EP4153794A1 - Aube pour une turbomachine, ayant un blindage de pointe d'aube et une couche anti-érosion, et procédé de production de ladite aube - Google Patents

Aube pour une turbomachine, ayant un blindage de pointe d'aube et une couche anti-érosion, et procédé de production de ladite aube

Info

Publication number
EP4153794A1
EP4153794A1 EP21724560.4A EP21724560A EP4153794A1 EP 4153794 A1 EP4153794 A1 EP 4153794A1 EP 21724560 A EP21724560 A EP 21724560A EP 4153794 A1 EP4153794 A1 EP 4153794A1
Authority
EP
European Patent Office
Prior art keywords
layer
blade
blade tip
metal
erosion
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.)
Pending
Application number
EP21724560.4A
Other languages
German (de)
English (en)
Inventor
Thomas Uihlein
Ralf Stolle
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP4153794A1 publication Critical patent/EP4153794A1/fr
Pending legal-status Critical Current

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
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
    • C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • 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
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
    • C23C14/54—Controlling or regulating the coating process
    • C23C14/542—Controlling the film thickness or evaporation rate
    • 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
    • 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
    • C23C28/347—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 layers adapted for cutting tools or wear applications
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D15/00—Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires
    • C—CHEMISTRY; METALLURGY
    • C25—ELECTROLYTIC OR ELECTROPHORETIC PROCESSES; APPARATUS THEREFOR
    • C25D—PROCESSES FOR THE ELECTROLYTIC OR ELECTROPHORETIC PRODUCTION OF COATINGS; ELECTROFORMING; APPARATUS THEREFOR
    • C25D3/00—Electroplating: Baths therefor
    • C25D3/02—Electroplating: Baths therefor from solutions
    • C25D3/12—Electroplating: Baths therefor from solutions of nickel or cobalt
    • 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
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • 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

Definitions

  • the present invention relates to a blade for a turbomachine with a blade tip armor and an erosion protection layer as well as a method for producing a corresponding blade.
  • Turbomachines such as stationary gas turbines or aircraft engines, have, among other things, a large number of blades which are rotatably arranged on a rotor in order either to compress the fluid flowing through the turbomachine or to be driven to rotate by the fluid.
  • the gap between the blade tips at the radial end of the blades and the flow channel limitation must be as small as possible, so that as little fluid as possible passes through the gap between the flow channel limitation and Shovels can flow.
  • so-called labyrinth seals are provided in known turbomachines for sealing between the blade tips and the flow channel delimitation, in which the blade tips move in a groove which, when the flow machine is in operation, moves in a sealing material at the flow channel delimitation Forms grinding in the blade tips.
  • blade tip armourings on the blade tips which are made of a metal mat Rix have embedded hard material particles in order to cut the groove for the labyrinth seal in the opposite sealing material of the flow channel delimitation by means of the hard material particles and to protect the blade tip from wear.
  • the blades of turbomachines also have protective coatings on the blade, such as anti-erosion layers, in order to also protect the blade material in the area of the blade from wear, for example due to erosion.
  • the laid-open specification DE 10 2010 049 398 A1 discloses a wear-resistant and oxidation-resistant turbine blade which comprises an oxidation-resistant, metallic layer, in particular an MCrAlY layer, where M is a metal, in particular nickel, cobalt or a combination thereof , and which can also have a ceramic thermal barrier coating.
  • a protective layer of abrasive material and binding material applied by means of laser deposition welding is provided on the blade tip.
  • the oxidation-resistant protective layer in the form of the MCrAlY layer is applied over the entire surface of the blade.
  • the MCrAlY layer is removed again mechanically in the area of the blade tip and then the wear-resistant protective layer is applied to the blade tip in the area of the blade tip by means of laser deposition welding, so that there is a separate protective layer in the form of blade tip armor on the blade tip and a different protective layer on the blade.
  • the present invention proposes, contrary to the state of the art, not only to provide them with a blade tip armor made of a metal layer with embedded hard material particles, but a thin erosion protection layer over the blade tip armor in the area of the blade tip to be provided in the range from 5 ⁇ m to 100 ⁇ m, since it has been shown that when a thin erosion protection layer is arranged over a blade tip armor, the rubbing behavior of the blade on the flow channel can be improved and thus the efficiency with regard to the seal between the flow channel boundary and the blade can be improved and the wear of the blade can be reduced.
  • the gap between the blade and the flow channel boundary can be designed to be narrower, so that the efficiency of the turbomachine is increased.
  • the blade tip armor underneath is protected by the erosion protection layer and prevents it from being quickly eroded.
  • the corresponding layer thickness of the erosion protection layer ensures that the blade tip armoring with the hard material particles embedded therein can nevertheless perform its function, ie the layer thickness of the erosion protection layer selected according to the invention ensures that that the hard material particles can still develop their abrasive effect.
  • the layer thickness can preferably be selected in the range from 10 to 50 ⁇ m, particularly preferably from 15 to 35 ⁇ m, in order to achieve a particularly effective effect.
  • the protective layer system in the area of the blade tip can be implemented simply by successively depositing the blade tip cladding and the corrosion protection layer.
  • the blade tip armor with the erosion protection layer arranged above it is applied in the area of the blade tip, which is arranged opposite the blade root and has a blade tip surface which points in the direction of the flow channel boundary, the blade tip armor with the erosion protection layer above it being provided on the blade tip surface.
  • the layer thickness of the blade tip armouring or erosion layer runs in the radially outward direction (radial when considering the axis of rotation of the turbomachine), which runs from the blade root in the direction of the blade tip.
  • the blade can have no blade tip armor in the area of the blade but the erosion protection layer so that the erosion protection layer can extend continuously over the blade and the blade tip.
  • the erosion protection layer in the area of the blade can be made significantly thicker.
  • the blade tip armor can be formed by a nickel layer with embedded hard material particles or an MCrAlY layer with embedded hard material particles, where M of the MCrAlY layer is a metal, in particular nickel, cobalt or iron and the embedded hard material particles are boron nitride and preferably cubic boron nitride and / or oxides, in particular aluminum oxide, and / or carbides.
  • the erosion protection layer can be formed by different erosion protection layers, as they are for example in DE 102004 001 392 A1 and DE 102007 027335 A1 or the WO 2010094256 A1, the disclosure content of the cited documents being fully incorporated by reference.
  • the erosion protection layer can be formed from a metal layer and a ceramic layer or ceramic-containing layer, wherein the metal layer can also be a metal alloy layer. Such layers can then be arranged repeatedly in a layer stack.
  • the partial erosion protection system can also be formed from a four-layer system which comprises a metal layer, a metal alloy layer, a metal-ceramic mixed layer and a ceramic layer.
  • three-layer systems with, for example, a metal alloy layer, a metal-ceramic mixed layer and a ceramic layer are also possible. These layer sequences of 2, 3 or 4 layers can be provided several times in the partial erosion protection system.
  • the individual partial layers and in this case in particular the metal-ceramic mixed layer can also be designed as gradient layers in which the composition changes in the direction of the layer thickness.
  • metals can be used for the metal layer and the metal alloy layer, such as titanium, platinum, palladium, tungsten, chromium, nickel or cobalt for the metal layer, and also metallic elements such as iron, aluminum, zirconium, and hafnium for the metal alloy layer , Tantalum, magnesium, molybdenum or silicon.
  • the layer sequence of the partial erosion protection system can be formed by a nickel layer, a nickel-chromium layer, a metal-ceramic layer with chromium and nitrogen, with an excess of chromium, and a chromium-nitride layer.
  • a titanium layer, a palladium layer or a platinum layer, to which a TiCrAl or CoAlCr material is applied can also be provided as the first metallic layer.
  • CrAlNi-x or TiAlNi-x can be provided as the metal-ceramic mixed layer, with TiAlN, TiAlSiN, AlTiN or a mixture of TiN and A1N being provided as the ceramic layer.
  • a chromium layer can be provided as the metal layer, a chromium-nickel layer as the metal alloy layer and a CrAlN layer with an excess of chromium and aluminum as the metal-ceramic mixed layer, and a CrAlN layer as the ceramic layer.
  • additional diffusion barrier layers for example in the form of a CrN layer, can be used between partial layers of the erosion protection Layer be provided.
  • phase-stabilizing elements such as tungsten, tantalum,
  • Molybdenum, silicon, titanium, vanadium or yttrium can be provided.
  • the metal-ceramic mixed layer or ceramic layer or ceramic-containing layer of the erosion protection layer can be formed by oxides, nitrides, carbides or borides of the constituents of the metal layer or the metal alloy layer.
  • the blade can be made of a titanium-based material, an iron-based material, a nickel-based material or a cobalt-based material, in which case the iron-based material can include chromium-containing steels or iron-based superalloys and the nickel-based material can comprise nickel-based superalloys and the cobalt-based material cobalt-based superalloys.
  • Corresponding base materials or base alloys are those alloys whose main component comprises the corresponding element according to which the base alloy is designated, so that, for example, in the case of an iron-based alloy, the main component is iron.
  • known base materials can be used for rotor blades of turbomachines.
  • the blade tip armor can be applied by any suitable method, for example by galvanic deposition of, for example, a nickel matrix with embedded hard material particles such as boron nitride particles, or by soldering or by applying a layer of slip or by vapor phase separation or by spraying, in particular thermal or plasma-assisted spraying.
  • the invention relates to a method for producing a blade of a turbomachine, in particular a blade according to one of the preceding aspects, in which a blade tip armor is applied first to the blade tip and then an erosion protection layer is applied over the blade tip armor .
  • the erosion protection layer is preferably applied directly and firmly adhering to the matrix of the blade tip armor.
  • the erosion protection layer can be deposited by vapor phase deposition, in particular physical vapor deposition (PVD), in particular Special evaporation, arc evaporation, electron beam evaporation, atomization (sputtering) and / or magnetron sputtering can be used.
  • PVD physical vapor deposition
  • Special evaporation, arc evaporation, electron beam evaporation, atomization (sputtering) and / or magnetron sputtering can be used.
  • Figure 1 is a perspective view of a blade as it can be used in turbomachines
  • FIG. 2 shows a plan view of the blade tip of the blade according to FIG. 1 and in FIG.
  • FIG. 3 in the partial images a) to c) a part of a turbine blade in a sectional view after various method steps of the method according to the invention.
  • FIG. 1 shows, in a purely schematic manner, a perspective view of a blade as it can be used in a turbo machine, such as, for example, a stationary gas turbine or an aircraft engine.
  • the blade 1 has a blade root 2 which can be inserted into a disk that rotates with a shaft of the turbomachine.
  • the blade 1 also has a blade 3, which is arranged in the flow channel of the turbo machine and either compresses the fluid that flows through the turbo machine or is driven by the fluid flowing past.
  • a shroud 10 is arranged between the blade root 2 and the blade 3.
  • At the radially outer end of the vane 1 is what is known as the vane tip 4, which, in order to avoid flow losses, rests as closely as possible on a surrounding flow channel housing or even grinds into it.
  • a blade tip armor is provided on the blade tip 4 (see 3), which also has a cutting function, so that the blade tip 4 can cut into a surrounding flow channel housing or sealing material arranged thereon.
  • the blade tip armor can be formed by a coating with a nickel matrix 6 with embedded, cubic boron nitride particles 7.
  • FIG. 2 shows in a purely schematic representation a top view of the blade of FIG. 1. It becomes clear that the blade tip 4 has a blade tip surface facing away from the blade root, which in the example shown has a banana-shaped basic shape. According to the invention, a blade tip armor and an erosion protection layer are arranged on the blade tip surface.
  • FIG. 3 shows, in partial images a) to c), the various stages in the production of a blade 1 with a blade tip armor 5 and an erosion protection layer 11 on the blade tip 4.
  • Part of a blade 1 with the blade 3 and the blade tip 4 is shown in partial image a) of FIG.
  • a blade tip armor 5 is applied to the blade tip 4, which consists of a nickel matrix 6 and embedded hard material particles 7 made of cubic boron nitride.
  • the blade tip armor 5 is applied, for example, by galvanic deposition of the nickel matrix 6, in which the cubic boron nitride particles are embedded.
  • the blade tip armoring can, however, also take place in other suitable ways.
  • the erosion protection layer 11 is applied (see FIG. 3 c)), the hard material particles 7 embedded in the blade tip armor 5, which protrude from the blade tip armor 5, being built into the erosion protection layer. Since the anti-erosion layer 11 is so thin, for example 25 ⁇ m, that protruding hard material particles 7 are not completely absorbed into the anti-erosion layer 11, some of the hard material particles 7 can protrude over the anti-erosion layer 11 in order to create a groove for the hard material with the hard material particles Cut the labyrinth seal in the sealing material opposite the flow channel boundary.
  • the erosion protection layer 11 can be deposited by physical vapor phase deposition (PVD physical vapor deposition), in particular by various methods of vapor deposition or the application of the corresponding partial layers of the multi-layer erosion protection layer by sputtering.
  • PVD physical vapor deposition physical vapor phase deposition
  • the present invention has been described in detail on the basis of the exemplary embodiments, but rather that modifications are possible in such a way that individual features are omitted or other types of combinations of features are realized - can be illuminated without departing from the scope of protection of the attached claims.
  • the present disclosure includes all combinations of the individual features shown in the various exemplary embodiments, so that individual features that are only described in connection with one exemplary embodiment can also be used in other exemplary embodiments or combinations of individual features that are not explicitly shown.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Inorganic Chemistry (AREA)
  • Electrochemistry (AREA)
  • Ceramic Engineering (AREA)
  • Composite Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne une aube pour une turbomachine, l'aube ayant un blindage de pointe d'aube (5) sur sa pointe d'aube (4) et ayant une couche anti-érosion (11) sur le blindage de pointe d'aube. La couche anti-érosion de l'aube a, dans la région de la pointe d'aube, une épaisseur de couche comprise dans la plage allant de 5 à 100 µm, plus particulièrement de 10 à 50 µm.
EP21724560.4A 2020-05-18 2021-04-28 Aube pour une turbomachine, ayant un blindage de pointe d'aube et une couche anti-érosion, et procédé de production de ladite aube Pending EP4153794A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102020206202.1A DE102020206202A1 (de) 2020-05-18 2020-05-18 Schaufel für eine Strömungsmaschine mit Schaufelspitzenpanzerung und Erosionsschutzschicht und Verfahren zur Herstellung Derselben
PCT/DE2021/100387 WO2021233496A1 (fr) 2020-05-18 2021-04-28 Aube pour une turbomachine, ayant un blindage de pointe d'aube et une couche anti-érosion, et procédé de production de ladite aube

Publications (1)

Publication Number Publication Date
EP4153794A1 true EP4153794A1 (fr) 2023-03-29

Family

ID=75887794

Family Applications (1)

Application Number Title Priority Date Filing Date
EP21724560.4A Pending EP4153794A1 (fr) 2020-05-18 2021-04-28 Aube pour une turbomachine, ayant un blindage de pointe d'aube et une couche anti-érosion, et procédé de production de ladite aube

Country Status (4)

Country Link
US (1) US20230340884A1 (fr)
EP (1) EP4153794A1 (fr)
DE (1) DE102020206202A1 (fr)
WO (1) WO2021233496A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114150256B (zh) * 2021-12-14 2023-11-03 中国航发南方工业有限公司 航空发动机小尺寸涡轮工作叶片的耐高温热腐蚀涂层

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2002256808A (ja) * 2001-02-28 2002-09-11 Mitsubishi Heavy Ind Ltd 燃焼エンジン、ガスタービン及び研磨層
DE102004001392A1 (de) * 2004-01-09 2005-08-04 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung und Bauteil mit einer Verschleißschutzbeschichtung
DE102005030266A1 (de) * 2005-06-29 2007-01-18 Mtu Aero Engines Gmbh Schaufel einer Turbomaschine mit einer Schaufelspitzenpanzerung
DE102005060712A1 (de) * 2005-12-20 2007-06-21 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufelspitzenpanzerung
US20080102296A1 (en) 2006-10-26 2008-05-01 Farshad Ghasripoor Erosion resistant coatings and methods of making
DE102007027335A1 (de) 2007-06-14 2008-12-18 Mtu Aero Engines Gmbh Verschleißschutzbeschichtung und Bauteil mit einer Verschleißschutzbeschichtung
DE102009010110B4 (de) 2009-02-21 2014-08-28 MTU Aero Engines AG Erosionsschutz-Beschichtungssystem für Gasturbinenbauteile
US20100226783A1 (en) * 2009-03-06 2010-09-09 General Electric Company Erosion and Corrosion Resistant Turbine Compressor Airfoil and Method of Making the Same
EP2316988B1 (fr) 2009-11-02 2015-07-08 Alstom Technology Ltd Aube de turbine résistant à l'usure et à l'oxydation
DE102011101576A1 (de) * 2011-05-13 2012-11-15 Mtu Aero Engines Gmbh Kombinierte Erwärmung zum Auflöten einer Spitzenpanzerung mittels Induktion und Laser
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
DE102015208783A1 (de) * 2015-05-12 2016-11-17 MTU Aero Engines AG Abdeckverfahren zur Herstellung einer Kombination von Schaufelspitzenpanzerung und Erosionsschutzschicht
DE102015213555A1 (de) * 2015-07-20 2017-03-09 MTU Aero Engines AG Dichtrippenpanzerung und Verfahren zur Herstellung derselben
EP3246430B1 (fr) * 2016-05-20 2021-12-08 MTU Aero Engines AG Procédé de fabrication d'aubes ou de système d'aubes d'une turbomachine comprenant des couches de protection contre l'érosion et composant ainsi fabriqué

Also Published As

Publication number Publication date
DE102020206202A1 (de) 2021-11-18
WO2021233496A1 (fr) 2021-11-25
US20230340884A1 (en) 2023-10-26

Similar Documents

Publication Publication Date Title
EP1741876B1 (fr) Aube de turbomachine comprenant une extrémité blindée
DE112009002080B4 (de) Erosions- und schlagbeständiger Überzug, Gasturbinentriebwerkskomponente und Gasturbine mit diesem sowie Verfahren zum Abscheiden desselben
EP1123455B1 (fr) Produit pourvu d'une couche thermo-isolante et procede de realisation d'une couche thermo-isolante
DE102011056181A1 (de) Komponenten mit Kühlkanälen und Herstellungsverfahren
EP2458025B1 (fr) Alliage, couche de protection et composant
EP1707650A1 (fr) Matrice et système de couches
DE3401742A1 (de) Rotor einer axialstroemungsmaschine
DE102007050918A1 (de) Erosionsbeständige Beschichtung und Verfahren der Herstellung
EP1974071B1 (fr) Élément à disposer dans un canal d'écoulement d'une turbomachine et procédé de pulvérisation pour réaliser un revêtement
DE102007005755A1 (de) Vorrichtung zum Schutz von Bauteilen mit brennbarer Titanlegierung vor Titanfeuer und Verfahren zu deren Herstellung
EP1716965A1 (fr) Brasure comprenant de la poudre d'apport métallique sous forme élémentaire
DE102015208783A1 (de) Abdeckverfahren zur Herstellung einer Kombination von Schaufelspitzenpanzerung und Erosionsschutzschicht
EP2696033A1 (fr) Elément d'aube d'une turbomachine avec couche de compensation ductile, turbomachine associée, procédé de fabrication d'elément d'aube et de turbomachine
EP1929060A1 (fr) Procede de production d'une couche de protection, couche de protection et composant pourvu d'une couche de protection
EP3246430B1 (fr) Procédé de fabrication d'aubes ou de système d'aubes d'une turbomachine comprenant des couches de protection contre l'érosion et composant ainsi fabriqué
EP1798299B1 (fr) Alliage, couche de protection et élément de construction
EP4153794A1 (fr) Aube pour une turbomachine, ayant un blindage de pointe d'aube et une couche anti-érosion, et procédé de production de ladite aube
DE112009002430T5 (de) Verfahren zur Abscheidung einer Beschichtung auf eine Blisk
EP3093371B1 (fr) Combinaison de blindage d'extremite d'aubes et de couche de protection contre l'erosion et son procede de fabrication
EP1790743A1 (fr) Alliage, couche de protection et composant
WO2006103125A1 (fr) Systeme de couches et procede pour realiser un systeme de couches
EP1854899A1 (fr) Alliage, couche de protection et composant
EP2537959B1 (fr) Revêtement multicouches anti-usure et procédé de fabrication
DE112020001189T5 (de) Turbinenlaufschaufel und Kontaktoberflächenherstellungsverfahren
EP1892311B1 (fr) Aube de turbine avec une système de revêtement

Legal Events

Date Code Title Description
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: UNKNOWN

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

Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE

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

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20221103

AK Designated contracting states

Kind code of ref document: A1

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

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)