WO2011000615A1 - Brûleur, en particulier pour turbines à gaz - Google Patents

Brûleur, en particulier pour turbines à gaz Download PDF

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Publication number
WO2011000615A1
WO2011000615A1 PCT/EP2010/056057 EP2010056057W WO2011000615A1 WO 2011000615 A1 WO2011000615 A1 WO 2011000615A1 EP 2010056057 W EP2010056057 W EP 2010056057W WO 2011000615 A1 WO2011000615 A1 WO 2011000615A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas
gas supply
channel
burner according
supply channel
Prior art date
Application number
PCT/EP2010/056057
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Mariano Cano Wolff
Andre Kluge
Tobias Krieger
Ulrich Wörz
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to CN201080029591.5A priority Critical patent/CN102472494B/zh
Priority to EP10718576.1A priority patent/EP2449310B1/fr
Priority to RU2012102975/06A priority patent/RU2533045C2/ru
Publication of WO2011000615A1 publication Critical patent/WO2011000615A1/fr

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
    • F23R3/283—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

  • Burner in particular for gas turbines The present invention relates to a burner and in particular to a gas turbine burner with a central fuel supply arrangement. In addition, the invention relates to a gas turbine. With regard to the global efforts to reduce the
  • the burner described in EP 0 276 696 B1 is a hybrid burner for premixing operation 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 possibility for feeding in inert materials is provided.
  • the central fuel supply assembly is surrounded by a main burner system having an air supply annular channel system with a swirler blading therein having a plurality of blades and gas pre-mixing nozzle pipes located upstream of the blades.
  • 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 themselves, as described, for example, in EP 0 580 683 B1.
  • the object of the present invention is therefore to provide a burner, in particular a gas turbine burner, which makes it possible to supply fuel gas to a second gas channel without the outer contour of the central gas channel
  • Fuel supply arrangement is changed significantly.
  • 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.
  • a separate gas supply channel is present in the gas supply pipe for each gas distribution channel.
  • 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 makes 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 can be present between the gas supply tube and the gas distribution channels, which cross-sections the annular flow cross-section and the circular flow cross-section with maximum flow areas for the gas flowing into the gas distribution channels.
  • the adapter piece forms part of the outer circumference of the outer tube and the outer tube has a corresponding recess in the peripheral wall, the adapter can be completely welded to the inner tube and the outer tube, so that the gas channels are sealed against each other.
  • 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. These are then arranged adjacent to each other and connected by means of a transition section with the gas supply channels.
  • 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 connections can 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. Further features, properties and advantages of the present invention will become apparent from the following description of embodiments with reference to the accompanying figures.
  • FIG. 1 shows the burner according to the invention in a highly schematized schematic diagram.
  • Figure 2 shows a section of a first embodiment of the burner according to the invention in a partially cutaway perspective view.
  • FIG. 3 shows a burner used in the first exemplary embodiment for the burner according to the invention
  • FIG. 4 shows flow cross sections of the first exemplary embodiment.
  • Figure 5 shows a detail of the first embodiment.
  • FIG. 6 shows a second exemplary embodiment of the burner according to the invention in a perspective view.
  • Figure 7 shows a gas supply pipe of the second embodiment in a perspective view.
  • Figure shows the gas connections of the gas supply pipe of Figure 7 in a perspective view.
  • FIG. 1 shows a burner according to the invention in a highly schematic diagram.
  • 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 can 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.
  • the main burner system surrounding the pilot burner system comprises a radial outer air supply duct 17, also called annular air duct, through which swirl blades 19 of a
  • 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 through the radial air supply channel 17 air.
  • Air flowing through the air supply channel 17 air can also by means of oil nozzles 25
  • 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 into 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 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 Figures 2 to 5.
  • the gas supply channels 35, 37 are arranged coaxially with one another 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 the first annular gas distributor channel 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 Rohrtei- Ie 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 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 for the flowing gas transferred maximum flow areas.
  • the adapter piece 49 is shown in Figure 3 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. Inside the adapter piece 49, 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 ones
  • FIG. 1 Flow cross sections, which result with the aid of the adapter piece at the outlet of the gas supply pipe 41, are shown in FIG. This shows the inlet openings 57, 59, which are provided with flow cross sections corresponding to the maximum flow areas, to the annular gas distribution channels 29, 31.
  • Figure 5 shows an enlarged detail of Figure 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 first specific embodiment described with reference to FIGS. 2 to 5 for the burner according to the invention offers the advantage that a negative influence on the airflow is obtained.
  • Flow can be avoided in particular in the radial air supply channel 17, since no change in the outer hub geometry or the gas supply pipe 41 needs to be made in comparison 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 pilot burner 63 arranged in its center 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 concrete embodiment is shown in Figure 7 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 next to each other instead of concentrically 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 concretesupplementarysbei- game for 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 carrier - 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, there is no 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)

Abstract

L'invention concerne un brûleur comportant un système central d'alimentation en combustible (27), un conduit d'air annulaire (17) entourant le système central d'alimentation en combustible (27) et servant à acheminer l'air de combustion et des aubes de tourbillonnement (19) disposées dans le conduit d'air annulaire (17). Les aubes de tourbillonnement (19) présentent de premières buses de gaz (21) pour injecter un combustible gazeux dans l'air de combustion et de secondes buses de gaz (23) pour injecter un combustible gazeux dans l'air de combustion. Les premières buses de gaz (21) sont alimentées par un premier canal de répartition du gaz (29) dans le système d'alimentation en combustible (23) et les secondes buses de gaz (23) sont alimentées par un second canal de répartition du gaz (31) dans le système d'alimentation en combustible (27). Le premier canal de répartition du gaz (29) et le second canal de répartition du gaz (31) sont alimentés en gaz de combustion par un tuyau d'alimentation en gaz (41) qui présente un premier canal d'alimentation en gaz (35) et un second canal d'alimentation en gaz (37), le premier canal d'alimentation en gaz (35) étant relié au premier canal de répartition du gaz (29) et le second canal d'alimentation en gaz (37) étant relié au second canal de répartition du gaz (31).
PCT/EP2010/056057 2009-06-30 2010-05-05 Brûleur, en particulier pour turbines à gaz WO2011000615A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
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 (2)

Application Number Priority Date Filing Date Title
EP09164156A EP2270398A1 (fr) 2009-06-30 2009-06-30 Brûleur notamment pour turbines à gaz
EP09164156.3 2009-06-30

Publications (1)

Publication Number Publication Date
WO2011000615A1 true WO2011000615A1 (fr) 2011-01-06

Family

ID=41314499

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/056057 WO2011000615A1 (fr) 2009-06-30 2010-05-05 Brûleur, en particulier 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 (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

Families Citing this family (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
DE102022207492A1 (de) * 2022-07-21 2024-02-01 Rolls-Royce Deutschland Ltd & Co Kg Düsenvorrichtung zur Zugabe zumindest eines gasförmigen Kraftstoffes und eines flüssigen Kraftstoffes, Set, Zuleitungssystem und Gasturbinenanordnung

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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
DE3860569D1 (de) 1987-01-26 1990-10-18 Siemens Ag Hybridbrenner fuer vormischbetrieb mit gas und/oder oel, insbesondere fuer gasturbinenanlagen.
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 (5)

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Publication number Priority date Publication date Assignee Title
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

Cited By (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

Also Published As

Publication number Publication date
EP2449310A1 (fr) 2012-05-09
RU2012102975A (ru) 2013-08-10
RU2533045C2 (ru) 2014-11-20
CN102472494A (zh) 2012-05-23
CN102472494B (zh) 2014-08-20
EP2449310B1 (fr) 2017-03-22
EP2270398A1 (fr) 2011-01-05

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