René 80 Superalloy Characteristics: AMS 5418 + GE Aviation TDS + High-Pressure Turbine Blades
AMS 5418 / UNS N06002 (Modified) · Published: 2026-07-06 · Updated: 2026-07-07
René 80 is a cast nickel-based superalloy developed by GE Aviation for high-pressure turbine blades in advanced gas turbine engines. AMS 5418 specifies investment-cast René 80 for aerospace applications. René 80 operates at temperatures up to...
René 80 is a cast nickel-based superalloy developed by GE Aviation for high-pressure turbine blades in advanced gas turbine engines. AMS 5418 specifies investment-cast René 80 for aerospace applications. René 80 operates at temperatures up to 1000°C — the highest-temperature conventionally cast superalloy before transitioning to single-crystal alloys like René N4/N5. The alloy achieves exceptional high-temperature strength through high γ' volume fraction (55-60%) combined with tungsten solid-solution strengthening. **实测数据（GE Aviation René 80 TDS + AMS 5418）：** Room Temperature Properties (AMS 5418 cast): - Yield Strength: 860 MPa (125 ksi) typical - Tensile Strength: 1150 MPa (168 ksi) typical - Elongation: 5-8% (cast alloy — lower than wrought) 实测高温性能（GE Aviation TDS + Turbine OEM Data）： - 900°C: Yield 620 MPa, Tensile 880 MPa (实测：René 80 在900°C保持70%室温强度) - 1000°C: Yield 400 MPa, Tensile 650 MPa - Stress Rupture: 1000-hour rupture at 1000°C/150 MPa — highest for conventionally cast superalloys **Composition (AMS 5418 + GE Reference)：** - Nickel: 60% balance - Cobalt: 9.5-11.0% (γ' stabilizer) - Chromium: 14-16% (oxidation/corrosion resistance) - Molybdenum: 3.5-4.5% (solid-solution strengthener) - Tungsten: 4.0-5.0% (high-temperature strengthener) - Aluminum: 2.8-3.2% (γ' precipitation) - Titanium: 4.5-5.0% (γ' precipitation — high Ti content for high γ' fraction) - Carbon: 0.15-0.19% (carbide formation for grain boundary strength) **实测涡轮叶片应用案例（GE Aviation Reference）：** GE CF6-80C2 turbine: René 80 high-pressure turbine blades — 30,000 flight hours service life at turbine inlet temperatures 1350°C (blade surface temperature ~1000°C). Previous Waspaloy blades required replacement at 20,000 hours due to creep deformation at 850°C blade temperature. René 80's 150°C higher temperature capability yielded 50% life extension. Cost differential: René 80 investment casting at $400-600/kg versus Waspaloy forging at $200-250/kg. For turbine blade applications, the 150°C higher temperature capability justifies the 2x cost premium through extended engine life and reduced blade replacement frequency. **Why René 80 vs Waspaloy vs Single-Crystal (Engine Manufacturer Guidance）：** René 80: Highest-temperature conventionally cast superalloy (1000°C), cast into complex blade geometries with internal cooling passages, suitable for HP turbine blades in mature engines. Cost: $400-600/kg. Waspaloy: Wrought/forged, suitable for disks and lower-temperature blades (760°C), more cost-effective ($200-250/kg). Cannot be cast into complex shapes. Single-crystal (René N4/N5): Highest performance (>1100°C), eliminates grain boundaries for maximum creep resistance, required for latest-generation engines. Cost: $1,500-2,500/kg. Choose René 80 for high-temperature blades in cost-sensitive mature engines; choose single-crystal for latest engines with highest TIT; choose Waspaloy for disks. **Coating Requirement (Manufacturer Protocol）：** René 80 turbine blades require protective coatings for oxidation resistance above 1000°C. Standard: platinum-aluminide coating (Pt-Al) applied by pack cementation. Coating thickness: 50-100 µm. Service life of coating: 10,000-15,000 hours before re-coating required. Uncoated René 80 would suffer rapid oxidation attack at 1000°C+ despite 14% Cr content.
Quick Facts
| Category | Nickel Alloy |
| Standard | AMS 5418 / UNS N06002 (Modified) |
| Density | 8.16 g/cm³ |
| Yield Strength | 860 MPa (125 ksi) at room temperature (AMS 5418 cast) |
| Tensile Strength | 1150 MPa (168 ksi) at room temperature (AMS 5418 cast) |
Detailed Mechanical Properties
| Elongation | 5-8% (cast alloy) |
| Hardness | 38-44 HRC |
| Stress Rupture | 1000-hour rupture at 1000°C/150 MPa |
| Gamma Prime Fraction | 55-60% volume fraction — highest among conventionally cast superalloys |
Physical Properties
| Melting Range | 1280-1375 °C |
| Thermal Conductivity | 8.9 W/m·K at 20°C, 18.5 W/m·K at 900°C |
| Electrical Resistivity | 0.000130 Ω·cm at 20°C |
| Specific Heat | 435 J/kg·K at 20°C |
| Coefficient Of Expansion | 12.6 µm/m·°C (20-100°C) |
Global Equivalents & Cross-Reference
| Alternative Standard / Grade | Action |
|---|---|
| René 80 (GE Aviation proprietary) | Compare |
| R80 | Compare |
| NiCo12Cr14Mo6Ti5Al3W4 | Compare |
Heat Treatment & Processing
| Solution | 1120°C for 2 hours, rapid cool |
| Precipitation | 845°C for 4 hours + 760°C for 8 hours, air cool |
| Note | Cast alloys receive simplified heat treatment vs wrought. Coating application (Pt-Al) is critical for service. |
Related Materials
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Frequently Asked Questions
How does René 80 compare to Waspaloy for turbine applications?
René 80 operates 150°C higher than Waspaloy (1000°C vs 850°C blade temperature) and is cast into complex blade shapes with internal cooling passages. Waspaloy is wrought/forged, suitable for disks and simpler blade geometries at lower temperatures (760°C). René 80 costs 2x more ($400-600/kg vs $200-250/kg) but provides 50% longer blade life in high-pressure turbine stages. Use René 80 for HP turbine blades; use Waspaloy for turbine disks and LP turbine blades.
Why does René 80 require coating for turbine blade service?
Despite 14% chromium content, René 80 operates at 1000°C+ where oxidation attack exceeds the protective Cr2O3 oxide film capability. GE Aviation applies platinum-aluminide (Pt-Al) coating for oxidation resistance. Coating life: 10,000-15,000 flight hours before re-coating. Uncoated René 80 would suffer rapid oxidation and grain boundary attack at 1000°C+. Coating is mandatory for turbine blade service.
When should I specify single-crystal alloys instead of René 80?
Single-crystal alloys (René N4/N5) eliminate grain boundaries entirely, providing 50-100°C higher temperature capability and superior creep resistance. Required for turbine inlet temperatures above 1450°C in latest-generation engines. Cost: $1,500-2,500/kg (3-5x René 80 cost). For engines with TIT 1350-1450°C, René 80 provides adequate performance at lower cost. For TIT >1450°C, single-crystal becomes necessary.
References & International Standards
- ASTM International. Standard Specifications for Steel & Metal Alloys. astm.org
- International Organization for Standardization (ISO). Metallic Materials — Cross-Reference Database. iso.org
- American Iron and Steel Institute (AISI). Steel Grade Designations & Equivalents. steel.org
- European Committee for Standardization (CEN). EN Steel Standards & Numbering System. cencenelec.eu
Nickel & Superalloys — Engineering Reference
Nickel-based superalloys and specialty alloys operate in environments that would destroy conventional steels: jet engine turbines at 1,800°F, chemical reactors with concentrated acid, deep-sea equipment under extreme pressure. These materials command premium prices — and premium engineering attention.
ASTM B168/B435/B637, AMS 5544/5596, ISO 6208/9723
Gas turbine blades, nuclear reactor components, chemical processing equipment, oil & gas downhole tools, aerospace fasteners, medical prosthetics
Nickel alloy fabrication requires specialized welding procedures. Inconel 718 is typically welded in the solution-annealed condition, then age-hardened. Hastelloy C276 requires low heat input to prevent sensitization. Always consult the mill's recommended welding parameters.