EP2331723A1 - Aube d'une turbine à gaz, et procédé de revêtement d'une aube d'une turbine à gaz - Google Patents

Aube d'une turbine à gaz, et procédé de revêtement d'une aube d'une turbine à gaz

Info

Publication number
EP2331723A1
EP2331723A1 EP09776056A EP09776056A EP2331723A1 EP 2331723 A1 EP2331723 A1 EP 2331723A1 EP 09776056 A EP09776056 A EP 09776056A EP 09776056 A EP09776056 A EP 09776056A EP 2331723 A1 EP2331723 A1 EP 2331723A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
blade
coating
chromium
particles
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.)
Granted
Application number
EP09776056A
Other languages
German (de)
English (en)
Other versions
EP2331723B1 (fr
Inventor
Heinrich Walter
Horst Pillhöfer
Michael Strasser
Karl-Heinz Manier
Max Morant
Richard Lange
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
Publication of EP2331723A1 publication Critical patent/EP2331723A1/fr
Application granted granted Critical
Publication of EP2331723B1 publication Critical patent/EP2331723B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/28—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes
    • C23C10/30—Solid state diffusion of only metal elements or silicon into metallic material surfaces using solids, e.g. powders, pastes using a layer of powder or paste on the surface
    • C23C10/32—Chromising
    • 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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F05D2260/00—Function
    • F05D2260/95—Preventing corrosion
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to a turbine blade of a gas turbine according to the preamble of claim 1. Furthermore, the invention relates to a method for coating a turbine blade of a gas turbine according to the preamble of patent claim 9.
  • a turbine blade of a gas turbine and a method for coating a turbine blade of a gas turbine is known, the turbine blade having an airfoil, a blade root and a platform positioned between the airfoil and the blade root.
  • a wear protection coating namely a corrosion-resistant protective coating, the wear protection coating being an MCrAlY coating.
  • Coating coating is. This coating coating has a chromium content of between 10% and 40% by weight.
  • the present invention is based on the problem of creating a novel turbine blade of a gas turbine and a novel method for coating a turbine blade.
  • the anticorrosive coating is a diffusion coating having a chromium content in the surface area of more than 30% by weight.
  • the inventive method for coating a turbine blade comprises at least the following steps: a) provision of a turbine blade; b) projecting at least one lacquer layer onto at least one region of the turbine blade, the lacquer comprising chromium particles and / or chromium alloy particles, halides and binders; c) drying the applied paint at a temperature between 5O 0 C and 600 ° C with decomposition of the binder; d) subsequent reaction bonding at a temperature between 900 0 C and 1160 0 C.
  • the life of turbine blades can be increased and an effective protection against hot gas corrosion or sulfidation can be realized, wherein this protection against the base material of the turbine blade is increased by a factor of 6. Even with a complex contouring of the underside of the platform and the transition region between the underside of the platform and the blade root, a good coating can be ensured.
  • Fig. 1 is a schematic view of a turbine blade of a gas turbine.
  • FIG. 1 shows a schematic illustration of a turbine blade 10 of a gas turbine designed as a rotor blade, wherein the turbine blade 10 comprises an airfoil 11, a blade root 12 and a platform 13 positioned between the airfoil 11 and the blade root 12.
  • the turbine blade 10 is coated on an underside 14 of the platform and / or on a transition region 15 between the underside 14 of the platform 13 and the blade root 12 with a corrosion protection coating.
  • the anticorrosive coating is a diffusion coating having a chromium content in the surface area of more than 30% by weight.
  • the anticorrosive coating is formed as a graded, ductile Inchromier Anlagen whose chromium content in the surface region is preferably between 40 wt .-% and 95 wt .-%.
  • An ⁇ -chromium phase fraction having a chromium content of more than 30% by weight of the corrosion protection coating is between 5% by weight and 50% by weight.
  • the remainder of the chromium content of the corrosion protection coating is formed by other chromium phases and by chromium dissolved in the mixed crystal of the base material.
  • the ⁇ -chromium phase content of the chromium content of the anticorrosive coating has a Vickers hardness of less than 800.
  • the total layer thickness of the anticorrosive coating is between 5 ⁇ m and 120 ⁇ m, preferably between 15 ⁇ m and 50 ⁇ m.
  • At least one coating layer is applied to the underside 14 of the platform 13 and / or the transition region 15 between the underside 14 of the platform 13 and the blade root 12, wherein the paint chromium particles and / or chromium alloy particles, halides and binder.
  • the particle size of the chromium particles and / or chromium alloy particles is in particular up to 20 microns.
  • the halides of the paint are preferably metal chloride particles, in particular CrCb particles and / or CrCb particles.
  • the binder of the paint is preferably an acrylic or glycol based or polyvinyl base.
  • the paint preferably has the following composition:
  • binder 25 to 95% by weight of binder; 0, 1 to 10% by weight CrC12 particles and / or CrC13 particles;
  • an acrylic acid ester or methacrylic acid ester, a methyl cellulose compound, a polysaccharide, a polyvinyl alcohol, a polyvinyl ether, a polyvinyl acetate, a polyvinylpyrrolidone or a colloidal silica mixture can be used to provide an aqueous dispersion. It is also possible to provide a nonaqueous dispersion as a lacquer.
  • At least one lacquer layer of this lacquer is applied to the underside 14 of the platform 13 and / or the transition region 15 between the platform 13 and the shower foot 12, preferably several lacquer layers are applied to these regions of the turbine blade, each lacquer layer having one Layer thickness between 2 microns and 50 microns is applied. It is preferably applied between one and ten layers of paint, in particular between three and six layers of paint.
  • a reaction connecting the chromium particles and / or chromium alloy particles with molten chrome chloride particles takes place at a temperature between 900 0 C and 1160 0 C, the reaction bonding for a period between 15 minutes and is carried out for 15 hours.
  • Subsequent to the reaction bonding is preferably a diffusion annealing of the formed pure chromium layer at a temperature between 95O 0 C and 1200 0 C for diffusing the chromium in the surface of the previously coated with the paint areas of the turbine blade, in which case preferably Cl compounds be withdrawn.
  • the diffusion annealing takes place for a time between 30 minutes and 12 hours.
  • the diffusion annealing is preferably carried out in a hydrogen atmosphere or in an inert gas partial pressure atmosphere with a pressure between ambient pressure, that is about 1000 mbar, and 0.01 mbar.
  • the diffusion annealing is preferably carried out in a halide atmosphere, in which case the hydrogen atmosphere or the inert gas partial pressure atmosphere comprises a gaseous addition of metal chloride particles, in particular a gaseous addition of CrCl 2 particles and / or CrCl 3 particles.
  • Argon is preferably used as the inert gas.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur une aube de turbine à gaz, comportant une pale (11), un pied (12) et une plateforme (13) située entre la pale et le pied, l'aube étant pourvue au moins par endroits d'une protection anti-corrosion, en particulier sur une face inférieure (14) de la plateforme et/ou dans la zone de transition (15) entre la face inférieure de la plateforme et le pied. Selon l'invention, le revêtement anti-corrosion est un revêtement de diffusion ayant une teneur en chrome dans la zone superficielle supérieure à 30 % en poids.
EP09776056A 2008-08-27 2009-08-01 Procédé de revêtement d'une aube d'une turbine à gaz Active EP2331723B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE200810039969 DE102008039969A1 (de) 2008-08-27 2008-08-27 Turbinenschaufel einer Gasturbine und Verfahren zum Beschichten einer Turbinenschaufel einer Gasturbine
PCT/DE2009/001095 WO2010022698A1 (fr) 2008-08-27 2009-08-01 Aube d'une turbine à gaz, et procédé de revêtement d'une aube d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2331723A1 true EP2331723A1 (fr) 2011-06-15
EP2331723B1 EP2331723B1 (fr) 2013-02-27

Family

ID=41199829

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09776056A Active EP2331723B1 (fr) 2008-08-27 2009-08-01 Procédé de revêtement d'une aube d'une turbine à gaz

Country Status (3)

Country Link
EP (1) EP2331723B1 (fr)
DE (1) DE102008039969A1 (fr)
WO (1) WO2010022698A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101933746B1 (ko) 2011-08-11 2018-12-28 몰 벨팅 시스템즈, 인코포레이티드. 사이클로 감속기 장치
DE102011089131A1 (de) * 2011-12-20 2013-06-20 Mtu Aero Engines Gmbh Diffusionsbeschichtungsverfahren und damit hergestellte Chromschicht
US20140004372A1 (en) * 2012-06-28 2014-01-02 Kevin L. Collins Chromium diffusion coating
DE102012015586A1 (de) 2012-08-08 2014-05-15 MTU Aero Engines AG Duplex Phasen CrAl-Beschichtung für verbesserten Korrosions-/Oxidations-Schutz
DE102014222024A1 (de) 2014-10-29 2016-06-16 MTU Aero Engines AG Schlicker und Verfahren zur Herstellung einer Oxidations- und Korrosionsbeständigen Diffusionschicht
DE102017212075A1 (de) * 2017-07-14 2019-01-17 MTU Aero Engines AG Verfahren zum Beschichten eines Bauteils für den Heißgaskanal einer Strömungsmaschine
DE102017213553A1 (de) 2017-08-04 2019-02-07 MTU Aero Engines AG Schaufel für strömungsmaschine mit verschiedenen diffusionsschutzschichten und verfahren zur herstellung

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1111192B1 (fr) 1999-12-20 2005-08-31 United Technologies Corporation Articles pourvus de revêtements résistants à la corrosion
GB0409486D0 (en) * 2004-04-28 2004-06-02 Diffusion Alloys Ltd Coatings for turbine blades
GB2421032A (en) * 2004-12-11 2006-06-14 Siemens Ind Turbomachinery Ltd A method of protecting a component against hot corrosion
GB2439313B (en) * 2006-06-24 2011-11-23 Siemens Ag Method of protecting a component against hot corrosion and a component protected by said method

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010022698A1 *

Also Published As

Publication number Publication date
DE102008039969A1 (de) 2010-03-04
WO2010022698A1 (fr) 2010-03-04
EP2331723B1 (fr) 2013-02-27

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