EP2270398A1 - Brûleur notamment pour turbines à gaz - Google Patents

Brûleur notamment pour turbines à gaz Download PDF

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Publication number
EP2270398A1
EP2270398A1 EP09164156A EP09164156A EP2270398A1 EP 2270398 A1 EP2270398 A1 EP 2270398A1 EP 09164156 A EP09164156 A EP 09164156A EP 09164156 A EP09164156 A EP 09164156A EP 2270398 A1 EP2270398 A1 EP 2270398A1
Authority
EP
European Patent Office
Prior art keywords
gas
gas supply
channel
burner according
fuel
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.)
Withdrawn
Application number
EP09164156A
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Mariano Cano Wolff
Andre Kluge
Tobias Krieger
Ulrich Wörz
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 EP09164156A priority Critical patent/EP2270398A1/fr
Priority to PCT/EP2010/056057 priority patent/WO2011000615A1/fr
Priority to CN201080029591.5A priority patent/CN102472494B/zh
Priority to EP10718576.1A priority patent/EP2449310B1/fr
Priority to RU2012102975/06A priority patent/RU2533045C2/ru
Publication of EP2270398A1 publication Critical patent/EP2270398A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07001—Air swirling vanes incorporating fuel injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23R2900/00001—Arrangements using bellows, e.g. to adjust volumes or reduce thermal stresses

Definitions

  • the present invention relates to a burner, and more particularly to a gas turbine combustor having a central fuel supply arrangement.
  • the invention relates to a gas turbine.
  • burners have been developed in recent years that have particularly low emissions of nitrogen oxides (NOx). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil and natural gas, either selectively or in combination operable to increase the security of supply and flexibility of operation. Such burners are for example in the EP 0 276 696 B1 described.
  • the in EP 0 276 696 B1 described burner is a hybrid burner for Vormisch plante with gas and / or oil, as it is used in particular for gas turbine plants.
  • the burner comprises a central fuel supply arrangement, in which also a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • a pilot burner system is integrated, which is operable with gas and / or oil as a so-called diffusion burner or as a separate premix burner.
  • the central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with therein a swirl blading with a plurality of blades and nozzle pipes arranged upstream of the blades for premixing with gas.
  • inlet nozzles for oil in the area of the swirl blading which allow premixing of the main air flow with oil.
  • the fuel gas can also be injected into the air duct through nozzle openings arranged in the swirl vanes itself, as described, for example, in US Pat EP 0 580 683 B1 is described.
  • the first object is achieved by a burner according to claim 1, the second object by a gas turbine according to claim 15.
  • the dependent claims contain advantageous embodiments of the invention.
  • a burner according to the invention has a central fuel supply arrangement and an annular air duct surrounding the central fuel supply arrangement for supplying combustion air on.
  • swirl vanes are arranged, which have first gas nozzles for injecting a gaseous fuel into the combustion air and second gas nozzles for injecting a gaseous fuel into the combustion air.
  • the first gas nozzles are fed by a first gas distribution channel in the fuel supply arrangement, the second gas nozzles by a second gas distribution channel in the fuel supply arrangement.
  • the first gas distribution channel and the second gas distribution channel are supplied with fuel gas from a gas supply tube having a first gas supply channel and a second gas supply channel, wherein the first gas supply channel is connected to the first gas distribution channel and the second gas supply channel to the second gas distribution channel.
  • the two gas distribution channels are supplied with fuel instead of two separate gas supply pipes via a single, common gas supply pipe, wherein in the gas supply pipe for each gas distribution channel a separate gas supply channel is present.
  • the contour of the central fuel supply arrangement as it is known for a single gas distribution channel, approximately corresponding to the burner EP 0 580 683 B1 be maintained even in the presence of two gas distribution channels.
  • the gas supply channels can either be arranged coaxially to each other in the gas supply pipe or side by side.
  • the two gas supply channels according to a first embodiment coaxial with each other in the gas supply pipe they can be formed by the gas supply pipe comprises an outer tube and an inner tube, wherein the first gas supply channel is formed by the gap between the outer tube and the inner tube and the second gas supply passage from the interior of the inner tube.
  • the two tubes may have different thermal Strains result. These can be compensated if the inner tube and / or the outer tube has or have an elastic compensation element which enables or permits axial expansion or compression of the inner tube.
  • the inner tube and / or the outer tube may be divided into two axial parts which are interconnected via a bellows. Basically corrugated bellows or bellows come into question. These allow an expansion or contraction of the respective tube and thus a compensation for different thermal expansions.
  • the first gas supply channel has an annular flow cross section and the second gas supply channel has a circular flow cross section.
  • an adapter piece may be provided between the gas supply tube and the gas distribution channels, which converts the annular flow cross section and the circular flow cross section in cross sections with maximum flow areas for the gas flowing into the gas distribution channels.
  • the first gas supply channel and the second gas supply channel may each have a flow cross-section with maximum for the flowing gas flow area at least at their ends facing the gas distribution channels. In this way, it is possible to ensure optimal inflow of the gas supplied via the gas supply channels into the gas distribution channels.
  • the first gas supply channel can be supplied with fuel via a first gas supply connection, while the second gas supply channel is supplied with fuel via a second gas supply connection.
  • a straight connecting line between the first gas supply port and the second gas supply port may include an angle to a straight connecting line between the first gas supply channel and the second gas supply channel, in particular an angle of 90 °.
  • the gas supply ports may each have a circular flow cross-section.
  • the transition section can then convert the circular flow cross sections in cross sections with maximum flow areas for the flowing gas.
  • the gas connections can be designed so that they correspond to the previous standard, possibly with the exception of their dimensions.
  • the gas supply pipe with the juxtaposed gas supply channels can be advantageously designed as a casting, which in particular allows the already described rotation of the straight connecting lines and also can realize a constant wall thickness over the entire component.
  • a gas turbine according to the invention comprises at least one burner according to the invention.
  • the flexibility in operating the gas turbine can be increased because a two-stage gas injection into the air supply channel is possible without significant changes to the aerodynamics of the burner are needed.
  • FIG. 1 shows a burner according to the invention in a highly schematic schematic diagram, which described the concept underlying the burner.
  • the burner according to the invention which can optionally be used in conjunction with a plurality of similar burners, for example in the combustion chamber of a gas turbine plant, comprises an inner pilot burner system and a main burner system concentrically surrounding the pilot burner system. Both pilot burner system and main burner system can optionally with gaseous and / or liquid fuels, such as, for example, natural gas or fuel oil operated.
  • the pilot burner system includes an inner oil supply passage 1 concentrically surrounded by an inner annular gas supply passage 3. This is in turn surrounded by an inner air supply channel or Inertstoffzubuchkanal 5 concentrically.
  • a suitable ignition system may be arranged in or on this air supply channel (not shown in the figure).
  • the pilot burner system has a combustion chamber 7 zuwerende outlet opening 9, in whose area a twist blading 11 is arranged in the air supply channel. Gas can be injected from the inner gas supply channel 3 in the area of the swirl blading or upstream of the swirl blading into the air supply channel 5 by means of nozzle openings 13. Oil from the oil supply channel can be injected by means of oil nozzles 15 downstream of the swirl blading into the supplied air or the supplied inert material.
  • the pilot burner system can be operated in a conventional manner with oil and / or gas as a diffusion burner, in which the fuel is injected directly into the flame.
  • a diffusion burner in which the fuel is injected directly into the flame.
  • the pilot burner system it is also possible to operate the pilot burner system as a premix burner, in which the fuel is thoroughly mixed with air before the mixture is fed to the flame.
  • the main burner system surrounding the pilot burner system comprises a radial outer air supply channel 17, also called an annular air channel, through which swirl blades 19 of a swirl blading extend.
  • These swirl vanes 19 have first gas nozzles 21 and second gas nozzles 23, through which fuel gas can be injected into the air flowing in through the radial air supply duct 17.
  • air can also be injected by means of oil nozzles 25 oil.
  • the first gas nozzles 21 and second gas nozzles 23 located in the swirl vanes 19 and the oil nozzles 25 are supplied with fuel via a radially inner fuel supply arrangement, the so-called hub 27.
  • this first and second annular gas distribution channels 29 and 31 are arranged, which supply the gas nozzles 21 and 23 with gas.
  • an annular oil distribution channel 33 is arranged, which supplies the oil nozzles 25 with oil.
  • the gas distribution channels 29, 31 and the oil distribution channel 33 are supplied via gas supply channels 35, 37 and via an oil supply channel 39 with the appropriate fuel.
  • the gas supply channels 35, 37, which supply the gas distribution channels 29, 31 with fuel, are integrated in a common gas supply pipe 41.
  • For the oil supply channel 39 is a separate oil supply pipe 43 before.
  • the integration of the two gas supply channels 35, 37 in a common gas supply pipe 41 has the advantage that the aerodynamics of the burner with respect to the air flowing into the air supply channels 5, 17 air compared to a burner with only a single gas supply channel and a single set of gas nozzles not changed.
  • the burner according to the invention can therefore replace existing burners in existing combustion systems without the aerodynamics of the combustion system thereby changing.
  • a first concrete embodiment of the burner according to the invention in particular the gas supply pipe 41 with the gas supply channels 35, 37 will be described below with reference to the FIGS. 2 to 5 described.
  • the gas supply channels 35, 37 are arranged coaxially with each other in the gas supply pipe 41.
  • the gas supply channel 37 supplying gas to the second annular gas distribution channel 31 is formed by the lumen of an inner tube 35, whereas that of the first annular gas distribution channel 29 supplying gas supply channel 35 from the cavity between the outer surface of the inner tube 45 and the inner surface of an outer tube 46 is formed.
  • the outer tube 46 forms the outer wall of the gas supply pipe 41.
  • the inner tube 45 is cooled by the gas flowing therethrough and the outer tube 46 is heated by the warm compressor air flowing along, the two tubes 45, 46 experience different thermal expansions.
  • the inner tube 45 is formed in two parts, wherein between the tube parts 45, 45 'an elastic compensation element 47 is arranged.
  • the elastic compensation element is designed as a bellows, which allows an axial displacement of the two tube parts 45, 45 'against each other. Different thermal expansions between the outer tube 46 and the inner tube 45 can thus be compensated.
  • the compensation element can also be arranged on the outer tube 46. Also, the provision of two compensation elements, one on the inner tube 45 and one on the outer tube 46, is possible. For the compensation element on the outer tube 46, this is analogous with respect to the design of the compensation element on the inner tube 45.
  • an adapter piece 49 is provided, which has the annular flow cross section of the first gas supply channel 35 and the circular flow cross section of the second gas supply channel 37 in flow cross sections with maximum flow areas for the flowing gas transferred. In this way, the flow from the gas supply channels into the respective annular gas distribution channels can be optimized, whereby more uniform heat transfer rates can be achieved and the life and the life prediction of the burner can be improved.
  • the adapter piece 49 is in FIG. 3 shown in a perspective view. It has an approximately semicircular curved edge portion 51 with an outer surface 53, which is adapted in its radius of curvature to the wall of the outer tube 46. In addition, it has a circular projection 55, which can be connected to the inner tube 45.
  • the circular flow cross section and the annular flow cross section are converted into flow cross sections optimized with regard to the creation of maximum flow areas.
  • the optimized flow cross sections which result with the aid of the adapter piece at the outlet of the gas supply pipe 41, are in FIG. 4 shown. This shows the flow openings provided with the corresponding flow cross-sections corresponding inlet openings 57, 59 to the annular gas distribution channels 29, 31st
  • FIG. 5 shows an enlarged section FIG. 2 in which the arrangement of the adapter piece 49 and the connection with the inner tube 45 and the outer tube 46 are shown.
  • the adapter piece 49 is connected by means of welded connections on the one hand to the hub 27 and on the other hand to the inner tube 45 and the outer tube 46. Due to the only part-circular configuration of the adapter piece 49, which is a semicircular configuration in the present embodiment, it is possible first to weld the adapter piece 49 to the hub 27, then to weld the inner tube 45 on the adapter piece 49 and finally over the outer tube 46 and to weld with the adapter piece 49. If the adapter piece 49 would have a completely annular wall element, in particular the dense bonding of the part of the adapter piece 49 forming the inner gas supply channel to the hub 27 would be difficult to accomplish.
  • the referring to the FIGS. 2 to 5 described first specific embodiment of the burner according to the invention has the advantage that has a negative impact on the air flow
  • the radial air supply channel 17 can avoid, since no change in the outer hub geometry or the gas supply pipe 41 needs to be compared to a burner with only one gas distribution channel.
  • the flow cross-sections can be optimally utilized with the aid of the adapter piece, whereby unnecessary pressure losses are avoided.
  • the embodiment according to the first concrete embodiment allows a robust construction, which also allows easy mounting.
  • FIG. 6 shows the hub 27 of the burner according to the invention with a arranged in its center pilot burner 63 and the gas supply pipe 141 in a perspective view.
  • a burner support 65 can be seen, in which there are two connections 67, 69 for the two gas supply ducts 135, 137 located in the gas supply pipe 141.
  • the gas supply pipe 141 of the second specific embodiment is in FIG. 7 shown in a perspective view. It differs from the gas supply pipe 41 of the first concrete embodiment in that the gas supply channels 135, 137 are arranged side by side instead of concentric with each other.
  • the geometry of the gas supply channels 135, 137 is selected such that there are flow cross sections with maximum flow areas at least at the hub-side outlet end 71 of the gas supply tube.
  • the two gas ports for the gas supply pipe 141 are arranged. These are also arranged side by side, but a connecting line A, which connects the centers of the two gas ports 67, 69 with each other by 90 ° with respect to a connecting line B, the centers of the gas supply channels 135, 137 at the hub end of the gas supply pipe 141 connects to each other Turned 90 °.
  • the twisting can also be done by other angles than 90 °, if another arrangement of the gas ports 67th , 69 in the burner carrier 65 is desired.
  • the gas supply pipe 141 of the second concrete embodiment of the burner according to the invention can be designed in particular as a cast construction. In such, in particular with a twisting of the channels in the pipe by 90 °, a constant wall thickness over the entire component can be achieved.
  • the design of the gas supply pipe 141 according to the second specific embodiment offers the particular advantage that the distribution of the gas supply channels in two separate gas connections between the burner carrier and the hub takes place. This simplifies the assembly of the burner. The burner carrier flange is then only provided with two fitting holes.
  • the tube construction hardly changes the aerodynamics compared to a burner with only one gas distribution channel in the hub. Since the transition section is located in the vicinity of the burner support - and thus away from the air ducts of the pilot burner and the main burner - this change in the gas supply pipe leads to a gas supply pipe with only one gas supply channel not to a significant change in the aerodynamics of the burner.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP09164156A 2009-06-30 2009-06-30 Brûleur notamment pour turbines à gaz Withdrawn EP2270398A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP09164156A EP2270398A1 (fr) 2009-06-30 2009-06-30 Brûleur notamment pour turbines à gaz
PCT/EP2010/056057 WO2011000615A1 (fr) 2009-06-30 2010-05-05 Brûleur, en particulier pour turbines à gaz
CN201080029591.5A CN102472494B (zh) 2009-06-30 2010-05-05 尤其用于燃气轮机的燃烧器
EP10718576.1A EP2449310B1 (fr) 2009-06-30 2010-05-05 Brûleur notamment pour turbines à gaz
RU2012102975/06A RU2533045C2 (ru) 2009-06-30 2010-05-05 Горелка, в частности, для газовых турбин

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09164156A EP2270398A1 (fr) 2009-06-30 2009-06-30 Brûleur notamment pour turbines à gaz

Publications (1)

Publication Number Publication Date
EP2270398A1 true EP2270398A1 (fr) 2011-01-05

Family

ID=41314499

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09164156A Withdrawn EP2270398A1 (fr) 2009-06-30 2009-06-30 Brûleur notamment pour turbines à gaz
EP10718576.1A Active EP2449310B1 (fr) 2009-06-30 2010-05-05 Brûleur notamment pour turbines à gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10718576.1A Active EP2449310B1 (fr) 2009-06-30 2010-05-05 Brûleur notamment pour turbines à gaz

Country Status (4)

Country Link
EP (2) EP2270398A1 (fr)
CN (1) CN102472494B (fr)
RU (1) RU2533045C2 (fr)
WO (1) WO2011000615A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2693202C2 (ru) * 2014-11-21 2019-07-01 Ансальдо Энергия С.П.А. Трубчатый инжектор для впрыска топлива в камеру сгорания газовой турбины
EP4310400A1 (fr) * 2022-07-21 2024-01-24 Rolls-Royce Deutschland Ltd & Co KG Dispositif de buse pour ajouter au moins un carburant gazeux et un carburant liquide, ensemble, système d'alimentation et ensemble turbine à gaz

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011116317A1 (de) * 2011-10-18 2013-04-18 Rolls-Royce Deutschland Ltd & Co Kg Magervormischbrenner eines Fluggasturbinentriebwerks

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276696B1 (fr) 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
WO1992019913A1 (fr) * 1991-04-25 1992-11-12 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
US5361578A (en) * 1992-08-21 1994-11-08 Westinghouse Electric Corporation Gas turbine dual fuel nozzle assembly with steam injection capability
WO1996015409A1 (fr) * 1994-11-10 1996-05-23 Westinghouse Electric Corporation Chambre de combustion de turbine a deux combustibles
EP0800038A2 (fr) * 1996-03-29 1997-10-08 General Electric Company Buse pour la combustion à diffusion et à prémélange dans une turbine
EP1507119A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brûleur et méthode de fonctionnement d'une turbine à gaz

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SU1204002A1 (ru) * 1984-07-04 1996-08-27 А.В. Андреев Способ подготовки топливовоздушной смеси в кольцевой камере сгорания газотурбинного двигателя
US5351578A (en) * 1992-11-20 1994-10-04 James Emter Resilient compressible clamping surface for circular saw blades
US5359847B1 (en) * 1993-06-01 1996-04-09 Westinghouse Electric Corp Dual fuel ultra-flow nox combustor
US6363726B1 (en) * 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
SE521293C2 (sv) * 2001-02-06 2003-10-21 Volvo Aero Corp Förfarande och anordning för tillförsel av bränsle till en brännkammare
EP1394471A1 (fr) * 2002-09-02 2004-03-03 Siemens Aktiengesellschaft Brûleur
EP1568942A1 (fr) * 2004-02-24 2005-08-31 Siemens Aktiengesellschaft Brûleur à prémélange et procédé pour brûler un gaz pauvre
US6993916B2 (en) * 2004-06-08 2006-02-07 General Electric Company Burner tube and method for mixing air and gas in a gas turbine engine
EP1614967B1 (fr) * 2004-07-09 2016-03-16 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276696B1 (fr) 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
WO1992019913A1 (fr) * 1991-04-25 1992-11-12 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
EP0580683B1 (fr) 1991-04-25 1995-11-08 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
US5361578A (en) * 1992-08-21 1994-11-08 Westinghouse Electric Corporation Gas turbine dual fuel nozzle assembly with steam injection capability
WO1996015409A1 (fr) * 1994-11-10 1996-05-23 Westinghouse Electric Corporation Chambre de combustion de turbine a deux combustibles
EP0800038A2 (fr) * 1996-03-29 1997-10-08 General Electric Company Buse pour la combustion à diffusion et à prémélange dans une turbine
EP1507119A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Brûleur et méthode de fonctionnement d'une turbine à gaz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2693202C2 (ru) * 2014-11-21 2019-07-01 Ансальдо Энергия С.П.А. Трубчатый инжектор для впрыска топлива в камеру сгорания газовой турбины
EP4310400A1 (fr) * 2022-07-21 2024-01-24 Rolls-Royce Deutschland Ltd & Co KG Dispositif de buse pour ajouter au moins un carburant gazeux et un carburant liquide, ensemble, système d'alimentation et ensemble turbine à gaz

Also Published As

Publication number Publication date
EP2449310A1 (fr) 2012-05-09
RU2012102975A (ru) 2013-08-10
RU2533045C2 (ru) 2014-11-20
WO2011000615A1 (fr) 2011-01-06
CN102472494A (zh) 2012-05-23
CN102472494B (zh) 2014-08-20
EP2449310B1 (fr) 2017-03-22

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