EP2842662B1 - Armour plating for a blade tip for titanium blades - Google Patents

Armour plating for a blade tip for titanium blades Download PDF

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Publication number
EP2842662B1
EP2842662B1 EP13182800.6A EP13182800A EP2842662B1 EP 2842662 B1 EP2842662 B1 EP 2842662B1 EP 13182800 A EP13182800 A EP 13182800A EP 2842662 B1 EP2842662 B1 EP 2842662B1
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EP
European Patent Office
Prior art keywords
blade
armor
vol
slip
binder
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EP13182800.6A
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German (de)
French (fr)
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EP2842662A1 (en
Inventor
André Werner
Artur Schüle
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MTU Aero Engines AG
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MTU Aero Engines AG
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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/06—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of composite workpieces or articles from parts, e.g. to form tipped tools
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C32/00—Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
    • 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
    • C23C24/082—Coating starting from inorganic powder by application of heat or pressure and heat without intermediate formation of a liquid in the layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium

Definitions

  • the present invention relates to the manufacture of a blade armor for a blade of a turbomachine, the blade being formed from a titanium material. Furthermore, the invention relates to a corresponding blade of a turbomachine with blade armor.
  • rotor blades rotate at high rotational speed around a shaft that runs along the longitudinal axis of the turbomachine.
  • seals so-called, are located in the area of the blades on the inside of the housing "Outer air seals" are provided, on which the rotor blades can rub against the operating state of the turbomachine in order to avoid a possible gap through which working gas could flow.
  • armoring of the tips of the rotor blades is provided.
  • ceramic materials based on aluminum oxide or zirconium oxide and cubic boron nitride are usually used for this purpose, which are applied by thermal spray layers in the case of aluminum oxide or zirconium oxide or via electrodeposition or by soldering in the case of cubic boron nitride.
  • WO2010 / 094273 A2 describes a method for producing an integral turbine-blade-disk unit, a so-called blisks for the turbine area of a gas turbine, in which a balanced property profile for the blades or blade blades and the rotor disk can be set.
  • the invention proposes to create armor based on a silt, which can be applied in a simple manner to at least a partial area of a blade made of a titanium material.
  • the slip comprises at least one metallic powder and at least one binder, the metallic powder being formed from a material comprising M, Cr and A1, where M is at least one element which is selected from the group consisting of iron, nickel and Includes cobalt.
  • the slurry After the slurry has been applied, the slurry can be dried.
  • the slip After drying or immediately after application without drying, the slip can be fired, so that armor arises from the slip.
  • tip armoring can be produced on a blade tip using the method according to the invention.
  • the titanium material that forms the blade at least in the area of the armor can be a titanium-based alloy or a material based on titanium aluminides.
  • Titanium material is understood to mean a material whose largest component in the chemical composition is titanium. Accordingly, alloys based on titanium aluminides are also considered to be titanium materials, even if aluminum is used in the case of such alloys in the same order of magnitude as titanium can be contained in the material.
  • the titanium aluminides can be based on ⁇ -TiAl or ⁇ 2 -Ti 3 Al.
  • the binder can be a ceramic binder, for example based on polysiloxanes or polysilazanes.
  • Polysiloxanes are understood to mean chemical compounds in which the silicon atoms are connected to one another via an oxygen atom, it being possible for a large number of Si-O-Si compounds to be linked to one another.
  • Polysilazanes are compounds in which silicon and nitrogen atoms form the chemical backbone in an alternating arrangement.
  • the binder and the metallic powder can each make up about half the volume of the silt, the metallic powder being in a range from 20% by volume to 70% by volume, in particular 40% by volume to 60% by volume, while the binder can have 80 vol.% to 30 vol.%, in particular 60 vol.% to 40 vol.%.
  • the particle sizes of the metallic powder can be in the range from 1 ⁇ m to 50 ⁇ m, in particular 2 ⁇ m to 5 ⁇ m, the specified particle sizes being average particle sizes or absolute particle sizes.
  • the slurry can be applied by spraying, brushing, rolling and / or dipping the component to be coated into the slurry. Since the armouring may only be required in certain sub-areas of the blade of a turbomachine, the slip can accordingly only be applied in the areas of the blade in which the armor is necessary and should be present.
  • the slip After application, the slip can be air-dried for a period of 0.5 to 5 hours, in particular 1 to 3 hours, preferably 1 to 2 hours.
  • the slip can then be fired by locally heating the blade in the area of the applied slip or by completely heating the blade. However, firing is also possible immediately without drying.
  • the firing can take place in particular at a temperature of 450 ° C. to 750 ° C., in particular 600 ° C. to 700 ° C., preferably around 650 ° C. for 0.5 hours to 2 hours, preferably around one hour in air or an inert gas atmosphere.
  • Burning destroys and removes the organic constituents in the binder, resulting in a blade armor in which metallic particles of FeCrAl, NiCrAl or CoCrAl are present in the armor structure adjacent to ceramic constituents, the ceramic constituents comprising silicon-based, ceramic compounds .
  • the pyrolysis can only partially take place, so that only partially ceramic compounds and / or partially ceramic compounds are present, that is to say compounds which still contain binders.
  • the silicon-based ceramic or partially ceramic connections can comprise silicon oxide, silicon carbide, silicon nitride and / or mixed forms thereof.
  • a running-in process can also be provided, in which the blade in a turbomachine is exposed to the operating conditions for a certain duration and / or several intervals at at least one speed of the machine, so that the heat introduced into the blade results in a Can form reaction zone between the armor and the titanium material, which improves the adhesion of the armor to the titanium material.
  • the running-in process can be designed in such a way that a plurality of operating intervals are provided, separated from one another by operating pauses or operating times with idling speeds, in which the turbomachine is operated at different speeds, in particular increasing speeds.
  • the reaction zone created by the targeted running-in process also offers protection against the heat brought into the blade by friction during normal operation of the turbomachine and thus reduces the risk of ignition of a titanium fire by the grinding process.
  • the Fig. 1 shows a perspective view of a moving blade 1 according to the present invention.
  • the rotor blade 1 comprises an airfoil 2 and a blade root 3 with a shroud which can be arranged in a disk of a turbomachine.
  • armor 4 is provided on the airfoil tip, which in operation can rub against an engine seal, the so-called “outer air seal" of the surrounding housing. Accordingly should the armor 4 protect the blade 1 and in particular the blade 2 from wear and heat.
  • the armor 4 also protects against titanium fire ignition, which could occur in the case of a blade 1 with a blade leaf 2 made from a titanium material.
  • the Fig. 2 shows a partial cross section through the armor 4 at the blade tip of the blade 1.
  • the armor 4 is formed by a layer consisting of metallic and ceramic components.
  • the representation of the Fig. 2 the composition in the armor 4 is purely schematic and shows metallic components 7 and ceramic components 8 which come from a ceramic binder.
  • the armor 4 was produced by applying and firing a slip, the slip comprising metallic powder and a binder.
  • the metallic powder of the slip, which has been used to form the armor 4 is formed in the exemplary embodiment from a FeCrAl alloy which has iron, chromium and aluminum as main components in this order, wherein further alloy components can be contained.
  • the metallic particles of the FeCrAl alloy are embedded in the slip in a ceramic binder based on polysilazane, the metallic powder accounting for 50% by volume and the binder also accounting for 50% by volume of the slip.
  • the slip After the slip has been applied by brushing or rolling or spraying in the area of the blade tip, the slip has been dried for two hours in air at room temperature. After drying, the slip was fired by means of local heating of the blade tip, which was carried out inductively in the exemplary embodiment.
  • the firing parameters were chosen with a firing temperature of 650 ° C., a holding time of one hour and a surrounding inert gas atmosphere.
  • the organic components of the binder have been partially decomposed by the pyrolysis, so that 4 silicon carbides, silicon nitrides and silicon carbonitrides have formed as ceramic components of the armor.
  • the FeCrAl particles of the metallic powder are embedded in this partially ceramic matrix and together with the ceramic matrix form the armor 4.
  • the blade 1 was installed in a turbomachine and the turbomachine was operated to carry out a running-in process in which a reaction layer 5 has formed between the armor 4 and the titanium base material due to the heat input generated thereby.
  • the running-in process can take place, for example, by intermittent operation of the turbomachine at different speeds. For example, five to ten intervals or stages of operation at speeds can be carried out, the relative speeds of the blade tip to the rubbing surface of the surrounding housing of 100 m / s, 120 m / s, 140 m / s, 160 m / s, 180 m / s and 200 m / s correspond. Between each operating interval or each operating level, the turbomachine can be switched off and take a break in the range of three to five minutes, the machine also being able to be operated in idle mode between the operating intervals. Acceleration and deceleration can take place with changes in speed of 100 revolutions per minute (RPM / s).
  • RPM revolutions per minute
  • reaction zone 5 generated by the running-in process improves the adhesion of the armor 4 to the titanium material 6 and also helps to avoid a titanium fire.

Description

HINTERGRUND DER ERFINDUNGBACKGROUND OF THE INVENTION GEBIET DER ERFINDUNGFIELD OF THE INVENTION

Die vorliegende Erfindung betrifft die Herstellung einer Schaufelpanzerung für eine Schaufel einer Strömungsmaschine, wobei die Schaufel aus einem Titan - Werkstoff gebildet ist. Darüber hinaus betrifft die Erfindung eine entsprechende Schaufel einer Strömungsmaschine mit einer Schaufelpanzerung.The present invention relates to the manufacture of a blade armor for a blade of a turbomachine, the blade being formed from a titanium material. Furthermore, the invention relates to a corresponding blade of a turbomachine with blade armor.

STAND DER TECHNIKSTATE OF THE ART

Bei Strömungsmaschinen, wie stationären Gasturbinen oder Flugzeugtriebwerken, drehen sich Laufschaufeln mit hoher Drehgeschwindigkeit um eine Welle, die entlang der Längsachse der Strömungsmaschine verläuft. Um zu gewährleisten, dass zwischen den Schaufelspitzen der sich drehenden Laufschaufeln und einem umgebenden Gehäuse des Strömungskanals keine Wirkungsgradverluste auf Grund des Durchströmens des Arbeitsgases durch Spalte zwischen den Schaufelspitzen und dem umgebenden Gehäuse auftreten, sind im Bereich der Laufschaufeln an der Innenseite des Gehäuses Dichtungen, sogenannte "Outer-Air-Seals", vorgesehen, an denen die Laufschaufeln je nach Betriebszustand der Strömungsmaschine anstreifen können, um einen möglichen Spalt zu vermeiden, durch den Arbeitsgas durchströmen könnte. Entsprechend wird zur Vermeidung von Verschleiß und Wärmeeintrag auf Grund der Reibung zwischen Schaufelspitzen und Gehäuse eine Panzerung der Spitzen der Laufschaufeln vorgesehen.In turbomachines, such as stationary gas turbines or aircraft engines, rotor blades rotate at high rotational speed around a shaft that runs along the longitudinal axis of the turbomachine. In order to ensure that there are no efficiency losses between the blade tips of the rotating blades and a surrounding housing of the flow channel due to the flow of the working gas through gaps between the blade tips and the surrounding housing, seals, so-called, are located in the area of the blades on the inside of the housing "Outer air seals" are provided, on which the rotor blades can rub against the operating state of the turbomachine in order to avoid a possible gap through which working gas could flow. Correspondingly, in order to avoid wear and the introduction of heat due to the friction between the blade tips and the casing, armoring of the tips of the rotor blades is provided.

Im Stand der Technik werden hierzu üblicherweise keramische Werkstoffe auf Basis von Aluminiumoxid oder Zirkonoxid sowie kubischem Bornitrid verwendet, die durch thermische Spritzschichten im Fall von Aluminiumoxid oder Zirkonoxid oder über galvanische Abscheidung oder durch Auflöten im Falle von kubischem Bornitrid aufgebracht werden.In the prior art, ceramic materials based on aluminum oxide or zirconium oxide and cubic boron nitride are usually used for this purpose, which are applied by thermal spray layers in the case of aluminum oxide or zirconium oxide or via electrodeposition or by soldering in the case of cubic boron nitride.

Aus der US 6,409,795 B2 ist zudem das Aufbringen von Formteilen aus MCrAl(Y) - Legierungen bekannt, wobei M entweder Nickel, Kobalt oder Eisen ist. WO2010/094273 A2 beschreibt ein Verfahren zur Herstellung einer integralen Turbinen-Schaufel-Scheiben-Einheit, einer sog. Blisks für den Turbinenbereich einer Gasturbine, bei welchen ein ausgewogenes Eigenschaftsprofil für die Schaufeln bzw. Schaufelblätter und die Rotorscheibe einstellbar ist.From the US 6,409,795 B2 it is also known to apply moldings made from MCrAl (Y) alloys, where M is either nickel, cobalt or iron. WO2010 / 094273 A2 describes a method for producing an integral turbine-blade-disk unit, a so-called blisks for the turbine area of a gas turbine, in which a balanced property profile for the blades or blade blades and the rotor disk can be set.

Allerdings sind die im Stand der Technik bekannten Verfahren und Stoffe zur Aufbringung von Panzerungen an Laufschaufeln sehr aufwändig und insbesondere für Titan - Werkstoffe wenig geeignet, da bei Titan - Werkstoffen zudem das Problem der Titanfeuerentzündung besteht, das bei hohem Wärmeeintrag durch Reibung der Schaufelspitzen an der Gehäusedichtung entstehen kann und zusätzlich berücksichtigt werden muss.However, the methods and materials known in the prior art for applying armor to rotor blades are very complex and, in particular, not very suitable for titanium materials, since the problem of titanium fire ignition is also encountered with titanium materials exists that can arise at high heat input due to friction of the blade tips on the housing seal and must also be taken into account.

OFFENBARUNG DER ERFINDUNGDISCLOSURE OF THE INVENTION AUFGABE DER ERFINDUNGOBJECT OF THE INVENTION

Es ist deshalb Aufgabe der vorliegenden Erfindung, ein Verfahren zur Herstellung einer Panzerung an Schaufeln einer Strömungsmaschine bereitzustellen, welches eine einfache Herstellung der Panzerung bei gleichzeitig guter Verschleißbeständigkeit und entsprechend guten Anstreifeigenschaften ermöglicht und Schaufeln aus Titan - Werkstoffen zudem zuverlässig vor der Titanfeuerentzündung schützt.It is therefore an object of the present invention to provide a method for producing armor on blades of a turbomachine, which enables simple manufacture of the armor with good wear resistance and correspondingly good abrasion properties and also reliably protects blades made of titanium materials from the ignition of titanium.

TECHNISCHE LÖSUNGTECHNICAL SOLUTION

Diese Aufgabe wird gelöst durch ein Verfahren mit den Merkmalen des Anspruchs 1 sowie eine Schaufel für eine Strömungsmaschine mit den Merkmalen des Anspruchs 12. Vorteilhafte Ausgestaltungen sind Gegenstand der abhängigen Ansprüche.This object is achieved by a method with the features of claim 1 and a blade for a turbomachine with the features of claim 12. Advantageous refinements are the subject of the dependent claims.

Die Erfindung schlägt vor, eine Panzerung auf Basis eines Schlickes zu erstellen, welcher in einfacher Weise auf mindestens einen Teilbereich einer Schaufel aus einem Titan - Werkstoff aufgebracht werden kann.The invention proposes to create armor based on a silt, which can be applied in a simple manner to at least a partial area of a blade made of a titanium material.

Der Schlicker umfasst erfindungsgemäß mindestens ein metallisches Pulver und mindestens ein Bindemittel, wobei das metallische Pulver aus einem Werkstoff gebildet ist, der M, Cr und A1 umfasst, wobei M mindestens ein Element ist, das ausgewählt ist aus der Gruppe, die Eisen, Nickel und Kobalt umfasst.According to the invention, the slip comprises at least one metallic powder and at least one binder, the metallic powder being formed from a material comprising M, Cr and A1, where M is at least one element which is selected from the group consisting of iron, nickel and Includes cobalt.

Nach dem Aufbringen des Schlickes kann der Schlicker getrocknet werden.After the slurry has been applied, the slurry can be dried.

Nach dem Trocknen oder direkt nach dem Aufbringen ohne Trocknen kann der Schlicker gebrannt werden, sodass aus dem Schlicker eine Panzerung entsteht.After drying or immediately after application without drying, the slip can be fired, so that armor arises from the slip.

Insbesondere kann mit dem erfindungsgemäßen Verfahren eine Spitzenpanzerung an einer Laufschaufelspitze hergestellt werden.In particular, tip armoring can be produced on a blade tip using the method according to the invention.

Der Titan - Werkstoff, der zumindest im Bereich der Panzerung die Schaufel bildet, kann eine Titan - Basislegierung oder ein Werkstoff auf Basis von Titanaluminiden sein. Unter Titan - Werkstoff wird somit ein Werkstoff verstanden, dessen größter Bestandteil der chemischen Zusammensetzung Titan ist. Entsprechend werden auch Legierungen auf Basis von Titanaluminiden als Titan - Werkstoff angesehen, auch wenn bei derartigen Legierungen Aluminium in der gleichen Größenordnung wie Titan in dem Werkstoff enthalten sein kann. Insbesondere können die Titanaluminide auf γ - TiAl oder α2-Ti3Al basieren.The titanium material that forms the blade at least in the area of the armor can be a titanium-based alloy or a material based on titanium aluminides. Titanium material is understood to mean a material whose largest component in the chemical composition is titanium. Accordingly, alloys based on titanium aluminides are also considered to be titanium materials, even if aluminum is used in the case of such alloys in the same order of magnitude as titanium can be contained in the material. In particular, the titanium aluminides can be based on γ-TiAl or α 2 -Ti 3 Al.

Das Bindemittel kann ein keramischer Binder, beispielsweise auf der Basis von Polysiloxanen oder Polysilazanen sein. Unter Polysiloxanen werden chemische Verbindungen verstanden, bei denen die Siliziumatome über ein Sauerstoffatom miteinander verbunden sind, wobei eine Vielzahl von Si-O-Si-Verbindungen miteinander verkettet sein können. Unter Polysilazanen werden Verbindungen verstanden, in denen Silizium- und Stickstoffatome in alternierender Anordnung das chemische Grundgerüst bilden.The binder can be a ceramic binder, for example based on polysiloxanes or polysilazanes. Polysiloxanes are understood to mean chemical compounds in which the silicon atoms are connected to one another via an oxygen atom, it being possible for a large number of Si-O-Si compounds to be linked to one another. Polysilazanes are compounds in which silicon and nitrogen atoms form the chemical backbone in an alternating arrangement.

Das Bindemittel und das metallische Pulver können jeweils ca. die Hälfte des Volumens des Schlickes ausmachen, wobei das metallische Pulver in einem Bereich von 20 Vol.% bis 70 Vol.%, insbesondere 40 Vol.% bis 60 Vol.% liegen kann, während das Bindemittel 80 Vol.% bis 30 Vol.%, insbesondere 60 Vol.% bis 40 Vol.% aufweisen kann.The binder and the metallic powder can each make up about half the volume of the silt, the metallic powder being in a range from 20% by volume to 70% by volume, in particular 40% by volume to 60% by volume, while the binder can have 80 vol.% to 30 vol.%, in particular 60 vol.% to 40 vol.%.

Die Partikelgrößen des metallischen Pulvers können im Bereich von 1 µm bis 50 µm, insbesondere 2 µm bis 5 µm liegen, wobei die angegebenen Partikelgrößen mittlere Partikelgrößen oder absolute Partikelgrößen sein können.The particle sizes of the metallic powder can be in the range from 1 μm to 50 μm, in particular 2 μm to 5 μm, the specified particle sizes being average particle sizes or absolute particle sizes.

Das Aufbringen des Schlickes kann durch Spritzen, Streichen, Rollen und/oder Tauchen des zu beschichtenden Bauteils in den Schlicker erfolgen. Da die Panzerung unter Umständen lediglich in entsprechenden Teilbereichen der Schaufel einer Strömungsmaschine erforderlich sein kann, kann der Schlicker entsprechend nur in den Bereichen der Schaufel aufgebracht werden, in denen die Panzerung erforderlich ist und vorliegen soll.The slurry can be applied by spraying, brushing, rolling and / or dipping the component to be coated into the slurry. Since the armouring may only be required in certain sub-areas of the blade of a turbomachine, the slip can accordingly only be applied in the areas of the blade in which the armor is necessary and should be present.

Nach dem Aufbringen kann der Schlicker für eine Zeitspanne von 0,5 bis 5 Stunden, insbesondere 1 bis 3 Stunden, vorzugsweise 1 bis 2 Stunden, an Luft trocknen.After application, the slip can be air-dried for a period of 0.5 to 5 hours, in particular 1 to 3 hours, preferably 1 to 2 hours.

Anschließend kann ein Brennen des Schlickers durch lokale Erwärmung der Schaufel im Bereich des aufgebrachten Schlickers oder vollständiges Erhitzen der Schaufel erfolgen. Allerdings ist ein Brennen auch ohne vorheriges Trocknen unmittelbar möglich. Das Brennen kann insbesondere bei einer Temperatur von 450°C bis 750°C, insbesondere 600°C bis 700°C, vorzugsweise um 650°C für 0,5 Stunden bis 2 Stunden, vorzugsweise um eine Stunde an Luft oder Inertgasatmosphäre erfolgen. Durch das Brennen werden bei dem Bindemittel die organischen Bestandteile zerstört und entfernt, sodass sich eine Schaufelpanzerung ergibt, bei der metallische Partikel aus FeCrAl, NiCrAl oder CoCrAl benachbart zu keramischen Bestandteilen im Gefüge der Panzerung vorhanden sind, wobei die keramischen Bestandteile siliziumbasierte, keramische Verbindungen umfassen. Bei der gewählten Temperatur und/oder Zeitdauer kann die Pyrolyse nur teilweise ablaufen, so dass nur teilweise keramische Verbindungen und/oder teilkeramische Verbindungen vorliegen, also Verbindungen, die noch Bindemittel enthalten. Die siliziumbasierten keramischen oder teilkeramischen Verbindungen können Siliziumoxid, Siliziumkarbid, Siliziumnitrid und/oder Mischformen daraus umfassen.The slip can then be fired by locally heating the blade in the area of the applied slip or by completely heating the blade. However, firing is also possible immediately without drying. The firing can take place in particular at a temperature of 450 ° C. to 750 ° C., in particular 600 ° C. to 700 ° C., preferably around 650 ° C. for 0.5 hours to 2 hours, preferably around one hour in air or an inert gas atmosphere. Burning destroys and removes the organic constituents in the binder, resulting in a blade armor in which metallic particles of FeCrAl, NiCrAl or CoCrAl are present in the armor structure adjacent to ceramic constituents, the ceramic constituents comprising silicon-based, ceramic compounds . At the selected temperature and / or period of time, the pyrolysis can only partially take place, so that only partially ceramic compounds and / or partially ceramic compounds are present, that is to say compounds which still contain binders. The silicon-based ceramic or partially ceramic connections can comprise silicon oxide, silicon carbide, silicon nitride and / or mixed forms thereof.

Nach dem Brennen des Schlickers kann weiterhin ein Einlaufprozess vorgesehen sein, bei dem die Schaufel in einer Strömungsmaschine für eine bestimmte Dauer und/oder mehrere Intervalle bei mindestens einer Drehzahl der Maschine den Betriebsbedingungen ausgesetzt wird, sodass sich durch die dadurch in die Schaufel eingebrachte Wärme eine Reaktionszone zwischen der Panzerung und dem Titan - Werkstoff ausbilden kann, welche die Haftung der Panzerung an dem Titan - Werkstoff verbessert. Insbesondere kann der Einlaufprozess so gestaltet sein, dass mehrere, voneinander durch Betriebspausen oder Betriebszeiten mit Leerlauf - Drehzahlen getrennte Betriebsintervalle vorgesehen sind, bei denen die Strömungsmaschine mit unterschiedlichen Drehzahlen, insbesondere sich steigernden Drehzahlen betrieben wird. Die durch den gezielten Einlaufprozess entstandene Reaktionszone bietet zudem einen Schutz vor der im Normalbetrieb der Strömungsmaschine durch Reibung in die Laufschaufel eingebrachten Wärme und reduziert somit die Gefahr der Entzündung eines Titanfeuers durch den Reibprozess.After the slurry has burned, a running-in process can also be provided, in which the blade in a turbomachine is exposed to the operating conditions for a certain duration and / or several intervals at at least one speed of the machine, so that the heat introduced into the blade results in a Can form reaction zone between the armor and the titanium material, which improves the adhesion of the armor to the titanium material. In particular, the running-in process can be designed in such a way that a plurality of operating intervals are provided, separated from one another by operating pauses or operating times with idling speeds, in which the turbomachine is operated at different speeds, in particular increasing speeds. The reaction zone created by the targeted running-in process also offers protection against the heat brought into the blade by friction during normal operation of the turbomachine and thus reduces the risk of ignition of a titanium fire by the grinding process.

KURZBESCHREIBUNG DER FIGURENBRIEF DESCRIPTION OF THE FIGURES

Die beigefügten Zeichnungen zeigen in rein schematischer Weise in

Fig. 1
eine perspektivische Darstellung einer erfindungsgemäßen Schaufel; und in
Fig. 2
eine teilweise Schnittansicht durch einen Oberflächenbereich aus Fig. 1
The accompanying drawings show in a purely schematic manner in
Fig. 1
a perspective view of a blade according to the invention; and in
Fig. 2
a partial sectional view through a surface area Fig. 1

AUSFÜHRUNGSBEISPIELEXAMPLE EXAMPLE

Weitere Vorteile, Kennzeichen und Merkmale der vorliegenden Erfindung werden bei der nachfolgenden detaillierten Beschreibung eines Ausführungsbeispiels anhand der beigefügten Figuren deutlich. Allerdings ist die Erfindung nicht auf dieses Ausführungsbeispiel beschränkt.Further advantages, characteristics and features of the present invention will become clear in the following detailed description of an exemplary embodiment with reference to the attached figures. However, the invention is not restricted to this exemplary embodiment.

Die Fig. 1 zeigt eine perspektivische Darstellung einer Laufschaufel 1 gemäß der vorliegenden Erfindung. Die Laufschaufel 1 umfasst ein Schaufelblatt 2 und einen Schaufelfuß 3 mit einem Deckband, der in einer Scheibe einer Strömungsmaschine angeordnet werden kann. An dem dem Schaufelfuß 3 gegenüberliegenden Ende des Schaufelblatts 2 ist an der Schaufelspitze eine Panzerung 4 vorgesehen, welche im Betrieb an einer Triebwerksdichtung, dem sogenannten "Outer-Air-Seal" des umgebenden Gehäuses anstreifen kann. Entsprechend soll die Panzerung 4 die Schaufel 1 und insbesondere das Schaufelblatt 2 vor Verschleiß und Wärmeeintrag schützen.The Fig. 1 shows a perspective view of a moving blade 1 according to the present invention. The rotor blade 1 comprises an airfoil 2 and a blade root 3 with a shroud which can be arranged in a disk of a turbomachine. At the end of the airfoil 2 opposite the airfoil 3, armor 4 is provided on the airfoil tip, which in operation can rub against an engine seal, the so-called "outer air seal" of the surrounding housing. Accordingly should the armor 4 protect the blade 1 and in particular the blade 2 from wear and heat.

Da die Schaufel 1 zumindest im Bereich des Schaufelblatts 2 aus einem Titan - Werkstoff gebildet ist, schützt die Panzerung 4 auch vor einer Titanfeuerentzündung, welche bei einer Schaufel 1 mit einem Schaufelblatt 2 aus einem Titan-Werkstoff auftreten könnte.Since the blade 1 is formed from a titanium material at least in the area of the blade leaf 2, the armor 4 also protects against titanium fire ignition, which could occur in the case of a blade 1 with a blade leaf 2 made from a titanium material.

Die Fig. 2 zeigt einen teilweisen Querschnitt durch die Panzerung 4 an der Schaufelspitze der Schaufel 1. Die Panzerung 4 ist durch eine Schicht gebildet, welche aus metallischen und keramischen Bestandteilen besteht. Die Darstellung der Fig. 2 bezüglich der Zusammensetzung in der Panzerung 4 ist rein schematisch und zeigt metallische Bestandteile 7 sowie keramische Bestandteile 8, die von einem keramischen Bindemittel stammen.The Fig. 2 shows a partial cross section through the armor 4 at the blade tip of the blade 1. The armor 4 is formed by a layer consisting of metallic and ceramic components. The representation of the Fig. 2 the composition in the armor 4 is purely schematic and shows metallic components 7 and ceramic components 8 which come from a ceramic binder.

Bei dem gezeigten Ausführungsbeispiel ist die Panzerung 4 durch das Aufbringen und Brennen eines Schlickers hergestellt worden, wobei der Schlicker metallisches Pulver und ein Bindemittel umfasst. Das metallische Pulver des Schlickers, welcher zur Bildung der Panzerung 4 eingesetzt worden ist, ist in dem Ausführungsbeispiel aus einer FeCrAl - Legierung gebildet, die als Hauptbestandteile in dieser Reihenfolge Eisen, Chrom und Aluminium aufweist, wobei weitere Legierungsbestandteile enthalten sein können.In the exemplary embodiment shown, the armor 4 was produced by applying and firing a slip, the slip comprising metallic powder and a binder. The metallic powder of the slip, which has been used to form the armor 4, is formed in the exemplary embodiment from a FeCrAl alloy which has iron, chromium and aluminum as main components in this order, wherein further alloy components can be contained.

Die metallischen Partikel der FeCrAl - Legierung sind in dem Schlicker in einem keramischen Binder auf Basis von Polysilazan eingebettet, wobei das metallische Pulver 50 Vol.% und der Binder ebenfalls 50 Vol.% des Schlickers ausmachen.The metallic particles of the FeCrAl alloy are embedded in the slip in a ceramic binder based on polysilazane, the metallic powder accounting for 50% by volume and the binder also accounting for 50% by volume of the slip.

Nach dem Auftragen des Schlickers durch Streichen oder Rollen bzw. Spritzen im Bereich der Schaufelspitze ist der Schlicker getrocknet worden und zwar für zwei Stunden an Luft bei Raumtemperatur. Nach der Trocknung ist der Schlicker gebrannt worden und zwar mittels einer lokalen Erwärmung der Schaufelspitze, die im Ausführungsbeispiel induktiv durchgeführt worden ist. Die Brennparameter sind bei dem gezeigten Ausführungsbeispiel mit einer Brenntemperatur von 650°C, einer Haltedauer von einer Stunde und einer umgebenden Inertgasatmosphäre gewählt worden. Durch die Pyrolyse sind die organischen Bestandteile des Bindemittels teilzersetzt worden, sodass sich als keramische Bestandteile der Panzerung 4 Siliziumcarbide, Siliziumnitride und Siliziumcarbonitride gebildet haben. In diese teilkeramische Matrix sind die FeCrAl - Partikel des metallischen Pulvers eingelagert und bilden zusammen mit der keramischen Matrix die Panzerung 4.After the slip has been applied by brushing or rolling or spraying in the area of the blade tip, the slip has been dried for two hours in air at room temperature. After drying, the slip was fired by means of local heating of the blade tip, which was carried out inductively in the exemplary embodiment. In the exemplary embodiment shown, the firing parameters were chosen with a firing temperature of 650 ° C., a holding time of one hour and a surrounding inert gas atmosphere. The organic components of the binder have been partially decomposed by the pyrolysis, so that 4 silicon carbides, silicon nitrides and silicon carbonitrides have formed as ceramic components of the armor. The FeCrAl particles of the metallic powder are embedded in this partially ceramic matrix and together with the ceramic matrix form the armor 4.

Nach dem Brennen ist die Schaufel 1 in eine Strömungsmaschine eingebaut worden und die Strömungsmaschine ist betrieben worden, um einen Einlaufprozess durchzuführen, bei dem sich aufgrund des dadurch erzeugten Wärmeeintrags eine Reaktionsschicht 5 zwischen der Panzerung 4 und dem Titan-Grundwerkstoff ausgebildet hat.After firing, the blade 1 was installed in a turbomachine and the turbomachine was operated to carry out a running-in process in which a reaction layer 5 has formed between the armor 4 and the titanium base material due to the heat input generated thereby.

Der Einlaufprozess kann beispielsweise durch intervallartigen Betrieb der Strömungsmaschine mit unterschiedlichen Drehzahlen erfolgen. So können beispielsweise fünf bis zehn Intervalle bzw. Stufen des Betriebs bei Drehzahlen durchgeführt werden, die Relativgeschwindigkeiten der Schaufelspitze zu dem Anstreifbelag des umgebenden Gehäuses von 100 m/s, 120 m/s, 140 m/s, 160 m/s, 180 m/s und 200 m/s entsprechen. Zwischen jedem Betriebsintervall bzw. jede Betriebsstufe kann die Strömungsmaschine abgeschaltet werden und eine Betriebspause im Bereich von drei bis fünf Minuten einlegen, wobei die Maschine in den Zeiten zwischen den Betriebsintervallen auch im Leerlauf betrieben werden kann. Die Beschleunigung und Abbremsung kann mit Drehzahländerungen von 100 Umdrehungen/Minute pro Sekunde (RPM/s) erfolgen.The running-in process can take place, for example, by intermittent operation of the turbomachine at different speeds. For example, five to ten intervals or stages of operation at speeds can be carried out, the relative speeds of the blade tip to the rubbing surface of the surrounding housing of 100 m / s, 120 m / s, 140 m / s, 160 m / s, 180 m / s and 200 m / s correspond. Between each operating interval or each operating level, the turbomachine can be switched off and take a break in the range of three to five minutes, the machine also being able to be operated in idle mode between the operating intervals. Acceleration and deceleration can take place with changes in speed of 100 revolutions per minute (RPM / s).

Die durch den Einlaufprozess erzeugte Reaktionszone 5 bewirkt eine Verbesserung der Haftung der Panzerung 4 auf dem Titan - Werkstoff 6 und trägt zudem dazu bei einen Titanbrand zu vermeiden.The reaction zone 5 generated by the running-in process improves the adhesion of the armor 4 to the titanium material 6 and also helps to avoid a titanium fire.

Obwohl die vorliegende Erfindung anhand des Ausführungsbeispiels detailliert beschrieben worden ist, ist für den Fachmann selbstverständlich, dass die Erfindung nicht auf dieses Ausführungsbeispiel beschränkt ist, sondern dass vielmehr Abwandlungen in der Weise möglich sind, dass einzelne Merkmale weggelassen oder andersartige Kombinationen von Merkmalen verwirklicht werden, solange der Schutzbereich der beigefügten Ansprüche nicht verlassen wird. Die Offenbarung der Beschreibung schließt sämtliche Kombinationen der vorgestellten Einzelmerkmale mit ein.Although the present invention has been described in detail with reference to the exemplary embodiment, it is self-evident to the person skilled in the art that the invention is not restricted to this exemplary embodiment, but rather that modifications are possible in such a way that individual features are omitted or other combinations of features are realized, as long as the scope of the appended claims is not left. The disclosure of the description includes all combinations of the individual features presented.

Claims (14)

  1. Method for producing blade armor for a blade of a turbomachine, the blade having an airfoil, wherein the airfoil (2) is formed from a titanium material and the method comprises the following steps:
    - providing a blade;
    - providing a slip which comprises a metal powder and a binder, wherein the metal powder is formed from a material that comprises M, Cr and Al, wherein M is at least one element selected from the group comprising Fe, Ni and Co, wherein the binder is a ceramic binder;
    - applying the slip to a subregion of the airfoil (2);
    - drying and/or firing the slip to form armor (4).
  2. Method according to claim 1, characterized in that the method for producing tip armor (4) is used on a rotor blade (1).
  3. Method according to either of the preceding claims, characterized in that the titanium material is a Ti-based alloy or a material based on titanium aluminides.
  4. Method according to any of the preceding claims, characterized in that the binder is a polysiloxane or a polysilazane.
  5. Method according to any of the preceding claims, characterized in that the slip comprises 20 vol.% to 70 vol.%, in particular 40 vol.% to 60 vol.%, preferably approximately 50 vol.%, metal powder and 80 vol.% to 30 vol.%, in particular 60 vol.% to 40 vol.%, preferably approximately 50 vol.%, binder.
  6. Method according to any of the preceding claims, characterized in that the metal powder has particles having average particle sizes or absolute particle sizes in the range of from 1 µm to 50 µm, in particular 2 µm to 5 µm.
  7. Method according to any of the preceding claims, characterized in that the slip is applied by spraying, brushing, rolling and/or dipping.
  8. Method according to any of the preceding claims, characterized in that the drying process is carried out at room temperature for 0.5 h to 5 h, in particular 1 h to 3 h, preferably 1 h to 2 h, in air.
  9. Method according to any of the preceding claims, characterized in that the slip is fired by locally warming or completely heating the blade.
  10. Method according to any of the preceding claims, characterized in that the pyrolysis process is carried out at temperatures of from 450°C to 750°C, in particular 600°C to 700°C, preferably approximately 650°C, for 0.5 h to 2 h, preferably approximately 1 h, in an inert gas atmosphere.
  11. Method according to any of the preceding claims, characterized in that, after the firing process, an abrading process is carried out, in which the blade (1) in the turbomachine is subjected to the operating conditions at at least one speed of the machine for a specific duration and/or a plurality of intervals, such that a reaction zone (5) is formed between the armor (4) and the titanium material (6).
  12. Blade of a turbomachine having blade armor produced according to any of the preceding claims, the blade (1) being formed from a titanium material and the armor (4) being arranged at least in subregions of the blade on the titanium material, characterized in that the armor comprises metal components (7) and ceramic components (8), the metal components being formed from a material that comprises M, Cr and Al, M being at least one element selected from the group comprising Fe, Ni and Co, and the ceramic components comprising silicon-based ceramic compounds.
  13. Blade according to claim 12, characterized in that the silicon-based ceramic compounds comprise silicon oxide, silicon carbide, silicon nitride and/or hybrids thereof.
  14. Blade according to either claim 12 or claim 13, characterized in that a reaction zone (5) is formed between the armor (4) and the titanium material (6).
EP13182800.6A 2013-09-03 2013-09-03 Armour plating for a blade tip for titanium blades Active EP2842662B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13182800.6A EP2842662B1 (en) 2013-09-03 2013-09-03 Armour plating for a blade tip for titanium blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13182800.6A EP2842662B1 (en) 2013-09-03 2013-09-03 Armour plating for a blade tip for titanium blades

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DE102019202387A1 (en) 2019-02-21 2020-08-27 MTU Aero Engines AG Blade for a high-speed turbine stage with a single sealing element
DE102019202388A1 (en) * 2019-02-21 2020-08-27 MTU Aero Engines AG Shroudless blade for a high-speed turbine stage

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WO1997037800A1 (en) 1996-04-10 1997-10-16 Tmt Research Development, Inc. Coating methods, coating products and coated articles
DE19946650C2 (en) * 1999-09-29 2003-11-27 Mtu Aero Engines Gmbh Process for the production of armor for a metallic component
US20090098394A1 (en) * 2006-12-26 2009-04-16 General Electric Company Strain tolerant corrosion protecting coating and tape method of application
DE102009010109A1 (en) * 2009-02-21 2010-09-23 Mtu Aero Engines Gmbh Production of a turbine blisk with an oxidation or corrosion protection layer

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