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High-damage-tolerance aluminum alloy for aviation and preparation method

A damage tolerance, aluminum alloy technology, applied in the field of aluminum alloy manufacturing, can solve the problems of small total deformation, insufficient core compound and grain breakage, difference in core and surface deformation, etc. The effect of bite, fracture toughness and stress corrosion resistance reduction, reduction of flat rate

Inactive Publication Date: 2020-10-30
TIANJIN ZHONGWANG ALUMINUM IND CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of this, in order to solve the problems that the above-mentioned industrially produced thick plates face a small amount of total deformation, there is a difference in the amount of deformation between the core and the surface layer, and the degree of brokenness of the core compound and crystal grains is not enough, the present invention provides a method that can improve the thickness direction of the plate. Aerospace high damage tolerance aluminum alloy with microstructure and performance uniformity and preparation method thereof

Method used

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  • High-damage-tolerance aluminum alloy for aviation and preparation method
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  • High-damage-tolerance aluminum alloy for aviation and preparation method

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Embodiment 1

[0029] A method for preparing a high damage tolerance type aluminum alloy for aviation, comprising the following steps:

[0030] A. Calculate the amount of each aluminum alloy raw material and prepare the aluminum alloy raw material according to the ratio. The ratio of the mass percentage of each element of the aluminum alloy raw material is as follows:

[0031] element Si Fe Cu mn Mg Cr Zn Ti Zr Impurities Al content 0.033 0.067 2.21 0.002 2.18 0.001 6.08 0.038 0.097 0.10 margin

[0032] The ratio of Zn / Mg is 2.79, and the ratio of Cu / Mg is 1.01. Put the prepared aluminum alloy raw materials into the melting furnace for melting. After stirring, slag removal, degassing and impurity removal, and filtering, the aluminum liquid is semi-continuously cast into aluminum alloy through a crystallizer. Alloy hot-rolled slab stock.

[0033] B. Perform three-level homogenization treatment on the cast aluminum alloy ingot after stress rel...

Embodiment 2

[0039] The difference between embodiment 2 and embodiment 1 is that, in step A, the mass percentage ratio of each element of the aluminum alloy raw material is as follows:

[0040] element Si Fe Cu mn Mg Cr Zn Ti Zr Impurities Al content 0.03 0.078 2.17 0.001 2.08 0.004 6.14 0.023 0.093 0.10 margin

[0041] Zn / Mg ratio 2.95, Cu / Mg ratio 1.04.

[0042] Step C is rolled to a thickness of 60 mm through 9 passes, and the reductions of each pass are 40 mm, 40 mm, 50 mm, 65 mm, 65 mm, 65 mm, 30 mm, 30 mm, and 20 mm to ensure the shape of the prepared aluminum alloy profile.

[0043] The amount of tensile deformation in step E is 2.4-2.6%.

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Abstract

The invention belongs to the technical field of aluminum alloy manufacturing, and relates to a high-damage-tolerance aluminum alloy for aviation and a preparation method. The aluminum alloy comprisesthe following raw material components: not greater than 0.22% of Si, not greater than 0.25% of Fe, 2.0-2.6% of Cu, not greater than 0.20% of Mn, 1.9-2.6% of Mg, not greater than 0.06% of Cr, 5.7-6.7%of Zn, 0.02-0.06% of Ti, 0.08-0.15% of Zr, not greater than 0.15% of Ti + Zr, not greater than 0.05% of single impurity, not greater than 0.15% of total impurity, and the balance Al; in the initial hot rolling phase, each pass adopts lower rolling reduction not greater than 50mm; no less than three high rolling reduction passes exist before the last but one pass of rolling; the single-pass rollingreduction is 60-70mm; and the last-pass rolling reduction is not greater than 35mm. The high-damage-tolerance aluminum alloy solves the problems of low total deformation, difference between core andsurface layer deformation and insufficient crushing degree of core compounds and grains in industrially produced thick plates.

Description

technical field [0001] The invention belongs to the technical field of aluminum alloy manufacturing, and relates to an aviation high damage tolerance aluminum alloy and a preparation method thereof, in particular to an aviation high damage tolerance Al-Zn-Mg-Cu alloy and a preparation method thereof. Background technique [0002] With the increasing demand for travel and the vigorous development of modern national defense, people's requirements for the performance of aircraft continue to increase. Aircraft structure design tends to be large-scale, lightweight and integrated. As a material with ultra-high specific strength, Al-Zn-Mg-Cu alloy is widely used in aircraft structural materials. Large-scale structural parts are produced by CNC machining of pre-stretched Al-Zn-Mg-Cu alloy thick plates, which can effectively reduce the number of parts and joints, reduce the amount of assembly, and improve structural strength. At the same time, it also makes the material selection de...

Claims

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Application Information

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IPC IPC(8): C22C21/10C22C1/02C22F1/053C21D9/00B21B3/00
CPCB21B3/00B21B2003/001C21D9/0081C22C1/026C22C21/10C22F1/002C22F1/053
Inventor 景子毅赵俊才付彦军玄宝葛浩龙杜凤彪程素玲祖立成
Owner TIANJIN ZHONGWANG ALUMINUM IND CO LTD
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