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WO2006094481A1 - Element, en particulier element de turbine a gaz - Google Patents

Element, en particulier element de turbine a gaz Download PDF

Info

Publication number
WO2006094481A1
WO2006094481A1 PCT/DE2006/000379 DE2006000379W WO2006094481A1 WO 2006094481 A1 WO2006094481 A1 WO 2006094481A1 DE 2006000379 W DE2006000379 W DE 2006000379W WO 2006094481 A1 WO2006094481 A1 WO 2006094481A1
Authority
WO
WIPO (PCT)
Prior art keywords
component
barrier layer
base body
component according
base
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.)
Ceased
Application number
PCT/DE2006/000379
Other languages
German (de)
English (en)
Inventor
Wolfgang Eichmann
Falko Heutling
Karl-Heinz Manier
Markus Uecker
Thomas Uihlein
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 US11/908,092 priority Critical patent/US20090269207A1/en
Priority to EP06722548A priority patent/EP1856306A1/fr
Priority to CA002600198A priority patent/CA2600198A1/fr
Publication of WO2006094481A1 publication Critical patent/WO2006094481A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • 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
    • C23C28/023—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 only coatings of metal elements only
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/131—Molybdenum
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
    • 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

  • Component in particular gas turbine component
  • the invention relates to a component, in particular a gas turbine component, according to the preamble of patent claim 1.
  • Components of a gas turbine such as the rotor blades, are provided with special anti-wear coatings to provide oxidation resistance, corrosion resistance, or erosion resistance on the surfaces.
  • the components of gas turbines are subject to wear during operation of the same or can be damaged in any other way.
  • it is generally necessary to remove or remove the wear-resistant coating from the part to be repaired in regions, partially or in total.
  • the removal or removal of coatings is also referred to as stripping.
  • stripping In the stripping process, a distinction is made between those in which the stripping takes place by mechanical means, by chemical means or by electrochemical means.
  • the present invention is based on the problem of creating a novel component, in particular a novel gas turbine component.
  • a barrier layer is positioned between the base body and the wear protection coating in order to protect the base body during a chemical or electrochemical stripping of the component.
  • a barrier layer between the main body and the wear protection coating of a coated component.
  • the barrier layer protects the main body of the component in a chemical or electrochemical stripping against attack by the stripping.
  • the barrier layer is resistant to chemical and electrochemical descaling.
  • the barrier layer preferably has a material composition adapted to the material composition of the base body, the material of the barrier layer being enriched or alloyed with a platinum group element and / or with nickel and / or with molybdenum in relation to the base material of the base body.
  • Fig. 1 is a schematic cross section through an inventive component.
  • the wear protection coating 12 is a multi-layer or multi-layer wear protection coating 12 made of the layers 13, 14 and 15.
  • the layers 13, 14 and 15 of the wear protection coating 12 may alternately comprise relatively hard and relatively soft layers or layers Act positions.
  • the number of layers of wear protection coating 12 is arbitrary and of minor importance to the present invention.
  • a barrier layer 16 is positioned between the wear protection coating 12 and the main body 11 of the construction according to the invention.
  • the barrier layer 16 is arranged between the main body 11 and the lowermost or innermost layer 13 of the wear-resistant coating 12.
  • the barrier layer 16 assumes the function of protecting the main body 11 against chemical attack during electrochemical or stratification of the component 10.
  • the barrier layer 16 is therefore resistant to chemical or electrochemical stripping and is not attacked or removed in such stripping, so that the base material of the base body 11 is not attacked or removed.
  • the barrier layer 16 has a material composition which is adapted to the material composition of the base body 11.
  • both the base body 11 and the barrier layer 16 are formed from a titanium-based alloy.
  • the material of the barrier layer 16 is enriched or alloyed with the base material of the base body 11 with at least one element of the platinum group and / or nickel and / or molybdenum.
  • the material of the barrier layer 16 platinum in a proportion of at least 0.05 wt .-% have.
  • the material of the barrier layer 16 palladium in a proportion of at least 0.05 wt .-% have.
  • the material of the barrier layer 16 may comprise nickel in a proportion of at least 0.50 wt .-% and / or molybdenum in a proportion of at least 4.00 wt .-%.
  • nickel in a proportion of at least 0.50 wt .-% and / or molybdenum in a proportion of at least 4.00 wt .-%.
  • One or more of these elements may be present in the above defined portions in the barrier layer 16.
  • the barrier layer protects the base material of the base body from attack during chemical stripping and during electrochemical stripping of the component. This ensures that in a stripping the material properties of the base material of the body are not adversely affected.
  • Another advantage of the barrier layer is that it is relatively smooth. Thus, after a delamination, a significantly better connection of a newly applied wear protection coating on the base body can be made possible than would be possible in the prior art in a body attacked or etched by the de-coating. Since the barrier layer has a material composition adapted to the material composition of the base body, there are no adaptation problems for the wear protection coating.

Landscapes

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

Abstract

L'invention concerne un élément, en particulier un élément pour une turbine à gaz, comprenant un corps de base (11) en matière première de base et un revêtement (12) protégeant contre l'usure, disposé sur la surface du corps de base (11), en particulier un revêtement protecteur contre la corrosion et/ou l'oxydation et/ou l'érosion. Selon l'invention, une couche de blocage (16) est positionnée entre le corps de base (11) et le revêtement (12) de protection contre l'usure, ce qui permet de protéger le corps de base (11) lors du retrait d'une couche chimique ou électrochimique du composant (10).
PCT/DE2006/000379 2005-03-10 2006-03-03 Element, en particulier element de turbine a gaz Ceased WO2006094481A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US11/908,092 US20090269207A1 (en) 2005-03-10 2006-03-03 Component, in particular, a gas turbine component
EP06722548A EP1856306A1 (fr) 2005-03-10 2006-03-03 Element, en particulier element de turbine a gaz
CA002600198A CA2600198A1 (fr) 2005-03-10 2006-03-03 Element, en particulier element de turbine a gaz

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005011011A DE102005011011A1 (de) 2005-03-10 2005-03-10 Bauteil, insbesondere Gasturbinenbauteil
DE102005011011.8 2005-03-10

Publications (1)

Publication Number Publication Date
WO2006094481A1 true WO2006094481A1 (fr) 2006-09-14

Family

ID=36646061

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2006/000379 Ceased WO2006094481A1 (fr) 2005-03-10 2006-03-03 Element, en particulier element de turbine a gaz

Country Status (5)

Country Link
US (1) US20090269207A1 (fr)
EP (1) EP1856306A1 (fr)
CA (1) CA2600198A1 (fr)
DE (1) DE102005011011A1 (fr)
WO (1) WO2006094481A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2566697C2 (ru) 2011-04-13 2015-10-27 Роллс-Ройс Корпорейшн Граничный барьерный для диффузии слой, включающий в себя иридий, на металлической подложке
EP2918705B1 (fr) 2014-03-12 2017-05-03 Rolls-Royce Corporation Revêtement comprenant une couche barrière de diffusion comprenant iridium et une couche d'oxyde et procédé de revêtement
DE102015208781A1 (de) * 2015-05-12 2016-11-17 MTU Aero Engines AG Kombination von Schaufelspitzenpanzerung und Erosionsschutzschicht sowie Verfahren zur Herstellung derselben

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4761346A (en) * 1984-11-19 1988-08-02 Avco Corporation Erosion-resistant coating system
WO1991002108A1 (fr) * 1989-08-10 1991-02-21 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0872575A2 (fr) * 1997-04-19 1998-10-21 Institut für Festkörper- und Werkstofforschung Dresden e.V. Revêtement protecteur de la surface pour alliages de titane
EP1342510A2 (fr) * 2002-03-09 2003-09-10 MTU Aero Engines GmbH Procédé de décapage d'éléments de moteur et dispositif d'exécution du procédé
EP1418256A2 (fr) * 2002-10-21 2004-05-12 General Electric Company Procedé, composition et dispositif de décapage partiel d'un revêtement sur un subatrat
WO2005068784A1 (fr) * 2004-01-13 2005-07-28 Mtu Aero Engines Gmbh Aube de turbomachine et procede de fabrication d'une plaque d'usure d'extremite de turbine sur les turbines d'une turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6071627A (en) * 1996-03-29 2000-06-06 Kabushiki Kaisha Toshiba Heat-resistant member and a method for evaluating quality of a heat-resistant member
US6830827B2 (en) * 2000-03-07 2004-12-14 Ebara Corporation Alloy coating, method for forming the same, and member for high temperature apparatuses
US6475642B1 (en) * 2000-08-31 2002-11-05 General Electric Company Oxidation-resistant coatings, and related articles and processes
US6620525B1 (en) * 2000-11-09 2003-09-16 General Electric Company Thermal barrier coating with improved erosion and impact resistance and process therefor
US20090176110A1 (en) * 2008-01-08 2009-07-09 General Electric Company Erosion and corrosion-resistant coating system and process therefor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4761346A (en) * 1984-11-19 1988-08-02 Avco Corporation Erosion-resistant coating system
WO1991002108A1 (fr) * 1989-08-10 1991-02-21 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0872575A2 (fr) * 1997-04-19 1998-10-21 Institut für Festkörper- und Werkstofforschung Dresden e.V. Revêtement protecteur de la surface pour alliages de titane
EP1342510A2 (fr) * 2002-03-09 2003-09-10 MTU Aero Engines GmbH Procédé de décapage d'éléments de moteur et dispositif d'exécution du procédé
EP1418256A2 (fr) * 2002-10-21 2004-05-12 General Electric Company Procedé, composition et dispositif de décapage partiel d'un revêtement sur un subatrat
WO2005068784A1 (fr) * 2004-01-13 2005-07-28 Mtu Aero Engines Gmbh Aube de turbomachine et procede de fabrication d'une plaque d'usure d'extremite de turbine sur les turbines d'une turbomachine

Also Published As

Publication number Publication date
DE102005011011A1 (de) 2006-09-14
US20090269207A1 (en) 2009-10-29
EP1856306A1 (fr) 2007-11-21
CA2600198A1 (fr) 2006-09-14

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