WO2008034392A1 - Élément de turbine - Google Patents

Élément de turbine Download PDF

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Publication number
WO2008034392A1
WO2008034392A1 PCT/DE2006/001654 DE2006001654W WO2008034392A1 WO 2008034392 A1 WO2008034392 A1 WO 2008034392A1 DE 2006001654 W DE2006001654 W DE 2006001654W WO 2008034392 A1 WO2008034392 A1 WO 2008034392A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine component
turbine
oxide
base material
particles
Prior art date
Application number
PCT/DE2006/001654
Other languages
German (de)
English (en)
Inventor
Rene Jabado
Jens Dahl Jensen
Ursus KRÜGER
Daniel Körtvelyessy
Volkmar LÜTHEN
Ralph Reiche
Michael Rindler
Raymond Ullrich
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/DE2006/001654 priority Critical patent/WO2008034392A1/fr
Priority to DE112006004142T priority patent/DE112006004142A5/de
Publication of WO2008034392A1 publication Critical patent/WO2008034392A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • 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
    • 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
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • C22C32/001—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides
    • C22C32/0015—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ with only oxides with only single oxides as main non-metallic constituents
    • C22C32/0026—Matrix based on Ni, Co, Cr or alloys thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for 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
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0463—Cobalt
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/11—Iron
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/134—Zirconium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2112—Aluminium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/21—Oxide ceramics
    • F05D2300/2118—Zirconium oxides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/228—Nitrides
    • F05D2300/2281—Nitrides of aluminium
    • 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
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a turbine component made of a metallic base material.
  • Turbine components that are exposed to a corrosive and / or oxidizing hot gas environment are made of metallic base materials, so-called high-temperature superalloys. These are iron (Fe), cobalt (Co) or nickel (Ni) based alloys. But despite the high heat resistance of such materials and although the turbine components are usually still provided with a corrosion and / or oxidation-inhibiting coating, cracks occur after a certain period of operation in a corrosive and / or oxidative hot gas environment due to oxidation. Oxides are then also formed on the crack surfaces. The oxides, which are formed from various constituents of the superalloy, lead to a degradation of the material properties and thereby to an increase in the cracks.
  • Turbine components must therefore be removed after a certain period of operation and subjected to refurbishment.
  • the crack walls are cleaned of oxides, the cracks filled up again and, if a coating was present, the coating applied again. If the oxidation has progressed too far, the part will be disposed of.
  • the cleaning of the cracks from the oxides in the course of a refurbishment is a complex process step, since the different oxides necessitate different cleaning treatments.
  • the oxides can also be removed mechanically, but this leads to a further loss of material and leads to an enlargement of the area to be replenished. In general, however, one endeavors to keep the areas to be filled as small as possible in order to avoid weak points in the rebuilt turbine component.
  • Object of the present invention is therefore to provide a turbine component available, in which the above problem does not occur or at least to a reduced extent.
  • a turbine component according to the invention consists of a metallic base material as well as of particles distributed in the base material of a particle material which has a higher affinity for oxygen than the base material. If cracks occur in such a turbine component, which may be, for example, a rotor or rotor of a turbine or a component of the combustion chamber lining, in which form oxides, the increased affinity of the particulate material for oxygen, that the oxide formed on the crack surfaces is an oxide of the particulate material. There is therefore only one type of oxide and no mixed oxide, as is the case in the prior art, since oxides of different constituents of the superalloy are formed there.
  • the particles are homogeneously distributed in the turbine component at least in the region in which cracks can occur.
  • the particulate material is chosen such that its oxide leads to a passivation of an oxidized surface.
  • Suitable particle materials are, for example, titanium (Ti), tantalum (Ta) or zirconium (Zr).
  • Ti titanium
  • Ta tantalum
  • Zr zirconium
  • the passivation of the crack surface by the oxide of the particulate material then prevents an expansion of the crack due to oxidation.
  • mixed oxides as occur in the prior art, an expansion of the cracks by progressive oxidation can not be avoided.
  • the described embodiment of the invention therefore, the operating life of a turbine component can be extended before it must be subjected to a refurbishment.
  • there are special cleaning processes for the oxides of titanium, tantalum and zircon which can be used in refurbishment.
  • the advantages of the particles introduced into the base material can be used, in particular, for base materials which are high-temperature resistant materials, for example iron, cobalt or nickel superalloys. Due to the high affinity of the particulate material for oxygen, it is advantageous if the particles are encapsulated.
  • the encapsulating material can then be chosen so that it Oxidation of the particulate material slows down and thus counteracts too much EnergyokoSetzung due to the oxidation.
  • the speed of the oxidation process can be influenced by the sheath. Suitable materials for the sheath are, for example, metal oxides or metal ceramics.
  • FIG. 1 shows a turbine blade as an example of a turbine component.
  • Figure 2 shows a highly schematic of a section through the
  • Figure 3 shows the section of Figure 2 with a crack whose walls are oxidized.
  • FIG. 1 shows a perspective view of a blade 120 or Leitschaufei 130 a turbomachine, which extends along a longitudinal axis 121.
  • 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 adjacent thereto and an airfoil 406 and a blade tip 415.
  • a guide vane 130 can the blade 130 at its 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. 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 for example, massive metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • 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; These documents are part of the disclosure regarding the chemical composition of the alloy.
  • 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.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. 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 ones Earth, or hafnium (Hf)).
  • 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 ones Earth, 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, which should be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • suitable coating processes such as electron beam evaporation (EB-PVD)
  • stalk-shaped grains are produced in the thermal barrier coating.
  • Other coating methods are conceivable, for example atmospheric plasma spraying (APS), LPPS, VPS or CVD.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on.
  • FIG. 2 shows, in highly schematic form, a section through the wall of the turbine blade 120. For the sake of simplicity, these are
  • Coatings that may be present on the surface 3 of the turbine blade 120, not shown.
  • coated titanium particles 5 are homogeneously distributed.
  • the material of the sheath is titanium nitride (TiN), ie a metal ceramic.
  • titanium particles instead of titanium particles, it is also possible for other particles, for example tantalum particles or zirconium particles with or without sheathing, to be distributed in the superalloy 1.
  • the mentioned particle materials All have two properties that make them suitable for use in the form of particles in the superalloy 1. On the one hand, there are special cleaning methods that can be used to remove the oxides of these materials. This allows the use of very special cleaning processes in the refurbishment of turbine blades. On the other hand, the oxides of these materials have a passivating effect, so that a resulting oxide counteracts further oxidation.
  • metal ceramics may also be used as material for the sheathing, for example aluminum nitride (AlN).
  • AlN aluminum nitride
  • metal oxides such as aluminum oxide (Al 2 O 3 ) or titanium oxide (TiO, Ti 2 O 3 , TiO 2 ).
  • FIG. 3 shows the detail from FIG. 2 after the turbine blade 120 in a gas turbine was in operation.
  • cracks 7 may have developed in the turbine blade 120, which extend from the surface 3 into the main body of the turbine blade 120. Due to the corrosive and / or oxidative properties of the hot gas to which the turbine blade 120 is exposed during operation, an oxide layer 9 is formed on the crack surface 8. Because of the higher affinity of the particulate material for oxygen compared to the material components of the superalloy, the oxide layer 9 formed on the crack surface 8 exclusively or almost exclusively consists of oxide of the particulate material, ie titanium oxide in the present exemplary embodiment.
  • this oxide has passivating properties, it counteracts an enlargement of the crack 7 by preventing further oxidation.
  • the oxide layer 9 can be removed with a cleaning method specially adapted to this oxide. The cleaning of cracks 7 in the turbine blade 120 (as well as in other turbine components) can therefore be optimized, which reduces the complexity and thus the cost of the refurbishment.
  • the oxidation of the base material can be inhibited.
  • the rate of components that must be replaced due to cracks that have excessive oxidation can therefore be reduced.
  • the embodiment of the turbine component according to the invention makes it possible to optimize the cleaning process for removing the oxide from the cracks.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

L'invention concerne un élément de turbine (120) comprenant un matériau de base (1) métallique dans lequel sont réparties des particules (5) composées d'un matériau qui présente une affinité avec l'oxygène supérieure à celle du matériau de base.
PCT/DE2006/001654 2006-09-18 2006-09-18 Élément de turbine WO2008034392A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/DE2006/001654 WO2008034392A1 (fr) 2006-09-18 2006-09-18 Élément de turbine
DE112006004142T DE112006004142A5 (de) 2006-09-18 2006-09-18 Turbinenbauteil

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/DE2006/001654 WO2008034392A1 (fr) 2006-09-18 2006-09-18 Élément de turbine

Publications (1)

Publication Number Publication Date
WO2008034392A1 true WO2008034392A1 (fr) 2008-03-27

Family

ID=37891728

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2006/001654 WO2008034392A1 (fr) 2006-09-18 2006-09-18 Élément de turbine

Country Status (2)

Country Link
DE (1) DE112006004142A5 (fr)
WO (1) WO2008034392A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010014832B4 (de) 2010-04-10 2018-04-26 Technische Universität Braunschweig Leicht bearbeitbare Nickelbasis-Legierung
CN113898416A (zh) * 2021-09-02 2022-01-07 北京航空航天大学 一种液态金属冷却叶片系统及其防腐蚀方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0534164A2 (fr) * 1991-08-28 1993-03-31 Hitachi, Ltd. Alliages résistant à la chaleur renforcés par dispersion de nitrures
DE4434515A1 (de) * 1993-09-27 1995-03-30 Hitachi Ltd Oxid-dispersionsverfestigte Legierung und aus dieser Legierung hergestellte Hochtemperaturausrüstung
JPH07242960A (ja) * 1994-02-28 1995-09-19 Daido Steel Co Ltd 酸化物分散強化合金の製造方法
DE4437463A1 (de) * 1994-07-11 1996-01-18 Max Planck Gesellschaft Kriechfester Hochtemperaturwerkstoff
EP1598434A1 (fr) * 2004-05-17 2005-11-23 General Electric Company Procédé de fabrication d'un article en alliage métallique sans fusion

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0534164A2 (fr) * 1991-08-28 1993-03-31 Hitachi, Ltd. Alliages résistant à la chaleur renforcés par dispersion de nitrures
DE4434515A1 (de) * 1993-09-27 1995-03-30 Hitachi Ltd Oxid-dispersionsverfestigte Legierung und aus dieser Legierung hergestellte Hochtemperaturausrüstung
JPH07242960A (ja) * 1994-02-28 1995-09-19 Daido Steel Co Ltd 酸化物分散強化合金の製造方法
DE4437463A1 (de) * 1994-07-11 1996-01-18 Max Planck Gesellschaft Kriechfester Hochtemperaturwerkstoff
EP1598434A1 (fr) * 2004-05-17 2005-11-23 General Electric Company Procédé de fabrication d'un article en alliage métallique sans fusion

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010014832B4 (de) 2010-04-10 2018-04-26 Technische Universität Braunschweig Leicht bearbeitbare Nickelbasis-Legierung
CN113898416A (zh) * 2021-09-02 2022-01-07 北京航空航天大学 一种液态金属冷却叶片系统及其防腐蚀方法
CN113898416B (zh) * 2021-09-02 2022-07-22 北京航空航天大学 一种液态金属冷却叶片系统及其防腐蚀方法

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Publication number Publication date
DE112006004142A5 (de) 2009-09-03

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