EP0717784B1 - Aluminium-silicon alloy sheet for mechanical, aircraft and space applications - Google Patents
Aluminium-silicon alloy sheet for mechanical, aircraft and space applications Download PDFInfo
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- EP0717784B1 EP0717784B1 EP95920993A EP95920993A EP0717784B1 EP 0717784 B1 EP0717784 B1 EP 0717784B1 EP 95920993 A EP95920993 A EP 95920993A EP 95920993 A EP95920993 A EP 95920993A EP 0717784 B1 EP0717784 B1 EP 0717784B1
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
- C22C21/02—Alloys based on aluminium with silicon as the next major constituent
- C22C21/04—Modified aluminium-silicon alloys
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
- C22F1/043—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 silicon as the next major constituent
Definitions
- the invention relates to the field of alloy sheets medium and high strength aluminum used in the mechanical, aeronautical and space engineering and in armament.
- high-strength aluminum alloys have been used in aeronautical and space construction, essentially Al-Cu alloys of the 2000 series (according to the designation of the Aluminum Association in the USA), for example alloys 2014 , 2019 and 2024, and Al-Zn-Mg and Al-Zn-Mg-Cu alloys of the 7000 series, for example alloys 7020 and 7075.
- alloys 2000 and 7000 have a much better temperature resistance than that of most alloys 2000 and 7000, and at least equivalent to that of alloys in these series specially studied for their temperature resistance, such as alloys 2019 and 2618.
- Al-Si alloys are widely used for the production of molded parts. However, in this form, they have far lower mechanical strength, fatigue and toughness properties than the wrought and transformed alloys 2000 and 7000 used in structural parts. In rare cases, they can be used in laminated form, in particular for covering plated sheets intended for the manufacture of brazed heat exchangers. Alloys 4343, 4104, 4045 and 4047 are thus used, for example, the properties sought in this case being essentially a low melting temperature and good wettability.
- Al-Si alloys can also be spun in the form of bars or profiles which, due to their good resistance to wear and temperature, are used in mechanical parts such as connecting rods, brake master cylinders, drive shafts , bearings and various components of motors and compressors.
- One of the alloys used for this purpose is 4032.
- French patent FR 2291284 describes the manufacture of AlSi alloy sheets containing 4 to 15% Si by continuous casting between two cooled cylinders. This casting mode is intended to increase the elongation at break, and therefore the formability. They are not high-strength sheets usable in structural applications, since the sheets are simply annealed and the elastic limits exemplified do not exceed not 220 MPa.
- the subject of the invention is therefore sheets heat treated by dissolving, quenching and optionally tempering so as to obtain an elastic limit R 0.2 greater than 320 MPa, intended for mechanical, naval, aeronautical or space construction made of alloy of following composition (by weight): Yes 6.5 to 11% Mg 0.5 to 1.0% Cu ⁇ 0.8% Fe ⁇ 0.3% Mn ⁇ 0.5% and / or Cr ⁇ 0.5% Sr 0.008 to 0.025% Ti ⁇ 0.02% the total of the other elements being less than 0.2%, the rest being aluminum.
- the silicon content is preferably between 6.5 and 8%, corresponding to that of the AS7G alloy.
- Another object of the invention is the use of especially medium or thick sheets of this alloy for the undersides of aircraft wings, of particularly thin sheets for the coating of aircraft fuselages, of sheets for the manufacture of tanks cryogenic rockets, floors and skips of industrial vehicles and hulls or supersructures of boats.
- Another object of the invention is the method of manufacturing sheets according to claim 9.
- the sheets according to the invention have silicon contents generally corresponding to the fields of alloys AS7G and AS9G according to French standard NF A 57-702 or the designations A 357 and A 359 of the Aluminum Association.
- Magnesium should not exceed 1% to avoid the formation of the insoluble intermetallic compound Mg 2 Si.
- Copper must be limited to 0.8% to avoid the formation of insoluble phases Mg 2 Si and Q (AlMgSiCu). This content also makes it possible to limit the sensitivity to intercrystalline corrosion.
- Iron is also limited to 0.3%, and preferably 0.08%, as it is in 7000 alloys for heavy plate, when good toughness and / or good elongation.
- the presence of titanium is linked to the refining of the titanium plates, identical to that used for current medium and high strength alloys.
- the sheets according to the invention can be obtained by vertical casting of plates, hot rolling up to 6 mm, optionally cold rolling in the case of thin sheets, dissolving between 545 and 555 ° C, quenching with cold water, maturation at room temperature and / or tempering between 6 and 24 hours at a temperature between 150 and 195 ° C.
- Hot rolling can be preceded by homogenization between 530 and 550 ° C for a duration of less than 20 h, short enough to avoid a globalization of the fibrous eutectic and a marked coalescence of the manganese and / or chromium, when the alloy contains it.
- a very fine, non-globular eutectic microstructure is obtained in the final state, which has a favorable effect on the toughness.
- the alloy is weldable by conventional TIG or MIG processes, continuous or pulsed, depending on whether it is a thin or thick sheet, and its density is always lower than that of traditional 2000 and 7000 alloys.
- Plates with a cross section of 380 x 120 mm of alloy of the following composition (by weight) were produced by vertical casting: Yes 6.77% Mg 0.59% Cu 0.24% Fe 0.06% Mn 0.31% Sr 0.016% Ti 0.01% the total of the other elements being less than 0.2% and the rest being aluminum.
- the alloy was homogenized at 550 ° C for 8 hours, after a temperature rise of 4 hours, reheated for 2 hours at 500 ° C, then hot rolled up to 20 mm thick on a reversible rolling mill.
- Cut sheets were placed in solution for 2 hours at 550 ° C, soaked in water and subjected to an income of 8 hours at 175 ° C, ie a state T651 according to the designations of the Aluminum Association.
- the alloy has a density of 2,678 and a modulus of elasticity E of 74,100 MPa, or a specific module of 27,670 MPa, was measured on the sheet by the hysteresis loop method in tension. 2.770, 72,500 MPa and 26,175 MPa respectively for a sheet of the same thickness in 2024 alloy in the T351 state, an increase of 5.7% in the specific module. This increase is more than 9% higher compared to alloy 2219 for welded construction.
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Abstract
Description
L'invention concerne le domaine des tôles en alliages d'aluminium à moyenne et haute résistance utilisées dans la construction mécanique, aéronautique et spatiale et dans l'armement.The invention relates to the field of alloy sheets medium and high strength aluminum used in the mechanical, aeronautical and space engineering and in armament.
Depuis de nombreuses années, on utilise dans la construction
aéronautique et spatiale des alliages d'aluminium à haute
résistance, essentiellement des alliages Al-Cu de la série
2000 (selon la désignation de l'Aluminum Association aux USA),
par exemple les alliages 2014, 2019 et 2024, et des alliages
Al-Zn-Mg et Al-Zn-Mg-Cu de la série 7000, par exemple les
alliages 7020 et 7075.
Le choix d'un alliage et d'une gamme de transformation, en
particulier de traitement thermique, résulte d'un compromis
souvent délicat entre diverses propriétés d'emploi telles que
les caractéristiques mécaniques statiques (résistance à la
rupture, limite élastique, module d'élasticité, allongement),
la résistance à la fatigue, importante pour des avions soumis
à des cycles répétés de décollage-atterrissage, la tenacité,
c'est-à-dire la résistance à la propagation de fissures, et la
corrosion sous tension. Il faut en plus tenir compte de
l'aptitude de l'alliage à être coulé, laminé et traité
thermiquement dans de bonnes conditions, de sa densité et
éventuellement de sa soudabilité.
Depuis plus de trente ans, des progrès continus ont été
accomplis pour améliorer les propriétés des alliages 2000 et
7000 utilisés en tôles minces pour le fuselage des avions et
en tôles moyennes et épaisses pour les voilures ou les
réservoirs cryogéniques des lanceurs et missiles, dans le but,
en particulier, d'alléger les structures sans compromettre les
autres propriétés.
Un pas important dans l'allégement a été accompli avec le
développement des alliages aluminium-lithium. Ainsi, un
alliage 8090 à 2,6% de lithium conduit à un module spécifique
(rapport du module d'élasticité à la densité) supérieur
d'environ 20% à celui du 2024 et de 24% à celui du 7075. Les
alliages à plus forte teneur en cuivre et à plus faible teneur
en lithium, comme le 2095, ont été aussi developpés à cause de
leur bon compromis entre la densité, le module d'élasticité et
la soudabilité. Dans ce cas, le gain sur le module spécifique
est d'environ 12% par rapport au 2219. Cependant, ces alliages
restent encore peu utilisés, essentiellement en raison de leur
coût de fabrication élevé.For many years, high-strength aluminum alloys have been used in aeronautical and space construction, essentially Al-Cu alloys of the 2000 series (according to the designation of the Aluminum Association in the USA), for example alloys 2014 , 2019 and 2024, and Al-Zn-Mg and Al-Zn-Mg-Cu alloys of the 7000 series, for example alloys 7020 and 7075.
The choice of an alloy and a transformation range, in particular of heat treatment, results from an often delicate compromise between various properties of use such as static mechanical characteristics (resistance to rupture, elastic limit, modulus d (elasticity, elongation), resistance to fatigue, important for airplanes subjected to repeated cycles of takeoff-landing, toughness, that is to say resistance to the propagation of cracks, and corrosion under stress. In addition, the ability of the alloy to be cast, rolled and heat treated under good conditions, its density and possibly its weldability must be taken into account.
For more than thirty years, continuous progress has been made to improve the properties of the 2000 and 7000 alloys used in thin sheets for the fuselage of aircraft and in medium and thick sheets for the wings or cryogenic tanks of launchers and missiles, in the aim, in particular, to lighten the structures without compromising the other properties.
An important step in the reduction has been accomplished with the development of aluminum-lithium alloys. Thus, an alloy 8090 with 2.6% of lithium leads to a specific modulus (ratio of the modulus of elasticity to the density) higher by approximately 20% than that of 2024 and 24% than that of 7075. The alloys with higher copper content and lower lithium content, like 2095, have also been developed because of their good compromise between density, modulus of elasticity and solderability. In this case, the gain on the specific module is around 12% compared to 2219. However, these alloys are still little used, mainly because of their high manufacturing cost.
La demanderesse, poursuivant ses recherches d'alliages pour
alléger les structures des avions, s'est aperçu qu'une autre
catégorie d'alliages utilisés habituellement sous forme
moulée, les alliages Al-Si de la série 4000, permettait non
seulement d'améliorer de manière sensible, entre 3 et 10%, le
module spécifique par rapport aux alliages 2000 et 7000, mais
présentait aussi un faisceau de propriétés en matière de
tenacité, résistance à la fatigue et corrosion sous tension
répondant aux exigences sévères de la construction
aéronautique, sans poser de problème difficile à la coulée, au
laminage et au traitement thermique. De plus, ces alliages
présentent une soudabilité bien meilleure que la plupart des
2000 et 7000, et au moins équivalente aux alliages de ces
séries spécialement dédiés au soudage, comme les alliages 2219
et 7020. Ils présentent enfin une résistance à la température
bien meilleure que celle de la plupart des alliages 2000 et
7000, et au moins équivalente à celle d'alliages de ces séries
spécialement étudiés pour leur tenue en température, tels que
les alliages 2019 et 2618.
Les alliages Al-Si sont utilisés très largement pour la
fabrication de pièces moulées. Ils présentent cependant, sous
cette forme, des propriétés de résistance mécanique, de
fatigue et de tenacité bien inférieures à celles des alliages
2000 et 7000 corroyés et transformés utilisés en pièces de
structure. Dans de rares cas, ils peuvent être utilisés sous
forme laminée, notamment pour la couverture de tôles plaquées
destinées à la fabrication d'échangeurs thermiques brasés. On
utilise ainsi, par exemple, les alliages 4343, 4104, 4045 et
4047, les propriétés recherchées dans ce cas étant
essentiellement une température de fusion faible et une bonne
mouillabilité.
Les alliages Al-Si peuvent également être filés sous forme de
barres ou profilés qui, en raison de leur bonne résistance à
l'usure et la température, sont utilisés dans des pièces
mécaniques telles que bielles, maítres-cylindres de freins,
arbres de transmission, paliers et divers composants de
moteurs et de compresseurs. Un des alliages utilisé à cette
fin est le 4032.
Le brevet français FR 2291284 décrit la fabrication de tôles
en alliage AlSi contenant de 4 à 15% de Si par coulée continue
entre deux cylindres refroidis. Ce mode de coulée est destiné
à accroítre l'allongement à la rupture, et donc la
formabilité.Il ne s'agit pas de tôles à haute résistance
utilisables dans des applications structurales, puisque les
tôles sont simplement recuites et les limites élastiques
exemplifiées ne dépassent pas 220 MPa.
Mais jamais personne jusqu'à présent n'a eu l'idée d'élaborer,
grâce à un choix judicieux de la composition et une gamme de
traitement thermique appropriée, des tôles en alliages Al-Si à
haute résistance mécanique utilisables pour des applications
structurales, notamment en construction mécanique, navale ou
aéronautique, par assemblages mécaniques ou soudés.
L'invention a ainsi pour objet des tôles traitées
thermiquement par mise en solution, trempe et éventuellement
revenu de manière à obtenir une limite élastique R0,2
supérieure à 320 MPa, destinées à la construction mécanique,
navale, aéronautique ou spatiale en alliage de composition
suivante (en poids):
La teneur en silicium est, de préférence, comprise entre 6,5
et 8%, correspondant à celle de l'alliage AS7G.
Un autre objet de l'invention est l'utilisation de tôles
notamment moyennes ou épaisses de cet alliage pour les intrados d'ailes
d'avions, de tôles notamment minces pour le revêtement de fuselages
d'avions, de tôles pour la fabrication de réservoirs
cryogéniques de fusées, de planchers et bennes de véhicules
industriels et de coques ou supersructures de bateaux.The Applicant, continuing its research into alloys to lighten the structures of aircraft, has noticed that another category of alloys usually used in molded form, Al-Si alloys of the 4000 series, not only makes it possible to improve significantly, between 3 and 10%, the specific modulus compared to alloys 2000 and 7000, but also had a bundle of properties in terms of toughness, resistance to fatigue and corrosion under stress meeting the severe requirements of aeronautical construction, without causing difficult problems in casting, rolling and heat treatment. In addition, these alloys have a much better weldability than most of the 2000 and 7000, and at least equivalent to the alloys of these series specially dedicated to welding, such as alloys 2219 and 7020. Finally, they have a much better temperature resistance than that of most alloys 2000 and 7000, and at least equivalent to that of alloys in these series specially studied for their temperature resistance, such as alloys 2019 and 2618.
Al-Si alloys are widely used for the production of molded parts. However, in this form, they have far lower mechanical strength, fatigue and toughness properties than the wrought and transformed alloys 2000 and 7000 used in structural parts. In rare cases, they can be used in laminated form, in particular for covering plated sheets intended for the manufacture of brazed heat exchangers. Alloys 4343, 4104, 4045 and 4047 are thus used, for example, the properties sought in this case being essentially a low melting temperature and good wettability.
Al-Si alloys can also be spun in the form of bars or profiles which, due to their good resistance to wear and temperature, are used in mechanical parts such as connecting rods, brake master cylinders, drive shafts , bearings and various components of motors and compressors. One of the alloys used for this purpose is 4032.
French patent FR 2291284 describes the manufacture of AlSi alloy sheets containing 4 to 15% Si by continuous casting between two cooled cylinders. This casting mode is intended to increase the elongation at break, and therefore the formability. They are not high-strength sheets usable in structural applications, since the sheets are simply annealed and the elastic limits exemplified do not exceed not 220 MPa.
But no one until now has had the idea of developing, thanks to a judicious choice of composition and an appropriate range of heat treatment, sheets of Al-Si alloys with high mechanical resistance usable for structural applications , in particular in mechanical, naval or aeronautical construction, by mechanical or welded assemblies.
The subject of the invention is therefore sheets heat treated by dissolving, quenching and optionally tempering so as to obtain an elastic limit R 0.2 greater than 320 MPa, intended for mechanical, naval, aeronautical or space construction made of alloy of following composition (by weight):
The silicon content is preferably between 6.5 and 8%, corresponding to that of the AS7G alloy.
Another object of the invention is the use of especially medium or thick sheets of this alloy for the undersides of aircraft wings, of particularly thin sheets for the coating of aircraft fuselages, of sheets for the manufacture of tanks cryogenic rockets, floors and skips of industrial vehicles and hulls or supersructures of boats.
Un autre objet de l'invention est le procédé de fabrication de tôles selon la revendicaiton 9.Another object of the invention is the method of manufacturing sheets according to claim 9.
Les tôles selon l'invention ont des teneurs en silicium
correspondant globalement aux domaines des alliages AS7G et
AS9G selon la norme française NF A 57-702 ou les désignations
A 357 et A 359 de l'Aluminum Association.
Le magnésium ne doit pas dépasser 1% pour éviter la formation
de composé intermétallique Mg2Si insoluble. Le cuivre doit
être limité à 0,8% pour éviter la formation de phases
insolubles Mg2Si et Q (AlMgSiCu). Cette teneur permet
également de limiter la sensibilité à la corrosion
intercristalline.
Le fer est également limité à 0,3%, et de préférence à 0,08%,
comme il l'est dans les alliages 7000 pour tôles fortes,
lorsqu'on a besoin d'une bonne tenacité et/ou d'un bon
allongement. La présence de titane est liée à l'affinage des
plaques au titane, identique à celui qui est pratiqué pour les
alliages actuels à moyenne et haute résistance. The sheets according to the invention have silicon contents generally corresponding to the fields of alloys AS7G and AS9G according to French standard NF A 57-702 or the designations A 357 and A 359 of the Aluminum Association.
Magnesium should not exceed 1% to avoid the formation of the insoluble intermetallic compound Mg 2 Si. Copper must be limited to 0.8% to avoid the formation of insoluble phases Mg 2 Si and Q (AlMgSiCu). This content also makes it possible to limit the sensitivity to intercrystalline corrosion.
Iron is also limited to 0.3%, and preferably 0.08%, as it is in 7000 alloys for heavy plate, when good toughness and / or good elongation. The presence of titanium is linked to the refining of the titanium plates, identical to that used for current medium and high strength alloys.
Comme cela se fait habituellement pour les alliages de moulage
de qualité, il est nécessaire de modifier l'alliage pour
éviter la formation de silicium primaire et obtenir une
structure eutectique fibrée finement dispersée. Pour cette
opération, le strontium est préférable au sodium qui pourrait
engendrer une fragilité à chaud à la transformation.
Les tôles selon l'invention peuvent être obtenues par coulée
verticale de plaques, un laminage à chaud jusqu'à 6 mm,
éventuellement un laminage à froid dans le cas de tôles
minces, une mise en solution entre 545 et 555°C, une trempe à
l'eau froide, une maturation à température ambiante et/ou un
revenu entre 6 et 24 h à une température comprise entre 150 et
195°C.
On peut faire précéder le laminage à chaud d'une
homogénéisation entre 530 et 550°C d'une durée inférieure à 20
h, suffisamment courte pour éviter une globulisation de
l'eutectique fibreux et une coalescence marquée des
dispersoïdes au manganèse et/ou au chrome, lorsque l'alliage
en contient. En l'absence d'homogénéisation, on obtient à
l'état final une microstructure eutectique très fine et non
globulisée, qui a un effet favorable sur la tenacité.
On peut ainsi obtenir à l'état T6 une limite élastique
supérieure à 320 et même 340 MPa, un allongement supérieur à 6
% dans le sens TL et 9% dans le sens L, et une tenacité,
mesurée par le facteur critique d'intensité de contraintes
K1c, supérieure à 20 MPaVm.
Dans ces conditions, l'alliage est soudable par des procédés
conventionnels TIG ou MIG, continus ou pulsés, selon qu'il
s'agit d'une tôle mince ou épaisse, et sa densité est toujours
inférieure à celle des alliages 2000 et 7000 traditionnels
ainsi qu'aux alliages Al-Li à teneur en lithium inférieure à
1%As is usually the case with quality molding alloys, it is necessary to modify the alloy to avoid the formation of primary silicon and to obtain a finely dispersed fibered eutectic structure. For this operation, strontium is preferable to sodium which could cause hot fragility during processing.
The sheets according to the invention can be obtained by vertical casting of plates, hot rolling up to 6 mm, optionally cold rolling in the case of thin sheets, dissolving between 545 and 555 ° C, quenching with cold water, maturation at room temperature and / or tempering between 6 and 24 hours at a temperature between 150 and 195 ° C.
Hot rolling can be preceded by homogenization between 530 and 550 ° C for a duration of less than 20 h, short enough to avoid a globalization of the fibrous eutectic and a marked coalescence of the manganese and / or chromium, when the alloy contains it. In the absence of homogenization, a very fine, non-globular eutectic microstructure is obtained in the final state, which has a favorable effect on the toughness.
One can thus obtain in the state T6 an elastic limit higher than 320 and even 340 MPa, an elongation higher than 6% in the direction TL and 9% in the direction L, and a tenacity, measured by the critical factor of intensity of constraints K1c, greater than 20 MPaVm.
Under these conditions, the alloy is weldable by conventional TIG or MIG processes, continuous or pulsed, depending on whether it is a thin or thick sheet, and its density is always lower than that of traditional 2000 and 7000 alloys. as well as Al-Li alloys with a lithium content of less than 1%
On a élaboré par coulée verticale des plaques de section 380 x
120 mm d'alliage de composition suivante (en poids):
L'alliage a été homogénéisé à 550°C pendant 8h, après une
montée en température de 4h, réchauffé pendant 2 h à 500°C,
puis laminé à chaud jusqu'à 20 mm d'épaisseur sur un laminoir
réversible. Des tôles découpées ont été mises en solution 2 h
à 550°C, trempées à l'eau et soumises à un revenu de 8h à
175°C, soit un état T651 selon les désignations de l'Aluminum
Association.
L'alliage a une densité de 2,678 et on a mesuré sur la tôle
par la méthode de la boucle d'hystérésis en traction, un
module d'élasticité E de 74100 MPa, soit un module spécifique
de 27670 MPa, à comparer avec les valeurs respectives de
2,770, 72500 MPa et 26175 MPa pour une tôle de même épaisseur
en alliage 2024 à l'état T351, soit une augmentation de 5,7%
du module spécifique. Cette augmentation est supérieure de
plus de 9% par rapport à l'alliage 2219 pour construction
soudée.
Les caractéristiques mécaniques, comparées à celles d'une tôle
en 2024 T351, sont les suivantes:
The alloy was homogenized at 550 ° C for 8 hours, after a temperature rise of 4 hours, reheated for 2 hours at 500 ° C, then hot rolled up to 20 mm thick on a reversible rolling mill. Cut sheets were placed in solution for 2 hours at 550 ° C, soaked in water and subjected to an income of 8 hours at 175 ° C, ie a state T651 according to the designations of the Aluminum Association.
The alloy has a density of 2,678 and a modulus of elasticity E of 74,100 MPa, or a specific module of 27,670 MPa, was measured on the sheet by the hysteresis loop method in tension. 2.770, 72,500 MPa and 26,175 MPa respectively for a sheet of the same thickness in 2024 alloy in the T351 state, an increase of 5.7% in the specific module. This increase is more than 9% higher compared to alloy 2219 for welded construction.
The mechanical characteristics, compared to those of a sheet in 2024 T351, are as follows:
Avec le même alliage que dans l'exemple 1, on réalise les
mêmes opérations, sauf que la plaque ne subit pas
d'homogénéisation avant le réchauffage précédant le laminage à
chaud. On mesure sur la tôle de 20 mm d'épaisseur un module
d'élasticité de 74170 MPa, soit une augmentation de 5,7% du
module spécifique par rapport au 2024 T351.
Les caractéristiques mécaniques mesurées sur la tôle de 20 mm
sont les suivantes:
The mechanical characteristics measured on the 20 mm sheet are as follows:
On constate que l'absence d'homogénéisation a un effet favorable sur l'allongement et sur la tenacité. Un examen micrographique comparé montre que la taille moyenne des particules au silicium, qui était de l'ordre de 7 microns pour la tôle homogénéisée, devient inférieure à 4 microns pour la tôle non homogénéisée.We find that the absence of homogenization has an effect favorable on elongation and tenacity. An exam compared micrographic shows that the average size of silicon particles, which was around 7 microns for the homogenized sheet becomes less than 4 microns for the non-homogenized sheet.
Claims (11)
- High strength aluminum alloy sheet metal heat treated by solution heat treating, quenching and possibly ageing to obtain a yield strength R0.2 greater than 320 MPa, for use in mechanical construction, shipbuilding, and the aeronautic and space industries, with composition (by weight)
Si 6.5 to 11% Mg 0.5 to 1.0% Cu < 0.8% Fe < 0.3% Mn < 0.5% and/or Cr: 0.5% Sr 0.008 to 0.025% Ti < 0.02% total other elements 0.2% the remainder aluminum. - Sheet metal according to claim 1, characterized in that the Si content is between 6.5 and 8%.
- Sheet metal according to one of claims 1 and 2, characterized in that the iron content is less than 0.08%.
- Use of sheet metal according to one of claims 1 to 3 for the manufacture of aircraft lower wing skins.
- Use of sheet metal according to claims 1 to 3 for the skin of aircraft fuselages.
- Use of sheet metal according to one of claims 1 to 3 for the manufacture of rocket cryogenic tanks.
- Use of sheet metal according to one of claims 1 to 3, for the manufacture of industrial vehicle floors or bins.
- Use of sheet metal according to one of claims 1 to 3 for the manufacture of ship hulls and superstructures.
- Process for manufacturing sheet metal according to one of claims 1 to 3, comprising the following steps:cast a slabreheat to between 480 and 520°Chot and possibly cold rollingsolution heat treat between 545 and 555°Cquench in cold waterand natural and/or artificial ageing
- Process according to claim 9, characterized in that it includes homogenization between 530 and 550°C for not more than 20 h, before reheating.
- Process according to one of claims 9 and 10, characterized in that it comprises 6h to 24h of ageing at between 150 and 195°C.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9407405 | 1994-06-13 | ||
FR9407405A FR2721041B1 (en) | 1994-06-13 | 1994-06-13 | Aluminum-silicon alloy sheet intended for mechanical, aeronautical and space construction. |
PCT/FR1995/000693 WO1995034691A1 (en) | 1994-06-13 | 1995-05-29 | Aluminium-silicon alloy sheet for mechanical, aircraft and space applications |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0717784A1 EP0717784A1 (en) | 1996-06-26 |
EP0717784B1 true EP0717784B1 (en) | 1998-09-16 |
Family
ID=9464309
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP95920993A Revoked EP0717784B1 (en) | 1994-06-13 | 1995-05-29 | Aluminium-silicon alloy sheet for mechanical, aircraft and space applications |
Country Status (8)
Country | Link |
---|---|
US (1) | US5837070A (en) |
EP (1) | EP0717784B1 (en) |
JP (1) | JPH09501988A (en) |
AT (1) | ATE171222T1 (en) |
CA (1) | CA2168946A1 (en) |
DE (1) | DE69504802T2 (en) |
FR (1) | FR2721041B1 (en) |
WO (1) | WO1995034691A1 (en) |
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Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE241389C (en) * | ||||
US3400057A (en) * | 1964-06-03 | 1968-09-03 | Reynolds Metals Co | Alloy and finishing system |
DE1255928B (en) * | 1966-01-13 | 1967-12-07 | Metallgesellschaft Ag | Process to achieve a long-lasting refining effect in aluminum-silicon alloys |
US4897124A (en) * | 1987-07-02 | 1990-01-30 | Sky Aluminium Co., Ltd. | Aluminum-alloy rolled sheet for forming and production method therefor |
JPH02159338A (en) * | 1988-12-12 | 1990-06-19 | Kobe Steel Ltd | Al-si alloy and its manufacture |
JP3183545B2 (en) * | 1991-10-09 | 2001-07-09 | 株式会社神戸製鋼所 | High strength aluminum brazing material for brazing sheet |
US5571347A (en) * | 1994-04-07 | 1996-11-05 | Northwest Aluminum Company | High strength MG-SI type aluminum alloy |
-
1994
- 1994-06-13 FR FR9407405A patent/FR2721041B1/en not_active Expired - Fee Related
-
1995
- 1995-05-29 JP JP8501711A patent/JPH09501988A/en active Pending
- 1995-05-29 EP EP95920993A patent/EP0717784B1/en not_active Revoked
- 1995-05-29 AT AT95920993T patent/ATE171222T1/en not_active IP Right Cessation
- 1995-05-29 US US08/537,864 patent/US5837070A/en not_active Expired - Fee Related
- 1995-05-29 DE DE69504802T patent/DE69504802T2/en not_active Revoked
- 1995-05-29 WO PCT/FR1995/000693 patent/WO1995034691A1/en not_active Application Discontinuation
- 1995-05-29 CA CA002168946A patent/CA2168946A1/en not_active Abandoned
Cited By (5)
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DE102006032699A1 (en) * | 2006-07-14 | 2008-01-17 | Bdw Technologies Gmbh & Co. Kg | Aluminum alloy and its use for a cast component, in particular a motor vehicle |
DE102006032699B4 (en) * | 2006-07-14 | 2010-09-09 | Bdw Technologies Gmbh & Co. Kg | Aluminum alloy and its use for a cast component, in particular a motor vehicle |
DE102009024190A1 (en) * | 2008-06-10 | 2010-02-18 | GM Global Technology Operations, Inc., Detroit | Sequential outsourcing of aluminum-silicon casting alloys |
US8728258B2 (en) | 2008-06-10 | 2014-05-20 | GM Global Technology Operations LLC | Sequential aging of aluminum silicon casting alloys |
RU2659514C1 (en) * | 2017-08-17 | 2018-07-02 | Общество с ограниченной ответственностью "Объединенная Компания РУСАЛ Инженерно-технологический центр" | Casting aluminum-silicon alloy |
Also Published As
Publication number | Publication date |
---|---|
DE69504802T2 (en) | 1999-03-25 |
US5837070A (en) | 1998-11-17 |
EP0717784A1 (en) | 1996-06-26 |
FR2721041A1 (en) | 1995-12-15 |
CA2168946A1 (en) | 1995-12-21 |
DE69504802D1 (en) | 1998-10-22 |
JPH09501988A (en) | 1997-02-25 |
FR2721041B1 (en) | 1997-10-10 |
ATE171222T1 (en) | 1998-10-15 |
WO1995034691A1 (en) | 1995-12-21 |
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