US20060157172A1 - Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product therefrom - Google Patents

Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product therefrom Download PDF

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US20060157172A1
US20060157172A1 US11/334,813 US33481306A US2006157172A1 US 20060157172 A1 US20060157172 A1 US 20060157172A1 US 33481306 A US33481306 A US 33481306A US 2006157172 A1 US2006157172 A1 US 2006157172A1
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semi
aluminum alloy
finished product
copper
alloy
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Gernot Fischer
Gregor Terlinde
Matthias Hilpert
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Otto Fuchs KG
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Otto Fuchs KG
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Assigned to OTTO FUCHS KG reassignment OTTO FUCHS KG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FISCHER, GERNOT, HILPERT, MATTHIAS, TERLINDE, GREGOR
Publication of US20060157172A1 publication Critical patent/US20060157172A1/en
Priority to US12/859,757 priority Critical patent/US20110008202A1/en
Priority to US13/136,301 priority patent/US20120202086A1/en
Priority to US14/101,036 priority patent/US20140099230A1/en
Priority to US14/861,853 priority patent/US10301710B2/en
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    • 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
    • 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
    • C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
    • 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
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals

Definitions

  • the invention relates to an aluminum alloy that is not sensitive to quenching, and which is used for the production of high-strength forged pieces low in inherent tension, and high-strength extruded and rolled products. Furthermore, the invention relates to a method for the production of a semi-finished product from such an aluminum alloy.
  • High-strength aluminum alloys are needed for the aeronautics and space industry, in particular, bearing hull, wing, and chassis parts which demonstrate high strength both under static stress and under dynamic stress.
  • the required strength properties can be achieved, in the case of the aforementioned semi-finished products, by using alloys from the 7000 group (7xxx alloys), in accordance with the classification of aluminum alloys prepared by the Aluminum Association (AA).
  • Die-forged pieces for parts that are subject to great stress in the aeronautics and space industry for example, parts made from the alloys AA 7075, AA 7175, AA 7475 and, particularly preferably, from the alloys AA 7049 and AA 7050, in America, and made from the alloys AA 7010, AA 7049A, and AA 7050A in Europe.
  • a high-strength aluminum alloy of the aforementioned type is known from WO 02/052053 A1, or U.S. Pat. No. 6,972,110 issued on Dec. 6, 2005 to Chakrabarti et al., the disclosure of which is hereby incorporated herein by reference. That reference discloses an alloy having an increased zinc content as compared with earlier alloys of the same type, coupled with a reduced copper and magnesium content.
  • the copper and magnesium content in the case of this previously known alloy amounts to less than 3.5%, in total.
  • the copper content itself is indicated as being 1.2-2.2 wt.-%, preferably 1.6-2.2 wt.-%.
  • this previously known alloy necessarily contains one or more elements from the group zirconium, scandium, and hafnium, with maximum proportions of 0.4 wt.-% zirconium, 0,4 wt.-% scandium, and 0.3 wt.-% hafnium.
  • the semi-finished products should be subjected to a special heat treatment to produce the semi-finished products from one of the aforementioned alloys.
  • These products can be in the form of forged pieces, wherein with this heat treatment, the extruded profiles, or the rolled sheets are treated to have the desired strength.
  • This treatment includes quenching from solution heat temperature, in most cases combined with subsequent cold forming at medium thickness values of more than 50 mm.
  • the cold forming serves to reduce the tensions induced during quenching.
  • the step of cold forming can occur by means of cold upsetting or also by means of stretching the semi-finished product, typically by 1-3%.
  • the semi-finished products produced should be as low in inherent tension as possible, to minimize any undesirable drawing during further processing.
  • the semi-finished products and also the finished parts produced from them should be low in inherent tension, to give the designer the possibility of utilizing the entire material potential.
  • the method steps to be used for the production of parts for aeronautics and space technology from the alloys AA 7050 as well as AA 7010, and also the maximum thickness of the semi-finished products used for the production of the parts are standardized and/or prescribed.
  • the maximal permissible thickness is 200 mm and presupposes that after quenching, the semi-finished product is necessarily subjected to a cold forming step, for the reasons indicated above. With extruded and rolled products, cold forming can be achieved in a fairly simple manner, because of the geometry, which is generally simple, via stretching in the longitudinal direction.
  • the invention relates to a high-strength aluminum alloy that is not sensitive to quenching, having the same or better strength properties as the alloys AA 7010 and AA 7050 which, at the same time, has lower inherent tensions due to quenching after cold forming, and from which semi-finished products having a medium thickness can be produced having great strength and fracture resistance, without the need for a cold forming step to reduce inherent tensions induced by quenching.
  • the invention further relates to a method for the production of a semi-finished product having the desired properties from this alloy.
  • a high-strength aluminum alloy that is not sensitive to quenching comprises an alloy consisting of: 7.0-10.5 wt. % zinc, 1.0-2.5 wt. % magnesium, 0.1-1.15 wt. % copper, 0.06-0.25 wt. % zirconium, 0.02-0.15 wt. % titanium, at most 0.5 wt. % manganese, at most 0.6 wt. % silver, at most 0.10 wt. % silicon, at most 0.10 wt. % iron, at most 0.04 wt.
  • % chrome and at least one element selected from the group consisting of: hafnium, scandium, strontium and/or vanadium with a summary content of at most 1.0 wt. %.
  • the alloy can also contain contaminants at proportions of at most 0.05 wt. % per element and a total proportion of at most 0.15 wt. %, wherein the remaining component includes aluminum.
  • the sum of the alloy elements zinc and magnesium and copper is at least 9 wt. %.
  • the invention can also relate to a process for treating the above alloy. That process can include a series of steps including hot forming a plurality of homogenized bars via forging, extrusion and/or rolling in the temperature range of 350-440° C. Next there can be a step of solution heat treating of a hot-formed semi-finished product at temperatures that are sufficiently high to bring the alloy elements necessary for hardening into solution uniformly distributed in the structure, preferably at 465-500° C. Next, there can be the step of quenching of the solution heat treated semi-finished products in water, in a water/glycol mixture, or in a salt mixture at temperatures between 100° C. and 170° C.
  • Step of cold forming of the quenched semi-finished product to reduce the inherent tensions that occurred during quenching in the quenching medium.
  • step of artificial aging of the quenched semi-finished product in at least one stage, whereby the heating rates, holding times, and temperatures are adjusted for optimization of the properties.
  • Semi-finished products having a medium thickness have temper hardening thickness values of 50-180 mm.
  • Semi-finished products having a greater thickness have a temper hardening thickness of >180 mm.
  • semi-finished products produced from the alloy can be mildly cooled, for example in a glycol/water mixture, without any noteworthy negative influence on the very good material properties, after subsequent warm settling. For this reason, the step of cold forming is not necessary for medium thickness values, since the inherent stresses induced with the mild cooling are non-critically low. Therefore it is possible to produce semi-finished products in the medium thickness range with this alloy, in a simple and inexpensive manner, namely without a cold-forming step that would otherwise be necessary.
  • the advantageous properties of the alloy as described above can also be utilized to simplify the production process of a part for the production of which a semi-finished product having a greater starting thickness is required, and which part has a medium thickness after being processed.
  • a semi-finished product having a greater thickness for example a forged one, is pre-processed by cutting, after the step of hot forming.
  • the pre-processing is designed so that the semi-finished product, which will then be quenched within the course of hot forming, undergoes a reduction in thickness.
  • This reduction in thickness is necessary for the production of the finished part, in any case, wherein the pre-processed semi-finished product can be subjected to heat treatment with mild quenching (glycol/water mixture), without performing a cold forming step that is otherwise necessary for greater thickness values.
  • mild quenching glycol/water mixture
  • semi-finished products having a medium thickness can therefore be quenched in mild manner, by means of glycol/water mixtures.
  • semi-finished products having a greater thickness such mild quenching is not practical because of the minimum cooling speed that is required. Accordingly, semi-finished products having a greater thickness are quenched in water. As a result of this, these semi-finished products are subsequently subjected to cold forming, for example upsetting or stretching by 1-5%.
  • the aforementioned properties of the semi-finished product produced from this alloy are unexpected, since contrary to the default values that result from the state of the art, the copper content is clearly lower than was the case for previously known high-strength aluminum alloys.
  • the copper content is only 0.8-1.1 wt. %.
  • the copper content is only about 50% of the preferred copper content of the aluminum alloys known from WO 02/052053 A1 or U.S. Pat. No. 6,972,110. It is surprising that very high strength values are achieved despite this. It is assumed that these properties are based on the balanced composition of the alloy components, which also includes the relative high zinc content values and the magnesium content that is adapted to this.
  • the sum of the elements magnesium, copper, and zinc are at least 9 wt. %. It has been shown that the desired strength properties can only be achieved if the elements magnesium, copper, and zinc in total are more than 9 wt. %. This characteristic of the alloy is a measure of the fact that the products have the desired strength properties. This rule also determines the heat treatability of the semi-finished products produced with the alloy.
  • the content will be limited to 0.2-0.7 wt. %, particularly to 0.20-0.40 wt. %.
  • the manganese content of the alloy was limited to a maximum 0.5 wt. %.
  • the ability to through-harden an Al—Zn—Cu—Mg alloy decreases with an increasing manganese content. For this reason, the manganese content is limited.
  • zirconium The reduced effect of the manganese with regard to controlling the structure is balanced out by means of adding zirconium. According to a preferred exemplary embodiment, the latter amounts to 0.14-0.20 wt. %.
  • Zirconium also precipitates from the structure during homogenization of the extruded bars, in the form of zirconium aluminides. These aluminides are generally configured to be more micro-dispersed than the manganese aluminides. For this reason, they are particularly helpful with regard to controlling recrystallization.
  • the zirconium aluminides that are formed are not made more coarse by the heat treatment that is provided, and are stable in the selected temperature ranges, in contrast to manganese aluminides. For this reason, zirconium is a necessary component of the alloy.
  • the titanium contained in the alloy primarily serves for making the grain fine during extrusion molding.
  • a value of 0.03-0.1 wt. % titanium is preferred, particularly 0.03-0.06 wt. % titanium added to the alloy.
  • the desired properties are achieved if the alloy components are used in the proportions of the range indicated.
  • Semi-finished products having the required properties can no longer be produced with an alloy in which one or more alloy components have a proportion that lies outside the range indicated.
  • the semi-finished products are produced from this alloy with the following steps:
  • Solution heat treating of the hot-formed semi-finished product at temperatures that are sufficiently high to bring the alloy elements necessary for hardening into solution uniformly distributed in the structure, preferably at 465-500° C.; Quenching of the solution heat treated semi-finished products in water, at a temperature between room temperature and 100° C., or in a water/glycol mixture, or in a salt mixture at temperatures between 100° C. and 170° C.; and
  • the artificial aging of the quenched semi-finished product occurs in two stages.
  • the semi-finished product is heated to a temperature of more than 100° C. and held at this temperature for more than eight hours, and in the second stage, it is heated to more than 130° C. and heated for more than five hours.
  • These two stages can be performed directly following one another.
  • the semi-finished product treated with the first stage can also cool off, and the second stage of artificial aging can be performed at a later point in time, without having to accept any disadvantages with regard to the desired properties of the semi-finished product.
  • FIG. 1 is a graph representing the strength behavior of various AA 7xxx alloys as a function of the average cooling speed during quenching from solution heat treatment temperature
  • FIG. 2 is a flow chart for a process for producing the alloy.
  • the two alloys Z1, Z2 have the following composition: Si Fe Cu Mn Mg Cr Zn Ti Zr Ti + Zr Alloy Z1 0.05 0.05 0.95 0.39 1.70 0.002 8.35 0.035 0.12 0.155 Alloy Z2 0.04 0.07 0.90 0.004 1.65 0.001 8.50 0.025 0.12 0.145
  • the alloys Z1, Z2 were cast to produce extrusion blocks having a diameter of 370 mm, on an industrial scale.
  • the extrusion blocks were homogenized to balance out the micro-segregation resulting from solidification.
  • the blocks were homogenized in two stages, in a temperature range of 465° C.-485° C., and cooled.
  • the homogenized blocks were pre-heated to 370° C. and formed multiple times to produce free-form forged pieces having a thickness of 250 mm and to a width of 500 mm.
  • the free-form forged pieces of alloy Z1 and Z2 were solution heat treated at 485° C. for at least 4 hours, quenched in water at room temperature, and subsequently artificially aged between 100° C. and 160° C., wherein the artificial aging was carried out in two stages.
  • the semi-finished product was heated to more than 100° C. and held at this temperature for more than eight hours.
  • the second stage which was carried out immediately after the first stage, took place at a temperature of more than 130° C. for more than five hours.
  • the results show that the R p02 and R m values are almost identical for all three stress directions, and lie above 490 MPa for the stretching limit (R p02 ) and above 520 MPa for tensile strength.
  • the A 5 values are highest for the L direction, and reach at least 4% breaking elongation (A 5 ) for the two transverse directions.
  • the K IC values are listed as follows: Alloy Test Direction Position K IC (MPa ⁇ m) R p0.2 (MPa) Z1 L-T Edge 30.5 529 L-T Core 32.9 504 T-L Edge 23.1 516 T-L Core 20.4 502 Z2 L-T Edge 30.3 514 L-T Core 35.9 520 T-L Edge 23.6 514 T-L Core 21.8 508
  • the stress crack corrosion resistance was determined on round samples for the LT and the ST position, according to ASTM G47 (alternating immersion test). The results are listed below for the alloy Z1: Electrical Stress Direction Stress Mpa Duration (Days) Conductivity LT 320 >30 34.7 ST 320 >30 34.7
  • forged pieces having the same parameters were produced from the alloy Z1.
  • the forged pieces were cold-upset in the short transverse direction (ST) after solution heat treatment and quenching, to reduce the inherent stresses resulting from quenching.
  • ST short transverse direction
  • the strength properties were determined at room temperature, in the sample positions “long” (L), “long-transverse” (LT), and “short-transverse” (ST).
  • the results show that the R p02 and R m values for all three stress directions are less, and that the lowest value was found for the short-transverse direction (ST).
  • the A 5 values are highest for the L direction, and reach-at least 6% breaking elongation (A 5 ) for the two-transverse directions.
  • the decrease in strength can be reduced by shortening the second hardening stage.
  • the K IC values are listed in the following table: Alloy Test Direction Position K IC (MPa ⁇ m) R p0.2 (MPa) Z1 L-T Edge 30.5 529 L-T Core 32.9 504 T-L Edge 23.1 516 T-L Core 20.4 502 Z1 + Cold L-T Edge 38.9 485 Upsetting L-T Core 42.2 448 T-L Edge 23.9 474 T-L Core 21.9 468
  • free-form forged pieces having a thickness of 150 mm and a width of 500 mm were produced from alloy Z1 and, after solution heat treatment, were quenched in water or a water/glycol mixture with approximately 20% and approximately 40%, respectively, and warm settled as described above.
  • One forged piece was additionally cold upset after being quenched in water.
  • the influence of the various cooling media was determined on drawn samples that were taken from the forged pieces in the directions “long” (L), “long-transverse” (LT), and “short-transverse” (ST).
  • the average strength properties of the alloy for a thickness of 150 mm for various cooling treatments are shown as follows: Quenching R p0.2 R m A 5 Medium Stress Direction (MPa) (MPa) (%) Water(RT) L 551 573 10.3 LT 515 544 7.5 ST 505 549 8.0 Water (RT) + L 491 537 12.8 Cold upsetting LT 465 520 8.7 ST 430 513 8.5 Water/Glycol L 545 566 12.5 (16-20%) LT 520 547 7.2 ST 512 548 8.3 Water/Glycol L 503 529 12.2 (38-40%) LT 493 525 5.0 ST 487 526 5.6
  • the K IC values are contained in the following table: Quenching Medium Test Direction K IC (MPa ⁇ m) R p.02 Water (RT) L-T 36.8 551 T-L 23.8 515 Water (RT) + Cold L-T 39.1 491 Upsetting T-L 24.1 465 Water/glycol L-T 28.2 545 (16-20%) T-L 20.7 520 Water/glycol L-T 35.4 503 (38-40%) T-L 18.5 493
  • the alloy Z1 was also cast in another example, analogous to the first example, and blocks for extrusion were produced.
  • the homogenized blocks were pre-heated to over 370° C. and pressed into extrusion profiles having a rectangular cross-section, with a thickness of 40 mm and a width of 100 mm.
  • the profiles were solution heat treated for at least 4 hours at 485° C., quenched in water at room temperature, and subsequently artificially aged between 100° C. and 160° C., in two stages (first stage: >100° C., >8 h; second stage: >130° C., >5 h).
  • the results show that the R p02 and R m values are highest in the L direction, at values of 600 MPa and 609 MPa, respectively, and lowest in the ST direction, at values of 505 MPa and 561 MPa, respectively.
  • the A 5 values are highest for the L direction, and reach at least 7% breaking elongation (A 5 ) for the two transverse directions.
  • FIG. 1 shows a diagram representing the strength behavior of various AA 7xxx alloys as a function of the average cooling speed during quenching from solution heat treatment temperature. It is clearly evident in this representation that the loss in strength when using the claimed aluminum alloy is significantly less, even at low cooling speeds, than in the case of the comparison alloys AA 7075, AA 7010, and AA 7050.
  • the strength values of the products/semi-finished products produced with the claimed alloy are significantly improved, in particular with regard to stress crack corrosion resistance, as compared with products of previously known alloys, which represents a result that was not foreseeable in the form that occurred.
  • the results shown are also interesting in that the strength values described can be particularly presented with artificial aging that is carried out in only two stages.
  • FIG. 2 shows a flow chart for a process for producing the alloy.
  • step 1 comprises providing the alloy which is disclosed in the above examples.
  • step 2 the alloy is hot formed as described above, and in step 3 , the alloy is solution heat treated as described above.
  • step 4 the alloy is quenched, while in step 5 , the alloy is optionally cold formed, while in step 6 , the alloy is artificially aged as described above.

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US11/334,813 2005-01-19 2006-01-18 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product therefrom Abandoned US20060157172A1 (en)

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US12/859,757 US20110008202A1 (en) 2005-01-19 2010-08-19 Alluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US13/136,301 US20120202086A1 (en) 2005-01-19 2011-07-28 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US14/101,036 US20140099230A1 (en) 2005-01-19 2013-12-09 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US14/861,853 US10301710B2 (en) 2005-01-19 2015-09-22 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product

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DE102005002390.8 2005-01-19

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US12/859,757 Abandoned US20110008202A1 (en) 2005-01-19 2010-08-19 Alluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US13/136,301 Abandoned US20120202086A1 (en) 2005-01-19 2011-07-28 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US14/101,036 Abandoned US20140099230A1 (en) 2005-01-19 2013-12-09 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US14/861,853 Expired - Fee Related US10301710B2 (en) 2005-01-19 2015-09-22 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product

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US14/101,036 Abandoned US20140099230A1 (en) 2005-01-19 2013-12-09 Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
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* Cited by examiner, † Cited by third party
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US20040211498A1 (en) * 2003-03-17 2004-10-28 Keidel Christian Joachim Method for producing an integrated monolithic aluminum structure and aluminum product machined from that structure
US20080283163A1 (en) * 2007-05-14 2008-11-20 Bray Gary H Aluminum Alloy Products Having Improved Property Combinations and Method for Artificially Aging Same
US20080299000A1 (en) * 2002-09-21 2008-12-04 Universal Alloy Corporation Aluminum-zinc-copper-magnesium-silver alloy wrought product
CN101818290A (zh) * 2010-05-28 2010-09-01 中南大学 一种同时添加Ag、Ge的低淬火敏感性铝合金
US20110008202A1 (en) * 2005-01-19 2011-01-13 Otto Fuchs Kg Alluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
AU2011226794B2 (en) * 2010-09-08 2012-04-05 Arconic Inc. Improved 7xxx aluminum alloys, and methods for producing the same
CN103131992A (zh) * 2011-11-29 2013-06-05 贵州铝厂 一种低锌热浸镀铝合金镀层材料
CN103732772A (zh) * 2011-11-07 2014-04-16 株式会社Uacj 高强度铝合金材料及其制造方法
CN104073698A (zh) * 2014-06-26 2014-10-01 龙口市丛林铝材有限公司 一种6系轨道车辆悬挂臂铝型材及其制备方法
US9163304B2 (en) 2010-04-20 2015-10-20 Alcoa Inc. High strength forged aluminum alloy products
US9347558B2 (en) 2010-08-25 2016-05-24 Spirit Aerosystems, Inc. Wrought and cast aluminum alloy with improved resistance to mechanical property degradation
US9353431B2 (en) 2011-06-23 2016-05-31 Uacj Corporation High-strength aluminum alloy material and process for producing the same
EP2942412B1 (en) 2014-05-06 2016-11-16 Goodrich Corporation Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver
US9587298B2 (en) 2013-02-19 2017-03-07 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
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US9926620B2 (en) 2012-03-07 2018-03-27 Arconic Inc. 2xxx aluminum alloys, and methods for producing the same
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US10208370B2 (en) 2014-01-29 2019-02-19 Uacj Corporation High-strength aluminum alloy and manufacturing method thereof
US10266933B2 (en) 2012-08-27 2019-04-23 Spirit Aerosystems, Inc. Aluminum-copper alloys with improved strength
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Citations (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3743549A (en) * 1971-02-09 1973-07-03 I Esercizio Dell Istituto Sper Thermomechanical process for improving the toughness of the high strength aluminum alloys
US3794531A (en) * 1970-10-23 1974-02-26 Fuchs O Fa Method of using a highly stable aluminum alloy in the production of recrystallization hardened products
US3943039A (en) * 1974-10-08 1976-03-09 Kaiser Aluminum & Chemical Corporation Anodizing pretreatment for nickel plating
US3945861A (en) * 1975-04-21 1976-03-23 Aluminum Company Of America High strength automobile bumper alloy
US4049474A (en) * 1975-07-25 1977-09-20 Evegny Dmitrievich Zakharov Aluminum-based alloy
US4063936A (en) * 1974-01-14 1977-12-20 Alloy Trading Co., Ltd. Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack
US4629517A (en) * 1982-12-27 1986-12-16 Aluminum Company Of America High strength and corrosion resistant aluminum article and method
US4828631A (en) * 1981-12-23 1989-05-09 Aluminum Company Of America High strength aluminum alloy resistant to exfoliation and method of making
US4830826A (en) * 1986-09-26 1989-05-16 Matsuo Kogyo Kabushiki Kaisha Process of manufacturing high-strength high-elasticity aluminum alloys
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
US4954188A (en) * 1981-12-23 1990-09-04 Aluminum Company Of America High strength aluminum alloy resistant to exfoliation and method of making
US5055257A (en) * 1986-03-20 1991-10-08 Aluminum Company Of America Superplastic aluminum products and alloys
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
US5277719A (en) * 1991-04-18 1994-01-11 Aluminum Company Of America Aluminum alloy thick plate product and method
US5312498A (en) * 1992-08-13 1994-05-17 Reynolds Metals Company Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness
US5560789A (en) * 1994-03-02 1996-10-01 Pechiney Recherche 7000 Alloy having high mechanical strength and a process for obtaining it
US5620652A (en) * 1994-05-25 1997-04-15 Ashurst Technology Corporation (Ireland) Limited Aluminum alloys containing scandium with zirconium additions
US6027582A (en) * 1996-01-25 2000-02-22 Pechiney Rhenalu Thick alZnMgCu alloy products with improved properties
US6048415A (en) * 1997-04-18 2000-04-11 Kabushiki Kaisha Kobe Seiko Sho High strength heat treatable 7000 series aluminum alloy of excellent corrosion resistance and a method of producing thereof
US20020150498A1 (en) * 2001-01-31 2002-10-17 Chakrabarti Dhruba J. Aluminum alloy having superior strength-toughness combinations in thick gauges
US20020162609A1 (en) * 2001-02-07 2002-11-07 Timothy Warner Manufacturing process for a high strength work hardened product made of AlZnMgCu alloy
US6565684B2 (en) * 2000-02-23 2003-05-20 Societe Metallurgique De Gerzat Manufacturing process for a hollow pressure vessel made of AlZnMgCu alloy
US20030213537A1 (en) * 2001-02-28 2003-11-20 Alex Cho Aluminum alloys
US20030219353A1 (en) * 2002-04-05 2003-11-27 Timothy Warner Al-Zn-Mg-Cu alloys and products with improved ratio of static mechanical characteristics to damage tolerance
US6726878B1 (en) * 1999-10-05 2004-04-27 Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie “Vserossiisky Nauchno-Issle-Dovatelsky Institut Aviatsionnykh Materialov” High strength aluminum based alloy and the article made thereof
US20040099352A1 (en) * 2002-09-21 2004-05-27 Iulian Gheorghe Aluminum-zinc-magnesium-copper alloy extrusion
US6743308B2 (en) * 2001-02-16 2004-06-01 Kabushiki Kaisha Kobe Seiko Sho. Aluminum alloy structural plate excelling in strength and corrosion resistance and method of manufacturing same
US20040136862A1 (en) * 2002-11-15 2004-07-15 Bray Gary H. Aluminum alloy product having improved combinations of properties
US6790407B2 (en) * 2000-08-01 2004-09-14 Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie “Vserossiisky auchno-Issledovatelsky Institut Aviatsionnykh Materialov” High-strength alloy based on aluminium and a product made of said alloy
US20050000610A1 (en) * 2001-10-24 2005-01-06 Gerhard Huber Production of water-free nitrocellulose and explosive substances that have a spheroidal shape
US20050023075A1 (en) * 2003-07-30 2005-02-03 Schmaeman Dale E. Reduced noise valve stack connection
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
US20050058568A1 (en) * 2003-06-24 2005-03-17 Pechiney Rhenalu Products made of Al-Zn-Mg-Cu alloys with an improved compromise between static mechanical characteristics and damage tolerance
US20050056353A1 (en) * 2003-04-23 2005-03-17 Brooks Charles E. High strength aluminum alloys and process for making the same
US20050072497A1 (en) * 2002-04-05 2005-04-07 Frank Eberl Al-Zn-Mg-Cu alloys and products with high mechanical characteristics and structural members suitable for aeronautical construction made thereof
US20050150579A1 (en) * 2000-12-21 2005-07-14 Chakrabarti Dhruba J. Aluminum alloy products having improved property combinations and method for artificially aging same
US20050150578A1 (en) * 2003-12-16 2005-07-14 Pechiney Rhenalu Metallurgical product and structure member for aircraft made of Al-Zn-Cu-Mg alloy
US20050189044A1 (en) * 2003-04-10 2005-09-01 Rinze Benedictus Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US20050238528A1 (en) * 2004-04-22 2005-10-27 Lin Jen C Heat treatable Al-Zn-Mg-Cu alloy for aerospace and automotive castings
US20080056932A1 (en) * 2006-06-30 2008-03-06 Alex Cho High Strength, Heat Treatable Aluminum Alloy

Family Cites Families (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4305763A (en) 1978-09-29 1981-12-15 The Boeing Company Method of producing an aluminum alloy product
FR2457908A1 (fr) 1979-06-01 1980-12-26 Gerzat Metallurg Procede de fabrication de corps creux en alliage d'aluminium et produits ainsi obtenus
FR2517702B1 (es) 1981-12-03 1985-11-15 Gerzat Metallurg
GB2114601B (en) 1981-12-23 1986-05-08 Aluminum Co Of America High strength aluminum alloy resistant to exfoliation and method of heat treatment
JPS58161747A (ja) † 1982-03-19 1983-09-26 Kobe Steel Ltd フラツシユバツト溶接部の耐応力腐蝕割れ性に優れた高強度アルミニウム合金
US4713216A (en) 1985-04-27 1987-12-15 Showa Aluminum Kabushiki Kaisha Aluminum alloys having high strength and resistance to stress and corrosion
AT384744B (de) 1986-02-07 1987-12-28 Austria Metall Verwendung einer legierung auf ein band aus a1 zn mg cu-legierungen fuer schwingend beanspruchte sportgeraete
FR2601967B1 (fr) 1986-07-24 1992-04-03 Cerzat Ste Metallurg Alliage a base d'al pour corps creux sous pression.
DE68927149T2 (de) 1988-10-12 1997-04-03 Aluminum Co Of America Verfahren zur Herstellung eines nichtkristallisierten, flachgewalzten, dünnen, wärmebehandelten Produktes auf Aluminiumbasis
FR2640644B1 (fr) 1988-12-19 1991-02-01 Pechiney Recherche Procede d'obtention par " pulverisation-depot " d'alliages d'al de la serie 7000 et de materiaux composites a renforts discontinus ayant pour matrice ces alliages a haute resistance mecanique et bonne ductilite
CA1340618C (en) 1989-01-13 1999-06-29 James T. Staley Aluminum alloy product having improved combinations of strength, toughness and corrosion resistance
FR2645546B1 (fr) 1989-04-05 1994-03-25 Pechiney Recherche Alliage a base d'al a haut module et a resistance mecanique elevee et procede d'obtention
CH682326A5 (es) 1990-06-11 1993-08-31 Alusuisse Lonza Services Ag
EP0462055A1 (de) 1990-06-11 1991-12-18 Alusuisse-Lonza Services Ag Vormaterial aus einer superplastischen AlZnMg-Legierung
FR2695942B1 (fr) 1992-09-22 1994-11-18 Gerzat Metallurg Alliage d'aluminium pour corps creux sous pression.
US5932037A (en) 1993-04-15 1999-08-03 Luxfer Group Limited Method of making hollow bodies
AU3813795A (en) 1994-09-26 1996-04-19 Ashurst Technology Corporation (Ireland) Limited High strength aluminum casting alloys for structural applications
JP3834076B2 (ja) * 1995-04-21 2006-10-18 昭和電工株式会社 押出材の製造方法
FR2744136B1 (fr) 1996-01-25 1998-03-06 Pechiney Rhenalu Produits epais en alliage alznmgcu a proprietes ameliorees
US6231995B1 (en) 1997-06-07 2001-05-15 Kabushiki Kaisha Kobe Seiko Sho Aluminum extruded door beam material
ATE217912T1 (de) 1997-08-04 2002-06-15 Corus Aluminium Walzprod Gmbh Hochverformbare, korrosionsbeständige al- legierung
US7135077B2 (en) 2000-05-24 2006-11-14 Pechiney Rhenalu Thick products made of heat-treatable aluminum alloy with improved toughness and process for manufacturing these products
US6562154B1 (en) 2000-06-12 2003-05-13 Aloca Inc. Aluminum sheet products having improved fatigue crack growth resistance and methods of making same
US6480440B2 (en) 2001-03-07 2002-11-12 Westerngeco, L.L.C. Seismic receiver motion compensation
US20050006010A1 (en) * 2002-06-24 2005-01-13 Rinze Benedictus Method for producing a high strength Al-Zn-Mg-Cu alloy
FR2846669B1 (fr) 2002-11-06 2005-07-22 Pechiney Rhenalu PROCEDE DE FABRICATION SIMPLIFIE DE PRODUITS LAMINES EN ALLIAGES A1-Zn-Mg, ET PRODUITS OBTENUS PAR CE PROCEDE
EP1441041A1 (de) 2003-01-16 2004-07-28 Alcan Technology & Management Ltd. Aluminiumlegierung mit hoher Festigkeit und geringer Abschreckempfindlichkeit
WO2004090185A1 (en) * 2003-04-10 2004-10-21 Corus Aluminium Walzprodukte Gmbh An al-zn-mg-cu alloy
EP1660272B1 (en) 2003-08-29 2017-12-27 Aleris Rolled Products Germany GmbH High strength aluminium alloy brazing sheet, brazed assembly and method for producing same
WO2005040440A1 (ja) 2003-10-23 2005-05-06 Aisin Keikinzoku Co., Ltd. 衝撃吸収性に優れたアルミニウム合金押出形材
US20050087266A1 (en) * 2003-10-23 2005-04-28 Shinji Makino Impact absorbing material
EP1544316B1 (fr) 2003-12-16 2012-03-07 Constellium France Tôle épaisse en alliage Al-Zn-Cu-Mg recristallisée à faible teneur en Zr
US20050238529A1 (en) 2004-04-22 2005-10-27 Lin Jen C Heat treatable Al-Zn-Mg alloy for aerospace and automotive castings
FR2872172B1 (fr) * 2004-06-25 2007-04-27 Pechiney Rhenalu Sa Produits en alliage d'aluminium a haute tenacite et haute resistance a la fatigue
ES2292075T5 (es) * 2005-01-19 2010-12-17 Otto Fuchs Kg Aleacion de aluminio no sensible al enfriamiento brusco, asi como procedimiento para fabricar un producto semiacabado a partir de esta aleacion.

Patent Citations (42)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3794531A (en) * 1970-10-23 1974-02-26 Fuchs O Fa Method of using a highly stable aluminum alloy in the production of recrystallization hardened products
US3743549A (en) * 1971-02-09 1973-07-03 I Esercizio Dell Istituto Sper Thermomechanical process for improving the toughness of the high strength aluminum alloys
US4863528A (en) * 1973-10-26 1989-09-05 Aluminum Company Of America Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same
US4063936A (en) * 1974-01-14 1977-12-20 Alloy Trading Co., Ltd. Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack
US3943039A (en) * 1974-10-08 1976-03-09 Kaiser Aluminum & Chemical Corporation Anodizing pretreatment for nickel plating
US3945861A (en) * 1975-04-21 1976-03-23 Aluminum Company Of America High strength automobile bumper alloy
US4049474A (en) * 1975-07-25 1977-09-20 Evegny Dmitrievich Zakharov Aluminum-based alloy
US4828631A (en) * 1981-12-23 1989-05-09 Aluminum Company Of America High strength aluminum alloy resistant to exfoliation and method of making
US4954188A (en) * 1981-12-23 1990-09-04 Aluminum Company Of America High strength aluminum alloy resistant to exfoliation and method of making
US4629517A (en) * 1982-12-27 1986-12-16 Aluminum Company Of America High strength and corrosion resistant aluminum article and method
US5055257A (en) * 1986-03-20 1991-10-08 Aluminum Company Of America Superplastic aluminum products and alloys
US4830826A (en) * 1986-09-26 1989-05-16 Matsuo Kogyo Kabushiki Kaisha Process of manufacturing high-strength high-elasticity aluminum alloys
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
US5277719A (en) * 1991-04-18 1994-01-11 Aluminum Company Of America Aluminum alloy thick plate product and method
US5312498A (en) * 1992-08-13 1994-05-17 Reynolds Metals Company Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness
US5560789A (en) * 1994-03-02 1996-10-01 Pechiney Recherche 7000 Alloy having high mechanical strength and a process for obtaining it
US5620652A (en) * 1994-05-25 1997-04-15 Ashurst Technology Corporation (Ireland) Limited Aluminum alloys containing scandium with zirconium additions
US6027582A (en) * 1996-01-25 2000-02-22 Pechiney Rhenalu Thick alZnMgCu alloy products with improved properties
US6048415A (en) * 1997-04-18 2000-04-11 Kabushiki Kaisha Kobe Seiko Sho High strength heat treatable 7000 series aluminum alloy of excellent corrosion resistance and a method of producing thereof
US6726878B1 (en) * 1999-10-05 2004-04-27 Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie “Vserossiisky Nauchno-Issle-Dovatelsky Institut Aviatsionnykh Materialov” High strength aluminum based alloy and the article made thereof
US6565684B2 (en) * 2000-02-23 2003-05-20 Societe Metallurgique De Gerzat Manufacturing process for a hollow pressure vessel made of AlZnMgCu alloy
US6790407B2 (en) * 2000-08-01 2004-09-14 Federalnoe Gosudarstvennoe Unitarnoe Predpriyatie “Vserossiisky auchno-Issledovatelsky Institut Aviatsionnykh Materialov” High-strength alloy based on aluminium and a product made of said alloy
US6972110B2 (en) * 2000-12-21 2005-12-06 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US20050257865A1 (en) * 2000-12-21 2005-11-24 Chakrabarti Dhruba J Aluminum alloy products having improved property combinations and method for artificially aging same
US20050150579A1 (en) * 2000-12-21 2005-07-14 Chakrabarti Dhruba J. Aluminum alloy products having improved property combinations and method for artificially aging same
US20020150498A1 (en) * 2001-01-31 2002-10-17 Chakrabarti Dhruba J. Aluminum alloy having superior strength-toughness combinations in thick gauges
US20020162609A1 (en) * 2001-02-07 2002-11-07 Timothy Warner Manufacturing process for a high strength work hardened product made of AlZnMgCu alloy
US6743308B2 (en) * 2001-02-16 2004-06-01 Kabushiki Kaisha Kobe Seiko Sho. Aluminum alloy structural plate excelling in strength and corrosion resistance and method of manufacturing same
US20030213537A1 (en) * 2001-02-28 2003-11-20 Alex Cho Aluminum alloys
US20050000610A1 (en) * 2001-10-24 2005-01-06 Gerhard Huber Production of water-free nitrocellulose and explosive substances that have a spheroidal shape
US20030219353A1 (en) * 2002-04-05 2003-11-27 Timothy Warner Al-Zn-Mg-Cu alloys and products with improved ratio of static mechanical characteristics to damage tolerance
US20050072497A1 (en) * 2002-04-05 2005-04-07 Frank Eberl Al-Zn-Mg-Cu alloys and products with high mechanical characteristics and structural members suitable for aeronautical construction made thereof
US20040099352A1 (en) * 2002-09-21 2004-05-27 Iulian Gheorghe Aluminum-zinc-magnesium-copper alloy extrusion
US20040136862A1 (en) * 2002-11-15 2004-07-15 Bray Gary H. Aluminum alloy product having improved combinations of properties
US20050034794A1 (en) * 2003-04-10 2005-02-17 Rinze Benedictus High strength Al-Zn alloy and method for producing such an alloy product
US20050189044A1 (en) * 2003-04-10 2005-09-01 Rinze Benedictus Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US20050056353A1 (en) * 2003-04-23 2005-03-17 Brooks Charles E. High strength aluminum alloys and process for making the same
US20050058568A1 (en) * 2003-06-24 2005-03-17 Pechiney Rhenalu Products made of Al-Zn-Mg-Cu alloys with an improved compromise between static mechanical characteristics and damage tolerance
US20050023075A1 (en) * 2003-07-30 2005-02-03 Schmaeman Dale E. Reduced noise valve stack connection
US20050150578A1 (en) * 2003-12-16 2005-07-14 Pechiney Rhenalu Metallurgical product and structure member for aircraft made of Al-Zn-Cu-Mg alloy
US20050238528A1 (en) * 2004-04-22 2005-10-27 Lin Jen C Heat treatable Al-Zn-Mg-Cu alloy for aerospace and automotive castings
US20080056932A1 (en) * 2006-06-30 2008-03-06 Alex Cho High Strength, Heat Treatable Aluminum Alloy

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080299000A1 (en) * 2002-09-21 2008-12-04 Universal Alloy Corporation Aluminum-zinc-copper-magnesium-silver alloy wrought product
US20040211498A1 (en) * 2003-03-17 2004-10-28 Keidel Christian Joachim Method for producing an integrated monolithic aluminum structure and aluminum product machined from that structure
US7610669B2 (en) * 2003-03-17 2009-11-03 Aleris Aluminum Koblenz Gmbh Method for producing an integrated monolithic aluminum structure and aluminum product machined from that structure
US20110008202A1 (en) * 2005-01-19 2011-01-13 Otto Fuchs Kg Alluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US10301710B2 (en) 2005-01-19 2019-05-28 Otto Fuchs Kg Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product
US9353430B2 (en) 2005-10-28 2016-05-31 Shipston Aluminum Technologies (Michigan), Inc. Lightweight, crash-sensitive automotive component
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
US8721811B2 (en) 2005-10-28 2014-05-13 Automotive Casting Technology, Inc. Method of creating a cast automotive product having an improved critical fracture strain
US8673209B2 (en) 2007-05-14 2014-03-18 Alcoa Inc. Aluminum alloy products having improved property combinations and method for artificially aging same
US20080283163A1 (en) * 2007-05-14 2008-11-20 Bray Gary H Aluminum Alloy Products Having Improved Property Combinations and Method for Artificially Aging Same
US9163304B2 (en) 2010-04-20 2015-10-20 Alcoa Inc. High strength forged aluminum alloy products
CN101818290A (zh) * 2010-05-28 2010-09-01 中南大学 一种同时添加Ag、Ge的低淬火敏感性铝合金
US9347558B2 (en) 2010-08-25 2016-05-24 Spirit Aerosystems, Inc. Wrought and cast aluminum alloy with improved resistance to mechanical property degradation
AU2011226794B2 (en) * 2010-09-08 2012-04-05 Arconic Inc. Improved 7xxx aluminum alloys, and methods for producing the same
US9359660B2 (en) 2010-09-08 2016-06-07 Alcoa Inc. 6XXX aluminum alloys, and methods for producing the same
US8999079B2 (en) 2010-09-08 2015-04-07 Alcoa, Inc. 6xxx aluminum alloys, and methods for producing the same
US9194028B2 (en) 2010-09-08 2015-11-24 Alcoa Inc. 2xxx aluminum alloys, and methods for producing the same
US9249484B2 (en) 2010-09-08 2016-02-02 Alcoa Inc. 7XXX aluminum alloys, and methods for producing the same
US9353431B2 (en) 2011-06-23 2016-05-31 Uacj Corporation High-strength aluminum alloy material and process for producing the same
CN103732772A (zh) * 2011-11-07 2014-04-16 株式会社Uacj 高强度铝合金材料及其制造方法
US9512510B2 (en) 2011-11-07 2016-12-06 Uacj Corporation High-strength aluminum alloy and process for producing same
CN103131992A (zh) * 2011-11-29 2013-06-05 贵州铝厂 一种低锌热浸镀铝合金镀层材料
US9926620B2 (en) 2012-03-07 2018-03-27 Arconic Inc. 2xxx aluminum alloys, and methods for producing the same
US10266933B2 (en) 2012-08-27 2019-04-23 Spirit Aerosystems, Inc. Aluminum-copper alloys with improved strength
US9587298B2 (en) 2013-02-19 2017-03-07 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
US10208370B2 (en) 2014-01-29 2019-02-19 Uacj Corporation High-strength aluminum alloy and manufacturing method thereof
EP2942412B1 (en) 2014-05-06 2016-11-16 Goodrich Corporation Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver
CN104073698A (zh) * 2014-06-26 2014-10-01 龙口市丛林铝材有限公司 一种6系轨道车辆悬挂臂铝型材及其制备方法
CN108070747A (zh) * 2016-11-14 2018-05-25 镇江市润州金山金属粉末厂 一种高性能钒锶合金
CN111051549A (zh) * 2017-04-05 2020-04-21 阿马格铸造公司 原材料及其应用和使用此原材料的增材制造方法
CN107240434A (zh) * 2017-06-27 2017-10-10 苏州菱慧电子科技有限公司 一种导电金属材料
CN108048715A (zh) * 2018-02-01 2018-05-18 佛山市三水凤铝铝业有限公司 一种用于消费电子产品壳体的高强度铝合金及其挤压方法
CN108468003A (zh) * 2018-04-11 2018-08-31 益阳仪纬科技有限公司 一种铝合金及其铸造方法
JP2021534320A (ja) * 2018-07-02 2021-12-09 オットー フックス カーゲー アルミニウム合金およびこのような合金から製造された過時効アルミニウム合金製品
JP7321195B2 (ja) 2018-07-02 2023-08-04 オットー フックス カーゲー アルミニウム合金およびこのような合金から製造された過時効アルミニウム合金製品
US11970756B2 (en) 2018-07-02 2024-04-30 Otto Fuchs Kommanditgesellschaft Aluminum alloy and overaged aluminum alloy product of such alloy
CN110699575A (zh) * 2019-09-27 2020-01-17 黄山市龙跃铜业有限公司 一种高强度高韧性铝合金及其制备方法

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US20160010195A1 (en) 2016-01-14
DE502005001724D1 (de) 2007-11-29
US20140099230A1 (en) 2014-04-10
EP1683882B2 (de) 2010-07-21
EP1683882B1 (de) 2007-10-17
US10301710B2 (en) 2019-05-28
EP1683882A1 (de) 2006-07-26
US20120202086A1 (en) 2012-08-09

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