EP1685264A1 - Piece resistant a des temperatures elevees - Google Patents

Piece resistant a des temperatures elevees

Info

Publication number
EP1685264A1
EP1685264A1 EP04790725A EP04790725A EP1685264A1 EP 1685264 A1 EP1685264 A1 EP 1685264A1 EP 04790725 A EP04790725 A EP 04790725A EP 04790725 A EP04790725 A EP 04790725A EP 1685264 A1 EP1685264 A1 EP 1685264A1
Authority
EP
European Patent Office
Prior art keywords
component according
strength
ppm
alloy
component
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.)
Withdrawn
Application number
EP04790725A
Other languages
German (de)
English (en)
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
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 EP04790725A priority Critical patent/EP1685264A1/fr
Priority to EP07019290A priority patent/EP1914326A3/fr
Publication of EP1685264A1 publication Critical patent/EP1685264A1/fr
Withdrawn legal-status Critical Current

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
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%

Definitions

  • the invention relates to a high-temperature-resistant component made of an alloy, in particular of a nickel, cobalt or iron-based superalloy with precipitates.
  • the nickel alloy consists of up to 0.3% carbon, 11-15% chromium, 8-12% cobalt, 1-2.5% molybdenum, 3-10% tungsten, 3.5-10% tantalum,
  • the ÜS-PS-5, 611, 670 discloses a blade for a gas turbine.
  • the rotor blade has a monocrystalline platform region and a monocrystalline airfoil.
  • An attachment region of the blade is designed with a directionally solidified structure.
  • the blade is cast from a superalloy having in percent by weight the following composition: up to 0.2% carbon, 5-14% chromium, 4-7% aluminum, 2-15% tungsten, 0.5-5% titanium, bis to 3% niobium, up to 6% molybdenum, up to 12% tantalum, up to 10.5% cobalt, up to 2% hafnium, up to 4% rhenium, up to 0.035% boron, up to 0.035% zirconium and the rest Nickel.
  • These broad ranges are intended to indicate alloy compositions that are generally suitable for the proposed gas turbine blade, but do not exhibit a composition range suitable for particular oxidation and corrosion resistance or strength.
  • EP 0 297 785 B1 discloses a nickel-based superalloy for single crystals.
  • the superalloy points in Percent by weight of the following composition: 6-15% chromium, 5-12% tungsten, 0.01-4% rhenium, 3-9% tantalum, 0.5-2% titanium, 4-7% aluminum and optionally 0.5- 3% molybdenum. With this superalloy, both a high-temperature crack resistance and a corrosion resistance are achieved to the
  • the titanium content shall not exceed 2% by weight.
  • a nickel-based superalloy is given, which has a particularly narrow coexistence zone for the solid and liquid phase and thus is particularly suitable for a single crystal casting process.
  • the alloy has the following composition in weight percent: 10-30% chromium, 0.1-5% niobium, 0.1-8% titanium, 0.1-8% aluminum,
  • 0.05-0.5% copper or instead of copper 0.1-3% tantalum, wherein in the former case optionally hafnium or rhenium may be present with a content of 0.05-3% and in the second case, instead of rhenium or Hafnium 0.05-0.5% copper. Furthermore, optionally 0.05-3% molybdenum or tungsten may be provided.
  • WO 01/09403 A1 shows a nickel-based alloy with 11-13% chromium, 3-5% tungsten, 0.5-2.5% molybdenum, 3-5% aluminum 3-5% titanium, 3-7% tantalum, 0 - 12% cobalt, 0 - 1% niobium 0 - 2% hafnium, 0 - 1% zirconium, 0 - 0.05% boron, 0 - 0.2% carbon, 1 - 5% rhenium, 0 - 5% ruthenium, balance nickel.
  • the rhenium-promoted formation of embrittling intermetallic phases (Cr- and / or rhenium-containing precipitates) leads to a reduction in the lifetime due to cracking.
  • U.S. Patent 3,907,555 shows an alloy containing up to 6.5% tin.
  • the values of tin are at least 1.0 wt%.
  • tin is listed as a constituent of a Ni base alloy in which the allowable amount of tin is less than 25 ppm. This means that the proportion of tin is an undesirable impurity.
  • US Pat. No. 6,308,767 shows a method of manufacturing superalloy oriented structures by cooling a melt in another liquid metal. However, it must be ensured that tin does not contaminate the superalloy. Tin is therefore an undesirable component of the alloy.
  • U.S. Pat. No. 6,505,673 discloses a solder alloy containing 4.5% tin.
  • the invention has for its object to provide a component made of an alloy, in particular of a nickel, cobalt or iron-based superalloy, the particularly favorable properties in terms of high temperature strength, oxidation and corrosion resistance and stability against ductility-reducing formation of intermetallic phases over a has a long service life.
  • the object directed to a component is achieved by specifying a high-temperature-resistant component made from an alloy which has at least one strength promoter with a proportion of at most 2000 ppm, in particular 1100 ppm.
  • Weight percent (wt%) comprises: 9 - ⁇ 11% chromium (9 to less than 11),
  • rhenium and / or ruthenium in particular up to 5%, maximum 2000 ppm strength promoter
  • the strength promoter for a nickel-, cobalt- or iron-based superalloy whose composition otherwise comprises the following elements in percent by weight (wt%): 11-13% chromium, 3-5% tungsten,
  • molybdenum 0.5-2.5% molybdenum, 3-5% aluminum, 3-5% titanium, 3-7% tantalum, 0.1-10% rhenium and / or ruthenium, in particular up to 5%, maximum 2000ppm strength promoter, balance Nickel, cobalt or iron and impurities.
  • the superalloy of the specified component is specified in its composition for the first time so that for the component particularly favorable properties in terms of its high-temperature strength, its oxidation and corrosion resistance and stability against the formation of ductility-reducing intermetallic phases.
  • the invention is based on a chromium-rich superalloy.
  • a refined and high proportion of precipitates is achieved by the addition of the strength promoter, for example, that it represents a disturbance in the system and serves as a nucleating agent or a Keiminitiator, so that small amount is already sufficient.
  • the superalloy contains at most one weight percent niobium.
  • the superalloy optionally contains at least one of the following elements:
  • the cobalt content of the superalloy is less than 12 weight percent, while the niobium content is at most one weight percent.
  • a proportion of cobalt between 6 and 10% and a content of zirconium between 0 and 0.1% is advantageous.
  • the component has a directionally solidified grain structure.
  • the grain boundaries are aligned substantially along an axis. This results in a particularly high strength along this axis.
  • the component has a monocrystalline structure.
  • the ' monocrystalline structure prevents strength-reducing grain boundaries in the component and results in a particularly high strength.
  • the component is designed as a Gasturbinenleit- or - laufschaufei.
  • a gas turbine blade is exposed to particularly high demands in terms of high temperature resistance and oxidation / corrosion resistance.
  • the component may also be a part (blade) of a steam turbine or aircraft turbine.
  • FIG. 1 shows a blade
  • FIG. 2 shows a gas turbine
  • FIG. 3 shows a combustion chamber
  • FIG. 1 shows a perspective view of a blade 120, 130 which extends along a longitudinal axis 121.
  • the blade 120 may be a blade 120 or stator 130 of a turbomachine.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for
  • Electricity generation a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjoining thereto and an airfoil 406.
  • Blade tip 415 have another platform (not shown).
  • 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 designed, for example, as a hammer head.
  • the blade 120, 130 indicates for a medium, which at the
  • Airfoil 406 flows past, a leading edge 409 and a trailing edge 412 on.
  • blade 120, 130 massive metallic materials are used in all regions 400, 403, 406 of the blade 120, 130, for example.
  • the blade 120, 130 can in this case by a casting process, including by directional solidification, by a Forging process, be made 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.
  • Structures are also called directionally solidified structures.
  • the blade 120, 130 may be hollow or solid. When the blade 120, 130 is to be cooled, it is hollow and may still have film cooling holes (not shown). As protection against corrosion, the blade 120, 130, for example, corresponding mostly metallic coatings and as protection against heat usually still a ceramic coating.
  • the turbine blade 120, 130 is made of a nickel, cobalt or iron base superalloy having, for example, one of the following compositions:
  • Further strength promoters are, for example, lead (Pb), gallium (Ga), calcium (Ca), selenium (Se), arsenic (As); bismuth (Bi), neodymium (Nd), praseodymium (Pr), copper (Cu), aluminum oxide (A1 2 0 3), magnesia (MgO), Hafnia (Hf0 2), zirconia (Zr0 2), spinels (MgAl 2 0 4 ), Carbides or nitrides, or iron (Fe) in nickel- or cobalt-based superalloys. It can also be used several strength promoters.
  • the strength promoters may be metallic and / or ceramic. Various strength promoters made of metal and / or ceramic can be used.
  • the added amount in ppm always refers to the total amount of precipitation conveyor.
  • FIG. 2 shows by way of example a gas turbine 100 in one embodiment
  • the gas turbine 100 has inside a to a
  • Rotation axis 102 rotatably mounted rotor 103, which also as
  • Turbine rotor is called.
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 106 communicates with, for example, an annular hot gas channel 111.
  • annular hot gas channel 111 There, for example, four turbine stages 112 connected in series form the turbine
  • Each turbine stage 112 is formed of two blade rings.
  • 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.
  • a generator or work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 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 in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled 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 direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106.
  • the substrates may have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • the material used is iron, nickel or cobalt-based superalloys of the alloy according to the invention.
  • 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 yttrium (Y) and / or at least one element of the rare Erden) and have heat through a thermal barrier coating.
  • the thermal barrier coating consists, for example, of ZrO 2 , Y 2 O 4 -ZrO 2 , ie it is not, partially or completely stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced in the thermal barrier coating.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 3 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a plurality of burners 102 arranged around the turbine shaft 103 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the turbine shaft 103 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 side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 is equipped on the working medium side with a particularly heat-resistant protective layer or made of high-temperature-resistant material. Due to the high temperatures in the interior of the combustion chamber 110, a cooling system is additionally provided for the heat shield elements 155 or for their holding elements.
  • the materials of the combustor wall 153 and its coatings are similar to the turbine blades 120, 130.
  • the combustion chamber 110 is designed in particular for detecting losses of the heat shield elements 155.
  • a number of temperature sensors 158 are positioned between the combustion chamber wall 153 and the heat shield elements 155.
  • FIG. 4 shows the results of a low-cycle fatigue test (LCF).
  • a certain relative elongation ⁇ is predetermined, that is, the sample is alternately loaded with predetermined relative elongation under tension or pressure.
  • the elongation is given and the experiment is carried out at different temperatures, e.g. 850 ° C or 950 ° C performed.
  • the number of cycles N is measured.
  • the maximum number of cycles performed until the sample is fractured is plotted on the graph.
  • the samples are better, which has the greater number of cycles at a certain strain ⁇ .
  • the experiments were carried out with a sample of a PWA 1483 alloy with a minimum tin content ⁇ 1 ppm and a tin content of 1110 ppm.
  • FIG. 5 shows the test results of high-cycle fatigue tests at 500 ° C.
  • the value of the AC voltage reached for the sample without tin is also normalized to 100%.
  • the samples with tin (lOOppm) could be exposed to a higher AC voltage even at a higher medium voltage in order to achieve the desired number of cycles of 10 8 cycles (fatigue strength).
  • FIG. 6 shows, like FIG. 5, the test results at a higher temperature of 800 ° C. at a mean stress of 0 MPa.
  • the value of the AC voltage reached for the sample without tin is normalized to 100%.
  • FIG. 7 shows, like FIG. 6, the test results at the temperature of 800 ° C. at an average voltage normalized to the mean stress of the sample without tin.
  • the value of the AC voltage reached for the sample without tin is also normalized to 100%.
  • the samples with tin (lOOppm) could be exposed to a higher AC voltage even at a higher medium voltage in order to achieve the desired number of cycles of 10 8 cycles (fatigue strength).

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  • 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

L'invention concerne une pièce résistant à des températures élevées, constituée d'un alliage, notamment d'un superalliage à base de nickel, présentant la composition suivante: 9-13 % en poids de Cr, 3-5 % en poids de W, 0,5-2,5 % en poids de Mo, 3-5 % en poids d'Al, 3-5 % en poids de Ti, 3-7 % en poids de Ta, 1-5 % en poids de Re, jusqu'à 2000 ppm d'un matériau améliorant la résistance mécanique (Sn), le reste étant constitué de nickel.
EP04790725A 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees Withdrawn EP1685264A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP04790725A EP1685264A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees
EP07019290A EP1914326A3 (fr) 2003-11-27 2004-10-21 Composant résistant aux températures élevées

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP03027388A EP1536026A1 (fr) 2003-11-27 2003-11-27 Pièce résistante à des températures élevées
PCT/EP2004/011923 WO2005061742A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees
EP04790725A EP1685264A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP07019290A Division EP1914326A3 (fr) 2003-11-27 2004-10-21 Composant résistant aux températures élevées

Publications (1)

Publication Number Publication Date
EP1685264A1 true EP1685264A1 (fr) 2006-08-02

Family

ID=34442900

Family Applications (3)

Application Number Title Priority Date Filing Date
EP03027388A Withdrawn EP1536026A1 (fr) 2003-11-27 2003-11-27 Pièce résistante à des températures élevées
EP07019290A Withdrawn EP1914326A3 (fr) 2003-11-27 2004-10-21 Composant résistant aux températures élevées
EP04790725A Withdrawn EP1685264A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees

Family Applications Before (2)

Application Number Title Priority Date Filing Date
EP03027388A Withdrawn EP1536026A1 (fr) 2003-11-27 2003-11-27 Pièce résistante à des températures élevées
EP07019290A Withdrawn EP1914326A3 (fr) 2003-11-27 2004-10-21 Composant résistant aux températures élevées

Country Status (4)

Country Link
US (1) US20070071607A1 (fr)
EP (3) EP1536026A1 (fr)
CN (1) CN100549197C (fr)
WO (1) WO2005061742A1 (fr)

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CN102443721B (zh) * 2010-10-13 2013-10-09 中国科学院金属研究所 一种组织稳定性好、易加工的镍钴基高温合金
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CN103789576B (zh) * 2014-01-15 2016-03-02 常州大学 一种高晶界强度镍基合金及其制备方法
DE102014220179A1 (de) * 2014-10-06 2016-04-07 Siemens Aktiengesellschaft Nickelbasierter Werkstoff mit Platin, Verwendung als Schweißzusatzwerkstoff und Bauteil
CN105506382A (zh) * 2015-12-21 2016-04-20 常熟市梅李合金材料有限公司 高电阻电热合金丝
CN106756250A (zh) * 2016-12-14 2017-05-31 张家港市广大机械锻造有限公司 一种用于航空器发射平台的高强耐火合金
CN106676366B (zh) * 2017-01-16 2018-12-28 宁国市华成金研科技有限公司 耐高温合金的制备方法
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WO2005061742A1 (fr) 2005-07-07
CN1886525A (zh) 2006-12-27
EP1914326A3 (fr) 2009-11-25
CN100549197C (zh) 2009-10-14
EP1914326A2 (fr) 2008-04-23
EP1536026A1 (fr) 2005-06-01

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