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Heat treatment method of fatigue-damage-resisting aviation skin Al-Cu-Mg T3 aluminum alloy

A technology of al-cu-mgt3, heat treatment method, applied in the field of heat treatment of Al-Cu-MgT3 aluminum alloy for fatigue damage-resistant aviation skin, can solve the complex fatigue behavior of aluminum alloy, the gap in fatigue damage resistance, increase the content, etc. problem, to slow down the recrystallization process, eliminate harmful texture, and improve fatigue performance.

Inactive Publication Date: 2018-05-11
DONGGUAN UNIV OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In the face of new national defense and security requirements, the localization of large aircraft is urgent. In view of this, China has started the independent research and development of Al-Cu-Mg T3 aluminum alloy materials with high fatigue resistance, and its composition is (Cuwt%=4.0~4.5, Mgwt %=1.2~1.6, Mnwt%=0.45~0.7, Fewt%≤0.12, Siwt%≤0.06); so far, domestic related brand 2E12 has been comparable to foreign 2524 in conventional mechanical properties, but there is still a gap in fatigue damage resistance
[0005] The fatigue behavior of aluminum alloys is relatively complex; in summary, the fatigue performance is mainly related to the microstructural characteristics such as the second phase, grain size, and grain texture; from a single factor and qualitative point of view, the larger grain size, Increasing the content of useful textures such as Cube and Goss, or reducing the content of residual second phases can all help to reduce the fatigue crack growth rate in the stable growth stage; need

Method used

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  • Heat treatment method of fatigue-damage-resisting aviation skin Al-Cu-Mg T3 aluminum alloy
  • Heat treatment method of fatigue-damage-resisting aviation skin Al-Cu-Mg T3 aluminum alloy

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] Put the roll-shaped material with a total length of 10m into the heating annealing furnace, then raise the temperature inside the heating annealing furnace to 280°C at a heating rate of 2K / s, and then send it in at an unwinding speed of 1m / s In the isothermal annealing furnace, the plate that enters the isothermal annealing furnace after the temperature rise annealing is stagnant in the isothermal annealing furnace with a temperature of 300 °C for 40 minutes, and then transferred to the solid solution furnace at a speed of 0.25 m / s; after isothermal After annealing, the plate that enters the solid solution furnace is stagnant in the solid solution furnace with a temperature of 515°C for 5 minutes, and then transported to the cooling room at a speed of 5m / s, and quenched by circulating room temperature water, and the quenching time is 4s. Then take it out and roll it up to get the final Al-Cu-Mg T3 plate sample, the fatigue crack growth rate is: da / dN=1.83×10 -3 mm / cycle...

Embodiment 2

[0022] Put the roll-shaped material with a total length of 30m into the heating annealing furnace, then raise the temperature inside the heating annealing furnace to 400°C at a heating rate of 0.5K / s, and then unwind and convey at a speed of 0.25m / s After being sent into the isothermal annealing furnace, the plate that enters the isothermal annealing furnace after the temperature rise annealing is stagnated in the isothermal annealing furnace with an inner temperature of 400°C for 20 minutes, and then transferred to the solid solution furnace at a speed of 1m / s; After isothermal annealing, the plates entering the solid solution furnace stagnate for 120 minutes in the solid solution furnace at a furnace temperature of 495 ° C, and then are transported to the cooling room at a speed of 0.25 m / s, and are quenched by circulating room temperature water. The quenching time is After 7s, it was taken out and rolled up to obtain the final Al-Cu-Mg T3 plate sample, and its fatigue perfor...

Embodiment 3

[0024] Put the roll-shaped material with a total length of 20m into the heating annealing furnace, then raise the temperature inside the heating annealing furnace to 320°C at a heating rate of 1K / s, and then send it to the After entering the isothermal annealing furnace, the plates entering the isothermal annealing furnace after the temperature rise annealing are stagnant in the isothermal annealing furnace with a temperature of 350 ° C for 30 minutes, and then transferred to the solid solution furnace at a speed of 0.6 m / s; After isothermal annealing, the plate entering the solid solution furnace is stagnant in the solid solution furnace with a temperature of 500 ° C for 60 minutes, and then transported to the cooling room at a speed of 3 m / s, and quenched by circulating room temperature water, and the quenching time is 6 s , then take it out and roll it up to get the final Al-Cu-Mg T3 plate sample, the fatigue performance is: da / dN=1.36×10 -3 mm / cycle, ΔK=30MPa.m 1 / 2 . The...

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Abstract

The invention relates to a heat treatment method of a fatigue-damage-resisting aviation skin Al-Cu-Mg T3 aluminum alloy. The method comprises four continuous stages including the rising annealing stage, the isothermal annealing stage, the solid solution treatment stage and the cooling stage; in the rising annealing stage, a coiled materials with the total length of 10 to 30 m is put into a risingannealing furnace, the temperature in the rising annealing furnace is increased to 280 DEG C to 400 DEG C at the rising rate of 0.25 to 2K / s, and then the material is fed into an isothermal annealingfurnace at the unreeling conveying speed of 0.25 to 1m / s. Through segmentation continuous heat treatment, three main micro-structure features of grain size, texture and the residual second phase in the alloy are coordinated overall and regulated. The three features are controlled, and the fatigue performance of the aviation skin Al-Cu-Mg T3 aluminum alloy board is further improved.

Description

technical field [0001] The invention relates to the field of material processing, in particular to an Al-Cu-Mg T3 aluminum alloy heat treatment method for fatigue damage-resistant aviation skins. Background technique [0002] Al-Cu-Mg-T3 aluminum alloy has high strength, excellent fracture toughness and fatigue damage resistance, and is widely used by aviation giants such as Boeing and Airbus to prepare fuselage frames, wing spars, and fuselage skins of large passenger aircraft materials etc. Its main elements are Al, Cu and Mg, auxiliary elements include Mn, Ti, etc., and also include a small amount of Fe and Si impurity elements, and the main strengthening phase of the alloy is S phase (Al 2 CuMg). [0003] Since the 1950s, Al-Cu-Mg has developed from 2024 to 2524 or even 2624, mainly by further controlling the content of Fe and Si impurities to further improve performance. In order to adapt to higher airworthiness standards, compared with the early 2024-T3 alloy, the p...

Claims

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Application Information

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IPC IPC(8): C22F1/04
CPCC22F1/04
Inventor 申芳华周梓荣李文芳田军孙振忠钟守炎陈举铭黄辉宇谢春晓郭建文邓君王康王艳林祝闻
Owner DONGGUAN UNIV OF TECH
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