EP1476699B1 - Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz - Google Patents

Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz Download PDF

Info

Publication number
EP1476699B1
EP1476699B1 EP02782607.2A EP02782607A EP1476699B1 EP 1476699 B1 EP1476699 B1 EP 1476699B1 EP 02782607 A EP02782607 A EP 02782607A EP 1476699 B1 EP1476699 B1 EP 1476699B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
damping
helmholtz damper
damping volume
volume
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related
Application number
EP02782607.2A
Other languages
German (de)
English (en)
Other versions
EP1476699A1 (fr
Inventor
Peter Graf
Stefan Tschirren
Helmar Wunderle
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1476699A1 publication Critical patent/EP1476699A1/fr
Application granted granted Critical
Publication of EP1476699B1 publication Critical patent/EP1476699B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Images

Classifications

    • 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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to the field of gas turbines. It relates to a combustion chamber for a gas turbine according to the preamble of claim 1.
  • Such a combustion chamber is z. B. from the EP-A1-0 597 138 respectively. US-A-5,373,695 known.
  • thermoacoustic oscillations in frequency and amplitude are influenced by the various geometric and operating parameters of the combustion chamber, the expected vibrations can be predicted only very poorly in a new combustion chamber. It may therefore be that the Helmholtz damper used on the combustion chamber are not optimally matched to the actually occurring vibrations in the combustion chamber.
  • the Helmholtz damper is designed such that its damping frequency adjustable, in particular continuously adjustable, is divided by the damping volume in a fixed and a variable damping volume, the former is chosen so that the thus achievable damping frequency in the Near the frequency of one of the expected in the combustion chamber thermoacoustic oscillations, and the damping volume is changed by changing the variable damping volume, wherein the variable damping volume is limited on one side by a displaceable piston on which Helmholtz damper an adjusting element is arranged, by means of which Piston is displaceable, and, since the combustion chamber is disposed within a turbine housing, the adjusting element is operable by a closable access opening in the turbine housing.
  • the damping can be easily adapted to the thermoacoustic behavior of the combustion chamber and optimized accordingly.
  • An exchange of parts or entire dampers is not required, so that can be dispensed with corresponding large-sized access options.
  • the adjustability of the Helmholtz damper the need for different resonant frequencies differently configured damper or damper parts manufacture and ready.
  • a preferred embodiment of the invention is characterized in that the damping volume of the Helmholtz damper is continuously variable.
  • the type of adjustability of the damping frequency can be realized in a particularly simple and effective manner, in that the adjusting element arranged on the Helmholtz damper is designed in the form of a threaded rod by means of which the piston can be displaced.
  • the combustion chamber is arranged within a turbine housing, it is particularly advantageous for the actuation of the Helmholtz damper if the adjusting element can be operated by a closable access opening in the turbine housing.
  • the adjustment can be easily formed so that only a small opening is necessary for its operation, which does not require significant changes to the turbine housing.
  • the damping effect of the Helmholtz damper is particularly high when, in a combustion chamber having at its inlet side a plurality of burners which open into the combustion chamber, which is arranged at least one Helmholtz damper on the inlet side in the immediate vicinity of the burner.
  • the at least one Helmholtz damper is preferably arranged between the rings.
  • Fig. 1 is in a section in cross section, the inlet side of the combustion chamber of a gas turbine with two rings of double-cone burner and arranged therebetween, adjustable Helmholtz damper according to a preferred embodiment of the invention reproduced.
  • the gas turbine 10 is enclosed by a gas turbine housing 11 within which a filled with compressed air plenum 12 is located.
  • the plenum 12 surrounds the combustion chamber 16, which is separated from the plenum 12 by a combustion chamber housing 13.
  • the arrangement of the combustion chamber 16 within the gas turbine 10 is substantially the same as in the aforementioned document EP-A1-0 597 138 described.
  • the combustion chamber 16 is bounded on the inlet side by a front cover 26.
  • the combustion chamber 16 is annular and is equipped with burners 14, 15, which are formed in a known manner as a double-cone burner and arranged in rings around the axis of the gas turbine, as shown in the EP-A1-0 597 138 is disclosed.
  • the burners 14, 15 are arranged in corresponding openings in the front cover 26 and open into the combustion chamber 16.
  • Helmholtz damper 17 are provided to dampen the excited in the combustion chamber 16 during the combustion process.
  • the Helmholtz damper 17 show according Fig. 2 in each case a damping volume 20, 21 that is composed of a fixed cylindrical damping volume 20 and a variable cylindrical damping volume 21.
  • the damping volume 20, 21 is connected to the combustion chamber 16 via a comparatively narrow connection channel 18.
  • the arrangement of connecting channel 18 and damping volume 20, 21 forms a damping resonator, whose resonant frequency is determined inter alia by the size of the damping volume 20, 21.
  • the fixed damping volume 20 is selected such that the damping frequency achievable therewith is close to the frequency of one of the thermoacoustic oscillations to be expected in the combustion chamber 16, and that with the addition of the variable damping volume 21, the possible variation range of this frequency is covered. In this way, it is possible to tune in a newly put into operation gas turbine, the Helmholtz damper 17 exactly on the occurring, previously not exactly known vibration frequencies and thus to obtain optimal damping with the least amount of resources. It goes without saying that also different sized Helmholtz damper 17 can be used in combination for damping different vibration frequencies.
  • the change of the variable damping volume 21 can basically be achieved in different ways. Particularly favorable for adjustability, however, is the in Fig. 1 and 2 shown embodiment according to the invention, in which the variable damping volume can be changed continuously by a displaceably mounted in the piston 22 volume.
  • the displacement of the piston 22 takes place in a particularly simple and secure manner via an adjusting element 23 in the form of a threaded rod which is rotatably mounted in a threaded hole 25 in the cover 24, which closes the variable volume 21 to the outside.
  • the piston 22 may be fixedly connected to the adjusting element 23. The adjustment takes place in this case by a thread in the cover 24, in which the adjusting element 23 is guided.
  • a slot may be provided on the outer end face of the adjusting element 23, in which the blade of a screwdriver can engage. If the adjustment (the threaded rod) 23 is rotated, the piston 22 moves along the cylinder axis of the damping volume 20, 21 and can assume different positions, as in Fig. 1 is indicated.
  • the damping volume 20, 21 also changes the frequency at which the damping occurs or has its maximum.
  • the configuration of the adjusting element 23 makes it possible to operate the adjusting element 23 in a simple manner from outside the turbine housing 11, without having to make any extensive arrangements on the turbine housing.
  • Fig. 1 is to operate the adjusting element 23 on the turbine housing 11 with the axis of rotation aligned a comparatively small access opening 19 is provided which comprises a screwed, lockable nozzle. In this way, it is possible to optimally adapt the damping behavior of the individual Helmholtz dampers 17 to the actually occurring during operation in the combustion chamber 16 thermoacoustic oscillations without great circumstances.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Air Supply (AREA)
  • Fluid-Damping Devices (AREA)

Claims (6)

  1. Chambre de combustion (16) pour une turbine à gaz (10), au niveau de laquelle chambre de combustion (16) est disposé, en vue de l'amortissement de vibrations thermoacoustiques, au moins un amortisseur de Helmholtz (17) dont le volume d'amortissement (20, 21) est en liaison avec la chambre de combustion (16) par le biais d'un conduit de liaison (18), l'amortisseur de Helmholtz (17) étant réalisé de telle sorte que sa fréquence d'amortissement puisse être réglée, et le volume d'amortissement (20, 21) étant divisé en un volume d'amortissement fixe (20) et un volume d'amortissement variable (21), le volume d'amortissement fixe (20) étant choisi de telle sorte que la fréquence d'amortissement pouvant être ainsi obtenue se situe à proximité de la fréquence de l'une des vibrations thermoacoustiques auxquelles l'on peut s'attendre dans la chambre de combustion (16), et que le volume d'amortissement (20, 21) puisse être modifié par la modification du volume d'amortissement variable (21), caractérisée en ce que le volume d'amortissement variable (21) est limité d'un côté par un piston (22) pouvant être déplacé, en ce qu'un élément de réglage (23) est disposé sur l'amortisseur de Helmholtz (17), au moyen duquel élément de réglage le piston (22) peut être déplacé, et en ce que la chambre de combustion (16) est disposée à l'intérieur d'un carter de turbine (11) et l'élément de réglage (23) peut être actionné à travers une ouverture d'accès (19) pouvant être fermée dans le carter de turbine (11).
  2. Chambre de combustion selon la revendication 1, caractérisée en ce que la fréquence d'amortissement de l'amortisseur de Helmholtz (17) peut être réglée en continu.
  3. Chambre de combustion selon la revendication 2, caractérisée en ce que le volume d'amortissement (20, 21) de l'amortisseur de Helmholtz (17) peut être modifié en continu.
  4. Chambre de combustion selon la revendication 1, caractérisée en ce que l'élément de réglage (23) est réalisé sous la forme d'une tige filetée.
  5. Chambre de combustion selon l'une quelconque des revendications 1 à 4, caractérisée en ce que la chambre de combustion (16) présente, sur son côté d'entrée (26), une pluralité de brûleurs (14, 15) qui débouchent dans la chambre de combustion (16), et en ce que l'au moins un amortisseur de Helmholtz (17) est disposé sur le côté d'entrée (26) à proximité immédiate des brûleurs (14, 15).
  6. Chambre de combustion selon la revendication 5, caractérisée en ce que la chambre de combustion (16) est annulaire, en ce que les brûleurs (14, 15) sont disposés sur des cercles concentriques et en ce que l'au moins un amortisseur de Helmholtz (17) est disposé entre les cercles.
EP02782607.2A 2002-01-16 2002-12-16 Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz Expired - Fee Related EP1476699B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH672002 2002-01-16
CH67022002 2002-01-16
PCT/CH2002/000696 WO2003060381A1 (fr) 2002-01-16 2002-12-16 Chambre de combustion et dispositif d'amortissement destine a reduire des pulsations de chambre de combustion dans un systeme de turbines a gaz

Publications (2)

Publication Number Publication Date
EP1476699A1 EP1476699A1 (fr) 2004-11-17
EP1476699B1 true EP1476699B1 (fr) 2013-11-13

Family

ID=4313973

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02782607.2A Expired - Fee Related EP1476699B1 (fr) 2002-01-16 2002-12-16 Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz

Country Status (5)

Country Link
US (1) US7331182B2 (fr)
EP (1) EP1476699B1 (fr)
CN (1) CN100523615C (fr)
AU (1) AU2002347185A1 (fr)
WO (1) WO2003060381A1 (fr)

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1596130B1 (fr) 2004-05-14 2014-12-31 Siemens Aktiengesellschaft Appareil pour absorber les oscillations thermo-acoustiques dans une chambre de combustion, présentant une fréquence de résonance variable
DE102005035085B4 (de) * 2005-07-20 2014-01-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Einstellung der akustischen Eigenschaften einer Brennkammer
FR2901578B1 (fr) * 2006-05-23 2008-07-25 Snecma Sa Corps central pour canal d'echappement d'un turboreacteur, turboreacteur
GB0610800D0 (en) * 2006-06-01 2006-07-12 Rolls Royce Plc Combustion chamber for a gas turbine engine
GB2443838B (en) * 2006-11-16 2009-01-28 Rolls Royce Plc Combustion control for a gas turbine
GB0708459D0 (en) * 2007-05-02 2007-06-06 Rolls Royce Plc A temperature controlling arrangement
US8127546B2 (en) * 2007-05-31 2012-03-06 Solar Turbines Inc. Turbine engine fuel injector with helmholtz resonators
JP4981615B2 (ja) * 2007-10-19 2012-07-25 三菱重工業株式会社 ガスタービン
CH700799A1 (de) * 2009-04-11 2010-10-15 Alstom Technology Ltd Brennkammer mit Helmholtzdämpfer für eine Gasturbine.
US8789372B2 (en) * 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator
RU2508506C2 (ru) * 2009-09-01 2014-02-27 Дженерал Электрик Компани Способ и установка для ввода текучей среды в камеру сгорания газотурбинного двигателя
CH702594A1 (de) 2010-01-28 2011-07-29 Alstom Technology Ltd Helmholtzdämpfer für den Einbau in die Brennkammer einer Gasturbine sowie Verfahren zum Einbau eines solchen Helmholtzdämpfers.
EP2397760B1 (fr) 2010-06-16 2020-11-18 Ansaldo Energia IP UK Limited Agencement d'amortisseur et procédé pour le concevoir
EP2397761B1 (fr) 2010-06-16 2021-10-06 Ansaldo Energia Switzerland AG Amortisseur de Helmholtz
US8973365B2 (en) 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators
US20140311156A1 (en) * 2011-09-22 2014-10-23 General Electric Company Combustor cap for damping low frequency dynamics
US9188340B2 (en) * 2011-11-18 2015-11-17 General Electric Company Gas turbine combustor endcover with adjustable flow restrictor and related method
EP2642204A1 (fr) * 2012-03-21 2013-09-25 Alstom Technology Ltd Amortissement à large bande simultanée à de multiples emplacements dans une chambre de combustion
RU2561956C2 (ru) * 2012-07-09 2015-09-10 Альстом Текнолоджи Лтд Газотурбинная система сгорания
ITMI20122265A1 (it) * 2012-12-28 2014-06-29 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas provvisto di risonatore di helmholtz
US20140216038A1 (en) * 2013-02-06 2014-08-07 General Electric Company Variable Volume Combustor with Cantilevered Support Structure
CN105008805A (zh) * 2013-02-28 2015-10-28 西门子公司 用于燃气轮机的减振设备、燃气轮机和用于衰减热声振动的方法
US9400108B2 (en) 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
EP2816289B1 (fr) 2013-05-24 2020-10-07 Ansaldo Energia IP UK Limited Amortisseur pour turbines à gaz
US9709279B2 (en) 2014-02-27 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9709278B2 (en) 2014-03-12 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9644846B2 (en) * 2014-04-08 2017-05-09 General Electric Company Systems and methods for control of combustion dynamics and modal coupling in gas turbine engine
US9845956B2 (en) 2014-04-09 2017-12-19 General Electric Company System and method for control of combustion dynamics in combustion system
US9845732B2 (en) 2014-05-28 2017-12-19 General Electric Company Systems and methods for variation of injectors for coherence reduction in combustion system
US10113747B2 (en) 2015-04-15 2018-10-30 General Electric Company Systems and methods for control of combustion dynamics in combustion system
US10221769B2 (en) * 2016-12-02 2019-03-05 General Electric Company System and apparatus for gas turbine combustor inner cap and extended resonating tubes
US10228138B2 (en) * 2016-12-02 2019-03-12 General Electric Company System and apparatus for gas turbine combustor inner cap and resonating tubes
US11260641B2 (en) 2019-05-10 2022-03-01 American Honda Motor Co., Inc. Apparatus for reticulation of adhesive and methods of use thereof
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1357501A (en) * 1917-08-15 1920-11-02 Henry E Elrod Company Power-generating unit for locomotive-headlights
US3275015A (en) * 1963-10-29 1966-09-27 Ibm Tuning fork oscillator
JPS5114550A (ja) * 1974-07-27 1976-02-05 Tokico Ltd Shoonki
JPS5551910A (en) * 1978-10-13 1980-04-16 Nippon Radiator Co Ltd Active muffler
GB2253076B (en) 1991-02-21 1994-08-03 Lotus Car Method and apparatus for attenuating acoustic vibrations in a medium
JPH07501137A (ja) 1991-11-15 1995-02-02 シーメンス アクチエンゲゼルシヤフト ガスタービン設備の燃焼室内の燃焼振動抑制装置
DE59208715D1 (de) 1992-11-09 1997-08-21 Asea Brown Boveri Gasturbinen-Brennkammer
DE19833326A1 (de) * 1998-07-24 2000-01-27 Opel Adam Ag Ansaugvorrichtung für eine Brennkraftmaschine
EP0985882B1 (fr) 1998-09-10 2003-12-03 ALSTOM (Switzerland) Ltd Amortissement des vibrations dans des combusteurs
DE10026121A1 (de) * 2000-05-26 2001-11-29 Alstom Power Nv Vorrichtung zur Dämpfung akustischer Schwingungen in einer Brennkammer
DE10058688B4 (de) 2000-11-25 2011-08-11 Alstom Technology Ltd. Dämpferanordnung zur Reduktion von Brennkammerpulsationen

Also Published As

Publication number Publication date
US7331182B2 (en) 2008-02-19
AU2002347185A1 (en) 2003-07-30
CN1615416A (zh) 2005-05-11
CN100523615C (zh) 2009-08-05
EP1476699A1 (fr) 2004-11-17
WO2003060381A1 (fr) 2003-07-24
US20050103018A1 (en) 2005-05-19

Similar Documents

Publication Publication Date Title
EP1476699B1 (fr) Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz
DE102005062284B4 (de) Brennkammer für eine Gasturbine
DE10058688B4 (de) Dämpferanordnung zur Reduktion von Brennkammerpulsationen
EP2354659A1 (fr) Amortisseur de Helmholtz pour l'intégration dans la chambre de combustion d'une turbine à gaz et procédé d'intégration d'un tel amortisseur de Helmholtz
DE2404001C2 (de) Schallunterdrückungsverkleidung für Strömungskanäle von Gasturbinentriebwerken
EP1158247B1 (fr) Dispositif pour la réduction des vibrations accoustiques dans une chambre de combustion
EP1423645B1 (fr) Ensemble amortisseur concu pour reduire les pulsations d'une chambre de combustion dans une installation de turbine a gaz
WO2010018069A1 (fr) Procédé pour régler un résonateur de helmholtz et résonateur de helmholtz destiné à mettre en œuvre le procédé
EP1738112B1 (fr) Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs
EP1004823A2 (fr) Dispositif d'amortissement pour la réduction de l'amplitude d'oscillation d'ondes acoustiques pour un brûleur
DE19640980B4 (de) Vorrichtung zur Dämpfung von thermoakustischen Schwingungen in einer Brennkammer
DE102004001985A1 (de) Variabel abgestimmter Teleskop-Resonator
EP2417394B1 (fr) Chambre de combustion dotée d'un amortisseur de helmholtz
EP0892217B1 (fr) Dispositif d'atténuation des vibrations d'une chambre de combustion
EP3117148B1 (fr) Système de combustion avec résonateur
DE102004041272B4 (de) Hybridbrennerlanze
EP0990851B1 (fr) Chambre de combustion pour une turbine à gaz
EP1605209A1 (fr) Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques
EP0974788B1 (fr) Dispositif d'atténuation adaptée de bruit dans une turbomachine
DE102009006431A1 (de) Austragvorrichtung
EP1010939B1 (fr) Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement
EP1078615B1 (fr) Dispositif de protection auditive
EP1596130B1 (fr) Appareil pour absorber les oscillations thermo-acoustiques dans une chambre de combustion, présentant une fréquence de résonance variable
EP0657693A2 (fr) Brûleur à gaz
DE4304201A1 (de) Brennkammer für eine Gasturbine

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: 20040707

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 IE IT LI LU MC NL PT SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO

17Q First examination report despatched

Effective date: 20070724

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 50215854

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F23M0013000000

Ipc: F23R0003000000

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: F23R 3/00 20060101AFI20130527BHEP

Ipc: F23M 99/00 20100101ALI20130527BHEP

INTG Intention to grant announced

Effective date: 20130614

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): DE GB

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: DE

Ref legal event code: R081

Ref document number: 50215854

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 50215854

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 50215854

Country of ref document: DE

Effective date: 20140109

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 50215854

Country of ref document: DE

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: 20140814

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 50215854

Country of ref document: DE

Effective date: 20140814

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 50215854

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 50215854

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

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

Ref country code: DE

Payment date: 20161213

Year of fee payment: 15

Ref country code: GB

Payment date: 20161222

Year of fee payment: 15

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 50215854

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20170824 AND 20170830

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50215854

Country of ref document: DE

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

Effective date: 20171216

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: 20180703

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: 20171216