Alcoa Inc.

Arconic Corporation

Aluminum Company of America

Arconic Technologies LLC

Gary H Bray

Jen C Lin

John Liu

Ralph R Sawtell

Roberto J Rioja

John Newman

Diana K Denzer

Paul E Magnusen

Gregory B Venema

Cindie Giummarra

Andre L Wilson

Dhruba J Chakrabarti

Cagatay Yanar

Rajeev G Kamat

Edward L Colvin

Robert W Westerlund

Shawn J Murtha

James Daniel Bryant

Lynette M Karabin

Shawn Patrick Sullivan

David J McNeish

Darl G Boysel

Gino Norman Iasella

Julien Boselli

Robert C Pahl

David A Lukasak

Les A Yocum

Mario Greco

Allison S Warren

Todd K Cogswell

Brett P Connor

Terrence N Thom

James T Staley

Francine S Bovard

John R Brockenbrough

Lynn Eugene Oswald

Shelly M Miyasato

Dhurba J Chakrabarti

Matthew D Garratt

Greg Venema

Patrick Ulysse

Yanar Cagatay

Mark A James

Severine Cambier

John M Newman

New 2xxx aluminum alloys containing vanadium are disclosed. In one embodiment, the aluminum alloy includes 3.3-4.1 wt. % Cu, 0.7-1.3 wt. % Mg, 0.01-0.16 wt. % V, 0.05-0.6 wt. % Mn, 0.01 to 0.4 wt. % of at least one grain structure control element, the balance being aluminum, incidental elements and impurities. The new alloys may realize an improved combination of properties, such as in the T39 or T89 tempers.

Aluminum-copper alloys containing vanadium

New magnesium-zinc aluminum alloy bodies and methods of producing the same are disclosed. The new magnesium-zinc aluminum alloy bodies generally include 3.0-6.0 wt. % magnesium and 2.5-5.0 wt. % zinc, where at least one of the magnesium and the zinc is the predominate alloying element of the aluminum alloy bodies other than aluminum, and wherein (wt. % Mg)/(wt. % Zn) is from 0.6 to 2.40, and may be produced by preparing the aluminum alloy body for post-solutionizing cold work, cold working by at least 25%, and then thermally treating. The new magnesium-zinc aluminum alloy bodies may realize improved strength and other properties.

Heat treatable aluminum alloys having magnesium and zinc

Improved aluminum-copper-lithium alloys are disclosed. The alloys may include 3.4-4.2 wt. % Cu, 0.9-1.4 wt. % Li, 0.3-0.7 wt. % Ag, 0.1-0.6 wt. % Mg, 0.2-0.8 wt. % Zn, 0.1-0.6 wt. % Mn, and 0.01-0.6 wt. % of at least one grain structure control element, the balance being aluminum and incidental elements and impurities. The alloys achieve an improved combination of properties over prior art alloys.

Aluminum-copper-lithium alloys

Heat treatable aluminum alloys having magnesium and zinc and methods for producing the same

Aluminum alloys having an improved combination of properties are provided. In one aspect, a method for producing the alloy includes preparing an aluminum alloy for artificial aging and artificially aging the alloy. In one embodiment, the artificially aging step includes aging the aluminum alloy at a temperature of at least about 250&#xb0; F., and final aging the aluminum alloy at a temperature of not greater than about 225&#xb0; F. and for at least about 20 hours.

Aging of aluminum alloys for improved combination of fatigue performance and strength

Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The instantly disclosed alloys are useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction.

Aluminum alloy products having improved property combinations and method for artificially aging same

Aluminum alloy products about 4 inches thick or less that possesses the ability to achieve, when solution heat treated, quenched, and artificially aged, and in parts made from the products, an improved combination of strength, fracture toughness and corrosion resistance, the alloy consisting essentially of: about 6.8 to about 8.5 wt. % Zn, about 1.5 to about 2.00 wt. % Mg, about 1.75 to about 2.3 wt. % Cu; about 0.05 to about 0.3 wt. % Zr, less than about 0.1 wt. % Mn, less than about 0.05 wt. % Cr, the balance Al, incidental elements and impurities and a method for making same. The invention alloy is useful in making structural members for commercial airplanes including, but not limited to, upper wing skins and stringers, spar caps, spar webs and ribs of either built-up or integral construction. The invention alloy may be aged by 2 or 3 step practices while exceeding the SCC requirements for applications for which the invention alloy is primarily intended. The flexibility of the invention in this regard is useful for its application in multi-alloy or multi-material systems joined by welding or bonding and subsequently aged.

Aluminum alloy having an improved combination of properties are provided. In one aspect, a method for producing the alloy includes preparing an aluminum alloy for artificial aging and artificially aging the alloy. In one embodiment, the artificially aging step includes aging the aluminum alloy at a temperature of at least about 250&#xb0; F., and final aging the aluminum alloy at a temperature of not greater than about 225&#xb0; F. and for at least about 20 hours. These aluminum alloys realize an improved combination of properties, including improved strength with at least equivalent fatigue crack growth resistance.

The invention provides a 2000 series aluminum alloy having enhanced damage tolerance, the alloy consisting essentially of about 3.0-4.0 wt % copper; about 0.4-1.1 wt % magnesium; up to about 0.8 wt % silver; up to about 1.0 wt % Zn; up to about 0.25 wt % Zr; up to about 0.9 wt % Mn; up to about 0.5 wt % Fe; and up to about 0.5 wt % Si, the balance substantially aluminum, incidental impurities and elements, said copper and magnesium present in a ratio of about 3.6-5 parts copper to about 1 part magnesium. The alloy is suitable for use in wrought or cast products including those used in aerospace applications, particularly sheet or plate structural members, extrusions and forgings, and provides an improved combination of strength and damage tolerance.

2000 Series alloys with enhanced damage tolerance performance for aerospace applications

An aluminum-copper-magnesium alloy having ancillary additions of lithium. The alloy composition includes from about 3 to about 5 weight percent Cu, from about 0.5 to about 2 weight percent Mg, and from about 0.01 to about 0.9 weight percent Li. The combined amount of Cu and Mg is maintained below a solubility limit of the aluminum alloy. The alloys possess improved combinations of fracture toughness and strength, and also exhibit good fatigue crack growth resistance.

Aluminum-copper-magnesium alloys having ancillary additions of lithium

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Murrysville, PA, United States of America

Gary H Bray