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UNS N07041
W.Nr 2.4973
Applications
Turbine blades, wheels, combustion chamber liners, after burners, and structural hardware.
Description
Rene 41 is a precipitation-hardenable Nickel-Chromium alloy with high strength and oxidation resistance at elevated temperatures from 1200°F - 1800°F.
Industries Supplied
Aerospace.
Nominal Composition
C: 0.12 max
Mn: 0.10 max
Si: 0.50 max
S: 0.015 max
Cr: 18.0 - 20.0
Co: 10.0 - 12.0
Mo: 9.0 - 10.50
Ti: 3.0 - 3.30
Al: 1.40 - 1.60
B: 0.003 - 0.010
Fe: 5.0 max
Cu: 0.50 max
Ni: Balance
Physical Properties
Density: 0.298 lb/in3, (8.25 g/cm3)
Modulus of Elasticity (E):
At 70°F (20°C): 31.6 x 103 ksi (218 GPa)
Modulus of Rigidity (G)
At 70°F (20°C): 12.1 x 103 ksi (83.4 GPa)
Coefficient of Expansion:
7.5 μin/in.-°F (70°F to 1000°F)
13.5 μm/m-°C (20°C to 538°C)
Electrical Resistivity: 51.5 μΩ.in, (131 μΩ.cm)
Thermal Conductivity: 62 Btu-in/ft2hr-°F, (9.0 W/m-K)
Applicable Specifications
Strip and Foil: AMS 5545, GE B50T59, GE B50TF109
Typical Mechanical Properties
Annealed
Heat Treatment: 1975°F (1079°C)
Tensile Strength: 170 ksi (1172 MPa) max
Suggested Operating Conditions: -300°F to 1500°F (-184°C to 815°C)
Spring Temper
Suggested Operating Conditions: -300°F to 1500°F (-184°C to 815°C)
After Precipitation Heat Treat
Heat Treatment: per AMS 5545
Tensile Strength: 160 ksi (1103 MPa) Min
Suggested Operating Conditions: -300°F to 1500°F (-184°C to 815°C)