24 July 2021 7000 Series Aluminum Alloy
7150 Aluminum Alloy Plate
Aluminium 7150 alloy is a heat treatable wrought alloy. It is used in the aerospace industry for manufacturing aircraft components. Heat treatment can improve its anti-corrosion properties with a low corresponding decrease in strength. Aluminum alloy 7150-T77 provides an unsurpassed combination of high strength and corrosion resistance compared to other 7000 series aerospace alloys of similar strength. 7150 T77 alloys have obtained the best combination of strength and corrosion properties.
Chemical composition:
| Chemical Element | Weight(%) |
|---|---|
| Aluminum, Al | 85.9 - 89.5 |
| Zinc, Zn | 7.2 - 8.2 |
| Magnesium, Mg | 2 - 2.9 |
| Copper, Cu | 1.2 - 1.9 |
| Silicon, Si | ≤ 0.15 |
| Titanium, Ti | ≤ 0.10 |
| Iron, Fe | ≤ 0.20 |
| Chromium, Cr | 0.10 - 0.22 |
| Manganese, Mn | ≤ 0.20 |
| Other (each) | ≤ 0.050 |
| Other (total) | ≤ 0.15 |
Mechanical Properties:
| Mechanical Properties | Metric | English | Comments |
|---|---|---|---|
| Tensile Strength, Ultimate | 593 MPa @Thickness 25.4 mm | 86000 psi @Thickness 1.00 in | LT Direction |
| 648 MPa @Thickness 25.4 mm | 94000 psi @Thickness 1.00 in | Longitudinal Direction | |
| Tensile Strength, Yield | 565 MPa @Thickness 25.4 mm | 82000 psi @Thickness 1.00 in | LT Direction |
| 614 MPa @Thickness 25.4 mm | 89000 psi @Thickness 1.00 in | Longitudinal Direction | |
| Elongation at Break | 9.0 % @Thickness 25.4 mm | 9.0 % @Thickness 1.00 in | LT Direction |
| 12 % @Thickness 25.4 mm | 12 % @Thickness 1.00 in | Longitudinal Direction | |
| Compressive Yield Strength | 634 MPa @Thickness 25.4 mm | 92000 psi @Thickness 1.00 in | Longitudinal Direction |
| Fracture Toughness | 24.2 MPa-m½ @Thickness 25.4 mm | 22.0 ksi-in½ @Thickness 1.00 in | KIC, T-L |
| 29.7 MPa-m½ @Thickness 25.4 mm | 27.0 ksi-in½ @Thickness 1.00 in | KIC, L-T |
Temper Statues:
- T6151 - Solution heat-treated, stress-relieved by controlled stretching (permanent set 0.5% to 3% for sheet, 1.5% to 3% for plate) and then artificially aged in underageing conditions to improve formability. The products receive no further straightening after stretching.
- T61511 - Solution heat-treated, stress-relieved by controlled stretching (permanent set 0.5% to 3% for sheet, 1.5% to 3% for plate) and then artificially aged in underageing conditions to improve formability. The products receive no further straightening after stretching except that minor straightening is allowed after stretching to comply with standard tolerances.
- T7751 - Solution heat-treated, stress-relieved by controlled stretching and then artificially overaged in order to achieve a good exfoliation corrosion resistance. The products recieve no further straightening after stretching.
- T77511 - Solution heat-treated, stress-relieved by controlled stretching and then artificially overaged in order to achieve a good exfoliation corrosion resistance. The products recieve no further straightening after stretching.except that minor straightening is allowed after stretching to comply with standard tolerances.