Alloy R-41 Forgings: Rene 41 / UNS N07041 / W.Nr 2.4973
Alloy R-41 is a vacuum-melted, gamma-prime precipitation-hardening nickel-base superalloy. Nominal composition is 19 Cr, 11 Co, 10 Mo, 3.1 Ti, 1.5 Al, balance nickel. It holds high strength from approximately 650 °C to 980 °C (1200 to 1800 °F). The alloy is also known as Rene 41, UNS N07041 and W.Nr 2.4973. Jiangyin Jiangnan Metal Co., Ltd. is an open-die forging factory in Jiangyin, Jiangsu Province, China. We produce Alloy R-41 as seamless rolled rings, forged discs, shafts, bars, flanges, sleeves and tube sheets to AMS 5712 and AMS 5713 chemistry, supplied solution treated or fully aged, with EN 10204 3.1 certification and 3.2 third-party witness on request. Ultrasonic testing is performed to EN 10228-3, SEP 1921 or ASTM A388. Quotations are returned within 24 hours.
Trademark notice. Rene 41® and the Rene alloy family are trademarks of the General Electric Company. Pyromet® is a registered trademark of Carpenter Technology Corporation. Haynes® is a registered trademark of Haynes International, Inc. Inconel® and Nimonic® are registered trademarks of Special Metals Corporation. Hastelloy® is a registered trademark of Haynes International, Inc. Material produced by those companies and sold under those brand names is theirs. Material we produce is correctly described as UNS N07041 / AMS 5712 / AMS 5713 / W.Nr 2.4973, the same generic chemistry manufactured independently by Jiangyin Jiangnan Metal Co., Ltd. We are not affiliated with, sponsored by, or endorsed by any of the trademark holders named. All other product names and trademarks are the property of their respective owners.
- UNS
- N07041
- W.Nr
- 2.4973
- Bar / forging spec
- AMS 57125713 vacuum melt
- Density
- 8.25g/cm³ (0.298 lb/in³)
- UTS aged, min
- 1420MPa (206 ksi)
- YS 0.2 %, min
- 1062MPa (154 ksi)
- Elongation, min
- 14%
- Service window
- 650 to 980°C (1200 to 1800 °F)
Alloy R-41 processing and service temperatures
Alloy R-41 is specified for load-bearing service between 650 °C and 980 °C. The forging window, solution temperature, ageing temperature and the band in which welds crack all fall on the same scale as the service temperature. The chart below plots them together.
The ageing temperature of 760 °C falls inside the service window, so gamma prime continues to develop during service. The same temperature falls inside the strain-age cracking band. A restrained weld heated through 650 to 870 °C precipitates gamma prime while residual stress is still present, and the joint can tear.
Multi-standard designation lookup
Drawings, mill certificates and OEM specifications often use different names for this alloy. Enter any of them to see the full set.
What is Alloy R-41 / Rene 41?
Alloy R-41 is a nickel-base superalloy strengthened by gamma-prime (γ′) precipitation. Chromium at 18 to 20 % provides oxidation resistance. Molybdenum at 9 to 10.5 % and cobalt at 10 to 12 % harden the austenitic nickel matrix in solid solution. Titanium at 3.0 to 3.3 % and aluminium at 1.4 to 1.8 % precipitate the ordered Ni₃(Al,Ti) γ′ phase during ageing. A boron addition of 0.003 to 0.010 % segregates to grain boundaries and controls creep-rupture life. The combination produces one of the strongest wrought superalloys available in forged form.
The alloy was developed by the General Electric Company and published as an ASM Alloy Digest data sheet in November 1958. It was used for the outer shell of the Mercury space capsule. It remains in production today for gas-turbine hot-section hardware operating above the useful range of Inconel 718.
Two characteristics govern how Alloy R-41 is specified and purchased.
- It is a high-temperature structural alloy, not a corrosion alloy. For acid or chloride service, Hastelloy C-276 or Alloy 625 is the correct selection. Alloy R-41 is specified when a component must carry stress at 700 to 980 °C.
- It is difficult to weld and difficult to machine. The same gamma prime that produces the strength also causes strain-age cracking in restrained weldments and makes the alloy work-harden rapidly under a cutting edge. Both must be addressed at the design stage. See the crack-risk checker.
Aluminium, titanium and boron are all reactive elements, so Alloy R-41 is vacuum melted. The normal routes are VIM + VAR (vacuum induction melting followed by vacuum arc remelting) and VIM + ESR (electroslag remelting). AMS 5713 requires vacuum-melted material. Air-melted stock is not accepted for aerospace hot-section components.
Alloy R-41, Rene 41, UNS N07041 and W.Nr 2.4973
The same chemistry appears under a dozen names depending on the specification body, the OEM and the age of the drawing. Jiangyin Jiangnan Metal Co., Ltd. accepts purchase orders written against any of them and supplies material certified as UNS N07041 / AMS 5712.
| Standard or body | Designation | Coverage |
|---|---|---|
| USA, trade name (GE) | Rene 41® | Original General Electric designation. A GE trademark. We supply the generic equivalents listed below. |
| USA, trade names (other) | Pyromet® Alloy 41, Haynes® R-41 | Producer brand names for the same chemistry. Trademarks of Carpenter Technology and Haynes International. |
| USA, UNS | UNS N07041 | Generic Unified Numbering System designation. Preferred wording on a purchase order. |
| Europe, Werkstoff | W.Nr 2.4973 | German and European material number |
| USA, AISI (legacy) | AISI 683 | Legacy designation found on older drawings |
| USA, SAE AMS | AMS 5712 | Bars, forgings, flash-welded rings and stock for forging. Primary specification for our products. |
| USA, SAE AMS | AMS 5713 | Bars, forgings and rings, vacuum melted. Specify where melt route must be controlled. |
| USA, SAE AMS | AMS 5545 | Sheet, strip and plate |
| USA, SAE AMS | AMS 5800 | Welding wire |
| USA, GE specifications | B50T59, B50TF76C, B50TF109C | B50T59 covers sheet, plate, strip, bars and forgings. B50TF109C covers solution-treated product. |
| UK, MSRR | MSRR 9500/241 | Welding wire |
| China, GB/T | GH4141 (GH141) | Chinese equivalent grade designation |
Chemical composition of Alloy R-41
The limits below are the AMS 5712 and AMS 5545 chemistry for UNS N07041, in weight percent, with nickel as the balance. Each heat is verified by optical emission spectrometry, with carbon and sulphur by combustion analysis. The full analysis is reported on the EN 10204 3.1 certificate.
| Element | Min | Max | Metallurgical function |
|---|---|---|---|
| Nickel (Ni) | Balance | Balance | Austenitic FCC matrix and host for the gamma-prime phase |
| Chromium (Cr) | 18.00 | 20.00 | Oxidation and hot-gas corrosion resistance through the Cr₂O₃ scale |
| Cobalt (Co) | 10.00 | 12.00 | Solid-solution strengthening, raises the gamma-prime solvus, improves thermal stability |
| Molybdenum (Mo) | 9.00 | 10.50 | Primary solid-solution strengthener and principal contributor to creep resistance |
| Titanium (Ti) | 3.00 | 3.30 | Gamma-prime former. With Al, sets the volume fraction of Ni₃(Al,Ti). |
| Aluminium (Al) | 1.40 | 1.80 | Gamma-prime former and secondary oxidation aid |
| Boron (B) | 0.003 | 0.010 | Grain-boundary segregant with a large effect on creep-rupture life |
| Carbon (C) | 0.06 | 0.12 | Forms MC and M₂₃C₆ carbides that pin grain boundaries. The narrow window balances creep life against weldability. |
| Iron (Fe) | — | 5.00 | Residual from raw material |
| Manganese (Mn) | — | 0.10 | Residual |
| Silicon (Si) | — | 0.50 | Residual deoxidiser |
| Copper (Cu) | — | 0.50 | Residual |
| Sulphur (S) | — | 0.015 | Impurity. Embrittles grain boundaries at temperature. |
Combined aluminium and titanium
Combined Al + Ti of approximately 4.4 to 5.1 % sets the gamma-prime volume fraction, and with it both the strength and the strain-age cracking sensitivity. At the upper end the alloy is stronger and harder to weld. At the lower end creep-rupture life falls. These two values are the most significant pair on an R-41 mill certificate.
Boron control
Boron is present at only 0.003 to 0.010 % but controls grain-boundary cohesion under creep. Below the minimum, rupture life falls sharply. Above the maximum, incipient melting during solution treatment becomes a risk. Boron should be requested explicitly on the certificate.
Mechanical properties of Alloy R-41 forgings
Properties depend on the heat-treatment route. The table gives specified room-temperature minima in the standard solution-treated and aged condition, together with typical as-annealed values that govern machining and forming.
| Condition | Tensile strength | Yield strength, 0.2 % | Elongation | Hardness |
|---|---|---|---|---|
| Solution treated and aged 1065 to 1080 °C AC, then 760 °C / 16 h AC |
1420 MPa min 206 ksi min |
1062 MPa min 154 ksi min |
14 % min | approx. 35 to 40 HRC |
| Solution annealed, unaged supply condition for machining and forming |
830 to 1100 MPa 120 to 160 ksi typical |
Reported on certificate | High | 363 HB max |
| Cold worked and aged wire and spring product |
1380 to 1550 MPa 200 to 225 ksi typical |
Reported on certificate | Reduced | — |
Strength at temperature
Room-temperature strength is not the reason Alloy R-41 is specified. Useful strength is retained to 980 °C. Between approximately 650 °C and 870 °C the design limit is tensile strength and low-cycle fatigue. Above 870 °C the limit becomes creep-rupture, and the heat treatment should change accordingly. See Route 2. Certified elevated-temperature tensile and stress-rupture data for the delivered heat are issued with the material certificate. State the design temperature and hold time at enquiry stage and we will confirm before the drawing is released.
Alloy R-41 physical properties
| Property | Metric | Imperial | Notes |
|---|---|---|---|
| Density | 8.25 g/cm³ | 0.298 lb/in³ | Used by the weight calculator |
| Melting range | 1316 to 1371 °C | 2400 to 2500 °F | Solidus to liquidus |
| Modulus of elasticity, E | 218 GPa | 31.6 × 10³ ksi | At 20 °C. Falls with temperature. |
| Modulus of rigidity, G | 83.4 GPa | 12.1 × 10³ ksi | At 20 °C |
| Coefficient of thermal expansion | 12.6 µm/m·°C | 7.0 µin/in·°F | 20 to 300 °C / 70 to 600 °F |
| Thermal conductivity | approx. 9.0 W/m·K | 62 Btu·in/ft²·h·°F | Low, typical of nickel superalloys. Relevant to machining heat and weld chill design. |
| Electrical resistivity | 131 µΩ·cm | 51.5 µΩ·in | High. Relevant to resistance welding parameters. |
| Magnetic response | Non-magnetic at room temperature | Austenitic FCC matrix | |
| Useful strength range | 650 to 980 °C | 1200 to 1800 °F | Withstands jet combustion gases to approximately 982 °C |
Alloy R-41 heat treatment: two standard routes
Property variation in Alloy R-41 is largely determined by the solution temperature. A higher solution temperature dissolves more gamma prime and carbide, coarsens the grain, and increases creep-rupture strength and room-temperature ductility. A lower solution temperature keeps the grain fine and increases tensile strength. The two cannot be obtained together. The choice must be made before forging, because grain size is established on the press.
Route 1, maximum tensile strength
Solution: 1065 to 1080 °C (1950 to 1975 °F), hold,
air cool.
Age: 760 °C (1400 °F) for 16 h, air cool.
The default route. Produces the 1420 MPa and 1062 MPa minima in Table 3, with fine grain and high tensile and fatigue strength.
Applied to: bolting, fasteners, springs, shafts, structural rings, and components limited by tensile strength or low-cycle fatigue below approximately 870 °C.
Route 2, maximum creep-rupture life
Solution: high-temperature cycle, typically
approx. 1175 °C (2150 °F) for 4 h, air cool.
Age: approx. 900 °C (1650 °F) for 4 h, air cool.
Produces coarser grain, lower room-temperature tensile strength, and higher rupture life and ductility at temperature.
Applied to: turbine casings, combustion hardware, nozzle components and any part under sustained load above 870 °C for thousands of hours.
Alloy R-41 heat-treatment route selector
Returns a complete printable cycle for the heat-treatment vendor.
Cycles follow the two standard AMS 5712 and AMS 5545 practices. Soak time scales at approximately 30 minutes per 25 mm of ruling section above the base hold. Where the purchase order or customer specification defines a cycle, that cycle governs. Final properties should be confirmed on test coupons taken from the same heat and heat-treatment charge.
Alloy R-41 service temperature check
Returns a verdict, the governing failure mode and an alternative alloy where R-41 is unsuitable.
First-pass screening based on published temperature limits for UNS N07041. It does not replace a creep-rupture calculation against certified data for the delivered heat, and does not account for stress level, section, coatings or surface condition. Final material selection is the responsibility of a qualified materials engineer.
Forging of Alloy R-41 at Jiangyin Jiangnan Metal
Alloy R-41 has a narrow hot-working window and a high flow stress. It is forged hot, in small increments, with frequent reheats. A superalloy ring requires considerably more passes than the same ring in AISI 4140. Finishing too cold causes cracking. Finishing too hot coarsens the grain beyond specification. The practical window is approximately 1010 to 1175 °C, with start and finish temperatures set per part and confirmed against the governing AMS or customer specification.
Vacuum-melted billet
VIM + VAR or VIM + ESR ingot. Heat number traced. Chemistry verified by OES and combustion analysis before cutting.
Homogenise and cog
Ingot breakdown on the hydraulic press to reduce segregation and establish the wrought structure.
Forge or ring roll
Multi-blow open-die forging or radial-axial ring rolling within the hot-working window, with controlled reheats between passes.
Controlled cool
Cooling rate set by section size, grain-size target and the following solution cycle.
Rough machine
Stock removed before heat treatment so the solution cycle reaches the core and residual stress is released early.
Solution treat
Route 1 at 1065 to 1080 °C, or the Route 2 high-temperature cycle. Air cool. Charts recorded per charge.
Age
760 °C for 16 h, or the Route 2 cycle. Furnace uniformity surveyed and logged.
NDT, test, certify
UT to EN 10228-3, SEP 1921 or ASTM A388. PT, tensile and hardness testing. EN 10204 3.1 or 3.2 certification, marking and packing.
Grain size is set during forging
The solution temperature that controls grain size also controls the property set, so forging reduction and finish temperature must be planned against the intended heat-treatment route. State the route, or the property target, at enquiry stage.
Machining stock allowance
Alloy R-41 work-hardens rapidly. Generous and even stock on the rough forging protects the finishing operation from a hardened surface layer and from distortion during ageing. Stock allowance is agreed per part rather than taken from a carbon-steel default.
Production capability for Alloy R-41 forgings
Jiangyin Jiangnan Metal Co., Ltd. operates an open-die forging plant at Jiangyin, Jiangsu Province, with hydraulic presses, forging hammers and radial-axial ring-rolling mills, supported by in-house heat treatment, NDT and a mechanical testing laboratory. The figures below are plant maxima across all grades. Superalloy envelopes are narrower and are confirmed per enquiry.
| Group | Equipment | Capability |
|---|---|---|
| Forging, heavy | Free-die hydraulic press | Up to 5,000 t class |
| Forging, hammers | Open-die forging hammers | 1 t, 3 t, 5 t, 9 t |
| Ring rolling | Radial-axial seamless ring mills | 3 m and 6 m mills |
| Plant envelope, diameter | All grades | 80 to 6,000 mm |
| Plant envelope, length | All grades | 100 to 12,000 mm |
| Plant envelope, weight | All grades | 10 to 15,000 kg |
| Heat treatment | Solution and ageing furnaces with recorded charts | Annealing, normalising, solution treatment, ageing, quench and temper |
| Machining | Turning, boring, milling | Rough or finish machined to customer drawing |
| NDT | Ultrasonic, magnetic particle, liquid penetrant | EN 10228-3, SEP 1921, ASTM A388, EN ISO 3452 |
| Laboratory | Spectrometer, universal testing machine, impact tester, hardness tester, metallographic microscope | Chemistry, tensile, impact, hardness, grain size, macroetch |
Alloy R-41 product forms
All forms are produced from vacuum-melted UNS N07041 stock and can be supplied as forged, solution treated, or solution treated and aged, rough machined or finish machined to drawing.
- Seamless rolled rings
- Contoured rings
- Gear ring blanks
- Forged discs and pancakes
- Forged shafts and spindles
- Stepped shafts
- Round bars
- Flat bars and blocks
- Forged flanges
- Sleeves and bushings
- Hollow and trepanned cylinders
- Tube sheets
- Forged pipes and tubes
- Valve bodies, stems and seat rings
- Nozzles
- Wheels and hubs
- Near-net-shape forgings to drawing
Rolled rings
The most economical route for R-41 rings above approximately 200 mm outside diameter. Radial-axial rolling produces circumferential grain flow, which suits rotating and pressure-containing rings.
Discs and pancakes
Upset from billet on the press. Preferred where the bore is small relative to the outside diameter, or where a contoured profile would be wasteful to roll.
Bars and shafts
Cogged and drawn out on the press, then straightened and inspected. Supplied cut to length, centreless ground or rough turned.
Near-net-shape
Raw material cost is high and machining rates are low, so die-formed profile that removes machining stock has a shorter payback on R-41 than on steel grades.
Alloy R-41 forging weight calculator
Returns net weight at 8.25 g/cm³ plus a rough billet allowance.
Net weight uses the nominal R-41 density of 8.25 g/cm³. The billet allowance is an estimating aid. Actual input weight depends on geometry, tolerance, grain-flow requirement and test-coupon provision.
Applications for Alloy R-41 forgings
Alloy R-41 is specified where metal temperature exceeds the useful range of Inconel 718 and the component must still carry load. The following applications account for most R-41 enquiries.
Gas turbine hot section
Turbine casings, seal rings, nozzle and combustor hardware, spacer rings and structural rings in continuous service between 700 and 980 °C. Route 2 heat treatment where rupture life governs.
High-temperature bolting
Bolts, studs, nuts and clamping hardware required to retain preload at temperature. Route 1 heat treatment, tensile-limited design.
Missile and launch hardware
Structural components and hot structure where mass is critical and the thermal environment excludes steel.
Afterburner and exhaust
Afterburner rings, flame-holder hardware, exhaust and tailpipe structure exposed to combustion gas.
Rotating hardware
Turbine wheels, discs, spacers and shafts where fatigue and creep both govern.
Springs and retaining rings
Hot springs and retaining hardware required not to relax at temperature.
Industrial heat processing
Furnace fixtures, hot-die tooling and heat-treatment jigs cycling into the R-41 range where lower-cost heat-resisting grades creep out of tolerance.
Power generation
Industrial gas-turbine hot-section components and high-temperature fastening in energy plant.
Alloy R-41 compared with Inconel 718, Waspaloy, Haynes 282 and X-750
These five alloys cover most of the wrought gamma-prime and gamma-double-prime hardened superalloy market. Alloy R-41 sits at the high-strength, low-weldability end of the range.
| Alloy | UNS | Strengthening | Practical upper limit | Weldability | Typical selection basis |
|---|---|---|---|---|---|
| Alloy R-41 | N07041 | Gamma prime Ni₃(Al,Ti), high Al+Ti | approx. 980 °C | Difficult, strain-age cracking | Highest strength between 700 and 980 °C where welding is limited or avoidable |
| Inconel 718 | N07718 | Gamma double prime Ni₃Nb | approx. 650 °C | Good, slow gamma-double-prime kinetics | Below 650 °C, lower cost, weldable, easier to machine |
| Waspaloy class | N07001 | Gamma prime, moderate Al+Ti | approx. 870 °C | Moderate | Similar temperature range to R-41 with easier fabrication and lower peak tensile strength |
| Haynes 282 class | N07208 | Gamma prime, lower Al+Ti | approx. 900 °C | Good, developed to avoid strain-age cracking | R-41 class creep strength combined with a welded design |
| Inconel X-750 | N07750 | Gamma prime, low Al+Ti | approx. 700 °C | Moderate | Springs and lower-temperature hardware |
Alloy substitution finder
Compares a current specification against Alloy R-41 for a stated service temperature and driver.
Guidance based on published typical properties and general engineering practice. Substitution decisions must be verified by a qualified materials engineer against the actual stress, environment, hold time, joining method and certification requirements of the application.
Welding, machining and grinding Alloy R-41
Welding and strain-age cracking
Alloy R-41 is susceptible to strain-age cracking. During welding, or during the heating leg of a post-weld cycle, the weld and heat-affected zone pass through approximately 650 to 870 °C, where gamma prime precipitates rapidly. Precipitation hardens the material while residual welding stress is still present and relaxing. Where the material hardens faster than the stress can relax, the joint tears, usually in the heat-affected zone.
- Weld in the fully solution-treated condition. Aged material should not be welded.
- Select the process for low heat input and low restraint. Resistance and electron-beam welding carry the lowest risk. GTAW is workable with direct-current straight polarity, tight fit-up, and copper backing bars or water-cooled fixtures to extract heat rapidly.
- Re-solution treat after welding, heating and cooling as rapidly as practical through the 650 to 870 °C band, then age.
- Eliminate the joint where possible. A rolled ring or near-net forging that removes a circumferential weld removes the risk.
- Filler: matching wire to AMS 5800 or MSRR 9500/241.
Score a joint for strain-age cracking risk
Machining
Alloy R-41 machines as a strong gamma-prime superalloy: low speed, heavy positive feed, rigid setup, no dwell. Thermal conductivity is approximately 9 W/m·K, so cutting heat is not conducted away through the workpiece and instead loads the tool.
- Machine in the solution-annealed condition wherever the tolerance plan allows. Aged material at 35 to 40 HRC is substantially slower.
- Sharp, rigid, positive-rake carbide. Ceramics only for continuous cuts on rigid setups.
- Maintain positive feed contact at all times. The alloy work-hardens under a rubbing edge and the following pass must then cut through the hardened layer.
- Flood coolant, generous nose radii, minimal tool overhang, and scheduled tool changes.
- Allow for ageing distortion. Rough machine, heat treat, then finish machine.
Grinding and surface integrity
Abusive grinding on a gamma-prime superalloy leaves tensile residual stress and can burn the surface, both of which reduce fatigue life. For fatigue-critical components, specify the surface finish, the permitted grinding practice, and shot peening where appropriate, on the drawing.
Strain-age cracking risk checker
Scores a proposed R-41 weld on material condition, process, thickness, restraint and post-weld treatment.
A qualitative screening aid based on published guidance for strain-age cracking in gamma-prime hardened nickel alloys. It is not a welding procedure qualification. Production joints in R-41 must be qualified by procedure and operator testing to the applicable code before use.
Alloy R-41 failure modes and prevention
Strain-age cracking
Cause: gamma prime precipitates in the 650 to 870 °C band while welding residual stress is still present.
Location: heat-affected zone of restrained welds and re-welded repairs.
Prevention: weld solution-treated material, minimise restraint and heat input, heat rapidly through the band, re-solution treat then age. See the risk checker.
Overheating in service
Cause: metal temperature above approximately 980 °C, or extended holds above 870 °C with Route 1 heat treatment.
Location: hot-section hardware following a change in duty cycle.
Prevention: select Route 2 for creep-dominated service. Verify with the service temperature check.
Grain-size non-conformance
Cause: forging finished too hot, insufficient reduction, or a solution temperature that does not match the intended route.
Location: heavy sections where core and skin see different thermal histories.
Prevention: specify grain size on the drawing and require macroetch verification.
Incipient melting
Cause: solution temperature too close to the solidus, aggravated by boron at the top of the range or by segregation.
Location: Route 2 high-temperature solution cycles.
Prevention: surveyed furnaces with recorded charts, verified thermocouples, and metallographic checks on first-off parts.
Forging bursts and laps
Cause: working below the hot-working window, or excessive reduction in a single blow on a high-flow-stress alloy.
Location: internal bursts at the centre of heavy sections, surface laps on complex profiles.
Prevention: controlled reheats, incremental reduction, and ultrasonic acceptance to EN 10228-3 or ASTM A388.
Surface-initiated fatigue
Cause: abusive grinding or machining leaving tensile residual stress and a work-hardened, micro-cracked layer.
Location: fillets, bores and ground features on rotating hardware.
Prevention: specify surface finish and grinding practice, use generous radii, and consider shot peening on fatigue-critical surfaces.
Standards, testing and certification for Alloy R-41 forgings
Material specifications
- AMS 5712, bars, forgings, flash-welded rings, stock for forging
- AMS 5713, the same forms, vacuum melted
- AMS 5545, sheet, strip, plate
- AMS 5800 and MSRR 9500/241, welding wire
- GE B50T59, B50TF76C, B50TF109C, OEM specifications
- Customer and project specifications worked to as written
Testing and inspection
- Chemistry by optical emission spectrometry, C and S by combustion
- Tensile and hardness on coupons from the same heat and charge
- Ultrasonic testing to EN 10228-3, SEP 1921 or ASTM A388, acceptance class per order
- Liquid penetrant to EN ISO 3452 or ASTM E1417
- Grain size and macroetch where specified
- Heat-treatment charts recorded and retained per charge
- ISO 9001:2015
- EN 10204 3.1 standard
- EN 10204 3.2 on request
- TUV, BV, DNV, Lloyd's, ABS witness
- Heat-number traceability
- Customer-witnessed hold points
Mill-certificate chemistry checker
Checks a heat analysis element by element against the AMS 5712 limits and flags the Al + Ti balance.
Screening aid only. Acceptance of a heat is the responsibility of the purchaser against the specification revision in force at the contract date. A full certificate review covers melt route, heat treatment, mechanical results and NDT in addition to chemistry.
How to specify an Alloy R-41 forging order
- State the generic designation. UNS N07041 / AMS 5712, or AMS 5713 where vacuum melting must be stated on the certificate.
- Select the heat-treatment route. Route 1 for tensile-limited parts, Route 2 for creep-limited parts. See the route selector. State the cycle rather than "solution treated and aged".
- Specify the melt route. VIM + VAR or VIM + ESR, and whether the certificate must state it.
- Provide the drawing. Finished dimensions, tolerances, machining stock, surface finish and required grain-flow direction.
- Define NDT acceptance. Ultrasonic standard and class (EN 10228-3, SEP 1921 or ASTM A388) and penetrant requirements.
- Specify certification. EN 10204 3.1, or 3.2 naming the witness body.
- State quantity, delivery target, delivery term and destination.
Drawing callout template
The template below can be copied into the material box of a drawing and edited at the bracketed items.
Eight common errors on Alloy R-41 orders
- Specifying R-41 with no heat-treatment route. The two routes produce different material. Name the cycle.
- Ordering under the Rene 41® trade name. That name belongs to General Electric. Specify UNS N07041 / AMS 5712 so that any qualified producer can quote.
- Designing a restrained weld into an R-41 assembly. Check the joint with the crack-risk tool before the drawing is released.
- Copying a transposed ksi and MPa data sheet. Tensile is 206 ksi = 1420 MPa. Yield is 154 ksi = 1062 MPa.
- Applying a carbon-steel machining allowance. R-41 requires generous, even stock and a rough machine, heat treat, finish machine sequence.
- Omitting boron from the certificate requirement. It is present at 0.003 to 0.010 % and controls rupture life. Request it explicitly.
- Specifying R-41 for a corrosion problem. It is a high-temperature structural alloy. For wet corrosion, specify C-276 or 625.
- Raising 3.2 certification after the order. Third-party witness affects lead time and price and should be stated at enquiry.
Alloy R-41 RFQ generator
Produces a complete enquiry text that can be copied, emailed or sent by WhatsApp.
Glossary
- Alloy R-41, R41
- Generic short names for the nickel-base superalloy designated UNS N07041.
- Rene 41®
- Original General Electric trade name. A GE trademark. Generic equivalents are UNS N07041, AMS 5712, AMS 5713 and W.Nr 2.4973.
- UNS N07041
- Unified Numbering System designation. The neutral name for purchase orders and drawings.
- W.Nr 2.4973
- European material number for the same chemistry.
- GH4141
- Chinese grade designation for the equivalent alloy.
- AMS 5712, AMS 5713
- SAE aerospace specifications for R-41 bars, forgings and flash-welded rings. AMS 5713 covers vacuum-melted material.
- Gamma prime
- The ordered Ni₃(Al,Ti) precipitate responsible for the strength of Alloy R-41. Its volume fraction is set by aluminium and titanium content.
- Strain-age cracking
- Cracking that occurs when gamma prime precipitates during heating through approximately 650 to 870 °C while welding residual stress is still present.
- Solution treatment
- High-temperature soak that dissolves gamma prime and carbides and sets grain size, followed by air cooling. The temperature selected determines whether the part is optimised for tensile strength or creep-rupture life.
- Ageing
- Lower-temperature hold, typically 760 °C for 16 hours, that precipitates gamma prime and develops final properties.
- Creep-rupture life
- Time to failure under sustained load at temperature. Above approximately 870 °C this becomes the design limit for Alloy R-41.
- VIM + VAR, VIM + ESR
- Vacuum induction melting followed by vacuum arc remelting or electroslag remelting. Used for R-41 because Al, Ti and B are reactive.
- EN 10204 3.1, 3.2
- Inspection document types. 3.1 is issued by the manufacturer's independent inspection function. 3.2 is countersigned by a third party nominated by the purchaser.
- EN 10228-3, SEP 1921, ASTM A388
- Ultrasonic testing standards for forgings, each with its own acceptance classes.
- Open-die forging
- Hot working between flat or simple dies with repeated manipulation. Suited to large, low-volume, high-value parts such as superalloy rings, discs and shafts.
- Seamless rolled ring
- A ring produced by piercing a billet and rolling it radially and axially, giving circumferential grain flow without a weld.
Alloy R-41 / UNS N07041 frequently asked questions
What is Alloy R-41?
Alloy R-41 is a vacuum-melted, gamma-prime precipitation-hardening nickel-base superalloy containing nominally 19 % chromium, 11 % cobalt, 10 % molybdenum, 3.1 % titanium and 1.5 % aluminium with the balance nickel. It is designated UNS N07041 and W.Nr 2.4973. It retains high strength from approximately 650 °C to 980 °C (1200 to 1800 °F) and is used for jet-engine hot-section parts, turbine casings, afterburner hardware, high-temperature bolting and missile components.
Are Alloy R-41, Rene 41 and UNS N07041 the same material?
Yes. Rene 41 is the original General Electric trade name. Alloy R-41 and R41 are the common generic short forms. UNS N07041 is the Unified Numbering System designation and W.Nr 2.4973 is the European material number. AISI 683, GE B50T59 and the Chinese grade GH4141 refer to the same chemistry. Jiangyin Jiangnan Metal Co., Ltd. supplies the material as UNS N07041 / AMS 5712, not under the Rene 41® trademark.
What is the chemical composition of Alloy R-41?
Chromium 18.00 to 20.00 %, molybdenum 9.00 to 10.50 %, cobalt 10.00 to 12.00 %, titanium 3.00 to 3.30 %, aluminium 1.40 to 1.80 %, boron 0.003 to 0.010 %, carbon 0.06 to 0.12 %, iron 5.00 % max, manganese 0.10 % max, silicon 0.50 % max, sulphur 0.015 % max, copper 0.50 % max, balance nickel. See Table 2.
What are the mechanical properties of Alloy R-41 forgings?
In the standard solution-treated and aged condition the specified room-temperature minima are 1420 MPa (206 ksi) tensile strength, 1062 MPa (154 ksi) 0.2 % yield strength and 14 % elongation. Modulus of elasticity is approximately 218 GPa at 20 °C. Hardness in the solution-annealed condition is typically 363 HB maximum.
What heat treatment is used for Alloy R-41?
Two routes are standard. Route 1, for maximum tensile strength: solution treat at 1065 to 1080 °C and air cool, then age at 760 °C for 16 hours and air cool. Route 2, for maximum creep-rupture life above 870 °C: solution treat at a higher temperature near 1175 °C and age near 900 °C for 4 hours. A higher solution temperature raises creep-rupture strength and room-temperature ductility. A lower solution temperature raises tensile strength.
What is the maximum service temperature of Alloy R-41?
Alloy R-41 retains useful high strength from approximately 650 °C to 980 °C (1200 to 1800 °F) and resists jet combustion gases to approximately 982 °C. Above approximately 870 °C the design driver changes from tensile strength to creep-rupture life, and the higher-solution-temperature heat treatment should be used.
Which specifications does Alloy R-41 forging material meet?
AMS 5712 covers bars, forgings, flash-welded rings and stock for forging. AMS 5713 covers the same forms in the vacuum-melted condition. AMS 5545 covers sheet, strip and plate. AMS 5800 covers welding wire. GE specifications B50T59, B50TF76C and B50TF109C also apply, together with MSRR 9500/241 for welding wire.
Why is Alloy R-41 difficult to weld?
Alloy R-41 is susceptible to strain-age cracking. Its high aluminium plus titanium content causes gamma prime to precipitate rapidly while the weldment is still under residual stress during heating through approximately 650 to 870 °C. Weld in the fully solution-treated condition, keep restraint and heat input low, use chill bars or water-cooled fixtures, and after welding re-solution treat with rapid heating and cooling through the band before ageing. Resistance and electron-beam welding carry the lowest risk. A proposed joint can be scored with the crack-risk checker.
What forms of Alloy R-41 forgings can you supply?
Jiangyin Jiangnan Metal Co., Ltd. supplies seamless rolled rings, contoured rings, forged discs and pancakes, shafts and spindles, round bars, forged flanges, sleeves and bushings, tube sheets, blocks and near-net-shape forgings in Alloy R-41 / UNS N07041, rough machined or finish machined to drawing.
How is Alloy R-41 melted?
Because of the reactive aluminium, titanium and boron additions, Alloy R-41 is vacuum melted. The normal routes are VIM + VAR (vacuum induction melting followed by vacuum arc remelting) and VIM + ESR (electroslag remelting). AMS 5713 requires vacuum-melted material.
What is the density of Alloy R-41?
The density of Alloy R-41 / UNS N07041 is approximately 8.25 g/cm³ (0.298 lb/in³). Its melting range is approximately 1316 to 1371 °C. The weight calculator converts dimensions to kilograms.
How does Alloy R-41 compare with Inconel 718 and Waspaloy?
Inconel 718 is niobium-strengthened, easier to weld and machine, and loses strength above approximately 650 °C. Alloy R-41 is stronger than 718 above 700 °C and is specified where 718 is outside its thermal range. Waspaloy occupies a similar temperature range with better weldability and lower peak tensile strength. Haynes 282 was developed to provide R-41 class creep strength while avoiding strain-age cracking. See Table 6.
Do you supply EN 10204 3.1 or 3.2 certificates for Alloy R-41 forgings?
Yes. EN 10204 3.1 mill certificates are standard on every order. EN 10204 3.2 certificates witnessed by a client-nominated third party such as TUV, BV, DNV, Lloyd's Register or ABS are available on request. Ultrasonic testing is reported to EN 10228-3, SEP 1921 or ASTM A388 as specified.
What information do you need to quote an Alloy R-41 forging?
Send the drawing or the finished dimensions, quantity, required specification (AMS 5712, AMS 5713 or a customer specification), the delivery condition (as forged, solution treated, or solution treated and aged), NDT and certificate requirements, and the destination port. Jiangyin Jiangnan Metal Co., Ltd. replies with price and lead time within 24 hours. The RFQ generator assembles this information.
Where is your Alloy R-41 forging factory located?
Jiangyin Jiangnan Metal Co., Ltd. is an open-die forging factory at No.1 Chengxiqiao Road, Zhouzhuang Town, Jiangyin City, Jiangsu Province, China. Telephone 0086-189-2135-9659, email sales@steelforgepieces.com. The plant exports forgings to more than 40 countries.
Technical references
Composition, property, specification and heat-treatment data on this page are taken from the published standards and engineering references below. Test results reported on our material certificates are independent and traceable to calibrated laboratory equipment.
- SAE AMS 5712, Alloy, Corrosion and Heat-Resistant, Bars, Forgings, Flash Welded Rings and Stock for Forging, 52Ni-19Cr-11Co-10Mo-3.1Ti-1.5Al, SAE International.
- SAE AMS 5713, Alloy, Corrosion and Heat-Resistant, Bars, Forgings and Rings, Vacuum Melted, 52Ni-19Cr-11Co-10Mo-3.1Ti-1.5Al, SAE International.
- SAE AMS 5545, Alloy, Corrosion and Heat-Resistant, Sheet, Strip and Plate, 52Ni-19Cr-11Co-10Mo-3.1Ti-1.5Al, SAE International.
- SAE AMS 5800, Alloy Welding Wire, 52Ni-19Cr-11Co-10Mo-3.1Ti-1.5Al, SAE International.
- ASM Alloy Digest Ni-47, G-E Alloy Rene 41, Heat and Corrosion Resisting Alloy, ASM International, published November 1958, revised January 1963.
- ASM Handbook, Volume 1, Properties and Selection: Irons, Steels and High-Performance Alloys, ASM International, section on wrought heat-resistant superalloys.
- ASM Handbook, Volume 14A, Metalworking: Bulk Forming, ASM International, forging of nickel-base superalloys.
- ASM Handbook, Volume 6, Welding, Brazing and Soldering, ASM International, strain-age cracking in precipitation-hardened nickel alloys.
- EN 10204:2004, Metallic products, types of inspection documents, CEN.
- EN 10228-3, Non-destructive testing of steel forgings, Part 3, Ultrasonic testing of ferritic or martensitic steel forgings, CEN.
- SEP 1921, Ultrasonic testing of steel forgings, Stahl-Eisen-Pruefblatt.
- ASTM A388/A388M, Standard Practice for Ultrasonic Examination of Steel Forgings, ASTM International.
- EN ISO 3452, Non-destructive testing, penetrant testing, ISO and CEN.
- General Electric specifications B50T59, B50TF76C and B50TF109C. MSRR 9500/241.
Standards are cited by designation. Material should be procured against the revision in force at the contract date. All trademarks are the property of their respective owners.
Request a quote for Alloy R-41 / UNS N07041 forgings
Send the drawing or the finished dimensions together with the heat-treatment route, NDT and certificate requirements. We confirm what is achievable in Alloy R-41, quote price and lead time, and reply within 24 hours. Where the specification is still open, state the service temperature and the load and we will advise whether Alloy R-41 is the appropriate selection.
Jiangyin Jiangnan Metal Co., Ltd., open-die forging factory
No.1 Chengxiqiao Road, Zhouzhuang Town, Jiangyin City, Jiangsu Province, China
Tel 0086-189-2135-9659
Email sales@steelforgepieces.com