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WO2008034392A1 - Turbine component - Google Patents

Turbine component 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
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.)
Ceased
Application number
PCT/DE2006/001654
Other languages
German (de)
French (fr)
Inventor
Rene Jabado
Jens Dahl Jensen
Ursus KRÜGER
Daniel Körtvelyessy
Volkmar LÜTHEN
Ralph Reiche
Michael Rindler
Raymond Ullrich
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to DE112006004142T priority Critical patent/DE112006004142A5/en
Priority to PCT/DE2006/001654 priority patent/WO2008034392A1/en
Publication of WO2008034392A1 publication Critical patent/WO2008034392A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • 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.

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

Abstract

The invention relates to a turbine component (120) consisting of a metal base material (1) and particles (5) of a particulate material that are distributed in said base material (1). The particulate material has a higher affinity with oxygen than the base material.

Description

Turbinenbauteil turbine component

Die Erfindung betrifft ein Turbinenbauteil aus einem metallischen Basismaterial .The invention relates to a turbine component made of a metallic base material.

Turbinenbauteile, die einer korrodierenden und/oder oxidie- renden Heißgasumgebung ausgesetzt sind, sind aus metallischen Basismaterialien, so genannten hochwarmfesten Superlegierun- gen hergestellt. Dies sind Legierungen auf Eisen (Fe)-, Kobalt (Co)- oder Nickel (Ni)-basis. Aber trotz der Hochwarmfestigkeit derartiger Materialien und obwohl die Turbinenbauteile zumeist noch mit einer korrosions- und/oder oxidationshemmenden Beschichtung versehen sind, treten nach einer bestimmten Betriebsdauer in einer korrosiven und/oder oxidati- ven Heißgasumgebung auf Grund von Oxidation Risse auf. Auf den Rissoberflächen bilden sich dann ebenfalls Oxide. Die Oxide, die aus verschiedenen Bestandteilen der Superlegierung gebildet werden, führen zu einer Degradierung der Materialeigenschaften und dadurch zu einer Vergrößerung der Risse. Turbinenbauteile müssen daher nach einer bestimmten Betriebsdauer ausgebaut und einer Wiederaufarbeitung (Refurbishment) unterzogen werden. Dabei werden die Risswände von Oxiden gesäubert, die Risse wieder aufgefüllt und, falls eine Beschichtung vorhanden war, die Beschichtung wieder aufgebracht. Falls die Oxidation zu weit fortgeschritten ist, wird das Teil entsorgt .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.

Das Reinigen der Risse von den Oxiden im Rahmen eines Refur- bishments ist ein aufwendiger Prozessschritt, da die verschiedenen Oxide verschiedene Säuberungsbehandlungen notwendig machen. Alternativ können die Oxide auch mechanisch entfernt werden, was jedoch zu einem weiteren Materialverlust und zu einer Vergrößerung des wieder aufzufüllenden Bereiches führt. Generell ist man jedoch bestrebt, die aufzufüllenden Bereiche möglichst klein zu halten, um Schwachstellen im wieder aufgearbeiteten Turbinenbauteil zu vermeiden.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. Alternatively, 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.

Aufgabe der vorliegenden Erfindung ist es daher, ein Turbinenbauteil zur Verfügung zu stellen, bei dem die oben genannte Problematik nicht oder zumindest im verringerten Umfange auftritt .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.

Diese Aufgabe wird durch einen Turbinenbauteil nach Anspruch 1 gelöst . Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.This object is achieved by a turbine component according to claim 1. The dependent claims contain advantageous embodiments of the invention.

Ein erfindungsgemäßes Turbinenbauteil besteht aus einem metallischen Basismaterial sowie aus im Basismaterial verteilten Partikeln aus einem Partikelmaterial, das eine höhere Affinität zu Sauerstoff aufweist als das Basismaterial. Falls in einem derartigen Turbinenbauteil, das beispielsweise eine Leit- oder Laufschaufei einer Turbine oder ein Bauelement der Brennkammerauskleidung sein kann, Risse auftreten, in denen sich Oxide bilden, so führt die erhöhte Affinität des Partikelmaterials zu Sauerstoff dazu, dass das an den Rissoberflächen gebildete Oxid ein Oxid des Partikelmaterials ist. Es entsteht daher lediglich eine Sorte Oxid und keine Mischoxid, wie dies im Stand der Technik der Fall ist, da dort Oxide aus verschiedenen Bestandteilen der Superlegierung gebildet werden. Da an der Rissoberfläche eines erfindungsgemäßen- Turbinenbauteils also lediglich ein einziges spezifisches Oxid vorliegt, wird zum Reinigen des Risses vom Oxid lediglich ein einziger Reinigungsprozess benötigt, der sehr speziell auf das spezifische Oxid abgestellt ist. Der Aufwand zum Reinigen der Risse im Rahmen des Refurbishments kann daher verringert werden. Auch eine Ausweitung der Risse auf Grund mechanischer Reinigungsprozesse kann vermieden werden. Das Partikelmaterial ist daher vorteilhafterweise im Hinblick auf einen Reini- gungsprozess zum Entfernen seines Oxides von einer Rissoberfläche ausgewählt .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. Since there is only a single specific oxide on the crack surface of a turbine component according to the invention, only a single cleaning process is required to clean the crack from the oxide, which is very specifically tailored to the specific oxide. The effort to clean the cracks in the context of the refurbishment can therefore be reduced. Also an extension of the cracks due to mechanical Cleaning processes can be avoided. The particulate material is therefore advantageously selected in view of a cleaning process for removing its oxide from a crack surface.

Damit sichergestellt werden kann, dass in allen Bereichen der Oberfläche eines Risses genügend Partikel zum Oxidieren vorhanden sind, ist es vorteilhaft, wenn die Partikel homogen im Turbinenbauteil zumindest in dem Bereich, in dem Risse auf- treten können, verteilt sind.In order to ensure that sufficient particles for oxidation are present in all regions of the surface of a crack, it is advantageous if the particles are homogeneously distributed in the turbine component at least in the region in which cracks can occur.

In einer äußert vorteilhaften Weiterbildung der Erfindung ist das Partikelmaterial so gewählt, dass sein Oxid zu einer Pas- sivierung einer oxidierten Oberfläche führt. Geeignete Parti- kelmaterialien sind hierbei beispielsweise Titan (Ti) , Tantal (Ta) oder Zirkon (Zr) . Die Passivierung der Rissoberfläche durch das Oxid des Partikelmaterials verhindert dann eine Ausweitung des Risses auf Grund von Oxidation. Bei Mischoxiden, wie sie im Stand der Technik auftreten, kann eine Aus- weitung der Risse durch fortschreitende Oxidation nicht vermieden werden. Mit der beschriebenen Ausgestaltung der Erfindung kann daher die Betriebsdauer eines Turbinenbauteils verlängert werden, bevor es einem Refurbishment unterzogen werden muss. Zusätzlich gibt es für die Oxide von Titan, Tantal und Zirkon spezielle Reinigungsprozesse, die im Refurbishment zum Einsatz kommen können.In an extremely advantageous development of the invention, the particulate material is chosen such that its oxide leads to a passivation of an oxidized surface. Suitable particle materials here are, for example, titanium (Ti), tantalum (Ta) or zirconium (Zr). The passivation of the crack surface by the oxide of the particulate material then prevents an expansion of the crack due to oxidation. With mixed oxides, as occur in the prior art, an expansion of the cracks by progressive oxidation can not be avoided. With 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. In addition, there are special cleaning processes for the oxides of titanium, tantalum and zircon which can be used in refurbishment.

Die Vorteile der in das Basismaterial eingebrachten Partikel lassen sich insbesondere bei Basismaterialien nutzen, die hochtemperaturfeste Materialien, beispielsweise Superlegie- rungen auf Eisen-, Kobalt-, oder Nickelbasis, sind. Auf Grund der hohen Affinität des Partikelmaterials zu Sauerstoff ist es vorteilhaft, wenn die Partikel ummantelt (gekapselt) sind. Das Kapselungsmaterial kann dann so gewählt sein, dass es die Oxidation des Partikelmaterials verlangsamt und somit einer zu starken EnergiefreiSetzung auf Grund der Oxidation entgegengewirkt. Außerdem kann die Geschwindigkeit des Oxidations- prozesses durch die Ummantelung beeinflusst werden. Geeignete Materialien für die Ummantelung sind beispielsweise Metall- oxide oder Metallkeramiken.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 EnergiefreiSetzung due to the oxidation. In addition, 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.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung ei- nes Ausführungsbeispiels unter Bezugnahme auf die beiliegenden Figuren.Further features, properties and advantages of the present invention will become apparent from the following description of an embodiment with reference to the accompanying figures.

Figur 1 zeigt eine Turbinenschaufel als ein Beispiel für ein Turbinenbauteil .FIG. 1 shows a turbine blade as an example of a turbine component.

Figur 2 zeigt stark schematisiert einen Schnitt durch dieFigure 2 shows a highly schematic of a section through the

Wand der Turbinenschaufel aus Figur 1.Wall of the turbine blade from FIG. 1.

Figur 3 zeigt den Schnitt aus Figur 2 mit einem Riss, dessen Wände oxidiert sind.Figure 3 shows the section of Figure 2 with a crack whose walls are oxidized.

Die Figur 1 zeigt in perspektivischer Ansicht eine Laufschaufel 120 oder Leitschaufei 130 einer Strömungsmaschine, die sich entlang einer Längsachse 121 erstreckt.1 shows a perspective view of a blade 120 or Leitschaufei 130 a turbomachine, which extends along a longitudinal axis 121.

Die Strömungsmaschine kann eine Gasturbine eines Flugzeugs oder eines Kraftwerks zur Elektrizitätserzeugung, eine Dampfturbine oder ein Kompressor sein.The turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.

Die Schaufel 120, 130 weist entlang der Längsachse 121 aufeinander folgend einen Befestigungsbereich 400, eine daran angrenzende Schaufelplattform 403 sowie ein Schaufelblatt 406 und eine Schaufelspitze 415 auf. Als Leitschaufel 130 kann die Schaufel 130 an ihrer Schaufelspitze 415 eine weitere Plattform aufweisen (nicht dargestellt) .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. As a guide vane 130 can the blade 130 at its blade tip 415 have another platform (not shown).

Im Befestigungsbereich 400 ist ein Schaufelfuß 183 gebildet, der zur Befestigung der Laufschaufeln 120, 130 an einer Welle oder einer Scheibe dient (nicht dargestellt) . Der Schaufelfuß 183 ist beispielsweise als Hammerkopf ausgestaltet. Andere Ausgestaltungen als Tannenbaum- oder Schwalbenschwanzfuß sind möglich. Die Schaufel 120, 130 weist für ein Medium, das an dem Schaufelblatt 406 vorbeiströmt, eine Anströmkante 409 und eine Abströmkante 412 auf.In the mounting region 400, 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.

Bei herkömmlichen Schaufeln 120, 130 werden in allen Berei- chen 400, 403, 406 der Schaufel 120, 130 beispielsweise massive metallische Werkstoffe, insbesondere Superlegierungen verwendet. Solche Superlegierungen sind beispielsweise aus der EP 1 204 776 Bl, EP 1 306 454, EP 1 319 729 Al, WO 99/67435 oder WO 00/44949 bekannt; diese Schriften sind bzgl. der chemischen Zusammensetzung der Legierung Teil der Offenbarung. Die Schaufel 120, 130 kann hierbei durch ein Gussverfahren, auch mittels gerichteter Erstarrung, durch ein Schmiedeverfahren, durch ein Fräsverfahren oder Kombinationen daraus gefertigt sein.In conventional blades 120, 130, for example, massive metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130. 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; 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.

Werkstücke mit einkristalliner Struktur oder Strukturen werden als Bauteile für Maschinen eingesetzt, die im Betrieb hohen mechanischen, thermischen und/oder chemischen Belastungen ausgesetzt sind. Die Fertigung von derartigen einkristallinen Werkstücken erfolgt z.B. durch gerichtetes Erstarren aus der Schmelze. Es handelt sich dabei um Gießverfahren, bei denen die flüssige metallische Legierung zur einkristallinen Struktur, d.h. zum einkristallinen Werkstück, oder gerichtet erstarrt. Dabei werden dendritische Kristalle entlang dem War- mefluss ausgerichtet und bilden entweder eine stängelkristal- line Kornstruktur (kolumnar, d.h. Körner, die über die ganze Länge des Werkstückes verlaufen und hier, dem allgemeinen Sprachgebrauch nach, als gerichtet erstarrt bezeichnet wer- den) oder eine einkristalline Struktur, d.h. das ganze Werkstück besteht aus einem einzigen Kristall . In diesen Verfahren muss man den Übergang zur globulitischen (polykristallinen) Erstarrung meiden, da sich durch ungerichtetes Wachstum notwendigerweise transversale und longitudinale Korngren- zen ausbilden, welche die guten Eigenschaften des gerichtet erstarrten oder einkristallinen Bauteiles zunichte machen. Ist allgemein von gerichtet erstarrten Gefügen die Rede, so sind damit sowohl Einkristalle gemeint, die keine Korngrenzen oder höchstens Kleinwinkelkorngrenzen aufweisen, als auch Stängelkristallstrukturen, die wohl in longitudinaler Richtung verlaufende Korngrenzen, aber keine transversalen Korngrenzen aufweisen. Bei diesen zweitgenannten kristallinen Strukturen spricht man auch von gerichtet erstarrten Gefügen (directionally solidified structures) . Solche Verfahren sind aus der US-PS 6,024,792 und der EP 0 892 090 Al bekannt; diese Schriften sind bzgl . des Erstarrungsverfahrens Teil der Offenbarung .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. The production of such monocrystalline workpieces, for example, by directed solidification from the melt. These are casting methods in which the liquid metallic alloy solidifies into a monocrystalline structure, ie a single-crystal workpiece, or directionally. Dendritic crystals are deposited along the aligned and form either a columnar crystal grain structure (columnar, ie grains that run the entire length of the workpiece and here, the general usage, referred to as directed solidified) or a monocrystalline structure, ie the entire workpiece consists from a single crystal. In these processes, one must avoid the transition to globulitic (polycrystalline) solidification, since non-directional growth necessarily produces transverse and longitudinal grain boundaries which negate the good properties of the directionally solidified or monocrystalline component. The term generally refers to 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. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1; These writings are with respect. the solidification process part of the disclosure.

Ebenso können die Schaufeln 120, 130 Beschichtungen gegen Korrosion oder Oxidation aufweisen, z. B. (MCrAlX; M ist zumindest ein Element der Gruppe Eisen (Fe) , Kobalt (Co) , Nickel (Ni) , X ist ein Aktivelement und steht für Yttrium (Y) und/oder Silizium und/oder zumindest ein Element der Seltenen Erden, bzw. Hafnium (Hf) ) . Solche Legierungen sind bekannt aus der EP 0 486 489 Bl, EP 0 786 017 Bl, EP 0 412 397 Bl oder EP 1 306 454 Al, die bzgl. der chemischen Zusammensetzung der Legierung Teil dieser Offenbarung sein sollen. Die Dichte liegt vorzugsweise bei 95% der theoretischen Dichte. Auf der MCrAlX-Schicht (als Zwischenschicht oder als äußerste Schicht) bildet sich eine schützende Aluminiumoxidschicht (TGO = thermal grown oxide layer) .Likewise, 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)). 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. On the MCrAlX layer (as an intermediate layer or as the outermost layer) Layer) forms a protective aluminum oxide layer (TGO = thermal grown oxide layer).

Auf der MCrAlX kann noch eine Wärmedämmschicht vorhanden sein, die vorzugsweise die äußerste Schicht ist, und besteht beispielsweise aus ZrO2, Y2O3-ZrO2, d.h. sie ist nicht, teilweise oder vollständig stabilisiert durch Yttriumoxid und/ oder Kalziumoxid und/oder Magnesiumoxid. Die Wärmedämmschicht bedeckt die gesamte MCrAlX-Schicht . Durch geeignete Beschich- tungsverfahren wie z.B. Elektronenstrahlverdampfen (EB-PVD) werden stängelförmige Körner in der Wärmedämmschicht erzeugt. Andere Beschichtungsverfahren sind denkbar, z.B. atmosphärisches Plasmaspritzen (APS) , LPPS, VPS oder CVD. Die Wärmedämmschicht kann poröse, mikro- oder makrorissbehaftete Kör- ner zur besseren Thermoschockbeständigkeit aufweisen. Die Wärmedämmschicht ist also vorzugsweise poröser als die MCrAlX-Schicht.On the MCrAlX may still be present a 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. By means of 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.

Die Schaufel 120, 130 kann hohl oder massiv ausgeführt sein. Wenn die Schaufel 120, 130 gekühlt werden soll, ist sie hohl und weist ggf. noch Filmkühllöcher 418 (gestrichelt angedeutet) auf.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.

Figur 2 zeigt stark schematisiert einen Schnitt durch die Wand der Turbinenschaufel 120. Der Einfachheit halber sindFIG. 2 shows, in highly schematic form, a section through the wall of the turbine blade 120. For the sake of simplicity, these are

Beschichtungen, die auf der Oberfläche 3 der Turbinenschaufel 120 vorhanden sein können, nicht dargestellt. In der Superle- gierung 1 der Turbinenschaufel 120 sind ummantelte Titanpartikel 5 homogen verteilt. Das Material der Ummantelung ist Titannitrid (TiN) , also eine Metallkeramik.Coatings that may be present on the surface 3 of the turbine blade 120, not shown. In the superalloy 1 of the turbine blade 120, coated titanium particles 5 are homogeneously distributed. The material of the sheath is titanium nitride (TiN), ie a metal ceramic.

Statt Titanpartikel können auch andere Partikel, etwa Tantalpartikel oder Zirkonpartikel mit oder ohne Ummantelung in der Superlegierung 1 verteilt sein. Die genannten Partikelmateri- alien weisen zwei Eigenschaften auf, die sie für den Einsatz in Form von Partikeln in der Superlegierung 1 geeignet machen. Zum einen gibt es spezielle Reinigungsverfahren, mit denen sich die Oxide dieser Materialien entfernen lassen. Dies ermöglicht den Einsatz sehr spezieller Reinigungsverfahren im Refurbishment für Turbinenschaufeln. Zum anderen haben die Oxide dieser Materialien eine passivierende Wirkung, so dass ein entstandenes Oxid einer weiteren Oxidierung entgegenwirkt .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.

Statt dem genannten TiN können auch andere Metallkeramiken als Material für die Ummantelung Verwendung finden, beispielsweise Aluminiumnitrid (AlN) . Alternativ oder zusätzlich zu metallkeramischen Materialien können auch Metalloxide wie etwa Aluminiumoxid (Al2O3) oder Titanoxid (TiO, Ti2O3, TiO2) Verwendung finden.Instead of said TiN, other metal ceramics may also be used as material for the sheathing, for example aluminum nitride (AlN). As an alternative or in addition to metal-ceramic materials, it is also possible to use metal oxides, such as aluminum oxide (Al 2 O 3 ) or titanium oxide (TiO, Ti 2 O 3 , TiO 2 ).

Figur 3 zeigt den Ausschnitt aus Figur 2, nachdem die Turbinenschaufel 120 in einer Gasturbine im Betrieb war. In der Turbinenschaufel 120 können im Betrieb Risse 7 entstanden sein, die sich von der Oberfläche 3 aus in den Grundkörper der Turbinenschaufel 120 hinein erstrecken. Auf Grund der korrosiven und/oder oxidativen Eigenschaften des Heißgases, dem die Turbinenschaufel 120 im Betrieb ausgesetzt ist, bil- det sich auf der Rissoberfläche 8 eine Oxidschicht 9 aus. Wegen der im Vergleich zu den Materialkomponenten der Superlegierung höheren Affinität des Partikelmaterials zu Sauerstoff besteht die auf der Rissoberfläche 8 gebildete Oxidschicht 9 ausschließlich oder nahezu ausschließlich aus Oxid des Parti- kelmaterials, also im vorliegenden Ausführungsbeispiel aus Titanoxid. Da dieses Oxid, wie zuvor erwähnt, passivierende Eigenschaften besitzt, wirkt es einer Vergrößerung des Risses 7 entgegen, indem es eine weitere Oxidation verhindert. Wenn die Turbinenschaufel 120 einem Refurbishment unterzogen wird, lässt sich die Oxidschicht 9 mit einem speziell an dieses Oxid angepassten Reinigungsverfahren entfernen. Das Reinigen von Rissen 7 in der Turbinenschaufel 120 (sowie in an- deren Turbinenbauteilen) kann daher optimiert werden, was den Aufwand und somit auch die Kosten des Refurbishments reduziert .FIG. 3 shows the detail from FIG. 2 after the turbine blade 120 in a gas turbine was in operation. During 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. Since this oxide, as mentioned above, has passivating properties, it counteracts an enlargement of the crack 7 by preventing further oxidation. When the turbine blade 120 is refurbished, 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.

Mit der erfindungsgemäßen Ausgestaltung des Turbinenbauteils kann die Oxidation des Basismaterials gehemmt werden. Die Rate von Bauteilen, die auf Grund von Rissen, welche eine zu starke Oxidation aufweisen, ausgetauscht werden müssen, kann daher reduziert werden. Zudem ermöglicht die erfindungsgemäße Ausgestaltung des Turbinenbauteils ein Optimieren des Reini- gungsprozesses zum Entfernen des Oxids aus den Rissen. With the inventive design of the turbine component, 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. In addition, 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.

Claims

Patentansprüche claims 1. Turbinenbauteil (120) aus einem metallischen Basismaterial (1) und im Basismaterial (1) verteilten Partikeln (5) aus ei- nem Partikelmaterial, das eine höhere Affinität zu Sauerstoff aufweist als das Basismaterial (1) .1. turbine component (120) of a metallic base material (1) and in the base material (1) distributed particles (5) of a particulate material having a higher affinity for oxygen than the base material (1). 2. Turbinenbauteil (120) nach Anspruch 1, in dem die Partikel (5) in einer homogenen Verteilung vorliegen.2. Turbine component (120) according to claim 1, in which the particles (5) are present in a homogeneous distribution. 3. Turbinenbauteil (120) nach Anspruch 1 oder 2, in dem das Basismaterial (1) ein hochtemperaturfestes Material ist3. turbine component (120) according to claim 1 or 2, in which the base material (1) is a high temperature resistant material 4. Turbinenbauteil (120) nach Anspruch 3, in dem das Basisma- terial (1) eine Superlegierung auf Eisen-, Kobalt- oder Nickelbasis ist.4. turbine component (120) according to claim 3, in which the base material (1) is an iron, cobalt or nickel-based superalloy. 5. Turbinenbauteil (120) nach einem der vorangehenden Ansprüche, in dem das Partikelmaterial (5) Titan, Tantal oder Zir- kon ist.5. turbine component (120) according to any one of the preceding claims, in which the particulate material (5) is titanium, tantalum or zirconium. 6. Turbinenbauteil (120) nach einem der vorangehenden Ansprüche, in dem die Partikel eine Ummantelung aufweisen.6. turbine component (120) according to any one of the preceding claims, in which the particles have a sheath. 7. Turbinenbauteil (120) nach Anspruch 6, in dem die Ummantelung ein Metalloxid und/oder eine Metallkeramik umfasst. 7. turbine component (120) according to claim 6, in which the sheath comprises a metal oxide and / or a metal ceramic.
PCT/DE2006/001654 2006-09-18 2006-09-18 Turbine component Ceased WO2008034392A1 (en)

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DE102010014832B4 (en) 2010-04-10 2018-04-26 Technische Universität Braunschweig Easy machinable nickel base alloy
CN113898416A (en) * 2021-09-02 2022-01-07 北京航空航天大学 A liquid metal cooling blade system and anti-corrosion method thereof

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DE4434515A1 (en) * 1993-09-27 1995-03-30 Hitachi Ltd Oxide dispersion strengthened alloy, and high-temperature equipment produced from this alloy
JPH07242960A (en) * 1994-02-28 1995-09-19 Daido Steel Co Ltd Method for producing oxide dispersion strengthened alloy
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Publication number Priority date Publication date Assignee Title
DE102010014832B4 (en) 2010-04-10 2018-04-26 Technische Universität Braunschweig Easy machinable nickel base alloy
CN113898416A (en) * 2021-09-02 2022-01-07 北京航空航天大学 A liquid metal cooling blade system and anti-corrosion method thereof
CN113898416B (en) * 2021-09-02 2022-07-22 北京航空航天大学 Liquid metal cooling blade system and anti-corrosion method thereof

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