US20150322556A1 - Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products - Google Patents

Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products Download PDF

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Publication number
US20150322556A1
US20150322556A1 US14/461,102 US201414461102A US2015322556A1 US 20150322556 A1 US20150322556 A1 US 20150322556A1 US 201414461102 A US201414461102 A US 201414461102A US 2015322556 A1 US2015322556 A1 US 2015322556A1
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United States
Prior art keywords
lithium
alloy
free
worked
aluminum alloy
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Abandoned
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US14/461,102
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English (en)
Inventor
Leslie Steele
Awadh B. Pandey
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Goodrich Corp
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Goodrich Corp
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Application filed by Goodrich Corp filed Critical Goodrich Corp
Priority to US14/461,102 priority Critical patent/US20150322556A1/en
Assigned to GOODRICH CORPORATION reassignment GOODRICH CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PANDEY, AWADH B., STEELE, LESLIE
Priority to CA2886124A priority patent/CA2886124A1/en
Priority to RU2015116924A priority patent/RU2015116924A/ru
Priority to EP15166597.3A priority patent/EP2942412B1/en
Publication of US20150322556A1 publication Critical patent/US20150322556A1/en
Abandoned legal-status Critical Current

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    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
    • 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
    • C22C21/12—Alloys based on aluminium with copper as the next major constituent
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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
    • 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
    • C22F1/057—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 copper as the next major constituent

Definitions

  • the present disclosure relates to high-temperature alloys, and, more specifically, to a substantially lithium-free elevated-temperature aluminum based alloy.
  • Aircraft components may be subjected to high airspeeds and elevated temperatures as result of flight.
  • Load bearing structures e.g., wheels and landing gear
  • Materials used to make components e.g. main wheels
  • Many of the components (such as piston housings) may also be subject to elevated temperatures. As a result, components may be subject to stress corrosion and ultimately failure over time.
  • a substantially lithium-free alloy may comprise copper from 4.8 wt. % to 5.4 wt. %, magnesium from 0.7 wt. % to 1.1 wt. %, silver from 0.55 wt. % to 0.7 wt. %, and lithium at or below 0.005 wt. %.
  • the substantially lithium-free alloy may further comprise silver from 0.56 wt. % to 0.7 wt. %.
  • the substantially lithium-free alloy may also comprise zirconium from 0.08 wt. % to 0.15 wt. %.
  • the substantially lithium-free alloy may include titanium at or below 0.06 wt. %, iron at or below 0.1 wt.
  • the silver may be from 0.6 wt. % to 0.7 wt. %.
  • Manganese may be from 0.45 wt. % to 0.8 wt. %.
  • the lithium may be at or below 0.003%.
  • a worked aircraft component may comprise an alloy including silver from 0.55 wt. % to 0.7 wt. % and lithium at or below 0.005 wt. %.
  • the worked aircraft component may further comprise the silver from 0.56 wt. % to 0.7 wt. %.
  • the worked aircraft component may be a wheel or a piston housing.
  • the alloy may further comprise titanium at or below 0.06 wt. %, iron at or below 0.1 wt. %, silicon at or below 0.08 wt. %, beryllium at or below 0.0001 wt. %, chromium at or below 0.05 wt. %, and zinc at or below 0.25 wt. %.
  • the worked aircraft component may be hardened by a precipitation heat treatment.
  • the alloy may further comprise copper from 4.8 wt. % to 5.4 wt. %, and magnesium from 0.7 wt. % to 1.1 wt. %.
  • the worked aircraft component may further comprise silver from 0.6 wt. % to 0.7 wt. %.
  • FIG. 1 illustrates a process of making a worked aluminum aircraft component from a substantially lithium-free aluminum alloy, in accordance with various embodiments.
  • any reference to singular includes plural embodiments, and any reference to more than one component or step may include a singular embodiment or step.
  • Surface shading lines may be used throughout the figures to denote different parts but not necessarily to denote the same or different materials.
  • % wt As used herein, the term “% wt,” “wt. %” or “% by weight,” used in reference to a substantially lithium-free aluminum alloy, may refer to the percentage weight of the substantially lithium-free aluminum alloy or a constituent of the substantially lithium-free aluminum alloy or a group of constituents of the substantially lithium-free aluminum alloy over the weight of the entire substantially lithium-free aluminum alloy.
  • FIG. 1 depicts a method 100 of making aircraft components using a worked aluminum alloy.
  • a substantially lithium-free aluminum alloy may be formed, for example by casting, such as by heating and melting one or more metals to form a homogenous solution (Step 102 ). The solution may be cooled to solidify the substantially lithium-free aluminum alloy.
  • the substantially lithium-free aluminum alloy may comprise copper (Cu) ranging from 4.8 wt. % to 5.4 wt. %, magnesium (Mg) ranging from 0.7 to 1.1 wt. %, and silver (Ag) ranging from 0.55 to 0.7 wt. %. Ag may preferably range from 0.56 to 0.7 wt. %, and Ag may further range from 0.6 wt.
  • the substantially lithium-free aluminum alloy may further comprise zirconium (Zr) ranging from 0.08 to 0.15 wt. %, and manganese (Mn) ranging from 0.45 to 0.8 wt. %.
  • Trace elements present in the substantially lithium-free aluminum alloy may include lithium (Li) not to exceed 0.005 wt. %, titanium (Ti) not to exceed 0.06 wt. %, iron (Fe) not to exceed 0.10 wt. %, silicon (Si) not to exceed 0.08 wt. %, beryllium (Be) not to exceed 0.0001 wt. %, chromium (Cr) not to exceed 0.05 wt.
  • the alloy may have a ratio between Cu and Mg that is closely controlled.
  • the ratio of Cu/Mg may range from 6.5 to 7.5. In various embodiments, the Cu/Mg ratio may be approximately 7.
  • the term “substantially lithium-free aluminum alloy” refers to the aluminum alloy at least partially comprising the foregoing composition.
  • the substantially lithium-free aluminum alloy may be substantially free from lithium to reduce brittleness and improve the toughness of the alloy.
  • Lithium may not be intentionally added to the substantially lithium-free aluminum alloy, though trace amounts (e.g., less than 0.005 wt. %, less than 0.003 wt. %, or less than 0.001 wt. %) may be present and regarded impurities.
  • the term “substantially lithium-free” may refer to an alloy having controlled amounts of lithium less than 0.005 wt. %, less than 0.003 wt. %, or less than 0.001 wt. %.
  • the amount of lithium introduced to the substantially lithium-free aluminum alloy may be tightly controlled by inspecting any aluminum prior to adding the aluminum to the substantially lithium-free aluminum alloy. For example, prior to using scrap aluminum to create the substantially lithium-free aluminum alloy, scrap aluminum should be inspected to determine the lithium content in the scrap aluminum. Scrap aluminum with excessive lithium content may not be used to create the substantially lithium-free aluminum alloy. Bauxite or aluminum oxide may also be used to produce a substantially lithium-free aluminum alloy without associated inspection for lithium.
  • the substantially lithium-free aluminum alloy may then be worked into a component (Step 104 ).
  • extrusion, folding, or heat forging may be used to work the substantially lithium-free aluminum alloy into the desired shape.
  • the substantially lithium-free aluminum alloy may be hot forged into a wheel, brake piston housing or any other component for use on an aircraft. If forging is used to shape the component, the component may then be quenched to precipitate harden the component (Step 106 ).
  • the copper and magnesium may precipitate out of solution with the metal as it is quenched to harden the substantially lithium-free aluminum alloy as well as improve strength and fatigue characteristics.
  • the substantially lithium-free aluminum alloy may then be aged to complete the precipitation hardening process.
  • the substantially lithium-free aluminum alloy may display increased strength characteristics compared an aluminum alloy having a composition, in weight percent, of about 4 percent copper, about 0.5 percent magnesium, about 0.8 percent manganese, and about 0.8 percent silicon, and the remainder aluminum, which is commonly known by the industry standard designation of aluminum 2014.
  • the term “about” in this context only refers to +/ ⁇ 0.15%.
  • the substantially lithium-free aluminum alloy may also have improved toughness compared to aluminum 2014, for example, and be more resistant to deformation or fracturing under load.
  • the substantially lithium-free aluminum alloy may further have improved thermal stability over aluminum 2014 in response to higher silver levels contained in the substantially lithium-free aluminum alloy.
  • aluminum 2014 may be used in environments that repeatedly reach temperatures of approximately 300° F. (149° C.).
  • the substantially lithium-free aluminum alloy may be used at higher temperatures, up to 350° F. (176° C.) or higher, while substantially maintaining strength and toughness.
  • the substantially lithium-free aluminum alloy displays improved fracture toughness, for example over aluminum 2014, as the amount of silver in the substantially lithium-free aluminum alloy increases.
  • the substantially lithium-free aluminum alloy is more resistant to stress corrosion cracking than aluminum 2014 because of the higher silver content in the substantially lithium-free aluminum alloy.
  • the substantially lithium-free aluminum alloy may also be substantially vanadium free.
  • the substantially lithium-free aluminum alloy may further have reduced weight and improved fatigue characteristics over aluminum 2014.
  • references to “various embodiments”, “one embodiment”, “an embodiment”, “an example embodiment”, etc. indicate that the embodiment described may include a particular feature, structure, or characteristic, but every embodiment may not necessarily include the particular feature, structure, or characteristic. Moreover, such phrases are not necessarily referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with an embodiment, it is submitted that it is within the knowledge of one skilled in the art to affect such feature, structure, or characteristic in connection with other embodiments whether or not explicitly described. After reading the description, it will be apparent to one skilled in the relevant art(s) how to implement the disclosure in alternative embodiments.

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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)
  • Heat Treatment Of Steel (AREA)
  • Heat Treatment Of Articles (AREA)
  • Forging (AREA)
US14/461,102 2014-05-06 2014-08-15 Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products Abandoned US20150322556A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US14/461,102 US20150322556A1 (en) 2014-05-06 2014-08-15 Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products
CA2886124A CA2886124A1 (en) 2014-05-06 2015-03-23 Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products
RU2015116924A RU2015116924A (ru) 2014-05-06 2015-05-05 Безлитиевый высокотемпературный сплав алюминий-медь-магний-серебро для кованых авиационных деталей
EP15166597.3A EP2942412B1 (en) 2014-05-06 2015-05-06 Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US201461989326P 2014-05-06 2014-05-06
US14/461,102 US20150322556A1 (en) 2014-05-06 2014-08-15 Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products

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US (1) US20150322556A1 (ru)
EP (1) EP2942412B1 (ru)
CA (1) CA2886124A1 (ru)
RU (1) RU2015116924A (ru)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106282702A (zh) * 2016-10-24 2017-01-04 马鞍山顺发机械制造有限公司 一种汽车铸造用高品质铝合金材料
FR3080860B1 (fr) * 2018-05-02 2020-04-17 Constellium Issoire Alliage aluminium cuivre lithium a resistance en compression et tenacite ameliorees
US20210121949A1 (en) * 2019-10-25 2021-04-29 Goodrich Corporation Shape memory alloy particle toughening of cast or additive manufactured al-cu-mg-ag-tib2
CN111020321B (zh) * 2019-12-11 2021-09-14 兰州飞行控制有限责任公司 一种适于锻造加工的Al-Cu系铸造合金及其制备方法

Citations (2)

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Publication number Priority date Publication date Assignee Title
US5879475A (en) * 1995-03-22 1999-03-09 Aluminum Company Of America Vanadium-free, lithium-free aluminum alloy suitable for forged aerospace products
US7527872B2 (en) * 2005-10-25 2009-05-05 Goodrich Corporation Treated aluminum article and method for making same

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JPH03107440A (ja) 1989-09-20 1991-05-07 Showa Alum Corp ロードセル用アルミニウム合金
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US7527872B2 (en) * 2005-10-25 2009-05-05 Goodrich Corporation Treated aluminum article and method for making same

Also Published As

Publication number Publication date
EP2942412B1 (en) 2016-11-16
RU2015116924A (ru) 2016-11-27
CA2886124A1 (en) 2015-11-06
EP2942412A1 (en) 2015-11-11
RU2015116924A3 (ru) 2018-11-02

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AS Assignment

Owner name: GOODRICH CORPORATION, NORTH CAROLINA

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:STEELE, LESLIE;PANDEY, AWADH B.;REEL/FRAME:033548/0141

Effective date: 20140815

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION