EP2942412B1 - Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver - Google Patents

Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver Download PDF

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Publication number
EP2942412B1
EP2942412B1 EP15166597.3A EP15166597A EP2942412B1 EP 2942412 B1 EP2942412 B1 EP 2942412B1 EP 15166597 A EP15166597 A EP 15166597A EP 2942412 B1 EP2942412 B1 EP 2942412B1
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EP
European Patent Office
Prior art keywords
lithium
aluminium alloy
free
silver
worked
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.)
Revoked
Application number
EP15166597.3A
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German (de)
English (en)
French (fr)
Other versions
EP2942412A1 (en
Inventor
Leslie Steele
Awadh B. Pandey
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.)
Goodrich Corp
Original Assignee
Goodrich Corp
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Publication date
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=53052738&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2942412(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Goodrich Corp filed Critical Goodrich Corp
Publication of EP2942412A1 publication Critical patent/EP2942412A1/en
Application granted granted Critical
Publication of EP2942412B1 publication Critical patent/EP2942412B1/en
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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 aluminium 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
  • Materials used to make components support aircraft weights and withstand inflight wind conditions.
  • 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.
  • US 5 652 063 discloses a substantially vanadium-free aluminium based alloy.
  • 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.%, 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 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 aluminium aircraft component from a substantially lithium-free aluminium 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 aluminium alloy, may refer to the percentage weight of the substantially lithium-free aluminium alloy or a constituent of the substantially lithium-free aluminium alloy or a group of constituents of the substantially lithium-free aluminium alloy over the weight of the entire substantially lithium-free aluminium alloy.
  • FIG. 1 depicts a method 100 of making aircraft components using a worked aluminium alloy.
  • a substantially lithium-free aluminium 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 aluminium alloy.
  • the substantially lithium-free aluminium 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.%.
  • the substantially lithium-free aluminium 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 aluminium 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.%, zinc (Zn) not to exceed 0.25 wt.%, and other individual trace elements each to not to exceed 0.05 wt.%, and other total trace elements not to exceed 0.15 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 aluminium alloy” refers to the aluminium alloy at least partially comprising the foregoing composition.
  • the substantially lithium-free aluminium 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 aluminium 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 aluminium alloy may be tightly controlled by inspecting any aluminium prior to adding the aluminium to the substantially lithium-free aluminium alloy. For example, prior to using scrap aluminium to create the substantially lithium-free aluminium alloy, scrap aluminium should be inspected to determine the lithium content in the scrap aluminium. Scrap aluminium with excessive lithium content may not be used to create the substantially lithium-free aluminium alloy. Bauxite or aluminium oxide may also be used to produce a substantially lithium-free aluminium alloy without associated inspection for lithium.
  • the substantially lithium-free aluminium alloy may then be worked into a component (Step 104).
  • extrusion, folding, or heat forging may be used to work the substantially lithium-free aluminium alloy into the desired shape.
  • the substantially lithium-free aluminium 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 aluminium alloy as well as improve strength and fatigue characteristics.
  • the substantially lithium-free aluminium alloy may then be aged to complete the precipitation hardening process.
  • the substantially lithium-free aluminium alloy may display increased strength characteristics compared an aluminium 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 aluminium, which is commonly known by the industry standard designation of aluminium 2014.
  • the term "about” in this context only refers to +/- 0.15%.
  • the substantially lithium-free aluminium alloy may also have improved toughness compared to aluminium 2014, for example, and be more resistant to deformation or fracturing under load.
  • the substantially lithium-free aluminium alloy may further have improved thermal stability over aluminium 2014 in response to higher silver levels contained in the substantially lithium-free aluminium alloy.
  • aluminium 2014 may be used in environments that repeatedly reach temperatures of approximately 300°F (149°C).
  • the substantially lithium-free aluminium 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 aluminium alloy displays improved fracture toughness, for example over aluminium 2014, as the amount of silver in the substantially lithium-free aluminium alloy increases.
  • the substantially lithium-free aluminium alloy is more resistant to stress corrosion cracking than aluminium 2014 because of the higher silver content in the substantially lithium-free aluminium alloy.
  • the substantially lithium-free aluminium alloy may also be substantially vanadium free.
  • the substantially lithium-free aluminium alloy may further have reduced weight and improved fatigue characteristics over aluminium 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)
  • Forging (AREA)
  • Heat Treatment Of Articles (AREA)
EP15166597.3A 2014-05-06 2015-05-06 Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver Revoked EP2942412B1 (en)

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

Publications (2)

Publication Number Publication Date
EP2942412A1 EP2942412A1 (en) 2015-11-11
EP2942412B1 true EP2942412B1 (en) 2016-11-16

Family

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Family Applications (1)

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EP15166597.3A Revoked EP2942412B1 (en) 2014-05-06 2015-05-06 Forged aerospace products from lithium-free aluminium alloy containing copper magnesium and silver

Country Status (4)

Country Link
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

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GB1320271A (en) 1971-01-29 1973-06-13 Atomic Energy Authority Uk Aluminium 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
US4474060A (en) 1982-07-12 1984-10-02 Goodyear Aerospace Corporation Torque readout sensor
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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JP2001181771A (ja) 1999-12-20 2001-07-03 Kobe Steel Ltd 高強度耐熱アルミニウム合金材
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EP1522600A1 (en) 2003-09-26 2005-04-13 Kabushiki Kaisha Kobe Seiko Sho Forged aluminium alloy material having excellent high temperature fatigue strength
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CA2843325A1 (en) 2011-08-17 2013-02-21 Otto Fuchs Kg Heat-resistant al-cu-mg-ag alloy and process for producing a semifinished part or product composed of such an aluminum alloy
JP2013142168A (ja) 2012-01-11 2013-07-22 Furukawa-Sky Aluminum Corp 耐クリープ特性に優れたアルミニウム合金
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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GB1320271A (en) 1971-01-29 1973-06-13 Atomic Energy Authority Uk Aluminium alloys
US4474060A (en) 1982-07-12 1984-10-02 Goodyear Aerospace Corporation Torque readout sensor
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
US5652063A (en) 1995-03-22 1997-07-29 Aluminum Company Of America Sheet or plate product made from a substantially vanadium-free aluminum alloy
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JP2001181771A (ja) 1999-12-20 2001-07-03 Kobe Steel Ltd 高強度耐熱アルミニウム合金材
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EP1522600A1 (en) 2003-09-26 2005-04-13 Kabushiki Kaisha Kobe Seiko Sho Forged aluminium alloy material having excellent high temperature fatigue strength
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WO2007111634A2 (en) 2005-09-07 2007-10-04 Alcoa Inc. 2000 series aluminium alloys with enhanced damage tolerance performance for aerospace applications aluminium-legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung fur luftfahrtanwendungen
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EP1780313A2 (en) 2005-10-25 2007-05-02 Goodrich Corporation Treated Aluminum Article And Method For Making Same
US7527872B2 (en) 2005-10-25 2009-05-05 Goodrich Corporation Treated aluminum article and method for making same
WO2011133248A2 (en) 2010-04-20 2011-10-27 Alcoa Inc. High strength forged aluminum alloy products
CA2843325A1 (en) 2011-08-17 2013-02-21 Otto Fuchs Kg Heat-resistant al-cu-mg-ag alloy and process for producing a semifinished part or product composed of such an aluminum alloy
JP2013142168A (ja) 2012-01-11 2013-07-22 Furukawa-Sky Aluminum Corp 耐クリープ特性に優れたアルミニウム合金
WO2013186635A2 (en) 2012-05-02 2013-12-19 Borealis Technical Limited Aircraft wheel bearing arrangement

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Also Published As

Publication number Publication date
RU2015116924A (ru) 2016-11-27
CA2886124A1 (en) 2015-11-06
RU2015116924A3 (ru) 2018-11-02
EP2942412A1 (en) 2015-11-11
US20150322556A1 (en) 2015-11-12

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