ES2256351T3 - Sistema de capas de aislamiento termico. - Google Patents

Sistema de capas de aislamiento termico.

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Publication number
ES2256351T3
ES2256351T3 ES02008046T ES02008046T ES2256351T3 ES 2256351 T3 ES2256351 T3 ES 2256351T3 ES 02008046 T ES02008046 T ES 02008046T ES 02008046 T ES02008046 T ES 02008046T ES 2256351 T3 ES2256351 T3 ES 2256351T3
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Prior art keywords
thermal insulation
layer
insulation layer
layer system
secondary phase
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Ulrich Dr. Bast
Peter Prof. Greil
Frank Muller
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Siemens AG
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Siemens AG
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    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
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    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
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    • C23C16/00—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes
    • C23C16/22—Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the deposition of inorganic material, other than metallic material
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    • C23C28/042—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D only coatings of inorganic non-metallic material including a refractory ceramic layer, e.g. refractory metal oxides, ZrO2, rare earth oxides
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    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
    • C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
    • C23C28/345—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer
    • C23C28/3455—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one oxide layer with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
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    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
    • C23C28/42—Coatings including alternating layers following a pattern, a periodic or defined repetition characterized by the composition of the alternating layers
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    • C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
    • C23C28/40—Coatings including alternating layers following a pattern, a periodic or defined repetition
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    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
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    • C23C4/06—Metallic material
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    • 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
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    • 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
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    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Inorganic Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Ceramic Engineering (AREA)
  • General Chemical & Material Sciences (AREA)
  • Coating By Spraying Or Casting (AREA)
  • Other Surface Treatments For Metallic Materials (AREA)
  • Laminated Bodies (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Thermal Insulation (AREA)
  • Physical Vapour Deposition (AREA)
  • Chemical Vapour Deposition (AREA)

Abstract

Sistema (19) de capas de aislamiento térmico que se compone de un sustrato (22) y al menos una capa (25, 28) que se coloca sobre éste, caracterizado porque la al menos una capa (25, 28) presenta una fase (34) secundaria en un material (31) de matriz que presenta una composición seleccionada del grupo La-Al-O, Sr-Ca-Zr-O, Gd-La-Al-O para mejorar las propiedades mecánicas.

Description

Sistema de capas de aislamiento térmico.
La invención se refiere a un sistema de capa de aislamiento térmico que consiste en un sustrato y capas que se colocan sobre éste.
Del documento EP 1 029 101 B1 se conoce una capa de aislamiento térmico, presentando la capa cerámica exterior la composición de materiales La-Al-Gd-O o Sr-Ca-Zr-O.
El documento US 5.545.484 presenta un sistema de capas, en el que el sustrato está reforzado mecánicamente mediante fibras.
Las capas de aislamiento térmico son esencialmente capas funcionales y deben proteger el sustrato, por ejemplo, de un calor demasiado elevado. El sustrato presenta una resistencia mecánica suficientemente elevada. Las capas de aislamiento térmico están sometidas igualmente a esfuerzos térmicos o esfuerzos mecánicos y pueden fallar por desconchamiento, porque surgen fisuras.
Por tanto, es objetivo de la invención mostrar un sistema de capas de aislamiento térmico y un procedimiento para la producción del mismo, en el que las capas puedan aguantar mejor esfuerzos térmicos y mecánicos.
El objetivo se alcanza mediante un sistema de capas de aislamiento térmico según la reivindicación 1. A este respecto, se agrega a al menos una capa de La-Al-O, Sr-Ca-Zr-O o Gd-La-Al-O una fase secundaria que mejora el capa en sus propiedades mecáni-
cas.
En las reivindicaciones dependientes 2 a 14 se exponen mejoras ventajosas adicionales del sistema de capas de aislamiento térmico, mediante las cuales se mejora la resistencia mecánica (a la flexión, a la compresión,...) y la tenacidad de fractura (K_{1}^{C}).
La fase secundaria puede estar presente en forma de fibras o partículas. Como fibras se consideran fibras de carbono convencionales o fibras de otro material o fibras cortas mono-cristalinas.
Las partículas que forman la fase secundaria pueden presentar los mismos elementos que el material de matriz de la capa o, sin embargo, seleccionarse también de otro sistema de materiales.
Cuando las partículas son alargadas, es decir, presentan una elevada relación entre la longitud y la superficie de sección transversal (elevado aspect-ratio) se refuerza ventajosamente la capa o el material de matriz de la capa, mediante la desviación de fisuras y/o la ramificación de fisuras.
Como capa que va a reforzarse puede seleccionarse una capa cerámica o metálica de las capas que se colocan sobre el sustrato. Especialmente ésta es la capa de aislamiento térmico.
En las figuras subsiguientes se muestran ejemplos de realización.
Muestran:
la figura 1, un álabe de turbina,
la figura 2, un sistema de capas de aislamiento térmico,
la figura 3, una representación esquemática de la microestructura de una capa del sistema de capas de aislamiento térmico según la invención y
la figura 4, esquemáticamente un dispositivo de revestimiento para poder realizar el procedimiento según la invención, y
las figuras 5 y 6, ejemplos de realización adicionales de la capa de aislamiento térmico según la invención.
Los mismos símbolos de referencia tienen en las diferentes figuras el mismo significado.
La figura 1 muestra en una vista en perspectiva un álabe 1 de rodete que se extiende a lo largo del eje 4 longitudinal.
El álabe 1 de rodete presenta a lo largo del eje 4 longitudinal sucesivamente una zona 7 de fijación, una plataforma 10 de álabe que limita con ella, así como una zona 13 de hoja de álabe.
En la zona 7 de fijación se forma un pie 16 de álabe que sirve para la fijación del álabe 1 de rodete a un árbol, no mostrado, de una máquina hidrodinámica, tampoco mostrada. El pie 16 de álabe está configurado, por ejemplo, como una cabeza de martillo. Son posibles otras configuraciones. En los álabes de rodete convencionales se usan en todas las zonas 7, 10, 13 y 16 materiales metálicos macizos. El álabe 1 de rodete puede fabricarse en este caso mediante un procedimiento de fundición, mediante un procedimiento de forjado, mediante un procedimiento de fresado o mediante combinaciones de los mismos.
Especialmente en la zona 13 de la hoja de álabe, que está sometida a temperaturas más elevadas, por ejemplo, de una turbina de gas, se aplica al menos una capa, especialmente una capa de protección frente a la oxidación / corrosión y una capa de aislamiento térmico que forma parte de un sistema de capas de aislamiento térmico.
La figura 2 muestra un sistema 19 de capas de aislamiento térmico de este tipo según la invención.
El sistema 19 de capas de aislamiento térmico presenta un sustrato 22, por ejemplo, una súper aleación basada en níquel o cobalto, sobre la que se aplica, por ejemplo, al menos un capa 25 intermedia.
La capa 25 intermedia puede consistir en varias capas, que sirven, por ejemplo, como barrera de difusión, como capa favorecedora de la adhesión (MCrAlY, M = Fe, Co, Ni), capa de protección frente a la corrosión o como capa de anclaje.
Sobre el sustrato 22 o sobre la al menos una capa 25 intermedia se aplica, por ejemplo, una capa 25 de aislamiento térmico cerámica. La al menos una capa 25 intermedia y la capa 28 de aislamiento térmico se someten a esfuerzos mecánicos.
La figura 3 muestra esquemáticamente una microestructura de la capa 25 intermedia o de la capa 28 de aislamiento térmico.
La capa 25, 28 según la invención consiste en una matriz 31 y una fase 34 secundaria. La matriz 31 se compone de granos que pueden presentar distintas formas (morfologías). Si se produce la matriz 31, por ejemplo, mediante inyección de plasma, los granos del material 31 de la matriz presentan así un diseño en forma de plaquita. La fase 34 secundaria puede, por ejemplo, mezclarse durante la inyección de plasma con el material 31 de la matriz y aplicarse conjuntamente mediante una boquilla de soplete (figura 4).
La fase 34 secundaria puede ser otra fase del material 31 de la matriz, pero también una fibra o una fibra corta mono-cristalina.
La fase 34 secundaria tiene el objetivo de reforzar la resistencia mecánica de la matriz 31. Esto puede garantizarse mediante el refuerzo con fibras o refuerzo con partículas con los mecanismos de refuerzo conocidos. Especialmente cuando la fase 34 secundaria presenta una forma alargada, se aumenta especialmente la resistencia mecánica de la matriz 31.
Como material 31 para la capa 28 de aislamiento térmico se usan los materiales dados a conocer en el documento EP 1 029 101 B1, es decir, los sistemas La_{1-x} Gd_{x} AlO_{3} o Ca_{1-x} Sr_{x} ZrO2_{3}. El documento EP 1 029 101 B1 debe ser especialmente parte de lo divulgado en la presente solicitud. Los elementos Gd y La pueden sustituirse por otros lantánidos.
Como fase 34 secundaria para el refuerzo de la matriz 31 para el material 31 de matriz Gd-La-Al-O se usa especialmente la fase 34 secundaria con la composición LaAl_{11}O_{18} (\beta-aluminato).
La capa 25, 28 puede producirse mediante diferentes procedimientos de revestimiento tales como, por ejemplo, inyección de plasma, procedimiento de CVD o PVD.
En la inyección de plasma puede mezclarse la fase 34 secundaria con el material 31 de la matriz y aplicarse mediante la boquilla de soplete sobre el sustrato 22 o la capa 25 intermedia.
Sin embargo, en determinadas fases 34 secundarias puede darse el caso de que la fase secundaria no sea estable en fase a las elevadas temperaturas de la inyección de plasma. Igualmente, en el procedimiento de CVD o PVD puede darse el caso de que con este procedimiento sólo pueda aplicarse una composición de material, a saber, la de la matriz 31. En este caso se aplica la fase secundaria a través de una boquilla 40 auxiliar independiente (figura 4) a la capa 25, 28.
La figura 4 muestra esquemáticamente un dispositivo de revestimiento con el que se aplica una fase secundaria y un material 31 de matriz.
Por medio de una boquilla 37 principal, que es, por ejemplo, una boquilla de soplete de una instalación de capa de plasma, o de un sustrato 37 de una instalación de PVD, se aplica el material 31 de la matriz sobre el sustrato 22 o la al menos una capa 25 intermedia.
Por medio de una fuente independiente, por ejemplo, una boquilla 40 auxiliar, se mezcla la fase 34 secundaria con el flujo de partículas del material 31 de matriz, de manera que se forma una matriz 31 con una fase secundaria, que presenta una proporción en volumen inferior al 50%.
La figura 5 muestra una capa de un sistema de capas de aislamiento térmico según la invención.
La capa 28 tiene al menos dos capas y se compone de dos capas 46 que no están reforzadas y una capa 43 que está reforzada mediante una fase secundaria.
La primera capa 46 está colocada, por ejemplo, sobre el sustrato 22 o la capa 25. Luego sigue la capa 43 y, como capa exterior, la capa 46 no reforzada. Las fisuras no pueden penetrar o sólo pueden hacerlo difícilmente a través de la capa 43, de manera que se evita un desprendimiento de la capa 28 respecto al sustrato 22.
La figura 6 muestra una capa de un sistema de capas de aislamiento térmico según la invención. La capa 28 tiene dos capas y consiste en un capa 46, que no está reforzada, y un capa 43, que está reforzada mediante una fase secundaria. La primer capa 43 está colocada, por ejemplo, sobre el sustrato 22 o la capa 25. Luego sigue la capa 43 como capa exterior o viceversa. Las fisuras no pueden penetrar o sólo pueden hacerlo difícilmente a través de la capa 43, de manera que se evita un desprendimiento de la capa 28 respecto al sustrato 22.

Claims (14)

1. Sistema (19) de capas de aislamiento térmico que se compone de un sustrato (22) y al menos una capa (25, 28) que se coloca sobre éste, caracterizado porque la al menos una capa (25, 28) presenta una fase (34) secundaria en un material (31) de matriz que presenta una composición seleccionada del grupo La-Al-O, Sr-Ca-Zr-O, Gd-La-Al-O para mejorar las propiedades mecánicas.
2. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la fase (34) secundaria está formada por partículas, de manera que se produce un refuerzo con partículas de la capa (25, 28).
3. Sistema de capas de aislamiento térmico según la reivindicación 2, caracterizado porque las partículas (34) presentan una forma alargada.
4. Sistema de capas de aislamiento térmico según la reivindicación 1 o 2, caracterizado porque la fase (34) secundaria es una fibra.
5. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la al menos una capa (25, 28) es una capa cerámica.
6. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la capa (25, 28) es un capa (28) de aislamiento térmico.
7. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la fase (34) secundaria presenta la composición LaAl_{11}O_{18}.
8. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la capa (25, 28) es una capa metálica, especialmente una capa (25) de MCrAlY.
9. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque se sustituye el lantano en el material de matriz o material de la fase secundaria por otros lantánidos.
10. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque el sistema (19) de capas de aislamiento térmico representa un álabe (1) de turbina.
11. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la capa (28) de aislamiento térmico tiene al menos dos capas.
12. Sistema de capas de aislamiento térmico según la reivindicación 11, caracterizado porque una parte exterior de la capa (28) de aislamiento térmico presenta la fase secundaria.
13. Sistema de capas de aislamiento térmico según la reivindicación 11, caracterizado porque una parte interior de la capa de aislamiento térmico presenta la fase (34) secundaria.
14. Sistema de capas de aislamiento térmico según la reivindicación 1, caracterizado porque la fase (34) secundaria sólo está presente localmente.
ES02008046T 2002-04-10 2002-04-10 Sistema de capas de aislamiento termico. Expired - Lifetime ES2256351T3 (es)

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US20040191544A1 (en) 2004-09-30
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EP1464721A3 (de) 2004-11-24
CN1646720A (zh) 2005-07-27
JP2005527704A (ja) 2005-09-15
EP1352985A1 (de) 2003-10-15
DE50205494D1 (de) 2006-03-30
WO2003085153A1 (de) 2003-10-16
EP1464721A2 (de) 2004-10-06

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