EP2198064A1 - Hot gas-guided component of a turbomachine - Google Patents

Hot gas-guided component of a turbomachine

Info

Publication number
EP2198064A1
EP2198064A1 EP08839697A EP08839697A EP2198064A1 EP 2198064 A1 EP2198064 A1 EP 2198064A1 EP 08839697 A EP08839697 A EP 08839697A EP 08839697 A EP08839697 A EP 08839697A EP 2198064 A1 EP2198064 A1 EP 2198064A1
Authority
EP
European Patent Office
Prior art keywords
hot gas
alloy
turbomachine
component according
guided 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Withdrawn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
EP08839697A
Other languages
German (de)
French (fr)
Inventor
Markus Beukenberg
Sharad Chandra
Norbert Czech
Roland Herzog
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.)
MAN Energy Solutions SE
Original Assignee
MAN Turbo AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MAN Turbo AG filed Critical MAN Turbo AG
Publication of EP2198064A1 publication Critical patent/EP2198064A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
    • B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
    • B23K35/24—Selection of soldering or welding materials proper
    • B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
    • B32B15/013—Layered products comprising a layer of metal all layers being exclusively metallic one layer being formed of an iron alloy or steel, another layer being formed of a metal other than iron or aluminium
    • B32B15/015—Layered products comprising a layer of metal all layers being exclusively metallic one layer being formed of an iron alloy or steel, another layer being formed of a metal other than iron or aluminium the said other metal being copper or nickel or an alloy thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/18—Layered products comprising a layer of metal comprising iron or steel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/005—Ferrous alloys, e.g. steel alloys containing rare earths, i.e. Sc, Y, Lanthanides
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/06—Ferrous alloys, e.g. steel alloys containing aluminium
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C38/00—Ferrous alloys, e.g. steel alloys
    • C22C38/18—Ferrous alloys, e.g. steel alloys containing chromium
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C23C30/005—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process on hard metal substrates
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12931—Co-, Fe-, or Ni-base components, alternative to each other
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12937—Co- or Ni-base component next to Fe-base component
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12944—Ni-base component
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12951—Fe-base component
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12951—Fe-base component
    • Y10T428/12972—Containing 0.01-1.7% carbon [i.e., steel]
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12771—Transition metal-base component
    • Y10T428/12861—Group VIII or IB metal-base component
    • Y10T428/12951—Fe-base component
    • Y10T428/12972—Containing 0.01-1.7% carbon [i.e., steel]
    • Y10T428/12979—Containing more than 10% nonferrous elements [e.g., high alloy, stainless]

Definitions

  • the present invention relates to a hot gas-guided component of a turbomachine according to the preamble of claim 1 and a turbomachine with such a component.
  • Hot gas-guided components of turbomachines such as combustion chamber linings, turbine inlet casings, hot gas ducts and turbine blading, must retain their functionality under extreme thermal and mechanical loads. The components are exposed to constant oxidation and corrosion attacks and the. Temperatures often exceed 1000 ° C. At the same time, compressed cooling air is only available to a limited extent.
  • Hot gas guided components which are subject to high thermal stress but not extreme mechanical stress, are conventionally made of mixed crystal cured nickel base wrought alloys, with the exception of turbine blading. Alloys of this type are characterized by a high heat resistance.
  • a disadvantage of nickel-base wrought alloys is their moderate oxidation capability.
  • the hot gas-guided components are usually provided with a hot gas-side ceramic-based coating.
  • such ceramic coatings are expensive to manufacture and apply.
  • the object of the present invention is to provide a hot gas-guided component of a turbomachine with an improved hot-gas-side lining in comparison to known ceramic coatings, and a turbomachine with such a component.
  • This object is achieved by a hot gas-guided component having the features of claim 1 and by a turbomachine having the features of claim 7.
  • a hot gas-guided component of a turbomachine according to the invention has, as a structural material and thus as a supporting construction, a mixed crystal-hardened nickel-base wrought alloy and a hot gas-side lining from the group of the iron-chromium-aluminum-yttrium alloys.
  • Iron-chromium-aluminum-yttrium alloys in short FeCrAlY alloys, have a very good oxidation resistance.
  • the temperature limit from the point of view of the oxidation criterion is about 1200 ° C.
  • the heat resistance of FeCrAlY alloys can be considered moderate.
  • the operating temperature and stability of the hot gas-guided component according to the invention are improved by the fact that the respectively excellent property of the alloys comes into play.
  • the hot gas side liner is made of an alumina-yttrium-hafnium alloy.
  • the active elements yttrium and hafnium the cyclic oxidation resistance of the hot gas side lining can be increased.
  • the FeCrAlY alloy has iron as its base and consists of 16% to 24% chromium, 3% to 9% aluminum, 0.02% to 0.2% yttrium, up to 0.1% hafnium up to 0.1% of zirconium and up to 0.1% of rare earth metals, in particular lanthanides.
  • the application of the hot gas side lining can be done by high temperature brazing, welding, or plating, in particular roll cladding.
  • a turbomachine according to the invention has at least one hot gas-guided component, which has a structure material of a mixed crystal-hardened nickel-base-nickel alloy, which is provided with a hot gas-side lining from the group of iron-chromium-aluminum-yttrium alloys.
  • a hot gas-guided component according to the invention of a turbomachine, in particular a gas turbine is designed as a composite material of a mixed crystal-hardened nickel or Ni-base nickel alloy and an oxidation-resistant ferrite iron-based alloy, in particular a FeCrAlY alloy.
  • the Ni base wrought alloy forms the supporting structure of the component
  • the FeCrAlY alloy is applied to the structural material as a hot gas side lining.
  • hot gas side means that the lining is applied to an inner surface of the component facing the hot gases.
  • “Cooling air side” in the sense of the invention means that a coating is arranged on an outer surface of the component facing the cooling air.
  • An exemplary hot gas guided component of a gas turbine is the so-called “breeze tube", which presents a hot gas guide channel between the combustors and the turbine blading and directs the hot gases from the combustor to the first turbine stage.
  • a preferred material from the group of FeCrAlY alloys is an aluminum-chromium-yttrium-hafnium alloy, short Aluchrom-YHf alloy.
  • yttrium (Y) and hafnium (Hf) can be added to increase the cyclic oxidation resistance of the FeCrAlY alloy further active elements such as zirconium (Zr).
  • an FeCrAlY alloy having iron (Fe) as a base element and chromium (Cr) of 16% to 24%, and aluminum (Al) of 3% to 9%, of 0.02% to 0.2% is preferred % Yttrium (Y), up to 0.1% hafnium (Hf), up to 0.1% zirconium (Zr) and up to 0.1% rare earth metals (SE).
  • Yttrium Y
  • Hf hafnium
  • Zr zirconium
  • SE rare earth metals
  • La rare earth metals
  • the FeCrAlY alloy is applied to the structural material by known high temperature soldering, welding, plating or roll cladding techniques.
  • a diffusion barrier z. B. based on the system Al-O-N are used.
  • the application of the FeCrAlY alloy as a lining is not limited to the hot gas side of the components, but it is also conceivable to sandwich the hot gas-led component.
  • the structural material of a mixed crystal-hardened Ni-base wrought alloy constitutes the supporting structural core which is arranged between a hot gas-side lining and a cooling-air-side coating based on the above-described FeCrAlY alloys.
  • Disclosed is a hot gas-guided component for a turbomachine, with a nickel-base wrought alloy as a structural material and a hot gas side lining from the group of iron-chromium-aluminum-yttrium alloys, and a turbomachine with such a component

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

The invention relates to a hot gas-guided component for a turbomachine, comprising a nickel base wrought alloy as the structural material and a lining on the hot gas side from the group of iron-chromium-aluminum-yttrium alloys, and to a turbomachine comprising such a component.

Description

Heißgasgeführte Komponente einer Strömungsmaschine Hot gas-guided component of a turbomachine
Die vorliegende Erfindung betrifft eine heißgasgeführte Komponente einer Strömungsmaschine nach dem Oberbegriff des Anspruchs 1 und eine Strömungsmaschine mit einer derartigen Komponente.The present invention relates to a hot gas-guided component of a turbomachine according to the preamble of claim 1 and a turbomachine with such a component.
Heißgasgeführte Komponenten von Strömungsmaschinen wie zum Beispiel Brennkammerauskleidungen, Turbineneintrittsgehäusen, Heißgaskanäle und Turbinenbeschaufelungen müssen unter extremen thermischen und mechanischen Belastungen ihre Funktionsfähigkeit behalten. Die Komponenten sind ständigen Oxidations- und Korrosionsangriffen ausgesetzt und die . Temperaturen übersteigen oft 10000C. Gleichzeitig steht komprimierte Kühlluft nur begrenzt zur Verfügung.Hot gas-guided components of turbomachines, such as combustion chamber linings, turbine inlet casings, hot gas ducts and turbine blading, must retain their functionality under extreme thermal and mechanical loads. The components are exposed to constant oxidation and corrosion attacks and the. Temperatures often exceed 1000 ° C. At the same time, compressed cooling air is only available to a limited extent.
Heißgasgeführten Komponenten, die einer hohen thermischen Belastung, nicht jedoch einer extremen mechanischen Belastung, ausgesetzt sind, werden mit Ausnahme der Turbinenbeschaufelung herkömmlicherweise aus einer mischkristallge- härteten Nickel-Basisknetlegierungen hergestellt. Legierungen dieser Art zeichnen sich durch eine hohe Warmfestigkeit aus. Nachteilig an Nickel-Basisknetlegierungen ist jedoch ihre mäßige Oxidationsfähigkeit. Zur Verringerung dieses Nachteiles werden die heißgasgeführten Komponenten meist mit einer heißgasseitigen Beschich- tung auf Keramikbasis versehen. Derartige Keramikbeschichtungen sind jedoch auf- wendig in der Herstellung und Aufbringung.Hot gas guided components, which are subject to high thermal stress but not extreme mechanical stress, are conventionally made of mixed crystal cured nickel base wrought alloys, with the exception of turbine blading. Alloys of this type are characterized by a high heat resistance. However, a disadvantage of nickel-base wrought alloys is their moderate oxidation capability. To reduce this disadvantage, the hot gas-guided components are usually provided with a hot gas-side ceramic-based coating. However, such ceramic coatings are expensive to manufacture and apply.
Aufgabe der vorliegenden Erfindung ist es, eine heißgasgeführte Komponente einer Strömungsmaschine mit einer gegenüber bekannten Keramikbeschichtungen verbesserten heißgasseitigen Auskleidung, sowie eine Strömungsmaschine mit einer derartigen Komponente zu schaffen. Diese Aufgabe wird gelöst durch eine heißgasgeführte Komponente mit den Merkmalen des Anspruchs 1 sowie durch eine Strömungsmaschine mit den Merkmalen des Anspruchs 7.The object of the present invention is to provide a hot gas-guided component of a turbomachine with an improved hot-gas-side lining in comparison to known ceramic coatings, and a turbomachine with such a component. This object is achieved by a hot gas-guided component having the features of claim 1 and by a turbomachine having the features of claim 7.
Eine erfindungsgemäße heißgasgeführte Komponente einer Strömungsmaschine weist als Strukturwerkstoff und somit als tragende Konstruktion eine mischkristallgehärtete Nickel-Basisknetlegierung und eine heißgasseitige Auskleidung aus der Gruppe der Eisen-Chrom-Aluminium-Yttrium-Legierungen auf.A hot gas-guided component of a turbomachine according to the invention has, as a structural material and thus as a supporting construction, a mixed crystal-hardened nickel-base wrought alloy and a hot gas-side lining from the group of the iron-chromium-aluminum-yttrium alloys.
Eisen-Chrom-Aluminium-Yttrium-Legierungen, kurz FeCrAlY-Legierungen, haben eine sehr gute Oxidationsbeständigkeit. Die Temperaturgrenze aus Sicht des Oxida- tionskriteriums beträgt etwa 1200°C. Somit kann die Betriebstemperatur und Standfestigkeit der heißgasgeführten Komponenten gesteigert werden, ohne dass die Lebensdauer des Strukturwerkstoffs durch Oxidation unverhältnismäßig verkürzt wird. Die Warmfestigkeit der FeCrAlY-Legierungen kann als mäßig bezeichnet werden. Die mäßigen Materialeigenschaften der beiden Legierungen - Nickel- Basisknetlegierungen, kurz Ni-Basislegierungen, zeigen eine mäßige Oxidationsbeständigkeit und FeCrAlY-Legierungen weisen eine mäßige Warmfestigkeit auf - werden durch den erfindungsgemäße Kombination und durch den erfindungsgemäßen Aufbau der heißgasgeführten Komponente durch die sehr gute Oxidationsbeständigkeit und Warmfestigkeit der jeweils anderen Legierung beseitigt. Mit anderen Worten, die Betriebstemperatur und Standfestigkeit der erfindungsgemäßen heißgasgeführten Komponente werden dadurch verbessert, dass die jeweils ausgezeichnete Eigenschaft der Legierungen zum Tragen kommt.Iron-chromium-aluminum-yttrium alloys, in short FeCrAlY alloys, have a very good oxidation resistance. The temperature limit from the point of view of the oxidation criterion is about 1200 ° C. Thus, the operating temperature and stability of the hot gas-guided components can be increased without the life of the structural material is disproportionately reduced by oxidation. The heat resistance of FeCrAlY alloys can be considered moderate. The moderate material properties of the two alloys - nickel base wrought alloys, in short Ni-base alloys, show a moderate oxidation resistance and FeCrAlY alloys have a moderate heat resistance - by the inventive combination and the inventive design of the hot gas component by the very good oxidation resistance and high temperature resistance the other alloy eliminated. In other words, the operating temperature and stability of the hot gas-guided component according to the invention are improved by the fact that the respectively excellent property of the alloys comes into play.
Bei einem Ausführungsbeispiel besteht die heißgasseitige Auskleidung aus einer Aluchrom-Yttrium-Hafnium-Legierung. Insbesondere mit den Aktivelementen Yttrium und Hafnium lässt sich die zyklische Oxidationsbeständigkeit der heißgasseitigen Auskleidung steigern.In one embodiment, the hot gas side liner is made of an alumina-yttrium-hafnium alloy. In particular, with the active elements yttrium and hafnium, the cyclic oxidation resistance of the hot gas side lining can be increased.
Bevorzugterweise weist die FeCrAlY-Legierung als Basiselement Eisen auf und besteht zu 16% bis 24% aus Chrom, zu 3% bis 9% aus Aluminium, zu 0,02% bis 0,2% Yttrium, bis zu 0,1 % aus Hafnium, bis zu 0,1% aus Zirkonium und bis zu 0,1 % aus Metallen aus der Gruppe der Seltenen Erden, insbesondere Lanthaniden. Die Aufbringung der heißgasseitigen Auskleidung kann durch Hochtemperaturlöten, Schweißen, oder Plattieren, insbesondere Walzplattieren, erfolgen.Preferably, the FeCrAlY alloy has iron as its base and consists of 16% to 24% chromium, 3% to 9% aluminum, 0.02% to 0.2% yttrium, up to 0.1% hafnium up to 0.1% of zirconium and up to 0.1% of rare earth metals, in particular lanthanides. The application of the hot gas side lining can be done by high temperature brazing, welding, or plating, in particular roll cladding.
Bei einem Ausführungsbeispiel ist der Strukturwerkstoff der heißgeführten Komponente sandwichartig zwischen der heißgasseitigen Auskleidung und einer kühlluftsei- tigen Beschichtung angeordnet, die bevorzugterweise aus einer Legierung aus der Gruppe der Nickel-Kobalt-Eisen-Chrom-Aluminium-Yttrium- (= MCrAIY-) Legierungen besteht.In one embodiment, the structural material of the hot run component is sandwiched between the hot gas side liner and a cool air side coating, which is preferably an alloy of the group of the nickel-cobalt-iron-chromium-aluminum-yttrium (= MCrAlY) alloys ,
Eine erfindungsgemäße Strömungsmaschine weist zumindest eine heißgasgeführte Komponente auf, die einen Strukturwerkstoff aus einer mischkristallgehärteten Nickel-Basisknetlegierung aufweist, der mit einer heißgasseitigen Auskleidung aus der Gruppe der Eisen-Chrom-Aluminium-Yttrium-Legierungen versehen ist.A turbomachine according to the invention has at least one hot gas-guided component, which has a structure material of a mixed crystal-hardened nickel-base-nickel alloy, which is provided with a hot gas-side lining from the group of iron-chromium-aluminum-yttrium alloys.
Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.
Im Folgenden werden bevorzugte Ausführungsbeispiele der Erfindung näher erläu- tert.In the following preferred embodiments of the invention will be explained in more detail.
Eine erfindungsgemäße heißgasgeführte Komponente einer Strömungsmaschine, insbesondere einer Gasturbine, ist als ein Verbundwerkstoff aus einer mischkristallgehärteten Nickel- bzw. Ni-Basisknetlegierung und einer oxidationsbeständigen ferri- tischen Eisenbasislegierung, insbesondere einer FeCrAlY-Legierung, ausgeführt. Dabei bildet die Ni-Basisknetlegierung die tragende Konstruktion bzw. den Strukturwerkstoff der Komponente und die FeCrAlY-Legierung ist als heißgasseitige Auskleidung auf den Strukturwerkstoff aufgebracht. „Heißgasseitig" im Sinne der Erfindung bedeutet, dass die Auskleidung auf einer den Heißgasen zugewandten Innenfläche der Komponente aufgebracht ist. Entsprechend bedeutet „kühlluftseitig" im Sinne der Erfindung, dass eine Beschichtung auf einer der Kühlluft zugewandten Außenfläche der Komponente angeordnet ist. Eine beispielhaft genannte heißgasgeführte Komponente einer Gasturbine ist das sogenannte „Hosenrohr", welches einen Heißgasführungskanal zwischen den Brennkammern und der Turbinenbeschaufelung darstellt und die Heißgase von der Brennkammer auf die ersten Turbinenstufe führt. Weitere heißgasgeführte Kompo- nenten sind zum Beispiel Brennkammerauskleidungen und Turbineneintrittsgehäusen.A hot gas-guided component according to the invention of a turbomachine, in particular a gas turbine, is designed as a composite material of a mixed crystal-hardened nickel or Ni-base nickel alloy and an oxidation-resistant ferrite iron-based alloy, in particular a FeCrAlY alloy. Here, the Ni base wrought alloy forms the supporting structure of the component, and the FeCrAlY alloy is applied to the structural material as a hot gas side lining. For the purposes of the invention, "hot gas side" means that the lining is applied to an inner surface of the component facing the hot gases. "Cooling air side" in the sense of the invention means that a coating is arranged on an outer surface of the component facing the cooling air. An exemplary hot gas guided component of a gas turbine is the so-called "breeze tube", which presents a hot gas guide channel between the combustors and the turbine blading and directs the hot gases from the combustor to the first turbine stage.
Ein bevorzugter Werkstoff aus der Gruppe der FeCrAlY-Legierungen ist eine Aluminium-Chrom-Yttrium-Hafnium-Legierung, kurz Aluchrom-YHf-Legierung.A preferred material from the group of FeCrAlY alloys is an aluminum-chromium-yttrium-hafnium alloy, short Aluchrom-YHf alloy.
Außer dem Aktivelement Yttrium (Y) und Hafnium (Hf) können zur Steigerung der zyklischen Oxidationsbeständigkeit der die FeCrAlY-Legierung noch weitere Aktivelemente wie zum Beispiel Zirkonium (Zr) beigemischt sein.In addition to the active element yttrium (Y) and hafnium (Hf) can be added to increase the cyclic oxidation resistance of the FeCrAlY alloy further active elements such as zirconium (Zr).
Insbesondere wird eine FeCrAlY-Legierung bevorzugt, die als Basiselement Eisen (Fe) aufweist und zu 16% bis 24% aus Chrom (Cr), zu 3% bis 9% aus Aluminium (AI), zu 0,02% bis 0,2% Yttrium (Y), bis zu 0,1 % aus Hafnium (Hf), bis zu 0,1% aus Zirkonium (Zr) und bis zu 0,1% aus Metallen aus der Gruppe der Seltenen Erden (SE) besteht. Aus der Gruppe der Seltenen Erden sind insbesondere die Lanthan- iden bzw. Lanthanoiden (La) zu nennen wie zum Beispiel Cer (Ce), Praseodym (Pr), Neodym (Nd) und Promethium (Pm).In particular, an FeCrAlY alloy having iron (Fe) as a base element and chromium (Cr) of 16% to 24%, and aluminum (Al) of 3% to 9%, of 0.02% to 0.2% is preferred % Yttrium (Y), up to 0.1% hafnium (Hf), up to 0.1% zirconium (Zr) and up to 0.1% rare earth metals (SE). From the group of rare earths, mention should be made in particular of the lanthanides or lanthanides (La), for example cerium (Ce), praseodymium (Pr), neodymium (Nd) and promethium (Pm).
Das Aufbringen der FeCrAlY-Legierung auf den Strukturwerkstoff erfolgt durch bekannte Hochtemperaturlöt-, Schweiß- oder Plattier- bzw. Walzplattierverfahren. Zur Verhinderung von Interdiffusion zwischen dem Strukturwerkstoff und der Auskleidung kann eine Diffusionsbarriere z. B. basierend auf dem System Al-O-N zum Einsatz kommen.The FeCrAlY alloy is applied to the structural material by known high temperature soldering, welding, plating or roll cladding techniques. To prevent interdiffusion between the structural material and the lining, a diffusion barrier z. B. based on the system Al-O-N are used.
Die Anwendung der FeCrAlY-Legierung als Auskleidung ist nicht auf die Heißgasseite der Komponenten beschränkt, sondern es ist ebenfalls vorstellbar, die heißgasge- führte Komponente sandwichartig aufzubauen. Hierbei stellt der Strukturwerkstoff aus einer mischkristallgehärteten Ni-Basisknetlegierung den tragenden Strukturkern dar, der zwischen einer heißgasseitige Auskleidung und einer kühlluftseitigen Be- schichtung jeweils auf Basis der vorbeschriebenen FeCrAlY-Legierungen angeordnet ist. Offenbart ist eine heißgasgeführte Komponente für eine Strömungsmaschine, mit einer Nickel-Basisknetlegierung als Strukturwerkstoff und einer heißgasseitigen Auskleidung aus der Gruppe der Eisen-Chrom-Aluminium-Yttrium-Legierungen, sowie eine Strömungsmaschine mit einer derartigen Komponente The application of the FeCrAlY alloy as a lining is not limited to the hot gas side of the components, but it is also conceivable to sandwich the hot gas-led component. Here, the structural material of a mixed crystal-hardened Ni-base wrought alloy constitutes the supporting structural core which is arranged between a hot gas-side lining and a cooling-air-side coating based on the above-described FeCrAlY alloys. Disclosed is a hot gas-guided component for a turbomachine, with a nickel-base wrought alloy as a structural material and a hot gas side lining from the group of iron-chromium-aluminum-yttrium alloys, and a turbomachine with such a component

Claims

Ansprüche claims
1. Heißgasgefϋhrte Komponente einer Strömungsmaschine mit einer mischkristall- gehärteten Nickel-Basisknetlegierung als Strukturwerkstoff, dadurch gekennzeichnet, dass die Komponente eine heißgasseitige Auskleidung aus der Gruppe der Eisen-Chrom-Aluminium-Yttrium-Legierungen aufweist.1. Heißgasgefϋhrte component of a turbomachine with a mixed crystal-hardened nickel basic mesh alloy as a structural material, characterized in that the component has a hot gas side lining from the group of iron-chromium-aluminum-yttrium alloys.
2. Heißgasgeführte Komponente nach Anspruch 1 , wobei die heißgasseitige Aus- kleidung eine Aluchrom-Yttrium-Hafnium-Legierung ist.2. A hot gas guided component according to claim 1, wherein the hot gas side lining is an alumina-yttrium-hafnium alloy.
3. Heißgasgeführte Komponente nach Anspruch 1 oder 2, wobei die Eisen-Chrom- Aluminium-Yttrium-Legierung als Basiselement Eisen, 16% bis 24% Chrom, 3% bis 9% Aluminium, 0,02% bis 0,2% Yttrium, bis zu 0,1% Hafnium, bis zu 0,1 % Zirkonium und bis zu 0,1% Metalle aus der Gruppe der Seltenen Erden, insbesondere Lanthaniden, aufweist.3. hot gas guided component according to claim 1 or 2, wherein the iron-chromium-aluminum-yttrium alloy as a base iron, 16% to 24% chromium, 3% to 9% aluminum, 0.02% to 0.2% yttrium, up to 0.1% hafnium, up to 0.1% zirconium and up to 0.1% rare earth metals, especially lanthanides.
4. Heißgasgeführte Komponente nach Anspruch 1 , 2 oder 3, wobei die heißgasseitige Auskleidung durch Hochtemperaturlöten, Schweißen oder Plattieren aufge- bracht ist.4. A hot gas guided component according to claim 1, 2 or 3, wherein the hot gas side lining is applied by high temperature brazing, welding or plating.
5. Heißgasgeführte Komponente nach einem der vorherigen Ansprüche, wobei zwischen Basiswerkstoff und Auskleidung eine Diffusionsbarriere zum Einsatz kommt.5. hot gas-guided component according to one of the preceding claims, wherein between the base material and lining a diffusion barrier is used.
6. Heißgasgeführte Komponente nach einem der vorhergehenden Ansprüche, wobei auf den Strukturwerkstoff eine kühlluftseitige Beschichtung aufgebracht ist.6. Hot gas-guided component according to one of the preceding claims, wherein a cooling-air-side coating is applied to the structure material.
7. Heißgasgeführte Komponente nach Anspruch 6, wobei die kühlluftseitige Be- Schichtung eine Legierung aus der Gruppe der - -MCrAIY- Legierungen ist.7. hot gas-guided component according to claim 6, wherein the cooling air-side coating is an alloy from the group of - -MCrAIY- alloys.
8. Strömungsmaschine mit einer heißgasgeführten Komponente nach einem der vorhergehenden Ansprüche. 8. Turbomachine with a hot gas-guided component according to one of the preceding claims.
EP08839697A 2007-10-09 2008-10-07 Hot gas-guided component of a turbomachine Withdrawn EP2198064A1 (en)

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
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Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0949410A2 (en) * 1998-04-07 1999-10-13 GHH BORSIG Turbomaschinen GmbH Coated transition duct for a gas turbine

Family Cites Families (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3542530A (en) * 1968-05-23 1970-11-24 United Aircraft Corp Nickel or cobalt base with a coating containing iron chromium and aluminum
US3754903A (en) 1970-09-15 1973-08-28 United Aircraft Corp High temperature oxidation resistant coating alloy
US3676085A (en) 1971-02-18 1972-07-11 United Aircraft Corp Cobalt base coating for the superalloys
US3928026A (en) 1974-05-13 1975-12-23 United Technologies Corp High temperature nicocraly coatings
US3979534A (en) * 1974-07-26 1976-09-07 General Electric Company Protective coatings for dispersion strengthened nickel-chromium/alloys
US3996021A (en) * 1974-11-07 1976-12-07 General Electric Company Metallic coated article with improved resistance to high temperature environmental conditions
US3955935A (en) * 1974-11-27 1976-05-11 General Motors Corporation Ductile corrosion resistant chromium-aluminum coating on superalloy substrate and method of forming
CA1082949A (en) * 1976-06-03 1980-08-05 William F. Schilling High-temperature austenitic alloys and articles utilizing the same
US4447503A (en) * 1980-05-01 1984-05-08 Howmet Turbine Components Corporation Superalloy coating composition with high temperature oxidation resistance
US4585481A (en) * 1981-08-05 1986-04-29 United Technologies Corporation Overlays coating for superalloys
JPS58110650A (en) * 1981-12-22 1983-07-01 Mitsubishi Heavy Ind Ltd Ni-base heat resistant alloy
SE8401757L (en) * 1984-03-30 1985-10-01 Yngve Lindblom METAL OXID CERAMIC SURFACES OF HIGH TEMPERATURE MATERIAL
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
CA1268139A (en) * 1984-10-05 1990-04-24 John Foster Composite electrodeposition including particles of craim.sub.2 where m.sub.2is y, si, ti or rare earth
US5240491A (en) 1991-07-08 1993-08-31 General Electric Company Alloy powder mixture for brazing of superalloy articles
US5413647A (en) * 1992-03-26 1995-05-09 General Electric Company Method for forming a thin-walled combustion liner for use in a gas turbine engine
EP0589072A1 (en) * 1992-09-21 1994-03-30 Asea Brown Boveri Ag Turbocharger for heavy fuel operation
JP3421758B2 (en) * 1993-09-27 2003-06-30 株式会社日立製作所 Oxide dispersion strengthened alloy and high temperature equipment composed of the alloy
US6129991A (en) * 1994-10-28 2000-10-10 Howmet Research Corporation Aluminide/MCrAlY coating system for superalloys
US5964091A (en) * 1995-07-11 1999-10-12 Hitachi, Ltd. Gas turbine combustor and gas turbine
US5955182A (en) * 1996-02-05 1999-09-21 Kabushiki Kaisha Toshiba Heat resisting member and its production method
US6117560A (en) * 1996-12-12 2000-09-12 United Technologies Corporation Thermal barrier coating systems and materials
JP2002513081A (en) * 1998-04-29 2002-05-08 シーメンス アクチエンゲゼルシヤフト Product with corrosion protection layer and method of manufacturing corrosion protection layer
US6455167B1 (en) * 1999-07-02 2002-09-24 General Electric Company Coating system utilizing an oxide diffusion barrier for improved performance and repair capability
US6294260B1 (en) * 1999-09-10 2001-09-25 Siemens Westinghouse Power Corporation In-situ formation of multiphase air plasma sprayed barrier coatings for turbine components
US6410159B1 (en) * 1999-10-29 2002-06-25 Praxair S. T. Technology, Inc. Self-bonding MCrAly powder
DE60041951D1 (en) * 1999-12-20 2009-05-20 United Technologies Corp Use of a cathode for vacuum arc evaporation
US6482537B1 (en) * 2000-03-24 2002-11-19 Honeywell International, Inc. Lower conductivity barrier coating
US6485025B1 (en) * 2000-11-27 2002-11-26 Neomet Limited Metallic cellular structure
US6526756B2 (en) * 2001-02-14 2003-03-04 General Electric Company Method and apparatus for enhancing heat transfer in a combustor liner for a gas turbine
JP3860422B2 (en) * 2001-02-16 2006-12-20 独立行政法人科学技術振興機構 Heat-resistant Ti alloy member excellent in high-temperature oxidation resistance and manufacturing method thereof
US6461108B1 (en) * 2001-03-27 2002-10-08 General Electric Company Cooled thermal barrier coating on a turbine blade tip
JP2003147464A (en) 2001-11-02 2003-05-21 Tocalo Co Ltd Member with high-temperature strength
US20030152814A1 (en) * 2002-02-11 2003-08-14 Dinesh Gupta Hybrid thermal barrier coating and method of making the same
CA2433613A1 (en) * 2002-08-13 2004-02-13 Russel J. Ruprecht, Jr. Spray method for mcralx coating
US7216485B2 (en) * 2004-09-03 2007-05-15 General Electric Company Adjusting airflow in turbine component by depositing overlay metallic coating
US7386980B2 (en) * 2005-02-02 2008-06-17 Power Systems Mfg., Llc Combustion liner with enhanced heat transfer

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0949410A2 (en) * 1998-04-07 1999-10-13 GHH BORSIG Turbomaschinen GmbH Coated transition duct for a gas turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2009049796A1 *

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