WO2004003244A1 - Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges - Google Patents
Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges Download PDFInfo
- Publication number
- WO2004003244A1 WO2004003244A1 PCT/EP2002/007193 EP0207193W WO2004003244A1 WO 2004003244 A1 WO2004003244 A1 WO 2004003244A1 EP 0207193 W EP0207193 W EP 0207193W WO 2004003244 A1 WO2004003244 A1 WO 2004003244A1
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- WO
- WIPO (PCT)
- Prior art keywords
- alloy
- weight
- semi
- finished product
- content
- Prior art date
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 88
- 239000000956 alloy Substances 0.000 title claims abstract description 88
- 239000011265 semifinished product Substances 0.000 title claims abstract description 33
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 11
- 229910000861 Mg alloy Inorganic materials 0.000 title abstract 2
- 229910001316 Ag alloy Inorganic materials 0.000 title description 2
- 239000010936 titanium Substances 0.000 claims abstract description 13
- 239000010949 copper Substances 0.000 claims abstract description 12
- 239000011572 manganese Substances 0.000 claims abstract description 12
- 239000011777 magnesium Substances 0.000 claims abstract description 11
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims abstract description 10
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims abstract description 10
- 229910052719 titanium Inorganic materials 0.000 claims abstract description 10
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 9
- 229910052748 manganese Inorganic materials 0.000 claims abstract description 9
- 230000003068 static effect Effects 0.000 claims abstract description 9
- 229910052802 copper Inorganic materials 0.000 claims abstract description 8
- 239000000203 mixture Substances 0.000 claims abstract description 8
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 7
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052749 magnesium Inorganic materials 0.000 claims abstract description 7
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 7
- 239000010703 silicon Substances 0.000 claims abstract description 7
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims abstract description 6
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052709 silver Inorganic materials 0.000 claims abstract description 6
- 239000004332 silver Substances 0.000 claims abstract description 6
- 229910000914 Mn alloy Inorganic materials 0.000 claims abstract description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 3
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 3
- 238000005242 forging Methods 0.000 claims description 7
- 238000000034 method Methods 0.000 claims description 7
- 238000010791 quenching Methods 0.000 claims description 6
- 230000000171 quenching effect Effects 0.000 claims description 6
- 238000000137 annealing Methods 0.000 claims description 4
- OWXLRKWPEIAGAT-UHFFFAOYSA-N [Mg].[Cu] Chemical compound [Mg].[Cu] OWXLRKWPEIAGAT-UHFFFAOYSA-N 0.000 claims description 3
- 238000005275 alloying Methods 0.000 claims description 3
- 238000013007 heat curing Methods 0.000 claims description 3
- 229910052742 iron Inorganic materials 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 2
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 2
- 229910052796 boron Inorganic materials 0.000 claims description 2
- 238000005266 casting Methods 0.000 claims description 2
- 238000009826 distribution Methods 0.000 claims description 2
- 238000002844 melting Methods 0.000 claims description 2
- 230000008018 melting Effects 0.000 claims description 2
- 229920001187 thermosetting polymer Polymers 0.000 claims description 2
- 229910052845 zircon Inorganic materials 0.000 claims description 2
- 229910052726 zirconium Inorganic materials 0.000 claims description 2
- GFQYVLUOOAAOGM-UHFFFAOYSA-N zirconium(iv) silicate Chemical compound [Zr+4].[O-][Si]([O-])([O-])[O-] GFQYVLUOOAAOGM-UHFFFAOYSA-N 0.000 claims description 2
- 238000005096 rolling process Methods 0.000 claims 1
- VSZWPYCFIRKVQL-UHFFFAOYSA-N selanylidenegallium;selenium Chemical compound [Se].[Se]=[Ga].[Se]=[Ga] VSZWPYCFIRKVQL-UHFFFAOYSA-N 0.000 abstract description 2
- 239000004411 aluminium Substances 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 5
- 238000012360 testing method Methods 0.000 description 5
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 229910000951 Aluminide Inorganic materials 0.000 description 3
- 238000009661 fatigue test Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000001556 precipitation Methods 0.000 description 2
- 229910000967 As alloy Inorganic materials 0.000 description 1
- 229910017818 Cu—Mg Inorganic materials 0.000 description 1
- 229910019015 Mg-Ag Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 229910001093 Zr alloy Inorganic materials 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000001723 curing Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
-
- 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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
-
- 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
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
Definitions
- the invention relates to an Al-Cu-Mg-Mn alloy for the production of semi-finished products with high static and dynamic strength properties. Furthermore, the invention relates to a semi-finished product made of such an alloy with high static and dynamic strength properties and a method for producing such a semi-finished product.
- Aluminum alloys AA 2014, AA 2214 which can withstand high static and dynamic loads, are, for example, die forgings for aircraft wheel and brake systems made from these AI alloys in the heat-hardened state. While the stated strength properties of the semi-finished products made from such an alloy are inherent in the semi-finished product, especially at lower temperatures, these properties decrease more rapidly at temperatures of more than 100 ° C. than in the case of alloys of group AA 2618. Semi-finished products made from such alloys have a higher Heat resistance and are used, for example, as compressor wheels for rechargeable diesel engines or for rotors in ultracentrifuges. At temperatures below 100 ° C, however, the aluminum alloys of groups AA 2014 and AA 2214 can withstand higher loads.
- Compressor wheels have started to use titanium alloys so that the compressor wheels made from them are given the necessary static and dynamic strength properties even at higher temperatures.
- titanium is expensive and in particular also not suitable for the production of aircraft wheels for this reason.
- titanium is less suitable as a wheel material due to its limited thermal conductivity.
- the alloy has the following composition:
- zirconium (Zr) 0.1 - 0.25% by weight of zirconium (Zr)
- the claimed alloy has a higher static and dynamic heat resistance and an improved creep resistance with very good fracture mechanical properties. These are achieved in particular with a copper-magnesium ratio between 5 and 9.5, in particular with a ratio between 6.3 and 9.3.
- the cup The content is preferably between 3.8 and 4.2% by weight and the magnesium content between 0.45 and 0.6% by weight.
- the copper content is significantly below the maximum solubility for copper in the presence of the claimed magnesium content. As a result, the proportion of insoluble, copper-containing phases is very low, taking into account the other alloying and accompanying elements. This results in an improvement in the dynamic properties and the fracture toughness of the semi-finished products made from such an alloy.
- part of the claimed alloy is silver with contents between 0.3 and 0.7% by weight, preferably 0.45 and 0.6% by weight.
- silicon (0.3-0.7% by weight, preferably 0.4-0.6% by weight)
- curing takes place using the same mechanisms as in silver-free Al-Cu-Mg alloys.
- the addition process is different for smaller silicon contents due to the addition of silver.
- the semi-finished products made from such an alloy do have good heat resistance and creep resistance in cooler conditions; however, they do not yet meet the desired requirements. Only silicon contents above 0.3% by weight suppress the otherwise typical change in the precipitation behavior of Al-Cu-Mg-Ag alloys, so that surprisingly higher strength values without sacrificing heat resistance and creep resistance in the Cu and Mg contents according to the invention are achievable.
- the manganese content of the claimed alloy is 0.1 to 0.5% by weight, preferably 0.2-0.4% by weight.
- the manganese content is limited to 0.4% by weight.
- manganese is an alloy component required for structural control.
- the zirconium alloy contains between 0.10 - 0.25% by weight.
- aluminides are even more finely dispersed than man- gan aluminides.
- zirconium aluminides contribute to the thermal stability of the alloy.
- titanium for grain refining, 0.05-0.15% by weight, preferably 0.10-0.15% by weight, of titanium is added to the alloy.
- the titanium is expediently added to the alloy in the form of an Al-5Ti-1 B master alloy, as a result of which the alloy automatically contains boron. This forms finely divided, insoluble titanium diborides. These contribute to the thermal stability of the alloy.
- the alloy can have a maximum of 0.15% iron, preferably 0.10% iron.
- Fig. 1 A diagram showing the 0.2% proof stress and the
- Fig. 3 a diagram showing the 0.2% proof stress and the
- 4a, 4b Diagrams illustrating the fatigue strength of the alloy according to the invention in comparison to a previously known alloy in the state T6 at room temperature and at a temperature of 200 ° C.
- Table 1 below gives the chemical composition of four alloys according to the invention (B, C, D, E) and the composition of the comparatively examined alloys AA 2214 and AA 2618 again (data in% by weight) (nb: not determined):
- Semi-finished products were produced from these alloys by the process steps given below: a) casting an ingot from an alloy, b) homogenizing the cast ingot at a temperature which is as close as possible to the melting point of the alloy for a time which is sufficiently long In order to achieve the most uniform possible distribution of the alloy elements in the cast structure, c) hot forming of the homogenized ingot by forging at a block temperature of about 420 ° C, d) solution annealing of the semi-finished product formed by forging at temperatures that are sufficiently high to allow for the Bring the necessary alloying elements evenly distributed in the structure in solution, whereby the solution annealing takes place in a temperature range at 505 ° C over a period of 3 hours, e) quenching the solution-annealed semi-finished product in water at room temperature, f) cold forming the quenched halves euge by cold upsetting by 1 to 2% and g) heat-curing the quenched semi-finished product at temperatures at 170 ° C over a
- L longitudinal direction: parallel to the main direction of deformation
- LT long transverse direction: parallel to the width direction
- ST short transverse direction: parallel to the thickness direction.
- the improved strengths of the alloy according to the invention can be clearly seen from Tables 2 and 3.
- the previously known alloy AA 2214 shows good strength values at room temperature, but not at higher temperatures.
- the creep resistance and the fracture toughness are not only better at room temperature but in particular also at higher temperatures with the claimed alloy than with the previously known alloys.
- This comparison also shows that the previously known alloys examined only have good properties with respect to individual strength parameters. In no case do they have good properties at all relevant strength values both at room temperature and at elevated temperatures. Just like the fatigue properties, the creep resistance of this previously known alloy is unsatisfactory. All of the strength parameters examined have very good properties and can only be determined in the alloy according to the invention.
- alloy E alloy according to the invention
- AA 2214 and AA 2618 previously known alloys
- the hot-forming step is carried out at a block temperature between 320 ° C and 460 ° C.
- the step of quenching the solution-annealed semifinished product can take place in a temperature range between room temperature and 100 ° C. (boiling) in water. It is also possible to use a water-glycol mixture for quenching, but the temperature of which should not exceed 50 ° C.
- thermosetting can be carried out over a period of 5 to 35 hours, preferably between 10 and 25 hours, in a temperature window between 170 ° C. and 210 ° C.
- continuous cast ingots were produced as described above and aircraft wheels were die-forged in the fore and finished dies at a temperature of 410 to 430 ° C. These wheels were then solution annealed at 505 ° C, quenched in a water-glycol mixture at room temperature and aged for 20 hours at 170 ° C.
- Fatigue tests on comparable samples of the two alloys mentioned also show that the wheels made from the claimed alloy achieve significantly better values than those made from the wheels made with the AA 2214 alloy. This applies to fatigue tests carried out at room temperature (cf. FIG. 4a) and to fatigue tests which were carried out at a test temperature of 200 ° C. (cf. FIG. 4b).
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Forging (AREA)
- Conductive Materials (AREA)
- Powder Metallurgy (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU2002368060A AU2002368060A1 (en) | 2002-06-29 | 2002-06-29 | Al/cu/mg/ag alloy with si, semi-finished product made from such an alloy and method for production of such a semi-finished product |
EP02751094A EP1518000B1 (de) | 2002-06-29 | 2002-06-29 | Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges |
PCT/EP2002/007193 WO2004003244A1 (de) | 2002-06-29 | 2002-06-29 | Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges |
US10/501,574 US7214279B2 (en) | 2002-06-29 | 2002-06-29 | Al/Cu/Mg/Ag alloy with Si, semi-finished product made from such an alloy and method for production of such a semi-finished product |
DE50204136T DE50204136D1 (de) | 2002-06-29 | 2002-06-29 | Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges |
AT02751094T ATE303457T1 (de) | 2002-06-29 | 2002-06-29 | Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2002/007193 WO2004003244A1 (de) | 2002-06-29 | 2002-06-29 | Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004003244A1 true WO2004003244A1 (de) | 2004-01-08 |
Family
ID=29797107
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2002/007193 WO2004003244A1 (de) | 2002-06-29 | 2002-06-29 | Al-cu-mg-ag-legierung mit si, halbzeug aus einer solchen legierung sowie verfahren zur herstellung eines solchen halbzeuges |
Country Status (6)
Country | Link |
---|---|
US (1) | US7214279B2 (de) |
EP (1) | EP1518000B1 (de) |
AT (1) | ATE303457T1 (de) |
AU (1) | AU2002368060A1 (de) |
DE (1) | DE50204136D1 (de) |
WO (1) | WO2004003244A1 (de) |
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EP1776486A2 (de) * | 2004-07-15 | 2007-04-25 | Alcoa Inc. | Legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung für luft- und raumfahrtanwendungen |
WO2007111634A2 (en) * | 2005-09-07 | 2007-10-04 | Alcoa Inc. | 2000 series aluminium alloys with enhanced damage tolerance performance for aerospace applications aluminium-legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung fur luftfahrtanwendungen |
RU2455529C2 (ru) * | 2006-04-29 | 2012-07-10 | Ёрликон Лайбольд Вакуум Гмбх | Ротор или статор турбомолекулярного насоса |
DE102013219050B3 (de) * | 2013-09-23 | 2015-01-22 | Oerlikon Leybold Vacuum Gmbh | Hochleistungsrotoren einer Turbomolekularpumpe |
WO2015040022A1 (de) | 2013-09-23 | 2015-03-26 | Oerlikon Leybold Vacuum Gmbh | Legierungen von rotoren einer turbomolekularpumpe |
US9353430B2 (en) | 2005-10-28 | 2016-05-31 | Shipston Aluminum Technologies (Michigan), Inc. | Lightweight, crash-sensitive automotive component |
US10240228B2 (en) | 2011-08-17 | 2019-03-26 | Otto Fuchs Kg | Heat-resistant Al—Cu—Mg—Ag alloy and process for producing a semifinished part or product composed of such an aluminum alloy |
US10280497B2 (en) | 2014-03-04 | 2019-05-07 | Otto Fuchs Kommanditgesellschaft | Aluminium bronze alloy, method for the production thereof and product made from aluminium bronze |
US10316398B2 (en) | 2014-05-16 | 2019-06-11 | Otto Fuchs Kommanditgesellschaft | High-tensile brass alloy and alloy product |
CN109898000A (zh) * | 2019-03-29 | 2019-06-18 | 郑州轻研合金科技有限公司 | 一种超高强耐热铝合金及其制备方法 |
US10570484B2 (en) | 2016-05-20 | 2020-02-25 | Otto Fuchs Kommanditgesellschaft | High tensile brass alloy and high tensile brass alloy product |
US11359263B2 (en) | 2016-05-20 | 2022-06-14 | Otto Fuchs Kommanditgesellschaft | Lead-free high tensile brass alloy and high tensile brass alloy product |
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RU2461643C1 (ru) * | 2011-06-20 | 2012-09-20 | Открытое акционерное общество "Раменское приборостроительное конструкторское бюро" (ОАО "РПКБ") | Способ термической стабилизации размеров деталей прецизионных приборов из закаленного алюминиевого сплава д20 |
US20150252454A1 (en) * | 2011-09-12 | 2015-09-10 | Alex Cho | High strength al-cu-mg-ag-si alloy for cast product structural applications |
US20150322556A1 (en) | 2014-05-06 | 2015-11-12 | Goodrich Corporation | Lithium free elevated temperature aluminum copper magnesium silver alloy for forged aerospace products |
CN103981410B (zh) * | 2014-05-27 | 2016-07-27 | 中南大学 | 一种高耐损伤铝合金及其制备方法 |
US9786440B2 (en) | 2014-12-17 | 2017-10-10 | Avx Corporation | Anode for use in a high voltage electrolytic capacitor |
CN108103373B (zh) * | 2017-12-28 | 2019-11-19 | 中南大学 | 一种含银Al-Cu-Mg合金及获得高强度P织构的热处理方法 |
US11009074B1 (en) * | 2019-11-11 | 2021-05-18 | Aktiebolaget Skf | Lightweight bearing cage for turbine engines and method of forming a lightweight bearing cage |
JP7469072B2 (ja) * | 2020-02-28 | 2024-04-16 | 株式会社神戸製鋼所 | アルミニウム合金鍛造材及びその製造方法 |
CN114855039B (zh) * | 2021-02-03 | 2023-06-23 | 中国石油化工股份有限公司 | 一种Al-Cu-Mg-Ag合金及其制备方法和应用 |
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GB1320271A (en) * | 1971-01-29 | 1973-06-13 | Atomic Energy Authority Uk | Aluminium alloys |
JPH03107440A (ja) * | 1989-09-20 | 1991-05-07 | Showa Alum Corp | ロードセル用アルミニウム合金 |
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2002
- 2002-06-29 DE DE50204136T patent/DE50204136D1/de not_active Expired - Lifetime
- 2002-06-29 WO PCT/EP2002/007193 patent/WO2004003244A1/de not_active Application Discontinuation
- 2002-06-29 EP EP02751094A patent/EP1518000B1/de not_active Expired - Lifetime
- 2002-06-29 AU AU2002368060A patent/AU2002368060A1/en not_active Abandoned
- 2002-06-29 AT AT02751094T patent/ATE303457T1/de not_active IP Right Cessation
- 2002-06-29 US US10/501,574 patent/US7214279B2/en not_active Expired - Lifetime
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GB1320271A (en) * | 1971-01-29 | 1973-06-13 | Atomic Energy Authority Uk | Aluminium alloys |
JPH03107440A (ja) * | 1989-09-20 | 1991-05-07 | Showa Alum Corp | ロードセル用アルミニウム合金 |
Non-Patent Citations (4)
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DATABASE CA [online] CHEMICAL ABSTRACTS SERVICE, COLUMBUS, OHIO, US; POLMEAR, I. J. ET AL: "After Concorde. Evaluation of an Al-Cu-Mg-Ag alloy for use in the proposed European supersonic transport", XP002227161, retrieved from STN Database accession no. 126:49942 * |
DAVIS J R: "Aluminum and Aluminum Alloys", March 1996, ASM SPECIALTY HANDBOOK. ALUMINUM AND ALUMINUM ALLOYS, ISBN: 0-87170-496-X, PAGE(S) 247-249,254-257,291-305,309-320, USA, XP002227160 * |
MATERIALS SCIENCE FORUM (1996), 217-222(PT. 3, ALUMINIUM ALLOYS, PT. 3), 1759-1764, XP009003900 * |
PATENT ABSTRACTS OF JAPAN vol. 015, no. 293 (C - 0853) 25 July 1991 (1991-07-25) * |
Cited By (19)
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EP1776486A4 (de) * | 2004-07-15 | 2009-09-30 | Alcoa Inc | Legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung für luft- und raumfahrtanwendungen |
EP1776486A2 (de) * | 2004-07-15 | 2007-04-25 | Alcoa Inc. | Legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung für luft- und raumfahrtanwendungen |
EP2458026A1 (de) * | 2004-07-15 | 2012-05-30 | Alcoa Inc. | 2000-Serie-Legierungen mit erhöhter Schadenstoleranzleistung für Luftfahrtanwendungen |
US7449073B2 (en) * | 2004-07-15 | 2008-11-11 | Alcoa Inc. | 2000 Series alloys with enhanced damage tolerance performance for aerospace applications |
US7547366B2 (en) * | 2004-07-15 | 2009-06-16 | Alcoa Inc. | 2000 Series alloys with enhanced damage tolerance performance for aerospace applications |
CN101410540B (zh) * | 2005-09-07 | 2013-03-06 | 美铝公司 | 用于航空应用的具有提高损伤容限性能的2000系列铝合金 |
WO2007111634A2 (en) * | 2005-09-07 | 2007-10-04 | Alcoa Inc. | 2000 series aluminium alloys with enhanced damage tolerance performance for aerospace applications aluminium-legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung fur luftfahrtanwendungen |
WO2007111634A3 (en) * | 2005-09-07 | 2007-12-06 | Alcoa Inc | 2000 series aluminium alloys with enhanced damage tolerance performance for aerospace applications aluminium-legierungen der 2000er-serie mit verbesserter schadenstoleranzleistung fur luftfahrtanwendungen |
US9353430B2 (en) | 2005-10-28 | 2016-05-31 | Shipston Aluminum Technologies (Michigan), Inc. | Lightweight, crash-sensitive automotive component |
RU2455529C2 (ru) * | 2006-04-29 | 2012-07-10 | Ёрликон Лайбольд Вакуум Гмбх | Ротор или статор турбомолекулярного насоса |
US10240228B2 (en) | 2011-08-17 | 2019-03-26 | Otto Fuchs Kg | Heat-resistant Al—Cu—Mg—Ag alloy and process for producing a semifinished part or product composed of such an aluminum alloy |
DE102013219050B3 (de) * | 2013-09-23 | 2015-01-22 | Oerlikon Leybold Vacuum Gmbh | Hochleistungsrotoren einer Turbomolekularpumpe |
DE102013219043A1 (de) | 2013-09-23 | 2015-03-26 | Oerlikon Leybold Vacuum Gmbh | Legierungen von Rotoren einer Turbomolekularpumpe |
WO2015040022A1 (de) | 2013-09-23 | 2015-03-26 | Oerlikon Leybold Vacuum Gmbh | Legierungen von rotoren einer turbomolekularpumpe |
US10280497B2 (en) | 2014-03-04 | 2019-05-07 | Otto Fuchs Kommanditgesellschaft | Aluminium bronze alloy, method for the production thereof and product made from aluminium bronze |
US10316398B2 (en) | 2014-05-16 | 2019-06-11 | Otto Fuchs Kommanditgesellschaft | High-tensile brass alloy and alloy product |
US10570484B2 (en) | 2016-05-20 | 2020-02-25 | Otto Fuchs Kommanditgesellschaft | High tensile brass alloy and high tensile brass alloy product |
US11359263B2 (en) | 2016-05-20 | 2022-06-14 | Otto Fuchs Kommanditgesellschaft | Lead-free high tensile brass alloy and high tensile brass alloy product |
CN109898000A (zh) * | 2019-03-29 | 2019-06-18 | 郑州轻研合金科技有限公司 | 一种超高强耐热铝合金及其制备方法 |
Also Published As
Publication number | Publication date |
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US20050115645A1 (en) | 2005-06-02 |
EP1518000A1 (de) | 2005-03-30 |
AU2002368060A1 (en) | 2004-01-19 |
EP1518000B1 (de) | 2005-08-31 |
ATE303457T1 (de) | 2005-09-15 |
US7214279B2 (en) | 2007-05-08 |
DE50204136D1 (de) | 2005-10-06 |
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