EP2044231B1 - Component with a reinforcing plating - Google Patents
Component with a reinforcing plating Download PDFInfo
- Publication number
- EP2044231B1 EP2044231B1 EP07722169A EP07722169A EP2044231B1 EP 2044231 B1 EP2044231 B1 EP 2044231B1 EP 07722169 A EP07722169 A EP 07722169A EP 07722169 A EP07722169 A EP 07722169A EP 2044231 B1 EP2044231 B1 EP 2044231B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- weight
- component
- cover layer
- metallic
- blade
- 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.)
- Expired - Fee Related
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Classifications
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- 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.
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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 fixed vanes, the blades rotating together with a rotor, and wherein the blades and the vanes are enclosed by a stationary housing.
- a stationary housing typically includes a plurality of rotating blades and a plurality of fixed vanes, the blades rotating together with a rotor, and wherein the blades and the vanes are enclosed by a stationary housing.
- sealing systems 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. 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 tip armor are known from the prior art known 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.
- the US 6,194,086 B1 discloses a blade of a gas turbine having a blade tip armor, the blade tip armor comprising a cover layer formed of abrasive particles incorporated in a metallic matrix material.
- 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 via a so-called low pressure plasma spraying on the component.
- 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.
- 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 according to Fig. 1 formed by abrasive particles 14 which are incorporated 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 MCrAlY 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 an MCrAlY material having the following composition: 14-22% by weight chromium (Cr), 6-14% by weight of cobalt (Co), 4-9% by weight of aluminum (A1), 5-8% by weight tantalum (Ta), 1-3% by weight rhenium (Re), 0.5-1% by weight hafnium (Hf), 0.5-1.5% by weight of silicon (Si), 0.3-1 wt% yttrium (Y), and in the rest of nickel.
- Cr chromium
- Co cobalt
- Al aluminum
- Ta tantalum
- Re 1-3% by weight rhenium
- Hf hafnium
- Si silicon
- Y 0.3-1 wt% yttrium
- composition of the MCrAlY material 18% by weight chromium (Cr), 10% by weight of cobalt (Co), 6.5% by weight of aluminum (Al), 6% by weight tantalum (Ta), 2% by weight rhenium (Re), 0.5% by weight hafnium (Hf), 1% by weight of silicon (Si), 0.3% by weight of yttrium (Y), and in the rest of nickel.
- 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 high-speed flame-spray 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.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Plasma & Fusion (AREA)
- Physics & Mathematics (AREA)
- Composite Materials (AREA)
- Inorganic Chemistry (AREA)
- Electrochemistry (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Coating By Spraying Or Casting (AREA)
Description
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 fixed vanes, the blades rotating together with a rotor, and wherein the blades and the vanes are enclosed by a stationary 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 Schaufelspitzenpanzerungen 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 tip armor are known from the prior art known 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
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 über 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.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.
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:
- Fig. 1:
- einen schematisierten Querschnitt durch eine auf einem Bauteil aufgebrachte Panzerung.
- Fig. 1:
- a schematic cross section through an applied on a component 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.
Die Schaufelspitzenpanzerung 11 verfügt über mindestens zwei Schichten, nämlich eine äußere Deckschicht 12 und eine innere Haftschicht 13. Im Ausführungsbeispiel der
Die Deckschicht 12 ist gemäß
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 Hochgeschwindigkeitsflammspritzen 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
Wie bereits erwähnt, sind das metallische Matrixmaterial 15 der Deckschicht 12 sowie die metallische Haftschicht 13 jeweils aus einem MCrAlY-Werkstoff gebildet, der folgende Zusammensetzung aufweist:
14-22 Gew.-% Chrom (Cr),
6-14 Gew.-% Kobalt (Co),
4-9 Gew.-% Aluminium (A1),
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.As already mentioned, the
14-22% by weight chromium (Cr),
6-14% by weight of cobalt (Co),
4-9% by weight of aluminum (A1),
5-8% by weight tantalum (Ta),
1-3% by weight rhenium (Re),
0.5-1% by weight hafnium (Hf),
0.5-1.5% by weight of silicon (Si),
0.3-1 wt% yttrium (Y), and
in the rest of nickel.
Besonders bevorzugt ist folgende Zusammensetzung des MCrAlY-Werkstoffs:
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.Particularly preferred is the following composition of the MCrAlY material:
18% by weight chromium (Cr),
10% by weight of cobalt (Co),
6.5% by weight of aluminum (Al),
6% by weight tantalum (Ta),
2% by weight rhenium (Re),
0.5% by weight hafnium (Hf),
1% by weight of silicon (Si),
0.3% by weight of yttrium (Y), and
in the rest of nickel.
Im Sinne der hier vorliegenden Erfindung wird demnach eine Laufschaufel mit einer Schaufelspitzenpanzerung bereitgestellt, wobei die Schaufelspitzenpanzerung eine Hochgeschwindigkeitsflammspritz-Haftschicht aufweist, die der Anbindung der Schaufelspitzenpanzerung 11 an die Schaufelspitze 10 dient, und wobei die Hochgeschwindigkeitsflammspritz-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
Claims (5)
- A component, in particular a moving blade of a gas turbine, having a reinforcing plating, in particular a blade-tip reinforcing plating, wherein the reinforcing plating comprises a cover layer which is formed from abrasive particles intercalated in a metallic matrix material, and wherein the cover layer is applied to a surface of the component with interposition of a metallic bonding layer,
characterised in that
the metallic bonding layer (13) is formed as a bonding layer that is applied to the component by high-velocity flame spraying, and in that the metallic matrix material (15) of the cover layer (12) is deposited by electroplating, wherein the metallic matrix material (15) of the cover layer (12) is formed from an MCrAlY-material and has the following composition:14-22 % by weight chromium (Cr),6-14 % by weight cobalt (Co),4-9 % by weight aluminium (Al),5-8 % by weight tantalum (Ta),1-3 % by weight rhenium (Re),0.5-1 % by weight hafnium (Hf),0.5-1.5 % by weight silicon (Si),0.3-1 % by weight yttrium (Y), andremainder nickel. - A component according to claim 1,
characterised in that
the MCrAIY-material has the following composition:18 % by weight chromium (Cr),10 % by weight cobalt (Co),6.5 % by weight aluminium (Al),6 % by weight tantalum (Ta),2 % by weight rhenium (Re),0.5 % by weight hafnium (Hf),1 % by weight silicon (Si),0.3 % by weight yttrium (Y), andremainder nickel. - A component according to one or more of claims 1 to 2,
characterised in that
the metallic bonding layer (13) is formed from an MCrAIY-material and has the following composition:14-22 % by weight chromium (Cr),6-14 % by weight cobalt (Co),4-9 % by weight aluminium (Al),5-8 % by weight tantalum (Ta),1-3 % by weight rhenium (Re),0.5-1 % by weight hafnium (Hf),0.5-1.5 % by weight silicon (Si),0.3-1 % by weight yttrium (Y), andremainder nickel. - A component according to claim 3,
characterised in that
the MCrAIY-material has the following composition:18 % by weight chromium (Cr),10 % by weight cobalt (Co),6.5 % by weight aluminium (Al),6 % by weight tantalum (Ta),2 % by weight rhenium (Re),0.5 % by weight hafnium (Hf),1 % by weight silicon (Si),0.3 % by weight yttrium (Y), andremainder nickel. - A component according to one or more of claims 1 to 4,
characterised in that
the abrasive particles (14) of the cover layer (12) are formed from cubic boron nitride.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PL07722169T PL2044231T3 (en) | 2006-04-11 | 2007-04-04 | Component with a reinforcing plating |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2044231A1 EP2044231A1 (en) | 2009-04-08 |
EP2044231B1 true EP2044231B1 (en) | 2009-12-30 |
Family
ID=38180702
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07722169A Expired - Fee Related EP2044231B1 (en) | 2006-04-11 | 2007-04-04 | Component with a reinforcing plating |
Country Status (5)
Country | Link |
---|---|
US (1) | US20090311552A1 (en) |
EP (1) | EP2044231B1 (en) |
DE (2) | DE102006016995A1 (en) |
PL (1) | PL2044231T3 (en) |
WO (1) | WO2007115551A1 (en) |
Families Citing this family (14)
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 |
US10927685B2 (en) * | 2018-07-19 | 2021-02-23 | Raytheon Technologies Corporation | Coating to improve oxidation and corrosion resistance of abrasive tip system |
US11028721B2 (en) * | 2018-07-19 | 2021-06-08 | Ratheon Technologies Corporation | Coating to improve oxidation and corrosion resistance of abrasive tip system |
US11073028B2 (en) * | 2018-07-19 | 2021-07-27 | Raytheon Technologies Corporation | Turbine abrasive blade tips with improved resistance to oxidation |
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)
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 |
-
2006
- 2006-04-11 DE DE102006016995A patent/DE102006016995A1/en not_active Withdrawn
-
2007
- 2007-04-04 WO PCT/DE2007/000611 patent/WO2007115551A1/en active Application Filing
- 2007-04-04 EP EP07722169A patent/EP2044231B1/en not_active Expired - Fee Related
- 2007-04-04 US US12/296,985 patent/US20090311552A1/en not_active Abandoned
- 2007-04-04 PL PL07722169T patent/PL2044231T3/en unknown
- 2007-04-04 DE DE502007002499T patent/DE502007002499D1/en active Active
Also Published As
Publication number | Publication date |
---|---|
DE502007002499D1 (en) | 2010-02-11 |
US20090311552A1 (en) | 2009-12-17 |
WO2007115551A1 (en) | 2007-10-18 |
PL2044231T3 (en) | 2010-06-30 |
DE102006016995A1 (en) | 2007-10-18 |
EP2044231A1 (en) | 2009-04-08 |
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