Bar and Rod
Plate and Sheet
Strip
Pipe and Tube
Wire
Welding
Powder Material
Cast Products
Forged Products
Fittings
Fastening
Round Bar:
φ2–500 mm, 1–6 m length
Flat/Square Bar:
4–100 mm thickness/width
Hex Bar:
A/F 3–100 mm
Hollow Bar:
OD 20–300 mm
Sheet:
0.3–6 mm thickness
Medium Plate:
6–25 mm thickness
Heavy Plate:
25–100 mm thickness
Standard Strip:
0.05–3 mm thick,
10–600 mm wide
Precision strip:
0.01–0.5 mm thick,
tight tolerance ±0.005 mm
Foil:
0.005–0.1 mm thick
Seamless Tube:
OD 6–450 mm,
WT 1–50 mm,
1–12 m length
Welded Tube:
OD 10–600 mm,
WT 1–20 mm
Capillary Tube:
OD 1–10 mm,
WT 0.1–2 mm
Wire Form:
Cold Drawn Wire,
Bright Wire,
Spring Wire,
Fine Wire,
Ultra-fine Wire
General Diameter:
φ0.1–10 mm
Coil Weight:
50–500 kg,
customizable tolerance
Solid Wire:
φ0.8–4.0 mm
Flux-cored Wire:
φ1.2–4.0 mm
Welding Rod:
φ2.0–5.0 mm
Powder Form:
AM 3D Printing Powder,
Spherical Powder,
Gas-atomized Powder,
Water-atomized Powder
Particle Size:
10–150 μm
Sphericity:
≥90% for AM grade
Cast Ingot:
φ200–800 mm
Precision Casting:
min wall 0.5 mm
Cast Pipe:
OD 100–600 mm,
WT 10–50 mm
Forged Bar:
Φ35–500 mm
Forged Ring:
OD 200–2000 mm
Forging Weight:
1–5000 kg
Fittings Form:
Elbow, Tee, Reducer, Flange, Cap, Outlet, Lap Joint
Size range:
1/2''–24'' (DN15–DN600)
Wall thickness:
Sch10–Sch160, STD, XS, XXS
Pressure Class:
150–2500 LB
Fastening Form:
Bolt, Nut, Screw, Stud, Washer, Pin, Rivet
Metric: M3–M64
Imperial: #4–2.5''
Length: 6–500 mm
Incoloy 901 is a precipitation-hardenable nickel-iron-chromium superalloy. This datasheet presents the material within the American (ASTM / ASME / UNS) standard system.
A nickel-iron-chromium alloy containing titanium and aluminium for precipitation hardening and molybdenum for solid-solution strengthening, Incoloy 901 develops its strength from γ′ (Ni₃(Ti,Al)) precipitates formed during ageing, distributed uniformly within an austenitic matrix. It offers high yield strength and excellent creep and stress-rupture resistance at temperatures to about 600 °C (1110 °F), with good corrosion resistance in the atmospheres typical of jet-engine operation. Its substantial iron content (the balance element) lowers raw-material cost relative to fully nickel-based grades and gives good forging characteristics. It is used in the solution-treated, stabilised and aged condition.
Typical applications include gas-turbine engine discs, shafts, rings, casings and seals, and other highly stressed components operating to about 600 °C.
| Property | Value | Unit |
|---|---|---|
| Density | 8.21 | g/cm³ |
| Melting range | 1280–1345 | °C |
| Elastic modulus | 206 | GPa |
| Coefficient of thermal expansion (20–100 °C) | 13.5 | µm/m·°C |
| Thermal conductivity (20 °C) | 12.0 | W/m·K |
| Specific heat (20 °C) | 440 | J/kg·K |
| Structure | Austenitic (FCC) | — |
| Element | Symbol | Min % | Max % | Role in Alloy |
|---|---|---|---|---|
| Nickel | Ni | 40.0 | 45.0 | Austenite former; γ′ matrix |
| Iron | Fe | Balance | — | Base element; forgeability, cost |
| Chromium | Cr | 11.0 | 14.0 | Oxidation / corrosion resistance |
| Molybdenum | Mo | 5.0 | 6.5 | Solid-solution strengthening |
| Titanium | Ti | 2.35 | 3.10 | γ′ (Ni₃Ti) precipitation strengthening |
| Aluminium | Al | — | 0.50 | γ′ formation |
| Cobalt | Co | — | 1.00 | Residual |
| Carbon | C | — | 0.10 | Carbide formation |
| Boron | B | — | 0.02 | Grain-boundary strengthening |
Solution-treated, stabilised and aged condition, typical values for UNS N09901.
| Condition | Property | Value |
|---|---|---|
| Solution treated & aged | Tensile strength (UTS) | ≥1035 MPa (150 ksi) |
| Solution treated & aged | 0.2% yield strength | ≥760 MPa (110 ksi) |
| Solution treated & aged | Elongation at break | ≥12 % |
| Solution treated & aged | Reduction of area | ≥15 % |
| — | Elastic modulus | 206 GPa |
Confirm against the mill test report. Properties depend on the solution, stabilisation and ageing treatment selected.
| Environment | Performance | Notes |
|---|---|---|
| Jet-engine atmospheres | Good | Suited to gas-turbine service |
| High-temperature oxidation | Good | To about 600 °C service |
| Aqueous / general | Good | Chromium + molybdenum bearing |
| Stress-corrosion cracking | Good | Generally resistant |
| Elevated-temperature strength | Excellent | Primary design advantage |
Corrosion and oxidation resistance is good for its class; the alloy is selected primarily for its high yield strength and creep resistance to about 600 °C combined with good forgeability.
A γ′ precipitation-hardenable superalloy; strengthened by solution treatment, stabilisation and ageing.
Solution Treatment Solution treat at approximately 1080–1107 °C (1975–2025 °F) for about 2 hours and air cool.
Precipitation Hardening (Ageing) Apply a stabilisation treatment at approximately 775–800 °C (1425–1475 °F) for 2–4 hours and air cool, followed by precipitation ageing at approximately 720–745 °C (1325–1375 °F) for about 24 hours and cool — precipitating γ′ (Ni₃(Ti,Al)).
Weldable by inert-gas processes; welding is performed in the solution-annealed condition with post-weld heat treatment and ageing. As a titanium-bearing γ′ alloy, care is taken to avoid strain-age cracking.
| Welding Process | Applicability | Filler / Consumable |
|---|---|---|
| GTAW / TIG | Good | Matching alloy 901 filler |
| GMAW / MIG | Good | Matching filler |
| EBW / laser | Good | Autogenous or matching filler |
Weld in the solution-annealed condition; apply post-weld solution and ageing to develop properties.
Machining Guidelines
| Parameter | Recommendation |
|---|---|
| Preferred condition | Solution-annealed for machining, then age |
| Machinability | Difficult; rigid setups, carbide tooling, slow speeds |
| Coolant | Ample coolant |
Forming Processes
| Process | Notes |
|---|---|
| Cold forming | In the annealed condition; work-hardens |
| Hot forming | Readily forged — a key advantage; solution and age afterward |
| Industry | Typical Components | Key Requirements |
|---|---|---|
| Aero gas turbine | Discs, shafts, rings, casings, seals | Yield strength + creep to ~600 °C |
| Land-based turbine | Rotor discs and forgings | Strength + forgeability |
| Power generation | Highly stressed rotating parts | Creep + stress-rupture resistance |
| Aerospace | Highly stressed forgings | Strength + toughness |
| Product Form | Standard / Designation | AMS |
|---|---|---|
| Bar, rod and forging stock | UNS N09901 · BS HR53 | AMS 5660 / 5661 |
| Flat bar and round | UNS N09901 | — |
| Wire and welding wire | UNS N09901 | — |
| Material designation | UNS N09901 | BS HR55 |
Nickel-iron-chromium precipitation-hardenable superalloy. UNS N09901.
| Alloy | Ni % | Mo % | Strengthening | Best Used For |
|---|---|---|---|---|
| Incoloy 901 | 40–45 | 5–6.5 | γ′ (Ti, Al) + Mo | Forgeable Ni-Fe-Cr disc alloy; gas-turbine discs/shafts to ~600 °C |
| Inconel 718 | 50–55 | 2.8–3.3 | γ′ + γ″ (Nb, Ti) | Most-used high-strength superalloy to ~700 °C |
| Inconel 706 | 39–44 | — | γ′ + γ″ (Nb, Ti) | 718-type strength, better fabricability; large discs |
| A-286 | 24–27 | 1.0–1.5 | γ′ (Ti) | Lower-cost Fe-base age-hardenable alloy |
| Waspaloy | Balance | 3.5–5 | γ′ (Al, Ti) | Higher-temperature turbine discs to ~700 °C |
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