EP1809779A1 - Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür - Google Patents

Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür

Info

Publication number
EP1809779A1
EP1809779A1 EP05805764A EP05805764A EP1809779A1 EP 1809779 A1 EP1809779 A1 EP 1809779A1 EP 05805764 A EP05805764 A EP 05805764A EP 05805764 A EP05805764 A EP 05805764A EP 1809779 A1 EP1809779 A1 EP 1809779A1
Authority
EP
European Patent Office
Prior art keywords
alloy
thickness
rolling plate
refining
blank
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP05805764A
Other languages
English (en)
French (fr)
Other versions
EP1809779B1 (de
Inventor
Bernard Bes
Philippe Jarry
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Constellium Issoire SAS
Original Assignee
Alcan Rhenalu SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alcan Rhenalu SAS filed Critical Alcan Rhenalu SAS
Publication of EP1809779A1 publication Critical patent/EP1809779A1/de
Application granted granted Critical
Publication of EP1809779B1 publication Critical patent/EP1809779B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22B—PRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
    • C22B21/00—Obtaining aluminium
    • C22B21/06—Obtaining aluminium refining
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22B—PRODUCTION AND REFINING OF METALS; PRETREATMENT OF RAW MATERIALS
    • C22B21/00—Obtaining aluminium
    • C22B21/06—Obtaining aluminium refining
    • C22B21/062—Obtaining aluminium refining using salt or fluxing agents
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/02—Making non-ferrous alloys by melting
    • C22C1/026—Alloys based on aluminium
    • 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
    • C22C21/02—Alloys based on aluminium with silicon 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
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium 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
    • C22C21/14—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
    • 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
    • C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
    • 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

Definitions

  • the invention relates to a new manufacturing method for high tenacity and high fatigue resistant aluminum alloy rolled products, as well as products obtained by this process.
  • This process comprises a particular refining of the liquid metal.
  • These sheets can be used as aircraft fuselage liner.
  • Al-Si-Mg-Cu alloys can be used for fuselage structural members. These elements must have on the one hand a high mechanical strength, and on the other hand good toughness and good resistance to fatigue. Any new possibilities, to improve one of these groups of properties without degrading others would be welcome.
  • Patent Application EP 1 205 567 A (Alcoa Inc.) teaches that the addition of Ti and B or C to a wrought alloy at a rate of 0.003 to 0.010% results in a foundry grain size of less than or equal to at 200 ⁇ m.
  • the object of the present invention is to propose a new process for obtaining highly recrystallized wrought products, preferably laminated products, and in particular 6xxx series alloy thin metal sheets with high mechanical strength which also show excellent toughness and fatigue resistance.
  • the subject of the invention is a process for manufacturing aluminum alloy products, in particular highly recrystallized products, with high toughness and fatigue resistance, which comprises the following steps: (a) preparing a bath of an alloy of aluminum alloy; 'aluminum,
  • step (f) subjecting the product resulting from step (d) or (e) to a heat treatment for dissolving and quenching, followed by controlled tensile stress relieving with a permanent elongation of between 0.5 and 5% , and possibly an income
  • the amount of refining is chosen such that the average size of the foundry grain of said raw form is greater than 500 ⁇ m.
  • Another object of the present invention is a rolling plate that can be obtained by the casting process.
  • Yet another object of the present invention is a sheet capable of being obtained from the process or from the rolling plate according to the invention.
  • Figure 1 shows the influence of refining and titanium content on the parameter p *.
  • Figure 2 shows the influence of refining and titanium content on the parameter s *.
  • the black triangle represents an alloy refined with TiB 2 , while the other alloys have been refined with AlTiC.
  • the designation of the alloys follows the rules of THE ALUMINUM ASSOCIATION.
  • the metallurgical states are defined in the European standard EN 515.
  • the chemical composition of standardized aluminum alloys is defined for example in the standard EN 573-3 as well as in the publications of THE ALUMINUM ASSOCIATION. These rules, standards and publications are known to those skilled in the art.
  • alloy of the 6xxx series or "alloy of the Al-Mg-Si type” is understood to mean aluminum alloys (i) whose chemical composition falls into one of the standardized designations of an alloy of the 6xxx series, or (ii) that is derived from an alloy corresponding to such a standardized designation by the addition or deletion of one or more chemical elements other than silicon or magnesium, and / or by the exceedance (to the up or down) of the standardized concentration limit of one or more chemical elements (including silicon and magnesium), it being understood that in both cases (i) and (ii), the application of the Standardized designation should lead to storing this modified alloy in the 6xxx series.
  • the static mechanical characteristics that is the breaking strength R m , the yield point R p o, 2, and the elongation at break A, are determined by a tensile test according to the EN 10002-1 standard, the location and direction of specimen collection being defined in EN 485-1.
  • Fatigue strength is determined by ASTM E 466 test, fatigue crack propagation speed (so-called da / dn test) according to ASTM E 647, and critical stress intensity factor Kc, Kco or K app. according to ASTM E 561.
  • the term "spun product” includes so-called “stretched” products, that is, products that are made by spinning followed by stretching.
  • a "structural element” or “structural element” of a mechanical construction is called a mechanical part, the failure of which is likely to endanger the safety of the said construction, its users, its users or others.
  • these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames)), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars) and the empennage composed in particular of horizontal stabilizers and vertical (horizontal or vertical stabilizers), as well as floor beams, seat rails and doors.
  • fuselage such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames)
  • the wings such as the wing skin
  • stiffeners stringers or stiffeners
  • ribs ribs
  • spars the empennage composed in particular of horizontal stabilizers and vertical
  • the present invention can be applied to mastering alloys of the lxxx, 2xxx, 3xxx, 4xxx, 5xxx, 6xxx, 7xxx and 8xxx series, and in particular to alloys of the 2xxx, 6xxx and 7xxx series, and more particularly to alloys of the series. 6xxx. It is based on the discovery that refining an aluminum alloy using a refining containing AlTiC-type phases added in the right proportion makes it possible to obtain a very particular microstructure of the cast raw form, and in particular a grain size greater than 500 ⁇ m and a regular distribution of intermetallic phases, observed by optical microscopy at a magnification Typically 50.
  • wrought products After hot transformation according to known processes, optionally followed by a cold conversion and a heat treatment, in particular for highly recrystallized products, wrought products are obtained which show, in a manner surprisingly, a significantly better toughness and a lower crack propagation rate than products made from raw forms obtained by known methods.
  • the term "highly recrystallized product” means a product for which the fraction of recrystallized grains measured between the quarter-thickness and the half-thickness of the finished products is greater than 70%.
  • the products from step (f) are strongly recrystallized.
  • AlTiC type phases we mean any ternary Al-Ti-C phase as well as any Ti-C binary phase in an aluminum matrix; this term notably includes the AlTiC 2 and TiC phases. These phases are typically added in a refining yarn.
  • the raw form produced by the process according to the invention may contain less than 0, 0001% boron.
  • the casting microstructure obtained by the process according to the invention is characterized by two parameters, p * (dimension [ ⁇ m]) and s * (dimension [ ⁇ m "1 ]) .
  • These parameters characterize more particularly the fineness and the uniformity of
  • the parameter p * characterizes the average distance between precipitates in the solidification structures, and therefore the mean dimension of the zones without precipitates .
  • the parameter s * characterizes the uniformity of the distribution. of these distances.
  • the precise definition of these two parameters as well as the method for their determination are specified in the article "Quantification of Spatial Distribution of As-Cast Microstructural Features" by Ph. Jarry, M. Boehm and S.
  • the parameters p * and s * are based on the optical microscopy analysis of polished sections of the raw form at a magnification typically of 50, or any other magnification which achieves a good compromise between a representative sample of the micro structure studied and the resolution needed.
  • Image acquisition is typically performed by a color CCD camera (charge-coupled device) connected to an image analysis computer.
  • the procedure of analysis described in detail in the aforementioned article by Ph. Jarry, M. Boehm and S. Antoine, comprises the following steps: a. acquisition of the image b. dark phase thresholding and binary analysis of grayscale images, c. suppression of very small phases (for a magnification of 50, a group of less than 5 pixels is considered as electronic noise), d. digital analysis of the image using a closure algorithm.
  • Digital image analysis is an iterative closing of the image with a step up.
  • the step i which closes the image Cj is defined by i successive dilations of the image of the same object (a dilation consisting of the replacement of each pixel of an image by the maximum value of its neighbors) followed by i successive erosions of the image of the same object (an erosion consisting of the replacement of each pixel of an image by the minimal value of its neighbors) of the image d (note that erosion and expansion operations are not commutative).
  • the surface ratio A which represents the surface fraction of objects, is plotted as a function of the number of closing steps.
  • A denotes the surface fraction of objects after transformation
  • a m i n denotes the initial surface fraction of intermetallic particles after thresholding
  • a max denotes their surface fraction corresponding to the conventional filling at which the algorithm is stopped (in practice 90%) in order to avoid problems of slow convergence at the end of filling
  • i is the number of computation steps
  • ⁇ is a coefficient of adjustment of the sigmoid slope.
  • the parameter p * represents the average distance between particles present in the matrix.
  • 1 / s * is proportional to the standard deviation of the distance distribution to the first neighbor between particles.
  • the parameter s * is therefore a measure of the regularity of the phase distribution in the matrix.
  • a rolling plate is manufactured according to the method of the invention, so as to obtain a value of s * greater than 0.92 ⁇ m -1 , and preferably greater than 0.94. ⁇ m "1 . It is preferred to simultaneously obtain a p * value of less than 107 microns.
  • the raw form obtained at the end of the casting such as a spinning billet, a forge billet or a rolling plate, is transformed hot and optionally cold to its final thickness.
  • the product of final thickness is then subjected to a solution and quenching heat treatment, followed by controlled tensile stress relieving with a permanent elongation of between 0.5 and 5%, and optionally followed by an income. If the permanent elongation obtained during tensioning by controlled tensing is less than 0.5%, the product does not reach sufficient flatness. If the permanent elongation achieved during controlled tensile stress relieving is greater than 5%, the damage tolerance properties may be affected.
  • the process according to the invention is particularly well suited for producing wrought products made of alloy of the 6xxx series, and more particularly of AA6056, of AA6156 or of similar alloys.
  • An advantageous embodiment for heat-treated alloys comprises converting the hot-rolling sheet into a sheet having a thickness of between 3 and 12 mm, and heat treating to the T6 state.
  • this process leads to a sheet with a tolerance to damage KR, determined in TL direction for a crack extension ⁇ a eff of 20 mm from a curve R measured according to ASTM E561, of at least 115 MPaVm, and preferably at least 116 MPaVm.
  • a sheet of alloys AA6056 or AA6156 manufactured by the process according to the invention also has in the T6 state in a thickness of between 3 and 12 mm a damage tolerance KR, determined in the TL direction for a crack extension ⁇ aeff of 60 mm obtained from a curve R measured according to ASTM E561, of at least 175 MPaVm.
  • improved KR parameter that results from the method according to the present invention may allow to increase the minimum guaranteed value of this parameter for a given constraint, knowing that this parameter, like all the parameters which characterize a product metallurgical, always shows a certain statistical dispersion.
  • Example 1 An AA6056 alloy was cast into two industrial-size rolling plates, in particular of a thickness of 446 mm, at a speed of 55 mm / min and at a temperature of 680 ° C.
  • Table 1 gives the refining method (wire A1T3CO, 15 or AT5B
  • AlT3C0,15 corresponds to a composition Al-3% Ti-0,15% C.
  • AT5B corresponds to a composition Al-5% Ti this product is also known under the commercial designation "AlTiB 5: 1"
  • the Ti content in mass ppm
  • the inoculation rate and mean values for the parameters s * and p * as defined above.
  • the parameters s * and p * were determined on samples cut at about 140 mm from the skin and at the third width of the rolling plates. Table 1
  • the parameter KR ( 2O ) refers to a crack extension value ⁇ a ef ⁇ of 20 mm.
  • the static mechanical characteristics of the two sheets hardly differ significantly.
  • the resistance to damage represented by the parameter KR, increases significantly when the refining of the liquid metal has been carried out with a wire containing phases of the AlTiC type.
  • the latter product the crack propagation rate is lower "when the intensity factor ⁇ iE stress reaches about 30 MPaVm.
  • Example 2 Other AA6056 alloy rolling plates were cast using the process according to the invention.
  • the refining and casting microstructure parameters are summarized in Table 3.
  • Figure 1 gives a comparison of the fineness of the casting microstructures (parameter p *) as a function of the Ti content and the type of refiner.
  • Figure 2 gives a comparison of the regularity of the casting microstructures (parameter s *). Commentary on Examples 1 and 2:
  • Table 4 summarizes the total Ti content in the alloys of Examples 1 and 2, as well as the size of the foundry grains.
  • the content between Ti and G provided by the refining wire can be calculated from the rate of inoculation and the composition of the wire:
  • a conventional refining at 0.7 kg / t ATB5 introduces about 7 ppm B.
  • a refining with 1 kg / t of AT3C0.15 type wire as used for these tests introduces about 1.5 ppm of C.
  • a refining of 0.5 kg / t of the same thread introduces half, or about 0.75 ppm of C, while a refining of 2 kg / t introduced the double, or about 3 ppm.
  • a refining of 1 kg / t of AT3C0.15 introduces about 30 ppm, a refining of 0.5 kg / t half (about 15 ppm), and a refining of 2 kg / t double (about 60 ppm).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Continuous Casting (AREA)
  • Metal Rolling (AREA)
  • Extrusion Of Metal (AREA)
  • Forging (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
EP05805764A 2004-09-24 2005-09-19 Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür Expired - Lifetime EP1809779B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0410138A FR2875815B1 (fr) 2004-09-24 2004-09-24 Produits en alliage d'aluminium a haute tenacite et procede d'elaboration
PCT/FR2005/002310 WO2006035133A1 (fr) 2004-09-24 2005-09-19 Produits en alliage d ' aluminium a haute tenacite et procede d ' elaboration

Publications (2)

Publication Number Publication Date
EP1809779A1 true EP1809779A1 (de) 2007-07-25
EP1809779B1 EP1809779B1 (de) 2010-04-07

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EP05805764A Expired - Lifetime EP1809779B1 (de) 2004-09-24 2005-09-19 Produkte aus hochfester aluminiumlegierung und herstellungsverfahren dafür

Country Status (8)

Country Link
US (2) US7615125B2 (de)
EP (1) EP1809779B1 (de)
CN (1) CN101027419B (de)
AT (1) ATE463588T1 (de)
DE (1) DE602005020487D1 (de)
ES (1) ES2344213T3 (de)
FR (1) FR2875815B1 (de)
WO (1) WO2006035133A1 (de)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN100491579C (zh) * 2003-03-17 2009-05-27 克里斯铝轧制品有限公司 制造整体单块铝结构的方法和由这种结构机加工的铝制件
DE102005014606A1 (de) * 2005-03-31 2006-10-05 Richard Bergner Verbindungstechnik Gmbh & Co. Kg Verfahren zur Herstellung eines Befestigungselements sowie Befestigungselement, insbesondere Schraube
CN101590591B (zh) * 2008-05-30 2011-08-03 杰出材料科技股份有限公司 容易焊接的高强度铝合金型材的制作方法
US8168015B2 (en) 2008-10-23 2012-05-01 GM Global Technology Operations LLC Direct quench heat treatment for aluminum alloy castings
US8636855B2 (en) * 2009-03-05 2014-01-28 GM Global Technology Operations LLC Methods of enhancing mechanical properties of aluminum alloy high pressure die castings
CN102009164B (zh) * 2010-12-07 2012-07-04 陕西宏远航空锻造有限责任公司 一种zl205铝合金熔模铸件的铸造方法
US8672020B2 (en) * 2011-03-15 2014-03-18 Shenzhen Sunxing Light Alloys Materials Co., Ltd. Method for producing aluminum-zirconium-carbon intermediate alloy
CN102206777B (zh) * 2011-06-10 2013-07-10 深圳市新星轻合金材料股份有限公司 铝-锆-钛-碳中间合金的制备方法
CN102392117A (zh) * 2011-11-02 2012-03-28 沈阳飞机工业（集团）有限公司 一种解决国产非预拉伸薄板化铣变形的方法
CN102528397A (zh) * 2012-01-31 2012-07-04 西南铝业（集团）有限责任公司 一种鞋模用铝合金排材的生产方法
CN102925732B (zh) * 2012-09-26 2014-05-07 霍山县龙鑫金属制品有限公司 一种掺杂镁元素的铝合金熔炼方法
CN103031454B (zh) * 2012-12-05 2015-06-03 安徽徽铝铝业有限公司 一种铝合金的熔炼用精炼剂制备方法
RU2542183C2 (ru) * 2013-07-09 2015-02-20 Открытое Акционерное Общество "Корпорация Всмпо-Ависма" Способ производства прессованных изделий из алюминиевого сплава серии 6000
FR3011252B1 (fr) * 2013-09-30 2015-10-09 Constellium France Tole d'intrados a proprietes de tolerance aux dommages ameliorees
FR3067044B1 (fr) † 2017-06-06 2019-06-28 Constellium Issoire Alliage d'aluminium comprenant du lithium a proprietes en fatigue ameliorees
CN107557604A (zh) * 2017-10-30 2018-01-09 湖南博溥立材料科技有限公司 铝合金精炼剂及其制备方法
FR3086872B1 (fr) * 2018-10-05 2022-05-27 C Tec Tech Center Procede de fabrication d'une piece en alliage d'aluminium
CN112410692A (zh) * 2020-11-28 2021-02-26 四川航天长征装备制造有限公司 2219铝合金细化晶粒的工艺方法

Family Cites Families (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU701000A1 (ru) 1978-04-22 1996-03-27 В.И. Добаткин Способ непрерывного литья
JPS60145365A (ja) * 1984-01-10 1985-07-31 Kobe Steel Ltd 溶接性および耐応力腐蝕割れ性が優れたＡｌ−Ζｎ−Ｍｇ合金の製造法
CA1289748C (en) * 1985-03-01 1991-10-01 Abinash Banerji Producing titanium carbide
US4873054A (en) * 1986-09-08 1989-10-10 Kb Alloys, Inc. Third element additions to aluminum-titanium master alloys
SE8702149L (sv) * 1987-05-22 1988-11-23 Baeckerud Innovation Ab Aluminiumfoerlegering
CH682402A5 (de) * 1990-12-21 1993-09-15 Alusuisse Lonza Services Ag Verfahren zum Herstellen einer Flüssig-Fest-Metallegierungsphase mit thixotropen Eigenschaften.
JPH04292449A (ja) 1991-03-19 1992-10-16 Kubota Corp 木の匂いのする窯業系板材
US5186238A (en) * 1991-04-25 1993-02-16 International Business Machines Corporation Liquid film interface cooling chuck for semiconductor wafer processing
JPH07292449A (ja) * 1994-04-21 1995-11-07 Sky Alum Co Ltd 陽極酸化処理用アルミニウム合金板の製造方法
US5480498A (en) * 1994-05-20 1996-01-02 Reynolds Metals Company Method of making aluminum sheet product and product therefrom
US6077363A (en) * 1996-06-17 2000-06-20 Pechiney Rhenalu Al-Cu-Mg sheet metals with low levels of residual stress
FR2782463B1 (fr) * 1998-08-24 2000-09-29 Pechiney Rhenalu Procede d'amelioration de la planeite d'une tole metallique
US6645321B2 (en) * 1999-09-10 2003-11-11 Geoffrey K. Sigworth Method for grain refinement of high strength aluminum casting alloys
US7135077B2 (en) * 2000-05-24 2006-11-14 Pechiney Rhenalu Thick products made of heat-treatable aluminum alloy with improved toughness and process for manufacturing these products
FR2811337B1 (fr) * 2000-07-05 2002-08-30 Pechiney Rhenalu Toles en alliage d'aluminium plaquees pour elements de structure d'aeronefs
CA2361484A1 (en) * 2000-11-10 2002-05-10 Men Glenn Chu Production of ultra-fine grain structure in as-cast aluminum alloys
CN1144886C (zh) * 2001-12-14 2004-04-07 温景林 铝钛碳细化剂合金线材的凝固与成形方法
BR0312098A (pt) * 2002-06-24 2005-03-29 Corus Aluminium Walzprod Gmbh Método para a produção de liga de al-mg-si balanceada de alta resistência e produto desta liga capaz de ser soldado
CN1418973A (zh) * 2002-12-18 2003-05-21 涿州市精英铝合金材料有限责任公司 一种铝钛碳中间合金晶粒细化剂

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006035133A1 *

Also Published As

Publication number Publication date
DE602005020487D1 (de) 2010-05-20
EP1809779B1 (de) 2010-04-07
US20060065331A1 (en) 2006-03-30
ES2344213T3 (es) 2010-08-20
WO2006035133A1 (fr) 2006-04-06
FR2875815B1 (fr) 2006-12-01
ATE463588T1 (de) 2010-04-15
US20100006186A1 (en) 2010-01-14
CN101027419A (zh) 2007-08-29
US7615125B2 (en) 2009-11-10
CN101027419B (zh) 2010-06-16
FR2875815A1 (fr) 2006-03-31

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