EP1914326A2 - Composant résistant aux températures élevées - Google Patents

Composant résistant aux températures élevées Download PDF

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Publication number
EP1914326A2
EP1914326A2 EP07019290A EP07019290A EP1914326A2 EP 1914326 A2 EP1914326 A2 EP 1914326A2 EP 07019290 A EP07019290 A EP 07019290A EP 07019290 A EP07019290 A EP 07019290A EP 1914326 A2 EP1914326 A2 EP 1914326A2
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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Withdrawn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
EP07019290A
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German (de)
English (en)
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EP1914326A3 (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
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP07019290A priority Critical patent/EP1914326A3/fr
Publication of EP1914326A2 publication Critical patent/EP1914326A2/fr
Publication of EP1914326A3 publication Critical patent/EP1914326A3/fr
Withdrawn legal-status Critical Current

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    • 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, 3.5- 4.5% titanium, 3-4% aluminum, 0.005-0.025% boron, 0.05-0.4% zirconium, balance nickel. Furthermore, 0.01-3% hafnium is additionally included in the alloy.
  • the described heat treatment causes a block-like carbide formation and a finely dispersed precipitation of a Ni 3 (Al, Ti) phase.
  • the US Patent No. 5,611,670 discloses a blade for a gas turbine.
  • the blade has a single crystal platform region and a single crystalline 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.
  • the EP 0 297 785 B1 is a nickel-based superalloy for single crystals disclosed.
  • 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.
  • This superalloy achieves both high temperature crack resistance and corrosion resistance. In order not to affect the corrosion resistance, the titanium content must not exceed two percent by weight.
  • the US Patent No. 5,122,206 is a nickel-based superalloy specified, 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 Copper 0.1-3% tantalum, in the former case optionally also hafnium or rhenium with a content of 0.05-3% may be present 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.
  • the WO 01/09403 A1 shows a nickel base alloy containing 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.
  • the 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%.
  • the U.S. Patent 6,308,767 shows a manufacturing method of directional structures of a superalloy, in which a melt is cooled 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.
  • 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.
  • the strength can be improved by a refined and high proportion of precipitates ( ⁇ '-phase) in the alloy.
  • the superalloy of the specified component is specified in its composition for the first time so that the component particularly favorable properties in terms of its high temperature resistance, 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 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 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 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 minimum content of the precipitation conveyor is preferably 50 ppm, in particular 75 ppm. It is preferably between 100 and 500 ppm and in particular 100 ppm.
  • the superalloy contains at most one weight percent niobium.
  • a particularly high high-temperature strength can also be achieved by addition of ruthenium and without a rhenium content, wherein the oxidation / corrosion resistance is also high in the given composition at the same time.
  • 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. Due to the monocrystalline structure strength-reducing grain boundaries are avoided in the component and there is a particularly high strength.
  • the component is designed as a gas turbine guide or - bucket.
  • 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 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 power 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.
  • the blade at its blade tip 415 may 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. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • blades 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 be made 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.
  • directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as 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.
  • Further strength promoters are, for example, lead (Pb), gallium (Ga), calcium (Ca), selenium (Se), arsenic (As); Bismuth (Bi), neodymium (Nd), praseodymium (Pr), copper (Cu), alumina (Al 2 O 3 ), magnesia (MgO), hafnia (HfO 2 ), zirconia (ZrO 2 ), spinels (MgAl 2 O 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 a partial longitudinal section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • 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 an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed of two blade rings.
  • a series 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. Coupled to the rotor 103 is 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. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • 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 anticorrosive coatings (MCrA1X; 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 ones 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 is the rotor 103 facing 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 specific relative elongation ⁇ is predetermined, ie the sample is loaded alternately with predetermined relative elongation under tension or pressure.
  • the elongation is specified and the experiment is carried out at various temperatures, such as 850 ° C or 950 ° C.
  • 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.
  • the curves containing 1110 ppm tin show higher number of cycles N than the samples without tin ( ⁇ 1 ppm).
  • FIG. 5 shows the test results of high-cycle fatigue tests at 500 ° C.
  • different AC voltages are applied at a certain temperature and a predetermined average voltage and a predetermined number of cycles in order to achieve a desired number of cycles of 10 8 cycles (fatigue strength).
  • the value of the mean voltage for the sample without tin is here standardized to 100%.
  • the value of the AC voltage reached for the sample without tin is also normalized to 100%.
  • the samples with tin (100 ppm) 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%. Again, the samples with 100 ppm tin are superior to the samples without tin.
  • 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 (100 ppm) 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)
EP07019290A 2003-11-27 2004-10-21 Composant résistant aux températures élevées Withdrawn EP1914326A3 (fr)

Priority Applications (1)

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

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
EP04790725A Division EP1685264A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees

Publications (2)

Publication Number Publication Date
EP1914326A2 true EP1914326A2 (fr) 2008-04-23
EP1914326A3 EP1914326A3 (fr) 2009-11-25

Family

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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
EP04790725A Withdrawn EP1685264A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees
EP07019290A Withdrawn EP1914326A3 (fr) 2003-11-27 2004-10-21 Composant résistant aux températures élevées

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
EP04790725A Withdrawn EP1685264A1 (fr) 2003-11-27 2004-10-21 Piece resistant a des temperatures elevees

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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DE102014220179A1 (de) * 2014-10-06 2016-04-07 Siemens Aktiengesellschaft Nickelbasierter Werkstoff mit Platin, Verwendung als Schweißzusatzwerkstoff und Bauteil

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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
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
CN107699806A (zh) * 2017-11-20 2018-02-16 广西双宸贸易有限责任公司 一种铁基高温材料
CN112593122B (zh) * 2020-12-09 2023-02-03 中国科学院金属研究所 一种长寿命高强抗热腐蚀单晶高温合金
CN112853154B (zh) * 2021-01-04 2022-02-22 广东省科学院中乌焊接研究所 镍基中间层合金材料及其制备方法、焊件及焊接方法以及应用
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EP1536026A1 (fr) 2005-06-01
CN100549197C (zh) 2009-10-14
EP1914326A3 (fr) 2009-11-25
US20070071607A1 (en) 2007-03-29
CN1886525A (zh) 2006-12-27
EP1685264A1 (fr) 2006-08-02

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