EP3746640A1 - Aube de turbine comprenant une pointe de pale résistante à l'oxydation - Google Patents

Aube de turbine comprenant une pointe de pale résistante à l'oxydation

Info

Publication number
EP3746640A1
EP3746640A1 EP19707283.8A EP19707283A EP3746640A1 EP 3746640 A1 EP3746640 A1 EP 3746640A1 EP 19707283 A EP19707283 A EP 19707283A EP 3746640 A1 EP3746640 A1 EP 3746640A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine blade
turbine
tip
weight
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP19707283.8A
Other languages
German (de)
English (en)
Inventor
Christian Brunhuber
Bernd Burbaum
Roland Häbel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens 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
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP3746640A1 publication Critical patent/EP3746640A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/34—Laser welding for purposes other than joining
    • B23K26/342—Build-up welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P9/00—Treating or finishing surfaces mechanically, with or without calibrating, primarily to resist wear or impact, e.g. smoothing or roughening turbine blades or bearings; Features of such surfaces not otherwise provided for, their treatment being unspecified
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y10/00—Processes of additive manufacturing
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/021—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer
    • C23C28/022—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal alloy layer with at least one MCrAlX layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/028—Including graded layers in composition or in physical properties, e.g. density, porosity, grain size
    • 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
    • C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • 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
    • C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
    • C23C24/10—Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
    • C23C24/103—Coating with metallic material, i.e. metals or metal alloys, optionally comprising hard particles, e.g. oxides, carbides or nitrides
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/02—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material
    • C23C28/027—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings only including layers of metallic material including at least one metal matrix material comprising a mixture of at least two metals or metal phases or metal matrix composites, e.g. metal matrix with embedded inorganic hard particles, CERMET, MMC.
    • 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
    • C23C4/067—Metallic material containing free particles of non-metal elements, e.g. carbon, silicon, boron, phosphorus or arsenic
    • 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
    • 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
    • F05D2240/307—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 tip of a rotor blade

Definitions

  • the invention relates to a turbine blade whose blade blade has a base body made of a first material and an Schaufeliblattspitze of a second, oxidation-resistant material, and a method for producing the said turbine blade.
  • a first aspect of the invention relates to a turbine rotor fel for the rotor of a gas turbine, comprising a radially extending blade root from the blade root, comprising a base body comprising a first material and a blade tip comprising a second material, wherein the second material is more resistant to oxidation as the first material.
  • the material of the blade tip is not
  • the second material making up the blade tip comprises an MCrAlY alloy.
  • MCrAlY alloys M stands for Co and / or Ni
  • an MCrAlY alloy can be applied directly to the first material.
  • additive manufacturing methods such as laser welding, selective laser melting and selective electron beam melting.
  • the second material has the following chemical composition:
  • This MCrAlY alloy has in this composition by a particularly high temperature resistance, which is advantageous in terms of cutting the blade blade tip into an abradable coating of the turbine housing corresponding effect, and thus contributes to the prevention of gap losses. Forming certain desired phases in the second material is within the discretion and skill of those in the art.
  • alloy Alloy 247 (A247) is used as the first material of the turbine blade according to the invention.
  • the use of A247 is advantageous because it makes the second material in the composition described above excellent in attachment to A247.
  • A247 is a directionally solidified or stängelkristalli ner material.
  • other alloys may be used as the first material, wherein different crystal orientations may be present.
  • the composition of the second material is designed to be graded at least in partial regions.
  • the composition of the second At least in some areas gradually from the Anbin training area to the first material to the rubbing edge.
  • Un sub-sections are understood to be sections of the second material, that is, for example, an area that adjoins the transition between the first and second material or includes this.
  • a graded composition is advantageous if the metallic bond between the first and second materials is not sufficiently strong.
  • the second material is preferably more similar in its content to individual or all elements of the composition within the respective range of the first material.
  • the second material is graded in the region of the transition from the first material to the second material such that thermo-mechanical stresses between the first Materi al and the second material are compensated. Furthermore, it is particularly preferred if the material of the blade blade tip in the direction of the squeal edge, ie the end of the blade tip in the radial direction, increasingly oxidati onsresistente properties. Particularly in the area of the squealer is a high oxidation resistance of part before because particularly aggressive conditions attack the material of the blade tip.
  • the second material of the turbine blade according to the invention preferably has ceramic particles.
  • the ceramic particles advantageously increase the abrasion resistance of the second material.
  • the concentration of the ceramic particles in the second material may be uniform across the volume of the blade airfoils, or may be higher as an alternative to the squealer edge. More preferably, cubic boron nitride (cBN) or silicon carbide (SiC) or a combination of these materials is used as a ceramic additive without being limited thereto.
  • turbine blade complex structures for cooling.
  • the grazing complex cooling structures such as cooling channels
  • the provision of the complex structures is made possible in particular by the above-mentioned additive manufacturing processes.
  • the turbine blade according to the invention is preferably a rotor blade of a gas turbine.
  • the gas turbine is vorzugswei se used in a gas and steam power plant.
  • a second aspect of the invention relates to a method for producing a turbine blade according to the invention, comprising the steps:
  • the second material can be applied directly to the first material.
  • the method includes additive manufacturing methods, eg laser deposition welding, selective laser melting and selective electron beam melting.
  • the method can produce complex structures in the region of the blade tip, in particular in the squealer edge, which contribute to the cooling of the blade tip.
  • Complex structures are, for example, channels and holes, which are suitable for the passage of fluid media. It is therefore preferred if the manufacture of the airfoil tip complex cooling structures in the blade tip he testifies. Particularly preferably, the complex cooling structures are generated in the squealer.
  • the composition of the powdery two th material is gradually changed during the course of application.
  • This is especially the method of laser deposition welding, in which the material to be applied is carried on the surface of the underlying material under simultaneous melting.
  • Laser deposition welding is advantageous here because it allows the powder composition to be varied in-situ during the welding process. It is therefore further preferred if a laser beam is used as the high-energy beam.
  • the powdery second material Kera mikteilchen be admixed.
  • concentration of the ceramic particles in the second material can be uniform over the volume of the show blade tip, or alternatively be higher to the grazing edge by the powdery second material in the direction of the squealer a larger Men ge ceramic particles is added than in the area of the transition between first and second material.
  • cBN cubic boron nitride
  • SiC silicon carbide
  • FIGS. Show it Figure 1 shows an embodiment of a turbine according to the invention nenschaufel.
  • FIG. 2 shows an enlarged view of the blade tip of the turbine blade according to FIG. 1.
  • Figure 3 is a schematic representation of an apparatus for
  • Figure 4 is a flow diagram of an embodiment of the inventions to the invention process.
  • Fig. 1 shows a rotor blade 1 for a gas turbine according to an embodiment of the present invention.
  • the running blade 1 comprises, as shown, a radially extending blade 2 with a blade leaf base body 3 and a blade tip 4. Furthermore, the blade 1 comprises a blade platform 5 and a blade root 6 in fir-tree-shaped design.
  • the blade tip 4 At the radial end of the end of the blade 2 and thus the blade tip 4 forming end, the blade tip 4 has a squeal 7. At the grazing edge 7 extends along the peripheral wall and aligned on the outside with this.
  • the blade body 3 has a first material.
  • the first material of the blade body is in the execution example, the alloy A247.
  • the first mate rial may include other alloys or hen best of these.
  • the blade tip 4 and thus also the squeal edge 7 comprise a second material which is an alloy of the MCrA-1Y type.
  • the second material is an alloy having the composition Co: 22-26% by weight, Cr: 14-18% by weight, Al: 9.5-11.5% by weight, Y: 0.2-0.7% by weight, Re: 0.0-1.8% by weight, Ta: 0.0-1.7% by weight and the remainder nickel and random and unconfined avoidable impurities.
  • the second material may also comprise or be made of other alloys.
  • the MCrAlY material comprises ceramic particles 8 of cubic boron nitride (cBN), silicon carbide (SiC) or a combination thereof or alternatively also of another material as additives.
  • the material of the blade tip 4 is formed graded at least in part areas.
  • the proportions of the alloy components of the alloy described above are gra dierend changed so that they are in the region of the transition 9 between the first material and second material as small as possible differences in terms of thermal expansion coefficients and coefficients of thermal conductivity.
  • the oxidation resistance of the material is higher than in the region of the transition 9.
  • the oxidation resistance of the material of the blade tip 4 increases in the radial direction.
  • the material of the blade tip 4 can not be formed grading out.
  • the amount or concentration of the above-described ke ramischen particles 8 may be graded in the material of the blade blade tip 4 may be formed.
  • the concentration of the ceramic particles 8 in the area of the squealer edge 7 is higher than in the transition area 9 between the first and the second material.
  • the region of the blade tip 4 with the squeal edge 7 is shown in detail in FIG. In the area of the on grazing edge 7 ceramic particles 8 can be seen. At the grazing edge 7 is formed as a 3D body. In this case, complex structures are formed in the squealer 7, FITS in the form of cooling channels, the input or output holes 10 are shown in the surface of the squealer 7. These complex structures 10 are particularly with addi tive manufacturing processes such as laser welding or produce selective laser melting.
  • a device 20 which is shown in FIG. 3, is provided in a construction chamber familiar to the person skilled in the art.
  • the build chamber contains a nitrogen or inert gas atmosphere to counter Lucasein conclusions in the material of the blade 2.
  • the device 20 comprises a laser device 21, which is formed from, to generate a laser beam 22 or len from an external laser source to an object to be irradiated len.
  • the laser device 21 has components known to the person skilled in the art, such as e.g. Fiber optic cable and deflecting mirror on.
  • the La serstrahl 22 is passed through a feeder 24 to the region of the blade tip 4.
  • the feeder 24 is connected to a reservoir 25 containing the second material from which the blade tip is to be made, in powder form.
  • the powder is conveyed via a device for conveying material 26, to the feeder 24.
  • the feed device 24 is preferably formed as a nozzle to inject the powdery second material oritessüst on the surface of the already existing material of the blade tip 4 so that it is brought directly to the melting on a material layer by the laser directly on when.
  • the powdery second material is supported in Fig. 3 on a base body 3 of an airfoil 2 of a blade to produce the tip of the airfoil 4.
  • a powdered second material, which is different from the first material is conveyed in egg ner determined amount from the reservoir 25 through the device for conveying material 26 to the feeder 24.
  • the pulverför shaped material is applied to the first material of the base body 3 or the already applied and solidified second material of the blade tip 4.
  • a third step S3 the second material is melted by the action of the laser beam 22 and fused with the underlying material.
  • the steps S2 and S3 can be performed simultaneously, since the laser beam 22 is passed through the feed device 24 and the powdery material already melted at the moment of applying gene.
  • Step S4 the construction platform is lowered. Steps S1-S4 are repeated in a number as necessary to complete the tip of the airfoil.
  • the blade tip can be made by powder bed processes such as selective laser melting or selective electron beam melting.
  • powder bed processes such as selective laser melting or selective electron beam melting.
  • a corresponding construction chamber would be provided in which a powder layer can be applied to a formed Mate rial slaughter and certain areas are melted in this material layer by means of a Ener giesstrahls and then solidified, and this process is repeated layer by layer, until the component is completed.

Landscapes

  • 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)
  • Optics & Photonics (AREA)
  • Plasma & Fusion (AREA)
  • Composite Materials (AREA)
  • Ceramic Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Abstract

L'invention concerne une aube (1) de turbine pour le rotor d'une turbine à gaz, qui comprend une pale (2) s'étendant depuis un pied (6) d'aube dans une direction radiale. La pale comporte un corps de base (3) de pale comprenant un premier matériau et une pointe (4) de pale comprenant un deuxième matériau. Le deuxième matériau est plus résistant à l'oxydation que le premier matériau. La composition du deuxième matériau est réalisée au moins de manière graduée en des zones partielles. L'invention concerne par ailleurs un procédé pour fabriquer l'aube de turbine selon l'invention. Le procédé comprend les étapes suivantes consistant à : fournir un corps de base, comportant un premier matériau, d'une pale de turbine sur une plate-forme de construction d'un dispositif servant à exécuter un procédé additif ; appliquer un deuxième matériau pulvérulent, qui est différent du premier matériau, en une quantité définie ; faire fondre le matériau pulvérulent par l'action d'un rayon à haute énergie ; abaisser la plate-forme de construction. Les étapes de l'application et de la fusion du matériau pulvérulent ainsi que de l'abaissement de la plate-forme de construction sont répétées autant de fois que cela est nécessaire pour finaliser la pointe de la pale.
EP19707283.8A 2018-03-28 2019-02-13 Aube de turbine comprenant une pointe de pale résistante à l'oxydation Withdrawn EP3746640A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018204724.3A DE102018204724A1 (de) 2018-03-28 2018-03-28 Turbinenschaufel mit oxidationsresistenter Schaufelblattspitze
PCT/EP2019/053531 WO2019185231A1 (fr) 2018-03-28 2019-02-13 Aube de turbine comprenant une pointe de pale résistante à l'oxydation

Publications (1)

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EP3746640A1 true EP3746640A1 (fr) 2020-12-09

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EP19707283.8A Withdrawn EP3746640A1 (fr) 2018-03-28 2019-02-13 Aube de turbine comprenant une pointe de pale résistante à l'oxydation

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US (1) US11371366B2 (fr)
EP (1) EP3746640A1 (fr)
CN (1) CN112004992A (fr)
DE (1) DE102018204724A1 (fr)
WO (1) WO2019185231A1 (fr)

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US4589823A (en) * 1984-04-27 1986-05-20 General Electric Company Rotor blade tip
JP2002371803A (ja) 2001-06-13 2002-12-26 Mitsubishi Heavy Ind Ltd 動翼用耐摩耗層の形成方法、耐摩耗層及びその再生方法
US7316850B2 (en) * 2004-03-02 2008-01-08 Honeywell International Inc. Modified MCrAlY coatings on turbine blade tips with improved durability
US20070003416A1 (en) * 2005-06-30 2007-01-04 General Electric Company Niobium silicide-based turbine components, and related methods for laser deposition
EP2317078B2 (fr) 2009-11-02 2021-09-01 Ansaldo Energia IP UK Limited Aube de turbine abrasive monocristalline
US9121288B2 (en) 2012-05-04 2015-09-01 Siemens Energy, Inc. Turbine blade with tuned damping structure
US20130302166A1 (en) * 2012-05-09 2013-11-14 Ching-Pang Lee Turbine blade with chamfered squealer tip formed from multiple components and convective cooling holes
US9776282B2 (en) * 2012-10-08 2017-10-03 Siemens Energy, Inc. Laser additive manufacture of three-dimensional components containing multiple materials formed as integrated systems
EP2845924A1 (fr) 2013-09-10 2015-03-11 Siemens Aktiengesellschaft Système poreux de couches en céramique
EP3029113B1 (fr) * 2014-12-05 2018-03-07 Ansaldo Energia Switzerland AG Substrat revêtu abrasif et son procédé de fabrication

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US11371366B2 (en) 2022-06-28
CN112004992A (zh) 2020-11-27
DE102018204724A1 (de) 2019-10-02
US20210017866A1 (en) 2021-01-21
WO2019185231A1 (fr) 2019-10-03

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