WO2009006871A2 - Aube pour turbomachine - Google Patents

Aube pour turbomachine Download PDF

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Publication number
WO2009006871A2
WO2009006871A2 PCT/DE2008/001042 DE2008001042W WO2009006871A2 WO 2009006871 A2 WO2009006871 A2 WO 2009006871A2 DE 2008001042 W DE2008001042 W DE 2008001042W WO 2009006871 A2 WO2009006871 A2 WO 2009006871A2
Authority
WO
WIPO (PCT)
Prior art keywords
wear protection
blade
ductile
protection layer
flow inlet
Prior art date
Application number
PCT/DE2008/001042
Other languages
German (de)
English (en)
Other versions
WO2009006871A3 (fr
Inventor
Bernd Kriegl
Thomas Uihlein
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
Publication of WO2009006871A2 publication Critical patent/WO2009006871A2/fr
Publication of WO2009006871A3 publication Critical patent/WO2009006871A3/fr

Links

Classifications

    • 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
    • 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
    • C23C28/04—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 of inorganic non-metallic material
    • C23C28/044—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 of inorganic non-metallic material coatings specially adapted for cutting tools or wear applications
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/20—Oxide or non-oxide ceramics
    • F05D2300/22—Non-oxide ceramics
    • F05D2300/226—Carbides
    • F05D2300/2262—Carbides of titanium, e.g. TiC
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a turbomachinery blade, in particular a gas turbine blade.
  • Turbomachinery blades such as. Gas turbine blades, have a blade root and an airfoil, the airfoil having a flow inlet edge and a flow outlet edge, and extending between the flow inlet edge and the flow outlet edge of the airfoil of a suction side and a pressure side thereof.
  • turbomachinery blades namely both stator vanes and rotor-side blades
  • turbomachinery blades may be damaged by erosion, bird strike or even hail.
  • wear protection systems are preferably formed as multilayer coating systems having at least one relatively hard, ceramic layer and at least one relatively soft, metallic layer alternately applied to the airfoil.
  • the present invention is based on the problem to create a novel turbomachinery blade, in particular a novel gas turbine blade.
  • This problem is solved by a turbomachine blade according to claim 1.
  • the blade leaf is coated with a ductile wear protection layer at least in the area of the flow inlet edge, the ductile wear protection layer having ceramic hard particles embedded in a metal matrix.
  • the invention proposes to coat the blade of a turbomachine, at least in the region of the flow inlet edge, with a ductile, not purely ceramic and not purely metallic wear protection layer, wherein the ductile wear protection layer comprises ceramic hard particles embedded in a metal matrix.
  • a ductile wear protection layer does not tend to crack and thus not flake off at an angle of incidence of particles by about 90 °. In this way, the flow inlet edge of a turbomachine can be effectively protected from erosion, bird strike or even hailstorm wear.
  • turbomachine blade is to be understood broadly and refers in particular to turbomachinery blades in the narrow or intrinsic sense or to flow profiles, such as, for example, turbomachinery blades.
  • Fig. 1 is a schematic representation of a turbomachinery blade.
  • Fig. 1 shows a schematic representation of a turbomachinery blade 10, in particular a gas turbine blade.
  • the turbomachine blade 10 is preferably a stator vane or a rotor-side blade of a gas turbine designed as an aircraft engine.
  • the turbomachine blade 10 comprises an airfoil 11 and a blade root 12, the airfoil 11 having a flow inlet edge 13 and a flow outlet flange 12.
  • edge 14 includes. Between the flow inlet edge 13 and the flow outlet edge 14 of the airfoil 11, a suction side and a pressure width of the airfoil extends.
  • the blade 11 is coated with a ductile wear protection layer at least in the area of the flow edge 13, the ductile wear protection layer having ceramic hard particles embedded in a metal matrix. Accordingly, the ductile wear protection layer is designed neither as a purely ceramic layer nor as a purely metallic layer; rather, metallic and ceramic phases are mixed next to one another in the ductile wear protection layer.
  • the ductile wear protection layer preferably has carbide particles embedded in a metal matrix, in particular carbide particles of titanium carbide or the like.
  • the ductile wear protection layer applied to the blade 11 at least in the region of the flow inlet edge 13 does not tend to crack or flake off at impact angles of foreign particles of the order of magnitude of approximately 90 °. Therefore, it is particularly suitable for protecting the flow inlet edge 13 of the airfoil 11 from erosion, bird strike or hailstorm wear.
  • the airfoil 11 is additionally coated with a hard wear protection system, this wear protection system preferably being designed as a multilayer layer system comprising at least one relatively hard, purely ceramic layer has at least one relatively soft, purely metallic layer. These layers are then alternately applied to the airfoil 11 to form the multilayer coating system.
  • the airfoil 11 is coated with the ductile wear protection layer and the hard wear protection system such that the airfoil 11 is completely coated with the hard wear protection system, wherein at least in the region of the flow inlet edge 13, the hard wear protection system is coated with the ductile wear protection layer.
  • the ductile wear protection layer is preferably applied exclusively to the flow inlet edge 13 and, if appropriate, to sections of the suction side and the pressure side of the blade leaf 11 which adjoin directly to the flow inlet edge 13.
  • the airfoil 11 is coated with the ductile wear protection layer and the hard wear protection system in such a way that the ductile wear protection layer is overcoated with the hard wear protection system at least in the area of the flow inlet edge 13.
  • the hard wear protection system in the region of the flow inlet edge 13 is then rapidly removed during operation, in which case the flow inlet edge 13 is protected against wear by erosion, hail or bird strike by the ductile wear protection layer.
  • the ductile wear protection layer is preferably applied exclusively in the region of the flow inlet edge 13 and, if appropriate, portions of the suction side and pressure side of the blade 11 adjoining directly to the flow inlet edge 13.
  • the airfoil 11 prefferably be coated with the hard wear protection system and the ductile wear protection layer, such that the ductile wear protection layer is applied exclusively to the flow inlet edge 13 and, if appropriate, immediately adjacent to the flow inlet edge 13 sections of the suction side and pressure side the hard wear protection system tem to the ductile wear protection layer connects and therefore the blade is coated exclusively in such areas with the hard wear protection system in which it is not coated with the ductile wear protection layer.
  • an airfoil 11 of a turbomachine blade 10 it is possible to optimally protect all areas of an airfoil 11 of a turbomachine blade 10 from erosion, hail or bird strike wear.
  • the blade 11 In the region of the flow inlet edge 13, the blade 11 is coated with the ductile wear protection layer.
  • the airfoil 11 is protected from wear by a hard wear protection system.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une aube (10) pour turbomachine, en particulier une aube pour turbine à gaz, qui présente une feuille d'aube (11) dotée d'un bord d'attaque (13) de l'écoulement et d'un bord de fuite (14) de l'écoulement, un côté d'aspiration et un côté sous pression de la feuille d'aube s'étendant entre le bord d'attaque de l'écoulement et le bord de fuite de l'écoulement. Selon l'invention, au moins dans la zone occupée par le bord d'attaque (13) de l'écoulement, la feuille d'aube (11) est revêtue d'une couche ductile de protection contre l'usure, la couche ductile de protection contre l'usure présentant des particules céramiques dures incorporées dans une matrice métallique.
PCT/DE2008/001042 2007-07-09 2008-06-21 Aube pour turbomachine WO2009006871A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007031932.2 2007-07-09
DE102007031932A DE102007031932A1 (de) 2007-07-09 2007-07-09 Turbomaschinenschaufel

Publications (2)

Publication Number Publication Date
WO2009006871A2 true WO2009006871A2 (fr) 2009-01-15
WO2009006871A3 WO2009006871A3 (fr) 2009-03-26

Family

ID=40121341

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2008/001042 WO2009006871A2 (fr) 2007-07-09 2008-06-21 Aube pour turbomachine

Country Status (2)

Country Link
DE (1) DE102007031932A1 (fr)
WO (1) WO2009006871A2 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8871297B2 (en) 2010-09-30 2014-10-28 Barry Barnett Method of applying a nanocrystalline coating to a gas turbine engine component
US9429029B2 (en) 2010-09-30 2016-08-30 Pratt & Whitney Canada Corp. Gas turbine blade and method of protecting same
US9427835B2 (en) 2012-02-29 2016-08-30 Pratt & Whitney Canada Corp. Nano-metal coated vane component for gas turbine engines and method of manufacturing same
US9587645B2 (en) 2010-09-30 2017-03-07 Pratt & Whitney Canada Corp. Airfoil blade

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008056578B4 (de) * 2008-11-10 2017-11-09 Airbus Defence and Space GmbH Verfahren zur Herstellung einer Erosionsschutzschicht für aerodynamische Komponenten und Strukturen
DE102008056741A1 (de) * 2008-11-11 2010-05-12 Mtu Aero Engines Gmbh Verschleissschutzschicht für Tial
DE102012200491B4 (de) * 2012-01-13 2015-05-28 Lufthansa Technik Ag Gasturbinenschaufel für ein Flugzeugtriebwerk und Verfahren zur Beschichtung einer Gasturbinenschaufel

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0366289A1 (fr) * 1988-10-11 1990-05-02 Midwest Research Technologies, Inc. Revêtements multicouches résistants à l'usure
EP0589072A1 (fr) * 1992-09-21 1994-03-30 Asea Brown Boveri Ag Turbocompresseur pour fonctionnement avec du carburant lourd
US5486096A (en) * 1994-06-30 1996-01-23 United Technologies Corporation Erosion resistant surface protection
DE4439950A1 (de) * 1994-11-09 1996-05-15 Mtu Muenchen Gmbh Metallisches Bauteil oder Substrat mit einer Verbundbeschichtung und Herstellungsverfahren
EP0844368A2 (fr) * 1996-11-26 1998-05-27 United Technologies Corporation Revêtissement partiel des aubes de turbine à gaz pour améliorer la résistance à la fatigue
EP0845547A1 (fr) * 1996-11-30 1998-06-03 ROLLS-ROYCE plc Revêtement resistant à haute température pour pièce en superalliage et procédé de sa fabrication
EP1541810A1 (fr) * 2003-12-11 2005-06-15 Siemens Aktiengesellschaft Utilisation de revêtement de barrière thermique pour un élément d'une turbine à vapeur et une turbine à vapeur
US20060275626A1 (en) * 2005-04-15 2006-12-07 Snecma Part for protecting the leading edge of a blade
US20070099027A1 (en) * 2005-10-28 2007-05-03 Anand Krishnamurthy Wear resistant coatings
WO2008116757A2 (fr) * 2007-03-27 2008-10-02 Alstom Technology Ltd Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0366289A1 (fr) * 1988-10-11 1990-05-02 Midwest Research Technologies, Inc. Revêtements multicouches résistants à l'usure
EP0589072A1 (fr) * 1992-09-21 1994-03-30 Asea Brown Boveri Ag Turbocompresseur pour fonctionnement avec du carburant lourd
US5486096A (en) * 1994-06-30 1996-01-23 United Technologies Corporation Erosion resistant surface protection
DE4439950A1 (de) * 1994-11-09 1996-05-15 Mtu Muenchen Gmbh Metallisches Bauteil oder Substrat mit einer Verbundbeschichtung und Herstellungsverfahren
EP0844368A2 (fr) * 1996-11-26 1998-05-27 United Technologies Corporation Revêtissement partiel des aubes de turbine à gaz pour améliorer la résistance à la fatigue
EP0845547A1 (fr) * 1996-11-30 1998-06-03 ROLLS-ROYCE plc Revêtement resistant à haute température pour pièce en superalliage et procédé de sa fabrication
EP1541810A1 (fr) * 2003-12-11 2005-06-15 Siemens Aktiengesellschaft Utilisation de revêtement de barrière thermique pour un élément d'une turbine à vapeur et une turbine à vapeur
US20060275626A1 (en) * 2005-04-15 2006-12-07 Snecma Part for protecting the leading edge of a blade
US20070099027A1 (en) * 2005-10-28 2007-05-03 Anand Krishnamurthy Wear resistant coatings
WO2008116757A2 (fr) * 2007-03-27 2008-10-02 Alstom Technology Ltd Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8871297B2 (en) 2010-09-30 2014-10-28 Barry Barnett Method of applying a nanocrystalline coating to a gas turbine engine component
US9429029B2 (en) 2010-09-30 2016-08-30 Pratt & Whitney Canada Corp. Gas turbine blade and method of protecting same
US9587645B2 (en) 2010-09-30 2017-03-07 Pratt & Whitney Canada Corp. Airfoil blade
US10364823B2 (en) 2010-09-30 2019-07-30 Pratt & Whitney Canada Corp. Airfoil blade
US10369593B2 (en) 2010-09-30 2019-08-06 Pratt & Whitney Canada Corp. Method of applying a nanocrystalline coating to a gas turbine engine component
US9427835B2 (en) 2012-02-29 2016-08-30 Pratt & Whitney Canada Corp. Nano-metal coated vane component for gas turbine engines and method of manufacturing same

Also Published As

Publication number Publication date
WO2009006871A3 (fr) 2009-03-26
DE102007031932A1 (de) 2009-01-15

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