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
Alloy 115 is a high-strength, precipitation-hardenable nickel-chromium-cobalt superalloy. This datasheet presents the material within the American / international (AMS / aerospace) standard system.
Developed as a creep-resisting alloy for service at temperatures up to about 1010 °C (1850 °F), Alloy 115 was created principally for turbine blades in aircraft gas turbines. It is a nickel-chromium-cobalt alloy strengthened by a molybdenum addition for solid-solution strengthening together with high levels of aluminium and titanium, which form a large volume fraction of the gamma-prime (γ′, Ni₃(Al,Ti)) phase for exceptional high-temperature strength and creep resistance. It offers superior oxidation resistance and high-temperature strength, and is hardened by solution treatment followed by ageing.
Typical applications include gas-turbine blades, nozzle guide vanes and disc components, exhaust valves, and high-temperature fasteners and engine components subject to severe stress and cyclic loading.
Typical values, fully heat-treated condition.
| Property | Value | Unit |
|---|---|---|
| Density | 7.85 | g/cm³ |
| Melting range | 1275–1335 | °C |
| Elastic modulus | 224 | GPa |
| Coefficient of thermal expansion (20–100 °C) | 12.0 | µm/m·°C |
| Thermal conductivity (20 °C) | 10.7 | W/m·K |
| Specific heat (20 °C) | 448 | J/kg·K |
| Structure | Austenitic (FCC) + γ′ | — |
Specified for the γ′ precipitation-hardened Ni-Cr-Co superalloy (Nimonic 115).
| Element | Symbol | Min % | Max % | Role in Alloy |
|---|---|---|---|---|
| Nickel | Ni | Balance | — | Base element; γ′ matrix |
| Chromium | Cr | 14.0 | 16.0 | Oxidation resistance |
| Cobalt | Co | 13.0 | 15.5 | Solid-solution; raises γ′ stability |
| Aluminium | Al | 4.50 | 5.50 | γ′ (Ni₃Al) precipitation strengthening |
| Titanium | Ti | 3.50 | 4.50 | γ′ (Ni₃Ti) precipitation strengthening |
| Molybdenum | Mo | 3.0 | 5.0 | Solid-solution strengthening |
| Carbon | C | 0.12 | 0.20 | Carbide formation |
| Iron | Fe | — | 1.0 | Residual |
| Zirconium | Zr | — | 0.10 | Grain-boundary strengthening |
| Boron | B | — | 0.20 | Grain-boundary strengthening |
Nominal: nickel-chromium-cobalt γ′ precipitation-hardened superalloy with Mo, high Al and Ti.
Fully heat-treated (solution-treated and aged) condition, typical values.
| Condition | Property | Value |
|---|---|---|
| Solution treated & aged | Tensile strength (UTS) | ≥1240 MPa (180 ksi) |
| Solution treated & aged | 0.2% yield strength | ≥865 MPa (125 ksi) |
| Solution treated & aged | Elongation at break | ≥12 % |
| At elevated temperature | Creep / rupture strength | Excellent to ~1010 °C |
| — | Elastic modulus | 224 GPa |
Confirm against the mill test report. The high γ′ volume fraction gives outstanding creep and rupture strength at turbine-blade operating temperatures.
| Environment | Performance | Notes |
|---|---|---|
| High-temperature oxidation | Excellent | High chromium + aluminium |
| Hot corrosion | Very Good | Turbine-blade service |
| Creep / stress rupture | Excellent | High γ′ content |
| Thermal fatigue | Very Good | Combined with high strength |
| Aqueous corrosion | Moderate | Not the primary design purpose |
The high chromium and aluminium contents give excellent high-temperature oxidation resistance, while the large γ′ volume fraction provides the outstanding creep and stress-rupture strength required for gas-turbine blade service to about 1010 °C.
A γ′ precipitation-hardenable superalloy; strengthened by solution treatment followed by ageing.
Solution Treatment Solution treat at approximately 1190 °C (2175 °F) for about 1.5 hours and air cool, dissolving the γ′ for subsequent controlled re-precipitation.
Precipitation Hardening (Ageing) Age at approximately 1100 °C (2012 °F) for about 6 hours and air cool, precipitating the γ′ (Ni₃(Al,Ti)) phase that develops the alloy's high-temperature strength and creep resistance.
Weldable with care; the high aluminium-plus-titanium content makes the alloy 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 115 filler |
| EBW / laser | With care | Autogenous or matching filler |
| 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; slow speeds, positive feeds |
| Coolant | Water-based coolant for high-speed operations |
Forming Processes
| Process | Notes |
|---|---|
| Cold forming | Good ductility but high strength; heavy-duty lubricants, clean after forming |
| Hot forming | Performed hot; solution treat and age afterward |
| Industry | Typical Components | Key Requirements |
|---|---|---|
| Aero gas turbine | Turbine blades, nozzle guide vanes | Creep + oxidation resistance |
| Power generation | Disc components, hot-section hardware | High-temperature strength |
| Motorsport / engine | Exhaust valves, fasteners, springs | Strength + surface stability |
| High-temperature | Severely stressed cyclic components | Creep + thermal-fatigue resistance |
| Product Form | Standard | Notes |
|---|---|---|
| Bar, billet and forgings | AMS 5911 · BS HR4 | γ′-hardened superalloy |
| Extruded / cold-worked section | AECMA PrEN 2196 / 2197 | Turbine-blade stock |
| Tube | Nimonic 115 | Special order |
| Parts | Nimonic 115 | Solution-treated and aged |
γ′ precipitation-hardened nickel-chromium-cobalt superalloy. AMS 5911.
| Alloy | Cr % | Co % | γ′ Formers | Best Used For |
|---|---|---|---|---|
| Alloy 115 | 14–16 | 13–15.5 | Al + Ti (high) | High-γ′ turbine-blade superalloy; creep strength to ~1010 °C |
| Alloy 105 | 14–16 | 18–22 | Al + Ti + Mo | High-temperature creep-resistant blade alloy |
| Alloy 90 | 18–21 | 15–21 | Al + Ti | Creep-resistant blade / disc alloy |
| Alloy 80A | 18–21 | ≤2 | Al + Ti | Age-hardened Ni-Cr; valves, fasteners |
| Alloy 263 | 19–21 | 19–21 | Al + Ti | Fabricable γ′ sheet / fabrication alloy |
+86 021 3355 6635
+86 133 7189 7780
zcalloy1001@gmail.com
Building E265, No. 2, Lane 158, Gangye Road, Xiaokunshan Town, Songjiang District, Shanghai
