EP2129812B1 - Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière - Google Patents

Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière Download PDF

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Publication number
EP2129812B1
EP2129812B1 EP08717723.4A EP08717723A EP2129812B1 EP 2129812 B1 EP2129812 B1 EP 2129812B1 EP 08717723 A EP08717723 A EP 08717723A EP 2129812 B1 EP2129812 B1 EP 2129812B1
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EP
European Patent Office
Prior art keywords
layer
blade body
erosion
blade
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.)
Active
Application number
EP08717723.4A
Other languages
German (de)
English (en)
Other versions
EP2129812A2 (fr
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/fr
Application granted granted Critical
Publication of EP2129812B1 publication Critical patent/EP2129812B1/fr
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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. 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.
  • 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.
  • 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 comprises 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 resistance 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 Al 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 the tape/foil brazing technique.
  • the second layer is a sacrificial slurry coating.
  • the sacrificial slurry coating for consists of a closely packed aluminum-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:
  • Deposition of the second layer may be effected using one or more standard spraying techniques.
  • the first layer is deposited on the base material by tape/foil brazing technique.
  • the first layer material is 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 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 11 that is bonded thereto.
  • the bilayer coating 11 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 resistance against water droplets or particles impacting on the leading edge 8 area 5.
  • 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 Al 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 11 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/phosphate basecoat that is sealed with a chemically inert chromate/phosphate topcoat on top of the basecoat (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 11 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 11.
  • 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).
  • first layer 3 On the base material tape/foil brazing technique is 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.
  • a corrosion protective bilayer coating 11 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.
  • Compressor blades with a bilayer structure of the present invention are reconditionable.

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

Claims (1)

  1. Procédé de fabrication d'une aube de turbomachine, le procédé comportant les étapes qui consistent à :
    prévoir un corps d'aube (2),
    utiliser une technique de brasage pour déposer sur le corps d'aube (2) une première couche (3) qui résiste à l'érosion et à la corrosion en recouvrant au moins une zone (5) critique vis-à-vis de la corrosion et en particulier une zone de bord d'attaque du corps d'aube (2),
    la technique de brasage utilisant un ruban ou une feuille de brasure contenant une matrice d'alliage de brasure dotée d'une charge constituée de particules abrasives résistant à l'érosion,
    avec ensuite
    le dépôt d'une deuxième couche sacrifiée (4) sur la première couche de manière à couvrir au moins la première couche (3), ladite deuxième couche (4) étant un revêtement sacrifié de suspension constitué d'un revêtement compact de base au chromate/phosphate chargé en aluminium, fermé hermétiquement par un revêtement supérieur chimiquement inerte au chromate/phosphate.
EP08717723.4A 2007-03-27 2008-03-13 Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière Active EP2129812B1 (fr)

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 (fr) 2007-03-27 2008-03-13 Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière

Publications (2)

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

Family

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Application Number Title Priority Date Filing Date
EP08717723.4A Active EP2129812B1 (fr) 2007-03-27 2008-03-13 Pale de turbomachine avec revêtement de protection contre l'érosion et la corrosion, et procédé de fabrication de cette dernière

Country Status (3)

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

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Publication number Priority date Publication date Assignee Title
DE102007031932A1 (de) * 2007-07-09 2009-01-15 Mtu Aero Engines Gmbh Turbomaschinenschaufel
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 (fr) 2013-02-15 2014-08-20 Alstom Technology Ltd Composant de turbomachine avec revêtement résistant à la corrosion et l'érosion, système et procédé de fabrication d'un tel composant
ITUB20152136A1 (it) * 2015-07-13 2017-01-13 Nuovo Pignone Srl Pala di turbomacchina con struttura protettiva, turbomacchina, e metodo per formare una struttura protettiva
EP3165774A1 (fr) * 2015-11-04 2017-05-10 Siemens Aktiengesellschaft Compresseur avec revêtement similaire sur des pales de compresseur et carter de compresseur et de turbine à gaz

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WO2006094935A1 (fr) * 2005-03-05 2006-09-14 Alstom Technology Ltd Aubes de turbine et procedes de depot sur celles-ci d'un revetement resistant a l'erosion

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US4036602A (en) * 1975-11-26 1977-07-19 Chromalloy American Corporation Diffusion coating of magnesium in metal substrates
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006094935A1 (fr) * 2005-03-05 2006-09-14 Alstom Technology Ltd Aubes de turbine et procedes de depot sur celles-ci d'un revetement resistant a l'erosion

Also Published As

Publication number Publication date
TWI424117B (zh) 2014-01-21
EP2129812A2 (fr) 2009-12-09
WO2008116757A3 (fr) 2009-01-15
TW200909667A (en) 2009-03-01
WO2008116757A2 (fr) 2008-10-02

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