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Name:Inconel 718
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Brief introduction: Inconel 718
INCONEL® 718 AMS 5662/AMS 5663/AMS 5596
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Inconel 718 is a nickel-chromium-molybdenum alloy designed to resist a wide range of severely corrosive environments, pitting and crevice corrosion. This nickel steel alloy also displays exceptionally high yield, tensile, and creep-rupture properties at high temperatures. This nickel alloy is used from cryogenic temperatures up to long term service at 1200° F. One of the distinguishing features of Inconel 718’s composition is the addition of niobium to permit age hardening which allows annealing and welding without spontaneous hardening during heating and cooling.

INCONEL® 718



The addition of niobium acts with the molybdenum to stiffen the alloy’s matrix and provide high strength without a strengthening heat treatment. Other popular nickel-chromium alloys are age hardened through the addition of aluminum and titanium.

This nickel steel alloy is readily fabricated and may be welded in either the annealed or precipitation (age) hardened condition. This superalloy is used in a variety of industries such as aerospace, chemical processing, marine engineering, pollution-control equipment, and nuclear reactors.


In what applications is Inconel 718 used?

  • Chemical processing
  • Aerospace
  • Liquid fuel rocket motor components
  • Pollution-control equipment
  • Nuclear reactors
  • Cryogenic storage tanks
  • Valves, fasteners, springs, mandrels, tubing hangers
  • Well head completion equipment and blow out preventers (BOP’s)
  • Gas turbine engine parts

Composition

Inconel alloys vary widely in their compositions, but all are predominantly nickel, with chromium as the second element.


Inconel Element, proportion by mass (%)
Ni Cr Fe Mo Nb & Ta Co Mn Cu Al Ti Si C S P B
600 ≥72.0 14.0–17.0 6.0–10.0 N/A ≤1.0 ≤0.5 ≤0.5 ≤0.15 ≤0.015
617 44.2–61.0 20.0–24.0 ≤3.0 8.0–10.0 10.0–15.0 ≤0.5 ≤0.5 0.8–1.5 ≤0.6 ≤0.5 0.05–0.15 ≤0.015 ≤0.015 ≤0.006
625 ≥58.0 20.0–23.0 ≤5.0 8.0–10.0 3.15–4.15 ≤1.0 ≤0.5 ≤0.4 ≤0.4 ≤0.5 ≤0.1 ≤0.015 ≤0.015
690 ≥58 27–31 7–11 ≤0.50 ≤0.50 ≤0.50 ≤0.05 ≤0.015
Nuclear grade 690 ≥58 28–31 7–11 ≤0.10 ≤0.50 ≤0.50 ≤0.50 ≤0.04 ≤0.015
718 50.0–55.0 17.0–21.0 Balance 2.8–3.3 4.75–5.5 ≤1.0 ≤0.35 ≤0.3 0.2–0.8 0.65–1.15 ≤0.35 ≤0.08 ≤0.015 ≤0.015 ≤0.006
X-750 ≥70.0 14.0–17.0 5.0–9.0 0.7–1.2 ≤1.0 ≤1.0 ≤0.5 0.4–1.0 2.25–2.75 ≤0.5 ≤0.08 ≤0.01


Heat Treatment
The following heat treatment should be used to obtain the best combination of tensile properties and stress rupture properties:
1 hr 1750°F to 1800°F (954 to 982°C) air cool + 8hr 1325°F (718°C) cool 100°F /hr to 1150°F (56 °C/hr to 621°C), hold 8 hrs and air cool.
To obtain the best room temperature and cryogenic tensile properties, the following heat treatment should be used:
1 to 2 hr 1950°F (1066°C), air cool + 8 hr 1325°F (718°C) cool 100°F/hr to 1150°F (56°C/hr to 621°C), hold 8 hr and air cool.


Workability
Hot Working
Hot-working is carried out using a 2050°F (1121°C) maximum furnace temperature. Hot-cold working in the range 1700/1850°F (927/1010°C) will improve the strength of the forging if the service temperature is below about 1100°F (593°C). Prolonged soaking at the forging temperature is not desirable. The material should be given uniform reductions to avoid the formation of duplex grain structures.


Machining
The alloy can be readily machined in either the annealed or the age-hardened condition. The age-hardened condition gives better chip action on chip breaker tools and produces a better finish. The annealed condition will give a slightly longer tool life.


Welding
Alloy 718 can be welded in either the annealed or the age condition. Welding in the aged condition will cause the formation of a softened heat-affected zone.


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