WO2010102609A1 - Procédé de fabrication d'un revêtement abrasif et pièce pour une turbomachine. - Google Patents

Procédé de fabrication d'un revêtement abrasif et pièce pour une turbomachine. Download PDF

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Publication number
WO2010102609A1
WO2010102609A1 PCT/DE2010/000255 DE2010000255W WO2010102609A1 WO 2010102609 A1 WO2010102609 A1 WO 2010102609A1 DE 2010000255 W DE2010000255 W DE 2010000255W WO 2010102609 A1 WO2010102609 A1 WO 2010102609A1
Authority
WO
WIPO (PCT)
Prior art keywords
component
turbomachine
coating
producing
abrasive
Prior art date
Application number
PCT/DE2010/000255
Other languages
German (de)
English (en)
Inventor
André Werner
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 WO2010102609A1 publication Critical patent/WO2010102609A1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/026—Anodisation with spark discharge
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/04—Anodisation of aluminium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/26—Anodisation of refractory metals or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D11/00—Electrolytic coating by surface reaction, i.e. forming conversion layers
    • C25D11/02—Anodisation
    • C25D11/30—Anodisation of magnesium or alloys based thereon
    • 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
    • F05D2300/21—Oxide ceramics

Definitions

  • the invention relates to a method for producing an abrasive coating on a light metal surface of a component of a turbomachine, in particular a compressor or turbine blade.
  • the invention further relates to a component for a turbomachine, in particular a compressor or turbine blade.
  • shear tip blade seals are a particular form of solution to such sealing problems.
  • the blade tips are oversized with abrasive cladding. When entering the turbine, the blade tips dig into soft inlet linings of the housing, so that it no longer comes to a direct contact of the turbine blades with the housing.
  • the blade tips are provided with hard tarnish.
  • the blade tips are provided with a shroud, which serves the relative fixation and the bias in the engine. Due to the frequent contact of adjacent blades on the shroud this wears particularly strong. To avoid this, the respective contact surfaces of the shroud are armored with a hard layer.
  • an impeller of a gas turbine wherein between the impeller and a housing, a sealing gap is provided which has labyrinth-like structural elements.
  • the surface areas of the impeller are composite educated.
  • the composite comprises a metallic matrix with a structured ceramic embedded therein. Parts of the ceramic phase emerge on the surface as elevations from the composite and thereby form the labyrinth-like structural elements.
  • EP 0 702 130 A2 shows a metallic engine component with a tarpaulin covering of a thermally sprayed ceramic layer, which is incorporated into an inlet lining.
  • the ceramic layer is profiled in such a way that it has edges capable of being cut, free spaces being arranged between the edges which absorb and clear out the wear of the inlet lining.
  • the object of the invention is to provide a cost-effective alternative for producing an abrasive coating of a turbomachinery component with improved adhesive properties.
  • the inventive method for producing an abrasive coating on a light metal surface of a component of a turbomachine, in particular a compressor or turbine blade is characterized in that the coating is formed by a conversion of the surface into an oxide ceramic. Since, in contrast to the methods commonly used in engine technology, the coating according to the invention is not produced by deposition or deposition of particles but by transformation of the component surface, a coating produced according to the invention has a significantly better adhesion. Depending on the component and production concept, cost savings compared to conventional methods are possible. Application potential exists mainly for components that are complete or whose surfaces are made of titanium alloys (including titanium aluminides).
  • the surface is converted by so-called plasma-electrolytic oxidation.
  • This method of converting a light metal surface which is also referred to in the literature as PEO (plasma electrolytic oxidation), plasma chemical oxidation, anodic oxidation with spark discharge (ANOF), dielectric breakdown process, micro arc oxidation (MAO) or anodic spark deposition (ASO) , is generally z.
  • PEO plasma electrolytic oxidation
  • ANOF anodic oxidation with spark discharge
  • MAO micro arc oxidation
  • ASO anodic spark deposition
  • the Protective layer in both directions, ie the layer forms partly above and partly below the original surface.
  • the pronounced hardness of the oxide-ceramic layer promotes damage-free shrinkage when rubbed against turbomachinery.
  • a further advantage of the coating produced in this way is that no interactions with the base material of the component surface are to be feared, especially at relatively high temperatures, since the coating is indeed a species-specific oxide.
  • the process of plasma electrolytic oxidation is suitable for a number of light metal alloys, eg. For alloys based on aluminum, magnesium or titanium, including titanium aluminides.
  • the invention also relates to a component for a turbomachine, in particular a compressor or turbine blade, which is characterized in that a light metal surface of the component has an abrasive oxide ceramic coating.
  • the oxide ceramic coating is an armor or tarnish.
  • FIG. 1 shows a rotor blade and a housing part of a turbomachine
  • Figure 2 shows a vane and a rotor of a turbomachine
  • Figures 3a, 3b in each case a compressor blade with fin seal.
  • a rotor blade 10 has at its tip an armor 12 produced according to the invention, which runs into an inlet lining 14 of a housing 16.
  • FIG. 2 a region of a rotor 18, which lies opposite a housing-fixed guide blade 20, is protected by a starting lining 22 produced according to the invention.
  • FIGS. 3 a and 3 b the extensions 24 of a cover strip 26 formed in the manner of a knife edge, which run into a housing-mounted inlet lining 28, are provided with an abrasive coating 30 produced according to the invention.
  • the component which is either complete or whose surface to be coated consists of a light metal alloy, is immersed in an acidic or basic electrolyte bath with a specific aqueous electrolyte.
  • the component forms the anode, the bath container usually the cathode.
  • the voltage applied to the device is significantly higher than that of anodization (anodization), typically greater than 200 V. This locally exceeds the dielectric strength of the growing oxide layer, causing electrostatic discharges.
  • the discharges form locally limited plasma reactors with high temperatures and high pressures that modify the growing oxide.
  • the modification may include melting, flowing, re-solidification, sintering, and densification of the growing oxide.
  • One of the main effects is the formation of an oxide ceramic, which z. For example, in the case of an aluminum surface, the conversion of amorphous alumina into harder crystalline forms such as corundum (Q-Al 2 O 3 ) is based.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Electrochemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Mechanical Engineering (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)

Abstract

L'invention concerne un procédé de fabrication d'un revêtement abrasif (12; 22; 30) sur une surface en métal léger d'une pièce (10; 18; 29) d'une turbomachine, notamment d'une aube de compresseur ou de turbine, qui est caractérisé en ce que le revêtement (12; 22; 30) est formé par une transformation de la surface en céramique d'oxyde. L'invention concerne également une pièce (10; 18; 26) pour une turbomachine, notamment une aube de compresseur ou de turbine, qui est caractérisée en ce que la surface de métal léger de la pièce (10; 18; 26) comporte un revêtement abrasif (12; 22; 30) en céramique d'oxyde.
PCT/DE2010/000255 2009-03-12 2010-03-10 Procédé de fabrication d'un revêtement abrasif et pièce pour une turbomachine. WO2010102609A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009012945.6 2009-03-12
DE200910012945 DE102009012945A1 (de) 2009-03-12 2009-03-12 Verfahren zur Herstellung einer abrasiven Beschichtung und Bauteil für eine Turbomaschine

Publications (1)

Publication Number Publication Date
WO2010102609A1 true WO2010102609A1 (fr) 2010-09-16

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Country Status (2)

Country Link
DE (1) DE102009012945A1 (fr)
WO (1) WO2010102609A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2996858A1 (fr) * 2012-10-17 2014-04-18 Figeac Aero Procede de fabrication de pieces de structure aeronautique et dispositif permettant de le mettre en oeuvre
WO2015158964A1 (fr) * 2014-04-15 2015-10-22 Figeac Aero Procédé de fabrication de pièces de structure aéronautique et dispositif permettant de le mettre en oeuvre
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2492443A1 (fr) * 2011-02-22 2012-08-29 Siemens Aktiengesellschaft Procédé de fabrication d'une couche de protection pour une aube directrice
EP2784268A1 (fr) 2013-03-28 2014-10-01 MTU Aero Engines GmbH Etanchéité extérieur d'une aube de turbine comprenant un revêtement ceramique sur le stator et le rotor respectivement
DE112015005466A5 (de) * 2014-12-04 2017-08-31 Meotec GmbH & Co. KG Bauteil einer Turboeinrichtung, Brennkraftmaschine mit einer Turboeinrichtung und Verfahren zum Herstellen eines Turboeinrichtungsbauteils
DE102015212330A1 (de) * 2015-07-01 2017-01-19 Bosch Mahle Turbo Systems Gmbh & Co. Kg Verfahren zum Beschichten eines Laufrades, insbesondere eines Turbinenrads und/oder Verdichterrads, eines Abgasturboladers

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CH314013A (de) * 1952-10-15 1956-05-31 Hard Aluminium Surfaces Limite Verfahren zur Erzeugung von harten Schichten auf Aluminium und Aluminiumlegierungen durch anodische Oxydation
US5487825A (en) * 1991-11-27 1996-01-30 Electro Chemical Engineering Gmbh Method of producing articles of aluminum, magnesium or titanium with an oxide ceramic layer filled with fluorine polymers
DE19721730A1 (de) * 1997-05-24 1998-11-26 Anatoli J Prof Dr Vassiliev Verfahren zum Erzeugen harter Oxidschichten an der Oberfläche eines Substrats auf Basis von Leichtmetallen
US6264817B1 (en) * 1997-12-30 2001-07-24 R-Amtech International, Inc. Method for microplasma oxidation of valve metals and their alloys
EP1541717A2 (fr) * 2003-11-22 2005-06-15 DaimlerChrysler AG Procédé de fabrication de composants en métaux légers recouverts qui sont disposés dans un courant de fluide turbulent
US6919012B1 (en) * 2003-03-25 2005-07-19 Olimex Group, Inc. Method of making a composite article comprising a ceramic coating
DE202008010896U1 (de) * 2008-08-05 2008-10-23 AHC Oberflächentechnik GmbH Werkstoff, insbesondere Bauteile, mit verbesserten Verschleißschutzschichten

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EP0661415A1 (fr) 1993-12-17 1995-07-05 Sulzer Innotec Ag Joint d'étanchéité entre un carter et un corps rotatif
DE4432998C1 (de) 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
DE19516815A1 (de) * 1995-05-08 1996-11-14 Electro Chem Eng Gmbh Keramisierter Leichtmetallkolben für Verbrennungsmotoren
AU1895399A (en) 1998-07-23 2000-02-14 Jury Dmitrievich Kalashnikov Internal combustion engine, part thereof comprising a surface coating, and method and devices for producing said part
US6197178B1 (en) 1999-04-02 2001-03-06 Microplasmic Corporation Method for forming ceramic coatings by micro-arc oxidation of reactive metals
JP4182002B2 (ja) * 2002-03-27 2008-11-19 アイル・コート・リミテッド 金属および合金にセラミック被膜を形成するプロセスと装置、およびこのプロセスによって生成される被膜
DE102005040648A1 (de) * 2005-08-27 2007-03-01 Leybold Vacuum Gmbh Beschichtete Gegenstände
EP1967615A1 (fr) * 2007-03-07 2008-09-10 Siemens Aktiengesellschaft Procédé destiné à l'application d'une couche d'isolation thermique et pièce de turbine dotée d'une couche d'isolation thermique
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Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH314013A (de) * 1952-10-15 1956-05-31 Hard Aluminium Surfaces Limite Verfahren zur Erzeugung von harten Schichten auf Aluminium und Aluminiumlegierungen durch anodische Oxydation
US5487825A (en) * 1991-11-27 1996-01-30 Electro Chemical Engineering Gmbh Method of producing articles of aluminum, magnesium or titanium with an oxide ceramic layer filled with fluorine polymers
DE19721730A1 (de) * 1997-05-24 1998-11-26 Anatoli J Prof Dr Vassiliev Verfahren zum Erzeugen harter Oxidschichten an der Oberfläche eines Substrats auf Basis von Leichtmetallen
US6264817B1 (en) * 1997-12-30 2001-07-24 R-Amtech International, Inc. Method for microplasma oxidation of valve metals and their alloys
US6919012B1 (en) * 2003-03-25 2005-07-19 Olimex Group, Inc. Method of making a composite article comprising a ceramic coating
EP1541717A2 (fr) * 2003-11-22 2005-06-15 DaimlerChrysler AG Procédé de fabrication de composants en métaux légers recouverts qui sont disposés dans un courant de fluide turbulent
DE202008010896U1 (de) * 2008-08-05 2008-10-23 AHC Oberflächentechnik GmbH Werkstoff, insbesondere Bauteile, mit verbesserten Verschleißschutzschichten

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2996858A1 (fr) * 2012-10-17 2014-04-18 Figeac Aero Procede de fabrication de pieces de structure aeronautique et dispositif permettant de le mettre en oeuvre
US9598973B2 (en) 2012-11-28 2017-03-21 General Electric Company Seal systems for use in turbomachines and methods of fabricating the same
WO2015158964A1 (fr) * 2014-04-15 2015-10-22 Figeac Aero Procédé de fabrication de pièces de structure aéronautique et dispositif permettant de le mettre en oeuvre

Also Published As

Publication number Publication date
DE102009012945A1 (de) 2010-09-16

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