EP2462379A1 - Stabilisation de la flamme d'un brûleur - Google Patents

Stabilisation de la flamme d'un brûleur

Info

Publication number
EP2462379A1
EP2462379A1 EP10740607A EP10740607A EP2462379A1 EP 2462379 A1 EP2462379 A1 EP 2462379A1 EP 10740607 A EP10740607 A EP 10740607A EP 10740607 A EP10740607 A EP 10740607A EP 2462379 A1 EP2462379 A1 EP 2462379A1
Authority
EP
European Patent Office
Prior art keywords
fluid
jet
burner
burner according
nozzle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10740607A
Other languages
German (de)
English (en)
Other versions
EP2462379B1 (fr
Inventor
Matthias Hase
Werner Krebs
Bernd Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP10740607.6A priority Critical patent/EP2462379B1/fr
Publication of EP2462379A1 publication Critical patent/EP2462379A1/fr
Application granted granted Critical
Publication of EP2462379B1 publication Critical patent/EP2462379B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/06—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber for completing combustion
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23D14/48—Nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/10—Premixing fluegas with fuel and combustion air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2202/00—Fluegas recirculation
    • F23C2202/20—Premixing fluegas with fuel
    • 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
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the present invention relates to a burner for stabilizing the flame of a gas turbine, which comprises a reaction space and several opening into the reaction chamber jet nozzles, wherein the jet nozzles by means of a fluid jet fluid is injected into the reaction space, wherein the fluid in the reaction space to Hot gas is burned, and a method for stabilizing the flame of a burner of a gas turbine.
  • Combustion-based combustion systems offer advantages over spin-stabilized systems due to the distributed heat release zones and the absence of spin-induced vortices, in particular from a thermoacoustic point of view.
  • By a suitable choice of the beam pulse small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus suppress pressure pulsations that are typical for spin-stabilized flames.
  • the jet flames are stabilized by mixing in hot recirculating gases.
  • the required temperatures of the recirculation zone can not be guaranteed in gas turbines, especially in the lower part load range, by the known ring arrangement of the beams with a central recirculation zone.
  • the stabilization of a jet flame therefore remains an incompletely solved task. It is therefore the object of the present invention to provide an advantageous burner of a gas turbine for stabilizing the flame of such a burner. Another object of the present invention is to provide a To provide some method for stabilizing the flame of such a burner.
  • the torch-related object is achieved by a burner for stabilizing the flame of a burner of a gas turbine according to claim 1.
  • the object related to the method is achieved by specifying a method according to claim 16.
  • the dependent claims contain further, advantageous embodiments of the invention.
  • the burner according to the invention of a gas turbine comprises a reaction space and a plurality of jet nozzles opening into the reaction space.
  • the jet nozzles With the jet nozzles, fluid is injected into the reaction space by means of a fluid jet. The fluid in the reaction space is then burned to hot gas.
  • the invention has recognized that the jet flame based combustion systems are stabilized by mixing in hot recirculating gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction.
  • At least one jet nozzle now has an annular gap which is arranged around the fluid jet. This sucks a portion of the hot gas from the reaction space, so that it flows against the fluid flow direction in the annular gap. According to the invention, the hot gas is now mixed with the fluid jet within the jet nozzle.
  • the annular gap is formed by means of an insert tube.
  • the sucked gases can have a high temperature, which can damage the burner under certain circumstances.
  • the insert tube is at least partially made of high-grade materials with and without coating, e.g. designed as a ceramic version with and without coating.
  • the insert tube has at least one opening in order to inject the hot gas into the fluid jet.
  • the at least one opening is arranged upstream.
  • the hot gas is sucked through the annular gap directly into the nozzle and is injected through the openings in the fluid jet.
  • the openings are therefore mounted in the directly limiting the fluid jet wall.
  • the size of the openings and the height of the annular gap are designed so that a good hot gas mixing in the air or the air / fuel mixture is ensured in the jet nozzle and that in the partial load range, the mixture temperature is brought to a value that ensures reliable ignition ,
  • the openings can be designed as bores or slots, which can also be set at an angle.
  • the insert tube at the upstream end to a thickening. If compressor air, with or without fuel, passes the feed tube past the nozzle to the nozzle, deflection losses can thus be avoided.
  • the thickening is diffused in the flow direction.
  • the insert tube is preferably designed to be diffused in the flow direction in the flow direction.
  • an increase of the static pressure difference between the combustion chamber and the fluid flowing in the nozzle at high speed can also be effected.
  • a second annular channel for guiding combustion air and / or fuel is provided around the insert tube.
  • means for increasing the heat transfer are provided in the second annular channel.
  • these agents are dimples and / or cooling fins and / or wings.
  • all other cooling concepts such as impingement cooling, convective cooling are also conceivable in which the compressor air or the compressor / fuel mixture is added to the reaction space.
  • the cooling air flowing through the second annular channel and / or fuel cools the insert tube thus fluid downstream.
  • the jet nozzle has a nozzle outlet with a diameter D.
  • the nozzle outlet is offset from the annular gap in the flow direction.
  • the offset comprises a length of 0-3 x diameter of the nozzle outlet. This ensures optimum intake, especially in partial load operation.
  • the fluid is compressor air which is premixed with fuel, partially premixed, or non-premixed.
  • the object relating to the method is achieved by specifying a method for stabilizing the flame of a burner of a gas turbine, which comprises a reaction space and a plurality of jet nozzles opening into the reaction space, wherein fluid is injected into the reaction space with the jet nozzles by means of a fluid jet, wherein the fluid is burned in the reaction space, whereby a hot gas is formed.
  • a method for stabilizing the flame of a burner of a gas turbine which comprises a reaction space and a plurality of jet nozzles opening into the reaction space, wherein fluid is injected into the reaction space with the jet nozzles by means of a fluid jet, wherein the fluid is burned in the reaction space, whereby a hot gas is formed.
  • at least one jet nozzle has an annular gap through which the hot gas is partially sucked in and flows into the annular gap counter to the fluid flow direction and is admixed with the fluid jet within the jet nozzle.
  • the fluid preferably flows into the reaction space at high speed.
  • a pressure difference is formed between the reaction space and the fluid jet flowing into the reaction space.
  • the fluid is formed at partial load operation of the burner from a fuel / compressor air mixture, and at full load from compressor air, which has only slightly or no fuel content.
  • These nozzles thus act in partial load operation as a pilot burner with pilot beams.
  • pilot beams are made smaller than the other beams so that less air passes through these nozzles, thus ensuring stabilization under partial load operation.
  • the burner is configured with a plurality of jet nozzles, of which, however, only one or a few nozzles according to the invention are. These then act as "pilot" at partial load as described above, and are supplied with little or no fuel at full load operation, thus avoiding increased NOx values during base load operation.
  • FIG. 1 shows a detail of a gas turbine with a
  • FIG. 2 shows schematically a section through a jet burner transversely to its longitudinal direction
  • Fig. 3 shows schematically a section through another
  • Jet burner transversely to its longitudinal direction
  • FIG. 5 schematically shows a second embodiment of a nozzle 6a according to the invention
  • FIG. 6 shows schematically a third embodiment of a nozzle 6b according to the invention
  • Fig. 7 shows schematically a fourth embodiment of a nozzle 6c according to the invention.
  • 1 shows a section of a gas turbine with a shaft 14 arranged along a shaft and not shown, and a parallel to the shaft axis 14 aligned combustion chamber 16 in a longitudinal section.
  • the combustion chamber 16 is rotationally symmetrical about a combustion chamber axis 18.
  • the combustion chamber axis 18 is arranged in this particular embodiment parallel to the shaft axis 14, wherein it can also run at an angle to the shaft axis 14, in extreme cases perpendicular to this.
  • An annular housing 10 of the combustion chamber 16 surrounds a reaction space 5, which is likewise embodied rotationally symmetrically about the combustion chamber axis 18.
  • an air or air / fuel mixture is introduced into the reaction space 5.
  • the recirculating hot gases 4 in the reaction space are indicated by 1.
  • FIG. 2 shows schematically a section through a
  • Jet burner perpendicular to a shaft axis 14 of the burner.
  • the burner comprises a housing 10, which has a circular gene cross-section. Within the housing 10, a certain number of jet nozzles 3 is arranged substantially annular. Each jet nozzle 3 has a circular cross section.
  • the burner may include a pilot burner 25.
  • FIG. 3 schematically shows a section through a further jet burner, wherein the section runs perpendicular to the center axis of the further burner.
  • the burner also has a housing 10 which has a circular cross-section and in which a number of inner and outer jet nozzles 3,30 is arranged.
  • the jet nozzles 3, 30 each have a circular cross-section, the outer jet nozzles 3 having an equal or larger cross-sectional area than the inner jet nozzles 30.
  • the outer jet nozzles 3 are arranged substantially annularly within the housing 10 and form an outer ring ,
  • the inner jet nozzles 30 are also arranged annularly within the housing 10.
  • the inner jet nozzles 30 form an inner ring that is concentric with the outer jet nozzle ring.
  • FIGS 2 and 3 show only examples of the arrangement of jet nozzles 3,30 within a jet burner. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 3,30 possible.
  • the jet flame-based combustion system offers advantages over spin-stabilized systems due to the distributed heat release zones and the lack of spin-induced vortex advantages, especially from a thermoacoustic point of view.
  • By a suitable choice of the jet pulse small-scale flow structures can be generated which dissipate acoustically induced heat release fluctuations and thus suppress pressure pulsations which are typical for spin-stabilizing flames.
  • Combustion systems are recombined by mixing in hot stabilizing gases. Especially in the lower part load range, however, care must be taken to ensure that additional stabilization mechanisms prevent a partial or complete flame extinction. This is now solved by means of the invention.
  • Fig. 4 shows a jet nozzle 6 according to the invention.
  • the burner comprises a reaction space 5 and a plurality of jet nozzles 6 which open into the reaction space 5.
  • the jet nozzle By means of the jet nozzle, fluid is injected into the reaction space 5 with a fluid jet 2.
  • the fluid In the reaction space 5, the fluid is burned to hot gas 4.
  • the fluid may be a fuel / air mixture, or even be formed from compressor air.
  • an annular gap is now available. This is formed from an insert tube 12.
  • the annular gap 8 is thus arranged around the fluid jet 2.
  • Hot gas 4 is now sucked into the nozzle 6 through this annular gap 8.
  • the particular static pressure difference between the combustion chamber 16 and the reaction chamber 5 and the fluid flowing at high speed fluid is used, which has a lowered static pressure due to the high flow rates.
  • Hot gas 4 now flows back through the annular gap 8 against the flow direction of the fluid jet 2 in the nozzle 6 into the nozzle 6. There, the hot gas 4 is mixed with the fluid jet 2.
  • the hot gas admixture is thus according to the invention within the nozzle 6. This corresponds to a defined mixing of hot gas in the nozzle 6, whereby a reliable ignition and thus a reliable stabilization of the entire burner is ensured.
  • the stabilization is particularly advantageous at partial load operation. According to the invention, therefore, only one or a few nozzles 6 of a jet burner can be used with this device for suction of hot gas 4 be configured. These can act as pilot burners at partial load operation.
  • the fluid may be a fuel / air mixture. To this end, it may additionally be advantageous that these "pilot jets" are made smaller than the other jets so that less compressor air passes through these nozzles 6. In full-load operation or near full load, the fluid is only supplied with little or no fuel. The fluid can then consist essentially of compressor air, which means that increased NOx values can be avoided in the case of base load.
  • the hot gas is sucked in through the annular gap 8. This is formed by an insert tube 12. Upstream in the insert tube 12, one or more openings 11 are formed, by means of which the hot gas 4 can be added to the fluid jet 2.
  • the openings 11 are in the insert tube 12 on the radiation side, that is arranged in the beam limiting wall.
  • the openings 11 can be designed as bores.
  • the size of the openings 11 and the radial height H of the annular gap 8 are designed so that a good
  • Hot gas mixing is ensured in the fluid jet 2 in the jet nozzle 6.
  • the nozzle 6 also has a nozzle outlet 22 with a diameter D.
  • the nozzle outlet 22 can be arranged opposite the annular gap 8 offset in the flow direction.
  • the offset 24 has a length L of 0mm-3x D (mm), where D is the diameter of the nozzle outlet 22.
  • the mixture temperature is brought to a value that ensures reliable ignition and thus a reliable stabilization of the entire burner in all driving ranges.
  • the fluid jet 2 may consist of an air / fuel mixture of different mixing quality.
  • the jet flame itself may be premixed, partially premixed or non-premixed.
  • Fig. 5 shows a further second embodiment of a nozzle 6a according to the invention.
  • a second annular channel 20 is present, which is arranged around the annular gap 8 around.
  • This annular channel 20 can essentially be designed to guide the compressor air or the air / fuel mixture to the nozzle inlet 28.
  • the combustion air or the fuel / air mixture can be used for cooling especially the radially outer wall of the insert tube 12. This is advantageous because the aspirated gases have a high temperature which otherwise could potentially damage the burner.
  • the annular channel 20 may also be designed with heat transfer increasing measures.
  • the hot gas-carrying passages so in particular the insert tube 12 made of high-quality materials, e.g. be made of ceramic or Keramikenthaitigen materials, the materials may still be coated.
  • FIG. 6 and Fig. 7 show further embodiments of a nozzle according to the invention 6b and 6c. These show nozzles which in particular increase the static pressure difference between the combustion chamber 16 or the reaction space 5 and the fluid jet flow 2 at the level of the mixing point.
  • FIG. 6 shows an insert tube 12a, which has a thickening 15 at the upstream end. The thickening 15 is executed rounded. Thus, wise deflection losses of the compressor air or the fuel / air mixture in the annular channel 20 can be avoided.
  • the thickening 15 may be formed diffusely 16 in the flow direction. This results in a particularly efficient pressure difference increase.
  • the openings 11 can also be designed as slots, which are optionally provided obliquely to.
  • Fig. 7 has a nozzle 6c, wherein the insert tube 12b is formed in the flow direction diffused 21 fluid flow side. Again, there is a particularly efficient pressure difference increase.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Gas Burners (AREA)

Abstract

L'invention concerne un brûleur d'une turbine à gaz qui comporte une chambre de réaction (5) et plusieurs buses (6) débouchant dans la chambre de réaction (5), du fluide étant injecté dans la chambre de réaction (5) avec les buses (6) par une sortie (22) au moyen d'un jet de fluide (2), le fluide étant brûlé dans la chambre de réaction (5) pour former du gaz chaud (4), une fente annulaire (8) étant disposée autour du jet de fluide (2) sur au moins une buse (6, 6a, 6b, 6c), de telle sorte qu'une partie du gaz chaud (4) est aspirée hors de l'espace de réaction (5), et entre dans la fente annulaire (8) dans le sens contraire au sens d'écoulement de fluide et est mélangée à l'intérieur de la buse (6, 6a, 6b, 6c) avec le jet de fluide (2) et la fente annulaire (8) étant formée au moyen d'un tuyau d'insertion (12, 12a, 12b), et le tuyau d'insertion (12a) présentant un épaississement (15) sur l'extrémité en aval du flux. L'invention concerne également un procédé pour la stabilisation de la flamme d'un tel brûleur d'une turbine à gaz.
EP10740607.6A 2009-08-03 2010-08-02 Stabilisation de la flamme d'un brûleur Not-in-force EP2462379B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10740607.6A EP2462379B1 (fr) 2009-08-03 2010-08-02 Stabilisation de la flamme d'un brûleur

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09167055A EP2295858A1 (fr) 2009-08-03 2009-08-03 Stabilisation de la flamme d'un brûleur
PCT/EP2010/061201 WO2011015549A1 (fr) 2009-08-03 2010-08-02 Stabilisation de la flamme d'un brûleur
EP10740607.6A EP2462379B1 (fr) 2009-08-03 2010-08-02 Stabilisation de la flamme d'un brûleur

Publications (2)

Publication Number Publication Date
EP2462379A1 true EP2462379A1 (fr) 2012-06-13
EP2462379B1 EP2462379B1 (fr) 2016-03-30

Family

ID=41479366

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09167055A Withdrawn EP2295858A1 (fr) 2009-08-03 2009-08-03 Stabilisation de la flamme d'un brûleur
EP10740607.6A Not-in-force EP2462379B1 (fr) 2009-08-03 2010-08-02 Stabilisation de la flamme d'un brûleur

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09167055A Withdrawn EP2295858A1 (fr) 2009-08-03 2009-08-03 Stabilisation de la flamme d'un brûleur

Country Status (5)

Country Link
US (1) US9074762B2 (fr)
EP (2) EP2295858A1 (fr)
CN (1) CN102472485B (fr)
RU (1) RU2533609C2 (fr)
WO (1) WO2011015549A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140270731A1 (en) * 2013-03-12 2014-09-18 Applied Materials, Inc. Thermal management apparatus for solid state light source arrays
FR3018900B1 (fr) * 2014-03-19 2016-04-15 Yahtec Dispositif de bruleur a pre melange gaz
RU2689654C2 (ru) 2014-04-10 2019-05-28 Софинтер С.П.А. Горелка
CN106895399B (zh) * 2017-04-25 2024-08-09 武建斌 一种醇基燃料锅炉内部用气化燃烧装置
CN109028043A (zh) * 2018-06-28 2018-12-18 广州市艾欣能能源科技有限责任公司 一种高效节能的锅炉

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2918117A (en) * 1956-10-04 1959-12-22 Petro Chem Process Company Inc Heavy fuel burner with combustion gas recirculating means
US3174526A (en) * 1960-08-23 1965-03-23 Linde Robert Albert Von Atomizing burner unit
BE795261A (fr) * 1972-02-10 1973-05-29 Bailey Frank W Bruleurs canon a retention de flamme bleue et systemes d'echangeur de chaleur
US3927958A (en) * 1974-10-29 1975-12-23 Gen Motors Corp Recirculating combustion apparatus
US4004875A (en) * 1975-01-23 1977-01-25 John Zink Company Low nox burner
DE3033988C2 (de) * 1980-09-10 1986-04-17 Karl-Friedrich Dipl.-Ing. Dipl.-Wirtsch.-Ing. 4100 Duisburg Schmid Gasbrenner mit integrierter Brennerkopf-Luftkühlung
DE3902601A1 (de) * 1989-01-28 1990-08-09 Buderus Heiztechnik Gmbh Gasgeblaesebrenner
RU2008559C1 (ru) * 1991-04-15 1994-02-28 Шестаков Николай Сергеевич Способ сжигания газа и устройство для его осуществления
US5240409A (en) * 1992-04-10 1993-08-31 Institute Of Gas Technology Premixed fuel/air burners
US5350293A (en) * 1993-07-20 1994-09-27 Institute Of Gas Technology Method for two-stage combustion utilizing forced internal recirculation
DE19505614A1 (de) * 1995-02-18 1996-08-22 Abb Management Ag Verfahren zum Betrieb eines Vormischbrenners
RU2093750C1 (ru) * 1995-03-09 1997-10-20 Самарский государственный технический университет Способ сжигания топливного газа и устройство для его осуществления
EP0911076A1 (fr) * 1997-10-23 1999-04-28 Haldor Topsoe A/S Four de reformage à recirculation interne
JP3924136B2 (ja) 2001-06-27 2007-06-06 三菱重工業株式会社 ガスタービン燃焼器
DE10217913B4 (de) * 2002-04-23 2004-10-07 WS Wärmeprozesstechnik GmbH Gasturbine mit Brennkammer zur flammenlosen Oxidation
SE0202836D0 (sv) * 2002-09-25 2002-09-25 Linde Ag Method and apparatus for heat treatment
CN100504174C (zh) 2003-12-16 2009-06-24 株式会社日立制作所 燃气轮机用燃烧器
EP1950494A1 (fr) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
EP2372245A1 (fr) * 2010-03-26 2011-10-05 Siemens Aktiengesellschaft Brûleur destiné à la stabilisation de la combustion d'une turbine à gaz ainsi que procédé
JP5555382B2 (ja) * 2012-05-25 2014-07-23 日野自動車株式会社 排気浄化装置用バーナー

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2011015549A1 *

Also Published As

Publication number Publication date
RU2533609C2 (ru) 2014-11-20
US9074762B2 (en) 2015-07-07
CN102472485B (zh) 2015-02-18
US20120186265A1 (en) 2012-07-26
RU2012108126A (ru) 2013-09-10
EP2295858A1 (fr) 2011-03-16
WO2011015549A1 (fr) 2011-02-10
EP2462379B1 (fr) 2016-03-30
CN102472485A (zh) 2012-05-23

Similar Documents

Publication Publication Date Title
EP2156095B1 (fr) Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
DE102012100368B4 (de) Brennkammerdüse
DE102010017779B4 (de) Radiale Einlassleitschaufeln für einen Brenner
EP3134677B1 (fr) Brûleur ayant un oscillateur fluidique, pour une turbine à gaz et turbine à gaz ayant le brûleur
DE102014117621A1 (de) Brennstoffinjektor mit Vormisch-Pilotdüse
EP1754002B1 (fr) Brûleur étagé à prémélange comprenant in injecteur de carburant liquide
EP2462379B1 (fr) Stabilisation de la flamme d'un brûleur
WO2012016748A2 (fr) Chambre de combustion de turbine à gaz
EP3301370B1 (fr) Tête de brûleur, système de brûleur et utilisation du système de brûleur dans la chambre de combustion d'une turbine à gaz
EP2409087A2 (fr) Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz
WO2011117042A1 (fr) Brûleur pour la stabilisation de la combustion d'une turbine à gaz
DE102017118166B4 (de) Brennerkopf, Brennersystem und Verwendung des Brennersystems
DE102014103021A1 (de) Diffusionsbrennkammereinrichtungsbrennstoffdüse zur Beschränkung von NOX Emissionen
EP3301371A1 (fr) Système de chambre de combustion, utilisation d'un système de chambre de combustion pourvu d'une turbine racoordée et procédé de mise en oeuvre d'un processus de combustion
EP3926238B1 (fr) Module d'une turbine à gaz pourvu de dérivation d'air de la chambre de combustion
EP1706672B1 (fr) Brûleur à prémélange et procédé permettant de faire fonctionner une chambre de combustion
WO2017025295A1 (fr) Lance de brûleur pour brûleur pilote
WO2010081578A1 (fr) Chambre de combustion et turbine à gaz
WO2023180320A1 (fr) Ensemble injecteur comprenant un tuyau de carburant central rendu étanche à un flux d'air entrant
DE19737311A1 (de) Verfahren und Vorrichtung zur Zufuhr von Verbrennungsabgasen in die Mischeinrichtung von Brennern ohne wirksame Beeinflussung der Flammenstabilität

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: 20120113

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 SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
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

INTG Intention to grant announced

Effective date: 20141031

17Q First examination report despatched

Effective date: 20141219

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20151008

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 SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 785812

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160415

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010011345

Country of ref document: DE

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: 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: 20160701

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: 20160630

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: 20160330

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: 20160330

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160330

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

Ref country code: LV

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

Effective date: 20160330

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: 20160330

Ref country code: SE

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

Effective date: 20160330

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: 20160330

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

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: 20160730

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: 20160330

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: 20160330

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

Ref country code: CZ

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

Effective date: 20160330

Ref country code: RO

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

Effective date: 20160330

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: 20160330

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: 20160330

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: 20160801

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: 20160330

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

Ref country code: IT

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

Effective date: 20160330

Ref country code: BE

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

Effective date: 20160831

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010011345

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: 20160330

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: DE

Ref legal event code: R119

Ref document number: 502010011345

Country of ref document: DE

26N No opposition filed

Effective date: 20170103

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

Ref country code: MC

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

Effective date: 20160330

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Effective date: 20160802

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

Ref country code: CH

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

Effective date: 20160831

Ref country code: LI

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

Effective date: 20160831

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20170428

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: 20160330

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: DE

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

Effective date: 20170301

Ref country code: GB

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

Effective date: 20160802

Ref country code: IE

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

Effective date: 20160802

Ref country code: FR

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

Effective date: 20160831

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: 20160802

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 785812

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160802

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: 20160802

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

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: 20100802

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: 20160330

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

Ref country code: TR

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

Effective date: 20160330

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: 20160330

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: 20160330

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

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: 20160330

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: 20160330