Rene 41

Rene 41 is a precipitation-hardening nickel-based alloy designed for high strength in severe conditions. Its chemical composition balances important elements to deliver lasting performance. The alloy contains 18–20% chromium, which adds oxidation resistance. Cobalt at 10–12% strengthens the structure, while 9–10.5% molybdenum improves creep resistance. Titanium (3.0–3.3%) and aluminum (1.4–1.6%) are the primary age-hardening elements that give Rene 41 metal its excellent strength. Nickel is the base element holding the alloy stable in high heat and corrosive settings. Small additions of carbon (0.06–0.12%), boron (0.003–0.010%), and controlled iron refine toughness and machinability. This precise balance makes Rene 41 material reliable in jet engines, turbines, and aerospace hardware.

Parag Metals supplies Rene 41 in different forms with each batch tested to meet industrial standards. The alloy retains remarkable strength even as temperature rises. At room temperature its tensile strength is approximately 1379 MPa (200 ksi) and at 870°C, it retains its strength at 621 MPa (90 ksi). At 925°C, yield strength drops from 1034 MPa (150 ksi) to 345 MPa (50 ksi), but ductility increases, with elongation rising from 12% to 19%. The hardness of aged Rene 41 is about 35 HRC, showing its ability to withstand heavy loads. This combination of strength and toughness is why Rene 41 is still chosen for extreme aerospace uses where failure is not an option.

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Rene 41 Sheet, Rene 41 Plate, Rene 41 Coils, Rene 41 Rods, Rene 41 Wires Suppliers in Mumbai, India.

Rene 41 material properties also highlight its durability under demanding service. It has a density of 8249 kg/m³ and a melting range of 1316–1371°C. The alloy is non-magnetic at room temperature and holds good electrical resistivity. Its thermal conductivity is low, which is typical for nickel alloys, but it increases with heat.Rene 41 can endure exposure to jet combustion gases up to 1800°F (982°C) and has a high resistance to oxidation and corrosion. Also, engineers have more control over strength and toughness depending on the end use as it is age-hardenable. Due to these features, the aerospace industry often has Rene 41 vs Inconel 718 comparisons as both alloys work well in high-temperature, high-stress settings.

Fabrication of Rene 41 requires skill and the right process. The alloy can be finished at roughly 1850–1900°F (1010–1038°C) and hot worked between 2100°F (1149°C). Due to the alloy’s quick work-hardening, cold working is possible but difficult. Frequent annealing is needed to avoid cracking. Tungsten carbide tools are recommended since Rene 41 machinability is difficult compared to softer alloys. After machining, aging, or solution treating might be needed and protective atmospheres are recommended to prevent surface oxidation. Rene 41 wire, bars, sheets and forgings are still in high demand for important industrial applications despite these challenges. Rene 41 is supplied in multiple forms, including bar, wire, sheet, plate, forgings, and strip, making it versatile for a wide range of uses. The alloy is often used in turbine casings, afterburner parts, bolts, buckets, and high-speed airframe components where both heat resistance and high strength are critical. These forms and applications show why Rene 41 material continues to be a reliable choice for aerospace and high-performance industries.

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Rene 41 Specification

Rod, Bar, Wire and Forging Stock	AMS 5545, AMS 5713, AMS 5800, AMS 5712, GE C50T71

Rene 41 Chemical Composition

The Rene 41 composition defines the alloy’s strength, corrosion resistance, and temperature stability. This table shows the controlled range of each element.

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

Rene 41 Mechanical Properties

These values highlight tensile strength, yield strength, hardness and elongation at different temperatures.

Mechanical Properties	21°C	427°C	538°C	649°C	760°C	871°C	982°C
Ultimate Tensile Strength (MPa)	1261.7	–	–	1117	1048	710.2	–
0.2% Yield Strength (MPa)	820.5	–	–	765.3	751.5	579.2	–
Elongation (%)	21	–	–	14	14	11	–
Coefficient of Thermal Expansion (µm/m°C)	13.3	13.7	14.3	15.1	15.1	15.5	16.7
Thermal Conductivity (kcal/hr·m·°C)	14.4	16.1	17.9	19.6	19.6	21.4	–
Modulus of Elasticity (×10⁵ MPa)	–	2	1.93	1.79	1.72	1.65	1.52

Rene 41 Material Properties

This section lists physical properties such as density, melting range, resistivity, and thermal behavior to guide engineers in choosing the alloy.

Temperature		ksi x 10(3)	MPa x 10(3)
°F	°C	ksi x 10(3)	MPa x 10(3)
80 200 600 1000 1200 1400 1600	27 93 316 538 649 760 871	31.6 31.0 29.3 27.3 26.0 24.8 23.2	218 214 202 188 179 171 160