EP2347101B1 - Turbine à gaz et moteur à turbine à gaz associé - Google Patents

Turbine à gaz et moteur à turbine à gaz associé Download PDF

Info

Publication number
EP2347101B1
EP2347101B1 EP09827201.6A EP09827201A EP2347101B1 EP 2347101 B1 EP2347101 B1 EP 2347101B1 EP 09827201 A EP09827201 A EP 09827201A EP 2347101 B1 EP2347101 B1 EP 2347101B1
Authority
EP
European Patent Office
Prior art keywords
turbine
gas turbine
gas
wall
hollow
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
EP09827201.6A
Other languages
German (de)
English (en)
Other versions
EP2347101A1 (fr
Inventor
Francois Benkler
Tobias Buchal
Andreas Böttcher
Martin Hartmann
Patricia Hülsmeier
Uwe Kahlstorf
Ekkehard Maldfeld
Dieter Minninger
Michael Neubauer
Peter Schröder
Rostislav Teteruk
Vyacheslav Veitsman
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 EP09827201.6A priority Critical patent/EP2347101B1/fr
Priority to PL09827201T priority patent/PL2347101T3/pl
Publication of EP2347101A1 publication Critical patent/EP2347101A1/fr
Application granted granted Critical
Publication of EP2347101B1 publication Critical patent/EP2347101B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings

Definitions

  • the invention relates to a gas turbine having a substantially hollow conical or hollow cylindrical, extending along a machine axis vane carrier and a segmented in the circumferential and / or axial direction in ring segments, substantially hollow cone-shaped or hollow cylindrical outer wall of an annular hot gas path whose ring segments by means of a number are fastened by hooking elements on the inside of the guide blade carrier.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a number of rotor blades which are usually combined into blade groups or rows of blades, are arranged thereon and drive the turbine shaft via a momentum transfer from the working medium.
  • guide vanes are also usually arranged between adjacent rotor blade rows and connected to the turbine housing, which are combined into rows of guide blades. These are attached to a usually hollow cylindrical or hollow cone-shaped vane carrier.
  • the hot gas channel is usually lined by so-called ring segments which form axial sections of the outer wall of the hot gas channel. These are usually fastened via hooking elements on the guide blade carrier, so that the entirety of the ring segments in the circumferential direction as well as the guide blade carrier form a hollow conical or hollow cylindrical structure.
  • the components of the gas turbine can deform by different thermal expansion in different operating conditions, which has a direct influence on the size of the radial gap between the blades and the outer wall of the hot gas channel.
  • These radial gaps are differently dimensioned when starting and stopping the turbine than in regular operation.
  • the gas turbine components such as guide vane or outer wall are always to be dimensioned so that the radial gaps are kept sufficiently large to cause any damage to the gas turbine in any operating condition.
  • a correspondingly comparatively generous design of the radial gaps leads to considerable losses in the efficiency.
  • the invention is therefore based on the object to provide a gas turbine, which allows a particularly high efficiency while maintaining the greatest possible operational safety and life.
  • interlocking elements of at least one of the ring segments of the input gas turbine engine are geometrically adjusted such that in the non-operating state the outer wall delimiting the hot gas path has a substantially elliptical cross-sectional contour in a section perpendicular to the machine axis.
  • the invention is based on the consideration that a particularly high efficiency would be possible by reducing the radial gaps in regular operation, ie, for example, full load operation of the gas turbine.
  • a comparatively large dimension of the radial gaps was required in particular because the turbine deforms differently in different operating states.
  • an ovalization of the cylindrical or conically shaped components of the gas turbine occurs, which must be taken into account in the design of the radial gaps.
  • the ovalization in the operation of the gas turbine should be kept as low as possible.
  • This cross-sectional contour should be designed in such a way that the cross-sectional contour present at room temperature after installation of the gas turbine is then circular due to thermal deformations occurring in the operating state
  • the thermal expansions should therefore not, as in the prior art JP 2005-042612 and JP 54-081409 to be suppressed.
  • the ring segments described at the beginning with which the hot gas path is lined outside the rotor blades, correspondingly.
  • the ring segments form in the axial section of the blades in the circumferential direction of the outer wall of the hot gas path, which thus together form the rotor blades the closest lying hollow cone-shaped or hollow cylindrical component of the gas turbine. Therefore, the cross-section perpendicular to the machine axis of the ring segments forming the outer wall of the hot gas path has the elliptical cross-sectional contour described in the inoperative state.
  • the ring segments forming the outer wall of the hot gas path in the axial section of the rotor blades are usually hooked in the guide blade carrier via hooking elements. Since the vane support is a relatively solid component which has a comparatively large deformation during operation, the cross-sectional contour formed by all ring segments in the operating state is often determined by the attachment or clamping of the ring segments in the vane support and its deformation during operation. It is therefore not absolutely necessary to manufacture the cold contour of the external wall consisting of ring segments in elliptical form, since the deformation induced by the contact points on the interlocking elements is established anyway.
  • the compensation of the ovalization of the guide vane carrier can therefore be achieved by advantageously only the individual hooking elements of the ring segments are adapted so that the outer wall of a substantially elliptical Has cross-sectional contour. Since these ring segments are exchangeable service parts, this makes it possible on the one hand to retrofit existing gas turbines, on the other hand to compensate for manufacturing errors in guide vanes and also a particularly simple adaptation to changing driving styles including other modified measures to reduce the radial gap.
  • the length of the main and minor axes of the elliptical cross-sectional contour in each case selected such that the respective component has a substantially circular cross-sectional contour by its thermal deformation in the operating state in the production of the hollow cone-shaped or hollow cylindrical components of the gas turbine.
  • This can be done, for example, by introducing an expected in operation by 90 degrees offset ovalization.
  • the elliptical shape of these components is thus chosen so that the deformations are compensated in the operating state just so that the operation produces a circular cross-section and thus over the entire circumference of the gas turbine same radial gaps are present, d. h.,
  • the radial gaps have no variance over the circumference. As a result, even in the construction of the radial gaps can be sized accordingly narrow, which has a higher efficiency of the gas turbine result.
  • the interlocking elements are adapted in their radial length and / or arranged to change the radial position of the interlocking elements in a corresponding retaining groove of the guide blade carrier inserts. These then lie between the hooks of the hooking elements and the retaining groove and thus lead along the circumference to different radial positions of ring segments.
  • De Facto can thus be provided either distributed along the circumference ring segments with different lengths radial entanglements in the vane support, or the Verhakungsetti the ring segments along a circumference are identical, in which case to change the radial Position of the ring segments along the circumference of different thickness supplements are used for the corresponding entanglements.
  • the turbine shaft in the cold operating state, can be displaced in the direction of the hot gas flow, so that an enlargement of the radial gap occurs in the case of a hollow conical shape of the outer wall with enlargement of the radius in the direction of the hot gas flow in the cold inoperative state, and thus in the cold state (eg when starting the combustion process) Gas turbine), the remaining counter-ovalization represents no restriction for the achievable radial gap in the warm state. As a result, an even greater efficiency of the gas turbine can be achieved.
  • such a gas turbine is used in a gas and steam turbine plant.
  • the advantages achieved by the invention are, in particular, that a particularly high efficiency of the gas turbine is achieved by a reduction of the radial gaps by a targeted design of the hollow cone-shaped or hollow cylindrical components of a gas turbine such that they have a substantially elliptical cross-sectional contour in the inoperative state.
  • a particularly high efficiency of the gas turbine is achieved by a reduction of the radial gaps by a targeted design of the hollow cone-shaped or hollow cylindrical components of a gas turbine such that they have a substantially elliptical cross-sectional contour in the inoperative state.
  • the gas turbine 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine unit 6 for driving the compressor 2 and a generator, not shown, or a working machine.
  • the turbine unit 6 and the compressor 2 are arranged on a common, also referred to as a turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its turbine axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the turbine unit 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine unit 6 comprises a number of stationary vanes 14, which are also attached in a donut-like manner to a vane support 16 of the turbine unit 6 to form rows of vanes.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine unit 6 flowing through the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of blades 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18 which is arranged to fix the respective vane 14 to a vane support 16 of the turbine unit 6 as a wall element.
  • the platform 18 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the working medium M flowing through the turbine unit 6.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 19, also referred to as a blade root.
  • each ring segment 21 is arranged on a guide blade carrier 16 of the turbine unit 6 respectively.
  • the inner surface of each ring segment 21 is also exposed to the hot, the turbine unit 6 flowing through the working medium M and therefore limits the outside of the annular hot gas path as the outer wall.
  • In the radial direction is the outer wall from the outer end of the opposite blades 12 spaced by a radial gap.
  • the ring segments 21 arranged between adjacent guide blade rows serve in particular as cover elements which protect the guide blade carrier 16 or other housing built-in components against thermal overstress by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is designed in the embodiment as a so-called annular combustion chamber, in which a plurality of circumferentially around the turbine shaft 8 arranged around burners 10 open into a common combustion chamber space.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8 around.
  • FIG. 2 and FIG. 3 now schematically show the guide vane 16 of the gas turbine 1 in a cross section perpendicular to the turbine axis 9 once left in the inoperative state, ie at cold gas turbine 1, and right in the operating state, ie at operating temperature.
  • the guide vane carrier 16 has a material temperature corresponding to the ambient temperature of the gas turbine.
  • the operating temperature is much higher; beyond 100 ° C.
  • the guide blade carrier 16 is composed of an upper segment 24 and a lower segment 26.
  • the two segments 24, 26 are connected to one another via flanges 28 and each form a connecting joint 30 at their connection point.
  • FIG. 2 4 illustrates a deformation of the prior art vane support 16 such that the distance between the peaks 32 of the respective upper and lower portions 24, 26 increases.
  • the cross section of the guide blade carrier 16 thereby deforms into a vertical ellipse.
  • a circular contour is shown for comparison in dashed line style.
  • the turbine shaft 8 is displaceable along the turbine axis 9.
  • the turbine shaft 8 In the cold state, that is, if there is an elliptical shape of the hot gas channel, then the turbine shaft 8 can be moved in the direction of the hot gas flow direction. As a result of the conical shape of the hot gas channel, this causes an enlargement of the radial gaps. Then, when in operation, a circular cross-section sets by thermal deformation, the turbine shaft 8 is displaced in the reverse direction to optimize the radial gap.
  • the ring segments 21 can be configured by a correspondingly introduced ovalization so that the hot gas channel receives a circular cross-section during operation.
  • the Verhakungs institute for fixing the ring segments 21 on the guide blade carrier 16 may be different lengths, ie be different lengths for different circumferential positions, or inserts between the hook and holding the guide vane 16 are introduced, which influence the radial position of the respective ring segments 21 with the same length Verhakungs instituten.
  • the perpendicular to the machine axis cross-sectional contour of the Ring segments 21 formed radially outer outer wall of the annular hot gas channel is namely largely determined by the passed through the Verhakungs institute the ring segments deformation of the vane support 16. Accordingly, in 2 and FIG. 3 Instead of guide vanes 16 also be understood - then flangeless - the outer wall of the hot gas path of a gas turbine.
  • the ovalization can be avoided in the operating state.
  • the radial gaps can be designed correspondingly smaller, resulting in a significantly higher overall efficiency of the gas turbine 1 without sacrificing operational safety.

Landscapes

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

Claims (5)

  1. Turbine ( 1 ) à gaz ayant un support ( 16 ) d' aubes directrices sensiblement en forme de cône creux ou de cylindre creux et s' étendant le long d'un axe de machine et une paroi extérieure d' un trajet annulaire pour du gaz chaud segmentée, dans la direction périphérique et/ou axiale, en segments ( 21 ) annulaires et sensiblement en forme de cône creux et/ou de cylindre creux, dont les segments ( 21 ) annulaires sont fixés au moyen d'un certains nombres d'éléments d' accrochage au côté intérieur du support ( 16 ) d' aubes directrices,
    caractérisée en ce que
    les éléments d' accrochage d' au moins l'un des segments ( 21 ) annulaires sont adaptés géométriquement de manière à ce que, dans l'état hors de fonctionnement suivant une coupe perpendiculaire à l'axe de la machine, la paroi extérieure délimitant le trajet pour du gaz chaud ait un contour de section transversale sensiblement en forme d' ellipse.
  2. Turbine ( 1 ) à gaz suivant la revendication 1,
    dans laquelle les longueurs du grand axe et du petit axe du contour de section transversale en forme d' ellipse sont choisies respectivement de manière à ce que la paroi extérieure ait, après la déformation thermique se produisant dans l'état de fonctionnement, un contour de section transversale sensiblement circulaire.
  3. Turbine ( 1 ) à gaz suivant la revendication 1 ou 2,
    dans laquelle les éléments d'accrochage sont adaptés dans leur longueur radiale et/ou pour des positions radiales différentes des éléments d' accrochage des cales sont disposées dans une rainure de maintien du support ( 16 ) d' aubes directrices.
  4. Turbine ( 1 ) à gaz suivant les revendications 1 à 3,
    qui comprend un arbre ( 8 ) de turbine ayant un certain nombre d' aubes ( 12 ) mobiles regroupées en rangées d' aubes mobiles et disposées tout autour d' un dispositif de palier de l' arbre ( 8 ) de la turbine, qui est conçu de manière à ce que l'arbre ( 8 ) de la turbine puisse coulisser le long de l' axe ( 9 ) de la turbine.
  5. Installation de turbine à gaz et de turbine à vapeur ayant une turbine ( 1 ) à gaz suivant l'une des revendications 1 à 4.
EP09827201.6A 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé Not-in-force EP2347101B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP09827201.6A EP2347101B1 (fr) 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé
PL09827201T PL2347101T3 (pl) 2008-11-19 2009-09-15 Turbina gazowa i odpowiednia przemysłowa instalacja turbiny gazowej lub parowej

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08020190A EP2189630A1 (fr) 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz
EP09827201.6A EP2347101B1 (fr) 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé
PCT/EP2009/061936 WO2010057698A1 (fr) 2008-11-19 2009-09-15 Turbine à gaz

Publications (2)

Publication Number Publication Date
EP2347101A1 EP2347101A1 (fr) 2011-07-27
EP2347101B1 true EP2347101B1 (fr) 2013-07-03

Family

ID=40532518

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08020190A Withdrawn EP2189630A1 (fr) 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz
EP09827201.6A Not-in-force EP2347101B1 (fr) 2008-11-19 2009-09-15 Turbine à gaz et moteur à turbine à gaz associé

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP08020190A Withdrawn EP2189630A1 (fr) 2008-11-19 2008-11-19 Turbine à gaz, support d'aube directrice pour une telle turbine à gaz, et moteur à turbine à gaz avec une telle turbine à gaz

Country Status (7)

Country Link
US (1) US9074490B2 (fr)
EP (2) EP2189630A1 (fr)
JP (1) JP5281167B2 (fr)
CN (1) CN102216570B (fr)
ES (1) ES2426099T3 (fr)
PL (1) PL2347101T3 (fr)
WO (1) WO2010057698A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8506245B2 (en) * 2010-07-08 2013-08-13 General Electric Company Steam turbine shell
JP5738127B2 (ja) * 2011-09-01 2015-06-17 三菱日立パワーシステムズ株式会社 蒸気タービン
EP3078448B1 (fr) * 2015-04-10 2018-07-11 Rolls-Royce Deutschland Ltd & Co KG Procédé d'usinage d'un carter pour une turbomachine.
ES2865387T3 (es) * 2017-08-04 2021-10-15 MTU Aero Engines AG Segmento de paletas guía para una turbina
KR102062594B1 (ko) * 2018-05-11 2020-01-06 두산중공업 주식회사 베인 캐리어, 이를 포함하는 압축기 및 가스 터빈

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3169748A (en) * 1962-12-06 1965-02-16 Westinghouse Electric Corp Turbine apparatus
JPS5481409A (en) * 1977-12-12 1979-06-28 Hitachi Ltd Turbine casing
US4426191A (en) * 1980-05-16 1984-01-17 United Technologies Corporation Flow directing assembly for a gas turbine engine
JPS58160502A (ja) 1982-03-19 1983-09-24 Toshiba Corp コンバインドサイクルプラントの起動方法
JPS62126225A (ja) * 1985-11-25 1987-06-08 Hitachi Ltd タ−ビン過給機のタ−ビンケ−ス
US5063661A (en) * 1990-07-05 1991-11-12 The United States Of America As Represented By The Secretary Of The Air Force Method of fabricating a split compressor case
US5605438A (en) * 1995-12-29 1997-02-25 General Electric Co. Casing distortion control for rotating machinery
CN1212323A (zh) * 1998-05-13 1999-03-31 韩凤琳 热流涡轮机
EP1131537B1 (fr) 1998-11-11 2004-10-06 Siemens Aktiengesellschaft Procede de fonctionnement d'une turbomachine
EP1022439B1 (fr) * 1999-01-20 2004-05-06 ALSTOM Technology Ltd Carter de turbine à vapeur ou à gaz
US6409471B1 (en) * 2001-02-16 2002-06-25 General Electric Company Shroud assembly and method of machining same
ATE353416T1 (de) * 2001-07-06 2007-02-15 R & D Dynamics Corp Hydrodynamische folien-gleitringdichtung
GB2383380B (en) * 2001-12-19 2005-05-25 Rolls Royce Plc Rotor assemblies for gas turbine engines
US6691019B2 (en) * 2001-12-21 2004-02-10 General Electric Company Method and system for controlling distortion of turbine case due to thermal variations
US6715297B1 (en) * 2002-09-20 2004-04-06 General Electric Company Methods and apparatus for supporting high temperature ducting
US6811315B2 (en) * 2002-12-18 2004-11-02 Pratt & Whitney Canada Corp. Compliant support for increased load capacity axial thrust bearing
JP2005042612A (ja) * 2003-07-22 2005-02-17 Ishikawajima Harima Heavy Ind Co Ltd ケーシング及びケーシングの変形防止システム並びにその方法
US7255929B2 (en) * 2003-12-12 2007-08-14 General Electric Company Use of spray coatings to achieve non-uniform seal clearances in turbomachinery
DE102004058487A1 (de) * 2004-12-04 2006-06-14 Mtu Aero Engines Gmbh Gasturbine
US7374396B2 (en) * 2005-02-28 2008-05-20 General Electric Company Bolt-on radial bleed manifold
US7681601B2 (en) * 2005-08-24 2010-03-23 Alstom Technology Ltd. Inner casing of a rotating thermal machine
US8801370B2 (en) * 2006-10-12 2014-08-12 General Electric Company Turbine case impingement cooling for heavy duty gas turbines
US8128353B2 (en) * 2008-09-30 2012-03-06 General Electric Company Method and apparatus for matching the thermal mass and stiffness of bolted split rings

Also Published As

Publication number Publication date
EP2347101A1 (fr) 2011-07-27
CN102216570A (zh) 2011-10-12
CN102216570B (zh) 2014-03-05
US20110280721A1 (en) 2011-11-17
JP5281167B2 (ja) 2013-09-04
JP2012508843A (ja) 2012-04-12
US9074490B2 (en) 2015-07-07
ES2426099T3 (es) 2013-10-21
WO2010057698A1 (fr) 2010-05-27
EP2189630A1 (fr) 2010-05-26
PL2347101T3 (pl) 2013-12-31

Similar Documents

Publication Publication Date Title
EP2342427B1 (fr) Support d'aubes statorique axialement segmenté d'une turbine à gaz
EP0991850B1 (fr) Arbre de turbine a vapeur avec refroidissement interne et procede pour refroidir un arbre de turbine
EP2342425B1 (fr) Turbine à gaz avec plaque de fixation entre la base d'aube et le disque
EP3153667B1 (fr) Dispositif de sécurisation axiale d'une aube mobile et dispositif de rotor équipé d'une telle sécurisation
DE102010016532A1 (de) Turbinengehäuse mit Bolzenlagerung
EP2344723B1 (fr) Turbine à gaz avec plaques d'étanchéité sur le disque de turbine
EP2347101B1 (fr) Turbine à gaz et moteur à turbine à gaz associé
EP1653049B1 (fr) Couronne d'aubes directrices pour turbines à gaz et procédé pour sa modification
EP2411631B1 (fr) Plaque d'étanchéité et système d'aube tournante
EP2206885A1 (fr) Turbine à gaz
EP2823154B1 (fr) Conduit de pontage pour fluide de refroidissement, aube statorique, turbine à gaz et centrale énergétique associées
EP2347100B1 (fr) Turbine à gaz avec insert de refroidissement
WO2009109430A1 (fr) Dispositif d’étanchéité et turbine à gaz
EP1731715A1 (fr) Transition d'une chambre de combustion à une turbine
EP2196628A1 (fr) Support d'aube directrice
EP2218882A1 (fr) Système de support d'aube directrice
EP1398569A1 (fr) Turbine à gaz
EP2324208A1 (fr) Support d'aubes directrices pour une turbine à gaz et procédé permettant de faire fonctionner une turbine à gaz
EP2194236A1 (fr) Carter de turbine
EP2218880A1 (fr) Système de contrôle actif de jeu pour turbine à gaz
EP2352909B1 (fr) Support d'aubes directrices
EP2184449A1 (fr) Support d'aube directrice, turbine à gaz et moteur à turbine à gaz ou à vapeur avec un tel support d'aube directrice
WO2010023036A1 (fr) Support d'aubes directrices pour une turbine à gaz
EP2236761A1 (fr) Support d'aube directrice

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20110421

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: AT

Ref legal event code: REF

Ref document number: 619914

Country of ref document: AT

Kind code of ref document: T

Effective date: 20130715

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502009007514

Country of ref document: DE

Effective date: 20130822

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2426099

Country of ref document: ES

Kind code of ref document: T3

Effective date: 20131021

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

REG Reference to a national code

Ref country code: NL

Ref legal event code: T3

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: PL

Ref legal event code: T3

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20131103

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130626

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20131003

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20131104

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20131004

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20130930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20140404

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20140530

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502009007514

Country of ref document: DE

Effective date: 20140404

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130915

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130915

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090915

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20130703

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20160914

Year of fee payment: 8

Ref country code: NL

Payment date: 20160905

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: AT

Payment date: 20160809

Year of fee payment: 8

Ref country code: PL

Payment date: 20160823

Year of fee payment: 8

Ref country code: CZ

Payment date: 20160914

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20161202

Year of fee payment: 8

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20161021

Year of fee payment: 8

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170915

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20171001

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 619914

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170915

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170915

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20171001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170915

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170930

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170930

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170915

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20181019

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20180926

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20181119

Year of fee payment: 10

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170916

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170915

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009007514

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190915