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
2.4654 is a nickel-base, age-hardenable superalloy with excellent high-temperature strength and good resistance to oxidation and hot corrosion, used at service temperatures up to about 650 °C (1200 °F) for critical rotating applications and to higher temperatures for static parts. This datasheet presents the material within the European (EN / Werkstoff-Nummer / ISO / AECMA) standard system.
Strength is derived from a combination of solid-solution strengthening (molybdenum, cobalt, chromium) and precipitation of the gamma-prime [Ni₃(Al,Ti)] phase developed during age hardening. The result is excellent strength and stability through temperatures of roughly 980 °C (1800 °F), with good corrosion resistance and resistance to oxidation and to the hot corrosion that results from combustion by-products in gas turbines and jet engines. Its strength and stability exceed those typically available from alloy 718, though it is more expensive and more difficult to hot-work and weld owing to γ′ strengthening.
It is heat-treated in a three-step sequence (solution treatment, stabilisation and aging). Typical applications are critical rotating gas-turbine and jet-engine components — compressor and turbine blades, discs, hubs, shafts, bolts, rings and spacers — requiring high strength to about 816 °C (1500 °F) and oxidation resistance to about 954 °C (1750 °F).
Values per VDM data, solution-treated and aged condition.
| Property | Value | Unit |
|---|---|---|
| Density | 8.19 | g/cm³ |
| Melting range | 1330–1360 | °C |
| Young's modulus (20 °C) | 213 | GPa |
| Specific heat capacity (20 °C) | 423 | J/kg·K |
| Thermal conductivity (20 °C) | 11.0 | W/m·K |
| Electrical resistivity (20 °C) | 1.24 | µΩ·m |
| Coefficient of thermal expansion (20–100 °C) | 12.2 | µm/m·°C |
| Strength retained to | ~980 (1800 °F) | °C |
| Rotating-application service | ~650 (1200 °F) | °C |
Composition per EN 10302 (W.Nr. 2.4654, NiCr20Co13Mo4Ti3Al).
| Element | Symbol | Min % | Max % | Role in Alloy |
|---|---|---|---|---|
| Nickel | Ni | Balance | — | Base; FCC matrix |
| Chromium | Cr | 18.0 | 21.0 | Oxidation / corrosion resistance |
| Cobalt | Co | 12.0 | 15.0 | Solid-solution + γ′ strengthening |
| Molybdenum | Mo | 3.5 | 5.0 | Solid-solution strengthening |
| Titanium | Ti | 2.8 | 3.3 | γ′ precipitation strengthening |
| Aluminium | Al | 1.2 | 1.6 | γ′ precipitation strengthening |
| Iron | Fe | — | 2.0 | Residual |
| Carbon | C | 0.02 | 0.10 | Carbide strengthening |
| Zirconium | Zr | 0.02 | 0.08 | Grain-boundary strengthening |
| Boron | B | 0.003 | 0.01 | Grain-boundary strengthening |
| Manganese | Mn | — | 1.0 | Deoxidiser |
| Silicon | Si | — | 0.15 | Deoxidiser |
| Copper | Cu | — | 0.1 | Residual |
| Phosphorus | P | — | 0.015 | Residual impurity |
| Sulphur | S | — | 0.015 | Residual impurity |
Nominal: Ni-20Cr-13Co-4Mo-3Ti-1.4Al. An age-hardenable Ni-Cr-Co alloy (alloy 263) strengthened by γ′; combines good weldability with high creep strength to ~850 °C — gas-turbine combustion and sheet components.
Precipitation-hardened (+P) condition, per EN 10302 for W.Nr. 2.4654.
| Property | Value | Unit |
|---|---|---|
| Tensile strength (Rm) | ≥1100 | MPa |
| 0.2% proof strength (Rp0.2) | ≥760 | MPa |
| Elongation at fracture (A) | 15–20 | % |
Values per EN/DIN; confirm against the inspection certificate (EN 10204).
| Environment | Performance | Notes |
|---|---|---|
| High-temperature strength (creep/rupture) | Excellent | γ′ strengthening; to ~980 °C |
| Oxidation | Excellent | To ~954 °C (1750 °F) |
| Hot corrosion | Good | Resists gas-turbine combustion by-products |
| General corrosion | Good | High Ni-Cr base |
| Thermal stability | Good | Stable γ′ to high temperature |
| Rotating-component fatigue | Excellent | Key for discs/blades/shafts |
A precipitation-hardening nickel-base superalloy. Strength is developed by a three-step sequence (solution treatment, stabilisation, aging).
A. For optimum high-temperature creep and stress-rupture properties Solution treatment: 1080 °C (1975 °F) / 4 h / air cool (hardness 20–25 HRC) Stabilisation: 845 °C (1550 °F) / 24 h / air cool Age harden: 760 °C (1400 °F) / 16 h / air cool (hardness 34–40 HRC)
B. For optimum room- and high-temperature tensile properties Solution treatment: 995–1035 °C (1825–1895 °F) / 4 h / oil quench Stabilisation: 845 °C (1550 °F) / 4 h / air cool Age harden: 760 °C / 16 h / air cool
Welding should be carried out before final aging owing to γ′ strain-age cracking susceptibility.
As a γ′-strengthened superalloy, Waspaloy is more difficult to weld than alloy 718 and is susceptible to strain-age cracking; it should be welded in the solution-treated (non-aged) condition, with aging applied afterwards. GTAW with matching filler is typical.
| Welding Process | Applicability | Filler / Consumable |
|---|---|---|
| GTAW / TIG | Possible (solution-treated; care for strain-age cracking) | EN ISO matching Ni-Cr-Co filler (solution-treated base) |
| Resistance / EB | Specialised | — |
Minimise restraint and heat input; post-weld solution + age to restore properties. Hot working and welding are more demanding than for alloy 718.
Machining Guidelines
| Parameter | Recommendation |
|---|---|
| Preferred condition | Machine solution-treated where possible; finish after aging |
| Work hardening | High; rigid setup, sharp carbide tooling, low speeds |
| Hot working | More difficult than alloy 718 (γ′ strengthening) |
| Coolant | Ample flood coolant |
Forming Processes
| Process | Notes |
|---|---|
| Hot working | Demanding; controlled temperature range |
| Cold forming | Limited; high work-hardening rate |
| Final aging | Three-step HT after forming/machining |
| Industry | Typical Components | Key Requirements |
|---|---|---|
| Gas turbines | Turbine discs, blades, hubs, shafts, spacers | High strength + creep to 816 °C |
| Jet engines | Rotating components, rings, seals | Strength + oxidation + hot corrosion |
| Aerospace | High-strength bolts and fasteners | Strength + fatigue at temperature |
| Power generation | Turbine rotating hardware | Creep + stability |
| High-temperature | Critical rotating parts to 650 °C | Stress-rupture strength |
| Product Form | Standard | Other |
|---|---|---|
| Rod, bar and forging stock | ISO 9723 / 9724 / 9725 | AECMA PrEN 2193 / 2194 / 2406 / 2958 / 2959 / 2960 / 3220 |
| Plate, sheet and strip | AECMA PrEN 2195 | — |
| Composition / designation | W.Nr. 2.4654 · NiCr19Co14Mo4Ti | — |
| Welding consumables | EN ISO matching Ni-Cr-Co filler | — |
Nickel-base age-hardenable superalloy. W.Nr. 2.4654; ISO 9723–9725; AECMA PrEN series.
| W.Nr. | Ni % | Cr % | Other | Best Used For |
|---|---|---|---|---|
| 2.4654 | bal(~58) | 18–21 | Co 13, Mo 4, Ti+Al | Rotating turbine parts to 816°C |
| 2.4668 | 50–55 | 17–21 | Nb+Ti+Al | Highest strength to 650°C; weldable |
| 2.4632 | bal | 18–21 | Co 18, Ti+Al | Age-hardened; to 920°C |
| 2.4634 | bal(~54) | 14–16 | Co 20, Mo, Al | Age-hardened; to 950°C |
| 2.4973 | bal | 18–20 | Co 11, Mo 10 | Higher-strength γ′; to 870°C |
021-33556635
13371897780
651280525@qq.com
No. 600, Si Chuang Road, Songjiang District, Shanghai
