EP1730441B1 - Device and method for stabilizing the flame in a burner - Google Patents

Device and method for stabilizing the flame in a burner Download PDF

Info

Publication number
EP1730441B1
EP1730441B1 EP05717130A EP05717130A EP1730441B1 EP 1730441 B1 EP1730441 B1 EP 1730441B1 EP 05717130 A EP05717130 A EP 05717130A EP 05717130 A EP05717130 A EP 05717130A EP 1730441 B1 EP1730441 B1 EP 1730441B1
Authority
EP
European Patent Office
Prior art keywords
air
catalyst
fuel mixture
burner
pilot fuel
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.)
Not-in-force
Application number
EP05717130A
Other languages
German (de)
French (fr)
Other versions
EP1730441A1 (en
Inventor
Richard Carroni
Thiemo Meeuwissen
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1730441A1 publication Critical patent/EP1730441A1/en
Application granted granted Critical
Publication of EP1730441B1 publication Critical patent/EP1730441B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/13002—Catalytic combustion followed by a homogeneous combustion phase or stabilizing a homogeneous combustion phase

Definitions

  • the invention relates to a device for flame stabilization in a burner, with a burner volume at least partially comprehensive burner housing into which at least one fuel line fuel and at least one air supply means air to form a propagating in a preferred flow direction air / fuel mixture can be introduced which is flammable in a combustion chamber downstream of the burner housing to form a stationary flame. Also described is a method of flame stabilization in a related burner.
  • Modern premix burners of which reference is made to a premix burner with conical burner housing, which in the EP 321 809 B1 are optimized from the point of view of their efficiency and their pollutant emissions.
  • the optimizations performed on the burner systems apply primarily to load ranges in which such burner systems are mainly operated to drive, for example, heat engines, mainly gas or steam turbine plants. Such systems are operated most of the time under full or part load conditions.
  • pilot gas supply through which mostly pilot gas, which experiences no or only a small premix with the supply air, is supplied to the flame via a burner lance arranged centrally in the burner.
  • pilot gas feeds result in so-called pilot flames, which are basically of the diffusion type, even in cases where the premix burner is operated under lean fuel conditions.
  • a further measure for flame stabilization provides for the use of catalysts which are provided in the mixing zone of a premix burner as part of a so-called catalytic pilot and, depending on the air-fuel ratio ⁇ and the oxygen present in the mixture, at least portions of the fuel contained in the air / fuel mixture to oxidize.
  • catalysts which are provided in the mixing zone of a premix burner as part of a so-called catalytic pilot and, depending on the air-fuel ratio ⁇ and the oxygen present in the mixture, at least portions of the fuel contained in the air / fuel mixture to oxidize.
  • a rich air-fuel mixture ie ⁇ ⁇ 1
  • it is possible by using catalytic reactors within the Vormischbrenner Schemees by partial oxidation of the fuel portion to produce so-called syngas, which consists of H 2 and CO and represents a highly reactive gas due to the hydrogen content.
  • a method is in each case removable, in which the partially oxidized by way of catalysis air / fuel mixture is mixed with cooling air to avoid auto-ignition and an associated diffusion flame and ultimately as a hot, lean, CH 4 mixture contained for the purpose of Stabilization to be supplied within the combustion chamber homogeneously forming flame.
  • the invention has for its object to provide an apparatus and a method for flame stabilization of a flame forming downstream of a premix burner such that the measures used for stabilization neither the flame stability, i. can permanently affect the flame site, nor lead to an increased nitrogen oxide emission. Rather, it should be possible to make flame-stabilizing precautions that are largely unrelated to the burner design and do not adversely affect the combustion characteristics optimized by the burner design. Thus, the measures to be taken should contribute to creating increased design flexibility in the design of premix burners and, in addition, to be able to be used on as many different burner systems as possible, without having to consider requirements with regard to special system optimization.
  • a device for flame stabilization in a burner is designed such that upstream of the flame, a catalyst arrangement is provided through which flows from the air / fuel mixture (4) separate air / pilot fuel mixture.
  • the catalyst arrangement has at least two catalyst stages which are arranged one behind the other in the flow direction of the air / fuel mixture forming inside the burner, of which the upstream arranged catalyst stage, the so-called POX catalyst, with an air / pilot fuel mixture is penetrated at a mixing ratio ⁇ ⁇ 1, through which the air / pilot fuel mixture is partially oxidized.
  • the downstream in the flow direction catalyst stage the so-called FOX catalyst is interspersed with a lean air / pilot fuel mixture with a mixing ratio ⁇ > 1, through which the lean air / pilot fuel mixture is completely oxidized to form an inert hot gas stream.
  • the method principle underlying the device according to the invention is based on a flame stabilization with the aid of at least 600 ° C, preferably up to 950 ° C, hot, chemically inert hot gas stream, which is introduced into or adjacent to the flame in the combustion chamber.
  • the hot, unreacted gas thermally stabilizes the homogenized flame forming within the combustion chamber, the inert nature of the hot hot gas components allowing the inert hot gas stream to be supplied anywhere in the burner system in the flame region without compromising flame position and temperature to change associated mixing times or to cause an increase in nitrogen oxide formation.
  • the inventive measure an unprecedented degree of design flexibility is created, which allows the inventively constructed device having a so-called two-stage pilot catalyst to combine with a variety of burner systems, largely without having to take into account optimization requirements that would be connected by special system constraints.
  • the two-stage catalyst arrangement can catalyze a fuel-rich, ie rich air / pilot fuel mixture with an air / pilot fuel ratio ⁇ ⁇ 1 with its first catalyst stage, the POX catalyst such that downstream of the POX catalyst, a partially oxidized air / pilot fuel mixture from the POX catalyst emerges.
  • the partially oxidized air / pilot fuel mixture is mixed with supply air downstream of the POX catalyst to form a lean air / pilot fuel mixture, ie ⁇ > 1, before it enters the FOX catalyst. within which the lean air / pilot fuel mixture is completely oxidized.
  • a hot gas that is very hot and chemically inert due to the exothermic oxidation reactions is formed, which is fed into the region of the combustion chamber in which the flame is formed for targeted thermal flame stabilization.
  • FIG. 1 shown schematic representation shows an inventively designed catalyst assembly 1, which encloses a flow channel 2 through which passes in the illustration from left to right an air flow L.
  • a first catalyst 3 Inside the catalyst arrangement 1, upstream of the flow channel 2 there is provided a first catalyst 3, the so-called POX catalyst, which has a plurality of catalyst channels oriented in the direction of flow, which are coated internally with suitably selected catalyst material and specifically for the catalysis of a rich air / pilot fuel mixture is selected.
  • the POX catalyst 3 is fed upstream of an air / pilot fuel mixture 4, which is composed of a fully mixed fuel flow m POX, fuel and an air flow m POX, air .
  • the air-pilot fuel mixture 4 entering into the POX catalytic converter 3 has an adjustable mixing ratio ⁇ POX as well as a selectively adjustable mixture inlet temperature T POX, in . Since, as already mentioned, the flow channels of the POX catalyst 3 are coated with a catalytic layer of suitable choice, preferably with rhodium or rhodium-containing material compound, and have corresponding flow geometries, any overheating of the channel walls by the catalytically assisted, exothermally acting partial oxidation of the fuel contained in the air-pilot fuel mixture 4 can be avoided.
  • the POX catalytic converter 3 ensures a homogeneously mixed outlet mixture 5 whose temperature T POX, out depends on the one hand on the inlet temperature T POX, in and on the air pilot fuel ratio ⁇ POX .
  • the outlet temperature T POX, out of the outlet mixture 5 is in a range between 600 ° C and 950 ° C, wherein the outlet mixture 5 consists mainly of CH 4 , N 2 , CO 2 and H 2 O.
  • the outlet mixture 5 has only a small proportion of the syngas described above, preferably with volume percentages below 5%.
  • oxygen contents O 2 may be contained in the outlet mixture 5 with a volume percentage of ⁇ 5%.
  • the air / pilot fuel mixture 4 supplied to the POX catalyst 3 has an air / fuel ratio ⁇ POX, typically between 0.15 and 0.4, ie that supplied to the POX catalyst 3 Air pilot fuel mixture is relatively rich in fuel or fat.
  • a predetermined amount of air L flowing around the POX catalytic converter 3 is admixed with the outlet mixture 5, with a specifically adjustable mass flow 6 m bypass and a predefinable air temperature T bypass which is identical to or similar to the inlet temperature T POX, is in the POX catalyst 3 supplied air-pilot fuel mixture 4. Downstream of the POX catalyst 3 thus forms a mixture which is heavily emaciated, typically with an air-pilot fuel ratio 4 ⁇ ⁇ 9.
  • the so emaciated Air pilot fuel mixture 7, with a suitably dimensioned mass flow m FOX, is fed to the so-called downstream FOX catalyst 8 in the flow direction through the catalyst assembly 1, wherein the lean air pilot fuel mixture 7 has a temperature T FOX, in , which is less than T POX, out is.
  • T POX With regard to the temperature T POX, out of the outlet mixture 5, care must be taken that it is low enough to be able to reliably rule out possible auto-ignition during the mixing of the supply air L with the partially oxidized air / pilot fuel mixture 5 emerging from the POX catalytic converter 3. This is assisted by providing a high degree of uniform distribution within the exit mixture 5 by providing corresponding channel guides in the POX catalyst 3, whereby so-called fuel pockets can be excluded. Furthermore, the partial oxidation taking place within the POX catalyst 3 ensures a substantially complete depletion of the mass flow of oxygen.
  • the temperature T FOX in typically moves in the range between 500 ° C and 950 ° C and depends in particular on the temperature T POX, out of the outlet mixture 5 and the amount of supplied bypass air m bypass . T FOX, in should always be greater than the ignition temperature of the FOX catalyst 8, so as to ensure that the lean air-pilot fuel mixture entering the FOX catalyst 8 is completely catalytically oxidized.
  • additional turbulence generating means such as Venturi arrangements or similar devices, may be provided to assist the mixing process.
  • the FOX catalyst 8 is lined innenden with suitable catalyst material, for example. Pd or Pt, by which it can be ensured that the FOX catalyst 8 passing through lean-air pilot fuel mixture. 7 is completely oxidized so that any fuel present in the mixture 7 is converted to CO 2 and H 2 O.
  • the gas mixture m FOX, out leaving the catalyst arrangement 1 thus has a very high temperature, typically T FOX, out up to 950 ° C. and contains mainly CO 2 , H 2 O, O 2 and N 2 . Only very small proportions of CH 4 can also be present, which, however, are unable to impair the chemically inert character of the exit gas 9.
  • the preferably with platinum or paladium innenden lined FOX catalyst 8 is able to achieve the adiabatic process temperatures of the gas mixture passing through the catalyst without succumbing itself material overheating, especially since the FOX catalyst 8 interspersed gas mixture is heavily emaciated and the associated adiabatic temperatures far below the material-specific maximum temperatures are.
  • the catalyst arrangement described above it is possible to produce a hot, inert gas stream and to use for thermal stabilization of a homogenized flame forming within a combustion chamber.
  • the inert nature of the gas stream makes it possible to inject the gas stream at any point of the burner or the combustion chamber, without suffering lasting effects within the forming in the burner mixture formation.
  • the feed of the invention has a hot inert gas stream into the burner area no influence on the auto-ignition behavior and the formation of nitrogen oxides.
  • the inventively proposed thermal stabilization of the homogenized flame within the combustion chamber by the fact that the flame location remains unchanged despite hot gas supply, whereby a flame displacement upstream within the burner is avoided. As a result, the mixing times and the associated nitrogen oxide emission are in no way affected. This provides improved design flexibility compared to previously known and used piloting methods.
  • the catalyst arrangement can be used effectively throughout the entire load range of the burner for firing, for example, a gas turbine plant, ie from start to full load.
  • a gas turbine plant ie from start to full load.
  • the electric preheater can be turned off.
  • FIG. 2 shows a schematic representation of a preferred arrangement possibility of the catalyst assembly 1 within a burner 10, which is preferably designed as a premix burner and the arrow is traversed in the flow direction of an inside of the burner 10 forming air / fuel mixture.
  • a swirling flow D forming in the flow direction forms due to flow-dynamic conditions, for example using a swirl generator, which bursts due to the unsteady flow cross-sectional widening between premix burner 10 and combustion chamber 11 and forms a return flow zone 12, in which a homogeneous flame 13 spatially stationary training.
  • the catalyst arrangement 1 is arranged centrically within the flow ratio in the premix burner 10. For complete mixing of the adjusting within the premix burner air / fuel mixture and to stabilize the flame additional swirl generator or vortex generators 14 are provided which radially surround the catalyst assembly 1.
  • the catalyst assembly 1 it is possible to position the catalyst assembly 1 also to another located within the premix burner 10 area. From the in FIG. 2 illustrated embodiment, it can be seen that the catalyst assembly 1 to form the hot, inert hot gas stream separately to Brenntsoff- / air supply to the burner, a separate air / pilot fuel mixture (4) is supplied. The air-fuel mixture flowing around the catalyst arrangement 1 is ignited in the combustion chamber 11 to form a homogeneous flame 13.
  • FIG. 3 Another possibility of using the inventively designed catalyst assembly 1 is shown.
  • the catalyst arrangement 1, as described in detail from the above FIG. 1 can be seen as a first burner stage is used within a two-stage burner assembly.
  • the catalyst stage 1 is thereby penetrated by the entire air / fuel mixture, which is passed through the burner assembly, and forms downstream of the catalyst assembly 1, a chemically inert hot gas 9, which is fed directly to a second burner stage 15, in the inert chemical hot gas additional fuel and bypass air is added.
  • the hot gas / fuel mixture which forms in this case ultimately ignites in the form of a homogeneous flame 13 downstream of the second burner stage 15.
  • a preferred embodiment for a possible design of the POX catalytic converter 3 provides a plurality of flow channels passing through the catalytic converter 3, which can be divided into two groups.
  • the air / pilot fuel mixture 4 is passed through a first group of flow channels which are coated with catalyst material, for example with rodium.
  • catalyst material for example with rodium.
  • the advantage of such an embodiment lies in an improved mixing of the outlet flows and also allows better control over the POX catalyst temperature T POX , especially since the flow rates of both flow components are set separately variable can be and the supply air for a targeted cooling of the POX catalyst 3 is used.
  • FIG. 4 is a comparable to FIG. 1
  • the generation of a highly reactive syngas containing hot gas could be particularly advantageous for difficult operating situations during the switching of the burner and under very low load conditions.
  • no supply air L, ie m bypass 0, admixed.
  • exiting from the POX catalyst 3 exit mixture 5 undergoes no emaciation.
  • the air / pilot fuel ratio supplied to the POX catalyst 3 is typically selected to promote syngas generation.
  • the air / pilot fuel ratio ⁇ is POX values> 0.25.
  • the problem with such an operating mode is the switching from the above-described syngas generating mode to the standard scenario according to the invention, in which only hot inert gases are formed with the aid of the catalyst arrangement.
  • the air / pilot fuel ratio ⁇ POX of the air / pilot fuel mixture 4 fed to the POX catalyst 3 is reduced to values ⁇ 0.15 by either increasing the mass flow m POX, fuel or reducing the air flow m POX, air .
  • the thereby resulting fatter, entering the POX catalyst 3 air / pilot fuel mixture 4 has a lower adiabatic temperature at which no syngas production comes about.
  • the exit temperature T POX, out drops to values between 500 ° C and 700 ° C.
  • the inlet temperature T FOX drops far below values of the outlet temperature T POX, out and assumes temperatures of much less than 600 ° C.
  • the amount of m bypass is then continuously increased so that the air / pilot fuel ratio of the mixture entering the FOX catalyst 8 is 7 ⁇ FOX, in ⁇ 1, and also ⁇ POX, can also be increased until the full load range is reached and the catalyst assembly produces only chemically inert hot gases.

Abstract

A device and a method for flame stabilization in a burner (10), includes a burner housing at least partially enclosing a burner volume, into which may be introduced via at least one fuel line, fuel, and via at least one air feed means, air, forming an air/fuel mixture spreading in a preferred flow direction, which may be ignited in a combustion chamber (11) connecting downstream of the burner housing to form a stationary flame (13). Upstream of the flame (13), a catalyst arrangement (1) is provided through which an air/pilot fuel mixture (4), separate from the air/fuel mixture, is flowable. The catalyst arrangement (1) has at least two catalyst stages which are located one behind the other in the through-flow direction, of which the catalyst stage (3) located upstream, the so-called POX-catalyst, is flow-washable by the air/pilot fuel mixture (4) with an air/pilot fuel mixture ratio lambda<1, by which catalyst stage (3) the air/pilot fuel mixture (4) is partially oxidized, and of which catalyst stages the downstream catalyst stage (8), the so-called FOX-catalyst, is flow-washable by a leaned air/pilot fuel mixture (7) with a mixture ratio lambda>1, by which the leaned air/pilot fuel mixture is completely oxidized forming an inert hot gas flow (9).

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf eine Vorrichtung zur Flammenstabilisierung in einem Brenner, mit einem ein Brennervolumen wenigstens teilweise umfassenden Brennergehäuse, in das über wenigstens eine Brennstoffleitung Brennstoff und über wenigstens ein Luftzuführungsmittel Luft unter Ausbildung eines sich in einer bevorzugten Strömungsrichtung ausbreitenden Luft-/Brennstoffgemisches einbringbar sind, das in einer sich stromab an das Brennergehäuse anschließenden Brennkammer unter Ausbildung einer stationären Flamme entzündbar ist. Ferner wird ein Verfahren zur Flammenstabilisierung in einem diesbezüglichen Brenner Beschrieben.The invention relates to a device for flame stabilization in a burner, with a burner volume at least partially comprehensive burner housing into which at least one fuel line fuel and at least one air supply means air to form a propagating in a preferred flow direction air / fuel mixture can be introduced which is flammable in a combustion chamber downstream of the burner housing to form a stationary flame. Also described is a method of flame stabilization in a related burner.

Stand der TechnikState of the art

Moderne Vormischbrenner, von denen stellvertretend auf einen Vormischbrenner mit kegelförmigen Brennergehäuse verwiesen wird, der in der EP 321 809 B1 beschrieben ist, sind unter dem Gesichtspunkt ihres Wirkungsgrades sowie hinsichtlich ihrer Schadstoffemissionen optimiert. Die an den Brennersystemen durchgeführten Optimierungen gelten vornehmlich für Lastbereiche, in denen derartige Brennersysteme hauptsächlich betrieben werden, um bspw. Wärmekraftmaschinen, hauptsächlich Gas- oder Dampfturbinenanlagen anzutreiben. Derartige Anlagen werden die meiste Zeit unter Voll- oder Teillastbedingungen betrieben.Modern premix burners, of which reference is made to a premix burner with conical burner housing, which in the EP 321 809 B1 are optimized from the point of view of their efficiency and their pollutant emissions. The optimizations performed on the burner systems apply primarily to load ranges in which such burner systems are mainly operated to drive, for example, heat engines, mainly gas or steam turbine plants. Such systems are operated most of the time under full or part load conditions.

An Hand des vorstehend genannten Beispiels eines kegelförmig ausgebildeten Vormischbrenners soll im Weiteren auf ein Problem hingewiesen werden, das sich beim Betrieb derartiger Brenner stellt. Nicht notwendiger Weise sind die nachstehenden Ausführungen auf kegelförmige Vormischbrenner beschränkt. Vielmehr betrifft das Problem alle gattungsgemäßen Vormischbrenner.With reference to the above-mentioned example of a cone-shaped premix burner, reference will now be made to a problem which arises in the operation of such burners. Not necessarily, the following discussion is limited to tapered premix burners. Rather, the problem relates to all generic Vormischbrenner.

In an sich bekannter Weise umschließen moderne Vormischbrenner sich konisch erweiternde Brennervolumen, den so genannten Drallraum, in den Luft- und Brennstoff unter Ausbildung einer sich axialwärts zum Drallraum konisch erweiternden Drallströmung eingespeist werden. Durch Vorsehen eines unsteten Strömungsüberganges zwischen dem Drallraum und dem sich an den Drallraum anschließenden Brennkammergehäuse platzt die Drallströmung auf und bildet innerhalb der Brennkammer eine Rückströmzone aus, in der das Brennstoffgemisch unter Ausbildung einer räumlich weitgehend stationären Flamme zündet. Um einen möglichst optimierten Verbrennungsprozess gewährleisten zu können, gilt es eine möglichst homogene und räumlich stationäre Flammenbildung zu unterstützen.In a manner known per se, modern premix burners surround conically widening burner volumes, the so-called swirl space, into which air and fuel are fed, forming a swirling flow that tapers conically axially toward the swirl space. By providing an unsteady flow transition between the swirl chamber and the combustion chamber housing adjoining the swirl chamber, the swirl flow bursts and forms within the combustion chamber a backflow zone in which ignites the fuel mixture to form a spatially largely stationary flame. In order to be able to ensure the most optimized combustion process, it is necessary to support as homogeneous and spatially stationary flame formation as possible.

Derartige Brenner werden jedoch unvermeidbar, wenn auch nur vorübergehend unter Last- und Betriebsbedingungen betrieben, unter denen sich eine homogen ausbildende, räumlich stationäre Flamme nicht oder nur mit erheblichen Einschränkungen ausbilden kann. Insbesondere unter Start- und Niedriglastbedingungen müssen zur Gewährleistung der an die Flammenqualität gestellten Forderungen entsprechende Maßnahmen zur Flammenstabilisierung ergriffen werden. Ein probates Mittel zur Flammenstabilisierung stellt die sogenannte Pilotgaszuführung dar, durch die zumeist über eine zentral im Brenner angeordnete Brennerlanze zusätzliches Pilotgas, das keine oder nur eine geringe Vormischung mit der Zuluft erfährt, der Flamme zugeführt wird. Derartige Pilotgasspeisungen führen zu sogenannten Pilotflammen, die grundsätzlich vom Diffusionstyp sind, selbst in Fällen, in denen der Vormischbrenner unter mageren Brennstoffbedingungen betrieben wird.However, such burners are inevitably, albeit temporarily operated under load and operating conditions, under which a homogeneous forming, spatially stationary flame can not or can only train with considerable restrictions. In particular, under start and low load conditions appropriate measures for flame stabilization must be taken to ensure the demands made on the flame quality. A tried-and-tested means of flame stabilization is the so-called pilot gas supply, through which mostly pilot gas, which experiences no or only a small premix with the supply air, is supplied to the flame via a burner lance arranged centrally in the burner. Such pilot gas feeds result in so-called pilot flames, which are basically of the diffusion type, even in cases where the premix burner is operated under lean fuel conditions.

Eine weitere Maßnahme zur Flammenstabilisierung sieht den Einsatz von Katalysatoren vor, die im Rahmen einer so genannten katalytischen Pilotierung im Durchmischungsbereich eines Vormischbrenners vorgesehen werden und in Abhängigkeit des Luft-Brennstoffverhältnisses λ sowie des im Gemisch vorhandenen Sauerstoffes zumindest Anteile des im Luft-/Brennstoffgemisch enthaltenen Brennstoffes zu oxidieren. Insbesondere bei einer fetten Luft-Brennstoffmischung, d.h. λ < 1, ist es möglich durch Einsatz katalytischer Reaktoren innerhalb des Vormischbrennerbereiches durch Teiloxidation des Brennstoffanteiles sogenanntes Syngas zu erzeugen, das aus H2 und CO besteht und aufgrund des Wasserstoffanteiles ein hochreaktionsfähiges Gas darstellt. So konnte experimentell nachgewiesen werden, dass eine gezielte Beimischung von Syngas in den sich in der Brennkammer ausbildenden Flammenbereiches eine verbesserte Verbrennungsstabilität in Bezug auf eine stabile Flammenlage sowie eine reduzierte Stickoxydemission erzielbar ist (siehe US 5,569,020 und Samuelsen, 99-GT-359, ASME-Turbo Indianapolis).A further measure for flame stabilization provides for the use of catalysts which are provided in the mixing zone of a premix burner as part of a so-called catalytic pilot and, depending on the air-fuel ratio λ and the oxygen present in the mixture, at least portions of the fuel contained in the air / fuel mixture to oxidize. In particular, in a rich air-fuel mixture, ie λ <1, it is possible by using catalytic reactors within the Vormischbrennerbereiches by partial oxidation of the fuel portion to produce so-called syngas, which consists of H 2 and CO and represents a highly reactive gas due to the hydrogen content. Thus it could be proven experimentally that a specific admixing of syngas in the flame zone forming in the combustion chamber can achieve an improved combustion stability with regard to a stable flame position and a reduced nitrogen oxide emission (cf. US 5,569,020 and Samuelsen, 99-GT-359, ASME-Turbo Indianapolis).

Auch ist es bekannt, durch katalytische Teiloxidation eine sich innerhalb eines Brenners ausbildenden Luft-/Brennstoffgemisches und durch geeignete Wahl des Luft-Brennstoffverhältnisses sowie der Eintrittstemperaturen des Luft-Brennstoffgemisches in den katalytischen Reaktor, ein Syngas-freies Gasgemisch bestehend aus CH4, N2, CO2 und H2O herzustellen, das aufgrund des im Gasgemisch enthaltenen Methans einem herkömmlichen, mageren, vorgemischten Pilotgas entspricht. Ein derartiges Verfahren ist beispielsweise der US 6,358 , 040 sowie der US 6,394,791 zu entnehmen. Aus diesen Druckschriften ist jeweils ein Verfahren entnehmbar, bei dem das im Wege einer Katalyse teiloxidierte Luft-/Brennstoffgemisch mit Kühlluft gemischt wird, um eine Selbstzündungen und eine damit verbundenen Diffusionsflamme zu vermeiden und letztlich als heißes, mageres, CH4 enthaltenes Gemisch zum Zwecke der Stabilisierung der sich innerhalb der Brennkammer homogen ausbildenden Flamme zugeführt zu werden.It is also known, by catalytic partial oxidation, forming within a burner air / fuel mixture and by suitable choice of the air-fuel ratio and the inlet temperatures of the air-fuel mixture in the catalytic reactor, a syngas-free gas mixture consisting of CH 4 , N 2 , CO 2 and H 2 O, which corresponds to a conventional, lean, premixed pilot gas due to the methane contained in the gas mixture. Such a method is for example the US 6,358 . 040 as well as the US 6,394,791 refer to. From these publications, a method is in each case removable, in which the partially oxidized by way of catalysis air / fuel mixture is mixed with cooling air to avoid auto-ignition and an associated diffusion flame and ultimately as a hot, lean, CH 4 mixture contained for the purpose of Stabilization to be supplied within the combustion chamber homogeneously forming flame.

Alle drei vorstehend beschriebenen Maßnahmen, sei es die Zuführung von Pilotgas unter Ausbildung einer Diffusionsflamme oder der Einsatz katalytischer Reaktoren zur Erzeugung Syngas-enthaltene oder Syngas-freie, aber in jedem Fall CH4 enthaltene Gasgemische, basieren auf der Mischung eines heißen, reaktiven Pilotgases mit dem sich im Vormischbrenner ausbildenden Luftbrennstoffgemisch. In allen Fällen ist es daher entscheidend, dass eine vollständige Durchmischung des reaktiven Pilotgases mit dem Luftbrennstoffgemisch hergestellt wird, noch bevor Selbstzündungen auftreten, um letztlich so genannte Hotspots sowie auch erhöhte Stickoxydemissionen zu vermeiden. Durch die zusätzliche Einspeisung eines reaktiven Pilotgases kann sich überdies die Flammenposition innerhalb der Brennkammer verändern, wodurch sich die Zeitspanne zur vollständigen Gemischausbildung reduziert, insbesondere in jenem Falle, in dem die Flamme eine Brennkammer-interne stromauforientierte Position einnimmt. Selbstredend ist damit eine erhöhte Ausbildung und Emission von Stickoxiden verbunden.All three measures described above, be it the supply of pilot gas to form a diffusion flame or the use of catalytic reactors Syngas-containing or syngas-free, but in any case CH 4 -containing gas mixtures are based on the mixture of a hot, reactive pilot gas with the air fuel mixture forming in the premix burner. In all cases, therefore, it is crucial that a complete mixing of the reactive pilot gas is made with the air fuel mixture, even before auto-ignition occurs, to ultimately avoid so-called hotspots and increased nitrogen oxide emissions. Moreover, the additional feed of a reactive pilot gas may change the flame position within the combustion chamber, thereby reducing the time required for complete mixture formation, particularly in the case where the flame occupies a combustion chamber internal upstream position. Of course, this is associated with increased training and emission of nitrogen oxides.

Der Einfluss auf die räumliche Lage der sich innerhalb der Brennkammer ausbildenden homogenen Flamme ist durch eine Pilotgaszufuhr umso größer, je brennstoffreicher das zugeführte Pilotgas ist. Insbesondere bei der sich im Wege der katalytisch unterstützten Teiloxidation möglichen Syngasausbildung kommt dem Ort der Einspeisung von Syngas relativ zur Flammelage eine erhebliche Bedeutung zu, zumal die Flammenlage sehr sensibel in Bezug auf eine Syngaseinspeisung reagieren könnte. Diese, mit Syngaseinspeisung verbundene Abhängigkeiten der Flammenlage sind in der US 5,937,632 ausführlich dargelegt und im Rahmen einer sogenannten chemischen Flammenstabilisierung beschrieben.The influence on the spatial position of forming within the combustion chamber homogeneous flame is greater by a pilot gas, the more fuel-rich the supplied pilot gas. Particularly in the case of the syngas formation which is possible by way of the catalytically assisted partial oxidation, the location of the feeding of syngas relative to the flame layer is of considerable importance, especially since the flame position could react very sensitively with respect to a syngas feed. These dependencies of the flame position associated with syngas feed are in the US 5,937,632 detailed and described in the context of a so-called chemical flame stabilization.

Zusammenfassend kann daher festgehalten werden, dass den vorstehend beschriebenen Maßnahmen zur Flammenstabilisierung beim Betrieb moderner Vormischbrenner insbesondere unter Teillastbedingungen oder während der Startphase, folgende Probleme entgegenstehen:

  • So gilt es zum einen, die Ausbildung sogenannter heißer Taschen zu vermeiden, d.h. unverbrannter Brennstoff, der mit dem Luft-/Brennstoffgemisch der Hauptströmung reagiert bevor das Gemisch eine vollständige Durchmischung erfahren hat. Zum anderen beeinflusst die bisher im Einsatz befindliche Pilotierungstechnik die Flammenposition und damit verbunden die verfügbare Zeit zur vollständigen Durchmischung des Luft-/Brennstoffgemisches, das bei zu früher Entzündung einen beträchtlichen Stickoxidanteil freisetzt.
In summary, it can therefore be stated that the above-described measures for flame stabilization in the operation of modern premix burners, in particular under partial load conditions or during the starting phase, have the following problems:
  • Thus, on the one hand, it is necessary to avoid the formation of so-called hot pockets, ie unburned fuel, which reacts with the air / fuel mixture of the main flow before the mixture has undergone a thorough mixing. On the other hand, the piloting technique used so far influences the flame position and the associated time to complete Mixing of the air / fuel mixture, which releases a considerable amount of nitric oxide in the case of too early ignition.

Darstellung der ErfindungPresentation of the invention

Der Erfindung liegt die Aufgabe zugrunde, eine Vorrichtung sowie ein Verfahren zur Flammenstabilisierung einer sich stromab eines Vormischbrenners ausbildenden Flamme derart anzugeben, dass die zur Stabilisierung eingesetzten Maßnahmen weder die Flammenstabilität, d.h. den Flammenort nachhaltig zu beeinträchtigen vermögen, noch zu einer erhöhten Stickoxidemission führen. Vielmehr soll es möglich sein, flammenstabilisierende Vorkehrungen zu treffen, die weitgehend nicht vom Brennerdesign abhängen und nicht die durch das Brennerkonzept optimierten Verbrennungseigenschaften nachhaltig beeinträchtigen. So sollen die zu treffenden Maßnahmen dazu beitragen, eine erhöhte Designflexibilität in der Ausbildung von Vormischbrennern zu schaffen und darüber hinaus an möglichst vielen unterschiedlichen Brennersystemen einsetztbar sein, ohne Erfordernisse hinsichtlich einer speziellen Systemoptimierung berücksichtigen zu müssen.The invention has for its object to provide an apparatus and a method for flame stabilization of a flame forming downstream of a premix burner such that the measures used for stabilization neither the flame stability, i. can permanently affect the flame site, nor lead to an increased nitrogen oxide emission. Rather, it should be possible to make flame-stabilizing precautions that are largely unrelated to the burner design and do not adversely affect the combustion characteristics optimized by the burner design. Thus, the measures to be taken should contribute to creating increased design flexibility in the design of premix burners and, in addition, to be able to be used on as many different burner systems as possible, without having to consider requirements with regard to special system optimization.

Die Lösung der der Erfindung zugrunde liegenden Aufgabe ist im Anspruch 1 angegeben. Ein erfindungsgemäßes Verfahren zur Flammenstabilisierung ist Gegenstand des Anspruches 8. Den Erfindungsgedanken vorteilhaft weiterbildende Merkmale sind Gegenstand der Unteransprüche sowie der Beschreibung insbesondere unter Bezugnahme auf die im Weiteren beschriebenen Ausführungsbeispiele zu entnehmen.The solution of the problem underlying the invention is specified in claim 1. An inventive method for flame stabilization is the subject of claim 8. The concept of the invention advantageously further features are the subject of the dependent claims and the description in particular with reference to the embodiments described below.

Erfindungsgemäß ist eine Vorrichtung zur Flammenstabilisierung in einem Brenner gemäß den Merkmalen des Oberbegriffes des Anspruches 1 derart ausgebildet, dass stromauf zur Flamme eine Katalysatoranordnung vorgesehen ist, durch die ein vom Luft-/Brennstoffgemisch (4) separates Luft-/Pilotbrennstoffgemisch hindurch strömt. Die Katalysatoranordnung verfügt über wenigstens zwei Katalysatorstufen, die in Strömungsrichtung des sich innerhalb des Brenners ausbildenden Luft-/Brennstoffgemisches hintereinander angeordnet sind, von denen die stromaufwärtig angeordnete Katalysatorstufe, der sogenannte POX-Katalysator, mit einem Luft-/Pilottbrennstoffgemisch bei einem Mischungsverhältnis λ < 1 durchsetzt wird, durch die das Luft-/Pilotbrennstoffgemisch teilweise oxidiert wird. Die in Durchströmungsrichtung stromabwärtige Katalysatorstufe, der sogenannte FOX-Katalysator, wird mit einem abgemagerten Luft-/Pilotbrennstoffgemisch mit einem Mischungsverhältnis λ > 1 durchsetzt, durch die das abgemagerte Luft-/Pilotbrennstoffgemisch vollständig unter Ausbildung eines inerten Heissgasstromes oxidiert wird.According to the invention a device for flame stabilization in a burner according to the features of the preamble of claim 1 is designed such that upstream of the flame, a catalyst arrangement is provided through which flows from the air / fuel mixture (4) separate air / pilot fuel mixture. The catalyst arrangement has at least two catalyst stages which are arranged one behind the other in the flow direction of the air / fuel mixture forming inside the burner, of which the upstream arranged catalyst stage, the so-called POX catalyst, with an air / pilot fuel mixture is penetrated at a mixing ratio λ <1, through which the air / pilot fuel mixture is partially oxidized. The downstream in the flow direction catalyst stage, the so-called FOX catalyst is interspersed with a lean air / pilot fuel mixture with a mixing ratio λ> 1, through which the lean air / pilot fuel mixture is completely oxidized to form an inert hot gas stream.

Das der erfindungsgemäßen Vorrichtung zugrundeliegende Verfahrensprinzip basiert auf einer Flammenstabilisierung mit Hilfe eines wenigstens 600°C, vorzugsweise bis zu 950°C, heißen, chemisch inerten Heissgasstromes, der in oder benachbart zur Flamme in die Brennkammer eingebracht wird. Das heiße, nicht reagierende Gas bewirkt eine thermische Stabilisierung der sich innerhalb der Brennkammer ausbildenden homogenisierten Flamme, wobei die inerte Natur der heißen Heissgasbestandteile es ermöglicht, den inerten Heissgasstrom an einer beliebigen Stelle innerhalb des Brennersystems der im Flammenbereich zuzuführen, ohne dabei die Flammenposition und die damit verbundene Mischzeiten zu verändern noch eine erhöhte Stickoxydbildung zu verursachen. Durch die erfindungsgemäße Maßnahme wird ein beispielloser Grad an Designflexibilität geschaffen, der es erlaubt, der erfindungsgemäß ausgebildete Vorrichtung, die einen sogenannten zweistufigen Pilotkatalysator aufweist, mit den unterschiedlichsten Brennersystemen zu kombinieren, weitgehend ohne dabei Optimierungserfordernisse die durch spezielle Systemzwänge verbunden wären, berücksichtigen zu müssen.The method principle underlying the device according to the invention is based on a flame stabilization with the aid of at least 600 ° C, preferably up to 950 ° C, hot, chemically inert hot gas stream, which is introduced into or adjacent to the flame in the combustion chamber. The hot, unreacted gas thermally stabilizes the homogenized flame forming within the combustion chamber, the inert nature of the hot hot gas components allowing the inert hot gas stream to be supplied anywhere in the burner system in the flame region without compromising flame position and temperature to change associated mixing times or to cause an increase in nitrogen oxide formation. The inventive measure an unprecedented degree of design flexibility is created, which allows the inventively constructed device having a so-called two-stage pilot catalyst to combine with a variety of burner systems, largely without having to take into account optimization requirements that would be connected by special system constraints.

Die zweistufig ausgebildete Katalysatoranordnung vermag mit ihrer ersten Katalysatorstufe, dem POX-Katalysator ein brennstoffreiches, d.h. fettes Luft-/Pilotbrennstoffgemisch mit einem Luft-/Pilotbrennstoffverhältnis λ < 1 derart zu katalysieren, dass stromab des POX-Katalysators ein teiloxidiertes Luft-/Pilotbrennstoffgemisch aus dem POX-Katalysator austritt. Über eine entsprechende Luftzuführung wird stromab des POX-Katalysators das teiloxidierte Luft-/Pilotbrennstoffgemisch mit Zuluft vermischt zur Ausbildung eines abgemagerten Luft-/Pilotbrennstoffgemisches, d.h. λ > 1, noch vor Eintritt in den FOX-Katalysator, innerhalb dem das abgemagerte Luft-/Pilotbrennstoffgemisch vollständig oxidiert wird. Schließlich wird nach Durchtritt durch die gesamte Katalysatoranordnung ein aufgrund der exothermen Oxidationsreaktionen sehr heißes und chemisch inertes Heissgas gebildet, das zur gezielten thermischen Flammenstabilisierung in den Bereich der Brennkammer, in dem sich die Flamme ausbildet, eingespeist wird.The two-stage catalyst arrangement can catalyze a fuel-rich, ie rich air / pilot fuel mixture with an air / pilot fuel ratio λ <1 with its first catalyst stage, the POX catalyst such that downstream of the POX catalyst, a partially oxidized air / pilot fuel mixture from the POX catalyst emerges. By means of a suitable air feed, the partially oxidized air / pilot fuel mixture is mixed with supply air downstream of the POX catalyst to form a lean air / pilot fuel mixture, ie λ> 1, before it enters the FOX catalyst. within which the lean air / pilot fuel mixture is completely oxidized. Finally, after passing through the entire catalyst arrangement, a hot gas that is very hot and chemically inert due to the exothermic oxidation reactions is formed, which is fed into the region of the combustion chamber in which the flame is formed for targeted thermal flame stabilization.

Kurze Beschreibung der ErfindungBrief description of the invention

Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnungen exemplarisch beschrieben. Es zeigen:

Fig. 1
schematisierte Darstellung der zweistufigen Katalysatoranordnung,
Fig. 2
schematisierte Darstellung der Katalysatoranordnung innerhalb eines Brennersystems,
Fig. 3
schematisierte Darstellung einer Katalysatoranordnung innerhalb einer zweistufigen Brenneranordnung sowie
Fig. 4
schematisierte Darstellung einer Katalysatoranordnung zur Realisierung einer Umschaltung zwischen chemischer und thermischer Flammenstabilisierung.
The invention will now be described by way of example without limitation of the general inventive idea by means of embodiments with reference to the drawings. Show it:
Fig. 1
schematic representation of the two-stage catalyst arrangement,
Fig. 2
schematic representation of the catalyst arrangement within a burner system,
Fig. 3
schematic representation of a catalyst arrangement within a two-stage burner assembly and
Fig. 4
Schematic representation of a catalyst arrangement for realizing a switch between chemical and thermal flame stabilization.

Wege zur Ausführung der Erfindung, gewerbliche VerwendbarkeitWays to carry out the invention, industrial usability

Die in Figur 1 dargestellte schematisierte Darstellung zeigt eine erfindungsgemäß ausgebildete Katalysatoranordnung 1, die einen Strömungskanal 2 umschließt, durch den in der Darstellung von links nach rechts eine Luftströmung L hindurchtritt. Innerhalb der Katalysatoranordnung 1 ist stromauf mittig zum Strömungskanal 2 ein erster Katalysator 3, der sogenannte POX-Katalysator vorgesehen, der über eine Vielzahl in Strömungsrichtung orientierte Katalysatorkanäle aufweist, die innwandig mit geeignet gewähltem Katalysatormaterial ausgekleidet sind und speziell zur Katalyse eines reichen Luft-/Pilotbrennstoffgemisches ausgewählt ist. Der POX-Katalysator 3 wird stromaufseitig von einem Luft-/Pilotbrennstoffgemisch 4 gespeist, das sich aus einem vollständig durchmischten Brennstoffstrom mPOX,fuel und einem Luftstrom mPOX,air zusammensetzt. Das in den POX-Katalysator 3 eintretende Luft-Pilotbrennstoffgemisch 4 verfügt über ein einstellbares Mischungsverhältnis λPOX sowie über eine gezielt einstellbare Gemischeintrittstemperatur TPOX,in. Da, wie bereits erwähnt, die Strömungskanäle des POX-Katalysators 3 mit einer katalytischen Schicht geeigneter Wahl überzogen sind, vorzugsweise mit Rhodium oder eine Rhodium enthaltende Materialverbindung, und über entsprechende Strömungsgeometrien verfügen, können jegliche Überhitzungen der Kanalwände durch die katalytisch unterstützte, exotherm wirkende Teiloxidation des im Luft-Pilotbrennstoffgemisch 4 enthaltenen Brennstoffes vermieden werden. Zugleich gewährleistet der POX-Katalysator 3 eine homogen durchmischte Austrittsmischung 5, deren Temperatur TPOX,out einerseits von der Eintrittstemperatur TPOX,in sowie dem Luft-Pilotbrennstoffverhältnis λPOX abhängt. Bei einer bevorzugten Ausführungsform liegt die Austrittstemperatur TPOX,out des Austrittsgemisches 5 in einem Bereich zwischen 600°C und 950°C, wobei die Austrittsmischung 5 vorwiegend aus CH4, N2, CO2 und H2O besteht. Darüber hinaus weist die Austrittsmischung 5 nur einen geringen Anteil des vorstehend beschriebenen Syngases auf, vorzugsweise mit Volumenprozenten unterhalb von 5%. Ebenso können Sauerstoffanteile O2 mit einem Volumenprozentanteil von < 5% in der Austrittsmischung 5 enthalten sein. Bei dem vorstehend beschriebenen Ausführungsbeispiel weist die den POX-Katalysator 3 zugeführte Luft-/Pilotbbrennstoffmischung 4 ein Luft-/Brennstoff-Verhältnis λPOX,in von typischer Weise zwischen 0,15 und 0,4 auf, d.h. die dem POX-Katalysator 3 zugeführte Luft-Pilotbrennstoffmischung ist verhältnismäßig brennstoffreich bzw. fett.In the FIG. 1 shown schematic representation shows an inventively designed catalyst assembly 1, which encloses a flow channel 2 through which passes in the illustration from left to right an air flow L. Inside the catalyst arrangement 1, upstream of the flow channel 2 there is provided a first catalyst 3, the so-called POX catalyst, which has a plurality of catalyst channels oriented in the direction of flow, which are coated internally with suitably selected catalyst material and specifically for the catalysis of a rich air / pilot fuel mixture is selected. The POX catalyst 3 is fed upstream of an air / pilot fuel mixture 4, which is composed of a fully mixed fuel flow m POX, fuel and an air flow m POX, air . The air-pilot fuel mixture 4 entering into the POX catalytic converter 3 has an adjustable mixing ratio λ POX as well as a selectively adjustable mixture inlet temperature T POX, in . Since, as already mentioned, the flow channels of the POX catalyst 3 are coated with a catalytic layer of suitable choice, preferably with rhodium or rhodium-containing material compound, and have corresponding flow geometries, any overheating of the channel walls by the catalytically assisted, exothermally acting partial oxidation of the fuel contained in the air-pilot fuel mixture 4 can be avoided. At the same time, the POX catalytic converter 3 ensures a homogeneously mixed outlet mixture 5 whose temperature T POX, out depends on the one hand on the inlet temperature T POX, in and on the air pilot fuel ratio λ POX . In a preferred embodiment, the outlet temperature T POX, out of the outlet mixture 5 is in a range between 600 ° C and 950 ° C, wherein the outlet mixture 5 consists mainly of CH 4 , N 2 , CO 2 and H 2 O. In addition, the outlet mixture 5 has only a small proportion of the syngas described above, preferably with volume percentages below 5%. Likewise, oxygen contents O 2 may be contained in the outlet mixture 5 with a volume percentage of <5%. In the embodiment described above, the air / pilot fuel mixture 4 supplied to the POX catalyst 3 has an air / fuel ratio λ POX, typically between 0.15 and 0.4, ie that supplied to the POX catalyst 3 Air pilot fuel mixture is relatively rich in fuel or fat.

Stromab des POX-Katalysators 3 wird dem Austrittsgemisch 5 eine vorgegebene Menge an den POX-Katalysator 3 umströmende Luft L zugemischt, mit einem gezielt einstellbaren Massenstrom 6 mbypass sowie einer vorgebbaren Lufttemperatur Tbypass, die identisch mit oder ähnlich zu der Eintrittstemperatur TPOX,in des dem POX-Katalysator 3 zugeführten Luft-Pilotbrennstoffgemisches 4 ist. Stromab des POX-Katalysators 3 bildet sich somit ein Gemisch aus, das stark abgemagert ist, typischer Weise mit einem Luft-Pilotbrennstoffverhältnis 4 < λ < 9. Das derart abgemagerte Luft-Pilotbrennstoffgemisch 7, mit einem geeignet dimensionierten Massenstrom mFOX,in wird dem in Strömungsrichtung durch die Katalysatoranordnung 1 stromab angeordneten, sogenannten FOX-Katalysator 8 zugeführt, wobei das abgemagerte Luft-Pilotbrennstoffgemisch 7 eine Temperatur TFOX,in aufweist, die kleiner als TPOX,out ist.Downstream of the POX catalyst 3, a predetermined amount of air L flowing around the POX catalytic converter 3 is admixed with the outlet mixture 5, with a specifically adjustable mass flow 6 m bypass and a predefinable air temperature T bypass which is identical to or similar to the inlet temperature T POX, is in the POX catalyst 3 supplied air-pilot fuel mixture 4. Downstream of the POX catalyst 3 thus forms a mixture which is heavily emaciated, typically with an air-pilot fuel ratio 4 <λ <9. The so emaciated Air pilot fuel mixture 7, with a suitably dimensioned mass flow m FOX, is fed to the so-called downstream FOX catalyst 8 in the flow direction through the catalyst assembly 1, wherein the lean air pilot fuel mixture 7 has a temperature T FOX, in , which is less than T POX, out is.

Hinsichtlich der Temperatur TPOX,out der Austrittsmischung 5 ist darauf zu achten, dass sie niedrig genug ist, um mögliche Selbstzündungen während der Durchmischung der Zuluft L mit der aus dem POX-Katalysator 3 austretenden teiloxidierten Luft-/Pilotbrennstoffmischung 5 sicher ausschließen zu können. Dies wird dadurch unterstützt, dass ein hoher Grad an Gleichverteilung innerhalb der Austrittsmischung 5 durch Vorsehen entsprechender Kanalführungen im POX-Katalysator 3 geschaffen wird, wodurch sogenannte Brennstofftaschen ausgeschlossen werden können. Ferner gewährleistet die innerhalb des POX-Katalysators 3 stattfindende Teiloxidation eine weitgehend vollständige Abreicherung des Massenstroms von Sauerstoff. Die Temperatur TFOX,in bewegt sich typischer Weise im Bereich zwischen 500°C und 950°C und hängt insbesondere von der Temperatur TPOX,out der Austrittsmischung 5 sowie der Menge der zugeführten Bypassluft mbypass ab. TFOX,in sollte jederzeit größer sein als die Zündtemperatur des FOX-Katalysators 8, so dass sichergestellt ist, dass das in den FOX-Katalysator 8 eintretende abgemagerte Luft-Pilotbrennstoffgemisch vollständig katalytisch oxidiert wird.With regard to the temperature T POX, out of the outlet mixture 5, care must be taken that it is low enough to be able to reliably rule out possible auto-ignition during the mixing of the supply air L with the partially oxidized air / pilot fuel mixture 5 emerging from the POX catalytic converter 3. This is assisted by providing a high degree of uniform distribution within the exit mixture 5 by providing corresponding channel guides in the POX catalyst 3, whereby so-called fuel pockets can be excluded. Furthermore, the partial oxidation taking place within the POX catalyst 3 ensures a substantially complete depletion of the mass flow of oxygen. The temperature T FOX, in typically moves in the range between 500 ° C and 950 ° C and depends in particular on the temperature T POX, out of the outlet mixture 5 and the amount of supplied bypass air m bypass . T FOX, in should always be greater than the ignition temperature of the FOX catalyst 8, so as to ensure that the lean air-pilot fuel mixture entering the FOX catalyst 8 is completely catalytically oxidized.

In vorteilhafter Weise können im Bereich zwischen dem POX-Katalysator 3 und dem FOX-Katalysator 8 zur vollständigen Durchmischung und Ausbildung eines abgemagerten Luft-Pilotbrennstoffgemisches zusätzliche turbolenzerzeugende Mittel, wie beispielsweise Venturi-Anordnungen oder ähnliche Vorrichtungen vorgesehen sein, um den Durchmischungsprozess zu unterstützen.Advantageously, in the region between the POX catalyst 3 and the FOX catalyst 8 for complete mixing and formation of a lean air-pilot fuel mixture additional turbulence generating means, such as Venturi arrangements or similar devices, may be provided to assist the mixing process.

Auch der FOX-Katalysator 8 ist innwandig mit geeignetem Katalysatormaterial ausgekleidet, bspw. Pd oder Pt, durch das gewährleistet werden kann, dass die den FOX-Katalysator 8 durchsetzende abgemagerte Luft-Pilotbrennstoffmischung 7 vollständig oxidiert wird, so dass jeglicher in der Mischung 7 vorhandene Brennstoff in CO2 und H2O umgewandelt wird. Das aus der Katalysatoranordnung 1 austretende Gasgemisch mFOX,out verfügt somit über eine sehr hohe Temperatur, typischer Weise TFOX,out bis zu 950°C und enthält hauptsächlich CO2, H2O, O2 und N2. Lediglich sehr geringe Anteile von CH4 können ebenso enthalten sein, die jedoch den chemisch inerten Charakter des Austrittsgases 9 nicht zu beeinträchtigen vermögen.Also, the FOX catalyst 8 is lined innenden with suitable catalyst material, for example. Pd or Pt, by which it can be ensured that the FOX catalyst 8 passing through lean-air pilot fuel mixture. 7 is completely oxidized so that any fuel present in the mixture 7 is converted to CO 2 and H 2 O. The gas mixture m FOX, out leaving the catalyst arrangement 1 thus has a very high temperature, typically T FOX, out up to 950 ° C. and contains mainly CO 2 , H 2 O, O 2 and N 2 . Only very small proportions of CH 4 can also be present, which, however, are unable to impair the chemically inert character of the exit gas 9.

Der vorzugsweise mit Platin oder Paladium innwandig ausgekleidete FOX-Katalysator 8 vermag die adiabatischen Prozesstemperaturen des den Katalysator durchsetzenden Gasgemisches zu erzielen ohne dabei selbst Materialüberhitzungen zu erliegen, zumal das den FOX-Katalysator 8 durchsetzende Gasgemisch stark abgemagert ist und die damit verbundenen adiabatischen Temperaturen weit unter den materialspezifischen Maximaltemperaturen liegen.The preferably with platinum or paladium innenden lined FOX catalyst 8 is able to achieve the adiabatic process temperatures of the gas mixture passing through the catalyst without succumbing itself material overheating, especially since the FOX catalyst 8 interspersed gas mixture is heavily emaciated and the associated adiabatic temperatures far below the material-specific maximum temperatures are.

Durchaus wäre es möglich, brennstoffreichere Gemische durch den FOX-Katalysator 8 zu leiten, doch müsste in diesem Fall eine zusätzliche Kühlvorkehrung am FOX-Katalysator 8 vorgesehen werden, wie beispielsweise eine zusätzliche Katalysatorkühlung mittels Bypassluft oder aber durch entsprechende Auswahl hochtemperaturfester Katalysatormaterialien. Auch könnte eine nur teilweise mit Katalysatormaterial vorgesehene Beschichtung der Katalysatorkanäle zu einer verbesserten Temperaturkontrolle innerhalb des FOX-Katalysators führen, doch würde diese Maßnahme andererseits zu einem erhöhten Anteil von CH4 im Abgasstrom 9 führen, wodurch der angestrebte chemische inerte Charakter des Abgasstromes 9 beeinträchtigt werden könnte.By all means it would be possible to pass fuel-rich mixtures through the FOX catalyst 8, but in this case additional cooling would have to be provided on the FOX catalyst 8, such as additional catalyst cooling by bypass air or by appropriate selection of high temperature catalyst materials. Also, an only partially provided with catalyst coating of the catalyst channels could lead to improved temperature control within the FOX catalyst, but this measure would on the other hand lead to an increased proportion of CH 4 in the exhaust stream 9, whereby the desired chemical inert character of the exhaust stream 9 are impaired could.

Mit Hilfe der vorstehend beschriebenen Katalysatoranordnung ist es möglich, einen heißen, inerten Gasstrom herzustellen und zur thermischen Stabilisierung einer innerhalb einer Brennkammer sich ausbildenden homogenisierten Flamme einzusetzen. Der inerte Charakter des Gasstromes gestattet es, den Gasstrom an einer beliebigen Stelle des Brenners oder der Brennkammer einzudüsen, ohne dabei nachhaltige Auswirkungen innerhalb der sich im Brenner ausbildenden Gemischbildung zu erleiden. Ebenso hat die erfindungsgemäße Einspeisung eines heißen inerten Gasstromes in den Brennerbereich keinerlei Einflüsse auf das Selbstzündungsverhalten sowie die Stickoxydbildung. Besondere Beachtung jedoch findet die erfindungsgemäß vorgeschlagene thermische Stabilisierung der homogenisierten Flamme innerhalb der Brennkammer durch die Tatsache, dass der Flammenort trotz Heissgaszuführung unverändert bleibt, wodurch eine Flammenverschiebung stromauf innerhalb des Brenners vermieden wird. Hierdurch werden die Durchmischungszeiten und die damit verbundene Stickoxydemission in keinster Weise beeinflusst. Dies verschafft eine verbesserte Designflexibilität verglichen zu den bisher bekannten und im Einsatz befindlichen Pilotierungsverfahren.With the aid of the catalyst arrangement described above, it is possible to produce a hot, inert gas stream and to use for thermal stabilization of a homogenized flame forming within a combustion chamber. The inert nature of the gas stream makes it possible to inject the gas stream at any point of the burner or the combustion chamber, without suffering lasting effects within the forming in the burner mixture formation. Likewise, the feed of the invention has a hot inert gas stream into the burner area no influence on the auto-ignition behavior and the formation of nitrogen oxides. Particular attention, however, finds the inventively proposed thermal stabilization of the homogenized flame within the combustion chamber by the fact that the flame location remains unchanged despite hot gas supply, whereby a flame displacement upstream within the burner is avoided. As a result, the mixing times and the associated nitrogen oxide emission are in no way affected. This provides improved design flexibility compared to previously known and used piloting methods.

Von besonderem Vorteil ist der Einsatz der erfindungsgemäß ausgebildeten Vorrichtung zur Flammenstabilisierung in Brennersystemen zur Befeuerung von Gasturbinenanlagen, in denen hohe Feuerungstemperaturen vorherrschen und Selbstzündungen von Luft-Brennstoffmischungen sehr viel wahrscheinlicher auftreten können. In derartigen Hochleistungsgasturbinenanlagen ist der Einsatz von bislang bekannten Pilotierungsverfahren verbunden mit den eingangs erläuterten Nachteilen in Bezug auf Flammenwanderung und Stickoxydbildung erschwert. Das erfindungsgemäße Verfahren läßt sich unabhängig von der Brennerlast ununterbrochen einsetzen, so insbesondere auch unter Vollastbedingungen, selbst wenn die Strömungsrate reduziert werden sollte. In vorteilhafter Weise können auf diese Weise aufwendige Spülungen von Brennstoffkanälen, wie sie bei bisher üblichen Pilotgaszuführungen zur Vermeidung von Rückzündungen in die Brennstoffleitung eingesetzt werden, vollständig verzichtet werden, so dass der damit verbundene zusätzliche Spülaufwand wegfällt.Of particular advantage is the use of the inventively designed device for flame stabilization in burner systems for firing gas turbine plants, in which high firing temperatures prevail and auto-ignition of air-fuel mixtures can occur much more likely. In such high-performance gas turbine systems, the use of hitherto known piloting methods, combined with the disadvantages explained in terms of flame migration and nitrogen oxide formation, is made more difficult. The method according to the invention can be used uninterrupted independently of the burner load, in particular under full load conditions, even if the flow rate should be reduced. Advantageously, can be completely dispensed with in this way consuming flushing of fuel channels, as used in previously common pilot gas supply to avoid flashback in the fuel line, so that the associated additional flushing eliminated.

Durch Vorsehen eines POX-Katalysators 3 mit einer geringen Zündtemperatur kann die Katalysatoranordnung während des gesamten Lastbereiches des Brenners zur Befeuerung beispielsweise einer Gasturbinenanlage, d.h. vom Anfahren bis zur Volllast, wirkungsvoll eingesetzt werden. So ist es insbesondere beim Anfahren einer Gasturbine vorteilhaft, das in den POX-Katalysator 3 eintretende Luft-/Pilotbrennstoffgemisch 4 vorzuwärmen, beispielsweise mit Hilfe einer elektrischen Vorheizung, die das Gemisch mPOX,air + mPOX,fuel auf die Zündtemperatur des POX-Katalysators 3 bringt. Ist der Katalysator während den Startbedingungen erst einmal erwärmt, so kann die elektrische Vorheizung ausgestellt werden. Durch das träge Temperaturverhalten des POX-Katalysators ist es insbesondere in dem vorstehend genannten Fall des Hochfahrens einer Gasturbine möglich, Luft-/Pilotbrennstoffgemische mit Temperaturen TPOX,in bereits wirkungsvoll zu katalysieren, obgleich TPOX,in bis zu 200°C geringer sein kann als die Zündtemperatur des Katalysators selbst. Auch ist es möglich, insbesondere unter Startbedingungen das Luft-/Pilotbrennstoffverhältnis λPOX durch entsprechende Variation der Brennstoffrate mPOX,fuel oder der Luftströmungsrate mPOX,air entsprechend zu variieren und einzustellen.By providing a POX catalyst 3 with a low ignition temperature, the catalyst arrangement can be used effectively throughout the entire load range of the burner for firing, for example, a gas turbine plant, ie from start to full load. Thus, it is particularly advantageous when starting a gas turbine to preheat the entering into the POX catalyst 3 air / pilot fuel mixture 4, for example by means of an electric Preheating, which brings the mixture M POX, air + m POX, fuel to the ignition temperature of the POX catalyst 3. Once the catalyst has been heated during the starting conditions, the electric preheater can be turned off. Due to the sluggish temperature behavior of the POX catalyst, it is possible, especially in the abovementioned case of starting up a gas turbine, to catalyze air / pilot fuel mixtures with temperatures T POX in an already effective manner, although T POX may be lower in up to 200 ° C. It is also possible, in particular under start conditions , to vary and set the air / pilot fuel ratio λ POX correspondingly by varying the fuel rate m POX, fuel or the air flow rate m POX, air accordingly.

Figur 2 zeigt eine schematisierte Darstellung einer bevorzugten Anordnungsmöglichkeit der Katalysatoranordnung 1 innerhalb eines Brenners 10, der vorzugsweise als Vormischbrenner ausgebildet ist und der gemäß Pfeildarstellung in Strömungsrichtung von einem sich innerhalb des Brenners 10 ausbildenden Luft-/Brennstoffgemisches durchsetzt wird. Innerhalb des Vormischbrenners 10 bildet sich aufgrund strömungsdynamischer Rahmenbedingungen, bspw. unter Einsatz eines Drallerzeugers, eine sich in Strömungsrichtung ausbildende Drallströmung D aus, die aufgrund der unsteten Strömungsquerschnittserweiterung zwischen Vormischbrenner 10 und Brennkammer 11 aufplatzt und eine Rückströmzone 12 bildet, in der sich eine homogene Flamme 13 räumlich stationär ausbildet. FIG. 2 shows a schematic representation of a preferred arrangement possibility of the catalyst assembly 1 within a burner 10, which is preferably designed as a premix burner and the arrow is traversed in the flow direction of an inside of the burner 10 forming air / fuel mixture. Within the premix burner 10, a swirling flow D forming in the flow direction forms due to flow-dynamic conditions, for example using a swirl generator, which bursts due to the unsteady flow cross-sectional widening between premix burner 10 and combustion chamber 11 and forms a return flow zone 12, in which a homogeneous flame 13 spatially stationary training.

Die Katalysatoranordnung 1 ist im gezeigten Ausführungsbeispiel zentrisch innerhalb des Strömungsverhältnisses im Vormischbrenner 10 angeordnet. Zur vollständigen Durchmischung des sich innerhalb des Vormischbrenners einstellenden Luft-/Brennstoffgemisches sowie zu Stabilisierung der Flamme sind zusätzliche Drallerzeuger bzw. Wirbelgeneratoren 14 vorgesehen, die radial die Katalysatoranordnung 1 umgeben.In the exemplary embodiment shown, the catalyst arrangement 1 is arranged centrically within the flow ratio in the premix burner 10. For complete mixing of the adjusting within the premix burner air / fuel mixture and to stabilize the flame additional swirl generator or vortex generators 14 are provided which radially surround the catalyst assembly 1.

Selbstverständlich ist es möglich, die Katalysatoranordnung 1 auch an einen anderen, innerhalb des Vormischbrenners 10 befindlichen Bereich zu positionieren. Aus dem in Figur 2 dargestellten Ausführungsbeispiel ist ferner zu entnehmen, dass der Katalysatoranordnung 1 zur Ausbildung des heißen, inerten Heissgasstromes getrennt zur Brenntsoff-/Luftversorgung des Brenner ein separates Luft-/Pilotbrennstoffgemisch (4) zugeführt wird. Das die Katalysatoranordnung 1 umströmende Luft-Brennstoffgemisch wird in der Brennkammer 11 unter Ausbildung einer homogenen Flamme 13 zur Zündung gebracht.Of course, it is possible to position the catalyst assembly 1 also to another located within the premix burner 10 area. From the in FIG. 2 illustrated embodiment, it can be seen that the catalyst assembly 1 to form the hot, inert hot gas stream separately to Brenntsoff- / air supply to the burner, a separate air / pilot fuel mixture (4) is supplied. The air-fuel mixture flowing around the catalyst arrangement 1 is ignited in the combustion chamber 11 to form a homogeneous flame 13.

In Figur 3 ist eine weitere Möglichkeit des Einsatzes der erfindungsgemäß ausgebildeten Katalysatoranordnung 1 dargestellt. Hier sei angenommen, dass die Katalysatoranordnung 1, wie sie im Einzelnen aus der vorstehend beschriebenen Figur 1 zu entnehmen ist, als eine erste Brennerstufe innerhalb einer zweistufigen Brenneranordnung eingesetzt wird. Die Katalysatorstufe 1 wird dabei vom gesamten Luft-/Brennstoffgemisch, das durch die Brenneranordnung geführt wird, durchsetzt und bildet stromab zur Katalysatoranordnung 1 ein chemisch inertes Heissgas 9 aus, das unmittelbar einer zweiten Brennerstufe 15 zugeführt wird, in der dem inerten chemischen Heissgas zusätzlicher Brennstoff sowie Bypassluft beigemischt wird. Das sich hierbei ausbildende Heissgas-/Brennstoffgemisch entzündet sich letztlich in Form einer homogenen Flamme 13 stromab der zweiten Brennerstufe 15.In FIG. 3 Another possibility of using the inventively designed catalyst assembly 1 is shown. Here it is assumed that the catalyst arrangement 1, as described in detail from the above FIG. 1 can be seen as a first burner stage is used within a two-stage burner assembly. The catalyst stage 1 is thereby penetrated by the entire air / fuel mixture, which is passed through the burner assembly, and forms downstream of the catalyst assembly 1, a chemically inert hot gas 9, which is fed directly to a second burner stage 15, in the inert chemical hot gas additional fuel and bypass air is added. The hot gas / fuel mixture which forms in this case ultimately ignites in the form of a homogeneous flame 13 downstream of the second burner stage 15.

Ein bevorzugtes Ausführungsbeispiel für ein mögliches Design des POX-Katalysators 3 sieht eine Vielzahl den Katalysator 3 durchsetzende Strömungskanäle vor, die in zwei Gruppen aufteilbar sind. So wird durch eine erste Gruppe von Strömungskanälen, die innwandig mit Katalysatormaterial beschichtet sind, beispielsweise mit Rodium, das Luft-/Pilotbrennstoffgemisch 4 geleitet. Getrennt hiervon wird durch die zweite Gruppe von den POX-Katalysator 3 durchsetzenden Strömungskanälen, die nicht notwendigerweise mit Katalysatormaterial beschichtet sein müssen, von Luft durchströmt. Der Vorteil einer derartigen Ausführungsform liegt in einer verbesserten Durchmischung der Austrittströmungen und ermöglicht überdies eine bessere Kontrolle über die POX-Katalysatortemperatur TPOX, zumal die Strömungsraten beider Strömungsanteile getrennt voneinander variabel eingestellt werden können und die Zuluft für eine gezielte Kühlung des POX-Katalysators 3 dient.A preferred embodiment for a possible design of the POX catalytic converter 3 provides a plurality of flow channels passing through the catalytic converter 3, which can be divided into two groups. Thus, the air / pilot fuel mixture 4 is passed through a first group of flow channels which are coated with catalyst material, for example with rodium. Separately, air flows through the second group of POX catalyst 3 passing through flow channels, which need not necessarily be coated with catalyst material. The advantage of such an embodiment lies in an improved mixing of the outlet flows and also allows better control over the POX catalyst temperature T POX , especially since the flow rates of both flow components are set separately variable can be and the supply air for a targeted cooling of the POX catalyst 3 is used.

In Figur 4 ist eine vergleichbar zur Figur 1 dargestellte Katalysatoranordnung 1 dargestellt, mit längs eines Strömungskanals 2 vorgesehenen POX-Katalysator 3 und FOX-Katalysator 8. Grundsätzlich ist es möglich, das Betriebskonzept, das der Erfindung zugrundeliegt derart zu modifizieren, so dass die Herstellung eines hochreaktiven Syngas enthaltenen Heissgases möglich wird. Die Erzeugung eines hochreaktiven Syngas enthaltenen Heissgases könnte insbesondere für schwierige Betriebssituationen während des Einschaltvorganges des Brenners sowie unter sehr niedrigen Lastbedingungen vorteilhaft sein. Um ein derartiges Syngas enthaltenes Heissgas zu erzeugen, wird im Unterschied zur beschriebenen Situation in Figur 1 keine Zuluft L, d.h. mbypass = 0, beigemischt. Somit erfährt die aus dem POX-Katalysator 3 austretende Austrittsmischung 5 keine Abmagerung. Das dem POX-Katalysator 3 zugeführte Luft-/Pilotbrennstoffverhältnis wird typischer Weise so gewählt, dass eine Syngas-Erzeugung unterstützt wird. Typischer Weise beträgt das Luft-/Pilotbrennstoffverhältnis λPOX-Werte > 0,25. Da das aus dem POX-Katalysator 3 austretende Austrittsgemisch 5 keine oder nur geringe Anteile von Sauerstoff enthält, typischer Weise < 3%, findet im nachfolgenden FOX-Katalysator 8 aufgrund des Sauerstoffmangels nur eine begrenzte Oxidationsreaktion statt. Somit werden die zur Flammenstabilisierung erforderlichen reaktive Heissgase vornehmlich im POX-Katalysator 3 gebildet.In FIG. 4 is a comparable to FIG. 1 In principle, it is possible to modify the operating concept underlying the invention so that the production of a highly reactive syngas contained hot gas is possible. The generation of a highly reactive syngas containing hot gas could be particularly advantageous for difficult operating situations during the switching of the burner and under very low load conditions. In order to produce such a syngas contained hot gas, unlike the situation described in FIG. 1 no supply air L, ie m bypass = 0, admixed. Thus exiting from the POX catalyst 3 exit mixture 5 undergoes no emaciation. The air / pilot fuel ratio supplied to the POX catalyst 3 is typically selected to promote syngas generation. Typically, the air / pilot fuel ratio λ is POX values> 0.25. Since the outlet mixture 5 leaving the POX catalyst 3 contains no or only small amounts of oxygen, typically <3%, only a limited oxidation reaction takes place in the downstream FOX catalyst 8 because of the lack of oxygen. Thus, the reactive hot gases required for flame stabilization are predominantly formed in the POX catalyst 3.

Problematisch bei einer derartigen Betriebsweise ist jedoch das Umschalten von dem vorstehend beschriebenen Syngas erzeugenden Mode zum erfindungsgemäßen Standardszenario, bei dem mit Hilfe der Katalysatoranordnung ausschließlich heiße inerte Gase gebildet werden. Problematisch ist, ausgehend vom Syngas erzeugenden Mode, bei dem mbypass = 0 ist, ein Zumischungsverhältnis von Bypassluft, bei dem das in den FOX-Katalysator 8 einströmende Luft-/Brennstoffgemisch 7 über ein stöchiometrisches Verhältnis verfügt, bei dem extreme Überhitzungen innerhalb des FOX-Katalysators 8 auftreten können, die irreparable Schäden verursachen können.However, the problem with such an operating mode is the switching from the above-described syngas generating mode to the standard scenario according to the invention, in which only hot inert gases are formed with the aid of the catalyst arrangement. A problem is, starting from the syngas generating mode in which m bypass = 0, a mixing ratio of bypass air, in which the flowing into the FOX catalyst 8 air / fuel mixture 7 has a stoichiometric ratio, in the extreme overheating within the FOX -Catalyst 8 may occur, which can cause irreparable damage.

Um dies zu vermeiden wird folgende Verfahrenstechnik vorgeschlagen: Im Falle der Niedriglast, d.h. im Syngas erzeugenden Mode, bei dem mbypass = 0 und typischerweise 0,25 < λPOX < 0,6 vorherrscht, gilt folgendes zu beachten. Beim Übergang in das erfindungsgemäße Standardszenario gilt es zwei Maßnahmen zeitgleich zu treffen: Dem sich innerhalb des Brenners ausbildenden Luft-/Brennstoffgemisch, das zur Zündung innerhalb der Brennkammer eine homogene Flamme ausbildet, wird ein wenig mehr Brennstoff beigegeben, unter Beachtung, dass die Flamme nicht ausgeblasen wird. Zeitgleich wird das Luft-/Pilotbrennstoffverhältnis λPOX des dem POX-Katalysator 3 zugeführten Luft-/Pilotbrennstoffgemisches 4 auf Werte < 0,15 reduziert, indem entweder der Massenstrom mPOX,fuel gesteigert oder der Luftzustrom mPOX,air reduziert wird. Das hierdurch entstehende fettere, in den POX-Katalysator 3 eintretende Luft-/Pilotbrennstoffgemisch 4 verfügt über eine niedrigere adiabatische Temperatur, bei der keine Syngasproduktion zustande kommt. Infolgedessen sinkt die Austrittstemperatur TPOX,out auf Werte zwischen 500 °C und 700 °C ab. Sobald die Bypassluft mbypass hinzugefügt wird, sinkt die Eintrittstemperatur TFOX,in weit unter Werte der Austrittstemperatur TPOX,out ab und nimmt Temperaturen von sehr viel kleiner als 600°C an. Hierbei sind die Strömungsraten mPOX,fuel, mPOX,air sowie mbypass und daraus resultierend mFOX,in, das TPOX,out und TFOX,in unter der Selbstzündungsschwelle eines stöchiometrischen Luftbrennstoffgemisches, wobei TFOX,in kleiner als die Zündtemperatur des FOX-Katalysators 8 ist. Aus diesem Grunde tritt keine Selbstzündung auf und der FOX-Katalysator 8 erleidet keine Überhitzungen, obwohl die Austrittsmischung 5 des POX-Katalysators 3 in Mischung mit der Zuluft mbypass für eine kurze Zeitspanne ein stöchiometrisches Gemisch darstellen. Der Betrag von mbypass wird anschließend kontinuierlich gesteigert, so dass das Luft-/Pilotbrennstoffverhältnis der in den FOX-Katalysator 8 eintretenden Mischung 7 λFOX,in ≥ 1 ist und ebenso λPOX,in ebenso gesteigert werden kann, bis der Volllastbereich erreicht wird und die Katalysatoranordnung ausschließlich chemisch inerte Heissgase erzeugt.In order to avoid this, the following process technology is proposed: In the case of the low load, ie in the syngas generating mode, in which m bypass = 0 and typically 0.25 <λ POX <0.6 prevails, the following should be noted. When making the transition to the standard scenario according to the invention, two measures must be taken at the same time: A little more fuel is added to the air / fuel mixture forming inside the burner, which forms a homogeneous flame for ignition within the combustion chamber, taking into account that the flame is not is blown out. At the same time, the air / pilot fuel ratio λ POX of the air / pilot fuel mixture 4 fed to the POX catalyst 3 is reduced to values <0.15 by either increasing the mass flow m POX, fuel or reducing the air flow m POX, air . The thereby resulting fatter, entering the POX catalyst 3 air / pilot fuel mixture 4 has a lower adiabatic temperature at which no syngas production comes about. As a result, the exit temperature T POX, out drops to values between 500 ° C and 700 ° C. As soon as the bypass air is added to the bypass , the inlet temperature T FOX drops far below values of the outlet temperature T POX, out and assumes temperatures of much less than 600 ° C. Here, the flow rates m POX, fuel , m POX, air and m bypass and resulting m FOX, in , the T POX, out and T FOX, in below the autoignition threshold of a stoichiometric air fuel mixture, where T FOX, in less than the ignition temperature of the FOX catalyst 8. For this reason, no self-ignition occurs and the FOX catalyst 8 suffers no overheating, although the outlet mixture 5 of the POX catalyst 3 in mixture with the supply m bypass for a short period of time represent a stoichiometric mixture. The amount of m bypass is then continuously increased so that the air / pilot fuel ratio of the mixture entering the FOX catalyst 8 is 7 λ FOX, in ≥ 1, and also λ POX, can also be increased until the full load range is reached and the catalyst assembly produces only chemically inert hot gases.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Katalysatoranordnungcatalyst assembly
22
Strömungskanalflow channel
33
POX-KatalysatorPOX-catalyst
44
Eintrittsluft-/Pilotbrennstoffgemisch in den POX-KatalysatorIntake air / pilot fuel mixture into the POX catalyst
55
Austrittsmischungexit mixture
66
BypassmassenstromBypass mass flow
77
Eintritts-Luft-/Brennstoffmischung in den FOX-KatalysatorEntry air / fuel mixture into the FOX catalyst
88th
FOX-KatalysatorFOX-catalyst
99
chemisch inerte Heissgasechemically inert hot gases
1010
Brennerburner
1111
Brennkammercombustion chamber
1212
Rückströmzonebackflow
1313
homogene Flammehomogeneous flame
1414
Wirbelgeneratorvortex generator
1515
zweite Brennerstufesecond burner stage
DD
Drallströmungswirl flow
LL
Zuluftsupply air
FF
Brennstofffuel

Claims (13)

  1. Device in a burner (10), with a burner housing at least partially enclosing a burner volume, into which may be introduced via at least one fuel line, fuel, and via at least one air feed means, air, forming an air/fuel mixture spreading in a preferred flow direction, which in a combustion chamber (11) connecting downstream of the burner housing may be ignited forming a stationary flame (13), wherein upstream to the flame (13) is provided a catalyst arrangement (1) through which an air/pilot fuel mixture (4) separate from the air/fuel mixture is flowable, and wherein the air/pilot fuel mixture (4) fed to the catalyst arrangement (1) can be fed separately to the air/fuel mixture developing inside the burner volume, which air/fuel mixture is ignited in the combustion chamber (11), characterized in that the catalyst arrangement (1) has at least two catalyst stages which are located one behind the other in the through-flow direction, of which the catalyst stage (3) located upstream, the so-called POX-catalyst, is flow-washable by an air/pilot fuel mixture with an air/pilot fuel mixture ratio λ < 1, by which catalyst stage (3) the air/pilot fuel mixture (4) is partially oxidized, and of which catalyst stages the downstream catalyst stage (8), the so-called FOX-catalyst, is flow-washable by a leaned air/pilot fuel mixture (7) with a mixture ratio λ > 1, by which the leaned air/pilot fuel mixture is completely oxidized forming an inert hot gas flow (9).
  2. Device according to Claim 1,
    characterized in that, between the POX- and FOX catalysts (3,8) an air feed (L) is provided, by which feed air can be added to the partially oxidized air/pilot fuel mixture (5) issuing from the POX-catalyst (3) in such a way that before entry into the FOX-catalyst (8) the leaned air/pilot fuel mixture (7) is formed.
  3. Device according to either of Claims 1 or 2,
    characterized in that upstream of the FOX-catalyst (8) flow turbulence-producing means (14) are provided, which serve for a complete mixing-through of the leaned air/pilot fuel mixture (4).
  4. Device according to one of Claims 1 to 3,
    characterized in that the burner is a premix burner.
  5. Device according to Claim 4,
    characterized in that the premix burner (10) has a premix burner housing preferably conically widening in the flow direction, to which in the flow direction the combustion chamber (11) is directly or indirectly connected separately by a mixing tube, and in that the catalyser arrangement (1) is provided inside the burner volume enclosed by the premix burner (10) or by the mixing tube.
  6. Device according to one of Claims 1 to 5
    characterized in that a fuel feed, preferably in the form of an air/fuel mixture, is provided indirectly or directly downstream of or parallel to the catalyst arrangement (1), by means of which fuel feed fuel can be added to the hot gas flow issuing from the catalyst arrangement (1).
  7. Method for flame stabilization in a burner (10), with a burner housing at least partially enclosing a burner volume, into which are introduced via at least one fuel line, fuel, and, via at least one air feed means, air, forming an air/fuel mixture spreading in a preferred flow direction, which, in a combustion chamber (11) connecting downstream of the burner housing is ignited forming a stationary flame, the flame (13) being stabilized by an inert hot gas flow (9) of at least 600°C which is introduced into the combustion chamber (11) in or adjacent to the flame (13), and the inert hot gas flow (9) being produced by catalytic oxidation of an air/pilot fuel mixture, characterized in that the catalytic oxidation takes place in two separate stages, in a first stage, the so-called POX-catalyst (3), in which an air/pilot fuel mixture (4) with a mixture ratio λ < 1 is partially oxidized and then leaned by admixing with air (L) and is fed to a second stage, the so-called FOX-catalyst (8) as a leaned air/pilot fuel mixture (7) with a mixture ratio λ > 1, in which second stage the leaned air/pilot fuel mixture (7) is completely oxidized and issues as an inert hot gas (9).
  8. Method according to Claim 7,
    characterized in that the air/pilot fuel mixture (4) for forming the inert hot gas flow (9) is formed and fed separately to the air/fuel mixture developing inside the burner volume, which air/fuel mixture is ignited inside the combustion chamber.
  9. Method according to Claim 7 or 8,
    characterized in that the air/pilot fuel mixture (4) entering the POX-catalyst (3) has an air/pilot fuel ratio λ of 0.15 ≤ λ ≤ 0.4, and
    in that the partially oxidized air/pilot fuel mixture (5) issuing directly from the POX-catalyst contains CH4, N2, CO2, H2O, and also a syngas content, i.e. H2 and CO, of less than 5% volume and an O2 content of less than 5% volume.
  10. Method according to one of Claims 7 to 9,
    characterized in that the inert hot gas flow (9) has temperatures between 600 and 950°C and consists almost entirely of CO2, H2O, O2 and N2.
  11. Method according to one of Claims 7 to 10,
    characterized in that the whole air-fuel mixture developing inside the burner volume catalyses to form the inert hot gas flow (9) then mixes with fuel and is ignited forming the flame (13) inside the combustion chamber (11).
  12. Use of the device according to one of Claims 1 to 6 for the stabilization of a homogenous flame (13) developing inside a combustion chamber (11) fired by a burner (1),
    characterized in that, depending on the burner load, the flame (13) is stabilized thermally or chemically by feed of a hot gas containing syngas consisting of H2 and CO.
  13. Use according to Claim 12,
    characterized in that, under start conditions or low load conditions, the flame (13) is chemically stabilized by the partially oxidized air/pilot fuel mixture (5) that issues directly from the POX-catalyst (3) being fed to the FOX-catalyst (8) without leaning, and in that, under normal- or high load conditions, the flame (13) is thermally stabilized by the partially oxidized air/pilot fuel mixture (5) that issues from the POX-catalyst (3) being leaned before entry into the FOX-catalyst (8).
EP05717130A 2004-03-30 2005-03-23 Device and method for stabilizing the flame in a burner Not-in-force EP1730441B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004015607 2004-03-30
PCT/EP2005/051333 WO2005095855A1 (en) 2004-03-30 2005-03-23 Device and method for stabilizing the flame in a burner

Publications (2)

Publication Number Publication Date
EP1730441A1 EP1730441A1 (en) 2006-12-13
EP1730441B1 true EP1730441B1 (en) 2008-03-19

Family

ID=34962516

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05717130A Not-in-force EP1730441B1 (en) 2004-03-30 2005-03-23 Device and method for stabilizing the flame in a burner

Country Status (6)

Country Link
US (1) US7467942B2 (en)
EP (1) EP1730441B1 (en)
AT (1) ATE389852T1 (en)
CA (1) CA2561255A1 (en)
DE (1) DE502005003324D1 (en)
WO (1) WO2005095855A1 (en)

Families Citing this family (73)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE502005003324D1 (en) 2004-03-30 2008-04-30 Alstom Technology Ltd DEVICE AND METHOD FOR FLAME STABILIZATION IN A BURNER
US7444820B2 (en) * 2004-10-20 2008-11-04 United Technologies Corporation Method and system for rich-lean catalytic combustion
EP2080952A1 (en) * 2008-01-17 2009-07-22 L'AIR LIQUIDE, Société Anonyme pour l'Etude et l'Exploitation des Procédés Georges Claude Burner and method for alternately implementing an oxycombustion and an air combustion
WO2009121008A2 (en) 2008-03-28 2009-10-01 Exxonmobil Upstream Research Company Low emission power generation and hydrocarbon recovery systems and methods
CA2715186C (en) 2008-03-28 2016-09-06 Exxonmobil Upstream Research Company Low emission power generation and hydrocarbon recovery systems and methods
CN102177326B (en) 2008-10-14 2014-05-07 埃克森美孚上游研究公司 Methods and systems for controlling the products of combustion
US8479720B1 (en) 2008-10-16 2013-07-09 Oscar Enrique Figueroa Heating device and method
US8684276B2 (en) * 2009-08-20 2014-04-01 Enerco Group, Inc. Portable catalytic heater
EA023673B1 (en) 2009-11-12 2016-06-30 Эксонмобил Апстрим Рисерч Компани Low emission power generation and hydrocarbon recovery system and method
EP2336083A1 (en) * 2009-12-17 2011-06-22 Topsøe Fuel Cell A/S Gas generator and processes for the conversion of a fuel into an oxygen-depleted gas and/or hydrogen-enriched gas
MX341981B (en) 2010-07-02 2016-09-08 Exxonmobil Upstream Res Company * Stoichiometric combustion with exhaust gas recirculation and direct contact cooler.
MY160833A (en) 2010-07-02 2017-03-31 Exxonmobil Upstream Res Co Stoichiometric combustion of enriched air with exhaust gas recirculation
CA2801499C (en) 2010-07-02 2017-01-03 Exxonmobil Upstream Research Company Low emission power generation systems and methods
AU2011271633B2 (en) 2010-07-02 2015-06-11 Exxonmobil Upstream Research Company Low emission triple-cycle power generation systems and methods
TWI593872B (en) 2011-03-22 2017-08-01 艾克頌美孚上游研究公司 Integrated system and methods of generating power
TWI563166B (en) 2011-03-22 2016-12-21 Exxonmobil Upstream Res Co Integrated generation systems and methods for generating power
TWI563165B (en) 2011-03-22 2016-12-21 Exxonmobil Upstream Res Co Power generation system and method for generating power
TWI564474B (en) 2011-03-22 2017-01-01 艾克頌美孚上游研究公司 Integrated systems for controlling stoichiometric combustion in turbine systems and methods of generating power using the same
CN104428490B (en) 2011-12-20 2018-06-05 埃克森美孚上游研究公司 The coal bed methane production of raising
US9353682B2 (en) 2012-04-12 2016-05-31 General Electric Company Methods, systems and apparatus relating to combustion turbine power plants with exhaust gas recirculation
US10273880B2 (en) 2012-04-26 2019-04-30 General Electric Company System and method of recirculating exhaust gas for use in a plurality of flow paths in a gas turbine engine
US9784185B2 (en) 2012-04-26 2017-10-10 General Electric Company System and method for cooling a gas turbine with an exhaust gas provided by the gas turbine
US10215412B2 (en) 2012-11-02 2019-02-26 General Electric Company System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system
US9611756B2 (en) 2012-11-02 2017-04-04 General Electric Company System and method for protecting components in a gas turbine engine with exhaust gas recirculation
US9869279B2 (en) 2012-11-02 2018-01-16 General Electric Company System and method for a multi-wall turbine combustor
US9631815B2 (en) 2012-12-28 2017-04-25 General Electric Company System and method for a turbine combustor
US9803865B2 (en) 2012-12-28 2017-10-31 General Electric Company System and method for a turbine combustor
US10161312B2 (en) 2012-11-02 2018-12-25 General Electric Company System and method for diffusion combustion with fuel-diluent mixing in a stoichiometric exhaust gas recirculation gas turbine system
US9599070B2 (en) 2012-11-02 2017-03-21 General Electric Company System and method for oxidant compression in a stoichiometric exhaust gas recirculation gas turbine system
US9574496B2 (en) 2012-12-28 2017-02-21 General Electric Company System and method for a turbine combustor
US10107495B2 (en) 2012-11-02 2018-10-23 General Electric Company Gas turbine combustor control system for stoichiometric combustion in the presence of a diluent
US9708977B2 (en) 2012-12-28 2017-07-18 General Electric Company System and method for reheat in gas turbine with exhaust gas recirculation
US10208677B2 (en) 2012-12-31 2019-02-19 General Electric Company Gas turbine load control system
US9581081B2 (en) 2013-01-13 2017-02-28 General Electric Company System and method for protecting components in a gas turbine engine with exhaust gas recirculation
US9512759B2 (en) 2013-02-06 2016-12-06 General Electric Company System and method for catalyst heat utilization for gas turbine with exhaust gas recirculation
TW201502356A (en) 2013-02-21 2015-01-16 Exxonmobil Upstream Res Co Reducing oxygen in a gas turbine exhaust
US9938861B2 (en) 2013-02-21 2018-04-10 Exxonmobil Upstream Research Company Fuel combusting method
WO2014133406A1 (en) 2013-02-28 2014-09-04 General Electric Company System and method for a turbine combustor
TW201500635A (en) 2013-03-08 2015-01-01 Exxonmobil Upstream Res Co Processing exhaust for use in enhanced oil recovery
AU2014226413B2 (en) 2013-03-08 2016-04-28 Exxonmobil Upstream Research Company Power generation and methane recovery from methane hydrates
US20140250945A1 (en) 2013-03-08 2014-09-11 Richard A. Huntington Carbon Dioxide Recovery
US9618261B2 (en) 2013-03-08 2017-04-11 Exxonmobil Upstream Research Company Power generation and LNG production
TWI654368B (en) 2013-06-28 2019-03-21 美商艾克頌美孚上游研究公司 System, method and media for controlling exhaust gas flow in an exhaust gas recirculation gas turbine system
US9835089B2 (en) 2013-06-28 2017-12-05 General Electric Company System and method for a fuel nozzle
US9617914B2 (en) 2013-06-28 2017-04-11 General Electric Company Systems and methods for monitoring gas turbine systems having exhaust gas recirculation
US9631542B2 (en) 2013-06-28 2017-04-25 General Electric Company System and method for exhausting combustion gases from gas turbine engines
US9587510B2 (en) 2013-07-30 2017-03-07 General Electric Company System and method for a gas turbine engine sensor
US9903588B2 (en) 2013-07-30 2018-02-27 General Electric Company System and method for barrier in passage of combustor of gas turbine engine with exhaust gas recirculation
US9951658B2 (en) 2013-07-31 2018-04-24 General Electric Company System and method for an oxidant heating system
CN103499106B (en) * 2013-09-11 2015-10-14 中国科学院力学研究所 A kind of method expanding the supersonic combustion flame stabilization limit
US9752458B2 (en) 2013-12-04 2017-09-05 General Electric Company System and method for a gas turbine engine
US10030588B2 (en) 2013-12-04 2018-07-24 General Electric Company Gas turbine combustor diagnostic system and method
US10227920B2 (en) 2014-01-15 2019-03-12 General Electric Company Gas turbine oxidant separation system
US9863267B2 (en) 2014-01-21 2018-01-09 General Electric Company System and method of control for a gas turbine engine
US9915200B2 (en) 2014-01-21 2018-03-13 General Electric Company System and method for controlling the combustion process in a gas turbine operating with exhaust gas recirculation
US10079564B2 (en) 2014-01-27 2018-09-18 General Electric Company System and method for a stoichiometric exhaust gas recirculation gas turbine system
US10047633B2 (en) 2014-05-16 2018-08-14 General Electric Company Bearing housing
US10060359B2 (en) 2014-06-30 2018-08-28 General Electric Company Method and system for combustion control for gas turbine system with exhaust gas recirculation
US10655542B2 (en) 2014-06-30 2020-05-19 General Electric Company Method and system for startup of gas turbine system drive trains with exhaust gas recirculation
US9885290B2 (en) 2014-06-30 2018-02-06 General Electric Company Erosion suppression system and method in an exhaust gas recirculation gas turbine system
US9819292B2 (en) 2014-12-31 2017-11-14 General Electric Company Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine
US9869247B2 (en) 2014-12-31 2018-01-16 General Electric Company Systems and methods of estimating a combustion equivalence ratio in a gas turbine with exhaust gas recirculation
US10788212B2 (en) 2015-01-12 2020-09-29 General Electric Company System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation
US10094566B2 (en) 2015-02-04 2018-10-09 General Electric Company Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation
US10253690B2 (en) 2015-02-04 2019-04-09 General Electric Company Turbine system with exhaust gas recirculation, separation and extraction
US10316746B2 (en) 2015-02-04 2019-06-11 General Electric Company Turbine system with exhaust gas recirculation, separation and extraction
US10267270B2 (en) 2015-02-06 2019-04-23 General Electric Company Systems and methods for carbon black production with a gas turbine engine having exhaust gas recirculation
EP3062019B1 (en) 2015-02-27 2018-11-21 Ansaldo Energia Switzerland AG Method and device for flame stabilization in a burner system of a stationary combustion engine
US10145269B2 (en) 2015-03-04 2018-12-04 General Electric Company System and method for cooling discharge flow
US10480792B2 (en) 2015-03-06 2019-11-19 General Electric Company Fuel staging in a gas turbine engine
BR112021008125A2 (en) * 2018-11-13 2021-08-03 Johnson Matthey Public Limited Company system, land, industrial, commercial, marine or air power generator, land, marine or mobile air vehicle, and, methods for operating the gas turbine engine system and for operating a recovery gas turbine engine
AT524310B1 (en) * 2020-11-24 2022-05-15 Avl List Gmbh Burner device for a fuel cell system
US20230014723A1 (en) * 2021-07-16 2023-01-19 Proof Energy Inc. Two-stage catalytic heating systems and methods of operating thereof

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4459126A (en) 1982-05-24 1984-07-10 United States Of America As Represented By The Administrator Of The Environmental Protection Agency Catalytic combustion process and system with wall heat loss control
CH674561A5 (en) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
GB9212794D0 (en) * 1992-06-16 1992-07-29 Ici Plc Catalytic combustion
DE4426351B4 (en) * 1994-07-25 2006-04-06 Alstom Combustion chamber for a gas turbine
DE4439619A1 (en) * 1994-11-05 1996-05-09 Abb Research Ltd Method and device for operating a premix burner
DE19654022A1 (en) 1996-12-21 1998-06-25 Abb Research Ltd Process for operating a gas turbine group
US6358040B1 (en) 2000-03-17 2002-03-19 Precision Combustion, Inc. Method and apparatus for a fuel-rich catalytic reactor
EP1485593A1 (en) 2002-02-22 2004-12-15 Catalytica Energy Systems, Inc. Catalytically piloted combustion system and methods of operation
WO2004020905A1 (en) * 2002-08-30 2004-03-11 Alstom Technology Ltd Method and device for combusting a fuel-oxidising agent mixture
WO2004094909A1 (en) * 2003-04-24 2004-11-04 Alstom Technology Ltd Method and device for operating a burner of a heat engine, especially a gas turbine plant
DE502005003324D1 (en) 2004-03-30 2008-04-30 Alstom Technology Ltd DEVICE AND METHOD FOR FLAME STABILIZATION IN A BURNER

Also Published As

Publication number Publication date
US7467942B2 (en) 2008-12-23
CA2561255A1 (en) 2005-10-13
US20070042301A1 (en) 2007-02-22
ATE389852T1 (en) 2008-04-15
EP1730441A1 (en) 2006-12-13
WO2005095855A1 (en) 2005-10-13
DE502005003324D1 (en) 2008-04-30

Similar Documents

Publication Publication Date Title
EP1730441B1 (en) Device and method for stabilizing the flame in a burner
EP1532400B1 (en) Method and device for combusting a fuel-oxidising agent mixture
WO2005095856A1 (en) Catalytic reactor and method for burning fuel-air mixtures by means of a catalytic reactor
EP2115353B1 (en) Combustion chamber for a gas turbine
DE69729505T2 (en) How a gas turbine combustor works
EP0710797B1 (en) Method and device for operating a premix burner
WO2006100176A1 (en) Method and device for combusting hydrogen in a premix burner
DE102009003453A1 (en) Combustion tube premixer and method for gas / air mixture formation in a gas turbine
EP1616131A1 (en) Method and device for operating a burner of a heat engine, especially a gas turbine plant
EP1723369A1 (en) Premix burner and method for combusting a low-calorific gas
DE102005061486B4 (en) Method for operating a combustion chamber of a gas turbine
EP1673576B1 (en) Method and device for the combustion of fuel
WO2003029725A1 (en) Method of combustion, in particular methods for the production of electrical current and/or heat
EP1754937A2 (en) Burner head and method of combusting fuel
EP1062461B1 (en) Combustion chamber and method for operating a combustion chamber
EP1989486A1 (en) Gas turbine burner and method of operating a gas turbine burner
DE102016208731A1 (en) Rocket propulsion system and method of operating a rocket propulsion system
EP1555484B1 (en) Process to operate a gas turbine combustor
DE2708940A1 (en) METHOD OF OPERATING A GAS TURBINE AND IMPROVED GAS TURBINE COMBUSTION CHAMBER
DE102020118325A1 (en) METHOD OF STAGED COMBUSTION OF A FUEL AND FUEL HEAD
EP1491824A2 (en) Catalytic reactor and associated operating method
DE102006015130A1 (en) Combustion method of gaseous fuel with air, involves homogeneous gas phase combustion of transformed catalytic air fuel mixture takes place as lean combustion at emission of both gas streams from catalytic burner
EP0816755A2 (en) Method and premix burner arrangment for the combustion of gaseous,liquid and/or pulverized fuels
DE4330160A1 (en) Method for operating a burner with gaseous or liquid fuels and burner for carrying out the method
DE4444125A1 (en) Process for clean combustion of pre=mixed gaseous or liquid fuels

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060913

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 502005003324

Country of ref document: DE

Date of ref document: 20080430

Kind code of ref document: P

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20080429

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
BERE Be: lapsed

Owner name: ALSTOM TECHNOLOGY LTD

Effective date: 20080331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080331

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080619

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080630

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080827

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080719

EN Fr: translation not filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: IE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

26N No opposition filed

Effective date: 20081222

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080619

Ref country code: FR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20090109

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080323

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090331

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080920

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080323

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080319

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20080620

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20110221

Year of fee payment: 7

Ref country code: DE

Payment date: 20110331

Year of fee payment: 7

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20120323

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502005003324

Country of ref document: DE

Effective date: 20121002

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120323

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20121002