Name: Rene 41
Brand: Rene

Material Overview

Rene 41 material profile

A concise grade introduction for buyers who need to confirm composition, properties, standards, available forms and suitable applications before sending an inquiry.

Engineering profile

Rene 41 is a vacuum-melted, precipitation-hardenable nickel-chromium-cobalt-molybdenum superalloy that develops exceptional tensile, creep and stress-rupture strength through gamma-prime precipitation. It retains useful strength and oxidation resistance at approximately 649-982 °C and is commonly selected for gas-turbine afterburner parts, nozzle diaphragms, combustion-system components, turbine wheels, rings, bolting, springs, missile hardware and other highly stressed aerospace components.

Technical data on this page is for material selection reference. Final acceptance values should be confirmed by the purchase standard, heat treatment condition, product form, size and material test certificate.

Chemical Composition

Rene 41 composition range

The following table shows common limiting composition values for Alloy 625 / UNS N06625. Actual product chemistry is reported by heat on the material test certificate.

Element	Symbol	Typical Requirement, wt.%	Role in Rene 41
Nickel	Ni	Balance	Forms the austenitic matrix and supports corrosion and high-temperature stability.
Chromium	Cr	18.0-20.0	Provides oxidation and hot-gas corrosion resistance.
Cobalt	Co	10.0-12.0	Improves matrix strength and high-temperature phase stability.
Molybdenum	Mo	9.0-10.5	Provides strong solid-solution strengthening and creep resistance.
Titanium	Ti	3.00-3.30	Promotes formation of the strengthening gamma-prime phase.
Aluminum	Al	1.40-1.80	Combines with nickel and titanium to produce gamma-prime precipitation.
Iron	Fe	5.0 max	Controlled residual element within the nickel-base matrix.
Carbon	C	0.12 max	Supports carbide formation and grain-boundary strength.
Boron	B	0.003-0.010	Improves grain-boundary strength and stress-rupture performance.
Manganese	Mn	0.10 max	Controlled minor element.
Silicon	Si	0.50 max	Controlled to maintain phase stability and processing performance.
Sulfur	S	0.015 max	Restricted impurity for hot workability and weld quality.
Copper	Cu	0.50 max	Controlled residual element.
Zirconium	Zr	0.07 max	Controlled microalloying element affecting grain-boundary behavior.

Physical Properties

Key physical and thermal data

These values help customers compare density, thermal behavior, magnetic response and conductivity during early material selection.

Property	Metric Value	Imperial / Additional Value	Condition
Density	8.25 g/cm3	0.298 lb/in3	Room temperature
Melting Range	1232-1391 °C	2250-2535 °F	Typical range
Specific Heat	452 J/kg·°C	0.108 Btu/lb·°F	Average from approximately 21-316 °C
Electrical Resistivity	127 µΩ·cm	50.0 µΩ·in	Approximately 0 °C; condition dependent
Modulus of Elasticity	218 GPa	31.6 x 10³ ksi	Approximately 21 °C
Modulus of Rigidity	83.4 GPa	12.1 x 10³ ksi	Approximately 21 °C
Magnetic Permeability	Less than 1.0022	Essentially non-magnetic	Approximately 21 °C at 200 oersted
Mean Coefficient of Thermal Expansion	13.5 x 10^-6 m/m·°C	21-538 °C	Temperature-averaged value
Mean Coefficient of Thermal Expansion	14.0 / 14.8 x 10^-6 m/m·°C	21-649 / 25-760 °C	Temperature-averaged values
Mean Coefficient of Thermal Expansion	15.7 / 16.8 x 10^-6 m/m·°C	25-871 / 25-982 °C	Temperature-averaged values
Thermal Conductivity	11.5 W/m·°C	80 Btu·in/ft2·h·°F	Approximately 149 °C
Thermal Conductivity	18.8 / 23.1 / 25.1 W/m·°C	At 538 / 760 / 871 °C	Temperature dependent

Mechanical Properties

Room-temperature mechanical properties

Mechanical properties vary with product form, size, processing route and heat treatment. The table below summarizes commonly referenced nominal values for material selection.

Test Temperature	Tensile Strength	Yield Strength, 0.2%	Elongation	Condition / Notes
Room temperature	Approximately 1260 MPa	Approximately 820 MPa	Approximately 21%	Representative heat-treated sheet; typically 33-40 HRC
649 °C	Approximately 1120 MPa	Approximately 765 MPa	Approximately 14%	Representative heat-treated sheet
760 °C	Approximately 1050 MPa	Approximately 750 MPa	Approximately 17%	Representative heat-treated sheet
871 °C	Approximately 710 MPa	Approximately 580 MPa	Approximately 11%	Representative heat-treated sheet
649 °C stress rupture	Approximately 738 MPa for 100 h; 621 MPa for 1000 h		Test dependent	Representative heat-treated sheet rupture strength
760 °C stress rupture	Approximately 434 MPa for 100 h; 296 MPa for 1000 h		Test dependent	Representative heat-treated sheet rupture strength
871 °C stress rupture	Approximately 159 MPa for 100 h; 90 MPa for 1000 h		Test dependent	Representative heat-treated sheet rupture strength
Values are typical rather than guaranteed. Properties vary significantly with product form, section size, solution temperature, cooling rate, aging treatment and testing direction.

For pressure equipment, aerospace parts or project-specific acceptance, use the minimum requirements in the specified ASTM, ASME, AMS, EN or customer drawing rather than nominal values.

Standards & Specifications

Common Rene 41 standards by product form

YSN128 can quote Alloy 625 products according to ASTM, ASME, AMS, EN, DIN, ISO or customer drawing requirements. Certificate scope can be matched to the purchase order.

Product Form / Condition	Common Standard	Scope	Buyer Note
Sheet, Plate and Strip	AMS 5545	Vacuum-melted flat products supplied in the solution heat-treated condition	Confirm thickness, heat treatment, grain requirements and current revision.
Bars, Forgings and Rings	AMS 5712	Vacuum-melted bar, forging, flash-welded ring and forging stock supplied solution treated	Final precipitation treatment may be performed after forming or machining.
Bars, Forgings and Rings	AMS 5713	Specified products supplied solution and precipitation heat treated	Confirm applicable size limits, required properties and heat-treatment certification.
Bare Welding Wire	AMS 5800	Vacuum induction melted and remelted matching-composition Rene 41 welding wire	Specify diameter, packaging, cleanliness and welding procedure qualification.
Investment Castings	AMS 5399	Vacuum-melted and vacuum-cast investment castings supplied solution treated	Castings require drawing-specific inspection and acceptance criteria.
Aerospace Design Data	MMPDS 6.3.7	Published aerospace material design information	Use only the current edition and the exact approved material condition.
Lower-Temperature Solution and Age	Approximately 1079 °C / 4 h / air cool + 760 °C / 16 h / air cool	Common route emphasizing tensile strength below approximately 927 °C	The applicable AMS or OEM specification controls the exact cycle and cooling requirements.
Higher-Temperature Solution and Age	Approximately 1177 °C / 4 h / air cool + 899 °C / 4 h / air cool	Common route used to improve ductility and stress-rupture performance	Heat treatment must be selected for product form, grain structure and design requirements.
OEM Specifications	GE B50T59, B50TF76, B50TF109 and drawing-specific requirements	Legacy and current aerospace engine components	Verify the exact OEM specification, revision and approved source before production.

Available Product Forms

Rene 41 supply range

Review available product forms, size ranges, standards and delivery options for this alloy.

Form	Common Size Range	Delivery Condition	Typical Applications	Page Link
Pipe & Tube	Seamless or welded sizes manufactured to drawing	Solution treated or heat treated to project requirements	Aerospace ducts, hot-gas systems and special fabricated assemblies	View Pipe & Tube
Round Bar	Small-diameter stock through large forged bar	Solution treated or solution and precipitation heat treated	Bolting, shafts, engine hardware and machined components	View Round Bar
Sheet & Plate	Thin sheet through drawing-based plate dimensions	Solution heat treated, descaled, pickled or cut to size	Afterburner parts, nozzle diaphragms and combustion-system components	View Sheet & Plate
Strip & Foil	Precision foil and slit strip in custom widths	Cold rolled, solution treated, bright or cleaned	Seals, springs, thermal shields and formed aerospace components	View Strip & Foil
Wire	Fine wire through heavy wire and heading stock	Cold drawn, solution treated or supplied for subsequent aging	Springs, fastener stock, mesh and precision hot-section parts	View Wire
Fasteners	Bolts, nuts, screws, studs and drawing-based aerospace hardware	Machined from qualified stock and aged to the specified condition	Gas turbines, missile systems and high-temperature structural joints	View Fasteners
Fittings	Elbows, tees, reducers and special drawing dimensions	Fabricated or machined to project-specific requirements	Hot-gas ducts and specialized aerospace fluid systems	View Fittings
Flanges	Forged rings and drawing-based machined flanges	Solution treated, aged, machined and inspected as specified	Turbine assemblies, hot-gas systems and aerospace connections	View Flanges
Forgings	Rings, discs, wheels, blocks and custom closed-die forgings	Solution treated or fully heat treated to AMS or OEM requirements	Turbine wheels, rings, engine parts and highly stressed hardware	View Forgings
Welding Wire	Standard and custom wire diameters, spool or straight length	Matching Rene 41 composition to AMS 5800	Qualified aerospace welding and component repair	View Welding Wire

Material Selection Guide

When to consider Rene 41

This guide helps buyers connect service conditions with the typical advantage of Alloy 625. Final selection should consider medium concentration, temperature, pressure, fabrication, availability and budget.

Alloy	Selection Strength	Typical Position	Selection Note
Rene 41	Exceptional tensile and stress-rupture strength through approximately 982 °C	Highly stressed turbine, afterburner, nozzle and aerospace hardware	Select when hot strength is critical and controlled fabrication is available.
HAYNES® 282®	Strong creep performance with substantially improved weldability and fabricability	Modern turbine, advanced boiler and high-temperature structural components	Often preferred for new fabricated designs where Rene 41 processing is difficult.
Waspaloy	Established high-temperature strength with broad turbine-component experience	Turbine discs, shafts, rings and engine hardware	Compare forging response, stress-rupture requirements and OEM approval.
Alloy 718	Good strength, excellent fabrication response and lower strain-age-cracking risk	Structural and rotating components at lower service temperatures	Usually preferred below approximately 650 °C when easier welding is important.
Alloy X-750	Useful precipitation-hardened strength with established spring and fastener service	Springs, fasteners, seals and moderately stressed hot components	Consider where Rene 41 strength is unnecessary and processing simplicity has priority.
HAYNES® 230®	Excellent oxidation resistance, thermal stability and sheet fabricability	Combustion, furnace and hot-gas containment components	Select for environmental resistance and fabrication rather than maximum aged strength.

Why Choose Us

Supply and quality support for Rene 41

For ranking traffic, buyers need more than a data sheet. This section gives clear trust signals for procurement, engineering and quality teams.

STASTM / ASME / AMS / EN

Quotation can be matched to project standards and product form specifications.

MTEN10204 3.1 MTC

Heat number, chemistry, mechanical properties and inspection records can be supplied.

QCPMI & Inspection

PMI, UT, dimensional inspection, visual inspection and packing check are available.

CSCustom Size

Cutting, machining allowance, rough machining and drawing-based supply can be arranged.

EPExport Packing

Wooden case, bundle, waterproof protection and international shipping documents.

RFFast Technical Reply

Send grade, size, standard, quantity and destination for a practical quotation route.

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FAQ

Rene 41 questions from buyers

Find practical answers about procurement, standards, fabrication and industrial applications.

Rene 41 is used for gas-turbine afterburner parts, nozzle diaphragms, turbine wheels, combustion-system components, rings, bolting, springs, missile hardware and other aerospace parts requiring high strength and oxidation resistance at elevated temperatures.

Yes. UNS N07041 is the standardized UNS designation for Rene 41. The alloy is also associated with W.Nr. 2.4973 and the legacy European designation NiCr19Co11Mo, but the exact specification and product condition should always be stated.

Rene 41 properties are developed by solution treatment followed by precipitation aging. A common lower-temperature route uses approximately 1079 °C for 4 hours followed by air cooling and 760 °C for 16 hours followed by air cooling. A higher-temperature route may use approximately 1177 °C for 4 hours followed by air cooling and 899 °C for 4 hours followed by air cooling. The applicable specification controls the exact cycle.

Rene 41 retains exceptional strength in the approximate range of 649-982 °C and provides oxidation resistance to about 982 °C in suitable environments. The actual design temperature depends on applied stress, exposure time, atmosphere, heat treatment and allowable design data.

We can quote sheet, plate, strip, foil, round bar, rod, wire, welding wire, rings, forgings, fasteners and drawing-based components. Pipe, tube, fittings and flanges require project-specific manufacturing and qualification because general-purpose commodity specifications are not normally available for these forms.

Common specifications include AMS 5545 for sheet and strip, AMS 5712 for solution-treated bars and forgings, AMS 5713 for solution and precipitation-treated bars and forgings, AMS 5800 for welding wire, AMS 5399 for investment castings and MMPDS 6.3.7 for aerospace design information.

Rene 41 can be welded, but it is sensitive to strain-age cracking. Welding should normally be performed in the fully solution-treated condition using a qualified low-restraint procedure and matching AMS 5800 filler where required. The assembly is commonly solution treated again and aged after welding, subject to the component specification.

Please send the grade or UNS number, product form, dimensions, quantity, applicable AMS or OEM specification, required heat treatment, mechanical properties, grain or ultrasonic requirements, certificate level, inspection plan and destination. Drawings are required for forgings, rings, fasteners and custom components.

Rene 41