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7050 7150 Aluminum forgings forged product parts

7050 is a high strength Al-Zn-Mg-Cu alloy, which can be strengthened by heat treatment. On the basis of 7075 superhard aluminium alloy, the chemical composition of the alloy was adjusted, the content of zinc and copper was increased, the grain was refined by zirconium instead of chromium, and the content of impurities such as silicon and iron was reduced. Due to the optimization of chemical composition and the over-aging treatment, the aluminium alloy has high fatigue limit, good toughness, good stress corrosion resistance and good hardenability while maintaining high strength. Its hot working performance is similar to 7075 alloy. It has general weldability and good cutting property.
 
7050 is mainly used for high strength, good fracture toughness, and high stress corrosion cracking resistance and spalling corrosion of the main bearing structural parts, such as aircraft structure with thick plates, extrusions, free forgings and die forgings, such as aircraft structure with thick plates, extrusions, free forgings and die forgings, including fuselage frames, partitions, wing beams, landing gear support parts and rivets. Because the alloy has good hardenability, it is especially suitable for manufacturing large thick section parts. The supply state of the aluminum alloy includes T74, T76 and T73. T74 should be selected for structural parts requiring high strength and stress corrosion cracking resistance; T76 should be generally used for structural parts requiring high strength and anti-spalling corrosion; and T73 is mainly used for rivet materials requiring high strength and good corrosion resistance.

 


The Brinell hardness of 7050 aluminium alloy forging in T74 state is 158HBW.
7150 T77 aluminium forging forged product parts are an improved 7050 Alloy with high strength and good corrosion resistance. The fatigue resistance of 7150 T651 is 10%-15% higher than that of 7075, and the fracture toughness is 10% higher. The SCC resistance of 7150 T651 is similar to that of 7075. Mainly used in large passenger aircraft upper wing structure, body plate girder flange, upper outer panel main wing longitudinal beam, fuselage reinforcement, keel beam, seat guide rail.
 
Reduce heat treatment stress and avoid quenching deformation.
After solution treatment, the free forgings should be pre-compressed before artificial aging, and the permanent deformation is 1.5%-5.0%, so as to eliminate the internal stress.
The formability of the alloy is similar to that of 7075 aluminium alloy. If the initial forging temperature is too high, hot forging is easy to occur, which is disadvantageous to the hammer forging process.
 

                        Tensile Properties of 7050 Aluminum Alloy T73652 Free Forging at Room Temperature
 
Thickness/mm      Direction Tension strength Rm/MPa Prescribed plastic elongation strength Rp0.2/MPa Provision of non-proportional compressive strength
Rpc0.2/MPa
Elongation A
(%)
≤50 Portrait 496 434 441 9
Long transverse 490 421 448 5
>50--75 Portrait 496 427 434 9
Long transverse 483 414 441 5
Short transverse 462 379 421 4
>50--110 Portrait 483 421 427 9
Long transverse 476 407 434 5
Short transverse 455 379 421 4

 
 
 
  
7050 7150 Chemical Composition
Alloy Si Fe Cu Mn Mg Cr Ni Zn Ti Zr Others Al
Single Total
7050 0.12 0.15 2.0~2.6 0.10 1.9~2.6 0.04 ~ 5.7~6.7 0.06 0.08~0.15 0.05 0.15 Rest
7150 0.12 0.15 1.9~2.5 0.10 2.0~2.7 0.04 ~ 5.9~6.9 0.06 0.08~0.15 0.05 0.15 Rest
 
 
 
 
 
 
Room Temperature Tensile Properties of Aluminum Alloy T736 State Die Forging
Thickness/mm      Direction Tension strength Rm/MPa Prescribed plastic elongation strength Rp0.2/MPa Provision of non-proportional compressive strength
Rpc0.2/MPa
Elongation A
(%)
≤50 portrait 496 427 434 7
transverse 469 386 400 5
>50--100 portrait 490 421 434 7
transverse 462 379 393 4
>100--125 portrait 483 414 434 7
transverse 455 372 379 3
 
Tensile Properties of 7050 Aluminum Alloy T736 State Die Forging at Room Temperature
Thickness/mm      Direction Tension strength Rm/MPa Prescribed plastic elongation strength Rp0.2/MPa Provision of non-proportional compressive strength
Rpc0.2/MPa
Elongation A
(%)
≤50 portrait 496 427 434 7
transverse 469 386 400 5
>50--100 portrait 490 421 434 7
transverse 462 379 393 4
>100--125 portrait 483 414 434 7
transverse 455 372 379 3
 

 

 
 
Low Temperature Tensile Properties of 7050 Aluminum Alloy Forgings
Alloy Temper Temperature Tension Strength Rm/MPa Prescribed plastic elongation strength  Rp0.2/MPa Elongation A
(%)
7050  T73652 -195 662 572 13
-80 586 503 14
-28 552 476 15
 
 
Tensile Properties of 7050 Aluminum Alloy Forgings at High Temperature
Alloy Temper Temperature/℃ holding time/h Tension Strength Rm/MPa Prescribed plastic elongation strength Rp0.2/MPa Elongation A
(%)
7050  T73652 24 - 524 455 15
100 0.1--10 462 427 16
100 469 434 16
1000 462 427 17
150 0.1 414 386 17
10 407 386 18
100 365 352 20
1000 290 276 23
175 0.1 379 345 19
10 324 310 22
100 248 234 25
1000 193 172 31
205 0.1 324 290 22
10 221 207 27
100 165 152 32
1000 131 110 45
 

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