WO2015062962A1 - Gas turbine burner hub with pilot burner - Google Patents

Gas turbine burner hub with pilot burner Download PDF

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Publication number
WO2015062962A1
WO2015062962A1 PCT/EP2014/072741 EP2014072741W WO2015062962A1 WO 2015062962 A1 WO2015062962 A1 WO 2015062962A1 EP 2014072741 W EP2014072741 W EP 2014072741W WO 2015062962 A1 WO2015062962 A1 WO 2015062962A1
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WO
WIPO (PCT)
Prior art keywords
burner
fuel
pilot
nozzles
channels
Prior art date
Application number
PCT/EP2014/072741
Other languages
German (de)
French (fr)
Inventor
Andreas Böttcher
Tobias Krieger
Patrick Lapp
Andreas Mann
Stefan Reich
Kai-Uwe Schildmacher
Sascha Staring
Daniel Vogtmann
Original Assignee
Siemens Aktiengesellschaft
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP14793808.8A priority Critical patent/EP3008390A1/en
Priority to US15/030,916 priority patent/US20160252254A1/en
Publication of WO2015062962A1 publication Critical patent/WO2015062962A1/en

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to a burner assembly, in particular a burner assembly with a main burner and a pilot burner, and refers to the mixture of fuel with air.
  • a burner assembly in particular a burner assembly with a main burner and a pilot burner, and refers to the mixture of fuel with air.
  • fuel is metered out as finely as possible and fed to the combustion air.
  • both the combustion air and the fuel by constructive measures in
  • Twisting movements offset This is typically done mainly by curved blades and fuel nozzles.
  • Pollutants such as nitrogen oxides (NO x) are mainly Exploitation ⁇ degree affected by the mixing ratio of fuel to air and the combustion. A complete combustion of the fuel is desirable wrestlers to pollutants ver ⁇ .
  • Gaseous fuels such as natural gas or synthesis gas, but also liquid fuels are suitable as fuel.
  • liquid fuel oil has mainly influenced the nozzle geometry in combination with the
  • Blade turbulence its mixing with air. Another actively influencing, for example, the depth of penetration of the fuel into the air flow or the turbulence of the fuel and thus finds an optimized mixing üb ⁇ SHORT- not take place.
  • the gas is emptied, for example, through holes in a swirl blade and with the
  • Compressor air premixed and twisted Both fuels, gas and oil, typically use a pilot burner to stabilize the premix flame.
  • a pilot burner For oil, it is an oil diffusion burner, for gas, it is a pilot gas burner.
  • the object of the invention is to provide said device wei ⁇ terzuentwickeln, so that a complete combustion as possible is achieved in the operation of the device.
  • a burner assembly for a combustion chamber in particular a gas turbine combustion chamber for firing fluidic fuels, comprising a main burner and a centrally therein reasonable associated pilot burner, which serves to ignite and / or to stabilize the combustion of the main burner, the main ⁇ burner a to arranged the pilot burner centrally ⁇ rale fuel supply arrangement, an annular air passage surrounding the central fuel supply arrangement for the supply of combustion air, primary fuel nozzle for injecting a substantially gaseous fuel into the annular air passage, wherein the first fuel nozzles are fed from a first fuel distributor in the central fuel supply arrangement, and second fuel nozzles for injecting a substantially liquid fuel into the annular air passage, the second fuel nozzles being fed by a second fuel distributor in the central fuel supply arrangement, channels v esigned are branched from Minim ⁇ least one of the fuel manifold and open out into the pilot burner and the pilot burner
  • the pilot burner comprises a pilot annular air duct for supplying combustion air and the channels open into this pilot annular air duct.
  • the channels branch off from the second fuel distributor and have nozzles at their ends which open into the pilot burner.
  • the second fuel distributor for injecting a substantially liquid fuel, so oil, is mechanically particularly stressed so that it is particularly advantageous here, if the nozzles cavitation ⁇ free and to exchange as needed can be screwed.
  • the annular air channel has swirl blades and the first fuel nozzles are arranged in these swirl blades.
  • the addition of fuel from the central fuel supply arrangement does not replace the independent supply of gas or oil in the pilot burner, but provides in combination with these for additional fuel enrichment why in advantageous embodiments of the pilot burner next to a channel independent gas supply channel also one of the Channels independent oil supply channel has.
  • the additional mass flows from the gas or oil distributors according to the invention are mixed with the compressor air in the pilot gas line and then combined with the fuel in the pilot burner.
  • An implementation of the invention can also take place in an existing design by the simple introduction of bores or nozzles.
  • the burner assembly 1 has a main axis 19 and includes a pilot burner 3 and a pilot burner 3 concentrically surrounding the main burner 2.
  • Both pilot burner 3 and main burner 2 can optionally with gaseous and / or liquid fuels, such as. Natural gas or fuel oil, operated.
  • the pilot burner 3 then includes as fuel channels an inner oil supply channel 18 and a concentrically surrounding this inner, annular gas supply channel 17. This is in turn surrounded by a pilot annular air channel 13 for the supply of combustion air 14 kon ⁇ centric.
  • a ge ⁇ One suitable ignition system can also be arranged in or on this pilot ring air duct 13 (not shown in the figure).
  • pilot annular air channel 13 further swirl blades 20 are arranged, which fuel nozzles 21 for supplying a fuel to a stream 14 of an oxygen-containing Ga ⁇ ses, typically having air.
  • the pilot burner 3 surrounding the main burner 2 comprises a relative to the main axis 19 of radially outer annular air passage 5 for the combustion air 6, extend through the several swirl ⁇ shovel 16 of a swirl vane.
  • Swirl vanes 16 have as fuel inlet first fuel nozzles 7, can be injected through the fuel gas into the air flowing through the annular air duct 5 6 through the fuel gas.
  • the first fuel nozzles 7 are fed via a first fuel distributor 8 in a central fuel supply arrangement 4.
  • a second fuel distributor 10 in the central fuel supply assembly 4 typically supplies second fuel nozzles 9 with oil.
  • the task of the pilot burner 3 is to maintain a stable combustion operation in the burner assembly 1, since this is usually operated with a tendency to instabilities lean mixture.
  • both channels 11 are now provided according to the invention, which branch off from the first fuel distributor 8 for the gas supply and open into the pilot burner 3, as well as channels 12 which branch off from a second fuel distributor 10 for oil.
  • the channels 12 have at their opening into the pilot burner 3 ends nozzles 15.
  • the channels 11, 12 are uniformly distributed over a circumference of the pilot lot-annular air channel 13 is distributed, and may be designed as a simple Boh ⁇ requirements.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

The invention relates to a burner arrangement (1) for a combustion chamber, in particular a gas turbine combustion chamber, for the combustion of fluid fuels, having a main burner (2) and a pilot burner (3) which is arranged centrally within said main burner and which serves for the ignition and/or stabilization of the combustion of the main burner (2), the main burner (2) comprising a central fuel feed arrangement (4) arranged around the pilot burner (3), an annular air duct (5) which surrounds the central fuel feed arrangement (4) and which serves for the supply of combustion air (6), first fuel nozzles (7) for the injection of a substantially gaseous fuel into the annular air duct (5), wherein the first fuel nozzles (7) are fed from a first fuel distributor (8) in the central fuel feed arrangement (4), and second fuel nozzles (9) for the injection of a substantially liquid fuel into the annular air duct (5), wherein the second fuel nozzles (9) are fed from a second fuel distributor (10) in the central fuel feed arrangement (4), wherein ducts (11, 12) are provided which branch off from at least one of the fuel distributors (8, 10) and issue into the pilot burner (3).

Description

Beschreibung description
GASTURBINENBRENNERNABE MIT PILOTBRENNER Die Erfindung betrifft eine Brenneranordnung, insbesondere eine Brenneranordnung mit einem Hauptbrenner und einem Pilotbrenner, und bezieht sich auf die Mischung von Brennstoff mit Luft. Beim Betrieb einer Gasturbinenanlage ist die Vermischung von Brennstoff mit Luft von entscheidender Bedeutung, um eine optimale und damit Schadstoffarme Verbrennung zu erzielen. Zu diesem Zweck wird Brennstoff möglichst fein dosiert ausgedüst und der Verbrennungsluft zugeführt. Um eine gute Vermischung der Fluide zu erreichen, werden sowohl die Verbrennungsluft als auch der Brennstoff durch konstruktive Maßnahmen in The invention relates to a burner assembly, in particular a burner assembly with a main burner and a pilot burner, and refers to the mixture of fuel with air. In the operation of a gas turbine plant, the mixing of fuel with air is of crucial importance in order to achieve optimum and thus low-emission combustion. For this purpose, fuel is metered out as finely as possible and fed to the combustion air. In order to achieve a good mixing of the fluids, both the combustion air and the fuel by constructive measures in
Drallbewegungen versetzt. Dies geschieht typischerweise hauptsächlich durch gekrümmte Schaufeln und Brennstoffdüsen . Die steigenden Auflagen zur Verringerung von Schadstoffen erfordern eine stetige Verbesserung der Verbrennung. Schadstoffe wie Stickoxide (NOx) werden hauptsächlich durch das Mischungsverhältnis von Brennstoff zu Luft und den Ausnutzungs¬ grad der Verbrennung beeinflusst. Eine vollständige Verbren- nung des Brennstoffs ist anzustreben um Schadstoffe zu ver¬ ringern . Twisting movements offset. This is typically done mainly by curved blades and fuel nozzles. The increasing requirements for the reduction of pollutants require a continuous improvement of combustion. Pollutants such as nitrogen oxides (NO x) are mainly Exploitation ¬ degree affected by the mixing ratio of fuel to air and the combustion. A complete combustion of the fuel is desirable wrestlers to pollutants ver ¬.
Als Brennstoff kommen dabei gasförmige Brennstoffe, wie Erd¬ gas oder Synthesegas, aber auch flüssige Brennstoffe in Fra- ge . Gerade beim flüssigen Brennstoff Öl beeinflusst bisher hauptsächlich die Düsengeometrie in Kombination mit der Gaseous fuels, such as natural gas or synthesis gas, but also liquid fuels are suitable as fuel. Especially with the liquid fuel oil has mainly influenced the nozzle geometry in combination with the
Schaufelverwirbelung dessen Vermischung mit Luft. Eine weitere aktive Einflussnahme auf beispielsweise die Eindringtiefe des Brennstoffs in den Luftstrom oder die Verwirbelung des Brennstoffs und damit eine optimierte Vermischung findet üb¬ licherweise nicht statt. Bei der Gasvormischeindüsung wird das Gas beispielsweise über Bohrungen in einer Drallschaufel ausgedüst und mit der Blade turbulence its mixing with air. Another actively influencing, for example, the depth of penetration of the fuel into the air flow or the turbulence of the fuel and thus finds an optimized mixing üb ¬ SHORT- not take place. In the Gasvormischeindüsung the gas is emptied, for example, through holes in a swirl blade and with the
Verdichterluft vorgemischt und verdrallt. Bei beiden Brennstoffen, Gas und Öl, wird typischerweise ein Pilotbrenner zur Stabilisierung der Vormischflamme eingesetzt. Bei Öl ist es ein Öldiffusionsbrenner, bei Gas ist es ein Pilotgasbrenner. Aufgabe der Erfindung ist es, die genannte Vorrichtung wei¬ terzuentwickeln, so dass im Betrieb der Vorrichtung eine möglichst vollständige Verbrennung erzielt wird. Compressor air premixed and twisted. Both fuels, gas and oil, typically use a pilot burner to stabilize the premix flame. For oil, it is an oil diffusion burner, for gas, it is a pilot gas burner. The object of the invention is to provide said device wei ¬ terzuentwickeln, so that a complete combustion as possible is achieved in the operation of the device.
Erfindungsgemäß wird diese Aufgabe gelöst durch die Brenner- anordnung gemäß Anspruch 1. Vorteilhafte Weiterbildungen der Erfindung sind in den abhängigen Ansprüchen definiert. Indem bei einer Brenneranordnung für eine Brennkammer, insbesondere eine Gasturbinenbrennkammer, zum Verfeuern fluidischer Brennstoffe, mit einem Hauptbrenner und einem zentral darin ange- ordneten Pilotbrenner, der zum Zünden und/oder zum Stabilisieren der Verbrennung des Hauptbrenners dient, der Haupt¬ brenner umfassend eine um den Pilotbrenner angeordnete zent¬ rale Brennstoffzufuhranordnung, einen die zentrale Brennstoffzufuhranordnung umgebenden Ringluftkanal zur Zuführung von Verbrennungsluft, erste Brennstoffdüsen zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffs in den Ringluftkanal, wobei die ersten Brennstoffdüsen von einem ersten BrennstoffVerteiler in der zentralen Brennstoffzufuhranordnung gespeist werden, und zweite Brennstoffdüsen zum Eindüsen eines im Wesentlichen flüssigen Brennstoffs in den Ringluftkanal, wobei die zweiten Brennstoffdüsen von einem zweiten BrennstoffVerteiler in der zentralen Brennstoffzufuhranordnung gespeist werden, Kanäle vorgesehen sind, die von mindes¬ tens einem der BrennstoffVerteiler abzweigen und in den Pi- lotbrenner münden und der Pilotbrenner einen von den Kanälen unabhängigen Gaszufuhrkanal aufweist, wird erreicht, dass die Pilotflamme infolge der Entnahme aus der Vormischpassage des Diagonalgitters im Hauptbrenner und Zugabe zum Pilotbrenner aufgewertet wird, wodurch die Verbrennung verbessert und de¬ ren Emissionen verringert werden. According to the invention this object is achieved by the burner arrangement according to claim 1. Advantageous developments of the invention are defined in the dependent claims. By comprising at a burner assembly for a combustion chamber, in particular a gas turbine combustion chamber for firing fluidic fuels, comprising a main burner and a centrally therein reasonable associated pilot burner, which serves to ignite and / or to stabilize the combustion of the main burner, the main ¬ burner a to arranged the pilot burner centrally ¬ rale fuel supply arrangement, an annular air passage surrounding the central fuel supply arrangement for the supply of combustion air, primary fuel nozzle for injecting a substantially gaseous fuel into the annular air passage, wherein the first fuel nozzles are fed from a first fuel distributor in the central fuel supply arrangement, and second fuel nozzles for injecting a substantially liquid fuel into the annular air passage, the second fuel nozzles being fed by a second fuel distributor in the central fuel supply arrangement, channels v esigned are branched from Minim ¬ least one of the fuel manifold and open out into the pilot burner and the pilot burner having a body independent of the channels, the gas supply channel, it is achieved that the pilot flame as a result of removal from the Vormischpassage the diagonal grating in the main burner, and adding to the pilot burner is enhanced, whereby combustion is improved and de ¬ ren is decreased.
Dabei ist es zweckmäßig, wenn der Pilotbrenner einen Pilot- Ringluftkanal zur Zuführung von Verbrennungsluft umfasst und die Kanäle in diesen Pilot-Ringluftkanal münden. It is expedient if the pilot burner comprises a pilot annular air duct for supplying combustion air and the channels open into this pilot annular air duct.
Um den Brennstoff möglichst gleichmäßig dem Pilot-Ringluft¬ kanal zuführen zu können, ist es vorteilhaft, wenn die Kanäle gleichmäßig über einen Umfang des Pilot-Ringluftkanals ver¬ teilt in diesen münden. In order to perform the fuel uniformly as possible to the pilot air-¬ ring canal, it is advantageous if the channels uniformly ver ¬ distributed over a circumference of the pilot channel in this annular air flow.
Dabei ist es zweckmäßig, weil einfach und kostengünstig umzu¬ setzen, wenn die Kanäle als Bohrungen ausgeführt sind. It is expedient, because simple and inexpensive umzu ¬ set if the channels are designed as holes.
In einer vorteilhaften Ausführungsform zweigen die Kanäle vom zweiten BrennstoffVerteiler ab und weisen an ihren in den Pilotbrenner mündenden Enden Düsen auf. Der zweite Brennstoff- Verteiler zum Eindüsen eines im Wesentlichen flüssigen Brenn- Stoffs, also Öl, ist mechanisch besonders belastet so dass es hier besonders vorteilhaft ist, wenn die Düsen kavitations¬ frei und zum bedarfsweisen Austauschen schraubbar sind. In an advantageous embodiment, the channels branch off from the second fuel distributor and have nozzles at their ends which open into the pilot burner. The second fuel distributor for injecting a substantially liquid fuel, so oil, is mechanically particularly stressed so that it is particularly advantageous here, if the nozzles cavitation ¬ free and to exchange as needed can be screwed.
Im Hinblick auf eine möglichst gute Durchmischung von Brenn- Stoff und Luft ist es vorteilhaft, wenn der Ringluftkanal Drallschaufeln aufweist und die ersten Brennstoffdüsen in diesen Drallschaufeln angeordnet sind. With regard to the best possible mixing of fuel and air, it is advantageous if the annular air channel has swirl blades and the first fuel nozzles are arranged in these swirl blades.
Die Zumischung von Brennstoff aus der zentralen Brennstoffzu- fuhranordnung ersetzt jedoch nicht die unabhängige Zufuhr von Gas oder Öl im Pilotbrenner, sondern sorgt in Kombination mit diesen für eine zusätzliche Brennstoffanreicherung weswegen in vorteilhaften Ausführungsformen der Pilotbrenner neben einem von den Kanälen unabhängigen Gaszufuhrkanal auch einen von den Kanälen unabhängigen Ölzufuhrkanal aufweist. Die gemäß der Erfindung zusätzlichen Massenströme aus den Gas- bzw. Ölverteilern werden mit der Verdichterluft im Pilotgasstrang vermischt und anschließend mit dem Brennstoff im Pilotbrenner kombiniert. Dadurch sind zusätzliche Brennstoff- anreicherungen und Mischungen möglich, die zu einer Verbesserung des Brennstoff/Luft Gemisches und damit zu einer Redu¬ zierung von Schadstoffen führen können. However, the addition of fuel from the central fuel supply arrangement does not replace the independent supply of gas or oil in the pilot burner, but provides in combination with these for additional fuel enrichment why in advantageous embodiments of the pilot burner next to a channel independent gas supply channel also one of the Channels independent oil supply channel has. The additional mass flows from the gas or oil distributors according to the invention are mixed with the compressor air in the pilot gas line and then combined with the fuel in the pilot burner. As a result, additional fuel enrichments and mixtures are possible, which can lead to an improvement of the fuel / air mixture and thus to Redu ¬ cation of pollutants.
Eine Implementierung der Erfindung kann auch in ein bestehen- des Design durch das einfache Einbringen von Bohrungen bzw. Düsen erfolgen. An implementation of the invention can also take place in an existing design by the simple introduction of bores or nozzles.
Die Erfindung wird beispielhaft anhand einer Zeichnung näher erläutert. Die Figur zeigt schematisch und nicht maßstäblich eine Brenneranordnung 1 nach der Erfindung, die ggf. in Verbindung mit mehreren gleichartigen Brenneranordnungen beispielsweise in der Brennkammer einer Gasturbinenanlage einge¬ setzt werden kann. Die Brenneranordnung 1 weist eine Hauptachse 19 auf und umfasst einen Pilotbrenner 3 und einen den Pilotbrenner 3 konzentrisch umgebenden Hauptbrenner 2. Sowohl Pilotbrenner 3 als auch Hauptbrenner 2 können wahlweise mit gasförmigen und/oder flüssigen Brennstoffen, wie bspw. Erdgas oder Heizöl, betrieben werden. Der Pilotbrenner 3 umfasst dann als Brennstoffkanäle einen inneren Ölzufuhrkanal 18 und einen diesen konzentrisch umgebenden inneren, ringförmigen Gaszufuhrkanal 17. Dieser ist wiederum von einem Pilot- Ringluftkanal 13 für die Zufuhr von Verbrennungsluft 14 kon¬ zentrisch umgeben. In oder an diesem Pilot-Ringluftkanal 13 kann zudem ein ge¬ eignetes Zündsystem angeordnet sein (in der Figur nicht dargestellt) . The invention will be explained in more detail by way of example with reference to a drawing. The figure shows schematically and not to scale a burner assembly 1 according to the invention, which can optionally be used in conjunction with several similar burner arrangements, for example in the combustion chamber of a gas turbine plant ¬ . The burner assembly 1 has a main axis 19 and includes a pilot burner 3 and a pilot burner 3 concentrically surrounding the main burner 2. Both pilot burner 3 and main burner 2 can optionally with gaseous and / or liquid fuels, such as. Natural gas or fuel oil, operated. The pilot burner 3 then includes as fuel channels an inner oil supply channel 18 and a concentrically surrounding this inner, annular gas supply channel 17. This is in turn surrounded by a pilot annular air channel 13 for the supply of combustion air 14 kon ¬ centric. A ge ¬ One suitable ignition system can also be arranged in or on this pilot ring air duct 13 (not shown in the figure).
Im Pilot-Ringluftkanal 13 sind ferner Drallschaufeln 20 ange- ordnet, welche Brennstoffdüsen 21 zur Zuführung eines Brennstoffes zu einem Strom 14 eines Sauerstoff enthaltenden Ga¬ ses, typischerweise Luft, aufweisen. Der den Pilotbrenner 3 umgebende Hauptbrenner 2 umfasst einen bezogen auf die Hauptachse 19 radial äußeren Ringluftkanal 5 für die Verbrennungsluft 6, durch den sich mehrere Drall¬ schaufeln 16 einer Drallbeschaufelung erstrecken. Diese In the pilot annular air channel 13 further swirl blades 20 are arranged, which fuel nozzles 21 for supplying a fuel to a stream 14 of an oxygen-containing Ga ¬ ses, typically having air. The pilot burner 3 surrounding the main burner 2 comprises a relative to the main axis 19 of radially outer annular air passage 5 for the combustion air 6, extend through the several swirl ¬ shovel 16 of a swirl vane. These
Drallschaufeln 16 weisen als Einlass für Brennstoff erste Brennstoffdüsen 7 auf, durch die Brenngas in die durch den Ringluftkanal 5 einströmende Luft 6 eingedüst werden kann. Die ersten Brennstoffdüsen 7 werden über einen ersten BrennstoffVerteiler 8 in einer zentralen Brennstoffzufuhranordnung 4 gespeist. Ein zweiter Brennstoff erteiler 10 in der zentralen Brennstoffzufuhranordnung 4 speist zweite Brennstoffdüsen 9 typischerweise mit Öl. Swirl vanes 16 have as fuel inlet first fuel nozzles 7, can be injected through the fuel gas into the air flowing through the annular air duct 5 6 through the fuel gas. The first fuel nozzles 7 are fed via a first fuel distributor 8 in a central fuel supply arrangement 4. A second fuel distributor 10 in the central fuel supply assembly 4 typically supplies second fuel nozzles 9 with oil.
Die Aufgabe des Pilotbrenners 3 besteht darin, einen stabilen Brennbetrieb in der Brenneranordnung 1 aufrecht zu erhalten, da diese meistens mit einem zu Instabilitäten neigenden Magergemisch betrieben wird. The task of the pilot burner 3 is to maintain a stable combustion operation in the burner assembly 1, since this is usually operated with a tendency to instabilities lean mixture.
Im Beispiel der Figur sind nun gemäß der Erfindung sowohl Ka- näle 11 vorgesehen, die vom ersten BrennstoffVerteiler 8 für die Gaszufuhr abzweigen und in den Pilotbrenner 3 münden, als auch Kanäle 12, die von einem zweiten BrennstoffVerteiler 10 für Öl abzweigen. Die Kanäle 12 weisen an ihren in den Pilotbrenner 3 mündenden Enden Düsen 15 auf. In the example of the figure, both channels 11 are now provided according to the invention, which branch off from the first fuel distributor 8 for the gas supply and open into the pilot burner 3, as well as channels 12 which branch off from a second fuel distributor 10 for oil. The channels 12 have at their opening into the pilot burner 3 ends nozzles 15.
Die Kanäle 11, 12 sind gleichmäßig über einen Umfang des Pi- lot-Ringluftkanals 13 verteilt und können als einfache Boh¬ rungen ausgeführt sein. The channels 11, 12 are uniformly distributed over a circumference of the pilot lot-annular air channel 13 is distributed, and may be designed as a simple Boh ¬ requirements.

Claims

Patentansprüche claims
1. Brenneranordnung (1) für eine Brennkammer, insbesondere eine Gasturbinenbrennkammer, zum Verfeuern fluidischer Brenn- Stoffe, mit einem Hauptbrenner (2) und einem zentral darin angeordneten Pilotbrenner (3), der zum Zünden und/oder zum Stabilisieren der Verbrennung des Hauptbrenners (2) dient, der Hauptbrenner (2) umfassend eine um den Pilotbrenner (3) angeordnete zentrale Brennstoffzufuhranordnung (4), einen die zentrale Brennstoffzufuhranordnung (4) umgebenden Ringluftkanal (5) zur Zuführung von Verbrennungsluft (6), erste Brenn¬ stoffdüsen (7) zum Eindüsen eines im Wesentlichen gasförmigen Brennstoffs in den Ringluftkanal (5) , wobei die ersten Brenn¬ stoffdüsen (7) von einem ersten BrennstoffVerteiler (8) in der zentralen Brennstoffzufuhranordnung (4) gespeist werden, und zweite Brennstoffdüsen (9) zum Eindüsen eines im Wesentlichen flüssigen Brennstoffs in den Ringluftkanal (5) , wobei die zweiten Brennstoffdüsen (9) von einem zweiten Brennstoffverteiler (10) in der zentralen Brennstoffzufuhranordnung (4) gespeist werden, dadurch gekennzeichnet, dass Kanäle (11, 12) vorgesehen sind, die von mindestens einem der BrennstoffVerteiler (8, 10) abzweigen und in den Pilotbrenner (3) münden und der Pilotbrenner (3) einen von den Kanälen (11) unabhängigen Gaszufuhrkanal (17) aufweist. A burner assembly (1) for a combustor, in particular a gas turbine combustor, for firing fluid fuels, comprising a main burner (2) and a pilot burner (3) centrally disposed therein for igniting and / or stabilizing combustion of the main burner (3). 2) is used, disposed of the main burner (2) comprising a (around the pilot burner 3) central fuel supply arrangement (4), a central fuel supply arrangement (4) surrounding annular air channel (5) for feeding combustion air (6), first combustion ¬ nozzles (7 ) for injecting a substantially gaseous fuel into the annular air channel (5), wherein the first combustion ¬ nozzles (7) from a first fuel manifold (8) in the central fuel supply arrangement (4) are fed, and second fuel nozzles (9) for injecting a substantially liquid fuel in the annular air passage (5), wherein the second fuel nozzles (9) from a second fuel distributor (10) in the central fuel supply assembly (4) are fed, characterized in that channels (11, 12) are provided, which branch off from at least one of the fuel distributor (8, 10) and into the pilot burner (3) and the pilot burner (3) one of Having the channels (11) independent gas supply channel (17).
2. Brenneranordnung (1) nach Anspruch 1, wobei der Pilotbrenner (3) einen Pilot-Ringluftkanal (13) zur Zuführung von Verbrennungsluft (14) umfasst und die Kanäle (11, 12) in die¬ sen Pilot-Ringluftkanal (13) münden. 2. Burner arrangement (1) according to claim 1, wherein the pilot burner (3) comprises a pilot annular air channel (13) for supplying combustion air (14) and the channels (11, 12) open into the ¬ sen pilot annular air channel (13) ,
3. Brenneranordnung (1) nach Anspruch 2, wobei die Kanäle (11, 12) gleichmäßig über einen Umfang des Pilot- Ringluftkanals (13) verteilt in diesen münden. 3. burner assembly (1) according to claim 2, wherein the channels (11, 12) evenly distributed over a circumference of the pilot ring air duct (13) open into this.
4. Brenneranordnung (1) nach einem der vorhergehenden Ansprüche, wobei die Kanäle (11, 12) als Bohrungen ausgeführt sind . 4. burner assembly (1) according to any one of the preceding claims, wherein the channels (11, 12) are designed as bores.
5. Brenneranordnung (1) nach einem der vorhergehenden Ansprüche, wobei die Kanäle (12) vom zweiten BrennstoffVertei¬ ler (10) abzweigen und an ihren in den Pilotbrenner (3) mündenden Enden Düsen (15) aufweisen. 5. burner assembly (1) according to any one of the preceding claims, wherein the channels (12) branch off from the second BrennstoffVertei ¬ ler (10) and at their opening into the pilot burner (3) ends nozzles (15).
6. Brenneranordnung (1) nach Anspruch 5, wobei die Düsen (15) kavitationsfrei und schraubbar sind. 6. burner assembly (1) according to claim 5, wherein the nozzles (15) cavitation free and are screwed.
7. Brenneranordnung (1) nach einem der vorhergehenden An- Sprüche, wobei der Ringluftkanal (15) Drallschaufeln (16) aufweist und die ersten Brennstoffdüsen (7) in diesen 7. burner assembly (1) according to one of the preceding arrival claims, wherein the annular air channel (15) swirl vanes (16) and the first fuel nozzles (7) in this
Drallschaufeln (16) angeordnet sind. Swirl vanes (16) are arranged.
8. Brenneranordnung (1) nach einem der vorhergehenden An- Sprüche, wobei der Pilotbrenner (3) einen von den Kanälen8. burner assembly (1) according to any one of the preceding claims, wherein the pilot burner (3) one of the channels
(12) unabhängigen Ölzufuhrkanal (18) aufweist. (12) independent oil supply channel (18).
PCT/EP2014/072741 2013-10-31 2014-10-23 Gas turbine burner hub with pilot burner WO2015062962A1 (en)

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