EP2344723B1 - Turbine à gaz avec plaques d'étanchéité sur le disque de turbine - Google Patents

Turbine à gaz avec plaques d'étanchéité sur le disque de turbine Download PDF

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Publication number
EP2344723B1
EP2344723B1 EP09782613.5A EP09782613A EP2344723B1 EP 2344723 B1 EP2344723 B1 EP 2344723B1 EP 09782613 A EP09782613 A EP 09782613A EP 2344723 B1 EP2344723 B1 EP 2344723B1
Authority
EP
European Patent Office
Prior art keywords
turbine
sealing plate
rotor
sealing
turbine 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
EP09782613.5A
Other languages
German (de)
English (en)
Other versions
EP2344723A1 (fr
Inventor
Björn Bilstein
Peter Schröder
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 EP09782613.5A priority Critical patent/EP2344723B1/fr
Publication of EP2344723A1 publication Critical patent/EP2344723A1/fr
Application granted granted Critical
Publication of EP2344723B1 publication Critical patent/EP2344723B1/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the combustor of the gas turbine may be embodied as a so-called annular combustor in which a plurality of burners circumferentially disposed about the turbine rotor discharge into a common combustor chamber surrounded by a high temperature resistant surround wall.
  • 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.
  • 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 the escape of the guided inside the turbine disk cooling air, which usually forwarded to the cooling of the turbine blades in selbige becomes.
  • a gas turbine in such a configuration is for example from the EP 1 944 471 A1 known.
  • This object is achieved according to the invention with a turbine rotor mentioned above, in which between the edge of the respective sealing plate and a side wall of the turbine disc groove closure pieces are arranged, and in which the edge extends over the entire azimuthal length of the sealing plate and the closure pieces for sealing in the azimuthal direction adjacent to each other, wherein the respective sealing plate comprises at least one substantially azimuthally on the side facing the turbine axis, the respective edge interrupting recess which is geometrically designed so that through this the closure pieces are inserted into the turbine disk groove.
  • the sealing plates are substantially circular section. As a result, the sealing plates are adapted to the shape of the turbine disk and it is thus ensured a reliable seal.
  • the larger, circular segment-shaped sealing plates then cover namely the same area as the previously scaly superimposed individual sealing plates.
  • the advantages associated with the invention are in particular that a substantially simplified and cheaper construction of the gas turbine is possible by reducing the number of sealing plates per side surface of the turbine disk of a gas turbine.
  • the design of the entire blade row is thereby significantly simplified and is less expensive to manufacture, since the sealing plates can be manufactured in the turning process.
  • the sealing plates have comparatively few leakage surfaces. This can be sealed much denser to reduce the loss of cooling air.
  • the turbine disk 38 includes a blade retention groove 40 in which the blade 12 (not shown) is disposed. Through the cooling air hole 42 1 cooling air is supplied during operation of the gas turbine, which cools the turbine disk 36 and is also forwarded to the blade 12, not shown.
  • FIG. 5 again shows the sealing plate 30 in the plan.
  • the notch 52 respectively introduced recess 56 is shown here, which interrupts the edge 47. It is adapted in its geometry to the size of the closure pieces 34, so that it is suitable for insertion of the closure piece 34 shown in more detail in the following figures.
  • closure pieces 34 can be lowered through the recess 56 and subsequently pushed along the edge 47 into its end position. Thus, a fixation of the already mounted sealing plate 30 is achieved on the turbine disk 38 and a good seal of the remaining gap.
  • the locking plate 36 is inserted radially, which also has a bore in the center. In this and the holes 48, 58 of the safety pin 32 is inserted. This secures the radial Locking plate 36 and in the circumferential direction, the closure piece 34 and the sealing plate 30. against axial pushing out of the securing bolt 32, the end of the locking plate 36 is bent radially downwards. The final assembly is in FIG. 14 shown.

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 (7)

  1. Rotor (8) de turbine,
    ayant un certain nombre d'aubes (12) mobiles rassemblées respectivement en rangées d'aubes mobiles et montées sur respectivement un disque (38) de turbine,
    dans lequel le disque (38) respectif de turbine a sur ses surfaces latérales un certain nombre de plaques (30) d'étanchéité en forme de segments d'anneau circulaire, qui sont insérés dans une rainure (62) de disque de turbine s'étendant azimutalement, dans lequel la plaque (30) d'étanchéité respective a, du côté tourné vers l'axe de la turbine, un bord (47) s'étendant azimutalement et à distance du bord intérieur de la plaque (30) d'étanchéité respective,
    dans lequel entre le bord (47) de la plaque (30) d'étanchéité respective et une paroi latérale de la rainue (62) du disque de turbine sont disposées des pièces (34) de fermeture,
    dans lequel le bord (47) s'étend sur toute la longueur azimutale de la plaque d'étanchéité et les pièces (34) de fermeture s'appliquent l'une à l'autre dans la direction azimutale pour assurer l'étanchéité,
    dans lequel la plaque (30) d'étanchéité respective comprend au moins un évidemment (56) s'étendant sensiblement azimutalement du côté tourné vers l'axe de la turbine, interrompant le bord (47) respectif et conçu géométriquement, de manière à ce que par cet évidemment des pièces (34) de fermeture puissent être insérées dans la rainure (62) du disque de turbine.
  2. Rotor (8) de turbine suivant la revendication 1,
    dans lequel il est prévu deux plaques (30) d'étanchéité par surface latérale.
  3. Rotor (8) de turbine suivant l'une des revendications 1 à 2, dans lequel dans les surfaces tournées respectivement l'une vers l'autre de deux plaques (30) d'étanchéité est ménagée une fente (54),
    dans lequel pour assurer l'étanchéité de l'espace intermédiaire, il est inséré entre les surfaces une tôle reliant les fentes (54) respectivement opposées.
  4. Rotor (8) de turbine suivant l'une des revendications 1 à 3, dans lequel la plaque (30) d'étanchéité respective a une aile (50) d'étanchéité s'étendant sensiblement azimutalement et axialement.
  5. Rotor (8) de turbine suivant l'une des revendications 1 à 4, dans lequel la pièce (34) de fermeture respective a un perçage (58), la plaque (30) d'étanchéité respective a un certain nombre d'encoches (52) et la paroi latérale délimitant la rainure (62) du disque de turbine a un perçage (48) de réception d'un axe (32) de fixation.
  6. Rotor (8) de turbine suivant l'une des revendications 1 à 5, dans lequel la plaque (30) d'étanchéité respective est fabriquée au tour.
  7. Installation de turbine à gaz ou de turbine à vapeur ayant un rotor (8) de turbine suivant l'une des revendications 1 à 6.
EP09782613.5A 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine Not-in-force EP2344723B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09782613.5A EP2344723B1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08018988A EP2182170A1 (fr) 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
EP09782613.5A EP2344723B1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
PCT/EP2009/061462 WO2010049196A1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Publications (2)

Publication Number Publication Date
EP2344723A1 EP2344723A1 (fr) 2011-07-20
EP2344723B1 true EP2344723B1 (fr) 2014-05-07

Family

ID=40506496

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08018988A Withdrawn EP2182170A1 (fr) 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
EP09782613.5A Not-in-force EP2344723B1 (fr) 2008-10-30 2009-09-04 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08018988A Withdrawn EP2182170A1 (fr) 2008-10-30 2008-10-30 Turbine à gaz avec plaques d'étanchéité sur le disque de turbine

Country Status (6)

Country Link
US (1) US8573943B2 (fr)
EP (2) EP2182170A1 (fr)
JP (1) JP5108152B2 (fr)
CN (1) CN102203389B (fr)
RU (1) RU2515697C2 (fr)
WO (1) WO2010049196A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3564489A1 (fr) 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor à surfaces de contact optimisées au niveau de forces centrifuges

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2973829B1 (fr) * 2011-04-05 2013-05-24 Snecma Flasque d'etancheite pour etage de turbine de turbomachine d'aeronef, comprenant
WO2013167346A1 (fr) * 2012-05-08 2013-11-14 Siemens Aktiengesellschaft Aube mobile de turbine et section axiale de rotor pour une turbine à gaz
GB201417039D0 (en) 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement
MX2019006638A (es) * 2016-12-13 2019-08-01 Mitsubishi Hitachi Power Sys Metodo para desmontar/montar turbina de gas, rotor de turbina de gas y turbina de gas.
WO2018110580A1 (fr) 2016-12-13 2018-06-21 三菱日立パワーシステムズ株式会社 Procédé de démontage/assemblage de turbine à gaz, ensemble plaque d'étanchéité et rotor de turbine à gaz
EP3521561A1 (fr) * 2018-02-02 2019-08-07 Siemens Aktiengesellschaft Rotor pourvu d'élément d'étanchéité et de bague d'étanchéité
CN110578557A (zh) * 2019-10-29 2019-12-17 北京动力机械研究所 一种涡轮叶片锁紧装置及其装配方法

Family Cites Families (13)

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Publication number Priority date Publication date Assignee Title
GB928349A (en) 1960-12-06 1963-06-12 Rolls Royce Improvements in or relating to bladed rotors of fluid flow machines
US3572966A (en) * 1969-01-17 1971-03-30 Westinghouse Electric Corp Seal plates for root cooled turbine rotor blades
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
RU1077380C (ru) * 1982-03-22 1995-06-19 Запорожское машиностроительное конструкторское бюро "Прогресс" Рабочее колесо турбомашины
US5257909A (en) * 1992-08-17 1993-11-02 General Electric Company Dovetail sealing device for axial dovetail rotor blades
US5281098A (en) * 1992-10-28 1994-01-25 General Electric Company Single ring blade retaining assembly
US5713721A (en) * 1996-05-09 1998-02-03 General Electric Co. Retention system for the blades of a rotary machine
EP1284339A1 (fr) * 2001-08-14 2003-02-19 Siemens Aktiengesellschaft Anneau de rétention et d'étanchéité pour un rotor d'une turbine à gaz
FR2857691B1 (fr) * 2003-07-17 2006-02-03 Snecma Moteurs Retention de flasque de rotor
GB0423363D0 (en) * 2004-10-21 2004-11-24 Rolls Royce Plc Rotor assembly retaining apparatus
FR2899636B1 (fr) * 2006-04-10 2008-07-04 Snecma Sa Dispositif de retention axiale d'un flasque de disque de rotor de turbomachine
ATE441776T1 (de) 2007-01-09 2009-09-15 Siemens Ag Axialer rotorabschnitt für einen rotor einer turbine
US7566201B2 (en) * 2007-01-30 2009-07-28 Siemens Energy, Inc. Turbine seal plate locking system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3564489A1 (fr) 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor à surfaces de contact optimisées au niveau de forces centrifuges
US11319824B2 (en) 2018-05-03 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with centrifugally optimized contact faces

Also Published As

Publication number Publication date
CN102203389B (zh) 2014-03-05
CN102203389A (zh) 2011-09-28
EP2344723A1 (fr) 2011-07-20
US8573943B2 (en) 2013-11-05
RU2011121660A (ru) 2012-12-10
WO2010049196A1 (fr) 2010-05-06
JP2012506968A (ja) 2012-03-22
EP2182170A1 (fr) 2010-05-05
JP5108152B2 (ja) 2012-12-26
US20110206524A1 (en) 2011-08-25
RU2515697C2 (ru) 2014-05-20

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