EP1510761A1 - Procédé de combustion d'un combustible fluide ainsi que brûleur, en particulier de turbine à gaz, pour la mise en oeuvre du procédé - Google Patents

Procédé de combustion d'un combustible fluide ainsi que brûleur, en particulier de turbine à gaz, pour la mise en oeuvre du procédé Download PDF

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Publication number
EP1510761A1
EP1510761A1 EP03018417A EP03018417A EP1510761A1 EP 1510761 A1 EP1510761 A1 EP 1510761A1 EP 03018417 A EP03018417 A EP 03018417A EP 03018417 A EP03018417 A EP 03018417A EP 1510761 A1 EP1510761 A1 EP 1510761A1
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EP
European Patent Office
Prior art keywords
fuel
burner
catalytic
reaction
flow
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Withdrawn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
EP03018417A
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German (de)
English (en)
Inventor
Bernd Dr. 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 EP03018417A priority Critical patent/EP1510761A1/fr
Priority to ES04763827.5T priority patent/ES2551930T3/es
Priority to US10/568,119 priority patent/US8540508B2/en
Priority to PCT/EP2004/008786 priority patent/WO2005019734A1/fr
Priority to JP2006522962A priority patent/JP4597986B2/ja
Priority to EP04763827.5A priority patent/EP1654497B1/fr
Publication of EP1510761A1 publication Critical patent/EP1510761A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • 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 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • F23C13/08—Apparatus in which combustion takes place in the presence of catalytic material characterised by the catalytic material
    • 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
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Definitions

  • the invention relates to a method for the combustion of a fluid fuel, in which fuel in a catalytic Reaction implemented and then catalytically prereacted Fuel burned in a secondary reaction becomes.
  • the invention further relates to a burner for combustion a fluidic fuel, wherein in the flow direction of the fuel in a flow channel before the Fuel outlet of a main burner of the fuel outlet a catalytic burner under catalytic conversion of the fuel is arranged.
  • the invention further relates a combustion chamber having such a burner and a gas turbine with such a combustion chamber.
  • Fuel oil and / or heating gas to be understood as he especially for gas turbines application finds. Under heating oil are doing all combustible liquids, eg. Petroleum, Methanol etc., and under fuel gas all combustible gases, eg. B. Natural gas, coal gas, syngas, biogas, propane, butane etc. Understood. Such burners with catalytic reaction are for example, in document EP-A-491 481.
  • a gas turbine usually consists of a compressor part, a Burner part and a turbine part.
  • the compressor part and the turbine part are usually located on a common Wave, which at the same time a generator for electricity generation drives.
  • In the compressor part is preheated Fresh air to the pressure required in the burner part compacted.
  • In the burner part is the compressed and preheated Fresh air with a fuel such.
  • the hot burner exhaust gas is the turbine part fed and relaxed work there.
  • the flame temperature or Flammentemperatur spitzenabsenkung in the burner part as nitrogen oxide-reducing.
  • This is the fuel gas or the compressed and preheated fresh air steam fed or injected water into the combustion chamber.
  • Such Measures that a nitric oxide emissions of the gas turbine per se Reduce, are considered primary measures for nitrogen oxide reduction designated. Accordingly, all are considered secondary Measures designated, in which once in the exhaust gas of a Gas turbine - or in general a combustion process - contained nitrogen oxides by subsequent measures be reduced.
  • One application of a catalytic process is disclosed, for example, in EP 0 832 397 B1, which shows a catalytic gas turbine combustor.
  • a portion of the fuel gas is withdrawn through a conduit system, passed through a catalytic stage and then fed back to the fuel gas to lower its catalytic ignition temperature.
  • the catalytic stage is in this case designed as a preforming stage, which comprises a catalyst system which is provided for the conversion of a hydrocarbon contained in the fuel gas into an alcohol and / or an aldehyde or H 2 and CO.
  • EP 0 832 399 B1 discloses a burner for combustion a fuel, wherein in the direction of flow of the fuel in a flow channel in front of the fuel outlet a main burner of the fuel outlet of a catalytic Support burner for stabilizing the main burner under catalytic Combustion of a pilot fuel stream provided is. This is based on the cross section of the flow channel for the fuel the catalytic support burner centrally and the main burner coronary arranged.
  • catalytic combustion systems exist this consists of a catalyst arranged axially is.
  • the catalyst only part of the fuel is in the energy released, causing stabilization the burnout of the remaining part of the chemically bound Energy in the axial direction downstream of the catalyst in a combustion chamber is improved.
  • This main reaction sets after a certain time, the so-called autoignition-time, one that is essentially dependent on the temperature and the Gas composition depends on the catalyst outlet.
  • the object of the invention is a method for combustion to enter a fluidic fuel with which a as complete as possible implementation of the fluidic fuel achievable with low pollutant emissions.
  • a Another object of the invention is to specify a Burner, in particular for a gas turbine, the Implementation of the method is suitable.
  • the object directed to a method according to the invention solved by a method for burning a fluidic Fuel, in which fuel in a catalytic reaction reacted and then catalytically prereacted Fuel is further burned in an after-reaction, wherein the vorreag faced fuel a swirl component, imprinted becomes.
  • the invention is based on the knowledge that the Afterreaction does not start until after a certain period of time Essentially of the temperature and gas composition the reaction products after the catalytic reaction depends.
  • the post-reaction which is related to the catalytic reaction connects, should thereby under as complete as possible Implementation in heat.
  • the fuel in the After-reaction continues to be burned, this must be complete burn out, with carbon monoxide and hydrocarbons in the Exhaust gas must be avoided.
  • the invention is based on the consideration that z. B. liquid fuels, such as fuel oil, which are not safe or only insufficiently reacted in a catalytic reaction can, usually in a limited existing Reaction volume can not be made to burn out, unless aerodynamic stabilization takes place. Also with practicable existing dimensions is the Problem given that even with partial catalytic conversion the after deduction of auto-ignition available Reaction times for the post-reaction are too small to be COfree to burn.
  • a fluidic Fuel may also preferably be a fuel-air mixture which is obtained by the fluidic Fuel with combustion air to the fuel-air mixture is mixed, which is catalytically reacted.
  • the pre-reacted fuel or a pre-reacted fuel-air mixture from the catalytic reaction is imparted a swirl component.
  • the pre-reacted is swirly Fuel for after-reaction in a combustion chamber, wherein a rotary flow is formed.
  • a spatially Controlled ignition of the post-reaction in the combustion chamber brought about.
  • the residence time can be adjusted by adjusting the Dralls and the resulting confectioning of the Rotational flow in terms of magnitude and direction of the fuel flow, be set. That way is at least on average, based on a residence time distribution the swirling reaction products of the catalytic Reaction, the Edzündzeittician spatially well fixable and thus a sufficient stabilization of the burnout for the Afterreaction ensured.
  • a gaseous fuel or a liquid fuel in particular Heating gas or fuel oil, burned.
  • the second mentioned, directed to a burner task is solved according to the invention by a burner for combustion a fluidic fuel, wherein in the flow direction of the fuel in a flow channel in front of the fuel outlet a main burner of the fuel outlet of a catalytic Burner under catalytic conversion of the fuel is arranged, wherein the catalytic burner a Number of catalytically active elements having such are arranged, that in the flow channel a rotary flow formed.
  • the flow direction of the fuel in the flow channel refers In this case, the axial flow direction along the Flow channels through a longitudinal axis of the Flow channel is set. Which is under the arrangement the catalytically acting elements forming rotary flow is as a rotary flow or swirling flow around the Flow direction or main flow direction of the fuel to understand in the flow channel.
  • a rotary flow or Swirl flow in the wake of the catalytically active elements is the fluidic fuel targeted a swirl component imprinted so that a (mean) circumferential velocity component is generated and the axial Velocity component along the longitudinal axis, that is along the flow direction of the fuel in the Flow channel, according to the swirling through the geometric arrangement of the catalytically active elements reduced.
  • the catalytic acting elements in a plane perpendicular to the flow direction arranged, wherein the fuel outlet of the catalytic acting elements in the flow channel opens. It is possible that a variety of catalytic acting elements along a circumference in the plane are arranged perpendicular to the flow direction, wherein in each case through the direction of the confluence of the fuel outlets a tangential component in the inflow into the Flow channel is achievable.
  • the catalytically active elements which in their entirety the catalytic burner to the catalytic Implementation of the fuel can form the rotary flow in be prepared in a predetermined manner, so that in the Combustion gives a desired residence time distribution, the a spatially controlled ignition of a homogeneous non-catalytic Afterreaction allows.
  • the system can advantageously be arranged so that as needed when using a z.
  • liquid Fuel also a conventional, that is non-catalytic Combustion, is adjustable.
  • the burner especially suitable for liquid fuels, and overcomes thus the disadvantage of previous catalytic combustion systems, especially for gas turbines, which are only available as single-fuel burners are known for gaseous fuels.
  • the axial length of the Flow channels adapted accordingly.
  • the burner is particularly flexible adaptable to the after a certain time (autoignition-time) onset main reaction in the main burner, which in the Essentially of the temperature and the gas composition at Fuel outlet of the catalytic burner depends and the as a post-reaction of the upstream catalytic Reaction takes place. Because of this targeted customization is a complete implementation in the main reaction possible.
  • a catalytically active Element designed as a honeycomb catalyst
  • the basic component at least one of the substances titanium dioxide, silicon dioxide and zirconia.
  • a noble metal or metal oxide which has an oxidizing effect on the fluidic fuel.
  • precious metals such as platinum, Rhodium, rhenium, iridium and metal oxides, such as.
  • metal ion zeolites can also be used and metal oxides of spinel type may be used.
  • honeycomb structure of the catalytic Acting elements as these through a variety of along an axis of the catalytic element extending channels is formed. This favors the catalytic Reaction due to the increase of the catalytically active Surface through the channels and on the other hand, a flow equalization within the honeycomb catalyst, so that a well-defined outflow of the catalytic pre-reacted fuel from the fuel outlet reached is, in accordance with defined manner a Spin component causes when entering the flow channel is.
  • the burner is according to the invention provided in a combustion chamber.
  • the combustion chamber comprises a combustion chamber, in which the burner preferably protrudes with the fuel outlet of the main burner or opens.
  • the combustion chamber is sufficiently dimensioned, so that a homogeneous, preferably non-catalytic Main reaction started and in the Combustion chamber a complete burnout of the fuel and so that maximum conversion into combustion heat is achieved.
  • such a combustion chamber is suitable for Use in a gas turbine, with one in the combustion chamber generated hot combustion gas to drive a Turbine part of the gas turbine is used.
  • the gas turbine according to FIG. 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive of the compressor 2 and a non-illustrated Generator or a working machine. These are the turbine 6 and the compressor 2 on a common, as well Turbine rotor designated turbine shaft 8 arranged with which is also connected to the generator or the working machine is, and which is rotatably mounted about its central axis 9.
  • the in the manner of an annular combustion chamber running combustion chamber. 4 is with a number of burners 10 for burning a liquid or gaseous fuel.
  • the burner 10 is configured as a catalytic combustion system and for a catalytic as well as a non-catalytic combustion reaction or combinations thereof. Of the Structure and operation of the burner 10 should be related to be discussed in more detail with Figures 2 and 3.
  • the turbine 6 has a number of with the turbine shaft. 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 includes a number of stationary vanes 14, which is also coronal under the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the turbine. 6 flowing through hot medium, the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between each two in the flow direction of the Working medium seen consecutive blade rows or blade boundaries.
  • a successive pair from a ring of vanes 14 or a row of guide vanes and from a wreath of bucket 12 or one Blade row is also referred to as a turbine stage.
  • Each vane 14 also has one as a blade root designated platform 18, which is for fixing the respective Guide vane 14 on the inner housing 16 of the turbine as a wall element is arranged.
  • the platform 18 is a thermal, comparatively heavily loaded component that the Outer boundary of a hot gas duct for the turbine 6 flowing through working medium M forms. Every blade is in an analogous manner via a so-called blade root Platform attached to the turbine shaft.
  • Between the spaced spaced platforms 18 of the vane 14 of two adjacent rows of vanes is respectively a guide ring 21 on the inner housing 16 of the turbine. 6 arranged.
  • each guide ring 21 is while also the hot, the turbine 6 flowing through Working medium M exposed and in the radial direction of outer end 22 of the blade 12 opposite it spaced by a gap.
  • the between adjacent Leitschaufelschschschitzschitzschitzschitzschitzschitzered guide rings 21 serve in particular as cover elements, the inner wall 16 or other housing mounting parts from thermal overload by the turbine 6 flowing through the hot Protect working medium M
  • the combustion chamber 4 is of a Combustion chamber housing 29 limited, wherein the combustion chamber side a Combustion chamber wall 24 is formed.
  • the combustion chamber 4 designed as a so-called annular combustion chamber, in the case of a plurality of circumferentially around the turbine shaft 8 around arranged burner in a common Combustor chamber or combustion chamber 27 open.
  • the burner 10th delivered and mixed into a fuel-air mixture and burned.
  • Combustion is the burner 10 as a catalytic combustion system designed with the a complete implementation of the fuel B is reached. That from the combustion process resulting hot gas, the working medium M, points comparatively high temperatures from 1000 ° C up to 1500 ° C on, to a correspondingly high efficiency of the gas turbine 1 to achieve.
  • the combustion chamber 4 for accordingly high temperatures designed. Even with these, for the materials unfavorable operating parameters a comparatively To allow high operating life, the combustion chamber wall 24th on its side facing the working medium M side with a Heat shield elements 26 formed combustion chamber lining Mistake. Due to the high temperatures inside the Combustion chamber 4 is also a for the heat shield elements 26 a not shown in detail cooling system provided.
  • the coming in the combustion chamber 4 of the gas turbine 1 used Burner 10 according to the invention is shown in FIG highly simplified sectional view presented to the underlying lying catalytic combustion concept as an example to explain.
  • the burner 10 for combustion of the fluidic Fuel B has a catalytic burner 35A, 35B and a main burner 37.
  • the main burner 37 includes a first flow channel 31A and a first flow channel concentrically surrounding the second flow channel 31B.
  • the catalytic burner 35A is the first flow channel 31A and the catalytic burner 35B assigned to the second flow channel 31B.
  • the flow channel 31A, 31B extends along a main thing or flow direction 33.
  • Catalytic burner 35A is catalytic acting elements 43C, 43D.
  • the catalytic burner 35B has catalytic elements 43A, 43B.
  • the catalytic acting elements 43A, 43B, 43C, 43D are e.g. when Honeycomb catalysts designed, consisting of a Basic component and a catalytically active component exist, wherein the catalytically active component a oxidizing effect on the fluidic fuel B exerts.
  • the catalytic elements 43A, 43B are in Fluid communication with the flow channel 31B, while the catalytically active elements 43C, 43D in fluid communication stand with the flow channel 31A.
  • the main burner 37 is along the flow direction 33 of the fuel B to the fuel outlet 41 of the catalytic burner 35A, 35B arranged and via the flow channel 31A, 31B with the catalytic burner 35A, 35B in fluid communication.
  • the Main burner 37 has a fuel outlet 39.
  • the catalytic burner 35A, 35B serves for the catalytic conversion or partial conversion of the Fuel B and sets a catalytic pre-reaction in Gang, after a auto-ignition time (autoignition-time) a Ignition of the prereacted fuel B in the main burner 37 causes. This leads to a stabilization of the burnout and to complete the burnout in a burnout zone 45, in the vicinity of the fuel outlet 39 of the Main burner 37 is formed.
  • the length L of the flow channel 31A, 31B is adapted, in particular to the reaction times to be considered and Flow rates of the fuel B.
  • the catalytic acting elements 43A, 43B, 43C, 43D are arranged such in that a rotary flow is formed in the flow channel 31A, 31B. This forms in the wake of the catalytically active Elements 43A, 43B, 43C, 43D after their fuel outlet 41 off.
  • FIG. 3 shows a view along the flow direction 33 of the burner 10 shown in Figure 2, the catalytic acting elements 43A, 43B are in a plane perpendicular to Flow direction 33 is arranged, wherein the fuel outlet 41 of the catalytic elements 43A, 43B in the Flow channel 31 B opens.
  • Analogous are the catalytic acting elements 43C, 43D in a plane perpendicular to Flow direction 33 is arranged, wherein the fuel outlet 41 of the catalytic elements 43C, 43D in the Flow channel 31A opens.
  • the catalytic burners 35A, 35B are along the flow direction 33 to each other spaced apart.
  • the pre-reacted fuel B a spin component is impressed. This is the pre-reacted swirling fuel B for post-reaction in a Ausbrandzone 45 transferred, wherein the rotational flow in the Flow channel 31A, 31B is formed.
  • By setting the residence time of the prereacted fuel B for the transfer becomes a spatially controlled ignition of the after-reaction brought about in the burn-out zone 45.
  • FIG. 3 shows two catalytic burners 35A, 35B with one respective flow channel 31A, 31B fluidically connected.
  • a realization of the invention can also through a burner 10 with only one catalytic burner 35A and a flow channel 31A associated therewith or with a plurality of such burners and associated flow channels.
  • the burner 10 of the Invention is first for a on a catalytic Combustion process based combustion system Operation with different fluidic fuels B possible. That means both liquid and gaseous Fuels B come into consideration.
  • the burner 10th z. B. when using a liquid fuel, for. B. Heating oil, if necessary, also in a conventional Operated with non-catalytic combustion which increases flexibility.
  • the liquid Combustion air fuel to a fuel-air mixture mixed.
  • the combustion air is preferably previously imprinted a swirl component, such as by Supply of combustion air through the swirl-inducing Catalyst elements or other swirl elements.
  • a swirl component such as by Supply of combustion air through the swirl-inducing Catalyst elements or other swirl elements.
  • the Combustion air will then be downstream of the swirl-inducing Catalyst elements a liquid fuel zugedüst.
  • a fuel-air mixture by Mixture of a fluidic, in particular liquid, Fuel can be generated with combustion air, which in a catalytic reaction at least partially implemented and then the catalytically pre-reacted fuel-air mixture is further burned, the pre-reacted Fuel-air mixture a swirl component is impressed.
  • the burner according to the invention can - depending on Fuel selection - under flow of the catalytic acting elements with a fluid fuel or Fuel-air mixture or - in particular at Liquid fuels - passing through combustion air and subsequent Zudüsung the liquid fuel operated become.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Exhaust Gas After Treatment (AREA)
  • Feeding And Controlling Fuel (AREA)
EP03018417A 2003-08-13 2003-08-13 Procédé de combustion d'un combustible fluide ainsi que brûleur, en particulier de turbine à gaz, pour la mise en oeuvre du procédé Withdrawn EP1510761A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP03018417A EP1510761A1 (fr) 2003-08-13 2003-08-13 Procédé de combustion d'un combustible fluide ainsi que brûleur, en particulier de turbine à gaz, pour la mise en oeuvre du procédé
ES04763827.5T ES2551930T3 (es) 2003-08-13 2004-08-05 Método para la combustión de un combustible fluido, así como quemador, en particular para una turbina de gas, para ejecutar el método
US10/568,119 US8540508B2 (en) 2003-08-13 2004-08-05 Method for the combustion of a fluid fuel, and burner, especially of a gas turbine, for carrying out said method
PCT/EP2004/008786 WO2005019734A1 (fr) 2003-08-13 2004-08-05 Procede de combustion d'un combustible fluide, et bruleur conçu en particulier pour une turbine a gaz et servant a la mise en oeuvre dudit procede
JP2006522962A JP4597986B2 (ja) 2003-08-13 2004-08-05 流体燃料のバーナ
EP04763827.5A EP1654497B1 (fr) 2003-08-13 2004-08-05 Procede de combustion d'un combustible fluide, et bruleur, en particulier de turbine a gaz, servant a la mise en oeuvre dudit procede

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03018417A EP1510761A1 (fr) 2003-08-13 2003-08-13 Procédé de combustion d'un combustible fluide ainsi que brûleur, en particulier de turbine à gaz, pour la mise en oeuvre du procédé

Publications (1)

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EP1510761A1 true EP1510761A1 (fr) 2005-03-02

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EP03018417A Withdrawn EP1510761A1 (fr) 2003-08-13 2003-08-13 Procédé de combustion d'un combustible fluide ainsi que brûleur, en particulier de turbine à gaz, pour la mise en oeuvre du procédé
EP04763827.5A Not-in-force EP1654497B1 (fr) 2003-08-13 2004-08-05 Procede de combustion d'un combustible fluide, et bruleur, en particulier de turbine a gaz, servant a la mise en oeuvre dudit procede

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP04763827.5A Not-in-force EP1654497B1 (fr) 2003-08-13 2004-08-05 Procede de combustion d'un combustible fluide, et bruleur, en particulier de turbine a gaz, servant a la mise en oeuvre dudit procede

Country Status (5)

Country Link
US (1) US8540508B2 (fr)
EP (2) EP1510761A1 (fr)
JP (1) JP4597986B2 (fr)
ES (1) ES2551930T3 (fr)
WO (1) WO2005019734A1 (fr)

Cited By (1)

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Publication number Priority date Publication date Assignee Title
US7568907B2 (en) 2005-12-22 2009-08-04 Alstom Technology Ltd. Combustion chamber with burner and associated operating method

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SE530775C2 (sv) * 2007-01-05 2008-09-09 Zemission Ab Värmeanordning för katalytisk förbränning av vätskeformiga bränslen samt en spis innefattande en sådan värmeanordning
EP2154428A1 (fr) * 2008-08-11 2010-02-17 Siemens Aktiengesellschaft Insert d'une buse à combustible
JP6190670B2 (ja) * 2013-08-30 2017-08-30 三菱日立パワーシステムズ株式会社 ガスタービン燃焼システム
CN104949154B (zh) * 2015-03-11 2017-10-31 龚雨晋 实现定容燃烧的装置及包括该装置的动力系统

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Publication number Priority date Publication date Assignee Title
US7568907B2 (en) 2005-12-22 2009-08-04 Alstom Technology Ltd. Combustion chamber with burner and associated operating method
DE102005061486B4 (de) * 2005-12-22 2018-07-12 Ansaldo Energia Switzerland AG Verfahren zum Betreiben einer Brennkammer einer Gasturbine

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WO2005019734A1 (fr) 2005-03-03
EP1654497B1 (fr) 2015-09-30
JP4597986B2 (ja) 2010-12-15
US20060260322A1 (en) 2006-11-23
US8540508B2 (en) 2013-09-24
ES2551930T3 (es) 2015-11-24
JP2007501928A (ja) 2007-02-01
EP1654497A1 (fr) 2006-05-10

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