Al-zn-cu-mg alloys and their manufacturing process

An aluminum-based alloy, mg1.55 technology, applied in the field of aluminum-based alloys, can solve the problems of long aging time and difficulty in mastering the three-step process

Inactive Publication Date: 2021-07-23
CONSTELLIUM ISSOIRE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The three-step aging time is long and difficult to master, and it is desirable to obtain high corrosion resistance without requiring such heat treatment
[0021] None of the literature describing high-strength 7xxx alloy products describes alloy products with no tendency to crack deviation and low fatigue crack growth rates, combined with high strength, high toughness properties, and high corrosion resistance

Method used

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  • Al-zn-cu-mg alloys and their manufacturing process
  • Al-zn-cu-mg alloys and their manufacturing process
  • Al-zn-cu-mg alloys and their manufacturing process

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0092] Two ingots were cast, one a product of the invention (A) and one a comparative example (B), having the following composition (Table 1):

[0093] Table 1: Composition (% by weight) of inventive and control castings.

[0094] alloy Si Fe Cu Mg Zn Ti Zr A 0.03 0.04 2.13 1.75 7.05 0.04 0.06 B 0.05 0.09 1.64 2.25 6.10 0.02 0.11

[0095] The ingots were then peeled and homogenized at about 475°C. The ingots were hot rolled into plates with a thickness of 102 mm (alloy A) or 110 mm (alloy B). The hot-rolling inlet temperature of alloy A is 350°C, and the hot-rolling inlet temperature of alloy B is 440°C. The panels were solution heat treated at a soak temperature of about 475°C. The plates were quenched and stretched with a permanent elongation of 2.0 to 2.5%.

[0096] The control plate was aged in two steps: 4 hours at 120°C followed by 15 hours at 155°C for a total equivalent time of 17 hours at 155°C to obtain the T7651 t...

Embodiment 2

[0116] Another ingot was cast, which had a composition according to the invention (C), (Table 6):

[0117] Table 6: Composition of Casting C (% by weight).

[0118] alloy Si Fe Cu Mg Zn Ti Zr C 0.03 0.04 2.15 1.65 7.11 0.03 0.10

[0119] The ingots were then peeled and homogenized at 475°C. The ingots were hot rolled into plates with a thickness of 152 mm. The hot rolling entrance temperature was 420°C. The panels were solution heat treated at a heat soak temperature of about 475°C. The plates were quenched and stretched with a permanent elongation of 2.0 to 2.5%.

[0120] Due to the high hot rolling temperature, the microstructure of the plate is different from the present invention, the plate produced has less than 20% recrystallized grains in the middle of the thickness.

[0121] Under the maximum load of 4KN and R=0.1, on the CT sample (CT10W40, thickness 10mm, width 40mm) along the L-S direction at the middle of the thickness and...

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Abstract

The invention relates to a rolled aluminum-based alloy product having a thickness of at least 80 mm comprising, (in weight %) : Zn 6.85-7.25, Mg 1.55-1.95, Cu 1.90-2.30, Zr 0.04-0.10, Ti 0-0.15, Fe 0-0.15, Si 0-0.15, other elements <=0.05 each and <=0.15 total, remainder Al, wherein at mid-thickness more than 75 % of grains are recrystallized or at mid-thickness 30-75 % of grains are recrystallized and non- recrystallized grains have an aspect ratio in a L / ST cross section less than 3. A process for the manufacture of a rolled aluminum-based alloy product comprises the steps of: (a) casting an ingot made in an alloy according to the invention, (b) conducting an homogenization of the ingot (c) conducting hot rolling of said homogenized ingot in one or more stages by rolling, (d) conducting a solution heat treatment a quench, (e) conducting stress relieving, and, (f) conducting an artificial aging treatment. The products of the invention are suitable for aircraft construction and have advantageous fatigue crack growth properties.

Description

technical field [0001] The present invention relates generally to aluminum-based alloys, and more particularly to Al-Zn-Cu-Mg aluminum-based alloys, particularly such alloys for aerospace applications. Background technique [0002] Over the years, Al-Zn-Cu-Mg aluminum-based alloys have been widely used in the aerospace industry. With the development of aircraft structures and efforts aimed at reducing weight and cost, there is a constant search for the best compromise between properties such as strength, toughness and corrosion resistance. In addition, process improvements in casting, rolling, and heat treatment can advantageously provide further control and property tradeoffs in the alloy composition map. [0003] Thick rolled, forged or extruded products made of Al-Zn-Cu-Mg aluminum base alloys are especially used in the production of integrally machined high-strength structural components for the aerospace industry, such as wing ribs, spars (spar), frame (frame) and oth...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C21/10C22F1/053
CPCC22C21/10C22F1/053C21D9/46
Inventor E·尼泽里R·惠切尔J-C·埃斯特罗姆
Owner CONSTELLIUM ISSOIRE
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