Alloy 115 / Nimonic 115 Forgings: W.Nr. 2.4636 Nickel-Chromium-Cobalt Superalloy

Published: 20 May 2019 · Last updated: 11 August 2026 · Technically reviewed by the Jiangyin Jiangnan Metal Co., Ltd. Metallurgical Engineering Team · Property data verified against Special Metals publication SMC-094 and the specifications cited in Technical References.

What Forged Shapes Are Available in Alloy 115 / Nimonic 115?

Jiangyin Jiangnan Metal Co., Ltd. manufactures Alloy 115 by three routes, selected by geometry and quantity. Open-die forging is the primary route and covers discs, shafts, blocks, sleeves and blade blanks. Seamless ring rolling produces rings and flange blanks where a continuous circumferential grain flow is required. Upset forging is used for short, large-diameter discs and hubs.

Alloy 115 is one of the hardest wrought superalloys to forge. Its aluminium plus titanium content of about 9% puts roughly 55–60% of the microstructure into γ′ precipitate, which raises hot flow stress enormously and narrows the usable working window to roughly 100 °C. That is why the size envelope for this grade is far smaller than our general factory capacity, and why the number of reheats is planned before the billet is ever put in the furnace.

What Is Alloy 115 / Nimonic 115?

Alloy 115 is a precipitation-hardened nickel-chromium-cobalt superalloy, material number 2.4636, strengthened with additions of molybdenum, aluminium and titanium. It was developed as a creep-resisting alloy for service at temperatures up to about 1010 °C, as turbine blades for aircraft gas turbines. It is the strongest and the most highly alloyed member of the wrought Nimonic series.

The chemistry does three jobs at once. About 15% chromium provides oxidation resistance at temperature. About 14% cobalt raises the γ′ solvus so the strengthening phase survives hotter before it dissolves. And 3–5% molybdenum stiffens the nickel matrix by solid-solution strengthening. On top of that sit the two elements that define the alloy: 4.5–5.5% aluminium and 3.5–4.5% titanium, which precipitate Ni₃(Al,Ti), the γ′ phase, at a volume fraction of roughly 55–60%.

Two consequences follow from that chemistry, and they matter more than any single datasheet number:

• It is a blade-class alloy, not a disc alloy. The γ′ fraction that gives Alloy 115 its creep strength at 950–1010 °C is the same thing that makes it hard to forge into large sections. Disc alloys such as Waspaloy and Udimet 720 deliberately trade some γ′ away in exchange for forgeability and fatigue performance in thick sections.
• It is effectively not fusion weldable in load-bearing joints. With Al + Ti around 9%, Alloy 115 sits far inside the strain-age cracking region of the classic Al–Ti weldability diagram. Designs that would be welded in Inconel 718 must be made as one-piece forgings in Alloy 115.

Typical service is anywhere metal has to carry load in air above about 900 °C for thousands of hours: gas-turbine blades and blade rings, hot-section discs and spacer rings, high-performance reciprocating-engine exhaust valves, and hot-gas-path hardware in industrial turbines.

How Did Alloy 115 Develop? A Short Timeline

What Designations and Specifications Cover Alloy 115?

Alloy 115 is unusual among superalloys in that it has no widely used UNS number. Purchase orders that name only "Alloy 115" or "Nimonic 115" without a material number or specification are a common source of confusion between buyer, trader and forge shop. The unambiguous identifier is W.Nr. 2.4636.

What Is the Chemical Composition of Alloy 115?

The limits below are the nominal composition published by Special Metals in bulletin SMC-094. Every heat we forge is analysed by spectrometer and the result is reported on the mill test certificate against these limits.

What Are the Mechanical Properties of Alloy 115?

Typical room-temperature values for forged bar in the fully heat-treated condition, after 1½ h at 1190 °C air cooled plus 6 h at 1100 °C air cooled:

Strength is retained well at temperature, which is the whole point of the alloy, but the shape of the curve matters more than any single number. Tensile strength stays high to about 750 °C, then falls progressively as γ′ begins to coarsen and dissolve. Above roughly 900 °C the design-limiting property is no longer tensile strength at all but creep and stress rupture.

What Are the Physical and Thermal Properties of Alloy 115?

Dynamic Young's modulus from 20 °C to 1000 °C

Modulus falls by about 35% across the working temperature range. Any thermal-stress or bolt-preload calculation that uses the room-temperature figure at service temperature will be badly wrong.

Mean coefficient of linear thermal expansion

Why Is Alloy 115 So Strong at Temperature? The γ′ Story

Every property that makes Alloy 115 attractive, and every difficulty it presents in the workshop, traces back to one microstructural fact: roughly 55–60% of its volume is γ′ precipitate.

γ′ is an ordered intermetallic, Ni₃(Al,Ti), that forms coherently inside the nickel matrix. Dislocations cannot cut through it easily, and because it is ordered, the resistance it offers actually rises with temperature over part of the range instead of falling. That anomalous behaviour is why a γ′ alloy can hold load at 950 °C when a solid-solution alloy of similar cost cannot.

The amount of γ′ you get is set almost entirely by aluminium and titanium. Alloy 115 pushes both near the practical limit:

Read that table as a single trade-off curve. Moving down it buys forgeability, weldability and machinability; moving up it buys temperature capability. Alloy 115 sits at the top, which is exactly why it is specified, and exactly why it costs what it costs to make.

How Does Alloy 115 Behave in Creep and Stress Rupture?

Above about 800 °C, Alloy 115 components are not designed against tensile strength. They are designed against creep, which is slow permanent deformation under a stress far below the yield point, and against stress rupture, the time to failure at a given stress and temperature.

Special Metals publishes the stress-rupture behaviour of Alloy 115 forged bar as a Larson-Miller master curve rather than as a table, because temperature and time trade against each other along a single parameter:

That relationship is what lets a 100-hour rig test at 1000 °C stand in for a 10,000-hour service prediction at a lower temperature. The converter below does the arithmetic in both directions. To read an actual rupture stress off the curve you still need Figure 2 of Special Metals bulletin SMC-094. We do not reproduce the curve here, and you should be sceptical of any supplier page that quotes single-point creep numbers without stating the stress, the temperature, the time and the source together.

How Is Alloy 115 Forged and Heat Treated?

Alloy 115 is at the difficult end of everything a forge shop does. Three things drive the process route.

A hot-working window about 100 °C wide

Incipient melting begins at 1260 °C, which sets a hard ceiling. Below roughly 1100 °C, γ′ re-precipitates and hot flow stress climbs steeply: the press stalls, the surface tears, and the piece cracks rather than flows. The usable window is therefore narrow, in practice around 1100–1200 °C, and the metal cools out of it fast because the alloy's thermal conductivity is only 10.6 W/m·°C. A section that has been on the anvil for ninety seconds is often already too cold to keep working.

The practical consequences: dies are preheated, transfer times are counted in seconds rather than minutes, and the number of reheats is planned as part of the forging sequence rather than decided on the shop floor. Reduction per pass is deliberately kept modest, because the alloy will not tolerate the heavy bites that a carbon steel accepts.

Melt cleanliness is bought, not inspected in

The 0.0015% lead limit, the 0.015% sulphur limit and the 0.01–0.025% boron window cannot be corrected downstream. Alloy 115 is melted EAF + VOD followed by ESR for industrial work, or VIM + VAR where aerospace-level cleanliness and inclusion control are specified. VIM + VAR costs more and takes longer; it is the right answer for rotating aerospace parts and the wrong answer for a static industrial ring. Decide before the billet is bought, and state it on the purchase order. See the drawing callout template.

The heat treatment is fixed and short

Unlike alloys with a menu of ageing options, Alloy 115 has one published cycle for forged bar:

Note how close 1190 °C sits to the 1260 °C melting point. Furnace uniformity has to be held tight. We work to ±10 °C or better and record the charts, because an over-temperature excursion on a superalloy of this composition means incipient melting at the grain boundaries and a scrapped forging that no amount of reheat treatment will recover.

Our production sequence for Alloy 115 forgings

1. Billet procurement and verification. EAF + VOD + ESR, or VIM + VAR to order. Certificate reviewed against the 2.4636 limits, with particular attention to Pb, S, B and Zr, before the billet is accepted into the works.
2. Preheat and soak. slow, staged heating to avoid thermal shock in a low-conductivity alloy. Soak time scaled to section thickness.
3. Cogging and open-die forging. within the working window, dies preheated, reduction per pass controlled, reheats planned in advance.
4. Ring rolling. where a ring is required, the pierced blank is rolled to size giving continuous circumferential grain flow.
5. Solution treatment. 1½ h at 1190 °C, air cool. Furnace charts recorded and issued.
6. Ageing. 6 h at 1100 °C, air cool.
7. Rough machining. to your drawing, or to a surface suitable for volumetric inspection.
8. Non-destructive testing. ultrasonic testing to EN 10228-3, SEP 1921 or ASTM A388 at the acceptance class on your order; penetrant testing to ASTM E165 where specified. Magnetic particle testing does not apply, because the alloy is non-magnetic.
9. Testing and certification. chemistry, tensile, hardness, ASTM E112 grain size; EN 10204 3.1, or 3.2 with third-party witness.
10. Marking, packing and despatch. heat number, grade and item number hard-stamped or vibro-etched so the part stays traceable to its certificate.

Can Alloy 115 Be Welded? Strain-Age Cracking Explained

The short answer is no: not for load-bearing joints, and not without accepting real risk. Alloy 115 sits deep inside the "difficult to weld" region of the classic aluminium–titanium weldability diagram, further in than Udimet 700, Rene 41 or Waspaloy.

The failure mechanism is strain-age cracking. During welding, and again during any post-weld heat treatment, the heat-affected zone passes through the temperature band where γ′ precipitates rapidly. The material hardens while it is still contracting under restraint from the surrounding cold metal. Ductility collapses at exactly the moment the strain arrives, and the heat-affected zone tears, often days later, and often invisibly until the part is in service.

Al + Ti is the controlling variable, and it is why the diagram is drawn on those two axes. Inconel 718, at Al + Ti ≈ 1.4%, precipitates γ″ slowly enough that a weld can be completed and heat treated before hardening catches up; that is the entire reason 718 dominates fabricated aerospace hardware. Alloy 115, at Al + Ti ≈ 9%, has no such window.

How Do You Machine Alloy 115?

Alloy 115 machines like the γ′ superalloy it is: it work-hardens instantly, conducts almost no heat away from the cutting edge, and contains hard MC carbides that abrade tooling. The three rules that matter more than any speed table:

• Never dwell, never rub. A tool that stops cutting but stays in contact work-hardens the surface, and the next pass is then cutting a harder material than the one you programmed for. Feed continuously, and lift clear rather than pausing.
• Take a deeper cut than feels comfortable. The depth of cut must get under the work-hardened layer left by the previous pass. A succession of light finishing passes is the single most common way to ruin both surface finish and tool life.
• Flood coolant, at pressure, aimed at the edge. With thermal conductivity of 10.6 W/m·°C, heat that is not carried away by the chip and the coolant goes straight into the tool.

Rigidity in the setup, sharp positive-geometry tooling, and taking the material in the solution-treated condition where the sequence allows will all extend tool life. Where a feature is deep, narrow or otherwise unfriendly to a cutting tool, EDM is often faster and cheaper than fighting it.

When Should You Choose Alloy 115 Over Nimonic 105, Waspaloy, Udimet 720 or Inconel 718?

Alloy 115 is the right answer in a narrow band of duties and the wrong answer outside it. The comparison below is the one buyers actually need: not which alloy is "better", but what each one costs you in the workshop for what it buys you in service.

Production Capability as an Alloy 115 Forging Manufacturer

Jiangyin Jiangnan Metal Co., Ltd. has forged nickel-base superalloys since 2008 at No.1 Chengxiqiao Road, Zhouzhuang Town, Jiangyin City, Jiangsu Province, China. Alloy 115 is produced to order. There is no stock in this grade anywhere in the world, and any supplier offering immediate ex-stock delivery of a 2.4636 forging is almost certainly offering something else.

Alloy 115 size envelope

Which Standards and Quality Documents Apply?

What the certificate will show

• Heat number, melt route and full chemical analysis against the 2.4636 limits
• Heat-treatment cycle actually applied, with furnace chart reference
• Tensile strength, 0.2% proof stress, elongation, reduction of area and hardness
• ASTM E112 grain size where specified
• Ultrasonic and penetrant test reports naming the standard and acceptance class
• Dimensional report and marking record

How Do You Specify an Alloy 115 Forging Order?

Seven items. If all seven are on the enquiry, we can quote firmly and the part will be right the first time.

1. Grade, unambiguously. "Alloy 115 / Nimonic 115, W.Nr. 2.4636, to BS HR 4." The material number is what removes doubt, because there is no UNS number to fall back on.
2. Product form and dimensions. A drawing, or rough dimensions plus the machining allowance you expect. State whether you want as-forged, heat treated, rough machined or finish machined.
3. Melt route. EAF + VOD + ESR, or VIM + VAR. This is a cost and lead-time driver and must be agreed before the billet is bought.
4. Heat treatment. The standard cycle is 1½ h / 1190 °C / AC + 6 h / 1100 °C / AC. If your specification calls for something else, state it in writing.
5. Grain size and mechanical testing. ASTM E112 grain size, test temperature, and the location and orientation of the test pieces.
6. NDT standard and acceptance class. EN 10228-3, SEP 1921 or ASTM A388, plus the class. Add ASTM E165 penetrant testing if surface examination is required. Do not specify magnetic particle testing, because it does not work on a non-magnetic alloy.
7. Certification. EN 10204 3.1, or 3.2 with the named third party.

Top 10 Mistakes When Specifying Alloy 115 Forgings

1. Ordering "Nimonic 115" with no material number. Nimonic is a Special Metals trademark; a generic supplier cannot sell you branded material. Write Alloy 115 / W.Nr. 2.4636 and the specification.
2. Quoting DIN 17754. It appears on many supplier datasheets but is not among the designations Special Metals publishes for this alloy. Confirm what your drawing actually intends.
3. Specifying magnetic particle inspection. Alloy 115 is fully austenitic and non-magnetic. MT will find nothing. Specify penetrant testing to ASTM E165 instead.
4. Designing a weldment. At Al + Ti ≈ 9% this alloy is a strain-age cracking material. Redesign as a one-piece forging before the drawing is released, not after the first weld cracks.
5. Using Alloy 115 below 850 °C. You pay a large premium for creep strength the design never uses, and inherit forging, machining and inspection difficulty. Check whether Waspaloy or Nimonic 80A carries the duty.
6. Leaving the melt route unstated. EAF + VOD + ESR and VIM + VAR are different products at different prices with different lead times. An unstated melt route means you are comparing quotations that are not comparable.
7. Ignoring the tramp-element limits. The 0.0015% lead limit is real and is what stops this alloy being made from mixed scrap. Ask how the offered material controls Pb, S and Bi.
8. Using the room-temperature modulus in a hot design. E falls from 216 GPa at 20 °C to 156 GPa at 900 °C. Bolt preload and thermal-stress calculations must use the hot value.
9. Assuming ex-stock availability. Nobody stocks Alloy 115 forgings. Lead time is billet-driven; ask for the billet position with the quotation.
10. Specifying a finishing allowance that is too small. Machining this alloy is slow and hard on tooling; too little stock means a scrapped forging, and too much means paying for metal you will cut away. Agree the allowance with the forge shop rather than assuming a steel-part default.

Drawing Callout Template for Alloy 115 Forgings

Copy this into your material callout box

MATERIAL:   ALLOY 115 / NIMONIC 115 TYPE, W.Nr. 2.4636
            Chemistry per BS HR 4 (alt: AECMA prEN 2196 / 2197)
            Nominal 15Cr - 14Co - 4Mo - 5Al - 4Ti, balance Ni

MELT:       EAF + VOD + ESR          [alt: VIM + VAR]
            Pb 0.0015% max, S 0.015% max, B 0.010-0.025%

CONDITION:  Solution treated 1-1/2 h @ 1190 C, air cool
            + aged 6 h @ 1100 C, air cool
            Furnace uniformity +/-10 C, charts to be supplied

FORM:       Open-die forging / seamless rolled ring per drawing
            Machining allowance ___ mm per surface

TESTING:    Chemical analysis, full heat
            Tensile per ASTM E8 / ISO 6892 at ___ C
            Hardness; grain size per ASTM E112, ___ or finer
            UT per EN 10228-3 class ___  [alt: SEP 1921 / ASTM A388]
            PT per ASTM E165
            NOTE: material is non-magnetic - MT does not apply

CERT:       EN 10204 3.1   [alt: 3.2 witnessed by ___ ]

MARKING:    Heat number, grade and item number, hard stamped
            in a low-stress area

Where Is Alloy 115 Used?

Request a Quote for Alloy 115 / Nimonic 115 Forgings

Send a drawing or the dimensions, the governing specification, the melt route and your certification requirement, and Jiangyin Jiangnan Metal Co., Ltd. will reply within 24 hours with price, lead time, the billet position and confirmation of the applicable standards. For complex enquiries, use the RFQ generator above to produce a complete specification sheet first.

Frequently Asked Questions About Alloy 115 / Nimonic 115

Glossary

W.Nr. 2.4636

The Werkstoff material number for the nickel-chromium-cobalt superalloy commonly called Alloy 115 or Nimonic 115. Because the alloy has no widely used UNS number, 2.4636 is the correct unambiguous identifier for purchase orders and drawings.

γ′ (gamma prime)

The ordered intermetallic Ni₃(Al,Ti) that precipitates coherently inside the nickel matrix and provides the strength of this class of alloy. Alloy 115 contains roughly 55–60% γ′ by volume, among the highest of any wrought superalloy.

γ′ solvus

The temperature above which γ′ dissolves back into the matrix. It sets the lower bound of the practical hot-working window and determines whether a forging operation is subsolvus (fine grain) or supersolvus (coarse grain, better creep resistance).

Solution treatment

Heating above the γ′ solvus, 1190 °C for Alloy 115, to dissolve the strengthening phase and homogenise the structure, followed by cooling. The first of the two heat-treatment stages.

Ageing

Holding at an intermediate temperature, 6 hours at 1100 °C for Alloy 115, to re-precipitate γ′ in a controlled size and distribution. The second heat-treatment stage, and the one that sets creep performance.

Strain-age cracking

Cracking in the heat-affected zone of a weld in a γ′-strengthened alloy, caused by the material hardening through γ′ precipitation while it is still contracting under restraint. The dominant weldability limit for high Al + Ti alloys, and the reason Alloy 115 is not considered weldable for load-bearing joints.

Al + Ti

The sum of aluminium and titanium content, used as the primary index of both γ′ volume fraction and weldability. Alloy 115 sits at about 9%; Inconel 718, at about 1.4%, is readily weldable.

Creep

Slow, permanent deformation under a constant stress well below the yield strength, occurring at temperatures above roughly 40% of the absolute melting point. The design-limiting behaviour for Alloy 115 above about 800 °C.

Stress rupture

Failure under a sustained load at temperature after a measurable time. Reported as a combination of stress, temperature and time to rupture, and usually presented as a Larson-Miller master curve rather than a table.

Larson-Miller parameter (LMP)

LMP = T(C + log₁₀ t), with T in kelvin, t in hours and C typically 20 for this alloy. It collapses temperature and time onto a single axis so that stress-rupture data across many conditions falls on one master curve.

Incipient melting

Localised melting at grain boundaries that begins near the lower end of the melting range, 1260 °C for Alloy 115, well below the point at which the bulk material melts. It permanently ruins a forging and cannot be recovered by reheat treatment, which is why furnace uniformity is controlled so tightly at the 1190 °C solution temperature.

ESR (electroslag remelting)

A secondary melting process in which a consumable electrode is remelted through a molten slag layer, refining the structure, lowering sulphur and reducing segregation. The standard secondary route for industrial-grade Alloy 115 billet.

VIM + VAR

Vacuum induction melting followed by vacuum arc remelting. The cleanest common route for superalloy billet, giving tight control of gases, tramp elements and inclusions. Normally specified for rotating aerospace components.

Tramp elements

Low-level impurities such as lead, bismuth and selenium that segregate to grain boundaries and destroy stress-rupture life. The 0.0015% lead limit in Alloy 115 is what prevents the alloy being melted from mixed scrap.

EN 10204 3.1 / 3.2

Types of inspection document. A 3.1 certificate is issued by the manufacturer's own independent quality department; a 3.2 certificate is countersigned by an independent third party such as TÜV, SGS, BV, DNV or Lloyd's Register.

ASTM E112 grain size

The standard method for reporting average grain size. Worth specifying on any creep-critical forging, because grain size in a supersolvus-treated superalloy has a direct effect on creep and fatigue behaviour.

Technical References

1. Special Metals Corporation, Publication SMC-094, NIMONIC® alloy 115, September 2004. Source of the nominal chemical composition, density, melting range, specific heat, thermal conductivity, electrical resistivity, mean coefficient of linear thermal expansion, dynamic Young's modulus, heat-treatment cycle and the list of designations and specifications cited on this page.
2. BS HR 4, Nickel base alloy billet, bar, forgings and parts, British Standards Institution. The usual governing specification for Alloy 115 forgings.
3. AECMA prEN 2196 and prEN 2197, aerospace series specifications for nickel base alloy Ni-P102HT bar and forgings.
4. AICMA Ni-P102-HT and AFNOR NCK 15ATD, additional national and industry designations for the same alloy.
5. EN 10204, Metallic products: types of inspection documents, CEN, Brussels.
6. EN 10228-3, Non-destructive testing of steel forgings: ultrasonic testing, CEN, Brussels.
7. SEP 1921, Ultrasonic testing of steel forgings, Stahl-Eisen-Prüfblatt, Verein Deutscher Eisenhüttenleute.
8. ASTM A388/A388M, Standard Practice for Ultrasonic Examination of Steel Forgings, ASTM International, West Conshohocken, PA.
9. ASTM E165/E165M, Standard Practice for Liquid Penetrant Testing for General Industry, ASTM International.
10. ASTM E112, Standard Test Methods for Determining Average Grain Size, ASTM International.
11. ASTM E8/E8M and ISO 6892-1/-2, tensile testing of metallic materials at room and elevated temperature.
12. F.R. Larson and J. Miller, A Time-Temperature Relationship for Rupture and Creep Stresses, Transactions of the ASME, 1952. The origin of the Larson-Miller parameter used in the converter on this page.
13. ASM Handbook, Volume 1: Properties and Selection: Irons, Steels, and High-Performance Alloys, ASM International, Materials Park, OH. Sections on wrought heat-resistant superalloys, γ′ strengthening and weldability of precipitation-hardened nickel alloys.
14. R.C. Reed, The Superalloys: Fundamentals and Applications, Cambridge University Press, 2006. Background on γ′ volume fraction, solvus behaviour and hot-working windows referenced in the discussion sections of this page.

Jiangyin Jiangnan Metal Co., Ltd. "Alloy 115 / Nimonic 115
(W.Nr. 2.4636) Forgings - Technical Datasheet and Manufacturing
Guide." Jiangyin, Jiangsu, China. Updated 11 August 2026.
https://www.steelforgepieces.com/Nickel-Alloy/Alloy-115.html

Alloy 115, also known as Nimonic 115 and W.Nr. 2.4636, is a
precipitation-hardened nickel-chromium-cobalt superalloy
strengthened with molybdenum, aluminium and titanium. Nominal
composition is 14.0-16.0% Cr, 13.0-15.5% Co, 3.0-5.0% Mo,
4.5-5.5% Al, 3.5-4.5% Ti, 0.12-0.20% C, 0.01-0.025% B,
0.15% Zr max, balance nickel. It was developed as a
creep-resisting alloy for service to about 1010 degrees C, as
turbine blades for aircraft gas turbines. Aluminium plus
titanium is about 9%, giving roughly 55-60% gamma-prime volume
fraction; the alloy is therefore difficult to forge and is not
considered weldable for load-bearing joints because of
strain-age cracking. Density is 7.85 g/cm3, melting range
1260-1315 degrees C, specific heat 444 J/kg-C at 20 C, thermal
conductivity 10.6 W/m-C at 20 C, electrical resistivity
139 microhm-cm at 20 C. Dynamic Young's modulus falls from
216 GPa at 20 C to 141 GPa at 1000 C. Mean coefficient of
linear thermal expansion rises from 12.0 x 10-6/K over
20-100 C to 17.0 x 10-6/K over 20-1000 C. The heat treatment
is 1.5 h at 1190 degrees C air cooled plus 6 h at 1100
degrees C air cooled. There is no UNS number in common use;
order against W.Nr. 2.4636 with BS HR 4 or AECMA prEN 2196
and 2197.

Forgings in this grade -- seamless rolled rings, discs, shafts,
bars, flanges, sleeves and near-net parts to drawing -- are
manufactured by Jiangyin Jiangnan Metal Co., Ltd., an open-die
forging factory at No.1 Chengxiqiao Road, Zhouzhuang Town,
Jiangyin City, Jiangsu Province, China. Material is EAF+VOD+ESR
melted, or VIM+VAR on request, solution treated and aged,
ultrasonically tested to EN 10228-3, SEP 1921 or ASTM A388, and
supplied with EN 10204 3.1 or 3.2 certification.
Contact: +86-189-2135-9659, sales@steelforgepieces.com,
https://www.steelforgepieces.com/