EP1076157A3 - Friction element for a turbomachine - Google Patents

Friction element for a turbomachine Download PDF

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Publication number
EP1076157A3
EP1076157A3 EP00810658A EP00810658A EP1076157A3 EP 1076157 A3 EP1076157 A3 EP 1076157A3 EP 00810658 A EP00810658 A EP 00810658A EP 00810658 A EP00810658 A EP 00810658A EP 1076157 A3 EP1076157 A3 EP 1076157A3
Authority
EP
European Patent Office
Prior art keywords
turbine blade
turbomachine
friction element
intermetallic felt
intermetallic
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
EP00810658A
Other languages
German (de)
French (fr)
Other versions
EP1076157B1 (en
EP1076157A2 (en
Inventor
Alexander Dr. Beeck
Mohamed Dr. Nazmy
Markus Dr. Oehl
Christoph Dr. Töennes
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.)
General Electric Technology GmbH
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1076157A2 publication Critical patent/EP1076157A2/en
Publication of EP1076157A3 publication Critical patent/EP1076157A3/en
Application granted granted Critical
Publication of EP1076157B1 publication Critical patent/EP1076157B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • 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

Abstract

Die Erfindung bezieht sich auf die Ausstattung einer Turbinenschaufel (1) einer Gasturbine mit einem intermetallischen Filz (2). Durch die Besetzung der Spitze (11) der Turbinenschaufel (1) mit dem intermetallischen Filz (2) und einem Überzug mit einem keramischen Material (3) kann ein verbesserter Schutz gegen thermische und mechanische Einwirkungen und eine verbesserte Oxidationsbeständigkeit erreicht werden. Es ist auch eine Anordnung des intermetallischen Filzes (2) an dem der Turbinenschaufel (1) gegenüberliegenden Rotor (4, 4a) bzw. Stator (4, 4b) oder auf der Plattform (12) der Turbinenschaufel (1) denkbar.

Figure 00000001
The invention relates to the equipment of a turbine blade (1) of a gas turbine with an intermetallic felt (2). By filling the tip (11) of the turbine blade (1) with the intermetallic felt (2) and a coating with a ceramic material (3), improved protection against thermal and mechanical effects and improved oxidation resistance can be achieved. It is also conceivable to arrange the intermetallic felt (2) on the rotor (4, 4a) or stator (4, 4b) opposite the turbine blade (1) or on the platform (12) of the turbine blade (1).
Figure 00000001
EP00810658A 1999-08-09 2000-07-24 Friction component of a thermal turbomachine Expired - Lifetime EP1076157B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19937577 1999-08-09
DE19937577A DE19937577A1 (en) 1999-08-09 1999-08-09 Frictional gas turbine component

Publications (3)

Publication Number Publication Date
EP1076157A2 EP1076157A2 (en) 2001-02-14
EP1076157A3 true EP1076157A3 (en) 2004-01-02
EP1076157B1 EP1076157B1 (en) 2011-07-13

Family

ID=7917752

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00810658A Expired - Lifetime EP1076157B1 (en) 1999-08-09 2000-07-24 Friction component of a thermal turbomachine

Country Status (4)

Country Link
US (1) US6499943B1 (en)
EP (1) EP1076157B1 (en)
JP (1) JP2001050005A (en)
DE (1) DE19937577A1 (en)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6670046B1 (en) * 2000-08-31 2003-12-30 Siemens Westinghouse Power Corporation Thermal barrier coating system for turbine components
EP1448874B1 (en) 2001-09-25 2007-12-26 ALSTOM Technology Ltd Joint system for reducing a sealing space in a rotary gas turbine
CN100430499C (en) 2002-08-16 2008-11-05 阿尔斯托姆科技有限公司 Intermetallic material and use of said material
DE10337094A1 (en) * 2003-08-12 2005-03-03 Mtu Aero Engines Gmbh Inlet lining for gas turbines and method for producing the same
DE10356586A1 (en) 2003-12-04 2005-07-07 Alstom Technology Ltd compressor rotor
JP2005201079A (en) * 2004-01-13 2005-07-28 Ishikawajima Harima Heavy Ind Co Ltd Turbine blade and its manufacturing method
DE102004010236A1 (en) * 2004-03-03 2005-09-15 Mtu Aero Engines Gmbh Metal ring structure for sealing gap between rotor blade tips and stator in e.g. gas turbine, has inner wall formed by metal fabric or felt
EP2031080B1 (en) 2007-08-30 2012-06-27 Alstom Technology Ltd High temperature alloy
JP4668976B2 (en) 2007-12-04 2011-04-13 株式会社日立製作所 Steam turbine seal structure
US8211524B1 (en) 2008-04-24 2012-07-03 Siemens Energy, Inc. CMC anchor for attaching a ceramic thermal barrier to metal
CH699206A1 (en) * 2008-07-25 2010-01-29 Alstom Technology Ltd High-temperature alloy.
JP5339503B2 (en) * 2008-09-12 2013-11-13 国立大学法人京都大学 Super ODS steel
US9394795B1 (en) * 2010-02-16 2016-07-19 J & S Design Llc Multiple piece turbine rotor blade
US20110299977A1 (en) * 2010-06-03 2011-12-08 General Electric Company Patch ring segment for a turbomachine compressor
FR2963382B1 (en) * 2010-08-02 2016-01-29 Snecma AUBES TURBINE WHEEL IN CERAMIC MATRIX COMPOSITE
US8888446B2 (en) * 2011-10-07 2014-11-18 General Electric Company Turbomachine rotor having patterned coating
EP2971560B1 (en) * 2013-03-15 2020-05-06 United Technologies Corporation Maxmet composites for turbine engine component tips

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3203869A1 (en) * 1982-02-05 1983-08-18 MTU Motoren- und Turbinen-Union München GmbH, 8000 München TURBINE BLADE FOR FLOWING MACHINES, ESPECIALLY GAS TURBINE ENGINES
DE3235230A1 (en) * 1982-09-23 1984-03-29 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gas turbine blade having a metal core and a ceramic vane
EP0132667A1 (en) * 1983-07-28 1985-02-13 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Thermally highly stressed cooled turbine blade
DE19750516A1 (en) * 1997-11-14 1999-05-20 Asea Brown Boveri Abradable seal
EP0919699A2 (en) * 1997-11-26 1999-06-02 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3964877A (en) * 1975-08-22 1976-06-22 General Electric Company Porous high temperature seal abradable member
DE2945531C2 (en) * 1979-11-10 1982-01-07 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Turbo blade with a material core and a ceramic blade
WO1993024672A1 (en) * 1992-05-29 1993-12-09 United Technologies Corporation Ceramic thermal barrier coating for rapid thermal cycling applications
DE19615549B8 (en) * 1996-04-19 2005-07-07 Alstom Device for thermal protection of a rotor of a high-pressure compressor
DE19848103A1 (en) * 1998-10-19 2000-04-20 Asea Brown Boveri Sealing arrangement
DE19848104A1 (en) * 1998-10-19 2000-04-20 Asea Brown Boveri Turbine blade
US6235370B1 (en) * 1999-03-03 2001-05-22 Siemens Westinghouse Power Corporation High temperature erosion resistant, abradable thermal barrier composite coating

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3203869A1 (en) * 1982-02-05 1983-08-18 MTU Motoren- und Turbinen-Union München GmbH, 8000 München TURBINE BLADE FOR FLOWING MACHINES, ESPECIALLY GAS TURBINE ENGINES
DE3235230A1 (en) * 1982-09-23 1984-03-29 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gas turbine blade having a metal core and a ceramic vane
EP0132667A1 (en) * 1983-07-28 1985-02-13 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Thermally highly stressed cooled turbine blade
DE19750516A1 (en) * 1997-11-14 1999-05-20 Asea Brown Boveri Abradable seal
EP0919699A2 (en) * 1997-11-26 1999-06-02 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system

Also Published As

Publication number Publication date
US6499943B1 (en) 2002-12-31
JP2001050005A (en) 2001-02-23
DE19937577A1 (en) 2001-02-15
EP1076157B1 (en) 2011-07-13
EP1076157A2 (en) 2001-02-14

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