Alloy R41
Alloy 41 is a Ni-base, precipitation hardening alloy with exceptionally high strength at room temperature and in the temperature range of 1200 - 1800ºF. Mechanical properties can be tailored to specific applications by using various combinations of solution treating and aging treatments. It is produced by double vacuum melting (vacuum induction melting plus vacuum arc remelting).
Major applications are hot components for jet engines and rocket engines, such as turbine blades, turbine wheels, torque rings, combustion chamber liners, afterburner parts, structural hardware, and various airframe and missile components.
National Specification
| ASTM | UNS | SEA AMS | British Standard | Werkstoff |
|---|---|---|---|---|
| N07041 | 5712 | 2.4973 |
Material may also be released to Customer Specifications, subject to enquiry.
Technical Data
Nominal Composition by Percent
| C | Cr | Co | Ti | Ni | Mo | Al | Fe | B | - | |
|---|---|---|---|---|---|---|---|---|---|---|
| Min | - | 18.0 | 10.0 | 3.0 | Bal | 9.0 | 1.4 | - | .003 | % |
| Max | 0.12 | 20.0 | 12.0 | 3.3 | 10.5 | 1.6 | 5.0 | .010 | % |
Typical Mechanical Properties
| Annealed and Aged Condition | PSI | MPa | % |
|---|---|---|---|
| Tensile Strength, min | 206,000 | 1420 | |
| Yield Strength (0.2% offset), min |
154,000 | 1065 | |
| Elongation on 4D, min | 14 | ||
| Reduction of Area | |||
| Hardness | 40 RC |