EP0132667A1 - 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
EP0132667A1
EP0132667A1 EP84107962A EP84107962A EP0132667A1 EP 0132667 A1 EP0132667 A1 EP 0132667A1 EP 84107962 A EP84107962 A EP 84107962A EP 84107962 A EP84107962 A EP 84107962A EP 0132667 A1 EP0132667 A1 EP 0132667A1
Authority
EP
European Patent Office
Prior art keywords
component according
ceramic
metal felt
ceramic layer
cooling air
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.)
Granted
Application number
EP84107962A
Other languages
German (de)
English (en)
Other versions
EP0132667B1 (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 component, in particular a turbine blade, with a load-bearing 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 component of the type mentioned, which can be cooled particularly well and effectively with a simple structure in operation.
  • the jacket consists of a layered composite, which is applied to the outside of a ceramic thermal insulation layer from a metal felt firmly connected to the webs of the cooling air guide grooves and covering the cooling air guide grooves.
  • the cooling air guide grooves are expediently already prefabricated in the investment casting process of the metallic support core or subsequently incorporated by milling, spark erosion or electrochemical removal.
  • the metal felt is advantageously soldered, welded or glued to the webs of the cooling air guide grooves.
  • the support core webs and the 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, NiCrAl, Hastelloy X, NiCrAlY alloy, CoCrAlY 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 partially infiltrates with ceramic from the outside and with is coated with a compact ceramic layer that forms the actual thermal insulation layer.
  • the infiltration and application of the ceramic layer is advantageously carried out 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 thus creates a new cooling concept for a thermally highly stressed cooled component: the cooling configuration of the effusion cooling is combined with a thermal barrier coating, which means that the air efusion associated with high cooling air consumption to reduce the heat transfer can be dispensed with. 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 component remains comparatively cold.
  • cooling air can be introduced by the invention with the same cooling effectiveness saves and the thermodynamic efficiency can be increased.
  • the heat-insulating ceramic layer can be produced much more densely by the metal felt intermediate layer than when it is applied directly 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 NiCrAl, is provided as an elastic carrier material for the outer thermal insulation layer 6 and offers a large surface area for optimal dissipation through the thermal insulation layer 6 flowing heat.
  • 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 of the ceramic layer, so that despite the increased gas temperature, a lower one Cooling air requirement is necessary.
  • the easily deformable metal felt 4 which is preferably a heat-resistant, e.g. B. NiCrAl felt, which is soldered from nickel-based alloy to the metallic support core, allows the application of a very dense and comparatively thick ceramic layer (compared to the application to massive metallic substrates), because of the differences in the thermal expansion between metal and ceramic
  • the easy deformability of the metal felt does not lead to the build-up of stresses that are impermissibly high 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 B 2 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)
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 true EP0132667A1 (fr) 1985-02-13
EP0132667B1 EP0132667B1 (fr) 1987-10-28

Family

ID=6205134

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)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0199321A1 (fr) * 1985-04-20 1986-10-29 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Echangeur de chaleur
EP0609795A1 (fr) * 1993-02-04 1994-08-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Couche d'isolation thermique céramique sur éléments métalliques et procédé de manufacture
DE19928871A1 (de) * 1999-06-24 2000-12-28 Abb Research Ltd Turbinenschaufel
EP1076157A2 (fr) 1999-08-09 2001-02-14 ALSTOM POWER (Schweiz) AG Elément de friction pour une turbomachine
US6412541B2 (en) 2000-05-17 2002-07-02 Alstom Power N.V. Process for producing a thermally loaded casting
DE102008058141A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
DE102008058142A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu

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JPS6217307A (ja) * 1985-07-17 1987-01-26 Natl Res Inst For Metals 空冷翼
US4838031A (en) * 1987-08-06 1989-06-13 Avco Corporation Internally cooled combustion chamber liner
US4838030A (en) * 1987-08-06 1989-06-13 Avco Corporation Combustion chamber liner having failure activated cooling and dectection system
JP2753235B2 (ja) * 1987-10-23 1998-05-18 財団法人電力中央研究所 遮熱緩衝層製造方法
US4790721A (en) * 1988-04-25 1988-12-13 Rockwell International Corporation Blade assembly
USRE34173E (en) * 1988-10-11 1993-02-02 Midwest Research Technologies, Inc. Multi-layer wear resistant coatings
US4904542A (en) * 1988-10-11 1990-02-27 Midwest Research Technologies, Inc. Multi-layer wear resistant coatings
US5102305A (en) * 1988-12-13 1992-04-07 Allied-Signal Inc. Turbomachine having a unitary ceramic rotating assembly
US5139716A (en) * 1990-02-20 1992-08-18 Loral Aerospace Corp. Method of fabricating coolable ceramic structures
US5367873A (en) * 1991-06-24 1994-11-29 United Technologies Corporation One-piece flameholder
DE4137373C1 (fr) * 1991-11-13 1993-06-17 Siemens Ag, 8000 Muenchen, De
US5413463A (en) * 1991-12-30 1995-05-09 General Electric Company Turbulated cooling passages in gas turbine buckets
US5295530A (en) * 1992-02-18 1994-03-22 General Motors Corporation Single-cast, high-temperature, thin wall structures and methods of making the same
US5279111A (en) * 1992-08-27 1994-01-18 Inco Limited Gas turbine cooling
US5493855A (en) * 1992-12-17 1996-02-27 Alfred E. Tisch Turbine having suspended rotor blades
US5454426A (en) * 1993-09-20 1995-10-03 Moseley; Thomas S. Thermal sweep insulation system for minimizing entropy increase of an associated adiabatic enthalpizer
US5626462A (en) * 1995-01-03 1997-05-06 General Electric Company Double-wall airfoil
UA23886C2 (uk) * 1996-03-12 2002-04-15 Юнайтед Технолоджіз Корп. Пратт Енд Уітні Спосіб виготовлення пустотілих виробів складної форми
DE19627860C1 (de) * 1996-07-11 1998-01-08 Mtu Muenchen Gmbh Schaufel für Strömungsmaschine mit metallischer Deckschicht
WO1998031922A1 (fr) * 1997-01-14 1998-07-23 Siemens Aktiengesellschaft Ailette de turbine pour une turbomachine, notamment une turbine a gaz
DE19750517A1 (de) * 1997-11-14 1999-05-20 Asea Brown Boveri Hitzeschild
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US6709230B2 (en) * 2002-05-31 2004-03-23 Siemens Westinghouse Power Corporation Ceramic matrix composite gas turbine vane
US6648597B1 (en) 2002-05-31 2003-11-18 Siemens Westinghouse Power Corporation Ceramic matrix composite turbine vane
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US7093359B2 (en) 2002-09-17 2006-08-22 Siemens Westinghouse Power Corporation Composite structure formed by CMC-on-insulation process
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US7275720B2 (en) * 2003-06-09 2007-10-02 The Boeing Company Actively cooled ceramic thermal protection system
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US9528382B2 (en) * 2009-11-10 2016-12-27 General Electric Company Airfoil heat shield
US8894363B2 (en) 2011-02-09 2014-11-25 Siemens Energy, Inc. Cooling module design and method for cooling components of a gas turbine system
US9334741B2 (en) 2010-04-22 2016-05-10 Siemens Energy, Inc. Discreetly defined porous wall structure for transpirational cooling
US8739404B2 (en) 2010-11-23 2014-06-03 General Electric Company Turbine components with cooling features and methods of manufacturing the same
US8793871B2 (en) 2011-03-17 2014-08-05 Siemens Energy, Inc. Process for making a wall with a porous element for component cooling
US20130094971A1 (en) * 2011-10-12 2013-04-18 General Electric Company Hot gas path component for turbine system
US9034465B2 (en) * 2012-06-08 2015-05-19 United Technologies Corporation Thermally insulative attachment
US9003657B2 (en) 2012-12-18 2015-04-14 General Electric Company Components with porous metal cooling and methods of manufacture
EP2959110B1 (fr) * 2013-02-23 2017-06-28 Rolls-Royce Corporation Composant de turbine à gaz
EP3049626B1 (fr) * 2013-09-23 2020-11-25 United Technologies Corporation Pale en cmc à bord de fuite pointu et sa procédé de fabrication
US10539041B2 (en) * 2013-10-22 2020-01-21 General Electric Company Cooled article and method of forming a cooled article
DE102013223585A1 (de) 2013-11-19 2015-06-03 MTU Aero Engines AG Einlaufbelag auf Basis von Metallfasern
US10934854B2 (en) * 2018-09-11 2021-03-02 General Electric Company CMC component cooling cavities
CN113287251A (zh) * 2019-01-10 2021-08-20 三菱重工发动机和增压器株式会社 马达和逆变器一体型旋转电机
FR3105649B1 (fr) * 2019-12-19 2021-11-26 Valeo Equip Electr Moteur Machine électrique tournante refroidie

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0199321A1 (fr) * 1985-04-20 1986-10-29 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Echangeur de chaleur
EP0609795A1 (fr) * 1993-02-04 1994-08-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Couche d'isolation thermique céramique sur éléments métalliques et procédé de manufacture
DE19928871A1 (de) * 1999-06-24 2000-12-28 Abb Research Ltd Turbinenschaufel
EP1076157A2 (fr) 1999-08-09 2001-02-14 ALSTOM POWER (Schweiz) AG Elément de friction pour une turbomachine
US6499943B1 (en) 1999-08-09 2002-12-31 Alstom (Switzerland Ltd Friction-susceptible component of a thermal turbo machine
EP1076157A3 (fr) * 1999-08-09 2004-01-02 ALSTOM (Switzerland) Ltd Elément de friction pour une turbomachine
US6412541B2 (en) 2000-05-17 2002-07-02 Alstom Power N.V. Process for producing a thermally loaded casting
DE102008058141A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen einer Schaufel für einen Rotor einer Strömungsmaschine
DE102008058142A1 (de) * 2008-11-20 2010-05-27 Mtu Aero Engines Gmbh Verfahren zum Herstellen und/oder Reparieren eines Rotors einer Strömungsmaschine und Rotor hierzu

Also Published As

Publication number Publication date
EP0132667B1 (fr) 1987-10-28
US4629397A (en) 1986-12-16
DE3467016D1 (en) 1987-12-03
JPS6045703A (ja) 1985-03-12
DE3327218A1 (de) 1985-02-07

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