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Aluminum copper lithium alloy with improved mechanical strength and toughness

a technology of aluminum copper lithium alloy and mechanical strength, applied in the direction of electrochemical generators, batteries, electrical equipment, etc., can solve the problems of affecting the properties of other alloys, contaminating other alloys, and inability to obtain properties as beneficial as those obtained with alloys containing silver such as the aa2050 alloy, and achieve the effect of improving properties

Pending Publication Date: 2018-12-20
CONSTELLIUM ISSOIRE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention is a new aluminum-based alloy that can be used to make various products, such as an aircraft structural element. The alloy contains specific amounts of copper, lithium, zinc, magnesium, zr, manganese, silver, iron, silicon, and other elements. The alloy is cast into a liquid metal bath and then cast into a product through homogenization, cold working, and solution heat treatment. The product is then stress-relieved and aged. The technical effects of this invention include improved strength, fatigue resistance, and corrosion resistance of the alloy and its products.

Problems solved by technology

It is observed that products according to prior art made of alloy essentially contain no silver making it impossible to obtain properties as beneficial as those obtained with alloys containing silver such as the AA2050 alloy.
The addition of silver, that is an element infrequently used in aluminum alloys, could contaminate other alloys during recycling and affect their properties because there is an effect at low contents.

Method used

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  • Aluminum copper lithium alloy with improved mechanical strength and toughness
  • Aluminum copper lithium alloy with improved mechanical strength and toughness
  • Aluminum copper lithium alloy with improved mechanical strength and toughness

Examples

Experimental program
Comparison scheme
Effect test

example 1

[0100]In this example, several 400 mm thick slabs with the composition given in table 1 were cast.

TABLE 1Composition as a % by weight of Al—Cu—Li alloys cast in the form of a slab.CuMnMgZnLiAgZrFeSiTi543.610.340.170.560.930.130.100.0230.0150.022553.600.520.170.540.940.130.100.0230.0150.021563.600.340.430.570.930.000.100.0210.0150.022573.620.550.340.560.950.000.100.0170.0150.023713.620.360.430.560.900.010.100.0400.0240.031723.550.000.510.560.900.000.100.0350.0230.029

[0101]The slabs were homogenized at about 500° C. for about 12 hours and then scalped. The slabs were then hot rolled to obtain 50 mm, 102 mm or 130 mm thick slabs. The plates were solution heat treated at 527° C. and quenched with cold water. The plates were then stretched to give a permanent elongation of 4% or 6%.

[0102]The plates were aged at 145° C. or at 150° C. Samples were taken at ¼-thickness to measure the static mechanical properties in tension and in toughness in the L, LT, L-T and T-L directions at ½-thickness...

example 2

[0106]In this example, several 120 mm thick slabs with the composition given in table 5 were cast.

TABLE 5Composition as a % by weight of Al—Cu—Li cast in the form of a slab.AlloyCuMnMgZnLiAgZrFeSiTi583.680.330.300.680.810.000.100.0210.0150.025593.640.350.320.000.850.120.100.0230.0150.025613.640.340.510.660.840.000.100.0200.0150.025623.670.350.330.700.860.140.100.0200.0150.025

[0107]The slabs were machined to a thickness of 100 mm. The slabs were homogenized at about 500° C. for about 12 hours and then scalped. After homogenization, the slabs were hot rolled to obtain 27 mm thick slabs. The plates were solution heat treated and quenched in cold water or in hot water at 90° C. so as to vary the quenching rate and stretched with a permanent set of 3.5%.

[0108]The plates were aged at between 15 h and 50 h at 155 ° C. Samples were taken at mid-thickness to measure static mechanical properties in tension and the toughness KQ. The width W of the test pieces used to measure the toughness in t...

example 3

[0110]In this example, we studied the effect of controlled stretching and ageing on toughness results Kapp and Keff measured by an R curve.

[0111]50 mm and 102 mm thick plates were obtained with alloys 56 and 71 in table 1. The plates were solution heat treated at 527° C. and were quenched in cold water. Plates made of alloy 56 were then stretched to a permanent elongation of 4% and plates made of alloy 71 were stretched to a permanent elongation of 6%.

[0112]Plates made of alloy 56 were then aged for 40 hours at 150° C. and plates made of alloy 71 were aged for 20 hours at 150° C.

[0113]Samples were taken at ½ thickness for 50 mm thick plates and at ¼-thickness for 102 mm and 130 mm thick plates, to measure mechanical static tension and toughness characteristics in plain stress Kapp and Keff in the L, LT, L-T and T-L directions. For toughness, the R curve was measured on CCT test pieces with width W=406 mm and thickness B=6.35 mm.

[0114]The results are summarized in Table 8 below:

TABLE...

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Abstract

The invention is a rolled and / or forged product, made of an aluminium-based alloy comprising, in % by weight, Cu: 3.2-4.0; Li: 0.80-0.95; Zn: 0.45-0.70; Mg: 0.15-0.7; Zr: 0.07-0.15; Mn: 0.1-0.6; Ag:<0.15; Fe+Si≤0.20; at least one element from Ti: 0.01-0.15; Se: 0.02-0.1; Cr: 0.02-0.1; Hf: 0.02-0.5; V: 0.02-0.1; other elements ≤0.05 each and ≤0.15 in total, remainder aluminium. In the process for manufacturing the products according to the invention a bath of liquid metal based on aluminium as alloy according to the invention is melted, an unwrought product is cast from said bath of liquid metal; said unwrought product is homogenized at a temperature between 450° C. and 550° C.; said unwrought product is hot worked and optionally cold worked preferably to a thickness of at least 15 mm: said product is solution treated between 490° C. and 530° C. for 15 min to 8 h and quenched; said product is drawn in a controlled manner with a permanent deformation of 1% to 7% and a tempering of said product is carried out. The product is advantageous for the manufacture of an aircraft structural component.

Description

DOMAIN OF THE INVENTION[0001]The invention relates to aluminum-copper-lithium alloy products, and more particularly such products and methods of manufacturing and use, intended particular for aeronautical and aerospatial construction.STATE OF PRIOR ART[0002]Products, and particularly thick rolled and / or forged products made of aluminum alloy, are developed to produce high strength parts intended particularly for the aeronautical industry, the aerospatial industry or mechanical construction, by cutting, surfacing or machining from one block.[0003]Aluminum alloys containing lithium are very attractive in this respect because lithium can reduce the density of aluminum by 3% and increase the modulus of elasticity by 6% for each percent by weight of lithium added. If these alloys are to be selected for use in aircraft, their performance in service must be as good as that of currently used alloys, particularly in terms of a balance between static mechanical strength properties (yield stre...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): C22F1/057C22F1/00C22C21/14C22C21/16C22C21/18
CPCC22F1/057C22F1/002C22C21/14C22C21/16C22C21/18H01M2220/20Y02E60/10
Inventor WHELCHEL, RICKYARBAB, ALIREZABES, BERNARDSIGLI, CHRISTOPHE
Owner CONSTELLIUM ISSOIRE
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