EP1249577A1 - 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
EP1249577A1
EP1249577A1 EP01109198A EP01109198A EP1249577A1 EP 1249577 A1 EP1249577 A1 EP 1249577A1 EP 01109198 A EP01109198 A EP 01109198A EP 01109198 A EP01109198 A EP 01109198A EP 1249577 A1 EP1249577 A1 EP 1249577A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
turbine according
guide part
rib
guide
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.)
Granted
Application number
EP01109198A
Other languages
German (de)
English (en)
Other versions
EP1249577B1 (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
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 ES01109198T priority Critical patent/ES2286054T3/es
Priority to DE50112597T priority patent/DE50112597D1/de
Priority to EP01109198A priority patent/EP1249577B1/fr
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 axially secured against rotation against each other sliding funnel-shaped guide parts as a carrier of rings forming an outer jacket of the gas channel.
  • Gas turbines are often not only in their starting phase, but also subject to changing loads even in continuous operation. This has especially with regard to that of individual components assume a transient temperature Operation as a result. To avoid damage to the turbine the individual components are therefore usually clamped in such a way that they are unhindered thermally induced dimensional changes can execute.
  • Turbine losses due to cross currents over their blade tips to minimize as much as possible are the smallest possible radial gap between the blade tips and these opposite guide surfaces. Because both the blades and their rotor as well as guide blades and their carriers as well as an all-connecting housing expand differently in time with each load change and / or shrink, there is an optimal radial Gap over the blade tips only for very few of any number of stationary operating states. The These gas turbines are therefore often operated with a not optimized gap width and therefore with a not optimized efficiency.
  • the invention is based on the object of a gas turbine system to develop further in such a way that with her over Variety of operating conditions an optimal blade tip gap is given, so that a basic requirement for Achieving good efficiency is guaranteed.
  • This task is the one specified for a gas turbine kind solved according to the invention, in which at least one of the funnel-shaped guide parts controlled axially by a motor is movable. Appropriately serve as a motor Variety of hydraulic on the circumference of the guide part Press. However, every other type of drive is Content of this invention.
  • the particular advantage of this arrangement lies in the possibility of the blade tip gap actively set by moving the guide part axially. at the limitation of the active adjustability to axial movements is advantageous due to the funnel-shaped shape given the conicity of the guide part, because due to this taper, any axial displacement will result the same also a change in the substantially radial looking at blade tip gap.
  • An embodiment of the invention is based on a drawing explained in more detail. The only figure of this drawing shows a longitudinal section through a turbine between a propellant and exit.
  • Blade rings 2 with a plurality of blades 3 wedged.
  • One by vane rings 4 with a variety gas flow 6 guided by guide vanes 5 expands through a Gas channel 7 and drives the blades 3.
  • the gas channel 7 has an annular cross section and is at its pressure side end with a hot gas chamber 8 connected from which compressed and heated gas Arrow direction is driven to a gas outlet opening 9.
  • a radially inner boundary of the gas channel 7 is from Hubs 10 of the rotor blades wedged on the turbine shaft 1 2 and carried by the inner ends of the guide vanes 5, non-rotating hubs 11 of the guide vane rings 4 educated. Joints between the hubs 10 and the hubs 11 are sealed by labyrinth seals.
  • a radially outer boundary of the gas channel 7 has one funnel-shaped, conical shape and is defined by rings 12 and 13 educated.
  • the rings 12 and 13 are funnel-shaped Guide parts 14 and 15 worn, the rings 12 the free
  • the ends of the blades 3 lie opposite one another and the rings 13 hold the outer ends of the guide vanes 5 and thus the wear 4 of these vane ring formed. Gaps between the rings 12 and 13 are separated by suitable Sealed sealing rings not shown.
  • the guide parts 14 and 15 are thick-walled, very rigid and on in cross section preferably rectangular blocks 16 axially slidably mounted.
  • the blocks 16 are in a housing 17th anchored and each of the guide parts 14 and 15 engages his both ends in a wreath from a variety of blocks 16, so that tilting for the guide parts 14 and 15 as well is excluded, like radial movements.
  • the housing 17 is as stiff as the guide parts 14 and 15 and carries on the inside, apart from the blocks 16 per guide part 14 or 15 a rigid rib 18.
  • This rigid rib 18 is in each case provided axially between the rings of blocks 16, which are assigned to the same guide part 14 or 15.
  • the rigid one Rib 18 is particularly practical in the axial direction not deformable.
  • Each of the guide parts 14 and 15 carries one radially outward protruding, comparatively thin-walled stop rib 19, which on the hot gas chamber 8 side of the associated rigid rib 18 with one of its free end supported bead 20 supports.
  • a reinforcement 21 is arranged, which is also the rigid Rib 18 is facing, but shorter in the axial direction than the bead is 20.
  • the guide parts 14 and 15 are in the gas outlet opening 9 facing area radially outwards through a cross section preferably comprises trapezoidal stiffening rib 22, the one radially oriented, the associated rigid Rib 18 has opposite stop surface 23. Between the rigid ribs 18 and their opposite Stop surface 23 are even on the circumference of the associated guide part 14 or 15 distributes a large number arranged by hydraulic presses. Piston 24 of these presses are based 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 membrane-like Partitions 26 divided into chambers.
  • the arrangement according to the invention now enables a targeted, active adjustment of just the width of this gap. To this For this purpose, this width is measured by sensors, not shown. If you want to reduce the gap width then by the motor represented by the presses Guide part 14 and / or 15 in the direction of the gas outlet opening 9 moved.
  • the stop rib 19 resiliently clamped so that they are in the opposite direction required movement the guide member 14 or 15 carrying them pushes back towards the hot gas chamber 8.
  • This task is achieved by the same guiding part 14 or 15 associated presses together have an axial force something 10 times that of gas flow 6 due to operational reasons exerted on the relevant guide member 14 or 15 axial force equivalent. Both axial forces act in the direction the gas outlet opening 9 and add up.
  • Deformation energy is used when adjusting a guide part 14 or 15 in the direction of the gas outlet opening 9 saved and serves in an opposite movement to generate a restoring force.
  • This restoring force is in any position of the associated guide part 14 or 15 larger than that due to the operation of the gas stream 6 on this applied axial force.
  • the restoring force is preferably 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)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
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.
DE50112597T DE50112597D1 (de) 2001-04-12 2001-04-12 Gasturbine mit axial verschiebbaren Gehäuseteilen
EP01109198A EP1249577B1 (fr) 2001-04-12 2001-04-12 Turbine à gaz avec des éléments de virole axialement mobile
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 true EP1249577A1 (fr) 2002-10-16
EP1249577B1 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 (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1520958A2 (fr) * 2003-09-30 2005-04-06 General Electric Company Méthode et dispositif de régulation de jeu dans des turbomachines
EP1900907A2 (fr) * 2006-09-08 2008-03-19 Siemens Power Generation, Inc. Système de réduction d'espace d'extrémité de pale de turbine pour moteur à turbine
EP1965035A1 (fr) 2007-03-02 2008-09-03 Siemens Aktiengesellschaft Minimisation des colonnes axiales sur des grilles de guidage réglables et sur le contourage pour extenseur de gaz chauds
WO2009074355A1 (fr) * 2007-12-10 2009-06-18 Siemens Aktiengesellschaft Turbomachine axiale à pertes d'interstice réduites
WO2010108876A1 (fr) 2009-03-26 2010-09-30 Siemens Aktiengesellschaft Turbomachine axiale à support d'aubes fixes déplaçable axialement
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
DE102010045851A1 (de) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine
EP3078815A1 (fr) * 2015-04-09 2016-10-12 United Technologies Corporation Commande de jeu active pour systèmes de rotors axiaux

Families Citing this family (23)

* 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
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
FR2920469A1 (fr) * 2007-08-30 2009-03-06 Snecma Sa Aube a calage variable de turbomachine
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
US8939715B2 (en) * 2010-03-22 2015-01-27 General Electric Company Active tip clearance control for shrouded gas turbine blades and related method
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
EP3008293B1 (fr) * 2013-09-27 2017-11-29 Siemens Aktiengesellschaft Moyeu de boîtier intérieur pour une turbine à gaz
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
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

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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
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
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade

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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
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
EP1243756A1 (fr) * 2001-03-23 2002-09-25 Siemens Aktiengesellschaft Turbine

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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
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
US5203673A (en) * 1992-01-21 1993-04-20 Westinghouse Electric Corp. Tip clearance control apparatus for a turbo-machine blade

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1520958A3 (fr) * 2003-09-30 2012-10-17 General Electric Company Méthode et dispositif de régulation de jeu dans des turbomachines
EP1520958A2 (fr) * 2003-09-30 2005-04-06 General Electric Company Méthode et dispositif de régulation de jeu dans des turbomachines
EP1900907A2 (fr) * 2006-09-08 2008-03-19 Siemens Power Generation, Inc. Système de réduction d'espace d'extrémité de pale de turbine pour moteur à turbine
EP1900907A3 (fr) * 2006-09-08 2009-12-16 Siemens Energy, Inc. Système de réduction d'espace d'extrémité de pale de turbine pour moteur à turbine
EP1965035A1 (fr) 2007-03-02 2008-09-03 Siemens Aktiengesellschaft Minimisation des colonnes axiales sur des grilles de guidage réglables et sur le contourage pour extenseur de gaz chauds
CN101255804B (zh) * 2007-03-02 2016-03-30 西门子公司 流体机，尤其是热气膨胀机
WO2009074355A1 (fr) * 2007-12-10 2009-06-18 Siemens Aktiengesellschaft Turbomachine axiale à pertes d'interstice réduites
WO2010108876A1 (fr) 2009-03-26 2010-09-30 Siemens Aktiengesellschaft Turbomachine axiale à support d'aubes fixes déplaçable axialement
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
US9068471B2 (en) 2009-05-28 2015-06-30 Mtu Aero Engines Gmbh Clearance control system, turbomachine and method for adjusting a running clearance between a rotor and a casing of a turbomachine
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
DE102010045851A1 (de) * 2010-09-17 2012-03-22 Mtu Aero Engines Gmbh Kompensation unterschiedlicher Längsdehnungen von Gehäuse und Rotorwelle einer Turbomaschine
EP3078815A1 (fr) * 2015-04-09 2016-10-12 United Technologies Corporation Commande de jeu active pour systèmes de rotors axiaux
US10323536B2 (en) 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems

Also Published As

Publication number Publication date
JP4283488B2 (ja) 2009-06-24
US20020164246A1 (en) 2002-11-07
CN100400797C (zh) 2008-07-09
CN1381670A (zh) 2002-11-27
EP1249577B1 (fr) 2007-06-06
DE50112597D1 (de) 2007-07-19
ES2286054T3 (es) 2007-12-01
JP2002327603A (ja) 2002-11-15
US6676372B2 (en) 2004-01-13

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