EP2491156A1 - Alliage à solidification directionnelle, et composant composé de cristaux en forme de tiges - Google Patents

Alliage à solidification directionnelle, et composant composé de cristaux en forme de tiges

Info

Publication number
EP2491156A1
EP2491156A1 EP09756148A EP09756148A EP2491156A1 EP 2491156 A1 EP2491156 A1 EP 2491156A1 EP 09756148 A EP09756148 A EP 09756148A EP 09756148 A EP09756148 A EP 09756148A EP 2491156 A1 EP2491156 A1 EP 2491156A1
Authority
EP
European Patent Office
Prior art keywords
superalloy according
weight
content
boron
iron
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.)
Granted
Application number
EP09756148A
Other languages
German (de)
English (en)
Other versions
EP2491156B1 (fr
Inventor
Winfried Esser
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.)
Siemens AG
Howmet Corp
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP18000230.5A priority Critical patent/EP3363923A1/fr
Publication of EP2491156A1 publication Critical patent/EP2491156A1/fr
Application granted granted Critical
Publication of EP2491156B1 publication Critical patent/EP2491156B1/fr
Not-in-force 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
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • 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

Definitions

  • the invention relates to an alloy which serves for the production of directionally solidified components, and to a component which has stem-shaped crystals.
  • nickel-based superalloys are often used.
  • single crystals or components with stalk-shaped grains are used.
  • the components with the columnar grains it depends on the grain boundary strength and the grain boundary from ⁇ decisions or the presence of foreign elements (impurities) are deposited at the grain boundaries. These elements can have a significant influence on the mechanical behavior at high temperatures.
  • WO 00/44949 discloses a nickel-base superalloy having a high molybdenum content.
  • US 6,231,692 also discloses a nickel-based high molybdenum alloy.
  • EP 1 329 527 B1 discloses a nickel-based superalloy in which the elements zirconium and hafnium are deliberately added.
  • EP 0 855 449 B1 also discloses a minimal addition of zircon.
  • these alloys have a low Kornskynfes ⁇ ACTION, which as affecting the overall strength of a component ⁇ by negative, or are not sufficiently ductile by zirconium and hafnium. Lower additions of certain elements can have a negative impact on these properties of the alloy if exceeded.
  • Figure 2 is a combustion chamber
  • Figure 3 is a gas turbine.
  • FIG. 1 shows a perspective view of a rotor blade 120 or guide vane show ⁇ 130 of a turbomachine, which extends along a longitudinal axis of the 121st
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has, along the longitudinal axis 121, a fastening area 400, an adjacent blade platform 403 and an airfoil 406 and a blade tip 415.
  • the vane 130 having at its blade tip 415 have a further platform (not Darge ⁇ asserted).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is, for example, as a hammerhead out staltet ⁇ . Other designs as fir tree or Schissebwschwanzfuß are possible.
  • the blade 120, 130 has for a medium which flows past the scene ⁇ felblatt 406 on a leading edge 409 and a trailing edge 412th
  • conventional blades 120, 130 in all regions 400, 403, 406 of the blade 120, 130, for example, massive metallic materials, in particular superalloys, are used.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • the blade 120, 130 can hereby be manufactured by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, ie grains over the entire length run the workpiece and here, the general usage, referred to as directionally solidified) or a monocrystalline structure, ie the entire workpiece be ⁇ is made of a single crystal.
  • a columnar grain structure columnar, ie grains over the entire length run the workpiece and here, the general usage, referred to as directionally solidified
  • a monocrystalline structure ie the entire workpiece be ⁇ is made of a single crystal.
  • Structures are also called directionally solidified structures.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. B. (MCrAlX, M is at least one element of the group iron (Fe), cobalt (Co),
  • Nickel (Ni) is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • the density is preferably 95% of the theoretical
  • the layer composition comprises Co-30Ni-28Cr-8A1-0, 6Y-0, 7Si or Co-28Ni-24Cr-10Al-0, 6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al are also preferably used. 0.6Y-3Re or Ni-12Co-21Cr-IIAl-O, 4Y-2Re or Ni-25Co-17Cr-10A1-0, 4Y-1, 5Re.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of Zr0 2 , Y2Ü3-Zr02, ie it is not, partially ⁇ or fully stabilized by yttria
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat insulating layer can comprise porous, micro- or macro-cracked compatible grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the
  • 120, 130 may have to be freed from protective layers after use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. Thereafter, a ⁇ As the coating of the component 120, 130, after which the component 120, the 130th
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and also has, if necessary, film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 2 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as so-called an annular combustion chamber, in which are arranged a plurality of in the circumferential direction about an axis of rotation 102 Burners 107 open into a common combustion chamber space 154, the flames 156 produce.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M facing side with a formed from heat shield elements 155. liner.
  • Each heat shield element 155 made of an alloy is equipped on the working fluid side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • a ceramic Wär ⁇ medämm Anlagen be present and consists for example of ZrÜ2, Y203 ⁇ Zr02, ie it is not, partially or fully ⁇ dig stabilized by yttrium and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the heat- insulating layer may have porous, micro- or macro-cracked Kör ⁇ ner for better thermal shock resistance.
  • Refurbishment means that heat shield elements 155 may be replaced after use by heat shielding elements 155
  • Protective layers must be freed (for example by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired.
  • the heat shield elements 155 are then, for example, hollow and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.
  • FIG. 3 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings .
  • a row 125 formed of rotor blades 120 follows.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the 105 ⁇ be compressed air provided at the turbine end of the compressor is supplied to the burners 107, where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands on the rotor blades 120 in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine connected to it ,
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the highest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the components in particular for the turbine ⁇ blade 120, 130 and components of the combustion chamber 110 are For example, iron-, nickel- or cobalt-based superalloys used.
  • Such superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium.
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
  • MCrAlX may still be present a thermal barrier coating, and consists for example of Zr02, Y203-Zr02, ie it is not, partially or completely stabilized by Ytt ⁇ riumoxid and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the guide blade 130 has a guide blade root facing the inner housing 138 of the turbine 108 (not shown here) and a guide blade foot opposite
  • the inventive alloy has the following contents in Ge ⁇ weight percent (wt%):
  • the superalloy comprises (in% by weight):
  • Zr Zircon
  • P phosphorus
  • S sulfur
  • Mn manganese
  • Silicon (Si) enhances oxidation resistance and causes deoxidation of the melt.
  • the proportion of iron (Fe) must not exceed 0.2% and may be at least 0.014Gew%.
  • Iron (Fe) is known as the ⁇ 'imager and nickel substituent. Silicon and iron also improve castability. A reduction of the elements would be rather undesirable.
  • the content of vanadium (V) is not greater than 75 ppm and is preferably at least 50 ppm.
  • the proportion of copper (Cu) may be up to 0. lGew% with minimum values from 0.001Gew%.
  • the content of hafnium (Hf) is not RESIZE ⁇ SSER than 50ppm. This is in contrast to the known ones
  • Alloys for directional solidification with columnar grains in which hafnium is deliberately added in larger proportions to stabilize the grain boundaries between the stem grains.
  • the boron content must not exceed a certain maximum value, since otherwise there will be a negative influence due to the melting point depressant.
  • the boron content is 150 ppm.
  • Ni niobium
  • Ni superalloys - The amount of niobium (Nb) - deliberately added in some Ni superalloys - may here be up to 75ppm with minimum values of 50ppm. Optimum carbide formation is achieved with 0.09% carbon (C).
  • grain boundary consolidators such as hafnium and zirconium is dispensed with.
  • Carbon content is higher than 0.08Gew%.
  • Impurities such as silicon (Si), manganese (Mn), iron (Fe) or copper (Cu).
  • Impurities of the alloys preferably have a maximum value of 10 ppm.
  • the proportion of sulfur (S) is at least 0.0003 wt% and at most 0.25 wt%.
  • the proportion of phosphorus (P) is at least 0.003 wt% and at most 0.025 wt%.
  • a higher purity of the alloy would be desirable, but hardly affordable and often not necessary.
  • components 120, 130 may be manufactured inexpensively but with known good high temperature properties.
  • the elements silicon (Si), iron (Fe), phosphorus (P) and sulfur (S) are accepted.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Dans la production de super-alliages à base de nickel de type connu, en vue d'obtenir des composants composés de monocristaux en forme de tiges, il n'est pas tenu compte, dans une mesure suffisante, de la résistance intercristalline. Le super-alliage à base de nickel selon l'invention présente une faible teneur en molybdène, et des valeurs ajustées à très haute précision, pour des éléments à résistance intercristalline et des éléments se séparant en interfaces granulaires.
EP09756148.4A 2009-10-20 2009-10-20 Alliage pour une solidification directionelle et l'article à grains en forme de colonne Not-in-force EP2491156B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18000230.5A EP3363923A1 (fr) 2009-10-20 2009-10-20 Alliage de solidification directionnelle et composant de cristaux en forme de tige

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/EP2009/063737 WO2011047714A1 (fr) 2009-10-20 2009-10-20 Alliage à solidification directionnelle, et composant composé de cristaux en forme de tiges

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP18000230.5A Division EP3363923A1 (fr) 2009-10-20 2009-10-20 Alliage de solidification directionnelle et composant de cristaux en forme de tige

Publications (2)

Publication Number Publication Date
EP2491156A1 true EP2491156A1 (fr) 2012-08-29
EP2491156B1 EP2491156B1 (fr) 2018-04-04

Family

ID=41571398

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09756148.4A Not-in-force EP2491156B1 (fr) 2009-10-20 2009-10-20 Alliage pour une solidification directionelle et l'article à grains en forme de colonne
EP18000230.5A Withdrawn EP3363923A1 (fr) 2009-10-20 2009-10-20 Alliage de solidification directionnelle et composant de cristaux en forme de tige

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP18000230.5A Withdrawn EP3363923A1 (fr) 2009-10-20 2009-10-20 Alliage de solidification directionnelle et composant de cristaux en forme de tige

Country Status (3)

Country Link
US (1) US9068251B2 (fr)
EP (2) EP2491156B1 (fr)
WO (1) WO2011047714A1 (fr)

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US8921730B2 (en) * 2011-06-22 2014-12-30 General Electric Company Method of fabricating a component and a manufactured component
CH705327A1 (de) 2011-07-19 2013-01-31 Alstom Technology Ltd Lot zum Hochtemperaturlöten und Verfahren zum Reparieren bzw. Herstellen von Bauteilen unter Verwendung dieses Lotes.
CN105624472A (zh) * 2015-12-28 2016-06-01 广东华科新材料研究院有限公司 一种3d打印用镍基高温合金粉及其制备方法
US11123791B2 (en) 2017-10-16 2021-09-21 General Electric Company Method for casting a mold
US11123790B2 (en) 2017-10-16 2021-09-21 General Electric Company Apparatus for casting a mold

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Also Published As

Publication number Publication date
US20120201713A1 (en) 2012-08-09
EP2491156B1 (fr) 2018-04-04
US9068251B2 (en) 2015-06-30
WO2011047714A1 (fr) 2011-04-28
EP3363923A1 (fr) 2018-08-22

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