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EP2044231B1 - Composant dote d'un blindage - Google Patents

Composant dote d'un blindage Download PDF

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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.)
Not-in-force
Application number
EP07722169A
Other languages
German (de)
English (en)
Other versions
EP2044231A1 (fr
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/pl
Publication of EP2044231A1 publication Critical patent/EP2044231A1/fr
Application granted granted Critical
Publication of EP2044231B1 publication Critical patent/EP2044231B1/fr
Not-in-force 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 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.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Organic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Plasma & Fusion (AREA)
  • Physics & Mathematics (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrochemistry (AREA)
  • Composite Materials (AREA)
  • Inorganic Chemistry (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)

Claims (5)

  1. Composant, en particulier aube d'une turbine à gaz, comportant une armature, en particulier une armature de pointe de l'aube, l'armature comportant une couche de recouvrement qui est formée de particules abrasives déposées dans un matériau à matrice métallique, la couche de recouvrement étant déposée sur une surface du composant en intercalant une couche d'adhésion métallique, caractérisé en ce que la couche d'adhésion métallique (13) est réalisée comme une couche d'adhésion appliquée sur le composant par le biais d'une métallisation à la flamme ultra-rapide, et en ce que le matériau à matrice (15) de la couche de recouvrement (12) est appliqué par électrodéposition galvanique, le matériau à matrice (15) métallique de la couche de recouvrement (12) étant formé à partir d'un élément MCrAlY et présentant la composition suivant
    14 - 22 % en poids de chrome (Cr),
    6 - 14 % en poids de cobalt (Co),
    4 - 9 % en poids d'aluminium (Al),
    5 - 8 % en poids de tantale (Ta),
    1 - 3 % en poids de rhénium (Re),
    0,5 - 1 % en poids d'hafnium (Hf),
    0,5 - 1,5 % en poids de silicium (Si),
    0,3 - 1 % en poids d'yttrium (Y), et
    le reste étant du nickel.
  2. Composant selon la revendication 1, caractérisé en ce que l'élément MCrAlY présente la composition suivante :
    18 % en poids de chrome (Cr),
    10 % en poids de cobalt (Co),
    6,5 % en poids d'aluminium (Al),
    6 % en poids de tantale (Ta),
    2 % en poids de rhénium (Re),
    0,5 % en poids d'hafnium (Hf),
    1 % en poids de silicium (Si),
    0,3 % en poids d'yttrium (Y), et
    le reste étant du nickel.
  3. Composant selon l'une quelconque ou plusieurs des revendications 1 à 2, caractérisé en ce que la couche d'adhésion métallique (13) est formée à partir de l'élément MCrAlY et présente la composition suivante :
    14 - 22 % en poids de chrome (Cr),
    6 - 14 % en poids de cobalt (Co),
    4 - 9 % en poids d'aluminium (Al),
    5 - 8 % en poids de tantale (Ta),
    1 - 3 % en poids de rhénium (Re),
    0,5 - 1 % en poids d'hafnium (Hf),
    0,5 - 1,5 % en poids de silicium (Si),
    0,3 - 1 % en poids d'yttrium (Y), et
    le reste étant du nickel.
  4. Composant selon la revendication 3, caractérisé en ce que l'élément MCrAlY présente la composition suivante :
    18 % en poids de chrome (Cr),
    10 % en poids de cobalt (Co),
    6,5 % en poids d'aluminium (Al),
    6 % en poids de tantale (Ta),
    2 % en poids de rhénium (Re),
    0,5 % en poids d'hafnium (Hf),
    1 % en poids de silicium (Si),
    0,3 % en poids d'yttrium (Y), et
    le reste étant du nickel.
  5. Composant selon l'une quelconque ou plusieurs des revendications 1 à 4, caractérisé en ce que les particules abrasives (14) de la couche de recouvrement (12) sont formées à partir de nitrure cubique de bore.
EP07722169A 2006-04-11 2007-04-04 Composant dote d'un blindage Not-in-force EP2044231B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL07722169T PL2044231T3 (pl) 2006-04-11 2007-04-04 Element konstrukcyjny z pancerzem

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006016995A DE102006016995A1 (de) 2006-04-11 2006-04-11 Bauteil mit einer Panzerung
PCT/DE2007/000611 WO2007115551A1 (fr) 2006-04-11 2007-04-04 Composant dote d'un blindage

Publications (2)

Publication Number Publication Date
EP2044231A1 EP2044231A1 (fr) 2009-04-08
EP2044231B1 true EP2044231B1 (fr) 2009-12-30

Family

ID=38180702

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07722169A Not-in-force EP2044231B1 (fr) 2006-04-11 2007-04-04 Composant dote d'un blindage

Country Status (5)

Country Link
US (1) US20090311552A1 (fr)
EP (1) EP2044231B1 (fr)
DE (2) DE102006016995A1 (fr)
PL (1) PL2044231T3 (fr)
WO (1) WO2007115551A1 (fr)

Families Citing this family (16)

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DE102008003100A1 (de) * 2008-01-03 2009-07-16 Mtu Aero Engines Gmbh Lötbeschichtung, Verfahren zum Beschichten eines Bauteils, Bauteil und Klebeband mit einer Lötbeschichtung
DE102008056741A1 (de) * 2008-11-11 2010-05-12 Mtu Aero Engines Gmbh Verschleissschutzschicht für Tial
DE102009018685A1 (de) 2009-04-23 2010-10-28 Mtu Aero Engines Gmbh Verfahren zur Herstellung einer Panzerung einer Schaufelspitze sowie entsprechend hergestellte Schaufeln und Gasturbinen
DE102009031313B4 (de) 2009-06-30 2018-07-05 MTU Aero Engines AG Beschichtung und Verfahren zum Beschichten eines Bauteils
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 (de) * 2013-09-18 2015-04-02 MTU Aero Engines AG Galvanisch hergestellte Verschleißschutzbeschichtung und Verfahren hierfür
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
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
US11536151B2 (en) 2020-04-24 2022-12-27 Raytheon Technologies Corporation Process and material configuration for making hot corrosion resistant HPC abrasive blade tips
CN115637400B (zh) * 2022-11-18 2023-03-21 矿冶科技集团有限公司 一种具有高结合力耐磨防护涂层的钛合金叶片及其制备方法
WO2025221991A1 (fr) * 2024-04-18 2025-10-23 Rtx Corporation Revêtement de pointe abrasive

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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 (de) * 1999-02-12 2000-08-17 Erwin Huehne Hochgeschwindigkeitsflammspritzkanone
NL1014924C2 (nl) * 1999-07-30 2001-02-01 Chromalloy Holland B V Beperking van de luchtweerstand voor componenten van een gasturbine motor.
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

Also Published As

Publication number Publication date
DE502007002499D1 (de) 2010-02-11
WO2007115551A1 (fr) 2007-10-18
DE102006016995A1 (de) 2007-10-18
US20090311552A1 (en) 2009-12-17
EP2044231A1 (fr) 2009-04-08
PL2044231T3 (pl) 2010-06-30

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