EP2494085B1 - Method for producing an abradable coating on a turbomachine - Google Patents

Method for producing an abradable coating on a turbomachine Download PDF

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Publication number
EP2494085B1
EP2494085B1 EP20100798476 EP10798476A EP2494085B1 EP 2494085 B1 EP2494085 B1 EP 2494085B1 EP 20100798476 EP20100798476 EP 20100798476 EP 10798476 A EP10798476 A EP 10798476A EP 2494085 B1 EP2494085 B1 EP 2494085B1
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EP
European Patent Office
Prior art keywords
electrodes
turbomachine
lining
electrode
precursor layer
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Not-in-force
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EP20100798476
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German (de)
French (fr)
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EP2494085A1 (en
Inventor
Wolfgang Wachter
Manuel Hertter
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MTU Aero Engines AG
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MTU Aero Engines AG
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    • 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
    • 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
    • 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
    • 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
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • 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
    • C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
    • C23C4/131—Wire arc spraying
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the present invention relates to a method for producing an inlet lining on a turbomachine, a component of a turbomachine and a turbomachine with an inlet lining.
  • Axial compressors and gas turbines such as used in gas turbine engines for aircraft or other mobile or stationary applications, typically include multiple stages with rotating blades and fixed vanes or stator vanes.
  • the rotor blades are rigidly connected to a rotor and rotate with it at high speed about an axis.
  • An essential feature of axial compressors and gas turbines are the pressure differences existing between the upstream side and the downstream side of each blade ring. Any pressure loss at the outer edge of a rotor blade ring or at the inner edge of a stator blade ring reduces the efficiency.
  • a sealing fin on the rotating component engages in a groove on the stationary component or vice versa.
  • the exact dimensions of the sealing fin and especially the groove are often not adjusted or created during production. Rather, for example, digs a hard material having a fin during an inlet operation of the turbomachine in an inlet lining and thus forms there the corresponding groove.
  • the inlet lining has to a material that can be easily removed.
  • Inlet linings are conventionally produced inter alia by flame spraying and plasma spraying.
  • a chemical reaction of the powdery material may occur in the hot flame.
  • the graphite may burn. This has a significant influence on the hardness of the layer produced, but is difficult to control or avoid. Overall, the flame spraying process caused considerable fluctuations in the thickness and other properties of the layer.
  • An object of the present invention is to provide an improved method for producing an inlet lining on a turbomachine, an improved component of a turbomachine and an improved turbomachine.
  • Various embodiments of the present invention are based on the idea to produce an inlet lining on a turbomachine or a component for a turbomachine by arc wire spraying.
  • the material of the inlet lining is removed by an arc between two electrodes of the electrodes and thrown by a gas stream on the surface to be coated.
  • An advantage of arc wire spraying is its relatively low cost for this application.
  • gas that need not contain oxygen to sustain a flame By choosing the gas that need not contain oxygen to sustain a flame, oxidation or other undesirable chemical reaction of the inlet facing material can still be prevented in the gas stream or even after deposition.
  • readily a mixture of several materials can be generated in a predetermined ratio by using electrodes with these materials in the desired ratio.
  • an inlet lining by means of arc wire spraying allows a significantly better reproducible result, in particular significantly better reproducible properties of the inlet lining, in comparison to some conventional methods.
  • the variation of the powder grain fraction and the resulting variation in hardness and other properties of the inlet lining can be substantially reduced.
  • a further advantage of generating an inlet covering by means of arc wire spraying is that the result, in particular the finished inlet lining, is considerably faster compared to some other methods. This, in turn, can simplify quality assurance and regulation of the process.
  • a material soluble in water or another predetermined solvent and a material insoluble in this predetermined solvent are simultaneously applied by electric arc wire spraying.
  • a material is also referred to as being soluble in a solvent, especially when it reacts with water or another predetermined solvent to form a compound which is soluble in the solvent. In the subsequent dissolution of the soluble material remain in the insoluble material pores, due to which the inlet lining is easy to remove.
  • an arc is generated between a first electrode having a first material and a second electrode having a second material.
  • a gas flow through the arc to the surface to be coated is created that entrains the first material and the second material from the arc and deposits it on the surface to form the inlet liner or a precursor layer of the inlet liner.
  • Each of the two electrodes can contain one of the two materials or both materials.
  • the first electrode has only a first material and the second electrode only a second material; or each of the two electrodes has both materials.
  • the first material is not soluble in a predetermined solvent - for example, water or an alcohol - while the second material is soluble in the predetermined solvent.
  • a predetermined solvent for example, water or an alcohol -
  • the solubilities of the first material and the second material differ significantly, for example by a factor of 10, 20, 50 or 100.
  • the layer produced as described is in this case a precursor layer of the inlet lining.
  • the second material is released from the precursor layer to yield a porous structure that is only or substantially only comprising the first material and forms the inlet liner.
  • the first material includes nickel.
  • the second material includes Al2OSn. Both the first material and the second material may further comprise additives, for example graphite, polyester, bentonite, boron nitride or another ceramic, mineral or organic substance.
  • the present invention further comprises a component of a turbomachine and a turbomachine with an inlet lining produced as described above.
  • FIG. 1 shows a schematic representation of a gas turbine engine for mobile or stationary applications as an example of a turbomachine.
  • the gas turbine engine 10 includes a low pressure compressor 11, a high pressure compressor 12, a combustor 13, a high pressure turbine 14, and a low pressure turbine 15.
  • the gas turbine engine 10 includes a plurality of stator blade rings and a plurality of rotor blade rings. In FIG. 1 only one rotor blade ring 17 is shown.
  • a component 20 is arranged with an inlet lining 21, in which a in FIG. 1 not shown sealing fin on the outer periphery of the rotor blade ring 17 can dig to form a gap seal or a labyrinth seal.
  • the representation of the rotor blade ring 17, the component 20 and the inlet lining 21 in the region of the low-pressure compressor 11 is exemplary.
  • An arrangement of the inlet lining according to the invention in the region of the high-pressure compressor 12 or in another region of the gas turbine engine 10 is also possible.
  • FIG. 2 1 shows a schematic representation of a device for producing a precursor layer 22 of an inlet lining 21 on a component 20 of a gas turbine engine.
  • the device comprises a first electrode 31 and a second electrode 32.
  • Each of the two electrodes 31, 32 comprises a jacket 33 and a filling 34. In the context of a clear representation, these are provided with reference numerals only at the first electrode 31.
  • the jacket 33 is tubular in the illustrated example with a circular, square or rectangular cross-section and a central cavity. In the central cavity of the shell 33, the filling 34 is arranged.
  • the jacket 33 has a first material, the filling 34 has a second material. At least one of the two materials has an electrical conductivity.
  • the two electrodes 31, 32 each formed from a wire, wherein the first electrode 31, the first material and the second electrode 32, the second material. Further, one of the two electrodes 31, 32 as shown above, two materials and the other electrode have only one material.
  • each of the two electrodes 31, 32 is connected to a pole of an electrical power source 39.
  • the electric power source 39 is, for example, a DC or AC or DC or AC source.
  • the device for producing a precursor layer 22 of an inlet lining on a turbomachine further comprises a nozzle 41, which is directed onto the gap between the electrodes 31, 32.
  • An in FIG. 2 not shown, is designed to generate a gas flow 42, which is directed from the nozzle 41 to the gap between the electrodes 31, 32.
  • an arc 37 is generated between the electrodes 31, 32 by means of the electric power source 39.
  • the electrodes 31, 32 are consumed.
  • material is melted or vaporized by the arc 37 at the ends of the electrodes 31, 32.
  • the arc 37 contains material of the electrodes 31, 32 in partially ionized atomic or molecular form or in the form of partially ionized atomic clusters, particles or droplets. This material is partially entrained by the gas flow exiting the nozzle 41.
  • the result is a coating stream of material of the electrodes 31, 32.
  • the gas stream thus hurls the material removed from the arc 37 of the electrodes 31, 32 onto the component 20 or the substrate to be coated.
  • the coating stream 47 strikes the component 20 and generates there the precursor layer 22 of an inlet lining. If oxidation of the materials of the electrodes 31, 32 in the arc 37 in the coating stream 47 and / or in the inlet lining 21 is to be avoided, the gas stream 42 may be oxygen-poor or oxygen-free, inert or reducing.
  • the composition of the precursor layer 22 on the component 20 is determined by the composition of the electrodes 31, 32. Both electrodes 31, 32 may have the same or different compositions of identical or different materials. Instead of the structure of each electrode 31, 32 shown in Figure 2 from a jacket 33 and a filling 34, one of the two electrodes 31, 32 or both electrodes 31, 32 have a homogeneous structure.
  • the first electrode 31 in the in FIG. 2 shown inhomogeneous structure or in a homogeneous structure has nickel.
  • the first electrode 31 may comprise a pure or metal-coated aggregate, for example graphite, polyester, bentonite, boron nitride or another ceramic, mineral or organic substance.
  • the mechanical properties of the aggregate are especially chosen so that it can easily be abraded or removed.
  • the second electrode 32 has Al 2 O s with a high solubility in water, acid, base or alcohol.
  • the precursor layer 22 is formed with the illustrated inhomogeneous thickness.
  • the precursor layer 22 can be produced with a homogeneous thickness or with a desired thickness profile.
  • the soluble material is released from the precursor layer by the action of the predetermined solvent. There remains a porous structure of the non-soluble material forming the inlet lining.
  • FIG. 3 shows a schematic flow diagram of a method for generating an inlet lining on a turbomachine. Although this method is also feasible on turbomachinery and with devices that differ from the above based on the Figures 1 and 2 are distinguished, reference numerals from the Figures 1 and 2 used by way of example to facilitate understanding.
  • a first step 101 an arc 37 is created between a first electrode 31 having a first material and a second electrode 32 having a second material.
  • a gas stream 42 is generated and directed from a nozzle 41 to the arc 37.
  • the gas stream entrains the first material and the second material from the arc 37 and deposits it on the surface to be coated to form a precursor layer 22.
  • the second material which is soluble in a predetermined solvent is dissolved out of the precursor layer 22 by the action of the predetermined solvent. There remains a porous structure of the first material forming the inlet lining 21.
  • the inlet lining 21 is produced, wherein the third step 103 is omitted.

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

Description

Verfahren zum Erzeugen eines Einlaufbelags an einer Strömungsmaschine. Ein ähnliches Verfahren wird in EP-A-0 361 709 offenbart.Method for producing an inlet lining on a turbomachine. A similar procedure is in EP-A-0 361 709 disclosed.

Die vorliegende Erfindung bezieht sich auf ein Verfahren zum Erzeugen eines Einlaufbelags an einer Strömungsmaschine, ein Bauteil einer Strömungsmaschine und eine Strömungsmaschine mit einem Einlaufbelag.The present invention relates to a method for producing an inlet lining on a turbomachine, a component of a turbomachine and a turbomachine with an inlet lining.

Axialverdichter und Gasturbinen, wie sie beispielsweise in Gasturbinentriebwerken für Luftfahrzeuge oder andere mobile oder stationäre Anwendungen verwendet werden, umfassen in der Regel mehrere Stufen mit rotierenden Laufschaufeln bzw. Rotorschaufeln und feststehenden Leitschaufeln bzw. Statorschaufeln. Die Rotorschaufeln sind mit einem Rotor starr verbunden und rotieren mit diesem mit hoher Drehzahl um eine Achse.Axial compressors and gas turbines, such as used in gas turbine engines for aircraft or other mobile or stationary applications, typically include multiple stages with rotating blades and fixed vanes or stator vanes. The rotor blades are rigidly connected to a rotor and rotate with it at high speed about an axis.

Ein wesentliches Merkmal von Axialverdichtern und Gasturbinen sind die Druckdifferenzen, die zwischen der stromaufwärtigen Seite und der stromabwärtigen Seite jedes Schaufelkranzes existieren. Jeder Druckverlust am äußeren Rand eines Rotorschaufelkranzes oder am inneren Rand eines Statorschaufelkranzes mindert den Wirkungsgrad.An essential feature of axial compressors and gas turbines are the pressure differences existing between the upstream side and the downstream side of each blade ring. Any pressure loss at the outer edge of a rotor blade ring or at the inner edge of a stator blade ring reduces the efficiency.

Aufgrund hoher Drehzahlen, teilweise hoher Temperaturen, radialer und axialer Auslenkungen, die aus Vibrationen und unterschiedlichen Ausdehnungskoeffizienten und Temperaturen der beteiligten Bauteile herrühren, werden überwiegend Labyrinthdichtungen bzw. Spaltdichtungen verwendet. Beispielsweise greift eine Dichtfinne am rotierenden Bauteil in eine Nut am ruhenden Bauteil ein oder umgekehrt.Due to high speeds, sometimes high temperatures, radial and axial deflections resulting from vibrations and different coefficients of expansion and temperatures of the components involved, mostly labyrinth seals or gap seals are used. For example, a sealing fin on the rotating component engages in a groove on the stationary component or vice versa.

Die genauen Abmessungen der Dichtfinne und vor allem der Nut werden oft nicht bereits bei der Fertigung eingestellt bzw. geschaffen. Vielmehr gräbt sich beispielsweise eine ein hartes Material aufweisende Finne während eines Einlaufvorgangs der Strömungsmaschine in einen Einlaufbelag ein und bildet so dort die korrespondierende Nut. Der Einlaufbelag weist dazu ein Material auf, das leicht abgetragen werden kann.The exact dimensions of the sealing fin and especially the groove are often not adjusted or created during production. Rather, for example, digs a hard material having a fin during an inlet operation of the turbomachine in an inlet lining and thus forms there the corresponding groove. The inlet lining has to a material that can be easily removed.

Einlaufbeläge werden herkömmlich unter anderem durch Flammspritzen und Plasmaspritzen erzeugt. Dabei kann jedoch in der heißen Flamme eine chemische Reaktion des pulverförmigen Materials auftreten. Beispielsweise kann beim Flammspritzen von Nickel und Graphit der Graphit verbrennen. Dies hat einen erheblichen Einfluss auf die Härte der erzeugten Schicht, ist jedoch schwer steuerbar oder vermeidbar. Insgesamt entstehen beim Flammspritzen prozessbedingt erhebliche Schwankungen in der Dicke und anderen Eigenschaften der Schicht.Inlet linings are conventionally produced inter alia by flame spraying and plasma spraying. However, a chemical reaction of the powdery material may occur in the hot flame. For example, during flame spraying of nickel and graphite, the graphite may burn. This has a significant influence on the hardness of the layer produced, but is difficult to control or avoid. Overall, the flame spraying process caused considerable fluctuations in the thickness and other properties of the layer.

Auch beim Plasmaspritzen ist eine genaue Steuerung bzw. Kontrolle aller Parameter erforderlich, um eine Härte des Einlaufbelags in einem gewünschten Bereich zu erhalten. Oft ist die -Beimischung von Polyester zum Pulver erforderlich. Das Polyester wird nach dem Beschichten in einem separaten Verfahrensschritt bei hoher Temperatur in einem Ofen ausgebrannt. Dies erzeugt erhebliche zusätzliche Kosten.Even in plasma spraying, precise control of all parameters is required to obtain a hardness of the inlet lining in a desired range. Often the blending of polyester to the powder is required. The polyester is burned off after coating in a separate process step at high temperature in an oven. This generates significant additional costs.

Eine Aufgabe der vorliegenden Erfindung besteht darin, ein verbessertes Verfahren zum Erzeugen eines Einlaufbelags an einer Strömungsmaschine, ein verbessertes Bauteil einer Strömungsmaschine und eine verbesserte Strömungsmaschine zu schaffen.An object of the present invention is to provide an improved method for producing an inlet lining on a turbomachine, an improved component of a turbomachine and an improved turbomachine.

Diese Aufgabe wird durch die Gegenstände der unabhängigen Ansprüche gelöst.This object is solved by the subject matters of the independent claims.

Weiterbildungen sind in den abhängigen Ansprüchen angegeben.Further developments are specified in the dependent claims.

Verschiedene Ausführungsformen der vorliegenden Erfindung beruhen auf der Idee, einen Einlaufbelag an einer Strömungsmaschine bzw. einem Bauteil für eine Strömungsmaschine durch Lichtbogendrahtspritzen zu erzeugen. Das Material des Einlaufbelags wird mit einem Lichtbogen zwischen zwei Elektroden von den Elektroden abgetragen und von einem Gasstrom auf die zu beschichtende Oberfläche geschleudert.Various embodiments of the present invention are based on the idea to produce an inlet lining on a turbomachine or a component for a turbomachine by arc wire spraying. The material of the inlet lining is removed by an arc between two electrodes of the electrodes and thrown by a gas stream on the surface to be coated.

Ein Vorteil des Lichtbogendrahtspritzens besteht in seinen gerade für diese Anwendung vergleichsweise geringen Kosten. Durch die Wahl des Gases, das keinen Sauerstoff zur Unterhaltung einer Flamme enthalten muss, kann eine Oxidation oder eine andere unerwünschte chemische Reaktion des den Einlaufbelag bildenden Materials noch im Gasstrom oder auch nach der Ablagerung verhindert werden. Ferner kann ohne Weiteres eine Mischung mehrerer Materialien in einem vorbestimmten Verhältnis erzeugt werden, indem Elektroden mit diesen Materialien im gewünschten Verhältnis verwendet werden.An advantage of arc wire spraying is its relatively low cost for this application. By choosing the gas that need not contain oxygen to sustain a flame, oxidation or other undesirable chemical reaction of the inlet facing material can still be prevented in the gas stream or even after deposition. Furthermore, readily a mixture of several materials can be generated in a predetermined ratio by using electrodes with these materials in the desired ratio.

Die Erzeugung eines Einlaufbelags mittels Lichtbogendrahtspritzens ermöglicht im Vergleich zu einigen herkömmlichen Verfahren ein deutlich besser reproduzierbares Ergebnis, insbesondere deutlich besser reproduzierbare Eigenschaften des Einlaufbelags. Beispielsweise kann die Variation der Pulverkornfraktion und die resultierende Variation der Härte und anderer Eigenschaften des Einlaufbelags wesentlich reduziert werden.The generation of an inlet lining by means of arc wire spraying allows a significantly better reproducible result, in particular significantly better reproducible properties of the inlet lining, in comparison to some conventional methods. For example, the variation of the powder grain fraction and the resulting variation in hardness and other properties of the inlet lining can be substantially reduced.

Ein weiterer Vorteil der Erzeugung eines Einlaufbelags mittels Lichtbogendrahtspritzens besteht darin, dass das Ergebnis, insbesondere der fertige Einlaufbelag, im Vergleich zu einigen anderen Verfahren erheblich schneller vorliegt. Dies wiederum kann die Qualitätssicherung und die Regelung des Prozesses vereinfachen.A further advantage of generating an inlet covering by means of arc wire spraying is that the result, in particular the finished inlet lining, is considerably faster compared to some other methods. This, in turn, can simplify quality assurance and regulation of the process.

Insbesondere werden ein in Wasser oder einem anderen vorbestimmten Lösungsmittel lösliches Material und ein in diesem vorbestimmten Lösungsmittel nicht lösliches Material gleichzeitig durch Lichtbogendrahtspritzen aufgetragen. Vorliegend wird ein Material insbesondere auch dann als löslich in einem Lösungsmittel bezeichnet, wenn es mit Wasser oder einem anderen vorbestimmten Lösungsmittel zu einer in dem Lösungsmittel löslichen Verbindung reagiert. Beim anschließenden Herauslösen des löslichen Materials verbleiben in dem unlöslichen Material Poren, aufgrund derer der Einlaufbelag leicht abtragbar ist.In particular, a material soluble in water or another predetermined solvent and a material insoluble in this predetermined solvent are simultaneously applied by electric arc wire spraying. In the present case, a material is also referred to as being soluble in a solvent, especially when it reacts with water or another predetermined solvent to form a compound which is soluble in the solvent. In the subsequent dissolution of the soluble material remain in the insoluble material pores, due to which the inlet lining is easy to remove.

Bei einem Verfahren zum Erzeugen eines Einlaufbelags an einer Oberfläche einer Strömungsmaschine wird ein Lichtbogen zwischen einer ersten Elektrode mit einem ersten Material und einer zweiten Elektrode mit einem zweiten Material erzeugt. Ein Gasstrom durch den Lichtbogen auf die zu beschichtende Oberfläche wird erzeugt, der das erste Material und das zweite Material aus dem Lichtbogen mitnimmt und auf der Oberfläche deponiert, um den Einlaufbelag oder eine Vorläuferschicht des Einlaufbelags zu bilden.In a method for producing an inlet lining on a surface of a turbomachine, an arc is generated between a first electrode having a first material and a second electrode having a second material. A gas flow through the arc to the surface to be coated is created that entrains the first material and the second material from the arc and deposits it on the surface to form the inlet liner or a precursor layer of the inlet liner.

Jede der beiden Elektroden kann eines der beiden Materialien oder beide Materialien enthalten. Beispielsweise weist die erste Elektrode nur ein erstes Material und die zweite Elektrode nur ein zweites Material auf; oder jede der beiden Elektroden weist beide Materialien auf.Each of the two electrodes can contain one of the two materials or both materials. For example, the first electrode has only a first material and the second electrode only a second material; or each of the two electrodes has both materials.

Insbesondere ist das erste Material in einem vorbestimmten Lösungsmittel - beispielsweise Wasser oder einem Alkohol - nicht löslich, während das zweite Material in dem vorbestimmten Lösungsmittel löslich ist. Dies schließt ein, dass die Löslichkeiten des ersten Materials und des zweiten Materials sich deutlich unterscheiden, beispielsweise um einen Faktor 10, 20, 50 oder 100. Die wie beschrieben erzeugte Schicht ist in diesem Fall eine Vorläuferschicht des Einlaufbelags. Bei Einwirkung des Lösungsmittels auf die Vorläuferschicht wird das zweite Material aus der Vorläuferschicht gelöst, um eine poröse Struktur zu erhalten, die nur noch oder im Wesentlichen nur noch das erste Material aufweist und den Einlaufbelag bildet.In particular, the first material is not soluble in a predetermined solvent - for example, water or an alcohol - while the second material is soluble in the predetermined solvent. This implies that the solubilities of the first material and the second material differ significantly, for example by a factor of 10, 20, 50 or 100. The layer produced as described is in this case a precursor layer of the inlet lining. Upon exposure of the precursor layer to the solvent, the second material is released from the precursor layer to yield a porous structure that is only or substantially only comprising the first material and forms the inlet liner.

Das erste Material umfasst Nickel. Das zweite Material umfasst Al2OSn. Sowohl das erste Material als auch das zweite Material kann ferner Zuschlagstoffe umfassen, beispielsweise Graphit, Polyester, Bentonit, Bornitrid oder einen anderen keramischen, mineralischen oder organischen Stoff.The first material includes nickel. The second material includes Al2OSn. Both the first material and the second material may further comprise additives, for example graphite, polyester, bentonite, boron nitride or another ceramic, mineral or organic substance.

Die vorliegende Erfindung umfasst ferner ein Bauteil einer Strömungsmaschine und eine Strömungsmaschine mit einem wie oben dargestellt erzeugten Einlaufbelag.The present invention further comprises a component of a turbomachine and a turbomachine with an inlet lining produced as described above.

Kurzbeschreibung der FigurenBrief description of the figures

Nachfolgend werden Ausführungsformen anhand der beigefügten Figuren näher erläutert. Es zeigen:

Figur 1
eine schematische Darstellung eines Gasturbinentriebwerks;
Figur 2
eine schematische Darstellung einer Vorrichtung zum Erzeugen eines Einlaufbelags an einem Gasturbinentriebwerk;
Figur 3
ein schematisches Flussdiagramm eines Verfahrens zum Erzeugen eines Einlaufbelags.
Embodiments will be explained in more detail with reference to the accompanying figures. Show it:
FIG. 1
a schematic representation of a gas turbine engine;
FIG. 2
a schematic representation of an apparatus for producing an inlet lining on a gas turbine engine;
FIG. 3
a schematic flow diagram of a method for generating an inlet pad.

Beschreibung der AusführungsformenDescription of the embodiments

Figur 1 zeigt eine schematische Darstellung eines Gasturbinentriebwerks für mobile oder stationäre Anwendungen als Beispiel einer Strömungsmaschine. Das Gasturbinentriebwerk 10 umfasst einen Niederdruckverdichter 11, einen Hochdruckverdichter 12, eine Brennkammer 13, eine Hochdruckturbine 14 und eine Niederdruckturbine 15. Das Gasturbinentriebwerk 10 weist mehrere Statorschaufelkränze und mehrere Rotorschaufelkränze auf. In Figur 1 ist davon nur ein Rotorschaufelkranz 17 dargestellt. Am äußeren Umfang des Rotorschaufelkranzes 17 ist ein Bauteil 20 mit einem Einlaufbelag 21 angeordnet, in dem sich eine in Figur 1 nicht dargestellte Dichtfinne am äußeren Umfang des Rotorschaufelkranzes 17 eingraben kann, um eine Spaltdichtung oder eine Labyrinthdichtung zu bilden. Die Darstellung des Rotorschaufelkranzes 17, des Bauteils 20 und des Einlaufbelags 21 im Bereich des Niederdruckverdichters 11 ist beispielhaft. Eine Anordnung des erfindungsgemäßen Einlaufbelags im Bereich des Hochdruckverdichters 12 oder in einem anderen Bereich des Gasturbinentriebwerks 10 ist ebenfalls möglich. FIG. 1 shows a schematic representation of a gas turbine engine for mobile or stationary applications as an example of a turbomachine. The gas turbine engine 10 includes a low pressure compressor 11, a high pressure compressor 12, a combustor 13, a high pressure turbine 14, and a low pressure turbine 15. The gas turbine engine 10 includes a plurality of stator blade rings and a plurality of rotor blade rings. In FIG. 1 only one rotor blade ring 17 is shown. On the outer circumference of the rotor blade ring 17, a component 20 is arranged with an inlet lining 21, in which a in FIG. 1 not shown sealing fin on the outer periphery of the rotor blade ring 17 can dig to form a gap seal or a labyrinth seal. The representation of the rotor blade ring 17, the component 20 and the inlet lining 21 in the region of the low-pressure compressor 11 is exemplary. An arrangement of the inlet lining according to the invention in the region of the high-pressure compressor 12 or in another region of the gas turbine engine 10 is also possible.

Figur 2 zeigt eine schematische Darstellung einer Vorrichtung zum Erzeugen einer Vorläuferschicht 22 eines Einlaufbelags 21 an einem Bauteil 20 eines Gasturbinentriebwerks. Die Vorrichtung umfasst eine erste Elektrode 31 und eine zweite Elektrode 32. Jede der beiden Elektroden 31, 32 umfasst einen Mantel 33 und eine Füllung 34. Im Sinne einer übersichtlichen Darstellung sind diese nur an der ersten Elektrode 31 mit Bezugszeichen versehen. FIG. 2 1 shows a schematic representation of a device for producing a precursor layer 22 of an inlet lining 21 on a component 20 of a gas turbine engine. The device comprises a first electrode 31 and a second electrode 32. Each of the two electrodes 31, 32 comprises a jacket 33 and a filling 34. In the context of a clear representation, these are provided with reference numerals only at the first electrode 31.

Der Mantel 33 ist bei dem dargestellten Beispiel rohrförmig mit einem kreisförmigen, quadratischen oder rechteckigen Querschnitt und einem zentralen Hohlraum. In dem zentralen Hohlraum des Mantels 33 ist die Füllung 34 angeordnet. Der Mantel 33 weist ein erstes Material auf, die Füllung 34 weist ein zweites Material auf. Zumindest eines der beiden Materialien weist eine elektrische Leitfähigkeit auf.The jacket 33 is tubular in the illustrated example with a circular, square or rectangular cross-section and a central cavity. In the central cavity of the shell 33, the filling 34 is arranged. The jacket 33 has a first material, the filling 34 has a second material. At least one of the two materials has an electrical conductivity.

Alternativ sind die beiden Elektroden 31, 32 aus je einem Draht gebildet, wobei die erste Elektrode 31 das erste Material und die zweite Elektrode 32 das zweite Material aufweist. Ferner kann eine der beiden Elektroden 31, 32 wie oben dargestellt zwei Materialien und die andere Elektrode nur ein Material aufweisen.Alternatively, the two electrodes 31, 32 each formed from a wire, wherein the first electrode 31, the first material and the second electrode 32, the second material. Further, one of the two electrodes 31, 32 as shown above, two materials and the other electrode have only one material.

Zur Erzeugung eines Lichtbogens 37 zwischen den beiden Elektroden 31, 32 ist jede der beiden Elektroden 31, 32 mit einem Pol einer elektrischen Leistungsquelle 39 verbunden. Die elektrische Leistungsquelle 39 ist beispielsweise eine Gleichspannungs- oder Wechselspannungs- oder Gleichstrom- oder Wechselstrom-Quelle.To generate an arc 37 between the two electrodes 31, 32, each of the two electrodes 31, 32 is connected to a pole of an electrical power source 39. The electric power source 39 is, for example, a DC or AC or DC or AC source.

Die Vorrichtung zum Erzeugen einer Vorläuferschicht 22 eines Einlaufbelags an einer Strömungsmaschine umfasst ferner eine Düse 41, die auf den Zwischenraum zwischen den Elektroden 31, 32 gerichtet ist. Eine in Figur 2 nicht dargestellte Einrichtung ist zur Erzeugung eines Gasstroms 42 ausgebildet, der von der Düse 41 auf den Zwischenraum zwischen den Elektroden 31, 32 gerichtet wird.The device for producing a precursor layer 22 of an inlet lining on a turbomachine further comprises a nozzle 41, which is directed onto the gap between the electrodes 31, 32. An in FIG. 2 not shown, is designed to generate a gas flow 42, which is directed from the nozzle 41 to the gap between the electrodes 31, 32.

Zur Erzeugung einer Vorläuferschicht 22 eines Einlaufbelags 21 an dem Bauteil 20 wird mittels der elektrischen Leistungsquelle 39 ein Lichtbogen 37 zwischen den Elektroden 31, 32 erzeugt. Durch den Lichtbogen 37 werden die Elektroden 31, 32 verbraucht. Insbesondere wird durch den Lichtbogen 37 an den Enden der Elektroden 31,32 Material abgeschmolzen oder verdampft. Der Lichtbogen 37 enthält Material der Elektroden 31, 32 in teilweise ionisierter atomarer oder molekularer Form oder in Form von teilweise ionisierten Atomclustern, Partikeln oder Tröpfchen. Dieses Material wird von dem aus der Düse 41 austretenden Gasstrom teilweise mitgenommen. Es entsteht ein Beschichtungsstrom aus Material der Elektroden 31, 32. Der Gasstrom schleudert also das vom Lichtbogen 37 abgetragene Material der Elektroden 31, 32 auf das Bauteil 20 bzw. das zu beschichtende Substrat. Der Beschichtungsstrom 47 trifft auf das Bauteil 20 und erzeugt dort die Vorläuferschicht 22 eines Einlaufbelags. Wenn eine Oxidation der Materialien der Elektroden 31, 32 im Lichtbogen 37 im Beschichtungsstrom 47 und/oder im Einlaufbelag 21 vermieden werden soll, kann der Gasstrom 42 sauerstoffarm oder sauerstofffrei, inert oder reduzierend sein.To generate a precursor layer 22 of an inlet lining 21 on the component 20, an arc 37 is generated between the electrodes 31, 32 by means of the electric power source 39. By the arc 37, the electrodes 31, 32 are consumed. In particular, material is melted or vaporized by the arc 37 at the ends of the electrodes 31, 32. The arc 37 contains material of the electrodes 31, 32 in partially ionized atomic or molecular form or in the form of partially ionized atomic clusters, particles or droplets. This material is partially entrained by the gas flow exiting the nozzle 41. The result is a coating stream of material of the electrodes 31, 32. The gas stream thus hurls the material removed from the arc 37 of the electrodes 31, 32 onto the component 20 or the substrate to be coated. The coating stream 47 strikes the component 20 and generates there the precursor layer 22 of an inlet lining. If oxidation of the materials of the electrodes 31, 32 in the arc 37 in the coating stream 47 and / or in the inlet lining 21 is to be avoided, the gas stream 42 may be oxygen-poor or oxygen-free, inert or reducing.

Die Zusammensetzung der Vorläuferschicht 22 am Bauteil 20 wird durch die Zusammensetzung der Elektroden 31, 32 bestimmt. Beide Elektroden 31, 32 können gleiche oder unterschiedliche Zusammensetzungen gleicher oder unterschiedlicher Materialien aufweisen. Anstelle des in Figur 2 dargestellten Aufbaus jeder Elektrode 31, 32 aus einem Mantel 33 und einer Füllung 34 können eine der beiden Elektroden 31, 32 oder beide Elektroden 31, 32 einen homogenen Aufbau aufweisen.The composition of the precursor layer 22 on the component 20 is determined by the composition of the electrodes 31, 32. Both electrodes 31, 32 may have the same or different compositions of identical or different materials. Instead of the structure of each electrode 31, 32 shown in Figure 2 from a jacket 33 and a filling 34, one of the two electrodes 31, 32 or both electrodes 31, 32 have a homogeneous structure.

Die erste Elektrode 31 in dem in Figur 2 dargestellten inhomogenen Aufbau oder in einem homogenen Aufbau weist Nickel auf. Ferner kann die erste Elektrode 31 einen reinen oder metallummantelten Zuschlagsstoff aufweisen, beispielsweise Graphit, Polyester, Bentonit, Bornitrid oder einen anderen keramischen, mineralischen oder organischen Stoff. Die mechanischen Eigenschaften des Zuschlagsstoffs sind insbesondere so gewählt, dass er leicht abgerieben bzw. abgetragen werden kann. Die zweite Elektrode 32 weist Al2OSn mit einer hohen Löslichkeit in Wasser, Säure, Base oder Alkohol auf.The first electrode 31 in the in FIG. 2 shown inhomogeneous structure or in a homogeneous structure has nickel. Furthermore, the first electrode 31 may comprise a pure or metal-coated aggregate, for example graphite, polyester, bentonite, boron nitride or another ceramic, mineral or organic substance. The mechanical properties of the aggregate are especially chosen so that it can easily be abraded or removed. The second electrode 32 has Al 2 O s with a high solubility in water, acid, base or alcohol.

Bei der in Figur 2 dargestellten Anordnung entsteht die Vorläuferschicht 22 mit der dargestellten inhomogenen Dicke. Durch eine laterale Bewegung des Bauteils und der Vorrichtung relativ zueinander kann die Vorläuferschicht 22 mit einer homogenen Dicke oder mit einem gewünschten Dickenprofil erzeugt werden.At the in FIG. 2 As shown arrangement, the precursor layer 22 is formed with the illustrated inhomogeneous thickness. By lateral movement of the component and the device relative to one another, the precursor layer 22 can be produced with a homogeneous thickness or with a desired thickness profile.

Nach dem Erzeugen der Vorläuferschicht 22 wird durch Einwirkung des vorbestimmten Lösungsmittels das lösliche Material aus der Vorläuferschicht gelöst. Es verbleibt eine poröse Struktur aus dem nicht-löslichen Material, die den Einlaufbelag bildet.After forming the precursor layer 22, the soluble material is released from the precursor layer by the action of the predetermined solvent. There remains a porous structure of the non-soluble material forming the inlet lining.

Figur 3 zeigt ein schematisches Flussdiagramm eines Verfahrens zum Erzeugen eines Einlaufbelags an einer Strömungsmaschine. Obwohl dieses Verfahren auch an Strömungsmaschinen und mit Vorrichtungen durchführbar ist, die sich von den oben anhand der Figuren 1 und 2 dargestellten unterscheiden, werden nachfolgend Bezugszeichen aus den Figuren 1 und 2 beispielhaft verwendet, um ein Verständnis zu erleichtern. FIG. 3 shows a schematic flow diagram of a method for generating an inlet lining on a turbomachine. Although this method is also feasible on turbomachinery and with devices that differ from the above based on the Figures 1 and 2 are distinguished, reference numerals from the Figures 1 and 2 used by way of example to facilitate understanding.

Bei einem ersten Schritt 101 wird ein Lichtbogen 37 zwischen einer ersten Elektrode 31 mit einem ersten Material und einer zweiten Elektrode 32 mit einem zweiten Material erzeugt. Bei einem zweiten Schritt 102 wird ein Gasstrom 42 erzeugt und von einer Düse 41 auf den Lichtbogen 37 gerichtet. Der Gasstrom nimmt das erste Material und das zweite Material aus dem Lichtbogen 37 mit und deponiert es auf der zu beschichtenden Oberfläche, um eine Vorläuferschicht 22 zu bilden. Bei einem dritten Schritt 103 wird das in einem vorbestimmten Lösungsmittel lösliche zweite Material durch Einwirkung des vorbestimmten Lösungsmittels auf die Vorläuferschicht 22 aus dieser gelöst. Es verbleibt eine poröse Struktur des ersten Materials, die den Einlaufbelag 21 bildet.In a first step 101, an arc 37 is created between a first electrode 31 having a first material and a second electrode 32 having a second material. In a second step 102, a gas stream 42 is generated and directed from a nozzle 41 to the arc 37. The gas stream entrains the first material and the second material from the arc 37 and deposits it on the surface to be coated to form a precursor layer 22. In a third step 103, the second material which is soluble in a predetermined solvent is dissolved out of the precursor layer 22 by the action of the predetermined solvent. There remains a porous structure of the first material forming the inlet lining 21.

Alternativ wird durch Ablagerung des Materials der Elektroden 31, 32 auf der zu beschichtenden Oberfläche unmittelbar der Einlaufbelag 21 erzeugt, wobei der dritte Schritt 103 entfällt.Alternatively, by depositing the material of the electrodes 31, 32 directly on the surface to be coated, the inlet lining 21 is produced, wherein the third step 103 is omitted.

Claims (7)

  1. Method to generate an abradable lining (21) on a surface of a continuous-flow machine (10), having the following steps:
    - generation (101) of an electric arc (37) between a first electrode (31) having a first material and a second electrode (32) having a second material;
    - generation (102) of a gas flow (42) through the electric arc (37) onto the surface which takes the first material and the second material from the electric arc (37) and deposits them on the surface in order to form the abradable lining (21) or a precursor layer (22) of the abradable lining (21),
    characterised in that the first material has nickel and the second material has Al20Sn.
  2. Method according to claim 1, in which both electrodes (31, 32) contain the first material and the second material.
  3. Method according to one of the preceding claims, in which the first material is not soluble in water or alcohol and the second material is soluble in water, alcohol, base or acid.
  4. Method according to one of the preceding claims, furthermore having the following step:
    - dissolution (103) of the second material from the precursor layer (22) of the abradable lining (21) by means of the predetermined solvent in order to obtain a porous structure of the first material which forms the abradable lining (21).
  5. Method according to one of the preceding claims, in which the first material furthermore comprises any one of graphite, polyester, bentonite, boron nitride or another ceramic, mineral or organic material.
  6. Component (20) of a continuous-flow machine (10) having an abradable lining (21) generated according to one of the preceding claims.
  7. Continuous-flow machine (10) having an abradable lining (21) generated according to one of the preceding claims.
EP20100798476 2009-10-31 2010-10-30 Method for producing an abradable coating on a turbomachine Not-in-force EP2494085B1 (en)

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DE102009051554A DE102009051554A1 (en) 2009-10-31 2009-10-31 Method for producing an inlet lining on a turbomachine
PCT/DE2010/001277 WO2011050792A1 (en) 2009-10-31 2010-10-30 Method for producing an abradable coating on a turbomachine

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US4027367A (en) * 1975-07-24 1977-06-07 Rondeau Henry S Spray bonding of nickel aluminum and nickel titanium alloys
US4396473A (en) * 1981-04-29 1983-08-02 Ppg Industries, Inc. Cathode prepared by electro arc spray metallization, electro arc spray metallization method of preparing a cathode, and electrolysis with a cathode prepared by electro arc spray metallization
US4764089A (en) * 1986-08-07 1988-08-16 Allied-Signal Inc. Abradable strain-tolerant ceramic coated turbine shroud
DE4130946C1 (en) * 1991-09-18 1992-09-03 Mtu Muenchen Gmbh
DE19716524C1 (en) * 1997-04-19 1998-08-20 Daimler Benz Aerospace Ag Method for producing a component with a cavity
DE19730008C1 (en) * 1997-07-12 1998-10-29 Mtu Muenchen Gmbh Sheathing for metallic engine component
US20020128151A1 (en) * 1998-05-01 2002-09-12 Michael P. Galligan Catalyst members having electric arc sprayed substrates and methods of making the same
DE10356953B4 (en) * 2003-12-05 2016-01-21 MTU Aero Engines AG Inlet lining for gas turbines and method for producing the same
DE102004043640B4 (en) * 2004-09-07 2006-12-14 Daimlerchrysler Ag Cylinder head gasket for light alloy crankcase
US8067711B2 (en) * 2005-07-14 2011-11-29 United Technologies Corporation Deposition apparatus and methods
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