US20090311552A1 - Component with a reinforcing plating - Google Patents

Component with a reinforcing plating Download PDF

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Publication number
US20090311552A1
US20090311552A1 US12/296,985 US29698507A US2009311552A1 US 20090311552 A1 US20090311552 A1 US 20090311552A1 US 29698507 A US29698507 A US 29698507A US 2009311552 A1 US2009311552 A1 US 2009311552A1
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Prior art keywords
weight
component
bonding layer
cover layer
metallic
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US12/296,985
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Karl-Heinz Manier
Josef Linska
Andre Werner
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MTU Aero Engines AG
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Individual
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Assigned to MTU AERO ENGINES GMBH reassignment MTU AERO ENGINES GMBH ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MANIER, KARL-HEINZ, LINSKA, JOSEF, WERNER, ANDRE
Publication of US20090311552A1 publication Critical patent/US20090311552A1/en
Abandoned legal-status Critical Current

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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.
    • 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 present invention relates to a component, in particular a gas turbine component such as a turbine rotor blade, having a plating, in particular a blade tip plating, as recited in the preamble of Claim 1 .
  • Turbomachines such as gas turbines, generally have a plurality of rotating rotor blades and a plurality of stationary guide blades, the rotor blades rotating together with a rotor and the rotor blades and guide blades being enclosed in a stationary housing.
  • it is important to optimize all components and subsystems, including what are known as sealing systems.
  • rotor blades in a compressor do not have shrouds. Therefore, ends or tips of the rotor blades are exposed to direct frictional contact with the stationary housing, in what is called blade rubbing. Such rubbing of the tips of the rotor blades in the housing is caused by manufacturing tolerances during the setting of a minimum radial gap. Because the frictional contact of the tips of the rotor blades wears material away from them, an undesired enlargement of the gap can result around the entire periphery of the housing and rotor. In order to avoid this, it is known from the prior art to plate the ends or tips of the rotor blades with a hard coating or with abrasive particles.
  • the present invention relates to a plating, in particular a blade tip plating, of a component, in particular a gas turbine rotor blade, with abrasive particles.
  • U.S. Pat. No. 6,194,086 B1 discloses a rotor blade of a gas turbine having a blade tip plating in which the blade tip plating comprises a cover layer that is made of abrasive particles embedded in a metallic matrix material.
  • the cover layer made up of the abrasive particles embedded in the metallic matrix material is applied onto the tip of a rotor blade that is to be plated with the interposition of a metallic bonding layer.
  • the metallic bonding layer is fashioned as a LPPS layer, and is accordingly applied to the component using low-pressure plasma spraying.
  • the disadvantage of such LPPS bonding layers is that in particular at high operating temperatures of up to 1200° C. they have low mechanical adhesion to the blade tip, so that during operation the blade tip plating can flake off.
  • the present invention is based on the problem of creating a new type of component having a plating. This problem is solved by a component as recited in Claim 1 .
  • the metallic bonding layer is fashioned as a bonding layer that is applied to the component using high-speed flame spraying, the metallic matrix material of the cover layer being galvanically deposited.
  • the bonding layer is applied to the component using high-speed flame spraying.
  • the plating adheres to the component better than is the case given the use of LPPS bonding layers.
  • the blade tip plating of the component accordingly has better mechanical bonding, in particular at high operating temperatures.
  • FIG. 1 shows a schematized cross-section of a plating applied to a component.
  • the present invention relates to a plated component, in particular a rotor blade of a gas turbine provided with a blade tip plating.
  • the rotor blade of the gas turbine is preferably realized as a high-pressure compressor rotor blade.
  • FIG. 1 shows a highly schematized cross-section of a blade tip 10 of a rotor blade, blade tip 10 of the rotor blade having a blade tip plating 11 .
  • Blade tip plating 11 has at least two layers, namely an outer cover layer 12 and an inner bonding layer 13 .
  • cover layer 12 is applied onto blade tip 10 via bonding layer 13 . Additional layers may be present between cover layer 12 and bonding layer 13 .
  • cover layer 12 is formed by abrasive particles 14 that are embedded in a metallic matrix material 15 .
  • Bonding layer 13 is realized as a metallic bonding layer.
  • Metallic bonding layer 13 and metallic matrix material 15 of cover layer 12 are each made of a MCrAlY material.
  • metallic bonding layer 13 is fashioned as a bonding layer applied to the component using high-speed flame spraying (HVOF). Due to the application of bonding layer 13 using high-speed flame spraying, said bonding layer is very strong and has low porosity, so that it adheres well to blade tip 10 .
  • Metallic matrix material 15 of cover layer 12 is deposited galvanically.
  • Abrasive particles 14 are embedded therein that are preferably formed as hard material particles made of cubic boron nitride.
  • metallic matrix material 15 of cover layer 12 , and metallic bonding layer 13 are each made of a MCrAlY material, preferably having 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:
  • chromium 18% by weight chromium, 10% by weight cobalt (Co), 6.5% by weight aluminum (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), remainder nickel.
  • Co cobalt
  • Al aluminum
  • Ta tantalum
  • Re rhenium
  • Hf hafnium
  • Si silicon
  • Y yttrium
  • a rotor blade having a blade tip plating, the plating having a high-speed flame-sprayed bonding layer that creates the bond of blade tip plating 11 to blade tip 10 , and high-speed flame-sprayed bonding layer 13 having high mechanical load capacity, in particular at high operating temperatures.
  • Bonding layer 13 bears cover layer 12 , which is formed of abrasive particles 14 embedded in metallic matrix material 15 , metallic matrix material 15 of cover layer 12 being galvanically deposited.

Abstract

A component, in particular a rotor blade of a gas turbine, having a blade tip plating, the plating including a cover layer that is formed of abrasive particles embedded in a metallic matrix material, and the cover layer being applied onto a surface of the component with the intermediate situation of a metallic bonding layer, wherein the metallic bonding layer is fashioned as a bonding layer applied to the component by high-speed flame spraying, and that the metallic matrix material of the cover layer is galvanically deposited.

Description

  • The present invention relates to a component, in particular a gas turbine component such as a turbine rotor blade, having a plating, in particular a blade tip plating, as recited in the preamble of Claim 1.
  • Turbomachines, such as gas turbines, generally have a plurality of rotating rotor blades and a plurality of stationary guide blades, the rotor blades rotating together with a rotor and the rotor blades and guide blades being enclosed in a stationary housing. In order to improve performance, it is important to optimize all components and subsystems, including what are known as sealing systems.
  • In turbomachines, a particular problem is the maintenance of a minimum gap between the rotating rotor blades and the stationary housing of a high-pressure compressor. This is because high-pressure compressors exhibit the highest absolute temperatures and temperature gradients, which makes it difficult to maintain the gap between the rotating rotor blades and the stationary housing. Inter alia, another reason for this is that compressor rotor blades do not have shrouds as are used in turbine rotor blades.
  • As just mentioned, rotor blades in a compressor do not have shrouds. Therefore, ends or tips of the rotor blades are exposed to direct frictional contact with the stationary housing, in what is called blade rubbing. Such rubbing of the tips of the rotor blades in the housing is caused by manufacturing tolerances during the setting of a minimum radial gap. Because the frictional contact of the tips of the rotor blades wears material away from them, an undesired enlargement of the gap can result around the entire periphery of the housing and rotor. In order to avoid this, it is known from the prior art to plate the ends or tips of the rotor blades with a hard coating or with abrasive particles. Two different types of blade tip platings are known from the prior art, namely, on the one hand, platings of a ceramic material or, on the other hand, platings of abrasive particles. The present invention relates to a plating, in particular a blade tip plating, of a component, in particular a gas turbine rotor blade, with abrasive particles.
  • U.S. Pat. No. 6,194,086 B1 discloses a rotor blade of a gas turbine having a blade tip plating in which the blade tip plating comprises a cover layer that is made of abrasive particles embedded in a metallic matrix material. The cover layer made up of the abrasive particles embedded in the metallic matrix material is applied onto the tip of a rotor blade that is to be plated with the interposition of a metallic bonding layer. The metallic bonding layer is fashioned as a LPPS layer, and is accordingly applied to the component using low-pressure plasma spraying. The disadvantage of such LPPS bonding layers is that in particular at high operating temperatures of up to 1200° C. they have low mechanical adhesion to the blade tip, so that during operation the blade tip plating can flake off.
  • Against this background, the present invention is based on the problem of creating a new type of component having a plating. This problem is solved by a component as recited in Claim 1. According to the present invention, the metallic bonding layer is fashioned as a bonding layer that is applied to the component using high-speed flame spraying, the metallic matrix material of the cover layer being galvanically deposited.
  • According to the present invention, the bonding layer is applied to the component using high-speed flame spraying. In this way, the plating adheres to the component better than is the case given the use of LPPS bonding layers. The blade tip plating of the component accordingly has better mechanical bonding, in particular at high operating temperatures.
  • Preferred further developments of the present invention result from the subclaims and from the following description. Exemplary embodiments of the present invention are explained in more detail on the basis of the drawing, without being limited thereto.
  • FIG. 1 shows a schematized cross-section of a plating applied to a component.
    •
  • The present invention relates to a plated component, in particular a rotor blade of a gas turbine provided with a blade tip plating. The rotor blade of the gas turbine is preferably realized as a high-pressure compressor rotor blade.
  • FIG. 1 shows a highly schematized cross-section of a blade tip 10 of a rotor blade, blade tip 10 of the rotor blade having a blade tip plating 11.
  • Blade tip plating 11 has at least two layers, namely an outer cover layer 12 and an inner bonding layer 13. In the exemplary embodiment shown in FIG. 1, cover layer 12 is applied onto blade tip 10 via bonding layer 13. Additional layers may be present between cover layer 12 and bonding layer 13.
  • According to FIG. 1, cover layer 12 is formed by abrasive particles 14 that are embedded in a metallic matrix material 15. Bonding layer 13 is realized as a metallic bonding layer. Metallic bonding layer 13 and metallic matrix material 15 of cover layer 12 are each made of a MCrAlY material.
  • According to the present invention, metallic bonding layer 13 is fashioned as a bonding layer applied to the component using high-speed flame spraying (HVOF). Due to the application of bonding layer 13 using high-speed flame spraying, said bonding layer is very strong and has low porosity, so that it adheres well to blade tip 10. Metallic matrix material 15 of cover layer 12 is deposited galvanically. Abrasive particles 14 are embedded therein that are preferably formed as hard material particles made of cubic boron nitride.
  • As already mentioned, metallic matrix material 15 of cover layer 12, and metallic bonding layer 13, are each made of a MCrAlY material, preferably having the following composition:
  • 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 rhenium (Re),
    0.5-1% by weight hafnium (Hf),
    0.5-1.5% by weight silicon (Si),
    0.3-1% by weight yttrium (Y),
    remainder nickel.
  • The following composition of the MCrAlY material is particularly preferred:
  • 18% by weight chromium,
    10% by weight cobalt (Co),
    6.5% by weight aluminum (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),
    remainder nickel.
  • According to the present invention, in this way a rotor blade is provided having a blade tip plating, the plating having a high-speed flame-sprayed bonding layer that creates the bond of blade tip plating 11 to blade tip 10, and high-speed flame-sprayed bonding layer 13 having high mechanical load capacity, in particular at high operating temperatures. Bonding layer 13 bears cover layer 12, which is formed of abrasive particles 14 embedded in metallic matrix material 15, metallic matrix material 15 of cover layer 12 being galvanically deposited.

Claims (7)

1. A component, in particular a rotor blade of a gas turbine, comprising: a blade tip plating, said plating including a cover layer that is formed of abrasive particles embedded in a metallic matrix material, and the cover layer being applied onto a surface of the component with the intermediate situation of a metallic bonding layer,
wherein
the metallic bonding layer is fashioned as a bonding layer applied to the component by high-speed flame spraying, and that the metallic matrix material of the cover layer is galvanically deposited.
2. The component as recited in claim 1,
wherein
the metallic matrix material of the cover layer is made of a MCrAlY material,or includes a MCrAlY material.
3. The component as recited in claim 2,
wherein
the metallic matrix material of the cover layer is made of a MCrAlY material and has the following composition:
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 rhenium (Re),
0.5-1% by weight hafnium (Hf),
0.5-1.5% by weight silicon (Si),
0.3-1% by weight yttrium (Y),
the remainder being in nickel.
4. The component as recited in claim 3,
wherein
the MCrAlY material has the following composition:
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% by weight hafnium (Hf),
1% by weight silicon (Si),
0.3% by weight yttrium (Y),
the remainder being nickel.
5. The component as recited in claim 1,
wherein
the metallic bonding layer is made of a MCrAlY material and has the following composition:
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 rhenium (Re),
0.5-1% by weight hafnium (Hf),
0.5-1.5% by weight silicon (Si),
0.3-1% by weight yttrium (Y),
the remainder being nickel.
6. The component as recited in claim 5,
wherein
the MCrAlY material has the following composition:
18% by weight chromium,
10% by weight cobalt (Co),
6.5% by weight aluminum (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),
the remainder being nickel.
7. The component as recited in claim 1,
wherein
the abrasive particles of the cover are made of cubic boron nitride.
US12/296,985 2006-04-11 2007-04-04 Component with a reinforcing plating Abandoned US20090311552A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102006016995.6 2006-04-11
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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US20090311552A1 true US20090311552A1 (en) 2009-12-17

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US (1) US20090311552A1 (en)
EP (1) EP2044231B1 (en)
DE (2) DE102006016995A1 (en)
PL (1) PL2044231T3 (en)
WO (1) WO2007115551A1 (en)

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US9021696B2 (en) 2009-04-23 2015-05-05 MTU Aero Engines AG Method for producing a plating of a vane tip and correspondingly produced vanes and gas turbines
US20160237832A1 (en) * 2015-02-12 2016-08-18 United Technologies Corporation Abrasive blade tip with improved wear at high interaction rate
US10428437B2 (en) 2013-09-18 2019-10-01 MTU Aero Engines AG Wear-resistant coating produced by electrodeposition and process therefor
US10450876B2 (en) 2015-04-15 2019-10-22 United Technologies Corporation Abrasive tip blade manufacture methods
US20200024971A1 (en) * 2018-07-19 2020-01-23 United Technologies Corporation Coating to improve oxidation and corrosion resistance of abrasive tip system
US10544699B2 (en) * 2017-12-19 2020-01-28 Rolls-Royce Corporation System and method for minimizing the turbine blade to vane platform overlap gap
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

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PL2044231T3 (en) 2010-06-30
DE502007002499D1 (en) 2010-02-11

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