Aleris Aluminum Koblenz Gmbh

Corus Aluminium Walzprodukte Gmbh

Constellium Issoire

Aleris Rolled Products Germany Gmbh

Constellium France

Christian Joachim Keidel

Guido Weber

Alfred Johann Peter Haszler

Rinze Benedictus

Alfred Ludwig Heinz

Alfred Johann Haszler

Achim Bürger

Hinrich Johannes Wilhelm Hargarter

Sabine Maria Spangel

Sunil Khosla

Andrew Norman

Achim Büerger

Nedia Telioui

Jörgen Van De Langkruis

Claus Jürgen Moritz

Hinrich Johannes Hargarter

William Sinclair Miller

Christiaan Reyndert Alderliesten

Achim Buerger

Claus Jurgen Moritz

Reyndert Christiaan Alderliesten

Johan Boezewinkel

Jorgen Van De Langkruis

Paola Valentina Morra

Sabri Sengo

Achim BÜRGER

Paola Valentina Absala Morra

An Al&#x2014;Zn&#x2014;Mg&#x2014;Cu alloy with improved damage tolerance-strength combination properties. The present invention relates to an aluminum alloy product comprising or consisting essentially of, in weight %, about 6.5 to 9.5 zinc (Zn), about 1.2 to 2.2% magnesium (Mg), about 1.0 to 1.9% copper (Cu), preferable (0.9 Mg&#x2212;0.6)&#x2264;Cu&#x2264;(0.9 Mg+0.05), about 0 to 0.5% zirconium (Zr), about 0 to 0.7% scandium (Sc), about 0 to 0.4% chromium (Cr), about 0 to 0.3% hafnium (Hf), about 0 to 0.4% titanium (Ti), about 0 to 0.8% manganese (Mn), the balance being aluminum (Al) and other incidental elements. The invention relates also to a method of manufacturing such as alloy.

Al&#x2014;Zn&#x2014;Mg&#x2014;Cu alloy with improved damage tolerance-strength combination properties

Fiber metal laminate () and an aircraft wing () having a longitudinal direction, comprising metal layers () and fiber reinforced plastic layers (&#x2033;) in between said metal layers (), wherein the metal layers () and the fiber reinforced plastic layers (&#x2033;) are bonded together, and wherein the fibers of at least some of the fiber reinforced plastic layers (&#x2033;) are arranged in a first group in a first plastic layer () and in a second group in a second plastic layer () whereby the fibers of the first group are at an angle with respect to the fibers of the second group, wherein said laminate () exhibits fibers of a first type and fibers of a second type, wherein the fibers of the first type being arranged in the said longitudinal direction of the laminate () in one or more of its fiber reinforced plastic layers (&#x2033;), and that it has adjacent fiber reinforced plastic layers () at or near a symmetry-plane of the laminate () that are provided with the fibers of the second type.

Aircraft wing and fiber metal laminate forming part of such an aircraft wing

The invention relates to an aluminium alloy wrought product with high strength and fracture toughness and high fatigue resistance and low fatigue crack growth rate, and having a composition for the alloy comprising, in weight %, about 0.3 to 1.0% magnesium (Mg), about 4.4 to 5.5% copper (Cu), about 0 to 0.20% iron (Fe), about 0 to 0.20% silicon (Si), about 0 to 0.40% zinc (Zn), and Mn in a range 0.15 to 0.8 as a dispersoids forming element in combination with one or more of dispersoids forming elements selected from the group consisting of: (Zr, Sc, Cr, Hf, Ag, Ti, V), in ranges of: about 0 to 0.5% zirconium (Zr), about 0 to 0.7% scandium (Sc), about 0 to 0.4% chromium (Cr), about 0 to 0.3% hafnium (Hf), about 0 to 0.4% titanium (Ti), about 0 to 1.0% silver (Ag), the balance being aluminium (Al) and other incidental elements, and whereby there is a limitation of the Cu&#x2014;Mg content such that &#x2212;1.1[Mg]+5.38&#x2266;[Cu]&#x2266;5.5. The invention further relates to a method of manufacturing such a product.

High-damage tolerant alloy product in particular for aerospace applications

Disclosed is a Al&#x2014;Zn alloy wrought product, and a method of manufacturing such a product, with an improved combination of high toughness and high strength by maintaining good corrosion resistance, the alloy including (in weight percent): Zn 6.0-11.0, Cu 1.4-2.2, Mg 1.4-2.4, Zr 0.05-0.15, Ti &#x3c;0.05, Hf and/or V &#x3c;0.25, and optionally Sc and/or Ce 0.05-0.25, and Mn 0.05-0.12, other elements each less than 0.05 and less than 0.50 in total, balance aluminium, wherein such alloy has an essentially fully unrecrystallized microstructure at least at the position T/10 of the finished product.

High-strength, high toughness Al-Zn alloy product and method for producing such product

Disclosed is a high damage tolerant Al&#x2014;Cu alloy of the AA2000 series having a high toughness and an improved fatigue crack growth resistance, including the following composition (in weight percent) Cu 3.8-4.7, Mg 1.0-1.6, Zr 0.06-0.18, Cr&#x3c;0.15, Mn&#x3e;0-0.50, Fe&#x2266;0.15, Si&#x2266;0.15, and Mn-containing dispersoids, the balance essentially aluminum and incidental elements and impurities, wherein the Mn-containing dispersoids are at least partially replaced by Zr-containing dispersoids. There is also disclosed a method for producing a rolled high damage tolerant Al&#x2014;Cu alloy product having a high toughness and an improved fatigue crack growth resistance, and applications of that product as a structural member of an aircraft.

High damage tolerant Al-Cu alloy

An Al&#x2014;Zn&#x2014;Mg&#x2014;Cu alloy with improved damage tolerance-strength combination properties. The present invention relates to an aluminium alloy product comprising or consisting essentially of, in weight %, about 6.5 to 9.5 zinc (Zn), about 1.2 to 2.2% magnesium (Mg), about 1.0 to 1.9% copper (Cu), preferable (0.9Mg&#x2212;0.6)&#x2266;Cu&#x2266;(0.9Mg+0.05), about 0 to 0.5% zirconium (Zr), about 0 to 0.7% scandium (Sc), about 0 to 0.4% chromium (Cr), about 0 to 0.3% hafnium (Hf), about 0 to 0.4% titanium (Ti), about 0 to 0.8% manganese (Mn), the balance being aluminium (Al) and other incidental elements. The invention relates also to a method of manufacturing such as alloy.

Al-Zn-Mg-Cu alloy with improved damage tolerance-strength combination properties

The present invention concerns a balanced Al&#x2014;Cu&#x2014;Mg&#x2014;Si alloy having a high toughness, good strength levels and an improved fatigue crack growth resistance, comprising essentially the following composition (in weight percent): Cu: 3.6-4.9, Mg: 1.0-1.8, Mn:&#x2266;0.50, preferably &#x3c;0.30, Si: 0.10-0.40, Zr:&#x2266;0.15, Cr:&#x2266;0.15, Fe:&#x2266;0.10, the balance essentially aluminum and incidental elements and impurities. There is also disclosed a method for producing the balanced Al&#x2014;Cu&#x2014;Mg&#x2014;Si alloy product having a high toughness and an improved fatigue crack growth resistance, and applications of that product as a structural member of an aircraft.

Balanced Al-Cu-Mg-Si alloy product

Disclosed is a high strength aluminium alloy brazing sheet, including an Al&#x2014;Cu core layer and at least one clad layer, the core layer having the following composition (in weight percent): Cu: 1.2-4.0, Mn: 0.06-1.5, Mg: 0.06-1.5, Si: up to 0.5, Zn: &#x2266;0.4, Zr: &#x2266;0.25, Fe: &#x2266;0.5, Ti: &#x2266;0.25, Cr: &#x2266;0.25; V&#x2266;0.25; the balance substantially aluminium and impurities, the clad layer including an Al&#x2014;Si based filler alloy and being applied on at least one side of the core layer. Also disclosed is a brazed assembly including the brazing sheet and the use of the brazing sheet for a brazing application such as a heat exchanger.

High strength aluminium alloy brazing sheet

Disclosed is an Al&#x2014;Cu alloy of the AA2000-series alloys with high toughness and an improved strength, including the following composition (in weight percent) Cu 4.5-5.5, Mg 0.5-1.6, Mn&#x2266;0.80, Zr&#x2266;0.18, Cr&#x2266;0.18, Si&#x2266;0.15, Fe&#x2266;0.15, the balance essentially aluminum and incidental elements and impurities, and wherein the amount (in weight %) of magnesium is either: (a) in a range of 1.0 to 1.6%, or alternatively (b) in a range of 0.50 to 1.2% when the amount of dispersoid forming elements such as Cr, Zr or Mn is controlled and (in weight %) in a range of 0.10 to 0.70%.

Al-Cu alloy with high toughness

Disclosed is a high damage tolerant Al&#x2014;Cu alloy of the AA2000 series having a high toughness and an improved fatigue crack growth resistance, including the following composition (in weight percent) Cu 3.8-4.7, Mg 1.0-1.6, Zr 0.06-0.18, Cr&#x3c;0.15, Mn&#x3e;0-0.50 , Fe&#x2266;0.15, Si&#x2266;0.15, and Mn-containing dispersoids, the balance essentially aluminum and incidental elements and impurities, wherein the Mn-containing dispersoids are at least partially replaced by Zr-containing dispersoids. There is also disclosed a method for producing a rolled high damage tolerant Al&#x2014;Cu alloy product having a high toughness and an improved fatigue crack growth resistance, and applications of that product as a structural member of an aircraft.

The present invention a high strength aluminium alloy brazing sheet, comprising an Al&#x2014;Zn core layer and at least one clad layer, the core layer including the following composition (in weight percent):  the balance aluminium and incidental elements and impurities. The clad layer includes an Al&#x2014;Si based filler alloy and is applied on at least one side of the core layer. The invention relates furthermore to a brazed assembly including such brazing sheet, to the use of such brazing sheet and to method for producing an aluminium alloy brazing sheet.

High strength aluminium alloy brazing sheet, brazed assembly and method for producing same

The present invention relates to a method for producing high strength balanced Al&#x2014;Mg&#x2014;Si alloy with an improved fatigue crack growth resistance and a low amount of intermetallics, comprising the steps of The pre-heating is preferably performed for 6 to 18 hours with temperatures between 530&#xb0; C. and 560&#xb0; C. The alloy has a fatigue crack growth rate at &#x394;K=20 MPa&#x221a;m of below 9.0E&#x2212;04 and at &#x394;K=40 MPa&#x221a;m of below 9.0E&#x2212;03, wherein the amount of intermetallics within the finally worked alloy product, according to the measured specific energy Delta H associated with the DSC signal, is below 1.5 J/g.

Method of producing a high strength balanced Al-Mg-Si alloy and a weldable product of that alloy

The invention relates to a weldable, high-strength aluminium alloy wrought product, which may be in the form of a rolled, extruded or forged form, containing the elements, in weight percent, Si 0.8 to 1.3, Cu 0.2 to 1.0, Mn 0.5 to 1.1, Mg 0.45 to 1.0, Ce 0.01 to 0.25, and preferably added in the form of a Misch Metal, Fe 0.01 to 0.3, Zr&#x3c;0.25, Cr&#x3c;0.25, Zn&#x3c;1.4, Ti&#x3c;0.25, V&#x3c;0.25, others each &#x3c;0.05 and total &#x3c;0.15, balance aluminium. The invention relates also to a method of manufacturing such an aluminium alloy product.

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Rinze Benedictus