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EP1249577B1 - Turbine à gaz avec des éléments de virole axialement mobile - Google Patents

Turbine à gaz avec des éléments de virole axialement mobile Download PDF

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Publication number
EP1249577B1
EP1249577B1 EP01109198A EP01109198A EP1249577B1 EP 1249577 B1 EP1249577 B1 EP 1249577B1 EP 01109198 A EP01109198 A EP 01109198A EP 01109198 A EP01109198 A EP 01109198A EP 1249577 B1 EP1249577 B1 EP 1249577B1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine according
guide part
rib
presses
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
EP01109198A
Other languages
German (de)
English (en)
Other versions
EP1249577A1 (fr
Inventor
Christian Dr. Scholz
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to ES01109198T priority Critical patent/ES2286054T3/es
Priority to EP01109198A priority patent/EP1249577B1/fr
Priority to DE50112597T priority patent/DE50112597D1/de
Priority to JP2002106196A priority patent/JP4283488B2/ja
Priority to US10/120,808 priority patent/US6676372B2/en
Priority to CNB02119078XA priority patent/CN100400797C/zh
Publication of EP1249577A1 publication Critical patent/EP1249577A1/fr
Application granted granted Critical
Publication of EP1249577B1 publication Critical patent/EP1249577B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor

Definitions

  • the invention relates to a gas turbine with a guide and with a blade ring in a gas channel and with a housing and secured therein against rotation axially mutually displaceable funnel-shaped guiding parts as a carrier of an outer shell of the gas channel forming rings.
  • Gas turbines are often subjected to changing loads not only in their starting phase, but also in continuous operation. This results in unsteady operation, especially with regard to the temperatures assumed by the individual components. To avoid damage to the turbine, therefore, the individual components are usually clamped so that they can perform thermally induced dimensional changes unhindered.
  • the outer channel wall is partially formed by a guide ring, which is opposite to the blade tips of blades and slidable for radial clearance adjustment of a drive in the axial direction.
  • the guide ring concentrically enclosing the blade ring is arranged in an annular recess of the housing of the gas turbine, wherein the space structure surrounding the recess is rigidly fixed to adjacent housing parts.
  • a multi-part stator blade carrier which is composed of radially movable segments, which are axially fixed by approaches.
  • To move the segments slidable segment carrier are provided in the outer conical wall of the annular space parallel to the wall.
  • the sliding surfaces of the segment carrier and their guides are each formed like a sawtooth and inclined relative to the displacement direction.
  • a displacement of the segment carrier causes a radial movement of the segments, which is used to adjust the radial gaps of all turbine stages.
  • the invention is based on the object to develop a gas turbine plant so that in her over a variety of operating conditions, an optimal blade tip gap is given, so that a basic requirement for achieving a good efficiency is guaranteed.
  • a gas turbine of the type specified in which at least one of the funnel-shaped guide parts controlled by a motor is axially displaceable.
  • a motor Suitably serve as a motor a plurality of distributed over the circumference of the guide part hydraulic presses.
  • any other type of drives is content of this invention.
  • the particular advantage of this arrangement is the possibility to actively set the blade tip gap by axial movement of the guide.
  • the conicity of the funnel-shaped design of the guide member is advantageously utilized, because as a result of this conicity, any axial displacement thereof also causes a change in the blade tip gap to be considered substantially radially.
  • rotor blade rings 2 are keyed with a plurality of blades 3.
  • a gas flow 6 guided through vane rings 4 with a multiplicity of vanes 5 expands through a gas duct 7, thereby driving the rotor blades 3.
  • the gas channel 7 has an annular cross-section and is connected at its pressure-side end with a hot gas chamber 8, is driven from the compressed and heated gas in the arrow direction to a gas outlet opening 9.
  • a radially inner boundary of the gas channel 7 is formed by hubs 10 of the blade rings 2 keyed on the turbine shaft 1 and non-rotating hubs 11 of the guide blade rings 4 carried by the inner ends of the guide blades 5. Joints between the hubs 10 and the hubs 11 are closed by labyrinth seals.
  • a radially outer boundary of the gas channel 7 has a funnel-shaped conical shape and is formed by rings 12 and 13.
  • the rings 12 and 13 are supported by funnel-shaped guideways 14 and 15, the rings 12 facing the free ends of the blades 3, and the rings 13 holding the outer ends of the vanes 5 and thus supporting the vane ring 4 formed by them as a whole. Gaps between the rings 12 and 13 are closed by suitable sealing rings, not shown.
  • the guide parts 14 and 15 are thick-walled, very stiff and mounted axially slidably on cross-sectionally preferably rectangular blocks 16.
  • the blocks 16 are anchored in a housing 17 and each of the guide parts 14 and 15 engages at its two ends in each case a wreath of a plurality of blocks 16, so that tilting for the guide parts 14 and 15 is also excluded, such as radial movements.
  • the housing 17 is, due to its shape and its wall thickness, as stiff as the conducting parts 14 and 15 and carries on its inside except the blocks 16 per guide member 14 and 15, a rigid rib 18.
  • This rigid rib 18 is axially between the Wreaths of blocks 16 provided, which are associated with the same guide member 14 and 15, respectively.
  • the rigid rib 18 is in particular practically not deformable in the axial direction.
  • Each of the guide parts 14 and 15 carries a radially outwardly projecting, relatively thin-walled stop rib 19, which is supported on the hot gas chamber 8 facing side of the associated rigid rib 18 with a bead 20 carried by its free end.
  • a reinforcement 21 is arranged, which is indeed also the rigid rib 18 faces, but shorter in the axial direction than the bead 20.
  • the guide parts 14 and 15 are in their gas outlet opening 9 facing portion radially outwardly by a preferably trapezoidal in cross section stiffening rib 22 includes a radially oriented, the associated rigid rib 18 opposite abutment surface 23 has. Between the rigid ribs 18 and their respective opposite stop surface 23 are distributed uniformly on the circumference of the associated guide member 14 or 15 a plurality of hydraulic presses. Pistons 24 of these presses are supported directly on the rigid rib 18 and associated cylinders 25 of the presses lie on the stop surface 23 of the stiffening rib 22. An annular space between the housing 17 and the guide parts 14 and 15 is divided by membrane-like partitions 26 into chambers.
  • the inventive arrangement now allows a targeted, active setting just the width of this gap. For this purpose, this width is measured by sensors, not shown. With a desired reduction of the gap width is then through the engine shown by the presses concerned Guiding 14 and / or 15 shifted in the direction of the gas outlet opening 9.
  • the stopper rib 19 is resiliently clamped, so that it pushes back in a direction required in the opposite direction of the movement carrying them guide member 14 or 15 in the direction of the hot gas chamber 8.
  • each of the same guide member 14 or 15 associated presses together reach an axial force which corresponds to something the 10 times an operationally exerted by the gas flow 6 to the relevant guide member 14 or 15 axial force. Both axial forces act in the direction of the gas outlet opening 9 and add up.
  • the deformation energy absorbed by the stop rib 19 during its deformation is stored in the adjustment of a guide part 14 or 15 in the direction of the gas outlet opening 9 and serves in an opposite movement to generate a restoring force.
  • This restoring force is greater in each position of the associated guide member 14 or 15, as the operationally from the gas flow 6 to this exerted axial force.
  • the restoring force is about 2 to 3 times as large as the operational axial force.

Landscapes

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

Claims (12)

  1. Turbine à gaz comprenant une couronne (4) d'aubes directrices et une couronne (2) d'aubes mobiles dans un canal (7) pour du gaz et un capteur (17), ainsi que, s'y trouvant, des parties (14/15) directrices en forme d'entonnoir pouvant, sans possibilité de tourner, être déplacées axialement les unes vers les autres, dans laquelle au moins l'une des parties (14/15) directrices en forme d'entonnoir peut être déplacée axialement en étant commandée par un moteur,
    caractérisée en ce que les parties (14/15) conductrices sont constituées sous la forme de support d'anneaux (12/13) formant une surface latérale extérieure du canal (7) pour les gaz.
  2. Turbine à gaz suivant la revendication 1,
    caractérisée en ce que plusieurs presses hydrauliques ou pneumatiques réparties sur le pourtour de la partie (14/15) directrice servent de moteur.
  3. Turbine à gaz suivant la revendication 1 ou 2,
    caractérisée en ce que des pistons (24) des presses s'appuient, par leur extrémité libre, sur une nervure (18) rigide fixée au carter.
  4. Turbine à gaz suivant l'une des revendications 1 à 3,
    caractérisée en ce que des vérins (25) glissant sur le piston (24) des presses sont portés par la partie (14/15) directrice.
  5. Turbine à gaz suivant l'une des revendications 1 à 4,
    caractérisée en ce que la partie (14/15) directrice porte, outre des anneaux (12/13) délimitant le canal (7) pour le gaz, au moins une couronne (4) d'aubes directrices.
  6. Turbine à gaz suivant l'une des revendications 1 à 5,
    caractérisée en ce qu'une nervure (19) de butée, en saillie radialement vers l'extérieur de la partie (14/15) directrice à la manière d'une bride, s'appuie, par son extrémité libre, sur la nervure (18) rigide fixée au carter et peut être déformée élastiquement par les presses.
  7. Turbine à gaz suivant l'une des revendications 1 à 6,
    caractérisée en ce qu'une force pouvant être produite conjointement par des presses alimentées par la même partie (14/15) directrice est plus grande, au moins du facteur 10, qu'une force axiale agissant, en raison du fonctionnement, sur la nervure (19) de butée.
  8. Turbine à gaz suivant l'une des revendications 1 à 7,
    caractérisée en ce qu'une force de rappel de la nervure (19) de butée déformée élastiquement est plus grande que la force axiale agissant, en raison du fonctionnement, sur la nervure (19) de butée.
  9. Turbine à gaz suivant l'une des revendications 1 à 8,
    caractérisée en ce que la force de rappel agrandit un intervalle de pointe d'aube mobile par déplacement de la partie (14/15) directrice en forme d'entonnoir.
  10. Turbine à gaz suivant l'une des revendications 1 à 9,
    caractérisée en ce que la nervure (19) de butée déformable élastiquement de type à bride a, sur sa racine, une butée d'extrémité (renfort 21) qui limite la déformation élastique.
  11. Turbine à gaz suivant l'une des revendications 1 à 10,
    caractérisée en ce que la partie (14/15) directrice est empêchée de se coincer tant axialement avant qu'axialement après la nervure (19) de butée et la nervure (18) fixée au carter par plusieurs guidages (bloc 16) axiaux répartis sur le pourtour de la partie (14) directrice.
  12. Turbine à gaz suivant l'une des revendications 1 à 11,
    caractérisée en ce que les guidages (bloc 16) axiaux sont portés par le carter (17).
EP01109198A 2001-04-12 2001-04-12 Turbine à gaz avec des éléments de virole axialement mobile Expired - Lifetime EP1249577B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
ES01109198T ES2286054T3 (es) 2001-04-12 2001-04-12 Turbina de gas con piezas de la carcasa axialmente desplazables.
EP01109198A EP1249577B1 (fr) 2001-04-12 2001-04-12 Turbine à gaz avec des éléments de virole axialement mobile
DE50112597T DE50112597D1 (de) 2001-04-12 2001-04-12 Gasturbine mit axial verschiebbaren Gehäuseteilen
JP2002106196A JP4283488B2 (ja) 2001-04-12 2002-04-09 ガスタービン
US10/120,808 US6676372B2 (en) 2001-04-12 2002-04-11 Gas turbine with axially mutually displaceable guide parts
CNB02119078XA CN100400797C (zh) 2001-04-12 2002-04-12 具有可轴向相对移动的引导部件的燃气轮机

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01109198A EP1249577B1 (fr) 2001-04-12 2001-04-12 Turbine à gaz avec des éléments de virole axialement mobile

Publications (2)

Publication Number Publication Date
EP1249577A1 EP1249577A1 (fr) 2002-10-16
EP1249577B1 true EP1249577B1 (fr) 2007-06-06

Family

ID=8177137

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01109198A Expired - Lifetime EP1249577B1 (fr) 2001-04-12 2001-04-12 Turbine à gaz avec des éléments de virole axialement mobile

Country Status (6)

Country Link
US (1) US6676372B2 (fr)
EP (1) EP1249577B1 (fr)
JP (1) JP4283488B2 (fr)
CN (1) CN100400797C (fr)
DE (1) DE50112597D1 (fr)
ES (1) ES2286054T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9057281B2 (en) 2009-03-26 2015-06-16 Siemens Aktiengesellschaft Axial turbomachine having an axially displaceable guide-blade carrier

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7222488B2 (en) * 2002-09-10 2007-05-29 General Electric Company Fabricated cowl for double annular combustor of a gas turbine engine
US7125223B2 (en) * 2003-09-30 2006-10-24 General Electric Company Method and apparatus for turbomachine active clearance control
GB0411850D0 (en) * 2004-05-27 2004-06-30 Rolls Royce Plc Spacing arrangement
US7234918B2 (en) * 2004-12-16 2007-06-26 Siemens Power Generation, Inc. Gap control system for turbine engines
DE102005018716A1 (de) * 2005-04-21 2006-10-26 Priebe, Klaus-Peter, Dipl.-Ing. Dichtspaltregelung
EP1746256A1 (fr) * 2005-07-20 2007-01-24 Siemens Aktiengesellschaft Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines
DE102005048982A1 (de) * 2005-10-13 2007-04-19 Mtu Aero Engines Gmbh Vorrichtung und Verfahren zum axialen Verschieben eines Turbinenrotors
US7909566B1 (en) 2006-04-20 2011-03-22 Florida Turbine Technologies, Inc. Rotor thrust balance activated tip clearance control system
US7549835B2 (en) * 2006-07-07 2009-06-23 Siemens Energy, Inc. Leakage flow control and seal wear minimization system for a turbine engine
US20080063513A1 (en) * 2006-09-08 2008-03-13 Siemens Power Generation, Inc. Turbine blade tip gap reduction system for a turbine engine
EP1965035B1 (fr) 2007-03-02 2013-12-18 Siemens Aktiengesellschaft Minimisation des jeux axials pour des aubes de guidage réglables et pour l'anneau profilé d'une machine de détente de gaz chaud
FR2920469A1 (fr) * 2007-08-30 2009-03-06 Snecma Sa Aube a calage variable de turbomachine
WO2009074355A1 (fr) * 2007-12-10 2009-06-18 Siemens Aktiengesellschaft Turbomachine axiale à pertes d'interstice réduites
US8277177B2 (en) * 2009-01-19 2012-10-02 Siemens Energy, Inc. Fluidic rim seal system for turbine engines
US20100196139A1 (en) * 2009-02-02 2010-08-05 Beeck Alexander R Leakage flow minimization system for a turbine engine
US8177476B2 (en) * 2009-03-25 2012-05-15 General Electric Company Method and apparatus for clearance control
US8177483B2 (en) * 2009-05-22 2012-05-15 General Electric Company Active casing alignment control system and method
DE102009023062A1 (de) 2009-05-28 2010-12-02 Mtu Aero Engines Gmbh Spaltkontrollsystem, Strömungsmaschine und Verfahren zum Einstellen eines Laufspalts zwischen einem Rotor und einer Ummantelung einer Strömungsmaschine
DE102009037620A1 (de) * 2009-08-14 2011-02-17 Mtu Aero Engines Gmbh Strömungsmaschine
EP2339122A1 (fr) * 2009-12-23 2011-06-29 Siemens Aktiengesellschaft Turbine avec chambre d'admission à volume réglable
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
DE102010045851A1 (de) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine
US9109608B2 (en) * 2011-12-15 2015-08-18 Siemens Energy, Inc. Compressor airfoil tip clearance optimization system
US9488062B2 (en) 2012-05-10 2016-11-08 General Electric Company Inner turbine shell axial movement
DE102012213016A1 (de) * 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Minimierung des Spalts zwischen einem Läufer und einem Gehäuse
CN105579669B (zh) * 2013-09-27 2017-07-07 西门子股份公司 用于燃气涡轮的内壳体毂
JP6223774B2 (ja) * 2013-10-15 2017-11-01 三菱日立パワーシステムズ株式会社 ガスタービン
US9840932B2 (en) 2014-10-06 2017-12-12 General Electric Company System and method for blade tip clearance control
CN104389645A (zh) * 2014-11-15 2015-03-04 哈尔滨广瀚燃气轮机有限公司 一种新型涡轮机高温热膨胀补偿静子密封结构
US10323536B2 (en) * 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems
CN106837432B (zh) * 2015-12-03 2019-10-11 上海电气电站设备有限公司 汽轮机胀差控制结构及控制方法
US20190178159A1 (en) * 2016-08-10 2019-06-13 In2Rbo, Inc. Multistage radial compressor and turbine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1426818A1 (de) * 1963-07-26 1969-03-13 Licentia Gmbh Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt
US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly
CH538046A (de) * 1971-11-10 1973-06-15 Bbc Brown Boveri & Cie Einrichtung zum Einstellen des Spitzenspiels an Strömungsmaschinen
DE2165528A1 (de) * 1971-12-30 1973-07-12 Kloeckner Humboldt Deutz Ag Einrichtung zum herstellen eines geringen spaltes zwischen den umlaufenden schaufeln und der wandung einer stroemungsmaschine
US4177004A (en) 1977-10-31 1979-12-04 General Electric Company Combined turbine shroud and vane support structure
GB2042646B (en) * 1979-02-20 1982-09-22 Rolls Royce Rotor blade tip clearance control for gas turbine engine
EP0103260A3 (fr) * 1982-09-06 1984-09-26 Hitachi, Ltd. Régulation du jeu des extrémités des aubes de turbine
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade
EP1243756A1 (fr) * 2001-03-23 2002-09-25 Siemens Aktiengesellschaft Turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9057281B2 (en) 2009-03-26 2015-06-16 Siemens Aktiengesellschaft Axial turbomachine having an axially displaceable guide-blade carrier

Also Published As

Publication number Publication date
JP4283488B2 (ja) 2009-06-24
US6676372B2 (en) 2004-01-13
JP2002327603A (ja) 2002-11-15
US20020164246A1 (en) 2002-11-07
CN100400797C (zh) 2008-07-09
DE50112597D1 (de) 2007-07-19
CN1381670A (zh) 2002-11-27
EP1249577A1 (fr) 2002-10-16
ES2286054T3 (es) 2007-12-01

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