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
Nimonic PK33 is a high-strength, precipitation-hardenable nickel-chromium-cobalt superalloy. This datasheet presents the material within the American / international (aerospace) standard system.
A nickel-base aerospace alloy developed principally to produce sheet with ultrahigh strength and good formability, Nimonic PK33 is a nickel-chromium-cobalt alloy strengthened by a substantial molybdenum addition for solid-solution strengthening together with aluminium and titanium, which form the gamma-prime (γ′, Ni₃(Al,Ti)) phase on ageing for high-temperature strength. It combines very high strength with good formability and high-temperature capability, and is hardened by solution treatment followed by ageing.
Typical applications include gas-turbine sheet components — flame tubes, combustion-chamber and hot-section sheet fabrications — and laser-drilled cooling-hole components and other high-strength aero-engine hardware.
| Property | Value | Unit |
|---|---|---|
| Density | 8.21 | g/cm³ |
| Melting range | 1290–1355 | °C |
| Elastic modulus | 222 | GPa |
| Coefficient of thermal expansion (20–100 °C) | 12.6 | µm/m·°C |
| Thermal conductivity (20 °C) | 10.8 | W/m·K |
| Specific heat (20 °C) | 444 | J/kg·K |
| Structure | Austenitic (FCC) + γ′ | — |
| Element | Symbol | Min % | Max % | Role in Alloy |
|---|---|---|---|---|
| Nickel | Ni | Balance | — | Base element; γ′ matrix |
| Chromium | Cr | 16.0 | 20.0 | Oxidation resistance |
| Cobalt | Co | 12.0 | 16.0 | Solid-solution; raises γ′ stability |
| Molybdenum | Mo | 5.0 | 9.0 | Solid-solution strengthening |
| Aluminium | Al | 1.70 | 2.50 | γ′ (Ni₃Al) precipitation strengthening |
| Titanium | Ti | 1.50 | 3.00 | γ′ (Ni₃Ti) precipitation strengthening |
| Boron | B | — | 0.005 | Grain-boundary strengthening |
| Zirconium | Zr | — | 0.06 | Grain-boundary strengthening |
| Sulfur | S | — | 0.015 | Residual |
Fully heat-treated (solution-treated and aged) condition, typical values.
| Condition | Property | Value |
|---|---|---|
| Solution treated & aged | Tensile strength (UTS) | ≥1200 MPa (174 ksi) |
| Solution treated & aged | 0.2% yield strength | ≥800 MPa (116 ksi) |
| Solution treated & aged | Elongation at break | ≥20 % |
| At elevated temperature | Creep / rupture strength | Retained at high temperature |
| — | Elastic modulus | 222 GPa |
Confirm against the mill test report. The γ′ volume fraction gives the ultrahigh sheet strength for which the alloy was developed, combined with good formability.
| Environment | Performance | Notes |
|---|---|---|
| High-temperature oxidation | Very Good | High chromium content |
| Hot corrosion | Good | Aero-engine hot-section service |
| Creep / stress rupture | Very Good | γ′-strengthened |
| Thermal fatigue | Good | Combined with high strength |
| Aqueous corrosion | Moderate | Not the primary design purpose |
The high chromium content gives good high-temperature oxidation resistance, while the γ′ volume fraction and molybdenum solid-solution strengthening provide the high strength and creep resistance required for aero-engine sheet components.
A γ′ precipitation-hardenable superalloy; strengthened by solution treatment followed by ageing.
Solution Treatment Solution treat / anneal at approximately 1107 °C (2025 °F) and air cool, dissolving the γ′ for subsequent controlled re-precipitation.
Precipitation Hardening (Ageing) Age at approximately 700–850 °C and air cool, precipitating the γ′ (Ni₃(Al,Ti)) phase that develops the alloy's high strength and creep resistance.
Weldable with care; like other high-aluminium-plus-titanium γ′ alloys it is susceptible to strain-age cracking, so welding of highly stressed, restrained components requires careful procedure. Matching alloy filler is used, or the nearest alloy richer in nickel, cobalt, chromium and molybdenum.
| Welding Process | Applicability | Filler / Consumable |
|---|---|---|
| GTAW / TIG | With care | Matching PK33 filler |
| Resistance / spot | Good | Sheet fabrication |
| Post-weld | Recommended | Solution treat and age |
Weld with matching filler and clean surfaces; manage restraint to avoid strain-age cracking, and apply post-weld heat treatment.
Machining Guidelines
| Parameter | Recommendation |
|---|---|
| Machinability | Difficult; high strength, work-hardens, rigid setups |
| Tooling | Carbide; heavy-duty equipment, slow speeds |
| Coolant | Water-based coolant for high-speed operations |
Forming Processes
| Process | Notes |
|---|---|
| Cold forming | Good formability (sheet); solution treat and age afterward |
| Hot forming | Performed hot; solution treat and age afterward |
| Industry | Typical Components | Key Requirements |
|---|---|---|
| Aero gas turbine | Flame tubes, combustion-chamber sheet | Ultrahigh strength + formability |
| Propulsion | Laser-drilled cooling-hole components | Strength + thermal capability |
| Power generation | Hot-section sheet fabrications | High-temperature strength |
| High-temperature | Severely stressed sheet hardware | Creep + oxidation resistance |
| Product Form | Standard | Notes |
|---|---|---|
| Sheet and strip | DTD 5057 / 5077 | Ultrahigh-strength sheet |
| Bar and forgings | Nimonic PK33 | γ′-hardened superalloy |
| Plate | Nimonic PK33 | — |
| Parts | Nimonic PK33 | Solution-treated and aged |
γ′ precipitation-hardened nickel-chromium-cobalt superalloy. Nimonic PK33.
| Alloy | Cr % | Co % | Mo % | Best Used For |
|---|---|---|---|---|
| Nimonic PK33 | 16–20 | 12–16 | 5–9 | Ultrahigh-strength γ′ sheet; gas-turbine flame tubes, hot-section fabrications |
| Nimonic 263 | 19–21 | 19–21 | 5.6–6.1 | Fabricable γ′ sheet / fabrication alloy |
| Nimonic 115 | 14–16 | 13–15.5 | 3–5 | High-γ′ turbine-blade superalloy |
| Nimonic 90 | 18–21 | 15–21 | — | Creep-resistant blade / disc alloy |
| Nimonic 80A | 18–21 | ≤2 | — | Age-hardened Ni-Cr; valves, fasteners |
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