EP1152124A1 - Garniture d'étanchéité - Google Patents

Garniture d'étanchéité Download PDF

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Publication number
EP1152124A1
EP1152124A1 EP00109543A EP00109543A EP1152124A1 EP 1152124 A1 EP1152124 A1 EP 1152124A1 EP 00109543 A EP00109543 A EP 00109543A EP 00109543 A EP00109543 A EP 00109543A EP 1152124 A1 EP1152124 A1 EP 1152124A1
Authority
EP
European Patent Office
Prior art keywords
covering
arrangement according
component
gap
sealing
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.)
Withdrawn
Application number
EP00109543A
Other languages
German (de)
English (en)
Inventor
Kai Dr.-Ing. Wieghardt
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP00109543A priority Critical patent/EP1152124A1/fr
Priority to JP2001580548A priority patent/JP2003532014A/ja
Priority to US10/275,178 priority patent/US6962342B2/en
Priority to CNB018088643A priority patent/CN1328481C/zh
Priority to EP01943277A priority patent/EP1278944A1/fr
Priority to PCT/EP2001/004576 priority patent/WO2001083951A1/fr
Publication of EP1152124A1 publication Critical patent/EP1152124A1/fr
Withdrawn legal-status Critical Current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
    • F01D11/122—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 with erodable or abradable material
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type

Definitions

  • the invention relates to an arrangement for a turbomachine, in particular a steam turbine, for sealing a Gap between a mobile and a stationary one Component, one of which is on a flanking the gap Surface bears an abrasion layer.
  • sealing tapes arranged axially one behind the other - including labyrinth seals called - used. These seals are characterized by sealing tapes arranged transversely to the flow, a gap that is usually several millimeters wide close almost completely. It is accepted that the sealing tapes sometimes during transient processes brush against the component opposite them and thereby wear yourself slightly.
  • labyrinth seals are used both in blading and in turbine construction Piston and shaft seals used.
  • a similarly acting special form of these seals is a honeycomb seal. This has on one side of the Gaps, mostly on the side fixed to the housing, one one Recreated honeycomb structure on the open surface a leakage flow through a multitude of small vortices in is hampered by the honeycomb structure. On flow resistance generated thereby prevents a free flow Flow in the through the honeycomb structure on a Side limited channel.
  • the US-PS 4,177,004 is already a turbine known in which there is a gap between a turbine blade and one encompassing these in the circumferential direction, in one Sealing the suspended ring of the housing. This arrangement is designed so that the turbine blade itself occasionally the ring that surrounds her. To be threatened The ring with one material is to avoid damage occupied, which causes no wear on the turbine blade.
  • the invention is based on the object, the amount of unused equipment flowing past the turbine blade - For example water vapor - without special apperatives Effort and without affecting operational security further decrease.
  • This object is for an arrangement of the solved type in that a component to be sealed in the area of the Crevice bears an abrasion layer, which as of her opposite component at least partially removable, porous covering is executed.
  • a porous abrasive layer in connection with its opposite Sealing tapes are the favorable properties a labyrinth seal and a honeycomb seal together connected. Because of the risk of intrusion the sealing tape in the facing surface is the Effectiveness of the sealing arrangement surprisingly significant increased. This makes using surprisingly simple and a significant improvement in economic resources Sealing performance achieved. Another benefit is the increased thermal shock resistance due to the porosity, which with increasing proportion of voids also with growing Flexibility of the covering goes hand in hand.
  • the surface opposite the covering is at least one parallel arranged to the direction of movement of the movable component, the gap closing, protruding like a cutting edge Sealing lip from a sealing tape, which when the Component slightly penetrates the covering and this partially ablates and that the thickness of the covering is equal to that 0.5 to 0.1 times the width of the gap flanked by it is.
  • the covering contains a mixture of a mineral and a metallic and / or evaporable or gasifiable component.
  • composition of the covering contains this granular material parts according to their at least partial Removal from the topping at its free Surface has depressions.
  • the covering preferably on that flanking the gap arranged at rest.
  • the sealing tape at their free ends preferably up to 0.2 to 0.5 mm, tapered.
  • the component 1 on the other side of the gap 3 opposite component 2 is preferred in the operating state dormant and bears one designed as a rubbing layer 7 Covering.
  • the covering has a thickness corresponding to that 0.5 to 0.1 times the width of the gap 3 and consists of a porous or foamy material, for example made of a foamed metal or a mixture of one mineral and a metallic component and / or contains a gasifiable or vaporizable component.
  • a leg 8 facing the covering of the L-shaped in cross section Sealing tape 5 grazes the covering and is on his slightly tapered end immersed in the coating. Thereby is the energy requirement during a brushing or one Penetration of the sealing tape 5 in the covering on a very limited small value.
  • the thickness of the sealing tape 5 is around 0.2 mm in its tapered area and lies about the size of the width of a channel 9, the between the sealing tape 5 and that shown by the covering Abstreif Anlagen 7 is formed and through which a leakage current 10 flows out of steam.
  • the flow resistance for the leakage flow 10 in the channel 9 is not simply by its length and its Cross section determined, but is due to the bumps in the surface of the surface significantly increased. This is thereby achieved that even within the short channel 9 and despite its comparatively narrow cross-section, a large number of small and very small vortices within the leakage flow are enforced in this area. Above all, this is one Consequence of the execution of the invention as a rubbing layer 7 applied covering.
  • FIGS. 2 and 4 have both in Component 1 and in component 2 sealing tapes 5, of which one each in the gap 3 between the two neighboring ones Components 1, 2 in the direction of the opposite Component 1 or 2 extends.
  • Fig. 2 since in the solution accordingly Fig. 2 only the component 2 with an abradable layer 7 is provided, the effect according to the invention is only for the sealing tapes 5 in the opposite component 1 reached.
  • the solution according to FIG. 4 works with each of the sealing tapes on both sides of the gap 3 a porous coating as a rubbing layer 7 together.
  • Fig. 5 shows a seal between a turbine shaft as moved component 1 and a shroud 11, the shroud 11 ends of guide vanes 12 supports. This is the gap 3 facing side of the shroud 11 executed and carries a on their axially parallel sub-areas Covering as a rubbing layer 7. Each step of the cover tape 11 stands at least one sealing tape 5.
  • the shroud 11 is composed of segments that together in the circumferential direction give the turbine shaft a complete ring.
  • FIG. 6 is an illustration of a seal between one Housing part as a resting component 2 and a shroud 13, the supports the ends of blades 14 against each other.
  • the one Component 2 facing side of the shroud 13 is stepped executed and each of the axially parallel step surfaces provided with a covering as a rubbing layer 7.
  • Sealing tape 5 is opposite.
  • the cover band 13 is also made of segments composed of each other to form a complete Complement the ring.
  • coverings designed according to the invention as a rubbing layer 7 is particularly suitable for use with Steam turbines, but is the same in all other flow machines can be used advantageously.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP00109543A 2000-05-04 2000-05-04 Garniture d'étanchéité Withdrawn EP1152124A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP00109543A EP1152124A1 (fr) 2000-05-04 2000-05-04 Garniture d'étanchéité
JP2001580548A JP2003532014A (ja) 2000-05-04 2001-04-23 隙間の漏止め装置
US10/275,178 US6962342B2 (en) 2000-05-04 2001-04-23 System for sealing off a gap
CNB018088643A CN1328481C (zh) 2000-05-04 2001-04-23 用于密封缝隙的系统
EP01943277A EP1278944A1 (fr) 2000-05-04 2001-04-23 Dispositif permettant d'obturer un interstice
PCT/EP2001/004576 WO2001083951A1 (fr) 2000-05-04 2001-04-23 Dispositif permettant d'obturer un interstice

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00109543A EP1152124A1 (fr) 2000-05-04 2000-05-04 Garniture d'étanchéité

Publications (1)

Publication Number Publication Date
EP1152124A1 true EP1152124A1 (fr) 2001-11-07

Family

ID=8168623

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00109543A Withdrawn EP1152124A1 (fr) 2000-05-04 2000-05-04 Garniture d'étanchéité
EP01943277A Withdrawn EP1278944A1 (fr) 2000-05-04 2001-04-23 Dispositif permettant d'obturer un interstice

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01943277A Withdrawn EP1278944A1 (fr) 2000-05-04 2001-04-23 Dispositif permettant d'obturer un interstice

Country Status (5)

Country Link
US (1) US6962342B2 (fr)
EP (2) EP1152124A1 (fr)
JP (1) JP2003532014A (fr)
CN (1) CN1328481C (fr)
WO (1) WO2001083951A1 (fr)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2019238A1 (fr) * 2007-07-25 2009-01-28 Siemens Aktiengesellschaft Couche de frottement pour un joint d'étanchéité d'un arbre de rotation et procédé d'application
EP2410133A1 (fr) * 2010-07-22 2012-01-25 Siemens Aktiengesellschaft Turbine à gaz et procédé d'étanchéification de courants de fuites
GB2492546A (en) * 2011-07-04 2013-01-09 Alstom Technology Ltd A labyrinth seal for an axial fluid flow turbomachine
US8500397B2 (en) 2007-12-04 2013-08-06 Hitachi, Ltd. Seals in steam turbine
EP2647795A1 (fr) * 2012-04-04 2013-10-09 MTU Aero Engines GmbH Système d'étanchéité pour turbomachine
EP2647796A1 (fr) * 2012-04-04 2013-10-09 MTU Aero Engines GmbH Système d'étanchéité pour turbomachine
ITUB20155442A1 (it) * 2015-11-11 2017-05-11 Ge Avio Srl Stadio di un motore a turbina a gas provvisto di una tenuta a labirinto
EP3290645A1 (fr) * 2016-08-30 2018-03-07 Mitsubishi Hitachi Power Systems, Ltd. Segment pour dispositif d'étanchéité, rotor de turbine et turbine le comprenant
EP3722561A1 (fr) * 2019-04-11 2020-10-14 Mitsubishi Hitachi Power Systems, Ltd. Rotor de turbine à vapeur et turbine à vapeur

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DE10047307A1 (de) * 2000-09-25 2002-08-01 Alstom Switzerland Ltd Dichtungsanordnung
US6969231B2 (en) * 2002-12-31 2005-11-29 General Electric Company Rotary machine sealing assembly
US20070069477A1 (en) * 2003-06-20 2007-03-29 Elliott Company Stepped labyrinth damper seal
DE10360164A1 (de) * 2003-12-20 2005-07-21 Mtu Aero Engines Gmbh Gasturbinenbauteil
DE102004044803A1 (de) * 2004-09-16 2006-03-30 WINKLER + DüNNEBIER AG Sich selbst einstellende Spaltdichtung zwischen zwei sich gegeneinander beweglicher Bauteile
DE102006013557B4 (de) * 2005-03-30 2015-09-24 Alstom Technology Ltd. Rotor für eine Dampfturbine
US20060228209A1 (en) * 2005-04-12 2006-10-12 General Electric Company Abradable seal between a turbine rotor and a stationary component
EP1715140A1 (fr) * 2005-04-21 2006-10-25 Siemens Aktiengesellschaft Aube de turbine ayant une bande couvrante et une couche de protection sur la bande couvrante
US20070273104A1 (en) * 2006-05-26 2007-11-29 Siemens Power Generation, Inc. Abradable labyrinth tooth seal
US8205335B2 (en) * 2007-06-12 2012-06-26 United Technologies Corporation Method of repairing knife edge seals
US20090072487A1 (en) * 2007-09-18 2009-03-19 Honeywell International, Inc. Notched tooth labyrinth seals and methods of manufacture
JP5101317B2 (ja) * 2008-01-25 2012-12-19 三菱重工業株式会社 シール構造
JP5040743B2 (ja) * 2008-03-12 2012-10-03 富士電機株式会社 タービンのコーティング施工方法
DE102008058087B4 (de) * 2008-11-19 2022-04-28 Sew-Eurodrive Gmbh & Co Kg Dichtungsanordnung
US8282346B2 (en) * 2009-04-06 2012-10-09 General Electric Company Methods, systems and/or apparatus relating to seals for turbine engines
JP5411569B2 (ja) * 2009-05-01 2014-02-12 株式会社日立製作所 シール構造とその制御方法
US8192166B2 (en) * 2009-05-12 2012-06-05 Siemens Energy, Inc. Tip shrouded turbine blade with sealing rail having non-uniform thickness
JP5570151B2 (ja) * 2009-07-21 2014-08-13 ユニ・チャーム株式会社 吸収性物品帯状体の裁断装置
DE102009053954A1 (de) * 2009-11-19 2011-06-09 Siemens Aktiengesellschaft Labyrinthdichtung und Verfahren zum Herstellen einer Labyrinthdichtung
DE102009055913A1 (de) * 2009-11-27 2011-06-09 Rolls-Royce Deutschland Ltd & Co Kg Labyrinthdichtung aus in eine Einlaufschicht eingreifenden Dichtringen
JP5558138B2 (ja) * 2010-02-25 2014-07-23 三菱重工業株式会社 タービン
US8910947B2 (en) * 2010-03-30 2014-12-16 United Technologies Corporation Method of forming a seal element
JP5600542B2 (ja) * 2010-09-29 2014-10-01 株式会社神戸製鋼所 回転機械の軸封装置
US8591181B2 (en) * 2010-10-18 2013-11-26 General Electric Company Turbomachine seal assembly
US8845283B2 (en) * 2010-11-29 2014-09-30 General Electric Company Compressor blade with flexible tip elements and process therefor
DE202011105609U1 (de) * 2011-09-12 2011-10-13 Alstom Technology Ltd. Labyrinthdichtung
US10215033B2 (en) * 2012-04-18 2019-02-26 General Electric Company Stator seal for turbine rub avoidance
US9464536B2 (en) * 2012-10-18 2016-10-11 General Electric Company Sealing arrangement for a turbine system and method of sealing between two turbine components
JP5951449B2 (ja) * 2012-11-02 2016-07-13 株式会社東芝 蒸気タービン
WO2015073321A1 (fr) * 2013-11-13 2015-05-21 United Technologies Corporation Joint externe étanche à l'air d'aube de turbomachines
CN107060900B (zh) * 2017-03-31 2023-06-16 沈阳北碳密封有限公司 蜂窝螺旋径向刷式梳齿剖分密封
US10598038B2 (en) 2017-11-21 2020-03-24 Honeywell International Inc. Labyrinth seal with variable tooth heights
CN109322997B (zh) * 2018-12-07 2020-07-24 中国航发沈阳发动机研究所 发动机密封结构
FR3091725B1 (fr) * 2019-01-14 2022-07-15 Safran Aircraft Engines Ensemble pour une turbomachine
CN110578546B (zh) * 2019-09-30 2021-08-06 中国计量大学 一种矿用无动力自动闭合风门

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US3547455A (en) * 1969-05-02 1970-12-15 Gen Electric Rotary seal including organic abradable material
US3701536A (en) * 1970-05-19 1972-10-31 Garrett Corp Labyrinth seal
US4139376A (en) * 1974-02-28 1979-02-13 Brunswick Corporation Abradable seal material and composition thereof
US4177004A (en) 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
US4257735A (en) * 1978-12-15 1981-03-24 General Electric Company Gas turbine engine seal and method for making same
US5326647A (en) * 1991-09-18 1994-07-05 Mtu Motoren- Und Turbinen-Union Abradable layer for a turbo-engine and a manufacturing process

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US5143383A (en) * 1984-06-04 1992-09-01 General Electric Company Stepped tooth rotating labyrinth seal
US4936745A (en) * 1988-12-16 1990-06-26 United Technologies Corporation Thin abradable ceramic air seal
US5017402A (en) * 1988-12-21 1991-05-21 United Technologies Corporation Method of coating abradable seal assembly
US5599026A (en) * 1995-09-06 1997-02-04 Innovative Technology, L.L.C. Turbine seal with sealing strip and rubbing strip
GB9717857D0 (en) * 1997-08-23 1997-10-29 Rolls Royce Plc Fluid Seal
EP0939142A1 (fr) * 1998-02-27 1999-09-01 Ticona GmbH Poudre pour pulvérisation thermique contenant un polysulfure d'arylène
US6352264B1 (en) * 1999-12-17 2002-03-05 United Technologies Corporation Abradable seal having improved properties

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3547455A (en) * 1969-05-02 1970-12-15 Gen Electric Rotary seal including organic abradable material
US3701536A (en) * 1970-05-19 1972-10-31 Garrett Corp Labyrinth seal
US4139376A (en) * 1974-02-28 1979-02-13 Brunswick Corporation Abradable seal material and composition thereof
US4177004A (en) 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
US4257735A (en) * 1978-12-15 1981-03-24 General Electric Company Gas turbine engine seal and method for making same
US5326647A (en) * 1991-09-18 1994-07-05 Mtu Motoren- Und Turbinen-Union Abradable layer for a turbo-engine and a manufacturing process

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2019238A1 (fr) * 2007-07-25 2009-01-28 Siemens Aktiengesellschaft Couche de frottement pour un joint d'étanchéité d'un arbre de rotation et procédé d'application
US8500397B2 (en) 2007-12-04 2013-08-06 Hitachi, Ltd. Seals in steam turbine
EP2372103B1 (fr) * 2007-12-04 2015-04-15 Mitsubishi Hitachi Power Systems, Ltd. Joint de turbine à vapeur
EP2410133A1 (fr) * 2010-07-22 2012-01-25 Siemens Aktiengesellschaft Turbine à gaz et procédé d'étanchéification de courants de fuites
GB2492546A (en) * 2011-07-04 2013-01-09 Alstom Technology Ltd A labyrinth seal for an axial fluid flow turbomachine
US9057279B2 (en) 2011-07-04 2015-06-16 Alstom Technology Ltd Labyrinth seals
EP2647795A1 (fr) * 2012-04-04 2013-10-09 MTU Aero Engines GmbH Système d'étanchéité pour turbomachine
EP2647796A1 (fr) * 2012-04-04 2013-10-09 MTU Aero Engines GmbH Système d'étanchéité pour turbomachine
ITUB20155442A1 (it) * 2015-11-11 2017-05-11 Ge Avio Srl Stadio di un motore a turbina a gas provvisto di una tenuta a labirinto
EP3168427A1 (fr) * 2015-11-11 2017-05-17 Ge Avio S.r.l. Étage de moteur de turbine à gaz muni d'un joint à labyrinthe
EP3290645A1 (fr) * 2016-08-30 2018-03-07 Mitsubishi Hitachi Power Systems, Ltd. Segment pour dispositif d'étanchéité, rotor de turbine et turbine le comprenant
EP3722561A1 (fr) * 2019-04-11 2020-10-14 Mitsubishi Hitachi Power Systems, Ltd. Rotor de turbine à vapeur et turbine à vapeur

Also Published As

Publication number Publication date
CN1328481C (zh) 2007-07-25
US20030107181A1 (en) 2003-06-12
EP1278944A1 (fr) 2003-01-29
CN1427921A (zh) 2003-07-02
WO2001083951A1 (fr) 2001-11-08
US6962342B2 (en) 2005-11-08
JP2003532014A (ja) 2003-10-28

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