US3561954A - Aluminum-base alloys - Google Patents

Aluminum-base alloys Download PDF

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Publication number
US3561954A
US3561954A US707024A US3561954DA US3561954A US 3561954 A US3561954 A US 3561954A US 707024 A US707024 A US 707024A US 3561954D A US3561954D A US 3561954DA US 3561954 A US3561954 A US 3561954A
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US
United States
Prior art keywords
germanium
alloys
magnesium
alloy
copper
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Expired - Lifetime
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US707024A
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English (en)
Inventor
Greville B Brook
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Fulmer Research Institute Ltd
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Fulmer Research Institute Ltd
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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

Definitions

  • This invention relates to aluminium-base alloys containing a strengthening element such as copper as a major alloying constituent, especially aluminium-base alloys containing magnesium in addition.
  • Aluminium-base alloys containing a strengthening alloying element such as copper as a major alloying constituent, and both copper and magnesium as major alloying constituents, are used extensively because of their desirable mechanical and physical properties and ease of manufacture. Recently they have found increasing use as Creep-resistant materials.
  • Such alloys respond to heat treatment at high temperatures of 450 to 550 C. depending on composition (usually called solution treatment), followed by rapid cooling to temperatures below 2.5a C. after which the alloys may be aged either at room temperature (natural ageing) or at elevated temperature (artificial ageing) to increase their strength. Artificial ageing produces more rapid hardening and enables the maximum strength to be attained. It may he necessary to deform the alloy, e.-g. for convenience in manufacture or to assist hardening, vand this is preferably carried out as soon as possible after rapid cooling following solution treatment and before the maximum hardness is reached.
  • the present invention provides an aluminum lbase alloy which consists essentially of 0.2% to 0.5% germanium, 0.1% to A0.5% magnesium, 2% to 7% copper and the balance essentially aluminum.
  • the preferred amount .of germanium is 0.2% to 0.4%, and more ⁇ particularly 0.02% to 0.25%.
  • the preferred amount of copper is 4.0% to 6.5%
  • any silicon present does not exceed ⁇ 0.5% any manganese present does not exceed 1% and any ironl present does not exceed 0.5
  • the alloys of the present invention may thus contain other elements, whether as impurities or as additions for modifying certain properties, provided that the impuritiesvor additions are not such as to prevent fthe attainment of the beneficial effects described herein.
  • silicon may be present in an amount up to 0.1% for alloys where avoidance-of room temperature aging is required, or in excess of 0.1% where easy fabrication is not of great importance, but resistance to .creep following artificial aging is required.
  • any of the known precipitate or grain reners may be added to the alloys of the present invention, lfor example, silver, titanium, chromium, vanadium or zirconium, for the purpose of modifying grain size or their effect on recrystallization behavior.
  • the aforesaid beneficial effects are (i) that the rate of hardening and maximum hardness attained on natural ageing are very much reduced so that it is not necessary to carry out operations involving deformation immediately after quenching from solution treatment; (ii) that the rate of hardening to maximum hardness and maximum mechanical properties on artificial ageing is considerably higher than in alloysfree from magnesium or germanium7 or containing either magnesium ,or germanium alone; and (iii) that the resistance to overageing at elevated temperatures especially during creep is better than in comparable alloys without magnesium plus germanium.
  • Alloy A increased in hardness from 83 D.P.N. to 92 D.P.N. whereas the hardness of Alloy B remained constant at 81 D.P.N. After 23 days the hardness of Alloy A had risen to 116, and Alloy B to 99 D.P.N.
  • the lower rate of hardening of the alloy containing magnesium, plus germanium is also shown by measureo ments of mechanical properties of forged bars solution treated at 530 C., quenched in Coldwater, and aged for 32 days at ambient temperature.
  • Alloy B containing germanium with magnesium not only has higher mechanical properties attained in a shorter ageing time at 170 C. or 190 C. but ages more slowly at room temperature after solution treatment.
  • FIG. 1 Ageing curves for Alloys A and B at 165 C. are also shown in FIG. 1. Similar effects are shown with somewhat lower copper contents and with alloys made from high purity aluminum.
  • FIG. 2 shows the hardness ageing erties in adding more than 0.2% germanium. The presence of silicon does not interfere with the effect of the combined magnesium plus germanium additions. Even in the presence of silicon, as little as 0.02% germanium causes a significant improvement in maximum strength and,y as in silicon-free alloys, there is only little advantage in adding more than about ⁇ 0.2% germanium.
  • Alloy B also shows more resistance to creep at temperatures in the region of 150 C. Forged bars of Alloy A and Alloy B 'were quenched from 530 C. into water and aged 24 hours and 116 hours respectively at 170 C. They A comparison of Alloys C, D and E shows that the presence of silicon does not interfere with the beneficial effect of magnesium plus germanium. A comparison of Alloys F and G shows that the only effect of further additions of germanium is further acceleration of hardening without any major increases. f f
  • One effect of silicon is to increase the amount of hardening occurring at ambient temperature after quenching from solution treatment. Whilst this is undesirable if the material is to be formed before ageing aty higher temperatures, there are circumstances when such hardening B 0.045 is desirable, e.g. after welding solution treated and aged material, when some strengthening of the re-solution treated and quenching zone is required without subsequent articial ageing of the whole structure.
  • the alloys according to the invention when intended for fabrication or welding, are solution treated at 530 C. and quenched in water before the fabrication or welding.
  • the alloys may be aged at temperatures in the range 150 C. to 2110" C. following the solution treatment.
  • An aluminum base alloy consisting essentially of 0.02% to 0.5% germanium, 0.1% to 0.5% magnesium, 2% to 7% copper and the balance essentially aluminum.
  • An aluminum base alloy according to claim 1 containing nickel in an amount up to 2.5% and iron in an amount up to 1.5%.
  • An aluminum base alloy according to claim 1 containing silicon in an amount up to 0.1%
  • An aluminum base alloy according to claim 1 containing silicon in an amount in excess of 0.1% and up to 0.5
  • A11 aluminum base alloy consisting essentially of 0.02% to 0.4% germanium, 0.1% to 0.5% magnesium, 4.0% to 6.5% copper and the balance essentially aluminum.
  • An aluminum base alloy according to claim 9 con taining 0.02% to 0.25% germanium.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Conductive Materials (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Manufacture And Refinement Of Metals (AREA)
  • Silicon Compounds (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)
US707024A 1967-02-27 1968-02-19 Aluminum-base alloys Expired - Lifetime US3561954A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9285/67A GB1211563A (en) 1967-02-27 1967-02-27 Improvements relating to aluminium-base alloys

Publications (1)

Publication Number Publication Date
US3561954A true US3561954A (en) 1971-02-09

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Family Applications (1)

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US707024A Expired - Lifetime US3561954A (en) 1967-02-27 1968-02-19 Aluminum-base alloys

Country Status (11)

Country Link
US (1) US3561954A (fr)
AT (1) AT305661B (fr)
BE (1) BE711370A (fr)
CH (1) CH515997A (fr)
DE (1) DE1608148C3 (fr)
DK (1) DK130356B (fr)
FR (1) FR1602294A (fr)
GB (1) GB1211563A (fr)
NL (1) NL139564B (fr)
NO (1) NO122344B (fr)
SE (1) SE331584B (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5376192A (en) * 1992-08-28 1994-12-27 Reynolds Metals Company High strength, high toughness aluminum-copper-magnesium-type aluminum alloy
US5630889A (en) * 1995-03-22 1997-05-20 Aluminum Company Of America Vanadium-free aluminum alloy suitable for extruded aerospace products
US5980657A (en) * 1998-03-10 1999-11-09 Micron Technology, Inc. Alloy for enhanced filling of high aspect ratio dual damascene structures
US6130156A (en) * 1998-04-01 2000-10-10 Texas Instruments Incorporated Variable doping of metal plugs for enhanced reliability
US6316356B1 (en) 1998-03-10 2001-11-13 Micron Technology, Inc. Thermal processing of metal alloys for an improved CMP process in integrated circuit fabrication
US6368427B1 (en) 1999-09-10 2002-04-09 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US20030010411A1 (en) * 2001-04-30 2003-01-16 David Mitlin Al-Cu-Si-Ge alloys
US20030204423A1 (en) * 2002-04-29 2003-10-30 Walter Koller Appraisal processing
US6645321B2 (en) 1999-09-10 2003-11-11 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US20100089502A1 (en) * 2007-03-14 2010-04-15 Aleris Aluminum Koblenz Gmbh Al-Cu ALLOY PRODUCT SUITABLE FOR AEROSPACE APPLICATION

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011122958A1 (fr) 2010-03-30 2011-10-06 Norsk Hydro Asa Alliage d'aluminium stable à haute température

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5376192A (en) * 1992-08-28 1994-12-27 Reynolds Metals Company High strength, high toughness aluminum-copper-magnesium-type aluminum alloy
US5630889A (en) * 1995-03-22 1997-05-20 Aluminum Company Of America Vanadium-free aluminum alloy suitable for extruded aerospace products
US6774035B2 (en) 1998-03-10 2004-08-10 Micron Technology, Inc. Thermal processing of metal alloys for an improved CMP process in integrated circuit fabrication
US5980657A (en) * 1998-03-10 1999-11-09 Micron Technology, Inc. Alloy for enhanced filling of high aspect ratio dual damascene structures
US6297156B1 (en) 1998-03-10 2001-10-02 Micron Technology, Inc. Method for enhanced filling of high aspect ratio dual damascene structures
US6316356B1 (en) 1998-03-10 2001-11-13 Micron Technology, Inc. Thermal processing of metal alloys for an improved CMP process in integrated circuit fabrication
US6784550B2 (en) 1998-03-10 2004-08-31 Micron Technology, Inc. Thermal processing of metal alloys for an improved CMP process in integrated circuit fabrication
US6130156A (en) * 1998-04-01 2000-10-10 Texas Instruments Incorporated Variable doping of metal plugs for enhanced reliability
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
US20030010411A1 (en) * 2001-04-30 2003-01-16 David Mitlin Al-Cu-Si-Ge alloys
US20030204423A1 (en) * 2002-04-29 2003-10-30 Walter Koller Appraisal processing
US20100089502A1 (en) * 2007-03-14 2010-04-15 Aleris Aluminum Koblenz Gmbh Al-Cu ALLOY PRODUCT SUITABLE FOR AEROSPACE APPLICATION
US8877123B2 (en) 2007-03-14 2014-11-04 Aleris Aluminum Koblenz Gmbh Al—Cu alloy product suitable for aerospace application

Also Published As

Publication number Publication date
DK130356C (fr) 1975-07-07
SE331584B (fr) 1971-01-04
DK130356B (da) 1975-02-10
DE1608148B2 (de) 1973-04-05
CH515997A (de) 1971-11-30
DE1608148A1 (de) 1972-04-20
GB1211563A (en) 1970-11-11
FR1602294A (fr) 1970-11-02
BE711370A (fr) 1968-07-01
NL139564B (nl) 1973-08-15
NO122344B (fr) 1971-06-14
AT305661B (de) 1973-03-12
NL6802648A (fr) 1968-08-28
DE1608148C3 (de) 1973-10-25

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