EP2342425B1 - Turbine à gaz avec plaque de fixation entre la base d'aube et le disque - Google Patents

Turbine à gaz avec plaque de fixation entre la base d'aube et le disque Download PDF

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Publication number
EP2342425B1
EP2342425B1 EP09824440A EP09824440A EP2342425B1 EP 2342425 B1 EP2342425 B1 EP 2342425B1 EP 09824440 A EP09824440 A EP 09824440A EP 09824440 A EP09824440 A EP 09824440A EP 2342425 B1 EP2342425 B1 EP 2342425B1
Authority
EP
European Patent Office
Prior art keywords
turbine
rotor
blade
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.)
Not-in-force
Application number
EP09824440A
Other languages
German (de)
English (en)
Other versions
EP2342425A1 (fr
Inventor
Nicholas F. 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 EP09824440A priority Critical patent/EP2342425B1/fr
Publication of EP2342425A1 publication Critical patent/EP2342425A1/fr
Application granted granted Critical
Publication of EP2342425B1 publication Critical patent/EP2342425B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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 turbine rotor for a gas turbine with a number of each combined into blade rows, each arranged on a turbine disk blades each having a blade root, which is arranged in each case in an axially extending blade holding the turbine disk, wherein between the respective blade root and a groove bottom the blade holding groove is arranged a securing plate for securing blades against displacement along the blade holding groove, which is fixed by means of folds on the turbine disk.
  • 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 rotor.
  • 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 combustion chamber of the gas turbine may be embodied as a so-called annular combustion chamber, in which a plurality of circumferentially arranged around the turbine rotor burners in a common, surrounded by a high temperature resistant surrounding wall combustion chamber space opens.
  • the combustion chamber is designed in its entirety as an annular structure.
  • 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 circularly circumferentially 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.
  • An input called turbine rotor is in each case from EP 1 703 078 A1 . DE 199 25 774 A1 . GB 643,914 and DE 100 31 116 A1 known. Furthermore, from the US 4,470,757 It is known to adjust the amount of cooling air flowing into a blade by means of sheets provided therefor alone.
  • the invention is therefore based on the object of specifying a turbine rotor for a gas turbine, which, used in a gas turbine, while maintaining the greatest possible operational safety and maximum gas turbine efficiency allows a simplified design.
  • a cooling air supply duct opens in the groove bottom of the blade holding grooves for coolant supply
  • the respective backup plate a number of cooling air holes for Having passage of coolant and the respective blade root comprises two of them with respect to the turbine axis substantially azimuthally extending grooves and in which the respective locking plate comprises two springs which are arranged such that they are positively connected to seal with the grooves of the blade root.
  • 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 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.
  • a securing plate is arranged between the respective blade root and the turbine rotor, which enables a particularly simple fixation of the blade root on the turbine disk and can be adapted flexibly to the respective geometric requirements of the fixing.
  • the respective securing plate 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 In order to guarantee a secure axial connection of the blade root with the locking plate, includes the respective Blade root first a number of in relation to the turbine rotor substantially azimuthally extending grooves and further the respective locking plate a number of springs which are arranged such that they are positively connected to the grooves of the blade root.
  • the grooves thus serve as a receptacle for corresponding springs on the backup plate.
  • the respective backup plate comprises a number of cooling air holes.
  • cooling air can be introduced through the interior of the turbine disk and through the corresponding cooling air holes in the securing plate into the blade root and thus into the turbine blade, thus enabling reliable cooling of the turbine blade.
  • the blade Due to the blade to be cooled, it can be supplied with cooling air via a cooling air supply channel opening into the groove bottom of the retaining groove.
  • a cooling air supply channel opening into the groove bottom of the retaining groove.
  • the tongue and groove connection of blade root and locking plate on the one hand and the seat of the locking plate between the blade root underside and groove bottom on the other hand also designed as a seal.
  • the previously used 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 rotor and could cause damage there.
  • a corresponding seal should be realized by other components.
  • 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 rotor substantially in the axial and azimuthal direction.
  • 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 rotor 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 can be eliminated by the introduction of locking plates between the blade root and turbine disk of a gas turbine, the previously customary sealing plates, 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 generator, not shown, or a working machine.
  • the turbine unit 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine rotor 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 rotor 8.
  • the blades 12 are arranged in a ring shape on the turbine rotor 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 rotor 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 attached to the turbine rotor 8 in a similar manner via a platform 19.
  • 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 configured in the exemplary embodiment as a so-called annular combustion chamber, in which a plurality of burners 10 arranged around the turbine rotor 8 in the circumferential direction 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 rotor 8 around.
  • FIG. 2 shows in detail a section through the outer periphery of a mounted on the turbine rotor 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 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.
  • 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)

Claims (5)

  1. Rotor ( 8 ) de turbine pour une turbine à gaz,
    ayant un certain nombre d'aubes ( 12 ) mobiles rassemblées en des rangées d'aubes mobiles montées respectivement sur un flasque ( 36 ) de turbine, pouvant être refroidies et ayant respectivement une emplanture ( 32 ) d'aube qui est montée respectivement dans une rainure ( 30 ) du flasque ( 36 ) de turbine, destinée au maintien d'une aube mobile et s'étendant dans la direction axiale,
    dans lequel entre l'emplanture ( 32 ) de l'aube respective et un fond de la rainure ( 30 ) de maintien de l'aube mobile est disposée une plaque ( 56 ) de fixation pour empêcher les aubes ( 12 ) mobiles de se déplacer le long de la rainure ( 30 ) de maintien d'une aube mobile, plaque qui est immobilisée sur la flasque ( 36 ) de turbine au moyen de chanfreins ( 58 ), caractérisé en ce que,
    pour l'apport de fluide de refroidissement, un canal ( 48 ) d'apport d'air de refroidissement débouche au fond des rainures ( 30 ) de maintien d'aube mobile, en ce que la plaque ( 56 ) de fixation respective a un certain nombre de trous ( 62 ) d'air de refroidissement pour le passage du fluide de refroidissement et
    en ce que l'emplanture ( 32 ) d'aube respective comprend deux rainures ( 52 ) s'étendant de manière sensiblement azimutale par rapport à l'axe de la turbine et dans laquelle la plaque ( 56 ) de fixation respective comprend deux ressorts ( 54 ), qui sont disposés de manière à pouvoir être pour l'étanchéité reliés à complémentarité de forme avec les rainures ( 52 ) de l'emplanture ( 32 ) de l'aube.
  2. Rotor ( 8 ) de turbine suivant la revendication 1,
    dans lequel l'emplanture ( 32 ) de l'aube respective a une aile ( 50 ) d'étanchéité.
  3. Rotor ( 8 ) de turbine suivant la revendication 2,
    dans lequel l'aile ( 50 ) d'étanchéité respective s'étend sensiblement dans la direction axiale et azimutale par rapport à l'axe de la turbine.
  4. Rotor ( 8 ) de turbine suivant l'une des revendications 2 ou 3, dans lequel l'emplanture ( 32 ) de l'aube respective a une aile ( 50 ) d'étanchéité dans les deux directions axiales.
  5. Installation de turbine à gaz et de turbine à vapeur comprenant un rotor ( 8 ) de turbine suivant l'une des revendications 1 à 4.
EP09824440A 2008-11-05 2009-09-10 Turbine à gaz avec plaque de fixation entre la base d'aube et le disque Not-in-force EP2342425B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09824440A EP2342425B1 (fr) 2008-11-05 2009-09-10 Turbine à gaz avec plaque de fixation entre la base d'aube et le disque

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08019366A EP2184443A1 (fr) 2008-11-05 2008-11-05 Turbine à gaz avec plaque de fixation entre le pied d'aube et le disque
EP09824440A EP2342425B1 (fr) 2008-11-05 2009-09-10 Turbine à gaz avec plaque de fixation entre la base d'aube et le disque
PCT/EP2009/061757 WO2010052053A1 (fr) 2008-11-05 2009-09-10 Turbine à gaz avec plaque de fixation entre la base d'aube et le disque

Publications (2)

Publication Number Publication Date
EP2342425A1 EP2342425A1 (fr) 2011-07-13
EP2342425B1 true EP2342425B1 (fr) 2012-10-17

Family

ID=40521729

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08019366A Withdrawn EP2184443A1 (fr) 2008-11-05 2008-11-05 Turbine à gaz avec plaque de fixation entre le pied d'aube et le disque
EP09824440A Not-in-force EP2342425B1 (fr) 2008-11-05 2009-09-10 Turbine à gaz avec plaque de fixation entre la base d'aube et le disque

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08019366A Withdrawn EP2184443A1 (fr) 2008-11-05 2008-11-05 Turbine à gaz avec plaque de fixation entre le pied d'aube et le disque

Country Status (6)

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

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EP2514923A1 (fr) * 2011-04-18 2012-10-24 MTU Aero Engines GmbH Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine
US8905716B2 (en) 2012-05-31 2014-12-09 United Technologies Corporation Ladder seal system for gas turbine engines
EP2725191B1 (fr) * 2012-10-23 2016-03-16 Alstom Technology Ltd Turbine à gaz et aube de turbine pour une telle turbine à gaz
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
KR102495162B1 (ko) 2018-07-23 2023-02-06 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 유동 인듀서를 갖는 커버 플레이트 및 터빈 블레이드들을 냉각하기 위한 방법
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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Also Published As

Publication number Publication date
JP2012510580A (ja) 2012-05-10
EP2342425A1 (fr) 2011-07-13
WO2010052053A1 (fr) 2010-05-14
RU2499890C2 (ru) 2013-11-27
US20110268564A1 (en) 2011-11-03
RU2011122606A (ru) 2012-12-20
EP2184443A1 (fr) 2010-05-12
CN102216567A (zh) 2011-10-12
US8657577B2 (en) 2014-02-25
JP5226876B2 (ja) 2013-07-03

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EP2184449A1 (fr) Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice

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