EP2414641B1 - Rotor de turbomachine axiale doté d'un disque d'étanchéité - Google Patents

Rotor de turbomachine axiale doté d'un disque d'étanchéité Download PDF

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Publication number
EP2414641B1
EP2414641B1 EP10715749.7A EP10715749A EP2414641B1 EP 2414641 B1 EP2414641 B1 EP 2414641B1 EP 10715749 A EP10715749 A EP 10715749A EP 2414641 B1 EP2414641 B1 EP 2414641B1
Authority
EP
European Patent Office
Prior art keywords
sealing ring
rotor
sealing
axial
radially
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
EP10715749.7A
Other languages
German (de)
English (en)
Other versions
EP2414641A1 (fr
Inventor
Sascha Dungs
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 EP10715749.7A priority Critical patent/EP2414641B1/fr
Priority to PL10715749T priority patent/PL2414641T3/pl
Publication of EP2414641A1 publication Critical patent/EP2414641A1/fr
Application granted granted Critical
Publication of EP2414641B1 publication Critical patent/EP2414641B1/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
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor

Definitions

  • the invention relates to a Axialturbomaschinenrotor with a sealing washer.
  • An axial turbomachine for example a gas turbine, has a turbine in which hot gas is expanded.
  • the temperature of the hot gas at the inlet to the turbine is to be selected as high as possible.
  • the maximum feasible temperature level of the hot gas is limited by turbine strength requirements defined by design and material selection of turbine components.
  • the temperature load and the mechanical stress of the components dictates their service life, which has to be above certain limits for reasons of safety and economy.
  • a conventional turbine rotor has a shaft and discs mounted thereon in rotationally symmetrical manner, on the outer edge of which a plurality of rotor blades are fastened next to each other over the circumference.
  • the blades and discs are sometimes the most stressed components in the turbine, which primarily defines servicing cycles of the gas turbine for these components.
  • the blades are made of a filigree structure that is traversed by cooling channels through which the cooling air flows to cool the blades.
  • the cooling channels open into the blade root, where the cooling channels are fed with the cooling air.
  • the object of the invention is to provide a Axialturbomaschinenrotor, which has a long service life.
  • the axial turbomachinery rotor according to the invention has a rotor body rotationally symmetrical about the rotor axis, a rotor blade having a plurality of blades, which are each fixed with their blade root on the rotor body, and a rotationally symmetrical about the rotor axis formed sealing disc, the radially adjacent with its outer edge inside is arranged on an axially extending projection of the blade root, so that between the blade root and the sealing disc, a cavity is formed, wherein on the outer edge of a radially outwardly opening groove is provided, in which a sealing ring is mounted, which during operation of the rotor under the action of Centrifugal force is slidable radially outward in the groove until the sealing ring bears radially on the inside of the projection and thereby seals the cavity on the blade root.
  • the sealing ring Due to the fact that, during operation of the axial turbomachinery rotor, the sealing ring is pressed against the projection by the centrifugal force, the sealing ring is biased against the projection over the entire circumference. Thus, the contact between the sealing ring and the projection is well sealed, whereby the sealing effect between the projection and the sealing disc is high.
  • the cavity is, for example, a channel for supplying cooling air to the blade root, as may for example be provided in a turbine of a gas turbine, leakage of cooling air at the sealing ring is small. This is the cooling of the blades with the cooling air effectively, whereby the life of the axial turbomachinery rotor is high.
  • the gasket includes a plurality of gasket segments, which allows the assembly of blades and gasket after manufacture of a rotor - welded or stacked from rotor disks - allows a stationary gas turbine.
  • the sealing disk segments are preferably coupled to each other in the circumferential direction with a stepped rebate.
  • the assembly of the sealing disc to the rotor body is simple, wherein with the help of the stepped rebate with an offset in the circumferential direction of the individual sealing disc segments to each other a gaping apart of the sealing disc segments is prevented.
  • the sealing ring is formed by a plurality of circumferentially successively arranged sealing ring segments, which are each inserted in the at the outer edge of their associated sealing disc segment.
  • the sealing ring segments preferably have two longitudinal ends facing away from each other, each of which is formed by an envelope, which is in engagement with a recess provided on the groove, so that the sealing ring segments are fixed in the circumferential direction in a form-fitting manner on the outer edge.
  • the envelopes are preferably designed as legs formed in the axial direction in an L-shaped manner.
  • each of the legs preferably has a radius of curvature which is at least greater than half the longitudinal extension of the affected leg. It is thereby achieved that at the longitudinal ends of the sealing ring segment rests gas-tight on the sealing disc segment.
  • the projection has a radially inwardly opening groove into which the outer edge engages radially movable and at the bottom of the sealing ring can be applied.
  • the outer edge of the sealing disc is advantageously accommodated in the groove of the projection, whereby harmful influences, in particular a mechanical and / or thermal stress, are reduced to the sealing ring.
  • a pressure difference is reduced transversely to the sealing ring, so that the sealing effect of the sealing ring is high.
  • the sealing ring segments are formed as a band having an elongated cross section, the longitudinal sides extend in the radial direction and the outer short side can be applied to the blade root. Characterized in that the longitudinal sides of the sealing ring segments extend in the radial direction, the sealing ring segments are guided in their radial movement in the groove of the sealing ring segments. Thus, a twisting and tilting of the sealing ring segments is prevented in the grooves of the sealing disc segments.
  • the axial turbomachine rotor is preferably an axial turbine rotor, and the rotor blades preferably have air ducts which open into the cavity at the blade root, wherein the cavity is provided for supplying cooling air and / or cooling air for the cooling air ducts.
  • an axial turbine rotor 1 has a plurality of rotor blades 2, which are lined up over the circumference of the axial turbine rotor 1 and thereby form a blade grid.
  • the axial turbine rotor 1 further comprises a disc 3, on which the rotor blades 2 are mounted.
  • Each blade 2 has an airfoil 4 with which the blade 2 is aerodynamically effective.
  • this has a blade root 5, which is held in a form-fitting manner in the disc 3, so that the blade 2 is fixed in the radial direction of the blade root 5.
  • a base plate 7 of the blade 2 is provided which extends in the axial direction and in the circumferential direction and is aerodynamically effective on its radially outer side.
  • the disc 2 is frontally limited with a plane perpendicular to the axis of the axial turbine rotor surface. Axially spaced from this surface, a sealing disc 7 is arranged, whereby between the sealing disc 7 and the disc 3, a cavity is formed. As a result, the cavity of the hot gas side 8 of the axial turbine rotor is limited by the sealing disk 7.
  • the cavity is adeluftzu 1500kanal 9, which is provided for the cooling air supply of cooling air to the blade root 5.
  • An inner edge 22, which is thickened with respect to the average wall thickness of the sealing disk 7, of the sealing disk 7 is radially hooked to the disk 3, as a result of which, in operation, the Seal 7 is held radially from the disc 3 directly.
  • the outer edge 10 of the sealing disc 7 is arranged radially adjacent to the radially inner side of the base plate 6, wherein the outer edge 10 of the sealing disc 7 engages in a provided in the radially inner side of the base plate 6, circumferential groove 11.
  • a circumferential groove 12 is provided, which opens radially outward into the groove 11 of the base plate 6.
  • the outer edge 10 of the sealing disc 7 is arranged radially at a distance from the bottom of the groove 11 of the base plate 6, so that a radial play 13 is provided.
  • a sealing ring 14 is inserted, which has a cross-section which is elongated or rectangular in the radial direction.
  • the groove 12 in the sealing disc 7 is provided in the sealing disc 7 so deep that the sealing ring 14 in the groove 12 is flush with the outer edge 10 of the sealing disc 7.
  • a centrifugal force which leads to a radial movement 15 of the sealing ring.
  • the radial movement 15 is completed by the sealing ring 14 until the sealing ring 14 rests against the bottom of the groove 11 in the base plate 6.
  • the radial play 13 is adjusted to the radial extent of the sealing ring 14 such that when concerns of the sealing ring 14 at the bottom of the groove 11 of the base plate 6 of the sealing ring 14 is still engaged with the groove 12 in the outer edge 10 of the sealing washer 7.
  • the sealing disc 7 is formed by a plurality of sealing disc segments 16, which are lined up next to each other over the circumference. At their edges at which the sealing disk segments 16 are arranged adjacent to each other, a stepped fold 17 is formed in each case by a stop 18 of a sealing disk segment 16 and with a the stop 18 corresponding step 19 of the other, adjacent sealing disc segment is formed.
  • each sealing ring segment 20 spans the outer edge 10 of its associated sealing disk segment 14 in the circumferential direction.
  • Each sealing ring segment 20 has two opposite sealing ring segment longitudinal ends 21.
  • Each sealing ring segment longitudinal end 21 is folded in the axial direction, whereby at each sealing ring segment longitudinal end 21, a leg 22 is formed, with which the sealing ring segment longitudinal end 21 is formed L-shaped.
  • a curvature is provided with a radius of curvature 23, wherein at the outer edge 10 of the sealing disk segment 16, a correspondingly shaped recess 24 is made.
  • the legs 22 and the recesses 24 are arranged on the outer edge 10 of the sealing disc segments 16 so that the legs 22 in the axial direction away from the stop 18 and the stage 19 show.
  • the strength of the sealing disc segments 16 in the region of the stepped rebate 17 is not unduly impaired by the provision of the recess 24.

Landscapes

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

Claims (9)

  1. Rotor de turbomachine axiale ayant un corps ( 3 ) de rotor de révolution autour de l'axe du rotor,
    une couronne d'aubes mobiles qui a une multiplicité d'aubes ( 2 ) mobiles fixées respectivement par leur emplanture ( 5 ) d'aubes au corps ( 3 ) du rotor,
    et un disque ( 7 ) d'étanchéité, qui est de révolution autour de l'axe du rotor et qui est disposé par son bord ( 10 ) extérieur radialement à l'intérieur au voisinage d'une saillie ( 6 ) s'étendant axialement de l'emplanture ( 5 ) de l'aube, de manière à former une cavité ( 9 ) entre l'emplanture ( 5 ) de l'aube et le disque ( 7 ) d'étanchéité,
    dans lequel il est prévu au bord ( 10 ) extérieur une rainure ( 12 ) radiale qui débouche vers l'extérieur et dans laquelle est montée un joint ( 14 ) torique qui, lorsque le rotor ( 1 ) fonctionne, peut, sous l'effet de la force ( 15 ) centrifuge, glisser radialement vers l'extérieur dans la rainure ( 12 ) jusqu'à ce que le joint ( 14 ) torique s'applique radialement au côté intérieur de la saillie ( 6 ) et rende ainsi étanche la cavité ( 9 ) de l'emplanture ( 7 ) de l'aube,
    caractérisé en ce que
    le disque ( 7 ) d'étanchéité est formé d'une multiplicité de segments ( 16 ) de disque d'étanchéité et le joint ( 14 ) torique d'une multiplicité de segments ( 20 ) de joint torique, qui sont disposés les uns derrière les autres dans la direction périphérique et qui s'appuient directement respectivement radialement sur le corps ( 3 ) du rotor, les segments ( 20 ) respectifs du joint torique étant insérés dans le bord ( 10 ) extérieur du segment ( 16 ) de disque d'étanchéité qui leur est associé.
  2. Rotor de turbomachine axiale suivant la revendication 1,
    dans lequel les segments ( 20 ) du joint torique ont deux extrémités ( 21 ) longitudinales éloignées l'une de l'autre qui sont formées respectivement par un pliage ( 22 ) qui est en prise avec un évidement ( 24 ) prévu dans la rainure ( 12 ) de manière à fixer les segments ( 20 ) du joint torique dans la direction périphérique à complémentarité de forme au bord ( 10 ) extérieur.
  3. Rotor de turbomachine axiale suivant la revendication 1 ou 2,
    dans lequel la saillie a une rainure ( 11 ) radiale débouchant vers l'intérieur, dans laquelle le bord ( 10 ) extérieur pénètre en étant mobile et au fond de laquelle le joint ( 14 ) torique peut être appliqué.
  4. Rotor de turbomachine axiale suivant la revendication 1, 2 ou 3,
    dans lequel les segments ( 16 ) du disque d'étanchéité sont couplés les uns aux autres dans la direction périphérique par une mortaise ( 17 ).
  5. Rotor de turbomachine axiale suivant l'une des revendications 1 à 4,
    dans lequel les pliages sont constitués sous la forme de branches ( 22 ) en forme de L dans la direction axiale.
  6. Rotor de turbomachine axiale suivant la revendication 5,
    caractérisé en ce que chacune des branches ( 22 ) a un rayon ( 23 ) de courbure qui est au moins plus grand que la moitié de l'étendue longitudinale de la branche ( 22 ) concernée.
  7. Rotor de turbomachine axiale suivant la revendication 5 ou 6,
    dans lequel la branche ( 22 ) pointe en des sens opposés de sorte que le segment ( 20 ) du joint torique est en forme de Z.
  8. Rotor de turbo machine axial suivant l'une des revendications 1 à 7,
    dans lequel les segments (20) du joint torique sont constitués sous la forme d'un ruban ayant une section transversale oblongue, de préférence rectangulaire, dont les grands côtés s'étendent dans la direction radiale et dont le petit côté, se trouvant à l'extérieur, peut être appliqué à l'emplanture ( 5 ) de l'aube.
  9. Rotor de turbomachine axiale suivant l'une des revendications 1 à 8,
    dans lequel le rotor de turbomachine axiale est un rotor ( 1 ) de turbomachine axiale et les aubes (2) mobiles ont des canaux pour de l'air de refroidissement, qui débouchent à l'emplanture ( 5 ) de l'aube dans la cavité ( 9 ), la cavité étant prévue pour l'apport d'air de refroidissement et/ou pour l'évacuation d'air de refroidissement pour les canaux pour de l'air de refroidissement.
EP10715749.7A 2009-03-31 2010-03-26 Rotor de turbomachine axiale doté d'un disque d'étanchéité Not-in-force EP2414641B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10715749.7A EP2414641B1 (fr) 2009-03-31 2010-03-26 Rotor de turbomachine axiale doté d'un disque d'étanchéité
PL10715749T PL2414641T3 (pl) 2009-03-31 2010-03-26 Wirnik osiowej maszyny wirnikowej z tarczą uszczelniającą

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09004781A EP2239419A1 (fr) 2009-03-31 2009-03-31 Rotor de turbomachine axiale doté d'un disque d'étanchéité
EP10715749.7A EP2414641B1 (fr) 2009-03-31 2010-03-26 Rotor de turbomachine axiale doté d'un disque d'étanchéité
PCT/EP2010/054001 WO2010112422A1 (fr) 2009-03-31 2010-03-26 Rotor à disque d'étanchéité pour turbomachine axiale

Publications (2)

Publication Number Publication Date
EP2414641A1 EP2414641A1 (fr) 2012-02-08
EP2414641B1 true EP2414641B1 (fr) 2013-07-03

Family

ID=41258149

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09004781A Withdrawn EP2239419A1 (fr) 2009-03-31 2009-03-31 Rotor de turbomachine axiale doté d'un disque d'étanchéité
EP10715749.7A Not-in-force EP2414641B1 (fr) 2009-03-31 2010-03-26 Rotor de turbomachine axiale doté d'un disque d'étanchéité

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09004781A Withdrawn EP2239419A1 (fr) 2009-03-31 2009-03-31 Rotor de turbomachine axiale doté d'un disque d'étanchéité

Country Status (7)

Country Link
US (1) US8920121B2 (fr)
EP (2) EP2239419A1 (fr)
JP (1) JP5324700B2 (fr)
CN (1) CN102378850B (fr)
ES (1) ES2426156T3 (fr)
PL (1) PL2414641T3 (fr)
WO (1) WO2010112422A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015193033A1 (fr) * 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Rotor pourvu de tôles d'étanchéité
CN105658912A (zh) * 2013-09-25 2016-06-08 斯奈克玛 涡轮机的旋转组件
EP3564489A1 (fr) 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor à surfaces de contact optimisées au niveau de forces centrifuges

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WO2014137435A2 (fr) 2013-03-05 2014-09-12 Rolls-Royce North American Technologies, Inc. Procédé de rétention de plaques de capot segmentées de turbine
EP2863019B1 (fr) 2013-10-18 2017-03-29 Siemens Aktiengesellschaft Agencement d'étanchéification
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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
DE102016107315A1 (de) * 2016-04-20 2017-10-26 Rolls-Royce Deutschland Ltd & Co Kg Rotor mit Überhang an Laufschaufeln für ein Sicherungselement
KR101850922B1 (ko) 2016-10-07 2018-04-20 두산중공업 주식회사 가스터빈용 연소 덕트 조립체
GB2560159B (en) 2017-02-23 2019-12-25 Advanced Risc Mach Ltd Widening arithmetic in a data processing apparatus
EP3438410B1 (fr) 2017-08-01 2021-09-29 General Electric Company Système d'étanchéité pour machine rotative
CN110005637B (zh) * 2018-01-04 2021-03-26 中国航发商用航空发动机有限责任公司 轴流式航空发动机转子
JP7092938B2 (ja) * 2018-08-02 2022-06-28 シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフト ２つのロータディスクの間にロータ組立要素を配置したロータ
US11093580B2 (en) 2018-10-31 2021-08-17 Advanced Micro Devices, Inc. Matrix multiplier with submatrix sequencing
DE102018218944A1 (de) * 2018-11-07 2020-05-07 Siemens Aktiengesellschaft Rotor mit Abdichtung zwischen Laufschaufeln
DE102018218942A1 (de) * 2018-11-07 2020-05-07 Siemens Aktiengesellschaft Rotor mit Abdichtung zwischen Laufschaufeln
CN114599859B (zh) * 2019-10-18 2023-11-17 西门子能源全球有限两合公司 具有设置在两个转子盘之间的转子构件的转子
US11168615B1 (en) * 2020-08-25 2021-11-09 Raytheon Technologies Corporation Double ring axial sealing design
CN117897551A (zh) * 2021-08-24 2024-04-16 西门子能源全球有限两合公司 转子和具有转子的流体机械

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Publication number Priority date Publication date Assignee Title
CN105658912A (zh) * 2013-09-25 2016-06-08 斯奈克玛 涡轮机的旋转组件
CN105658912B (zh) * 2013-09-25 2018-03-13 斯奈克玛 涡轮机的旋转组件
WO2015193033A1 (fr) * 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Rotor pourvu de tôles d'étanchéité
EP2957725A1 (fr) 2014-06-16 2015-12-23 Siemens Aktiengesellschaft Rotor avec toles d'étanchéité
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
JP2012522169A (ja) 2012-09-20
EP2239419A1 (fr) 2010-10-13
US20120034087A1 (en) 2012-02-09
EP2414641A1 (fr) 2012-02-08
ES2426156T3 (es) 2013-10-21
CN102378850B (zh) 2014-07-16
WO2010112422A1 (fr) 2010-10-07
JP5324700B2 (ja) 2013-10-23
US8920121B2 (en) 2014-12-30
CN102378850A (zh) 2012-03-14
PL2414641T3 (pl) 2013-12-31

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