EP1544316A2 - Dickes Bech aus Al-Zn-Cu-Mg Zirkonarmen rekristallisierten Legierung - Google Patents

Dickes Bech aus Al-Zn-Cu-Mg Zirkonarmen rekristallisierten Legierung Download PDF

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Publication number
EP1544316A2
EP1544316A2 EP04356197A EP04356197A EP1544316A2 EP 1544316 A2 EP1544316 A2 EP 1544316A2 EP 04356197 A EP04356197 A EP 04356197A EP 04356197 A EP04356197 A EP 04356197A EP 1544316 A2 EP1544316 A2 EP 1544316A2
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EP
European Patent Office
Prior art keywords
sheet
alloy
sheet according
mpa
low
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
EP04356197A
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English (en)
French (fr)
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EP1544316B1 (de
EP1544316A3 (de
Inventor
David Dumont
Vic Dangerfield
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
Constellium Rolled Products Ravenswood LLC
Original Assignee
Alcan Rhenalu SAS
Pechiney Rhenalu SAS
Pechiney Rolled Products LLC
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Application filed by Alcan Rhenalu SAS, Pechiney Rhenalu SAS, Pechiney Rolled Products LLC filed Critical Alcan Rhenalu SAS
Publication of EP1544316A2 publication Critical patent/EP1544316A2/de
Publication of EP1544316A3 publication Critical patent/EP1544316A3/de
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/10—Alloys based on aluminium with zinc 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
    • C22F1/053—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

Definitions

  • the present invention relates to sheet metal aluminum alloys of the Al-Zn-Cu-Mg type intended for manufacture of structural elements used in the aerospace industry.
  • patent EP 0 876 514 B1 describes a Thick Al-Zn-Cu-Mg alloy product with a fraction volume of recrystallized grains less than 35% between quarter and mid-thickness.
  • RPFF fatigue crack propagation
  • the present invention addresses the problem of knowing how to improve the resistance to the propagation of fatigue cracks in a thick alloy sheet Al-Zn-Cu-Mg.
  • a first object of the present invention is a thick sheet of Al-Zn-Cu-Mg alloy, comprising 0.04 to 0.09% by weight of Zr, said sheet having a from recrystallization greater than 35% to one quarter of thickness.
  • a second object is a manufacturing process a thick sheet of Al-Zn-Cu-Mg alloy comprising from 0.04 to 0.09% by weight of Zr, said process comprising hot rolling a blank of said sheet at a temperature of less than 420 ° C. This method makes it possible to obtain a sheet having a recrystallization greater than 35% to one quarter of thickness.
  • FIGS. 1 to 7 relate to certain aspects of the invention as described herein. They are purely illustrative and non-limiting.
  • Figure 1 shows the dimensions of specimens RPFF according to an embodiment of the present invention.
  • Figure 2 shows the test results of fatigue crack propagation (PFF) on a sheet of 856385) according to an embodiment of the present invention.
  • Figure 3 is a microscope characterization electronic scanning (SEM) of fracture surfaces of a reference material.
  • Figure 4 shows the results of PFF tests on a rolled sheet with an outlet temperature lower.
  • Figure 5 shows test results from PFF on a sheet with a lower Zr content.
  • Figure 6 shows a comparison of the path of the crack near the threshold for materials (a) and low Zr (b) according to a embodiment.
  • Figure 7 is a schematic representation of RPFF differences between reference materials and low Zr content according to one embodiment.
  • the fatigue strength is determined by a test according to ASTM E 466, and the fatigue crack growth rate (so-called da / dn test) according to ASTM E 647.
  • the curve R is determined according to ASTM standard 561. From the curve R, the critical stress intensity factor K c is calculated, ie the intensity factor which causes the instability of the crack.
  • the stress intensity factor K CO is also calculated by assigning to the critical load the initial length of the crack at the beginning of the monotonic loading. These two values are calculated for a specimen of the desired shape. K app designates the K CO corresponding to the specimen used to make the R curve test.
  • these structural elements include the elements that make up the fuselage (such as the fuselage skin (fuselage skin in English), stiffeners or fuselage stringers, the bulkheads (bulkheads), fuselage frames (circumferential frames), wings (such as the skin of wing (wing), stiffeners (stringers or stiffeners), ribs and spars) and the empennage composed in particular of stabilizers horizontal and vertical (horizontal or vertical stabilizers), as well as floor profiles (floor beams), seat tracks and doors.
  • fuselage such as the fuselage skin (fuselage skin in English), stiffeners or fuselage stringers, the bulkheads (bulkheads), fuselage frames (circumferential frames), wings (such as the skin of wing (wing), stiffeners (stringers or stiffeners), ribs and spars
  • the empennage composed in particular of stabilizers horizontal and vertical (horizontal or vertical stabilizers), as well as floor profiles (floor beams), seat tracks and doors.
  • the Zr content is between 0.05 and 0.07%.
  • Such an alloy can be cast in the form of a rolling plate, and can be processed according to the known processes in thick plates. These processes make always intervene at least one rolling pass at hot.
  • the sheet according to the invention is a strong plate (thick sheet), because the technical effect of the invention will be noticeable only for a sheet that is not completely recrystallized, whereas a thin sheet may be .
  • its thickness is at least 15 mm, and preferably at least 20 mm; its thickness can reach or exceed 100 mm.
  • the sheet according to the invention has a recrystallization rate at a quarter of the thickness (E / 4) greater than 35%, and preferably greater than 50%, but must not be completely recrystallized. As such, it is preferred that the recrystallization rate at E / 4 does not exceed 90%.
  • a sheet according to the invention in alloy according to one of the preferred embodiments (that is to say in alloy AA7040 or comprising from 5.8 to 6.8% of Zn, from 1.5 to 2.5% of Cu, from 1.5 to 2.5% Mg, from 0.04 to 0.09% of Zr) has a tenacity K IC (LT) > 30 MPa ⁇ m, and preferentially in addition a toughness K IC (TL ) > 25 MPa ⁇ m, and even more preferably in addition to these two previous values a toughness K IC (ST) > 25 MPa ⁇ m.
  • the sheet according to the invention can be manufactured by a process that includes hot rolling a roughing said sheet at a temperature which is less than 420 ° C. Then this sheet can be subjected to type T7651 treatment; this treatment includes an income.
  • the recrystallization rate itself has a low effect in areas near the threshold; the curves nominal values are slightly different because of a closure effect induced by the roughness, the path of the crack being more tortuous.
  • the recrystallized grains of the low-grade material Zr content are probably larger. It is suggested to laminate this material cold in order to obtain a microstructure comparable in terms of size of grain and then test its resistance to the fatigue crack propagation.
  • the sheets according to the invention can be used, especially in the form of thick plates, for the manufacture of structural elements for aeronautical construction.
  • the tests were performed with a cyclic load frequency of 35 Hz and a load ratio of 0.1.
  • the length of the fatigue cracks was continuously monitored using a compliance technique. It was also evaluated by optical observation of the surface of the test piece after polishing.
  • the fatigue crack propagation threshold stress intensity range, ⁇ K th is arbitrarily defined as the stress intensity coefficient range, ⁇ K, which corresponds to a fatigue crack propagation rate, da /. dN, 10 -10 m / cycle.
  • the tests were interrupted before the fracture in order to characterize the path of the rift.
  • the surface of the specimen is observed optically after acid attack (perpendicularly to the plan of propagation of the crack).
  • the surface morphologies after fracture were examined under a microscope scanning electronics. A correction due to the effect closure has been applied systematically in order to rationalize the observed differences.
  • Figure 2 shows the crack propagation of fatigue in the air through the reference material (% low recruits).
  • Figure 4 shows the crack propagation of fatigue (measured in the air) through a material rolled at a low rolling temperature (TL) (%) rec. high) in the L-T direction. This one was compared to the reference material (low recrystallization). All tests were conducted with a ratio of R load of 0.1.
  • This difference may be due to a roughness-induced closure effect in the ⁇ K range of 1.2 to 8 MPa m .
  • the path of the crack is more tortuous for the low Zr material (see Figure 6).
  • the fracture surfaces are mainly transgranular, as for the other two materials, and have a large amount of secondary cracks.
  • Figure 5 shows the crack propagation of fatigue in the air through the low material Zr content (% high recryst) in the L-T direction. Comparison with the reference material (% recrist. low). All tests were done with a ratio R load of 0.1.
  • Figure 6 shows a comparison of the path cracks near the threshold for materials reference (a) and low Zr (b) content. Samples tested in L-T orientation, at E / 4.
  • Figure 7 is a diagram of the differences of RPFF between reference materials and low Zr content. (Curve right: low material Zr content. Left curve: material of reference).

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  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Metal Rolling (AREA)
  • Heat Treatment Of Steel (AREA)
  • Conductive Materials (AREA)
  • Laminated Bodies (AREA)
  • Cookers (AREA)
EP04356197A 2003-12-16 2004-12-15 Dickes Bech aus Al-Zn-Cu-Mg Zirkonarmen rekristallisierten Legierung Expired - Lifetime EP1544316B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US52959303P 2003-12-16 2003-12-16
US529593P 2003-12-16

Publications (3)

Publication Number Publication Date
EP1544316A2 true EP1544316A2 (de) 2005-06-22
EP1544316A3 EP1544316A3 (de) 2007-05-09
EP1544316B1 EP1544316B1 (de) 2012-03-07

Family

ID=34520277

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04356197A Expired - Lifetime EP1544316B1 (de) 2003-12-16 2004-12-15 Dickes Bech aus Al-Zn-Cu-Mg Zirkonarmen rekristallisierten Legierung

Country Status (4)

Country Link
US (1) US7520945B2 (de)
EP (1) EP1544316B1 (de)
AT (1) ATE548476T1 (de)
ES (1) ES2383528T3 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7520945B2 (en) 2003-12-16 2009-04-21 Alcan Rhenalu Recrystallized Al-Zn-Cu-Mg plate with low zirconium
US10301710B2 (en) 2005-01-19 2019-05-28 Otto Fuchs Kg Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE602006011447D1 (de) * 2005-02-10 2010-02-11 Alcan Rolled Products Ravenswood Llc Legierungen auf al-zn-cu-mg aluminum-basis, verfahren zu ihrer herstellung und verwendung
US9163304B2 (en) 2010-04-20 2015-10-20 Alcoa Inc. High strength forged aluminum alloy products
CN109890663B (zh) 2016-08-26 2023-04-14 形状集团 用于横向弯曲挤压成形铝梁从而温热成型车辆结构件的温热成型工艺和设备
US11072844B2 (en) 2016-10-24 2021-07-27 Shape Corp. Multi-stage aluminum alloy forming and thermal processing method for the production of vehicle components
KR101974913B1 (ko) * 2017-04-13 2019-05-07 한국기계연구원 알루미늄-아연-구리(Al-Zn-Cu) 합금 및 이의 제조방법
EP3670690A1 (de) 2018-12-20 2020-06-24 Constellium Issoire Al-zn-cu-mg-legierungen und deren herstellungsverfahren
CN113105115B (zh) * 2021-04-14 2022-02-18 东北大学 一种具有自修复功能的耐高温搪瓷基复合涂层及其制备方法

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4305763A (en) * 1978-09-29 1981-12-15 The Boeing Company Method of producing an aluminum alloy product
CA1173277A (en) * 1979-09-29 1984-08-28 Yoshio Baba Aircraft stringer material and method for producing the same
US5277719A (en) * 1991-04-18 1994-01-11 Aluminum Company Of America Aluminum alloy thick plate product and method
US6027582A (en) * 1996-01-25 2000-02-22 Pechiney Rhenalu Thick alZnMgCu alloy products with improved properties
FR2744136B1 (fr) * 1996-01-25 1998-03-06 Pechiney Rhenalu Produits epais en alliage alznmgcu a proprietes ameliorees
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
IL156386A0 (en) * 2000-12-21 2004-01-04 Alcoa Inc Aluminum alloy products and artificial aging method
ATE548476T1 (de) 2003-12-16 2012-03-15 Constellium France Dickes bech aus al-zn-cu-mg zirkonarmen rekristallisierten legierung

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7520945B2 (en) 2003-12-16 2009-04-21 Alcan Rhenalu Recrystallized Al-Zn-Cu-Mg plate with low zirconium
US10301710B2 (en) 2005-01-19 2019-05-28 Otto Fuchs Kg Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product

Also Published As

Publication number Publication date
EP1544316B1 (de) 2012-03-07
EP1544316A3 (de) 2007-05-09
ES2383528T3 (es) 2012-06-21
US20050167016A1 (en) 2005-08-04
ATE548476T1 (de) 2012-03-15
US7520945B2 (en) 2009-04-21

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