EP1957756B1 - Method for manufacturing a run-in coating - Google Patents

Method for manufacturing a run-in coating Download PDF

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Publication number
EP1957756B1
EP1957756B1 EP06828577A EP06828577A EP1957756B1 EP 1957756 B1 EP1957756 B1 EP 1957756B1 EP 06828577 A EP06828577 A EP 06828577A EP 06828577 A EP06828577 A EP 06828577A EP 1957756 B1 EP1957756 B1 EP 1957756B1
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EP
European Patent Office
Prior art keywords
heat treatment
run
coating
temperature
process temperature
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Not-in-force
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EP06828577A
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German (de)
French (fr)
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EP1957756A1 (en
Inventor
Manfred A. DÄUBLER
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MTU Aero Engines AG
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MTU Aero Engines GmbH
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Publication of EP1957756A1 publication Critical patent/EP1957756A1/en
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Classifications

    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/18—After-treatment
    • 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
    • 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
    • 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
    • F05D2230/40—Heat treatment

Definitions

  • the invention relates to a method for producing an inlet lining according to the preamble of claim 1.
  • Turbomachines such as gas turbines, typically include a plurality of rotating blades and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a fixed housing.
  • sealing systems Particularly problematic in turbomachinery compliance with a minimum gap between the rotating blades and the fixed housing of a high pressure compressor. Namely high absolute temperatures and temperature gradients occur in high-pressure compressors, which makes it more difficult for the rotating blades to cling to the stationary housing. This is partly due to the fact that in compressor blades on shrouds, as used in turbine blades, is dispensed with.
  • the document US-A1-3,713,206 relates to a method for producing a metallic inlet lining on a metallic housing.
  • a nickel felt is soldered onto the housing and finally coated with chromium or chromium and aluminum.
  • the coating is carried out in conjunction with a heat treatment at temperatures of 800 ° C to 1100 ° C.
  • the document US-B1-6,383,658 protects coatings sprayed by the HVOF process whose adhesion to a substrate is enhanced by a diffusion-promoting heat treatment.
  • the document EP-A2-1 010 861 concerns an inlet lining including manufacturing process.
  • the thermally sprayed, shrinkable layer consists of aluminum and silicon with embedded plastic particles of methyl methacrylate as filler. By a heat treatment at least 274 ° C, a part of the plastic particles is evaporated and leaves pores in the inlet lining.
  • the document GB-A-2 397 307 refers to a method for producing a thermally sprayed, metallic inlet lining.
  • An at least local heat treatment increases the erosion resistance by compacting or reinforcing the particle compound. This is done z. At temperatures from 450 ° C to 500 ° C or from 925 ° C to 975 ° C.
  • the document US-A-5,024,884 protects a plasma-sprayed, metallic enamel coating whose surface is improved in its erosion resistance with a metallic / ceramic cover layer.
  • the topcoat is heat treated at 100 ° C to 425 ° C.
  • the present invention is based on the problem to provide a particularly effective method for producing an inlet lining.
  • the process time duration of the heat treatment is adapted to the process temperature of the heat treatment such that the process time duration is shorter, the higher the process temperature.
  • the inlet lining produced according to the invention is preferably used in compressors or in low-pressure turbines.
  • the hardening and oxidation of the metallic matrix is pre-embossed in metallic inlet linings, which ultimately sets the desired hardness of the inlet lining and improves the runability of the inlet lining and is stabilized. Due to the heat treatment of the inlet lining provided, it is, so to speak, subjected to an artificial aging process, so that the same has a stable run-in behavior during later operation.
  • the heat treatment is carried out at a process temperature which is above the temperature at which the inlet lining is maximally exposed during operation of the turbomachine.
  • the process temperature of the heat treatment is preferably 50 ° C to 200 ° C above the maximum operating temperature of the inlet lining.
  • the process time of the heat treatment is preferably between 1 hour and 200 hours.
  • the provided inlet lining is rinsed before the heat treatment in a chemical solution or a chemical bath.
  • the process time duration of the subsequent heat treatment can be shortened.
  • the present invention relates to a method for producing an inlet lining on a stator-side component of a turbomachine, in particular on a housing section of a gas turbine aircraft engine.
  • the inlet lining provided for the purpose of optimizing the shrinkability of the same is subjected to a heat treatment.
  • the heat treatment is carried out at a process temperature which is above the temperature at which the inlet lining is maximally exposed during operation of the turbomachine.
  • inlet coverings made of a metallic material that is to say for metallic inlet coverings
  • curing and oxidation of the metallic matrix can be pre-stamped, so that the inlet lining has an improved and stabilized enmeshability.
  • the hardness of the metallic inlet linings is optimized by the heat treatment, which is carried out at a process temperature above the maximum operating temperature of the inlet lining, so that the inlet lining is capable of running even at high operating temperatures and maintains this property over the operating time of the turbomachine.
  • the hardness of the abradable coating which arises during the heat treatment is determined by a superimposition of two effects, namely hardening and oxidation of the abradable coating, the curing increasing the hardness of the abradable coating as the heat treatment increases, while the oxidation reduces the hardness of the abradable coating.
  • the hardness of the inlet lining can be set exactly.
  • a metallic inlet lining preferably a porous inlet lining of a NiCrAl material or a CoNiCrAlY-hBN material is provided by thermal spraying, which is then subjected to the heat treatment.
  • the process temperature of the heat treatment is around 50 ° C to 200 ° C, preferably around 100 ° C to 150 ° C, above the maximum operating temperature of the inlet lining.
  • the heat treatment is preferably carried out at a process temperature between 600 ° C and 800 ° C. At a maximum operating temperature of 650 ° C, the heat treatment is preferably carried out at 750 ° C.
  • the heat treatment of the provided inlet lining is carried out during a process period of between 1 hour and 200 hours, preferably during a process period of between 2 hours and 20 hours.
  • the process temperature of the heat treatment of the inlet lining of the respective stage is adapted to the corresponding maximum operating temperature.
  • an e.g. subjected to heat treatment during the provision of the same during the manufacture of new parts or during the repair of the inlet lining is carried out at a process temperature which is above the maximum operating temperature of the inlet lining, and is carried out for a time adapted to the respective temperature.
  • the provided inlet lining is subjected to artificial aging, whereby ultimately its running-in ability can be optimized and stabilized.
  • a provided, porous inlet lining is rinsed before the heat treatment in a chemical solution. After rinsing, a drying and then the heat treatment, whereby due to capillary effects, the solution remains after drying in pores of the inlet lining. By rinsing, the process time duration of the subsequent heat treatment can be shortened, since the solution in particular supports the oxidation of the metallic matrix.
  • the rinsing may e.g. in a solution of demineralized water and sodium hydroxide or caustic soda.
  • rinsing can be done in diethylene glycol monobutyl ether or in a solution of sodium hydroxide and monophenyl glycol and sodium cumene sulfonate.

Abstract

A method for the production of a run-in coating is provided, whereby a metallic run-in coating material is provided on a component on the stator side of a turbomachine, especially a gas turbine. According to an embodiment of the invention, the provided run-in coating undergoes a heat treatment for purposes of improving its run-in characteristics.

Description

Die Erfindung betrifft ein Verfahren zum Herstellen eines Einlaufbelags gemäß dem Oberbegriff des Anspruchs 1.The invention relates to a method for producing an inlet lining according to the preamble of claim 1.

Turbomaschinen, wie zum Beispiel Gasturbinen, umfassen in der Regel mehrere rotierende Laufschaufeln sowie mehrere feststehende Leitschaufeln, wobei die Laufschaufeln zusammen mit einem Rotor rotieren, und wobei die Laufschaufeln sowie die Leitschaufeln von einem feststehenden Gehäuse umschlossen sind. Zur Leistungssteigerung ist es von Bedeutung, alle Komponenten und Subsysteme zu optimieren. Hierzu zählen auch die sogenannten Dichtsysteme. Besonders problematisch ist bei Turbomaschinen die Einhaltung eines minimalen Spalts zwischen den rotierenden Laufschaufeln und dem feststehenden Gehäuse eines Hochdruckverdichters. Bei Hochdruckverdichtern treten nämlich hohe absolute Temperaturen sowie Temperaturengradienten auf, was die Spalthaltung der rotierenden Laufschaufeln zum feststehenden Gehäuse erschwert. Dies liegt unter anderem auch darin begründet, dass bei Verdichterlaufschaufeln auf Deckbänder, wie sie bei Turbinenlaufschaufeln verwendet werden, verzichtet wird.Turbomachines, such as gas turbines, typically include a plurality of rotating blades and a plurality of fixed vanes, the blades rotating together with a rotor, and the blades and vanes being enclosed by a fixed housing. To increase performance, it is important to optimize all components and subsystems. These include the so-called sealing systems. Particularly problematic in turbomachinery compliance with a minimum gap between the rotating blades and the fixed housing of a high pressure compressor. Namely high absolute temperatures and temperature gradients occur in high-pressure compressors, which makes it more difficult for the rotating blades to cling to the stationary housing. This is partly due to the fact that in compressor blades on shrouds, as used in turbine blades, is dispensed with.

Wie bereits erwähnt, verfügen Laufschaufeln im Verdichter über kein Deckband. Daher sind Enden bzw. Spitzen der Laufschaufeln beim sogenannten Anstreifen in das feststehende Gehäuse einem direkten Reibkontakt mit dem Gehäuse ausgesetzt. Ein solches Anstreifen der Spitzen der Laufschaufeln in das Gehäuse wird bei Einstellung eines minimalen Radialspalts durch Fertigungstoleranzen hervorgerufen. Da durch den Reibkontakt der Spitzen der Laufschaufeln an denselben Material abgetragen wird, kann sich über den gesamten Umfang von Gehäuse und Rotor eine unerwünschte Spaltvergrößerung einstellen. Um dies zu vermeiden ist es aus dem Stand der Technik bereits bekannt, die Enden bzw. Spitzen der Laufschaufeln mit einem harten Belag oder mit abrasiven Partikeln zu panzern.As mentioned earlier, blades in the compressor have no shroud. Therefore, tips of the blades are exposed to so-called rubbing into the fixed housing in direct frictional contact with the housing. Such a rubbing of the tips of the blades into the housing is caused by setting a minimum radial gap by manufacturing tolerances. As is removed by the frictional contact of the tips of the blades on the same material, over the entire circumference of the housing and rotor can set an undesirable gap magnification. To avoid this, it is already known from the prior art to armor the ends or tips of the blades with a hard coating or with abrasive particles.

Eine andere Möglichkeit, den Verschleiß an den Spitzen der Laufschaufeln zu vermeiden und für eine optimierte Abdichtung zwischen den Enden bzw. Spitzen der Laufschaufeln und dem feststehenden Gehäuse zu sorgen, besteht in der Beschichtung des Gehäuses mit einem sogenannten Einlaufbelag. Bei einem Materialabtrag an einem Einlaufbelag wird der Radialspalt nicht über den gesamten Umfang vergrößert, sondern in der Regel nur sichelförmig. Hierdurch wird ein Leistungsabfall des Triebwerks vermieden. Gehäuse mit einem Einlaufbelag sind aus dem Stand der Technik bekannt. Aus dem Stand der Technik bekannte Einlaufbeläge für Verdichter werden üblicherweise aus einem metallischen Werkstoff hergestellt, der über thermisches Spritzen auf ein statorseitiges Bauteil des Gehäuses aufgetragen wird. Im Betrieb einer Turbomaschine ist jedoch festzustellen, dass sich abhängig von der Betriebstemperatur das Einlaufverhalten solcher Einlaufbeläge derart verändert, dass dieselben bei steigenden Betriebstemperaturen eine zunehmende Härte aufweisen, wodurch die Gefahr von Beschädigungen der in den Einlaufbelag anstreifenden Laufschaufeln besteht. Es besteht daher ein Bedarf an Einlaufbelägen, die über den gesamten Bereich der auftretenden Betriebstemperaturen eine angepasste Härte und damit gute Einlauffähigkeit aufweisen, sodass die Gefahr von Beschädigungen der Laufschaufeln beim Anstreifen in den Einlaufbelag reduziert wird.Another way to avoid the wear on the tips of the blades and to ensure an optimized seal between the tips and tips of the blades and the stationary housing, consists in the coating of the housing with a so-called inlet lining. In a material removal at an inlet lining of the radial gap is not increased over the entire circumference, but usually only sickle-shaped. As a result, a power loss of the engine is avoided. Housings with an inlet lining are known from the prior art. Inlet linings for compressors known from the prior art are usually made of a metallic material which is applied by thermal spraying to a stator-side component of the housing. In the operation of a turbomachine, however, it should be noted that, depending on the operating temperature, the running-in behavior of such inlet linings changes such that they have an increasing hardness with increasing operating temperatures, whereby there is the risk of damage to the rotor blades grazing into the inlet lining. There is therefore a need for inlet coverings, which have over the entire range of operating temperatures occurring an adapted hardness and thus good drainability, so that the risk of damage to the blades when rubbed into the inlet lining is reduced.

Das Dokument US-A1-3 713 206 betrifft ein Verfahren zum Herstellen eines metallischen Einlaufbelags auf einem metallischen Gehäuse. Dabei wird ein Nickelfilz auf das Gehäuse aufgelötet und abschließend mit Chrom oder Chrom und Aluminium beschichtet. Die Beschichtung erfolgt in Verbindung mit einer Wärmebehandlung bei Temperaturen von 800 °C bis 1100 °C.The document US-A1-3,713,206 relates to a method for producing a metallic inlet lining on a metallic housing. In the process, a nickel felt is soldered onto the housing and finally coated with chromium or chromium and aluminum. The coating is carried out in conjunction with a heat treatment at temperatures of 800 ° C to 1100 ° C.

Das Dokument US-B1-6 383 658 schützt nach dem HVOF-Verfahren gespritzte Beschichtungen, deren Haftung an einem Substrat durch eine diffusionsfördernde Wärmebehandlung verstärkt wird.The document US-B1-6,383,658 protects coatings sprayed by the HVOF process whose adhesion to a substrate is enhanced by a diffusion-promoting heat treatment.

Das Dokument EP-A2-1 010 861 betrifft einen Einlaufbelag samt Herstellverfahren. Die thermisch gespritzte, einlauffähige Schicht besteht aus Aluminium und Silizium mit eingelagerten Kunststoffteilchen aus MethylMethacrylat als Füllstoff. Durch eine Wärmebehandlung bei mindestens 274 °C wird ein Teil der Kunststoffpartikel verdampft und hinterlässt Poren im Einlaufbelag.The document EP-A2-1 010 861 concerns an inlet lining including manufacturing process. The thermally sprayed, shrinkable layer consists of aluminum and silicon with embedded plastic particles of methyl methacrylate as filler. By a heat treatment at least 274 ° C, a part of the plastic particles is evaporated and leaves pores in the inlet lining.

Das Dokument GB-A-2 397 307 bezieht sich auf ein Verfahren zur Herstellung eines thermisch gespritzten, metallischen Einlaufbelags. Durch eine zumindest örtliche Wärmebehandlung wird durch Verdichten bzw. Verstärken der Partikelverbindung die Erosionsbeständigkeit erhöht. Dies erfolgt z. B. bei Temperaturen von 450 °C bis 500°C oder von 925°C bis 975 °C.The document GB-A-2 397 307 refers to a method for producing a thermally sprayed, metallic inlet lining. An at least local heat treatment increases the erosion resistance by compacting or reinforcing the particle compound. This is done z. At temperatures from 450 ° C to 500 ° C or from 925 ° C to 975 ° C.

Das Dokument US-A-5 024 884 schützt einen plasmagespritzten, metallischen Einlaufbelag, dessen Oberfläche mit einer metallisch/keramischen Deckschicht in ihrer Erosionsbeständigkeit verbessert ist. Die Deckschicht ist bei 100 °C bis 425 °C wärmebehandelt.The document US-A-5,024,884 protects a plasma-sprayed, metallic enamel coating whose surface is improved in its erosion resistance with a metallic / ceramic cover layer. The topcoat is heat treated at 100 ° C to 425 ° C.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein besonders effektives Verfahren zum Herstellen eines Einlaufbelags zu schaffen.On this basis, the present invention is based on the problem to provide a particularly effective method for producing an inlet lining.

Dieses Problem wird durch ein Verfahren zum Herstellen eines Einlaufbelags im Sinne von Anspruch 1 gelöst. Dabei wird der bereitgestellte Einlaufbelag zur Verbesserung der Einlauffähigkeit desselben einer Wärmebehandlung unterzogen. Erfindungsgemäß wird die Prozesszeitdauer der Wärmebehandlung an die Prozesstemperatur der Wärmebehandlung derart angepasst, dass die Prozesszeitdauer um so kürzer ist, je höher die Prozesstemperatur ist. Der erfindungemäß hergestellte Einlaufbelag findet bevorzugt in Verdichtern oder in Niederdruckturbinen Verwendung.This problem is solved by a method for producing an inlet lining in the sense of claim 1. In this case, the provided inlet lining to improve the running ability of the same is subjected to a heat treatment. According to the invention, the process time duration of the heat treatment is adapted to the process temperature of the heat treatment such that the process time duration is shorter, the higher the process temperature. The inlet lining produced according to the invention is preferably used in compressors or in low-pressure turbines.

Im Sinne der hier vorliegenden Erfindung wird vorgeschlagen, einen z.B. bei einer Neufertigung bzw. Reparatur bereitgestellten Einlaufbelag zur Verbesserung der Einlauffähigkeit desselben einer Wärmebehandlung zu unterziehen. Durch die Wärmebehandlung wird bei metallischen Einlaufbelägen die Aushärtung und die Oxidation der metallischen Matrix vorgeprägt, wodurch letztendlich die gewünschte Härte des Einlaufbelags eingestellt und die Einlauffähigkeit des Einlaufbelags verbessert und stabilisiert wird. Durch die Wärmebehandlung des bereitgestellten Einlaufbelags wird derselbe sozusagen einem künstlichen Alterungsprozess unterzogen, sodass derselbe im späteren Betrieb ein stabiles Einlaufverhalten aufweist.For the purposes of the present invention, it is proposed to use e.g. to undergo a heat treatment for the purpose of improving the running-in capability provided by a new production or repair. By the heat treatment, the hardening and oxidation of the metallic matrix is pre-embossed in metallic inlet linings, which ultimately sets the desired hardness of the inlet lining and improves the runability of the inlet lining and is stabilized. Due to the heat treatment of the inlet lining provided, it is, so to speak, subjected to an artificial aging process, so that the same has a stable run-in behavior during later operation.

Gemäß der Erfindung wird die Wärmebehandlung bei einer Prozesstemperatur durchgeführt, die oberhalb der Temperatur liegt, welcher der Einlaufbelag im Betrieb der Turbomaschine maximal ausgesetzt wird. Die Prozesstemperatur der Wärmebehandlung liegt dabei vorzugsweise um 50°C bis 200°C oberhalb der maximalen Betriebstemperatur des Einlaufbelags. Die Prozesszeitdauer der Wärmebehandlung liegt bevorzugt zwischen 1 Stunde und 200 Stunden.According to the invention, the heat treatment is carried out at a process temperature which is above the temperature at which the inlet lining is maximally exposed during operation of the turbomachine. The process temperature of the heat treatment is preferably 50 ° C to 200 ° C above the maximum operating temperature of the inlet lining. The process time of the heat treatment is preferably between 1 hour and 200 hours.

Nach einer vorteilhaften Weiterbildung der Erfindung wird der bereitgestellte Einlaufbelag vor der Wärmebehandlung in einer chemischen Lösung bzw. einem chemischen Bad gespült. Hierdurch kann die Prozesszeitdauer der nachfolgenden Wärmebehandlung verkürzt werden.According to an advantageous embodiment of the invention, the provided inlet lining is rinsed before the heat treatment in a chemical solution or a chemical bath. As a result, the process time duration of the subsequent heat treatment can be shortened.

Die hier vorliegende Erfindung betrifft ein Verfahren zum Herstellen eines Einlaufbelags auf einem statorseitigen Bauteil einer Turbomaschine, insbesondere auf einem Gehäuseabschnitt eines Gasturbinenflugtriebwerks. Erfindungsgemäß wird nach Bereitstellen eines Einlaufbelags bei der Neuteilfertigung oder Reparatur der bereitgestellte Einlaufbelag zur Optimierung der Einlauffähigkeit desselben einer Wärmebehandlung unterzogen. Die Wärmebehandlung wird dabei bei einer Prozesstemperatur durchgeführt, die oberhalb der Temperatur liegt, welcher der Einlaufbelag im Betrieb der Turbomaschine maximal ausgesetzt wird. Hierdurch kann bei Einlaufbelägen aus einem metallischen Werkstoff, also bei metallischen Einlaufbelägen, die Aushärtung sowie die Oxidation der metallischen Matrix vorgeprägt werden, sodass der Einlaufbelag über eine verbesserte sowie stabilisierte Einlauffähigkeit verfügt. Die Härte der metallischen Einlaufbeläge wird durch die Wärmebehandlung, die bei einer Prozesstemperatur oberhalb der maximalen Betriebstemperatur des Einlaufbelags durchgeführt wird, derart optimiert, dass der Einlaufbelag auch bei hohen Betriebstemperaturen einlauffähig ist und diese Eigenschaft über die Betriebszeit der Turbomaschine beibehält.The present invention relates to a method for producing an inlet lining on a stator-side component of a turbomachine, in particular on a housing section of a gas turbine aircraft engine. According to the invention, after the provision of an inlet covering in the manufacture of new parts or repair, the inlet lining provided for the purpose of optimizing the shrinkability of the same is subjected to a heat treatment. The heat treatment is carried out at a process temperature which is above the temperature at which the inlet lining is maximally exposed during operation of the turbomachine. As a result, in the case of inlet coverings made of a metallic material, that is to say for metallic inlet coverings, curing and oxidation of the metallic matrix can be pre-stamped, so that the inlet lining has an improved and stabilized enmeshability. The hardness of the metallic inlet linings is optimized by the heat treatment, which is carried out at a process temperature above the maximum operating temperature of the inlet lining, so that the inlet lining is capable of running even at high operating temperatures and maintains this property over the operating time of the turbomachine.

Die sich bei der Wärmebehandlung einstellende Härte des Einlaufbelags wird durch eine Überlagerung zweier Effekte bestimmt, nämlich durch die Aushärtung sowie die Oxidation des Einlaufbelags, wobei mit zunehmender Zeitdauer der Wärmebehandlung die Aushärtung die Härte des Einlaufbelags erhöht, die Oxidation hingegen die Härte des Einlaufbelags verringert. Durch gezielte Auswahl der Zeitdauer der Wärmebehandlung kann die Härte des Einlaufbelags exakt eingestellt werden.The hardness of the abradable coating which arises during the heat treatment is determined by a superimposition of two effects, namely hardening and oxidation of the abradable coating, the curing increasing the hardness of the abradable coating as the heat treatment increases, while the oxidation reduces the hardness of the abradable coating. Through selective selection of the duration of the heat treatment, the hardness of the inlet lining can be set exactly.

Als metallischer Einlaufbelag wird vorzugsweise ein poröser Einlaufbelag aus einem NiCrAl-Werkstoff oder aus einem CoNiCrAlY-hBN-Werkstoff durch thermischen Spritzen bereitgestellt, welcher anschließend der Wärmebehandlung unterzogen wird.As a metallic inlet lining preferably a porous inlet lining of a NiCrAl material or a CoNiCrAlY-hBN material is provided by thermal spraying, which is then subjected to the heat treatment.

Die Prozesstemperatur der Wärmebehandlung liegt um 50°C bis 200°C, vorzugsweise um 100°C bis 150°C, oberhalb der maximalen Betriebstemperatur des Einlaufbelags.The process temperature of the heat treatment is around 50 ° C to 200 ° C, preferably around 100 ° C to 150 ° C, above the maximum operating temperature of the inlet lining.

Wird der Einlaufbelag im Betrieb der Turbomaschine z.B. Betriebstemperaturen zwischen 450°C und 650°C ausgesetzt, so erfolgt die Wärmebehandlung desselben vorzugsweise bei einer Prozesstemperatur zwischen 600°C und 800°C. Bei einer maximalen Betriebstemperaturen von 650°C erfolgt die Wärmebehandlung bevorzugt bei 750°C.If the inlet lining during operation of the turbomachine, e.g. Operating temperatures between 450 ° C and 650 ° C exposed, the heat treatment is preferably carried out at a process temperature between 600 ° C and 800 ° C. At a maximum operating temperature of 650 ° C, the heat treatment is preferably carried out at 750 ° C.

Die Wärmebehandlung des bereitgestellten Einlaufbelags wird dabei während einer Prozesszeitdauer zwischen 1 Stunde und 200 Stunden, vorzugsweise während einer Prozesszeitdauer zwischen 2 Stunden und 20 Stunden, durchgeführt. Je höher die Prozesstemperatur der Wärmebehandlung ist, desto kürzer ist die Prozesszeitdauer derselben.The heat treatment of the provided inlet lining is carried out during a process period of between 1 hour and 200 hours, preferably during a process period of between 2 hours and 20 hours. The higher the process temperature of the heat treatment, the shorter the process time duration of the same.

Bei mehrstufigen Verdichtern, bei welchen die einzelnen Stufen desselben unterschiedlichen maximalen Betriebstemperaturen ausgesetzt sind, ist die Prozesstemperatur der Wärmebehandlung des Einlaufbelag der jeweiligen Stufe an die entsprechende maximale Betriebstemperatur angepasst.For multi-stage compressors in which the individual stages of the same are exposed to different maximum operating temperatures, the process temperature of the heat treatment of the inlet lining of the respective stage is adapted to the corresponding maximum operating temperature.

Mit dem erfindungsgemäßen Verfahren wird demnach ein z.B. bei der Neuteilfertigung oder bei der Reparatur bereitgestellter Einlaufbelag im Anschluss an das Bereitstellen desselben einer Wärmebehandlung unterzogen. Die Wärmebehandlung erfolgt dabei bei einer Prozesstemperatur, die oberhalb der maximalen Betriebstemperatur des Einlaufbelags liegt, und wird für eine an die jeweilige Temperatur angepasste Zeitdauer durchgeführt. Hierdurch wird der bereitgestellte Einlaufbelag einer künstlichen Alterung unterzogen, wodurch letztendlich dessen Einlauffähigkeit optimiert und stabilisiert werden kann.Accordingly, with the method according to the invention, an e.g. subjected to heat treatment during the provision of the same during the manufacture of new parts or during the repair of the inlet lining. The heat treatment is carried out at a process temperature which is above the maximum operating temperature of the inlet lining, and is carried out for a time adapted to the respective temperature. As a result, the provided inlet lining is subjected to artificial aging, whereby ultimately its running-in ability can be optimized and stabilized.

Nach einer vorteilhaften Weiterbildung der Erfindung wird ein bereitgestellter, poröser Einlaufbelag vor der Wärmebehandlung in einer chemischen Lösung gespült. Im Anschluss an das Spülen erfolgt eine Trocknung und anschließend die Wärmebehandlung, wobei bedingt durch Kapillareffekte die Lösung nach der Trocknung in Poren des Einlaufbelags verbleibt. Durch das Spülen kann die Prozesszeitdauer der nachfolgenden Wärmebehandlung verkürzt werden, da die Lösung insbesondere die Oxidation der metallischen Matrix unterstützt.According to an advantageous embodiment of the invention, a provided, porous inlet lining is rinsed before the heat treatment in a chemical solution. After rinsing, a drying and then the heat treatment, whereby due to capillary effects, the solution remains after drying in pores of the inlet lining. By rinsing, the process time duration of the subsequent heat treatment can be shortened, since the solution in particular supports the oxidation of the metallic matrix.

Das Spülen kann z.B. in einer Lösung aus demineralisiertem Wasser und Natriumhydroxid oder Natronlauge erfolgen. Alternativ kann das Spülen in Diethylenglykolmonobutylether oder in einer Lösung aus Natriumhydroxid und Monophenylglykol und Natriumcumolsufonat erfolgen.The rinsing may e.g. in a solution of demineralized water and sodium hydroxide or caustic soda. Alternatively, rinsing can be done in diethylene glycol monobutyl ether or in a solution of sodium hydroxide and monophenyl glycol and sodium cumene sulfonate.

Claims (12)

  1. A method for producing a run-in coating, wherein a metallic run-in coating is provided on a component of a turbo-engine, in particular a gas turbine, on the stator side, wherein
    the run-in coating provided is subjected to a heat treatment in order to improve its running-in ability, and wherein
    the heat treatment is carried out at a process temperature which lies above the maximum temperature to which the run-in coating is exposed during operation of the turbo-engine,
    characterised in that
    the process duration of the heat treatment is adapted to the process temperature of the heat treatment in such a way that the process duration is shorter, the higher the process temperature.
  2. A method according to Claim 1, characterised in that the process temperature of the heat treatment is 50°C to 200°C above the maximum operating temperature of the run-in coating.
  3. A method according to Claim 2, characterised in that the process temperature of the heat treatment is 100°C to 150°C above the maximum operating temperature of the run-in coating.
  4. A method according to Claim 2 or 3, characterised in that the process temperature of the heat treatment lies between 600°C and 800°C.
  5. A method according to one of Claims 1 to 4, characterised in that the heat treatment is carried out for a process duration of between 1 hour and 200 hours.
  6. A method according to Claim 5, characterised in that the process duration of the heat treatment lies between 2 hours and 20 hours.
  7. A method according to one of Claims 1 to 6, characterised in that a porous run-in coating is provided as the metallic run-in coating by thermal spraying.
  8. A method according to one of Claims 1 to 7, characterised in that the run-in coating provided is rinsed in a chemical solution prior to the heat treatment.
  9. A method according to Claim 8, characterised in that drying and then the heat treatment takes place following the rinsing.
  10. A method according to Claim 8 or 9, characterised in that the run-in coating provided is rinsed in a solution of demineralised water and sodium hydroxide or sodium hydroxide solution.
  11. A method according to Claim 8 or 9, characterised in that the run-in coating provided is rinsed in diethylene glycol monobutyl ether.
  12. A method according to Claim 8 or 9, characterised in that the run-in coating provided is rinsed in a solution of sodium hydroxide and monophenyl glycol and sodium cumene sulphonate.
EP06828577A 2005-12-07 2006-11-30 Method for manufacturing a run-in coating Not-in-force EP1957756B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005058324A DE102005058324A1 (en) 2005-12-07 2005-12-07 Method for producing an inlet lining
PCT/DE2006/002122 WO2007065403A1 (en) 2005-12-07 2006-11-30 Method for manufacturing a run-in coating

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EP1957756A1 EP1957756A1 (en) 2008-08-20
EP1957756B1 true EP1957756B1 (en) 2011-05-04

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US (1) US20110020560A1 (en)
EP (1) EP1957756B1 (en)
JP (1) JP2009518571A (en)
AT (1) ATE508254T1 (en)
CA (1) CA2631362A1 (en)
DE (2) DE102005058324A1 (en)
WO (1) WO2007065403A1 (en)

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DE102008005479A1 (en) * 2008-01-23 2009-07-30 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine has compressor with set of blades, where blades are provided with free end in each case, and adjacent intake layer is formed on free end of blades at circular housing area
EP2647795B1 (en) * 2012-04-04 2018-11-07 MTU Aero Engines AG Seal system for a turbo engine
EP2876172A1 (en) * 2013-11-26 2015-05-27 MTU Aero Engines GmbH Method for producing and repairing components of a turbo engine made from nickel-based superalloys

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Publication number Publication date
DE102005058324A1 (en) 2007-06-14
EP1957756A1 (en) 2008-08-20
WO2007065403A1 (en) 2007-06-14
JP2009518571A (en) 2009-05-07
US20110020560A1 (en) 2011-01-27
DE502006009452D1 (en) 2011-06-16
ATE508254T1 (en) 2011-05-15
CA2631362A1 (en) 2007-06-14

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