CA2398667C - Non-age-hardening aluminum alloy as a semifinished material for structures - Google Patents
Non-age-hardening aluminum alloy as a semifinished material for structures Download PDFInfo
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- CA2398667C CA2398667C CA2398667A CA2398667A CA2398667C CA 2398667 C CA2398667 C CA 2398667C CA 2398667 A CA2398667 A CA 2398667A CA 2398667 A CA2398667 A CA 2398667A CA 2398667 C CA2398667 C CA 2398667C
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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
- C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
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- Hard Magnetic Materials (AREA)
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Abstract
The present invention relates to the chemical composition of alloys, in particular naturally hard semifinished-material alloys, which are intended to be used in this form as material for semifinished materials.
Proposed is a naturally hard aluminum alloy for semifinished materials which, in addition to magnesium, titanium, beryllium, zirconium, scandium, and cerium, is also made of manganese, copper, zinc, and an element group containing iron and silicon, the ratio of iron to silicon being in the range of 1 to 5.
Proposed is a naturally hard aluminum alloy for semifinished materials which, in addition to magnesium, titanium, beryllium, zirconium, scandium, and cerium, is also made of manganese, copper, zinc, and an element group containing iron and silicon, the ratio of iron to silicon being in the range of 1 to 5.
Description
NON-AGE-HARDENING ALUMINUM ALLOY AS A SEMIFINISHED MATERIAL
FOR STRUCTURES
The present invention relates to the composition of alloys, in particular naturally hard semifinished-material alloys, which are intended to be used in this form as material for structures.
Naturally hard aluminum alloys are used in metallurgy as semifinished materials for structures (see GOST standard 4784-74), but primarily in the form of AMg6 alloy, which contains the following (in % by weight):
magnesium 5.8 - 6.8 manganese 0.5 - 0.8 titanium 0.02 - 0.1 beryllium 0.0002 - 0.005 aluminum balance However, such an alloy does not have adequate physical properties, in particular a low 0.2% yield strength in the case of cold-formed and hot-formed semifinished materials.
A naturally hard aluminum alloy, which is used as a semifinished material for structures (see the patent RU No.
2085607, IPC class C22 C 21/06), also belongs to the related art as a prototype having the following chemical composition (% by weight):
magnesium 3.9 - 4.9 titanium 0.01 -0.1 beryllium 0.0001 - 0.005 zirconium 0.05 - 0.15 scandium 0.20 - 0.50 cerium 0.001 - 0.004 aluminum balance This known alloy does not have sufficient static and dynamic strength, while having high processibility during the manufacturing process, high corrosion resistance, good weldability, and a high readiness for operation under low-temperature conditions.
The subject matter of the present invention is a new, naturally hard aluminum alloy for semifinished materials which, in addition,to magnesium, titanium, beryllium, zirconium, scandium, and cerium, is also made of manganese, copper, zinc, and an element group containing iron and silicon, in the following composition of the components (weight%), the ratio of iron to silicon being in the range of 1 to 5:
magnesium 5.0 - 5.6 titanium 0.01 - 0.05 beryllium 0.0001 - 0.005 zirconium 0.05 - 0.15 scandium 0.18 - 0.30 cerium 0.001 - 0.004 manganese 0.05 - 0.18 copper 0.05 - 0.15 zinc 0.05 - 0.15 element group including iron and silicon 0.04 - 0.24 aluminum balance The alloy of the present invention is distinguished from the conventional one by its addition of manganese, copper, zinc, and an element [chemical] group containing iron and silicon, the components having the following proportions (weighto), and the ratio of iron to silicon having to be between 1 and 5:
magnesium 5.0 - 5.6 titanium 0.01 - 0.05 beryllium 0.0001 - 0.005 zirconium 0.05 - 0.15 scandium 0.18 - 0.30 cerium 0.001 - 0.004 manganese 0.05 - 0.18 copper 0.05 - 0.15 zinc 0.05 - 0.15 element group including iron and silicon 0.04 - 0.24 aluminum balance The technical effect.consists in the improvement of the static and dynamic physical properties of the alloy, which means that the service life, operational reliability, and weight value of the structures subjected to static and dynamic loads improve, in particular those of the structures of various aircraft and spacecraft, including craft that burn cryogenic fuel.
Due to the present invention's proportions between the chemical levels and the chemical constituents, the alloy has a rather ductile matrix, which is made up of a mixed crystal of dissolved magnesium, manganese, copper, and zinc in aluminum.
The particularly high readiness of the alloy for operation under cyclical dynamic loads is due to the high ductility of the matrix. Secondary precipitation of finely distributed intermetallic particles, which contain aluminum, scandium, zirconium, titanium, and other transition metals occurring in the alloy, provides for both the high static strength of the alloy and a high resistance to crack propagation during cyclical loading. The setpoint value of the ratio of iron to silicon optimizes the morphology of the primary intermetallic compounds, which result from the solidification, are principally made of aluminum, iron, and silicon, and provide for an improvement in the static strength of the alloy, while its dynamic strength and plasticity are maintained.
Example Using A85 aluminum, MG90 magnesium, copper MO, zinc TsO, binary key alloys such as aluminum-titanium, aluminum-beryllium, aluminum-zirconium, aluminum-scandium, aluminum-cerium, aluminum-manganese, aluminum-iron, and silumin as an additive, the melt was prepared in an electric oven, on which 165 x 550 mm flat ingots of the alloy according to the present invention were cast with the aid of semicontinuous casting techniques (Table 1); the ingots having a minimum (composition 1), optimum (composition 2), and maximum (composition 3) proportion of constituents, including proportions of the constituents going beyond the present limitations (compositions 4 and 5), as well as the conventional alloy (composition 6) (see Table 1).
If the alloy is prepared under metallurgical production conditions, then scrap metal made of aluminum-magnesium alloys may be used as an additive.
The ingots were homogenized and machined to a thickness of 140 mm. They were subsequently hot-rolled to a thickness of 7 mm at a temperature of 400 C and then cold-rolled to a thickness of 4 mm. The cold-rolled sheets were heat-treated in an electric oven. The heat-treated sheets were used as test material.
Standard transverse specimens taken out [Standard specimens cross-cut out] of the sheets were used to determine the static tensile strength (R,,,, R.po,2, A) and the dynamic strength:
- number of cycles to failure (N) in determining the short-term strength (LCF), for which specimens having a notch factor of Kt = 2.5 and a maximum stress amaX = 160 MPa are used;
- crack-propagation speed da/dN in a range of the stress intensity factor AK = 31.2 MPamo.s;
- critical stress intensity factor Kc in the state of planar [two-dimensional] stress, the width (B) of the specimen being 160 mm.
All tests were conducted at room temperature.
The test results are listed in Table 2.
Table 2 verifies that the alloy of the present invention has a higher static and dynamic strength than the conventional alloy. This allows one to reduce the weight of the structures made of the alloy according to the present invention by 10 to 15%, in order to reduce operating costs, which is particularly important to the aircraft industry. The high readiness of the alloy according to the present invention to operate under static and dynamic conditions, as well as the fact that the alloy according to the present invention is a naturally hard alloy having a high corrosion resistance and good weldability, allows one to use it for the construction of completely new aircraft and spacecraft, sea-going vessels, land-bound vehicles, and other vehicles whose structural elements are joined by welding. The alloy according to the present invention may be used as base material in welded structures, and as a welding additive for welded connections.
FOR STRUCTURES
The present invention relates to the composition of alloys, in particular naturally hard semifinished-material alloys, which are intended to be used in this form as material for structures.
Naturally hard aluminum alloys are used in metallurgy as semifinished materials for structures (see GOST standard 4784-74), but primarily in the form of AMg6 alloy, which contains the following (in % by weight):
magnesium 5.8 - 6.8 manganese 0.5 - 0.8 titanium 0.02 - 0.1 beryllium 0.0002 - 0.005 aluminum balance However, such an alloy does not have adequate physical properties, in particular a low 0.2% yield strength in the case of cold-formed and hot-formed semifinished materials.
A naturally hard aluminum alloy, which is used as a semifinished material for structures (see the patent RU No.
2085607, IPC class C22 C 21/06), also belongs to the related art as a prototype having the following chemical composition (% by weight):
magnesium 3.9 - 4.9 titanium 0.01 -0.1 beryllium 0.0001 - 0.005 zirconium 0.05 - 0.15 scandium 0.20 - 0.50 cerium 0.001 - 0.004 aluminum balance This known alloy does not have sufficient static and dynamic strength, while having high processibility during the manufacturing process, high corrosion resistance, good weldability, and a high readiness for operation under low-temperature conditions.
The subject matter of the present invention is a new, naturally hard aluminum alloy for semifinished materials which, in addition,to magnesium, titanium, beryllium, zirconium, scandium, and cerium, is also made of manganese, copper, zinc, and an element group containing iron and silicon, in the following composition of the components (weight%), the ratio of iron to silicon being in the range of 1 to 5:
magnesium 5.0 - 5.6 titanium 0.01 - 0.05 beryllium 0.0001 - 0.005 zirconium 0.05 - 0.15 scandium 0.18 - 0.30 cerium 0.001 - 0.004 manganese 0.05 - 0.18 copper 0.05 - 0.15 zinc 0.05 - 0.15 element group including iron and silicon 0.04 - 0.24 aluminum balance The alloy of the present invention is distinguished from the conventional one by its addition of manganese, copper, zinc, and an element [chemical] group containing iron and silicon, the components having the following proportions (weighto), and the ratio of iron to silicon having to be between 1 and 5:
magnesium 5.0 - 5.6 titanium 0.01 - 0.05 beryllium 0.0001 - 0.005 zirconium 0.05 - 0.15 scandium 0.18 - 0.30 cerium 0.001 - 0.004 manganese 0.05 - 0.18 copper 0.05 - 0.15 zinc 0.05 - 0.15 element group including iron and silicon 0.04 - 0.24 aluminum balance The technical effect.consists in the improvement of the static and dynamic physical properties of the alloy, which means that the service life, operational reliability, and weight value of the structures subjected to static and dynamic loads improve, in particular those of the structures of various aircraft and spacecraft, including craft that burn cryogenic fuel.
Due to the present invention's proportions between the chemical levels and the chemical constituents, the alloy has a rather ductile matrix, which is made up of a mixed crystal of dissolved magnesium, manganese, copper, and zinc in aluminum.
The particularly high readiness of the alloy for operation under cyclical dynamic loads is due to the high ductility of the matrix. Secondary precipitation of finely distributed intermetallic particles, which contain aluminum, scandium, zirconium, titanium, and other transition metals occurring in the alloy, provides for both the high static strength of the alloy and a high resistance to crack propagation during cyclical loading. The setpoint value of the ratio of iron to silicon optimizes the morphology of the primary intermetallic compounds, which result from the solidification, are principally made of aluminum, iron, and silicon, and provide for an improvement in the static strength of the alloy, while its dynamic strength and plasticity are maintained.
Example Using A85 aluminum, MG90 magnesium, copper MO, zinc TsO, binary key alloys such as aluminum-titanium, aluminum-beryllium, aluminum-zirconium, aluminum-scandium, aluminum-cerium, aluminum-manganese, aluminum-iron, and silumin as an additive, the melt was prepared in an electric oven, on which 165 x 550 mm flat ingots of the alloy according to the present invention were cast with the aid of semicontinuous casting techniques (Table 1); the ingots having a minimum (composition 1), optimum (composition 2), and maximum (composition 3) proportion of constituents, including proportions of the constituents going beyond the present limitations (compositions 4 and 5), as well as the conventional alloy (composition 6) (see Table 1).
If the alloy is prepared under metallurgical production conditions, then scrap metal made of aluminum-magnesium alloys may be used as an additive.
The ingots were homogenized and machined to a thickness of 140 mm. They were subsequently hot-rolled to a thickness of 7 mm at a temperature of 400 C and then cold-rolled to a thickness of 4 mm. The cold-rolled sheets were heat-treated in an electric oven. The heat-treated sheets were used as test material.
Standard transverse specimens taken out [Standard specimens cross-cut out] of the sheets were used to determine the static tensile strength (R,,,, R.po,2, A) and the dynamic strength:
- number of cycles to failure (N) in determining the short-term strength (LCF), for which specimens having a notch factor of Kt = 2.5 and a maximum stress amaX = 160 MPa are used;
- crack-propagation speed da/dN in a range of the stress intensity factor AK = 31.2 MPamo.s;
- critical stress intensity factor Kc in the state of planar [two-dimensional] stress, the width (B) of the specimen being 160 mm.
All tests were conducted at room temperature.
The test results are listed in Table 2.
Table 2 verifies that the alloy of the present invention has a higher static and dynamic strength than the conventional alloy. This allows one to reduce the weight of the structures made of the alloy according to the present invention by 10 to 15%, in order to reduce operating costs, which is particularly important to the aircraft industry. The high readiness of the alloy according to the present invention to operate under static and dynamic conditions, as well as the fact that the alloy according to the present invention is a naturally hard alloy having a high corrosion resistance and good weldability, allows one to use it for the construction of completely new aircraft and spacecraft, sea-going vessels, land-bound vehicles, and other vehicles whose structural elements are joined by welding. The alloy according to the present invention may be used as base material in welded structures, and as a welding additive for welded connections.
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Claims
1. A naturally hard aluminum alloy as a semifinished material for a structure, comprising:
magnesium from 5.0 to 5.6 weight percent;
titanium from 0.01 to 0.05 weight percent;
beryllium from 0.0001 to 0.005 weight percent;
zirconium from 0.05 to 0.15 weight percent;
scandium from 0.18 to 0.30 weight percent;
cerium from 0.001 to 0.004 weight percent;
manganese from 0.05 to 0.18 weight percent;
copper from 0.05 to 0.15 weight percent;
zinc from 0.05 to 0.15 weight percent;
0.04 to 0.24 weight percent total iron and silicon, wherein the ratio of iron to silicon is in a range of 1 to 5;
a balance of aluminum.
magnesium from 5.0 to 5.6 weight percent;
titanium from 0.01 to 0.05 weight percent;
beryllium from 0.0001 to 0.005 weight percent;
zirconium from 0.05 to 0.15 weight percent;
scandium from 0.18 to 0.30 weight percent;
cerium from 0.001 to 0.004 weight percent;
manganese from 0.05 to 0.18 weight percent;
copper from 0.05 to 0.15 weight percent;
zinc from 0.05 to 0.15 weight percent;
0.04 to 0.24 weight percent total iron and silicon, wherein the ratio of iron to silicon is in a range of 1 to 5;
a balance of aluminum.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP00128050A EP1217085B1 (en) | 2000-12-21 | 2000-12-21 | Non hardenable aluminium alloy as semi-product for structures |
| EP00128050.2 | 2000-12-21 | ||
| PCT/EP2001/014797 WO2002050325A1 (en) | 2000-12-21 | 2001-12-14 | Non-hardenable aluminium alloy as a semi-finished product for structures |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2398667A1 CA2398667A1 (en) | 2002-06-27 |
| CA2398667C true CA2398667C (en) | 2010-05-18 |
Family
ID=8170749
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2398667A Expired - Fee Related CA2398667C (en) | 2000-12-21 | 2001-12-14 | Non-age-hardening aluminum alloy as a semifinished material for structures |
Country Status (9)
| Country | Link |
|---|---|
| EP (1) | EP1217085B1 (en) |
| JP (1) | JP4212893B2 (en) |
| CN (1) | CN1173059C (en) |
| AT (1) | ATE251231T1 (en) |
| CA (1) | CA2398667C (en) |
| DE (1) | DE50003940D1 (en) |
| ES (1) | ES2207459T3 (en) |
| RU (1) | RU2277603C2 (en) |
| WO (1) | WO2002050325A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10450634B2 (en) | 2015-02-11 | 2019-10-22 | Scandium International Mining Corporation | Scandium-containing master alloys and method for making the same |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8852365B2 (en) * | 2009-01-07 | 2014-10-07 | The Boeing Company | Weldable high-strength aluminum alloys |
| CN102912199A (en) * | 2012-10-29 | 2013-02-06 | 虞海香 | Aluminum alloy sheet for vehicle body |
| CN104313414A (en) * | 2014-11-06 | 2015-01-28 | 广西柳州银海铝业股份有限公司 | Aluminum-magnesium alloy and preparation method of plate of aluminum-magnesium alloy |
| EP3181711B1 (en) | 2015-12-14 | 2020-02-26 | Apworks GmbH | Aluminium alloy containing scandium for powder metallurgy technologies |
| RU2636781C2 (en) * | 2015-12-25 | 2017-11-28 | ООО "СМВ Инжиниринг" | High-strength thermally non-strengthened aluminium alloy and method for its production |
| EP3556875B1 (en) * | 2018-04-18 | 2020-12-16 | Newfrey LLC | Fastener made of aluminium alloy comprising scandium |
| RU2726520C1 (en) * | 2019-09-03 | 2020-07-14 | федеральное государственное автономное образовательное учреждение высшего образования "Самарский национальный исследовательский университет имени академика С.П. Королёва" | Welded thermally non-hardened alloy based on al-mg system |
| CN113231601A (en) * | 2021-04-15 | 2021-08-10 | 安徽天平机械股份有限公司 | Reduction gearbox shell casting method |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2038405C1 (en) * | 1993-02-19 | 1995-06-27 | Всероссийский научно-исследовательский институт авиационных материалов | Aluminium-base alloy |
| FR2717827B1 (en) * | 1994-03-28 | 1996-04-26 | Jean Pierre Collin | Aluminum alloy with high Scandium contents and process for manufacturing this alloy. |
| RU2085607C1 (en) * | 1995-06-30 | 1997-07-27 | Борис Иванович Бондарев | Deformable thermally cryogenic unreinforced aluminium- based alloy |
| US6531004B1 (en) * | 1998-08-21 | 2003-03-11 | Eads Deutschland Gmbh | Weldable anti-corrosive aluminium-magnesium alloy containing a high amount of magnesium, especially for use in aviation |
-
2000
- 2000-12-21 ES ES00128050T patent/ES2207459T3/en not_active Expired - Lifetime
- 2000-12-21 DE DE50003940T patent/DE50003940D1/en not_active Expired - Lifetime
- 2000-12-21 AT AT00128050T patent/ATE251231T1/en not_active IP Right Cessation
- 2000-12-21 EP EP00128050A patent/EP1217085B1/en not_active Expired - Lifetime
-
2001
- 2001-12-14 JP JP2002551202A patent/JP4212893B2/en not_active Expired - Fee Related
- 2001-12-14 RU RU2003116892/02A patent/RU2277603C2/en not_active IP Right Cessation
- 2001-12-14 WO PCT/EP2001/014797 patent/WO2002050325A1/en active Application Filing
- 2001-12-14 CN CNB018053572A patent/CN1173059C/en not_active Expired - Fee Related
- 2001-12-14 CA CA2398667A patent/CA2398667C/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10450634B2 (en) | 2015-02-11 | 2019-10-22 | Scandium International Mining Corporation | Scandium-containing master alloys and method for making the same |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1217085A1 (en) | 2002-06-26 |
| RU2277603C2 (en) | 2006-06-10 |
| JP2004516385A (en) | 2004-06-03 |
| ES2207459T3 (en) | 2004-06-01 |
| WO2002050325A1 (en) | 2002-06-27 |
| EP1217085B1 (en) | 2003-10-01 |
| JP4212893B2 (en) | 2009-01-21 |
| CN1404533A (en) | 2003-03-19 |
| CN1173059C (en) | 2004-10-27 |
| ATE251231T1 (en) | 2003-10-15 |
| CA2398667A1 (en) | 2002-06-27 |
| DE50003940D1 (en) | 2003-11-06 |
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