EP2522909B1 - Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur - Google Patents

Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur Download PDF

Info

Publication number
EP2522909B1
EP2522909B1 EP11165818.3A EP11165818A EP2522909B1 EP 2522909 B1 EP2522909 B1 EP 2522909B1 EP 11165818 A EP11165818 A EP 11165818A EP 2522909 B1 EP2522909 B1 EP 2522909B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
burner
optical sensor
insert
wall
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
EP11165818.3A
Other languages
German (de)
English (en)
Other versions
EP2522909A1 (fr
Inventor
Andreas Böttcher
Olga Deiss
Sabine GRENDEL
Jens Kleinfeld
Andre Kluge
Tobias Krieger
Daniel Vogtmann
Marcus ZURHORST
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
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 EP11165818.3A priority Critical patent/EP2522909B1/fr
Priority to RU2012119495/06A priority patent/RU2012119495A/ru
Priority to CN2012101487241A priority patent/CN102777935A/zh
Publication of EP2522909A1 publication Critical patent/EP2522909A1/fr
Application granted granted Critical
Publication of EP2522909B1 publication Critical patent/EP2522909B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/02—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium
    • F23N5/08—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements
    • F23N5/082—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements using electronic means
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/10—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to unwanted deposits on blades, in working-fluid conduits or the like
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F23N5/242—Preventing development of abnormal or undesired conditions, i.e. safety arrangements using electronic means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2229/00—Flame sensors
    • F23N2229/20—Camera viewing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2231/00—Fail safe
    • F23N2231/10—Fail safe for component failures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2241/00—Applications
    • F23N2241/20—Gas turbines

Definitions

  • the invention relates to a burner gas turbine with at least one according to the preamble of claim 1, as from US 2006/0088793 A known.
  • the invention relates to a method for controlling a gas turbine with such a burner.
  • Combustion chambers are u. a. Component of gas turbines, which are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. The fuel is burned to burners in their downstream combustion chambers, wherein compressed air is supplied by an air compressor.
  • each burner can be assigned a separate combustion chamber, wherein the working medium flowing out of the combustion chambers can be brought together before or in the turbine unit.
  • the combustion chamber can also be designed in a so-called annular combustion chamber design, in which a plurality, in particular all, of the burner open into a common, usually annular combustion chamber.
  • the turbine unit has a number of rotatable turbine blades connected to the turbine shaft.
  • the turbine blades are arranged in a ring on the turbine shaft and thus form a number of blade rows.
  • the turbine comprises a number of fixed turbine vanes, which are also annular with the formation of rows of vanes on an inner casing the turbine are attached.
  • the turbine blades serve to drive the turbine shaft by momentum transfer from the working medium flowing through the turbine.
  • the turbine guide vanes serve to guide the flow of the working medium between two respective rows of rotor blades or rotor blade rings viewed in the flow direction of the working medium.
  • a successive pair of a turbine nozzle vane or vane row and a turbine blade ring or blade row downstream of the working medium in the flow direction form a turbine stage.
  • the combustion chamber wall is usually provided on its inner side with an existing of heat shield elements inner lining, which can be provided with particularly heat-resistant protective layers, and which are cooled by the actual combustion chamber wall through.
  • the invention is therefore based on the object of specifying an improved burner in a gas turbine. Another object is to specify a method for controlling a gas turbine with this burner.
  • the object related to the burner is achieved by the specification of a burner according to claim 1.
  • the object related to the method is achieved by the specification of a method according to claim 5.
  • the burner comprises a combustion chamber, a combustion chamber interior and a burner chamber wall and a number of downstream of the combustion chamber arranged turbine blades with a first row of turbine blades.
  • the burner comprises a burner insert which secures the burner to the combustion chamber wall.
  • the burner insert has a combustion chamber insert wall.
  • the combustion chamber insert wall is upstream of the combustion chamber interior.
  • the burner comprises at least one Zumischbrennstofflanze, which is supplied in the Zumischbrunstoff safely with Zumischbrennstoff and is formed during operation without Zumischbrennstoff as a fuel lance dummy.
  • at least one optical sensor is arranged on or adjacent to the combustion chamber insert wall during operation of the burner with admixed fuel.
  • At least one optical sensor disposed in the fuel lance dummy in operation without Zumischbrennstoff invention, at least one optical sensor disposed in the fuel lance dummy.
  • the optical sensor which is designed in particular as a camera, lies directly opposite the first turbine guide vane row.
  • the optical sensor provides by this arrangement images with which the first turbine vane row can be monitored. If the entire area of the first turbine vane row is to be monitored, only a small number of sensors are required for this purpose. Compared to the acoustic system, which can be influenced by other sounds, such a burner with an optical sensor is more reliable.
  • the state of the first turbine guide vane row can thus be optically monitored without the gas turbine resting.
  • the arrangement of the optical sensor in the fuel lance dummy has the additional advantage that the optical sensor is easy to install and remove.
  • the first turbine vane row can be monitored online with the optical sensor.
  • the gas turbine can be shut down in time if the condition of the blades is critical or, for example, foreign bodies are located immediately before the first row of turbine blades.
  • At least two burners are provided, which are arranged in the circumferential direction of a combustion chamber, wherein each burner comprises a burner insert, which attaches each of the burners to the combustion chamber wall, wherein each burner insert has a combustion chamber wall, and wherein the at least two combustion chamber insert walls also in the circumferential direction of the combustion chamber while leaving a gap adjacent to each other and with the optical sensor disposed in the gap between the combustor liner walls.
  • the combustion liner wall adjoins the combustion chamber wall leaving a gap.
  • the optical sensor is disposed in the gap between the combustor liner wall and the combustion chamber wall. In these arrangements, the sensor is located directly opposite the first row of turbine blades and is also particularly easy to attach.
  • images are returned from the optical sensor and foreign objects are automatically detected in the images returned from the optical sensor by means of suitable software.
  • a warning is issued and the gas turbine is brought to a standstill.
  • FIG. 1 A section of a combustion chamber is in FIG. 1 shown in a sectional view.
  • a burner 1 a burner insert 3, which annularly surrounds the burner 1, and to recognize a part of the combustion chamber wall 5.
  • the combustion chamber is arranged in a Brennschplenum 4 and extends annularly around a turbine shaft (not shown).
  • the burner 1 is inserted into a receptacle of the burner insert 3.
  • the burner insert 3 adjoins the combustion chamber wall 5 and closes the combustion chamber from the front side.
  • the burner insert 3 comprises a carrier, which is designed as a grooved ring 7.
  • a burner insert wall 9 which at the same time represents the end wall of the combustion chamber surrounding the burner 1.
  • the front side of the combustion chamber basically consists only of combustion chamber insert walls 9.
  • the burner wall 27 surrounding the burner opening 33 can be seen.
  • a separate burner insert 3 is present for each burner 1.
  • the burner insert walls 9 of adjacent burner inserts 3 adjoin in the circumferential direction while leaving a gap 20 (FIG. FIG. 2 ) to each other.
  • the combustion chamber insert walls 9 also adjoin the combustion chamber wall 5 while leaving a gap 30. Both in the gap 30 and in the gap 20 (FIG. FIG. 2 ) seals (not shown) may be arranged.
  • the burner 1 has a Zumischbrenner with Zumischbrennstof Lanze 23.
  • the burner 1 can be operated with Zumischbrennstoff or without Zumischbrennstoff.
  • the Zumischbrenner is operated with liquid fuel, such as fuel oil. If the burner 1 is operated without liquid fuel, the Zumischbrennstof Lanze 23 is replaced with a dummy fuel dummy (not shown).
  • the combustion chamber wall 5 is provided on its inside with a protective layer of heat shield elements (not shown).
  • FIG. 2 shows the arrangement of an optical sensor according to the invention, which is designed in particular as a security camera 22, in the gap 20 between two combustion chamber insert walls 3.
  • the surveillance camera 22 may also be disposed adjacent to or in other areas of the combustion chamber insert walls 3.
  • the radially outer combustion chamber wall 5 A and the radially inner combustion chamber wall 5 B can be seen, which connect the combustion chamber insert wall 9 with the combustion chamber wall 5.
  • at least two burners 1 during operation of the burner 1 ( FIG. 1 ) with liquid fuel at least one monitoring camera 22 in the gap 20 between the combustion chamber insert walls 3 is arranged.
  • the camera 22 lies directly opposite the first turbine guide vane row (not shown) and thus can overlook as much space as possible.
  • the surveillance camera 22 provides camera images that monitor the area in front of the first turbine nozzle row (not shown).
  • the complete area of the first turbine vane row (not shown) can thus be monitored by a small number of cameras 22, which are arranged in the gap 20 between the circumferentially arranged combustion chamber insert walls 9.
  • the camera 22 may also be disposed in the gap 30 between the combustor liner wall 3 and the radially outer combustion chamber wall 5a and the radially inner combustion chamber wall 5B, respectively.
  • At least one monitoring camera 22 is additionally or alternatively arranged in the Zumischbrennstofflanzengetrappe (not shown), so that here the surveillance camera 22 is installed directly in the burner 1.
  • the monitoring camera 22 is easily installable and removable from outside the combustion chamber (not shown).
  • the surveillance camera 22 returns images that are analyzed with appropriate software and automatically detects foreign objects. At a predetermined size of the foreign body will issue a warning and then brought the gas turbine to a standstill and thus regulated the gas turbine.
  • the status of the first turbine nozzle row (not shown) is monitored online with the returned images.
  • combustion chamber can also be designed as an approximately cylindrical combustion chamber with at least one burner and at least one burner insert on the end face of the cylinder.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Combustion (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Testing Of Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

  1. Turbine à gaz comprenant au moins un brûleur ( 1 ), ayant une chambre de combustion, un intérieur ( 2 ) de chambre de combustion et une paroi ( 5 ) de chambre de combustion, ainsi qu'une série d'aubes de turbine, disposées en aval de la chambre de combustion, en ayant une première série d'aubes directrices de turbine, le brûleur ( 1 ) comprenant un insert ( 3 ) de brûleur, qui fixe le brûleur à la paroi ( 5 ) de la chambre de combustion, l'insert ( 3 ) de brûleur ayant une paroi ( 9 ) d'insert de chambre de combustion, et la paroi ( 9 ) d'insert de chambre de combustion étant montée en avant par rapport à l'intérieur ( 2 ) de la chambre de combustion et le brûleur ( 1 ) comprenant au moins une lance ( 23 ) d'addition de combustible de mélange, qui, en fonctionnement en combustible de mélange, est alimentée en combustible de mélange, et, en fonctionnement sans combustible de mélange, est constituée sous la forme d'un simulacre de lance à combustible,
    caractérisée en ce que,
    lorsque le brûleur ( 1 ) fonctionne avec du combustible de mélange, au moins un capteur ( 22 ) optique est monté sur ou au voisinage de la paroi ( 9 ) d'insert de chambre de combustion et/ou, en fonctionnement sans combustible de mélange, au moins un capteur ( 22 ) optique est monté dans le simulacre de lance de combustible, de manière à pouvoir contrôler la première série d'aubes directrices de turbine par le montage du capteur optique.
  2. Turbine à gaz suivant la revendication 1,
    caractérisée en ce que la première série d'aubes directrices de turbine peut être contrôlée en ligne par le capteur optique.
  3. Turbine à gaz suivant l'une des revendications 1 à 2,
    caractérisée en ce qu'il est prévu au moins deux brûleurs ( 1 ), qui sont disposés dans la direction périphérique d'une chambre de combustion, chaque brûleur ( 1 ) comprenant un insert ( 3 ) de brûleur qui fixe chacun des brûleurs ( 1 ) à la paroi ( 5 ) de la chambre de combustion, chaque insert ( 3 ) de brûleur ayant une paroi ( 9 ) d'insert de chambre de combustion et les au moins deux parois ( 9 ) d'insert de chambre de combustion étant voisines l'une de l'autre dans la direction périphérique de la chambre de combustion en laissant un intervalle ( 20 ) et le capteur optique est disposé dans l'intervalle ( 20 ).
  4. Turbine à gaz suivant l'une des revendications 1 à 3,
    caractérisée en ce que la paroi ( 9 ) d'insert de chambre de combustion est voisine de la paroi ( 5 ) de la chambre de combustion en laissant un interstice ( 30 ) et le capteur optique est disposé dans l'interstice ( 30 ).
  5. Procédé de régulation de la turbine à gaz ayant au moins un brûleur et un capteur optique suivant l'une des revendications précédentes,
    caractérisé en ce que le capteur optique fournit des images en retour et on détecte, dans les images fournies en retour par le capteur optique, au moyen d'un logiciel approprié, automatiquement des corps étrangers, et, pour une dimension fixée à l'avance du corps étranger, on émet un avertissement et on met la turbine à gaz à l'arrêt.
EP11165818.3A 2011-05-12 2011-05-12 Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur Not-in-force EP2522909B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP11165818.3A EP2522909B1 (fr) 2011-05-12 2011-05-12 Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur
RU2012119495/06A RU2012119495A (ru) 2011-05-12 2012-05-11 Горелка и способ регулирования газовой турбины с указанной горелкой
CN2012101487241A CN102777935A (zh) 2011-05-12 2012-05-14 燃烧器和用这种燃烧器控制燃气轮机的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11165818.3A EP2522909B1 (fr) 2011-05-12 2011-05-12 Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur

Publications (2)

Publication Number Publication Date
EP2522909A1 EP2522909A1 (fr) 2012-11-14
EP2522909B1 true EP2522909B1 (fr) 2015-04-08

Family

ID=44582059

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11165818.3A Not-in-force EP2522909B1 (fr) 2011-05-12 2011-05-12 Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur

Country Status (3)

Country Link
EP (1) EP2522909B1 (fr)
CN (1) CN102777935A (fr)
RU (1) RU2012119495A (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019217983A1 (de) * 2019-11-21 2021-05-27 Siemens Aktiengesellschaft Brennereinsatz, Verfahren zu dessen Herstellung sowie Verwendung eines solchen Brennereinsatzes

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL1018974C2 (nl) * 2001-09-18 2003-04-04 Kema Nv Werkwijze en inrichting voor het onderzoeken van de rek van langwerpige lichamen.
US20060088793A1 (en) * 2004-10-22 2006-04-27 Siemens Westinghouse Power Corporation Optical viewing system for monitoring a wide angle area of interest exposed to high temperature
EP1767855A1 (fr) * 2005-09-27 2007-03-28 Siemens Aktiengesellschaft Chambre de combustion et turbine à gaz
US7432505B2 (en) * 2006-05-04 2008-10-07 Siemens Power Generation, Inc. Infrared-based method and apparatus for online detection of cracks in steam turbine components
EP2040062A1 (fr) * 2007-09-18 2009-03-25 Siemens Aktiengesellschaft Inspection de chambres à haute température
US7853433B2 (en) * 2008-09-24 2010-12-14 Siemens Energy, Inc. Combustion anomaly detection via wavelet analysis of dynamic sensor signals

Also Published As

Publication number Publication date
CN102777935A (zh) 2012-11-14
RU2012119495A (ru) 2013-11-20
EP2522909A1 (fr) 2012-11-14

Similar Documents

Publication Publication Date Title
EP1443275B1 (fr) Chambre de combustion
EP1446557B1 (fr) Turbomachine
DE102011056237A1 (de) Verfahren, Systeme und Vorrichtungen zur Detektion von Materialfehlern in Brennkammern von Verbrennungsturbinen
DE102007042767A1 (de) Mehrschichtiger Abschirmungsring für einen Flugantrieb
EP2379846B1 (fr) Structure de support d'aubes directrices pour turbomachine
EP2084368B1 (fr) Aube de turbine
DE10311038A1 (de) Rotoreinsatzbaugruppe und Retrofit-Verfahren
EP2035669A1 (fr) Système d'air secondaire pour turbine de turbocompresseur
DE102011056239A1 (de) Verfahren, Systeme und Vorrichtungen zur Detektion von Materialfehlern in Brennkammern von Verbrennungsturbinen
EP2522909B1 (fr) Turbine à gaz avec brûleur et procédé de réglage d'une turbine à gaz dotée d'un tel brûleur
EP1904717B1 (fr) Element de carter conducteur de gaz chaud, enveloppe de protection d'arbre et systeme de turbine a gaz
EP2206885A1 (fr) Turbine à gaz
WO2004090423A1 (fr) Element d'ecran thermique
EP1724526A1 (fr) Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
DE102012100170A1 (de) Verfahren, Systeme und Vorrichtungen zum Erkennen von Materialdefekten in Brennkammern von Verbrennungskraft-Turbinenmaschinen
EP2725203B1 (fr) Conduite d'air froid dans une structure de boîtier d'une turbomachine
DE102012023626A1 (de) Hochdruck-Verdichter, insbesondere einer Gasturbine
EP1636461B1 (fr) Turbomachine, en particulier turbine a gaz
EP1429077B1 (fr) Turbine à gaz
EP1473517A1 (fr) Chambre de combustion
DE102012014646A1 (de) Kompressorrotor
EP2040062A1 (fr) Inspection de chambres à haute température
EP2024684A1 (fr) Composant de machine blindé et turbine à gaz
DE102006010863B4 (de) Turbomaschine, insbesondere Verdichter
EP2995859A1 (fr) Élément de bouclier thermique pour un bouclier thermique d'une chambre de combustion

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: 20120507

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL 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 RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

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

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F23N 5/08 20060101AFI20141006BHEP

Ipc: F01D 21/10 20060101ALI20141006BHEP

Ipc: F23R 3/60 20060101ALI20141006BHEP

Ipc: F23N 5/24 20060101ALI20141006BHEP

Ipc: F01D 21/00 20060101ALI20141006BHEP

INTG Intention to grant announced

Effective date: 20141024

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): AL 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 RS 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

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: FR

Ref legal event code: PLFP

Year of fee payment: 5

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 720878

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150515

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502011006494

Country of ref document: DE

Effective date: 20150521

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

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

Ref country code: GB

Payment date: 20150511

Year of fee payment: 5

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20150408

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

Ref country code: FR

Payment date: 20150513

Year of fee payment: 5

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150408

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150408

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: 20150810

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: 20150408

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: 20150708

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: 20150408

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: 20150408

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

Ref country code: DE

Payment date: 20150720

Year of fee payment: 5

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

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: 20150709

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: 20150408

Ref country code: RS

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: 20150408

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: 20150808

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

Ref country code: IT

Payment date: 20150513

Year of fee payment: 5

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502011006494

Country of ref document: DE

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

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: 20150408

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: 20150408

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: 20150408

Ref country code: LI

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

Effective date: 20150531

Ref country code: CH

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

Effective date: 20150531

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

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

Ref country code: RO

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

Effective date: 20150408

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: 20150408

Ref country code: PL

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: 20150408

Ref country code: CZ

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: 20150408

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

Ref country code: SE

Payment date: 20150507

Year of fee payment: 5

26N No opposition filed

Effective date: 20160111

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: 20150512

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: 20150408

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502011006494

Country of ref document: DE

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

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: 20150408

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

Effective date: 20160512

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

Ref country code: SE

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

Effective date: 20160513

Ref country code: IT

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

Effective date: 20160512

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170131

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: 20160531

Ref country code: DE

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

Effective date: 20161201

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: 20160512

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: 20150408

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: 20150408

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: 20110512

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: 20150408

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 720878

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160512

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

Ref country code: BE

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

Effective date: 20150531

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: 20160512

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: 20150408

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: 20150512

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

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: 20150408

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

Ref country code: AL

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: 20150408