EP0132667B1 - Aube de turbine refroidie soumise à une charge thermique élevée - Google Patents

Aube de turbine refroidie soumise à une charge thermique élevée Download PDF

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Publication number
EP0132667B1
EP0132667B1 EP84107962A EP84107962A EP0132667B1 EP 0132667 B1 EP0132667 B1 EP 0132667B1 EP 84107962 A EP84107962 A EP 84107962A EP 84107962 A EP84107962 A EP 84107962A EP 0132667 B1 EP0132667 B1 EP 0132667B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
blade according
ceramic
metal felt
coating
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP84107962A
Other languages
German (de)
English (en)
Other versions
EP0132667A1 (fr
Inventor
Klaus Dr.Rer.Nat. Dipl.-Chem. Schweitzer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0132667A1 publication Critical patent/EP0132667A1/fr
Application granted granted Critical
Publication of EP0132667B1 publication Critical patent/EP0132667B1/fr
Expired legal-status Critical Current

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Classifications

    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/005—Selecting particular materials
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S165/00—Heat exchange
    • Y10S165/907—Porous
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12444—Embodying fibers interengaged or between layers [e.g., paper, etc.]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • 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
    • Y10T428/12611—Oxide-containing component

Definitions

  • the invention relates to a thermally highly stressed cooled turbine blade, with a supporting metallic core, which has integrated cooling air guide grooves on its surface and with a heat-insulating jacket.
  • the object of the invention is to provide a thermally highly stressed cooled turbine blade of the type mentioned, which can be cooled particularly well and effectively in operation with a simple structure.
  • the jacket consists of a layer composite which is applied to the outside of a ceramic thermal insulation layer from a metal felt which is firmly connected to the webs of the cooling air guide grooves and covers the cooling air guide grooves.
  • the cooling air guide grooves are expediently already prefabricated during the investment casting process of the metallic support core or subsequently incorporated by milling, spark erosion or electrochemical removal.
  • a heat-insulating component from a layer composite, which consists of a metal felt layer, a ceramic cover layer and an intermediate metal layer connecting the other two.
  • the metal felt layer is supposed to compensate for the different thermal expansions of the ceramic cover layer and the metallic substrate by their elasticity.
  • the metal felt layer is not exposed to cooling air.
  • the metal felt is advantageously soldered, welded or glued to the webs of the cooling air guide grooves.
  • the support core webs and outer jacket are cast in one piece and are therefore comparatively complex to manufacture.
  • the metal felt suitably consists of a high-temperature and corrosion-resistant alloy, in particular based on nickel and / or cobalt (for example NiCr, NiCrAI, Hastelloy X, NiCrAIY alloy, CoCrAIY alloy).
  • a high-temperature and corrosion-resistant alloy in particular based on nickel and / or cobalt (for example NiCr, NiCrAI, Hastelloy X, NiCrAIY alloy, CoCrAIY alloy).
  • the metal felt serves as an elastic carrier material for a ceramic thermal barrier coating, which can be applied to the felt in various ways. For a particularly good hold, it is provided that the metal felt is partially infiltrated with ceramic from the outside and is coated on the outside with a compact ceramic layer which forms the actual thermal insulation layer.
  • the ceramic layer is expediently infiltrated and applied by thermal spraying or by a slip sintering process.
  • the layer can also be infiltrated and applied by chemical vapor deposition (CVD).
  • CVD chemical vapor deposition
  • the ceramic layer expediently consists of partially or fully stabilized zirconium oxide. It can be applied to the metal felt by one of the aforementioned methods, but also by a combination of several of the aforementioned methods.
  • the outer surface of the actual ceramic thermal barrier coating is expediently polished and / or aerodynamically shaped in order to better serve turbine blade purposes.
  • the invention therefore creates a new cooling concept for a thermally highly stressed cooled turbine blade: the cooling configuration of the effusion cooling is combined with a thermal barrier coating, which means that the air effusion associated with high cooling air consumption can be reduced to reduce the heat transfer. Instead, the thermal insulation of a ceramic layer is used. The heat that still flows through the thermal insulation layer is optimally dissipated through the metal felt, which has a very large surface area, namely the heat is removed directly from the thermal insulation layer, so that the load-bearing metal support core of the highly stressed turbine blade remains comparatively cold. In comparison to effusion cooling, cooling air can be saved and the thermodynamic efficiency increased by the invention with the same cooling effectiveness.
  • the heat-insulating ceramic layer can be made much denser by the metal felt intermediate layer than when directly applied to the compact metallic base body, so that very good thermal insulation is possible.
  • the interior of a turbine blade 1 is shown schematically in FIG. 1.
  • the turbine blade 1 is composed of a metallic support core 2, a metal felt 4 surrounding the metallic support core 2 and a ceramic thermal insulation layer 6 surrounding the outside of the metal felt 4 in a composite construction.
  • the metal support core is a nickel-based alloy and has cooling air guide grooves 3 with webs 5 on its surface, to which the metal felt 4 is soldered, welded or glued.
  • the metal felt itself is based on NiCrAI, is provided as an elastic carrier material for the outer thermal insulation layer 6 and offers a large surface area for optimal dissipation of the heat flowing through the thermal insulation layer 6.
  • the outer heat insulation layer 6 is partially or fully stabilized zirconium oxide, with a good anchoring of the outer heat insulation layer 6 with the metal felt 4 by partial infiltration of the felt, preferably by chemical vapor deposition (CVD).
  • the infiltration layer of the felt is clearly shown in detail A in FIG. 2.
  • the compact zirconium oxide layer is deposited on it, which takes over the actual heat-insulating function.
  • the advantage of the invention is that the heat does not have to flow through the entire component during operation, but is supplied to the cooling medium in the shortest possible way, the heat flow being kept low overall due to the low thermal conductivity or ceramic layer, so that despite an increased gas temperature, a lower one Cooling air requirement is necessary.
  • the easily deformable metal felt 4 which is preferably a NiCrAI felt, which is made of heat-resistant, e.g. Nickel-based alloy is soldered onto the metallic support core, which allows the application of a very dense and comparatively thick ceramic layer (compared to the application on solid metallic substrates), since the differences in the thermal expansion between metal and ceramic due to the easy deformability of the metal felt do not lead to the build-up of leads to impermissible high voltages for the ceramic.
  • a turbine blade trailing edge is shown in detail B1, which is comparatively pointed and contains the ends of the enclosed metal felt 4.
  • the detail B2 illustrated in FIG. 3 is characterized by a different drive edge construction with a larger rounding.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laminated Bodies (AREA)

Claims (10)

1. Aube de turbine fortement sollicitée thermiquement et refroidie (1 ), comportant un noyau métallique de soutien (2), qui présente, à sa surface, des rainures intégrées (3) de passage de l'air de refroidissement, et une enveloppe isolante, caractérisée en ce que l'enveloppe est formée d'un complexe de couches constitué d'un feutre métallique (4) qui est fermement relié avec les barrettes (5) des rainures de passage de l'air de refroidissement (3), qui recouvre les rainures de passage de l'air de refroidissement (3) et sur lequel est rapportée, extérieurement, une couche isolante céramique (6).
2. Aube de turbine selon la revendication 1, caractérisée en ce que le feutre métallique (4) est brasé, soudé ou collé sur les barrettes (5).
3. Aube de turbiné selon la revendication 1 ou 2, caractérisée en ce que le feutre métallique (4) est constitué-d'un alliage résistant à haute température et à la corrosion.
4. Aube de turbine selon la revendication 3, caractérisée en ce que le feutre métallique (4) est un alliage à base de nickelet/ou de cobalt.
5. Aube de turbine selon les revendications 1 à 4, caractérisée en ce que le feutre métallique (4) est partiellement infiltré, de l'extérieur, parla céramique (7) et est revêtu extérieurement d'une couche de céramique compacte qui forme la couche isolante proprement dite (6).
6. Aube de turbine selon la revendication 5, caractérisée en ce que l'infiltration et l'apport de la couche céramique se font par projection thermique.
7. Aube de turbine selon la revendication 5 ou 6, caractérisée en ce que l'infiltration et l'apport de la couche céramique se font par un procédé de frittage de barbotine.
8. Aube de turbine selon les revendications 5 à 7, caractérisée en ce que l'infiltration et l'apport de la couche céramique se font par dépôt chimique en phase gazeuse.
9. Aube de turbine selon les revendications 1 à 8, caractérisée en ce que la couche isolante (6) est polie extérieurement et/ou reçoit une forme aérodynamique.
10. Aube de turbine selon les revendications 5 à 9, caractérisée en ce que la couche céramique est constituée d'oxyde de zirconium partiellement ou totalementstabilisé.
EP84107962A 1983-07-28 1984-07-07 Aube de turbine refroidie soumise à une charge thermique élevée Expired EP0132667B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19833327218 DE3327218A1 (de) 1983-07-28 1983-07-28 Thermisch hochbeanspruchtes, gekuehltes bauteil, insbesondere turbinenschaufel
DE3327218 1983-07-28

Publications (2)

Publication Number Publication Date
EP0132667A1 EP0132667A1 (fr) 1985-02-13
EP0132667B1 true EP0132667B1 (fr) 1987-10-28

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP84107962A Expired EP0132667B1 (fr) 1983-07-28 1984-07-07 Aube de turbine refroidie soumise à une charge thermique élevée

Country Status (4)

Country Link
US (1) US4629397A (fr)
EP (1) EP0132667B1 (fr)
JP (1) JPS6045703A (fr)
DE (2) DE3327218A1 (fr)

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EP1076157A2 (fr) 1999-08-09 2001-02-14 ALSTOM POWER (Schweiz) AG Elément de friction pour une turbomachine
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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1076157A2 (fr) 1999-08-09 2001-02-14 ALSTOM POWER (Schweiz) AG Elément de friction pour une turbomachine
DE19937577A1 (de) * 1999-08-09 2001-02-15 Abb Alstom Power Ch Ag Reibungsbehaftete Gasturbinenkomponente
DE10024302A1 (de) * 2000-05-17 2001-11-22 Alstom Power Nv Verfahren zur Herstellung eines thermisch belasteten Gussteils
EP1645347A1 (fr) 2000-05-17 2006-04-12 Alstom Technology Ltd Procédé de fabrication d'une pièce moulée à charge thermique élevée
US7141128B2 (en) 2002-08-16 2006-11-28 Alstom Technology Ltd Intermetallic material and use of this material

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US4629397A (en) 1986-12-16
DE3467016D1 (en) 1987-12-03
JPS6045703A (ja) 1985-03-12
DE3327218A1 (de) 1985-02-07
EP0132667A1 (fr) 1985-02-13

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