High damage tolerant aa6xxx-series alloy for aerospace application

a high damage tolerance, aerospace technology, applied in the direction of manufacturing tools, welding/cutting media/materials, welding apparatus, etc., can solve the problems of 6000 series alloys that are generally unsuitable for commercial aircraft design, lack of known alloys, and insufficient strength for most structural aerospace applications, etc., to achieve the effect of improving corrosion resistance properties

a high damage tolerance, aerospace technology, applied in the direction of manufacturing tools, welding/cutting media/materials, welding apparatus, etc., can solve the problems of 6000 series alloys that are generally unsuitable for commercial aircraft design, lack of known alloys, and insufficient strength for most structural aerospace applications, etc., to achieve the effect of improving corrosion resistance properties

US20080145266A1Inactive Publication Date: 2008-06-19ALERIS ALUMINUM KOBLENZ GMBH
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  • High damage tolerant aa6xxx-series alloy for aerospace application

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[0059]Five different alloys have been DC-cast into ingots, then subsequently scalped, pre-heated for about 6 hours at 560° C. (heating-up speed about 30° C. / h), hot rolled to a gauge of 8 mm whereby the hot-mill entry temperature was about 480° C., cold rolled to a final gauge of 2 mm, solution heat treated for 10 min. at 560° C., water quenched, 2% stretch, aged to a T6-temper by holding for 4 hours at 190° C. and followed by air cooling to room temperature. Table 1 gives the chemical composition of the five alloys cast. The alloy composition of Alloy No. A is a regular 6013 alloy for reference purposes. Alloy No. B is the 6013 alloy with increased Cr content, and is also a reference alloy. Alloys Nos. C to E are according to this invention.

TABLE 1The chemical compositions of the ingot cast alloys.No.AlloySiMgFeCuMnCrTiZrA60130.730.770.120.840.35—0.01—(ref.)BRef.0.740.770.120.840.360.10.01—Cinv.0.710.740.120.860.35—0.12—Dinv.0.720.760.130.840.36 0.090.12—Einv.0.740.790.120.840.350....

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Abstract

A weldable aluminum alloy wrought product having high strength and improved resistance to intergranular corrosion, the alloy consisting essentially of, in weight percent: Si 0.2-1.3, Mg 0.4-1.5, Cu 0.1-1.1, Mn up to 0.7, Fe 0.02-0.3, Zn up to 0.9, Cr up to 0.25, Ti 0.06-0.19, Zr up to 0.2, Ag up to 0.5, and wherein 0.1<Ti+Cr<0.35, other elements and unavoidable impurities each <0.05, total <0.20, and the balance aluminum.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]This claims the benefit of United States provisional patent application No. 60 / 814,068 filed Jun. 16, 2006, and claims priority of European patent application number 06012379 filed Jun. 16, 2006, both incorporated herein by reference.FIELD OF THE INVENTION[0002]This invention pertains to aluminum aerospace alloys. More particularly, this invention pertains to aluminum alloys of the AA6xxx-series (or AA6000-series) that are suitable for welding, yet have improved performance properties, particularly corrosion resistance and damage tolerance properties.BACKGROUND TO THE INVENTION[0003]As will be appreciated herein below, except as otherwise indicated, alloy designations and temper designations refer to the Aluminum Association designations in Aluminum Standards and Data and the Registration Records, as published by the Aluminum Association.[0004]For any description of alloy composition or preferred alloy compositions, all references to perce...

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Application Information

Patent Timeline
19 Jun 2008
Publication
US20080145266A1
IPC
C22C21/14
CPC
B23K35/286; B23K2203/10; C22C21/00; C22F1/05; C22C21/14; C22C21/16; C22F1/04; C22C21/08
Inventors
CHEN, SHANGPING; ZHUANG, LINZHONG