EP2044231A1 - Component with a reinforcing plating - Google Patents

Component with a reinforcing plating

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Publication number
EP2044231A1
EP2044231A1 EP07722169A EP07722169A EP2044231A1 EP 2044231 A1 EP2044231 A1 EP 2044231A1 EP 07722169 A EP07722169 A EP 07722169A EP 07722169 A EP07722169 A EP 07722169A EP 2044231 A1 EP2044231 A1 EP 2044231A1
Authority
EP
European Patent Office
Prior art keywords
weight
component
cover layer
metallic
armor
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.)
Granted
Application number
EP07722169A
Other languages
German (de)
French (fr)
Other versions
EP2044231B1 (en
Inventor
Karl-Heinz Manier
Josef Linska
Andre Werner
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Priority to PL07722169T priority Critical patent/PL2044231T3/en
Publication of EP2044231A1 publication Critical patent/EP2044231A1/en
Application granted granted Critical
Publication of EP2044231B1 publication Critical patent/EP2044231B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/027—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal matrix material comprising a mixture of at least two metals or metal phases or metal matrix composites, e.g. metal matrix with embedded inorganic hard particles, CERMET, MMC.
    • 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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C23C28/022—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer with at least one MCrAlX layer
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/129—Flame spraying
    • 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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D15/00—Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires
    • C25D15/02—Combined electrolytic and electrophoretic processes with charged materials
    • 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
    • Y10T428/12486—Laterally noncoextensive components [e.g., embedded, etc.]

Definitions

  • the invention relates to a component, in particular a gas turbine component such as a blade, with an armor, in particular a blade tip armor, according to the preamble of claim 1.
  • Turbomachines such as gas turbines, typically include a plurality of rotating blades and a plurality of stationary vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a fixed housing. To increase performance, it is important to optimize all components and subsystems. These include the so-called sealing systems.
  • blades in the compressor have no shroud. Therefore, tips of the blades are exposed to so-called rubbing into the fixed housing in direct frictional contact with the housing. Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances. As is removed by the frictional contact of the tips of the blades on the same material, over the entire circumference of the housing and rotor can set an undesirable gap magnification.
  • Two different types of blade tips are known from the prior art.
  • the present invention relates to an armor, in particular a blade tip armor, a component, in particular a gas turbine blade, with abrasive particles.
  • US 6,194,086 Bl discloses a blade of a gas turbine with a blade tip armor, wherein the blade tip armor comprises a cover layer, which is formed from in a metallic matrix material embedded abrasive particles.
  • the cover layer of the abrasive particles embedded in the metallic matrix material is applied to the tip of a blade to be coated with the interposition of a metallic adhesion-promoting layer.
  • the metallic adhesive layer is formed as LPPS layer and therefore applied to the component via a so-called low pressure plasma spraying.
  • the disadvantage of such LPPS adhesive layers is that they have a low mechanical adhesion to the blade tip, especially at high operating temperatures of up to 1200 ° C., so that the blade tip armor may flake off during operation.
  • the present invention based on the problem of creating a novel component with an armor.
  • This problem is solved by a component in the sense of claim 1.
  • the metallic adhesive layer is formed as an adhesive layer applied to the component via high-speed flame spraying, wherein the metallic matrix material of the cover layer is electrodeposited.
  • the adhesive layer is applied to the component via high-speed flame spraying.
  • the armor adheres better to the component at high temperatures than when using LPPS adhesive layers.
  • the blade tip armor of the component therefore has a higher mechanical adhesion, especially at high operating temperatures.
  • Fig. 1 a schematic cross section through an applied on a component
  • the invention relates to an armored component, in particular a blade provided with a blade tip armor of a gas turbine.
  • the blade of the gas turbine is designed as a high-pressure compressor blade.
  • FIG. 1 shows a highly schematic cross section through a blade tip 10 of a blade, wherein the blade tip 10 of the blade carries a blade tip armor 11.
  • the blade tip armor 11 has at least two layers, namely an outer cover layer 12 and an inner adhesive layer 13.
  • the cover layer 12 is applied to the blade tip 10 via the adhesive layer 13.
  • additional additional layers may be present between the cover layer 12 and the adhesion layer 13.
  • the cover layer 12 is formed by abrasive particles 14, which are embedded in a metallic matrix material 15.
  • the adhesive layer 13 is designed as a metallic adhesive layer.
  • the metallic adhesive layer 13 and the metallic matrix material 15 of the cover layer 12 are each formed from a MCr Al Y material.
  • the metallic adhesive layer 13 is formed as a high-speed flame spraying (HVOF) applied to the component adhesive layer.
  • HVOF high-speed flame spraying
  • the metallic matrix material 15 of the cover layer 12 is electrodeposited.
  • the abrasive particles 14 are embedded, which are preferably formed as hard particles of cubic boron nitride.
  • the metallic matrix material 15 of the cover layer 12 and the metallic adhesion layer 13 are each formed from a MCr Al Y material which preferably has the following composition:
  • Cr chromium
  • Co cobalt
  • Al aluminum
  • Ta tantalum
  • Re rhenium
  • Hf hafnium
  • Si silicon
  • Y yttrium
  • composition of the MCrAlY material is particularly preferred.
  • Cr chromium
  • Co cobalt
  • Al aluminum
  • Ta tantalum
  • Re rhenium
  • Hf hafnium
  • Si silicon
  • Y yttrium
  • a blade is provided with a blade tip armor, wherein the blade tip armor a high speed flame-spray adhesive layer which serves to connect the blade tip armor 11 to the blade tip 10, and wherein the Hochgeschwindig- Flammspritz adhesive layer 13 has a high mechanical strength, especially at high operating temperatures.
  • the adhesion layer 13 carries the cover layer 12, which is formed from abrasive particles 14 embedded in the metallic matrix material 15, the metallic matrix material 15 of the cover layer 12 being electrodeposited.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • Inorganic Chemistry (AREA)
  • Composite Materials (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrochemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)

Abstract

The invention relates to a component, in particular a rotor blade of a gas turbine, with a reinforcing plating, in particular a blade tip plating, wherein the reinforcing plating (11) comprises a top layer (12), which is formed from abrasive particles (14) intercalated in a metallic matrix material (15), and wherein the top layer (12) is applied to a surface of the component (10) with a metallic bonding layer (13) in-between. According to the invention, the metallic bonding layer (13) is formed as a bonding layer applied to the component (10) by high-velocity flame spraying, with the metallic matrix material (15) of the top layer (12) being deposited by electroplating.

Description

Bauteil mit einer Panzerung Component with an armor
Die Erfindung betrifft ein Bauteil, insbesondere ein Gasturbinenbauteil wie eine Laufschaufel, mit einer Panzerung, insbesondere einer Schaufelspitzenpanzerung, nach dem Oberbegriff des Anspruchs 1.The invention relates to a component, in particular a gas turbine component such as a blade, with an armor, in particular a blade tip armor, according to the preamble of claim 1.
Turbomaschinen, wie zum Beispiel Gasturbinen, umfassen in der Regel mehrere rotierende Laufschaufeln sowie mehrere feststehende Leitschaufeln, wobei die Laufschaufeln zusammen mit einem Rotor rotieren, und wobei die Laufschaufeln sowie die Leitschaufeln von einem feststehenden Gehäuse umschlossen sind. Zur Leistungssteigerung ist es von Bedeutung, alle Komponenten und Subsysteme zu optimieren. Hierzu zählen auch die sogenannten Dichtsysteme.Turbomachines, such as gas turbines, typically include a plurality of rotating blades and a plurality of stationary vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a fixed housing. To increase performance, it is important to optimize all components and subsystems. These include the so-called sealing systems.
Besonders problematisch ist bei Turbomaschinen die Einhaltung eines minimalen Spalts zwischen den rotierenden Laufschaufeln und dem feststehenden Gehäuse eines Hochdruckverdichters. Bei Hochdruckverdichtern treten nämlich die größten absoluten Temperaturen sowie Temperaturengradienten auf, was die Spalthaltung der rotierenden Laufschaufeln zum feststehenden Gehäuse erschwert. Dies liegt unter anderem auch darin begründet, dass bei Verdichterlaufschaufeln auf Deckbänder, wie sie bei Turbinenlaufschaufeln verwendet werden, verzichtet wird.Particularly problematic in turbomachinery compliance with a minimum gap between the rotating blades and the fixed housing of a high pressure compressor. Namely, the highest absolute temperatures and temperature gradients occur in high-pressure compressors, which makes it more difficult for the rotating blades to cling to the stationary housing. This is partly due to the fact that in compressor blades on shrouds, as used in turbine blades, is dispensed with.
Wie bereits erwähnt, verfügen Laufschaufeln im Verdichter über kein Deckband. Daher sind Enden bzw. Spitzen der Laufschaufeln beim sogenannten Anstreifen in das feststehende Gehäuse einem direkten Reibkontakt mit dem Gehäuse ausgesetzt. Ein solches Anstreifen der Spitzen der Laufschaufeln in das Gehäuse wird bei Einstellung eines minimalen Radialspalts durch Fertigungstoleranzen hervorgerufen. Da durch den Reibkontakt der Spitzen der Laufschaufeln an denselben Material abgetragen wird, kann sich über den gesamten Umfang von Gehäuse und Rotor eine unerwünschte Spaltvergrößerung einstellen. Um dies zu vermeiden ist es aus dem Stand der Technik bereits bekannt, die Enden bzw. Spitzen der Laufschaufeln mit einem harten Belag oder mit abrasiven Partikeln zu panzern. Dabei sind aus dem Stand der Technik zwei unterschiedliche Typen von Schaufelspitzen- panzerungen bekannt, nämlich Schaufelspitzenpanzerungen aus einem keramischen Werkstoff oder Schaufelspitzenpanzerungen aus abrasiven Partikeln. Die hier vorliegende Erfindung betrifft eine Panzerung, insbesondere eine Schaufelspitzenpanzerung, eines Bauteils, insbesondere einer Gasturbinenlaufschaufel, mit abrasiven Partikeln.As mentioned earlier, blades in the compressor have no shroud. Therefore, tips of the blades are exposed to so-called rubbing into the fixed housing in direct frictional contact with the housing. Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances. As is removed by the frictional contact of the tips of the blades on the same material, over the entire circumference of the housing and rotor can set an undesirable gap magnification. To avoid this, it is already known from the prior art to armor the ends or tips of the blades with a hard coating or with abrasive particles. Two different types of blade tips are known from the prior art. armor known, namely blade tip armor made of a ceramic material or blade tip armor from abrasive particles. The present invention relates to an armor, in particular a blade tip armor, a component, in particular a gas turbine blade, with abrasive particles.
Die US 6,194,086 Bl offenbart eine Laufschaufel einer Gasturbine mit einer Schaufelspitzenpanzerung, wobei die Schaufelspitzenpanzerung eine Deckschicht umfasst, die aus in ein metallisches Matrixmaterial eingelagerten, abrasiven Partikeln gebildet ist. Die Deckschicht aus den in das metallische Matrixmaterial eingelagerten, abrasiven Partikeln ist unter Zwischenanordnung einer metallischen Haftvermittlungsschicht auf die Spitze einer zu panzernden Laufschaufel aufgebracht. Dabei ist die metallische Haftschicht als LPPS- Schicht ausgebildet und demnach über ein sogenanntes Low Pressure Plasma Spraying auf das Bauteil aufgebracht. Der Nachteil solcher LPPS Haftschichten liegt darin, dass dieselben insbesondere bei hohen Betriebstemperaturen von bis zu 1.200° C eine geringe mechanische Haftung an der Schaufelspitze aufweisen, so dass es im Betrieb zu einem Abplatzen der Schaufelspitzenpanzerung kommen kann.US 6,194,086 Bl discloses a blade of a gas turbine with a blade tip armor, wherein the blade tip armor comprises a cover layer, which is formed from in a metallic matrix material embedded abrasive particles. The cover layer of the abrasive particles embedded in the metallic matrix material is applied to the tip of a blade to be coated with the interposition of a metallic adhesion-promoting layer. In this case, the metallic adhesive layer is formed as LPPS layer and therefore applied to the component via a so-called low pressure plasma spraying. The disadvantage of such LPPS adhesive layers is that they have a low mechanical adhesion to the blade tip, especially at high operating temperatures of up to 1200 ° C., so that the blade tip armor may flake off during operation.
Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Bauteil mit einer Panzerung zu schaffen. Dieses Problem wird durch ein Bauteil im Sinne von Anspruch 1 gelöst. Erfindungsgemäß ist die metallische Haftschicht als eine ü- ber Hochgeschwindigkeitsflammspritzen auf das Bauteil aufgebrachte Haftschicht ausgebildet, wobei das metallische Matrixmaterial der Deckschicht galvanisch abgeschieden ist.On this basis, the present invention based on the problem of creating a novel component with an armor. This problem is solved by a component in the sense of claim 1. According to the invention, the metallic adhesive layer is formed as an adhesive layer applied to the component via high-speed flame spraying, wherein the metallic matrix material of the cover layer is electrodeposited.
Erfindungsgemäß ist die Haftschicht über Hochgeschwindigkeitsflammspritzen auf das Bauteil aufgebracht. Hierdurch haftet die Panzerung bei hohen Temperaturen besser auf dem Bauteil als bei Verwendung von LPPS Haftschichten. Die Schaufelspitzenpanzerung des Bauteils verfügt demnach über eine höhere mechanische Haftung, insbesondere bei hohen Betriebstemperaturen. Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigt:According to the invention, the adhesive layer is applied to the component via high-speed flame spraying. As a result, the armor adheres better to the component at high temperatures than when using LPPS adhesive layers. The blade tip armor of the component therefore has a higher mechanical adhesion, especially at high operating temperatures. Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1 : einen schematisierten Querschnitt durch eine auf einem Bauteil aufgebrachteFig. 1: a schematic cross section through an applied on a component
Panzerung.Armor.
Die Erfindung betrifft ein gepanzertes Bauteil, insbesondere eine mit einer Schaufelspitzenpanzerung versehene Laufschaufel einer Gasturbine. Bevorzugt ist die Laufschaufel der Gasturbine als Hochdruckverdichterlaufschaufel ausgeführt.The invention relates to an armored component, in particular a blade provided with a blade tip armor of a gas turbine. Preferably, the blade of the gas turbine is designed as a high-pressure compressor blade.
Fig. 1 zeigt einen stark schematisierten Querschnitt durch eine Schaufelspitze 10 einer Laufschaufel, wobei die Schaufelspitze 10 der Laufschaufel eine Schaufelspitzenpanzerung 11 trägt.1 shows a highly schematic cross section through a blade tip 10 of a blade, wherein the blade tip 10 of the blade carries a blade tip armor 11.
Die Schaufelspitzenpanzerung 11 verfugt über mindestens zwei Schichten, nämlich eine äußere Deckschicht 12 und eine innere Haftschicht 13. Im Ausfuhrungsbeispiel der Fig. 1 ist die Deckschicht 12 über die Haftschicht 13 auf die Schaufelspitze 10 aufgebracht. Zwischen der Deckschicht 12 und der Haftschicht 13 können gegebenenfalls weitere, zusätzliche Schichten vorhanden sein.The blade tip armor 11 has at least two layers, namely an outer cover layer 12 and an inner adhesive layer 13. In the exemplary embodiment of FIG. 1, the cover layer 12 is applied to the blade tip 10 via the adhesive layer 13. Optionally, additional additional layers may be present between the cover layer 12 and the adhesion layer 13.
Die Deckschicht 12 ist gemäß Fig. 1 von abrasiven Partikeln 14 gebildet, die in ein metallisches Matrixmaterial 15 eingelagert sind. Die Haftschicht 13 ist als metallische Haftschicht ausgeführt. Die metallische Haftschicht 13 sowie das metallische Matrixmaterial 15 der Deckschicht 12 sind jeweils aus einem MCr Al Y- Werkstoff gebildet.According to FIG. 1, the cover layer 12 is formed by abrasive particles 14, which are embedded in a metallic matrix material 15. The adhesive layer 13 is designed as a metallic adhesive layer. The metallic adhesive layer 13 and the metallic matrix material 15 of the cover layer 12 are each formed from a MCr Al Y material.
Im Sinne der hier vorliegenden Erfindung ist die metallische Haftschicht 13 als eine über Hochgeschwindigkeitsflammspritzen (HVOF) auf das Bauteil aufgebrachte Haftschicht ausgebildet. Durch das Aufbringen der Haftschicht 13 mit Hilfe von Hochgeschwindig- keitsflammspritzen wird dieselbe sehr fest und wenig porös, so dass dieselbe letztendlich auf der Schaufelspitze 10 gut haftet. Das metallische Matrixmaterial 15 der Deckschicht 12 wird galvanisch abgeschieden. In dasselbe sind die abrasiven Partikel 14 eingelagert, die vorzugsweise als Hartstoffpartikel aus kubischem Bornitrid gebildet sind.For the purposes of the present invention, the metallic adhesive layer 13 is formed as a high-speed flame spraying (HVOF) applied to the component adhesive layer. By applying the adhesive layer 13 by means of high-speed flame spraying, it becomes very strong and less porous, so that it finally adheres well to the blade tip 10. The metallic matrix material 15 of the cover layer 12 is electrodeposited. In the same, the abrasive particles 14 are embedded, which are preferably formed as hard particles of cubic boron nitride.
Wie bereits erwähnt, sind das metallische Matrixmaterial 15 der Deckschicht 12 sowie die metallische Haftschicht 13 jeweils aus einem MCr Al Y- Werkstoff gebildet, der vorzugsweise folgende Zusammensetzung aufweist:As already mentioned, the metallic matrix material 15 of the cover layer 12 and the metallic adhesion layer 13 are each formed from a MCr Al Y material which preferably has the following composition:
14-22 Gew.-% Chrom (Cr), 6-14 Gew.-% Kobalt (Co), 4-9 Gew.-% Aluminium (Al), 5-8 Gew.-% Tantal (Ta), 1-3 Gew.-% Rhenium (Re), 0,5-1 Gew.-% Hafnium (Hf), 0,5-1,5 Gew.-% Silizium (Si), 0,3-1 Gew.-% Yttrium (Y), und im Rest Nickel.14-22% by weight chromium (Cr), 6-14% by weight cobalt (Co), 4-9% by weight aluminum (Al), 5-8% by weight tantalum (Ta), 1- 3% by weight of rhenium (Re), 0.5-1% by weight of hafnium (Hf), 0.5-1.5% by weight of silicon (Si), 0.3-1% by weight of yttrium (Y), and in the rest nickel.
Besonders bevorzugt ist folgende Zusammensetzung des MCrAlY-Werkstoffs:Particularly preferred is the following composition of the MCrAlY material:
18 Gew.-% Chrom (Cr), 10 Gew.-% Kobalt (Co), 6,5 Gew.-% Aluminium (Al), 6 Gew.-% Tantal (Ta), 2 Gew.-% Rhenium (Re), 0,5 Gew.-% Hafnium (Hf), 1 Gew.-% Silizium (Si), 0,3 Gew.-% Yttrium (Y), und im Rest Nickel.18% by weight chromium (Cr), 10% by weight cobalt (Co), 6.5% by weight aluminum (Al), 6% by weight tantalum (Ta), 2% by weight rhenium (Re ), 0.5 wt% hafnium (Hf), 1 wt% silicon (Si), 0.3 wt% yttrium (Y), and the remainder nickel.
Im Sinne der hier vorliegenden Erfindung wird demnach eine Laufschaufel mit einer Schaufelspitzenpanzerung bereitgestellt, wobei die Schaufelspitzenpanzerung eine Hoch- geschwindigkeitsflammspritz-Haftschicht aufweist, die der Anbindung der Schaufelspitzenpanzerung 11 an die Schaufelspitze 10 dient, und wobei die Hochgeschwindig- keitsflammspritz-Haftschicht 13 eine hohe mechanische Belastbarkeit, insbesondere bei hohen Betriebstemperaturen aufweist. Die Haftschicht 13 trägt die Deckschicht 12, die aus in das metallische Matrixmaterial 15 eingelagerten abrasiven Partikeln 14 gebildet ist, wobei das metallische Matrixmaterial 15 der Deckschicht 12 galvanisch abgeschieden ist.According to the present invention, therefore, a blade is provided with a blade tip armor, wherein the blade tip armor a high speed flame-spray adhesive layer which serves to connect the blade tip armor 11 to the blade tip 10, and wherein the Hochgeschwindig- Flammspritz adhesive layer 13 has a high mechanical strength, especially at high operating temperatures. The adhesion layer 13 carries the cover layer 12, which is formed from abrasive particles 14 embedded in the metallic matrix material 15, the metallic matrix material 15 of the cover layer 12 being electrodeposited.
* * * * * *

Claims

Patentansprüche claims
1. Bauteil, insbesondere Laufschaufel einer Gasturbine, mit einer Panzerung, insbesondere einer Schaufelspitzenpanzerung, wobei die Panzerung eine Deckschicht umfasst, die aus in ein metallisches Matrixmaterial eingelagerten, abrasiven Partikeln gebildet ist, und wobei die Deckschicht unter Zwischenanordnung einer metallischen Haftschicht auf eine Oberfläche des Bauteils aufgebracht ist, dadurch gekennzeichnet, dass die metallische Haftschicht (13) als eine über Hochgeschwindigkeitsflammsprit- zen auf das Bauteil aufgebrachte Haftschicht ausgebildet ist, und dass das metallische Matrixmaterial (15) der Deckschicht (12) galvanisch abgeschiedenen ist.1. component, in particular blade of a gas turbine, with an armor, in particular a blade tip armor, wherein the armor comprises a cover layer, which is formed from embedded in a metallic matrix material, abrasive particles, and wherein the cover layer with interposition of a metallic adhesive layer on a surface of the Component is applied, characterized in that the metallic adhesive layer (13) is formed as a zen on Hochgeschwindigkeitsflammsprit- applied to the component adhesive layer, and that the metallic matrix material (15) of the cover layer (12) is electrodeposited.
2. Bauteil nach Anspruch 1, dadurch gekennzeichnet, dass das metallische Matrixmaterial (15) der Deckschicht (12) aus einem MCrAlY- Werkstoff gebildet ist oder einen MCrAlY- Werkstoff aufweist.2. Component according to claim 1, characterized in that the metallic matrix material (15) of the cover layer (12) is formed from a MCrAlY material or comprises a MCrAlY material.
3. Bauteil nach Anspruch 2, dadurch gekennzeichnet, dass das metallische Matrixmaterial (15) der Deckschicht (12) aus einem MCrAlY-3. Component according to claim 2, characterized in that the metallic matrix material (15) of the cover layer (12) consists of a MCrAlY-
Werkstoff gebildet ist und folgende Zusammensetzung aufweist:Material is formed and has the following composition:
14-22 Gew.-% Chrom (Cr),14-22% by weight chromium (Cr),
6-14 Gew.-% Kobalt (Co),6-14% by weight of cobalt (Co),
4-9 Gew.-% Aluminium (Al),4-9% by weight of aluminum (Al),
5-8 Gew.-% Tantal (Ta),5-8% by weight tantalum (Ta),
1-3 Gew.-% Rhenium (Re)5 1-3% by weight of rhenium (Re) 5
0,5-1 Gew.-% Hafnium (Hf),0.5-1% by weight hafnium (Hf),
0,5-1,5 Gew.-% Silizium (Si),0.5-1.5% by weight of silicon (Si),
0,3-1 Gew.-% Yttrium (Y), und im Rest Nickel. 0.3-1 wt% yttrium (Y), and the remainder nickel.
4. Bauteil nach Anspruch 3, dadurch gekennzeichnet, dass der MCrAl Y- Werkstoff folgende Zusammensetzung aufweist:4. Component according to claim 3, characterized in that the MCrAl Y material has the following composition:
18 Gew.-% Chrom (Cr),18% by weight chromium (Cr),
10 Gew.-% Kobalt (Co),10% by weight of cobalt (Co),
6,5 Gew.-% Aluminium (Al),6.5% by weight of aluminum (Al),
6 Gew.-% Tantal (Ta),6% by weight tantalum (Ta),
2 Gew.-% Rhenium (Re),2% by weight rhenium (Re),
0,5 Gew.-% Hafnium (Hf),0.5% by weight hafnium (Hf),
1 Gew.-% Silizium (Si),1% by weight of silicon (Si),
0,3 Gew.-% Yttrium (Y), und im Rest Nickel.0.3 wt .-% yttrium (Y), and the balance nickel.
5. Bauteil nach einem oder mehreren der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die metallische Haftschicht (13) aus einem MCrAl Y- Werkstoff gebildet ist und folgende Zusammensetzung aufweist:5. Component according to one or more of claims 1 to 4, characterized in that the metallic adhesive layer (13) is formed from a MCrAl Y material and has the following composition:
14-22 Gew.-% Chrom (Cr),14-22% by weight chromium (Cr),
6-14 Gew.-% Kobalt (Co),6-14% by weight of cobalt (Co),
4-9 Gew.-% Aluminium (Al),4-9% by weight of aluminum (Al),
5-8 Gew.-% Tantal (Ta),5-8% by weight tantalum (Ta),
1-3 Gew.-% Rhenium (Re),1-3% by weight rhenium (Re),
0,5-1 Gew.-% Hafnium (Hf),0.5-1% by weight hafnium (Hf),
0,5-1,5 Gew.-% Silizium (Si),0.5-1.5% by weight of silicon (Si),
0,3-1 Gew.-% Yttrium (Y), und im Rest Nickel. 0.3-1 wt% yttrium (Y), and the remainder nickel.
6. Bauteil nach Anspruch 5, dadurch gekennzeichnet, dass der MCrAl Y- Werkstoff folgende Zusammensetzung aufweist:6. Component according to claim 5, characterized in that the MCrAl Y material has the following composition:
18 Gew.-% Chrom (Cr)5 18% by weight chromium (Cr) 5
10 Gew.-% Kobalt (Co),10% by weight of cobalt (Co),
6,5 Gew.-% Aluminium (Al),6.5% by weight of aluminum (Al),
6 Gew.-% Tantal (Ta),6% by weight tantalum (Ta),
2 Gew.-% Rhenium (Re),2% by weight rhenium (Re),
0,5 Gew.-% Hafnium (Hf),0.5% by weight hafnium (Hf),
1 Gew.-% Silizium (Si),1% by weight of silicon (Si),
0,3 Gew.-% Yttrium (Y), und im Rest Nickel.0.3 wt .-% yttrium (Y), and the balance nickel.
7. Bauteil nach einem oder mehreren der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass die abrasiven Partikeln (14) der Deckschicht (12) aus kubischem Bornitrid gebildet sind.7. Component according to one or more of claims 1 to 6, characterized in that the abrasive particles (14) of the cover layer (12) are formed of cubic boron nitride.
# * * # * *
EP07722169A 2006-04-11 2007-04-04 Component with a reinforcing plating Expired - Fee Related EP2044231B1 (en)

Priority Applications (1)

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DE102006016995A DE102006016995A1 (en) 2006-04-11 2006-04-11 Component with an armor
PCT/DE2007/000611 WO2007115551A1 (en) 2006-04-11 2007-04-04 Component with a reinforcing plating

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EP (1) EP2044231B1 (en)
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3597860A1 (en) * 2018-07-19 2020-01-22 United Technologies Corporation Coating to improve oxidation and corrosion resistance of abrasive tip system

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008003100A1 (en) * 2008-01-03 2009-07-16 Mtu Aero Engines Gmbh Solder coating, method for coating a component, component and adhesive tape with a solder coating
DE102008056741A1 (en) * 2008-11-11 2010-05-12 Mtu Aero Engines Gmbh Wear protection layer for Tial
DE102009018685A1 (en) * 2009-04-23 2010-10-28 Mtu Aero Engines Gmbh Method for producing an armor of a blade tip as well as correspondingly produced blades and gas turbines
DE102009031313B4 (en) 2009-06-30 2018-07-05 MTU Aero Engines AG Coating and method for coating a component
US20120128525A1 (en) * 2010-11-24 2012-05-24 Kulkarni Anand A Metallic Bondcoat or Alloy with a High y/y' Transition Temperature and a Component
US20140037970A1 (en) * 2012-08-03 2014-02-06 General Electric Company Reinforced articles and methods of making the same
DE102013218687A1 (en) 2013-09-18 2015-04-02 MTU Aero Engines AG Galvanized wear protection coating and method therefor
US20160237832A1 (en) * 2015-02-12 2016-08-18 United Technologies Corporation Abrasive blade tip with improved wear at high interaction rate
US10450876B2 (en) * 2015-04-15 2019-10-22 United Technologies Corporation Abrasive tip blade manufacture methods
US10544699B2 (en) * 2017-12-19 2020-01-28 Rolls-Royce Corporation System and method for minimizing the turbine blade to vane platform overlap gap
US11073028B2 (en) * 2018-07-19 2021-07-27 Raytheon Technologies Corporation Turbine abrasive blade tips with improved resistance to oxidation
US11028721B2 (en) 2018-07-19 2021-06-08 Ratheon Technologies Corporation Coating to improve oxidation and corrosion resistance of abrasive tip system
US11536151B2 (en) 2020-04-24 2022-12-27 Raytheon Technologies Corporation Process and material configuration for making hot corrosion resistant HPC abrasive blade tips

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5316866A (en) * 1991-09-09 1994-05-31 General Electric Company Strengthened protective coatings for superalloys
US5584663A (en) * 1994-08-15 1996-12-17 General Electric Company Environmentally-resistant turbine blade tip
US5935407A (en) * 1997-11-06 1999-08-10 Chromalloy Gas Turbine Corporation Method for producing abrasive tips for gas turbine blades
DE19905811A1 (en) * 1999-02-12 2000-08-17 Erwin Huehne High speed flame spray gun for thermal spraying of rod, wire or powder-form filler materials, has connection constructed so that liquid and gaseous fuels and oxidation gas can be directed separately into combustion chamber
NL1014924C2 (en) * 1999-07-30 2001-02-01 Chromalloy Holland B V Limitation of air resistance for components of a gas turbine engine.
US6706319B2 (en) * 2001-12-05 2004-03-16 Siemens Westinghouse Power Corporation Mixed powder deposition of components for wear, erosion and abrasion resistant applications
US7547478B2 (en) * 2002-12-13 2009-06-16 General Electric Company Article including a substrate with a metallic coating and a protective coating thereon, and its preparation and use in component restoration

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007115551A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3597860A1 (en) * 2018-07-19 2020-01-22 United Technologies Corporation Coating to improve oxidation and corrosion resistance of abrasive tip system

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US20090311552A1 (en) 2009-12-17
DE102006016995A1 (en) 2007-10-18
WO2007115551A1 (en) 2007-10-18
EP2044231B1 (en) 2009-12-30
DE502007002499D1 (en) 2010-02-11
PL2044231T3 (en) 2010-06-30

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