WO2023151747A1 - Alliage de nickel, poudre destinée à la production d'un alliage de nickel, et composant contenant un alliage de nickel - Google Patents

Alliage de nickel, poudre destinée à la production d'un alliage de nickel, et composant contenant un alliage de nickel Download PDF

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Publication number
WO2023151747A1
WO2023151747A1 PCT/DE2023/100068 DE2023100068W WO2023151747A1 WO 2023151747 A1 WO2023151747 A1 WO 2023151747A1 DE 2023100068 W DE2023100068 W DE 2023100068W WO 2023151747 A1 WO2023151747 A1 WO 2023151747A1
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Prior art keywords
inclusive
nickel alloy
mass fraction
nickel
powder
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PCT/DE2023/100068
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German (de)
English (en)
Inventor
Benedikt Albert
Michael KASTENHUBER
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MTU Aero Engines AG
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Publication of WO2023151747A1 publication Critical patent/WO2023151747A1/fr

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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%
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F1/00—Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • C22C1/0433—Nickel- or cobalt-based alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps

Definitions

  • NICKEL ALLOY POWDER FOR THE PRODUCTION OF A NICKEL ALLOY AND COMPONENT CONTAINING A NICKEL ALLOY
  • the invention relates to a nickel alloy according to the features of the preamble of claim 1, a powder for the production of a nickel alloy according to the features of the preamble of claim 14 and a component for a thermal gas turbine according to the features of the preamble of claim 15.
  • high-temperature nickel alloys are used in particular in gas turbines, combustors and chemical reactors.
  • a chromium content of 10-20% by weight is characteristic of high-temperature and heat-resistant nickel alloys in order to ensure the necessary oxidation resistance in higher temperature ranges.
  • high-temperature nickel alloys have an alloy content between 3-10% by weight molybdenum and between 10-20% by weight cobalt. Cobalt aids in the formation of high temperature precipitate particles and improves the creep resistance of the surrounding matrix.
  • Molybdenum and tungsten are solid solution forming alloy components that increase the strength and creep rupture strength of the alloy.
  • Aluminum and titanium alloy components result in the formation of hardenable y' phases, which increase the strength and creep rupture strength of the alloy.
  • high-temperature nickel alloys are highly formable.
  • US Pat. No. 11,085,104 B2 discloses a method for producing a heat-resistant Ni-based superalloy rod with good bending deformability and a heat-resistant Ni-based superalloy wire.
  • the method for manufacturing a heat-resistant Ni-base superalloy wire comprises a rod-making step of manufacturing a heat-resistant Ni-base superalloy rod; and a bar processing step of repeating plastic working at a working rate of 40% or less plural times in the direction of the axis from the peripheral surface of the bar at a temperature of 500°C or less until the cumulative working rate reaches 60% or more, to reduce the cross-sectional area of the rod.
  • a wire obtained by the crafting process from A Ni-base heat-resistant superalloy has a plastic-worked or recrystallized microstructure.
  • An amount of the precipitated gamma primary phase in the balance at 700°C is not less than 35 mol%, the composition in mass% being 0 to 0.2% C, 8.0 to 22.0% Cr, 2.0 to 8. 0% Al, 0.4 to 7.0% Ti, 0 to 28.0% Co, 2.0 to 7.0% Mo, 0 to 6.0% W, 0 to 4.0% Nb , 0 to 3.0% Ta, 0 to 10.0% Fe, 0 to 1.2% V, 0 to 1.0% Hf, 0 to 0.300% B, 0 to 0.300% Zr and the balance Ni and impurities , amounts.
  • EP 3 263 722 B1 describes a method for heat treating a workpiece comprising a nickel-based superalloy.
  • the nickel-base superalloy comprises: from 0.1% to 6% by weight tantalum or from 0.1% to 6% by weight a combination of both titanium and tantalum; from 0.1% to 6% by weight aluminum; and from 0.5 weight percent to 9 weight percent niobium, wherein an atomic ratio of tantalum to aluminum or an atomic ratio of a combination of both titanium and tantalum to aluminum is in a range of 0.1 to 4, the nickel-base superalloy further being 10 chromium from 0% to about 45% by weight, cobalt from 0% to about 40% by weight, iron from 0% to 40% by weight, molybdenum from 0% to 4% by weight, tungsten from 0% to 4% by weight, hafnium from 0% to 2% by weight, hafnium from 0% by weight to 0.1 wt.% zirconium, from 0 wt.
  • EP 3 791 004 A1 discloses a nickel-based alloy composition.
  • the nickel-based alloy composition consists of, in weight percent: between 9.0 and 13.2% chromium, between 5.9 and 24.9% cobalt, between 0.0 and 4.0% iron, between 1.1 and 4 .4% molybdenum, between 0. 0 and 8.0% tungsten, between 2.8 and 3.7% aluminum, between 0.3 and 5.1% titanium, between 0.0 and 4.0% niobium, more as 2.4% tantalum and 9.5% or less tantalum, between 0.01 and 0.
  • JP 6889418 B2 discloses an alloy.
  • Gamma prime phase at 700°C is 35 mol% or more, and in mass%, C: 0 to 0.25%, Cr: 8.0 to 25.0%, Al: 0.5 to 8 0%, Ti: 0.4 to 7.0%, Co: 0 to 28.0%, Mo: 0 to 8%, W: 0 to 6.0%, Nb: 0 to 4.0%, Ta : 0 to 3.0%, Fe: 0 to 10.0%, V: 0 to 1.2%, Hf: 0 to 1.0%, B: 0 to 0.300%, Zr: 0 to 0.300 In the process for producing a Ni-base superheat-resistant alloy containing % and having a component composition of the balance being Ni and unavoidable impurities.
  • EP 3 183 372 B1 discloses a hafnium-containing gamma nickel-based superalloy consisting of: 10% by weight to 22% by weight cobalt; 9 wt% to 14 wt% chromium; 0 wt% to 10 wt% tantalum; 2% to 6% by weight aluminum; 2% to 6% by weight titanium;
  • JP 6748951 B2 discloses a method for producing a super heat-resistant nickel-based alloy.
  • the composition of the components of the alloy is in mass %, C: 0-0.25%, Cr: 8.0-25.0%, Al: 0.5-8.0%, Ti: 0.4-7, 0%, Co: 0 to 28.0%, Mo: 0 to 8%, W: 0 to 15.0%, Nb: 0 to 4.0%, Ta: 0 to 5.0%, Fe: 0 to 10.0%, V: 0 to 1.2%, Hf: 0 to 3.0%, B: 0 to 0.300%, Zr: 0 to 0.300%, the balance being Ni and impurities.
  • JP 2019-183263 A discloses a Ni-based superalloy material suitable for cold working.
  • the composition of the components of the superalloy material is in mass%, C: 0-0.25%, Cr: 8.0-25.0%, Al: 0.5-8.0%, Ti: 0.4-7, 0%, Co: 0 to 28.0%, Mo: 0 to 8%, W: 0 to 15.0%, Nb: 0 to 4.0%, Ta: 0 to 5.0%, Fe: 0 to 10.0%, V: 0 to 1.2%, Hf: 0 to 3.0%, B: 0 to 0.300%, Zr: 0 to 0.300%, the balance being Ni and impurities.
  • a first aspect of the invention relates to a nickel alloy, in particular for producing a component for a thermal gas turbine.
  • the nickel alloy can in particular be produced by powder metallurgy. It is envisaged that the nickel alloy has a specific alloy composition which is characterized by specified mass fractions of the alloying elements.
  • the alloy composition comprises chromium in a mass fraction of 10% to 15% inclusive; cobalt in a mass fraction of 14% to 20% inclusive; molybdenum with a mass fraction of 3% up to and including 8%; Tungsten in a mass fraction of 2% to 6% inclusive; niobium with a mass fraction of 0.5% up to and including 3%; Aluminum with a mass fraction of 3% up to and including 6%; Titanium with a mass fraction of 3% up to and including 6%; hafnium in a mass fraction of 0.1% to 0.2% inclusive; tantalum with a mass fraction of 2% up to and including 3%; carbon in a mass fraction of 0.01% to 0.1% inclusive; boron in a mass fraction of 0.02% to 0.1% inclusive; zirconium in a mass fraction of 0.05% to 0.2% inclusive; A remaining portion is nickel, which may include unavoidable impurities.
  • the nickel alloy includes the following alloying elements:
  • the nickel alloy of the predetermined alloy composition has the advantage that it forms a homogeneous microstructure without macroscopic segregations during powder metallurgical manufacture.
  • a microstructure of the alloy has a proportion of a y' phase, which leads to advantageous strength properties being achieved in a temperature range of 700-760 °C. It has been shown that the structure has a small proportion of Frank-Kasper phases (TCP phases), so that damage tolerance requirements are not jeopardized by them.
  • TCP phases Frank-Kasper phases
  • the alloy shows a high thermal stability of the y-matrix, which is achieved through optimized solid solution hardening. At the same time, by adjusting the respective element ratios, high thermal stability is achieved not only for the matrix but above all for the grain boundaries, so that the alloy is particularly heat-resistant. There is a high stability of the y" phase, which prevents a transformation of the y" phase into a 6-phase.
  • the invention also includes developments that result in further advantages.
  • the nickel alloy comprises molybdenum with a mass fraction of 3.0% to 6%.
  • the mass fraction of molybdenum is 3.0 %, 3.5%, 4.0%, 4.5%, 5.0%, 5.5%, or 6.0%.
  • Intermediate values to the mass fractions mentioned above are also conceivable within the ranges according to the invention.
  • the nickel alloy includes tungsten with a mass fraction of 2.0% to 4%.
  • the mass fraction of tungsten is 2.0%, 2.5%, 3.0%, 3.5%, 4.0%.
  • Intermediate values to the mass fractions mentioned above are also conceivable within the ranges according to the invention.
  • a development of the invention provides that the proportion by mass of cobalt to the proportion by mass of chromium in the nickel alloy has a ratio of between 4:3 and 7:5 inclusive. In other words, it is contemplated that the proportions by weight of cobalt and chromium will be in a ratio of between 4:3 to 7:5 inclusive.
  • the further development has the advantage that the ratio between 4 to 3 up to and including 7 to 5 has a particularly positive effect on the stacking fault energy in the material, as a result of which the mechanical properties are improved.
  • a further development of the invention provides that the proportion by mass of aluminum to the proportion by mass of titanium in the nickel alloy has a ratio of between 1:1 and 2:1 inclusive. In other words, it is contemplated that the proportions by mass of aluminum and titanium will be in a ratio of between 1:1 to 2:1 inclusive.
  • the further development results in the advantage that the ratio leads to a desired characteristic of the y' phase, in particular its microstructure and misfit.
  • a development of the invention provides that the proportion by mass of molybdenum to the proportion by mass of niobium has a ratio of between 5:2 and 7:2 inclusive.
  • the proportions by mass of molybdenum and niobium will be in a ratio of between 5:2 to 7:2 inclusive.
  • the ratio is preferably 3 to 1.
  • the described ratio of the mass fraction of molybdenum to the mass fraction of niobium leads to a limited one , but stable proportion of von y" precipitations, with simultaneous stabilization of recrystallized grain boundaries and stable, finely distributed carbides. This can increase the strength of the alloy.
  • a development of the invention provides that the proportion by mass of tungsten to the proportion by mass of tantalum in the nickel alloy has a ratio of between 9:6 and 11:6 inclusive.
  • the proportions by mass of molybdenum and niobium will be in a ratio of between 9:6 to 11:6 inclusive.
  • the ratio is preferably 5 to 3.
  • the ratio mentioned results in a high-temperature-stable microstructure of the alloy.
  • a further development of the invention provides that the total mass fraction of cobalt and chromium in the nickel alloy is at most 35%. In other words, it is intended that a sum of the mass fraction of cobalt and the mass fraction of chromium is at most 35%. In other words, it is provided that the total mass fraction of cobalt and the mass fraction of chromium have a value of less than or equal to 35%.
  • a proportion of the TCP phases in the alloy is limited, giving the alloy higher long-term high-temperature resistance.
  • a development of the invention provides that the total mass fraction of aluminum and titanium in the nickel alloy is at least 7%. In other words, it is provided that a sum of the mass fraction of aluminum and the mass fraction of titanium is at least 7%. In other words, it is provided that the total mass fraction of aluminum and the mass fraction of titanium have a value greater than or equal to 7%.
  • the further development results in the advantage that a desired characteristic of the y' phase, in particular its microstructure and misfit, is achieved.
  • a development of the invention provides that the total mass fraction of niobium and titanium in the nickel alloy is at least 3.5%. In other words, it is provided that a sum of the mass fraction of niobium and the mass fraction of titanium is at least 3.5%. In other words, it is provided that the total mass fraction of niobium and the mass fraction of titanium have a value greater than or equal to 3.5%
  • a further development of the invention provides that the total proportion by mass of niobium and tantalum in the nickel alloy is at least 3.5%. In other words, it is provided that a sum of the mass fraction of niobium and the mass fraction of tantalum is at least 3.5%. In other words, it is provided that the total mass fraction of niobium and the mass fraction of tantalum have a value greater than or equal to 3.5%.
  • a development of the invention provides that the total mass fraction of molybdenum and tungsten in the nickel alloy is at least 5%. In other words, it is provided that a sum of the mass fraction of molybdenum and the mass fraction of tungsten is at least 5%. In other words, it is provided that the total mass fraction of molybdenum and the mass fraction of tungsten have a value greater than or equal to 5%.
  • the further development results in the advantage that the high-temperature strength of the alloy is increased.
  • a further development of the invention provides that the proportion by mass of nickel in the nickel alloy is at least 50%.
  • the nickel alloy has nickel with a mass fraction of at least 50%.
  • a second aspect of the invention relates to a powder for producing a nickel alloy according to the first aspect of the invention.
  • the powder is intended in particular for the production of the nickel alloy by means of a powder metallurgical process and has a predetermined composition. It is provided that the powder has a specific powder composition, which is characterized by predetermined mass percentages by weight of the powder elements.
  • the powder composition comprises chromium in a mass fraction of 10% to 15% inclusive; cobalt in a mass fraction of 14% to 20% inclusive; Molybdenum in a mass fraction of 3% to 8% inclusive; Tungsten in a mass fraction of 2% to 6% inclusive; niobium with a mass fraction of 0.5 up to and including 3%; Aluminum with a mass fraction of 3% up to and including 6%; Titanium with a mass fraction of 3% up to and including 6%; hafnium in a mass fraction of 0.1 to 0.2% inclusive; tantalum with a mass fraction of 2 up to and including 3 %; carbon in a mass fraction from 0.01 to 0.1% inclusive; boron in a mass fraction of 0.02 to 0.1% inclusive; zirconium with a mass fraction of 0.05 to 0.2% inclusive; A remaining portion is nickel.
  • the powder includes the following powder elements: 10%, 11%, 12%, 13%, 14%, or 15% by weight chromium; 14%, 15%, 16%, 17%, 18%, 19%, 20% by weight cobalt; Molybdenum with a mass fraction of 3.0%, 3.5%, 4.0%, 4.5%, 5.0%, 5.5%, 6.0%, 6.5%, 7.0%, 7.5%, 8.0%; tungsten with a mass fraction of 2.0%, 2.5%, 3.0%, 3.5%, 4.0%; niobium with a mass fraction of 0.5%, 1.0%, 1.5%, 2.0%, 2.5%, 3.0%; aluminum with a mass fraction of 3.0%, 3.5%, 4.0%, 4.5%, 5.0%, 5.5%, 6.0%; titanium with a mass fraction of 3.0%, 3.5%, 4.0%, 4.5%, 5.0%, 5.5%, 6.0%; Hafnium with a mass fraction of 0.10%, 0.11%, 0.12%, 0.13%, 0.14%, 0.15%, 0.16%, 0.17%, 0.1
  • a third aspect of the invention relates to a component for a thermal gas turbine, comprising a nickel alloy according to the first aspect of the invention.
  • the component can in particular be a rotor for a thermal gas turbine.
  • the component can be manufactured by powder metallurgy from a powder according to the second aspect of the invention.
  • a fourth aspect of the invention relates to a method for producing a powder intended for producing a component made of a nickel alloy.
  • the nickel alloy may be a nickel alloy according to the first aspect of the invention.
  • the method comprises at least one step of compiling alloying elements of the powder.
  • the alloying elements are melted into a master melt in one step.
  • the master melt is atomized by an atomization process, for example by means of gas atomization, plasma atomization or centrifugal processes.
  • the atomization produces particles of the master melt, which lead to powder ticles of the powder solidify.
  • the powder thereby formed may be a powder according to the second aspect of the invention.
  • a fifth aspect of the invention relates to a method for producing a component.
  • the component may be a component according to the third aspect of the invention.
  • the method includes at least one step of arranging a powder in a predetermined shape.
  • the powder can be a powder according to the second aspect of the invention.
  • the method comprises at least one step of compacting the powder in the predetermined shape and sintering the powder in the predetermined shape.
  • FIG. 1 shows a schematic representation of a method for producing a component
  • FIG. 2 shows a schematic representation of a further method for producing a component
  • FIG. 3 shows a schematic representation of a component.
  • FIG. 1 shows a schematic representation of a method for producing a component.
  • the method shown in FIG. 10 can describe a primary manufacturing method--also referred to as the primary manufacturing route--for manufacturing the component 5.
  • the component 5 can have a nickel alloy 1 .
  • the method can be provided to manufacture the component 5, which can be a rotor component of a turbine, for example.
  • the component 5 can in particular be a so-called blisk or a so-called bling.
  • the component 5 can be provided for arrangement in a thermal gas turbine.
  • the component 5 can be provided for use in a temperature range of, for example, 600-700° C. and for this purpose can have the nickel alloy 1 designed for this temperature range.
  • the nickel alloy 1 can have a predetermined composition and can be manufactured by powder metallurgy.
  • a powder 2 is provided, which can have a desired composition of the elements.
  • the elements with respective mass fractions are melted to form a master melt.
  • So-called ingots or ingots which can contain one or more of the elements, can be melted.
  • a pillar can be made from the master melt.
  • the pillar can have a frozen, solid form as well as a molten form.
  • the master melt can have a predetermined composition, which is specified, for example, in TAB. 1 can be described: TAB. 1
  • atomization to produce the powder 2 can take place.
  • the column can be melted and atomized in a plasma atomization process.
  • fluid atomization can be performed, wherein the column is atomized by a jet of fluid.
  • the atomizing fluid can be an inert gas or a liquid.
  • the solidified column can be melted again and the melt broken up using a centrifugal process.
  • the column can be melted and the melt broken up using vibrational force using ultrasound.
  • powder particles can form which solidify.
  • the powder 2 can be obtained by collecting the powder particles.
  • a consolidation can take place in a method step S3.
  • the powder 2 can be filled into a capsule and pre-compacted to produce a billet 3 .
  • the pre-compression can be carried out under a predetermined pressure and a predetermined temperature.
  • the powder 2 can be precompacted, for example, by hot isostatic pressing.
  • the ticket 3 can be processed in a conversion process.
  • the conversion process can include an extrusion process.
  • the billet 3 can be formed into a blank 4 in a method step S5.
  • the forming process may include a forging process.
  • the raw part can be further processed into the component 5 in the method step.
  • FIG. 2 shows a schematic representation of a further method for producing a component.
  • the method shown can describe a secondary manufacturing method—also referred to as a secondary manufacturing route—for manufacturing the component 5 .
  • the method may be the same as that shown in FIG. 1 described method steps S1 and S2 for the production of the powder 2 include.
  • a method step S6 following the method step S2 it can be provided that the powder 2 is pressed under a predetermined pressure into a predetermined shape, which the billet 3 should have, for example.
  • the pressed powder 2 can be sintered at a predetermined temperature.
  • the billet can be produced by sintering.
  • a consolidation step of the billet 3 can be provided in a method step S8 in order to provide the blank for the production of the component.
  • the raw part 4 can be post-compacted by means of hot isostatic pressing (HIP).
  • FIG. 3 shows a schematic representation of a component.
  • the component 4 can in particular be a blisk or a bling, which can be provided for arrangement in a gas turbine.
  • the component 5 can have the nickel alloy 1 and according to the FIG. 1 or that shown in FIG. 2 shown method be made.
  • nickel-based forged materials produced conventionally using an ingot process are available, which are already at the limit in terms of their temperature loads and stress loads at a maximum operating temperature.
  • nickel alloys include, for example, DA718 and U720 LI.
  • alloys produced by powder metallurgy that can be used at higher temperatures and loads are known from the prior art.
  • an alloy produced by powder metallurgy and a method for producing a component, in particular a rotor component for aircraft engines, with a defined composition and fixed ratios of some alloying elements to one another are described.
  • the solution can include the following:
  • a range of nickel alloy composition in weight percent as given in TAB. 1 is described.
  • the fixed ratios of individual alloying elements to one another can be specified as specified in TAB. 2 is described. This is done through the steps of powder production, so that the starting material already has the desired composition for the later forging process.
  • a third point can be the limitation of various partial sums of the alloying elements in order to enable stable production and the process chain with the same properties, as in TAB. 3 is described.
  • microstructural properties are achieved by adjusting the composition mentioned above. These properties include a homogeneous microstructure through the manufacture of the component through the manufacture using the powder metallurgy process.
  • the microstructure has an advantageous proportion of y'-precipitations, so that excellent strength properties are achieved in the temperature range of 700-760°C.
  • a high stability of the resulting grain boundaries is set.
  • the shape and stabilization via the alloying elements also result in a highly heat-resistant alloy.
  • the nickel alloy has a relatively small proportion of TCP phases, in particular the Laves phases, and the c phases. There can be a high thermal stability of the gamma matrix in the nickel alloy due to optimized solid solution strengthening.
  • the y"-phase has a high stability, so that a transformation of the y"-phase into a 6-phase is prevented.
  • the invention provides a nickel alloy which is designed both for an operating temperature and for mechanical stress in aircraft gas turbines.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
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  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne un alliage de nickel (1) destiné, en particulier, à la fabrication d'un composant (3) d'une turbine à gaz thermique, caractérisé par les fractions massiques suivantes d'une composition d'alliage : de 10 % inclus à 15 % inclus de chrome ; de 14 % inclus à 20 % inclus de cobalt ; de 3 % inclus à 8 % inclus de molybdène ; de 2 % inclus à 6 % inclus de tungstène ; de 0,5 % inclus à 3 % inclus de niobium ; de 3 % inclus à 6 % inclus d'aluminium ; de 3 % inclus à 6 % inclus de titane ; de 0,1 % inclus à 0,2 % inclus d'hafnium ; de 2 % inclus à 4 % inclus de tantale ; de 0,01 % inclus à 0,1 % inclus de carbone ; de 0,02 % inclus à 0,1 % inclus de bore ; de 0,05 % inclus à 0,2 % inclus de zirconium ; le reste étant constitué de nickel.
PCT/DE2023/100068 2022-02-14 2023-01-30 Alliage de nickel, poudre destinée à la production d'un alliage de nickel, et composant contenant un alliage de nickel WO2023151747A1 (fr)

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DE102022103420.8 2022-02-14
DE102022103420.8A DE102022103420A1 (de) 2022-02-14 2022-02-14 Nickellegierung, Pulver zur Herstellung einer Nickellegierung, Bauteil, Verfahren zur Herstellung einer Nickellegierung sowie Verfahren zur Herstellung eines Bauteils

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Citations (9)

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US20100329883A1 (en) * 2009-06-30 2010-12-30 General Electric Company Method of controlling and refining final grain size in supersolvus heat treated nickel-base superalloys
WO2012047352A2 (fr) * 2010-07-09 2012-04-12 General Electric Company Alliage à base de nickel, son traitement et les composants formés à partir dudit alliage
EP3183372A2 (fr) 2014-08-18 2017-06-28 General Electric Company Superalliages améliorés par l'ajout de zirconium
EP3263722A1 (fr) 2016-06-30 2018-01-03 General Electric Company Procédés de préparation d'articles en superalliage et articles associés
JP2019183263A (ja) 2018-04-04 2019-10-24 日立金属株式会社 冷間加工用Ｎｉ基超耐熱合金素材
EP3791004A1 (fr) 2018-05-11 2021-03-17 Alloyed Limited Alliage à base de nickel
JP6889418B2 (ja) 2018-03-06 2021-06-18 日立金属株式会社 Ｎｉ基超耐熱合金の製造方法およびＮｉ基超耐熱合金
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