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Read MoreRene 41 Supplier and Stockist in India
Largest Rene 41 Stockist in Mumbai, India. AMS 5545 Rene 41 Sheets Supplier, Rene 41 Round Bars Stockist (AMS 5712/5713), Rene 41 Plates Dealer. Reliable Aerospace Grade Rene 41 Distributor & Exporter.
Rene 41 (UNS N07041) is a nickel-chromium alloy strengthened with cobalt, molybdenum, and titanium, engineered to deliver exceptional strength, oxidation resistance, and creep resistance at elevated temperatures. Capable of maintaining mechanical stability up to 1800°F (982°C), Rene 41 is widely used in the aerospace and defense industries for turbine engines, afterburner components, fasteners, and other critical high-temperature applications. Its outstanding resistance to thermal fatigue and corrosion ensures reliable performance in the most demanding environments.
Rene 41 Stockist in India
At Bhansali AeroAlloys, we provide premium-quality Rene 41 round bars, sheets, plates, and custom forms tailored to meet the exacting standards of aerospace and defense applications. With a strong focus on precision, durability, and timely delivery, we ensure that our materials perform flawlessly in mission-critical systems. For technical guidance, customized solutions, or pricing inquiries, reach out to our expert team today at sales@bhansaliaeroalloys.com and partner with a trusted supplier of advanced high-temperature alloys.
Type Analysis
| Element | Min | Max |
|---|---|---|
| Carbon | 0.06 | 0.12 |
| Manganese | -- | 0.10 |
| Silicon | -- | 0.20 |
| Chromium | 18.0 | 20.0 |
| Nickel | Balance | -- |
| Boron | 0.003 | 0.010 |
| Iron | -- | 5.00 |
| Cobalt | 10.0 | 12.0 |
| Titanium | 3.00 | 3.30 |
| Aluminum | 1.40 | 1.60 |
| Molybdenum | 9.00 | 10.50 |
Corrosion Resistance
Offers exceptional corrosion and oxidation resistance, withstanding jet engine combustion gases at temperatures up to 1800°F (982°C).
Applications
Used in afterburner components, turbine casings, wheels, buckets, bolts, and fasteners for jet engines and high-speed airframes.
Physical Properties
| Property | Value |
|---|---|
| Density (lb/in³) | 0.298 |
| Density (kg/m³) | 8249 |
| Melting Range (°F) | 2400–2500°F |
| Melting Range (°C) | 1316–1371°C |
| Specific Heat (Btu/lb-°F) | 0.108 (70–600°F) |
| Specific Heat (kJ/kg-K) | 0.452 (21–316°C) |
Modulus of Elasticity
| Temperature | Temp (°F) | Temp (°C) | ksi x 10³ | MPa x 10³ |
|---|---|---|---|---|
| — | 80 | 27 | 31.6 | 218 |
| 200 | 93 | 31.0 | 214 | |
| 600 | 316 | 29.3 | 202 | |
| 1000 | 538 | 27.3 | 188 | |
| 1200 | 649 | 26.0 | 179 | |
| 1400 | 760 | 24.8 | 171 | |
| 1600 | 871 | 23.2 | 160 |
Electrical Resistivity
| Condition | ohms c/mf | microhm-mm |
|---|---|---|
| Hot rolled | 787.1 | 1310 |
| A + 1950°F, 4 hrs, AC | 751.6 | 1250 |
| B + 1400°F, 16 hrs, AC | 761.4 | 1270 |
| A + 2150°F, 30 min, AC | 803.0 | 1330 |
| D + 1650°F, 4 hrs, AC | 807.2 | 1340 |
Mean Coefficient of Thermal Expansion
| Temperature | Temperature | Coefficient of Expansion | ||
|---|---|---|---|---|
| °F | °C | 10⁻⁶/°F | 10⁻⁶/°C | |
| — | 200 | 93 | 6.7 | 12.1 |
| — | 600 | 316 | 7.0 | 12.6 |
| — | 1000 | 538 | 7.5 | 13.5 |
| — | 1200 | 649 | 7.8 | 14.0 |
| — | 1400 | 760 | 8.2 | 14.8 |
| — | 1600 | 871 | 8.8 | 15.8 |
| — | 1800 | 982 | 9.3 | 16.7 |
| — | 2000 | 1093 | 9.0 | 17.8 |
Thermal Conductivity
| Temperature | Temperature | Thermal Conductivity | ||
|---|---|---|---|---|
| °F | °C | Btu-in/ft²-hr-°F | W/m-K | |
| — | 300 | 149 | 80 | 11.5 |
| — | 600 | 316 | 102 | 14.7 |
| — | 1000 | 538 | 131 | 18.9 |
| — | 1200 | 649 | 146 | 21.1 |
| — | 1400 | 760 | 161 | 23.2 |
| — | 1600 | 871 | 175 | 25.2 |
Heat Treatment
| Step | Details |
|---|---|
| Annealing | Quench from above gamma prime solvus (1950°F / 1066°C) for lowest hardness. Hardness: Rockwell B 98 / C 30. |
| Solution Treatment | Gamma prime solvus: 1960–1980°F (1071–1082°C). Fine grain: 1900–1925°F (1038–1052°C), hold 4 hrs, air cool. |
| Stress Rupture Improvement | Above solvus: 1975°F (1080°C), hold 1 hr, air cool. |
| Precipitation Hardening | 1400°F (760°C) for 16 hrs, air cool. Final hardness Rockwell C 40–45. |
Workability & Machining
| Process | Details |
|---|---|
| Hot Working / Forging | Best forged between 2100°F (1149°C) and finishing at 1850–1900°F (1010–1038°C). |
| Cold Working | Rapid work hardening; frequent annealing required. Avoid strain age cracking by heating quickly through aging range. |
| Machinability | Difficult to machine. Use tungsten carbide tools. Typical tool geometry: 0° back rake, 6° side rake, 7° clearance, 10° end cutting edge, 45° side cutting edge, 1/16" nose radius. |
| Machining Conditions | Feed: 0.005–0.011"/rev, Depth of cut: 1/32–1/8", Speed: 30–60 FPM. Fully treated or partially aged gives better finish. Aging causes size contraction (~0.0013" per inch). |
| Welding | Weldable by inert gas-arc. Part should be solution treated before welding. Post-weld: solution treat and optionally age at 1650°F (899°C) for 1 hr before final aging. |
