CoCr20W15Ni Forgings: UNS R30605 / W.Nr. 2.4964 / L-605 Cobalt Superalloy

Published: 12 May 2022  |  Last updated: 16 August 2026  |  Technically reviewed by the Jiangyin Jiangnan Metal Co., Ltd. Metallurgical Engineering Team

Jiangyin Jiangnan Metal Co., Ltd. is an independent open-die forging factory in Jiangyin, Jiangsu Province, China, producing CoCr20W15Ni / UNS R30605 / W.Nr. 2.4964 / GH5605, the generic cobalt-chromium-tungsten-nickel chemistry behind the Haynes® 25, L-605 and Stellite® 25 names, in solution-annealed condition to AMS 5759, ASTM F90, ISO 5832-5 or GB/T 14992. Our specialisation in this grade is seamless rolled rings and forged discs for gas-turbine hot sections, plus valve seat rings, sleeves and bushings for erosive and sour service. Material is melted by VIM + ESR or VIM + ESR + VAR, ultrasonically tested to EN 10228-3, SEP 1921 or ASTM A388, and released with EN 10204 3.1 certification as standard or 3.2 third-party witness on request.

What forged products are available in CoCr20W15Ni / UNS R30605?

Jiangyin Jiangnan Metal Co., Ltd. manufactures CoCr20W15Ni forgings by three routes, chosen by geometry and quantity. Seamless ring rolling is the dominant route for this grade and produces combustor rings, casing rings, valve seat rings and bearing races. The radial-axial mill delivers continuous circumferential grain flow, which is what gives a cobalt-alloy ring its hoop strength and thermal-fatigue life. Open-die forging covers shafts, discs, sleeves, blocks and tube sheets, and is used wherever the part is too large or too low-volume to justify tooling. Upset forging is reserved for short, large-cross-section hubs and flange blanks. Closed-die tooling is available for repeat production but is rarely economic below a few hundred pieces in a cobalt alloy, because die wear at the 1150–1220 °C working temperature is severe.

Because CoCr20W15Ni has roughly twice the hot flow stress of austenitic stainless steel and a narrow working window, the practical size envelope for this grade is smaller than our steel capability. Near-net-shape forging is worth pursuing here more than in any other grade we run: at cobalt raw-material prices, removing 30–40 % of the machining stock at the forge usually saves more than the extra forging operations cost.

What is CoCr20W15Ni?

CoCr20W15Ni is a wrought, solid-solution-strengthened cobalt-base superalloy containing nominally 20 % chromium, 15 % tungsten and 10 % nickel, with cobalt making up the balance at roughly 49–53 %. The name is the European convention read literally: cobalt base, 20 % Cr, 15 % W, plus nickel. Its European material number is W.Nr. 2.4964; in the United States the same alloy is UNS R30605, universally known in industry as L-605 or Alloy 25.

Each element does a specific job. Tungsten is the strengthener, a large, slow-diffusing atom that distorts the cobalt lattice and resists dislocation motion at temperature, which is why L-605 keeps useful strength where precipitation-hardened alloys have already softened. Chromium forms the protective Cr₂O₃ scale that gives oxidation and sulphidation resistance. Nickel stabilises the face-centred-cubic matrix so the alloy does not transform to the brittle hexagonal form on cooling, and makes it forgeable and weldable at all. Carbon at 0.05–0.15 % forms M₆C and M₂₃C₆ carbides that pin grain boundaries during hot work.

The alloy was developed in the late 1940s by Haynes Stellite as a wrought version of the cast Stellite hardfacing family, keeping the cobalt-chromium-tungsten backbone but cutting the carbon far enough to eliminate the brittle primary carbide network and make the material forgeable. It became the standard combustor and afterburner material on first-generation military jet engines, and because it has been in service for seventy-five years it is one of the best-characterised superalloys in existence, with published data across a wider range of conditions than most modern alloys can offer.

Three practical characteristics dominate how CoCr20W15Ni is used:

• It is not age hardenable. There is no solution-plus-age cycle and no H-condition. The only heat treatment is a solution anneal; any additional strength must come from cold work.
• It stays non-magnetic. The face-centred-cubic matrix is stable, so unlike austenitic stainless steel the alloy does not become magnetic after cold working, which is why it appears in instrument, sensor and implant specifications.
• It embrittles at intermediate temperature. Long exposure between roughly 650 and 1040 °C precipitates carbides and σ-type phases that cut room-temperature ductility dramatically. The part is still sound at temperature; the risk is cracking during shutdown handling, thermal cycling or repair welding.

Is CoCr20W15Ni a nickel alloy or a cobalt alloy?

It is a cobalt-base alloy. Cobalt is the balance element at roughly 49–53 %; the 9–11 % nickel is a deliberate but minor addition made to stabilise the austenitic matrix. Metallurgically CoCr20W15Ni belongs with Haynes 188, Stellite and MP35N, not with Inconel and Hastelloy.

This page sits in our Nickel & Cobalt Alloy section because that is where buyers look for it. The same engineers who specify Inconel 617 and Hastelloy X specify L-605, and most distributor catalogues group them together. The distinction matters commercially in two ways worth knowing before you write a purchase order. First, pricing follows the cobalt market, not nickel: cobalt is a by-product of copper and nickel mining with concentrated supply, so CoCr20W15Ni prices can move independently of, and far more sharply than, the LME nickel index that governs Inconel pricing. Second, export and conflict-minerals documentation differs. Cobalt-bearing alloys attract responsible-sourcing questions on some aerospace and medical supply chains that nickel alloys do not.

What is the UNS R30605 / 2.4964 / L-605 / GH5605 equivalent of CoCr20W15Ni?

CoCr20W15Ni appears under a dozen names depending on which body wrote the specification. Every designation in the table below refers to the identical Co-20Cr-15W-10Ni chemistry, and Jiangyin Jiangnan Metal Co., Ltd. accepts purchase orders under all of them, supplying material certified against whichever specification the order names.

What is the chemical composition of CoCr20W15Ni / UNS R30605?

The chemistry below is the ASTM F90 / AMS 5759 baseline, which is also the composition given in most mill datasheets for L-605 and Alloy 25. Cobalt is reported as the balance rather than as a range, so a certificate showing cobalt between about 49 and 53 % is normal and correct.

How do AMS 5759, ASTM F90, W.Nr. 2.4964 and GH5605 differ?

Most supplier pages present these four specifications as identical. They are not. The alloying elements are the same, but the tramp-element limits and the required test programme differ in ways that decide whether one heat can be released against several standards. This matters commercially: a heat melted to the European limits satisfies the American limits automatically, but not the other way round.

What are the mechanical properties of CoCr20W15Ni forgings?

CoCr20W15Ni is supplied solution annealed. The values below are the guaranteed minima for bars and forged pieces under the DIN 2.4964 requirement, the figures most European purchase orders reference, alongside the typical measured values our mill certificates actually report, which are substantially higher. Both are given because engineers size parts on the minima but troubleshoot on the typicals.

The wide gap between minimum and typical is characteristic of this alloy and is worth exploiting. Because the DIN minima date from a period when melting practice was less clean, modern VIM + ESR material comfortably exceeds them. If your design is limited by the 850 MPa minimum but the part would work at 950 MPa, specify a contractual tensile minimum above the standard value in the purchase order rather than changing alloy. We can commit to it and test to it, and it is far cheaper than moving to a precipitation-hardened grade.

How does CoCr20W15Ni behave at elevated temperature?

This is the reason the alloy exists. Below about 650 °C, CoCr20W15Ni loses strength slowly and predictably. Between 650 and 870 °C the tungsten in solid solution is still pinning dislocations effectively and the alloy outperforms every common solid-solution nickel alloy. Above 870 °C the curve falls steeply and the useful limit becomes creep, not tensile strength.

Note the ductility minimum around 760 °C, where elongation drops to about 30 % before recovering. That trough is caused by grain-boundary carbide precipitation and is exactly the temperature band where combustor hardware often runs. It is a reason to specify a controlled grain size rather than accepting whatever the forging produces.

What are the physical properties of CoCr20W15Ni?

How oxidation- and corrosion-resistant is CoCr20W15Ni?

The 20 % chromium forms a continuous, adherent Cr₂O₃ scale that protects the alloy in air and combustion gas to about 980 °C in continuous service and around 1095 °C intermittently. Above that, chromia becomes volatile as CrO₃ in flowing gas and the scale stops protecting.

Where CoCr20W15Ni genuinely beats the nickel alloys is sulphidation. Nickel forms a low-melting Ni-Ni₃S₂ eutectic at around 645 °C that destroys nickel alloys rapidly in sulphur-bearing atmospheres; cobalt has no equivalent weakness. This is why L-605 survives in dirty fuels, sour gas, waste incineration and coal-fired environments where Hastelloy X and Inconel 617 degrade. It also has genuinely good wear, galling and cavitation resistance, inherited from the Stellite hardfacing family, which is why it appears in valve seat rings and bushings rather than only in turbine parts.

Why does CoCr20W15Ni lose ductility in service?

This is the single most important thing to understand about the alloy, and the one most often missed. CoCr20W15Ni does not stay as ductile as it was delivered. Extended exposure between roughly 650 °C and 1040 °C precipitates M₂₃C₆ and M₆C carbides plus intermetallic Laves and σ-type phases on the grain boundaries. At temperature the part is unaffected, and the phases even add some creep strength. The damage shows up when it comes back to room temperature: elongation can fall from 55 % as-delivered to below 10 %, and Charpy energy can drop by three quarters.

The consequences are practical rather than theoretical:

• Handling and repair. A combustor ring that has run for a few thousand hours can crack during removal, straightening or transport, in a way the same part would have survived when new.
• Weld repair. Welding aged material without a prior full solution anneal is a common cause of heat-affected-zone cracking. Anneal first, then weld, then anneal again.
• Thermal-fatigue design. Life predictions based on as-delivered ductility will be optimistic. Use aged-condition ductility for any part that sees many start-stop cycles.
• It is reversible. A full solution anneal at 1177–1232 °C with rapid quench redissolves the phases and restores ductility. Overhaul programmes for turbine hardware routinely exploit this.

CoCr20W15Ni vs Haynes 188, Hastelloy X, Inconel 617 and Waspaloy

Superalloy selection is a set of trade-offs rather than a ranking. The table below places CoCr20W15Ni against the alloys it actually competes with in enquiries we receive.

CoCr20W15Ni for surgical implants: ASTM F90 and ISO 5832-5

The same chemistry is qualified as an implant material under ASTM F90 and ISO 5832-5, where it is usually just called Co-Cr-W-Ni or F90. It is chosen for excellent corrosion resistance in body fluid, high strength in the cold-worked condition, and the fact that it is non-magnetic, which matters for MRI compatibility.

Ordering implant-grade material is a different exercise from ordering turbine material, and the difference is documentation rather than chemistry:

CoCr20W15Ni failure modes and how to prevent them

How is CoCr20W15Ni heat treated?

There is only one heat treatment: solution annealing. CoCr20W15Ni contains no γ′-forming aluminium or titanium, so it cannot be age hardened and there is no H-condition, no ageing curve and no aged property table. Any strength above the annealed level must come from cold work.

The cooling rate is where most annealing failures happen. A thin ring quenches easily; a 200 mm-thick disc does not, and the core can spend long enough in the precipitation range to lose ductility even though the surface hardness passes. For heavy sections we quench directly from the furnace with agitation and take the test coupon from a location representative of the slowest-cooling region, not from the edge.

How is CoCr20W15Ni forged?

CoCr20W15Ni is forgeable but demanding. Its hot flow stress is roughly twice that of austenitic stainless steel at the same temperature, the working window is narrow, and it work-hardens fast enough that a press stroke which would be routine in steel can crack it.

Grain-size control deserves particular attention in this grade. Coarse grain does more than reduce fatigue life. It scatters ultrasound so badly that a legitimate indication can be lost in the noise, or clean material can be rejected for a signal that is only grain structure. If your part will be ultrasonically inspected to a tight acceptance class, specify the grain size in the purchase order and agree the ultrasonic acceptance criteria before manufacture, not after the first report.

Can CoCr20W15Ni be welded?

Yes, and it welds better than most superalloys. Gas tungsten arc (GTAW/TIG) is the usual process; gas metal arc, shielded metal arc, plasma, electron beam and resistance welding are all used successfully. Submerged arc welding is not recommended. The slow cooling under flux keeps the weld in the carbide-precipitation range too long.

How is CoCr20W15Ni machined?

CoCr20W15Ni is genuinely difficult to machine, at roughly 10–15 % of the machinability of free-machining B1112 steel, harder than Inconel 718 in the annealed state. It work-hardens aggressively, so any dwell, rubbing or light spring pass hardens the surface ahead of the tool and destroys the edge on the next contact. Low thermal conductivity concentrates the heat in the cutting zone rather than carrying it away in the chip.

Three rules matter more than parameter tables. Never dwell. Keep the tool moving with positive feed at all times; a stationary rotating tool creates a work-hardened glaze that the next pass has to fight through. Take a deeper cut than instinct suggests. Depth of cut must stay below the previously hardened layer, so light passes are counterproductive. A 2 mm cut works well where 0.3 mm will not. Flood coolant, generously. High-pressure through-tool delivery gives a substantial tool-life improvement over external flood.

CoCr20W15Ni production capability at Jiangyin Jiangnan Metal

Jiangyin Jiangnan Metal Co., Ltd. has operated as an integrated melting works and open-die forge at No.1 Chengxiqiao Road, Zhouzhuang Town, Jiangyin City, Jiangsu Province, China since 1997. The plant employs 460 people, including 9 senior engineers, 32 intermediate engineers and 140 technicians, and holds CCS, BV, DNV, LR and NK classification society approvals. Forgings ship to North America, Europe, the Middle East and Asia-Pacific.

Two facts about this plant matter for a cobalt superalloy order. The melt shop runs vacuum induction melting, vacuum arc remelting and protective-atmosphere electroslag remelting on site, so a CoCr20W15Ni ingot does not have to be bought in. And three high-temperature car-bottom furnaces are available for the solution treatment this alloy cannot be certified without.

The working envelope for CoCr20W15Ni is much smaller than the envelope for steel, and the limit is not the press. It is the solution-annealing furnace. A forging that cannot be solution treated in one piece cannot be certified to AMS 5759, ASTM F90 or ISO 5832-5 no matter what the press can squeeze. Every figure in the table below is traced to the equipment that sets it, so you can check it against your drawing before you enquire.

Rings larger than 1,300 mm outside diameter can be forged and rolled here, on mills that go to 6,000 mm, but they cannot be solution annealed here in one piece. If your part is above that size, say so at enquiry. We will either quote it with the solution treatment placed at an accredited outside furnace or tell you it is not a job for this plant. The general steel envelope, up to 6,000 mm diameter and 30 tonnes, is described on the open-die forging parts page.

Process route for a CoCr20W15Ni forging

Equipment used for CoCr20W15Ni production

Which standards and quality documents apply to CoCr20W15Ni forgings?

For CoCr20W15Ni orders at Jiangyin Jiangnan Metal Co., Ltd. the dominant specification is AMS 5759 for bars, forgings and rings, with W.Nr. 2.4964 named alongside it on European projects and ASTM F90 / ISO 5832-5 when the material is implant-destined. Chinese projects reference GH5605 under GB/T 14992.

How to specify a CoCr20W15Ni forging order

Cobalt superalloy orders go wrong in different places from steel orders. There is no H-condition to choose, but melt route, grain size and ultrasonic acceptance all need to be stated explicitly, and rarely are. The seven steps below cover what actually needs to be on the purchase order.

Ten mistakes engineers make when ordering CoCr20W15Ni

1. Asking for an aged or H-condition. CoCr20W15Ni is not age hardenable. A purchase order calling for “solution treated and aged” cannot be filled as written and will stall at order review. Specify solution annealed, or specify a cold-work level.
2. Ordering against a trademark. A line item reading only “Haynes 25” can strictly only be filled by Haynes International. Write UNS R30605 / CoCr20W15Ni per AMS 5759 and independent producers can quote it.
3. Ignoring intermediate-temperature embrittlement. Designing on as-delivered ductility for a part that will run thousands of hours at 700–900 °C is the most common technical error in this alloy. Use aged-condition ductility.
4. Sizing hot parts on tensile data. Above about 650 °C the limit is creep. Short-time tensile strength at 870 °C is around 325 MPa, but the stress for 10,000 hours' life there is roughly a tenth of that.
5. Leaving the ultrasonic acceptance class unstated. Cobalt alloys are ultrasonically noisy. Without an agreed class and grain-size requirement, disputes over indications after machining are close to inevitable.
6. Specifying magnetic particle inspection. The alloy is non-magnetic, so magnetic particle inspection does not work. Specify liquid penetrant instead.
7. Converting from a nickel alloy without redoing the weight. At 9.13 g/cm³ this alloy is 11 % heavier than Inconel 718. Rotating parts see proportionally higher centrifugal stress and every billet costs more than the volume suggests.
8. Assuming reducing-acid resistance. There is no molybdenum in CoCr20W15Ni. It is excellent against sulphidation and oxidation but poor in hydrochloric and sulphuric acid, which is Hastelloy C-276 or B-3 territory.
9. Allowing slow cooling after annealing. A heavy section that furnace-cools re-precipitates carbides through 1040–650 °C and arrives brittle even though the surface hardness passes. Require a rapid quench and a coupon from the slowest-cooling region.
10. Welding service-aged material without annealing. Repair welding an embrittled part is a reliable way to crack it. Solution anneal, then weld, then anneal again.

CoCr20W15Ni drawing callout template

Copy this into the material block of your drawing and edit the bracketed items. It eliminates most of the ambiguity that causes requests for clarification at quotation.

MATERIAL: CoCr20W15Ni / UNS R30605 / W.Nr. 2.4964
 per AMS 5759
 [add: ASTM F90 / ISO 5832-5 for implant use]
 [add: GB/T 14992 GH5605 for Chinese projects]

MELT ROUTE: VIM + ESR minimum
 [VIM + ESR + VAR for aerospace rotating / implant]

CONDITION: Solution annealed 1177-1232 C, rapid quench
 Hardness [<= 282 HB]

FORGING: Minimum reduction ratio 4:1
 Finish forging temperature not below 950 C
 Grain size ASTM E112 [5] or finer

NDE: UT per [EN 10228-3 / SEP 1921 / ASTM A388],
 acceptance class [__]
 PT per [ASTM E1417 / EN ISO 3452]
 NOTE: material is non-magnetic - MT not applicable

TESTING: Room-temperature tensile + hardness (mandatory)
 [Elevated-temperature tensile at ___ C]
 [Stress rupture ___ MPa / ___ C / ___ h]
 Test coupon from slowest-cooling section

CERT: EN 10204 3.1
 [3.2 witnessed by ______ ]
 Multi-designation certificate requested:
 CoCr20W15Ni / R30605 / 2.4964 / AMS 5759 / GH5605

SURFACE: Ra [__] um on sealing / bearing faces
MARKING: Heat number, designation, drawing number,
 low-stress stamped or vibro-etched on
 non-functional surface

Where is CoCr20W15Ni used?

Glossary of CoCr20W15Ni terms

CoCr20W15Ni

European composition-based designation for the cobalt-base alloy containing nominally 20 % chromium, 15 % tungsten and 10 % nickel. Material number W.Nr. 2.4964.

UNS R30605

American Unified Numbering System code for the identical chemistry. The safest single designation to write on a purchase order.

L-605 / Alloy 25

Common industrial names for the same alloy, in general use and not trademarked.

Haynes® 25

Registered trademark of Haynes International, Inc. for their production of this chemistry. Generic equivalents: UNS R30605, CoCr20W15Ni, AMS 5759.

Stellite® 25

Registered trademark of Kennametal Inc. The wrought L-605 chemistry originated as a low-carbon, forgeable derivative of the cast Stellite hardfacing family.

GH5605 / GH605

Chinese high-temperature alloy designation under GB/T 14992. Also written KC20WN.

AMS 5759

SAE aerospace specification covering bars, forgings and rings in this alloy, solution heat treated. The governing spec for most forged product.

AMS 5537

SAE aerospace specification for sheet, strip and plate in the same chemistry.

AMS 5796

SAE specification for matching welding wire.

ASTM F90

ASTM specification for wrought Co-20Cr-15W-10Ni alloy for surgical implant applications; adds cleanliness, grain size and traceability requirements.

ISO 5832-5

International standard for the same implant alloy, part of the ISO 5832 series covering metallic implant materials.

Solid-solution strengthening

Strengthening by dissolving large atoms, tungsten in this case, in the metal lattice so they obstruct dislocation motion. Unlike precipitation hardening it needs no ageing treatment and does not over-age in service.

Solution anneal

Heating to 1177–1232 °C to redissolve carbides and intermetallic phases, followed by rapid quenching to keep them in solution. The only heat treatment applied to this alloy.

Intermediate-temperature embrittlement

Loss of room-temperature ductility caused by carbide and intermetallic precipitation during long exposure at roughly 650–1040 °C. Reversible by re-annealing.

Larson-Miller parameter (LMP)

A time-temperature parameter, LMP = T(K) × (C + log₁₀ t), used to collapse creep-rupture data from many temperatures and durations onto one master curve. C ≈ 20 for this alloy.

Sulphidation

Attack by sulphur-bearing gases forming metal sulphides. Nickel alloys are vulnerable because of a low-melting Ni-Ni₃S₂ eutectic; cobalt alloys such as this one are not, which is their principal advantage.

Hot corrosion (type I / type II)

Accelerated attack under molten salt deposits. Type I occurs around 800–950 °C, type II around 700–800 °C. Deposit chemistry, usually sodium sulphate, matters more than the base alloy.

VIM + ESR

Vacuum induction melting followed by electroslag remelting, the standard melt route for this grade, giving controlled chemistry and low inclusion content.

EN 10204 3.1 / 3.2

Inspection document types. 3.1 is issued by the manufacturer's independent quality department; 3.2 is countersigned by an independent third party or the purchaser's representative.

Seamless rolled ring

A ring produced by piercing a forged billet and rolling it out on a radial-axial mill, giving continuous circumferential grain flow, mechanically superior to a ring cut from plate or welded from bar.

Frequently asked questions about CoCr20W15Ni / UNS R30605

Technical references

Chemistry, mechanical, physical, heat-treatment and corrosion data on this page are drawn from the published standards and engineering references listed below. Test results reported on our material certificates are independent measurements made on the material supplied.

1. AMS 5759, Alloy, Corrosion and Heat Resistant, Bars, Forgings, and Rings, 51Co – 20Cr – 15W – 10Ni, Solution Heat Treated, SAE International.
2. AMS 5537, Alloy, Corrosion and Heat Resistant, Sheet, Strip, and Plate, 51Co – 20Cr – 15W – 10Ni, Solution Heat Treated, SAE International.
3. AMS 5796, Alloy, Corrosion and Heat Resistant, Welding Wire, 51Co – 20Cr – 15W – 10Ni, SAE International.
4. ASTM F90, Standard Specification for Wrought Cobalt-20Chromium-15Tungsten-10Nickel Alloy for Surgical Implant Applications (UNS R30605), ASTM International.
5. ISO 5832-5, Implants for surgery. Metallic materials. Part 5: Wrought cobalt-chromium-tungsten-nickel alloy, International Organization for Standardization.
6. GB/T 14992, Designation and specification of high temperature alloys and intermetallic compound materials, Standardization Administration of China (GH5605 / GH605).
7. NACE MR0175 / ISO 15156-3, Petroleum and natural gas industries. Materials for use in H₂S-containing environments. Part 3: Cracking-resistant CRAs and other alloys.
8. EN 10204, Metallic products. Types of inspection documents, CEN.
9. EN 10228-3, Non-destructive testing of steel forgings. Part 3: Ultrasonic testing of ferritic or martensitic steel forgings, CEN; and SEP 1921, Stahl-Eisen-Prüfblatt, ultrasonic testing of forgings.
10. ASTM A388, Standard Practice for Ultrasonic Examination of Steel Forgings, ASTM International.
11. ASTM E112, Standard Test Methods for Determining Average Grain Size, ASTM International.
12. ASTM E1417, Standard Practice for Liquid Penetrant Testing, ASTM International.
13. ASM Handbook, Volume 1: Properties and Selection: Irons, Steels, and High-Performance Alloys, ASM International. Cobalt-base heat-resistant alloys.
14. ASM Specialty Handbook: Heat-Resistant Materials, J.R. Davis (ed.), ASM International. Wrought cobalt-base superalloys.
15. ASM Handbook, Volume 14A: Metalworking: Bulk Forming, ASM International. Forging of heat-resistant alloys.
16. ASM Handbook, Volume 16: Machining, ASM International. Machining of superalloys.
17. Sims, C.T., Stoloff, N.S. and Hagel, W.C. (eds.), Superalloys II, Wiley. Cobalt-base alloys and solid-solution strengthening.
18. Donachie, M.J. and Donachie, S.J., Superalloys: A Technical Guide, 2nd edition, ASM International.

Standards are referenced by number without revision, since revisions change; for procurement, always cite the revision in force at contract date. Values quoted are typical published data for the alloy class and are given for engineering guidance. They are not a warranty of the properties of any particular delivery. All trademarks are the property of their respective owners.