US3287185A - Process for improving alloys based on aluminum, zinc and magnesium, and alloys obtained thereby - Google Patents
Process for improving alloys based on aluminum, zinc and magnesium, and alloys obtained thereby Download PDFInfo
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- US3287185A US3287185A US323584A US32358463A US3287185A US 3287185 A US3287185 A US 3287185A US 323584 A US323584 A US 323584A US 32358463 A US32358463 A US 32358463A US 3287185 A US3287185 A US 3287185A
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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
- C22C21/10—Alloys based on aluminium with zinc as the next major constituent
Definitions
- the present invention concerns a process for improving alloys based on aluminum, zinc and magnesium, and the alloys obtained by applying this process.
- Alloys are described by symbols prescribed by norm AFNOR number A 02-001 of May 1944; thus the symbol A-ZG describes an alloy containing aluminum, zinc and magnesium, while the symbol A-Z4G describes an alloy theoretically containing 4% of zinc and less than 4% of magnesium, the rest being made up of aluminum.
- alloys are based on aluminum, zinc and magnesium, the other components being optional and being essentially intended to improve the characteristics of the alloy by making the grain fine, by improving the surface of the alloy, its mechanical properties, its capacity for welding, and its suitability for anodic oxidation and surface treatment, and by increasing resistance to corrosion, with or without tension. Components other than those mentioned above may be used to obtain certain special properties.
- alloys have the common feature of being selfhardening; that is to say, they gain desirable characteristics by natural aging, after being made into a solid solution, either by an extrusion operation or separate heat treatment in a range of temperatures from about 350 to 500 C. followed by cooling in air to room temperature or by quenching or rapid cooling.
- the present invention has for its object a process enabling an alloy of which the basic components are aluminum, zinc and magnesium and which has undergone quenching or cooling in air, to be given mechanical properties similar to those obtained in several months of natural aging, but in a treatment that may be carried out within a few days and preferably within 48 hours, and it is a related object to produce new and improved aluminum, zinc and magnesium base alloys and products by the described process.
- cadmium is added to the base alloy and, after the resultant alloy has undergone a quenching or cooling in air operation, it is subjected to an artificial aging treatment at a temperature within the range of to C. for a time which may range from 0 up to 48 hours, and preferably 10 to 48 hours.
- the alloy according to the invention is made up as follows:
- Breaking load R l8 kg./sq. mm.
- Elastic limit E 9 kg./sq. mm.
- Elongation A 22% it hardens slowly after this treatment, and the following characteristics are obtained after 30 to 45 days:
- the alloy has average resistance and great ductility.
- Table I compares the effects of these artificial aging Percent processes, after heat treatment consisting of. heating for Zinc 2.5 to 4 2 hours at 425 followed by cooling in air, firstly on a Magnesium 1.5 to 2.5 conventional A-Z4G alloy, of which the composition is Cadmium 0.005 to 0.5 given above, and secondly on the same alloy with 0.05% Manganese 0 to 0.7 of cadmium added to it; the effect produced on the alloy Chromium 0 to 0.5 containing cadmium by the 24-hour artificial aging process Iron 0 to 0.5 at 160 C. is virtually identical with the efiect produced Titanium- 0 to 0.5 on the conventional alloy by the 200-hour artificial aging 25 Silicon 0 to 0.5 at 100 C. Remainder aluminum plus impurities.
- Percent The amount of cadmium incorporated may be from Zinc 2 to 9 0.005%, constituting a minimum below which no meas Magnesium 0,5 to 3 urable effect can be ascertained, to 0.5%, the upper limit Manganese 0 to 1.5 above which the alloy becomes difiicult to cast.
- the Chromium 0 t 0,5 cadmium has no perceptible undesirable effect on the Titanium 0 to.0.5 welding characteristics or corrosion resistance of the al- Silicon Q t 1 loys.
- the alloys can still hardened by natural aging under Iron 0 t 1 the same conditions as for a corresponding alloy without Zirconium 0 t 0,5 1 cadmium. Copper 0 to 3 It will be understood that the invention includes the Cadmium 0.005 to 0.5
- the alloy has been subjected to a solution heat treatment step which includes quenching or air cooling and which has been artificially aged to a temperature of Remainder aluminum plus impurities.
- the alloy has been subjected to a solution heat treatment step which includes quenching or air cooling 5 6 and which has been artificially aged to a temperature of 2,915,390 12/1959 Criner 75142 100 to 180 C. for a time within the range of 6 to 48 3,031,299 4/1962 Criner 14832.5 hours.
- a solution heat treatment step which includes quenching or air cooling 5 6 and which has been artificially aged to a temperature of 2,915,390 12/1959 Criner 75142 100 to 180 C. for a time within the range of 6 to 48 3,031,299 4/1962 Criner 14832.5 hours.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Preventing Corrosion Or Incrustation Of Metals (AREA)
- Heat Treatments In General, Especially Conveying And Cooling (AREA)
- Heat Treatment Of Articles (AREA)
Description
United States Patent PROCESS FOR IMPROVING ALLOYS BASED ON ALUMINUM, ZINC AND MAGNESIUM, AND AL- LOYS OBTAINED THEREBY Pierre Vachet, Meudon, and Guido-Edgar Perrier, Chambery, France, assignors to Pechiney-Compagnie de groduits Chimiques et Electrometallurgiques, Paris,
rance No Drawing. Filed Nov. 14, 1963, Ser. No. 323,584 Claims priority, applicafionzlrance, Nov. 15, 1962,
915,5 Claims. (Cl. 148-159) The present invention concerns a process for improving alloys based on aluminum, zinc and magnesium, and the alloys obtained by applying this process.
Alloys are described by symbols prescribed by norm AFNOR number A 02-001 of May 1944; thus the symbol A-ZG describes an alloy containing aluminum, zinc and magnesium, while the symbol A-Z4G describes an alloy theoretically containing 4% of zinc and less than 4% of magnesium, the rest being made up of aluminum.
It is known that alloys of the following composition:
have average mechanical and chemical properties, which make them suitable for many uses.
These alloys are based on aluminum, zinc and magnesium, the other components being optional and being essentially intended to improve the characteristics of the alloy by making the grain fine, by improving the surface of the alloy, its mechanical properties, its capacity for welding, and its suitability for anodic oxidation and surface treatment, and by increasing resistance to corrosion, with or without tension. Components other than those mentioned above may be used to obtain certain special properties.
These alloys have the common feature of being selfhardening; that is to say, they gain desirable characteristics by natural aging, after being made into a solid solution, either by an extrusion operation or separate heat treatment in a range of temperatures from about 350 to 500 C. followed by cooling in air to room temperature or by quenching or rapid cooling.
These alloys have great plasticity immediately after solution treatment, but they continue to harden slowly thereafter. The time required to obtain the final mechanical properties, which may be up to three months, often constitutes a serious disadvantage for industrial purposes.
An attempt has therefore been made to proceed with industrial tempering treatments, with the following results:
For alloys based on aluminum, zinc and magnesium without any copper-and wherein the zinc content is from 2% to 4.5%, the classic example being the alloy known as A-Z4G, no treatment of the industrial type has been found to be suitable, since such treatments only give metal mechanical properties which are far inferior to those obtained by natural aging. It is only with artificial aging processes lasting about 200 hours at a temperature of about 100 C. that desirable properties can be obtained, but such processing is commercially undesirable.
In the case of alloys of the same type, but with a zinc content of between 4.5% and 9%, some industrially applicable artificial aging treatments may be found, but these require very exact time and temperature controls, and the time for treatment is still relatively long.
The present invention has for its object a process enabling an alloy of which the basic components are aluminum, zinc and magnesium and which has undergone quenching or cooling in air, to be given mechanical properties similar to those obtained in several months of natural aging, but in a treatment that may be carried out within a few days and preferably within 48 hours, and it is a related object to produce new and improved aluminum, zinc and magnesium base alloys and products by the described process.
In accordance with the practice of this invention, from 0.005% to 0.50% of cadmium is added to the base alloy and, after the resultant alloy has undergone a quenching or cooling in air operation, it is subjected to an artificial aging treatment at a temperature within the range of to C. for a time which may range from 0 up to 48 hours, and preferably 10 to 48 hours.
The alloy according to the invention is made up as follows:
the remainder being aluminum plus small amounts of impurities.
The invention thus defined will now be explained in greater detail with the aid of the following examples, which are given by way of illustration, but not by way of limitation:
An alloy of the type A246 and composed of the following:
Percent Zinc 3 .5 Magnesium 2.0 Manganese 0.3 Chromium 0.15 Iron 0.20 Titanium 0.20 Silicon 0.05 Aluminum 93.60
will be taken as an example; it has the following properties:
it is solution heat treated by cooling in air after being heated to a temperature of 350 to 500 C.; it has great plasticity when freshly treated:
Breaking load R=l8 kg./sq. mm. Elastic limit E=9 kg./sq. mm. Elongation A=22% it hardens slowly after this treatment, and the following characteristics are obtained after 30 to 45 days:
R=35 kg./sq. mm. E=20 kg./sq. mm. A=20% it can easily be welded, the welded zone recovering its mechanical properties due to the self-hardening process; it has good resistance to marine corrosion.
The alloy has average resistance and great ductility.
An attempt was made to obtain the characteristics obtainable by natural aging, by means of a rapid industrial 2. The process as claimed in claim 1 in which the alloy consists esesntially of:
treatment: the following characteristics were found after Percent artificial aging for 200 hours at 100 C.: Zinc 2 to 9 Magnesium 0.5 to 3 g q- Manganese 0 to 1.5 g q- Irlm- Chromium 0 to 0.5 Titanium 0 to 0.5
Silicon 0 to 1 The time required for such treatment is unacceptable Iron 0 to 1 for common commercial practice. 10 Zirconium 0 to 05 In the process described, the above alloy was modified Copper 0 to 3 by adding 0.05% of cadmium. After natural cooling, Cadmium 0005 to 0.5 the alloy was subjected to an industrial artificial aging Remaindm. aluminum plusrimpurities process lasting from about 12 to 24 hours at a temperature of 160 C. The process was effective to produce 15 3. The process as claimed in claim 1 in which the alloy an alloy having satisfactory properties. consists essentially of:
Table I compares the effects of these artificial aging Percent processes, after heat treatment consisting of. heating for Zinc 2.5 to 4 2 hours at 425 followed by cooling in air, firstly on a Magnesium 1.5 to 2.5 conventional A-Z4G alloy, of which the composition is Cadmium 0.005 to 0.5 given above, and secondly on the same alloy with 0.05% Manganese 0 to 0.7 of cadmium added to it; the effect produced on the alloy Chromium 0 to 0.5 containing cadmium by the 24-hour artificial aging process Iron 0 to 0.5 at 160 C. is virtually identical with the efiect produced Titanium- 0 to 0.5 on the conventional alloy by the 200-hour artificial aging 25 Silicon 0 to 0.5 at 100 C. Remainder aluminum plus impurities.
TABLE I Artificial aging 12 hours at 160 0. Artificial aging 24 hours at 160 0.
Alloy E R Percent A E R Percent A kgJsq. mm. kg./sq. mm. kg.lsq. mm. kg./sq. mm.
Conventional A-Z4G- 16. 9 28. 4 19. 5 17. 1 28. 6 17. 8 A-Z4G with cadmium added 25. 9 34. 4 15. 3 27.1 35. s 15. 5
The longer the time between quenching and artificial 4. An alloy having the following composition: aging, the more favorable is the result. Percent The amount of cadmium incorporated may be from Zinc 2 to 9 0.005%, constituting a minimum below which no meas Magnesium 0,5 to 3 urable effect can be ascertained, to 0.5%, the upper limit Manganese 0 to 1.5 above which the alloy becomes difiicult to cast. The Chromium 0 t 0,5 cadmium has no perceptible undesirable effect on the Titanium 0 to.0.5 welding characteristics or corrosion resistance of the al- Silicon Q t 1 loys. The alloys can still hardened by natural aging under Iron 0 t 1 the same conditions as for a corresponding alloy without Zirconium 0 t 0,5 1 cadmium. Copper 0 to 3 It will be understood that the invention includes the Cadmium 0.005 to 0.5
alloy and product thereof and any process in which cadmium is added to an alloy based on aluminum, zinc and magnesium with a view to permitting an artificial aging treatment of industrially acceptable duration to be carried out following a solution treatment by quenching or natural air cooling.
It will be further understood that changes may be made in the details of formulation and methods without departing from the spirit of the invention, especially as defined in the following claims.
Weclaim:
1. In a process of heat treating an aluminum-zinc-magnesium alloy wherein said alloy is solution heat treated followed by quenching or air cooling and artificial aging at a temperature within the range of 100-180 C. for a time within the range of 6 and 48 hours, the improvement comprising the addition of cadmium as an essential alloying element in an amount within the range of 0.005 to 0.5 percent to reduce the time required for artificially aging said alloy.
Remainder aluminum plus impurities.
in which the alloy has been subjected to a solution heat treatment step which includes quenching or air cooling and which has been artificially aged to a temperature of Remainder aluminum plus impurities.
in which the alloy has been subjected to a solution heat treatment step which includes quenching or air cooling 5 6 and which has been artificially aged to a temperature of 2,915,390 12/1959 Criner 75142 100 to 180 C. for a time within the range of 6 to 48 3,031,299 4/1962 Criner 14832.5 hours.
FOREIGN PATENTS References Cited Examiner 5 476,930 12/1937 Great Britain.
UNITED STATES PATENTS 1,785,774 12/1930 Hybinette 148--159 X DAVID RECK Examme" 2,076,577 4/ 1937 Kempf 75-146 C. N. LOVELL, Assistant Examiner.
Claims (1)
1. IN A PROCESS OF HEAT TREATING AN ALUMINUM-ZINC-MAGNESIUM ALLOY WHEREIN SAID ALLOY IS SOLUTION HEAT TREATED FOLLOWED BY QUENCHING OR AIR COOLING AND ARTIFICIAL AGING AT A TEMPERATURE WITHIN THE RANGE OF 100-180*C. FOR A TIME WITHIN THE RANGE OF 6 AND 48 HOURS, THE IMPROVEMENT COMPRISING THE ADDITION OF CADMIUM AS AN ESSENTIAL ALLOYING ELEMENT IN AN AMOUNT WITHIN THE RANGE OF 0.005 TO 0.5 PERCENT TO REDUCE THE TIME REQUIRED FOR ARTIFICIALLY AGING SAID ALLOY.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR915526A FR1347204A (en) | 1962-11-15 | 1962-11-15 | Process for improving aluminum, zinc and magnesium based alloys and alloys obtained |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3287185A true US3287185A (en) | 1966-11-22 |
Family
ID=8790868
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US323584A Expired - Lifetime US3287185A (en) | 1962-11-15 | 1963-11-14 | Process for improving alloys based on aluminum, zinc and magnesium, and alloys obtained thereby |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US3287185A (en) |
| BE (1) | BE639908A (en) |
| CH (1) | CH425240A (en) |
| FR (1) | FR1347204A (en) |
| GB (1) | GB1029486A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3414407A (en) * | 1966-04-26 | 1968-12-03 | Revere Copper & Brass Inc | Aluminum-zinc-magnesium alloy |
| US3620854A (en) * | 1968-02-23 | 1971-11-16 | North American Rockwell | Aluminum casting alloy |
| US4832758A (en) * | 1973-10-26 | 1989-05-23 | Aluminum Company Of America | Producing combined high strength and high corrosion resistance in Al-Zn-MG-CU alloys |
| US4863528A (en) * | 1973-10-26 | 1989-09-05 | Aluminum Company Of America | Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same |
| US5221377A (en) * | 1987-09-21 | 1993-06-22 | Aluminum Company Of America | Aluminum alloy product having improved combinations of properties |
| US5496426A (en) * | 1994-07-20 | 1996-03-05 | Aluminum Company Of America | Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product |
| US5643372A (en) * | 1993-09-28 | 1997-07-01 | Pechiney Rhenalu | Process for the desensitisation to intercrystalline corrosion of 2000 and 6000 series Al alloys and corresponding products |
| US20060174980A1 (en) * | 2004-10-05 | 2006-08-10 | Corus Aluminium Walzprodukte Gmbh | High-strength, high toughness Al-Zn alloy product and method for producing such product |
| US20070204937A1 (en) * | 2005-07-21 | 2007-09-06 | Aleris Koblenz Aluminum Gmbh | Wrought aluminium aa7000-series alloy product and method of producing said product |
| US20080173378A1 (en) * | 2006-07-07 | 2008-07-24 | Aleris Aluminum Koblenz Gmbh | Aa7000-series aluminum alloy products and a method of manufacturing thereof |
| US20080173377A1 (en) * | 2006-07-07 | 2008-07-24 | Aleris Aluminum Koblenz Gmbh | Aa7000-series aluminum alloy products and a method of manufacturing thereof |
| US20090269608A1 (en) * | 2003-04-10 | 2009-10-29 | Aleris Aluminum Koblenz Gmbh | Al-Zn-Mg-Cu ALLOY WITH IMPROVED DAMAGE TOLERANCE-STRENGTH COMBINATION PROPERTIES |
| US20090320969A1 (en) * | 2003-04-10 | 2009-12-31 | Aleris Aluminum Koblenz Gmbh | HIGH STENGTH Al-Zn ALLOY AND METHOD FOR PRODUCING SUCH AN ALLOY PRODUCT |
| CN101243196B (en) * | 2005-07-21 | 2011-01-12 | 阿勒里斯铝业科布伦茨有限公司 | A wrought aluminum aa7000-series alloy product and method of producing said product |
| WO2020214750A1 (en) * | 2019-04-19 | 2020-10-22 | Magna International Inc. | Non-heat-treated casting alloys for automotive structural applications |
| US11879166B2 (en) * | 2018-11-12 | 2024-01-23 | Novelis Koblenz Gmbh | 7XXX-series aluminium alloy product |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1548155A (en) * | 1966-12-26 | 1968-11-29 | ||
| DE1758496B1 (en) * | 1968-06-14 | 1971-09-08 | Vaw Ver Aluminium Werke Ag | COMPOSITE MATERIAL SHEET FOR THE MANUFACTURING OF HOLLOW BODIES |
| JPS4958011A (en) * | 1972-10-06 | 1974-06-05 | ||
| NO144777C (en) * | 1976-06-24 | 1981-11-04 | Alusuisse | CORROSION RESISTANT ALUMINUM ALLOY. |
| ATE217912T1 (en) * | 1997-08-04 | 2002-06-15 | Corus Aluminium Walzprod Gmbh | HIGHLY DEFORMABLE, CORROSION-RESISTANT ALLOY |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1785774A (en) * | 1929-05-18 | 1930-12-23 | Hybinette Patents Corp | Plastic heat-treated aluminum alloy |
| US2076577A (en) * | 1935-12-28 | 1937-04-13 | Aluminum Co Of America | Free cutting alloys |
| GB476930A (en) * | 1936-03-16 | 1937-12-16 | Tennyson Fraser Bradbury | A new aluminium alloy |
| US2915390A (en) * | 1958-01-13 | 1959-12-01 | Aluminum Co Of America | Aluminum base alloy |
| US3031299A (en) * | 1960-08-23 | 1962-04-24 | Aluminum Co Of America | Aluminum base alloy |
-
0
- BE BE639908D patent/BE639908A/xx unknown
-
1962
- 1962-11-15 FR FR915526A patent/FR1347204A/en not_active Expired
-
1963
- 1963-11-14 CH CH1396763A patent/CH425240A/en unknown
- 1963-11-14 US US323584A patent/US3287185A/en not_active Expired - Lifetime
- 1963-11-14 GB GB45034/63A patent/GB1029486A/en not_active Expired
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1785774A (en) * | 1929-05-18 | 1930-12-23 | Hybinette Patents Corp | Plastic heat-treated aluminum alloy |
| US2076577A (en) * | 1935-12-28 | 1937-04-13 | Aluminum Co Of America | Free cutting alloys |
| GB476930A (en) * | 1936-03-16 | 1937-12-16 | Tennyson Fraser Bradbury | A new aluminium alloy |
| US2915390A (en) * | 1958-01-13 | 1959-12-01 | Aluminum Co Of America | Aluminum base alloy |
| US3031299A (en) * | 1960-08-23 | 1962-04-24 | Aluminum Co Of America | Aluminum base alloy |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3414407A (en) * | 1966-04-26 | 1968-12-03 | Revere Copper & Brass Inc | Aluminum-zinc-magnesium alloy |
| US3620854A (en) * | 1968-02-23 | 1971-11-16 | North American Rockwell | Aluminum casting alloy |
| US4832758A (en) * | 1973-10-26 | 1989-05-23 | Aluminum Company Of America | Producing combined high strength and high corrosion resistance in Al-Zn-MG-CU alloys |
| US4863528A (en) * | 1973-10-26 | 1989-09-05 | Aluminum Company Of America | Aluminum alloy product having improved combinations of strength and corrosion resistance properties and method for producing the same |
| US5221377A (en) * | 1987-09-21 | 1993-06-22 | Aluminum Company Of America | Aluminum alloy product having improved combinations of properties |
| US5643372A (en) * | 1993-09-28 | 1997-07-01 | Pechiney Rhenalu | Process for the desensitisation to intercrystalline corrosion of 2000 and 6000 series Al alloys and corresponding products |
| US5496426A (en) * | 1994-07-20 | 1996-03-05 | Aluminum Company Of America | Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product |
| US20090269608A1 (en) * | 2003-04-10 | 2009-10-29 | Aleris Aluminum Koblenz Gmbh | Al-Zn-Mg-Cu ALLOY WITH IMPROVED DAMAGE TOLERANCE-STRENGTH COMBINATION PROPERTIES |
| US10472707B2 (en) | 2003-04-10 | 2019-11-12 | Aleris Rolled Products Germany Gmbh | Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties |
| US20090320969A1 (en) * | 2003-04-10 | 2009-12-31 | Aleris Aluminum Koblenz Gmbh | HIGH STENGTH Al-Zn ALLOY AND METHOD FOR PRODUCING SUCH AN ALLOY PRODUCT |
| US7883591B2 (en) | 2004-10-05 | 2011-02-08 | Aleris Aluminum Koblenz Gmbh | High-strength, high toughness Al-Zn alloy product and method for producing such product |
| US20060174980A1 (en) * | 2004-10-05 | 2006-08-10 | Corus Aluminium Walzprodukte Gmbh | High-strength, high toughness Al-Zn alloy product and method for producing such product |
| CN101243196B (en) * | 2005-07-21 | 2011-01-12 | 阿勒里斯铝业科布伦茨有限公司 | A wrought aluminum aa7000-series alloy product and method of producing said product |
| US20070204937A1 (en) * | 2005-07-21 | 2007-09-06 | Aleris Koblenz Aluminum Gmbh | Wrought aluminium aa7000-series alloy product and method of producing said product |
| US20080210349A1 (en) * | 2006-07-07 | 2008-09-04 | Aleris Aluminum Koblenz Gmbh | Aa2000-series aluminum alloy products and a method of manufacturing thereof |
| US20080173377A1 (en) * | 2006-07-07 | 2008-07-24 | Aleris Aluminum Koblenz Gmbh | Aa7000-series aluminum alloy products and a method of manufacturing thereof |
| US20080173378A1 (en) * | 2006-07-07 | 2008-07-24 | Aleris Aluminum Koblenz Gmbh | Aa7000-series aluminum alloy products and a method of manufacturing thereof |
| US8002913B2 (en) | 2006-07-07 | 2011-08-23 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
| US8088234B2 (en) | 2006-07-07 | 2012-01-03 | Aleris Aluminum Koblenz Gmbh | AA2000-series aluminum alloy products and a method of manufacturing thereof |
| US8608876B2 (en) | 2006-07-07 | 2013-12-17 | Aleris Aluminum Koblenz Gmbh | AA7000-series aluminum alloy products and a method of manufacturing thereof |
| US11879166B2 (en) * | 2018-11-12 | 2024-01-23 | Novelis Koblenz Gmbh | 7XXX-series aluminium alloy product |
| WO2020214750A1 (en) * | 2019-04-19 | 2020-10-22 | Magna International Inc. | Non-heat-treated casting alloys for automotive structural applications |
Also Published As
| Publication number | Publication date |
|---|---|
| GB1029486A (en) | 1966-05-11 |
| FR1347204A (en) | 1963-12-27 |
| BE639908A (en) | |
| CH425240A (en) | 1966-11-30 |
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