US3843357A - High strength aluminum alloy - Google Patents

High strength aluminum alloy Download PDF

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Publication number
US3843357A
US3843357A US00392480A US39248073A US3843357A US 3843357 A US3843357 A US 3843357A US 00392480 A US00392480 A US 00392480A US 39248073 A US39248073 A US 39248073A US 3843357 A US3843357 A US 3843357A
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US
United States
Prior art keywords
aluminum
alloy
weight
high strength
less
Prior art date
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Expired - Lifetime
Application number
US00392480A
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English (en)
Inventor
I Niimi
Y Kaneko
Y Komiyama
M Hashimoto
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.)
Toyota Motor Corp
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Toyota Motor Corp
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Publication date
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Publication of US3843357A publication Critical patent/US3843357A/en
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent

Definitions

  • the present invention relates to high strength aluminum alloy for casting having a tensile strength not less than 50 kg/mm. at high temperatures and an elongation not less than 1.5%.
  • the alloy consists of 3.0- 6.0% zinc, 2.0-4.0% magnesium, 01-04% titamum, 0.1-0.4% chromium, 0.020.2% lithium and the balance aluminum and inevitable impurities.
  • copper may be added but not more than 2.0%.
  • aluminum alloy castings having a high tensile strength at room as well as high temperatures are being increasingly required. These alloys are replacing iron materials such as iron castings.
  • aluminumzinc-magnesium alloys have been developed, but they must contain a very large amount of zinc or magnesium in order to attain a tensile strength not less than 50 kg./mrn. 0n the other hand, the alloys containing a large amount of zinc or magnesium are subject to hot cracking during casting or reduction of the stress corrosion resistance. Obviously, such defects render these materials unacceptable.
  • the high strength aluminum alloy of the present invention is used for casting purposes and is directed to and improving the strength of the casting during heating. Hot cracking is prevented, and the weight of casting is reduced.
  • the high strength aluminum casting alloy of the present invention is based on an aluminum-zinc-magnesium alloy to which various elements are added with their amounts being limited as follows.
  • the high strength aluminum casting alloy of the present invention is composed of, by weight, 3.0-6.0% zinc, 2.0-4.0% magnesium, 0.l-0.4% titanium, (Ll-0.4% chromium, 0.02-0.2% lithium, copper not more than 2.0%, and the remainder of aluminum and inevitable impurities.
  • the alloy compositions are indicated in Table 1.
  • high strength aluminum casting alloy of the present invention was not limited to those described and the series of numbers used in the composition of this alloy are referred to in the following experimental examples.
  • the above aluminum alloys with Nos. 1 to 8 were retained, after casting, at 470 C. for 16 hours, immediately followed by quenching (in water at room temperature), and then subjected to an artificial aging at C. for 24 hours, corresponding to H8 T -Temper, and their room temperature tensile strength, high temperature tensile strength and elongation were determined.
  • the T -tempered materials were machined into test pieces having a parallel portion of 8 x 40 mm.
  • test pieces were preheated at the respective temperatures of C., 250 C., and 350 C. for 100 hours, and thereafter the pieces were set to a test machine and retained therein at the respective temperatures for 15 additional minutes before the tension test.
  • test pieces were preheated at the respective temperatures of 150 C., 250 C., and 350 C. for 100 hours prior to the measurement of tensile strength at the respective temperatures.
  • the hot crack test is generally described as follows.
  • the material to be tested is cast into an annular metal mold and its contraction upon solidfying is restricted by a core.
  • the total length of cracks generated thereby is determined. The results are indicated in Table 4.
  • a content of zinc less than 3.0% does not provide a tensile strength not less than 50 kg./mm. while its content exceeding 6.0% adversely affects the castability and the stress corrosion resistance of the material.
  • a content of magnesium less than 2.0% does not provide a tensile strength not less than 50 kg./mm. while its content exceeding adversely affects the castability and the stress corrosion resistance of the material.
  • a content of lithium less than 0.02% decreases the tensile strength at both room temperature and high temperatures, while a content exceeding 0.2% reduces the tensile strength at both room temperature and high temperatures. With more than 0.2% lithium elongation is reduced as well as the eifect for preventing hot cracks. Also, more than 0.2% lithium deteriorates the surface condition of casting.
  • a content of titanium and chromium less than 0.1% each does not produce the effect for preventing the hot crack, while their respective contents exceeding 0.4% lowers the elongation.
  • a high strength aluminum casting alloy having a tensile strength of not less than 50 kg./mm. at room temperatures and an elongation of not less than 1.5%, the alloy consisting substantially of 3.0-6.0% by weight zinc, 2.0-4.0% by weight magnesium, 0.10.4% by weight titanium, 01-04% by weight chromium, 0.02-0.2% by weight lithium, and the balance aluminum and inevitable impurities.
  • a high strength aluminum casting alloy as in claim 1 additionally including not more than 2.0% by weight copper.

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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)
US00392480A 1972-10-31 1973-08-29 High strength aluminum alloy Expired - Lifetime US3843357A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP47109098A JPS5222610B2 (enrdf_load_html_response) 1972-10-31 1972-10-31

Publications (1)

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US3843357A true US3843357A (en) 1974-10-22

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US00392480A Expired - Lifetime US3843357A (en) 1972-10-31 1973-08-29 High strength aluminum alloy

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JP (1) JPS5222610B2 (enrdf_load_html_response)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4172181A (en) * 1977-05-10 1979-10-23 Furukawa Aluminum Co., Ltd. Composite material for vacuum brazing
US6368427B1 (en) 1999-09-10 2002-04-09 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US6645321B2 (en) 1999-09-10 2003-11-11 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US20140251511A1 (en) * 2013-03-09 2014-09-11 Alcoa Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
EP2959029A4 (en) * 2013-02-19 2016-10-05 Alcoa Inc HEAT-TREATABLE ALUMINUM ALLOYS WITH MAGNESIUM AND ZINC AND METHOD FOR THE PRODUCTION THEREOF
CN107815569A (zh) * 2017-09-29 2018-03-20 宁波优适捷传动件有限公司 一种汽车转向节及其制备方法
US12123078B2 (en) 2019-02-20 2024-10-22 Howmet Aerospace Inc. Aluminum-magnesium-zinc aluminum alloys

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110629084B (zh) * 2019-09-23 2021-01-15 山东南山铝业股份有限公司 一种高导热变形铝合金的制备方法及产品

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4172181A (en) * 1977-05-10 1979-10-23 Furukawa Aluminum Co., Ltd. Composite material for vacuum brazing
US6368427B1 (en) 1999-09-10 2002-04-09 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US6645321B2 (en) 1999-09-10 2003-11-11 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
EP2959029A4 (en) * 2013-02-19 2016-10-05 Alcoa Inc HEAT-TREATABLE ALUMINUM ALLOYS WITH MAGNESIUM AND ZINC AND METHOD FOR THE PRODUCTION THEREOF
EP2964799A4 (en) * 2013-03-09 2016-12-21 Alcoa Inc HEAT-TREATABLE ALUMINUM ALLOYS WITH MAGNESIUM AND ZINC AND METHOD FOR THE PRODUCTION THEREOF
US9315885B2 (en) * 2013-03-09 2016-04-19 Alcoa Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
US20140251511A1 (en) * 2013-03-09 2014-09-11 Alcoa Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
US9580775B2 (en) * 2013-03-09 2017-02-28 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
US9850556B2 (en) * 2013-03-09 2017-12-26 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
US20180094339A1 (en) * 2013-03-09 2018-04-05 Arconic Inc. Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same
CN107815569A (zh) * 2017-09-29 2018-03-20 宁波优适捷传动件有限公司 一种汽车转向节及其制备方法
CN107815569B (zh) * 2017-09-29 2019-05-10 宁波优适捷传动件有限公司 一种汽车转向节及其制备方法
US12123078B2 (en) 2019-02-20 2024-10-22 Howmet Aerospace Inc. Aluminum-magnesium-zinc aluminum alloys

Also Published As

Publication number Publication date
JPS5222610B2 (enrdf_load_html_response) 1977-06-18
JPS4965915A (enrdf_load_html_response) 1974-06-26

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