Nimonic 105 Nickel Based Superalloy


Nimonic alloy 90 is a wrought nickel-chromium-cobalt base alloy strengthened by additions of titanium and aluminium. It has been developed as an age-hardenable creep resisting alloy for service at temperatures up to 920°C (1688°F). The alloy is used for turbine blades, discs, forgings, ring sections and hot-working tools.


NIMONIC® alloy 105 (W. Nr. 2.4634) is a wrought nickel-cobalt-chromium-base alloy strengthened by additions of molybdenum, aluminum and titanium. It has been developed for service up to 950°C, and combines the high strength of the age-hardening nickel-base alloys with good creep resistance.


NIMONIC alloy 105 is produced by high frequency melting in air followed by casting in air, or, for more critical applications the alloy is produced by vacuum melting and electroslag refining. The alloy is used for turbine blades, discs, forgings, ring sections, bolts and fasteners.



A precipitation-hardenable nickel-chromium-cobalt alloy with an addition of molybdenum for solid-solution strengthening. It is similar to NIMONIC alloy 105 but has higher levels of aluminum and titanium for increased strengthening by precipitation hardening. The alloy has high strength and creep resistance at temperatures to about 1850°F (1010°C). Used for turbine blades in aircraft gas turbines.


Physical Properties:


Melting Point (°C)DensityModulus of Elasticity
in Tension
1290 – 1345  8.01g/cm3188 GPa


Mechanical Properties:


Tensile Strength
Yield Strength
Minimum 0.2% offset
% Elongation
in 2" Minimum


Chemical Composition:






Welding techniques recommended for Nimonic 105 include gas-tungsten arc welding, gas metal-arc welding, submerged-arc welding and shielded metal-arc welding. Usage of a matching alloy filler metal is recommended for the welding process and if a matching filler is absent, an alloy rich in Ni, Co, Cr, Mo is can be used. During the absence of a matching filler metal.


Heat Treatment:


Nimonic 105 can be heat treated in 4 four steps. The steps are as follows: Solution annealing for 4 h at 1149°C (2100°F) followed by air cooling. Heating for 16 h at 1056°C (1925°F) followed by air cooling. Heating for 16 h at 849°C (1560°F). Air cooling to reach precipitation-hardening.





Mechanical & Physical Properties21.1°C93.3°C148.9°C204.4°C315.6°C371.1°C426.7°C537.8°C648.9°C750°C815°C870°C982°C1093°C1204°C
Ultimate Tensile Strength /MPa114011231123108410911101110110641038---175--
0.2% Yield Strength /MPa776762762735735743743740720---152--
Reduction of area %313131383039393738---73--
Elongation %222020212024242325---42--
Minimum Creep 0.0001% per hr--------4282329354---
10,000 hr Rupture Strength--------4712631356512--
Coefficient of Thermal Expansion /µm/m°C12.
Thermal Conductivity /kcal/(hr.m.°C)9.36310.4110.4111.6712.8914.0414.0415.216.02---22.54--
Modulus of Elasticity / GPa188184184179174168168161154---110--

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