EP0206107A2 - Aube de turbine hybride métal-céramique - Google Patents

Aube de turbine hybride métal-céramique Download PDF

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Publication number
EP0206107A2
EP0206107A2 EP86107927A EP86107927A EP0206107A2 EP 0206107 A2 EP0206107 A2 EP 0206107A2 EP 86107927 A EP86107927 A EP 86107927A EP 86107927 A EP86107927 A EP 86107927A EP 0206107 A2 EP0206107 A2 EP 0206107A2
Authority
EP
European Patent Office
Prior art keywords
core
blade
pin
insulator
shirt
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
EP86107927A
Other languages
German (de)
English (en)
Other versions
EP0206107B1 (fr
EP0206107A3 (en
Inventor
Werner Dr.-Ing. Hüther
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 AG
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 EP0206107A2 publication Critical patent/EP0206107A2/fr
Publication of EP0206107A3 publication Critical patent/EP0206107A3/de
Application granted granted Critical
Publication of EP0206107B1 publication Critical patent/EP0206107B1/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics

Definitions

  • the invention relates to a hybrid blade, in particular a guide or rotor blade of a turbomachine composed of metal-ceramic, the more temperature-resistant material forming the inner part.
  • composite blades are already known from DE-OS 28 34 843 and DE-PS 28 34 846.
  • DE-OS 3110096 describes a blade with the features of the preamble of claim 1. Proceeding from this, the object of the invention is to create a blade which can compensate for the different thermal expansion coefficients of the metallic core and the ceramic jacket, depending on the material used, allows a large core cross section and avoids local stress peaks in the ceramic jacket and both are easy to machine are. This object is achieved by the features of the characterizing part of claim 1.
  • the solution according to the invention is that the pin (7) is formed in one piece with the blade casing (4), that the core (1) is designed in a U-shape so that its leg ends over the pin (7) in the longitudinal direction of the blade can be inserted into the blade root (5), after which the base of the core (1) rests on the pin (7) with the interposition of an insulator (3) and the leg ends of the core (2) are fixed in the blade root (5) so that they cannot be detached.
  • the main advantage of the invention is that the ceramic is under pressure in the transition area metal / ceramic. This transition area is relatively small, so that thermal expansion can be controlled safely. In addition, the heat transfer from the jacket to the core is reduced, both of which are easy to machine.
  • the outer shirt-like part consists of ceramic, in particular of fiber-reinforced ceramic such as SiC fibers in SiC or SiC fibers in Si 3 N 4 or carbon fiber reinforced carbon with a silicon carbide protective layer.
  • the core has the reference number 1, it is in one piece, U-shaped and penetrated by a slot 2 which extends in the longitudinal direction of the blade and does not extend over the entire length, as shown in FIG. 3, but ends earlier at a base.
  • the width of the slot is dimensioned such that it can accommodate the insulator 3, shown in FIG. 2, which serves the connection between the core 1 and the jacket 4.
  • the jacket 4 has a greater height than the core and a cavity 8 in the central area for receiving the core 1.
  • the foot is designated 5 and receives the shirt 4 in a recess 6.
  • the jacket has a pin 7 in the slot 2 comes to rest.
  • the foot 5 for example a dovetail foot or a fir tree foot, also receives the U-shaped core 1 in the center at the other side.
  • It is preferably made of metallic Material, made the same or similar to the core 1, preferably by eroding from solid material. It can also be produced in an investment casting process.
  • the jacket 4 made of high-temperature-resistant ceramic is preferably produced by injection molding a sinterable SiC material or Si 3N4 or by cold isostatic pressing of a ceramic powder in a mold with a core and subsequent processing of the green compact to the almost final shape.
  • the core 1 is produced, for example, by investment casting, if desired, post-processing by grinding is possible.
  • the core can also be eroded from solid, in particular metallic material, or can be produced in single crystal by directional solidification in the casting process.
  • the slot 2 which is produced in the usual way, for example by milling, is ground on its contact surfaces with the insulator 3 and the pin 7.
  • Another fine processing can also be used, which is suitable for delivering smooth parallel surfaces, as are also desired on the insulator. This should enable a slight displacement of the jacket and core due to thermal expansion during operation.
  • the parallelism of the contact surfaces to each other should be less than 0.5 ⁇ m, for example.
  • the insulator 3 should preferably consist of partially stabilized zirconium oxide as a high-temperature-resistant ceramic, in particular Y 2 0 3 in Z r0 2 .
  • the baffle 9 can also serve as radiation protection, i.e. it shields the core 1 from heat transfer from the blade casing 4.
  • the guide plate 9 does not touch the jacket 4, but is fastened, in particular soldered, at a distance from the jacket and core in the base 5 (FIG. 6).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP86107927A 1985-06-19 1986-06-10 Aube de turbine hybride métal-céramique Expired EP0206107B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3521782 1985-06-19
DE19853521782 DE3521782A1 (de) 1985-06-19 1985-06-19 Hybridschaufel aus metall und keramik zusammengesetzt

Publications (3)

Publication Number Publication Date
EP0206107A2 true EP0206107A2 (fr) 1986-12-30
EP0206107A3 EP0206107A3 (en) 1987-04-29
EP0206107B1 EP0206107B1 (fr) 1988-08-17

Family

ID=6273547

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86107927A Expired EP0206107B1 (fr) 1985-06-19 1986-06-10 Aube de turbine hybride métal-céramique

Country Status (4)

Country Link
US (1) US4645421A (fr)
EP (1) EP0206107B1 (fr)
JP (1) JPS6248903A (fr)
DE (2) DE3521782A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2853688A3 (fr) * 2013-09-30 2015-07-22 MTU Aero Engines GmbH Aube pour une turbine à gaz

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2834125B2 (ja) * 1987-10-23 1998-12-09 財団法人電力中央研究所 複層遮熱構造
US4790721A (en) * 1988-04-25 1988-12-13 Rockwell International Corporation Blade assembly
JP2602929B2 (ja) * 1988-11-21 1997-04-23 株式会社東芝 ターボ機械の動翼構造
US5854525A (en) * 1993-07-30 1998-12-29 Jeumont Industrie Jacketed rotary machine
FR2766157B1 (fr) * 1997-07-15 1999-10-01 Eurocopter France Dispositif de protection thermique d'organes elastomeriques, ensemble de tels dispositifs pour la protection par temps froid d'un rotor de giravion, et rotor de giravion equipe d'un tel ensemble
US6572372B1 (en) * 2000-04-25 2003-06-03 Align Technology, Inc. Embedded features and methods of a dental appliance
EP1173657B1 (fr) * 1999-03-09 2003-08-20 Siemens Aktiengesellschaft Aube de turbine et son procede de production
US6514046B1 (en) 2000-09-29 2003-02-04 Siemens Westinghouse Power Corporation Ceramic composite vane with metallic substructure
US6648597B1 (en) 2002-05-31 2003-11-18 Siemens Westinghouse Power Corporation Ceramic matrix composite turbine vane
US6709230B2 (en) 2002-05-31 2004-03-23 Siemens Westinghouse Power Corporation Ceramic matrix composite gas turbine vane
US7093359B2 (en) 2002-09-17 2006-08-22 Siemens Westinghouse Power Corporation Composite structure formed by CMC-on-insulation process
US9068464B2 (en) * 2002-09-17 2015-06-30 Siemens Energy, Inc. Method of joining ceramic parts and articles so formed
US7080971B2 (en) 2003-03-12 2006-07-25 Florida Turbine Technologies, Inc. Cooled turbine spar shell blade construction
US7435058B2 (en) * 2005-01-18 2008-10-14 Siemens Power Generation, Inc. Ceramic matrix composite vane with chordwise stiffener
DE102007012320A1 (de) * 2007-03-09 2008-09-11 Rolls-Royce Deutschland Ltd & Co Kg Turbinenschaufel mit im Schaufelfuß ausgebildeter Mikroturbinendüse
US8075280B2 (en) * 2008-09-08 2011-12-13 Siemens Energy, Inc. Composite blade and method of manufacture
CH700071A1 (de) 2008-12-12 2010-06-15 Alstom Technology Ltd Laufschaufel für eine Gasturbine.
US8007242B1 (en) 2009-03-16 2011-08-30 Florida Turbine Technologies, Inc. High temperature turbine rotor blade
US8256088B2 (en) * 2009-08-24 2012-09-04 Siemens Energy, Inc. Joining mechanism with stem tension and interlocked compression ring
US10605086B2 (en) 2012-11-20 2020-03-31 Honeywell International Inc. Turbine engines with ceramic vanes and methods for manufacturing the same
EP2959110B1 (fr) 2013-02-23 2017-06-28 Rolls-Royce Corporation Composant de turbine à gaz
US10724380B2 (en) * 2017-08-07 2020-07-28 General Electric Company CMC blade with internal support
US10612399B2 (en) 2018-06-01 2020-04-07 Rolls-Royce North American Technologies Inc. Turbine vane assembly with ceramic matrix composite components
US10808560B2 (en) 2018-06-20 2020-10-20 Rolls-Royce Corporation Turbine vane assembly with ceramic matrix composite components
US20200248568A1 (en) * 2019-02-01 2020-08-06 Rolls-Royce Plc Turbine vane assembly with ceramic matrix composite components and temperature management features
US20220090504A1 (en) * 2020-09-24 2022-03-24 General Electric Company Rotor blade for a gas turbine engine having a metallic structural member and a composite fairing

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR999820A (fr) * 1946-01-11 1952-02-05 Perfectionnements aux turbines à gaz
FR2187032A5 (fr) * 1972-05-29 1974-01-11 Berry Sa Ets
DE2834864C3 (de) * 1978-08-09 1981-11-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Laufschaufel für eine Gasturbine
DE2834843A1 (de) * 1978-08-09 1980-06-26 Motoren Turbinen Union Zusammengesetzte keramik-gasturbinenschaufel
US4247259A (en) * 1979-04-18 1981-01-27 Avco Corporation Composite ceramic/metallic turbine blade and method of making same
FR2463849A1 (fr) * 1979-08-23 1981-02-27 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux aubes tournantes de turbines a gaz, et aux turbines a gaz equipees de ces aubes
US4519745A (en) * 1980-09-19 1985-05-28 Rockwell International Corporation Rotor blade and stator vane using ceramic shell
DE3110096C2 (de) * 1981-03-16 1983-05-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbinenlaufschaufel für Gasturbinentriebwerke
DE3129304A1 (de) * 1981-07-24 1983-02-10 MTU Motoren- und Turbinen-Union München GmbH, 8000 München "von heissgas beaufschlagte turbinenschaufel"
DE3203869C2 (de) * 1982-02-05 1984-05-10 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbinenlaufschaufel für Strömungsmaschinen, insbesondere Gasturbinentriebwerke
FR2538029A1 (fr) * 1982-12-15 1984-06-22 Onera (Off Nat Aerospatiale) Perfectionnements apportes aux aubes ceramiques, tournantes ou fixes de turbomachines
DE3306896A1 (de) * 1983-02-26 1984-08-30 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Heissgasbeaufschlagte turbinenschaufel mit metallenem stuetzkern und umgebendem keramischen schaufelblatt

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2853688A3 (fr) * 2013-09-30 2015-07-22 MTU Aero Engines GmbH Aube pour une turbine à gaz

Also Published As

Publication number Publication date
DE3521782A1 (de) 1987-01-02
DE3660556D1 (en) 1988-09-22
JPS6248903A (ja) 1987-03-03
US4645421A (en) 1987-02-24
EP0206107B1 (fr) 1988-08-17
EP0206107A3 (en) 1987-04-29

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