EP2129812A2 - Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same - Google Patents

Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same

Info

Publication number
EP2129812A2
EP2129812A2 EP08717723A EP08717723A EP2129812A2 EP 2129812 A2 EP2129812 A2 EP 2129812A2 EP 08717723 A EP08717723 A EP 08717723A EP 08717723 A EP08717723 A EP 08717723A EP 2129812 A2 EP2129812 A2 EP 2129812A2
Authority
EP
European Patent Office
Prior art keywords
layer
blade
turbomachine blade
turbomachine
corrosion
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
EP08717723A
Other languages
German (de)
French (fr)
Other versions
EP2129812B1 (en
Inventor
Marie-Gilles Barril
Piero-Daniele Grasso
Alexander Stankowski
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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
Priority claimed from US11/765,599 external-priority patent/US8113787B2/en
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2129812A2 publication Critical patent/EP2129812A2/en
Application granted granted Critical
Publication of EP2129812B1 publication Critical patent/EP2129812B1/en
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
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
    • 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
    • C23C28/324—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 matrix material layer comprising a mixture of at least two metals or metal phases or a metal-matrix material with hard embedded particles, e.g. WC-Me
    • 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
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/173—Aluminium alloys, e.g. AlCuMgPb

Definitions

  • the present invention relates to a turbomachine blade, in particular to a compressor blade for use in a gas turbine engine.
  • the present invention also relates to a method of manufacturing a turbomachine blade, the method comprising the step of depositing a corrosion and erosion protective coating on the turbomachine blade body.
  • turbomachine blades in particular compressor blades, which are made of metallic material such as stainless steel, are susceptible to corrosion, in particular pitting corrosion.
  • Pitting corrosion is a form of localized corrosion that leads to the creation of small holes in the metallic material based on galvanic corrosion.
  • pitting corrosion can be initiated by small surface defects such as scratches, holes or local changes of the composition of the material and it may be aggravated by salt deposits and humidity during operation or stand still of the turbine engine. Due to water droplets and particulate matter impacting on the leading edge area of compressor blades in a gas turbine pitting corrosion is a frequently occuring degradation mechanism for compressor blading.
  • a turbomachine blade which may be a compressor blade, comprises a blade body and a corrosion and erosion protective multilayered coating bonded to the blade body.
  • the multilayered coating com- prises an erosion resistant first layer and a sacrificial second layer with the latter one being provided in overlying relationship to the first one.
  • the erosion resistant first layer is selected so as to provide erosion re- sistance against water droplets or particles impacting on it.
  • the first layer may be selected so as to provide stainless steel corrosion resistance as well.
  • the erosion resistant first layer is deposited so that it covers at least an corrosion (and erosion) critical area of the blade body such as a leading edge area of the blade.
  • the first layer exclusively covers the erosion critical area of the blade body and does not cover any area of the blade body not belonging to the erosion critical area.
  • the first layer preferably covers an area of up to 30% of the chord length starting from the leading edge towards the suction and pressure sides of the blade that is to say towards the trailing edge of the blade.
  • the first layer may cover an area of from 5 to 30% of the chord length starting from the leading edge towards the trailing edge. But it may also cover an area of up to 60% or more of the chord length starting from the leading edge towards the trailing edge in case of a stronger impact of particulate matter and water droplets.
  • the sacrificial second layer is deposited so that it covers the first layer at least totally. However, it may be preferred that the sacrificial second layer covers the blade body totally.
  • the first layer is sandwiched between the blade body and the second layer. Accordingly, the first layer is arranged so as to be an intermediate layer between the blade body and the second layer in an adjacent relationship relative to the blade body and the second layer.
  • the first layer may have a layer thickness in the range of from 50 to 100 micrometer ( ⁇ m) while the second layer may have a layer thickness in the range of from 50 to 100 micrometer ( ⁇ m) resulting in a total protective coating thickness in the range of from 100 to 200 micrometer ( ⁇ m) with a maximum total thickness of 200 micrometer ( ⁇ m).
  • the first layer is selected so as to be a braze tape or a foil containing a matrix of braze alloy with an erosion resistant filler material essentially consisting of abrasive particles.
  • the braze alloy may be a Silver (Ag)-based alloy or an Aluminum (Al)-based alloy or any other suitable alloy.
  • the erosion resistant filler may be selected so as to consist of one or more filler materials selected from the group consisting of AI 2 O 3 , WC, CrC or any other suitable erosion resistant material.
  • the filler content may range from 60 to 90 Vol.-% of the first layer and sizes of the filler particles may range from 10 to 30 micrometer ( ⁇ m).
  • a roughness of the first layer is made to be smaller than 2.3 micrometer ( ⁇ m) depending on the first layer deposition technique.
  • the first layer material is deposited using one or more deposition techniques selected from HVOF (High Velocity Oxygen Fuel)-spraying technique, tape/foil brazing technique, CVD (Chemical Vapor Deposition) technique and laser cladding technique.
  • HVOF High Velocity Oxygen Fuel
  • the first layer material may be deposited using HVOF (High Velocity Oxygen Fuel)- spraying technique.
  • the second layer is preferably a sacrificial slurry coating.
  • the sacrificial slurry coating may, for instance, consist of a closely packed alumi- num-filled chromate/phophate basecoat that is sealed with a chemically inert chromate/phosphate topcoat on top of the basecoat.
  • a roughness of the sacrificial slurry coating is made to be smaller than 1.6 micrometer ( ⁇ m) depending on the first layer deposition technique.
  • a method of manufacturing above- described turbomachine blade comprises the steps of:
  • - second deposition step of depositing a sacrificial second layer over the first layer in order to cover at least the first layer and preferably the whole blade body.
  • Deposition of the second layer may be effected using one or more standard spraying techniques.
  • the first layer may be deposited on the base material by one of the two preferred following techniques selected from tape/foil brazing technique or HVOF (High Velocity Oxygen Fuel)-spraying technique.
  • HVOF High Velocity Oxygen Fuel
  • other deposition techniques such as CVD (Chemical Vapor Deposition) technique or Laser Cladding technique may also be used.
  • the first layer material consists of one or more materials selected from the group of stainless steel and nickel (Ni)-based alloys
  • the first layer material may be deposited using HVOF (High Velocity Oxy- gen Fuel)-spraying technique.
  • the first layer material may be deposited using tape/foil brazing technique. Upon doing so, brazing temperatures used may not exceed a tempering temperature of the stainless steel blade body material.
  • FIG. 1 schematically depicts a transversal sectional view of an embodiment of a compressor blade provided with a corrosion protective coating according to the present invention
  • FIG. 2 schematically depicts a method of manufacturing the compressor blade shown in FIG. 1.
  • FIG. 1 shows a transversal sectional view of an embodiment of a compressor blade for a gas turbine which is provided with a corrosion protective coating according to the present invention.
  • a compressor blade 1 comprises a blade body (substrate) 2 that for instance is made of stainless steel. Due to its typical body shape, the blade body has a major bulged pressure side 7 (in FIG. 1 upper side) and a minor bulged suction side 6 (in FIG. 1 lower side) both of which are formed to converge in a dull leading edge 8 and an acute trailing edge 9 of the blade body 2.
  • the outer surface 10 of the blade body 2 is covered with a corrosion and erosion protective bilayer coating 1 1 that is bonded thereto.
  • the bilayer coating 1 1 comprises a lower erosion resistant first layer 3 that is provided on the surface of blade body 2 and arranged in a leading edge area 5 surrounding the leading edge 8 on both the suction side 6 and the pressure side 7 of the blade body 2.
  • the first layer 3 covers a covering area of up to 60% of the airfoil chord length starting from the leading edge 8 towards the trailing edge 9 of the blade body 2.
  • the airfoil chord length can be identified by the outer surface 10 of the blade body 2.
  • the erosion resistant first layer 3 material is selected so as to provide erosion re- sistance against water droplets or particles impacting on the leading edge 8 area 5. It is selected so as to provide stainless steel corrosion resistance of the blade body 2 as well.
  • the first layer 3 is a braze tape or foil containing a matrix of braze alloy, such as a Silver (Ag)-based alloy or an Aluminium (Al)-based alloy, and an erosion resistant filler material, such as AI 2 O 3 , WC and CrC.
  • the filler content ranges from 60 to 90 Vol.-% of the first layer 3 and sizes of the filler particles preferably range from 10 to 30 micrometers ( ⁇ m).
  • the layer thickness of the first layer 3 preferably ranges from 50 to 100 ⁇ m.
  • the bilayer coating 1 1 further comprises an upper sacrificial second layer 4 that covers (is deposited on) the first layer 3 and the remaining non-covered parts of the blade body 2 surface 10.
  • the first layer 3 is sandwiched between the blade body 2 and the second layer 4.
  • the second layer 4 is a sacrificial slurry coating that consists of a closely packed aluminum-filled chromate/phophate basecoat that is sealed with a chemically inert chromate/phosphate topcoat on top of the base- coat (both basecoat and topcoat are not further detailed in FIG. 1 ).
  • the second layer 4 has a layer thickness ranging from 50 to 100 ⁇ m resulting in a total bilayer coating 1 1 thickness ranging from 100 to 200 ⁇ m.
  • FIG. 2 schematically depicts a method of manufacturing the compressor blade 1 shown in FIG. 1 , the method comprising two deposition steps for depositing the corrosion protective bilayer coating 1 1.
  • the erosion resistant first layer 3 is deposited on the surface (outer skin) 10 of the blade body 2 in the leading edge 8 area 5 (step II).
  • the sacrificial slurry second layer 4 is deposited on both the first layer 3 and the remaining non-covered portions of the blade body 2 surface 10 to thereby coat the whole blade body 2 (step III).
  • HVOF High Velocity Oxygen Fuel
  • deposition techniques such as CVD (Chemical Vapor Deposition) technique or Laser Cladding technique may also be used.
  • Deposition of the second layer may be effected using one or more standard spraying techniques. The deposition techniques may be selected so as to achieve a roughness of both the erosion resistant first layer 3 and sacrificial slurry second layer 4 of less than 2.3 ⁇ m.

Landscapes

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

Abstract

A turbomachine blade (1 ) comprises a blade body (2) and a corrosion and erosion protective multilayered coating (1 1 ) bonded thereto, the multilayered coating (1 1 ) comprising an erosion resistant first layer (3) at least covering a corrosion and erosion critical area (5) of the blade body (2) and a sacrificial second layer (4) pro¬ vided over the first layer (3) at least covering the first layer (3), preferably covering the blade totally. A method of manufacturing such a turbomachine blade comprises the steps of providing a blade and depositing the erosion resistant first layer on the blade body so as to cover at least the corrosion and erosion critical area, followed by deposit¬ ing the sacrificial second layer over the first layer at least covering the first layer.

Description

TURBOMACHINE BLADE WITH EROSION AND CORROSION PROTECTIVE COATING AND METHOD OF MANUFACTURING THE SAME
FIELD OF THE INVENTION
The present invention relates to a turbomachine blade, in particular to a compressor blade for use in a gas turbine engine. The present invention also relates to a method of manufacturing a turbomachine blade, the method comprising the step of depositing a corrosion and erosion protective coating on the turbomachine blade body.
BACKGROUND OF THE INVENTION
It is known from the state of the art that turbomachine blades, in particular compressor blades, which are made of metallic material such as stainless steel, are susceptible to corrosion, in particular pitting corrosion.
Pitting corrosion is a form of localized corrosion that leads to the creation of small holes in the metallic material based on galvanic corrosion. As is known, pitting corrosion can be initiated by small surface defects such as scratches, holes or local changes of the composition of the material and it may be aggravated by salt deposits and humidity during operation or stand still of the turbine engine. Due to water droplets and particulate matter impacting on the leading edge area of compressor blades in a gas turbine pitting corrosion is a frequently occuring degradation mechanism for compressor blading.
Moreover, pitting corrosion is extremely insidious as it causes only little loss of ma- terial with small effects on the metal surface. However, it causes serious damages in the deep structure of the metal. When corrosion pits reach a certain depth, par- ticularly in the leading edge area of the blade, they can lead to the formation of cracks, which may finally result in blade failure due to high cyclic fatigue (HCF).
In order to avoid pitting corrosion, it is known to deposit corrosion protective layers on the blade body material. In recent years, sacrificial slurry coatings have become rather popular for use as corrosion protective layers, in particular for use in the front stages in compressor blading. These coatings are sacrificial because they are attacked instead of the blading material. However, it has become apparent that even sacrificial slurry coatings are prone to degradation in highly erosive conditions as they typically can be found at the leading edges of compressor blades due to water droplets and particles that hit the blades very hard. Because of local loss of the coating's erosion resistant property, corrosion of the leading edge area may occur.
SUMMARY OF THE INVENTION
In light of the above, it is an object of the invention to suppress pitting corrosion of a turbomachine blade and to provide a turbomachine blade that has an improved corrosion and erosion protective coating to enable a longer working life of the blade. It is another object of the invention to provide a method of manufacturing such a turbomachine blade.
The afore-mentioned objects are achieved by a turbomachine blade as described in independent claim 1 and a method of manufacturing such a turbomachine blade according to claim 26, respectively. Preferred embodiments are the subject of the dependent claims.
According to one aspect of the invention a turbomachine blade, which may be a compressor blade, comprises a blade body and a corrosion and erosion protective multilayered coating bonded to the blade body. The multilayered coating com- prises an erosion resistant first layer and a sacrificial second layer with the latter one being provided in overlying relationship to the first one.
Preferably, the erosion resistant first layer is selected so as to provide erosion re- sistance against water droplets or particles impacting on it. In case the blade body is made of stainless steel, the first layer may be selected so as to provide stainless steel corrosion resistance as well.
According to a further aspect of the invention, the erosion resistant first layer is deposited so that it covers at least an corrosion (and erosion) critical area of the blade body such as a leading edge area of the blade. However, it may be preferred that the first layer exclusively covers the erosion critical area of the blade body and does not cover any area of the blade body not belonging to the erosion critical area.
Depending on the severity of the erosion attack, the first layer preferably covers an area of up to 30% of the chord length starting from the leading edge towards the suction and pressure sides of the blade that is to say towards the trailing edge of the blade. The first layer may cover an area of from 5 to 30% of the chord length starting from the leading edge towards the trailing edge. But it may also cover an area of up to 60% or more of the chord length starting from the leading edge towards the trailing edge in case of a stronger impact of particulate matter and water droplets.
The sacrificial second layer is deposited so that it covers the first layer at least totally. However, it may be preferred that the sacrificial second layer covers the blade body totally.
In the turbomachine blade of the present invention, it may be preferred that the first layer is sandwiched between the blade body and the second layer. Accordingly, the first layer is arranged so as to be an intermediate layer between the blade body and the second layer in an adjacent relationship relative to the blade body and the second layer.
In the present invention, the first layer may have a layer thickness in the range of from 50 to 100 micrometer (μm) while the second layer may have a layer thickness in the range of from 50 to 100 micrometer (μm) resulting in a total protective coating thickness in the range of from 100 to 200 micrometer (μm) with a maximum total thickness of 200 micrometer (μm).
Preferably, the first layer is selected so as to be a braze tape or a foil containing a matrix of braze alloy with an erosion resistant filler material essentially consisting of abrasive particles. The braze alloy may be a Silver (Ag)-based alloy or an Aluminum (Al)-based alloy or any other suitable alloy. The erosion resistant filler may be selected so as to consist of one or more filler materials selected from the group consisting of AI2O3, WC, CrC or any other suitable erosion resistant material. The filler content may range from 60 to 90 Vol.-% of the first layer and sizes of the filler particles may range from 10 to 30 micrometer (μm).
In the present invention, a roughness of the first layer is made to be smaller than 2.3 micrometer (μm) depending on the first layer deposition technique.
Preferably, the first layer material is deposited using one or more deposition techniques selected from HVOF (High Velocity Oxygen Fuel)-spraying technique, tape/foil brazing technique, CVD (Chemical Vapor Deposition) technique and laser cladding technique. In case the first layer material consists of one or more materials selected from the group of stainless steel and nickel (Ni)-based alloys, the first layer material may be deposited using HVOF (High Velocity Oxygen Fuel)- spraying technique.
In the present invention, the second layer is preferably a sacrificial slurry coating. The sacrificial slurry coating may, for instance, consist of a closely packed alumi- num-filled chromate/phophate basecoat that is sealed with a chemically inert chromate/phosphate topcoat on top of the basecoat. Preferably, a roughness of the sacrificial slurry coating is made to be smaller than 1.6 micrometer (μm) depending on the first layer deposition technique.
According to a further aspect of the invention, a method of manufacturing above- described turbomachine blade comprises the steps of:
- providing the blade body, followed by
- a two-step process of depositing the corrosion and erosion protective coating on the blade body, namely
- a first deposition step of depositing an erosion and corrosion resistant first layer in order to cover at least the corrosion critical area, in particular the leading edge area of the blade body, and a subsequent
- second deposition step of depositing a sacrificial second layer over the first layer in order to cover at least the first layer and preferably the whole blade body.
Deposition of the second layer may be effected using one or more standard spraying techniques. The first layer may be deposited on the base material by one of the two preferred following techniques selected from tape/foil brazing technique or HVOF (High Velocity Oxygen Fuel)-spraying technique. However other deposition techniques such as CVD (Chemical Vapor Deposition) technique or Laser Cladding technique may also be used. In case the first layer material consists of one or more materials selected from the group of stainless steel and nickel (Ni)-based alloys, the first layer material may be deposited using HVOF (High Velocity Oxy- gen Fuel)-spraying technique.
In a turbomachine blade having a blade body made of stainless steel, the first layer material may be deposited using tape/foil brazing technique. Upon doing so, brazing temperatures used may not exceed a tempering temperature of the stainless steel blade body material. The above and still further objects, features and advantages of the present invention will become apparent upon consideration of the following detailed description of an embodiment thereof.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 schematically depicts a transversal sectional view of an embodiment of a compressor blade provided with a corrosion protective coating according to the present invention;
FIG. 2 schematically depicts a method of manufacturing the compressor blade shown in FIG. 1.
DETAILED DESCRIPTION OF AN EMBODIMENT
An embodiment of the present invention will be described in detail below with reference to the accompanying drawings.
Reference is now made to FIG. 1 that shows a transversal sectional view of an embodiment of a compressor blade for a gas turbine which is provided with a corrosion protective coating according to the present invention.
A compressor blade 1 comprises a blade body (substrate) 2 that for instance is made of stainless steel. Due to its typical body shape, the blade body has a major bulged pressure side 7 (in FIG. 1 upper side) and a minor bulged suction side 6 (in FIG. 1 lower side) both of which are formed to converge in a dull leading edge 8 and an acute trailing edge 9 of the blade body 2. The outer surface 10 of the blade body 2 is covered with a corrosion and erosion protective bilayer coating 1 1 that is bonded thereto. The bilayer coating 1 1 comprises a lower erosion resistant first layer 3 that is provided on the surface of blade body 2 and arranged in a leading edge area 5 surrounding the leading edge 8 on both the suction side 6 and the pressure side 7 of the blade body 2. The first layer 3 covers a covering area of up to 60% of the airfoil chord length starting from the leading edge 8 towards the trailing edge 9 of the blade body 2. In FIG. 1 , the airfoil chord length can be identified by the outer surface 10 of the blade body 2.
The erosion resistant first layer 3 material is selected so as to provide erosion re- sistance against water droplets or particles impacting on the leading edge 8 area 5. It is selected so as to provide stainless steel corrosion resistance of the blade body 2 as well.
To this end the first layer 3 is a braze tape or foil containing a matrix of braze alloy, such as a Silver (Ag)-based alloy or an Aluminium (Al)-based alloy, and an erosion resistant filler material, such as AI2O3, WC and CrC. The filler content ranges from 60 to 90 Vol.-% of the first layer 3 and sizes of the filler particles preferably range from 10 to 30 micrometers (μm). The layer thickness of the first layer 3 preferably ranges from 50 to 100 μm.
The bilayer coating 1 1 further comprises an upper sacrificial second layer 4 that covers (is deposited on) the first layer 3 and the remaining non-covered parts of the blade body 2 surface 10. The first layer 3 is sandwiched between the blade body 2 and the second layer 4. The second layer 4 is a sacrificial slurry coating that consists of a closely packed aluminum-filled chromate/phophate basecoat that is sealed with a chemically inert chromate/phosphate topcoat on top of the base- coat (both basecoat and topcoat are not further detailed in FIG. 1 ). The second layer 4 has a layer thickness ranging from 50 to 100 μm resulting in a total bilayer coating 1 1 thickness ranging from 100 to 200 μm. Reference is now made to FIG. 2 that schematically depicts a method of manufacturing the compressor blade 1 shown in FIG. 1 , the method comprising two deposition steps for depositing the corrosion protective bilayer coating 1 1.
After a non-covered blade body 2 has been provided (step I), the erosion resistant first layer 3 is deposited on the surface (outer skin) 10 of the blade body 2 in the leading edge 8 area 5 (step II). In a further step, starting from a partly covered blade body 2 (step II), the sacrificial slurry second layer 4 is deposited on both the first layer 3 and the remaining non-covered portions of the blade body 2 surface 10 to thereby coat the whole blade body 2 (step III).
To deposit the first layer 3 on the base material tape/foil brazing technique or HVOF (High Velocity Oxygen Fuel)-spraying technique may be used. However other deposition techniques such as CVD (Chemical Vapor Deposition) technique or Laser Cladding technique may also be used. Deposition of the second layer may be effected using one or more standard spraying techniques. The deposition techniques may be selected so as to achieve a roughness of both the erosion resistant first layer 3 and sacrificial slurry second layer 4 of less than 2.3 μm.
As can be seen from the above, by bonding a corrosion protective bilayer coating 1 1 on the outer surface 10 of the blade body 2 the working life of the blade 1 can be increased significantly because of the provision of an increased local erosion and corrosion protection and the risk of premature failure due to pitting corrosion attack is reduced. The bilayer coating and the process for coating can be realized with low costs. By restricting the erosion resistant first layer 3 to the leading edge area 5 of the blade body 2 that is particularly endangered by early erosion, manufacturing costs and time can be reduced additionally. Compressor blades with a bilayer structure of the present invention are recondi- tionable. Reference list
1 Turbomachine blade
2 Blade body
3 Erosion and corrosion resistant first layer
4 Sacrificial second layer
5 Leading edge area
6 Suction side
7 Pressure side
8 Leading edge
9 Trailing edge
10 Blade body surface
1 1 Corrosion protective bilayer coating

Claims

1. A turbomachine blade (1 ) comprising a blade body (2) and a corrosion pro- tective multilayered coating (1 1 ) bonded thereto, the multilayered coating (1 1 ) comprising an erosion and corrosion resistant first layer (3) at least covering a corrosion and erosion critical area (5) of the blade body (2) and a sacrificial second layer (4) provided over the first layer (3) so as to cover the first layer (3).
2. A turbomachine blade (1 ) according to claim 1 wherein the first layer (3) exclusively covers the corrosion and erosion critical area (5) of the blade body (2).
3. A turbomachine blade (1 ) according to anyone of claims 1 and 2 wherein the second layer (4) totally covers the blade body (2).
4. A turbomachine blade (1 ) according to anyone of claims 1 to 3 wherein the first layer (3) is sandwiched in between the blade body (2) and the second layer (4).
5. A turbomachine blade (1 ) according to anyone of claims 1 to 4 wherein the corrosion critical area is a leading edge area (5) of the blade.
6. A turbomachine blade (1 ) according to claim 5 wherein the first layer (3) covers an area of up to 30% of the chord length starting from the leading edge (8) to- wards the trailing edge (9) of the blade body (2).
7. A turbomachine blade (1 ) according to claim 5 wherein the first layer (3) covers an area of from 5 to 30% of the chord length starting from the leading edge (8) towards the trailing edge (9) of the blade body (2).
8. A turbomachine blade (1 ) according to claim 5 wherein the first layer (3) covers an area of up to 60% of the chord length starting from the leading edge (8) towards the trailing edge (9) of the blade body (2).
9. A turbomachine blade (1 ) according to any one of the preceding claims wherein the first layer (3) has a layer thickness in the range of from 50 to 100 micrometer.
10. A turbomachine blade (1 ) according to any one of the preceding claims wherein the second layer (4) has a layer thickness in the range of from 50 to 100 micrometer.
1 1. A turbomachine blade (1 ) according to any one of the preceding claims wherein the first layer (3) is selected so as to provide erosion resistance against the impact of water droplets or particles.
12. A turbomachine blade (1 ) according to any one of the preceding claims wherein the blade body (2) material is stainless steel.
13. A turbomachine blade (1 ) according to claim 12 wherein the first layer (3) is selected so as to provide stainless steel corrosion resistance.
14. A turbomachine blade (1 ) according to any one of the preceding claims wherein a roughness of the first layer (3) is less than 2.3 micrometer.
15. A turbomachine blade (1 ) according to any one of the preceding claims wherein the first layer (3) is a braze tape or foil containing a matrix of braze alloy with an erosion resistant filler consisting of abrasive particles.
16. A turbomachine blade (1 ) according to claim 15 wherein the braze alloy is a Silver (Ag)-based alloy or an Aluminum (Al)-based alloy.
17. A turbomachine blade (1 ) according to any one of the preceding claims wherein the erosion resistant filler consists of one or more filler materials selected from the group consisting of AI2O3, WC and CrC.
18. A turbomachine blade (1 ) according to any one of the preceding claims wherein the filler content ranges from 60 to 90 Vol.-% of the first layer (3).
19. A turbomachine blade (1 ) according to any one of the preceding claims wherein sizes of the filler particles range from 10 to 30 micrometer.
20. A turbomachine blade (1 ) according to any one of the preceding claims wherein the first layer material is deposited by one or more techniques selected from HVOF (High Velocity Oxygen Fuel)-spraying technique, tape/foil brazing technique, CVD (Chemical Vapor Deposition) technique and laser cladding technique.
21. A turbomachine blade (1 ) according to any one of the preceding claims wherein the first layer (3) material is being deposited by HVOF (High Velocity Oxygen Fuel)-spraying technique, and the first layer (3) material consists of one or more materials selected from the group of stainless steel and nickel (Ni)-based alloys.
22. A turbomachine blade (1 ) according to any one of the preceding claims wherein the second layer (4) is a sacrificial slurry coating.
23. A turbomachine blade (1 ) according to claim 22 wherein the sacrificial slurry coating consists of a closely packed aluminum-filled chromate/phophate basecoat sealed with a chemically inert chromate/phosphate topcoat.
24. A turbomachine blade (1 ) according to any one of the preceding claims wherein a roughness of the sacrificial slurry coating is less than 1.6 micrometers.
25. A turbomachine blade (1 ) according to any one of the preceding claims wherein the blade (1 ) is a compressor blade.
26. A method of manufacturing a turbomachine blade comprising the steps of:
- providing a blade body (2);
- depositing an erosion and corrosion resistant first layer (3) on the blade body (2) so as to cover at least a corrosion critical area (5), in particular a leading edge area, of the blade body (2), followed by
- depositing a sacrificial second layer (4) over the first layer so as to cover at least the first layer.
27. A method according to claim 26 wherein the the first layer is deposited so as to cover the corrosion critical area of the blade body exclusively.
28. A method according to any one of claims 26 and 27 wherein the second layer is deposited so as to cover the blade body totally.
29. A method according to any one of claims 26 to 28 wherein the first layer material is deposited using one more deposition techniques selected from HVOF (High Velocity Oxygen Fuel)-spraying technique, tape/foil brazing technique, CVD (Chemical Vapor Deposition) technique and laser cladding technique.
30. A method according to any one of claims 26 to 28 wherein the first layer material is deposited using HVOF (High Velocity Oxygen Fuel)-spraying technique and the first layer material being selected from one or more selected from stainless steel and nickel (Ni)-based alloy.
EP08717723.4A 2007-03-27 2008-03-13 Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same Active EP2129812B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102007015310 2007-03-27
US11/765,599 US8113787B2 (en) 2007-06-20 2007-06-20 Turbomachine blade with erosion and corrosion protective coating and method of manufacturing
PCT/EP2008/052979 WO2008116757A2 (en) 2007-03-27 2008-03-13 Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same

Publications (2)

Publication Number Publication Date
EP2129812A2 true EP2129812A2 (en) 2009-12-09
EP2129812B1 EP2129812B1 (en) 2013-04-17

Family

ID=39773189

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08717723.4A Active EP2129812B1 (en) 2007-03-27 2008-03-13 Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same

Country Status (3)

Country Link
EP (1) EP2129812B1 (en)
TW (1) TWI424117B (en)
WO (1) WO2008116757A2 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007031932A1 (en) * 2007-07-09 2009-01-15 Mtu Aero Engines Gmbh A blade
US20100226783A1 (en) * 2009-03-06 2010-09-09 General Electric Company Erosion and Corrosion Resistant Turbine Compressor Airfoil and Method of Making the Same
EP2767616A1 (en) 2013-02-15 2014-08-20 Alstom Technology Ltd Turbomachine component with an erosion and corrosion resistant coating system and method for manufacturing such a component
ITUB20152136A1 (en) * 2015-07-13 2017-01-13 Nuovo Pignone Srl TURBOMACCHINA PADDLE WITH PROTECTIVE STRUCTURE, TURBOMACCHINA, AND METHOD FOR FORMING A PROTECTIVE STRUCTURE
EP3165774A1 (en) * 2015-11-04 2017-05-10 Siemens Aktiengesellschaft Compressor with similar coating on compressor blades and compressor casing and gas turbine

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3951612A (en) * 1974-11-12 1976-04-20 Aerospace Materials Inc. Erosion resistant coatings
US4036602A (en) * 1975-11-26 1977-07-19 Chromalloy American Corporation Diffusion coating of magnesium in metal substrates
US4537632A (en) * 1983-10-19 1985-08-27 Sermatech International, Inc. Spherical aluminum particles in coatings
GB9006311D0 (en) * 1990-03-17 1990-05-16 Atomic Energy Authority Uk Surface protection of titanium
DK0451512T3 (en) * 1990-04-11 1993-12-27 Asea Brown Boveri Method of coating buckets
US5279649A (en) * 1992-06-01 1994-01-18 Solar Turbines Incorporated Coating composition and method of forming
CA2129874C (en) * 1993-09-03 1999-07-20 Richard M. Douglas Powder for use in thermal spraying
US5997604A (en) * 1998-06-26 1999-12-07 C. A. Patents, L.L.C. Coating tape
US20040124231A1 (en) * 1999-06-29 2004-07-01 Hasz Wayne Charles Method for coating a substrate
US6609894B2 (en) * 2001-06-26 2003-08-26 General Electric Company Airfoils with improved oxidation resistance and manufacture and repair thereof
US7186092B2 (en) * 2004-07-26 2007-03-06 General Electric Company Airfoil having improved impact and erosion resistance and method for preparing same
US20060115661A1 (en) * 2004-12-01 2006-06-01 General Electric Company Protection of thermal barrier coating by a sacrificial coating
GB0504576D0 (en) * 2005-03-05 2005-04-13 Alstom Technology Ltd Turbine blades and methods for depositing an erosion resistant coating on the same
US7601400B2 (en) * 2005-03-10 2009-10-13 General Electric Company Liquid electrostatic coating composition comprising corrosion resistant metal particulates and method for using same
US7435056B2 (en) * 2006-02-28 2008-10-14 Honeywell International Inc. Leading edge erosion protection for composite stator vanes

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008116757A2 *

Also Published As

Publication number Publication date
WO2008116757A2 (en) 2008-10-02
TW200909667A (en) 2009-03-01
WO2008116757A3 (en) 2009-01-15
TWI424117B (en) 2014-01-21
EP2129812B1 (en) 2013-04-17

Similar Documents

Publication Publication Date Title
US8113787B2 (en) Turbomachine blade with erosion and corrosion protective coating and method of manufacturing
CA2734605C (en) Erosion- and impact-resistant coatings
CN103993913B (en) There is turbine components and its manufacture method of anti-erosion and corrosion resistant coating system
EP1076158B1 (en) Gas turbine component having location-dependent protective coatings thereon
US9109279B2 (en) Method for coating a blade and blade of a gas turbine
US11859499B2 (en) Turbine clearance control coatings and method
EP1647612B1 (en) Coating system and method for vibrational damping of gas turbine engine airfoils
EP1995350B1 (en) High temperature component with thermal barrier coating
US20090324401A1 (en) Article having a protective coating and methods
RU2374075C2 (en) Wear-resistant protective coat and part with such coat
EP2471974B2 (en) Gas turbine component having thermal barrier coating and a gas turbine using the component
US20080014347A1 (en) Method for manufacturing a erosion preventative diamond-like coating for a turbine engine compressor blade
EP2088225A1 (en) Erosion and corrosion-resistant coating system and process therefor
US7229705B1 (en) Mischmetal oxide TBC
EP2149623A2 (en) Thermal barrier coatings and methods of producing same
EP2129812B1 (en) Turbomachine blade with erosion and corrosion protective coating and method of manufacturing the same
WO2013167312A1 (en) Airfoil arrangement with ptal bond coating and thermal barrier coating, and corresponding manufacturing method
JP2003041358A (en) Process for applying heat shielding coating system on metallic substrate
US10414694B2 (en) Toughened bond layer and method of production
JP2014520205A (en) Method for applying a protective layer, a part coated with a protective layer, and a gas turbine comprising such a part

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

17P Request for examination filed

Effective date: 20090918

AK Designated contracting states

Kind code of ref document: A2

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

17Q First examination report despatched

Effective date: 20100618

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIN1 Information on inventor provided before grant (corrected)

Inventor name: BARRIL, MARIE-GILLES

Inventor name: GRASSO, PIERO-DANIELE

Inventor name: STANKOWSKI, ALEXANDER

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 607375

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130515

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602008023881

Country of ref document: DE

Effective date: 20130613

REG Reference to a national code

Ref country code: AT

Ref legal event code: MK05

Ref document number: 607375

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130417

REG Reference to a national code

Ref country code: NL

Ref legal event code: T3

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130817

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130819

Ref country code: AT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130718

Ref country code: BE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130728

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130717

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130717

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

26N No opposition filed

Effective date: 20140120

REG Reference to a national code

Ref country code: HU

Ref legal event code: AG4A

Ref document number: E018728

Country of ref document: HU

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602008023881

Country of ref document: DE

Effective date: 20140120

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20140313

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20140313

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

REG Reference to a national code

Ref country code: CH

Ref legal event code: PFA

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD, CH

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130417

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602008023881

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 602008023881

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

REG Reference to a national code

Ref country code: HU

Ref legal event code: HC9C

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER(S): ALSTOM TECHNOLOGY LTD, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: HC

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH; CH

Free format text: DETAILS ASSIGNMENT: VERANDERING VAN EIGENAAR(S), VERANDERING VAN NAAM VAN DE EIGENAAR(S); FORMER OWNER NAME: ALSTOM TECHNOLOGY LTD

Effective date: 20161006

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: ALSTOM TECHNOLOGY LTD, CH

Effective date: 20161110

REG Reference to a national code

Ref country code: CH

Ref legal event code: PUE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: NL

Ref legal event code: PD

Owner name: ANSALDO ENERGIA IP UK LIMITED; GB

Free format text: DETAILS ASSIGNMENT: CHANGE OF OWNER(S), ASSIGNMENT; FORMER OWNER NAME: GENERAL ELECTRIC TECHNOLOGY GMBH

Effective date: 20170301

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20170322

Year of fee payment: 10

Ref country code: CH

Payment date: 20170322

Year of fee payment: 10

Ref country code: NL

Payment date: 20170321

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: HU

Payment date: 20170316

Year of fee payment: 10

Ref country code: GB

Payment date: 20170322

Year of fee payment: 10

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 602008023881

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20170824 AND 20170830

REG Reference to a national code

Ref country code: HU

Ref legal event code: GB9C

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER(S): ALSTOM TECHNOLOGY LTD, CH; GENERAL ELECTRIC TECHNOLOGY GMBH, CH

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Effective date: 20171221

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20180401

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20180313

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180314

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180313

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180331

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180331

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240321

Year of fee payment: 17

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240329

Year of fee payment: 17

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20240430