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EP3000981A1 - Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique - Google Patents

Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique Download PDF

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Publication number
EP3000981A1
EP3000981A1 EP14186779.6A EP14186779A EP3000981A1 EP 3000981 A1 EP3000981 A1 EP 3000981A1 EP 14186779 A EP14186779 A EP 14186779A EP 3000981 A1 EP3000981 A1 EP 3000981A1
Authority
EP
European Patent Office
Prior art keywords
ring
ring segments
wear protection
wear
compressor
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Withdrawn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
EP14186779.6A
Other languages
German (de)
English (en)
Inventor
Klaus-Peter Bur
Andreas Böttcher
Maria Etzold
Thomas Grieb
Patrick Lapp
Katrin Linnemann
Andreas Mann
Britta Puyn
Achim Schirrmacher
Michael Winterstein
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 EP14186779.6A priority Critical patent/EP3000981A1/fr
Priority to EP15774558.9A priority patent/EP3169875B1/fr
Priority to PCT/EP2015/072114 priority patent/WO2016050641A1/fr
Priority to CN201580052577.XA priority patent/CN107075963B/zh
Publication of EP3000981A1 publication Critical patent/EP3000981A1/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Withdrawn legal-status Critical Current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
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the invention relates to a connection arrangement of a compressor blade equipped with a plurality of vanes of a compressor with at least two interacting ring segments of the compressor guide and with sealing elements for sealing expansion joints formed by the two ring segments.
  • the invention further relates to a turbine or a compressor with at least one compressor guide disc comprising at least two ring segments.
  • a gas turbine for example, essentially consists of a compressor device, a combustion chamber device and the actual turbine device.
  • the compressor device By means of the compressor device, air drawn in from the surroundings is compressed and then fed to the combustion chamber device, in which a fuel (fuel gas) mixed with the compressed air is burned under similar pressure conditions as in the compressor device as an air-fuel mixture. Following this, this air-fuel mixture in the turbine device is depressurized while performing work to ambient pressure.
  • the inner ring here consists of two ring parts, which serve to define pronounced on the respective Leitschaufelfuß retaining elements of the individual vanes, wherein the two ring parts are designed such that they firmly surround these holding elements. As a rule, these ring parts are welded together.
  • the disk-type compressor guide disk can be composed of different numbers of ring segments arranged around the rotor axis, wherein a division of the compressor guide disk into at least two halves is required in order to be able to carry out, for example, maintenance measures.
  • the individual ring segments are fixed to each other at interfaces, these interfaces must also be sealed in order to separate successively connected compressor stages on the inner ring better from each other.
  • an expansion joint is provided in each case in order to be able to compensate for thermally induced expansion differences with respect to the individual ring segments, wherein different connection variations exist with regard to the interfaces.
  • connection variant provides a tooth arrangement, in which the mutually facing end faces of the two circumferentially immediately adjacent ring segments each have a row of teeth whose teeth can engage in each other to fix the ring segments to each other.
  • Another connection variant provides a sealing element with a cross-sealing sheet with at least two intersecting and thereby interlocking sealing sheet metal elements, which thereby lie in grooves located in the inner ring.
  • cross-sealing sheets fix the ring segments to each other and on the other hand seal the expansion joint between these ring segments well.
  • connection variants are poor or no sealing effects between the individual ring segments, an undesirably high wear on the ring segments of the inner ring or its ring parts and / or a material fatigue caused breaking out of material parts on the components of the connection arrangement, whereby there is a risk that relevant outbreaks get into the flow path of the compressor and / or the turbine and cause even greater damage there.
  • connection arrangement of equipped with a plurality of vanes Ver Whyrleitput a compressor with at least two interacting ring segments of Ver Whyrleitrise and with sealing elements for sealing formed by the two ring segments expansion joints, wherein this connection arrangement is characterized by wear protection means to reduce a conditional by the sealing elements wear on the at least two interacting ring segments.
  • connection arrangement according to the invention is designed such that the material of the ring segments in the areas less wear, in which the expansion elements are arranged and could come into direct contact or contact with the ring segments. This significantly reduces the risk of unpredictable material eruptions on the ring segments.
  • the wear protection means are preferably chosen such that the material of the ring segments wears less strongly than the material of the sealing elements.
  • connection arrangement essentially comprises the at least two interacting ring segments of the compressor guide disk as well as the sealing elements for sealing expansion joints formed by the two ring segments and also the present wear protection means.
  • the present disc-shaped compressor guide disk consists essentially of an inner ring, of an outer ring and of a multiplicity of guide vanes held by the inner ring and the outer ring.
  • the inner ring is in this case subdivided into at least two arcuate ring segments, which are arranged concentrically around the compressor or turbine central axis to form the inner ring.
  • arcuate ring segments are connected to each other at their respective end faces facing each other such that they form the inner ring.
  • these arcuate ring segments in turn consist of two interconnected ring parts or inner ring parts, which are designed such that the plurality of vanes are held concentrically around the compressor or turbine central axis around.
  • these ring parts are welded together after insertion of the guide vanes in one of the ring parts and the subsequent bringing together of the mutually corresponding ring parts.
  • the guide vanes are arranged in total in the respective ring segment at a defined distance fixed to each other.
  • the inner ring is composed of at least two arcuate ring segments, which in turn consist of at least two ring segment parts.
  • the structure described above with respect to the inner ring may also apply to the outer ring of the compressor guide.
  • connection arrangement according to the invention can advantageously be used on a wide variety of compressors or turbines with such compressors, such as gas turbines or the like, in order to significantly reduce the risk of malfunctions there.
  • the object of the invention is also achieved by a turbine or a compressor having at least one compressor guide disc comprising at least two ring segments, wherein the compressor guide disc has a connection arrangement according to one of the features described here.
  • the present anti-wear agents can be of various types to the ring segments or the ring parts in a region in which the sealing elements are arranged to better protect against wear can.
  • the present wear protection agents are solid-state wear protection agents which are connected in a form-fitting and / or materially bonded manner to the ring segments or their ring parts.
  • the wear protection means are arranged stationary relative to the ring segments or their ring parts.
  • the wear protection means comprise a wear protection sleeve, which is arranged at least partially between the sealing means and the at least two interacting ring segments.
  • a wear protection sleeve is arranged between the sealing means and the ring segment surfaces of the ring segments, which at least partially surrounds the sealing means such that they are held at a distance from the ring segments, the risk of premature wear of the ring segments due to an effective contact between the sealing elements and the ring segments can be completely ruled out ,
  • wear sleeve in the context of the invention describes any components which can be arranged between a sealing element and a ring segment such that this ring segment is shielded from the sealing element.
  • the sealing element is not in direct contact with the ring element.
  • the wear protection sleeve has at least two insertion grooves arranged at right angles to one another, into which the sealing means can be inserted.
  • a cross-seal plate arrangement can be provided.
  • the sealing elements can still be positioned exactly in the inner ring part.
  • the wear protection sleeve is arranged between two ring parts of the at least two interacting ring segments. It is not only advantageous if the wear sleeve with respect to two opposing ring segments reduces wear, but also with respect to two ring parts of a ring segment.
  • the wear protection sleeve can be even better integrated into the connection arrangement when the wear protection sleeve is arranged directly adjacent to two annular parts forming the ring segment.
  • the wear sleeve is arranged in sealing element receiving grooves at least one of the ring segments, so that the wear protection sleeve can be particularly intimately connected to the ring segments.
  • the wear protection means at least partially in operative contact with the sealing elements Coming ring segment surfaces applied wear protection layer.
  • Such a wear protection layer can be obtained by plating, nitriding or the like of the respective regions.
  • a very good wear protection can be achieved if the wear protection layer is arranged in a region of end faces of the at least two interacting ring segments.
  • end faces denotes those surface regions of the ring segments or the ring parts of the ring segments which are present at the opposite ends of the ring segments.
  • These surface areas may also relate to the ring segments or the ring parts of the ring segments existing grooves or the like.
  • an embodiment variant which is advantageous in this respect provides for the wear-resistant layer to be arranged on surfaces of sealing element receiving grooves of the at least two interacting ring segments.
  • the ring segments can be better protected against wear by the sealing elements, if the wear protection layer is harder than a ring segment material.
  • the wear protection means comprise sealing means which are made softer than the at least two interacting ring parts.
  • Another structurally advantageous realization of the wear protection means is to make the sealing means softer than the ring segments directly in operative contact with them. In this way it can be avoided that the areas of the ring segments or the ring parts of the ring segments, which come into direct contact with the sealing means, wear out faster due to this contact.
  • a particularly good sealing in the region of the expansion joint between two ring segments can be achieved if the present sealing elements comprise two intermeshing cross-sealing sheet metal elements.
  • the at least two mutually interacting ring segments are two seated on a rotor shaft or a rotor disk ring segments of an inner ring of the Verêtrleitin.
  • a preferred embodiment provides that the at least two mutually interacting ring segments are each assembled from at least two ring parts.
  • connection assembly 1 is partially shown with respect to a compressor baffle 2 of a compressor (not shown) of a turbine (not shown), this connection assembly 1 essentially comprising two interacting ring segments 3 (shown only by way of example) and a sealing element 4 for sealing one between the two two ring segments 3 provided expansion joint 5 includes.
  • the compressor baffle 2 consists essentially of an inner ring 6, an outer ring (not shown) and a plurality of supported by the inner ring 6 and the outer ring Vanes 107 (see example only figures 2 and 3, numbered only as an example).
  • This inner ring 6 is composed of a plurality of concentric about an axis of rotation (not shown) of the Ver Whyrleita 2 arranged around ring segments 3 together.
  • the Ver Whyrleita 2 is characterized by a plurality of connection assemblies 1.
  • the ring segments 3 are each assembled from two ring parts 8 and 9, wherein the two ring parts 8 and 9 are welded together.
  • the sealing element 4 consists in this first embodiment of a Wiendichtblechelement 10, which in turn consists of two nested and perpendicular to each other arranged sealing plates 11 and 12.
  • connection arrangement 1 still has wear protection means 15, by means of which wear on a region of the two interacting ring segments 3 can be reduced, in which the funneldichtblechelement 8 comes into contact with the ring members 6 and 7 of the respective ring segment 3.
  • the material of the ring segments 3 is less strained by the wear protection means 15.
  • the wear protection means 15 comprise a wear sleeve 16 which is integrated in the connection arrangement 1 such that the cross-sealing sheet element 8 does not come into direct contact with the ring parts 8 and 9 and thus also not directly with the two ring segments 3 forming the expansion joint 5 ,
  • the wear sleeve 16 is in this case made of a material which is softer than the material of the ring segments third or the ring parts 8 and 9, so that the wear sleeve 16 is subject to wear rather than the ring segments third
  • the wear sleeve 16 has at least two mutually perpendicular insertion grooves 17 and 18, in which the sealing plates 11 and 12 of the funneldichtblechelements 10 and the sealing element 4 are inserted.
  • the wear sleeve 16 is arranged directly adjacent to the two ring segment 8 forming the respective ring segment 8 and 9, so that the softer wear sleeve 16 directly (numbered only exemplarily here) of the respective ring segment 3 and the respective ring member 8 and 9 is in operative contact.
  • connection arrangement 101 is partially shown with respect to a compressor guide disk 102 of another compressor (not shown) of another turbine (not shown here), said connection arrangement 101 essentially comprising two interacting ring segments 103 (FIG. shown only by way of example) and a sealing element, not shown here, for sealing an expansion joint 105 provided between the two ring segments 103.
  • the sealing element, not shown, is formed in this further embodiment in the form of a funneldichtblechelements with two sealing plates (see. FIG. 1 ).
  • the compressor baffle 102 essentially consists of an inner ring 106, an outer ring (not shown) and a plurality of vanes 107 supported by the inner ring 106 and the outer ring.
  • the inner ring 106 in turn is composed of several concentric about an axis of rotation (not shown) of the Ver Whyrleitrise 102 arranged around ring segments 103 together.
  • the Ver Whyrleitrise 102 includes several such connection assemblies 1.
  • the ring segments 103 are again joined together from two ring parts 108 and 109.
  • connection arrangement 101 has wear protection means 115 which comprise a wear protection layer 130 applied at least partially to the ring segment surfaces 119 coming into operative contact with the sealing element (numbered only as an example).
  • This wear protection layer 130 is at least in this further embodiment harder than the material of the ring segments 103, so that the ring segments 103 are very well protected against wear caused by the sealing elements.
  • this wear protection layer 130 is only in the range of formed by the ring segments 103 end faces 133 (numbered only as an example) again.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP14186779.6A 2014-09-29 2014-09-29 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique Withdrawn EP3000981A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP14186779.6A EP3000981A1 (fr) 2014-09-29 2014-09-29 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique
EP15774558.9A EP3169875B1 (fr) 2014-09-29 2015-09-25 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique
PCT/EP2015/072114 WO2016050641A1 (fr) 2014-09-29 2015-09-25 Système destiné à assurer l'étanchéité de l'interstice entre deux segments d'une couronne d'aubes fixes
CN201580052577.XA CN107075963B (zh) 2014-09-29 2015-09-25 用于密封导向叶片的两个区段之间的间隙的装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14186779.6A EP3000981A1 (fr) 2014-09-29 2014-09-29 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique

Publications (1)

Publication Number Publication Date
EP3000981A1 true EP3000981A1 (fr) 2016-03-30

Family

ID=51625912

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14186779.6A Withdrawn EP3000981A1 (fr) 2014-09-29 2014-09-29 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique
EP15774558.9A Not-in-force EP3169875B1 (fr) 2014-09-29 2015-09-25 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15774558.9A Not-in-force EP3169875B1 (fr) 2014-09-29 2015-09-25 Agencement pour étanchéifier la fente entre deux segments d'un anneau statorique

Country Status (3)

Country Link
EP (2) EP3000981A1 (fr)
CN (1) CN107075963B (fr)
WO (1) WO2016050641A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111120011B (zh) * 2018-10-30 2024-06-21 中国联合重型燃气轮机技术有限公司 静叶环

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1378689A2 (fr) * 2002-07-03 2004-01-07 ALSTOM (Switzerland) Ltd Joint pour l'étanchéité de l'interstice entre deux composants
GB2396193A (en) * 2002-12-10 2004-06-16 Alstom Technology Ltd A seal arrangement for sealing the junction between two parts f the housing of a gas turbine
US20040240986A1 (en) * 2003-05-29 2004-12-02 Burdgick Steven Sebastian Horizontal joint sealing system for steam turbine diaphragm assemblies
JP2005016324A (ja) * 2003-06-23 2005-01-20 Hitachi Ltd シール装置及びガスタービン
EP1808578A1 (fr) * 2006-01-12 2007-07-18 Rolls-Royce plc Dispositif d'étanchéité
US20080050236A1 (en) * 2006-08-24 2008-02-28 Siemens Power Generation, Inc. Thermally sprayed conformal seal
EP1918549A1 (fr) * 2005-08-23 2008-05-07 Mitsubishi Heavy Industries, Ltd. Structure d etancheite de systeme de combustion a turbine a gaz
EP2014875A2 (fr) * 2007-07-10 2009-01-14 United Technologies Corporation Systèmes de turbines à gaz avec joints d'étanchéité
US20100054932A1 (en) * 2008-09-03 2010-03-04 Siemens Power Generation, Inc. Circumferential Shroud Inserts for a Gas Turbine Vane Platform
EP2479384A2 (fr) * 2011-01-24 2012-07-25 United Technologies Corporation Ensemble de joint à languette à refroidissement de face
WO2013189883A1 (fr) * 2012-06-18 2013-12-27 Alstom Technology Ltd Joint entre des pièces statiques de turbine

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1378689A2 (fr) * 2002-07-03 2004-01-07 ALSTOM (Switzerland) Ltd Joint pour l'étanchéité de l'interstice entre deux composants
GB2396193A (en) * 2002-12-10 2004-06-16 Alstom Technology Ltd A seal arrangement for sealing the junction between two parts f the housing of a gas turbine
US20040240986A1 (en) * 2003-05-29 2004-12-02 Burdgick Steven Sebastian Horizontal joint sealing system for steam turbine diaphragm assemblies
JP2005016324A (ja) * 2003-06-23 2005-01-20 Hitachi Ltd シール装置及びガスタービン
EP1918549A1 (fr) * 2005-08-23 2008-05-07 Mitsubishi Heavy Industries, Ltd. Structure d etancheite de systeme de combustion a turbine a gaz
EP1808578A1 (fr) * 2006-01-12 2007-07-18 Rolls-Royce plc Dispositif d'étanchéité
US20080050236A1 (en) * 2006-08-24 2008-02-28 Siemens Power Generation, Inc. Thermally sprayed conformal seal
EP2014875A2 (fr) * 2007-07-10 2009-01-14 United Technologies Corporation Systèmes de turbines à gaz avec joints d'étanchéité
US20100054932A1 (en) * 2008-09-03 2010-03-04 Siemens Power Generation, Inc. Circumferential Shroud Inserts for a Gas Turbine Vane Platform
EP2479384A2 (fr) * 2011-01-24 2012-07-25 United Technologies Corporation Ensemble de joint à languette à refroidissement de face
WO2013189883A1 (fr) * 2012-06-18 2013-12-27 Alstom Technology Ltd Joint entre des pièces statiques de turbine

Also Published As

Publication number Publication date
WO2016050641A1 (fr) 2016-04-07
CN107075963A (zh) 2017-08-18
CN107075963B (zh) 2019-10-15
EP3169875A1 (fr) 2017-05-24
EP3169875B1 (fr) 2018-07-11

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