EP1231290A1 - Verfahren zur Herstellung eines hochfesten Knetproduktes aus AlZnMgCu-Legierung - Google Patents

Verfahren zur Herstellung eines hochfesten Knetproduktes aus AlZnMgCu-Legierung Download PDF

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Publication number
EP1231290A1
EP1231290A1 EP02356018A EP02356018A EP1231290A1 EP 1231290 A1 EP1231290 A1 EP 1231290A1 EP 02356018 A EP02356018 A EP 02356018A EP 02356018 A EP02356018 A EP 02356018A EP 1231290 A1 EP1231290 A1 EP 1231290A1
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European Patent Office
Prior art keywords
temperature
alloy
tempering
duration
stage
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Ceased
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EP02356018A
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English (en)
French (fr)
Inventor
Timothy Warner
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Constellium Issoire SAS
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Pechiney Rhenalu SAS
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    • 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
    • C22F1/053—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 zinc 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
    • C22C21/10—Alloys based on aluminium with zinc as the next major constituent

Definitions

  • the invention relates to the manufacture of wrought products by rolling, spinning or forging of aluminum alloy of the AlZnMgCu type with high mechanical resistance, used in particular in aeronautical construction, in particular for the upper surfaces of airplane wings.
  • Alloys of the Al-Zn-Mg-Cu type have been used for more than 50 years in the aeronautical construction, and in particular for the wing upper surfaces. So we used alloys 7075, 7178, 7050, 7150 and, more recently, alloys 7055 and 7449. These alloys were most often used in the T6 state, i.e. at an income corresponding to the maximum of the elastic limit in traction, or to an over-income state T76, T79 or T77 to obtain better corrosion resistance.
  • the state of the art shows on the one hand that the mechanical resistance to compression is an essential property for the upper surfaces of fenders, and that, share the manufacturers of high resistance alloys offer for this application produced either in the T6 state, corresponding to the peak of elastic limit in tension, or an over-tempered T7 state with better corrosion resistance, but with a loss of mechanical strength.
  • the invention aims to further improve the mechanical strength in compression high resistance 7000 alloy products intended in particular for upper surfaces of aircraft wings without loss on other properties of use
  • Another subject of the invention is the rolled, spun or forged product obtained by said process.
  • Yet another object of the invention is the structural element for construction mechanical, and in particular aeronautical, made from at least one product laminated, spun or forged obtained by said process.
  • Figure 1 represents the typical properties, namely the elastic limit in tension (direction L), the tensile strength (direction L), the elastic limit in compression (direction L) and the corrosion threshold under tension (direction ST), of sheets thickness between 15 and 40 mm in alloys 7150-T651, 7449-T651 and 7449-T7951 according to the prior art.
  • FIG. 2 represents the time-temperature domain of the income of the process according to the invention.
  • FIG. 3 represents the breaking strength and the elastic limit in tension of 38 mm thick sheets of alloy 7449 of Example 1 as a function of time equivalent to 120 ° C of tempering for different tempering temperatures.
  • Figure 4 shows the tensile strength (direction L) and the limit tensile and compressive strength (L direction) of 38 mm 7449 alloy sheets of example 2 as a function of the time equivalent to 120 ° C. of the income.
  • FIG. 5 represents the compressive elastic limit of the sheets of alloys A and
  • Example 3 as a function of the time equivalent to 120 ° C. of the income.
  • the invention is based on highlighting a difference between the resistance peak mechanical tensile obtained income, which corresponds to what is called usually the state T6, and the peak of mechanical resistance in compression.
  • the metallurgists have always used tensile strength to define the T6 state of maximum resistance to income.
  • the process according to the invention applies to alloys of the Al-Zn-Mg-Cu type with a content high in zinc, between 7 and 11%, with a magnesium content included between 1.8 and 3%, and preferably between 1.8 and 2.4%, and a copper content between 1.2 and 2.6% and preferably between 1.6 and 2.2%.
  • a zinc content of 7% the invention seems to be of little interest because it is no longer used in construction aeronautics of such alloys for the manufacture of structural elements used in compression.
  • a zinc content of 11% we encounter difficulties during the industrial casting of sufficiently large plates or billets for the production of sheets, profiles or forgings suitable for the manufacture of said structural elements.
  • the process according to the invention applies in particular to the alloys used for the manufacture of aircraft wing upper surface elements, for example alloys 7055, 7349 and 7449, in the form of wrought products, that is to say rolled, extruded or forged.
  • This method comprises, in known manner, the manufacture of a blank, namely a plate for rolled products, a billet for extruded products or a block of forge for forged products.
  • This blank is preferably homogenized to a temperature close to the starting melting temperature of the alloy, such as indicated in patent application EP 0670377. It is then transformed by hot rolling, spinning or forging, to the desired size.
  • the product obtained is dissolved, also at a temperature fairly close to the temperature of starting melting of the alloy, this temperature being controlled by analysis differential enthalpy. Dissolution is followed by quenching, generally with cold water. The quenched product is preferably subjected to controlled traction leading to a permanent elongation of between 1 and 5%.
  • the product then undergoes an income to obtain the elastic limit peak in compression direction L.
  • the income can be mono-level, that is to say comprising a temperature rise ramp, linear or not as a function of time, a constant temperature within the temperature tolerance limit of the oven used, and a cooling to room temperature.
  • the bearing is at a temperature between 120 and 150 ° C, and of a duration included in the AEFG parallelogram in FIG. 2, and preferably between 120 and 145 ° C of a duration included in the parallelogram ABCD of figure 2.
  • the income can also be bi-level, with a first level at a temperature between 80 and 120 ° C, and a second level at a higher temperature, between 120 and 160 ° C.
  • It can also be tri-level, with a first and a second level within the same limits as two-level income, and a third level at a temperature lower than the second, between 100 and 140 ° C. Considering of the time required, in industrial ovens, for temperature rises, it it is hardly possible to have stages of less than 2 hours duration, and preferably at 5 a.m.
  • t (eq) ⁇ exp (-16000 / T) dt exp (-16000 / T ref ) in which T is the temperature of the tempering stage in ° K, t the treatment time in hours and T ref the reference temperature taken here at 120 ° C, or 393 ° K.
  • the duration of the tempering is between 100 and 250 h of time equivalent to 120 ° C., and 50 to 200 h longer than the equivalent time corresponding to the tempering T651.
  • the duration of tempering necessary to reach the peak in compression depends on the composition of the alloy, and in particular on the Cu / Mg ratio, the necessary duration increasing with this ratio.
  • the wrought product, and in particular the rolled, extruded or forged product obtained by the process according to the invention can be advantageously used for manufacturing structural elements, particularly in aircraft construction. Thanks to the increase in the elastic limit in compression which results from the process according to the invention, a structural element made from at least one spun, laminated product or forged according to the invention, shows with respect to a structural element of the same dimension and made from wrought, extruded or forged products according to the prior art better resistance during compressive stress. In an achievement preferred of the invention, the structural element is an aircraft wing upper surface.
  • the sheets have undergone a pre-enlargement to pass from a plate width of 1100 mm to 2500 mm, hot rolling up to 38 mm with exit temperature at 378 ° C, dissolution at 475 ° C, quenching in cold water, and traction controlled at 2.8% permanent elongation after waiting 1 hour after quenching.
  • R m to less than 5 MPa, while remaining industrially acceptable. In this case, it is a 48 h treatment at 120 ° C.
  • the income leading to the peak of elastic limit in compression is located at an equivalent time of the order of 150 h, that is to say at a time intermediate equivalent between a T651 income and a T7951 income.
  • the beach interesting is between 100 and 250 h of time equivalent to 120 ° C, or 50 to 200 h more than that of T651 income.
  • This income at peak compression leads to a gain 19 MPa compared to T651 income and 25 MPa compared to T7951 income.
  • the sheets were made from two alloys 7449, the thicknesses and compositions of which are given in Table 4. Alloy e (mm) Yes Fe Cu mg Zn Zr Ti AT 30 0.049 0,075 1.87 2.35 8.38 0.11 0.03 B 23 0,045 0.068 1.95 2.27 8.31 0.10

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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)
  • Extrusion Of Metal (AREA)
EP02356018A 2001-02-07 2002-02-05 Verfahren zur Herstellung eines hochfesten Knetproduktes aus AlZnMgCu-Legierung Ceased EP1231290A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0101617A FR2820438B1 (fr) 2001-02-07 2001-02-07 Procede de fabrication d'un produit corroye a haute resistance en alliage alznmagcu
FR0101617 2001-02-07

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EP1231290A1 true EP1231290A1 (de) 2002-08-14

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EP02356018A Ceased EP1231290A1 (de) 2001-02-07 2002-02-05 Verfahren zur Herstellung eines hochfesten Knetproduktes aus AlZnMgCu-Legierung

Country Status (4)

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US (1) US20020162609A1 (de)
EP (1) EP1231290A1 (de)
DE (1) DE1231290T1 (de)
FR (1) FR2820438B1 (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2838136A1 (fr) * 2002-04-05 2003-10-10 Pechiney Rhenalu PRODUITS EN ALLIAGE A1-Zn-Mg-Cu A COMPROMIS CARACTERISTIQUES STATISTIQUES/TOLERANCE AUX DOMMAGES AMELIORE
FR2879217A1 (fr) * 2004-12-13 2006-06-16 Pechiney Rhenalu Sa Toles fortes en alliage ai-zn-cu-mg a faibles contraintes internes
WO2008003506A2 (en) * 2006-07-07 2008-01-10 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminium alloy products and a method of manufacturing thereof
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US7883591B2 (en) 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
RU2443793C1 (ru) * 2010-10-08 2012-02-27 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Высокопрочный сплав на основе алюминия и способ получения изделия из него
CN104404321A (zh) * 2014-11-26 2015-03-11 中国石油天然气集团公司 一种超深井用超高强度铝合金钻杆管体及其制造方法
CN104532090A (zh) * 2014-12-31 2015-04-22 中国石油天然气集团公司 一种580MPa级铝合金钻杆用管体及其制造方法
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050006010A1 (en) * 2002-06-24 2005-01-13 Rinze Benedictus Method for producing a high strength Al-Zn-Mg-Cu alloy
US7214281B2 (en) * 2002-09-21 2007-05-08 Universal Alloy Corporation Aluminum-zinc-magnesium-copper alloy extrusion
US7060139B2 (en) * 2002-11-08 2006-06-13 Ues, Inc. High strength aluminum alloy composition
US20050056353A1 (en) * 2003-04-23 2005-03-17 Brooks Charles E. High strength aluminum alloys and process for making the same
DE102005045341A1 (de) * 2004-10-05 2006-07-20 Corus Aluminium Walzprodukte Gmbh Hochfestes, hochzähes Al-Zn-Legierungsprodukt und Verfahren zum Herstellen eines solches Produkts
ES2292075T5 (es) * 2005-01-19 2010-12-17 Otto Fuchs Kg Aleacion de aluminio no sensible al enfriamiento brusco, asi como procedimiento para fabricar un producto semiacabado a partir de esta aleacion.
RU2406773C2 (ru) * 2005-02-01 2010-12-20 Тимоти Лэнган Деформированный алюминиевый сплав системы алюминий-цинк-магний-скандий и способ его получения
US20060213591A1 (en) * 2005-03-24 2006-09-28 Brooks Charles E High strength aluminum alloys and process for making the same
US9410229B2 (en) 2005-03-24 2016-08-09 Kaiser Aluminum Fabricated Products, Llc High strength aluminum alloys and process for making the same
US20060289093A1 (en) * 2005-05-25 2006-12-28 Howmet Corporation Al-Zn-Mg-Ag high-strength alloy for aerospace and automotive castings
US8157932B2 (en) * 2005-05-25 2012-04-17 Alcoa Inc. Al-Zn-Mg-Cu-Sc high strength alloy for aerospace and automotive castings
US20070151636A1 (en) * 2005-07-21 2007-07-05 Corus Aluminium Walzprodukte Gmbh Wrought aluminium AA7000-series alloy product and method of producing said product
US20070204937A1 (en) * 2005-07-21 2007-09-06 Aleris Koblenz Aluminum Gmbh Wrought aluminium aa7000-series alloy product and method of producing said product
US8083871B2 (en) 2005-10-28 2011-12-27 Automotive Casting Technology, Inc. High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting
CN102002615B (zh) * 2010-10-21 2012-11-21 哈尔滨工业大学 超高强铝合金材料及用于制备分离机内筒的管坯的制备方法
CN102732761B (zh) * 2012-06-18 2014-01-08 中国航空工业集团公司北京航空材料研究院 一种7000系铝合金材料及其制备方法
CN104561700B (zh) * 2014-12-31 2018-02-02 中国石油天然气集团公司 一种620MPa级铝合金钻杆用管体及其制造方法
CN104805342B (zh) * 2015-05-21 2017-08-11 湖南稀土金属材料研究院 铝合金材料及其制备方法和应用
CN107058829A (zh) * 2017-06-27 2017-08-18 桂林理工大学 具有超细晶结构的高性能含钪高锌变形铝合金及制备方法
CN108746447B (zh) * 2018-05-16 2020-03-17 江苏理工学院 一种高强耐蚀铝合金锻件制造工艺
CN108687160B (zh) * 2018-05-16 2020-02-14 江苏理工学院 一种铝合金板材处理工艺
CN108642410B (zh) * 2018-05-16 2020-01-03 江苏理工学院 一种提高铝合金板材综合力学性能的工艺方法
CN108890218B (zh) * 2018-05-16 2020-02-14 江苏理工学院 一种高强耐热铝合金锻件制造工艺
CN110129640B (zh) * 2019-06-28 2020-05-05 江西理工大学 一种增材制造用7000系铝合金线材及其制备方法
CN110484791B (zh) * 2019-08-16 2021-03-02 西安铝轻新材料科技有限公司 一种客车车架用高强高韧铝合金及其制备方法
CN110396629B (zh) * 2019-08-16 2021-04-20 中国航发北京航空材料研究院 一种800MPa级铝合金挤压型材及其制备方法
CN111440974B (zh) * 2020-04-28 2021-04-16 北京工业大学 一种高强度铝合金及其制造方法
CN112281032B (zh) * 2020-10-20 2022-04-19 中国兵器科学研究院宁波分院 一种铝合金焊材的制备方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4477292A (en) * 1973-10-26 1984-10-16 Aluminum Company Of America Three-step aging to obtain high strength and corrosion resistance in Al-Zn-Mg-Cu alloys
US4832758A (en) * 1973-10-26 1989-05-23 Aluminum Company Of America Producing combined high strength and high corrosion resistance in Al-Zn-MG-CU alloys
EP0377779A1 (de) * 1989-01-13 1990-07-18 Aluminum Company Of America Erzeugnis aus einer Aluminium-Legierung mit verbesserten Kombinationen der Festigkeit, der Zähigkeit und der Korrosionsbeständigkeit
US5108520A (en) * 1980-02-27 1992-04-28 Aluminum Company Of America Heat treatment of precipitation hardening alloys

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4954188A (en) * 1981-12-23 1990-09-04 Aluminum Company Of America High strength aluminum alloy resistant to exfoliation and method of making
US5221377A (en) * 1987-09-21 1993-06-22 Aluminum Company Of America Aluminum alloy product having improved combinations of properties
JP3705320B2 (ja) * 1997-04-18 2005-10-12 株式会社神戸製鋼所 耐食性に優れる高強度熱処理型７０００系アルミニウム合金
IL156386A0 (en) * 2000-12-21 2004-01-04 Alcoa Inc Aluminum alloy products and artificial aging method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4477292A (en) * 1973-10-26 1984-10-16 Aluminum Company Of America Three-step aging to obtain high strength and corrosion resistance in Al-Zn-Mg-Cu alloys
US4832758A (en) * 1973-10-26 1989-05-23 Aluminum Company Of America Producing combined high strength and high corrosion resistance in Al-Zn-MG-CU alloys
US5108520A (en) * 1980-02-27 1992-04-28 Aluminum Company Of America Heat treatment of precipitation hardening alloys
EP0377779A1 (de) * 1989-01-13 1990-07-18 Aluminum Company Of America Erzeugnis aus einer Aluminium-Legierung mit verbesserten Kombinationen der Festigkeit, der Zähigkeit und der Korrosionsbeständigkeit

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
CHEMICAL ABSTRACTS, vol. 133, no. 26, 25 December 2000, Columbus, Ohio, US; abstract no. 364991, HEYMES, F. ET AL: "New aluminum semi-products for airframe application" XP002185362 *
INT. CONF. NEW DEV. METALL. PROCESS TECHNOL., PROC. (1999), 417-422 PUBLISHER: VEREIN DEUTSCHER EISENHUETTENLEUTE, DUESSELDORF, GERMANY., 1999 *
J,E,HATCH: "Aluminium", 1984, ASM, OHIO, US, XP002185361 *

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003085145A2 (fr) * 2002-04-05 2003-10-16 Pechiney Rhenalu Produits en alliages al-zn-mg- cu
WO2003085145A3 (fr) * 2002-04-05 2004-04-01 Pechiney Rhenalu Produits en alliages al-zn-mg- cu
FR2838136A1 (fr) * 2002-04-05 2003-10-10 Pechiney Rhenalu PRODUITS EN ALLIAGE A1-Zn-Mg-Cu A COMPROMIS CARACTERISTIQUES STATISTIQUES/TOLERANCE AUX DOMMAGES AMELIORE
US7666267B2 (en) 2003-04-10 2010-02-23 Aleris Aluminum Koblenz Gmbh Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties
US10472707B2 (en) 2003-04-10 2019-11-12 Aleris Rolled Products Germany Gmbh Al—Zn—Mg—Cu alloy with improved damage tolerance-strength combination properties
US7883591B2 (en) 2004-10-05 2011-02-08 Aleris Aluminum Koblenz Gmbh High-strength, high toughness Al-Zn alloy product and method for producing such product
WO2006064113A1 (fr) * 2004-12-13 2006-06-22 Alcan Rhenalu TOLES FORTES EN ALLIAGE Al-Zn-Cu-Mg A FAIBLES CONTRAINTES INTERNES
FR2879217A1 (fr) * 2004-12-13 2006-06-16 Pechiney Rhenalu Sa Toles fortes en alliage ai-zn-cu-mg a faibles contraintes internes
WO2008003506A3 (en) * 2006-07-07 2008-04-17 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminium alloy products and a method of manufacturing thereof
WO2008003506A2 (en) * 2006-07-07 2008-01-10 Aleris Aluminum Koblenz Gmbh Aa7000-series aluminium alloy products and a method of manufacturing thereof
US8002913B2 (en) 2006-07-07 2011-08-23 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
US8088234B2 (en) 2006-07-07 2012-01-03 Aleris Aluminum Koblenz Gmbh AA2000-series aluminum alloy products and a method of manufacturing thereof
US8608876B2 (en) 2006-07-07 2013-12-17 Aleris Aluminum Koblenz Gmbh AA7000-series aluminum alloy products and a method of manufacturing thereof
RU2443793C1 (ru) * 2010-10-08 2012-02-27 Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") Высокопрочный сплав на основе алюминия и способ получения изделия из него
CN104404321A (zh) * 2014-11-26 2015-03-11 中国石油天然气集团公司 一种超深井用超高强度铝合金钻杆管体及其制造方法
CN104404321B (zh) * 2014-11-26 2016-08-24 中国石油天然气集团公司 一种超深井用超高强度铝合金钻杆管体及其制造方法
CN104532090A (zh) * 2014-12-31 2015-04-22 中国石油天然气集团公司 一种580MPa级铝合金钻杆用管体及其制造方法

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US20020162609A1 (en) 2002-11-07
DE1231290T1 (de) 2003-01-09
FR2820438A1 (fr) 2002-08-09
FR2820438B1 (fr) 2003-03-07

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