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
NiCr19CoMo is a precipitation-hardenable nickel–chromium-base superalloy with exceptionally high strength, developed by General Electric, that retains its strength from room temperature through about 871 °C (1600 °F). This datasheet presents the material within the European (EN / Werkstoff-Nummer) standard system.
Strength is derived from solid-solution strengthening (significant cobalt and molybdenum additions) together with precipitation of the gamma-prime [Ni₃(Al,Ti)] phase developed during age hardening. The high molybdenum content (about 9–10.5%) distinguishes it from related γ′ alloys and contributes to its exceptional strength, while ~19% chromium gives outstanding oxidation resistance to ~871 °C. It is designed for severely stressed high-temperature applications and famously formed the outer shell of the Mercury space capsule, owing to its ability to retain high strength at very high temperatures.
The alloy is sensitive to strain-age cracking during welding, so it must be welded in the fully solution-treated condition, with rapid heating/cooling through the 650–870 °C (1200–1600 °F) range and post-weld solution treatment plus aging. Typical applications include hot components for jet and rocket engines, turbine blades and wheels, torque rings, high-strength bolting and springs, and missile components.
Values per manufacturer data, solution-treated and aged condition.
| Property | Value | Unit |
|---|---|---|
| Density | 8.25 | g/cm³ |
| Melting range | 1307–1343 | °C |
| Young's modulus (20 °C) | 220 | GPa |
| Specific heat capacity (20 °C) | 418 | J/kg·K |
| Thermal conductivity (20 °C) | 9.0 | W/m·K |
| Electrical resistivity (20 °C) | 1.31 | µΩ·m |
| Coefficient of thermal expansion (20–100 °C) | 12.1 | µm/m·°C |
| Strength retained to | ~871 (1600 °F) | °C |
| Service range | 650–980 | °C |
Composition per DIN (W.Nr. 2.4973, NiCr19CoMo).
| Element | Symbol | Min % | Max % | Role in Alloy |
|---|---|---|---|---|
| Nickel | Ni | Balance | — | Base; FCC matrix |
| Chromium | Cr | 18.0 | 20.0 | Oxidation / corrosion resistance |
| Cobalt | Co | 10.0 | 12.0 | Solid-solution + γ′ strengthening |
| Molybdenum | Mo | 9.0 | 10.5 | Solid-solution strengthening |
| Titanium | Ti | 2.8 | 3.3 | γ′ precipitation strengthening |
| Aluminium | Al | 1.4 | 1.8 | γ′ precipitation strengthening |
| Iron | Fe | — | 5.0 | Residual |
| Carbon | C | — | 0.12 | Carbide strengthening |
| Boron | B | 0.003 | 0.01 | Grain-boundary strengthening |
| Manganese | Mn | — | 0.1 | Deoxidiser |
| Silicon | Si | — | 0.5 | Deoxidiser |
| Phosphorus | P | — | 0.015 | Residual impurity |
| Sulphur | S | — | 0.015 | Residual impurity |
Nominal: Ni-19Cr-11Co-10Mo-3Ti-1.6Al. A high-strength age-hardenable Ni-Cr-Co-Mo superalloy (alloy 41) strengthened by γ′; very high creep strength for jet-engine and high-temperature airframe parts to ~870 °C.
Solution-treated and aged condition (1066 °C/4h AC + 760 °C/16h AC), per DIN for W.Nr. 2.4973.
| Property | Value | Unit |
|---|---|---|
| Tensile strength (Rm) | ≥1240 | MPa |
| 0.2% proof strength (Rp0.2) | ≥930 | MPa |
| Elongation at fracture (A) | ≥10 | % |
Values per EN/DIN; confirm against the inspection certificate (EN 10204).
| Environment | Performance | Notes |
|---|---|---|
| High-temperature strength | Exceptional | Highest of the common wrought γ′ alloys; to ~871 °C |
| Oxidation | Outstanding | To ~871 °C (1600 °F) |
| Creep / stress-rupture | Excellent | High Mo + γ′ |
| Hot corrosion | Good | Gas-turbine combustion environments |
| General corrosion | Good | High Ni-Cr base |
| Strain-age cracking (welding) | Sensitive | Weld in solution-treated condition only |
A precipitation-hardening nickel-base superalloy. Strength is developed by solution treatment followed by aging.
Solution Treatment Temperature: ~1065–1080 °C (1950–1975 °F), followed by rapid cooling (air or oil)
Age Hardening Temperature: ~760 °C (1400 °F) / ~16 h / air cool (for high-strength applications); alternative ~900 °C (1650 °F) cycles are used for optimum creep-rupture properties.
Welding caution: the alloy is sensitive to strain-age cracking; it must be in the fully solution-treated condition before welding, with rapid heating/cooling through the 650–870 °C range, followed by post-weld solution treatment and aging.
alloy 41 is sensitive to strain-age cracking during welding (a consequence of its high γ′ content), so it must be welded in the fully solution-treated condition. Sound welds can be made by resistance and electron-beam methods; GTAW with DC straight polarity requires good joint fit-up and cooling via copper backing bars or water-cooled fixtures.
| Welding Process | Applicability | Notes |
|---|---|---|
| Resistance / EB | Good | Preferred for sound welds |
| GTAW / TIG | Possible | DCSP; good fit-up; copper backing / water cooling |
After welding, the assembly should be solution-treated with rapid heating and cooling through the 650–870 °C (1200–1600 °F) range, followed by aging. Use matching filler (MSRR 9500/241 matching wire (solution-treated base)).
Machining Guidelines
| Parameter | Recommendation |
|---|---|
| Preferred condition | Machine solution-treated; finish before/after aging per part |
| Work hardening | High; rigid setup, sharp carbide tooling, low speeds |
| Hot working | Demanding (high γ′); controlled temperature |
| Coolant | Ample flood coolant |
Forming Processes
| Process | Notes |
|---|---|
| Hot working | High-temperature, controlled range |
| Cold forming | Limited; high work-hardening rate |
| Final aging | After forming/machining to develop full strength |
| Industry | Typical Components | Key Requirements |
|---|---|---|
| Jet engines | Hot-section components, turbine blades and wheels | Exceptional strength to 871 °C |
| Rocket / aerospace | Rocket-engine parts, missile components, capsule shell | Strength at extreme temperature |
| Gas turbines | Torque rings, turbine hardware | Creep + oxidation resistance |
| Fasteners | High-strength bolting, springs | Strength + fatigue at temperature |
| High-temperature structures | Severely stressed hot parts | Stress-rupture strength |
| Product Form | Standard | Other |
|---|---|---|
| Sheet, strip, plate | W.Nr. 2.4973 | — |
| Bar, rod, forging stock | W.Nr. 2.4973 | — |
| Welding wire | MSRR 9500/241 | — |
| Composition / designation | W.Nr. 2.4973 · NiCr19CoMo | — |
Nickel-base age-hardenable superalloy. W.Nr. 2.4973; MSRR 9500/241.
| EN Symbol | Ni % | Cr % | Other | Best Used For |
|---|---|---|---|---|
| NiCr19CoMo | bal | 18–20 | Co 11, Mo 10, Ti+Al | Highest-strength wrought γ′; to 871°C |
| NiCr19Co14Mo4Ti | bal(~58) | 18–21 | Co 13, Mo 4, Ti+Al | Rotating turbine parts to 816°C |
| NiCr19Fe19Nb5Mo3 | 50–55 | 17–21 | Nb+Ti+Al | High strength to 650°C; weldable |
| NiCo20Cr15MoAlTi | bal(~54) | 14–16 | Co 20, Mo, Al | Age-hardened; to 950°C |
| NiCr18Co19Mo4Ti3Al3 | bal | 17–19 | Co 19, Mo, Ti+Al | Age-hardened; turbine blades |
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