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)