Alloy 75 is an 80/20 nickel – chromium alloy. First introduced in the 1940’s for turbine blades in Whittle Jet Engines, it is now widely used where oxidation and scaling resistance is required, coupled with medium strength at high temperatures.
| % | Ni | Cr | Fe | Mn | C | Si | Ph | Ti | Cu |
|---|---|---|---|---|---|---|---|---|---|
| Min | Balance | 18 | 0 | 0 | 0.08 | 0 | 0 | 0.2 | 0 |
| Max | Balance | 21 | 5 | 1 | 0.15 | 1 | 0.03 | 0.6 | 0.50 |
Alloy 75 is made up of nickel and chromium. The alloy is known for its outstanding performance at high temperature where creep stress-rupture properties are not critical. Titanium is added to increase the overall strength of the alloy. Alloy 75 is primarily used in low stress, elevated temperature applications which require some oxidation resistance.
Alloy 75 is used for numerous fabricated components in both the aerospace and gas turbine industries. Alloy 75 is popular due to its ease of fabrication and the fact that it’s readily formed.
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| Mechanical & Physical Properties | 21.1°C | 100°C | 204.4°C | 315.6°C | 400 °C | 537.8°C | 648.9°C | 700°C | 760 °C | 815 °C | 870 °C | 982 °C |
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Ultimate Tensile Strength /MPa | 792 | - | - | - | - | 726 | 473 | - | 286 | - | 139 | 66 |
| 0.2% Yield Strength /MPa | 407 | - | - | - | - | 363 | 275 | - | 152 | - | 68 | 31 |
| Elongation % | 31 | - | - | - | - | 27 | 32 | - | 75 | - | 90 | 91 |
| 1,000 hr Rupture Strength | - | - | - | - | - | - | 83 | 47 | 26 | 15 | 8.3 | - |
| Coefficient of Thermal Expansion /µm/m°C ** | - | 11 | 12.7 | 13.4 | 13.9 | 14.3 | 15 | 15.4 | - | 16.5 | 17.1 | 18.2 |
| Thermal Conductivity /kcal/(hr.m.°C) ** | 10.06 | - | - | - | - | - | - | - | - | - | - | - |
| Modulus of Elasticity / GPa | 221 | 216 | 210 | 203 | 197 | 190 | 181 | 173 | - | 165 | 153 | 140 |
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