Rene 41®
Rene 41® is a high-performance, precipitation-hardenable nickel-based alloy engineered for extreme environments. This nickel-chromium alloy offers outstanding high-temperature strength and excellent oxidation resistance in the temperature range of 1200°F to 1800°F (649°C to 982°C), making it ideal for use in aerospace and high-heat applications. Rene 41® maintains its mechanical integrity under high stress and thermal cycling, offering a superior combination of creep resistance, fatigue strength, and surface stability at elevated temperatures. It is precipitation-hardened through a heat treatment process that enhances its strength characteristics while retaining corrosion and oxidation resistance.
- Inventory & Specs
- Chemical Composition
- Physical Properties
- Mechanical Properties
- Datasheet
- Additional Info
- FAQs
Inventory Size Ranges for Rene 41®
| Type | Thickness | AMS Standards | UNS | W.NR | Get a Quote |
|---|---|---|---|---|---|
| Precision Reroll Strip | 0.005" | AMS 5545 | UNS N07041 | W.Nr 2.4973 | Get a Quote |
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Advanced Inventory Size Ranges for Rene 41®
| Type | Size Range | Get a Quote |
|---|---|---|
| Get a Quote |
Characteristics of Rene 41®
Rene 41® maintains very high tensile strength from 1200–1800 °F (649–982 °C). This alloy was designed specifically for severely stressed components in high-heat environments. Rene 41® exhibits outstanding resistance to creep deformation under long-term high-temperature loading. This alloy is highly resistant to oxidation and is suitable for components exposed to repeated thermal and mechanical cycling.
Working with Rene 41®
Rene 41® is one of the more difficult nickel alloys to machine, so it is important to keep surface speeds low and deed rates steady. Cold forming is possible with this alloy but requires significant force. This alloy work-hardens quickly, so multiple small reductions are safer than one large one. Intermediate anneals are often necessary for complex shapes and springback is substantial due to high strength. Rene 41® is a precipitation-hardening superalloy, so heat treatment is essential for achieving final properties. It is important to control temperature, as incorrect aging can reduce creep strength. Overheating can coarsen precipitates and permanently degrade performance. Welding this alloy is possible, but requires expertise, as Rene 41® is susceptible to strain-age cracking. Heat-affected zones can lose ductility and post-weld heat treatment is often required to restore properties.
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Common Trade Names
Industry Applications for Rene 41®
- Turbine blades
- Wheels
- Combustion chamber liners
- After burners
- Structural hardware
Chemical Composition
| Element | Percent by Weight Min | Percent by Weight Max | |
|---|---|---|---|
| C | Carbon | - | 0.12 |
| Mn | Manganese | - | 0.10 |
| Si | Silicon | - | 0.50 |
| S | Sulfur | - | 0.15 |
| Cr | Chromium | 18.00 | 20.00 |
| Co | Cobalt | 10.00 | 12.00 |
| Mo | Molybdenum | 9.00 | 10.50 |
| Ti | Titanium | 3.00 | 3.30 |
| Al | Aluminum | 1.40 | 1.60 |
| B | Boron | 0.003 | 0.010 |
| Fe | Iron | - | 5.00 |
| Cu | Copper | - | 0.50 |
| Ni | Nickel | - | Balance |
Physical Properties
| Property | At 70°F | At 20°C |
|---|---|---|
| Density | 0.298 lb/in³ | 8.25 g/cm³ |
| Modulus of Elasticity (E) | 31.6 x 10³ ksi | 218 GPa |
| Modulus of Rigidity (G) | 12.1 x 10³ ksi | 83.4GPa |
| Coefficient of Expansion | 7.5 microinches/in.-°F (70-1000°F) | 102.0 microhm-cm°C (20-538°C) |
| Electrical Resistivity | 51.5 microhm-in | 131 microhm-cm |
| Thermal Conductivity | 62 Btu●in/ft²●h●°F | 9.0 W/wm●°C |
Mechanical Properties
| Condition | Heat Treatment | Tensile Strength, ksi | Suggested Operating Conditions |
|---|---|---|---|
| Annealed | 1975°F (1079°C) | 170 | -300°F - 1500°F (-184°C - 815°C) |
| Spring Temper | -300°F - 1500°F (-184°C - 815°C) | ||
| After Precipitation Heat Treat | Per AMS 5545 | 160 | -300°F - 1500°F (-184°C - 815°C) |
Datasheet
Additional Info
A Brief History of Rene 41®
Rene 41® was introduced in the 1950s during a period of rapid advancement in jet propulsion and high‑temperature metallurgy. As aircraft engines pushed into hotter and more demanding operating ranges, existing nickel alloys could no longer provide the strength and creep resistance required for sustained performance. Metallurgists developed Rene 41® as part of a new generation of superalloys designed specifically for extreme thermal and mechanical stress. Its ability to retain strength at temperatures approaching 1800 °F made it one of the most important early high‑temperature alloys in aerospace history.
How Rene 41® was Developed
The development of Rene 41® centered on creating a precipitation‑hardened nickel‑based alloy capable of resisting creep, oxidation, and thermal fatigue. Engineers achieved this by incorporating significant amounts of chromium, cobalt, molybdenum, titanium, and aluminum. Through controlled solution‑annealing and aging heat treatments, the alloy could be tailored to deliver exceptional high‑temperature strength. This metallurgical design made Rene 41® one of the earliest superalloys to combine both oxidation resistance and long‑term structural stability at elevated temperatures.
Early Applications of Rene 41®
Rene 41® quickly found its place in the aerospace industry, particularly in components exposed to extreme heat and stress. Early applications included turbine casings, afterburner parts, fasteners, and structural hardware in high‑performance military aircraft. The alloy also played a role in early rocket engine development, where its creep resistance and oxidation stability were essential for combustion‑chamber components.
How Rene 41® is Used Today
Today, Rene 41® remains a trusted material in aerospace, defense, and high‑temperature industrial systems. It is widely used in jet engine hardware, turbine components, high‑strength fasteners, and exhaust structures that must endure repeated thermal cycling. In the space industry, it continues to serve in rocket engine parts and hot‑section hardware where long‑term creep resistance is critical. Beyond aerospace, Rene 41® appears in industrial furnaces, high‑temperature tooling, and specialty applications requiring exceptional strength at elevated temperatures.
Your Trusted Supplier of Rene 41®
United Performance Metals supplies Rene 41® in precision thin gauge strip size 0.005". This product is used in places where extreme heat, high stress, and long-term reliability are non-negotiable. It is commonly used for jet engines, rocket engines, space hardware, aerospace structural components, and industrial high-temperature systems.
Product FAQs
The alloy is strengthened through solution annealing and aging, which promote the formation of gamma‑prime (γ′) precipitates. These precipitates give the alloy its high‑temperature strength and creep resistance.
Rene 41® maintains excellent mechanical strength from room temperature up to roughly 1600–1800 °F, depending on the specific heat‑treat condition and application.