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A method for manufacturing an aluminum alloy section bar used for aviation

A technology of aluminum alloy profiles and aluminum alloy ingots, which is applied in the field of aluminum alloy profile manufacturing, can solve the problems of low tensile strength, elongation after fracture and low peeling corrosion performance, and achieve excellent comprehensive mechanical properties, good formability, and surface good quality effect

Inactive Publication Date: 2018-06-15
郝金芳
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention aims to solve the problems of low tensile strength, specified non-proportional elongation strength, elongation after fracture and low exfoliation corrosion performance of various aluminum alloy profiles produced by the existing technology, and provides a kind of double-stage aging to manufacture aviation aluminum alloys. profile method

Method used

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Effect test

specific Embodiment approach 1

[0020] Specific implementation mode 1: In this implementation mode, a method for manufacturing aluminum alloy profiles for aviation using double-stage aging is specifically prepared according to the following steps:

[0021] 1. Melting: Zn: 5.9%-6.9%, Mg: 2.0%-2.7%, Cu: 1.9%-2.5%, Zr: 0.08%-0.15%, Si: ≤0.12%, Fe: ≤0.15%, Mn: ≤0.10%, Cr: ≤0.04%, Ti: ≤0.06%, and the balance is Al Weighing pure aluminum ingots, pure copper ingots, pure magnesium ingots, pure zinc ingots, aluminum-zirconium alloy ingots, aluminum Titanium alloy ingots and aluminum titanium boron grain refiner are added to a dry melting furnace, and melted at a temperature of 720°C to 760°C for 6h to 7h to obtain an aluminum alloy melt;

[0022] 2. Casting: Put the aluminum alloy solution obtained in step 1 at a temperature of 715°C-750°C, a casting speed of 80mm / min-90mm / min, a cooling water strength of 0.01MPa-0.03MPa, and a cooling water temperature of 18°C-25 Casting rods with a diameter of 192mm to 195mm unde...

specific Embodiment approach 2

[0032] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that in step 1, according to the mass percentage of elements, Zn: 6.2% to 6.5%, Mg: 2.2% to 2.5%, Cu: 2.0% to 2.2%, Zr: 0.09%~0.12%, Si: ≤0.10%, Fe: ≤0.12%, Mn: ≤0.06%, Cr: ≤0.03%, Ti: ≤0.05%, and the balance is Al Weigh pure aluminum ingots, pure copper Ingots, pure magnesium ingots, pure zinc ingots, aluminum-zirconium alloy ingots, aluminum-titanium alloy ingots and aluminum-titanium-boron grain refiners are added to the dry melting furnace. Others are the same as in the first embodiment.

specific Embodiment approach 3

[0033] Specific embodiment three: the difference between this embodiment and specific embodiment one or two is: in step one, according to the mass percentage of elements, Zn: 6.4%, Mg: 2.3%, Cu: 2.1%, Zr: 0.10%, Si: 0.05%, Fe: 0.08%, Mn: 0.05%, Cr: 0.02%, Ti: 0.03%, and the balance is Al to weigh pure aluminum ingots, pure copper ingots, pure magnesium ingots, pure zinc ingots, aluminum-zirconium alloy ingots, Al-Ti alloy ingot and Al-Ti-B grain refiner are added into the dry melting furnace. Others are the same as in the first or second embodiment.

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Abstract

The invention relates to a method for manufacturing an aluminum alloy section bar, particularly relates to a method for manufacturing an aluminum alloy section bar used for aviation, and overcomes a problem that various aluminum alloy section bars produced by conventional processes are low in tensile strength, low in proof strength at non-proportional extension, low in percentage elongation afterfracture and low in exfoliation corrosion performance. The method includes 1) smelting, 2) casting, 3) cutting off, 4) lathing to remove skin, 5) annealing, 6) heating, 7) extrusion, 8) solution treatment and water quenching, 9) stretching and 10) ageing treatment. Through alloy component optimization and through adoption of optimized solution treatment and ageing treatment processes after extrusion, integrated performance requirements of users on the alloy section bar are met, the prepared aluminum alloy section bar has a good physical dimension, good surface quality, good forming performancein industrial production and excellent comprehensive mechanical performance. The method is used for manufacturing the aluminum alloy section bar used for aviation.

Description

technical field [0001] The invention relates to a method for manufacturing an aluminum alloy profile. Background technique [0002] Aluminum alloy materials have a wide range of applications, and can be used in various fields such as construction, electronic appliances, transportation, aviation, and aerospace in industry. At present, a certain aviation product in my country requires a special profile, which requires the tensile strength of this aluminum alloy T74511 profile to reach 540N / mm 2 , The specified non-proportional extension strength reaches 480N / mm 2 , The elongation after breaking reaches 8%, and the exfoliation corrosion performance reaches EB level. [0003] In the research in this field, the title of the invention is "A Method for Manufacturing Aluminum Alloy Rivet Rods for Aerospace", which discloses a method for preparing aluminum alloys with copper as the main component and single-stage aging; the title of the invention is "A Large "Preparation Method of...

Claims

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Application Information

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IPC IPC(8): C22C21/10C22C1/03C22F1/053
CPCC22C21/10C22C1/026C22C1/03C22F1/053
Inventor 郝金芳
Owner 郝金芳
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