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WO2015047128A1 - Procédé de fabrication d'alliage à base de nickel comprenant un post-traitement thermique et élément comportant l'alliage à base de nickel - Google Patents

Procédé de fabrication d'alliage à base de nickel comprenant un post-traitement thermique et élément comportant l'alliage à base de nickel Download PDF

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Publication number
WO2015047128A1
WO2015047128A1 PCT/RU2013/000848 RU2013000848W WO2015047128A1 WO 2015047128 A1 WO2015047128 A1 WO 2015047128A1 RU 2013000848 W RU2013000848 W RU 2013000848W WO 2015047128 A1 WO2015047128 A1 WO 2015047128A1
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WO
WIPO (PCT)
Prior art keywords
nickel
hours
treatment
alloy
grain size
Prior art date
Application number
PCT/RU2013/000848
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English (en)
Inventor
Mikhail Vladimirovich RYAZANOV
Original Assignee
Siemens Aktiengesellschaft
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Filing date
Publication date
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Priority to PCT/RU2013/000848 priority Critical patent/WO2015047128A1/fr
Publication of WO2015047128A1 publication Critical patent/WO2015047128A1/fr

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Classifications

    • 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
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • 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
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • 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
    • 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
    • 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
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/24—After-treatment of workpieces or articles
    • B22F2003/248—Thermal after-treatment
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the present invention relates to a method for nickel-based alloy manufacturing with post heat-treatment to increase the mean grain size within the alloy of fine-grained structure comprising second-phase particles.
  • the present invention re- lates further to a component manufactured using the method, particularly a component within a turbine.
  • Nickel-based alloys so-called superalloys are extensively used for example for high-duty components. These components are comprised inter alia by combustion engines and gas turbines.
  • the so-called superalloys have superior mechanical properties and a high corrosion/oxidation resistance at elevated temperatures.
  • An example for a superalloy is the Alloy 718, which is one of the most widely used nickel-based superalloys.
  • the mechanical properties of Ni-based superalloys are very much depending on grain size of the fee gamma ( ⁇ ) phase matrix. Life time and creep resistance increase with grain size. On the other hand, excessively large grains lower the tensile strength. In superalloys an equilibrium balance should be kept in order to achieve superior mechanical performance at elevated temperatures .
  • additive layer manufacturing can result in more fine-grained microstructures which are less advantageous in terms of fatigue and creep- rupture properties.
  • components produced from powder metal gamma-prime ( ⁇ ' ) precipitation-strengthened nickel-base superalloys are consolidated, such as by hot isostatic pressing (HIP) and/or extrusion consolidation.
  • HIP hot isostatic pressing
  • the resulting billet is iso- thermally forged at temperatures slightly below the ⁇ ' solvus temperature of the alloy, to approach superplastic forming conditions. That allows the filling of the die cavity without the accumulation of significant metallurgical strains.
  • these alloys are then heat treated above their ⁇ ' solvus temperatures. This is generally referred to as a super-solvus heat treatment, to cause uniform coarsening of the grains.
  • Alloy 718 can be worked and heat treated above the ⁇ phase solvus temperature, which is at 1010°C, or at a temperature between the ⁇ phase solvus and the ⁇ ' ' phase solvus temperature, which is at 910°C, for grain-size control.
  • the grain-size control is an important aspect of current high-strength superalloy production .
  • the object of the present invention is to present a method for nickel-based alloy manufacturing to increase the mean grain size within the alloy of fine-grained structure which comprises pinning second-phase particles.
  • an object of the present invention is to dissolve the grain- boundary precipitates in nickel-base superalloys, containing for example carbon and/or boron and to increase the size of the grains above a value of limiting grain size D L existing without using the method according to the present invention.
  • a further object of the present invention is to present a component of an arrangement manufactured using the method according to the present invention with desired properties, particularly within heavy-duty use.
  • a method for nickel-based alloy manufacturing according to the present invention comprises a post heat-treatment to increase the mean grain size D within the alloy of fine-grained structure with second-phase particles.
  • the second-phase particles can be for example carbon and/or boron containing compounds accumulated at the grain boundaries.
  • An annealing step is comprised for a defined period of time t an neai in hours respectively h, at a temperature T in the range of more than 1000°C.
  • the second-phase particles are dissolved, particularly totally in the material matrix.
  • Metal carbides and/or borides, particularly accumulated at the grain boundaries are dissolved at temperatures higher than 1000°C.
  • the reduction and/or total solving of precipitates from the grain boundaries enables a grain size growth above a limiting grain size value D L , which exists in the presence of pinning second-phase particles.
  • the defined period of time t an neai can be substantially in the range of 3 hours and more, particularly 3 hours. With a post heat-treatment with annealing times t an neai longer or in the range of 3 hours, the grain size D grows above the before ex- isting limiting grain size value D L .
  • a longer period of time tanneai is correlated with more energy used.
  • a post heat-treatment time t an neai of 3 hours can be advantageous.
  • the temperature T during the annealing step can be in the range of 1140°C to 1150°C. With a temperature T below 1000°C metal carbides and/or borides are not dissolved. Very high temperatures T, for example above 1200°C lead to an increase of grain size to values, where the material shows a strongly reduced tensile strength.
  • the nickel-based alloy can be a gamma double prime ( ⁇ ' ' ) precipitation-hardened nickel-base superalloy, particularly Alloy 718. This kind of alloy is widely used in components re- quiring high mechanical strength at high temperatures.
  • a heat treatment, particularly before the post heat-treatment can be comprised with the following steps:
  • the post heat-treatment according to the present invention particularly follows to the heat treatment in time.
  • a coarsening of particles, particularly of second-phase metal carbide particles can be caused by the post heat-treatment.
  • the mean grain size D within the alloy can be increased by the post heat-treatment to a predefined value, particularly greater than the value of the limiting grain size D L without post heat-treatment.
  • the predefined value D can be in the range of 20 to 45 pm.
  • a material with this value can show high tensile strength and a high life time as well as creep resistance.
  • the value of grain size D can be a good compromise between values with very high tensile strength and values with very high life time as well as creep resistance.
  • a component of an arrangement according to the present inven tion is manufactured with the method described before.
  • the component can be comprised by a turbine, particularly by a gas turbine. It can be for example a rotor shaft, a turbine blade or an other component.
  • FIG 1 illustrates the effect of grain size D in m on time to rupture t R in hours for a homogeneous mi- crostructure known from the state of the art, see B. Pieraggi et al., and
  • FIG 2 illustrates the calculated correlation of the lim- iting grain size D L in ⁇ on second-phase particle radius r P in m for a random distribution of sec- ond-phase particles within the metal matrix of Al- loy 718
  • FIG 3 illustrates the correlation between temperature T in °C and the mean second-phase particle radius r M in ⁇ for annealing time t an neai 1 hour and for 3 hours calculated for Alloy 718.
  • Ni-based superalloys particularly the widely used Alloy 718
  • the mechanical properties of Ni-based superalloys depend much on the grain size of the fee gamma ( ⁇ ) phase matrix.
  • ⁇ fee gamma
  • the life and creep resistance increase with the grain size D.
  • FIG 1 the correlation between the time to rupture t R in hours and the grain size D for a homogeneous microstructure is shown, at a temperature T of 650°C and a pressure of 730 MPa. This correlation is known from the state of the art, see B. Pieraggi et al.
  • the time to rupture t R decreases as the grain size D decreases, or the AST grain size number D ASTM increases.
  • the crack growth rate is inversely proportional to the grain size D. Excessively large grains can lower the ten- sile strength. So, for high-duty components for example in combustion engines or gas turbines, where materials are required with long life time, high creep resistance and high tensile strength, a balanced material is used. The grain size is large enough to give a long life time and high creep re- sistance, but low enough to give a high tensile strength.
  • a nickel- based alloy with balanced properties can be obtained.
  • Alloy 718 a grain size in the range of 20 to 45 ⁇ is suitable for components used particularly in gas turbine engines .
  • dispersions of second-phase particles like metal carbides can significantly inhibit grain growth, by exerting a pinning force on migrating grain boundaries during thermal treatment. This effect is widely known as Zener pinning.
  • the final grain size is re- stricted to an upper limit, the so-called limiting grain size D L , beyond which normal grain growth ceases.
  • the relationship between the limiting grain size and the dispersed second phase can be expressed as
  • D L k-r P / f n
  • r P and f are the size and volume fraction of the second-phase particles
  • k and n are constants.
  • FIG 2 shows the effect of the second-phase particle radius on the limiting grain size for the case of random particle- boundary intersection.
  • the limiting grain size decreases with increasing volume fraction of the second-phase.
  • a post-heat treatment according to the present invention can ensure sufficient coarsening of for example metal carbide particles, allowing to adjust the matrix grain sizes of finegrained materials to a desired value.
  • the value can be selected according to ranges derived from FIG 1.
  • the desired grain size range is often limited to values between 20 to 45 ym, which corresponds to ASTM val- ues of 6 to 8.
  • the mean particle size should exceed 0.2 ym.
  • Figure 3 illustrates the dependence of the calculated mean MC particle size, i.e. mean particle radius r M in pm, as a function of temperature T in °C for two different annealing times.
  • the curve marked with squares corresponds to an annealing time tgnneai 1 hour and the curve marked with circles corresponds to an annealing time t an n ea i of 3 hours. Both curves were calculated for Alloy 718.
  • the appropriate coarsening of metal carbide particles for materials with desired properties according to FIG 2 can be achieved by annealing in the temperature range 1140°C to 1150°C for 3 hours or more. Much longer annealing times increase costs and consume energy, so an annealing time t ann eai of 3 hours can be optimal to achieve the desired grain size for example for gas turbine components .
  • the post-heat treatment according to the present invention can further facilitate a rapid relief of internal stresses, induced during additive manufacturing.
  • Nickel-base superalloys can contain 15 to 20% Fe, 17 to 20% Cr, 4.75 to 5.5% Nb, 2.8 to 3.3% Mo, 0.65 to 1.15% Ti, up to 0.6% Al, up to 0.05% C, up to 0.006% B, up to 0.015% P, the balance being nickel. Other compositions and components are possible too.
  • the nickel-base superalloys can be produced for example by additive manufacturing techniques, e.g. selective laser melting or electron beam melting.
  • the nickel-base superalloys are used i.a. as material to produce components of arrangements like turbines, such as gas turbines, other engines and parts of heavy duty equipment.
  • the process for improving the mechanical properties, such as fatigue and creep-rupture resistance includes heat treatment of as-fabricated components in the temperature range 1140°C to 1150°C for 3 hours or more, so as to enable grain growth in the presence of inert second-phase particles up to a desired size range.
  • the component can be then subjected to a two-step aging at temperatures of 719°C and 621°C, respectively, and finally air cooled to room temperature.
  • embodiments according to the present invention can be combined with each other and/or can be combined with embodiments known from the state of the art.
  • the method can be used for other nickel-based alloys like Inconel 939 and so on.
  • Components of an arrangement according to the present invention can be turbine discs of air craft turbines or parts of combustion engines. Much longer annealing times t an neai than 3 hours can be used depending on the material composition and desired grain size.
  • the balance between properties like long life time, high creep resistance on one side and high tensile strength on the other can be chosen, and desired grain size values can accordingly be achieved.
  • a main advantage of the method of the present invention is that according to desired properties of the nickel-based alloy of fine-grained structure comprising pinning particles, a grain size can be adjusted with a post heat-treatment even to values of the mean grain size D above a limiting grain size D L , which exists without the post heat-treatment.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Powder Metallurgy (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention porte sur un procédé de fabrication d'alliage à base de nickel comprenant un post-traitement thermique pour augmenter la taille moyenne D des grains dans l'alliage, ce dernier ayant une structure à grains fins comportant des particules de phase secondaire. Une étape de recuit est comprise dans le procédé pendant une durée tde recuit définie à une température T de plus de 1000 °C. La présente invention porte en outre sur un élément fabriqué à l'aide du procédé, en particulier un élément dans une turbine.
PCT/RU2013/000848 2013-09-27 2013-09-27 Procédé de fabrication d'alliage à base de nickel comprenant un post-traitement thermique et élément comportant l'alliage à base de nickel WO2015047128A1 (fr)

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PCT/RU2013/000848 WO2015047128A1 (fr) 2013-09-27 2013-09-27 Procédé de fabrication d'alliage à base de nickel comprenant un post-traitement thermique et élément comportant l'alliage à base de nickel

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106180719A (zh) * 2016-09-27 2016-12-07 飞而康快速制造科技有限责任公司 激光选区熔化增材制造的in718构件、系统、热处理方法及装置
WO2017053480A1 (fr) * 2015-09-21 2017-03-30 Confluent Medical Technologies, Inc. Dispositifs superélastiques fabriqués à base d'alliages nitihf au moyen de techniques de métallurgie des poudres
WO2017194451A1 (fr) * 2016-05-09 2017-11-16 Siemens Aktiengesellschaft Prétraitement, procédé d'impression 3d d'un élément structural et système associé
EP3391983A4 (fr) * 2016-05-12 2019-01-16 Mitsubishi Heavy Industries, Ltd. Procédé de fabrication d'un élément métallique
US10378087B2 (en) 2015-12-09 2019-08-13 General Electric Company Nickel base super alloys and methods of making the same
US10577679B1 (en) 2018-12-04 2020-03-03 General Electric Company Gamma prime strengthened nickel superalloy for additive manufacturing
CN113477942A (zh) * 2021-07-01 2021-10-08 西南交通大学 基于SLM的高强高塑性Inconel718合金的制备方法

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US5244515A (en) 1992-03-03 1993-09-14 The Babcock & Wilcox Company Heat treatment of Alloy 718 for improved stress corrosion cracking resistance
GB2486046A (en) * 2010-10-20 2012-06-06 Materials Solutions Making an article from a superalloy by additive layer manufacturing
EP2586887A1 (fr) * 2011-10-31 2013-05-01 Alstom Technology Ltd Procédé de fabrication de composants ou de coupons constitués d'un superalliage à haute température

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Publication number Priority date Publication date Assignee Title
FR2324753A1 (fr) * 1975-09-22 1977-04-15 United Technologies Corp Procede de traitement thermique des superalliages a base de nickel
US5244515A (en) 1992-03-03 1993-09-14 The Babcock & Wilcox Company Heat treatment of Alloy 718 for improved stress corrosion cracking resistance
GB2486046A (en) * 2010-10-20 2012-06-06 Materials Solutions Making an article from a superalloy by additive layer manufacturing
EP2586887A1 (fr) * 2011-10-31 2013-05-01 Alstom Technology Ltd Procédé de fabrication de composants ou de coupons constitués d'un superalliage à haute température

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D. FURRER; H. FECHT: "Ni-based superalloys for turbine disks", JOM, vol. 51, 1999, pages 14 - 17
GUO W M ET AL: "Microstructure, Properties and Heat Treatment Process of Powder Metallurgy Superalloy FGH95", JOURNAL OF IRON AND STEEL RESEARCH INTERNATIONAL, GANGTIE YANJIU XUEBAO, CN, vol. 13, no. 5, 1 September 2006 (2006-09-01), pages 65 - 68, XP022933576, ISSN: 1006-706X, [retrieved on 20060901], DOI: 10.1016/S1006-706X(06)60097-6 *
OJO O A ET AL: "On incipient melting during high temperature heat treatment of cast Inconel 738 superalloy", JOURNAL OF MATERIALS SCIENCE, KLUWER ACADEMIC PUBLISHERS, BO, vol. 39, no. 24, 1 December 2004 (2004-12-01), pages 7401 - 7404, XP019210101, ISSN: 1573-4803, DOI: 10.1023/B:JMSC.0000048761.32712.EB *

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2017053480A1 (fr) * 2015-09-21 2017-03-30 Confluent Medical Technologies, Inc. Dispositifs superélastiques fabriqués à base d'alliages nitihf au moyen de techniques de métallurgie des poudres
US10378087B2 (en) 2015-12-09 2019-08-13 General Electric Company Nickel base super alloys and methods of making the same
US10801088B2 (en) 2015-12-09 2020-10-13 General Electric Company Nickel base super alloys and methods of making the same
CN109153074A (zh) * 2016-05-09 2019-01-04 西门子股份公司 预处理、用于增材制造构件的方法和设备
WO2017194451A1 (fr) * 2016-05-09 2017-11-16 Siemens Aktiengesellschaft Prétraitement, procédé d'impression 3d d'un élément structural et système associé
US11148196B2 (en) 2016-05-09 2021-10-19 Siemens Energy Global GmbH & Co. KG Pre-treatment, method for additive production of a component, and device
CN109153074B (zh) * 2016-05-09 2021-11-09 西门子股份公司 预处理、用于增材制造构件的方法和设备
EP3391983A4 (fr) * 2016-05-12 2019-01-16 Mitsubishi Heavy Industries, Ltd. Procédé de fabrication d'un élément métallique
CN106180719B (zh) * 2016-09-27 2019-01-18 飞而康快速制造科技有限责任公司 激光选区熔化增材制造的in718构件、系统、热处理方法及装置
CN106180719A (zh) * 2016-09-27 2016-12-07 飞而康快速制造科技有限责任公司 激光选区熔化增材制造的in718构件、系统、热处理方法及装置
US10577679B1 (en) 2018-12-04 2020-03-03 General Electric Company Gamma prime strengthened nickel superalloy for additive manufacturing
CN113477942A (zh) * 2021-07-01 2021-10-08 西南交通大学 基于SLM的高强高塑性Inconel718合金的制备方法
CN113477942B (zh) * 2021-07-01 2022-08-09 西南交通大学 基于SLM的高强高塑性Inconel718合金的制备方法

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