EP1507119A1 - Brûleur et méthode de fonctionnement d'une turbine à gaz - Google Patents

Brûleur et méthode de fonctionnement d'une turbine à gaz Download PDF

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Publication number
EP1507119A1
EP1507119A1 EP03018408A EP03018408A EP1507119A1 EP 1507119 A1 EP1507119 A1 EP 1507119A1 EP 03018408 A EP03018408 A EP 03018408A EP 03018408 A EP03018408 A EP 03018408A EP 1507119 A1 EP1507119 A1 EP 1507119A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
inlet
inlet devices
gas turbine
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Withdrawn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
EP03018408A
Other languages
German (de)
English (en)
Inventor
Malte Dr. Blomeyer
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 EP03018408A priority Critical patent/EP1507119A1/fr
Priority to PCT/EP2004/008115 priority patent/WO2005019733A1/fr
Priority to EP04763360.7A priority patent/EP1654496B1/fr
Priority to JP2006522924A priority patent/JP4430074B2/ja
Priority to CNB2004800282182A priority patent/CN100545517C/zh
Priority to US10/568,120 priority patent/US7654090B2/en
Priority to ES04763360.7T priority patent/ES2551440T3/es
Publication of EP1507119A1 publication Critical patent/EP1507119A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • 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
    • F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes

Definitions

  • the invention relates to a burner with an annular Premix channel, radially distributed in the fuel introduced is.
  • the invention also relates to a method of operation a gas turbine with a burner having an annular Premix channel has.
  • the swirl vanes of the disclosed Swirl lattices are hollow, with openings at the Surface of the swirl blades in the radial direction with Swirl blades extend. These openings become fuel embedded in the premix channel, previously the hollow Swirl blades was supplied. This will be on the radial height of the premix channel uniform inlet of Fuel in the flowing through the premixing combustion air reached. At the same time, through the inlet of the Fuel from all swirl blades also a uniform Distribution of fuel in the circumferential direction of the premix channel reached. This has a high homogeneity of then in the combustion zone flowing combustion air-fuel mixture According. Such homogeneity is desirable for low nitrogen oxide emissions, since the formation of nitric oxide exponditiell grows with the flame temperature.
  • the object of the invention is to specify a burner with an annular premixing channel, which can be adjusted with regard to its combustion stability as a function of the prevailing operating conditions.
  • Another object of the invention is the disclosure of a method for operating a gas turbine, in which a burner is adjusted depending on the operating state of the gas turbine so that the highest possible flame stability and lowest possible pollutant emissions result.
  • the task directed to a burner is according to the invention solved by a directed along an axis burner with an annular Vormischkanal, in the fuel radially distributed is introduced, wherein the radial distribution of the fuel during operation of the burner adjustable is.
  • the radial distribution of the fuel is the distribution of the fuel along a line perpendicular to the axis of Burner.
  • the invention is proposed for the first time, the to make the radial distribution of the fuel adjustable, so that it reacts to different operating conditions can. So far, only static fuel distributions by means of the geometry and inlet positions of fuel and combustion air realized.
  • the invention works In contrast, from the knowledge that pollutant emissions and combustion stabilities at various operating conditions of the burner favorably by a changed radial Distribution of the fuel can be influenced.
  • To the Example is usually sought in a full load operation, that fuel is as homogeneous as possible in the combustion air is distributed to keep nitrogen oxide emissions low.
  • Such combustion vibrations occur at Flame instabilities, the pressure fluctuations in a combustion chamber entail, in which the burner opens.
  • By Reverse reflection from the combustion chamber walls of these pressure fluctuations in the flame area or in the mixing area of Fuel and combustion air can be in-phase Overlay a positive feedback of flame instability and pressure fluctuations occur, creating a stable Combustion vibration can be built. This leads to high sound emissions and vibrations in the combustion system, the damage may result.
  • a change in the Distribution profile of the fuel inlet can be this positive Interrupt feedback and thus the combustion oscillation suppress.
  • the opening cross sections lose weight.
  • the inlet devices of the first part and of the second part alternately along the circumference of the premixing channel arranged.
  • the inlet devices of the first and the second part are so alternately next to each other arranged around the circumference.
  • the inlet devices of the first follow Part and the second part in the axial direction of the premixing channel each other.
  • fuel from the intake devices of the first Partly embedded in the premix channel and in the flow direction subsequently, fuel from the inlet devices of the second part.
  • This can in particular both from the inlet devices of the first part as well as the inlet devices of the second part with the circumference of the premix channel evenly distributed fuel can be let in.
  • the overlay of the fuel inlet from the two Divide yields the desired radial distribution for the entire Fuel inlet.
  • a first and a second around the axis the burner fuel supply line provided, wherein a pressure difference of the fuel pressure in the two Fuel supply lines to each other depending on the operating condition of the burner is adjustable. More preferred is the first Part of the inlet device with the first fuel supply line and the second part of the inlet device with the second Fuel supply connected.
  • the fuel inlet the first part and the second part of the inlet devices independently of each other as desired.
  • the necessary for the desired distribution Pressure in the first and second fuel supply set.
  • there are thus different Amounts of fuel that exceed the first or the second inlet device are inserted, so that the entire fuel inlet of the desired distribution accordingly is set.
  • the inlet devices are radially in the premixing channel protruding tubes, inside which the fuel is supplied. These tubes then become out of the inlet openings the fuel is admitted into the premixing channel.
  • the inlet devices are radially in the Premix channel protruding swirl vanes, in the interior of the Fuel is supplied.
  • the inlet openings on the surface of the swirl vanes preferably in near a blade leading edge, arranged.
  • the swirl blades thus fulfill a dual function by the impart necessary swirl for combustion stabilization and also at the same time as an inlet device for the fuel act.
  • the first part of the inlet devices is off radially protruding into the premix tube and the second tube Part of the inlet devices from radially into the premixing channel protruding swirl vanes formed. It can be both the first Part and the second part of the inlet devices upstream arranged from the other part in the premix channel be.
  • the tubes are upstream of the swirl vanes arranged, resulting in a higher mixing of Fuel and combustion air when passing through the vortex grid leads. With increased security against a flashback but it may be cheaper, the tubes downstream to arrange the swirl vanes.
  • the burner is a gas turbine burner, in particular for a stationary gas turbine with a power greater than 50 MW.
  • a gas turbine has a compressor on, the air is highly compressed and fed to the burner.
  • the burner opens into a gas turbine combustor, in the the burner flame is included. That in the combustion chamber generated hot exhaust gas then flows into a turbine part, in the turbine blades are flowed around by the hot gas.
  • large stationary gas turbines are demanding in terms of low pollutant emissions and in terms of low tendency to form combustion oscillations posed.
  • the burner has a central, from Vormischkanal enclosed diffusion burner on.
  • the object directed to a method according to the invention solved by specifying a method for operating a gas turbine with a burner for burning a fuel in air, which burner is an annular Vormischkanal in which the fuel in a radial distribution is initiated, the radial distribution depending on the operating state of the gas turbine is set.
  • a radial distribution is set so that an area a local maximum in the radial distribution of the fuel concentration forms in the fuel-air mixture.
  • FIG. 1 shows a gas turbine 1.
  • the gas turbine 1 has a common turbine shaft 8 arranged a compressor 3 and a turbine part 7. Between compressor 3 and turbine part 7, an annular combustion chamber 5 is connected.
  • an annular combustion chamber 5 In the Annular combustion chamber 5 open around the circumference distributed a number of premix burners 9.
  • Premix burners 9 become air 11 supplied from the compressor 3 highly compressed.
  • Fuel 13 Air 11 and Fuel 13 are mixed and via the premix burner. 9 introduced into the combustion chamber 5, where it is a hot gas 15th to be burned.
  • FIG. 2 shows a premix burner 9. This is along an axis 10 directed.
  • the premix burner 9 has a annular Vormischkanal 21.
  • the premix channel 21 surrounds a central diffusion burner 23.
  • the premix channel 21 has an annular central surface 22, which in cross section forms an angle to the burner axis 10.
  • the premix channel 21 has a radially outer outer surface 18th and a radially inner inner surface 20.
  • an annular swirl lattice 25 which consists of individual Swirl vanes 26 is constructed.
  • fuel inlet tube 27 in the premix channel 21 are hollow and have inlet openings 29 on.
  • Air 11 passed through the premixing channel 21 In the burner of the prior art in Figure 2 is Air 11 passed through the premixing channel 21.
  • the air 11 flows past the fuel inlet tube 27.
  • the fuel inlet tube 27, fuel 13 is supplied to the interior, which from the inlet openings 29 into the air 11th exit.
  • the air 11 is above the swirl blades 26 in Twist lattice 25 gives a twist, which is a combustion stabilization serves.
  • the swirl vanes 26 are designed to that they also fuel 13 can be fed.
  • About not inlet openings on the surface of the Swirl blade 26 is also fuel 13 in the air 11th embedded in the premix channel 21.
  • Fuel 13 and air 11 are mixed in Vormischkanal 21 to a fuel-air mixture 28, which emerges from the premix burner 9 and burned there in a combustion zone.
  • premix combustion At a lean premix combustion, i. with relatively little fuel 13 in the air 11, such premix combustion tends to instabilities at the flame, i. it comes to fluctuations or even to extinguish the flame.
  • This combustion often becomes the central diffusion burner 21 used, which also air 11 and fuel 13 are supplied. These are, however, essentially first mixed in the combustion zone, with a is chosen fatter mixture. With the flame of the diffusion burner 23, premix combustion can be stabilized.
  • the premix burner 9 shown in FIG. 2 becomes fuel 13 in a fixed, static distribution in the premix channel 21 initiated.
  • Figure 3 shows a section of a longitudinal section through a premixing channel according to the prior art. It is a Section through a swirl blade 26 of the swirl lattice 25 shown. From an annular, radially inward, i. in the area the inner surface 20 of the Vormischkanals 21 is an annular Fuel supply line 41 is arranged. From this annular Fuel supply line 41 becomes fuel 13 the swirl vanes 26 supplied. The swirl vanes 26 are all the same Arrangement and the same opening cross-section at their inlet openings 29 on.
  • FIG. 4 shows in a section of a longitudinal section through the premixing channel 21 a comparison with Figure 3 changed arrangement, which becomes clear together with Figure 5.
  • FIG. 4 and FIG. 5 each show a section through two adjacent ones Swirl vanes 26, i.
  • FIG. 4 shows a first swirl blade 26 and Figure 5 an adjacent swirl blade 26th
  • the opening cross sections change the inlet openings 29, and indeed the opening cross sections in the direction of the inner surface 20th of premix channel 21, i. not in the direction of here illustrated axis 10, larger.
  • the opening cross sections the inlet openings 29 of the illustrated in Figure 5 Twist bucket 26 smaller in the same direction.
  • Inlet openings 29 are each followed by a swirl blade 26 with inlet openings 29, whose opening cross-sections downsize in the direction of the axis 10.
  • the swirl blades 26 of FIG. 4 form a first part 31 of inlet devices for the admission of fuel 13 in the Vormischkanal 21.
  • the swirl vanes 26 of Figure 5 form a second part 33 of inlet devices to the inlet of fuel 13 in the premixing channel 21.
  • FIGS. 6 and 7 show, like the inlet devices 31, 33 are supplied with the fuel 13.
  • the first part 31 the inlet device is made of an annular fuel supply line 43 supplied between the diffusion burner 23 and the premixing channel 21 is arranged.
  • the second Part 33 is a second, independent annular Fuel supply line 45 supplied with fuel 13.
  • the second annular fuel supply line 45 is the first fuel supply line 43 arranged immediately adjacent.
  • the radial distribution of the fuel 13 then changed be when a combustion vibration in the combustion chamber. 5 occurs that exceeds a certain threshold amplitude.
  • Such combustion vibrations may be due to flame instabilities and a feedback of pressure fluctuations and form dense fluctuations in the fuel-air mixture.
  • this feedback mechanism can be interrupted and suppress the combustion vibrations thereby become.
  • Figure 8 shows again in a section of a cross section through the Vormischkanal 21, the changing arrangement the first part 31 of inlet devices and the second one Part 33 of inlet devices each formed as Swirl vanes 26 in the swirl lattice 25.
  • FIG. 9 shows another possible configuration of the arrangement the first part 31 and the second part 33 of the inlet devices.
  • a section through a longitudinal section through the premix channel 21 points in the flow direction of the Air 11 arranged one behind the other, the first part 31 and the second part 33 of the inlet devices.
  • the first part 31 This is made up of tubes, which are in the Vormischkanal 21 protrude.
  • the second part 33 is made of swirl blades 26 educated.
  • the opening cross sections of the inlet openings 29 turn in opposite directions, i. towards the Increase axis 10 or toward the inner surface 20 the inlet openings 29 of the first part 31 of the inlet devices, while the opening cross sections of the inlet openings 29 of the second part 33 of the inlet device zoom out in the direction of the axis 10.
  • This axial Graduation of the first part 31 and the second part 33 of the Inlet devices may also fuel 13 in the circumferential direction be introduced very evenly in Vormischkanal 21.
EP03018408A 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz Withdrawn EP1507119A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP03018408A EP1507119A1 (fr) 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz
PCT/EP2004/008115 WO2005019733A1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz
EP04763360.7A EP1654496B1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz
JP2006522924A JP4430074B2 (ja) 2003-08-13 2004-07-20 バーナおよびガスタービンの運転方法
CNB2004800282182A CN100545517C (zh) 2003-08-13 2004-07-20 燃烧器和燃气轮机的运行方法
US10/568,120 US7654090B2 (en) 2003-08-13 2004-07-20 Burner and method for operating a gas turbine
ES04763360.7T ES2551440T3 (es) 2003-08-13 2004-07-20 Quemador y procedimiento para hacer funcionar una turbina de gas

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03018408A EP1507119A1 (fr) 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP1507119A1 true EP1507119A1 (fr) 2005-02-16

Family

ID=33560792

Family Applications (2)

Application Number Title Priority Date Filing Date
EP03018408A Withdrawn EP1507119A1 (fr) 2003-08-13 2003-08-13 Brûleur et méthode de fonctionnement d'une turbine à gaz
EP04763360.7A Not-in-force EP1654496B1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP04763360.7A Not-in-force EP1654496B1 (fr) 2003-08-13 2004-07-20 Bruleur et procede pour faire fonctionner une turbine a gaz

Country Status (6)

Country Link
US (1) US7654090B2 (fr)
EP (2) EP1507119A1 (fr)
JP (1) JP4430074B2 (fr)
CN (1) CN100545517C (fr)
ES (1) ES2551440T3 (fr)
WO (1) WO2005019733A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
EP1890083A1 (fr) * 2006-08-16 2008-02-20 Siemens Aktiengesellschaft Injecteur de carburant pour une turbine à gaz
EP1992878A1 (fr) * 2007-05-18 2008-11-19 Siemens Aktiengesellschaft Distributeur de combustible
EP2230458A1 (fr) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
EP2270398A1 (fr) * 2009-06-30 2011-01-05 Siemens Aktiengesellschaft Brûleur notamment pour turbines à gaz
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
DE102010027808A1 (de) * 2010-04-15 2011-10-20 Siemens Aktiengesellschaft Drallerzeuger für einen Brenner
DE102007004864C5 (de) * 2006-03-30 2014-09-25 Mitsubishi Heavy Industries, Ltd. Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
US9016601B2 (en) 2007-05-18 2015-04-28 Siemens Aktiengesellschaft Fuel distributor
DE102022106814A1 (de) 2022-03-23 2023-09-28 Dürr Systems Ag Jet-Brennervorrichtung

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JP4719059B2 (ja) * 2006-04-14 2011-07-06 三菱重工業株式会社 ガスタービンの予混合燃焼バーナー
KR100820233B1 (ko) * 2006-10-31 2008-04-08 한국전력공사 연소기 및 이를 포함하는 멀티 연소기, 그리고 연소방법
EP2107300A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Ensemble de tourbillonnement avec injecteur à gaz
US20100326079A1 (en) * 2009-06-25 2010-12-30 Baifang Zuo Method and system to reduce vane swirl angle in a gas turbine engine
DE102009038848A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brenner, insbesondere für Gasturbinen
US8276385B2 (en) * 2009-10-08 2012-10-02 General Electric Company Staged multi-tube premixing injector
DE102009045950A1 (de) * 2009-10-23 2011-04-28 Man Diesel & Turbo Se Drallerzeuger
EP2402652A1 (fr) * 2010-07-01 2012-01-04 Siemens Aktiengesellschaft Brûleur
US20120125004A1 (en) * 2010-11-19 2012-05-24 General Electric Company Combustor premixer
US9163841B2 (en) * 2011-09-23 2015-10-20 Siemens Aktiengesellschaft Cast manifold for dry low NOx gas turbine engine
US9052112B2 (en) * 2012-02-27 2015-06-09 General Electric Company Combustor and method for purging a combustor
WO2013128572A1 (fr) * 2012-02-28 2013-09-06 三菱重工業株式会社 Brûleur, et turbine à gaz
US20150316266A1 (en) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
EP2942565A1 (fr) * 2014-05-05 2015-11-11 Siemens Aktiengesellschaft Procédé de fonctionnement d'un système de brûleur
DE102018205874A1 (de) 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brenner mit selektiver Anpassung des Bohrungsmusters für die Gaseindüsung
CN113757719B (zh) * 2021-09-18 2023-05-05 北京航空航天大学 燃烧室燃烧振荡的控制方法及燃烧室

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EP0747636A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Chambre de combustion avec faible émissions pour turbines à gaz industrielles
US20010052229A1 (en) * 1998-02-10 2001-12-20 General Electric Company Burner with uniform fuel/air premixing for low emissions combustion
EP1193450A1 (fr) * 2000-09-29 2002-04-03 General Electric Company Mélangeur comprenant plusieurs vrilles

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GB2375601A (en) 2001-05-18 2002-11-20 Siemens Ag Burner apparatus for reducing combustion vibrations
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US5435126A (en) * 1994-03-14 1995-07-25 General Electric Company Fuel nozzle for a turbine having dual capability for diffusion and premix combustion and methods of operation
EP0747636A2 (fr) * 1995-06-05 1996-12-11 Allison Engine Company, Inc. Chambre de combustion avec faible émissions pour turbines à gaz industrielles
US20010052229A1 (en) * 1998-02-10 2001-12-20 General Electric Company Burner with uniform fuel/air premixing for low emissions combustion
EP1193450A1 (fr) * 2000-09-29 2002-04-03 General Electric Company Mélangeur comprenant plusieurs vrilles

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007004864C5 (de) * 2006-03-30 2014-09-25 Mitsubishi Heavy Industries, Ltd. Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
WO2007115989A1 (fr) * 2006-04-07 2007-10-18 Siemens Aktiengesellschaft Bruleur de turbine a gaz
EP1843098A1 (fr) * 2006-04-07 2007-10-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
US8596074B2 (en) 2006-04-07 2013-12-03 Siemens Aktiengesellschaft Gas turbine combustor
EP1890083A1 (fr) * 2006-08-16 2008-02-20 Siemens Aktiengesellschaft Injecteur de carburant pour une turbine à gaz
RU2470228C2 (ru) * 2007-05-18 2012-12-20 Сименс Акциенгезелльшафт Распределитель топлива
EP1992878A1 (fr) * 2007-05-18 2008-11-19 Siemens Aktiengesellschaft Distributeur de combustible
WO2008141955A1 (fr) * 2007-05-18 2008-11-27 Siemens Aktiengesellschaft Distributeur de combustible
US9016601B2 (en) 2007-05-18 2015-04-28 Siemens Aktiengesellschaft Fuel distributor
CN101688669B (zh) * 2007-05-18 2011-06-08 西门子公司 燃料分配器
EP2230458A1 (fr) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Agencement de brûleur pour combustibles liquides et procédé de fabrication d'un agencement de brûleur
WO2010105956A1 (fr) * 2009-03-17 2010-09-23 Siemens Aktiengesellschaft Dispositif de brûleur pour combustibles fluides et procédé de fabrication du dispositif de brûleur
WO2011000615A1 (fr) * 2009-06-30 2011-01-06 Siemens Aktiengesellschaft Brûleur, en particulier pour turbines à gaz
RU2533045C2 (ru) * 2009-06-30 2014-11-20 Сименс Акциенгезелльшафт Горелка, в частности, для газовых турбин
EP2270398A1 (fr) * 2009-06-30 2011-01-05 Siemens Aktiengesellschaft Brûleur notamment pour turbines à gaz
DE102009038845A8 (de) * 2009-08-26 2011-06-01 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
DE102010027808A1 (de) * 2010-04-15 2011-10-20 Siemens Aktiengesellschaft Drallerzeuger für einen Brenner
DE102022106814A1 (de) 2022-03-23 2023-09-28 Dürr Systems Ag Jet-Brennervorrichtung

Also Published As

Publication number Publication date
US20070031771A1 (en) 2007-02-08
JP4430074B2 (ja) 2010-03-10
WO2005019733A1 (fr) 2005-03-03
CN1860333A (zh) 2006-11-08
CN100545517C (zh) 2009-09-30
ES2551440T3 (es) 2015-11-19
EP1654496B1 (fr) 2015-08-26
JP2007501926A (ja) 2007-02-01
US7654090B2 (en) 2010-02-02
EP1654496A1 (fr) 2006-05-10

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