CN103146969A - High strength al-zn alloy and method for producing such an alloy product - Google Patents
High strength al-zn alloy and method for producing such an alloy product Download PDFInfo
- Publication number
- CN103146969A CN103146969A CN201310039039XA CN201310039039A CN103146969A CN 103146969 A CN103146969 A CN 103146969A CN 201310039039X A CN201310039039X A CN 201310039039XA CN 201310039039 A CN201310039039 A CN 201310039039A CN 103146969 A CN103146969 A CN 103146969A
- Authority
- CN
- China
- Prior art keywords
- alloy
- alloy product
- weight
- product according
- amount
- 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
Links
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 181
- 239000000956 alloy Substances 0.000 title claims abstract description 181
- 238000004519 manufacturing process Methods 0.000 title description 11
- 229910001297 Zn alloy Inorganic materials 0.000 title 1
- 229910018137 Al-Zn Inorganic materials 0.000 claims abstract description 37
- 229910018573 Al—Zn Inorganic materials 0.000 claims abstract description 37
- 230000007797 corrosion Effects 0.000 claims abstract description 35
- 238000005260 corrosion Methods 0.000 claims abstract description 35
- 238000000034 method Methods 0.000 claims abstract description 26
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 15
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 15
- 239000004411 aluminium Substances 0.000 claims abstract description 13
- 229910052802 copper Inorganic materials 0.000 claims description 24
- 230000032683 aging Effects 0.000 claims description 23
- 229910052749 magnesium Inorganic materials 0.000 claims description 23
- 238000005266 casting Methods 0.000 claims description 16
- 230000006872 improvement Effects 0.000 claims description 13
- 238000010438 heat treatment Methods 0.000 claims description 10
- 238000007669 thermal treatment Methods 0.000 claims description 8
- 239000000203 mixture Substances 0.000 claims description 6
- 238000010791 quenching Methods 0.000 claims description 6
- 238000005242 forging Methods 0.000 claims 2
- 238000005482 strain hardening Methods 0.000 claims 2
- 229910052748 manganese Inorganic materials 0.000 abstract description 11
- 229910052726 zirconium Inorganic materials 0.000 abstract description 2
- 239000010949 copper Substances 0.000 description 39
- 239000011777 magnesium Substances 0.000 description 34
- 238000005496 tempering Methods 0.000 description 33
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 23
- 239000011701 zinc Substances 0.000 description 23
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 22
- 239000011572 manganese Substances 0.000 description 17
- 230000035882 stress Effects 0.000 description 16
- 239000000126 substance Substances 0.000 description 16
- 238000012360 testing method Methods 0.000 description 16
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 14
- 229910052725 zinc Inorganic materials 0.000 description 14
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 description 10
- 239000000243 solution Substances 0.000 description 8
- 229910000838 Al alloy Inorganic materials 0.000 description 7
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 7
- FAPWRFPIFSIZLT-UHFFFAOYSA-M Sodium chloride Chemical compound [Na+].[Cl-] FAPWRFPIFSIZLT-UHFFFAOYSA-M 0.000 description 6
- 230000006835 compression Effects 0.000 description 6
- 238000007906 compression Methods 0.000 description 6
- 230000000593 degrading effect Effects 0.000 description 5
- 239000012535 impurity Substances 0.000 description 5
- 230000000171 quenching effect Effects 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 239000010936 titanium Substances 0.000 description 4
- 230000002180 anti-stress Effects 0.000 description 3
- 238000005336 cracking Methods 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- 239000011780 sodium chloride Substances 0.000 description 3
- 229910000905 alloy phase Inorganic materials 0.000 description 2
- 238000005275 alloying Methods 0.000 description 2
- 238000000137 annealing Methods 0.000 description 2
- 230000023753 dehiscence Effects 0.000 description 2
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 description 2
- DZQLQEYLEYWJIB-UHFFFAOYSA-O 4-ammoniobutanal Chemical compound [NH3+]CCCC=O DZQLQEYLEYWJIB-UHFFFAOYSA-O 0.000 description 1
- 239000002970 Calcium lactobionate Substances 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 description 1
- 239000007864 aqueous solution Substances 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005097 cold rolling Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000000265 homogenisation Methods 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000004881 precipitation hardening Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- 229910052710 silicon Inorganic materials 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000007655 standard test method Methods 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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
- C22C21/10—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
Landscapes
- Chemical & Material Sciences (AREA)
- Organic Chemistry (AREA)
- Materials Engineering (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Forging (AREA)
- Heat Treatment Of Steel (AREA)
- Metal Rolling (AREA)
- Heat Treatment Of Articles (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laminated Bodies (AREA)
- Manufacture And Refinement Of Metals (AREA)
- Prevention Of Electric Corrosion (AREA)
Abstract
The present invention relates to a high strength Al-Zn alloy product with an improved combination of corrosion resistance and toughness, the alloy including essentially (in weight percent): Zn: 6.0-9.5, Cu: 1.3-2.4, Mg: 1.5-2.6, Mn and Zr<0.25 but preferably in a range between 0.05 and 0.15 for higher Zn contents, other elements each less than 0.05 and less than 0.25 in total, balance aluminium, wherein (in weight percent): 0.1[Cu]+1.3<[Mg]<0.2[Cu]+2.15. The invention also relates to a method to produce these alloy products, and to some preferred applications thereof such as upper wing applications in aerospace.
Description
The application is be on April 9th, 2004, denomination of invention the applying date for the application number of " production method of high strength Al-Zn alloy and this alloy product " be the dividing an application of patent application of 200480009567.X.
The present invention relates to the malleable high strength Al-Zn alloy with improvement solidity to corrosion and toughness combination according to claim 1, production method with malleable high strength Al-Zn alloy of improvement solidity to corrosion and toughness combination according to claim 9, and the plate product of the optional this alloy of producing according to this method.More specifically, the present invention relates to adopt aluminium association about the malleable high strength Al-Zn alloy of 7000-series of the international nomenclature name of structure aerospace applications.Even more specifically, the present invention relates to have improved strength, the new chemical composition range of the Al-Zn alloy of toughness and solidity to corrosion combination, it does not need special timeliness or temper.
People know and are relating in relative high strength, high tenacity and corrosion proof many application in this technical field, for example use heat treatable aluminium alloy in airframe, vehicle component and other are used.Aluminium alloy AA7050 and AA7150 show high strength in the tempering of T6-type, for example referring to US-6, and 315,842.In addition, the AA7x75 that separates out-harden, AA7x55 alloy product show intensity values in the T6 tempering.People know that the T6 tempering can improve alloy strength, and wherein above-mentioned AA7x50, AA7x75 and the AA7x55 alloy product that contains a large amount of zinc, copper and magnesium is known because of its high strength-to-weight ratio, and therefore are applied in airplane industry especially.Yet these application cause contacting with various weather condition, therefore need strict controlled working and aging condition so that suitable intensity and solidity to corrosion to be provided, and comprise that counter stress corrodes and degrade both solidity to corrosions.
In order to improve stress corrosion resistant and anti-degrading property and fracture toughness property, people know that these AA7000-series alloys are manually carried out overaging to be processed.When artificial aging is processed T79, T76, T74 or the tempering of T73-type, their stress corrosion resistant, anti-degrade corrodibility and fracture toughness property improves (T73 is best, and T79 is close to T6) according to described order, sacrificed intensity but compare with the T6 tempered condition.A kind of acceptable tempered condition is the T74-type tempering of the limited overaging condition between T73 and T76, in order to reach tensile strength, anticorrosion stress-resistant, the anti-acceptable level that degrades corrodibility and fracture toughness property.By alloy product was processed 6-24 hour and approximately carried out such T74 tempering in 14 hours under 171 ℃ in 121 ℃ of lower overaging of temperature.
According to the standard of particular aircraft part, even on intensity, toughness or solidity to corrosion, little improvement also can cause weight saving, this will change into the interior fuel oil saving of time limit of service of aircraft.In order to satisfy these requirements, developed the alloy of several other 7000-train types:
EP-0377779 discloses a kind of improved production method that is used for 7055 alloys of sheet applications (the top wing member that for example has high tenacity and good corrosive nature) in aerospace field, the method comprises the steps: the base substrate with following composition is processed, in % by weight:
Zn:7.6-8.4
Cu:2.2-2.6
Mg:1.8-2.1，
Be selected from one or more following elements:
Zr:0.5-0.2
Mn:0.05-0.4
V:0.03-0.2
Hf:0.03-0.5，
The total amount of described element is no more than 0.6 % by weight, and the aluminium of surplus adds incidental impurities; Described product is carried out solution heat treatment and quenching, and or heat product to one or more temperature of 79 ℃ to 163 ℃ by continuous three times, perhaps at first such product is heated to one or more temperature of 79 ℃ to 141 ℃ more than two hours or two hours, or heat product to one or more temperature of 148 ℃ to 174 ℃, this product is carried out artificial aging process.These products demonstrate " EB " or better anti-the degrading property of improvement, and the corresponding object of the AA7x50 of its yield strength ratio similar size under the T76-tempered condition is high by approximately 15%.The corresponding object of the 7x50-T77 of their similar sizes of their strength ratio is still high at least about 5% (this paper below will use AA7150-T77 as the reference alloy).
US-5,312,498 disclose the method for another kind of production aluminium-Ji alloy product, and this alloy product has improved anti-degrading property and fracture toughness property, has balanced zinc, copper and magnesium level, so that there is no excessive copper and magnesium.The production method of this aluminium-Ji alloy product has adopted a step or two step ageing treatment, and balanced in conjunction with the stoichiometry of copper, magnesium and zinc.Two step timeliness operations are disclosed, wherein at first about 121 ℃ of these alloys of ageing treatment approximately 9 hours, then by second timeliness step approximately 157 ℃ approximately 10-16 hour, air cooling subsequently.Such statutes of limitations are for the light sheet products that is used for lower wing, covering application or fuselage skin.
US-4,954,188 disclose a kind of method that aldural is provided, and it is characterized in that using anti-the degrading property of improvement of the alloy that is comprised of following alloying element, in % by weight:
Zn:5.9-8.2
Cu:1.5-3.0
Mg:1.5-4.0
Cr:<0.04，
Total amount is less than other element of 0.5 for example zirconium, manganese, iron, silicon and titanium, surplus is aluminium, this alloy is processed into the product of predetermined shape, the reshaping product is carried out solution heat treatment, quenching, and to this thermal treatment and quenching product at by the temperature of 132 ℃ to 140 ℃ ageing treatment 6-30 hour.By reducing aging temp rather than picture US-3 for example in the past, the rising temperature of instructing in 881,966 or US-3,794,531 can obtain high strength, high tenacity and the high corrosion resistance of needs in this alloy.
Once reported, known separating out under the T6 tempered condition-hardening aluminum alloy AA7075 and other AA7000-series alloy can not provide enough solidity to corrosions under certain conditions.Yet compare with the T6 condition, the T7-type tempering that improves these Alloy Anti stress corrosion crack character significantly reduces intensity.
Therefore US-5,221,377 disclose basically by about 7.6-8.4 % by weight Zn, approximately 1.8-2.2 % by weight Mg and the about alloy product that forms of 2.0-2.6 % by weight Cu.The yield strength ratio of alloy product has excellent toughness and the corresponding goods of corrosion proof 7x50-T6 are high by approximately 10% like this.It is reported that yield strength surpasses 579MPa, and have " EC " or better anti-degrading property (EXCO) level.
US-5,496,426 disclose as US-5, and 221, disclosed alloy in 377, and a kind of method, the method comprise hot bundle, annealing and cold rolling, and it is 20% to 70% that preferred shrinkage subtracts scope, preferably, correspondingly carry out controlled annealing, thereby demonstrate the performance that is better than the AA7075-T6 performance.Although AA7075-T6 does not test (the SCC resistance of 40 days in the 35%NaCl alternating immersion test) by anti-stress corrosiveness under 138MPa, disclosed processing alloy has 241MPa SCC drag.
US-5, 108, 520 and US-4, 477, 292 disclose a kind of technique of the precipitation-hardening metal alloy of solid solution-Re-processing being carried out timeliness, this technique comprises three step timeliness, comprise that (1) is being significantly higher than room temperature but at lower than one or more temperature of 163 ℃, this alloy aging is processed significantly lower than the peak value yield strength, (2) then approximately at one or more temperature of 190 ℃, this alloy is being carried out ageing treatment, in order to improve the solidity to corrosion of this alloy, after this (3) are being significantly higher than room temperature but at lower than one or more temperature of 163 ℃, this alloy is carried out ageing treatment, improve yield strength.The product that obtains demonstrates good strength characteristics and good corrosive property.But this three steps statutes of limitations trouble is difficult to carry out simultaneously, and the cost of therefore producing this alloy increases.
Therefore, the purpose of this invention is to provide a kind of improvement Al-Zn alloy that is preferred for plate product, this alloy has toughness and the corrosive property balance of high strength and improvement.More specifically, the purpose of this invention is to provide a kind of alloy, it can be used for having the top wing application of improvement compression yield strength in aerospace, and this alloy property is better than the performance of the conventional AA7055-alloy under the T77 tempering.
Another object of the present invention is to provide the AA7000-series alloys, and this alloy shows intensity and interior toughness and the corrosion resisting property of T73-type tempering range in T6-type tempering range.
In addition, an object of the present invention is to provide a kind of alloy, this alloy can be used for timeliness-creep forming technique, and it is a kind of alloy that does not need complexity or trouble aging technique.
The present invention has many preferred purposes.
Utilize feature claimed in claim 1 can reach above-mentioned purpose of the present invention.Describe in the dependent claims and describe in detail other preferred implementation.Define the preferred method of producing this alloy in claim 9, and require and described various plate products in claim 14 and corresponding subordinate-claim.
Should be understood that hereinafter, unless otherwise noted, alloy nomenclature and timeliness title mean the ABAL's title in US aluminum all Aluminum Standards and Data and the Registration Records that deliver of association.Unless otherwise noted, all percentage ratios are all weight percentage.
Use has the high strength Al-Zn alloy product of improvement solidity to corrosion and toughness combination can realize above-mentioned purpose of the present invention, and this alloy mainly comprises (in % by weight):
Zn is 6.0-9.5 approximately
Cu is 1.3-2.4 approximately
Mg is 1.5-2.6 approximately
Mn<0.12
Zr＜0.20, and preferred 0.05-0.15
Cr<0.10
Fe＜0.25, and preferred＜0.12
Si＜0.25, and preferred＜0.12
Ti<0.10
Hf and/or V＜0.25, and
Ce and/or Sc＜0.20 alternatively, especially in the 0.05-0.15 scope, other each element is all lower than 0.05, and total amount is lower than 0.25, surplus is aluminium, wherein (by weight percentage):
0.1[Cu]+1.3<[Mg]<0.2[Cu]+2.15，
And preferred 0.2[Cu]+1.3＜[Mg]＜0.1[Cu]+2.15.
When being processed into the sheet products that preferably can be used for the application of aerospace top wing, such chemical composition range of AA7000-series alloy shows fabulous performance.
Do not use above-mentioned trouble and complicated T77 timeliness circulation time, above-mentioned chemical constitution have with the T77-tempering under existing AA7x50 or the quite or better character of AA7x55 series alloy.The aluminium product that this chemical constitution obtains not only has good cost, and production is also simpler, because need procedure of processing still less.In addition, this chemical constitution allows to use new production technology, can not carry out the timeliness creep forming during as use T77-tempering alloy.Even better, previously defined chemical constitution timeliness can be become the T77-tempering, wherein compare with two step timeliness operations described below, solidity to corrosion also is improved, and has wherein especially improved the Peeling Corrosion characteristic.
By the present invention, when having found to use the particular combination of the Mg of relatively large Zn and specified range and Cu, the list of elements of selected scope reveals significantly better intensity, toughness and corrosive property combination, for example anti-degrading property and stress corrosion dehiscence resistant.
To have reported in order improving and to have degraded and the stress corrosion crack performance, copper content should keep highlyer, preferably higher than about 2.2 % by weight, it is reported and uses relatively low zinc content can reach better intensity and density combinations.
But, in the present invention, found that the relation that improves the zinc amount and optimize magnesium and copper can obtain better intensity, keep simultaneously good corrosive property and the toughness that is better than conventional T77-tempering alloy.Therefore, when advantageously not containing any manganese, the total content scope of zinc, magnesium and copper is about 11.50-12.50 (in % by weight), and when manganese is arranged, lower than 11.00, this moment, manganese was preferably 0.06-0.12 (in % by weight).
The preferred amounts of magnesium is 0.2[Cu]+1.3＜[Mg]＜0.1[Cu]+2.15, more preferably 0.2[Cu]+1.4＜[Mg]＜0.1[Cu]+1.9.The scope of copper is about 1.5-2.1, and more preferably 1.5 to lower than 2.0.The balance of magnesium and copper is important for chemistry of the present invention.
Copper and magnesium are the important elements that improves alloy strength.The too low meeting of the amount of magnesium and copper causes strength decreased, yet the too high meeting of the amount of magnesium and copper makes the corrosive property of alloy product lower, also can cause the weldability problem of alloy product.Prior art adopt specific timeliness operation to improve intensity and use a small amount of magnesium and copper in order to obtain good corrosive property.In order to reach the inner feelings of tearing open of intensity, toughness and corrosive property, the amount (take % by weight) of having found copper and magnesium approximately 1.5-2.3 can provide good balance as thick alloy product.But this corrosive property is vital parameter for thin alloy product, therefore must use copper and the magnesium of small amount, thereby produces lower intensity.In the present invention's whole chemical constitutions required for protection, might reach now the strength level in T6-tempering alloys range, keep simultaneously and corrosive nature characteristic like T74-tempering alloy type.
Except the amount of magnesium and copper, the invention discloses the amount of magnesium and copper and the balance of zinc, particularly make this alloy have the balance of magnesium and the zinc of these performance characteristics.The improvement solidity to corrosion of alloy of the present invention has EB or better, preferred EA or the better anti-performance (" EXCO ") of degrading.
These degrade performance according to stress corrosion dehiscence resistant (" SCC ") and anti-degrading property (" EXCO ") standard test, become at present AA7075, AA7050 and the AA7150-product of T73, T74 and T76 tempering for ageing treatment, and typical T6 tempering property needs.In order to determine whether commercial alloys satisfies the SCC standard, make the test sample of appointment stand the effect of predetermined test conditions.Allow bar-shaped sample stand such circulation: flooded in the 3.5%NaCl aqueous solution 10 minutes, then dry air is 50 minutes, stretches from two ends with constant strain (stress level) simultaneously.Usually carried out such test minimum 20 days (if before finishing in 20 days sample lost efficacy or cracking be time still less).This test is ASTM standard G47 (G47-98) test.
For the extruded alloy product that comprises light sheet products, adopt another preferred SCC-test of carrying out according to ASTM standard G47 (G38-73).This test comprises the opposite end of adopting constant strain level and alternating impregnating condition compression C-shape substantially similar to the above to encircle.Although AA7075, AA7050 or AA7150-T6 tempering alloy SCC test failure within less than the time of 20 days, and to degrade performance be EC or ED, and the solidity to corrosion characteristic increases with tempering T76-, T74-, T73.The characteristic of degrading of T73 is EA or better.This paper the following describes specific embodiment.
The amount of zinc (in % by weight) is approximately 8.1 o'clock, and the chemical constitution of alloy of the present invention has approximately 1.93 magnesium and the preferred amounts of copper.But, if manganese lower than 0.05, and preferably lower than 0.02, the amount of zinc (in % by weight) is 6.1-8.3, more preferably 6.1-7.0.Preferred implementations more of the present invention have been described in this paper the following examples.
The amount of zinc was higher than 7.6 o'clock, and the amount of manganese (in % by weight) is preferably approximately 0.06-0.12.In the operating period that may cause the alloy microstructure recrystallize, manganese helps or helps to control grain-size.This preferred manganese level is lower than the AA7000-series alloy of routine, but zinc level is when raising, and the manganese level can raise.
The amount of other alloying element Ce and/or Sc is lower than 0.20, preferred 0.05-0.15, preferred approximately 0.10.
Have the preferred production process of the malleable high strength Al-Zn alloy product of improvement solidity to corrosion and toughness combination, the method comprises the steps:
A) casting has the ingot casting of following composition (by weight percentage):
Zn is 6.0-9.5 approximately
Cu is 1.3-2.4 approximately
Mg is 1.5-2.6 approximately
Mn<0.12
Zr＜0.20, preferred 0.05-0.15
Cr<0.10
Fe<0.25
Si<0.25
Ti<0.10
Hf and/or V＜0.25, Ce and/or Sc＜0.20 alternatively,
Other each element is all lower than 0.05, and total amount is lower than 0.25, and surplus is aluminium, and wherein (by weight percentage):
0.1[Cu]+1.3<[Mg]<0.2[Cu]+2.15，
B) after the casting to ingot homogenization and/or preheat,
C) ingot casting is carried out hot-work and is cold worked into alternatively converted products,
D) solution heat treatment under being enough to make the temperature and time condition during all soluble components enter sosoloid basically of this alloy, and
E) by a kind of method in spray quenching or the quenching of the submergence in water or other quenchant, the solution heat treatment product is quenched.
Also can further realize characteristic of the present invention by preferred method, preferred method comprises carries out the artificial aging processing to processing and solution heat treatment product, wherein the timeliness step is included in temperature 105-135 ℃, the preferred approximately thermal treatment for the first time under 120 ℃ 2-20 hour, preferred approximately 8 hours, and higher than 135 ℃, but lower than 210 ℃, at the temperature of preferred 155 ℃ thermal treatment 4-12 hour for the second time, preferred approximately 8-10 hour.
By such two step ageing treatment, obtain and corrosive property like T76-tempering alloy corrosion property class.But, can also carry out artificial aging to processing and heat treated article, wherein this timeliness step is included at 105-135 ℃ of temperature thermal treatment for the third time more than 20 hours, below 30 hours.This T77-temper aging operation is known, and compares with two-step timeliness operation and can also improve its performance characteristic.But two-step timeliness operation can obtain thin alloy product, and these product sections and T77-tempered product quite and partly are better than T77-tempering goods.
In addition, also may adopt two-step timeliness operation will process with the heat treated article artificial aging and be processed into T79-or T76-tempering.After casting, after ingot casting is carried out homogenizing and/or preheats, preferably ingot casting is carried out hot-work, and optional this hot-work product is cold worked into the 15-45mm converted products, thereby obtain thin plate.
The alloy that employing has the alloy of above-mentioned composition or production according to the method described above can obtain this high strength Al-Zn sheet alloy product.Such plate product preferably can be used as thin aircraft component, more preferably as the structural shape member that extends.Even more preferably as the top wing member, be preferably used as the plate product of the thin skin member of aircraft top wing or stringer.
By the detailed description of following preferred embodiment, will become apparent according to aforementioned and further feature and the advantage of alloy of the present invention.
Embodiment 1
For comparing, the performance to alloy of the present invention and AA7150-T77 alloy tests.Find, the embodiment of alloy of the present invention demonstrates the improvement with respect to conventional AA7150-T77-tempering alloy.
According to technical scale, four kinds of different aluminum alloy casts are caused ingot, homogenizing, 410 ℃ of preheatings more than 6 hours and be rolled into the sheet material of 30 millimeters.After this, these sheet materials are carried out solution heat treatment at 475 ℃ and then carry out shrend.Then adopt two after this ,-step T79-T76 timeliness operation is carried out ageing treatment to the product that quenches.Chemical constitution is as shown in table 1.
Table 1
The chemical constitution of sheet alloy (take % by weight), surplus are aluminium and inevitable impurity, the Mn of alloy 1-4≤0.02:
After this according to following test conditions, this aging alloy is tested:
Measure tensile yield strength according to EN10.002, measure the anti-characteristic (" EXCO ") of degrading according to ASTM G-34-97, measure stress corrosion crack (" SCC ") according to ASTM G-47-98, all are measured Kahn-Tear (toughness) and measure compression yield strength (" CYS ") according to ASTM E-9 according to ASTM E-399 all along the ST-direction.
Listed the result of the T79-T76 timeliness plate product of four kinds of alloys as shown in table 1, wherein with the AA7150-T77 tempering alloy ratio of routine than the time in table 2a, and with the AA7150-T76/T74/T6 tempering alloy ratio of routine than the time in table 2b:
Table 2a
The intensity of table 1 alloy (30 millimeters sheet material) and the comparison overview of toughness and three kinds of reference alloys (AA7150-T77), with alloy 1-4 timeliness to T79-T76:
Do not lose efficacy after NF=40 days.
Table 2b
The corrosive property of table 1 alloy (30 millimeters sheet material) and the comparison overview of three kinds of reference alloys (AA7150-T76, AA7150-T74, AA7150-T6); With alloy 1-4 timeliness to T79-T76:
| ? | The SCC threshold value |
| Alloy 1 | NF when 172MPa |
| Alloy 2 | NF when 240MPa |
| Alloy 3 | NF when 240MPa |
| Alloy 4 | NF when 240MPa |
| AA7150-T76 | 117-172MPa |
| AA7150-T74 | 240MPa |
| AA7150-T6 | <48MPa |
Do not lose efficacy after NF=40 days.
2a, b can find out by table, and alloy 1,2 and 4 demonstrates better intensity/toughness combination.Alloy 2,3 and 4 all has acceptable EXCO performance, and its interalloy 2,3 and 4 has than the much higher compression yield strength of alloy 1 (AA7050-alloy).Alloy 2 and 4 has makes them be very suitable for the balancing performance that the top wing in aerospace is used, thereby shows the balancing performance that is better than conventional 7150T77 alloy.But, can also use the T77 tempering to alloy of the present invention, as shown in table 3.
Table 3
Carry out the alloy 2 and 4 of tempering according to the T77 tempered condition, intensity, toughness and corrosive property overview.
Alloy 4 likely has been carried out other SCC test, wherein prepare alloy 4-sample (measuring the standard test methods of the stress corrosion cracking cracking susceptibility of AA7000-series aluminium alloy products) according to the operation of describing in ASTM G-47-98, and be exposed to aggressive atmosphere (according to estimate the alternately immerse of the standard implementation method of metal and Alloy Anti stress corrosion crack by alternately immerse in 3.5%NaCl solution) according to ASTM G-44-94.
As shown in table 4, alloy 4 samples are selected four different stress levels.To each stress level, make three samples be exposed to testing circumstance (ASTM G-44).Take out a sample after 1 week, and make two other sample expose 40 days.When period of contact does not occur ftractureing, measure its tensile property, as shown in table 4.
Table 4
Alloy 4 is exposed to four tensile strength performance overviews after different stress levels, applies prestress along the LT direction.
As can be seen from Table 4, do not measure the reduction of residual strength along with the increase of load, for the tensile strength performance of paying close attention to, this means measurable stress corrosion not occur after 40 days.
Embodiment 2
When the higher strength level of needs and toughness properties when not too important, the alloy that preferred conventional AA7055-T77 alloy is used as top wing, rather than AA7150-T77 alloy.Therefore, the invention discloses copper and the magnesium compositing range of optimization, it demonstrates with conventional AA7055-T77 alloy phase works as or better properties.
11 kinds of different aluminum alloy casts are caused ingot, and they have the listed following chemical constitution of table 5.
Table 5
The chemical constitution of 11 kinds of alloys (take % by weight), surplus are aluminium and inevitable impurity, Zr=0.08, Si=0.05, Fe=0.08.
| Alloy | Cu | Mg | Zn | Mn |
| 1 | 2.40 | 2.20 | 8.2 | 0.00 |
| 2 | 1.94 | 2.33 | 8.2 | 0.00 |
| 3 | 1.26 | 2.32 | 8.1 | 0.00 |
| 4 | 2.36 | 1.94 | 8.1 | 0.00 |
| 5 | 1.94 | 1.92 | 8.1 | 0.00 |
| 6 | 1.30 | 2.09 | 8.2 | 0.00 |
| 7 | 1.92 | 1.54 | 8.1 | 0.00 |
| 8 | 1.27 | 1.57 | 8.1 | 0.00 |
| 9 | 2.34 | 2.25 | 8.1 | 0.07 |
| 10 | 2.38 | 2.09 | 8.1 | 0.00 |
| 11 | 2.35 | 1.53 | 8.2 | 0.00 |
Preheat this casting alloy 6 hours under 410 ℃, then this alloy is rolled into and measures its intensity and property of toughness after 28 mm sizes.After this, carry out solution heat treatment and shrend at 475 ℃.120 ℃ of ageing treatment 8 hours and 155 ℃ of ageing treatment 8-10 hours (T79-T76-tempering).Result is as shown in table 6.
Table 6
Intensity and the toughness overview of 11 kinds of alloys of table 5 on the direction of indicating.
When alloy 3-8 and 11 demonstrated good property of toughness, alloy 1-5 and 9 and 10 demonstrated good strength characteristics.Therefore, alloy 3,4 and 5 demonstrates the well balanced of intensity and toughness, therefore, is clear that very zinc content (take % by weight) is at 8.1 o'clock, and copper content is higher than 1.3, and Mg content is higher than 1.6.This tittle is the lower limit of copper and magnesium scope.As can be seen from Table 6, when the level of copper and magnesium is too high (alloy 1,2,9 and 10), toughness will drop to unacceptable low-level.
Embodiment 3
Studied the impact of manganese on alloy property of the present invention.Discovery has in the alloy of high zinc content, and best manganese level is 0.05-0.12.As shown in table 7 and table 8.The chemical property that all are not mentioned and machined parameters be similar with embodiment 2 all.
Table 7
The chemical constitution (in % by weight) of three kinds of alloys (Mn-0, Mn-1 and Mn-2), surplus are aluminium and inevitable impurity, Zr=0.08, Si=0.05, Fe=0.08.
| Alloy | Cu | Mg | Zn | Mn |
| Mn-0 | 1.94 | 2.33 | 8.2 | 0.00 |
| Mn-1 | 1.94 | 2.27 | 8.1 | 0.06 |
| Mn-2 | 1.96 | 2.29 | 8.2 | 0.12 |
Table 8
3 kinds of alloys of table 7 are in intensity and the toughness overview of indicating direction.
As shown in table 8, when strength characteristics increases, property of toughness reduces.For the alloy of Gao Xinliang, the manganese level of optimization is 0.05-0.12.
Embodiment 4
When the higher strength level of needs and toughness properties when not too important, the alloy that preferred conventional AA7055-T77 alloy is used as top wing, rather than AA7150-T77 alloy.Therefore, the invention discloses copper and the magnesium compositing range of optimization, it demonstrates with conventional AA7055-T77 alloy phase works as or better properties.
Two kinds of different aluminum alloy casts are caused ingot, and they have following chemical constitution as listed in table 9.
Table 9
The chemical constitution of three kinds of alloys (in % by weight), surplus are aluminium and inevitable impurity, Zr=0.08, Si=0.05, Fe=0.08; (Ref=AA7055 alloy).
| Alloy | Si | Fe | Cu | Mn | Mg | Cr | Zn | Ti | Zr |
| 1 | 0.05 | 0.09 | 2.24 | 0.01 | 2.37 | 0.01 | 7.89 | 0.04 | 0.10 |
| 2 | 0.04 | 0.07 | 1.82 | 0.08 | 2.18 | 0.00 | 8.04 | 0.03 | 0.10 |
| Ref. | ? | ? | 2.1-2.6 | ? | 1.8-2.2 | ? | 7.6-8.4 | ? | ? |
Tested the strength characteristics of alloy 1 and 2.These characteristics are as shown in table 10.Alloy 2 carries out temper (T79-T76 and T77) according to two kinds of tempered condition.Measure reference alloy A A7055 (M-Ref) under the T77 tempering, given simultaneously the technical data (showing bright with Ref) of the AA7055 reference alloy under the T77 tempering.
Table 10
Alloy 2 under two kinds of alloys of the present invention of table 9, two kinds of tempered condition, the reference alloy (AA7055) measured are (M-Ref) and the intensity overview of technique thin plate (Ref).
| Alloy | Tempering | Rp-L | Rp-LT | Rp-ST | Rm-L | Rm-LT | Rm-ST |
| 1 | T79-T76 | 604 | 593 | 559 | 634 | 631 | 613 |
| 2 | T79-T76 | 612 | 598 | 571 | 645 | 634 | 618 |
| 2 | T77 | 619 | 606 | 569 | 640 | 631 | 610 |
| Ref | T77 | 614 | 614 | - | 634 | 641 | - |
| M-Ref | T77 | 621 | 611 | 537 | 638 | 634 | 599 |
Along the property of toughness of LT and TL direction and as shown in table 11 along compression yield strength characteristic and the corrosive property feature of L and LT direction.
Table 11
Toughness and the CYS performance of two kinds of alloys of the present invention on different tempered condition and different tests direction in table 9, NF=did not lose efficacy after 40 days at the stress level of appointment, otherwise pointed out the number of days that sample lost efficacy.
Alloy of the present invention has and tensile property like conventional AA7055-T77 alloy type.But, be better than conventional AA7055-T77 alloy in the performance of ST direction.In addition, stress corrosion characteristics is better than the AA055-T77 alloy.Therefore, alloy of the present invention can be used as and also can be used for the cheaper alternative of the AA7055-T77 tempering alloy of timeliness-creep forming, thereby shows excellent compression yield strength and solidity to corrosion.
Fully describe now the present invention, obviously for those skilled in the art, can make many changes and modification in the situation that do not deviate from purport and the scope of invention as herein described.The appended claims are to limit the present invention.
Claims (29)
1. have the combination of improvement solidity to corrosion and toughness through the high strength Al-Zn of forging alloy product, described alloy mainly comprises in % by weight:
Zn6.0-9.5
Cu1.3-2.4
Mg1.5-2.6
Mn<0.12
Zr<0.20
Cr<0.10
Fe<0.25
Si<0.25
Ti<0.10
Hf and V sum＜0.25, and
Randomly, Ce and Sc sum＜0.20,
Other element is separately lower than 0.05, and total amount is lower than 0.25, and surplus is aluminium, and wherein, in % by weight:
[(0.1×Cu)+1.3]<[Mg]<[(0.2×Cu)+2.15]，
And, in two step timeliness operations with described alloy artificial aging to T79 or T76 degree of temper.
2. Al-Zn alloy product according to claim 1, wherein, the amount of Mg is [(0.2 * Cu)+1.3]＜[Mg]＜[(0.1 * Cu)+2.15] in the scope of % by weight.
3. Al-Zn alloy product according to claim 1, wherein, the amount of Mg is [(0.2 * Cu)+1.4]＜[Mg]＜[(0.1 * Cu)+1.9] in the scope of % by weight.
4. Al-Zn alloy product according to claim 1, wherein, described alloy product has the above antistripping corrodibility " EXCO " of EB.
5. Al-Zn alloy product according to claim 1, wherein, described alloy product has the above antistripping corrosion " EXCO " of EA.
6. Al-Zn alloy product according to claim 1, wherein, the amount of Cu is 1.5-2.1 in the scope of % by weight.
7. Al-Zn alloy product according to claim 1, wherein, the amount of Cu is 1.5-2.0 in the scope of % by weight.
8. Al-Zn alloy product according to claim 1, wherein, the amount of Zr is 0.05-0.15 in the scope of % by weight.
9. Al-Zn alloy product according to claim 1, wherein, the amount of Zn is 8.1 o'clock in % by weight, the amount of Mg and Cu is 1.93 in % by weight.
10. Al-Zn alloy product according to claim 1, wherein, lower than 0.05 the time, the amount of Zn is 6.1-8.3 in the scope of % by weight as Mn.
11. Al-Zn alloy product according to claim 1, wherein, lower than 0.05 the time, the amount of Zn is 6.1-7.0 in the scope of % by weight as Mn.
12. Al-Zn alloy product according to claim 1, wherein, lower than 0.02 the time, the amount of Zn is 6.1-8.3 in the scope of % by weight as Mn.
13. Al-Zn alloy product according to claim 1, wherein, lower than 0.02 the time, the amount of Zn is 6.1-7.0 in the scope of % by weight as Mn.
14. Al-Zn alloy product according to claim 1, wherein, the amount of Zn was higher than 7.6 o'clock, and the amount of Mn is 0.06-0.12 in the scope of % by weight.
15. Al-Zn alloy product according to claim 1, wherein, the amount of Fe in % by weight lower than 0.12.
16. Al-Zn alloy product according to claim 1, wherein, the amount of Si in % by weight lower than 0.12.
17. Al-Zn alloy product according to claim 1, wherein, described two step timeliness operations are comprised of the following step: carried out at the temperature of 105 ℃ to 135 ℃ the first thermal treatment 2-20 hour; And, higher than 135 ℃ but carried out at lower than the temperature of 210 ℃ the second thermal treatment 4-12 hour.
18. Al-Zn alloy product according to claim 1, wherein, described product is plate product.
19. Al-Zn alloy product according to claim 1, wherein, described product is that thickness is the plate product of 15-45 millimeter.
20. Al-Zn alloy product according to claim 19, wherein, described plate product is thin aircraft component.
21. Al-Zn alloy product according to claim 19, wherein, described plate product is the elongated structure shaped element of aircraft.
22. Al-Zn alloy product according to claim 19, wherein, described plate product is the top wing member of aircraft.
23. Al-Zn alloy product according to claim 19, wherein, described plate product is the top wing thin skin member of aircraft.
24. Al-Zn alloy product according to claim 19, wherein, described plate product is the stringer of aircraft.
25. Al-Zn alloy product according to claim 19, wherein, described plate product is the stringer of aircraft top wing.
26. produce the method through the high strength Al-Zn of forging alloy product with improved combination of solidity to corrosion and toughness according to claim 1, described method comprises the steps:
A) casting has the ingot casting of following composition in % by weight:
Zn6.0-9.5
Cu1.3-2.4
Mg1.5-2.6
Mn<0.12
Zr<0.20
Cr<0.10
Fe<0.25
Si<0.25
Ti<0.10
Hf and/or V＜0.25,
Randomly, Ce and/or Sc＜0.20,
Other element is separately lower than 0.05, and total amount is lower than 0.25, and surplus is aluminium, wherein, and in % by weight:
[(0.1×Cu)+1.3]<[Mg]<[(0.2×Cu)+2.15]，
B) ingot casting after casting is carried out homogenizing and/or preheats,
C) ingot casting hot-work is carried out cold working with optional, becomes through converted products,
D) solution heat treatment,
E) will quench through the product of solution heat treatment, and
F) adopt two step timeliness operations will through processing and through the product artificial aging of solution heat treatment to T79 or T76 degree of temper.
27. method according to claim 26, wherein, the amount of Zr is 0.05-0.15 in the scope of % by weight.
28. method according to claim 26, wherein, described two step timeliness operations comprised the following steps: to carry out at the temperature of 105 ℃ to 135 ℃ the first thermal treatment 2-20 hour; And, higher than 135 ℃ but carried out at lower than the temperature of 210 ℃ the second thermal treatment 4-12 hour.
29. method according to claim 26, wherein, after the ingot casting after casting carries out homogenizing or preheats, with described ingot casting hot-work with optionally carry out cold working, become thickness and be the 15-45 millimeter through converted products.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP03076049 | 2003-04-10 | ||
| EP03076049.0 | 2003-04-10 | ||
| CN200480009567.XA CN1780925B (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200480009567.XA Division CN1780925B (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103146969A true CN103146969A (en) | 2013-06-12 |
| CN103146969B CN103146969B (en) | 2015-07-08 |
Family
ID=33041014
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310039039.XA Expired - Lifetime CN103146969B (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
| CN200480009567.XA Expired - Lifetime CN1780925B (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200480009567.XA Expired - Lifetime CN1780925B (en) | 2003-04-10 | 2004-04-09 | High strength al-zn alloy and method for producing such an alloy product |
Country Status (12)
| Country | Link |
|---|---|
| US (2) | US20050034794A1 (en) |
| JP (1) | JP4964586B2 (en) |
| CN (2) | CN103146969B (en) |
| AT (1) | AT502294B1 (en) |
| BR (1) | BRPI0409360A (en) |
| CA (2) | CA2519387C (en) |
| DE (1) | DE112004000596B4 (en) |
| ES (2) | ES2398002B2 (en) |
| FR (1) | FR2853666B1 (en) |
| GB (1) | GB2415203B (en) |
| RU (1) | RU2353699C2 (en) |
| WO (1) | WO2004090183A1 (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103667825A (en) * | 2013-12-30 | 2014-03-26 | 上海华峰新材料研发科技有限公司 | Ultra-strong strength, high-toughness and anticorrosive aluminum alloy and preparation method for same |
| CN106435303A (en) * | 2016-03-07 | 2017-02-22 | 中安顺兴（北京）安全技术有限公司 | High-strength high-toughness rare earth aluminum alloy material and preparation method thereof |
| CN107245617A (en) * | 2017-06-13 | 2017-10-13 | 上海新益电力线路器材有限公司 | A kind of power circuit power transmission and transformation aluminium alloy element and preparation method thereof |
| CN108179332A (en) * | 2017-12-29 | 2018-06-19 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar and its production method |
| CN108220845A (en) * | 2017-12-29 | 2018-06-29 | 西南铝业（集团）有限责任公司 | A kind of solid solution aging technique of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN113373356A (en) * | 2021-06-21 | 2021-09-10 | 哈尔滨工程大学 | Al-Zn-Mg-Cu-Re aluminum alloy and preparation method thereof |
| CN116287902A (en) * | 2023-03-21 | 2023-06-23 | 西安交通大学 | Al-Mg-Zn alloy wire for additive manufacturing and preparation method thereof |
| CN117161121A (en) * | 2023-09-06 | 2023-12-05 | 大庆冬青技术开发有限公司 | High-strength high-toughness rare aluminum alloy toughness ceramic oil pipe and downhole tool pipe column |
| CN117821815A (en) * | 2024-03-04 | 2024-04-05 | 鼎镁新材料科技股份有限公司 | High-strength coarse-grain-free Al-Zn-Mg-Cu aluminum alloy for motorcycle wheels and preparation method thereof |
Families Citing this family (74)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP4932473B2 (en) * | 2003-03-17 | 2012-05-16 | アレリス、アルミナム、コブレンツ、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツング | Method of manufacturing an integrated monolithic aluminum structure and aluminum products machined from the structure |
| GB2426979B (en) | 2003-04-10 | 2007-05-23 | Corus Aluminium Walzprod Gmbh | An Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties |
| US20060085528A1 (en) * | 2004-10-01 | 2006-04-20 | Steve Thomas | System and method for monitoring network communications for pestware |
| 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 |
| DE502005001724D1 (en) * | 2005-01-19 | 2007-11-29 | Fuchs Kg Otto | Quench-resistant aluminum alloy and method for producing a semifinished product from this alloy |
| CN100441715C (en) * | 2005-03-07 | 2008-12-10 | 东北轻合金有限责任公司 | Super large-scale aluminium alloy free forging piece and its prodn. method |
| 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 |
| US8157932B2 (en) * | 2005-05-25 | 2012-04-17 | Alcoa Inc. | Al-Zn-Mg-Cu-Sc high strength alloy for aerospace and automotive castings |
| US20060289093A1 (en) * | 2005-05-25 | 2006-12-28 | Howmet Corporation | Al-Zn-Mg-Ag high-strength alloy for aerospace and automotive castings |
| CN1303237C (en) * | 2005-09-19 | 2007-03-07 | 陈继忠 | Aluminium alloy screw and its manufacturing method |
| US8083871B2 (en) * | 2005-10-28 | 2011-12-27 | Automotive Casting Technology, Inc. | High crashworthiness Al-Si-Mg alloy and methods for producing automotive casting |
| EP2038447B1 (en) * | 2006-07-07 | 2017-07-19 | Aleris Aluminum Koblenz GmbH | Method of manufacturing aa2000-series aluminium alloy products |
| FR2907796B1 (en) | 2006-07-07 | 2011-06-10 | Aleris Aluminum Koblenz Gmbh | ALUMINUM ALLOY PRODUCTS OF THE AA7000 SERIES AND METHOD FOR MANUFACTURING THE SAME |
| US8840737B2 (en) | 2007-05-14 | 2014-09-23 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
| US8673209B2 (en) * | 2007-05-14 | 2014-03-18 | Alcoa Inc. | Aluminum alloy products having improved property combinations and method for artificially aging same |
| CN102066596B (en) | 2008-06-24 | 2016-08-17 | 阿勒里斯铝业科布伦茨有限公司 | There is the Al-Zn-Mg alloy product of the quenching sensitive of reduction |
| CN101407876A (en) * | 2008-09-17 | 2009-04-15 | 北京有色金属研究总院 | Aluminum alloy material for manufacturing large cross section main load-carrying structure member and preparation thereof |
| US8206517B1 (en) | 2009-01-20 | 2012-06-26 | Alcoa Inc. | Aluminum alloys having improved ballistics and armor protection performance |
| US9163304B2 (en) | 2010-04-20 | 2015-10-20 | Alcoa Inc. | High strength forged aluminum alloy products |
| RU2449047C1 (en) * | 2010-10-29 | 2012-04-27 | Федеральное государственное образовательное учреждение высшего профессионального образования "Национальный исследовательский технологический университет "МИСиС" | Method for obtaining superplastic sheet of high-strength aluminium alloy |
| CA2836261A1 (en) * | 2011-05-21 | 2012-11-29 | Questek Innovations Llc | Aluminum alloys |
| CN102251158A (en) * | 2011-07-09 | 2011-11-23 | 浙江巨科铝业有限公司 | Aluminium alloy for vehicle hub and preparation method thereof |
| CN102489973B (en) * | 2011-12-23 | 2013-08-28 | 东北轻合金有限责任公司 | Method for manufacturing aluminum alloy hollow section for sedan bumper |
| EP2662467A1 (en) * | 2012-04-22 | 2013-11-13 | Kaiser Aluminum Fabricated Products, LLC | Ultra-thick high strength 7xxx series aluminum alloy products and methods of making such products |
| CN102760508B (en) * | 2012-07-18 | 2014-05-28 | 中南大学 | High-conductivity creep-resistant aluminium alloy cable conductor containing Hf and Ce and preparation method thereof |
| CN102978549A (en) * | 2012-11-21 | 2013-03-20 | 中南大学 | Method for bending creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN102978544B (en) * | 2012-11-21 | 2014-08-20 | 中南大学 | Method for multilevel creep age forming of Al-Zn-Mg-Cu series aluminium alloy plate |
| CN103540875A (en) * | 2013-03-09 | 2014-01-29 | 中南大学 | Bending creep aging method for Al-Zn-Mg-Cu aluminum alloy plate |
| CN103409710A (en) * | 2013-07-05 | 2013-11-27 | 中南大学 | Aging heat treatment method of Al-Zn-Mg-Cu aluminum alloy |
| RU2553781C1 (en) * | 2014-03-07 | 2015-06-20 | Закрытое акционерное общество "Военно-промышленная инвестиционная группа "ВИЛС" | High-strength heat-treatable aluminium alloy and article made thereof |
| CN104789838A (en) * | 2014-05-07 | 2015-07-22 | 天长市正牧铝业科技有限公司 | Strong and tough aluminum alloy for baseball bat |
| CN104789836B (en) * | 2014-05-07 | 2017-05-24 | 天长市正牧铝业科技有限公司 | Lightweight high-strength aluminum alloy |
| CN104789839B (en) * | 2014-05-07 | 2017-06-30 | 天长市正牧铝业科技有限公司 | A kind of lightweight tenacity aluminum alloy |
| CN104789835A (en) * | 2014-05-07 | 2015-07-22 | 天长市正牧铝业科技有限公司 | High-strength and high-toughness aluminum alloy for baseball bat |
| CN104789837A (en) * | 2014-05-07 | 2015-07-22 | 天长市正牧铝业科技有限公司 | Aluminum alloy material used for manufacturing baseball bat |
| CN104047502B (en) * | 2014-05-26 | 2016-05-18 | 安徽盛达前亮铝业有限公司 | Door jamb |
| CN104060915B (en) * | 2014-05-26 | 2016-07-06 | 安徽盛达前亮铝业有限公司 | Inside open interior wing side plate |
| CN104060917B (en) * | 2014-05-26 | 2016-02-10 | 安徽盛达前亮铝业有限公司 | Side plate aluminium extruded sections under interior wing |
| CN104294117A (en) * | 2014-10-29 | 2015-01-21 | 严静儿 | High-ductility aluminum alloy |
| CN104294116A (en) * | 2014-10-29 | 2015-01-21 | 严静儿 | High-performance aluminum alloy |
| CN105838944B (en) * | 2015-01-16 | 2017-09-19 | 昆山捷安特轻合金科技有限公司 | A kind of carbody high strength weldable aluminium and preparation method thereof |
| CN106555086A (en) * | 2015-09-24 | 2017-04-05 | 湖南稀土金属材料研究院 | A kind of high strength anti-corrosion Al-Zn-Mg- (Cu) line aluminium alloy bar and preparation method thereof |
| CN105112746B (en) * | 2015-09-25 | 2017-05-17 | 沈阳工业大学 | High-strength Al-Zn-Mg-Cu-Ce-Y-Er-La-Sc wrought aluminum alloy and manufacturing method thereof |
| RU2613270C1 (en) * | 2015-10-20 | 2017-03-15 | Открытое акционерное общество "Всероссийский институт легких сплавов" (ОАО "ВИЛС") | HIGH-STRENGTH ALUMINIUM-BASED WROUGHT ALLOY OF Al-Zn-Mg-Cu-SYSTEM AND ARTICLE MADE THEREOF |
| EP3368702B1 (en) * | 2015-10-29 | 2023-08-16 | Howmet Aerospace Inc. | Improved wrought 7xxx aluminum alloys, and methods for making the same |
| SI3265595T1 (en) * | 2015-10-30 | 2019-05-31 | Novelis, Inc. | High strength 7xxx aluminum alloys and methods of making the same |
| RU2610190C1 (en) * | 2015-11-05 | 2017-02-08 | Федеральное государственное унитарное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" (ФГУП "ВИАМ") | High-strength aluminium alloy and article made of it |
| EP3181711B1 (en) * | 2015-12-14 | 2020-02-26 | Apworks GmbH | Aluminium alloy containing scandium for powder metallurgy technologies |
| DE102016001500A1 (en) * | 2016-02-11 | 2017-08-17 | Airbus Defence and Space GmbH | Al-Mg-Zn alloy for the integral construction of ALM structures |
| CN105935733A (en) * | 2016-06-14 | 2016-09-14 | 山东南山铝业股份有限公司 | Preparation method of large-size high-strength aluminum alloy forged cake |
| CN105964849A (en) * | 2016-06-14 | 2016-09-28 | 山东南山铝业股份有限公司 | Isothermal die forging technology for large-size high-strength aluminum alloy parts |
| CA3032261A1 (en) | 2016-08-26 | 2018-03-01 | Shape Corp. | Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component |
| 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 |
| CN106399775A (en) * | 2016-11-11 | 2017-02-15 | 湖北万佳宏铝业股份有限公司 | High-strength aluminum alloy material formula and preparation method thereof |
| RU2654224C1 (en) * | 2016-12-26 | 2018-05-17 | Российская Федерация, от имени которой выступает Государственная корпорация по космической деятельности "РОСКОСМОС" | Aluminum-based alloy for anti-meteorite protection |
| MX2019014060A (en) * | 2017-05-30 | 2020-02-05 | Obshchestvo S Ogranichennoy Otvetstvennostyu Obedinennaya Kompaniya Rusal Inzhenerno Tekh Tsentr | High-strength aluminium-based alloy. |
| FR3068370B1 (en) * | 2017-07-03 | 2019-08-02 | Constellium Issoire | AL-ZN-CU-MG ALLOYS AND PROCESS FOR PRODUCING THE SAME |
| CN107447140B (en) * | 2017-07-26 | 2019-02-05 | 广西大学 | A kind of high strength alumin ium alloy and preparation method thereof haveing excellent performance |
| FR3071513B1 (en) * | 2017-09-26 | 2022-02-11 | Constellium Issoire | HIGH STRENGTH AL-ZN-CU-MG ALLOYS AND METHOD OF MANUFACTURING |
| CN108149095A (en) * | 2017-12-29 | 2018-06-12 | 西南铝业（集团）有限责任公司 | A kind of production method of the strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar |
| CN107937776A (en) * | 2017-12-29 | 2018-04-20 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar |
| CN107937847A (en) * | 2017-12-29 | 2018-04-20 | 西南铝业（集团）有限责任公司 | A kind of homogenizing heat treatment of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| RU2691475C1 (en) * | 2018-09-24 | 2019-06-14 | Федеральное государственное автономное образовательное учреждение высшего образования "Национальный исследовательский технологический университет "МИСиС" | Cast aluminum alloy with cerium additive |
| ES2936261T3 (en) * | 2018-11-12 | 2023-03-15 | Novelis Koblenz Gmbh | 7xxx series aluminum alloy product |
| EP3670690A1 (en) | 2018-12-20 | 2020-06-24 | Constellium Issoire | Al-zn-cu-mg alloys and their manufacturing process |
| CA3125048A1 (en) | 2019-06-03 | 2021-02-18 | Novelis Inc. | Ultra-high strength aluminum alloy products and methods of making the same |
| BR112021026189A2 (en) * | 2019-06-24 | 2022-02-15 | Arconic Tech Llc | Improved thick 7xxx series forged aluminum alloys and methods for making the same |
| CN110592443B (en) * | 2019-08-27 | 2021-03-23 | 江苏大学 | Heat-resistant corrosion-resistant 680MPa-730MPa Ti alloyed aluminum alloy and preparation method thereof |
| CN111575618B (en) * | 2020-05-15 | 2021-07-02 | 江苏理工学院 | Treatment method for reducing cracking tendency of large-deformation rolling Al-Zn alloy |
| US20220145439A1 (en) * | 2020-11-11 | 2022-05-12 | Kaiser Aluminum Fabricated Products, Llc | High Strength and High Fracture Toughness 7xxx Aerospace Alloy Products |
| CN112941379A (en) * | 2021-01-22 | 2021-06-11 | 宁波胶点密封工业有限公司 | Aluminum alloy plate for producing die and preparation process thereof |
| EP4386097A1 (en) | 2022-12-12 | 2024-06-19 | Constellium Rolled Products Ravenswood, LLC | 7xxx wrought products with improved compromise of tensile and toughness properties and method for producing |
| WO2024126341A1 (en) | 2022-12-12 | 2024-06-20 | Constellium Rolled Products Ravenswood, Llc | 7xxx wrought products with improved compromise of tensile and toughness properties and method for producing |
Citations (7)
| 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 |
| GB2114601A (en) * | 1981-12-23 | 1983-08-24 | Aluminum Co Of America | High strength aluminum alloy resistant to exfoliation and method of heat treatment |
| US5108520A (en) * | 1980-02-27 | 1992-04-28 | Aluminum Company Of America | Heat treatment of precipitation hardening alloys |
| EP0587274A1 (en) * | 1992-08-13 | 1994-03-16 | Reynolds Metals Company | Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness and product thereof |
| US6315842B1 (en) * | 1997-07-21 | 2001-11-13 | Pechiney Rhenalu | Thick alznmgcu alloy products with improved properties |
| WO2002052053A1 (en) * | 2000-12-21 | 2002-07-04 | Alcoa Inc. | Aluminum alloy products and artificial aging nethod |
| EP0829552B1 (en) * | 1996-09-11 | 2003-07-16 | Aluminum Company Of America | Aluminium alloy products suited for commercial jet aircraft wing members |
Family Cites Families (98)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2249349A (en) * | 1939-08-23 | 1941-07-15 | Aluminum Co Of America | Method of hot working an aluminum base alloy and product thereof |
| BE639908A (en) * | 1962-11-15 | |||
| US3305410A (en) * | 1964-04-24 | 1967-02-21 | Reynolds Metals Co | Heat treatment of aluminum |
| US3418090A (en) * | 1966-03-14 | 1968-12-24 | Reynolds Metals Co | Composite aluminum article |
| US3674448A (en) * | 1969-04-21 | 1972-07-04 | Aluminum Co Of America | Anodic aluminum material and articles and composite articles comprising the material |
| DE2052000C3 (en) * | 1970-10-23 | 1974-09-12 | Fa. Otto Fuchs, 5882 Meinerzhagen | Use of a high-strength aluminum alloy |
| US3826688A (en) * | 1971-01-08 | 1974-07-30 | Reynolds Metals Co | Aluminum alloy system |
| US3881966A (en) * | 1971-03-04 | 1975-05-06 | Aluminum Co Of America | Method for making aluminum alloy product |
| US3857973A (en) * | 1971-03-12 | 1974-12-31 | Aluminum Co Of America | Aluminum alloy container end and sealed container thereof |
| US3791880A (en) * | 1972-06-30 | 1974-02-12 | Aluminum Co Of America | Tear resistant sheet and plate and method for producing |
| US3791876A (en) * | 1972-10-24 | 1974-02-12 | Aluminum Co Of America | Method of making high strength aluminum alloy forgings and product produced thereby |
| 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 |
| US4140549A (en) * | 1974-09-13 | 1979-02-20 | Southwire Company | Method of fabricating an aluminum alloy electrical conductor |
| US3984259A (en) * | 1975-08-22 | 1976-10-05 | Aluminum Company Of America | Aluminum cartridge case |
| FR2393070A1 (en) * | 1977-06-02 | 1978-12-29 | Cegedur | THERMAL TREATMENT PROCESS OF ALUMINUM ALLOY SHEETS |
| FR2409319A1 (en) * | 1977-11-21 | 1979-06-15 | Cegedur | THERMAL TREATMENT PROCESS FOR THIN 7000 SERIES ALUMINUM ALLOY PRODUCTS |
| JPS5953347B2 (en) * | 1979-09-29 | 1984-12-24 | 住友軽金属工業株式会社 | Manufacturing method of aircraft stringer material |
| JPS5929663B2 (en) * | 1980-12-24 | 1984-07-21 | 三菱アルミニウム株式会社 | High-strength Al alloy for baseball bats with excellent extrusion processability |
| JPS57161045A (en) * | 1981-03-31 | 1982-10-04 | Sumitomo Light Metal Ind Ltd | Fine-grain high-strength aluminum alloy material and its manufacture |
| JPS5852386A (en) * | 1981-09-24 | 1983-03-28 | Mitsubishi Oil Co Ltd | Preparation of raw material pitch for carbon fiber |
| US4954188A (en) * | 1981-12-23 | 1990-09-04 | Aluminum Company Of America | High strength aluminum alloy resistant to exfoliation and method of making |
| US4828631A (en) * | 1981-12-23 | 1989-05-09 | Aluminum Company Of America | High strength aluminum alloy resistant to exfoliation and method of making |
| JPS5928555A (en) * | 1982-08-06 | 1984-02-15 | Sumitomo Light Metal Ind Ltd | High tensile aluminum alloy good in extrudability and excellent in strength and toughness |
| US4711762A (en) * | 1982-09-22 | 1987-12-08 | Aluminum Company Of America | Aluminum base alloys of the A1-Cu-Mg-Zn type |
| US4589932A (en) * | 1983-02-03 | 1986-05-20 | Aluminum Company Of America | Aluminum 6XXX alloy products of high strength and toughness having stable response to high temperature artificial aging treatments and method for producing |
| JPS6013047A (en) * | 1983-06-30 | 1985-01-23 | Showa Alum Corp | High-strength aluminum alloy with superior cold workability |
| US4618382A (en) * | 1983-10-17 | 1986-10-21 | Kabushiki Kaisha Kobe Seiko Sho | Superplastic aluminium alloy sheets |
| US4713216A (en) * | 1985-04-27 | 1987-12-15 | Showa Aluminum Kabushiki Kaisha | Aluminum alloys having high strength and resistance to stress and corrosion |
| FR2601967B1 (en) * | 1986-07-24 | 1992-04-03 | Cerzat Ste Metallurg | AL-BASED ALLOY FOR HOLLOW BODIES UNDER PRESSURE. |
| JPS63297180A (en) * | 1987-05-27 | 1988-12-05 | 昭和アルミニウム株式会社 | Bicycle frame by adhesive structure |
| US5221377A (en) * | 1987-09-21 | 1993-06-22 | Aluminum Company Of America | Aluminum alloy product having improved combinations of properties |
| US4927470A (en) * | 1988-10-12 | 1990-05-22 | Aluminum Company Of America | Thin gauge aluminum plate product by isothermal treatment and ramp anneal |
| US4988394A (en) * | 1988-10-12 | 1991-01-29 | Aluminum Company Of America | Method of producing unrecrystallized thin gauge aluminum products by heat treating and further working |
| US4946517A (en) * | 1988-10-12 | 1990-08-07 | Aluminum Company Of America | Unrecrystallized aluminum plate product by ramp annealing |
| CA1340618C (en) * | 1989-01-13 | 1999-06-29 | James T. Staley | Aluminum alloy product having improved combinations of strength, toughness and corrosion resistance |
| US4976790A (en) * | 1989-02-24 | 1990-12-11 | Golden Aluminum Company | Process for preparing low earing aluminum alloy strip |
| FR2645546B1 (en) * | 1989-04-05 | 1994-03-25 | Pechiney Recherche | HIGH MODULATED AL MECHANICAL ALLOY WITH HIGH MECHANICAL RESISTANCE AND METHOD FOR OBTAINING SAME |
| JPH03140433A (en) * | 1989-10-27 | 1991-06-14 | Nkk Corp | High strength aluminum alloy having excellent corrosion resistance |
| US5213639A (en) * | 1990-08-27 | 1993-05-25 | Aluminum Company Of America | Damage tolerant aluminum alloy products useful for aircraft applications such as skin |
| US5186235A (en) * | 1990-10-31 | 1993-02-16 | Reynolds Metals Company | Homogenization of aluminum coil |
| US5277719A (en) * | 1991-04-18 | 1994-01-11 | Aluminum Company Of America | Aluminum alloy thick plate product and method |
| US5496423A (en) * | 1992-06-23 | 1996-03-05 | Kaiser Aluminum & Chemical Corporation | Method of manufacturing aluminum sheet stock using two sequences of continuous, in-line operations |
| US5356495A (en) * | 1992-06-23 | 1994-10-18 | Kaiser Aluminum & Chemical Corporation | Method of manufacturing can body sheet using two sequences of continuous, in-line operations |
| US5313639A (en) * | 1992-06-26 | 1994-05-17 | George Chao | Computer with security device for controlling access thereto |
| US5376192A (en) * | 1992-08-28 | 1994-12-27 | Reynolds Metals Company | High strength, high toughness aluminum-copper-magnesium-type aluminum alloy |
| FR2716896B1 (en) * | 1994-03-02 | 1996-04-26 | Pechiney Recherche | Alloy 7000 with high mechanical resistance and process for obtaining it. |
| JPH07316601A (en) * | 1994-03-28 | 1995-12-05 | Toyo Alum Kk | Production of rapidly solidified aluminum powder and aluminum alloy compact |
| US5919323A (en) * | 1994-05-11 | 1999-07-06 | Aluminum Company Of America | Corrosion resistant aluminum alloy rolled sheet |
| US5496426A (en) * | 1994-07-20 | 1996-03-05 | Aluminum Company Of America | Aluminum alloy product having good combinations of mechanical and corrosion resistance properties and formability and process for producing such product |
| FR2726007B1 (en) * | 1994-10-25 | 1996-12-13 | Pechiney Rhenalu | PROCESS FOR PRODUCING ALSIMGCU ALLOY PRODUCTS WITH IMPROVED INTERCRYSTALLINE CORROSION RESISTANCE |
| US5624632A (en) * | 1995-01-31 | 1997-04-29 | Aluminum Company Of America | Aluminum magnesium alloy product containing dispersoids |
| JP4208156B2 (en) * | 1995-02-24 | 2009-01-14 | 住友軽金属工業株式会社 | Manufacturing method of high strength aluminum alloy extruded material |
| US5681405A (en) * | 1995-03-09 | 1997-10-28 | Golden Aluminum Company | Method for making an improved aluminum alloy sheet product |
| EP0817870A4 (en) * | 1995-03-21 | 1998-08-05 | Kaiser Aluminium Chem Corp | A method of manufacturing aluminum aircraft sheet |
| CA2218024C (en) * | 1995-05-11 | 2008-07-22 | Kaiser Aluminum And Chemical Corporation | Improved damage tolerant aluminum 6xxx alloy |
| US5865911A (en) * | 1995-05-26 | 1999-02-02 | Aluminum Company Of America | Aluminum alloy products suited for commercial jet aircraft wing members |
| US5863359A (en) * | 1995-06-09 | 1999-01-26 | Aluminum Company Of America | Aluminum alloy products suited for commercial jet aircraft wing members |
| FR2737225B1 (en) * | 1995-07-28 | 1997-09-05 | Pechiney Rhenalu | AL-CU-MG ALLOY WITH HIGH FLUID RESISTANCE |
| US5718780A (en) * | 1995-12-18 | 1998-02-17 | Reynolds Metals Company | Process and apparatus to enhance the paintbake response and aging stability of aluminum sheet materials and product therefrom |
| US6027582A (en) * | 1996-01-25 | 2000-02-22 | Pechiney Rhenalu | Thick alZnMgCu alloy products with improved properties |
| EP0799900A1 (en) * | 1996-04-04 | 1997-10-08 | Hoogovens Aluminium Walzprodukte GmbH | High strength aluminium-magnesium alloy material for large welded structures |
| CA2279985C (en) * | 1997-02-19 | 2003-10-14 | Alcan International Limited | Process for producing aluminium alloy sheet |
| JP3705320B2 (en) * | 1997-04-18 | 2005-10-12 | 株式会社神戸製鋼所 | High strength heat treatment type 7000 series aluminum alloy with excellent corrosion resistance |
| WO1999031287A1 (en) * | 1997-12-12 | 1999-06-24 | Aluminum Company Of America | Aluminum alloy with a high toughness for use as plate in aerospace applications |
| US6224992B1 (en) * | 1998-02-12 | 2001-05-01 | Alcoa Inc. | Composite body panel and vehicle incorporating same |
| FR2789406B1 (en) * | 1999-02-04 | 2001-03-23 | Pechiney Rhenalu | ALCuMg ALLOY PRODUCT FOR AIRCRAFT STRUCTURAL ELEMENT |
| BR0008694A (en) * | 1999-03-01 | 2001-12-26 | Alcan Int Ltd | Method for aluminum sheet aa6000 |
| JP4053243B2 (en) * | 1999-03-18 | 2008-02-27 | コラス・アルミニウム・バルツプロドウクテ・ゲーエムベーハー | Weldable aluminum alloy structural material |
| FR2792001B1 (en) * | 1999-04-12 | 2001-05-18 | Pechiney Rhenalu | PROCESS FOR MANUFACTURING TYPE 2024 ALUMINUM ALLOY SHAPED PARTS |
| JP3494591B2 (en) * | 1999-06-23 | 2004-02-09 | 株式会社デンソー | Aluminum alloy brazing sheet with good corrosion resistance for vacuum brazing and heat exchanger using the same |
| RU2165995C1 (en) * | 1999-10-05 | 2001-04-27 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Highly string aluminium-based alloy and product made of said alloy |
| FR2802946B1 (en) * | 1999-12-28 | 2002-02-15 | Pechiney Rhenalu | AL-CU-MG ALLOY AIRCRAFT STRUCTURAL ELEMENT |
| FR2805282B1 (en) * | 2000-02-23 | 2002-04-12 | Gerzat Metallurg | A1ZNMGCU ALLOY PRESSURE HOLLOW BODY PROCESS |
| 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 |
| US6562154B1 (en) * | 2000-06-12 | 2003-05-13 | Aloca Inc. | Aluminum sheet products having improved fatigue crack growth resistance and methods of making same |
| RU2184166C2 (en) * | 2000-08-01 | 2002-06-27 | Государственное предприятие "Всероссийский научно-исследовательский институт авиационных материалов" | Aluminum-based high-strength alloy and product manufactured therefrom |
| JP4285916B2 (en) * | 2001-02-16 | 2009-06-24 | 株式会社神戸製鋼所 | Manufacturing method of aluminum alloy plate for structural use with high strength and high corrosion resistance |
| US20030051784A1 (en) * | 2001-03-20 | 2003-03-20 | Denzer Diana K. | Method for increasing the strength and/or corrosion resistance of 7000 series Al aerospace alloy products |
| US6543122B1 (en) * | 2001-09-21 | 2003-04-08 | Alcoa Inc. | Process for producing thick sheet from direct chill cast cold rolled aluminum alloy |
| JP4022491B2 (en) * | 2002-03-27 | 2007-12-19 | 株式会社神戸製鋼所 | Aluminum alloy bat |
| FR2838135B1 (en) * | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | CORROSIVE ALLOY PRODUCTS A1-Zn-Mg-Cu WITH VERY HIGH MECHANICAL CHARACTERISTICS, AND AIRCRAFT STRUCTURE ELEMENTS |
| FR2838136B1 (en) * | 2002-04-05 | 2005-01-28 | Pechiney Rhenalu | ALLOY PRODUCTS A1-Zn-Mg-Cu HAS COMPROMISED STATISTICAL CHARACTERISTICS / DAMAGE TOLERANCE IMPROVED |
| US20050006010A1 (en) * | 2002-06-24 | 2005-01-13 | Rinze Benedictus | Method for producing a high strength Al-Zn-Mg-Cu alloy |
| CA2485525C (en) * | 2002-06-24 | 2010-09-21 | Corus Aluminium Walzprodukte Gmbh | Method of producing high strength balanced al-mg-si alloy and a weldable product of that alloy |
| FR2842212B1 (en) * | 2002-07-11 | 2004-08-13 | Pechiney Rhenalu | A1-CU-MG ALLOY AIRCRAFT STRUCTURAL ELEMENT |
| FR2846669B1 (en) * | 2002-11-06 | 2005-07-22 | Pechiney Rhenalu | PROCESS FOR THE SIMPLIFIED MANUFACTURE OF LAMINATED PRODUCTS OF A1-Zn-Mg ALLOYS AND PRODUCTS OBTAINED THEREBY |
| US7060139B2 (en) * | 2002-11-08 | 2006-06-13 | Ues, Inc. | High strength aluminum alloy composition |
| CA2506393C (en) * | 2002-11-15 | 2009-10-27 | Alcoa Inc. | Aluminum alloy product having improved combinations of properties |
| JP4932473B2 (en) * | 2003-03-17 | 2012-05-16 | アレリス、アルミナム、コブレンツ、ゲゼルシャフト、ミット、ベシュレンクテル、ハフツング | Method of manufacturing an integrated monolithic aluminum structure and aluminum products machined from the structure |
| GB2426979B (en) * | 2003-04-10 | 2007-05-23 | Corus Aluminium Walzprod Gmbh | An Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties |
| US8043445B2 (en) * | 2003-06-06 | 2011-10-25 | Aleris Aluminum Koblenz Gmbh | High-damage tolerant alloy product in particular for aerospace applications |
| JP2005016937A (en) * | 2003-06-06 | 2005-01-20 | Denso Corp | Aluminum heat exchanger with excellent corrosion resistance |
| US20050095447A1 (en) * | 2003-10-29 | 2005-05-05 | Stephen Baumann | High-strength aluminum alloy composite and resultant 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 |
| US20070151636A1 (en) * | 2005-07-21 | 2007-07-05 | Corus Aluminium Walzprodukte Gmbh | Wrought aluminium AA7000-series alloy product and method of producing said product |
| FR2907796B1 (en) * | 2006-07-07 | 2011-06-10 | Aleris Aluminum Koblenz Gmbh | ALUMINUM ALLOY PRODUCTS OF THE AA7000 SERIES AND METHOD FOR MANUFACTURING THE SAME |
| EP2038447B1 (en) * | 2006-07-07 | 2017-07-19 | Aleris Aluminum Koblenz GmbH | Method of manufacturing aa2000-series aluminium alloy products |
| EP2389458B1 (en) * | 2009-01-22 | 2015-09-16 | Alcoa Inc. | Improved aluminum-copper alloys containing vanadium |
-
2004
- 2004-04-07 US US10/819,130 patent/US20050034794A1/en not_active Abandoned
- 2004-04-09 DE DE112004000596T patent/DE112004000596B4/en not_active Revoked
- 2004-04-09 ES ES201131194A patent/ES2398002B2/en not_active Expired - Fee Related
- 2004-04-09 JP JP2006505139A patent/JP4964586B2/en not_active Expired - Lifetime
- 2004-04-09 CA CA2519387A patent/CA2519387C/en not_active Expired - Lifetime
- 2004-04-09 ES ES200550065A patent/ES2288389A1/en active Pending
- 2004-04-09 GB GB0520502A patent/GB2415203B/en not_active Expired - Lifetime
- 2004-04-09 CN CN201310039039.XA patent/CN103146969B/en not_active Expired - Lifetime
- 2004-04-09 AT AT0911004A patent/AT502294B1/en not_active IP Right Cessation
- 2004-04-09 FR FR0403746A patent/FR2853666B1/en not_active Expired - Lifetime
- 2004-04-09 RU RU2005134846/02A patent/RU2353699C2/en active
- 2004-04-09 BR BRPI0409360-7A patent/BRPI0409360A/en not_active Application Discontinuation
- 2004-04-09 CN CN200480009567.XA patent/CN1780925B/en not_active Expired - Lifetime
- 2004-04-09 WO PCT/EP2004/003997 patent/WO2004090183A1/en not_active Application Discontinuation
- 2004-04-09 CA CA2881183A patent/CA2881183C/en not_active Expired - Lifetime
-
2009
- 2009-08-25 US US12/547,466 patent/US20090320969A1/en not_active Abandoned
Patent Citations (7)
| 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 |
| US5108520A (en) * | 1980-02-27 | 1992-04-28 | Aluminum Company Of America | Heat treatment of precipitation hardening alloys |
| GB2114601A (en) * | 1981-12-23 | 1983-08-24 | Aluminum Co Of America | High strength aluminum alloy resistant to exfoliation and method of heat treatment |
| EP0587274A1 (en) * | 1992-08-13 | 1994-03-16 | Reynolds Metals Company | Method of producing an aluminum-zinc-magnesium-copper alloy having improved exfoliation resistance and fracture toughness and product thereof |
| EP0829552B1 (en) * | 1996-09-11 | 2003-07-16 | Aluminum Company Of America | Aluminium alloy products suited for commercial jet aircraft wing members |
| US6315842B1 (en) * | 1997-07-21 | 2001-11-13 | Pechiney Rhenalu | Thick alznmgcu alloy products with improved properties |
| WO2002052053A1 (en) * | 2000-12-21 | 2002-07-04 | Alcoa Inc. | Aluminum alloy products and artificial aging nethod |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103667825B (en) * | 2013-12-30 | 2016-04-13 | 上海华峰新材料研发科技有限公司 | A kind of ultra-high-strength/tenacity anticorodal and manufacture method thereof |
| CN103667825A (en) * | 2013-12-30 | 2014-03-26 | 上海华峰新材料研发科技有限公司 | Ultra-strong strength, high-toughness and anticorrosive aluminum alloy and preparation method for same |
| CN106435303B (en) * | 2016-03-07 | 2018-08-03 | 中安顺兴（北京）安全技术有限公司 | A kind of high intensity, high-ductility rare earth aluminum alloy material and preparation method thereof |
| CN106435303A (en) * | 2016-03-07 | 2017-02-22 | 中安顺兴（北京）安全技术有限公司 | High-strength high-toughness rare earth aluminum alloy material and preparation method thereof |
| CN107245617A (en) * | 2017-06-13 | 2017-10-13 | 上海新益电力线路器材有限公司 | A kind of power circuit power transmission and transformation aluminium alloy element and preparation method thereof |
| CN107245617B (en) * | 2017-06-13 | 2019-07-05 | 上海新益电力线路器材有限公司 | A kind of power circuit power transmission and transformation aluminium alloy element and preparation method thereof |
| CN108220845A (en) * | 2017-12-29 | 2018-06-29 | 西南铝业（集团）有限责任公司 | A kind of solid solution aging technique of the strong 7 line aluminium alloy material of superelevation for heavy haul train draw bar |
| CN108179332A (en) * | 2017-12-29 | 2018-06-19 | 西南铝业（集团）有限责任公司 | A kind of strong 7 line aluminium alloy material of inexpensive superelevation for heavy haul train draw bar and its production method |
| CN113373356A (en) * | 2021-06-21 | 2021-09-10 | 哈尔滨工程大学 | Al-Zn-Mg-Cu-Re aluminum alloy and preparation method thereof |
| CN116287902A (en) * | 2023-03-21 | 2023-06-23 | 西安交通大学 | Al-Mg-Zn alloy wire for additive manufacturing and preparation method thereof |
| CN117161121A (en) * | 2023-09-06 | 2023-12-05 | 大庆冬青技术开发有限公司 | High-strength high-toughness rare aluminum alloy toughness ceramic oil pipe and downhole tool pipe column |
| CN117821815A (en) * | 2024-03-04 | 2024-04-05 | 鼎镁新材料科技股份有限公司 | High-strength coarse-grain-free Al-Zn-Mg-Cu aluminum alloy for motorcycle wheels and preparation method thereof |
| CN117821815B (en) * | 2024-03-04 | 2024-06-04 | 鼎镁新材料科技股份有限公司 | High-strength coarse-grain-free Al-Zn-Mg-Cu aluminum alloy for motorcycle wheels and preparation method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2353699C2 (en) | 2009-04-27 |
| AT502294B1 (en) | 2010-02-15 |
| JP4964586B2 (en) | 2012-07-04 |
| US20090320969A1 (en) | 2009-12-31 |
| DE112004000596B4 (en) | 2011-03-24 |
| WO2004090183A1 (en) | 2004-10-21 |
| DE112004000596T5 (en) | 2006-03-09 |
| GB2415203A (en) | 2005-12-21 |
| ES2398002B2 (en) | 2015-01-22 |
| CN103146969B (en) | 2015-07-08 |
| CA2519387C (en) | 2015-06-02 |
| GB2415203B (en) | 2007-01-03 |
| CN1780925B (en) | 2013-03-27 |
| ES2398002A1 (en) | 2013-03-13 |
| CA2881183A1 (en) | 2004-10-21 |
| BRPI0409360A (en) | 2006-04-25 |
| RU2005134846A (en) | 2006-04-10 |
| GB0520502D0 (en) | 2005-11-16 |
| CN1780925A (en) | 2006-05-31 |
| AT502294A1 (en) | 2007-02-15 |
| CA2519387A1 (en) | 2004-10-21 |
| FR2853666B1 (en) | 2007-05-11 |
| US20050034794A1 (en) | 2005-02-17 |
| CA2881183C (en) | 2018-06-12 |
| ES2288389A1 (en) | 2008-01-01 |
| FR2853666A1 (en) | 2004-10-15 |
| JP2006522872A (en) | 2006-10-05 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1780925B (en) | High strength al-zn alloy and method for producing such an alloy product | |
| CA2485524C (en) | Method for producing a high strength al-zn-mg-cu alloy | |
| EP3124633B1 (en) | An automotive suspension part and method for producing same | |
| EP2921567B1 (en) | Aluminum alloy material for high-pressure hydrogen gas containers and method for producing same | |
| EP0020505B1 (en) | Method of producing aluminum alloys | |
| US20160010195A1 (en) | Aluminum alloy that is not sensitive to quenching, as well as method for the production of a semi-finished product | |
| US7993474B2 (en) | Aircraft structural member made of an Al-Cu-Mg alloy | |
| CN105543595B (en) | High intensity, high formability, inexpensive aluminum-copper-lithium alloys | |
| US20020162609A1 (en) | Manufacturing process for a high strength work hardened product made of AlZnMgCu alloy | |
| CN105324501B (en) | Stressed-skin construction component on the wing prepared by aluminium, copper and lithium alloy | |
| US20030207141A1 (en) | Aircraft structure element made of an Al-Cu-Mg- alloy | |
| JP2008516079A5 (en) | ||
| JP2008516079A (en) | High strength, high toughness Al-Zn alloy products and methods for producing such products | |
| US11174535B2 (en) | Isotropic plates made from aluminum-copper-lithium alloy for manufacturing aircraft fuselages | |
| CN103834837A (en) | Al- Zn-Cu-Mg aluminum base alloys and methods of manufacture and use | |
| US20210292861A1 (en) | Process for manufacturing thin sheets made of 7xxx aluminum alloy suitable for shaping and assembly | |
| CN107709590A (en) | The metallic plate for motor vehicle body with high mechanical properties | |
| CN113302327A (en) | 7xxx series aluminum alloy products | |
| US20230220530A1 (en) | Use of products made from aluminium copper magnesium alloy that perform well at high temperature | |
| WO2005049878A2 (en) | Method for producing a high damage tolerant aluminium alloy | |
| CN109868400A (en) | A kind of low cost for high formability light sheet products, is substantially free of the aluminium lithium alloy of Zr | |
| CN109844151A (en) | The thin plate made of Al-Mg-Sc alloy for aerospace applications | |
| US20020014290A1 (en) | Al-si-mg aluminum alloy aircraft structural component production method | |
| EP3555333A1 (en) | Aluminum alloys and methods of making the same | |
| US20230313353A1 (en) | High strength and low quench sensitive 7xxx series aluminum alloys and methods of making |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Koblenz, Germany Patentee after: ALERIS ALUMINUM KOBLENZ GmbH Address before: Koblenz, Germany Patentee before: CORUS ALUMINIUM WALZPRODUKTE GmbH Address after: Koblenz, Germany Patentee after: Novelis Coblenz LLC Address before: Koblenz, Germany Patentee before: ALERIS ROLLED PRODUCTS GERMANY GmbH |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20230413 Address after: Koblenz, Germany Patentee after: ALERIS ROLLED PRODUCTS GERMANY GmbH Address before: Koblenz, Germany Patentee before: ALERIS ALUMINUM KOBLENZ GmbH |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20150708 |