CN109868400A - A kind of low cost for high formability light sheet products, is substantially free of the aluminium lithium alloy of Zr - Google Patents
A kind of low cost for high formability light sheet products, is substantially free of the aluminium lithium alloy of Zr Download PDFInfo
- Publication number
- CN109868400A CN109868400A CN201811464125.4A CN201811464125A CN109868400A CN 109868400 A CN109868400 A CN 109868400A CN 201811464125 A CN201811464125 A CN 201811464125A CN 109868400 A CN109868400 A CN 109868400A
- Authority
- CN
- China
- Prior art keywords
- weight
- aluminum
- copper
- lithium alloys
- thickness
- 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.)
- Pending
Links
- 239000001989 lithium alloy Substances 0.000 title claims abstract description 75
- 229910001148 Al-Li alloy Inorganic materials 0.000 title claims description 57
- FCVHBUFELUXTLR-UHFFFAOYSA-N [Li].[AlH3] Chemical compound [Li].[AlH3] FCVHBUFELUXTLR-UHFFFAOYSA-N 0.000 title description 7
- 229910000733 Li alloy Inorganic materials 0.000 claims abstract description 73
- -1 aluminum-copper-lithium Chemical compound 0.000 claims abstract description 65
- 238000000034 method Methods 0.000 claims abstract description 20
- 229910052782 aluminium Inorganic materials 0.000 claims abstract description 19
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical group [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims abstract description 18
- 239000012535 impurity Substances 0.000 claims abstract description 18
- 238000004519 manufacturing process Methods 0.000 claims abstract description 17
- 239000004411 aluminium Substances 0.000 claims abstract description 8
- 229910045601 alloy Inorganic materials 0.000 claims description 103
- 239000000956 alloy Substances 0.000 claims description 103
- 238000005266 casting Methods 0.000 claims description 19
- 230000032683 aging Effects 0.000 claims description 16
- 238000010438 heat treatment Methods 0.000 claims description 14
- 229910052726 zirconium Inorganic materials 0.000 claims description 14
- 238000010791 quenching Methods 0.000 claims description 11
- 230000000171 quenching effect Effects 0.000 claims description 11
- 229910000838 Al alloy Inorganic materials 0.000 claims description 10
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- 238000005096 rolling process Methods 0.000 claims description 9
- 238000005097 cold rolling Methods 0.000 claims description 8
- 229910052709 silver Inorganic materials 0.000 claims description 6
- 238000005098 hot rolling Methods 0.000 claims description 5
- 238000005242 forging Methods 0.000 claims description 3
- 238000001125 extrusion Methods 0.000 claims 1
- 229910000846 In alloy Inorganic materials 0.000 abstract description 3
- 239000011777 magnesium Substances 0.000 description 31
- 239000011701 zinc Substances 0.000 description 24
- 239000010949 copper Substances 0.000 description 17
- 230000007797 corrosion Effects 0.000 description 15
- 238000005260 corrosion Methods 0.000 description 15
- 239000000126 substance Substances 0.000 description 13
- 238000005452 bending Methods 0.000 description 11
- 239000013078 crystal Substances 0.000 description 11
- 229910052744 lithium Inorganic materials 0.000 description 10
- 229910052749 magnesium Inorganic materials 0.000 description 10
- 230000000694 effects Effects 0.000 description 8
- 239000000463 material Substances 0.000 description 8
- 238000012360 testing method Methods 0.000 description 8
- 230000008901 benefit Effects 0.000 description 7
- 238000001953 recrystallisation Methods 0.000 description 7
- 229910052748 manganese Inorganic materials 0.000 description 6
- 239000000243 solution Substances 0.000 description 6
- 229910001369 Brass Inorganic materials 0.000 description 5
- 239000010951 brass Substances 0.000 description 5
- 229910052802 copper Inorganic materials 0.000 description 5
- 238000010586 diagram Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 5
- 229910052725 zinc Inorganic materials 0.000 description 5
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 4
- 229910052742 iron Inorganic materials 0.000 description 4
- 238000005272 metallurgy Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 239000000654 additive Substances 0.000 description 3
- 230000000996 additive effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 239000006185 dispersion Substances 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 230000004044 response Effects 0.000 description 3
- 229910052710 silicon Inorganic materials 0.000 description 3
- 239000006104 solid solution Substances 0.000 description 3
- 238000005482 strain hardening Methods 0.000 description 3
- 230000035882 stress Effects 0.000 description 3
- 238000010998 test method Methods 0.000 description 3
- 229910001316 Ag alloy Inorganic materials 0.000 description 2
- 229910018182 Al—Cu Inorganic materials 0.000 description 2
- 229910000806 Latten Inorganic materials 0.000 description 2
- 229910000861 Mg alloy Inorganic materials 0.000 description 2
- 238000005275 alloying Methods 0.000 description 2
- 230000002929 anti-fatigue Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 239000011572 manganese Substances 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 239000010944 silver (metal) Substances 0.000 description 2
- 229910000679 solder Inorganic materials 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- PEDCQBHIVMGVHV-UHFFFAOYSA-N Glycerine Chemical compound OCC(O)CO PEDCQBHIVMGVHV-UHFFFAOYSA-N 0.000 description 1
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 238000002441 X-ray diffraction Methods 0.000 description 1
- 229910000928 Yellow copper Inorganic materials 0.000 description 1
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 description 1
- 229910001093 Zr alloy Inorganic materials 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 210000001787 dendrite Anatomy 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000005315 distribution function Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 239000008187 granular material Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 235000012771 pancakes Nutrition 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000004064 recycling Methods 0.000 description 1
- 238000001028 reflection method Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000010301 surface-oxidation reaction Methods 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/057—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with copper as the next major constituent
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B3/00—Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D25/00—Working sheet metal of limited length by stretching, e.g. for straightening
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D7/00—Casting ingots, e.g. from ferrous metals
- B22D7/005—Casting ingots, e.g. from ferrous metals from non-ferrous metals
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/14—Alloys based on aluminium with copper as the next major constituent with silicon
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/16—Alloys based on aluminium with copper as the next major constituent with magnesium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/12—Alloys based on aluminium with copper as the next major constituent
- C22C21/18—Alloys based on aluminium with copper as the next major constituent with zinc
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21B—ROLLING OF METAL
- B21B3/00—Rolling materials of special alloys so far as the composition of the alloy requires or permits special rolling methods or sequences ; Rolling of aluminium, copper, zinc or other non-ferrous metals
- B21B2003/001—Aluminium or its alloys
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Metal Rolling (AREA)
Abstract
A kind of low cost is disclosed, Zr, the 2xxx aluminum-copper-lithium alloys of low-density are substantially free of.Aluminum-copper-lithium alloys can be produced into the panel products of high formability, be capable of forming with a thickness of the modified product of 0.01 " to 0.249 ".Aluminum-copper-lithium alloys of the invention include the Cu of 3.2 to 4.1 weight %, the Li of 1.0 to 1.8 weight %, the Mg of 0.8 to 1.2 weight %, the Zn of 0.10 to 0.50 weight %, the Mn of 0.10 to 1.0 weight %, the at most Si of 0.12 weight %, the at most Fe of 0.15 weight %, the at most Ti of 0.15 weight %, the at most impurity element of 0.15 weight %, the total amount of these impurity elements is no more than 0.35 weight %, and difference is aluminium.Ag should not be intentionally added, and should not be used as the element unintentionally added and more than 0.1 weight %.Zr should not be intentionally added, and should not be used as the element unintentionally added and more than 0.05 weight %.In alloy of the invention, weight percent of the Mg at least equal to or higher than 2 × Zn.Additionally provide the method that manufacture includes the modified product of aluminum-copper-lithium alloys of the invention.
Description
Technical field
Present invention relates in general to Solder for Al-Cu Joint Welding-lithium-magnesium base alloy products.
Background technique
In order to reduce aircraft weight energetically to obtain better fuel efficiency, fuselage and aluminum material manufacturer are being accumulated
Low-density aluminum-copper-lithium alloys are sought in polar region.Forming process is extremely important for manufacture complex parts, especially for needing aluminium sheet
Aircraft application.Although formability is critically important, fuselage manufacturer it is also expected to lower density, higher intensity, preferably it is resistance to
Corrosivity and higher fracture toughness, to realize weight saving, lower aircraft maintenance and operation cost.
Aluminium-lithium (Al-Li) product of production thin plate is a kind of extreme metallurgy and technological challenge, wherein the strength of materials,
High-performance is also required in terms of formability, fracture toughness, fatigue resistance and corrosion resistance.
Metallurgical target first is that obtaining desired microstructure and texture to provide desired performance.For thin plate,
Al-Li product, this is especially difficult to control.Microstructure and texture are (i.e. equal by the chemical component of alloy and most of manufacturing steps
Change, hot rolling and cold rolling, annealing, solution heat treatment and stretching) strong influence.
Al-Li plate, especially thin plate are more difficult to manufacture than traditional 2xxx and 7xxx alloy.This is thin Al-Li plate to rolling
The result that system cracks, surface oxidation and deformation are more sensitive.Due to these limitations, there is a small process window to can be used for optimizing institute
Desired microstructure and texture.
Therefore, this is a significant challenge for design aluminium-lithium plate alloy, which realizes desired performance
Combination (intensity, formability and cost have good damage tolerance and corrosion resistance).The serious limitation of these manufacturing technologies challenge
The production of high-intensitive thin plate Al-Li product.
Therefore, only a kind of Al-Li alloy, i.e. AA2090, be registered as thickness less than 0.063 " rolling panel products,
And only a kind of additional alloy, i.e. AA2198, be registered as thickness less than 0.125 " rolling panel products, and only
Two additional alloys, i.e. AA2195 and AA2199, registration for thickness less than 0.5 " milled sheet/plate product, based on by
Aluminum Association (The Aluminum Association) is in " the Registration Record Series-of publication in 2011
Tempers for Aluminum and Aluminum Alloys Production " and 2017 publication
“Addendum to 2011Tan Sheets of Registration Record Series–Tempers for
Aluminum and Aluminum Alloys Production”。
It is also be reflected in patents and patent applications for these metallurgy of rolled sheet product and technological challenge.In fact,
A large amount of patent or patent application relate generally to plate product (> 0.5 "), but only a small number of suitable for panel products.
From the perspective of formability, desired metallurgical structure will be with fine recrystallization grains.This is to obtain institute
It is expected that the key feature of formability.Grain structure can be influenced by both chemistry and machined parameters.Chemically from the point of view of angle, many institutes
The known Zr that adds extensively in most of Al-Li and 7xxx alloy series is as grain structure control element.By 2017 1
" the International Alloy Designation and Chemical Composition Limits for of moon publication
In Wrought Aluminum and Wrought Aluminum Alloys ", there are 29 kinds of activity in Aluminum Association registration
Aluminium lithium alloy.All 29 kinds of alloys all contain Zr.Meanwhile there are many Al-Li patents and patent applications containing Zr.
Although it is believed that Zr prevents the recrystallization of most conventional aluminium alloy as the addition of dispersion element of volume, but for having
The Al-Li alloy of more complicated alloying element, unclear or not exclusively understanding.One research is claimed in Al-Li alloy
Zr is added to form relevant Al3Zr phase, this effectively prevents recrystallizations, but produce with the strong of obvious crystal texture
" thin pancake (pan cake) " shape distortion grain structure.However, another research is claimed, due in AA2198 type Al-Li alloy
The other elements of middle addition such as Mn, Zr confrontation recrystallization are invalid.Another research is drawn a conclusion, in Al-Li alloy Zr and
There are extremely complex interactions between other dispersion element of volume, and author thinks that Zr prevents from recrystallizing with low-down
Effect because Zr has low-down solute degree of supersaturation in the dendrite near border that can occur of recrystallization most probable.
Other than Zr is to the complex effects of recrystallization, influence of the Zr addition to intensity is further complicated, because it can
Hardening constituent relevant to Li can potentially be influenced.Studies have shown that Al3Up to 1.3% Li can be absorbed in Zr, causes potential low
Intensity.
In short, the prior art it is clear or significantly about Zr in aluminium-lithium thin product to recrystallization or crystal texture
Or the introduction of the influence of intensity.
The cost of Al-Li alloy product is also challenging.Silver-colored (Ag) is added to many a new generation's Al-Li alloys
In, to improve final products performance, increase significant cost of alloy.The registered Al-Li alloy sheets of four kinds be previously mentioned
In product, two of them (AA2198 and AA2195) contains Ag.In addition, Ag is very popular in Al-Li alloy, such as a large amount of Al-
Li alloy patents and patent applications are shown.Therefore, inexpensive Al-Li plate is provided by eliminating the addition of Ag while keeping
The properties of product shown such as these prior art examples that Ag is provided are a significant challenges.
Based on registered AA2198Al-Li plate alloy, it is known that applied for aircraft body or light plate gauge slab
Aluminum-copper-lithium alloys.The alloy includes the Ag of 0.1 to 0.8 weight %, therefore is not considered as low-cost alloy.In addition, it have pair
In the relatively low intensity of Al-Li alloy.
Based on registered AA2060Al-Li alloy, it is known that have the aluminum-copper-magnesium alloys of the lithium addition of auxiliary.It is required that protecting
The lithium content of shield is only 0.01 to 0.8 weight %；Since this limited lithium adds, this is not considered as real " low-density "
Alloy.
Based on registered AA2055Al-Li alloy, it is known that a kind of improved aluminum-copper-lithium alloys.The alloy includes 0.3
It to the Ag of 0.7 weight %, therefore is not considered as low-cost alloy.The alloy is squeezed for high-intensitive.
Based on registered AA2050Al-Li thick plate alloys, it is known that have the alloy of wide chemical composition ranges, including 0.2
To the Ag of 0.8 weight %.This is not considered as low-cost alloy.AA2050 is designed for 12.7mm (0.5 ") to 127mm (5 ")
Plate product and Ag including 0.15 to 0.35 weight %.In addition, the alloy be suitable for thickness range be 30mm (1.2 ") extremely
The slab of 100mm (3.9 ").
Known another kind aluminium alloy, the Ag including 0.05 to 1.2 weight %, therefore be not considered as low-cost alloy.It should
The major advantage of alloy is that have high intensity, ductility, excellent solderability and natural aging response.
In general, currently associated teaching in prior art: (1) needing low-density, high formability, low cost, high intensity strongly
And good damage tolerance and corrosive nature, it is able to produce the Al-Li alloy of light sheet products；(2) producing such product is one
Item extreme metallurgy and technological challenge；(3) expensive Ag additive is to obtain better metallurgical quality, but this significant increase
The cost of Al-Li product.(4) Zr is added to extensively in Al-Li alloy, but acts on it unclear.
Summary of the invention
The present invention provides low cost, and high formability is substantially free of the low-density Al-Li alloy of Zr, and it is suitable for manufactures to transport
Defeated component, such as aerospace structural members.Aluminum-copper-lithium alloys of the invention include 3.2 to 4.1 weight % Cu, 1.0 to 1.8
The Li of weight %, the Mg of 0.8 to 1.2 weight %, the Zn of 0.10 to 0.50 weight %, the Mn of 0.10 to 1.0 weight %, at most
The Si of 0.12 weight %, the at most Fe of 0.15 weight %, the at most Ti of 0.15 weight %, the impurity member of at most 0.15 weight %
The total amount of element, these impurity elements is no more than 0.35 weight %, and difference is aluminium.0.1 weight % is not to be exceeded in Ag, and preferably not
It intentionally adds.0.05 weight % is not to be exceeded in Zr, and does not preferably intentionally add.In alloy of the invention, Mg
Weight percent at least equal to or higher than 2 × Zn.Additionally provide the method for manufacture deformation aluminum-copper-lithium alloys product of the invention.
Preferably, aluminum-copper-lithium alloys of the invention are the more preferable 0.01-0.125 inchs with a thickness of 0.01-0.249 inches
Plate, squeeze out or forging deformation product.It was surprisingly found that aluminum-copper-lithium alloys of the invention are non-without Ag or very small amount of
The Ag intentionally added, without the Zr or very small amount of Zr unintentionally added and high Mg content, be able to produce with a thickness of
0.01 to 0.249 inch of panel products, with excellent formability, low-density, low cost, high intensity and good damage
Hurt tolerance and corrosion resistance.Another aspect of the present invention is the method for manufacture aluminum-copper-lithium alloys of the invention.
Detailed description of the invention
By the way that below in conjunction with attached drawing detailed description of the preferred embodiment, the features and advantages of the present invention will become aobvious and easy
See, in which:
Fig. 1 is the to show Al-Li T3 state 0.05 " figure of the forming limit diagram (FLD) of the plate of plate gauge；
Fig. 2 is the figure for showing the forming limit diagram (FLD) of plate of Al-Li T3 state 0.09 " to 0.1 " plate gauge；
" the density between the invention alloy and non-invention alloy sheets of the low cost of the not argentiferous of thickness that Fig. 3 is to show 0.05
With the combined comparison figure of bending property；
Fig. 4 is shown between the invention alloy and non-invention alloy sheets of the low cost without Ag of 0.09 " to 0.11 " thickness
Density and bending property combined comparison figure；
Fig. 5 is to show 0.05 " plate LT TYS of different aging times under the aging temp of 330 ℉ figure；
Fig. 6 is the combined figure for showing the ratio tensile yield strength (TYS) and minimum bend ratio in the direction LT；
Fig. 7 is the combined figure for showing the ratio tensile yield strength (TYS) and minimum bend ratio in the direction L；
Fig. 8 is the typical surface image shown after exposure number is tested in 72 hours and 672 hours MASTMASSIS
Photo；
Fig. 9 is the figure for being shown as the da/dN of the function of the stress intensity factor of Al-Li plate of T8 state；
Figure 10 is to show alloy sheets of the present invention compared with the fatigue crack growth rate between tradition 7075-T6 plate
Figure；
Figure 11 is the effective crack propagation (Da for being shown as the Al-Li plate of T8 stateeff) function effective crack resistance
KReffFigure；
Figure 12 is the photo for showing the grain structure of Al-Li plate 115565B4；
Figure 13 is the photo for showing the grain structure of Al-Li plate 115702B3；
Figure 14 is the photo for showing the grain structure of Al-Li plate 115733B8；
Figure 15 is the photo for showing the grain structure of Al-Li plate 115713B0；
Figure 16 is the photo for showing the grain structure of Al-Li plate 638309A5；
Figure 17 is the photo for showing the grain structure of Al-Li plate 115654B6；
Figure 18 is the to show 0.05 " figure of the ratio of thick plates " soft " and " hard " texture component；
Figure 19 is the to show about 0.1 " figure of the ratio of thick plates " soft " and " hard " texture component；
Figure 20 is the typical case for being shown as " soft " and " hard " texture component of the function of the plate gauge of the position Th/4, minimum, excellent
Select the figure of minimum and more preferably the smallest ratio；And
Figure 21 is the typical case for being shown as " soft " and " hard " texture component of the function of the plate gauge of the position Th/2, minimum, excellent
The minimum figure with more preferably minimum rate of choosing.
Specific embodiment
The present invention relates to aluminum-copper-lithium alloys, especially Solder for Al-Cu Joint Welding-lithium-magnesium alloy.Aluminum-copper-lithium alloys of the invention include 3.2 to
The Cu of 4.1 weight %, the Li of 1.0 to 1.8 weight, the Mg of 0.8 to 1.2 weight %, the Zn of 0.10 to 0.50 weight %, 0.10 to
The Mn of 1.0 weight %, the at most Si of 0.12 weight %, the at most Fe of 0.15 weight %, the at most Ti of 0.15 weight %, at most
The total amount of the impurity element of 0.15 weight %, these impurity elements is no more than 0.35 weight %, and difference is aluminium.It should not intentionally add
Ag, and should not be used as impurity element and more than 0.1 weight %.Aluminum-copper-lithium alloys of the invention are answered " substantially free of Zr ", this meaning
Should not intentionally add Zr, and should not be used as impurity element and more than 0.05 weight %.In alloy of the invention, Mg is at least
Weight percent equal to or higher than 2 × Zn.
In alternative embodiments, aluminum-copper-lithium alloys include Cu, the Li of 1.1 to 1.7 weight % of 3.4 to 3.9 weight %,
The Mg of 0.8 to 1.2 weight %, the Zn of 0.20 to 0.50 weight %, the Mn of 0.20 to 0.6 weight %, 0.12 weight %'s of maximum
Si, the Fe of 0.15 weight % of maximum.The embodiment of this aluminum-copper-lithium alloys also has at least equal to or is higher than 2 × Zn weight percent
The Mg content of ratio.In addition, aluminum-copper-lithium alloys may include less than the Ag of 0.1 weight % unintentionally added, preferably smaller than 0.05 weight
Measure the Ag unintentionally, the even more preferably less than Ag unintentionally of 0.01 weight % of %.Aluminum-copper-lithium alloys may include less than 0.05,
Or 0.04 or 0.03 or 0.02 or even 0.01 weight % Zr unintentionally.In a preferred embodiment, without intentionally
Ag and Zr are added in aluminum-copper-lithium alloys.
Aluminum-copper-lithium alloys of the invention can be used for producing modified product, it is preferable that and thickness range is 0.01-0.249 inches,
It is highly preferred that thickness range is 0.01-0.125 inches.Other than low-density and low cost, aluminum-copper-lithium alloys of the invention are
Modified product with excellent formability, high intensity and good damage tolerance and corrosive nature.
This product be suitable for many structure applications, especially be used for aerospace structural members, such as frame, stringer and
Fuselage.Several manufacturing process can be used for manufacturing sheet metal parts in aluminum-copper-lithium alloys of the invention.Common method is roller
O ing, stretch forming, hammering forming, punching press, drawing and forming and hydroforming.It can the example made of these manufacturing process
Property component include but is not limited to fuselage ring, body longeron, figuration fuselage skin, constant cross-section covering, wirning harness folder, be used for
The bracket of the cable of control system, for primary structure (such as fuselage ring) internal part attachment point, for by fuselage
Frame be attached to the shear band of fuselage skin, the shear band for rib to be attached to wing cover, rib, be used for rib is attached
It is connected to clip, empennage covering, empennage rib, cabin skin, the engine leading edge entrance covering, pressure bulkhead covering, pylon of spar
Covering, the bracket for avionic device to be attached to structure member, the bracket for being used to be attached passenger oxygen systems, aviation electricity
Sub- device housings, for shelf of avionic device component etc..
This application discloses a kind of alloys substantially free of Zr, and without Zr is intentionally added, almost all is added
In all 29 kinds of activity Al-Li alloys registered in Aluminum Association, based on being published in January, 2017
“International Alloy Designation and Chemical Composition Limits for Wrought
Aluminum and Wrought Aluminum Alloys".As described in " background of invention " part, although being widely believed that Zr is formed
Al3Zr dispersion granule with control grain structure and be also possible to improve intensity, Zr in complicated Al-Li alloy thin product really
Influence is cut it is unclear that or being fully apparent from.The presently disclosed Al-Li alloy substantially free of Zr innovatively changes metallurgy side
Method, to obtain desired grain structure, to obtain the excellent formability and intensity that are suitable for aerospace applications.
Therefore, in one embodiment, Zr is intentionally added in aluminum-copper-lithium alloys of the invention.Due to unintentionally adding
The impurity element added, Zr are likely to be present in alloy.In this case, 0.05 weight % is not to be exceeded in Zr.Aluminum-copper-lithium alloys can
Including having the Ag less than 0.05 weight %, less than the Zr of 0.04 weight %, less than the Zr of 0.03 weight %, less than 0.02 weight
Measure the alternate embodiments of the Zr or the Zr less than 0.01 weight % of %.
The amount of the copper added in aluminum-copper-lithium alloys of the invention is 3.2 to 4.1 weight %, primarily to improving intensity
But also improve the combination of intensity, formability and fracture toughness.Excessive Cu will lead to unfavorable intermetallic particles, this can be to material
Expect performance, such as ductility, formability and fracture toughness, has a negative impact.In these cases, it is necessary to consider Cu and its
His element, such as Li and Mg, interaction.Other than the alternative upper and lower bound of Zr listed above, the present invention is also
Including alternate embodiments, wherein the upper limit of Cu content or lower limit can be selected from 3.2,3.3,3.4,3.5,3.6,3.7,3.8,3.9,
4.0 and 4.1 weight %.In a preferred embodiment, Cu is 3.4 to 3.9 weight %, special compared with prior art, to provide enhancing
Determine properties of product, while keeping the composition of relatively high performance in remaining attribute.
Lithium is added in aluminum-copper-lithium alloys of the invention with the range of 1.0 to 1.8 weight %.Add the main benefit of Li element
Place is to reduce density and increase elasticity modulus and intensity.Combined with other elements such as Cu, Li to improve intensity, damage tolerance and
Corrosive nature is crucial.However, the Li content of too a large amount can produce fracture toughness, the anisotropy of tensile property and formability
Raw negative effect.Other than the alternative upper and lower bound of Zr listed above and Cu, the invention also includes alternative implementations
Example, wherein the upper limit of Li content or lower limit can be selected from 1.0,1.1,1.2,1.3,1.4,1.5,1.6,1.7,1.8 weight %.?
In one preferred embodiment, Li is in the range of 1.1 to 1.7 weight %.
Mg is added in aluminum-copper-lithium alloys of the invention with the range of 0.8 to 1.2 weight %.Addition Mg main purpose be
Intensity is improved, secondary objective is slightly to reduce density.However, the Mg for crossing a large amount can reduce solubility of the Li in matrix, from
And it has a negative impact to the timeliness potentiality of higher intensity.In addition to the alternative upper and lower bound of Zr, Cu and Li listed above
Except, the invention also includes alternate embodiments, and wherein the upper limit of Mg amount or lower limit can be selected from 0.8,0.9,1.0,1.1 and
1.2 weight %.
The Zn that low content is added in aluminum-copper-lithium alloys of the invention is intended to improve corrosion resistance.It is believed that zinc in crystal grain into
Enter solid solution and the pitting potential of matrix is made to become less high, and it is poor to reduce the electrochemical potentials between crystal boundary and matrix, from
And improve static and Dynamic Corrosion property.In one embodiment, the additive amount of Zn is 0.1 to 0.5 weight %.In addition to above-listed
Except the alternative upper and lower bound of Zr, Cu, Li and Mg out, the invention also includes alternate embodiments, wherein Zn content
The upper limit or lower limit can be selected from 0.1,0.2,0.3,0.4 and 0.5 weight %.In a preferred embodiment, Zn is 0.2 to 0.5
In the range of weight %.
However, the addition of Zn must be careful, because what Zn may be added the beneficial effect of corrosion resistance by Mg
It is strong to influence.The prior art claims that excessively high and too low Mg/Zn has poor with the assessment of SCC test method by removing
Corrosion resistance.However, these the low-down Mg contents of statement based on 0.05 to 0.6 weight %.In the present patent application, Mg
Content is much higher (0.8 to 1.2 weight %).In addition, the ratio of Mg/Zn may also potentially influence texture.Texture may also be by
To the influence of other alloying elements such as Cu and Li.Present patent application shows the Mg/Zn ratio higher than 2.0 for 0.8 to 1.2
High Mg content in the range of weight % has excellent corrosion resistance.In one embodiment, Mg/Zn ratio should be higher than that 2.0.Also
Negative effect due to Zn to density, the Mg/Zn ratio higher than 2.0 facilitate the low-density of Al-Li alloy of the present invention.
In one embodiment, Ag is intentionally added in aluminum-copper-lithium alloys of the invention.Ag may be due to unintentionally adding
Add and is present in alloy.In this case, 0.10 weight % is not to be exceeded in Ag.In addition to Zr, Cu, Li, Mg listed above
Except the alternative upper and lower bound of Zn, the invention also includes alternate embodiments, and wherein aluminum-copper-lithium alloys, which may include, is less than
It is the Ag of 0.1 weight % unintentionally added, less than the Ag of 0.05 weight % unintentionally added or non-less than 0.01 weight %
The Ag intentionally added.Teaching in prior art Ag is necessary to improving final products performance, therefore is included in many aluminium-lithium and closes
In golden and many patents and patent applications.However, the significant cost for increasing alloy of Ag.In aluminum-copper-lithium alloys of the invention
In preferred embodiment, in order to reduce cost, be not includes Ag intentionally.It was surprisingly found that aluminum-copper-lithium alloys of the invention, no
Ag is added to provide low cost, can be used for producing high intensity, high formability, excellent corrosion resistance and good damage tolerance
The panel products of energy, the structure application suitable for especially aerospace field.
Mn is intentionally added for better mechanical isotropy and formability to improve grain structure.In addition to listed above
Except the alternative upper and lower bound of Zr, Cu, Li, Mg, Zn and Ag, the invention also includes alternate embodiments, wherein Mn content
The upper limit or lower limit can be selected from 0.1,0.2,0.3,0.4,0.5,0.6,0.7,0.8,0.9 and 1.0 weight %.Preferably at one
In embodiment, the additive amount of Mn is in the range of 0.20 to 0.6 weight %.
The additional amount of Ti can be at most 0.15 weight %.The purpose of addition Ti is mainly used for the crystal grain refinement in casting.
Other than the alternative upper and lower bound of Zr, Cu, Li, Mg, Zn, Ag and Mn listed above, the invention also includes alternative
Embodiment, wherein the upper limit of Ti content can selected from 0.01,0.02,0.05,0.06,0.07,0.08,0.09,0.10,0.11,
0.12, the Ti of 0.13,0.14 and 0.15 weight %.
Si and Fe can be used as impurity and be present in aluminum-copper-lithium alloys of the invention, but not intentionally add.Work as presence
When, the content of Si is necessary≤content≤0.15 weight %, Si content preferably≤0.05 weight % of 0.12 weight %, Fe,
The content of Fe preferably≤0.08 weight %.In one embodiment, aluminum-copper-lithium alloys of the invention include that the maximum level of Si is
The maximum level of 0.12 weight %, Fe is 0.15 weight %.In a preferred embodiment, the maximum level of Si is 0.05 weight
% is measured, the maximum level of Fe is 0.08 weight %.
Aluminum-copper-lithium alloys of the invention may also include " impurity element " of low content, not include intentionally." impurity member
Element " refers to any other element (Al, Cu, Li, Mg, Zr, Zn, Mn, Ag, Fe, Si and Ti) in addition to above-mentioned element.
Low cost of the invention, high formability, the Al-Li alloy substantially free of Zr can be used for producing modified product.?
In one embodiment, aluminum-copper-lithium alloys of the invention are able to produce rolled products, and preferred thickness range is 0.01-0.249 inches,
Plate or volume product more preferably in 0.01-0.125 inch range.
Known technique manufacture rolled products, such as casting, homogenizing, hot rolling, optional cold rolling, solution heat treatment can be used
Reason and quenching, optional stretching and leveling and ageing treatment.Traditional direct cooling (DC) casting method casting can be passed through
Ingot casting.Can be at 454 to 549 DEG C (850 to 1020 ℉), preferably 482 to 543 DEG C (900 to 1010 ℉), more preferably 496
Homogenize ingot casting at a temperature of to 538 DEG C (925 to 1000 ℉).Hot-rolled temperature can be 343 to 499 DEG C (650 to 930 ℉),
Preferably 357 to 482 DEG C (675 to 900 ℉), more preferably 371 to 466 DEG C (700 to 870 ℉).Especially for most thin plate
Rule, it may be necessary to optional cold rolling.Cold working, which subtracts thickness, to be 20% to 95%, it is therefore preferable to 40% to 90%.Product can be
454 to 543 DEG C (850 to 1010 ℉), preferably 482 to 538 DEG C (900 to 1000 ℉), more preferably 493 to 532 DEG C (920
Solution heat treatment is carried out within the temperature range of to 990 ℉).Modified product cold water is quenched to room temperature, and can optionally be stretched
Or it is cold working to more 15%, preferably 2 to 8%.It is real that quenching product can be subjected to any timeliness well known by persons skilled in the art
It tramples, including but not limited to generates the step timeliness practice of final desired state (such as T8 state), it is tough to obtain intensity, fracture
The more preferable combination of degree, corrosion resistance, is that aerospace component is highly desirable to.Aging temp can be at 121 to 205 DEG C (250
To 400 ℉), preferably at 135 to 193 DEG C (275 to 380 ℉), more preferably at 149 to 182 DEG C (300 to 360
In the range of ℉), and aging time can be in the range of 2 to 60 hours, and preferably 10 to 48 hours.
It is astonishing that the unique chemical property of the aluminum-copper-lithium alloys of present patent application and appropriate processing cause thin plate to have
Material property, such as ideal crystal texture, this consumingly influences material property, such as formability.Usually spread out by X-ray
Instrument equipment evaluation texture is penetrated, and can determine the volume fraction of texture component.The most common texture component packet of aluminum alloy plate materials
It includes cube: { 001 },<100>；R- cubes: { 001 },<110>；Gauss: { 011 }<100>；Brass: { 011 }<211>；S:{ 123 }
<634>, copper-{ 112 }<111>.It generally believes brass and S texture is " hard " texture, because their " hardly possiblies " deform, and sum of cubes R-
It cube is " soft " texture, because their " more easily " deform.The ratio of " soft "/" hard " texture component is crucial for formability
: the ratio is higher, and formability is better.In one embodiment, " soft " of T3 status component/" hard " texture ratio is in plate four
At/mono- thickness (th/4) and center thickness (th/2) respectively higher than " 0.75-0.5 × plate gauge " and " 0.85-5.0 × plate gauge ".
In a preferred embodiment, which is respectively higher than " 0.83-0.5 at a quarter thickness (th/4) and center thickness (th/2)
× plate gauge " and " 0.98-5.0 × plate gauge ".In a more preferred embodiment, the ratio is at a quarter thickness (th/4) and center
At thickness (th/2) respectively higher than " 0.9-0.5 × plate gauge " and " 1.1-5.0 × plate gauge ".The unit of plate gauge (gage) is inch.
Due to unique chemical property, this unique crystal texture material property is provided needed for aerospace applications
The desirable combination of intensity, density and formability.In one embodiment, minimum LT bend ratio is less than " 24.30-0.0292 × " ratio
LTTYS " ", and minimum L bend ratio is less than " 13.11-0.0146 × " than L TYS " ".In a preferred embodiment, minimum LT is curved
Song is than being less than " 23.65-0.0292 × " than LT TYS " ", and minimum L bend ratio is less than " 12.88-0.0146 × " ratio
LTYS"".It is equal to long-cross directional stretch yield strength (as unit of ksi) divided by density (with lb/in than LT TYS3For unit).
It is equal to longitudinal stretching yield strength (as unit of ksi) divided by density (with lb/in than L TYS3For unit).So specific strength
Unit is " ksi/ (lb/in3)”。
Geometry designed by needing to be formed as many aerospace components (such as frame) is for final application.
Therefore, formability is also static and dynamic state material performance critical consideration.Usually by simple bend test method and/
Or more complicated forming limit diagram (FLD) method assesses formability.For aluminum-copper-lithium alloys of the invention, T3 is focused primarily upon
The formability of state plate.For high-intensitive 7xxx and 2xxx alloy sheets, O state is usually supplied to machine by aluminium manufacturer (aluminum recycling)
Body manufacturer.O state plate is processed in different ways, such as forming, solid solution, cold water quenching and timeliness.Provided T3 state
Plate has significant cost advantage, because it eliminates the mistake of solid solution and cold water quenching technical step in fuselage manufacturer
Journey.
Following example illustrate various aspects of the invention, it is no intended to limit the scope of the invention.
Example 1: the product research based on laboratory scale ingot casting
In order to study effect of the Zr to thin product performance, especially strength character in Al-Li alloy, by three pairs comprising Zr and
Book mould ingot casting substantially free of Zr casts and is processed into 0.05 " panel products, wherein the size of ingot casting is about 1.25 "
×6"×12".Table 1 gives the chemical component of this 6 kinds of book mould ingot castings.First pair (#1 compares #2) has relatively high Cu
And contain Zr substantially free of Zr, #2 without Ag, #1.Second pair (#3 compare #4) has low Cu and without Ag, #3 substantially free of
Zr, #4 contain Zr.Third has relatively high Li and Mg to (#5 compares #6), and is added with Ag, and #5 is substantially free of Zr, #6
Contain Zr.
Table 1: the chemical component of sample
To book mould ingot casting carry out peeling surface, homogenizing, hot rolling, cold rolling, solution heat treatment, quenching, stretching, with timely
It imitates to the final " plate of thickness of T8 state 0.05.
By ingot casting 496 to 538 DEG C (925 to 1000 ℉) at a temperature of be homogenized.Hot rolling temperature range is 399 to 466 DEG C
(750 to 870 ℉)." the plate of thickness by ingot casting multistage hot deformation at 0.06 to 0.20.Although cold rolling is that optionally, own
Exemplary book mould plate is all further cold-rolled to 0.05 " thickness.Temperature of the cold-reduced sheet at 493 to 532 DEG C (920 to 990 ℉)
Solution heat treatment is carried out in range.Plate cold water is quenched to room temperature.Although it is optional for stretching or being cold worked, all exemplary
Plate is all stretched with 2% to 6%.The plate of stretching is continued 24 hours within the temperature range of 166 DEG C (330 ℉), timeliness to T8 shape
State.Assess the tensile property of T8 state plate.
Table 2 gives the plate stretching performance under T8 (timeliness) state.With ASTM B557 criterion along rolling direction
(L) 0.2% offset yield intensity (TYS) and ultimate tensile strength (UTS).Based on first to (#1 and #2), substantially free of
The alloy #1 of Zr has the intensity than the alloy #2 high 4.3ksi containing Zr.Although without the 1st to (#1 and #2) significantly, low Cu water
Flat second shows (#3 and #4) the intensity ratio #2 high 1.1ksi of the alloy (#3) substantially free of Zr.For third to (#5
And #6), the alloy Zr#5 substantially free of Zr and the alloy #6 containing Zr have closely similar intensity, show Zr to the benefit of intensity
In the case that place's (seeing first pair and second pair) exists only in no Ag.The result also shows that influence of the Zr to intensity is unknown
It is aobvious, and may be extremely complex for Al-Li alloy: by comparing the third added with Ag to (#5 and #6), and do not add
The first of Ag is to (#1 and #2), in fact it has surprisingly been found that first pair of no Ag has with the third containing Ag to similar intensity.
Table 2: the density and tensile property of laboratory scale panel products
Example 2: full commercial scale example
Based on " example 1 ", the laboratory scale research of effect of the Zr to strength character is had studied.Pass through DC (directly cooling)
Casting technique cast the Al-Li alloy cast ingots of six plant-scale 406mm (16 ") thickness simultaneously production to 0.05 " to 0.11 " thickness
Plate.The alloy substantially free of Zr with the Zr content unintentionally added in plant-scale ingot casting reflects normally
Industrial practice.Table 3 gives the chemical component of these commercial scale ingot castings.Three batches (115565B4,115733B8 and
It 115654B6) is alloy of the invention.Since Zr, Ag are different with Cu content, other three kinds of alloys are not alloys of the invention.Batch
638309A5 is AA2198 alloy, is used as the benchmark alloy of Al-Li panel products.Due to low Cu, high Li, high Mg, without Ag and low
Zr, all alloys of the present invention have much lower density.
Table 3: the complete exemplary chemical component of commercial scale and density
By ingot casting 496 to 538 DEG C (925 to 1000 ℉) at a temperature of be homogenized.Hot-rolled temperature is 371 to 466 DEG C (700
To 870 ℉).By ingot casting multistage hot deformation at 0.06 to 0.20 " thickness.Although cold rolling is optionally, all plates are all further
Be cold-rolled to 0.108 ", 0.085 ", 0.05 " and 0.025 " thickness.Temperature model of the cold-reduced sheet at 493 to 532 DEG C (920 to 990 ℉)
Enclose interior carry out solution heat treatment.Plate cold water is quenched to room temperature.Although stretching or cold working being optionally, all example boards are all
Stretch 2 to 7%.The plate of the stretching of not artificial aging is used to T3 state to stretch and formability assessment.By the plate of stretching into
One step timeliness is to T8 state, to carry out intensity, fracture and fatigue behaviour assessment.Aging temp is 166 DEG C (330 ℉) to 171 DEG C
Continue 14 to 32 hours under (340 ℉).
The most critical performance of T3 state plate or volume is formability, because T3 state plate or volume will be initially formed as having difference
The component of profile, then artificially timeliness is used to be served by T8 state.It is bent by standard single shaft and forming limit diagram
(FLD) test assessment formability.
Figures 1 and 2 show that forming limit diagram (FLD), the invention and non-invention of respectively 0.05 " and about 0.1 " thickness
Plate.(ratify within 2008) design code evaluation FLD again based on ASTM E2218-02.It is produced by the point by the constriction identification on sample
Raw shaping limit curve (FLC).
" plate gauge, alloy sheets 115733B8 of the invention as shown in Figure 1, using identical 0.05 for all molding conditions
With formability more better than non-invention latten 115713B0 (higher critical principal strain).The discovery is suitable for higher
Plate gauge range (0.09 " to 0.1 "), alloy sheets 115565B4 of the invention have more preferable than non-invention latten 115702B0
Formability (higher critical principal strain), although the advantage is more stronger than under other conditions under certain conditions.
T3 state plate benging performance is also assessed based on ASTM 290-09.By one end of plate sample together with bent support mold
It is fixed together with vice.Plate other end applied force with against the radius bend of support mode to 180 °.After bending, check
Sample surfaces are to determine whether crackle.Bend ratio R/t, i.e. support mode radius (R) and plate thickness (t), it is curved commonly used in assessing
Qu Xingneng.Bend ratio is lower, and expression bending property is better.
Table 4 gives the bending property without Ag low-cost alloy plate in T3 state.In general, alloy sheets of the invention have
There is better bending forming.The discovery is identical as FLD assessment result before.The direction L usually there is lower bend ratio and
There is no face crack.Lower ratio indicates better bending property.Similar plate gauge and identical test are orientated, this hair
Bright alloy sheets have bending property more better than non-invention alloy sheets.In addition, alloy of the invention has than widely used
The better bending property of 2024T3 plate, wherein minimum bend ratio required by industrial specification AMS 4037 is 2.5t.
Bending property without Ag low-cost alloy plate under table 4:T3 state
Density is another key factor of aerospace applications.When considering density and formability together, the present invention is closed
The advantage of gold becomes readily apparent from.Fig. 3 and Fig. 4 gives the density between no Ag low cost invention alloy and non-invention alloy sheets
With the comparison of bending property combination.Compared with non-invention alloy sheets, alloy sheets of the invention have lower density and lower
Minimum bend ratio.
T3 state plate exists along rolling direction (L), long transverse direction (LT) and the tensile property from rolling direction 45 degree (L45)
It is provided in table 5.Alloy sheets of the invention have than existing 2198 alloy sheets of T3 state and according to the 2024-T3 of AMS4037 most
Small higher intensity.For alloy of the present invention, different stretch be orientated L, LT and L45 intensity difference (i.e. intra-face anisotropy) nor
It is often low.
The tensile property of table 5:T3 state plate
Table 6 and Fig. 5 give the tensile property under the LT orientation of the different aging times under 330 ℉.It is effective for institute
Time, alloy sheets of the invention have the intensity more much higher than existing 2198 benchmark alloy sheets.Equally, it is free of with non-invention
Ag alloy sheets are compared, and the invention alloy sheets without Ag have lower density and lower minimum bend ratio.
The LT tensile property of different aging times under table 6:330 ℉ aging temp
Based on aging response as a result, selecting specific timeliness to practice (target timeliness is practiced) according to alloy and plate gauge.At this
It carries out and is disclosed including the comprehensive of intensity intra-face anisotropy, corrosion resistance, fracture toughness and anti-fatigue performance in patent application
Close characterization.
Table 7 gives the tensile property that different-alloy and plate gauge are orientated along L, LT and L45.Alloy sheets of the invention have than
The much higher intensity of 2198 alloy of benchmark (638309A5).The intensity of alloy sheets of the present invention is slightly below non-invention alloy sheets
The intensity of 115702B3 and 115713B0.Equally, compared with non-invention is without Ag alloy sheets 115713B0 and 115702B3, no
The alloy sheets of invention containing Ag have lower density and lower minimum bend ratio.
Table 7: the tensile property that different-alloy and plate gauge are orientated along L, LT and L45
As previously mentioned, the combination of intensity, density and formability is crucial for aerospace applications.Alloy of the present invention
Uniqueness can illustrate in figure 6 and figure 7, respectively indicate ratio tensile yield strength (TYS) and the minimum bend on the direction L and LT
The combination of ratio.The minimum LT bend ratio of alloy sheets of the present invention is smaller than " 24.30-0.0292 × " than LT TYS " ", and this conjunction
The minimum L bend ratio of golden plate is smaller than " 13.11-0.0146 × " than L TYS " ".Preferably, minimum LT bend ratio is less than
" 23.65-0.0292 × " than LT TYS " ", and minimum L bend ratio is less than " 12.88-0.0146 × " than L TYS " ".Than strong
Degree is equal to intensity divided by density.The unit of specific strength is " ksi/ (lb/in3)”。
Corrosion resistance is the key Design Consideration of fuselage manufacturer.MASTMASSIS test is commonly referred to be Al-Li
The good representative accelerated corrosion test method of based alloy.
MASTMASSIS test is carried out under the conditions of dry bottom based on ASTM G85-11Annex-2.Among plate thickness, sample
Product are having a size of 2.0 " L × 2.0 " LT.During entire test, the temperature of exposure chamber is 49 ± 2 DEG C.
0.05 " invention alloy sheets 115733B8 is tested at T/2 (mid-depth) thickness position.Test time is
24,48,96,168,336,504 and 672 hours.Fig. 8 is by 72 hours and 672 hours MASTMASSIS test exposure durations
The photo of typical surface image afterwards.Surface is very clean glossy.All exposure durations all do not remove significantly.For institute
There is exposure duration, it can be deduced that spot corrosion/EA excellent anticorrosive.
Fatigue crack growth rate (FCGR) is assessed based on ASTM E647-08 (9.1).Fig. 9 is shown as in T8 shape
The figure of the da/dN of the function of the stress intensity factor of all present invention and non-present invention alloy sheets without Ag of state.Test-strips
Part includes L-T orientation, and stress ratio is 0.1 and frequency is 10Hz.What is interesting is observe that all plates have similar antifatigue split
Line scalability, although invention alloy sheets (115654B6,115733B8,115565B4) have than non-invention alloy sheets
(115713B0,115702B3) lower density and better formability.
The excellent fatigue crack scalability of alloy of the present invention can be illustrated in Figure 10.7075-T6 data come from ASM hand
Volume.Alloy sheets of the invention have the fatigue crack growth rate (da/dN) more much slower than common 7075-T6 plate.
Fracture toughness is assessed based on ASTM E561-10e2 and ASTM B646-06a.Common 16 " wide and 40 " long examination
Sample is used for center cracked tension fracture toughness testing.Figure 11 is the effective crack propagation (Da for being shown as Al-Li plateeff) letter
Several effective crack resistance KReffFigure.All Al-Li plates are tested with T8 state and L-T orientation.Alloy sheets of the invention
(115654B6 and 115733B8) has the fracture toughness similar with non-present invention alloy sheets (115713B0 and 115702B3).It answers
This should be mentioned that, alloy sheets of the invention (115654B6,115733B8) have than non-present invention alloy sheets (115713B0 and
115702B3) lower density and better formability.
The example 2 (full commercial scale example) shows the uniqueness and distinctive chemical component (no Ag, base of alloy of the present invention
Without the combination of Zr and Cu, Li, Mg, Mn and Zn in sheet) it can provide the excellent formability of Al-Li panel products, low-density, excellent
Different intensity, corrosion resistance, fracture toughness and fatigue crack scalability.
Due to unique chemical property, this unique performance, especially formability are micro- by uniqueness as disclosed below
Structure and the response of the result of crystal texture.
Figure 12 to Figure 17 gives the grain structure of Al-Li plate.It is well known that strong shadow of the grain structure by the plate gauge of plate
It rings.Therefore, the comparison of microstructure depends on plate gauge." plate of plate gauge, alloy sheets of the invention for similar 0.09 to 0.11
115565B4 has and more equiaxial grain structure finer than non-present invention alloy sheets 115702B3.0.05 " when plate gauge, this
The alloy sheets 115713B0 of invention has, equiaxial crystal grain knot finer than non-present invention alloy sheets 115713B0 and 638309A5
Structure.The alloy 115654B6 of the invention for very thin plate (0.025 "), be clearly observed it is a kind of very fine, it is equiaxial
Grain structure.In industry it is well known that finer and more equiaxial grain structure usually have less form anisotropy and
Better forming property.The ideal grain structure of alloy sheets of the present invention is mainly due to the unique chemical component for being substantially free of Zr
And the unique combination of Cu, Li, Mn and Mg.
Crystal texture influences final products performance, especially formability strongly.Use Rigaku D/Max X-Ray diffraction
Instrument measures T3 state plate texture.By using the alpha-emitting Schulz back reflection method of CuK, α rotation angle is 15 ° to 90 °, α stepping angle
It is 5 °.Generate four width pole figures: { 111 }, { 200 }, { 220 } and { 311 }, be subsequently used for calculate orientation distribution function (ODF) and
The most common texture component relative to cube: { 001 },<100>；R- cubes: { 001 },<110>；Gauss: { 011 }<100>；It is yellow
Copper: { 011 }<211>；S:{ 123 }<634>, the volume fraction of copper-{ 112 }<111>.It generally believes brass and S texture is " hard "
Texture, because their " being difficult to " deform, and R- cubes of sum of cubes is " soft " texture, because their " more easily " deform.
Table 8 summarizes T3 state plate in the Main Texture component of T/4 (a quarter thickness) and T/2 (interior thickness) position
And its volume fraction.It is well known that texture and final plate thickness are closely related.Non-present invention alloy sheets (115713B8 and
115702B3) there is very typical rolling texture --- very strong brass and S texture " hard " component.On the contrary, similar
Under plate thickness, alloy sheets of the invention (115565B4 and 115733B8) have very strong R- cubes of sum of cubes " soft " texture.
The ratio of " soft " and " hard " texture component of two kinds of plate thickness provides in Figure 18 and Figure 19.Soft=cube %+R- cubes of %, firmly
=brass+S%.Equally, alloy sheets of the invention have " soft " and " hard " texture component more much higher than non-present invention alloy sheets
Ratio.Since the present invention is identical with the machining Practice of non-present invention alloy sheets, this unique texture difference can attribution
In the combination for lacking Zr and other elements such as Cu, Li, Mg, Mn.
In terms of the ratio of " soft " and " hard " texture component, the uniqueness of crystal texture can be distinguished in Figure 20 and Figure 21
It is further illustrated for Th/4 and Th/2.The minimum rate of alloy of the present invention is in plate a quarter thickness (th/4) and center thickness
(th/2) at respectively higher than " 0.75-0.5 × plate gauge " and " 0.85-5.0 × plate gauge ".For alloy of the present invention, preferred ratio
At th/4 and th/2 respectively higher than " 0.83-0.5 × plate gauge " and " 0.98-5.0 × plate gauge ".It is more excellent for alloy of the present invention
The ratio of choosing is respectively higher than " 0.9-0.5 × plate gauge " and " 1.1-5.0 × plate gauge " at th/4 and th/2.The unit of plate gauge is English
It is very little.
Texture component and its volume of the table 8:T3 state plate in T/4 (a quarter thickness) and T/2 (interior thickness) position
Point
Number
Although the particular embodiment of the present invention has been disclosed, it will be appreciated, however, by one skilled in the art that can be according to this
Various modifications and change of the disclosed general teachings development to these details.Therefore, disclosed specific arrangements are only explanation
Property, it does not limit the scope of the invention, if appended claims and its any and all equivalents, the scope of the present invention will
Give comprehensive range.
Claims (33)
1. a kind of low cost, high formability are substantially free of the Al-Li alloy of Zr, comprising:
The Cu of 3.2 to 4.1 weight %, the Li of 1.0 to 1.8 weight %,
The Mg of 0.8 to 1.2 weight %, the Zn of 0.10 to 0.50 weight %,
The Mn of 0.1 to 1.0 weight %, less than the Ag of 0.1 weight %,
Less than the Zr of 0.05 weight %, the at most Ti of 0.15 weight %,
The at most Si of 0.12 weight %, the at most Fe of 0.15 weight %,
The total amount of at most every kind of impurity element of 0.15 weight %, these impurity elements is no more than 0.35 weight %,
Difference is aluminium, and
Wherein Mg content is by weight percentage at least equal to or higher than twice of Zn.
2. aluminum-copper-lithium alloys according to claim 1, the Cu including 3.4 to 3.9 weight %.
3. aluminum-copper-lithium alloys according to any one of claim 1 to 2, the Li including 1.1 to 1.7 weight %.
4. aluminum-copper-lithium alloys according to any one of claim 1 to 3, the Zn including 0.20 to 0.50 weight %.
5. aluminum-copper-lithium alloys according to any one of claim 1 to 4, the Mn including 0.2 to 0.6 weight %.
6. aluminum-copper-lithium alloys according to any one of claim 1 to 5, wherein not adding Zr intentionally into aluminium alloy.
7. aluminum-copper-lithium alloys according to any one of claim 1 to 6, the Ag including being up to 0.05 weight %.
8. aluminum-copper-lithium alloys according to any one of claim 1 to 7, the Ag including being up to 0.01 weight %.
9. aluminum-copper-lithium alloys according to any one of claim 1 to 8, wherein not adding Ag intentionally into aluminium alloy.
10. aluminum-copper-lithium alloys according to any one of claim 1 to 9, the Si including being up to 0.05 weight %.
11. aluminum-copper-lithium alloys according to any one of claim 1 to 10, the Fe including being up to 0.08 weight %.
12. a kind of low cost, high formability are substantially free of the Al-Li alloy of Zr, comprising:
The Cu of 3.4 to 3.9 weight %, the Li of 1.1 to 1.7 weight %,
The Mg of 0.8 to 1.2 weight %, the Zn of 0.20 to 0.50 weight %,
The Mn of 0.20 to 0.6 weight %, less than the Ag of 0.05 weight %,
Less than the Zr of 0.05 weight %, the at most Ti of 0.15 weight %,
The at most Si of 0.05 weight %, the at most Fe of 0.08 weight %,
The total amount of at most every kind of impurity element of 0.15 weight %, these impurity elements is no more than 0.35 weight %,
Difference is aluminium, and
Wherein Mg content is by weight percentage at least equal to or higher than twice of Zn.
13. aluminum-copper-lithium alloys according to any one of claim 1 to 12, wherein the aluminum-copper-lithium alloys be 0.01 to
0.249 " form of thick rolling, extrusion or forging product.
14. aluminum-copper-lithium alloys according to claim 13, wherein the aluminum-copper-lithium alloys have the thickness of 0.01 " to 0.125 "
Degree.
15. aluminum-copper-lithium alloys according to any one of claim 1 to 12, wherein aluminum-copper-lithium alloys be with 0.01 " extremely
0.249 " plate of thickness or the form of volume.
16. aluminum-copper-lithium alloys according to claim 15, wherein aluminum-copper-lithium alloys have the thickness of 0.01 " to 0.125 ".
17. a kind of including according to claim 1 to the rolled products of aluminum-copper-lithium alloys described in any one of 16, having 0.01 " extremely
0.249 " thickness, in a quarter thickness (th/4) and center thickness of plate under solution heat treatment, quenching and stretching condition
(th/2) ratio for being higher than " soft " and " hard " texture of " 0.75-0.5 × plate gauge " and " 0.9-5.0 × plate gauge " is shown at respectively
Rate, the unit of plate gauge are inch.
18. a kind of including according to claim 1 to the rolled products of aluminum-copper-lithium alloys described in any one of 16, having 0.01 " extremely
0.249 " thickness, in a quarter thickness (th/4) and center thickness of plate under solution heat treatment, quenching and stretching condition
(th/2) ratio for being higher than " soft " and " hard " texture of " 0.8-0.5 × plate gauge " and " 1.0-5.0 × plate gauge " is shown at respectively,
The unit of plate gauge is inch.
19. a kind of including according to claim 1 to the rolled products of aluminum-copper-lithium alloys described in any one of 18, having 0.01 " extremely
0.249 " thickness, in a quarter thickness (th/4) and center thickness of plate under solution heat treatment, quenching and stretching condition
(th/2) ratio for being higher than " soft " and " hard " texture of " 0.9-0.5 × plate gauge " and " 1.1-5.0 × plate gauge " is shown at respectively,
The unit of plate gauge is inch.
20. rolled products described in any one of 7 to 19 according to claim 1, wherein aluminum-copper-lithium alloys be with 0.01 " extremely
0.125 " plate of thickness or the form of volume.
21. a kind of including according to claim 1 to the rolled products of aluminum-copper-lithium alloys described in any one of 20, having 0.01 " extremely
0.249 " thickness, in solution heat treatment, quenching, stretch and artificial aging under the conditions of show and be less than " 24.30-0.0292 ×
The minimum LT bend ratio of " than LT TYS " ", and it is less than the minimum L bend ratio of " 13.11-0.0146 × " than L TYS " ", than strong
The unit of degree is " ksi/ (lb/in3)”。
22. a kind of including according to claim 1 to the rolled products of aluminum-copper-lithium alloys described in any one of 20, having 0.01 " extremely
0.249 " thickness, in solution heat treatment, quenching, stretch and artificial aging under the conditions of show and be less than " 23.65-0.0292 ×
The minimum LT bend ratio of " than LT TYS " ", and it is less than the minimum L bend ratio of " 12.88-0.0146 × " than L TYS " ", than strong
The unit of degree is " ksi/ (lb/in3)”。
23. the rolled products according to claim 21 or 22, wherein aluminum-copper-lithium alloys are the thickness with 0.01 " to 0.125 "
The plate of degree or the form of volume.
24. a kind of manufacture is high-intensitive, high formability, the method for inexpensive aluminum-copper-lithium alloys, which comprises
A. casting include according to claim 1 to the blank of the aluminium alloy cast ingot of aluminum-copper-lithium alloys product described in any one of 23,
Generate slab；
B. it is homogenized slab, generates the slab of homogenizing；
C. by one of the group of selecting free rolling, extruding and forging to constitute or a variety of methods to the slab of homogenizing carry out heat plus
Work forms turned blank；
D. optionally cold rolling turned blank；
E. the turned blank of solution heat treatment (SHT) optionally cold rolling generates SHT blank；
F. cold water quenches the SHT blank to generate cold water quenching SHT blank；
G. it optionally stretches cold water and quenches SHT blank；And
H. artificial aging cold water quenches, the SHT blank optionally stretched.
25. according to the method for claim 24, wherein the step of homogenizing is included in 454 to 549 DEG C (850 to 1020
It is homogenized at a temperature of ℉).
26. the method according to claim 24 or 25, wherein the hot worked step is included in 343 to 499 DEG C (650
Hot rolling is carried out at a temperature of to 930 ℉).
27. the method according to any one of claim 24 to 26, wherein described the step of being optionally cold worked includes cold
Subtract thickness 20% to 95%.
28. the method according to any one of claim 24 to 27, wherein the step of solution heat treatment is included in 454
Solution heat treatment is carried out within the temperature range of to 543 DEG C (850 to 1010 ℉).
29. the method according to any one of claim 24 to 28, wherein described the step of optionally stretching includes stretching
At most 15%.
30. the method according to any one of claim 24 to 29, wherein the step of timeliness includes 121 to 205 ℉
(400 ℉ of 250to), aging time can be in the range of 2 to 60 hours.
31. a kind of low cost, high formability, the Al-Li alloy of no Zr, no Ag, comprising:
The Cu of 3.4 to 3.9 weight %, the Li of 1.1 to 1.7 weight %,
The Mg of 0.8 to 1.2 weight %, the Zn of 0.20 to 0.50 weight %,
The Mn of 0.20 to 0.6 weight %, less than the Ag of 0.05 weight %,
Less than the Zr of 0.05 weight %, the at most Ti of 0.15 weight %,
The at most Si of 0.05 weight %, the at most Fe of 0.08 weight %,
The total amount of at most every kind of impurity element of 0.15 weight %, these impurity elements is no more than 0.35 weight %,
Difference is aluminium, and
Wherein Mg content is by weight percentage at least equal to or higher than twice of Zn.
Wherein the aluminum-copper-lithium alloys are the rolled alloy product of the thickness with 0.01 " to 0.249 ".
32. aluminum-copper-lithium alloys according to claim 31, wherein the aluminum-copper-lithium alloys have the thickness of 0.01 " to 0.125 "
Degree.
33. the aluminum-copper-lithium alloys according to any one of claim 31 to 32, wherein the aluminum-copper-lithium alloys are without any
The Zr and Ag intentionally added.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US15/830,569 US20190169727A1 (en) | 2017-12-04 | 2017-12-04 | Low Cost, Substantially Zr-Free Aluminum-Lithium Alloy for Thin Sheet Product with High Formability |
| US15/830,569 | 2017-12-04 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109868400A true CN109868400A (en) | 2019-06-11 |
Family
ID=64604518
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811464125.4A Pending CN109868400A (en) | 2017-12-04 | 2018-12-03 | A kind of low cost for high formability light sheet products, is substantially free of the aluminium lithium alloy of Zr |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20190169727A1 (en) |
| EP (1) | EP3495520B1 (en) |
| CN (1) | CN109868400A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112376001A (en) * | 2020-10-09 | 2021-02-19 | 江苏永茂普隆汽车配件制造有限公司 | Forging and heat treatment process of free forging |
| CN115927934A (en) * | 2022-07-01 | 2023-04-07 | 湖北汽车工业学院 | Al-Cu casting alloy with {001} < x10> texture and preparation method and application thereof |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20190233921A1 (en) * | 2018-02-01 | 2019-08-01 | Kaiser Aluminum Fabricated Products, Llc | Low Cost, Low Density, Substantially Ag-Free and Zn-Free Aluminum-Lithium Plate Alloy for Aerospace Application |
| CN112877624B (en) * | 2021-01-13 | 2022-01-18 | 广东省科学院材料与加工研究所 | Corrosion-resistant Al-Zn-Mg-Cu alloy, and preparation method and application thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04337044A (en) * | 1991-05-10 | 1992-11-25 | Arishiumu:Kk | High strength al-li alloy excellent in scc resistance |
| CN101341267A (en) * | 2005-12-20 | 2009-01-07 | 爱尔康何纳吕公司 | Sheet made of high-toughness aluminium alloy containing copper and lithium for an aircraft fuselage |
| CN102834502A (en) * | 2010-04-12 | 2012-12-19 | 美铝公司 | 2xxx series aluminum lithium alloys having low strength differential |
| CN105543595A (en) * | 2014-10-26 | 2016-05-04 | 凯撒铝制品有限公司 | High strength, high formability, and low cost aluminum-lithium alloys |
| CN105814221A (en) * | 2013-12-05 | 2016-07-27 | 伊苏瓦尔肯联铝业 | Aluminum/copper/lithium alloy material for underwing element having enhanced properties |
| WO2017088914A1 (en) * | 2015-11-25 | 2017-06-01 | Otto Fuchs - Kommanditgesellschaft - | Tube for use in conjunction with a deep drilled hole |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2257435B (en) * | 1991-07-11 | 1995-04-05 | Aluminum Co Of America | Aluminum-lithium alloys and method of making the same |
| CN101967588B (en) | 2010-10-27 | 2012-08-29 | 中国航空工业集团公司北京航空材料研究院 | Damage-resistant aluminum-lithium alloy and preparation method thereof |
| CN102021457B (en) | 2010-10-27 | 2012-06-27 | 中国航空工业集团公司北京航空材料研究院 | High-toughness aluminum lithium alloy and preparation method thereof |
-
2017
- 2017-12-04 US US15/830,569 patent/US20190169727A1/en not_active Abandoned
-
2018
- 2018-12-03 CN CN201811464125.4A patent/CN109868400A/en active Pending
- 2018-12-04 EP EP18210045.3A patent/EP3495520B1/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH04337044A (en) * | 1991-05-10 | 1992-11-25 | Arishiumu:Kk | High strength al-li alloy excellent in scc resistance |
| CN101341267A (en) * | 2005-12-20 | 2009-01-07 | 爱尔康何纳吕公司 | Sheet made of high-toughness aluminium alloy containing copper and lithium for an aircraft fuselage |
| CN102834502A (en) * | 2010-04-12 | 2012-12-19 | 美铝公司 | 2xxx series aluminum lithium alloys having low strength differential |
| CN105814221A (en) * | 2013-12-05 | 2016-07-27 | 伊苏瓦尔肯联铝业 | Aluminum/copper/lithium alloy material for underwing element having enhanced properties |
| CN105543595A (en) * | 2014-10-26 | 2016-05-04 | 凯撒铝制品有限公司 | High strength, high formability, and low cost aluminum-lithium alloys |
| WO2017088914A1 (en) * | 2015-11-25 | 2017-06-01 | Otto Fuchs - Kommanditgesellschaft - | Tube for use in conjunction with a deep drilled hole |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112376001A (en) * | 2020-10-09 | 2021-02-19 | 江苏永茂普隆汽车配件制造有限公司 | Forging and heat treatment process of free forging |
| CN115927934A (en) * | 2022-07-01 | 2023-04-07 | 湖北汽车工业学院 | Al-Cu casting alloy with {001} < x10> texture and preparation method and application thereof |
| CN115927934B (en) * | 2022-07-01 | 2024-01-26 | 湖北汽车工业学院 | Al-Cu casting alloy with {001} < x10> texture and preparation method and application thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| US20190169727A1 (en) | 2019-06-06 |
| EP3495520C0 (en) | 2023-06-07 |
| EP3495520A1 (en) | 2019-06-12 |
| EP3495520B1 (en) | 2023-06-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105543595B (en) | High intensity, high formability, inexpensive aluminum-copper-lithium alloys | |
| RU2404276C2 (en) | PRODUCT FROM HIGH-STRENGTH, HIGH-VISCOSITY Al-Zn ALLOY AND MANUFACTURING METHOD OF SUCH PRODUCT | |
| CA2485524C (en) | Method for producing a high strength al-zn-mg-cu alloy | |
| CA2627070C (en) | Al-cu-mg alloy suitable for aerospace application | |
| JP6771456B2 (en) | Aluminum alloy products and preparation methods | |
| CN109868400A (en) | A kind of low cost for high formability light sheet products, is substantially free of the aluminium lithium alloy of Zr | |
| EP3649268B1 (en) | Al- zn-cu-mg alloys and their manufacturing process | |
| US20010006082A1 (en) | Aircraft structure element made of an Al-Cu-Mg alloy | |
| WO2004090183A1 (en) | High strength al-zn alloy and method for producing such an alloy product | |
| CN103834837A (en) | Al- Zn-Cu-Mg aluminum base alloys and methods of manufacture and use | |
| EP2456899A2 (en) | Improved 5xxx aluminum alloys and wrought aluminum alloy products made therefrom | |
| US20150240338A1 (en) | Ultra-Thick High Strength 7xxx Series Aluminum Alloy Products and Methods of Making Such Products | |
| CN113302327A (en) | 7xxx series aluminum alloy products | |
| CN110106409A (en) | Low cost, low-density, the aluminium substantially without Ag and without Zn-lithium plate alloy for space flight and aviation application | |
| CN111492074A (en) | Improved method for producing aluminium-copper-lithium alloy plates for the production of aircraft fuselages | |
| CN112877554A (en) | Preparation method of high-strength and high-toughness easy-welding corrosion-resistant Al-Mg-Zn-Cu alloy | |
| EP3880856A2 (en) | 2xxx aluminum alloys | |
| US20190368009A1 (en) | High Strength, Better Fatigue Crack Deviation Performance, and High Anisotropic Ductility 7xxx Aluminum Alloy Products and Methods of Making Such Products |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190611 |