Rene 41 is a nickel-based superalloy with excellent high-temperature strength, creep resistance, and oxidation resistance. It is commonly used in turbine components, combustion chambers, and other parts exposed to extreme heat.
Inconel 718 is a precipitation-hardened nickel alloy with high strength, good fatigue resistance, and excellent weldability. It is widely used in aircraft engines, gas turbines, and high-stress industrial components.
A precipitation-hardened nickel-based superalloy offering exceptional high-temperature strength, creep resistance and oxidation resistance, widely used in turbine components, combustion hardware, rocket engines and high-temperature fasteners.
View Rene 41A precipitation-hardenable nickel-chromium-iron superalloy combining high strength, good fatigue resistance and reliable performance at elevated temperatures, widely used in aircraft engines, gas turbines, rocket components and high-performance fasteners.
View Inconel 718Review the key differences before confirming chemical media, product form, standard, certificate and delivery schedule.
| Comparison Item | Rene 41 | Inconel 718 | Selection Note |
|---|---|---|---|
| Basic Information | |||
| UNS Number | N07041 | N07718 | Use the UNS number on drawings, MTCs and purchase specifications. |
| Alloy Type | Nickel-chromium-cobalt-molybdenum superalloy | Nickel-chromium-iron-niobium-molybdenum superalloy | Rene 41 is optimized for high-temperature strength, while 718 combines high strength with easier fabrication. |
| Strengthening Method | Gamma-prime precipitation hardened | Primarily gamma-double-prime precipitation hardened | Both alloys require controlled solution and aging treatments to develop their intended properties. |
| Typical Product Forms | Sheet, plate, bar, wire, forgings, rings and fasteners | Sheet, plate, bar, wire, forgings, rings and fasteners | 718 generally has broader availability and more established commercial supply routes. |
| Chemical Composition | |||
| Nickel (Ni) | Balance, approximately 55% | 50.0-55.0% | Both alloys use a nickel-rich matrix for high-temperature stability. |
| Chromium (Cr) | 18.0-20.0% | 17.0-21.0% | Chromium provides oxidation and hot-corrosion resistance in both alloys. |
| Cobalt (Co) | 10.0-12.0% | 1.0% max | The high cobalt content of Rene 41 supports strength and phase stability at elevated temperatures. |
| Molybdenum (Mo) | 9.0-10.5% | 2.8-3.3% | Rene 41 contains more molybdenum for strong solid-solution strengthening. |
| Niobium + Tantalum (Nb + Ta) | Not intentionally added | 4.75-5.50% | Niobium is the principal contributor to gamma-double-prime strengthening in 718. |
| Titanium (Ti) | 3.0-3.3% | 0.65-1.15% | The higher titanium content of Rene 41 promotes strong gamma-prime precipitation. |
| Aluminum (Al) | 1.4-1.8% | 0.20-0.80% | Aluminum combines with titanium to form the primary strengthening phase in Rene 41. |
| Iron (Fe) | 5.0% max | Balance | 718 contains significantly more iron and is generally less alloy-intensive. |
| Carbon (C) | 0.06-0.12% | 0.08% max | The higher carbon range of Rene 41 promotes carbide strengthening at grain boundaries. |
| Boron (B) | 0.003-0.010% | 0.006% max | Small boron additions help improve grain-boundary strength and stress-rupture performance. |
| Mechanical Properties | |||
| Typical Condition | Solution treated and aged | Solution treated and precipitation hardened | Mechanical values depend strongly on product form, section size and heat-treatment cycle. |
| Yield Strength, RT | Approx. 1,035 MPa | Approx. 1,035 MPa | Both can provide high room-temperature yield strength in fully heat-treated conditions. |
| Tensile Strength, RT | Approx. 1,400 MPa | Approx. 1,275 MPa | Rene 41 can provide higher tensile strength, depending on product form and heat treatment. |
| Elongation, RT | Approx. 10-15% | Approx. 12-20% | 718 generally provides more consistent ductility and easier fabrication. |
| Creep Strength | Excellent up to approximately 870°C | Excellent up to approximately 650°C | Rene 41 maintains useful creep strength at significantly higher temperatures. |
| Stress-Rupture Strength | Excellent at high temperatures | Excellent at intermediate temperatures | Rene 41 is preferred when long-term rupture strength above the normal range of 718 is required. |
| Fatigue Strength | Excellent at elevated temperatures | Excellent at room and intermediate temperatures | Use project-specific fatigue data for the actual temperature, stress ratio and design life. |
| Weldability | Difficult; susceptible to strain-age cracking | Good with established qualified procedures | 718 is generally easier to weld and repair; Rene 41 requires tighter process and heat-treatment control. |
| Temperature Performance | |||
| Typical Strength-Limited Service | Up to approximately 870°C | Up to approximately 650°C | Actual limits depend on applied stress, exposure time, environment and design code. |
| Oxidation Resistance | Excellent at elevated temperatures | Good to excellent at moderate elevated temperatures | Rene 41 is generally better suited to prolonged exposure at higher temperatures. |
| Thermal Stability | Excellent within its intended high-temperature range | Good, but strengthening phases lose stability at higher temperatures | 718 should not replace Rene 41 where sustained service substantially exceeds approximately 650°C. |
| High-Temperature Load Capability | Superior above approximately 650°C | Excellent below approximately 650°C | Rene 41 provides the stronger option for highly loaded hot-section components. |
| Price Comparison | |||
| Relative Material Cost | Higher | High | Rene 41 generally costs more because of its cobalt and molybdenum content and lower production volume. |
| Stock Availability | Limited; some forms and sizes may require special production | Widely available in common aerospace and industrial forms | 718 is usually easier to source for urgent requirements and small quantities. |
| Fabrication Cost | Very high | High | Rene 41 requires demanding machining, welding and heat-treatment controls. |
| Quotation Factors | Form, size, quantity, heat treatment, testing, cobalt price and aerospace approvals | Form, size, quantity, heat treatment, testing, machining and aerospace approvals | Final pricing should be based on the actual drawing, specification, certification and delivery requirements. |
| Performance & Application | |||
| Primary Advantage | High creep and stress-rupture strength at temperatures beyond the practical range of 718 | Excellent strength, fatigue resistance, weldability and commercial availability | The operating temperature and fabrication requirements are usually the decisive factors. |
| Corrosion Resistance | Good oxidation and hot-corrosion resistance | Good general corrosion and oxidation resistance | Neither grade should be selected for aggressive chemical service without environment-specific corrosion data. |
| Machinability | Difficult | Difficult, but supported by well-established machining practices | Rene 41 generally causes greater tool wear and requires more conservative machining parameters. |
| Typical Applications | Gas-turbine combustion components, turbine casings, exhaust parts, afterburner components and high-temperature fasteners | Turbine disks, shafts, compressor parts, aerospace fasteners, rocket components and oilfield equipment | Rene 41 is used in hotter components; 718 is widely used in highly loaded intermediate-temperature parts. |
| Best Use Case | High-load service requiring creep and rupture strength at approximately 650-870°C | High-strength service up to approximately 650°C with better weldability and availability | Select Rene 41 for higher-temperature capability and 718 for a more economical and fabrication-friendly solution. |
Values are typical references for article comparison. Final supply should follow the ordered standard, product form, heat treatment, mill test certificate and project requirements.
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