EP1573172B1 - Turbine et procédé de démontage des aubes fixes d'une turbine - Google Patents

Turbine et procédé de démontage des aubes fixes d'une turbine Download PDF

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Publication number
EP1573172B1
EP1573172B1 EP03789132A EP03789132A EP1573172B1 EP 1573172 B1 EP1573172 B1 EP 1573172B1 EP 03789132 A EP03789132 A EP 03789132A EP 03789132 A EP03789132 A EP 03789132A EP 1573172 B1 EP1573172 B1 EP 1573172B1
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EP
European Patent Office
Prior art keywords
guide
blade
turbine
clamping device
rotor
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.)
Expired - Lifetime
Application number
EP03789132A
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German (de)
English (en)
Other versions
EP1573172A1 (fr
Inventor
Peter Tiemann
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 EP03789132A priority Critical patent/EP1573172B1/fr
Publication of EP1573172A1 publication Critical patent/EP1573172A1/fr
Application granted granted Critical
Publication of EP1573172B1 publication Critical patent/EP1573172B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Definitions

  • the present invention relates to a turbine according to the preamble of claim 1, and a method for removing the guide vanes of a turbine according to the preamble of claim 9.
  • the DE 606 029 discloses the production of a vane ring for steam or gas turbines in which strips or strips are wrapped around two rollers so that they assume an annular shape.
  • the bands or strips are provided with cutouts into which the blade is inserted.
  • weld the vane ring After inserting all blades, weld the vane ring.
  • the blades are first attached to the strips (which form the platforms) by means of spot welding, and the welding is then continued as build-up welding on the outside of the strips until a sufficient thickness of the weld metal has been formed, which is then partially turned off .can.
  • the welded vane ring is clamped in a lathe and processed until a cross-section schwalbenschwaazförmiger coaxial circumferential approach remains. Subsequently, the circumferential approach, ie the one-piece vane ring, mounted in a circular, tensioned by screws or rivets holder.
  • a vane carrier for a gas turbine is known.
  • the guide blade carrier has on its side facing the hot gas channel inside in its axial longitudinal extent a plurality of successively arranged grooves which are annular in the circumferential direction and are each provided with an undercut.
  • the grooves serve to receive vane feet of a vane. For this the foot of a vane is inserted in the circumferential direction in the annular groove.
  • the gas turbine is opened, so that the guide vane carrier is accessible and the guide vanes can be pushed out of the groove.
  • the opening of the gas turbine is time-consuming and requires a corresponding long standstill of the gas turbine.
  • Object of the present invention is to shorten the downtime of the turbine during repair, inspection and / or maintenance.
  • the inventive solution provides that the Leitschaufelfuß and / or Leitschaufelkopf each vane by means of an accessible from the combustion chamber, manually releasable clamping device is or can be fixed.
  • the downtime of a gas turbine can be shortened profitably by the exchangeable vane can be removed through the accessible combustion chamber.
  • at least one clamping device defining the guide blade can be reached from the combustion chamber.
  • One of the Leitschaufelfuß fixing clamping device is provided on the inner housing and / or the other clamping device defines the Leitschaufelkopf and is arranged on the mounting ring.
  • the clamping device can be fixed to the inner housing or to the fastening housing and the Leitschaufelfuß or Leitschaufelkopf clamped in an operating position by means of an axially extending tie rod.
  • the inner housing or the mounting ring serves as an abutment for the clamping device.
  • the tie rod clamps the clamping device once on the inner housing or on the mounting ring and once on the guide vane.
  • At least the part of the clamping device facing the combustion chamber can be removed from the clearance profile of the guide blade after removal of the tie rod for dismantling the guide vane by the combustion chamber.
  • the clearance profile of the vane is described by the contour of the vane, which results from the view of the combustion chamber in the axial direction. The vane is exposed after moving out of the clamping device from the clearance space.
  • the clamping device is fastened in a parking position exposing the vane foot or guide vane head, this can not hinder the removal of the guide vanes. Accidental entanglement of the clamping device with the vane during its removal of the vane is thus bypassed. Furthermore, the clamping device is effectively secured against accidental falling out. Unintentionally dropped components can cause mechanical damage during operation of the gas turbine.
  • the clamping device comprises two radially extending retaining stops, which can be clamped by means of the tie rod.
  • the two holding stops of a clamping device respectively encompass elements of the inner housing as an abutment and at the same time the Leitschaufelfuß or the Leitschaufelkopf.
  • the retaining stops are clamped by means of the tie rod.
  • the guide vane is located in the direction of flow of a working medium first vane row.
  • the guide vane is easier to reach from the combustion chamber.
  • the clamping device is removable after removal of the guide vane from the inner housing.
  • a guide ring arranged downstream in the flow direction of a working medium is manually accessible.
  • the wear-prone guide ring is thus, similar to the guide vane, particularly easily and quickly accessible for maintenance and / or repair work, without the inner casing of the turbine must be opened.
  • the invention provides that a guide blade of the first row of guide blades seen in the flow direction of the working medium is taken out manually through the combustion chamber by the sequence of the following steps:
  • the arranged on the inner housing clamping device is released, moved to a Leitschaufelfuß exposing parking position and fixed there again.
  • the further arranged on the inner mounting ring clamping device is released, so that the Leitschaufelkopf is exposed.
  • the guide vane is axially displaced against the direction of flow of the working medium, possibly moved radially inwards and tilted around the vane head, so that the vane is then free to move radially outward.
  • the Fig. 1 shows a gas turbine 1 in a longitudinal partial section.
  • the gas turbine 1 has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner.
  • a suction housing 4 Along the rotor 3 follow one another a suction housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17, which communicates with an annular hot gas duct 18.
  • There four successive turbine stages 10 form the turbine 8.
  • Each turbine stage 10 is formed of two blade rings.
  • As seen in the flow direction of a working medium 11 follows in the hot gas channel 18 a Leitschaufelsch 13 a formed of blades 15 row 14.
  • the vanes 12 are attached to the stator 23, whereas the blades 15 of a row 14 are mounted by means of a turbine disk 19 on the rotor 3.
  • air 16 is sucked and compressed by the compressor 4 through the intake housing.
  • the compressed air provided at the turbine-side end of the compressor 5 is led to the burners 7 where it is mixed with a fuel.
  • the mixture is then burned to form the working medium 11 in the combustion chamber 17.
  • the working medium 11 flows along the hot gas channel 18 past the guide vanes 12 and the blades 15.
  • the working fluid 11 relaxes impulsively, so that the blades 15 drive the rotor 3 and this the driven machine coupled to it.
  • the exposed to the hot working fluid 11 components are subject to thermal stresses during operation of the gas turbine 1.
  • the guide vanes 12 and rotor blades 15 of the first turbine stage 10, viewed in the direction of flow of the working medium 11, are subjected to the highest thermal stress in addition to the heat shield bricks which line the annular combustion chamber 6. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • Fig. 2 shows a section through the partially illustrated annular combustion chamber 6 and through the first turbine stage 10, which is formed from the guide vane 12 and the downstream blade 15.
  • the blades 12, 15 are arranged in a star shape around the rotor 3 of the gas turbine.
  • the blade 15 is seated on a turbine disk 19, which is arranged on the rotor 3, whereas the guide blade 12 on Stator is attached.
  • the vane 12 has a guide blade root 21 facing the inner casing 20 of the turbine 8 and a vane head 22 opposite the vane root 21.
  • the vane head 22 faces the rotor 3 and fixed to a mounting ring 24 of the stator 23.
  • the clamping device 25 Arranged on the guide blade root 21 and on the inner housing 20 is a clamping device 25 in an operating position.
  • the clamping device 25 comprises two retaining stops 26, 27 and a helical tie rod 28, which is only hinted at here.
  • the retaining stop 27 engages around a projection 29 formed on the guide blade root 21, which projection extends parallel to the axial direction of the rotor 3.
  • An extending in the radial direction of the rotor 3 further projection 30 is also formed on the Leitschaufelfuß 21.
  • This projection 30 protrudes between the two holding stops 26, 27 in such a way that they firmly clamp the projection 30 when the tie rod 28 is tensioned.
  • the inner housing 20 serves as an abutment for the clamping device 25, which defines the Leitschaufelfuß 21 and thus also the vane 12 itself.
  • the tie rod 28 extends through the inner housing 20, wherein it extends through an axial bore 32, which is slot-shaped seen in the radial direction. Radially closest to the outside, a projection 31 is arranged on the inner housing 20.
  • a further clamping device 35 is arranged in its operating position on the guide blade head 22 and on the fastening ring 24.
  • This has two holding stops 36, 37 which clamp by means of a tie rod 38 integrally formed on the guide vane head 22, radially projecting third projection 33 on the fastening ring 24.
  • the arranged on the guide blade root 21 clamping device 25 is achieved by the two holding stops 26, 27 are loosened by releasing the tie rod 28 so far that the retaining stop 27, the projection 29 releases. At the same time, the retaining stop 26 is displaced so far in the direction of the annular combustion chamber 6 that the projection 31 can be encompassed by this. Then the clamping device 25, i. the first retaining stop 26, the second retaining stop 27 and the tie rod 28, jointly moved radially outward. For this purpose, the axial bore 32 is formed slot-like in cross-section. In the radially outer position of the tie rod 28 is tensioned again, so that the clamping device 25 is fixed in its parking position. The Leitschaufelfuß 21 is completely released from her. Viewed from the viewpoint of the annular combustion chamber 6, the contour of the first holding stop 26 is located outside the contour of the guide blade root 21, i. the clamping device 25 is located outside the clearance of the guide vane 12th
  • the guide vane head 22 is exposed by, for this purpose, the tie rod 38 of the fastening ring 24 disposed on the clamping device 35 is released, so that the holding stops 36, 37 release a formed on the vane head 22 third projection 33.
  • the movable clamping device 35 is moved so far radially inward that it surrounds a projection 34 of the fastening ring 24. Then the clamping device 35 is braced again, so that it is in its parking position.
  • the clamping device 35 arranged on the guide blade head 22 is located outside the clearance profile of the guide blade 12.
  • the thus-exposed guide blade 12 can now be removed from the guide blade row 13, in which it is displaced counter to the flow direction of the working medium 11 and then slightly radially inward. This displacement is indicated by the arrow 40. Then, the vane 12 is tilted around the vane head 22 in the direction of the combustion chamber 6. Then, the guide vane 12 is moved into the combustion chamber 17 of the annular combustion chamber 6 and the gas turbine 1 removed.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une turbine (1) ainsi qu'un procédé de démontage d'une aube fixe (12) de turbine. La turbine (1) selon l'invention comprend un rotor (3) s'étendant en direction axiale, ainsi qu'une chambre de combustion (6) accessible qui communique avec un canal à gaz chaud annulaire (18) dans lequel sont disposées une pluralité d'aubes fixes (12) de façon à former une rangée d'aubes fixes (13). Selon l'invention, chaque aube fixe (12) comprend une emplanture d'aube fixe (21) qui est fixée sur le logement interne, ainsi qu'une tête d'aube fixe (22) qui est opposée à ladite emplanture (21), orientée vers le rotor (3) et fixée sur une bague de fixation (24) de la turbine (1) qui entoure ledit rotor (3). L'objectif de la présente invention est de réduire la durée d'inutilisation de cette turbine (1) lors des travaux de réparation, de révision et/ou d'entretien. A cet effet, l'emplanture (21) et/ou la tête (22) des aubes fixes peut/peuvent être fixée(s) au moyen d'un dispositif de serrage (25, 35) à démontage manuel.

Claims (9)

  1. Turbine ( 1 ) comprenant un rotor ( 3 ) s'étendant dans une direction axiale et une chambre de combustion ( 6 ) accessible, qui communique avec un canal ( 18 ) annulaire pour du gaz chaud, dans lequel une pluralité d'aubes ( 12 ) directrices est disposée en formant une rangée ( 13 ) d'aubes directrices,
    dans laquelle chaque aube directrice a une emplanture ( 21 ) d'aube directrice fixée au carter ( 20 ) intérieur et une tête ( 22 ) d'aube directrice opposée à l'emplanture ( 21 ) d'aube directrice tournée vers le rotor ( 3 ) et fixée à un anneau ( 24 ) de fixation de la turbine ( 1 ) entourant le rotor ( 3 ), caractérisée
    en ce que l'emplanture ( 21 ) de l'aube directrice et/ou la tête ( 22 ) de l'aube directrice de chaque aube ( 21 ) directrice peut être fixée ou sont fixées au moyen d'un dispositif ( 25, 35 ) de serrage accessible à partir de la chambre de combustion et pouvant être desserré manuellement.
  2. Turbine ( 1 ) suivant la revendication 1,
    caractérisée
    en ce que le dispositif ( 25, 35 ) de serrage est fixé au carter ( 20 ) intérieur ou à l'anneau ( 24 ) de fixation et serre l'emplanture ( 21 ) de l'aube directrice ou la tête ( 22 ) de l'aube directrice en une position de fonctionnement, au moyen d'un tirant ( 28, 38 ) s'étendant dans la direction axiale.
  3. Turbine ( 1 ) suivant la revendication 1 ou 2,
    caractérisée
    en ce que pour le démontage de l'aube ( 12 ) directrice par la chambre de combustion ( 6 ), au moins la partie tournée vers la chambre de combustion ( 6 ) du dispositif ( 25, 35 ) de serrage, peut être retirée après avoir desserré le tirant ( 28, 38 ) du profil d'espace libre de l'aube ( 12 ) directrice.
  4. Turbine ( 1 ) suivant l'une des revendications précédentes,
    caractérisée
    en ce que, pour retirer l'aube ( 12 ) directrice, le dispositif ( 25, 35 ) de serrage peut être fixé dans une position de repos mettant à découvert l'emplanture ( 21 ) de l'aube directrice et la tête ( 22 ) de l'aube directrice.
  5. Turbine ( 1 ) suivant l'une des revendications précédentes,
    caractérisée
    en ce que le dispositif ( 25, 35 ) de serrage comprend deux butées ( 26, 27, 36, 37 ) de maintien, s'étendant radialement et pouvant être serrées au moyen du tirant ( 28, 38 ).
  6. Turbine ( 1 ) suivant l'une de revendications précédentes,
    caractérisée
    en ce que l'aube ( 12 ) directrice est disposée dans la première rangée ( 13 ) d'aubes directrices, considérée dans le sens d'écoulement d'un fluide ( 11 ) de travail.
  7. Turbine ( 1 ) suivant l'une des revendications précédentes,
    caractérisée
    en ce que le dispositif ( 25 ) de serrage peut, après retrait de l'aube ( 12 ) directrice, être retiré du carter ( 20 ) intérieur.
  8. Turbine ( 1 ) suivant l'une des revendications précédentes,
    caractérisée
    en ce qu'après retrait du dispositif ( 25 ) de serrage fixé au carter ( 20 ) intérieur, un anneau de guidage disposé en aval dans la direction d'écoulement d'un fluide ( 21 ) de travail est accessible manuellement.
  9. Procédé de démontage d'une aube ( 12 ) directrice d'une turbine ( 1 ) ayant un rotor ( 3 ) s'étendant en direction axiale et une chambre de combustion ( 6 ) accessible, qui communique avec un canal ( 18 ) annulaire pour du gaz chaud, dans lequel une pluralité d'aubes ( 12 ) directrices est disposée en formant une rangée ( 13 ) d'aubes directrices,
    dans lequel chaque aube ( 12 ) directrice a une emplanture ( 21 ) d'aube directrice fixée au carter ( 20 ) intérieur et une tête ( 22 ) d'aube directrice opposée à l'emplanture ( 21 ) d'aube directrice, tournée vers le rotor ( 3 ) et fixée à un anneau ( 24 ) de fixation de la turbine ( 1 ) entourant le rotor ( 3 ),
    suivant l'une ou plusieurs des revendications précédentes, caractérisé
    en ce que l'on retire l'aube ( 12 ) directrice de la première rangée d'aubes directrices, vue dans le sens d'écoulement du fluide ( 25, 35 ) de travail, manuellement en passant par la chambre de combustion ( 6 ) par la succession de stades suivantes :
    a. on desserre le dispositif ( 25 ) de serrage, disposé dans le carter intérieur, puis on le met dans une position de repos dégageant l'emplanture ( 21 ) de l'aube directrice et on l'y refixe,
    b. on desserre l'autre dispositif ( 35 ) de serrage disposé sur l'anneau ( 24 ) intérieur de fixation, de manière à dégager la tête ( 22 ) de l'aube directrice,
    c. on déplace l'aube ( 12 ) directrice axialement dans le sens contraire au sens d'écoulement du fluide de travail et ensuite on la bascule autour de la tête ( 22 ) de l'aube directrice,
    d. de sorte que l'aube ( 12 ) directrice, par déplacement radial, est libre vers l'extérieur.
EP03789132A 2002-12-19 2003-12-04 Turbine et procédé de démontage des aubes fixes d'une turbine Expired - Lifetime EP1573172B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03789132A EP1573172B1 (fr) 2002-12-19 2003-12-04 Turbine et procédé de démontage des aubes fixes d'une turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02028511 2002-12-19
EP02028511 2002-12-19
PCT/EP2003/013711 WO2004057158A1 (fr) 2002-12-19 2003-12-04 Turbine, dispositif de fixation pour aubes fixes et procede de demontage des aubes fixes d'une turbine
EP03789132A EP1573172B1 (fr) 2002-12-19 2003-12-04 Turbine et procédé de démontage des aubes fixes d'une turbine

Publications (2)

Publication Number Publication Date
EP1573172A1 EP1573172A1 (fr) 2005-09-14
EP1573172B1 true EP1573172B1 (fr) 2010-12-01

Family

ID=32668728

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03789132A Expired - Lifetime EP1573172B1 (fr) 2002-12-19 2003-12-04 Turbine et procédé de démontage des aubes fixes d'une turbine

Country Status (6)

Country Link
US (1) US7290983B2 (fr)
EP (1) EP1573172B1 (fr)
CN (1) CN100412322C (fr)
DE (1) DE50313299D1 (fr)
ES (1) ES2356629T3 (fr)
WO (1) WO2004057158A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017204953A1 (de) 2017-03-23 2018-09-27 MTU Aero Engines AG Strömungsmaschine, Verfahren und Leitschaufelreihensystem

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EP1731711A1 (fr) * 2005-06-10 2006-12-13 Siemens Aktiengesellschaft Transition de la chambre de combustion à la turbine, écran thermique et aube du distributeur de turbine
DE102006050907A1 (de) 2006-10-28 2008-05-15 Man Turbo Ag Leitvorrichtung einer Strömungsmaschine sowie Leitschaufel für eine derartige Leitvorrichtung
EP2206885A1 (fr) 2009-01-08 2010-07-14 Siemens Aktiengesellschaft Turbine à gaz
US8863365B2 (en) * 2010-01-22 2014-10-21 Siemens Energy, Inc. Removal of stuck blade in a turbine engine
US9470422B2 (en) * 2013-10-22 2016-10-18 Siemens Energy, Inc. Gas turbine structural mounting arrangement between combustion gas duct annular chamber and turbine vane carrier
EP2868868A1 (fr) * 2013-11-05 2015-05-06 Siemens Aktiengesellschaft Dispositif de montage et procédé de montage d'une aube statorique
EP2980359A1 (fr) 2014-07-30 2016-02-03 Siemens Aktiengesellschaft Joint d'étanchéité de têtes d'aube directrice par rapport à un composant de stator interne
US9816387B2 (en) 2014-09-09 2017-11-14 United Technologies Corporation Attachment faces for clamped turbine stator of a gas turbine engine
CN104675450A (zh) * 2015-01-30 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机持环固定结构
CN108005732B (zh) * 2017-12-20 2024-04-19 华瑞（江苏）燃机服务有限公司 一种燃气轮机透平静叶组件的拆卸机构
US11560806B1 (en) 2021-12-27 2023-01-24 General Electric Company Turbine nozzle assembly

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Cited By (1)

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Publication number Priority date Publication date Assignee Title
DE102017204953A1 (de) 2017-03-23 2018-09-27 MTU Aero Engines AG Strömungsmaschine, Verfahren und Leitschaufelreihensystem

Also Published As

Publication number Publication date
CN1729352A (zh) 2006-02-01
DE50313299D1 (de) 2011-01-13
WO2004057158A1 (fr) 2004-07-08
US20060251518A1 (en) 2006-11-09
ES2356629T3 (es) 2011-04-11
US7290983B2 (en) 2007-11-06
CN100412322C (zh) 2008-08-20
EP1573172A1 (fr) 2005-09-14

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