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Materials

Nickel-based alloy Inconel 718

Range of application

Nickel-based alloy for the production of components for high-temperature applications. Typical applications are turbine construction (aviation or stationary turbines) or exhaust tracts within motor sports applications.

Technical data after recommended heat treatment

1 Tensile test at 20°C to DIN EN 50125.
2 By using a special heat treatment a higher elongation can be achieved.
3 Preliminary values subject to change or update.
Yield Point Rp0,21 1000 - 1100 N/mm2
Tensile Strength Rm1 1250 - 1350 N/mm2
Elongation A1 8 - 12 %
Young's modulus 1 approx. 200.000 N/mm2
Thermal conductivity λ2 approx. 12 Wm/k
Coefficient of thermal expansion approx. 13 · 10-6 K-1

Heat treatment

Perform heat treatment under an argon atmosphere in two steps. At first solution annealing (980 °C for one hour), after-wards allow the components to cool in the oven. In the second step aging (720 °C for 8 hours). After this procedure allow the component to cool down to 620 °C within two hours. Afterwards maintain this temperature for further 8 hours.

Chemical Composition

COMPONENT   INDICATIVE VALUE (%)

Ni      50,0 – 55,0
Cr      17,0 – 21,0
Nb     4,75 – 5,50
Mo    2,80 – 3,30
Ti      0,65 – 1,15
Al      0,20 – 0,80
Co     0,0 – 1,0
C       0,0 – 0,08
Mn   0,00 – 0,35
Si      0,00 – 0,35
P       0,000 – 0,015
S       0,000 – 0,015
B      0,000 – 0,006
Cu    0 – 0,3