Aleris Aluminum Koblenz Gmbh

Corus Aluminium Walzprodukte Gmbh

Hoogovens Aluminium Walzprodukte Gmbh

Aleris Rolled Products Germany Gmbh

Alfred Ludwig Heinz

Christian Joachim Keidel

Rinze Benedictus

Alfred Johann Peter Haszler

Otmar M Muller

Nedia Telioui

Hinrich Johannes Wilhelm Hargarter

Sabine Maria Spangel

Sunil Khosla

Alfred Johann Haszler

Andrew Norman

Achim Büerger

Guido Weber

Werner A Schelb

Claus Jürgen Moritz

Jörgen Van De Langkruis

Hinrich Johannes Hargarter

Otmar Martin M&uuml;ller

Achim Buerger

Claus Jurgen Moritz

Johan Boezewinkel

Jorgen Van De Langkruis

Paola Valentina Morra

Sabri Sengo

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

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

A method for producing an integrated monolithic aluminum structure, including the steps of: (a) providing an aluminum alloy plate from an aluminum alloy with a predetermined thickness (y), (b) shaping or forming the alloy plate to obtain a predetermined shaped structure, (c) heat-treating the shaped structure, (d) machining, e.g. high velocity machining, the shaped structure to obtain an integrated monolithic aluminum structure.

Method for producing an integrated monolithic aluminum structure and aluminum product machined from that structure

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 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.

Stress relieving of an age hardenable aluminium alloy product

The invention relates to a product comprising an aluminum base alloy consisting of (in weight %): Cu 3.8-4.9, Mg 1.2-1.8, Mn 0.1-0.9, Fe max. 0.12, Si max. 0.10, Ti max. 0.15, Zn max. 0.20, Cr max. 0.10, impurities each max. 0.05, total max. 0.15, balance aluminum. The product having a minimum L-0.2%yield strength of 300 MPa or more, a minimum LT-0.2%yield strength of 270 MPa, a minimum T-L fracture toughness K,of 100 MPa.m or more for a 700 mm wide CCT-panel, and has in both L/ST- and LT/ST-sections an average grain size of at least 6 according to ASTM E-112. Further the invention relates to a method for the manufacturing of such a product.

Damage tolerant aluminum alloy product and method of its manufacture

Stress relieving of an age hardenable aluminium alloy product after solution heat treatment and quenching, is carried out by a permanent cold plastic deformation applied by the steps of:

Stress relieving of an age hardenable aluminum alloy product

Process for manufacturing thick aluminum alloy plate having improved properties comprising the hot deformation of an ingot, wherein the hot deformation comprises the combination of

Manufacture of thick aluminum alloy plate

An aluminium alloy plate is provided with a thickness of more than 2 inches, e.g. 6, 7 or 8 inches, and having an average logarithmic fatigue life of more than 100,000 cycles determined in accordance with ASTM test method E 466. The density of micropores with a size larger than 80 .mu.m in all locations in the midplane (T/2) midwidth position at head and tail ends of the finished plate as measured by Optical Microscopy of samples in any plane perpendicular to the midplane is less than 0.025 micropores per cm.sup.2. The plate may be formed by degassing of a melt to give a specified porosity of the cast ingot, and by hot rolling with at least one specified high reduction ratio pass.

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Niederahr, Germany

Alfred Ludwig Heinz