EP1654497B1 - Procede de combustion d'un combustible fluide, et bruleur, en particulier de turbine a gaz, servant a la mise en oeuvre dudit procede - Google Patents

Procede de combustion d'un combustible fluide, et bruleur, en particulier de turbine a gaz, servant a la mise en oeuvre dudit procede Download PDF

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Publication number
EP1654497B1
EP1654497B1 EP04763827.5A EP04763827A EP1654497B1 EP 1654497 B1 EP1654497 B1 EP 1654497B1 EP 04763827 A EP04763827 A EP 04763827A EP 1654497 B1 EP1654497 B1 EP 1654497B1
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EP
European Patent Office
Prior art keywords
fuel
burner
catalytic
flow channel
catalytically
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EP04763827.5A
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German (de)
English (en)
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EP1654497A1 (fr
Inventor
Bernd Prade
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Siemens AG
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Siemens AG
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    • 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 burner for combustion of a fluidic fuel, wherein in the flow direction of the fuel in a flow channel in front of the fuel outlet of a main burner, the fuel outlet of a catalytic burner is arranged with catalytic conversion of the fuel, wherein the catalytic burner has a number of catalytically active elements, which are arranged such that a rotary flow is formed in the flow channel and the catalytically active elements are arranged in a plane perpendicular to the flow direction, wherein the fuel outlet of the catalytically active elements opens into the flow channel.
  • the invention further relates to a combustion chamber having such a burner and a gas turbine with such a combustion chamber.
  • the invention further relates to a method for combustion of a fluid fuel in a burner of the aforementioned type, in which the fuel is reacted in a catalytic reaction and then further catalytically pre-reacted fuel in a post-reaction, wherein the vorreag faced fuel a swirl component is impressed.
  • a fluidic fuel is to be understood as meaning, in particular, heating oil and / or heating gas, as used in particular for gas turbines.
  • heating oil and / or heating gas as used in particular for gas turbines.
  • all combustible liquids eg. As petroleum, methanol, etc.
  • all combustible gases eg. As natural gas, coal gas, synthesis gas, biogas, propane, butane, etc.
  • Such burners with catalytic reaction are for example in the document EP-A-491 481 shown.
  • 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 simultaneously drives a generator for generating electricity.
  • preheated fresh air is compressed to the pressure required in the burner part.
  • the compressed and preheated fresh air with a fuel such. As natural gas or fuel oil burned.
  • the hot burner exhaust gas is supplied to the turbine part and there relaxes work.
  • the flame temperature or flame temperature peak reduction in the burner part acts as nitrogen oxide reducing.
  • the fuel gas or the compressed and preheated fresh air steam is supplied or injected water into the combustion chamber.
  • Such measures which reduce nitric oxide emissions of the gas turbine per se, are referred to as primary measures for nitrogen oxide reduction. Accordingly, all measures are referred to as secondary measures in which once in the exhaust gas of a gas turbine - or generally a combustion process - contained nitrogen oxides are reduced by subsequent measures.
  • the method of selective catalytic reduction has prevailed worldwide, in which the nitrogen oxides are contacted together with a reducing agent, preferably ammonia, to a catalyst and thereby form harmless nitrogen and water.
  • a reducing agent preferably ammonia
  • the arranged in the exhaust duct catalysts for nitrogen oxide reduction naturally cause a pressure drop in the exhaust passage, which causes a power loss of the turbine. Even a power loss of a few thousandths of a power of the gas turbine of, for example, 150 MV and a power sales price of about 8 cents per kWh of electricity seriously affects the achievable with such a device result.
  • the EP 1 359 377 A1 describes a burner with a number of catalysts, which open into a discharge space.
  • partially reacted hot fuel-oxidizer mixture flows along a flow direction into a combustion chamber where auto-ignition of the mixture takes place.
  • the mouths of the catalysts in the outflow space are arranged so that the inflow of the partially reacted mixture takes place in the outflow space in a plane which is perpendicular to the flow direction in the outflow space, so that the inflowing mixture receives a twist.
  • the WO03 / 072919 A1 describes a burner system with a catalytic pilot burner.
  • the US 2002/0182555 A1 , the WO 96/41991 and the EP 0 953 806 A2 describe axially symmetrical burner arrangements with catalysts, which are traversed by the fuel in the axial direction.
  • the outlet section of the catalyst is designed as a swirl generator.
  • the catalyst is a swirl generator downstream of flow.
  • An application of a catalytic process is also in the EP 0 832 397 B1 discloses 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.
  • the EP 0 832 399 B1 discloses a burner for combustion of a fuel, wherein in the flow direction of the fuel in a flow channel in front of the fuel outlet of a main burner, the fuel outlet of a catalytic backup burner for stabilizing the main burner is provided under catalytic combustion of a pilot fuel stream.
  • the catalytic support burner is arranged centrally and the main burner coronary.
  • the catalytic combustion systems described above consist of a catalyst arranged axially is. In the catalyst, only a portion of the energy contained in the fuel is released, thereby improving the stabilization of the burn-out of the remaining portion of the chemically combined energy in the axial direction downstream of the catalyst in a combustion chamber.
  • This main reaction sets in after a certain time, the so-called autoignition time, which depends essentially on the temperature and the gas composition at the catalyst exit.
  • the object of the invention is to provide a method for the combustion of a fluidic fuel, with the most complete implementation of the fluid fuel at low pollutant emissions can be achieved.
  • 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 according to the invention is achieved by a method for combustion of a fluid fuel in a burner of the type mentioned, in which the fuel is reacted in a catalytic reaction and then catalytically pre-reacted fuel is further burned in a post-reaction, wherein the pre-reacted fuel Swirl component, is impressed, wherein the burner is designed according to one of claims 1 to 5 and the catalytically pre-reacted fuel at an angle of 15 ° to 75 ° relative to a defined by the flow direction of the main axis flows into the flow channel.
  • the invention is based on the recognition that the after-reaction only starts after a certain time, which depends essentially on the temperature and the gas composition of the reaction products after the catalytic reaction.
  • the after-reaction, which is followed by the catalytic reaction should take place under as complete as possible conversion into heat.
  • the invention is based on the consideration that z.
  • liquid fuels such as fuel oil
  • which can not be implemented safely or only insufficiently in a catalytic reaction usually can not be made to burn in a limited reaction volume, unless aerodynamic stabilization takes place.
  • aerodynamic stabilization takes place.
  • Also with practicable existing dimensions there is the problem that, even with catalytic partial conversion, the reaction times available after deduction of the autoignition time are too short for the CO 2 reaction to be free of CO 2.
  • a fluidic fuel may also be preferably a fuel-air mixture, which is obtained by the fluidic fuel is mixed with combustion air to the fuel-air mixture, which is catalytically reacted.
  • a swirl component is impressed. The swirl of the prereacted fuel ensures that the fuel which escapes from the catalytic reaction has more reaction time available than was the case with a swirl-free, that is to say purely axial, reaction coordinate of the conventional catalytic combustion systems.
  • the prereacted fuel will reach the autoignition time - viewed in an axial coordinate - at a significantly reduced distance, because the swirl reduces the axial velocity component of the pre-reacted fuel and causes a swirl induced circumferential velocity component, and most importantly, a backflow zone is produced.
  • the pre-reacted fuel is still burned, sufficient reaction volume available, so that the fuel - without significant axial space expansion of the combustion system - can be completely burned out.
  • the pre-reacted swirl-fueled fuel is transferred to the post-reaction in a combustion chamber, wherein a rotary flow is formed.
  • a spatially controlled ignition of the after-reaction in the combustion chamber is brought about.
  • the residence time can be adjusted by adjusting the twist and thereby producing the rotary flow in terms of magnitude and direction of the fuel flow.
  • a catalytic pre-reaction with a non-catalytic after-reaction is advantageously combined, wherein a spatially controlled ignition of the homogeneous non-catalytic after-reaction is ensured by the swirl component of the catalytically pre-reacted fuel or possibly liquid-fueled downstream of the catalyst.
  • a gaseous fuel or a liquid fuel in particular heating gas or fuel oil, is burnt as the fluidic fuel.
  • the object directed to a burner is achieved according to the invention by a burner for combustion of a fluidic fuel in which, in the flow direction of the fuel in a flow channel in front of the fuel outlet of a main burner, the fuel outlet of a catalytic burner is arranged under catalytic conversion of the fuel, wherein the catalytic burner has a number of catalytically active elements, which are arranged such that forms a rotary flow in the flow channel and the catalytically active elements are arranged in a plane perpendicular to the flow direction, wherein the fuel outlet of the catalytically acting elements in the flow channel opens, wherein the confluence of the catalytically active elements in the flow channel at an angle of 15 ° to 75 ° relative to a defined by the flow direction of the main axis.
  • the flow direction of the fuel in the flow channel in this case refers to the axial flow direction along the flow channel, which is defined by a longitudinal axis of the flow channel.
  • the rotary flow forming under the arrangement of the catalytically acting elements is to be understood as a rotary flow or swirling flow around the flow direction or main flow direction of the fuel in the flow channel.
  • the rotational flow in the wake of the catalytically active elements is preferably formed after the fuel outlet, for example, the fuel outlet opens perpendicular to a longitudinal axis of the flow channel in the flow channel, wherein relative to the longitudinal axis of the fuel outlet is arranged offset, so that a swirl is generated.
  • the fluidic fuel is targeted to 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 is reduced according to the twisting by the geometric arrangement of the catalytically active elements.
  • the catalytically active elements are arranged in a plane perpendicular to the flow direction, wherein the fuel outlet of the catalytically active elements opens into the flow channel.
  • a multiplicity of catalytically active elements it is possible for a multiplicity of catalytically active elements to be arranged along a circumference in the plane perpendicular to the flow direction, wherein a tangential component can be achieved in each case through the direction of the confluence of the fuel outlets with the inflow into the flow channel.
  • the rotary flow can be assembled in a predetermined manner, so that in the combustion chamber results in a desired residence time distribution, the spatially controlled ignition of a homogeneous non-catalytic secondary reaction allows.
  • the system can also be advantageously arranged so that, if necessary, when using a z. B. liquid fuel and a conventional, that is, non-catalytic combustion, is adjustable.
  • the burner is particularly suitable for liquid fuels, and thus overcomes the disadvantage of previous catalytic combustion systems, especially for gas turbines, which are known only as a single-fuel burner for gaseous fuels.
  • the axial length of the flow channel is adapted to adjust a predetermined residence time of fuel in the flow channel accordingly.
  • the length of the flow channel that is, the determination of the distance of the fuel outlet of the main burner from the fuel outlet of the catalytic burner, taking into account the rotational flow due to the imposed spin and the relevant autoignition time, is a residence time appropriate for initiating and assisting the combustion of the main burner adjustable.
  • the burner is particularly flexible adaptable to the main reaction after a certain time (autoignition-time) in the main burner, which depends essentially 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 adaptation, full implementation in the main reaction is possible.
  • a catalytically active element is configured as a honeycomb catalyst having as a basic constituent at least one of the substances titanium dioxide, silicon dioxide and zirconium oxide.
  • the honeycomb catalyst more preferably has a noble metal or metal oxide which has an oxidizing effect on the fluidic fuel.
  • 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.
  • the transition metal oxides vanadium oxide, tungsten oxide, molybdenum oxide, chromium oxide, copper oxide, manganese oxide and oxides of lanthanides such.
  • cerium oxide metal ion zeolites and spinel-type metal oxides may be used.
  • the honeycomb structure of the catalytically active elements proves particularly advantageous since it is formed by a multiplicity of channels extending along an axis of the catalytically active element. 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 catalytically pre-reacted fuel from the fuel outlet is achieved, in a well-defined manner a swirl component when entering the Flow channel is effected.
  • the burner is provided according to the invention in a combustion chamber.
  • the combustion chamber in this case comprises a combustion chamber into which the burner preferably projects or opens with the fuel outlet of the main burner.
  • the combustion chamber is sufficiently dimensioned so that a homogeneous, preferably non-catalytic main reaction is set in motion and a complete combustion of the fuel and thus maximum conversion into combustion heat is achieved in the combustion chamber.
  • such a combustion chamber is suitable for use in a gas turbine, wherein a hot combustion gas generated in the combustion chamber is used to drive a turbine part of the gas turbine.
  • 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 a non-illustrated Generator or a working machine.
  • the turbine 6 and the compressor 2 are arranged on a common, also called turbine rotor turbine shaft 8, with which the generator or the working machine is connected, and which is rotatably mounted about its central axis 9.
  • the running in the manner of an annular combustion chamber 4 is equipped with a number of burners 10 for the combustion of a liquid or gaseous fuel.
  • the burner 10 is configured as a catalytic combustion system and designed for a catalytic as well as a non-catalytic combustion reaction or combinations thereof. The structure and operation of the burner 10 is intended in connection with the FIGS. 2 and 3 be discussed in more detail.
  • the turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the blades 12 are arranged in a ring on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 comprises a number of fixed vanes 14, which are also fixed in a ring shape with the formation of rows of vanes on an inner casing 16 of the turbine 6.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from the hot medium flowing through the turbine 6, the working medium M.
  • the vanes 14, however, serve to guide the flow of the working medium M between two successive rows of blades or blade boundaries seen in the flow direction of the working medium.
  • a sequential pair of a ring of vanes 14 or a row of vanes and a ring of blade 12 or a blade row is also referred to as a turbine stage.
  • Each guide blade 14 has a platform 18, also referred to as a blade root, which is arranged as a wall element for fixing the respective guide blade 14 to the inner housing 16 of the turbine.
  • the platform 18 is a thermal, relatively heavily loaded component, which is the outer boundary of a hot gas channel for the turbine. 6 flowing through working medium M forms.
  • Each blade is fastened to the turbine shaft in an analogous manner via a platform, also referred to as a blade root.
  • each guide ring 21 on the inner housing 16 of the turbine 6 is arranged.
  • the outer surface of each guide ring 21 is also exposed to the hot, the turbine 6 flowing through the working medium M and spaced in the radial direction from the outer end 22 of the blade 12 opposite it through a gap.
  • the arranged between adjacent rows of vanes guide rings 21 are used in particular as cover that protect the inner wall 16 or other housing-mounting components from thermal overload by the hot working medium M flowing through the turbine 6.
  • the combustion chamber 4 is delimited by a combustion chamber housing 29, wherein a combustion chamber wall 24 is formed on the combustion chamber side.
  • the combustion chamber 4 is configured as a so-called annular combustion chamber, in which a plurality of burners arranged around the turbine shaft 8 in the circumferential direction open into a common combustion chamber space 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 around.
  • a fluid fuel B and combustion air A is delivered to the burner 10 and mixed to a fuel-air mixture and burned.
  • combustion of the burner 10 is designed as a catalytic combustion system with the full implementation of the fuel B can be achieved.
  • the hot gas resulting from the combustion process, the working medium M has comparatively high temperatures of 1000 ° C. up to 1500 ° C., in order to achieve a correspondingly high efficiency of the gas turbine 1.
  • the combustion chamber 4 for accordingly high temperatures designed.
  • the combustion chamber wall 24 is provided on its side facing the working medium M side with a combustion chamber lining formed of heat shield elements 26. Due to the high temperatures in the interior of the combustion chamber 4, a not-shown cooling system is also provided for the heat shield elements 26.
  • the burner 10 used in the combustion chamber 4 of the gas turbine 1 according to the invention is shown in FIG. 2 in a highly simplified sectional view to exemplify the underlying catalytic combustion concept.
  • the burner 10 for combustion of the fluidic fuel B has a catalytic burner 35 A, 35 B and a main burner 37.
  • the main burner 37 comprises a first flow channel 31A and a second flow channel 31B concentrically surrounding the first flow channel.
  • the catalytic burner 35A is associated with the first flow channel 31A and the catalytic burner 35B with the second flow channel 31B.
  • the flow channel 31A, 31B extends along a main or flow direction 33.
  • the catalytic burner 35A has catalytic elements 43C, 43D.
  • the catalytic burner 35B has catalytic elements 43A, 43B.
  • the catalytically active elements 43A, 43B, 43C, 43D are configured, for example, as honeycomb catalysts, which consist of a basic component and a catalytically active component, wherein the catalytically active component exerts an oxidizing effect on the fluidic fuel B.
  • the catalytically active elements 43A, 43B are in fluid 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 in fluid 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 sets in motion a catalytic pre-reaction, which causes an ignition of the pre-reacted fuel B in the main burner 37 after an autoignition time. This leads to a stabilization of the burnout and to a 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, in particular to the reaction times and flow rates of the fuel B to be considered.
  • the catalytically active elements 43A, 43B, 43C, 43D are arranged in this way 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 from.
  • FIG. 3 shows a view along the flow direction 33 of FIG. 2
  • the catalytically active elements 43A, 43B are arranged in a plane perpendicular to the flow direction 33, wherein the fuel outlet 41 of the catalytically active elements 43A, 43B opens into the flow channel 31B.
  • the catalytic elements 43C, 43D are arranged in a plane perpendicular to the flow direction 33, wherein the fuel outlet 41 of the catalytically acting elements 43C, 43D opens into the flow channel 31A.
  • the catalytic burners 35 A, 35 B are arranged spaced apart along the flow direction 33.
  • the fluidic fuel B is fed to a catalytic burner 35A, 35B and at least partially reacted there in a catalytic reaction. Subsequently, the thus catalytically pre-reacted fuel B is further burned in a post-reaction in the Ausbrandzone 45 of the main burner.
  • the prereacted fuel B is imparted with a swirl component.
  • the prereacted spin-containing fuel B is transferred to the post-reaction in a burn-out zone 45, wherein the rotary flow is formed in the flow channel 31A, 31B.
  • the space, in particular the axial extension, of the burner 10 is limited to manageable dimensions and at the same time ensures a spatially controlled ignition of the after-reaction in the main burner 37 associated Ausbrandzone 45.
  • the burn-out zone 45 is accordingly limited in its axial dimension due to the rotary flow of the fluidic fuel B, so that a realization with customarily dimensioned combustion chambers 4 and combustion chambers 27 (cf. FIG. 1 ), in particular for use in a gas turbine 1, can be realized.
  • a homogeneous non-catalytic secondary reaction is ignited, which leads to a complete burn-out of the fuel B, which is already at least partially pre-reacted in the catalytic burner 35A, 35B.
  • two catalytic burners 35A, 35B are fluidly 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 31A associated with it, or else with a plurality of such burners and associated flow channels.
  • operation with different fluid fuels B is possible for the first time for a combustion system based on a catalytic combustion process. This means that both liquid and gaseous fuels B come into consideration.
  • the burner 10 z. B. when using a liquid fuel, for.
  • the liquid fuel is mixed with combustion air to a fuel-air mixture.
  • the combustion air is preferably previously already impressed by a swirl component, for example by supplying the combustion air via the swirl-inducing catalyst elements or via other swirl elements.
  • the combustion air is then injected downstream of the spin-effecting catalyst elements, a liquid fuel.
  • a fuel-air mixture can be generated by mixing a fluid, in particular liquid, fuel with combustion air, which at least partially reacted in a catalytic reaction and then the catalytically pre-reacted fuel-air mixture is further burned, wherein the vorreag faced fuel-air mixture, a swirl component is impressed.
  • the burner according to the invention can be operated by flowing through the catalytically active elements with a fluid fuel or air-fuel mixture or, in particular in the case of liquid fuels, by flowing through combustion air 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)

Claims (13)

  1. Brûleur (10) de combustion d'un combustible (B) fluide, dans lequel il est monté, dans le sens (33) de l'écoulement du combustible (B) dans un canal (31A, 31B) d'écoulement, en amont de la sortie (39) de combustible d'un brûleur (37) principal la sortie (41) de combustible d'un brûleur (35A, 35B) catalytique avec conversion catalytique du combustible (B),
    dans lequel le brûleur (35A, 35B) catalytique a un certain nombre d'éléments (43A, 43B, 43C, 43D) à effet catalytique, qui sont disposés de manière à donner dans le canal (31A, 31B) un écoulement tournant et les éléments (43A, 43B, 43C, 43D) à effet catalytique sont disposés dans un plan perpendiculairement au sens (33) d'écoulement, la sortie (41) de combustible des éléments (43A, 43B, 43C, 43D) à effet catalytique débouchant dans le canal (31A, 31B) d'écoulement,
    caractérisé en ce que l'embouchure des éléments (43A, 43B, 43C, 43D) à effet catalytique dans le canal (31A, 31B) d'écoulement s'effectue sous un angle de 15° à 75° par rapport à un axe principal défini par le sens (33) de l'écoulement.
  2. Brûleur (10) suivant la revendication 1,
    caractérisé en ce que l'écoulement tournant se forme dans la queue des éléments (43A, 43B, 43C, 43D) à effet catalytique après sa sortie (41) de combustible.
  3. Brûleur (10) suivant la revendication 1 ou 2,
    caractérisé en ce que, pour le réglage d'un temps de séjour donné à l'avance du combustible (B) dans le canal (31A, 31B) d'écoulement, la longueur (L) du canal (31B, 31B) d'écoulement est adaptable.
  4. Brûleur (10) suivant l'une des revendications 1 à 3,
    caractérisé en ce qu'un élément (43A, 43B, 43C, 43D) à effet catalytique est conformé en catalyseur à nid d'abeilles, qui a comme constituant de base au moins l'une des substances dioxyde de titane, oxyde de silicium et oxyde de zirconium.
  5. Brûleur (10) suivant la revendication 4,
    caractérisé en ce que, comme constituant actif catalytiquement, le catalyseur à nid d'abeilles a un métal fin ou un oxyde métallique, qui a un effet oxydant sur le combustible (B) fluide.
  6. Chambre de combustion (4) comprenant un brûleur (10) suivant l'une des revendications 1 à 5.
  7. Turbine (1) à gaz comprenant une chambre de combustion (4) suivant la revendication 6.
  8. Procédé de combustion d'un combustible (8) fluide dans un brûleur suivant le préambule de la revendication 1, dans lequel on transforme le combustible (B) dans une réaction catalytique et ensuite on continue à brûler dans une post-réaction du combustible (B) ayant préréagi catalytiquement, une composante de tourbillonnement étant imprimée au combustible (B) ayant préréagi,
    caractérisé en ce que le brûleur est constitué suivant l'une des revendications 1 à 5 et le combustible (B) ayant préréagi catalytiquement entre dans le canal (31A, 31B) d'écoulement sous un angle de 15° à 75° par rapport à l'axe principal défini par le sens (33) d'écoulement.
  9. Procédé suivant la revendication 8,
    caractérisé en ce qu'on dérive du combustible (B), ayant préréagi et mis en tourbillonnement, pour la post-réaction dans une chambre de combustion (27), un écoulement tournant étant formé.
  10. Procédé suivant la revendication 9,
    caractérisé en ce qu'en réglant pour la dérivation le temps de séjour du combustible (B) ayant préréagi, on provoque un amorçage contrôlé dans l'espace de la post-réaction dans la chambre de combustion (27).
  11. Procédé suivant la revendication 10,
    caractérisé en ce qu'on amorce une post-réaction homogène non catalytique.
  12. Procédé suivant l'une des revendications 8 à 11,
    caractérisé en ce que l'on brûle complètement le combustible (B) dans la post-réaction.
  13. Procédé suivant l'une des revendications 8 à 12,
    caractérisé en ce que l'on brûle comme combustible (B) fluide un gaz ou un combustible liquide, notamment du gaz de chauffage ou du mazout.
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 EP1654497A1 (fr) 2006-05-10
EP1654497B1 true EP1654497B1 (fr) 2015-09-30

Family

ID=34089588

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

Family Applications Before (1)

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

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)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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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US4040252A (en) * 1976-01-30 1977-08-09 United Technologies Corporation Catalytic premixing combustor
DE2841105C2 (de) * 1978-09-21 1986-10-16 Siemens AG, 1000 Berlin und 8000 München Vergasungsbrenner
DE3474714D1 (en) * 1983-12-07 1988-11-24 Toshiba Kk Nitrogen oxides decreasing combustion method
JPS61276627A (ja) * 1985-05-30 1986-12-06 Toshiba Corp ガスタ−ビン燃焼器
JPS62141425A (ja) 1985-12-13 1987-06-24 Tokyo Electric Power Co Inc:The ガスタ−ビン燃焼器
US4692306A (en) * 1986-03-24 1987-09-08 Kinetics Technology International Corporation Catalytic reaction apparatus
GB9027331D0 (en) 1990-12-18 1991-02-06 Ici Plc Catalytic combustion
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US5355668A (en) * 1993-01-29 1994-10-18 General Electric Company Catalyst-bearing component of gas turbine engine
ES2142588T3 (es) * 1995-06-12 2000-04-16 Siemens Ag Quemador catalitico de encendido de una turbina de gas.
DE19521308A1 (de) 1995-06-12 1996-12-19 Siemens Ag Gasturbine zur Verbrennung eines Brenngases
US6015285A (en) * 1998-01-30 2000-01-18 Gas Research Institute Catalytic combustion process
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DE50313028D1 (de) * 2002-05-02 2010-10-14 Alstom Technology Ltd Katalytischer Brenner

Also Published As

Publication number Publication date
ES2551930T3 (es) 2015-11-24
US8540508B2 (en) 2013-09-24
WO2005019734A1 (fr) 2005-03-03
US20060260322A1 (en) 2006-11-23
EP1510761A1 (fr) 2005-03-02
JP2007501928A (ja) 2007-02-01
EP1654497A1 (fr) 2006-05-10
JP4597986B2 (ja) 2010-12-15

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