WO2012140337A1 - Alliages aluminium cuivre magnesium performants a haute temperature - Google Patents
Alliages aluminium cuivre magnesium performants a haute temperature Download PDFInfo
- Publication number
- WO2012140337A1 WO2012140337A1 PCT/FR2012/000134 FR2012000134W WO2012140337A1 WO 2012140337 A1 WO2012140337 A1 WO 2012140337A1 FR 2012000134 W FR2012000134 W FR 2012000134W WO 2012140337 A1 WO2012140337 A1 WO 2012140337A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- corr
- weight
- product
- alloy
- wrought
- Prior art date
Links
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
- 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
-
- 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
-
- 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
Definitions
- the invention relates to aluminum-copper-magnesium alloy products, more particularly, such products, their manufacturing processes and use, intended to be implemented at high temperature.
- Certain aluminum alloys are commonly used for applications in which they have a high temperature of use, typically between 100 and 200 ° C, for example as structural part or means of attachment near motor in the automotive industry or aerospace or structural part in supersonic aircraft.
- the good mechanical performance at high temperature means in particular on the one hand the thermal stability, that is to say that the mechanical properties measured at room temperature are stable after aging for a long time at the temperature of use, and of on the other hand the hot performance that is to say that the mechanical properties measured at high temperature (static mechanical properties, creep resistance) are high.
- the AA2618 alloy which comprises (% by weight):
- Patent FR 2279852 by CEGEDUR PECHINEY proposes an alloy with a reduced iron and nickel content of the following composition (by weight):
- the alloy may also contain Zr, Mn, Cr, V or Mo at levels less than 0.4%, and optionally Cd, In, Sn or Be less than 0.2% each, Zn less than 8% or Ag less than 1%. With this alloy, a significant improvement in the stress concentration factor K1c representative of the resistance to crack propagation is obtained.
- the patent application EP 0 756 017 A1 (Pechiney Rhenalu) relates to an aluminum alloy with a high creep resistance of composition (% by weight):
- the patent RU2210614C1 describes an alloy of composition (in% by weight)
- Composition AA2219 alloy (in% by weight) Cu: 5.8 - 6.8 Mn: 0.20 - 0.40 Ti: 0.02 - 0.10, Zr: 0.10 - 0.25 V : 0.05 - 0.15 Mg ⁇ 0.02 is also known for high temperature applications.
- Al-Cu-Mg alloys are also known.
- US Pat. No. 3,826,688 teaches an alloy of composition (in% by weight), Cu: 2.9 - 3.7, Mg: 1.3 - 1.7 and Mn: 0.1 - 0.4.
- the patent application EP 0 038 605 A1 teaches an alloy of composition (in% by weight), Cu: 3.8 - 4.4, Mg: 1, 2 - 1.8 and Mn: 0.3 - 0.9 , maximum 0.12 Si, 0.15 Fe, 0.25 Zn, 0.15 Ti and 0.10 Cr.
- a first subject of the invention is a wrought product made of aluminum alloy of composition, in% by weight,
- Another subject of the invention is a method of manufacturing a wrought product according to the invention comprising, successively,
- said alloy typically in the form of a rolling plate, a spinning billet, a bar blank or a wire, optionally homogenizing the product thus cast so as to reach a temperature of between 450 ° C. and 520 ° C.,
- the dissolution of the product thus deformed by a heat treatment making it possible to reach a temperature of between 490 and 520 ° C. and preferably between 500 and 510 ° C. for 15 minutes to 8 hours, and then quenching,
- Yet another object of the invention is the use of a wrought product according to the invention in an application in which said product is maintained at temperatures of 100 ° C. to 200 ° C. for a significant period of at least 200 hours. hours.
- FIG. 1 Representation of the composition domain according to the invention in the plan
- Figure 2 Evolution of the elastic limit R p o, 2 with the aging time for the rolled products of Example 1; Fig 2a: aging at 150 ° C, Fig 2b: aging at 200 ° C, Fig 2c: aging at 250 ° C.
- Figure 3 Evolution of the elastic limit R p o, 2 with the aging time at 150 ° C for the spun products of Example 2; Fig 3a: T6 state, Fig 3b: T8 state. Description of the invention
- the static mechanical characteristics in tension in other words the tensile strength R m , the conventional yield stress at 0.2% elongation R p0 , 2 , and the elongation at break A%, are determined by a tensile test according to standard NF EN ISO 6892-1, the sampling and the direction of the test being defined by the EN 485-1 standard.
- the hot tensile tests are carried out according to standard NF EN 10002-5.
- the creep tests are carried out according to ASTM standard El 39-06. Unless otherwise specified, the definitions of EN 12258 apply.
- the present inventors have found that, surprisingly, there is a compositional range of Al-Cu-Mg alloys containing Mn which makes it possible to obtain particularly high performance wrought products at high temperature.
- composition of the wrought products of the invention is defined according to the content of iron, manganese and silicon.
- Cu Corr and Mg corr Corrected Cu and Mg contents, called Cu Corr and Mg corr corresponding to the contents of these elements which are not trapped by intermetallic compounds containing iron, manganese or silicon, are defined. This correction is important in defining the Cu and Mg composition domain of the invention because the iron and manganese containing intermetallic compounds formed with the copper and the intermetallic compounds formed with the silicon-containing magnesium generally can not be processed. solution.
- Cu corr and Mg corr thus correspond to the Cu and Mg contents available after solution dissolution for the formation during the recovery of the nanometric phases contributing to hardening.
- Cu Corr Cu - 2.28 Fe is calculated.
- the copper and magnesium contents thus corrected must obey the following inequalities: Cu corr> 0.9 (Mg corr ) + 4.3 (preferably Cu corr > - 0.9 ( corr. Mg) + 4.5)
- the magnesium content is such that Mg cor r is between 1.5 and 2.6% by weight and preferably between 1.6 and 2.4% by weight.
- Mg CO rr is at least 1.8% by weight and preferably at least 1.9% by weight. This embodiment is particularly advantageous for products in the T6 state.
- the copper content is such that Cu corr is between 2.6 and 3.7% by weight.
- Cu cor r is at least 2.7% by weight and preferably at least 2.8% by weight.
- the maximum magnesium content is 2.86% by weight corresponding to a Mg content corr of 2.6% by weight, obtained for an Si content of 0.2% by weight.
- the minimum magnesium content is 1.5% by weight, obtained for a Si content of 0% by weight.
- the maximum copper content is 3.69% by weight, obtained for a manganese content of 0.5% by weight and corresponding to a corrected r horn Cu content of 3.29% by weight.
- the corresponding domain in the plane Mg corr : Cu corr is shown in Figure 1.
- an advantageous range of composition of the products according to the invention has a magnesium content of between 1.6 and 2.2% by weight and preferably between 1.8 and 2.1% by weight. and / or a copper content of between 2.8 and 3.7% by weight and preferably between 2.9 and 3.4% by weight.
- the products according to the invention contain 0.2 to 0.5% by weight of manganese, which contributes in particular to the control of the granular structure.
- the present inventors have found that the simultaneous addition of manganese and zirconium is advantageous for further improving the control of the granular structure.
- the Zr content is at least 0.07% by weight and preferably at least 0.08% by weight.
- the products according to the invention contain 0.09 to 0.15% by weight of zirconium and 0.25 to 0.45% by weight of manganese.
- the chromium content is at most 0.25% by weight. In one embodiment of the invention, the chromium content is between 0.05 and 0.25% by weight and can contribute in particular to the control of the granular structure. However, the presence of chromium can cause problems of recycling and sensitivity to quenching, especially for products whose thickness is at least 50 mm. In another embodiment, the chromium content is less than 0.05% by weight.
- the titanium content is between 0.01 and 0.15% by weight.
- the addition of titanium contributes in particular to the refining of the grains during casting. In one embodiment, it is preferred to limit the addition of titanium to a maximum value of 0.05% by weight. However, a larger ripening may be useful. Thus, in another embodiment of the invention, the titanium content is between 0.07 and 0.14% by weight.
- the iron and silicon contents are at most 0.2% by weight each. In an advantageous embodiment of the invention, the iron and / or silicon contents are at most 0.1% by weight and preferably 0.08% by weight.
- the equations for calculating Cu and Mg CO CO rr rr including changes of Fe and Si and to achieve the same value of Cu corr more copper is added when the iron content increases.
- the content of the other elements is less than 0.05% by weight.
- the rest is aluminum.
- the wrought products according to the invention are typically sheets, profiles, bars or wires, but can also be screws, bolts or rivets.
- the method of manufacturing the products according to the invention comprises the successive stages of elaboration of the alloy, casting, optionally homogenization, deformation, dissolution, tempering, optionally cold deformation and tempering.
- a bath of liquid metal is produced so as to obtain an aluminum alloy of composition according to the invention.
- the liquid metal bath is then typically cast in the form of a rolling plate, spinning billet, bar blank or wire.
- the product thus cast is then homogenized so as to reach a temperature of between 450 ° C. and 520 ° C. and preferably between 500 ° C. and 510 ° C. for a period of between 5 and 60 hours.
- the homogenization treatment can be carried out in one or more stages.
- the product is then typically deformed by rolling, spinning and / or drawing and / or drawing and / or coining.
- the product thus deformed is then dissolved in a heat treatment to reach a temperature of between 490 and 520 ° C and preferably between 500 and 510 ° C for 15 min to 8 h, and then quenched.
- the quality of dissolution can be evaluated by calorimetry and / or optical microscopy.
- the objective being that Cu and Mg are in solid solution with the exception of Cu and bound Mg in the intermetallic compounds containing manganese of iron and / or silicon.
- the product can then optionally undergo a cold deformation.
- an income is achieved in which the product reaches a temperature between 160 and 210 ° C and preferably between 175 and 195 ° C for 5 to 100 hours and preferably 10 to 50h.
- the income can be achieved in one or more levels.
- the income conditions are determined so that the mechanical resistance Rpo , 2 is maximum ("peak" income).
- the first embodiment of the process according to the invention comprises the successive stages of elaboration of the alloy, cast in the form of a plate or billet, optionally homogenization, hot deformation, dissolution, tempering, optionally cold deformation and tempering. .
- the liquid metal bath is cast in the form of a rolling plate or a spinning billet.
- the optionally homogenized rolling plate or spinning billet is then hot deformed by rolling or spinning.
- the hot deformation of the first embodiment is performed so as to maintain a temperature of at least 300 ° C.
- a temperature of at least 350 ° C. and preferably at least 380 ° C. is maintained during the hot deformation.
- no significant cold deformation is carried out, in particular by cold rolling, between the hot deformation and the dissolution. Indeed, such a cold deformation step would lead to a recrystallized structure that is undesirable in the context of the invention for wrought products in the form of sheets or profiles.
- Significant cold deformation is typically a deformation of at least about 5%.
- the sheet or the profile thus obtained is then put in solution by a heat treatment making it possible to reach a temperature of between 490 and 520 ° C. and preferably between 500 and 510 ° C. for 15 minutes to 8 hours, and then quenched typically with the water.
- substantially non-recrystallized granular structure means a non-recrystallized granular structure content at mid-thickness greater than 70% and preferably greater than 85%.
- the sheet or the profile obtained can then optionally undergo a cold deformation.
- the cold deformation is a controlled traction with a permanent elongation of 2 to 5% to improve the mechanical strength and to obtain a T8 state after income.
- the sheets and profiles obtained according to the first embodiment of the method of the invention have the advantage of having a high mechanical strength and good performance at high temperature.
- the sheets and profiles according to the invention preferably have, in the longitudinal direction T8, a yield strength R p0 , 2 of at least 440 MPa, preferably at least 450 MPa and, preferably, at least 450 MPa. at least 455 MPa.
- an elastic limit R p o, 2 of at least 470 MPa can advantageously be obtained in the longitudinal direction.
- the reduction of the elastic limit of the sheets and profiles according to the invention in the T8 state in the longitudinal direction is advantageously less than 12%, preferably less than 10% and, preferably, less than 8%.
- the profiles according to the invention advantageously have, in the T8 state, a yield strength measured at 150 ° C. in the longitudinal direction of at least 370 MPa and preferably at least 380 MPa.
- the sheets or profiles made in the embodiment in which the Mg content is such that Mg corr is at least 1.8% by weight advantageously have a yield strength measured at 150 ° C. in the longitudinal direction of at least 340 MPa and a decrease in yield strength after 2000h aging at 150 ° C less than 5%.
- the second embodiment of the method according to the invention comprises the successive stages of elaboration of the alloy, cast in the form of wire blank or bar, optionally homogenization, hot deformation and / or cold by spinning and / or stretching and / or drawing and optionally by subsequent striking of the wire or bar obtained to obtain screws, bolts or rivets, dissolution, quenching and tempering.
- the liquid metal bath is cast as a blank of wire or bar, preferably on a casting wheel, typically with the continuous casting process known as " Properzi ".
- the wire blank or bar may also be a spinning billet.
- the blank wire or bar is then deformed hot and / or cold by spinning and / or drawing and / or drawing.
- the wire blank or bar is a spinning billet, it will be hot-spun before being cold-formed by drawing and / or drawing, whereas if the wire blank or bar has been obtained by continuous casting and hot deformation at the outlet of the casting wheel, it will only be necessary to deform it cold.
- the wire or bar obtained can be struck at this point to obtain screws, bolts or rivets.
- the product thus obtained is then put in solution by a heat treatment making it possible to reach a temperature of between 490 and 520 ° C. and preferably between 500 and 510 ° C. for 15 minutes to 8 hours, and then typically quenched with water. .
- essentially recrystallized structure is meant a recrystallization rate of at least 80% and preferably a fine grain structure and homogeneous size.
- the product obtained can then optionally undergo a cold deformation.
- T6 state has an Mg content such that Mg corr is at least equal to 1.8% by weight.
- the products obtained according to the second embodiment of the process of the invention advantageously have in the T8 state in the longitudinal direction a yield strength R p0 , 2 of at least 460 MPa, preferably at least 480 MPa. and after aging at 150 ° C. for 2000 h, a decrease in the yield strength in the longitudinal direction of less than 10%, preferably less than 8%.
- the products according to the invention are particularly useful for applications in which the products are maintained at temperatures of 100 ° C to 200 ° C, typically at about 150 ° C, for a significant period of at least 200 hours and preferably at least 2000 hours.
- the products according to the invention are useful for fasteners intended for use in a motor typically for automobiles, such as screws or bolts or rivets.
- the products according to the invention are also useful for the manufacture of parts of the nacelle and / or aircraft attachment masts.
- the nacelle designates all the supports and hoods of an engine of a multi-engine aircraft
- the products according to the invention are also useful for the manufacture of aircraft wing leading edges.
- the products according to the invention are also useful for the manufacture of fuselage of supersonic aircraft.
- Alloys A-1 and C-1 have a composition according to the invention.
- composition (% by weight)
- the plates were homogenized at a temperature between 500 ° C. and 540 ° C., adapted according to the alloy, hot rolled to a thickness of 15 mm, dissolved at a temperature of between 500 ° C. and 540 ° C, matched to the alloy, quenched with water by immersion, traced by 3 to 4% and returned to 190 ° C to reach the peak tensile strength limit at T8.
- the alloy plate A-1 was homogenized in two steps of 10 h at 500 ° C. and 20 h at 509 ° C., the sheet obtained after rolling being put in solution for 2 hours at 507 ° C. and returned for 12 hours at 190 ° C.
- the alloy plate B-1 was homogenized in two steps of 10 h at 500 ° C. and then 20 h at 503 ° C., the sheet obtained after rolling being put in solution for 2 h at 500 ° C. and returned for 8 h at 190 ° C.
- the alloy plate C-1 was homogenized in two steps of 10 h at 500 ° C. and 20 h at 503 ° C., the sheet obtained after rolling being put in solution for 2 hours at 504 ° C. and returned for 12 hours at 190 ° C.
- the alloy plate D-1 was homogenized in two steps of 10 h at 500 ° C. and 20 h at 536 ° C., the sheet obtained after rolling being put in solution for 2 h at 535 ° C. and returned for 8 h at 190 ° C.
- the sheets obtained had a substantially non-recrystallized granular structure.
- the sheets thus obtained were characterized in the longitudinal direction before and after aging at several temperatures and for several durations. The results are shown in Table 2 Table 2 - Mechanical properties obtained at mid-thickness L-direction before and after aging (MPa)
- FIGS. 2a to 2c The evolution of the mechanical properties with the aging time for the different temperatures studied are shown in FIGS. 2a to 2c. It can be seen that for an aging temperature of 200 ° C., the sheets according to the invention (A-1 and C-1) have, for 2000 h of aging, an elasticity limit improved by more than 15% with respect to the reference sheets. (B-1 and D-1). 0 Example 2.
- alloys A-2 and C-2 have a composition according to the invention.
- compositions are given in Table 3.
- Table 3 Composition (% by weight)
- the billets were homogenized at a temperature of between 500 ° C. and 520 ° C., adapted according to the alloy and spun into cylindrical bars 13 mm in diameter, dissolved at a temperature of between 500 ° C. and 520 ° C. ° C, adapted in function of the alloy, soaked in water.
- the alloy billet A-2 was homogenized 24h at 508 ° C. and the bars obtained dissolved at 506 ° C.
- the alloy billet C-2 was homogenized 24h at 508 ° C. and the bars obtained dissolved at 503 ° C.
- alloy wires 6056 in the T6 state with a diameter of 12 mm and alloy bars 2618 in the T8 state with a diameter of 40 mm were used.
- the products according to the invention have, in particular, a breaking strength significantly higher than that of conventionally used reference products such as alloy 6056 (T6) or alloy 2618 (T8).
- Creep tests were carried out according to ASTM El 39-06 for a stress of 285 MPa and at a temperature of 150 ° C. In particular, the service life, the deformation after 200h and the stationary creep rate were measured. The results are collated in Table 6.
- a 13 mm diameter C-2 alloy cylindrical bar was obtained by hot spinning from a billet homogenized 24h at 508 ° C. The bar was then stretched cold to obtain a wire of diameter 10; 55 mm. The yarn thus obtained was dissolved for 1 hour at 503 ° C., fractionated by 3 to 4% and then returned for 12 hours at 190 ° C. to obtain a T8 state.
- the granular structure of the yarn thus obtained was essentially recrystallized and had a fine and homogeneous grain
Landscapes
- 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)
- Powder Metallurgy (AREA)
- Forging (AREA)
- Compositions Of Macromolecular Compounds (AREA)
- Extrusion Of Metal (AREA)
- Heat Treatment Of Steel (AREA)
- Connection Of Plates (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2832085A CA2832085C (fr) | 2011-04-15 | 2012-04-06 | Alliages aluminium cuivre magnesium performants a haute temperature |
EP12717140.3A EP2697406B1 (fr) | 2011-04-15 | 2012-04-06 | Alliages aluminium cuivre magnesium performants a haute temperature |
BR112013026381-4A BR112013026381B1 (pt) | 2011-04-15 | 2012-04-06 | Produto forjado em liga de alúminio, e seu processo de fabricação |
CN201280028959.5A CN103608478B (zh) | 2011-04-15 | 2012-04-06 | 高温下性能好的铝铜镁合金 |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201161475806P | 2011-04-15 | 2011-04-15 | |
FR1101187A FR2974118B1 (fr) | 2011-04-15 | 2011-04-15 | Alliages aluminium cuivre magnesium performants a haute temperature |
FR1101187 | 2011-04-15 | ||
US61/475,806 | 2011-04-15 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012140337A1 true WO2012140337A1 (fr) | 2012-10-18 |
Family
ID=44550857
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2012/000134 WO2012140337A1 (fr) | 2011-04-15 | 2012-04-06 | Alliages aluminium cuivre magnesium performants a haute temperature |
Country Status (7)
Country | Link |
---|---|
US (1) | US9869008B2 (fr) |
EP (1) | EP2697406B1 (fr) |
CN (1) | CN103608478B (fr) |
BR (1) | BR112013026381B1 (fr) |
CA (1) | CA2832085C (fr) |
FR (1) | FR2974118B1 (fr) |
WO (1) | WO2012140337A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021245345A1 (fr) | 2020-06-04 | 2021-12-09 | Constellium Issoire | Utilisation de produits en alliage aluminium cuivre magnesium performants a haute temperature |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104164635A (zh) * | 2013-05-17 | 2014-11-26 | 中国石油天然气集团公司 | 一种提高铝合金钻杆用Al-Cu-Mg合金室温强度和高温性能的方法 |
FR3040711B1 (fr) * | 2015-09-03 | 2017-08-11 | Constellium Issoire | Produit extrude en alliage al-cu-mg a compromis ameliore entre resistance mecanique et tenacite |
CN105112748A (zh) * | 2015-09-08 | 2015-12-02 | 苏州慧驰轻合金精密成型科技有限公司 | 一种高强度铸造铝合金及其制备方法 |
CN105170765A (zh) * | 2015-10-29 | 2015-12-23 | 无锡桥阳机械制造有限公司 | 一种镁合金加工工艺 |
CA3032261A1 (fr) | 2016-08-26 | 2018-03-01 | Shape Corp. | Procede de formage a chaud et appareil de pliage transversal d'une poutre d'aluminium profilee pour former a chaud un composant structural de vehicule |
EP3529394A4 (fr) | 2016-10-24 | 2020-06-24 | Shape Corp. | Procédé de formage et de traitement thermique d'un alliage d'aluminium en plusieurs étapes pour la production de composants pour véhicules |
RS58876B1 (sr) * | 2017-02-17 | 2019-08-30 | Drahtwerk Elisental W Erdmann Gmbh & Co | Legura aluminijuma |
CN106929721A (zh) * | 2017-03-29 | 2017-07-07 | 沈阳工业大学 | 一种低热裂倾向的高强度Al‑Cu合金及其制备方法 |
CN107514414A (zh) * | 2017-10-17 | 2017-12-26 | 苏州华丰不锈钢紧固件有限公司 | 一种吊环自攻螺钉 |
US20200407828A1 (en) * | 2018-03-13 | 2020-12-31 | The Penn State Research Foundation | Aluminum alloys for additive manufacturing |
CN109055838A (zh) * | 2018-09-11 | 2018-12-21 | 湖南工业大学 | 一种高强韧的铝合金材料及其在制备弹壳方面的应用 |
CN109158604A (zh) * | 2018-09-11 | 2019-01-08 | 湖南工业大学 | 一种铝合金弹壳制造方法及弹壳 |
CN110484792B (zh) * | 2019-09-27 | 2021-02-26 | 福建省闽发铝业股份有限公司 | 一种提高铝型材抗压强度的熔铸生产工艺 |
US11009074B1 (en) * | 2019-11-11 | 2021-05-18 | Aktiebolaget Skf | Lightweight bearing cage for turbine engines and method of forming a lightweight bearing cage |
CN110724866A (zh) * | 2019-11-28 | 2020-01-24 | 西南铝业(集团)有限责任公司 | 一种2014铝合金航空精密轮毂模锻件的无锆毛坯 |
CN111235443A (zh) * | 2020-03-30 | 2020-06-05 | 天津忠旺铝业有限公司 | 一种低加工变形2系铝合金板材的制备方法 |
CN112143988A (zh) * | 2020-10-14 | 2020-12-29 | 北京科技大学 | 一种通过长期低温时效处理提高Al-Cu-Li合金力学性能的方法 |
CN112342442A (zh) * | 2020-11-23 | 2021-02-09 | 超捷紧固系统(上海)股份有限公司 | 一种用铝制功能连接件与紧固件制造及材料配制方法 |
CN113584362A (zh) * | 2021-07-29 | 2021-11-02 | 山东创新金属科技有限公司 | 一种汽车发动机用耐高温抗腐蚀的铝合金及其制备方法 |
CN114686787B (zh) * | 2022-03-29 | 2023-02-03 | 宁波江丰电子材料股份有限公司 | 含颗粒状富铁相的6061铝合金及其制备方法和气体分配盘 |
CN115449678B (zh) * | 2022-10-20 | 2023-06-09 | 佛山市南海俊隆包装材料有限公司 | 一种防锈铝合金钉线及其生产工艺 |
CN116804261B (zh) * | 2023-08-21 | 2023-12-01 | 成都先进金属材料产业技术研究院股份有限公司 | 一种gh738合金棒材及其制备方法 |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3826688A (en) | 1971-01-08 | 1974-07-30 | Reynolds Metals Co | Aluminum alloy system |
FR2279852A1 (fr) | 1974-07-23 | 1976-02-20 | Cegedur | Alliage d'aluminium de bonne tenue au fluage et de resistance a la propagation des criques amelioree |
EP0038605A1 (fr) | 1980-04-18 | 1981-10-28 | The Boeing Company | Procédé de fabrication, à partir d'un alliage d'aluminium, d'un produit plat ou d'un produit extrude |
US5213639A (en) * | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
WO1994005820A1 (fr) * | 1992-08-28 | 1994-03-17 | Reynolds Metals Company | Alliage d'aluminium resistant contenant du cuivre et du magnesium |
WO1996029440A1 (fr) * | 1995-03-21 | 1996-09-26 | Kaiser Aluminum & Chemical Corporation | Procede de fabrication de toles d'aluminium pour l'aeronautique |
EP0756017A1 (fr) | 1995-07-28 | 1997-01-29 | Pechiney Rhenalu | Alliage aluminium-cuivre-magnésium alloy à résistance élevée au fluage |
WO1999031287A1 (fr) * | 1997-12-12 | 1999-06-24 | Aluminum Company Of America | Alliage d'aluminium a tenacite elevee destine a etre utilise comme plaque dans des applications aerospatiales |
RU2210614C1 (ru) | 2001-12-21 | 2003-08-20 | Региональный общественный фонд содействия защите интеллектуальной собственности | Сплав на основе алюминия, изделие из этого сплава и способ его изготовления |
FR2843754A1 (fr) * | 2002-08-20 | 2004-02-27 | Corus Aluminium Walzprod Gmbh | Alliage ai-cu-mg-si equilibre |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4845543A (en) * | 1983-09-28 | 1989-07-04 | Hitachi, Ltd. | Semiconductor device and method of manufacturing the same |
FR2792001B1 (fr) * | 1999-04-12 | 2001-05-18 | Pechiney Rhenalu | Procede de fabrication de pieces de forme en alliage d'aluminium type 2024 |
FR2925523B1 (fr) * | 2007-12-21 | 2010-05-21 | Alcan Rhenalu | Produit lamine ameliore en alliage aluminium-lithium pour applications aeronautiques |
CA2771585C (fr) * | 2009-09-04 | 2015-11-24 | Alcoa Inc. | Procede de vieillissement d'alliages d'aluminium permettant d'obtenir une performance de protection amelioree contre les balles |
-
2011
- 2011-04-15 FR FR1101187A patent/FR2974118B1/fr not_active Expired - Fee Related
-
2012
- 2012-04-06 WO PCT/FR2012/000134 patent/WO2012140337A1/fr active Application Filing
- 2012-04-06 CA CA2832085A patent/CA2832085C/fr active Active
- 2012-04-06 BR BR112013026381-4A patent/BR112013026381B1/pt active IP Right Grant
- 2012-04-06 CN CN201280028959.5A patent/CN103608478B/zh active Active
- 2012-04-06 EP EP12717140.3A patent/EP2697406B1/fr active Active
- 2012-04-13 US US13/446,617 patent/US9869008B2/en active Active
Patent Citations (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3826688A (en) | 1971-01-08 | 1974-07-30 | Reynolds Metals Co | Aluminum alloy system |
FR2279852A1 (fr) | 1974-07-23 | 1976-02-20 | Cegedur | Alliage d'aluminium de bonne tenue au fluage et de resistance a la propagation des criques amelioree |
EP0038605A1 (fr) | 1980-04-18 | 1981-10-28 | The Boeing Company | Procédé de fabrication, à partir d'un alliage d'aluminium, d'un produit plat ou d'un produit extrude |
US5213639A (en) * | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
WO1994005820A1 (fr) * | 1992-08-28 | 1994-03-17 | Reynolds Metals Company | Alliage d'aluminium resistant contenant du cuivre et du magnesium |
US5593516A (en) | 1992-08-28 | 1997-01-14 | Reynolds Metals Company | High strength, high toughness aluminum-copper-magnesium-type aluminum alloy |
WO1996029440A1 (fr) * | 1995-03-21 | 1996-09-26 | Kaiser Aluminum & Chemical Corporation | Procede de fabrication de toles d'aluminium pour l'aeronautique |
EP0756017A1 (fr) | 1995-07-28 | 1997-01-29 | Pechiney Rhenalu | Alliage aluminium-cuivre-magnésium alloy à résistance élevée au fluage |
WO1999031287A1 (fr) * | 1997-12-12 | 1999-06-24 | Aluminum Company Of America | Alliage d'aluminium a tenacite elevee destine a etre utilise comme plaque dans des applications aerospatiales |
US6444058B1 (en) | 1997-12-12 | 2002-09-03 | Alcoa Inc. | High toughness plate alloy for aerospace applications |
RU2210614C1 (ru) | 2001-12-21 | 2003-08-20 | Региональный общественный фонд содействия защите интеллектуальной собственности | Сплав на основе алюминия, изделие из этого сплава и способ его изготовления |
FR2843754A1 (fr) * | 2002-08-20 | 2004-02-27 | Corus Aluminium Walzprod Gmbh | Alliage ai-cu-mg-si equilibre |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2021245345A1 (fr) | 2020-06-04 | 2021-12-09 | Constellium Issoire | Utilisation de produits en alliage aluminium cuivre magnesium performants a haute temperature |
FR3111143A1 (fr) | 2020-06-04 | 2021-12-10 | Constellium Issoire | Produits en alliage aluminium cuivre magnésium performants à haute température |
Also Published As
Publication number | Publication date |
---|---|
US20120261036A1 (en) | 2012-10-18 |
CA2832085A1 (fr) | 2012-10-18 |
BR112013026381A2 (pt) | 2016-12-27 |
EP2697406A1 (fr) | 2014-02-19 |
FR2974118B1 (fr) | 2013-04-26 |
CN103608478A (zh) | 2014-02-26 |
CA2832085C (fr) | 2019-02-26 |
EP2697406B1 (fr) | 2017-09-13 |
CN103608478B (zh) | 2015-11-25 |
BR112013026381B1 (pt) | 2019-06-25 |
FR2974118A1 (fr) | 2012-10-19 |
US9869008B2 (en) | 2018-01-16 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2697406B1 (fr) | Alliages aluminium cuivre magnesium performants a haute temperature | |
EP1966402B1 (fr) | Tole en aluminium-cuivre-lithium a haute tenacite pour fuselage d'avion | |
EP3201372B1 (fr) | Tôles isotropes en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion et procédé de fabrication de celle-ci | |
EP1766102B1 (fr) | Procede de fabrication de produits en alliage d'aluminium a haute tenacite et haute resistance a la fatigue | |
EP2981632B1 (fr) | Tôles minces en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion | |
FR2838135A1 (fr) | PRODUITS CORROYES EN ALLIAGES A1-Zn-Mg-Cu A TRES HAUTES CARACTERISTIQUES MECANIQUES, ET ELEMENTS DE STRUCTURE D'AERONEF | |
FR3007423A1 (fr) | Element de structure extrados en alliage aluminium cuivre lithium | |
EP4162089B1 (fr) | Utilisation de produits en alliage aluminium cuivre magnesium performants a haute temperature | |
WO2014162068A1 (fr) | Tôles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselages d'avion | |
EP1633900A1 (fr) | Piece de peau de carrosserie automobile en tole d'alliage al-si-mg fixee sur structure acier | |
WO2017064396A1 (fr) | Composant de structure de caisse automobile presentant un excellent compromis entre resistance mecanique et comportement au crash | |
EP3526358A1 (fr) | Toles minces en alliage aluminium-magnesium-scandium pour applications aerospatiales | |
CA3085811A1 (fr) | Procede de fabrication ameliore de toles en alliage d'aluminium-cuivre-lithium pour la fabrication de fuselage d'avion | |
JP2020084278A (ja) | Al−Mg−Si系アルミニウム合金押出引抜材及びその製造方法 | |
WO2002055750A2 (fr) | PRODUITS LAMINES OU FILES EN ALLIAGE D'ALUMINIUM AL-Mn A RESISTANCE A LA CORROSION AMELIOREE | |
WO2018185425A1 (fr) | Procede ameliore de fabrication de composant de structure de caisse automobile | |
FR3132306A1 (fr) | Tôle mince améliorée en alliage d’aluminium-cuivre-lithium | |
WO2003074747A1 (fr) | Tole ou ba 0nde en alliage al-mg pour la fabrication de pieces pliees a faible rayon de pliage | |
CH697192A5 (fr) | Alliage d'Aluminium. |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 12717140 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2832085 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
REEP | Request for entry into the european phase |
Ref document number: 2012717140 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2012717140 Country of ref document: EP |
|
REG | Reference to national code |
Ref country code: BR Ref legal event code: B01A Ref document number: 112013026381 Country of ref document: BR |
|
ENP | Entry into the national phase |
Ref document number: 112013026381 Country of ref document: BR Kind code of ref document: A2 Effective date: 20131014 |