A precipitation-hardenable nickel-chromiumcobalt 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.

STANDARD PRODUCT FORMS

Round and extruded section.

MAJOR SPECIFICATIONS

BS HR4, Werkstoff Nr. 2.4636, AECMA Pr EN 2196, 2197

LIMITING CHEMICAL COMPOSITION, %

Ni .......Remainder
Cr ......14.0 – 16.0
Co .....13.0 – 15.5
Mo .........3.0 – 5.0
Ti ...........3.5 – 4.5
Al ...........4.5 – 5.5
C .........0.12 – 0.2
Si ...........1.0 max.
Cu..........0.2 max.
Fe ..........1.0 max.
Mn .........1.0 max.
S .......0.015 max.
B ....0.01 – 0.025
Zr .........0.15 max.

PHYSICAL CONSTANTS AND THERMAL PROPERTIES

Density, Ib/in³ ........................................................................0.284
g/cm³ ..........................................................................7.85
Melting Range, °F ...................................................2300 – 2400
°C ...................................................1260 – 1315
Specific Heat, Btu/lb • °F ....................................................0.106
J/kg • °C ...........................................................444
Coefficient of Expansion, 68 – 212°F, 10^-6 in/in • °F........6.7
20 – 100°C, µm/m • °C .........12.0
Thermal Conductivity, Btu • in/ft² • h • °F ..........................73.5
W/m • °C..........................................10.6
Electrical Resistivity, ohm • circ mil/ft ...............................836
µ Ω• m ................................................1.39

TYPICAL MECHANICAL PROPERTIES

NIMONIC 263

NIMONIC 105