WO2001012868A1 - Alliages aluminium-magnesium-scandium avec hafnium - Google Patents

Alliages aluminium-magnesium-scandium avec hafnium Download PDF

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Publication number
WO2001012868A1
WO2001012868A1 PCT/US2000/019559 US0019559W WO0112868A1 WO 2001012868 A1 WO2001012868 A1 WO 2001012868A1 US 0019559 W US0019559 W US 0019559W WO 0112868 A1 WO0112868 A1 WO 0112868A1
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WIPO (PCT)
Prior art keywords
auoy
aluminum
alloys
incidental impurities
alloy
Prior art date
Application number
PCT/US2000/019559
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English (en)
Inventor
Micky T. Fernandes
Original Assignee
Kaiser Aluminum And Chemical Corporation
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 Kaiser Aluminum And Chemical Corporation filed Critical Kaiser Aluminum And Chemical Corporation
Priority to AU75710/00A priority Critical patent/AU7571000A/en
Publication of WO2001012868A1 publication Critical patent/WO2001012868A1/fr

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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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent

Definitions

  • the present invention relates to Al-Mg-Sc alloy compositions for use in aerospace applications, and the like, in which hafnium is added to the alloys to improve their tensile properties.
  • Aluminum alloys containing magnesium as the principal alloying element have two potential advantages for aircraft structures: they are lighter than the standard 2000 and 7000 series alloys; and unlike the latter materials, they are weldable by conventional fusion techniques, which could lower manufacturing costs by reducing the 2-3 million rivets typically used to assemble a commercial airliner.
  • a number of aluminum alloys have been developed in which magnesium is added to improve strength. These alloys are particularly suited for aerospace applications because of their strength and damage resistance. However, these alloys are not particularly suited for aerospace applications because their strength levels are not high enough.
  • improved Al-Mg based alloys have been developed in which a dispersoid generating element, such as scandium, is added to the alloy. The addition of scandium to the alloys results in the formation of Al 3 Sc dispersoids, which are precipitates that are known to impart significantly greater strength and corrosion resistance to products made from the alloys.
  • the tensile properties of Al-Mg-Sc based alloys deteriorate rapidly with thermomechanical processing and high temperature operations, such as rolling, that are necessary to form aircraft fuselage components.
  • the degradation in tensile properties occurs because the scandium dispersoids must be small in size and large in number to impart increased strength to the alloy, and high temperature operations cause them to grow too large.
  • the present invention relates to Al-Mg-Sc based alloy in which an additional dispersoid generating element, hafhium, is added to the alloys to substantially eliminate degradation of the tensile properties during rolling and other thermomechanical and high temperature operations.
  • the addition of hafnium to the alloys has been found to reduce growth of the scandium dispersoid particles during these thermal operations, thus enabling the scandium particles to maintain their strength enhancing characteristics.
  • the present invention comprises alloys, and products made therefrom, whose wt. % composition comprises 1.0-8.0% Mg, 0.05-0.6% Sc, 0.05-0.20% Hf, and the balance aluminum and incidental impurities.
  • a small amount of manganese preferably 0.1-0.8 wt.%, is added to the alloys to improve the strength characteristics even further.
  • the alloy's tensile properties were not degraded after rolling operations in which the sample was hot and cold rolled to a thin sheet suitable for use in an aircraft skin, and then annealed.
  • the alloy can be strengthened further by the addition of 0.05-0.20% Zr, either with or without the manganese.
  • All of the embodiments of the present invention comprise Al-Mg-Sc based alloys, and products made therefrom, in which hafhium is added to the alloys to increase strength and corrosion resistance.
  • the alloys preferably include 1.0-8.0% Mg, 0.05- 0.6% Sc, 0.05-0.20% Hf, and the balance aluminum and incidental impurities, with the most preferred ranges of the recited elements being 4.0-6.0% Mg, 0.2-0.4% Sc, and 0.08-0.15% Hf. Within these ranges, a composition of 5.0% Mg, 0.25% Sc, 0.12% Hf, and the balance aluminum and incidental impurities is believed to provide the best results.
  • each element in the subject alloys is as follows. Mg added to the alloys in the recited amount increases the strength of the alloy substantially. However, if Mg is added in amounts above approximately 8%, the resulting alloy becomes difficult to process. Sc is added to generate Al 3 Sc dispersoids, which as stated previously, substantially increase the strength and corrosion resistance of the alloys. Hf is the most significant element in the alloys of the present invention. This element, like Sc, is another dispersoid generating element that can be used in place of Sc to achieve improvements in strength and corrosion resistance. However, the inventor has discovered that when Hf is used in combination with Sc, the Hf acts to stabilize the Al 3 Sc dispersoids during rolling and thermal processing.
  • the Al 3 Sc dispersoids will grow too large during thermal processing, and substantially diminish the alloys' tensile properties.
  • the addition of Hf to the alloy limits the growth of the Al 3 Sc dispersoids.
  • the amounts of Sc and Hf added to the alloys must not, however, be above the recited ranges to avoid primary formations in the alloys that would once again, diminish their tensile and other properties.
  • manganese and/or zirconium are added to the alloys to improve their tensile properties further.
  • the proportions of the other elements in the alloys remain the same, and the preferred range in wt. % for the manganese is 0.1-0.8, and for the zirconium is 0.5-2.0.
  • the composition of the alloys is thus 1.0-8.0% Mg, 0.05-0.6% Sc, 0.05-0.20% Hf, 0.1-0.8% Mn and/or 0.05-0.20% Zr, and the balance aluminum and incidental impurities, with the most preferred ranges of the recited elements being 4.0-6.0% Mg, 0.2-0.4% Sc, 0.08-0.15% Hf, and 0.3-0.7% Mn and/or 0.08- 0.15% Zr. Within these ranges, a composition of 5.0% Mg, 0.25% Sc, 0.12% Hf, 0.6% Mn and/or 0.12% Zr, and the balance aluminum and incidental impurities is believed to provide the best results.
  • EXAMPLE 1 To test the tensile properties of an alloy formed in accordance with the present invention, a rolled sheet sample alloy was prepared as follows, and subjected to testing. First, a 3" x 9" ingot was cast of an alloy having the following wt. % composition: 5% Mg, 0.2% Sc, 0.12% H ⁇ 0.5% Mn, the balance AL and incidental impurities. This ingot was then subjected, without homogenization, to conventional rolling operations until it was formed into a sheet of 0.063" thickness. The sheet was then annealed at 550° F for 8 hours. For comparison purposes, additional rolled sheet samples were prepared in the same manner, but with different alloy compositions.
  • a first of the comparison alloys did not contain hafhium and manganese so that this sample's alloy composition was 5% Mg, 0.2% Sc, the balance Al, and incidental impurities.
  • the second and third comparison alloy compositions included 0.11% zirconium, with the third sample also containing 0.5% manganese.
  • the Zr containing samples were employed because it is known that Zr also stabilizes the Al 3 Sc dispersoids, and thus improves the tensile properties of the rolled sheets.
  • test results indicate that substantial improvements in strength properties are obtained when hafnium and manganese are added to an Al-Mg-Sc alloy.
  • improvements of over 10% and 30% were achieved for the ultimate tensile strength and yield strength, respectfully, over the comparison sheet sample comprised of an Al-Mg-Sc alloy without hafnium and manganese.
  • the obtained values for all three parameters also compare favorably with the comparison sample containing 0.11% Zr, although they were somewhat less than the comparison sample containing both Zr and Mn.
  • Example 1 and the values expected for the other Al-Mg- Sc-Hf alloys of Examples 2-4 indicate that the alloys can readily be employed in rolled sheet form for various aerospace appUcations, such as for aircraft fuselage skins, etc. As stated previously, these appUcations for the subject aUoys are particularly attractive because of the superior corrosion resistance and weldabiUty of Al-Mg-Sc aUoys.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Continuous Casting (AREA)

Abstract

Cette invention se rapporte à des alliages à base de Al-Mg-Sc, qui contiennent de l'hafnium pour empêcher la dégradation de leurs propriétés de traction lors du laminage et d'autres opérations thermomécaniques et sous haute température. Ces alliages contiennent de l'aluminium et 1,08 à 8,0 % de Mg, 0,05 à 0,6 % de Sc et 0,05 à 0,20 % de Hf. D'autres éléments, tels que Mn et Zr, peuvent être ajoutés à ces alliages pour améliorer encore davantage leurs propriétés de traction.
PCT/US2000/019559 1999-08-12 2000-08-02 Alliages aluminium-magnesium-scandium avec hafnium WO2001012868A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU75710/00A AU7571000A (en) 1999-08-12 2000-08-02 Aluminum-magnesium-scandium alloys with hafnium

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US37258399A 1999-08-12 1999-08-12
US09/372,583 1999-08-12

Publications (1)

Publication Number Publication Date
WO2001012868A1 true WO2001012868A1 (fr) 2001-02-22

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PCT/US2000/019559 WO2001012868A1 (fr) 1999-08-12 2000-08-02 Alliages aluminium-magnesium-scandium avec hafnium

Country Status (2)

Country Link
AU (1) AU7571000A (fr)
WO (1) WO2001012868A1 (fr)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1439239A1 (fr) * 2003-01-15 2004-07-21 United Technologies Corporation Alliage à base d'aluminium
EP2241644A1 (fr) * 2009-04-07 2010-10-20 United Technologies Corporation Alliages d'aluminium L12 traitables thermiquement
US8002912B2 (en) 2008-04-18 2011-08-23 United Technologies Corporation High strength L12 aluminum alloys
EP2546373A1 (fr) * 2011-07-13 2013-01-16 Aleris Aluminum Koblenz GmbH Procédé de fabrication d'un produit de feuille d'alliage AI-Mg
US8409497B2 (en) 2009-10-16 2013-04-02 United Technologies Corporation Hot and cold rolling high strength L12 aluminum alloys
US8409496B2 (en) 2009-09-14 2013-04-02 United Technologies Corporation Superplastic forming high strength L12 aluminum alloys
US8728389B2 (en) 2009-09-01 2014-05-20 United Technologies Corporation Fabrication of L12 aluminum alloy tanks and other vessels by roll forming, spin forming, and friction stir welding
US8778098B2 (en) 2008-12-09 2014-07-15 United Technologies Corporation Method for producing high strength aluminum alloy powder containing L12 intermetallic dispersoids
US8778099B2 (en) 2008-12-09 2014-07-15 United Technologies Corporation Conversion process for heat treatable L12 aluminum alloys
US9127334B2 (en) 2009-05-07 2015-09-08 United Technologies Corporation Direct forging and rolling of L12 aluminum alloys for armor applications
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
US9611522B2 (en) 2009-05-06 2017-04-04 United Technologies Corporation Spray deposition of L12 aluminum alloys

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5066342A (en) * 1988-01-28 1991-11-19 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5108519A (en) * 1988-01-28 1992-04-28 Aluminum Company Of America Aluminum-lithium alloys suitable for forgings
US5624632A (en) * 1995-01-31 1997-04-29 Aluminum Company Of America Aluminum magnesium alloy product containing dispersoids

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5066342A (en) * 1988-01-28 1991-11-19 Aluminum Company Of America Aluminum-lithium alloys and method of making the same
US5108519A (en) * 1988-01-28 1992-04-28 Aluminum Company Of America Aluminum-lithium alloys suitable for forgings
US5624632A (en) * 1995-01-31 1997-04-29 Aluminum Company Of America Aluminum magnesium alloy product containing dispersoids

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1439239A1 (fr) * 2003-01-15 2004-07-21 United Technologies Corporation Alliage à base d'aluminium
US8002912B2 (en) 2008-04-18 2011-08-23 United Technologies Corporation High strength L12 aluminum alloys
US8778098B2 (en) 2008-12-09 2014-07-15 United Technologies Corporation Method for producing high strength aluminum alloy powder containing L12 intermetallic dispersoids
US8778099B2 (en) 2008-12-09 2014-07-15 United Technologies Corporation Conversion process for heat treatable L12 aluminum alloys
EP2241644A1 (fr) * 2009-04-07 2010-10-20 United Technologies Corporation Alliages d'aluminium L12 traitables thermiquement
US9611522B2 (en) 2009-05-06 2017-04-04 United Technologies Corporation Spray deposition of L12 aluminum alloys
US9127334B2 (en) 2009-05-07 2015-09-08 United Technologies Corporation Direct forging and rolling of L12 aluminum alloys for armor applications
US8728389B2 (en) 2009-09-01 2014-05-20 United Technologies Corporation Fabrication of L12 aluminum alloy tanks and other vessels by roll forming, spin forming, and friction stir welding
US8409496B2 (en) 2009-09-14 2013-04-02 United Technologies Corporation Superplastic forming high strength L12 aluminum alloys
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
WO2013007471A1 (fr) * 2011-07-13 2013-01-17 Aleris Aluminum Koblenz Gmbh Procédé de fabrication d'un produit de tôle d'alliage d'al-mg
EP2546373A1 (fr) * 2011-07-13 2013-01-16 Aleris Aluminum Koblenz GmbH Procédé de fabrication d'un produit de feuille d'alliage AI-Mg

Also Published As

Publication number Publication date
AU7571000A (en) 2001-03-13

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