S+D METALS

Alloy 718 | 2.4668 | AMS 5596

UNS N07718 | ASTM B670 | DMD 0424-22 | NACE MR0175

Alloy 718 is a precipitation hardenable nickel-chromium alloy with additions of niobium, molybdenum, aluminium and
titanium for improved corrosion resistance combined with extremely high strength and excellent weldability. Though
originally developed for aerospace applications the unique combination of strength and corrosion resistance of Alloy
718 made it candidate for applications in the oil and gas sector.

Material according to AMS 5596 is supplied in the solution annealed condition for ease of fabrication and machining.
The material must be precipitation heat treated to develop full strength.

Alloy 718 plate is widely used in applications that require high strength, corrosion resistance and heat resistance.

 

Areas of application for ALLOY 718 | 2.4668 | AMS 5596

aircraft structural panels, heat shields, engine mounting brackets and exhaust ducts, heat exchanger plates, pressure vessels and storage tanks, offshore platform components

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Available from stock in the following dimensions

  • 1,00 x 914 mm
  • 1,50 x 914 mm
  • 2,00 x 914 mm

Details at a glance

Chemical composition - limits in % according AMS 5596

Ni
50,00 - 55,00
Cr
17,00 - 21,00
Nb
4,75 - 5,50
Mo
2,80 - 3,30
Co
max. 1,00
Ti
0,65 - 1,15
Al
0,20 - 0,80
Mn
max. 0,35
Si
max. 0,35
Cu
max. 0,30
C
max. 0,08
T
max. 0,05
S
max. 0,015
P
max. 0,015
B
max. 0,006
Fe
Rest

Physical constants and thermal properties

Density
8,19 g/cm³
Melting point
1260 - 1336 °C
Thermal conductivity at 20°C
9,5 W/m · °C
Coefficient of expansion at 21 - 93°C
13,1 μm/m · °C

Typical mechanical properties - room temperature, once precipitation treated according AMS 5596

Yield strength
min. 827 MPa
Tensile strength
min. 1034 MPa
Elongation
min. 20 %

Downloads

Downloads

Datasheets_Alloy 718.pdfDatasheets_Alloy 718.pdf