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WO2025178553A1 - Alliage à base de nickel à résistance mécanique élevée - Google Patents

Alliage à base de nickel à résistance mécanique élevée

Info

Publication number
WO2025178553A1
WO2025178553A1 PCT/SE2025/050165 SE2025050165W WO2025178553A1 WO 2025178553 A1 WO2025178553 A1 WO 2025178553A1 SE 2025050165 W SE2025050165 W SE 2025050165W WO 2025178553 A1 WO2025178553 A1 WO 2025178553A1
Authority
WO
WIPO (PCT)
Prior art keywords
weight
nickel
based alloy
hours
content
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
PCT/SE2025/050165
Other languages
English (en)
Inventor
Patrick Conway
Christina HARALDSSON
Rohit OJHA
Guocai Chai
Ehsan GHASSEMALI
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Alleima Emea AB
Original Assignee
Alleima Emea AB
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alleima Emea AB filed Critical Alleima Emea AB
Publication of WO2025178553A1 publication Critical patent/WO2025178553A1/fr
Pending legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C30/00—Alloys containing less than 50% by weight of each constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/002—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working by rapid cooling or quenching; cooling agents used therefor
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon

Definitions

  • the present invention relates to a nickel-based alloy, a method of making a nickel-base alloy and an article including a nickel-base alloy.
  • Gamma double prime is a phase that occurs in nickel superalloys with significant additions of niobium or vanadium.
  • the y" phase has larger lattice parameters compared to the solid solution fee y’ phase, and the size, morphology and distribution of the y" precipitates are considered to induce a bit of strain in atomic level leading to a strengthening effect and contributing to the mechanical performance of some superalloys.
  • delta (6) is a metastable precipitate and has limited thermal stability up to about 649°C, after which it transforms into delta (6) phase.
  • Delta (6) is a Nb-rich phase with an ordered orthorhombic structure, is incoherent with the austenite matrix and appears as long needles at grain boundaries, twin boundaries, or within grains.
  • a small amount of delta phase is beneficial to control grain growth during solution annealing and ageing and can deliberately be precipitated during a heat treatment called “delta dump.” However, too much delta phase is detrimental and decreases the fracture toughness, strength, and creep resistance.
  • small secondary carbides precipitate and grow, which may increase hardness of the superalloy. Small secondary carbides are visible in SEM.
  • large blocky carbonitrides of Ti and Nb may be present in the microstructure, which can act as crack initiation sites and reduce fatigue performance. Under certain heat treatment conditions, these carbonitrides can precipitate as a grain boundary film that degrades ductility.
  • Alloy 718 (UNS N07718), developed in the 1950s, has been one of the most widely used nickel-based superalloys. Alloy 718 has high strength along with balanced creep and stress rupture properties up to about 649°C. While most high strength nickel-based superalloys derive their strength by the precipitation of y’ phase with aluminium and titanium being major strengthening elements, i.e. , Nis(AI ,Ti), Alloy 718 is strengthened mainly by y” phase (gamma double prime) with niobium, i.e. NisNb, being a major strengthening element and with a small amount of y’ phase playing a secondary strengthening role.
  • y gamma double prime
  • Alloy 718 Since the y” phase has a higher strengthening effect than y’ phase at the same volume fraction and particle size, Alloy 718 is generally stronger than most superalloys strengthened by y’ phase precipitation. In addition, y” phase precipitation in Alloy 718 results in good high temperature time-dependent mechanical properties such as creep and stress rupture properties. The processing characteristics of Alloy 718, such as castability, hot workability and weldability, are also good, thereby making fabrication of articles from Alloy 718 relatively easy. These processing characteristics are believed to be closely related to the lower precipitation temperature and the sluggish precipitation kinetics of the y” phase associated with Alloy 718.
  • Rene® 220 alloy is a nickel-based superalloy with the same processing advantages (castability, weldability, workability) as Alloy 718, but with temperature capabilities of up to 704°C.
  • Rene® 220 alloy is very expensive, at least partly because it contains more than 2 percent, typically 3 percent, of tantalum, which can be from 10 to 50 times the cost of cobalt and niobium.
  • Rene® 220 alloy has a relatively high 5 phase content, which decreases the fracture toughness, strength, and creep resistance.
  • Waspaloy® Another nickel-based superalloy, known as Waspaloy® (UNS N07001), is also widely used for aerospace and gas turbine engine components.
  • Waspaloy® has useful strength and good oxidation resistance in gas turbine engine atmospheres up to 870°C. Its creep rupture strength is superior to that of Alloy 718 at temperatures above 620-650°C.
  • Waspaloy® is more expensive than Alloy 718, resulting, at least partly, from increased amounts of the alloying elements nickel, cobalt, and molybdenum.
  • processing characteristics, such as hot workability and weldability are inferior to those of Alloy 718 due to strengthening by y’, which leads to higher manufacturing costs and more limited component repairability.
  • Alloy 718Plus® (UNS N07818) in the early 2000s, another y’ phase strengthened nickel-base alloy, which is commercially available from ATI Allvac, Monroe, NC. It is assumed that the levels and ratios of aluminium, titanium and niobium in Alloy 718Plus® provide a thermally stable microstructure and advantageous high-temperature mechanical properties, including substantial rupture and creep strength. The aluminium and titanium contents of Alloy 718Plus® alloy, in conjunction with the niobium content, are considered to result in the alloy being strengthened by y’ phase and y” phase, with y’ phase being the predominant strengthening phase.
  • Alloy 718Plus® has a relatively large ratio of aluminium to titanium that is believed to increase thermal stability. Whereas Alloy 718 contains no cobalt, and Rene® 220 and Waspaloy® contain about 12-15 weight percent of cobalt, Alloy 718Plus® has a cobalt level in the order of about 8 to 10 weight percent, which is assumed to contribute to improved stress rupture properties after long periods of exposure to high temperatures.
  • Solution annealing is a process in which the alloy is heated to a temperature above its critical point (crystallization temperature), maintained at suitable temperature for an appropriate amount of time and then cooled either by air cooling or water quenching to recrystallize.
  • annealing atoms migrate in the crystal lattice and the number of dislocations decreases, and grain size and phase composition may change. Annealing leads to a change in ductility and hardness of the alloy.
  • Ageing is a subsequent heat treatment used to increase the yield strength and in superalloys, it is applied to improve high-temperature strength. Ageing relies on changes in solid solubility with temperature to produce different intermetallic phases, which impede the movement of dislocations or defects in the crystal lattice. Since dislocations are often the dominant carriers of plasticity, this serves to harden the material. Unlike ordinary tempering, alloys often must be kept at elevated temperature for hours to allow precipitation to take place. Due to this time delay, the process is called “ageing”. Solution treatment (annealing) and ageing is sometimes abbreviated "STA”.
  • a recommended heat treatment process includes solution annealing at a temperature in the range from about 950°C to about 980°C for 1 hour, followed by a subsequent two-step ageing process with a first step at a temperature of about 720°C to about 788°C for a time of about 2 to 8 hours, air cooling down to a temperature of about 620°C to about 704°C and holding again for a time of about 8 hours as the second step.
  • Suitable annealing and ageing temperatures and times of alloys rely to a large extent on experience and empirical data. Even though phase diagrams of certain elements and knowledge about chemical and metallurgical behaviour of such elements may provide a rough hint towards suitable heat treatment conditions to obtain certain properties, due to the complexity of possible interactions in multi-element alloys, precise predictions are difficult or impossible to make.
  • the present invention therefore provides a nickel-based alloy comprising the following contents of elements, in weight-%:
  • V Vanadium
  • B Boron
  • the present invention also relates to a method for making a nickel-based alloy as defined hereinabove or hereinafter which is subjected to processing, including solution annealing, cooling and ageing.
  • the alloy may be further processed to an article of manufacture or into any other desired form, such as, for example, a disk, a blade, a fastener, a case, or a shaft fabricated from or including the nickel-based alloy of the present invention.
  • the articles formed of the nickel-based alloy of the present invention may be particularly advantageous when intended for in load-bearing and high temperature applications, such as components in the hot sections of turbine engines, such as turbine blades.
  • Manganese (Mn) up to 2.0
  • V Vanadium (V) up to 3.5
  • Manganese (Mn) up to 2.0 weight-%
  • At least 0.6 weight% of Al is added to provide creep strength. Furthermore, in high temperature environments, Al may have a positive impact on the corrosion resistance by forming a stable passive layer on the surface. On the other hand, if the Al content exceeds 2.0 wt%, the weldability and hot workability may be negatively influenced. According to embodiments, the Al content is from 0.80 to 1 .75 weight-%, such as from 0.80 to 1.70.
  • Titanium (Ti) 0.5 to 1.5 weiqht-%
  • Ti is added to provide improved high temperature strength and creep strength. To obtain this effect, it is necessary that the content of Ti is at least 0.5 wt%. According to embodiments, the content of Ti is as at least 0.7 wt%. On the other hand, if the Ti content exceeds 1.5 wt%, the weldability and hot workability may be negatively influenced. According to embodiments, the content of Ti is 0.7 to 1.3 weight%.
  • Ta may be added up to 1.5 weight%. According to embodiments, Ta may be present in 0.005 to 1.5 weight%. According to embodiments, the content of Ta is at least 0.01 wt%. If the Ta content exceeds 1.5 wt%, the hot workability may be negatively affected and there may also be a risk for formation of unwanted Laves phases. According to embodiments, the content of Ta is from 0.01 to 1.3 weight%, such as from 0.01 to 1.2 weight-%.
  • the Cu may be added to provide additional stability of the austenite phase. However, if the Cu content exceeds 2.5 wt%, the weldability and hot workability may be negatively influenced. According to embodiments, the highest content of Cu is up to 2.5 weight-%, the highest content of Cu is up to 2.3 weight-%, such as up to 1 .5 weight-%.
  • the present invention also relates to a method for making a nickel-based alloy, the method comprising:
  • the solution annealing step (or only referred to as “annealing”) of the hot-rolled samples included heating at 1150°C for 30 minutes and then water quenching down to about room temperature.
  • the densities of the samples were measured in the as-annealed condition according to the standard ISO 3369-2006. During measurement the material is weighted, first in air and then in water. Applying the Archimedes principle, the density of the material is calculated with high accuracy. Mechanical tests
  • the mechanical properties of the alloys according to the invention are similar or even better than the mechanical properties of comparative Alloy 718 and Alloy 718Plus.
  • the alloys according to the invention show both higher Rp0.2 and higher Rm, but in some cases lower elongation, than Alloy 718 and Alloy 718Plus at RT and 650°C.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Heat Treatment Of Steel (AREA)

Abstract

Un alliage à base de nickel d'une composition spécifiée d'éléments présente une résistance mécanique élevée, la somme des teneurs en % en poids de titane (Ti), d'aluminium (Al), de niobium (Nb), de tantale (Ta) et de vanadium (V) étant d'au moins 1,35 fois la teneur en % en poids de cobalt (Co).
PCT/SE2025/050165 2024-02-22 2025-02-21 Alliage à base de nickel à résistance mécanique élevée Pending WO2025178553A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
IN202411012781 2024-02-22
IN202411012781 2024-02-22
SE2430212 2024-04-19
SE2430212-7 2024-04-19

Publications (1)

Publication Number Publication Date
WO2025178553A1 true WO2025178553A1 (fr) 2025-08-28

Family

ID=96847625

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2025/050165 Pending WO2025178553A1 (fr) 2024-02-22 2025-02-21 Alliage à base de nickel à résistance mécanique élevée

Country Status (1)

Country Link
WO (1) WO2025178553A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0953138A (ja) * 1995-08-17 1997-02-25 Daido Steel Co Ltd ディーゼルエンジン用バルブとその製造方法
US6730264B2 (en) * 2002-05-13 2004-05-04 Ati Properties, Inc. Nickel-base alloy
US20070029014A1 (en) * 2003-10-06 2007-02-08 Ati Properties, Inc. Nickel-base alloys and methods of heat treating nickel-base alloys
US7531054B2 (en) * 2005-08-24 2009-05-12 Ati Properties, Inc. Nickel alloy and method including direct aging
US20110308674A1 (en) * 2007-10-25 2011-12-22 Volvo Aero Corporation Method, alloy and component

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0953138A (ja) * 1995-08-17 1997-02-25 Daido Steel Co Ltd ディーゼルエンジン用バルブとその製造方法
US6730264B2 (en) * 2002-05-13 2004-05-04 Ati Properties, Inc. Nickel-base alloy
US20070029014A1 (en) * 2003-10-06 2007-02-08 Ati Properties, Inc. Nickel-base alloys and methods of heat treating nickel-base alloys
US7531054B2 (en) * 2005-08-24 2009-05-12 Ati Properties, Inc. Nickel alloy and method including direct aging
US20110308674A1 (en) * 2007-10-25 2011-12-22 Volvo Aero Corporation Method, alloy and component

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