temperature, and is based on the equilibrium composition of the aluminum matrix at the aging temperature, after accounting for the phase fraction of precipitates present at the aging temperature.
  • the matrix composition can be computed with any suitable thermodynamic database and calculation packages such as Thermo-Calc ® software version N offered by Thermo-Calc Software (McMurray, PA).
  • an alloy can be produced by adding zinc, copper, and magnesium to an aluminum matrix, in amounts calculated using the SCC index, such that the SCC index is maintained at or below about 1.6 (e.g., about 1.6, about 1.5, about 1.4, about 1.3, about 1.2, about 1.1, about 1.0, about 0.9, about 0.8, about 0.7, about 0.6, about 0.5, about 0.4, about 0.3, about 0.2, about 0.1, or less).
  • the alloy may contain other components and/or additives, including other components and/or additives as specified herein, and may be further processed using a variety of processing techniques known in the art, and also including the processing techniques described herein, such as press-forging, homogenizing, aging, and the like.
  • the alloy can be first homogenized after solidification from the melt by heating it from room temperature to 400°C at 1°C per minute, holding it at 400°C for 12 hours, heating it from 400°C at 1°C per minute, and holding it at 460°C-480°C for 24-48 hours.
  • the homogenized alloy can then, in another embodiment, be hot-worked, e.g., extruded to a change in cross section, then solution heat-treated at 460°C-480°C for 1-4 hours, then aged at a first temperature of 100°C-120°C for 6-12 hours, then heated to a second temperature of 160°C-180°C and held at the second temperature for 8-30 hours, and quenched with water.
  • heat treatments can assist in forming the r
  • different homogenization, forging, aging, and/or other forming or heat treatment techniques may be used.
  • the alloy may be optionally subjected to a stress-relief treatment between the solution
  • the stress-relief treatment can include stretching the alloy, compressing the alloy, or combinations thereof.
  • the disclosed alloys incorporate dispersoid forming elements in amounts sufficient to inhibit recrystallization.
  • Such dispersoid formers may include scandium and zirconium.
  • the dispersoid formers may form dispersed Ll 2 phase particles in the alloy, wherein the Ll 2 phase constitutes about 0.1% by volume of the alloy.
  • the alloys are hardened by the r
  • -MgZn 2 phase may constitute about 3% to about 8% by volume of the alloy.
  • -MgZn 2 phase may form within grains and/or at grain boundaries, and may form as discrete particles and/or linked particles. Linked particles are often more likely to form at grain boundaries, adversely affecting the SCC resistance. Accordingly, in one embodiment, the alloy contains r
  • Various heat treatments that are known in the art or otherwise disclosed herein can be used to guide the formation of r
  • the composition of an alloy includes, by weight, about 5.8% to about 6.8%> zinc, about 2.5% to about 3.0% magnesium, about 1.5% to about 2.3% copper, 0%> to about 0.2%> scandium, 0%> to about 0.2%> zirconium, and optionally less than about 0.50% silver, the balance essentially aluminum and incidental elements and impurities.
  • the alloy may include the elements in the nominal composition, as well as additional elements; in another embodiment, the alloy may consist essentially of the elements in the nominal composition; and in a further embodiment, the alloy may consist only of the elements in the nominal composition.
  • Incidental elements and impurities in the disclosed alloys may include, but are not limited to, silicon, iron, chromium, nickel, vanadium, titanium, or mixtures thereof, and may be present in the alloys disclosed herein in amounts totaling no more than 1%, no more than 0.9%, no more than 0.8%, no more than 0.7%, no more than 0.6%, no more than 0.5%, no more than 0.4%, no more than 0.3%, no more than 0.2%, no more than 0.1%, no more than 0.05%, no more than 0.01%, or no more than 0.001%. Additionally, in one embodiment, the alloy has a predominately face-centered cubic crystal structure, with additional phases and precipitates, such as those disclosed herein.
  • the alloy has a stress-corrosion cracking threshold stress of at least about 240 MPa using an ASTM G47 short-transverse test specimen and a yield strength of at least about 510 MPa using an ASTM E8 longitudinal test specimen.
  • ASTM G47 covers the test method of sampling, type of specimen, specimen preparation, test environment, and method of exposure for determining the susceptibility to SCC of aluminum alloys.
  • ASTM E8 covers the testing apparatus, test specimens, and testing procedure for tensile testing.
  • a melt for alloy A was prepared by heating a charge of starting materials, the charge having the nominal composition of 6.3 Zn, 2.7 Mg, 1.6 Cu, 0.10 Sc, 0.05 Zr, and balance Al, in wt%.
  • the alloy includes a variance in the constituents in the range of plus or minus ten percent of the nominal (mean) value.
  • the melt weighed about 450 grams.
  • the alloy was homogenized by heating it from room temperature to 460°C at 1°C per minute and holding it at 460°C for 8 hours.
  • the homogenized alloy was press-forged down to 50% reduction in height, to about 5 cm in short-transverse thickness. Specimens were excised in the short-transverse direction to measure the fracture toughness, K Ic , and the SCC resistance, Kiscc-
  • a melt for alloy B was prepared by heating a charge of starting materials, the charge having the nominal composition of 6.5 Zn, 1.5 Mg, 1.6 Cu, 0.50 Ag, 0.10 Sc, 0.05 Zr, and balance Al, in wt%. The melt weighed about 450 grams. Alloy B is a counterexample. Although alloy B includes Zn and Cu in amounts similar to alloy A, the lower Mg content raises the SCC index, undesirably lowering Kiscc- A comparison of the properties of alloy B and 7050 is shown in Table 1. Table 1 also indicates the SCC Index of the alloy, calculated using equation [1] above. The alloy 7050 was subjected to a heat treatment identical to alloy B, which was also identical to the heat treatment and processing described above with respect to alloy A (EXAMPLE 1). The tensile strength was also measured, and the results are listed in Table 2.
  • a melt for alloy C was prepared by heating a charge of starting materials, the charge having the nominal composition of 5.8 Zn, 3.0 Mg, 2.2 Cu, 0.05 Sc, 0.05 Zr, and balance Al, in wt%.
  • the alloy C includes a variance in the constituents in the range of plus or minus ten percent of the nominal (mean) value.
  • the melt weighed about 450 grams.
  • the alloy was homogenized by heating it from room temperature to 460°C at 1°C per minute and holding it at 460°C for 8 hours. The homogenized alloy was press-forged down to 50% reduction in height, to about 4 cm in short-transverse thickness.
  • the alloys according to the disclosed aspects and embodiments produce physical properties that are comparable or superior to those of alloy 7050, and in particular, the alloys A and C have a lower SCC Index compared to alloy 7050, which indicates a superior resistance to SCC.
  • the hardness is superior to that of alloy 7050, and the SCC resistance is also superior to alloy 7050.
  • the fracture toughness (K Ic ) yield stress, ultimate tensile stress, and ductility are all comparable to those of alloy 7050.
  • alloy C the hardness, yield stress, ultimate tensile stress, and SCC resistance are superior to those of alloy 7050, and the ductility is comparable.
  • the fracture toughness (Ki c ) of alloy C was found to be slightly lower than that of alloy 7050. It is noted that the Kiscc of alloys A and C are very close to the theoretical limit (i.e. the Ki c value).
  • a melt was prepared by heating a charge of starting materials, the charge having the nominal composition of 6.3 Zn, 2.7 Mg, 1.6 Cu, 0.12 Zr, and balance Al, in wt%, which is the same as alloy A.
  • the as-cast alloy A-l was generally shaped like a cylinder, measuring about 18 cm in diameter and 56 cm in height, and weighing about 50 kg. After being cooled to room temperature, the as-cast alloy A-l was homogenized by heating it in a furnace from room temperature to 400° C at 1°C per minute, holding it at 400°C for 12 hours, heating it from 400°C at 1°C per minute, and holding it at 460°C-480°C for 24-48 hours.
  • the homogenized alloy A-l was extruded to a cylindrical billet, reducing the diameter to about 8 cm in diameter. This represents an extrusion ratio of about 51 ⁇ 2: 1.
  • Specimens were excised and subjected first to a solution heat-treatment ("SHT"), and then to an aging heat-treatment.
  • SHT solution heat-treatment
  • the solution heat-treatment was conducted by subjecting the specimens to a temperature of 460°C or 465°C for 2 hours.
  • the SCC resistance was measured according to a rising step load (RSL) method developed by Lou Raymond & Associates in Newport Beach, CA, generally as follows. Machined notched samples in the fully heat-treated condition were used for the testing. Initial fracture toughness (K lc ) testing was performed in air at a rapid loading rate to first determine the maximum breaking load. The test specimen geometry was changed to increase the amount of constraint. An effective stress intensity K p was calculated, since the specimen had a machined notch instead of a fatigue pre-crack as required by ASTM E399. Previous testing of 7075-T6 aluminum alloy in a similar way found that the value for K p was approximately 1.5 times the value for K lc .
  • RSL rising step load
  • the RSL method was employed to measure the Kiscc of the samples.
  • the aluminum specimens were anodically charged by coupling them to PH17-4 adapters in a 3.5% salt-water environment.
  • Alloy A-l showed a K lc value of 38.8 ksi-in 1 ⁇ 2 and a Kiscc value greater than 38 ksi-in 1 ⁇ 2 .
  • a melt for alloy D was prepared by heating a charge of starting materials, the charge having the nominal composition of 6.3 Zn, 2.7 Mg, 1.6 Cu, 0.12 Zr, and balance Al, in wt%.
  • the alloy D preferably includes a variance in the constituents in the range of plus or minus ten percent of the nominal (mean) value, and is substantially free of scandium.
  • the as-cast alloy D was generally shaped like a cylinder, measuring about 18 cm in diameter and 56 cm in height, and weighing about 50 kg.
  • the as-cast alloy D was homogenized by heating it from room temperature to 400°C at 1°C per minute, holding it at 400°C for 12 hours, heating it from 400°C at 1°C per minute, and holding it at 460°C-480°C for 24-48 hours.
  • the homogenized alloy D was extruded to a cylindrical billet, reducing the diameter to about 8 cm in diameter. This represents an extrusion ratio of about 51 ⁇ 2: 1.
  • Specimens were excised and subjected first to a solution heat-treatment, and then to an aging heat-treatment.
  • the solution heat-treatment was conducted by subjecting the specimens to a temperature of 460°C, 465°C, or 470°C for 2 hours.
  • Alloy D has about 20% higher YS than 7050-T74 in the longitudinal direction and about 13% to about 15% higher YS than 7050-T74 in the transverse and 45° direction, with comparable elongations and %RA.
  • the strength values of alloy D represent a significant improvement over 7050-T74.
  • the SCC threshold stress of alloy D was measured by a 30-day accelerated stress corrosion testing according to ASTM G47. Short-transverse samples of alloy D were solution heat-treated at 460°C for 2 hours, and heat-treated according to the T7x heat treatment. Fig. 1 shows the SCC threshold stress and typical longitudinal yield strength of alloy D in comparison to conventional aluminum alloys. The samples of alloy D passed a stress level of about 380 MPa, which is above the highest SCC temper designation currently in use, namely, T73. Thus, the combination of strength and SCC resistance of alloy D is substantially improved over that of conventional aluminum alloys.
  • the SCC resistance was measured according to the RSL method. Machined notched samples in the fully heat-treated condition were used for the testing. Ki c testing was performed in air at a rapid loading rate to first determine the maximum breaking load. The test specimen geometry was changed to increase the amount of constraint. An effective stress intensity K p was calculated. Having measured the maximum breaking load, the RSL method was employed to measure the Kiscc of the samples. During the SCC test, the aluminum specimens were anodically charged by coupling them to PHI 7-4 adapters in a 3.5% salt-water environment.
  • Alloy D specimens that were solution heat-treated at 460°C for 2 hours and heat-treated according to the T7x heat treatment showed a Ki c value of 47.8 ksi-in 1 ⁇ 2 and a Kiscc value of 20.0 ksi-in 1 ⁇ 2 .
  • alloy D specimens solution heat-treated at 470°C for 2 hours and heat-treated according to the T7x heat treatment showed a K lc value of 55.4 ksi-in 1 ⁇ 2 and a Kiscc value of 15.0 ksi-in 1/2 .

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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)
  • Extrusion Of Metal (AREA)
  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Investigating And Analyzing Materials By Characteristic Methods (AREA)
  • Forging (AREA)
  • Conductive Materials (AREA)

Abstract

La présente invention concerne un alliage contenant, en poids, environ 5,8 % à environ 6,8 % de zinc, environ 2,5 % à environ 3,0 % de magnésium, environ 1,5 % à environ 2,3 % de cuivre, 0 % à environ 0,2 % de scandium, 0 % à environ 0,2 % de zirconium et éventuellement moins d'environ 0,50 % d'argent, le reste étant essentiellement constitué d'aluminium, d'éléments non désirés et d'impuretés. Dans certains modes de réalisation, l'alliage présente une contrainte seuil de fissuration par corrosion sous contrainte d'au moins 240 MPa environ en utilisant une éprouvette d'essai en travers court ASTM G47 et une limite d'élasticité d'au moins 510 MPa environ en utilisant une éprouvette d'essai en direction longitudinale ASTM E8.
EP12789530.8A 2011-05-21 2012-05-21 Alliages d'aluminium Withdrawn EP2714954A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201161488713P 2011-05-21 2011-05-21
PCT/US2012/038796 WO2012162226A2 (fr) 2011-05-21 2012-05-21 Alliages d'aluminium

Publications (2)

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EP2714954A2 true EP2714954A2 (fr) 2014-04-09
EP2714954A4 EP2714954A4 (fr) 2015-08-19

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US (1) US20120291926A1 (fr)
EP (1) EP2714954A4 (fr)
CA (1) CA2836261A1 (fr)
WO (1) WO2012162226A2 (fr)

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US9218316B2 (en) 2011-01-05 2015-12-22 Sphero, Inc. Remotely controlling a self-propelled device in a virtualized environment
US9150263B2 (en) 2011-01-05 2015-10-06 Sphero, Inc. Self-propelled device implementing three-dimensional control
US9429940B2 (en) 2011-01-05 2016-08-30 Sphero, Inc. Self propelled device with magnetic coupling
US10281915B2 (en) 2011-01-05 2019-05-07 Sphero, Inc. Multi-purposed self-propelled device
AU2012362827B2 (en) 2011-12-30 2016-12-22 Scoperta, Inc. Coating compositions
US9292758B2 (en) 2012-05-14 2016-03-22 Sphero, Inc. Augmentation of elements in data content
JP2015524951A (ja) 2012-05-14 2015-08-27 オルボティックス, インコーポレイテッドOrbotix, Inc. 画像内で丸い物体を検出することによるコンピューティングデバイスの操作
US9827487B2 (en) 2012-05-14 2017-11-28 Sphero, Inc. Interactive augmented reality using a self-propelled device
US10056791B2 (en) 2012-07-13 2018-08-21 Sphero, Inc. Self-optimizing power transfer
US9829882B2 (en) 2013-12-20 2017-11-28 Sphero, Inc. Self-propelled device with center of mass drive system
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Publication number Publication date
CA2836261A1 (fr) 2012-11-29
WO2012162226A3 (fr) 2014-05-08
WO2012162226A2 (fr) 2012-11-29
EP2714954A4 (fr) 2015-08-19
US20120291926A1 (en) 2012-11-22

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