EP1654497A1 - Procede de combustion d'un combustible fluide, et bruleur con u en particulier pour une turbine a gaz et servant a la mise en oeuvre dudit procede - Google Patents

Procede de combustion d'un combustible fluide, et bruleur con u en particulier pour une turbine a gaz et servant a la mise en oeuvre dudit procede

Info

Publication number
EP1654497A1
EP1654497A1 EP04763827A EP04763827A EP1654497A1 EP 1654497 A1 EP1654497 A1 EP 1654497A1 EP 04763827 A EP04763827 A EP 04763827A EP 04763827 A EP04763827 A EP 04763827A EP 1654497 A1 EP1654497 A1 EP 1654497A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
catalytic
reaction
flow channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP04763827A
Other languages
German (de)
English (en)
Other versions
EP1654497B1 (fr
Inventor
Bernd Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP04763827.5A priority Critical patent/EP1654497B1/fr
Publication of EP1654497A1 publication Critical patent/EP1654497A1/fr
Application granted granted Critical
Publication of EP1654497B1 publication Critical patent/EP1654497B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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 fluidic fuel, in which fuel is converted in a catalytic reaction and subsequently catalytically pre-reacted fuel is burned further in a post-reaction.
  • the invention further relates to a burner for the combustion of a fluidic fuel, in which the fuel outlet of a catalytic burner with catalytic conversion of the fuel is arranged in a flow channel in the flow direction of the fuel in front of the fuel outlet of a main burner.
  • the invention further relates to a combustion chamber having such a burner and a gas turbine with such a combustion chamber.
  • a fluidic fuel is to be understood below to mean, in particular, heating oil and / or heating gas, as is used in particular for gas turbines.
  • All flammable liquids e.g. B. petroleum, methanol, etc.
  • all flammable gases for. B. natural gas, coal gas, synthesis gas, biogas, propane, butane, etc. understood.
  • Such burners with a catalytic reaction are shown, for example, in document EP-A-491 481.
  • Burner systems of this type are also suitable for applications in turbomachinery, such as gas turbines.
  • 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 shaft, which at the same time drives a generator for generating electricity.
  • preheated fresh air is compressed to the pressure required in the burner section.
  • the compressed and pre- warmed fresh air with a fuel such as B. burned natural gas or heating oil.
  • the hot burner exhaust gas is fed to the turbine section and expanded there while performing work.
  • the reduction in flame temperature or flame temperature in the burner section has a nitrogen oxide-reducing effect.
  • steam is supplied to the fuel gas or the compressed and preheated fresh air or water is injected into the combustion chamber.
  • Measures which reduce nitrogen oxide emissions per se from the gas turbine are referred to as primary measures for reducing nitrogen oxides. Accordingly, all measures are referred to as secondary measures in which nitrogen oxides contained in the exhaust gas of a gas turbine - or in general a combustion process - are reduced by subsequent measures.
  • An application of a catalytic process is disclosed for example in EP 0 832 397 B1, which shows a catalytic gas turbine burner. Part of the fuel gas is drawn off through a line system, passed through a catalytic stage and then fed back to the fuel gas to lower its catalytic ignition temperature.
  • the catalytic stage is designed as a preforming stage, which comprises a catalyst system which is provided for converting 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 combusting a fuel, in which, in the direction of flow of the fuel in a flow channel in front of the fuel outlet of a main burner, the fuel outlet of a catalytic auxiliary burner for stabilizing the main burner under ca talytical combustion of a pilot fuel stream is provided.
  • the catalytic auxiliary burner is arranged centrally and the main burner is arranged coronary.
  • the catalytic combustion systems described above consist of a catalyst which is arranged axially. Only a part of the energy contained in the fuel is released in the catalytic converter, which improves the stabilization of the burnout of the remaining part of the chemically bound energy in the axial direction downstream of the catalytic converter in a combustion chamber. This main reaction begins after a certain time, the so-called autoignition- ti e, which essentially depends on the temperature and the gas composition at the catalyst outlet.
  • the object of the invention is to enter a method for the combustion of a fluidic fuel, with which the most complete possible conversion of the fluidic fuel can be achieved with low pollutant emissions.
  • Another object of the invention is to provide a burner, in particular for a gas turbine, which is suitable for carrying out the method.
  • the object directed to a method is achieved according to the invention by a method for the combustion of a fluidic fuel, in which fuel is converted in a catalytic reaction and then catalytically prereacted fuel is further burned in a post-reaction, with a swirl component being impressed on the prereacted fuel.
  • the invention is based on the knowledge that the after-reaction only begins after a certain time, which essentially depends on the temperature and the gas composition of the reaction products after the catalytic reaction.
  • the post-reaction that follows the catalytic reaction should take place with the most complete possible conversion into heat.
  • the invention is based on the consideration that z. B. liquid fuels, such as heating oil, which can not be safely or insufficiently implemented in a catalytic reaction, can generally not be burned out in a limited reaction volume, unless aerodynamic stabilization takes place. With practically existing dimensions, there is also the problem that even with catalytic partial conversion, the reaction times available after deduction of the autoignition time are too short for the after-reaction to burn without CO.
  • a fluidic fuel can preferably also be a fuel-air Be mixture that is obtained by mixing the fluid fuel with combustion air to the fuel-air mixture, which is catalytically reacted.
  • a swirl component be applied to the pre-reacted fuel or a pre-reacted fuel-air mixture from the catalytic reaction. The swirl of the pre-reacted fuel ensures that the fuel escaping from the catalytic reaction has more reaction time available than with a swirl-free, ie purely axial
  • Reaction coordinate of the conventional catalytic combustion systems was the case. Because of the swirl, the pre-reacted fuel will achieve the autoignition time - viewed in an axial coordinate - over a significantly reduced distance, because the swirl reduces the axial speed component of the pre-reacted fuel and causes a peripheral speed component induced by the swirl, and above all a backflow zone is produced. This means that there is sufficient reaction volume available for the post-reaction in which the pre-reacted fuel continues to be burned, so that the fuel can be completely burnt out without any significant increase in the axial installation space of the combustion system.
  • the pre-reacted swirling fuel is transferred to a combustion chamber for the after-reaction, a rotary flow being formed.
  • a spatially controlled ignition of the after-reaction in the combustion chamber is preferably brought about by setting the residence time of the pre-reacted fuel for the transfer.
  • the dwell time can be adjusted by adjusting the swirl and the resulting assembly of the rotary flow with regard to the amount and direction of the fuel flow.
  • the auto-ignition point can be fixed spatially well, and thus a sufficient stabilization of the burnout for the after-reaction is ensured.
  • a homogeneous non-catalytic after-reaction is preferably ignited as the after-reaction.
  • The is further preferred
  • a catalytic pre-reaction is advantageously combined with a non-catalytic post-reaction, the spatially controlled ignition of the homogeneous non-catalytic post-reaction being ensured by the swirl component of the catalytically pre-reacted fuel or, if necessary, liquid fuel injected stramab away from the catalyst.
  • a gaseous fuel or a liquid fuel in particular heating gas or heating oil, is burned as the fluid fuel.
  • the second-mentioned object directed to a burner is achieved according to the invention by a burner for the combustion of a fluidic fuel, in which the fuel outlet of a catalytic burner is arranged in the flow direction of the fuel in a flow channel in front of the fuel outlet of a main burner with catalytic conversion of the fuel, the catalytic one Burner has a number of catalytically active elements which are arranged such that a rotary flow is formed in the flow channel.
  • the flow direction of the fuel in the flow channel here designates the axial flow direction along the flow channel, which is defined by a longitudinal axis of the
  • the three-way flow which forms under the arrangement of the catalytically active elements is to be understood as a three-way flow or swirled flow around the flow direction or main flow direction of the fuel in the flow channel.
  • the rotary flow is preferably formed in the wake of the catalytically active elements after their fuel outlet, for example by the fuel outlet opening into the flow channel perpendicular to a longitudinal axis of the flow channel, the fuel outlet being arranged offset with respect to the longitudinal axis, so that a swirl is generated .
  • a swirl component is deliberately impressed on the fluidic fuel, so that a (mean) peripheral speed component is generated and the axial speed component along the longitudinal axis, that is, along the flow direction of the fuel in the flow channel, is reduced according to the swirl by the geometric arrangement of the catalytically active elements.
  • the catalytically active elements are arranged in a plane perpendicular to the direction of flow, the fuel outlet of the catalytically active elements opening into the flow channel. It is possible here for a multiplicity of catalytically active elements to be arranged along a circumference in the plane perpendicular to the direction of flow, with a tangential component in each case in the direction of the confluence of the fuel outlets
  • the rotary flow can be assembled in a predetermined manner, so that there is a desired residence time distribution in the combustion chamber, which ensures spatially controlled ignition of a homogeneous non-catalytic after-reaction enabled.
  • the system can advantageously also be arranged so that, if necessary, when using a z. B. liquid
  • a conventional, ie non-catalytic combustion, fuel can also be set.
  • the burner is therefore also particularly suitable for liquid fuels and thus overcomes the disadvantage of previous catalytic combustion systems, in particular for gas turbines, which are only known as single-fuel burners for gaseous fuels.
  • the axial length of the flow channel is preferably adapted accordingly to set a predetermined residence time of fuel in the flow channel.
  • the burner can thus be adapted particularly flexibly to the main reaction in the main burner that begins after a certain time (autoignition time), which essentially depends on the temperature and the gas composition at the fuel outlet of the catalytic burner and which takes place as a post-reaction of the upstream catalytic reaction. Due to this targeted adjustment, a complete implementation in the main reaction is possible.
  • Element designed as a honeycomb catalyst which has at least one of the substances titanium dioxide, silicon dioxide and zirconium oxide as a basic component.
  • the honeycomb catalyst furthermore preferably has a noble metal or metal oxide as catalytically active component, which has an oxidizing effect on the fluid fuel.
  • a noble metal or metal oxide as catalytically active component, which has an oxidizing effect on the fluid fuel.
  • noble metals such as platinum, rhodium, rhenium, iridium and metal oxides, such as. B. the transition metal oxides vananadium oxide, tungsten oxide, molybdenum oxide, chromium oxide, copper oxide, manganese oxide and oxides of lananoids, such as. B. cerium oxide.
  • metal ion zeolites and metal oxides of the spinel type can also be used.
  • the honeycomb structure of the catalytically active elements proves to be particularly advantageous since it is formed by a plurality of channels extending along an axis of the catalytically active element. This favors the catalytic reaction due to the increase in 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 catalytically prereacted fuel from the fuel outlet is achieved, with a swirl component at the inlet in a correspondingly defined manner is effected in the flow channel.
  • the burner according to the invention is provided in a combustion chamber.
  • the combustion chamber comprises a combustion chamber, into which the burner preferably projects or opens with the fuel outlet of the main burner.
  • the combustion chamber is dimensioned sufficiently so that a homogeneous, preferably non-catalytic main reaction is started and in the combustion chamber a complete burnout of the fuel and thus maximum conversion into heat of combustion is achieved.
  • Such a combustion chamber is preferably suitable for use in a gas turbine, a hot combustion gas generated in the combustion chamber being used to drive a turbine part of the gas turbine.
  • FIG. 1 shows a half section through a gas turbine
  • Figure 2 is a sectional view of a simplified representation of a burner according to the invention.
  • Figure 3 shows the burner shown in Figure 2 in a view in the main flow direction of the fuel.
  • the gas turbine according to FIG. 1 has a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 for driving the compressor 2 and one not shown in more detail Generator or a work machine.
  • the turbine 6 and the compressor 2 are arranged on a common turbine shaft 8, also referred to as a turbine rotor, to which the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4, which is designed as an annular combustion chamber, is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the burner 10 is designed as a catalytic combustion system and is designed for a catalytic and a non-catalytic combustion reaction or combinations thereof. The structure and the mode of operation of the burner 10 are to be discussed in more detail in connection with FIGS. 2 and 3.
  • the turbine 6 has a number of rotatable rotor blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of fixed guide vanes 14, which are also ring-shaped with the formation of
  • Guide vane rows are attached to an inner housing 16 of the turbine 6.
  • the rotor blades 12 serve to drive the turbine shaft 8 by transferring momentum from the hot medium flowing through the turbine 6, the working medium M.
  • the guide blades 14, serve to guide the flow of the working medium M between two successive rows of rotor blades or rotor blade limits, as seen in the flow direction of the working medium.
  • a successive pair of a ring of guide vanes 14 or a row of guide vanes and a ring of rotor blades 12 or a row of rotor blades is also referred to as a turbine stage.
  • Each guide vane 14 has a platform 18, also referred to as a blade root, which is arranged as a wall element for fixing the respective guide vane 14 to the inner casing 16 of the turbine.
  • the platform 18 is a thermal, comparatively heavily loaded component that defines the outer boundary of a hot gas duct for the turbine 6 flowing through working medium M forms.
  • Each rotor blade is attached to the turbine shaft in an analogous manner via a platform, also referred to as a blade root.
  • a guide ring 21 is arranged on the inner casing 16 of the turbine 6 between the spaced-apart platforms 18 of the guide vane 14 of two adjacent rows of guide vanes.
  • each guide ring 21 is also exposed to the hot working medium M flowing through the turbine 6 and is spaced in the radial direction from the outer end 22 of the rotor blade 12 opposite it by a gap.
  • the guide rings 21 arranged between adjacent rows of guide blades serve in particular as cover elements which protect the inner wall 16 or other housing installation parts against thermal overloading by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is delimited by a combustion chamber housing 29, a combustion chamber wall 24 being formed on the combustion chamber side.
  • the combustion chamber 4 is designed as a so-called annular combustion chamber, in which a plurality of burners arranged in the circumferential direction around the turbine shaft 8 open into a common combustion chamber or combustion chamber 27.
  • the combustion chamber 4 is configured in its entirety as an annular structure which is positioned around the turbine shaft 8.
  • a fluid fuel B and combustion air A are fed to the burner 10 and mixed and burned to form a fuel-air mixture.
  • burner 10 is designed as a catalytic combustion system with which a complete conversion of fuel B can be achieved.
  • the hot gas resulting from the combustion process, the working medium M has comparatively high temperatures of 1000 ° C. to 1500 ° C. in order to achieve a correspondingly high efficiency of the gas turbine 1.
  • the combustion chamber 4 is appropriate designed for high temperatures.
  • the combustion chamber wall 24 is provided on its side facing the working medium M with a combustion chamber lining formed from heat shield elements 26. Due to the high temperatures inside the combustion chamber 4, a cooling system (not shown in more detail) is also provided for the heat shield elements 26.
  • the burner 10 according to the invention used in the combustion chamber 4 of the gas turbine 1 is shown in a greatly simplified sectional view in FIG. 2 in order to explain the underlying catalytic combustion concept as an example.
  • 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 comprises a first flow channel 31A and a second flow channel 3IB concentrically surrounding the first flow channel.
  • the catalytic burner 35A is assigned to the first flow channel 31A and the catalytic burner 35B is assigned to the second flow channel 31B.
  • the flow channel 31A, 31B extends along a main thing or flow direction 33.
  • the flow direction 33 is also the axial flow direction or main flow direction of the fuel B in the flow channel 31A, 31B.
  • the catalytic burner 35A has catalytically active elements 43C, 43D.
  • the catalytic burner 35B has catalytically active elements 43A, 43B.
  • the catalytically active elements 43A, 43B, 43C, 43D are designed, for example, as honeycomb catalysts which consist of a basic component and a catalytically active component, the catalytically active component having an oxidizing effect on the fluidic fuel B.
  • the catalytically active elements 43A, 43B are in flow communication with the flow channel 31B, while the catalytically active elements 43C, 43D are in flow communication with the flow channel 31A.
  • the main burner 37 is arranged along the flow direction 33 of the fuel B after the fuel outlet 41 of the catalytic burner 35A, 35B and is in flow communication with the catalytic burner 35A, 35B via the flow channel 31A, 31B.
  • the main burner 37 has a fuel outlet 39.
  • the fuel outlet 41 of the catalytic burner 35A, 35B is provided in the flow direction 33 of the fuel B in the flow channel 31A, 31B in front of the fuel outlet 39 of the main burner 37.
  • the catalytic burner 35A, 35B serves for the catalytic conversion or partial conversion of the fuel B and initiates a catalytic prereaction which, after an autoignition time, causes the prereacted fuel B to be ignited in the main burner 37. This leads to stabilization of the burnout and to completion of the burnout in a burnout zone 45 which is formed in the vicinity of the fuel outlet 39 of the main burner 37.
  • the length L of the flow channel 31A, 31B is adapted to set a predetermined residence time of fuel B in the flow channel 31A, 31B, in particular to the reaction times and flow rates of the fuel B to be taken into account.
  • FIG. 3 shows a view along the flow direction 33 of the burner 10 shown in FIG. 2.
  • the catalytically active elements 43A, 43B are arranged in a plane perpendicular to the flow direction 33, the fuel outlet 41 of the catalytically active elements 43A, 43B opening into the flow channel 31B , Analogously, the catalytically active elements 43C, 43D are arranged in a plane perpendicular to the flow direction 33, with the fuel outlet 41 of the catalytically active elements 43C, 43D opens into the flow channel 31A.
  • the catalytic burners 35A, 35B are arranged at a distance from one another along the flow direction 33.
  • the fluidic fuel B is fed to a catalytic burner 35A, 35B and is at least partially converted there in a catalytic reaction. Subsequently, the catalytically prereacted fuel B is further burned in a post-reaction in the burnout zone 45 of the main burner. A swirl component is impressed on the pre-reacted fuel B. The pre-reacted swirling fuel B is transferred to a burnout zone 45 for the after-reaction, the rotary flow being formed in the flow channel 31A, 31B. By adjusting the residence time of the pre-reacted fuel B for the transfer, a spatially controlled ignition of the after-reaction in the burnout zone 45 is brought about.
  • the installation space, in particular the axial extent, of the burner 10 is limited to manageable dimensions and, at the same time, a spatially controlled ignition of the after-reaction in the burnout zone 45 assigned to the main burner 37 is ensured.
  • the burnout zone 45 is correspondingly limited in its axial dimension due to the rotary flow of the fluidic fuel B, so that an implementation with customarily dimensioned combustion chambers 4 and combustion chambers 27 (compare FIG. 1), in particular for use in a gas turbine 1, can be implemented.
  • a homogeneous non-catalytic after-reaction is ignited in the burnout zone 45, which leads to a complete burnout of the fuel B which has already been at least partially pre-reacted in the catalytic burner 35A, 35B.
  • two catalytic burners 35A, 35B are fluidically connected to a respective flow channel 31A, 31B.
  • an implementation of the invention can also be achieved by a burner 10 with only one catalytic burner 35A and a flow channel 3LA assigned to it, or also with a plurality of such burners and assigned flow channels.
  • operation with different fluidic fuels B is possible for the first time for a combustion system based on a catalytic combustion process. That means both liquid and gaseous
  • Fuels B come into consideration.
  • the burner 10 z. B. when using a liquid fuel, e.g. As heating oil, if necessary, can also be operated in a conventional operating mode with non-catalytic combustion, which increases flexibility.
  • the liquid fuel is mixed with combustion air to form a fuel-air mixture.
  • a swirl component is preferably previously impressed on the combustion air, for example by supplying the combustion air via the swirl-effecting catalyst elements or via other swirl elements.
  • a liquid fuel is then injected into the combustion air downstream of the swirling catalyst elements.
  • a fuel-air mixture can also be generated by mixing a fluid, in particular liquid, fuel with combustion air, which is at least partially converted in a catalytic reaction and then the catalytically prereacted fuel-air mixture is burned further, a swirl component being impressed on the prereacted fuel-air mixture.
  • the burner according to the invention can - depending on the choice of fuel - be operated with a fluidic fuel or fuel-air mixture flowing through the catalytically active elements or - in particular in the case of liquid fuels - with combustion air flowing through and subsequent injection of the liquid fuel.

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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)

Abstract

L'invention concerne un procédé de combustion d'un combustible fluide (B), consistant à transformer ledit combustible (B) au moyen d'une réaction catalytique, puis, à soumettre le combustible (B) ayant subi une réaction catalytique préalable, à une combustion ultérieure au cours d'une réaction subséquente. Une composante de turbulence est appliquée au combustible (B) ayant subi une réaction préalable, ce qui permet de réguler spatialement l'amorçage de la réaction subséquente, et ainsi de réaliser une combustion complète. Cette invention concerne également un brûleur (10) servant à la combustion d'un combustible fluide (B). Selon l'invention, la sortie de combustible (31) d'un brûleur catalytique (35A, 35B) est disposée, dans la direction d'écoulement (33) du combustible (B), dans un conduit d'écoulement (31A, 31B), avant la sortie de combustible (39) d'un brûleur principal (37), et le combustible (B) est transformé catalytiquement. Ledit brûleur catalytique (35A, 35B) comprend une pluralité d'éléments à action catalytique (43A, 43B, 43C, 43D) qui sont disposés de façon qu'un écoulement rotatif se forme dans le conduit d'écoulement (31A, 31B). Cette invention peut être mise en oeuvre en particulier dans des chambres de combustion de turbines à gaz.
EP04763827.5A 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 Not-in-force EP1654497B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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 (3)

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
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
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

Publications (2)

Publication Number Publication Date
EP1654497A1 true EP1654497A1 (fr) 2006-05-10
EP1654497B1 EP1654497B1 (fr) 2015-09-30

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Family Applications (2)

Application Number Title Priority Date Filing Date
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

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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

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)

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DE102005061486B4 (de) 2005-12-22 2018-07-12 Ansaldo Energia Switzerland AG Verfahren zum Betreiben einer Brennkammer einer Gasturbine
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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ES2551930T3 (es) 2015-11-24
US8540508B2 (en) 2013-09-24
WO2005019734A1 (fr) 2005-03-03
US20060260322A1 (en) 2006-11-23
EP1654497B1 (fr) 2015-09-30
EP1510761A1 (fr) 2005-03-02
JP2007501928A (ja) 2007-02-01
JP4597986B2 (ja) 2010-12-15

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