Alloy 718 (Inconel 718) Nickel Alloy
Alloy 718
Sourced upon request
- EN2.4668
- ENNiCr19Fe19Nb5Mo3
- UNSN07718
- AMS5662 / 5663
- TicariInconel® 718
Precipitation-hardening nickel-chromium alloy. High strength, creep and fatigue resistance up to 650 °C; the most widely used superalloy in aerospace gas turbines. Sourced to AMS specifications.
01Material Properties
- Rm ≈ 1240–1400 MPa (solution treated + aged)
- Creep resistance up to 650 °C
- Tough also at cryogenic temperatures
- Sluggish ageing response → good weldability
- Good corrosion and oxidation resistance
02Applications
- Gas turbine discs, blades and casings
- Aerospace fasteners
- Rocket engine parts
- Oil and gas downhole equipment
- Cryogenic tanks and valves
03Delivery Condition
- Solution treated or solution treated + aged (AMS 5662 / 5663); bar, plate, forgings.
04Heat Treatment
Typical values
- Solution treatment
- 955–980 °C, 1 h; air/water
- Ageing (double)
- 720 °C 8 h → furnace cool to 620 °C → 620 °C 8 h; air
- After ageing
- ≈ 40–45 HRC; Rm ≥ 1240 MPa
- Solution-treated hardness
- ≈ 20–25 HRC
- Post-weld
- Repeat solution treatment + ageing
Heat treatment cycle (schematic)
Ageing diagram (approximate)
Values are approximate and for information only; they vary with section size, heat and furnace conditions. Binding values are determined from the manufacturer’s data under laboratory conditions.
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