EP2684982A1 - Couche de protection pour un composant d'une turbomachine - Google Patents

Couche de protection pour un composant d'une turbomachine Download PDF

Info

Publication number
EP2684982A1
EP2684982A1 EP12175910.4A EP12175910A EP2684982A1 EP 2684982 A1 EP2684982 A1 EP 2684982A1 EP 12175910 A EP12175910 A EP 12175910A EP 2684982 A1 EP2684982 A1 EP 2684982A1
Authority
EP
European Patent Office
Prior art keywords
component
hard material
layer
material layer
ceramic hard
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.)
Withdrawn
Application number
EP12175910.4A
Other languages
German (de)
English (en)
Inventor
Jochen Barnikel
Manuel Ettler
Friedhelm Schmitz
Jörg SCHÜRHOFF
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP12175910.4A priority Critical patent/EP2684982A1/fr
Priority to PCT/EP2013/062155 priority patent/WO2014009089A1/fr
Priority to CN201390000611.5U priority patent/CN204803410U/zh
Publication of EP2684982A1 publication Critical patent/EP2684982A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C23C28/3215—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer 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
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • 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
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer

Definitions

  • the invention relates to a component for a turbomachine, in particular steam turbine, with a component surface.
  • Vibration increases as the blade natural frequencies resonate at operating speeds or other transient frequencies.
  • the materials used in thermally stressed zones of a steam turbine must fulfill two characteristics. These are on the one hand the oxidation resistance and on the other hand the creep rupture strength. Basically, materials are known that can meet such requirements, such as nickel-based alloys, which are increasingly used. However, such materials are relatively expensive. Therefore, the materials mentioned above by significantly cheaper materials, such as ferritic 10% chromium steels or similar replaced. The disadvantage of such ferritic 10% chromium steels or other similar materials is that they do not have sufficient oxidation resistance and are therefore unsuitable for some applications in the steam turbine.
  • the thermally stressed components have been exposed in areas exposed to approximately 600 ° C hot steam, such as e.g. High-pressure or medium-pressure turbine blades, partially made of nickel-based alloys.
  • the established chromium steels are generally no longer used at steam temperatures in the range of well above 600 ° C, since the oxidation resistance of such chromium steels in this range is no longer sufficient.
  • a component for a turbomachine in particular a steam turbine, with a component surface, wherein a ceramic hard material layer is applied directly to the component surface, wherein a metallic layer is applied directly to the ceramic hard material layer.
  • a duplex protective layer consisting of two layers is applied to the component.
  • the component has a component surface, wherein a ceramic hard material layer is arranged directly on this component surface. It is essential here that the ceramic hard material layer is applied directly to the component surface, ie, that no intermediate layer is arranged between the component surface and the ceramic hard material layer.
  • a metallic layer is applied directly to this ceramic hard material layer. It is also important here again that no further intermediate layer is arranged between the ceramic hard material layer and the metallic layer.
  • the invention is based on the idea that the duplex layer according to the invention offers improved oxidation protection and improved erosion resistance. This means that the base material of the component does not necessarily have to be a nickel-based alloy. Instead, cheaper materials can be used instead of the nickel-based alloy.
  • the thicknesses of the ceramic hard material layer, the metallic protective layer and the second ceramic hard material layer have thicknesses in the range from 5 ⁇ m to 25 ⁇ m.
  • FIG. 1 shows a component 1.
  • This component is designed for use in a turbomachine.
  • turbomachine is understood, for example, a steam turbine, a compressor or a gas turbine or other thermal machines.
  • the component has a component surface 2.
  • a ceramic hard material layer 3 is arranged directly.
  • the ceramic hard material layer 3 is arranged directly on the component surface, ie, no further layer is arranged between the ceramic hard material layer 3 and the component surface 2.
  • On the ceramic hard coating is directly a metallic layer 4 is arranged.
  • the metallic layer 4 is arranged directly on the ceramic hard material layer 3, ie no further intermediate layer is arranged between the metallic layer 4 and the ceramic hard material layer 3.
  • the embodiment according to FIG. 1 may be referred to as a duplex layer because the erosion and oxidation protection layer on the component surface 2 comprises two layers.
  • the ceramic hard material layer 3 is formed such that the thickness of the ceramic hard material layer 3 is in the range of 5 .mu.m to 25 .mu.m.
  • the metallic layer 4 is formed in such a way that the metallic layer 4 has a thickness which lies in the range between 5 ⁇ m and 25 ⁇ m.
  • the second ceramic hard material layer 5 is formed in such a way that the second ceramic hard material layer 5 has a thickness which lies in the range between 5 ⁇ m to 25 ⁇ m.
  • the component is designed, for example, as a turbine blade for a steam turbine.
  • the turbine blade may be a blade or a vane.
  • the combination of the two layers comprising the ceramic hard material layer 3 and the metallic layer 4 form a very good protection of the component 1 against oxidation and at the same time also offer good erosion resistance.
  • the ceramic hard material layer 3 acts primarily as a diffusion barrier, which ensures that there is no interdiffusion between the base material of the component 1 and the metallic protective layer 4. In addition, this layer already offers good oxidation protection.
  • the metallic layer 4 offers a very good protection against oxidation and erosion, in particular against particles which strike the surface perpendicular to the surface.
  • the triplex layer is carried out at sites particularly subject to erosion.
  • the second ceramic hard material layer 5 in the triplex layer offers particularly good protection as erosion protection and additionally as oxidation protection.
  • duplex and / or triplex layers are preferably applied by means of a PVD method, in which case in particular sputtering methods are to be used.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Inorganic Chemistry (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
EP12175910.4A 2012-07-11 2012-07-11 Couche de protection pour un composant d'une turbomachine Withdrawn EP2684982A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP12175910.4A EP2684982A1 (fr) 2012-07-11 2012-07-11 Couche de protection pour un composant d'une turbomachine
PCT/EP2013/062155 WO2014009089A1 (fr) 2012-07-11 2013-06-12 Couche protectrice pour une pièce de turbomachine
CN201390000611.5U CN204803410U (zh) 2012-07-11 2013-06-12 用于流体机械的部件

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12175910.4A EP2684982A1 (fr) 2012-07-11 2012-07-11 Couche de protection pour un composant d'une turbomachine

Publications (1)

Publication Number Publication Date
EP2684982A1 true EP2684982A1 (fr) 2014-01-15

Family

ID=46754260

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12175910.4A Withdrawn EP2684982A1 (fr) 2012-07-11 2012-07-11 Couche de protection pour un composant d'une turbomachine

Country Status (3)

Country Link
EP (1) EP2684982A1 (fr)
CN (1) CN204803410U (fr)
WO (1) WO2014009089A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2907888A1 (fr) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Aube de compresseur dotée d'un revêtement dur résistant à la corrosion
DE102016222296A1 (de) * 2016-11-14 2018-05-17 Siemens Aktiengesellschaft Mehrlagige aluminiumhaltige Schutzbeschichtung und Bauteil

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT7941U1 (de) * 2004-12-02 2005-11-15 Ceratizit Austria Gmbh Werkzeug zur spanabhebenden bearbeitung
US20070078521A1 (en) * 2005-09-30 2007-04-05 Depuy Products, Inc. Aluminum oxide coated implants and components
DE102007050918A1 (de) * 2006-10-26 2008-04-30 General Electric Co. Erosionsbeständige Beschichtung und Verfahren der Herstellung
DE102007027335A1 (de) * 2007-06-14 2008-12-18 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung und Bauteil mit einer Verschleißschutzbeschichtung
EP2072636A2 (fr) * 2007-12-21 2009-06-24 Sandvik Intellectual Property AB Procédé de fabrication d'un outil de coupe et outil de coupe

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AT7941U1 (de) * 2004-12-02 2005-11-15 Ceratizit Austria Gmbh Werkzeug zur spanabhebenden bearbeitung
US20070078521A1 (en) * 2005-09-30 2007-04-05 Depuy Products, Inc. Aluminum oxide coated implants and components
DE102007050918A1 (de) * 2006-10-26 2008-04-30 General Electric Co. Erosionsbeständige Beschichtung und Verfahren der Herstellung
DE102007027335A1 (de) * 2007-06-14 2008-12-18 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung und Bauteil mit einer Verschleißschutzbeschichtung
EP2072636A2 (fr) * 2007-12-21 2009-06-24 Sandvik Intellectual Property AB Procédé de fabrication d'un outil de coupe et outil de coupe

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2907888A1 (fr) * 2014-02-14 2015-08-19 Siemens Aktiengesellschaft Aube de compresseur dotée d'un revêtement dur résistant à la corrosion
WO2015121000A1 (fr) * 2014-02-14 2015-08-20 Siemens Aktiengesellschaft Aube de compresseur pourvue d'un revêtement dur résistant à l'érosion
US10465535B2 (en) 2014-02-14 2019-11-05 Siemens Aktiengesellschaft Compressor blade or vane having an erosion-resistant hard material coating
DE102016222296A1 (de) * 2016-11-14 2018-05-17 Siemens Aktiengesellschaft Mehrlagige aluminiumhaltige Schutzbeschichtung und Bauteil
US11078574B2 (en) 2016-11-14 2021-08-03 Siemens Energy Global GmbH & Co. KG Multilayered aluminiferous protective coating and component

Also Published As

Publication number Publication date
WO2014009089A1 (fr) 2014-01-16
CN204803410U (zh) 2015-11-25

Similar Documents

Publication Publication Date Title
EP2044231B1 (fr) Composant dote d'un blindage
EP1741876B1 (fr) Aube de turbomachine comprenant une extrémité blindée
DE102007005755A1 (de) Vorrichtung zum Schutz von Bauteilen mit brennbarer Titanlegierung vor Titanfeuer und Verfahren zu deren Herstellung
WO2005066384A1 (fr) Revetement de protection contre l'usure et piece comportant un revetement de protection contre l'usure
EP3093372B1 (fr) Procede de recouvrement destine a produire une combinaison de blindage d'extremite d'aubes et couche de protection contre l'erosion
EP1734145A1 (fr) Composant ayant un revêtement avec une barrière thermique et une couche resistante à l'erosion, procéde de manufacture et méthode pour son utilisation
WO2005061856A1 (fr) Composant de turbine comprenant une couche d'isolation thermique et une couche de protection contre l'erosion
DE102016201523A1 (de) Schaufel einer Strömungsmaschine mit Schaufelfusswärmedämmung
DE102004002943B4 (de) Schichtsystem für eine Rotor-/Statordichtung einer Strömungsmaschine
WO2004007787A1 (fr) Systeme stratifie
WO2009006871A2 (fr) Aube pour turbomachine
EP2684982A1 (fr) Couche de protection pour un composant d'une turbomachine
EP1692322B1 (fr) Couche de protection metallique
EP1929060A1 (fr) Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection
EP3077572B1 (fr) Résistance à l'usure d'un composant à haute température améliorée par un revêtement au cobalt
EP2807288B1 (fr) Composant de turbomachine à revêtement fonctionnel
EP3423752B1 (fr) Élément exposé à un écoulement et procédé de revêtement d'un élément exposé à un écoulement
EP1892311B1 (fr) Aube de turbine avec une système de revêtement
EP2976440B1 (fr) Revêtement protecteur et élément de turbine à gaz pourvu de ce revêtement protecteur
EP3347200B1 (fr) Aube de turbine avec une barrière thermique double couche locale
DE102016215158A1 (de) Korrosions- und erosionsbeständiges Schutzschichtsystem und Verdichterschaufel
EP4155431A1 (fr) Procédé de fabrication et composant fabriqué selon ce procédé à partir d'un superalliage à base de nickel pour le canal de gaz chaud d'une turbomachine
EP2913425A1 (fr) Couche d'isolation thermique avec alliage iridium-rhodium
DE102009058853A1 (de) Turbinenschaufel
DE102014207790A1 (de) Kühlfluidkanal

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20140716