US3561954A - Aluminum-base alloys - Google Patents
Aluminum-base alloys Download PDFInfo
- 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
- Authority
- US
- United States
- Prior art keywords
- germanium
- alloys
- magnesium
- alloy
- copper
- 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.)
- Expired - Lifetime
Links
Images
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
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.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Conductive Materials (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Silicon Compounds (AREA)
- Crystals, And After-Treatments Of Crystals (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
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 |
Family
ID=9869043
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US707024A Expired - Lifetime US3561954A (en) | 1967-02-27 | 1968-02-19 | Aluminum-base alloys |
Country Status (11)
Country | Link |
---|---|
US (1) | US3561954A (it) |
AT (1) | AT305661B (it) |
BE (1) | BE711370A (it) |
CH (1) | CH515997A (it) |
DE (1) | DE1608148C3 (it) |
DK (1) | DK130356B (it) |
FR (1) | FR1602294A (it) |
GB (1) | GB1211563A (it) |
NL (1) | NL139564B (it) |
NO (1) | NO122344B (it) |
SE (1) | SE331584B (it) |
Cited By (10)
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011122958A1 (en) | 2010-03-30 | 2011-10-06 | Norsk Hydro Asa | High temperature stable aluminium alloy |
-
1967
- 1967-02-27 GB GB9285/67A patent/GB1211563A/en not_active Expired
-
1968
- 1968-02-19 US US707024A patent/US3561954A/en not_active Expired - Lifetime
- 1968-02-19 DK DK64968AA patent/DK130356B/da unknown
- 1968-02-22 DE DE1608148A patent/DE1608148C3/de not_active Expired
- 1968-02-23 NL NL686802648A patent/NL139564B/xx unknown
- 1968-02-26 SE SE02471/68A patent/SE331584B/xx unknown
- 1968-02-26 NO NO0686/68A patent/NO122344B/no unknown
- 1968-02-27 FR FR1602294D patent/FR1602294A/fr not_active Expired
- 1968-02-27 BE BE711370D patent/BE711370A/xx unknown
- 1968-02-27 CH CH283368A patent/CH515997A/de not_active IP Right Cessation
- 1968-02-27 AT AT185168A patent/AT305661B/de not_active IP Right Cessation
Cited By (14)
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 |
---|---|
NO122344B (it) | 1971-06-14 |
DK130356C (it) | 1975-07-07 |
NL139564B (nl) | 1973-08-15 |
BE711370A (it) | 1968-07-01 |
DE1608148B2 (de) | 1973-04-05 |
DE1608148C3 (de) | 1973-10-25 |
GB1211563A (en) | 1970-11-11 |
FR1602294A (it) | 1970-11-02 |
NL6802648A (it) | 1968-08-28 |
CH515997A (de) | 1971-11-30 |
DE1608148A1 (de) | 1972-04-20 |
AT305661B (de) | 1973-03-12 |
SE331584B (it) | 1971-01-04 |
DK130356B (da) | 1975-02-10 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4073667A (en) | Processing for improved stress relaxation resistance in copper alloys exhibiting spinodal decomposition | |
US3351463A (en) | High strength nickel-base alloys | |
US4588553A (en) | Aluminium alloys | |
US2950187A (en) | Iron-calcium base alloy | |
CA1228251A (en) | Aluminium alloys | |
US3561954A (en) | Aluminum-base alloys | |
US3402043A (en) | Copper base alloys | |
NO764316L (it) | ||
US4067750A (en) | Method of processing copper base alloys | |
US4063936A (en) | Aluminum alloy having high mechanical strength and elongation and resistant to stress corrosion crack | |
US2783143A (en) | Age-hardenable, copper-base alloy | |
US3318690A (en) | Age hardening manganese-containing maraging steel | |
US6231700B1 (en) | Boron-copper-magnesium-tin alloy and method for making same | |
US2919186A (en) | Uranium alloys | |
US2810641A (en) | Precipitation hardenable copper, nickel, aluminum, zirconium alloys | |
US2586647A (en) | Aluminum alloy | |
US3314829A (en) | High strength pressure die casting alloy | |
US1766871A (en) | Lead alloy | |
US3082082A (en) | High strength, corrosionresistant alloy | |
US3322533A (en) | Aluminum base casting alloys | |
US3330653A (en) | Copper-zirconium-vanadium alloys | |
Hunsicker et al. | Stress-corrosion resistance of high-strength Al-Zn-Mg-Cu alloys with and without silver additions | |
US3384517A (en) | Copper/iron/aluminm alloys | |
US2801167A (en) | Titanium alloy | |
US1991162A (en) | Process for improving coppertitanium alloys |