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