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
2.4632 is a wrought, age-hardenable nickel–chromium–cobalt alloy strengthened by additions of titanium and aluminium, developed as a creep-resisting material for service at temperatures up to 920 °C (1688 °F). This datasheet presents the material within the European (DIN / EN / Werkstoff-Nummer / BS) standard system.
It builds on the composition with a substantial cobalt addition (~16–21%), which raises the high-temperature strength and extends the useful service temperature. Titanium and aluminium form a gamma-prime [Ni₃(Al,Ti)] phase during aging that provides high tensile strength and excellent creep-rupture strength, while the 18–21% chromium content gives good oxidation resistance and corrosion resistance in the 815–870 °C range. The alloy also offers high fatigue strength and good formability and weldability under repeated heating and cooling.
It is used for gas-turbine components (turbine blades, discs, forgings and ring sections, combustor liners), aircraft-engine components, exhaust and afterburner parts, hot-working tools, and high-temperature springs. Strength is developed by a solution treatment followed by aging; welding is carried out before the final age-hardening treatment.
Values per official datasheet, solution-treated and aged condition.
| Property | Value | Unit |
|---|---|---|
| Density | 8.19 | g/cm³ |
| Melting range | 1310–1370 | °C |
| Young's modulus (20 °C) | 228 | GPa |
| Specific heat capacity (20 °C) | 444 | J/kg·K |
| Thermal conductivity (20 °C) | 11.47 | W/m·K |
| Electrical resistivity (20 °C) | 1.19 | µΩ·m |
| Coefficient of thermal expansion (20–100 °C) | 12.7 | µm/m·°C |
| Maximum creep-resistance temperature | ~920 | °C |
Composition per DIN 17742 (W.Nr. 2.4632, NiCr20Co18Ti).
| Element | Symbol | Min % | Max % | Role in Alloy |
|---|---|---|---|---|
| Nickel | Ni | Balance | — | Base; FCC matrix |
| Chromium | Cr | 18.0 | 21.0 | Oxidation / corrosion resistance |
| Cobalt | Co | 15.0 | 21.0 | Solid-solution + γ′ strengthening |
| Titanium | Ti | 1.8 | 3.0 | γ′ precipitation strengthening |
| Aluminium | Al | 1.0 | 2.0 | γ′ precipitation strengthening |
| Iron | Fe | — | 1.5 | Residual |
| Manganese | Mn | — | 1.0 | Deoxidiser |
| Silicon | Si | — | 1.0 | Deoxidiser |
| Copper | Cu | — | 0.2 | Residual |
| Carbon | C | — | 0.13 | Carbide strengthening |
| Boron | B | — | 0.02 | Grain-boundary strengthening |
| Zirconium | Zr | — | 0.15 | Grain-boundary strengthening |
| Phosphorus | P | — | 0.02 | Residual impurity |
| Sulphur | S | — | 0.015 | Residual impurity |
Nominal: Ni-20Cr-18Co-2.4Ti-1.4Al. An age-hardenable Ni-Cr-Co alloy with higher γ′ content than 80A, developed for creep-resistant service to ~920 °C — turbine blades, discs, forgings and rings.
Solution-treated and aged condition, per DIN 17742 for W.Nr. 2.4632.
| Property | Value | Unit |
|---|---|---|
| Tensile strength (Rm) | ≥1100 | MPa |
| 0.2% proof strength (Rp0.2) | ≥700 | MPa |
| Elongation at fracture (A) | ≥15 | % |
| Brinell hardness | ~300–380 | HB |
Values per EN/DIN; confirm against the inspection certificate (EN 10204).
| Environment | Performance | Notes |
|---|---|---|
| Creep / stress-rupture (to 920 °C) | Outstanding | Co + γ′ strengthening; primary selling point |
| High-temperature oxidation | Good | Protective Cr₂O₃ scale |
| Corrosion (815–870 °C) | Good | Good resistance in this range |
| High-cycle fatigue | Excellent | High fatigue strength |
| Thermal cycling | Good | Good formability/weldability under repeated heating/cooling |
| Chloride stress-corrosion cracking | Good | High nickel content |
| Pitting / crevice (chlorides) | Good | Can be compromised in highly oxidising/reducing conditions |
A precipitation-hardening alloy. Strength is developed by solution treatment followed by aging.
Solution Treatment Temperature: ~1080 °C (1975 °F), ~8 h, air cool
Aging Temperature: ~700 °C (1290 °F), ~16 h, air cool Purpose: precipitates γ′ [Ni₃(Al,Ti)] for high tensile and creep-rupture strength.
Sheet practice: 2–3 min/1150 °C/fluidised-bath quench + 20 min/1040 °C/AC (softening) + 4 h/750 °C/AC. Welding is carried out before final aging; minimise restraint to avoid strain-age cracking.
Good formability and weldability. As a γ′-strengthening alloy it can be susceptible to strain-age cracking, so welding is carried out in the solution-treated condition with age-hardening applied afterwards.
| Welding Process | Applicability | Filler / Consumable |
|---|---|---|
| GTAW / TIG · GMAW / MIG | Satisfactory (≤5 mm; solution-treated) | EN ISO matching Ni-Cr-Co filler (solution-treated base) |
| Resistance welding | Readily joined | — |
| EB / friction / flash-butt | For thicker sections | — |
Post-weld solution treatment + aging is recommended to restore full strength. Hot working range: 1050–1200 °C.
Machining Guidelines
| Parameter | Recommendation |
|---|---|
| Preferred condition | Solution-treated (machine before final aging where possible) |
| Work hardening | High rate; rigid setup, positive rake, sharp tooling |
| Cutting | Low-to-moderate speed, ample feed, generous coolant |
Forming Processes
| Process | Notes |
|---|---|
| Hot working | 1050–1200 °C |
| Cold forming | In solution-treated condition; high work-hardening rate; good formability |
| Final aging | After forming/machining to develop full strength |
| Industry | Typical Components | Key Requirements |
|---|---|---|
| Gas turbines | Turbine blades, discs, forgings, ring sections, combustor liners | High creep-rupture strength to 920 °C |
| Aerospace | Aircraft-engine components, exhaust systems, afterburner parts | High strength + fatigue + oxidation resistance |
| High-temperature springs | Springs for automotive, aerospace, chemical processing | Strength + fatigue resistance at temperature |
| Tooling | Hot-working tool components | Hot strength + thermal fatigue |
| Automotive | High-temperature engine hardware | Creep + oxidation resistance |
| Product Form | Standard | Other |
|---|---|---|
| Rod, bar, wire, forging stock | BS HR2 / HR501 / HR502 / HR503 | AECMA PrEN 2295 / 2296 |
| Plate, sheet and strip | BS HR202 | AECMA PrEN 2298 |
| Pipe and tube | BS HR402 | AECMA PrEN 2299 |
| Composition / designation | W.Nr. 2.4632 · NiCr20Co18Ti | AFNOR NCK20TA (AIR 9165) · BS 3075 NA19 |
| Welding consumables | EN ISO matching Ni-Cr-Co filler | — |
W.Nr. 2.4632 (NiCr20Co18Ti); BS HR2 / HR202 / HR402 / HR501–503; MSRR 7137 / 7017.
| W.Nr. | Ni % | Cr % | Other | Best Used For |
|---|---|---|---|---|
| 2.4632 | bal | 18–21 | Co 15–21, Ti+Al | Age-hardened Ni-Cr-Co; creep to 920°C |
| 2.4952 | bal | 18–21 | Ti+Al (no Co) | Age-hardened Ni-Cr; to 815°C |
| 2.4951 | bal | 18–21 | Ti 0.2–0.6 | Solution-strengthened base; oxidation to 1100°C |
| 2.4654 | bal | 18–21 | Co 12–15, Mo | Higher-strength γ′; sustained >700°C |
| 2.4650 | bal | 19–21 | Co ~20, Mo | Sheet-fabricable; combustor hardware |
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