EP2184443A1 - Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe - Google Patents

Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe Download PDF

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Publication number
EP2184443A1
EP2184443A1 EP08019366A EP08019366A EP2184443A1 EP 2184443 A1 EP2184443 A1 EP 2184443A1 EP 08019366 A EP08019366 A EP 08019366A EP 08019366 A EP08019366 A EP 08019366A EP 2184443 A1 EP2184443 A1 EP 2184443A1
Authority
EP
European Patent Office
Prior art keywords
turbine
blade
gas turbine
blade root
disk
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Withdrawn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
EP08019366A
Other languages
German (de)
English (en)
French (fr)
Inventor
Nicholas Martin
Christoph Schiefer
Peter Schröder
Bernd Van Den Toorn
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 EP08019366A priority Critical patent/EP2184443A1/de
Priority to PCT/EP2009/061757 priority patent/WO2010052053A1/de
Priority to RU2011122606/06A priority patent/RU2499890C2/ru
Priority to JP2011533645A priority patent/JP5226876B2/ja
Priority to EP09824440A priority patent/EP2342425B1/de
Priority to US13/127,604 priority patent/US8657577B2/en
Priority to CN200980144347.0A priority patent/CN102216567A/zh
Publication of EP2184443A1 publication Critical patent/EP2184443A1/de
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the invention relates to a gas turbine with a number of guide vanes combined by means of a guide vane carrier on a turbine housing and with a number of rotor blades, each arranged on a turbine disk rotor blades each having a blade root.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or blade rows, are arranged thereon.
  • a turbine disk is usually provided for each turbine stage, to which the blades are fastened by means of their blade root.
  • For guiding the flow of the working medium in the turbine unit also commonly associated between adjacent blade rows with the turbine housing and combined into rows of guide vanes are arranged.
  • the combustor of the gas turbine may be embodied as a so-called annular combustor wherein a plurality of burners circumferentially disposed about the turbine shaft into a common, high temperature resistant combustor Surrounding wall surrounding the combustion chamber space opens.
  • the combustion chamber is designed in its entirety as an annular structure.
  • a plurality of combustion chambers In addition to a single combustion chamber can also be provided a plurality of combustion chambers.
  • first row of guide vanes of a turbine unit which, together with the blade row immediately downstream in the flow direction of the working medium, forms a first turbine stage of the turbine unit, which is usually followed by further turbine stages.
  • sealing plates are usually provided on the turbine disks, which are mounted circumferentially circularly on the turbine disk on the respective surfaces normal to the turbine axis.
  • a sealing plate is usually provided per turbine blade on each side of the turbine disk.
  • the sealing plates fulfill even more functions. On the one hand they form the axial fixation of the turbine blades by appropriate fasteners, on the other hand they not only seal the turbine disk against penetration of hot gas from the outside, but also avoid leakage of guided inside the turbine disk cooling air, which usually forwarded to the cooling of the turbine blades in selbige becomes.
  • the invention is therefore based on the object to provide a gas turbine, which allows a simplified construction while maintaining the greatest possible operational safety and the greatest possible efficiency.
  • the invention is based on the consideration that a simplified construction of the gas turbine, in particular in the area of the turbine disks, would be possible if the hitherto customary construction could be simplified with scale-like sealing plates. A particularly simple embodiment would be possible in particular if the sealing plates could be completely eliminated. The problem here, however, is the resulting lack of fixation of the turbine blades in the axial direction. If the sealing plates are omitted, axial fixing of the turbine blades should therefore take place in a different manner. Is to arranged between the respective blade root and the turbine shaft, a backup plate, which allows a particularly simple fixation of the blade root on the turbine disk and can be flexibly adapted to the respective geometric requirements of the fixation.
  • the respective securing plate advantageously comprises a number of bends. These include the turbine disk in the axial direction and thus enable a secure fixation.
  • a fixation by folds is also particularly easy to manufacture by the not yet folded, flat locking plate is first fixed to the blade root of the turbine screw, the blade root is inserted with the backup plate and then the backup plate is folded for axial fixation. As a result, a particularly simple installation is possible in addition to secure fixation.
  • the respective blade root advantageously comprises first a number of grooves extending substantially azimuthally with respect to the turbine shaft, and furthermore the respective securing plate a number of springs arranged such that they are positively connected with the grooves of the blade root.
  • the grooves thus serve as a receptacle for corresponding springs on the backup plate.
  • the respective locking plate comprises a number of cooling air holes.
  • sealing plates are not only the axial fixation of the blades, but also seal the blade root against hot gas, which could penetrate from the interior towards the turbine shaft and could cause damage there.
  • a corresponding sealing by other components should be realized.
  • no new components should be added, but the sealing function should be realized by existing components by appropriate modifications.
  • sealing wings which each extend to the adjacent guide blade rows, should be fastened to the blade roots of the rotor blades.
  • the respective sealing wing extends with respect to the turbine shaft substantially in the axial and azimuthal directions.
  • the sealing takes place in a plane perpendicular to the potential penetration direction of the hot working medium.
  • complete sealing of the region lying below the blade root in the direction of the turbine shaft is achieved against hot gas flowing inside the gas turbine.
  • the respective blade root in each case has a sealing wing in both axial directions. This makes it possible to achieve a seal against penetrating hot gas on both sides of the turbine blade.
  • such a gas turbine is used in a gas and steam turbine plant.
  • the advantages associated with the invention are in particular that by the introduction of locking plates between the blade root and turbine disk of a gas turbine the previously customary sealing plates can be omitted, so that a much simplified and cheaper construction of the gas turbine is possible.
  • the design of the entire blade row is thereby considerably simplified, in addition, the weight can be reduced so that fewer mechanical loads occur and the turbine disk can be made correspondingly smaller and cheaper.
  • the previously required complex grooves for fixing the sealing plate in the turbine disk can be omitted.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a non-illustrated Generator or a working machine.
  • the turbine unit 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine unit 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6.
  • Each blade 12 is fixed in a similar manner via a platform 19 on the turbine shaft 8.
  • a guide ring 21 is arranged on a guide blade carrier 16 of the turbine unit 6.
  • the outer surface of each guide ring 21 is also exposed to the hot, the turbine unit 6 flowing through the working medium M and spaced in the radial direction from the outer end of the opposite blades 12 through a gap.
  • the guide rings 21 arranged between adjacent rows of guide blades serve in particular as cover elements which protect the inner housing 16 in the guide blade carrier or other housing installation parts from thermal overstress by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 around.
  • FIG. 2 shows in detail a section through the outer periphery of a mounted on the turbine shaft 8 turbine disk a blade stage of the turbine unit 6 according to the prior art.
  • a blade 12 is arranged in a blade holding groove 30 with its blade root 32.
  • the blade root 32 of the blade 12 is fir-tree-shaped in cross-section and corresponds to the Christmas tree shape of the blade holding groove 30.
  • the schematic representation of the contour of the blade root 32 and the blade holding groove 30 is compared to the rest of the representation of FIG. 2 played rotated by 90 °.
  • the illustrated blade containment groove 30 extends between the side surfaces 34 of the turbine disk 36.
  • head ends of guide vanes 14 are schematically indicated, which - viewed in the flow direction of the working medium of the gas turbine - are arranged upstream and downstream of the rotor blade 12.
  • the vanes 14 are arranged radially in wreaths.
  • the vanes 14 of each ring are stabilized by a head side provided mounting ring 38.
  • sealing disks 40 are used circumferentially on each of the side walls 34 in a scale-like manner. These are held on their upper side in a groove 42 introduced into the rotor blade 12 and fixed on its underside by a securing bolt 44.
  • the sealing plates 40 also provide for an axial fixation of the blade root 32 in the blade root groove 30 and secure it against axial displacement. The radial and azimuthal securing has already been achieved by the Christmas tree shape of the blade retaining groove 30. Furthermore, the sealing plates 40 prevent leakage of cooling air channels 48 introduced through the turbine disk 36 into the blade root 32 and the rotor blade 12.
  • the blade 12 and the adjacent vanes 14 can be seen with the corresponding attachments.
  • sealing plates 40, 32 are mounted directly on the blade root 32 sealing wings 50. These prevent penetration of hot working medium from the interior of the gas turbine 1 into the areas in the vicinity of the turbine shaft.
  • grooves 52 extending substantially azimuthally with respect to the turbine shaft are inserted in the blade root. These engage in springs 54 of the backup plate 56 a.
  • the securing plate 56 is provided with folds 58, which engage in corresponding recesses 60 of the turbine disk 36.
  • Such a construction is also particularly easy to manufacture:
  • the backup plate 56 is not folded before assembly so know so no bends 58.
  • the springs 54 of the backup plate 56 are first inserted into the grooves 52. Subsequently, the blade root 32 is pushed into the blade holding groove 30 and the backup plate folded and thus fixed.
  • the backup plate 56 is enlarged again in FIG. 4 shown. Clearly visible are the springs 54 for fixing the blade root 32 of the blade 12 and the bends 58 for fixing on the turbine disk 36.
  • the fuse plate 56 also has a number of cooling air holes 62, so that a passage of cooling air from the interior of the turbine disk 36 in the blade root 32 and in the blade 12 is ensured.

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)
EP08019366A 2008-11-05 2008-11-05 Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe Withdrawn EP2184443A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP08019366A EP2184443A1 (de) 2008-11-05 2008-11-05 Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe
PCT/EP2009/061757 WO2010052053A1 (de) 2008-11-05 2009-09-10 Gasturbine mit sicherungsplatte zwischen schaufelfuss und scheibe
RU2011122606/06A RU2499890C2 (ru) 2008-11-05 2009-09-10 Газовая турбина, снабженная предохранительной пластиной между ножкой лопатки и диском
JP2011533645A JP5226876B2 (ja) 2008-11-05 2009-09-10 ブレードルートとディスクとの間にロック用プレートを有したガスタービン
EP09824440A EP2342425B1 (de) 2008-11-05 2009-09-10 Gasturbine mit sicherungsplatte zwischen schaufelfuss und scheibe
US13/127,604 US8657577B2 (en) 2008-11-05 2009-09-10 Gas turbine with securing plate between blade base and disk
CN200980144347.0A CN102216567A (zh) 2008-11-05 2009-09-10 叶片根部与叶轮盘之间具有安全板的燃气涡轮机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08019366A EP2184443A1 (de) 2008-11-05 2008-11-05 Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe

Publications (1)

Publication Number Publication Date
EP2184443A1 true EP2184443A1 (de) 2010-05-12

Family

ID=40521729

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08019366A Withdrawn EP2184443A1 (de) 2008-11-05 2008-11-05 Gasturbine mit Sicherungsplatte zwischen Schaufelfuss und Scheibe
EP09824440A Not-in-force EP2342425B1 (de) 2008-11-05 2009-09-10 Gasturbine mit sicherungsplatte zwischen schaufelfuss und scheibe

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09824440A Not-in-force EP2342425B1 (de) 2008-11-05 2009-09-10 Gasturbine mit sicherungsplatte zwischen schaufelfuss und scheibe

Country Status (6)

Country Link
US (1) US8657577B2 (ru)
EP (2) EP2184443A1 (ru)
JP (1) JP5226876B2 (ru)
CN (1) CN102216567A (ru)
RU (1) RU2499890C2 (ru)
WO (1) WO2010052053A1 (ru)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2514923A1 (de) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Blendeneinrichtung, integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8905716B2 (en) 2012-05-31 2014-12-09 United Technologies Corporation Ladder seal system for gas turbine engines
EP2725191B1 (en) * 2012-10-23 2016-03-16 Alstom Technology Ltd Gas turbine and turbine blade for such a gas turbine
JP6613611B2 (ja) * 2015-05-15 2019-12-04 株式会社Ｉｈｉ タービンブレード取付構造
CN107030244B (zh) * 2017-04-18 2018-08-31 中国科学院工程热物理研究所 一种用于转子榫连接锁销装配的工装结构
WO2020023005A1 (en) * 2018-07-23 2020-01-30 Siemens Aktiengesellschaft Cover plate with flow inducer and method for cooling turbine blades
GB2607886A (en) * 2021-06-11 2022-12-21 Siemens Energy Global Gmbh & Co Kg Rotor assembly and method of assembling a rotor assembly for a gas turbine engine
CN113464211B (zh) * 2021-07-19 2024-02-09 中国联合重型燃气轮机技术有限公司 燃气轮机用密封板及燃气轮机

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GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
DE1802931U (de) * 1959-08-07 1959-12-24 Entwicklungsbau Pirna Veb Verriegelungsblech fuer mit tannenbaumfuessen versehene laufradschaufeln von gasturbinen u. dgl.
US4029436A (en) * 1975-06-17 1977-06-14 United Technologies Corporation Blade root feather seal
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
EP0340149A1 (en) * 1988-04-25 1989-11-02 United Technologies Corporation Dirt removal means for air cooled blades
DE19925774A1 (de) * 1999-06-05 2000-12-07 Asea Brown Boveri Axiale Sicherungseinrichtung für Laufschaufeln axial durchströmter Turbomaschinen
DE10031116A1 (de) * 2000-06-26 2002-01-03 Abb Turbo Systems Ag Baden Axiale Sicherungseinrichtung für Laufschaufeln axial durchströmter Turbomaschinen
DE10140259C1 (de) * 2001-08-16 2003-01-30 Man B & W Diesel Ag Axialturbine
EP1703078A1 (de) * 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Biegevorrichtung und Verfahren zum Biegen eines Sicherungsbleches in einem Verdichter oder einer Turbine
US20080253895A1 (en) * 2007-04-12 2008-10-16 Eugene Gekht Blade retention system for use in a gas turbine engine

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Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB643914A (en) * 1948-03-08 1950-09-27 Joseph Stanley Hall Improvements in and relating to turbine or like blade securing means
DE1802931U (de) * 1959-08-07 1959-12-24 Entwicklungsbau Pirna Veb Verriegelungsblech fuer mit tannenbaumfuessen versehene laufradschaufeln von gasturbinen u. dgl.
US4029436A (en) * 1975-06-17 1977-06-14 United Technologies Corporation Blade root feather seal
US4470757A (en) * 1982-02-25 1984-09-11 United Technologies Corporation Sideplate retention for a turbine rotor
EP0340149A1 (en) * 1988-04-25 1989-11-02 United Technologies Corporation Dirt removal means for air cooled blades
DE19925774A1 (de) * 1999-06-05 2000-12-07 Asea Brown Boveri Axiale Sicherungseinrichtung für Laufschaufeln axial durchströmter Turbomaschinen
DE10031116A1 (de) * 2000-06-26 2002-01-03 Abb Turbo Systems Ag Baden Axiale Sicherungseinrichtung für Laufschaufeln axial durchströmter Turbomaschinen
DE10140259C1 (de) * 2001-08-16 2003-01-30 Man B & W Diesel Ag Axialturbine
EP1703078A1 (de) * 2005-03-17 2006-09-20 Siemens Aktiengesellschaft Biegevorrichtung und Verfahren zum Biegen eines Sicherungsbleches in einem Verdichter oder einer Turbine
US20080253895A1 (en) * 2007-04-12 2008-10-16 Eugene Gekht Blade retention system for use in a gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2514923A1 (de) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Blendeneinrichtung, integral beschaufelter Rotorgrundkörper, Verfahren und Strömungsmaschine

Also Published As

Publication number Publication date
RU2011122606A (ru) 2012-12-20
WO2010052053A1 (de) 2010-05-14
JP5226876B2 (ja) 2013-07-03
US20110268564A1 (en) 2011-11-03
EP2342425A1 (de) 2011-07-13
JP2012510580A (ja) 2012-05-10
US8657577B2 (en) 2014-02-25
CN102216567A (zh) 2011-10-12
RU2499890C2 (ru) 2013-11-27
EP2342425B1 (de) 2012-10-17

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