EP3572623A1 - Aube de turbine à double alliage fabriquée par fabrication additive de pulvérisation métallique - Google Patents

Aube de turbine à double alliage fabriquée par fabrication additive de pulvérisation métallique Download PDF

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Publication number
EP3572623A1
EP3572623A1 EP18174258.6A EP18174258A EP3572623A1 EP 3572623 A1 EP3572623 A1 EP 3572623A1 EP 18174258 A EP18174258 A EP 18174258A EP 3572623 A1 EP3572623 A1 EP 3572623A1
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EP
European Patent Office
Prior art keywords
alloy
content
turbine blade
root portion
cast
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.)
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Application number
EP18174258.6A
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German (de)
English (en)
Inventor
Geoffrey Marchant
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Siemens AG
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP18174258.6A priority Critical patent/EP3572623A1/fr
Publication of EP3572623A1 publication Critical patent/EP3572623A1/fr
Withdrawn legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • C23C24/00—Coating starting from inorganic powder
    • C23C24/02—Coating starting from inorganic powder by application of pressure only
    • C23C24/04—Impact or kinetic deposition of particles
    • 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
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/06—Metallic material
    • C23C4/08—Metallic material containing only metal elements
    • 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
    • C23C4/18—After-treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2230/312—Layer deposition by plasma spraying
    • 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
    • F05D2300/175—Superalloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures

Definitions

  • the present invention relates to turbine blades and methods of manufacturing the same.
  • the present invention relates to dual alloy turbine blades and processes for making these.
  • the present invention relates especially to the production of turbine blades having a high creep strength aerofoil section and a corrosion-resistant root section.
  • Turbines are useful for the extraction of electric power from the combustion of fuel, including gas and liquid fuels. Gas turbines are also useful for providing mechanical drive in the pumping of gas and oils. However, the operation of gas turbines exposes the turbine blades in the hot section of the gas turbine to mechanical stress and corrosive conditions.
  • the present invention may be used with land based gas turbines as well as with aero engines.
  • a turbine blade comprising an aerofoil portion and a root portion, the method comprising the steps of:
  • a turbine blade comprising a cast component of a first alloy composition comprising an aerofoil portion and a root portion, wherein the surface of the root portion is covered with a second alloy composition.
  • a gas turbine comprising at least one turbine blade according to the second aspect of the present invention.
  • step (a) involves providing a cast component of a first alloy composition.
  • the cast component may be produced using any suitable casting process. Such processes will be known to the person skilled in the art.
  • the cast component is produced using normal investment casting techniques.
  • the dimensions of the casting used in step (a) may be selected to ensure the root portion can accommodate a coating.
  • Step (a) may optionally involve shaping the cast root portion to generate a cast root portion of suitable dimensions.
  • the shaping comprises machining the cast root portion.
  • the first alloy composition may comprise any suitable turbine blade alloy.
  • turbine blade alloy we mean to refer to an alloy having chemical and physical properties rendering it suitable for use as a turbine blade. Turbine blade alloys will be known to the person skilled in the art.
  • the first alloy composition may be provided as an equiaxed, directionally solidified, or single crystal alloy.
  • the first alloy composition is preferably a nickel based low chromium alloy.
  • Suitable low chromium alloys comprise a majority of nickel and have a chromium content of less than 12 wt%.
  • the nickel based low chromium alloy has a chromium content of up to 10 wt%, preferably up to 9.5 wt%, more preferably up to 9 wt%.
  • the nickel based low chromium alloy has a chromium content of at least 1 wt%, suitably at least 2 wt%, preferably at least 3 wt%, more preferably at least 4 wt%, for example at least 5 wt%.
  • the nickel based low chromium alloy may optionally comprise one or more additional strengthening elements.
  • additional strengthening elements include aluminium, titanium, tantalum, tungsten, rhenium, molybdenum and cobalt.
  • Aluminium when present, is suitably included in the nickel based low chromium alloy in an amount of from 3 to 7 wt%, preferably 5 to 6 wt%.
  • Titanium when present, is suitably included in the nickel based low chromium alloy in an amount of from 0 to 4 wt%, preferably 0.5 to 1.5 wt%.
  • Tantalum when present, is suitably included in the nickel based low chromium alloy in an amount of from 1.5 to 12 wt%, preferably 1.5 to 7 wt%.
  • Tungsten when present, is suitably included in the nickel based low chromium alloy in an amount of from 4 to 12.5 wt%, preferably 4 to 9 wt%.
  • Rhenium when present, is suitably included in the nickel based low chromium alloy in an amount of from 3 to 7 wt%, preferably 3 to 6 wt%.
  • rhenium is absent.
  • Molybdenum when present, is suitably included in the nickel based low chromium alloy in an amount of from 0.05 to 6 wt%, preferably 0.2 to 2 wt%.
  • Cobalt when present, is suitably included in the nickel based low chromium alloy in an amount of from 5 to 12 wt%, preferably 6 to 11 wt%.
  • the low chromium alloy is a nickel based alloy having a chromium content of 5 to 10 wt%, an aluminium content of 3 to 7 wt%, a titanium content of 0 to 4 wt%, a tantalum content of 3 to 7 wt%, a tungsten content of 4 to 10 wt%, a rhenium content of 0 to 4 wt%, a molybdenum content of up to 6 wt%, and a cobalt content of 6 to 12 wt%.
  • Equiaxed and directionally solidified low chromium alloys may suitably comprise up to 0.2 wt% carbon and up to 0.03 wt% boron to facilitate carbide and/or boride strengthening phases in said alloys.
  • the tight control of these two elements i.e., 0.01 wt% maximum may be) necessary to prevent such phases forming.
  • Non-limiting examples of a low chromium equiaxed grain alloy include those sold under trade names MarM247 and CM247.
  • a non-limiting example of a low chromium directionally solidified alloy is CM247DS.
  • Non-limiting examples of a low chromium single crystal alloy include those sold under trade names CMSX4 and CMSX8. These materials are available from Cannon Muskegon Corp.
  • Step (b) of the method of the present invention involves applying a second alloy composition to the surface of the cast root portion provided in step (a) to provide an oversized root portion.
  • the second alloy composition is applied to at least a portion of the surface of the cast root portion.
  • the second alloy composition is applied to the majority of the surface of the cast root portion. More preferably the second alloy composition is applied to substantially all of the surface of the cast root portion such that entire surface of the cast root portion is covered by the second alloy composition.
  • the second alloy composition may be applied to the cast root portion using any suitable means. Such means will be known to the person skilled in the art.
  • the second alloy composition is applied to the cast root portion using a metal spray process.
  • Suitable metal spray processes include High Velocity Oxy-Fuel (HVOF), Low Pressure Plasma Spraying (LPPS), and Cold Spray. Other such processions will be known to the skilled person.
  • the second alloy composition may comprise any alloy having chemical or physical properties rendering it suitable for use as the surface of the root portion of a turbine blade. These chemical and physical properties include having relatively high fatigue strength and being resistant to the corrosive atmosphere of a gas turbine during operation.
  • the second alloy composition is preferably a nickel based high chromium alloy.
  • Suitable high chromium alloys comprise a majority of nickel and have a chromium content of more than 12 wt%.
  • the nickel based high chromium alloy has a chromium content of at least 13 wt%, for example at least 14 wt%. In some embodiments the nickel based high chromium alloy may have a chromium content of more than 16 wt%, for example more than 18 wt% or more than 20 wt%.
  • the nickel based high chromium alloy has a chromium content of up to 30 wt%, suitably up to 26 wt%, preferably up to 24 wt%.
  • the nickel based high chromium alloy may optionally comprise one or more additional elements.
  • Suitable additional elements include cobalt, aluminium, titanium, tantalum, tungsten, molybdenum and niobium.
  • Cobalt when present, is suitably included in the nickel based high chromium alloy in an amount of from 5 to 20 wt%. In such embodiments cobalt is present in an amount of from 7 to 10 wt%. In some embodiments cobalt is present in an amount of from 18 to 20 wt%.
  • Aluminium when present, is suitably included in the nickel based high chromium alloy in an amount of from 1 to 6 wt%, preferably 1 to 4 wt%.
  • Titanium when present, is suitably included in the nickel based high chromium alloy in an amount of from 0.1 to 5 wt%, preferably 3 to 4 wt%.
  • Tantalum when present, is suitably included in the nickel based high chromium alloy in an amount of from 0.5 to 4 wt%, preferably 1 to 2.5 wt%.
  • Tungsten when present, is suitably included in the nickel based high chromium alloy in an amount of from 1 to 7 wt%, preferably 1 to 4 wt%.
  • Molybdenum when present, is suitably included in the nickel based high chromium alloy in an amount of from 1 to 4 wt%, preferably 1 to 2.5 wt%.
  • Niobium when present, is suitably included in the nickel based high chromium alloy in an amount of from 0.1 to 5 wt%, preferably 0.5 to 2 wt%.
  • the high chromium alloy is a nickel based alloy having a chromium content of 12 to 23 wt%, a cobalt content of 8 to 20 wt%, an aluminium content of 1 to 6 wt%, a titanium content of 0 to 5 wt%, a tantalum content of 1 to 3 wt%, a tungsten content of 1 to 4 wt%, a molybdenum content of 1 to 4 wt%, and a niobium content of 0 to 2 wt%.
  • the nickel based high chromium alloy may suitably comprise up to 0.25 wt% carbon and up to 0.025 wt% boron to facilitate carbide and/or boride strengthening phases in the alloy.
  • the tight control of these carbon and boron together with control of zirconium content may help to ensure the best stability of the alloy.
  • Non-limiting examples of a nickel based high chromium alloy include those materials sold under the trade names IN939, IN6203DS, IN738LC, STAL15, STAL125, and IN792.
  • IN939, IN6203DS, IN738LC and IN792 are available from Special Metals Ltd.
  • STAL15 and STAL125 are available from Siemens pic.
  • the nickel based high chromium alloy is selected from IN939 and IN738LC.
  • the nickel based high chromium alloy is IN939.
  • Step (c) of the method of the present invention involves shaping the oversized root portion into the final desired root shape. This is suitably achieved by machining the oversized root portion.
  • the thickness of the second alloy composition on the surface of the cast root portion may allow some areas to be machined and other areas to be left as sprayed. Suitable machining techniques will be known to the skilled person in the art and include, for example, grinding, electrical discharge machining (EDM) and electrochemical machining (ECM).
  • the method of the first aspect of the invention further involves a step (d) of heat treating the shaped component provided in step (c).
  • Suitable heat treatments will depend on the specific alloy used. The selection of a suitable heat treatment step or steps will be within the competence of the person skilled in the art.
  • Step (d) is preferably carried out at a temperature high enough to cause diffusion bonding of first alloy composition and the second alloy composition and increase the strength of the interface.
  • one or more heat treatment steps may be carried out to increase the bulk strength of the cast and sprayed parts of the turbine blade.
  • heat treatment steps include a diffusion bonding cycle followed by a solution heat treatment and then precipitation or ageing cycles.
  • Heat treatments are suitably carried out in a vacuum or in a protective atmosphere.
  • temperatures for heat treatment may be 1100 to 1200°C, although in some cases temperatures of up to 1300°C may be used. Heat treatments are typically carried out for at least 2 to 4 hours.
  • the second alloy composition may be optionally subjected to hot isostatic pressing to increase density and thereby increase material properties such as fatigue strength.
  • the aerofoil portion of the turbine blade may suitably be provided with a protective coating.
  • Suitable protective coatings will be known to the person skilled in the art.
  • the protective coating is suitably applied to at least a portion of the surface of the cast aerofoil portion, preferably to the majority of the surface of the cast aerofoil portion, and more preferably to substantially all of the surface of the cast aerofoil portion.
  • the protective coating may be applied by any suitable means.
  • suitable means will be known to the person skilled in the art and include, for example, chemical vapour deposition (CVD), slurry spray processes and thermal spray processes. In some embodiments thermal spray processes are preferred.
  • the cast component of the turbine blade is covered by the second alloy composition around the root portion and the protective coating around the aerofoil portion such that the first alloy composition is not exposed in use to the operating atmosphere.
  • the turbine blades produced in accordance with the method of the present invention suitably have a high creep strength aerofoil portion and a high fatigue strength, corrosion resistant root portion.
  • the combination of traditional casting techniques and advanced metal spraying processes according to the present invention allow a turbine blade component to be manufactured with a high chromium alloy root surface (where fatigue and corrosion fatigue properties are important but creep less so) and a low chromium single crystal or directionally solidified alloy aerofoil (where creep strength is more important than fatigue).
  • a high chromium blade root resists corrosion related cracking in the high stressed area of the blade root on turbines operated in poor environments or with poor quality fuel.
  • the spraying process produces extremely fine grained microstructures that can give excellent tensile and fatigue properties and this is of great benefit in the root section of the blade where fatigue is often the life limiting factor.
  • Use of a spray process rather than a process such as welding or laser metal deposition avoids melting of the first alloy composition and potential dilution effects between the first alloy composition and second alloy composition. This can avoid shrinkage and cracking defects associated with welding processes.
  • High strength turbine blade alloys are difficult to weld without solidification cracking during welding or strain age cracking on post weld heat treatment.
  • Application of the second alloy composition by a metal spray process can avoid these defects.
  • a further advantage of using a spray process is that it can be carried out more quickly and at a lower cost than some alternative processes.
  • Figure 1 shows a cross-sectional view of a turbine blade at various stages of the manufacturing process according to the present invention.
  • a blade casting (1) is produced from a first alloy composition, for example by investment casting.
  • the initial surface shape of the cast root portion (2) can be provided directly by investment casting or machining of the investment casting.
  • a second alloy composition (3) is sprayed onto the cast root portion (2) to produce an oversized root portion having an outer surface (4).
  • the oversized root portion is machined to obtain a root portion having a finished shape (5).
  • a nickel based for chromium alloy is CM247DS. This has the following composition: Min Max Max Chromium 8.0 8.50 Silicon 0.03 Cobalt 9.0 9.50 Copper 0.005 Titanium 0.6 0.9 Bismuth 0.0001 Aluminum 5.45 5.75 Selenium 0.0005 Tungsten 9.3 9.7 Silver 0.0005 Tantalum 3.1 3.3 Lead 0.0005 Carbon 0.07 0.08 Vanadium 0.10 Hafnium 1.2 1.6 Sulfur 0.0005 Zirconium 0.005 0.02 Oxygen 0.0025 Boron 0.01 0.02 Iron 0.5 Molybdenum 0.4 0.6 Phosphorus 0.005 Nitrogen 0.005 Gallium 0.0015 Nickel Balance
  • a nickel based low chromium alloy is CMSX4. This has the following composition: Element Weight % Carbon 0.01 max Chromium 6.2 - 6.6 Cobalt 9.3 - 10.0 Tungsten 6.2 - 6.6 Niobium 0.1 max Tantalum 6.3 - 6.7 Hafnium 0.07 - 0.12 Titanium 0.9 - 1.1 Aluminum 5.45 - 5.75 Aluminum + Titanium 6.35 - 6.85 Rhenium 2.8 - 3.1 Zirconium 0.0075 max (75 ppm max) Boron 0.0025 max (25 ppm max) Nitrogen 0.001 max (10 ppm max) Sulphur 0.0005 max (5 ppm max) Phosphorus 0.003 max (30 ppm max) Iron 0.15 max Molybdenum 0.5 - 0.7 Silicon 0.04 max Manganese 0.01 max Copper 0.005 max (50 ppm max) Lead 0.0002 max (2 ppm max) Bismuth 0.00002 max (0.2 ppm max) Telluri
  • the second alloy composition a nickel based high chromium alloy is IN939.
  • This has the following composition: Element Percentage Carbon 0.13 - 0.17 Chromium 22.0 - 22.8 Cobalt 18.5 - 19.5 Tungsten 1.8 - 2.2 Niobium 0.9 - 1.1 Tantalum 1.3 - 1.5 Titanium 3.6 - 3.8 Aluminum 1.8 - 2.0 Zirconium 0.02 - 0.03 Iron 0.5 max Silicon 0.2 max Manganese 0.2 max Boron 0.004 - 0.006 (40 - 60 ppm) Sulphur 0.005 max (50 ppm max) Nitrogen 0.005 max (50 ppm max) Oxygen 0.002 max (20 ppm max) Silver 0.0005 max (5 ppm max) Selenium 0.0005 max (5 ppm max) Bismuth 0.00005 max (0.5 ppm max) Lead 0.00005 max (0.5 ppm max) Nickel BALANCE
  • the second alloy composition, a nickel based high chromium alloy is IN738LC.
  • This has the following composition: Minimum% Maximum% Carbon 0.09 0.13 Silicon - 0.30 Manganese - 0.20 Sulphur - 0.015 Phosphorous - 0.015 Cobalt 8.00 9.00 Copper - 0.10 Iron - 0.5 Chromium 15.70 16.30 Aluminum 3.20 3.70 Titanium 3.20 3.70 Molybdenum 1.50 2.00 Boron 0.007 0.012 Zirconium 0.03 0.08 Niobium 0.60 1.10 Tantalum 1.50 2.00 Tungsten 2.40 2.80 Aluminium + Titanium 6.50 7.20 Nickel Balance

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18174258.6A 2018-05-25 2018-05-25 Aube de turbine à double alliage fabriquée par fabrication additive de pulvérisation métallique Withdrawn EP3572623A1 (fr)

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EP18174258.6A EP3572623A1 (fr) 2018-05-25 2018-05-25 Aube de turbine à double alliage fabriquée par fabrication additive de pulvérisation métallique

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11662300B2 (en) 2019-09-19 2023-05-30 Westinghouse Electric Company Llc Apparatus for performing in-situ adhesion test of cold spray deposits and method of employing
US11898986B2 (en) 2012-10-10 2024-02-13 Westinghouse Electric Company Llc Systems and methods for steam generator tube analysis for detection of tube degradation
US11935662B2 (en) 2019-07-02 2024-03-19 Westinghouse Electric Company Llc Elongate SiC fuel elements
EP4389924A1 (fr) * 2022-12-19 2024-06-26 Siemens Energy Global GmbH & Co. KG Superalliage micro-allié et traitement thermique

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0367958A1 (fr) * 1988-11-10 1990-05-16 AlliedSignal Inc. Aube de turbine avec structure double
WO2000017490A2 (fr) * 1998-09-03 2000-03-30 Arnold James E Procedes de reparation et de remise aux normes d'ailettes de turbine a gaz
WO2007140805A1 (fr) * 2006-06-08 2007-12-13 Siemens Aktiengesellschaft Composants de turbine revêtus et procédé pour revêtir un composant de turbine
EP2876185A1 (fr) * 2013-11-21 2015-05-27 Siemens Aktiengesellschaft Article revêtu et procédé d'application d'un revêtement sur un article
EP3075880A1 (fr) * 2015-04-01 2016-10-05 Siemens Aktiengesellschaft Lame à double alliage

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0367958A1 (fr) * 1988-11-10 1990-05-16 AlliedSignal Inc. Aube de turbine avec structure double
WO2000017490A2 (fr) * 1998-09-03 2000-03-30 Arnold James E Procedes de reparation et de remise aux normes d'ailettes de turbine a gaz
WO2007140805A1 (fr) * 2006-06-08 2007-12-13 Siemens Aktiengesellschaft Composants de turbine revêtus et procédé pour revêtir un composant de turbine
EP2876185A1 (fr) * 2013-11-21 2015-05-27 Siemens Aktiengesellschaft Article revêtu et procédé d'application d'un revêtement sur un article
EP3075880A1 (fr) * 2015-04-01 2016-10-05 Siemens Aktiengesellschaft Lame à double alliage

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11898986B2 (en) 2012-10-10 2024-02-13 Westinghouse Electric Company Llc Systems and methods for steam generator tube analysis for detection of tube degradation
US11935662B2 (en) 2019-07-02 2024-03-19 Westinghouse Electric Company Llc Elongate SiC fuel elements
US11662300B2 (en) 2019-09-19 2023-05-30 Westinghouse Electric Company Llc Apparatus for performing in-situ adhesion test of cold spray deposits and method of employing
EP4389924A1 (fr) * 2022-12-19 2024-06-26 Siemens Energy Global GmbH & Co. KG Superalliage micro-allié et traitement thermique

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