A method for manufacturing a 7-series aluminum alloy profile for the upper girder of a civil aircraft wing

A technology for aluminum alloy profiles and alloy profiles, which is used in metal extrusion control equipment, manufacturing tools, metal extrusion and other directions, can solve problems such as large extrusion deformation resistance, serious casting cracking tendency, and aircraft delivery risks. The effect of enhancing lateral performance and reducing residual stress

Active Publication Date: 2022-04-29
SHANDONG NANSHAN ALUMINUM +1
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AI Technical Summary

Problems solved by technology

However, the existing technology only conducts process research and organizational control according to the requirements of the AMS4336 standard, and does not carry out process optimization and performance improvement according to the service conditions and performance requirements of the 7-series aluminum alloy profiles used for wing girders in China's civil aircraft manufacturing industry. Therefore, Only profiles that meet the standard requirements of AMS4336 can be obtained, but cannot meet the requirements for the use of long stringers on the wings of civil aircraft
[0008] The reason is that the domestic civil aviation industry started late and lacked the demand for the use of long stringers on the wings of civil aircraft. As a result, aluminum profile manufacturers did not fully understand the performance and requirements of the long stringers on the wings of civil aircraft. Not enough time and effort have been invested in relevant research and development, therefore, it has been impossible to produce profiles that fully meet the requirements for the use of long stringers on civil aviation wings for a long time
Secondly, the 7055 alloy itself has a serious casting cracking tendency, high extrusion deformation resistance, and strong quenching sensitivity. It has very high requirements for equipment technology level and process control ability, and these technologies have been under patent protection and blockade for a long time.
Domestic enterprises have made unremitting efforts to produce profiles that meet the requirements of the AMS4336 standard, and have made great progress, but they are still unable to produce 7-series aluminum alloy profiles that meet the requirements for the use of long girders on the wings
[0009] Since the launch of the domestic civil aircraft project, the 7-series aluminum alloy profiles used for the wing girders have been relying on imports, which not only increases the manufacturing cost of the whole aircraft, but also faces the risk of aircraft delivery due to the cut-off of profiles at any time

Method used

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  • A method for manufacturing a 7-series aluminum alloy profile for the upper girder of a civil aircraft wing
  • A method for manufacturing a 7-series aluminum alloy profile for the upper girder of a civil aircraft wing
  • A method for manufacturing a 7-series aluminum alloy profile for the upper girder of a civil aircraft wing

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Experimental program
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Effect test

Embodiment 1

[0044] Step 1: Use semi-continuous casting to produce large-scale 7-series ingots with all indicators meeting the technical specifications, and perform homogenization annealing. Chemical analysis of the ingot revealed that the Si content was 0.04%, the Fe content was 0.08%, the Cu content was 2.24%, the Mg content was 2.0%, the Mn content was 0.01%, the Cr content was 0.0072%, the Zn content was 8.05%, and the Ti content was 0.045%. , Zr content 0.103%;

[0045] Step 2: Heat and heat-preserve the mold with a box-type mold heating furnace to ensure that the core of the mold is warm and the mold temperature is heated to 390°C;

[0046] Step 3: The set temperature of the extrusion barrel is 400°C, and the extrusion can only be carried out after the temperature reaches. ℃ / m; Put the heated ingot into the extrusion cylinder, put the ingot head side into the left and right double-hole molds, and perform reverse extrusion. The extrusion axis speed of reverse extrusion is 0.5mm / s , ...

Embodiment 2

[0050] Step 1: Use semi-continuous casting to produce large-scale 7-series ingots with all indicators meeting the technical specifications, and perform homogenization annealing. Chemical analysis of the ingot shows that the Si content is 0.05%, the Fe content is 0.09%, the Cu content is 2.38%, the Mg content is 2.1%, the Mn content is 0.01%, the Cr content is 0.0092%, the Zn content is 8.14%, and the Ti content is 0.032%. , Zr content 0.113%;

[0051] Step 2: Heat and heat-preserve the mold with a box-type mold heating furnace to ensure that the core of the mold is warm and the mold temperature is heated to 410°C;

[0052] Step 3: The temperature of the extrusion barrel is set at 420°C, and the extrusion can only be carried out after the temperature reaches the temperature. ℃ / m, put the heated ingot into the extrusion cylinder, put the ingot head side into the left and right double-hole molds, and perform reverse extrusion. The extrusion axis speed of reverse extrusion is 0.1...

Embodiment 3

[0056] Step 1: Use semi-continuous casting to produce large-scale 7-series ingots with all indicators meeting the technical specifications, and perform homogenization annealing. Chemical analysis of the ingot shows that the Si content is 0.05%, the Fe content is 0.09%, the Cu content is 2.38%, the Mg content is 2.1%, the Mn content is 0.01%, the Cr content is 0.0092%, the Zn content is 8.14%, and the Ti content is 0.032%. , Zr content 0.113%;

[0057] Step 2: Heat and heat-preserve the mold with a box-type mold heating furnace to ensure that the core of the mold is warm and the mold temperature is heated to 410°C;

[0058]Step 3: Set the temperature of the extrusion barrel to 420°C, set the temperature at the head end of the ingot to 430°C, and the temperature of the ingot from the head end to the tail end shows a gradient downward trend, and the temperature gradient is 20°C / m. The ingot is loaded into the extrusion cylinder, and the head end of the ingot is loaded into the l...

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Abstract

A 7-series aluminum alloy profile for the upper girder of a civil aircraft wing and a manufacturing method thereof, belonging to the field of manufacturing aluminum alloy profiles for civil aircraft, the mass percentages of each substance in the alloy profile are: Cu content 2.1%-2.4%, Mg content 2.0%-2.2%, Zn content 7.8%-8.2%, Ti content 0.02%-0.06%, Zr content 0.08%-0.12%, Fe content less than 0.10%, Mn content less than 0.05%, Cr content less than 0.02% , the content of other impurities is less than 0.15%, and the balance is Al. The present invention improves the lateral performance of the profile, reduces the residual stress of the profile, and produces a product that meets the requirements of the domestic civil aircraft wing by adopting technical means such as die hole layout optimization, isothermal reverse extrusion of ingot step heating, and low-stress step quenching. Truss uses the required profiles.

Description

technical field [0001] The invention belongs to the field of manufacturing aluminum alloy profiles for civil aircraft, and in particular relates to a method for manufacturing 7-series aluminum alloy profiles for girders on wings of civil aircraft. Background technique [0002] The level of the aviation manufacturing industry is an important symbol of national strength. Since my country launched the first large-scale civil aircraft development project in 1970, my country's aviation manufacturing industry has made significant progress. Especially in the past ten years, with the development of my country's economy and civil aviation industry With the rapid development, the air transport industry has shown huge market demand. The development of commercial aircraft with independent intellectual property rights has been put on the agenda as one of the national goals. The development projects of ARJ21 new regional aircraft and large passenger aircraft C919 have been launched successi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C22C21/10C22C1/03C22C1/06C22F1/053B22D11/18B22D11/115C21D1/42C21D1/667B21C23/21B21C31/00B21C29/02B21C29/04B21D3/00
CPCC22C21/10C22C1/026C22C1/03C22C1/06C22F1/053C22F1/002B22D11/18B22D11/115C21D1/42C21D1/667B21C23/21B21C31/00B21C29/02B21C29/04B21D3/00Y02P10/25
Inventor 吕正风孙有政赵国群李红萍曹善鹏赵佳蕾隋来智马军星
Owner SHANDONG NANSHAN ALUMINUM
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