EP2129874A2 - Bague d'étanchéité pour des turbomachines - Google Patents

Bague d'étanchéité pour des turbomachines

Info

Publication number
EP2129874A2
EP2129874A2 EP08735648A EP08735648A EP2129874A2 EP 2129874 A2 EP2129874 A2 EP 2129874A2 EP 08735648 A EP08735648 A EP 08735648A EP 08735648 A EP08735648 A EP 08735648A EP 2129874 A2 EP2129874 A2 EP 2129874A2
Authority
EP
European Patent Office
Prior art keywords
sealing
segments
sealing ring
parting line
turbomachine
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Withdrawn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
EP08735648A
Other languages
German (de)
English (en)
Inventor
Stefan Brück
Eduard Jenikejew
Matthias Neef
Norbert Sürken
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
Publication of EP2129874A2 publication Critical patent/EP2129874A2/fr
Withdrawn legal-status Critical Current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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a composite of individual sealing segments sealing ring for turbomachines, wherein springs are mounted between the individual sealing segments and securing elements are provided for holding the sealing segments on the parting line of the turbomachine.
  • sealing elements of different types are used to seal different pressure chambers.
  • special sealing elements are often used, which are radially movable and can yield in the case of rotor vibrations or Rotorausschurgi.
  • resilient sealing segments wherein springs press the sealing elements radially in the direction of the shaft, or so-called “retractable seals”.
  • the springs are arranged between the segments, so that a ring of sealing elements is pushed away from the shaft and closes only during operation of the machine by the pressure drop over the sealed point.
  • the "retractable seals" technology is particularly suitable for turbines where large relative movement between the rotor and the housing is to be expected during startup and shutdown.
  • the sealing elements are then far enough away from the rotor, close at a certain pressure and fulfill their task as sealing elements under operating conditions. Important is the perfect and predictable function of closing the segments.
  • Object of the present invention is to provide a sealing ring of the type mentioned, in which the closing behavior is significantly improved.
  • the closing behavior can be significantly improved if the sealing segments are designed on the parting line so that adjacent sealing segments in the upper and lower part of the housing of the turbomachine mesh after assembly.
  • the sealing segment which first moves without friction on the parting line, takes along the other sealing segment.
  • the friction force is distributed at the parting line between two sealing segments. It can be shown that the difference between see beginning and end of the closing process compared to the known version can be reduced by 30%.
  • An expedient embodiment of the sealing ring according to the present invention is characterized in that one end of the sealing segment at the parting line has a projecting cylindrical pin extending in the axial direction of the turbomachine, which fits into a corresponding recess at the end of the adjacent sealing segment. This represents a particularly simple embodiment.
  • FIG. 1 shows the principle of "retractable seals” technology
  • FIG. 2 shows a known embodiment of a sealing ring according to the "retractable seal" technology
  • FIG. 3 shows a perspective view of the end of a sealing segment on the parting line according to the present invention
  • Figure 4 and Figure 5 schematically the closing of sealing segments in a known embodiment of the sealing ring
  • FIG. 1 shows the principle of a sealing ring according to the "re- tractable seals" technology.
  • the individual sealing segments are designated, which are pressed apart by springs 2 in the rest state.
  • the rotor 3 is located within the illustrated sealing ring.
  • the securing elements 4 are provided at the parting line of the housing of the turbomachine.
  • FIG. 2 shows a known embodiment in which the sealing segments 5, 6 are pressed apart by means of springs 7 and held by the securing elements 9 on the parting line of the housing of the turbomachine. Inside the sealing ring is the rotor 8.
  • Figure 3 shows a perspective view of one end of a sealing segment on the parting line according to the present invention.
  • one end of the sealing segment on the parting line is made with a projecting cylindrical pin which fits into a corresponding recess on the end of the adjacent sealing segment.
  • any other form-fitting connection is conceivable in which the parts are guided together in their radial movement, but the pressing apart in the circumferential direction is not hindered.
  • Figure 4 and Figure 5 show the movement of the sealing segments on the parting line in a known embodiment
  • Figure 6 and Figure 7 shows the movement of the sealing segments on the parting line according to a sealing ring, which is formed according to the present invention.
  • FIG. 4 and FIG. 6 respectively show the state before the closing of the sealing ring and FIGS. 5 and 7 show schematically the state after the closing of the sealing ring.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)

Abstract

La présente invention concerne une bague d'étanchéité pour des turbomachines, laquelle bague est composée de segments d'étanchéité individuels. Des ressorts sont montés entre les segments d'étanchéité individuels et des éléments de fixation sont prévus au niveau du joint de la turbomachine afin de maintenir les segments d'étanchéité. Afin d'assurer une fermeture sûre des éléments d'étanchéité, même au niveau du joint, les segments d'étanchéité au niveau du joint sont reliés les uns aux autres selon un assemblage par complémentarité de forme.
EP08735648A 2007-04-03 2008-04-01 Bague d'étanchéité pour des turbomachines Withdrawn EP2129874A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007016104A DE102007016104A1 (de) 2007-04-03 2007-04-03 Dichtungsring für Strömungsmaschinen
PCT/EP2008/053875 WO2008119800A2 (fr) 2007-04-03 2008-04-01 Bague d'étanchéité pour des turbomachines

Publications (1)

Publication Number Publication Date
EP2129874A2 true EP2129874A2 (fr) 2009-12-09

Family

ID=39675878

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08735648A Withdrawn EP2129874A2 (fr) 2007-04-03 2008-04-01 Bague d'étanchéité pour des turbomachines

Country Status (4)

Country Link
US (1) US8413993B2 (fr)
EP (1) EP2129874A2 (fr)
DE (1) DE102007016104A1 (fr)
WO (1) WO2008119800A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104197020A (zh) * 2014-08-15 2014-12-10 江苏透平密封高科技有限公司 一种用于轴端的径向动态可调接触式密封装置
AT522694B1 (de) 2019-11-29 2021-01-15 Zma Eng Gmbh Wellendichtung zum Abdichten von Rotoren
US20240318567A1 (en) * 2023-03-24 2024-09-26 General Electric Company Seal support assembly for a turbine engine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030141669A1 (en) * 2002-01-29 2003-07-31 Chevrette Richard Jon Retractable packing ring lower half segment retaining key and method for retaining retractable packing ring lower half segment

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1275581A (en) * 1969-10-20 1972-05-24 Copper Roller Bearings Company Improvements in or relating to shaft seals
US5395124A (en) * 1993-01-04 1995-03-07 Imo Industries, Inc. Retractible segmented packing ring for fluid turbines having gravity springs to neutralize packing segment weight forces
US5464226A (en) * 1993-12-06 1995-11-07 Demag Delaval Turbomachinery Corp. Turbocare Division Retractable packing rings for steam turbines
CN1215251C (zh) * 1996-08-05 2005-08-17 罗纳德·E·布兰登 流体涡轮机的密封装置
US5934684A (en) * 1997-05-27 1999-08-10 Brandon; Ronald Earl Retractable segmented packing ring for fluid turbines having gravity springs to neutralize packing segment weight forces
US6220603B1 (en) * 1998-07-13 2001-04-24 Ronald Earl Brandon Non retractable segmented packing ring for fluid turbines having special springs to reduce forces during shaft rubbing
EP1243755A1 (fr) * 2001-03-16 2002-09-25 Ronald E. Brandon Turbine à fluide élastique employant un anneau d'étanchéité
JP2002285802A (ja) * 2001-03-26 2002-10-03 Toshiba Corp 回転機械のラビリンスシール装置
US6695316B2 (en) * 2001-09-21 2004-02-24 General Electric Company Apparatus and methods for supporting a retractable packing ring

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030141669A1 (en) * 2002-01-29 2003-07-31 Chevrette Richard Jon Retractable packing ring lower half segment retaining key and method for retaining retractable packing ring lower half segment

Also Published As

Publication number Publication date
US20100164181A1 (en) 2010-07-01
WO2008119800A3 (fr) 2009-01-22
US8413993B2 (en) 2013-04-09
WO2008119800A2 (fr) 2008-10-09
DE102007016104A1 (de) 2008-10-09

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