EP1010939B1 - Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement - Google Patents

Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement Download PDF

Info

Publication number
EP1010939B1
EP1010939B1 EP98811230A EP98811230A EP1010939B1 EP 1010939 B1 EP1010939 B1 EP 1010939B1 EP 98811230 A EP98811230 A EP 98811230A EP 98811230 A EP98811230 A EP 98811230A EP 1010939 B1 EP1010939 B1 EP 1010939B1
Authority
EP
European Patent Office
Prior art keywords
fuel
volume
fuel supply
supply system
burner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP98811230A
Other languages
German (de)
English (en)
Other versions
EP1010939A1 (fr
Inventor
Jakob Prof. Dr. Keller
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 Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Priority to EP98811230A priority Critical patent/EP1010939B1/fr
Priority to DE59810760T priority patent/DE59810760D1/de
Priority to US09/458,095 priority patent/US6305927B1/en
Publication of EP1010939A1 publication Critical patent/EP1010939A1/fr
Application granted granted Critical
Publication of EP1010939B1 publication Critical patent/EP1010939B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to the field of burners, in particular the burner for use in gas turbines. It concerns a burner with a fuel supply system, in which the fuel supply system is fuel transported to the burner, the fuel in the burner into a combustion chamber is injected where the fuel is burned.
  • Burners of gas turbines serve the fuel and the combustion air in a controlled manner and controllably inject into a combustion chamber and there to burn the fuel.
  • the burners can be used in many different ways Arrangement in the wall of the combustion chamber, and will be charged with fuel by means of a fuel supply system.
  • the injection The fuel in the burner must be in order to optimally control the combustion process in the various operating states of the turbine ensure controllable and done in the best possible way.
  • More and more strict regulations regarding emissions of combustion processes make a highly specialized and complicated injection and mixing of combustion air and fuel in the Burner essential.
  • EP-B1-0 321 809 describes a so-called double-cone burner become known for liquid and gaseous fuels without a premix section, in which combustion air supplied from the outside through at least two inlet slots tangentially between displaced, hollow half-cones enters and flows there towards the combustion chamber, and in which on the Combustion chamber facing away, tapered side of the half-cones fuel centrally or from distribution channels that run along the air inlet slots Rows of holes are injected transversely into the incoming air.
  • acoustic oscillations which also under the term "singing flame” are known. These are mostly oscillations, which from the interaction of inflows of the combustion mixture and the actual combustion process in the combustion chamber.
  • These largely coherently periodic pressure fluctuations can, for example with a burner of the type mentioned above under typical operating conditions to acoustic vibrations with frequencies of about 80 to 100 Hz to lead. Since these frequencies have typical fundamental eigenmodes of Combustion chambers of gas turbines can collapse, make them thermoacoustic Oscillations are a problem.
  • WO93 / 10401 is a device for suppressing combustion vibrations known in a combustion chamber of a gas turbine plant.
  • Fuel supply lines of the burner acoustically effective elements such as Helmholtz resonators or resonance pipes arranged.
  • the invention is therefore based on the object, a burner with at least a fuel supply system through which a fuel flow to the burner is supplied, the supplied fuel is injected via fuel nozzles, and then burned in a combustion chamber provide who is able to train and reinforce periodic To prevent pressure fluctuations in the combustion chamber at least partially.
  • a first preferred embodiment of the invention is characterized in that that the means at least a first, immediately upstream of the fuel nozzles arranged volume comprise, through which volume the fuel flow flows, and that this first volume is upstream over a first Narrowing with the fuel delivery system located further upstream communicates.
  • This first volume is essentially preferred chosen smaller than a certain critical volume, and especially continues the cross-sectional area of the first constriction is smaller than a certain critical Cross-sectional area formed.
  • Another embodiment of the invention is characterized in that a second volume is arranged upstream of the first constriction which the fuel stream flows, and that this second volume upstream via a second constriction with the one located further upstream Fuel supply system is connected.
  • This arrangement allows the effective prevention of the coupling under special, essentially unchangeable Design specifications of the burner and the fuel supply system.
  • the fuel supply system can be viewed acoustically, as shown in FIG. 1, as a throttle, that is to say as an opening 10 with a negligible length and cross-sectional area A F , through which fuel the density ⁇ F from a large volume at pressure p F into another large one Volume, the combustion chamber 11, flows at pressure p l . It is assumed that the following applies: p F > p l . In addition, it is assumed that the fuel supply volume has a constant pressure p F , while the pressure in the injection space p l can be subject to fluctuations.
  • the pressure fluctuations in the injection space therefore have a directly linear effect to fluctuations in fuel injection speed 12 and vice versa, i.e. there is a direct coupling of the two sizes.
  • ⁇ 1 the critical fuel injection velocity u FC here compared to simple injection systems at least to the value
  • the use of check valves with a second, upstream opening of variable cross-sectional area In this case, the pressure drop across the fuel supply system can be kept to a minimum even for very low fuel injection speeds.
  • a fuel nozzle of cross-sectional area AF with an upstream fuel supply line of length L and cross-sectional area AT forms an acoustic coupling of the shape leads, where c F represents the speed of sound in the fuel gas.
  • FIG. 3 schematically shows a burner of the applicant's type EV17i, such as that installed in a applicant's type GT26 gas turbine.
  • the fuel is supplied to the burner 14 via a fuel supply line 15.
  • the line 15 initially opens into an annular distribution chamber 16, from which fuel distribution channels run along the conical outer surface of the double-cone burner.
  • These distribution channels have, on the side facing the burner, a plurality of fuel nozzles 10 through which the fuel can flow into the burner and thus into the combustion chamber 11.
  • the diameter of the fuel feed 15 is approximately 38 mm, although according to the above criterion it should not be more than 21 mm.
  • a simple way of acoustically hardening the specified structure is the introduction of a Helmholtz volume with a suitable cross-sectional area A and length l between the fuel supply line 15 and the fuel nozzles 10, as is shown schematically in FIG. 2b). It is of great advantage to set the dimensioning of the volume and the constriction in such a way that at least one resonance of the fuel supply system coincides with the most important fundamental acoustic natural frequency of the combustion chamber.
  • the response function a ( ⁇ ) can be calculated.
  • Size unit value print bar 18 Nozzle cross-sectional area m 2 0.000111 Temperature of methane K 323 Mass flow of methane kg / s 0167 Length of the line m 2 Diameter of the pipe m 0038 Length of the first volume m 0.1 Cross-sectional area of the first volume m 2 6.5e-3
  • the damping factor a ( ⁇ ) (attenuation factor) as a function of the frequency of the pressure fluctuations under consideration for the conditions listed in Table 1 is shown in FIG.
  • FIG. 4 shows that the damping occurs only in narrow areas around the resonance frequencies of the fuel supply system. It can also be clearly seen from FIG.
  • the fuel supply system behaves like a simple and almost completely undamped throttle, and thus the resonance behavior of the fuel supply system does not at all match that of the combustion chamber is coordinated.
  • a line constriction 17 as also shown in FIG. 3, is now introduced into the fuel supply line 15, the resonance frequency of the fuel supply system shifts and widens in the range from 90 to 100 Hz and the minimum value of a at this frequency is approximately 0.35-0.4.
  • This is done by simply using an insert 17 (or a constriction in the line caused in another way) of 300 mm in length and an inside diameter of 21 mm.
  • a further improvement can be achieved with the values given in table 2 by increasing the length of the insert 17 from 300 mm to 500 mm and additionally reducing the first volume from 650 cm 3 to 400 cm 3 .
  • the resulting absorption profile is shown in FIG. 6, it shows in the resonance range from 90 to 100Hz an absorption of remarkable 90% in Compared to the simple throttle.
  • the acoustic hardening of a burner of the type EV18 from the applicant, as it is installed in a gas turbine of the type GT26, is to serve as a further exemplary embodiment.
  • the fuel is fed to the burner 14 via annular fuel distribution lines 18, which jointly supply the burners arranged in a ring in the annular combustion chamber of the turbine.
  • the fuel branches off from the annular fuel distribution line 18 via a second constriction 19 and enters a volume which is normally formed by the volumes 20 and 22 without the partition wall 23 shown in FIG. 8 and the first constriction 21.
  • the fuel is guided through the fuel distribution channels 22 along the cone of the burner 14 and passes through the fuel nozzles 10 into the combustion chamber 11, where it is mixed with combustion air.
  • the easiest way to do this is to arrange two volumes upstream of the fuel nozzle 10 and connected to the fuel supply line via two constrictions, as is shown schematically in FIG.
  • a possible technical implementation is shown in Figure 8.
  • a partition 23 separates the large volume into the fuel distribution channels 22 and a second volume 20, and a constriction 21 which is wound around the burner and is designed as a line connects the two volumes.
  • the absorption characteristic in FIG. 9 is obtained.
  • Size unit value print bar 18 Nozzle cross-sectional area m 2 9.08e-5 Temperature of methane K 323 Mass flow of methane kg / s 0133 Length of the second narrowing m 00:04 Cross-sectional area of the second constriction m 2 0.000314 Second volume m 3 0.0015 Length of the first narrowing m 1.2 Cross-sectional area of the first constriction m 2 0.000314 First volume m 3 0.00015
  • this arrangement and dimensioning are used a perfect damping of the two volumes connected in series acoustic coupling with the natural frequency of the combustion chamber of approx. 90 Hz a considerable width of the resonance condition, with a deviation of approx. ⁇ 30Hz namely 2/3 are still absorbed by the resonance condition.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Claims (10)

  1. Brûleur (14) d'une chambre de combustion avec au moins un système d'alimentation en combustible (15, 16, 18, 20, 22) par lequel un flux de combustible (12) peut être introduit dans le brûleur (14) et qui est relié avec des buses d'injection de combustible (10) disposées dans le brûleur (14), au moins un volume de Helmholtz (16, 22) disposé juste en amont des buses d'injection de combustible (10) étant prévu, volume (16, 22) à travers lequel le combustible s'écoule, ce qui empêche que des fluctuations de pression périodiques apparaissant dans la chambre de combustion n'entraínent des fluctuations du flux de combustible (12) dans le système d'alimentation en combustible (15, 16, 18, 20, 22) et que ce premier volume de Helmholtz (16, 22) ne se trouve en connexion en amont, via un premier étranglement (17, 21), avec le système d'alimentation en combustible (15, 18, 20) disposé plus loin en amont, caractérisé en ce que le premier étranglement (17) est constitué d'un insert de forme tubulaire dans une conduite d'amenée de combustible (15) disposée en amont du premier volume de Helmholtz (16) ou d'un tronçon de conduite rétrécie entre la conduite d'amenée de combustible (15) et le premier volume de Helmholtz (16).
  2. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon la revendication 1, caractérisé en ce que les fluctuations de pression périodiques apparaissant dans la chambre de combustion (11) sont des oscillations acoustiques et en ce que celles-ci se situent dans la plage des oscillations propres acoustiques de la chambre de combustion (11).
  3. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon la revendication 2, caractérisé en ce que les fluctuations du flux de combustible (12) dans le système d'alimentation en combustible (15,16,18,20,22) sont périodiques et en ce qu'en particulier, la fréquence de ces fluctuations périodiques du flux de combustible (12) se situe dans la plage des oscillations propres acoustiques de la chambre de combustion (11).
  4. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon l'une quelconque des revendications 1 à 3, caractérisé en ce que le premier volume de Helmholtz (16, 22) est inférieur à un volume critique (Vcrit) et en ce que le volume critique (Vcrit) est donné approximativement par le quotient du produit de la surface de la section transversale (AF) de l'ouverture de la buse d'injection de combustible (10) et du carré de la vitesse du son (cF) dans le premier volume (16,22) par le produit de la fréquence angulaire (w) de l'oscillation acoustique et de la vitesse d'écoulement (uF) du flux de combustible (12).
  5. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon l'une quelconque des revendications 1 à 4, caractérisé en ce que le premier étranglement (17,21) présente une surface de section transversale (AT), laquelle est essentiellement inférieure ou égale au produit de la surface de la section transversale (AF) de la buse d'injection de combustible (10) et de l'inverse du nombre de Mach (1/M=cF/uF).
  6. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon l'une quelconque des revendications 1 à 5, caractérisé en ce que les dimensionnements du premier volume de Helmholtz (16,22) et du premier étranglement (17,21) sont choisis de telle manière qu'une résonance de l'absorption du système d'alimentation en combustible se situe essentiellement dans la plage des modes propres de la chambre de combustion (11) .
  7. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon l'une quelconque des revendications 1 à 6, caractérisé en ce que le premier volume de Helmholtz (16) est formé par un espace de distribution annulaire et par des canaux de distribution situés en aval de celui-ci et s'étendant au moins partiellement à l'extérieur du brûleur (14) et en ce que le combustible s'écoule dans la chambre de combustion (11) via les buses d'injection de combustible (10) à partir des canaux de distribution.
  8. Brûleur (14) avec un système d'alimentation en combustible (18,20,22) selon l'une quelconque des revendications 1 à 6, caractérisé en ce qu'en amont du premier étranglement (21), on a disposé un deuxième volume de Helmholtz (20) à travers lequel le flux de combustible (12) s'écoule et en ce que ce deuxième volume (20) est en connexion en amont via un deuxième étranglement (19) avec le système d'alimentation en combustible (18) situé plus loin en amont.
  9. Brûleur (14) avec un système d'alimentation en combustible (15,16,18,20,22) selon la revendication 8, caractérisé en ce que les dimensionnements du premier volume de Helmholtz (22) et du deuxième volume de Helmholtz (20) ainsi que ceux du premier étranglement (21) et du deuxième étranglement (19) sont choisis de telle manière qu'une résonance de l'absorption du système d'alimentation en combustible se situe essentiellement dans la plage des modes propres de la chambre de combustion (11).
  10. Brûleur (14) avec un système d'alimentation en combustible (18,20,22) selon l'une quelconque des revendications 8 ou 9, caractérisé en ce que le premier étranglement (21) est constitué en tant que conduite de section transversale réduite, laquelle relie le premier volume de Helmholtz (22) au deuxième volume de Helmholtz (20) séparé du premier volume de Helmholtz (22) par une paroi de séparation (23).
EP98811230A 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement Expired - Lifetime EP1010939B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP98811230A EP1010939B1 (fr) 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement
DE59810760T DE59810760D1 (de) 1998-12-15 1998-12-15 Brennkammer mit akustisch gedämpftem Brennstoffversorgungssystem
US09/458,095 US6305927B1 (en) 1998-12-15 1999-12-10 Burner with acoustically damped fuel supply system

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811230A EP1010939B1 (fr) 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement

Publications (2)

Publication Number Publication Date
EP1010939A1 EP1010939A1 (fr) 2000-06-21
EP1010939B1 true EP1010939B1 (fr) 2004-02-11

Family

ID=8236485

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98811230A Expired - Lifetime EP1010939B1 (fr) 1998-12-15 1998-12-15 Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement

Country Status (3)

Country Link
US (1) US6305927B1 (fr)
EP (1) EP1010939B1 (fr)
DE (1) DE59810760D1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1342952A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement d'un brûleur et turbine à gaz
EP1342953A1 (fr) * 2002-03-07 2003-09-10 Siemens Aktiengesellschaft Turbine à gaz
US6820431B2 (en) * 2002-10-31 2004-11-23 General Electric Company Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly
WO2004051063A1 (fr) * 2002-12-02 2004-06-17 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine a gaz et turbine a gaz equipee de cette chambre de combustion
US8028512B2 (en) 2007-11-28 2011-10-04 Solar Turbines Inc. Active combustion control for a turbine engine
JP5357631B2 (ja) * 2009-06-09 2013-12-04 三菱重工業株式会社 燃料ノズル、これを備えた燃焼器及びガスタービン
US8474265B2 (en) 2009-07-29 2013-07-02 General Electric Company Fuel nozzle for a turbine combustor, and methods of forming same
US8322140B2 (en) * 2010-01-04 2012-12-04 General Electric Company Fuel system acoustic feature to mitigate combustion dynamics for multi-nozzle dry low NOx combustion system and method
EP2397760B1 (fr) 2010-06-16 2020-11-18 Ansaldo Energia IP UK Limited Agencement d'amortisseur et procédé pour le concevoir
US9127837B2 (en) * 2010-06-22 2015-09-08 Carrier Corporation Low pressure drop, low NOx, induced draft gas heaters
US9188340B2 (en) * 2011-11-18 2015-11-17 General Electric Company Gas turbine combustor endcover with adjustable flow restrictor and related method
US9400108B2 (en) 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
DE102019110258A1 (de) 2019-04-15 2020-10-15 Deutsches Zentrum für Luft- und Raumfahrt e.V. Injektorvorrichtung für eine Triebwerksvorrichtung, Triebwerksvorrichtung und Luft- und/oder Raumfahrzeug

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1702731A (en) * 1929-02-19 Method of and apparatus for combustion otf
US804002A (en) * 1903-10-10 1905-11-07 Eugene Alfred Javal Gas-blowpipe.
US2765004A (en) * 1953-07-21 1956-10-02 Harold W Williams Dropper assembly
US2943641A (en) * 1956-01-30 1960-07-05 Richfield Oil Corp Device for attenuating pulsative flow in gases
US3807527A (en) * 1973-03-14 1974-04-30 Tenneco Inc Pulse converter for exhaust system
US4464314A (en) * 1980-01-02 1984-08-07 Surovikin Vitaly F Aerodynamic apparatus for mixing components of a fuel mixture
JPS57108512A (en) * 1980-12-26 1982-07-06 Babcock Hitachi Kk Gas burner
US4760695A (en) * 1986-08-28 1988-08-02 United Technologies Corporation Acoustic oscillatory pressure control for ramjet
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
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
US5349813A (en) * 1992-11-09 1994-09-27 Foster Wheeler Energy Corporation Vibration of systems comprised of hot and cold components
US5494438A (en) * 1994-02-08 1996-02-27 National Science Council Sudden expansion combustion chamber with slotted inlet port
IT1278601B1 (it) * 1994-07-05 1997-11-24 Necchi Compressori Silenziatore per motocompressore, per apparati frigoriferi
DE19504610C2 (de) * 1995-02-13 2003-06-18 Alstom Vorrichtung zur Dämpfung thermoakustischer Druckschwingungen
DE19542918A1 (de) * 1995-11-17 1997-05-22 Asea Brown Boveri Vorrichtung zur Dämpfung thermoakustischer Druckschwingungen
US6058709A (en) * 1996-11-06 2000-05-09 The United States Of America Represented By The United States Department Of Energy Dynamically balanced fuel nozzle and method of operation
DE19649486A1 (de) * 1996-11-29 1998-06-04 Abb Research Ltd Brennkammer

Also Published As

Publication number Publication date
EP1010939A1 (fr) 2000-06-21
DE59810760D1 (de) 2004-03-18
US6305927B1 (en) 2001-10-23

Similar Documents

Publication Publication Date Title
DE60007946T2 (de) Eine Brennkammer
EP1010939B1 (fr) Chambre de combustion avec système d'alimentation en carburant amorti acoustiquement
DE10205839B4 (de) Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
EP0985882B1 (fr) Amortissement des vibrations dans des combusteurs
EP0571782B1 (fr) Procédé de fonctionnement d'une chambre de combustion pour turbine à gaz
DE69308383T2 (de) Verfahren und Vorrichtung zum Verhindern der Konzentrierungschwingungen von Luft-Kraftstoff in einer Brennkammer
EP1864056B1 (fr) Bruleur de premelange destine a une chambre de combustion de turbine a gaz
EP2318672A1 (fr) Procédé pour régler un résonateur de helmholtz et résonateur de helmholtz destiné à mettre en oeuvre le procédé
EP1738112B1 (fr) Moteur de fusée avec amortissement de vibrations de la chambre de combustion au moyen de resonateurs
EP1199516A1 (fr) Brûleur
EP1730447A1 (fr) Brûleur
EP1828684A1 (fr) Bruleur de premelange dote d'un parcours de melange
DE19948674B4 (de) Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen
EP0687860A2 (fr) Chambre de combustion à allumage automatique
EP0576717A1 (fr) Chambre de combustion de turbine à gaz
EP0592717A1 (fr) Brûleur opérant au gaz du type à prémélange
WO2005121649A2 (fr) Injecteur pour carburant liquide et bruleur a premelange etage pourvu dudit injecteur
EP0719983A1 (fr) Procédé et dispositif d'alimentation du combustible gazeuse vers un brûleur à prémélange
EP0971172B1 (fr) Chambre de combustion pour turbine à gaz avec paroi à structure silencieuse
EP1463911B1 (fr) Bruleur presentant une injection de combustible etagee
EP0481111A1 (fr) Chambre de combustion pour turbine à gaz
DE19939235B4 (de) Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
EP0974788A1 (fr) Dispositif d'atténuation adaptée de bruit dans une turbomachine
EP0742411B1 (fr) Alimentation en air pour une chambre de combustion à prémélange
EP1001214B1 (fr) Brûleur

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

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20001027

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

Owner name: ALSTOM POWER (SCHWEIZ) AG

AKX Designation fees paid

Free format text: DE FR GB

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

Owner name: ALSTOM

17Q First examination report despatched

Effective date: 20020325

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

Owner name: ALSTOM (SWITZERLAND) LTD

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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 FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 59810760

Country of ref document: DE

Date of ref document: 20040318

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20040520

ET Fr: translation filed
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: 20041112

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810760

Country of ref document: DE

Representative=s name: UWE ROESLER, DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120802 AND 20120808

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810760

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810760

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810760

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810760

Country of ref document: DE

Owner name: ALSTOM TECHNOLOGY LTD., CH

Free format text: FORMER OWNER: ALSTOM (SWITZERLAND) LTD., BADEN, CH

Effective date: 20120713

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Owner name: ALSTOM TECHNOLOGY LTD., CH

Effective date: 20120918

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810760

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810760

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

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

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810760

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

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

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: ALSTOM TECHNOLOGY LTD, CH

Effective date: 20161110

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 19

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

Ref country code: GB

Payment date: 20161222

Year of fee payment: 19

Ref country code: DE

Payment date: 20161213

Year of fee payment: 19

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

Ref country code: FR

Payment date: 20161222

Year of fee payment: 19

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 59810760

Country of ref document: DE

Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 59810760

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: FR

Ref legal event code: TP

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Effective date: 20171221

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 59810760

Country of ref document: DE

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

Effective date: 20171215

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180831

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

Ref country code: FR

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

Effective date: 20180102

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: 20171215