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WO2000012933A1 - Hybrid burner and method for operating a hybrid burner - Google Patents

Hybrid burner and method for operating a hybrid burner Download PDF

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Publication number
WO2000012933A1
WO2000012933A1 PCT/DE1999/002532 DE9902532W WO0012933A1 WO 2000012933 A1 WO2000012933 A1 WO 2000012933A1 DE 9902532 W DE9902532 W DE 9902532W WO 0012933 A1 WO0012933 A1 WO 0012933A1
Authority
WO
WIPO (PCT)
Prior art keywords
burner
pilot
main
gas stream
fuel gas
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.)
Ceased
Application number
PCT/DE1999/002532
Other languages
German (de)
French (fr)
Inventor
Carsten Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of WO2000012933A1 publication Critical patent/WO2000012933A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • F23C6/047—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure with fuel supply in stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion simultaneously or alternately of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • 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
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines

Definitions

  • the invention relates to a hybrid burner with a main burner and a pilot burner and a method for operating a hybrid burner.
  • the principle of a hybrid burner is described in the article "Progress in No y and CO Emission Reduction of Gas Turbines", H. Maghon, P. Behrenbnnk, W. Termuehlen and G. Gärtner, ASME / IEEE Power Generation Conference, Boston, October 1990. It is based on the fact that comparatively little fuel is burned in a lot of combustion air, in particular to reduce nitrogen oxide emissions, this lean combustion being stabilized by a pilot flame of a pilot burner
  • the pilot burner works as a diffusion burner, ie fuel and combustion air are combined at the location of the combustion.
  • the premix or main burner can be designed, for example, as an annular channel which surrounds a centrally arranged pilot burner.
  • EP 0 573 300 B1 shows a method for a combustion with low nitrogen oxide production and a corresponding one
  • a central combustion air stream is supplied with fuel at its surface and burned in an annular first combustion zone surrounding the combustion air stream.
  • a secondary fuel is injected into a low-oxygen zone formed by this annular combustion zone. The secondary fuel partially burns in the low oxygen zone of the annular first combustion zone, thereby reducing nitrogen oxide formation.
  • the object of the invention is to provide a hybrid burner with low nitrogen oxide emissions. Another object of the invention is to provide a method for operating a hybrid burner in which only small amounts of nitrogen oxides are formed.
  • the object directed to a hybrid burner is achieved by a hybrid burner directed along a burner axis, comprising a main burner designed as a premix burner for a main fuel gas stream and a pilot burner designed as a diffusion burner for a pilot fuel gas stream, the pilot fuel gas stream being combustible at least partially separately from the main fuel gas stream.
  • a staged combustion is realized internally in a hybrid burner for the first time.
  • the pilot fuel gas stream from the pilot burner is at least partially burned.
  • the pilot burner functions as a diffusion burner, which means that there is no intensive premixing of fuel and combustion air, but the fuel is combined with the combustion air at the point of combustion.
  • the hot pilot fuel gas stream then ignites the main fuel gas stream, creating a second stage of combustion.
  • the combustion products of the first combustion stage thus stabilize the reaction in the main fuel gas flow.
  • the flame temperature of the second combustion stage ie the combustion of the
  • the two-stage combustion also ensures that the combustion takes place in a larger reaction volume. This dampens the occurrence of burns, because local, spontaneous burns, which
  • the main combustible gas stream is preferably ignitable at a main combustion position and the pilot combustible gas stream is combustible in such a way that more than half of it is burned at a pilot combustion position, the pilot combustion position along the burner axis being upstream of the main combustion position in terms of flow technology.
  • the pilot fuel gas stream is burned at least half before it ignites the main fuel gas stream.
  • Combustion air can preferably be fed to the main burner in a main air duct and the pilot burner in a pilot air duct, a main swirl grille being arranged in the main air duct and a pilot swirl grille being arranged in the pilot air duct, and the pilot swirl grille along the burner axis in terms of flow technology lies in front of the main swirl grille.
  • a swirl grille gives the combustion air a swirl for both the main burner and the pilot burner. Such a swirl stabilizes the combustion.
  • the swirl grille of the pilot burner is preferably arranged in terms of flow technology in front of the swirl grille of the main burner along the burner axis.
  • a respective reference point which is equivalent for both swirl grids, for example the respective center of gravity of the swirl grids has an axial position along the burner axis.
  • the axial position for the pilot swirl grille lies before the axial position of the main swirl grille.
  • the main burner preferably surrounds the pilot burner, preferably in the form of an annular channel.
  • the main burner for the pilot burner further preferably forms a pre-combustion chamber with a pre-combustion chamber wall, the pre-combustion chamber wall being able to be cooled by the main combustion gas flow.
  • the main burner surrounds the pilot burner with its combustion air duct, e.g. in the form of an annular gap.
  • the inner wall of this gap duct represents a pre-combustion chamber wall for the combustion of the pilot combustion gas stream which takes place in the first stage of the combustion.
  • the main combustion gas stream convectively cools this pre-combustion chamber wall.
  • the hybrid burner can preferably be operated with natural gas or petroleum.
  • the hybrid burner is preferably for a gas turbine, e.g. for an aircraft engine, designed, but preferably for a stationary gas turbine.
  • the object directed to a hybrid burner is further achieved by a hybrid burner directed along a burner axis, comprising a main burner designed as a premix burner for a main combustion gas flow and a pilot burner designed as a diffusion burner for a pilot combustion gas flow, the pilot burner opening into a pre-combustion chamber which exits with an off diameter to a main combustion chamber and a height which is defined by the distance of the pilot burner to the outlet, the height being at least xx% of the outlet diameter.
  • a pilot combustion chamber for the pilot burner which has the above-mentioned minimum height in comparison to its outlet diameter, burns the pilot combustion gas stream at least partially independently and separately from the main combustion gas stream before it ignites the main combustion gas stream. This achieves a staged combustion, which has the advantages mentioned above.
  • the object directed to a method is achieved by a method for operating a hybrid burner, in which a main fuel gas stream is generated by premixing fuel and air and is burned by ignition on a burning pilot fuel gas stream, the pilot fuel gas stream becoming more before it ignites the main fuel gas stream than half is burned.
  • the main fuel gas stream is preferably guided to surround the pilot fuel gas stream.
  • the invention is explained in more detail in an exemplary embodiment.
  • the single figure shows a schematic section of a longitudinal section through a hybrid burner 1 of a gas turbine, not shown.
  • the hybrid burner 1 is formed from a pilot burner 3 and a main burner 5.
  • the pilot burner 3 has a central lance 7 for generating a pilot flame.
  • the lance 7 is surrounded by a pilot air duct 9.
  • Fuel feed lines 11 open into the pilot air channel 9 Combustion air flowing in the pilot air duct 9 is led via the fuel supply lines 11 crude oil or natural gas.
  • the pilot fuel gas stream 13 emerges from the pilot burner 3 as a fuel-air mixture.
  • the main burner 5 surrounds the pilot burner 3 with an air duct in the form of an annular gap, hereinafter referred to as the main air duct 6.
  • the main combustion gas stream 15 is guided in the main air duct 6.
  • the main fuel gas stream 15 consists of a mixture of air and fuel, the fuel, for example natural gas or oil, being supplied by means not shown in detail.
  • the main air duct 6 has a duct wall 17 consisting of an inner wall 17A and an outer wall 17B.
  • the inner wall 17A has an end area which represents a pre-combustion chamber wall 19.
  • This pre-combustion chamber wall 19 surrounds the mouth 20 of the pilot burner 3 and defines a pre-combustion chamber 21 with an outlet 23 to the combustion chamber 40 (not shown in more detail).
  • the outlet 23 has an outlet diameter 25.
  • the mouth 20 of the pilot burner 3 is at a distance from the outlet 23, which defines the height A of the pre-combustion chamber 21.
  • the ratio of the height A to the outlet diameter 25 is preferably greater than 50%, in particular greater than 100%.
  • the main fuel gas stream 15 comes into contact with the pilot fuel gas stream 13 via the cross section of the main air duct 6 at the outlet 23, identified in longitudinal section by a point H.
  • the main combustion gas stream 15 is ignited in the process.
  • a main combustion position HB results for the point H on the burner axis 2 of the hybrid burner 1.
  • the pilot combustible gas stream 13 has been burned by more than half along the burner axis 2 at a pilot combustion position P.
  • the pilot combustion position P lies along the burner axis 2 in terms of flow technology before the main combustion position HB.
  • a first stage of a combustion of the pilot fuel gas stream 13 takes place in the pre-combustion chamber 21.
  • the pilot fuel gas stream 13 is thus separated and independent of the main fuel gas stream 15 at least partially burned.
  • the pilot fuel gas stream 13 or its hot combustion products then ignite the main fuel gas stream 15, which results in a second stage of combustion.
  • This two-stage combustion reduces the maximum flame temperatures that occur during combustion. This results in a reduced nitrogen oxide emission, since the nitrogen oxide formation increases exponentially with the flame temperature.
  • combustion vibrations have their starting point, among other things, in spontaneous, local performance releases of the combustion. A greater distribution of such power releases leads to mutual interference and thus suppression of combustion vibrations.
  • the main fuel gas stream 15 is preferably given a swirl by a swirl grille 27.
  • the swirl grille 27 has a center point 29 in longitudinal section.
  • the center point 29 has an axial position D2 on the burner axis 2.
  • the pilot fuel gas stream is also given a swirl by a swirl grille 31.
  • the swirl grid 31 has a center point 33 in longitudinal section.
  • the center 33 has an axial position D1 on the burner axis 2. In terms of flow technology, the axial position D2 lies behind the axial position D1.
  • the pre-combustion chamber wall 19 is cooled by the main combustion gas stream 15.
  • the pre-combustion chamber wall 19 can be on the outside, i.e. be ribbed in the main air duct 6.

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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 hybrid burner (1) having a central pilot burner (3) and a main burner (5) surrounding the pilot burner (3). The pilot burner (3) is staggered backwards in relation to the main burner (5) in such a way staged combustion occurs.

Description

Beschreibungdescription

Hybridbrenner und Verfahren zum Betrieb eines HybridbrennersHybrid burner and method for operating a hybrid burner

Die Erfindung betrifft einen Hybridbrenner mit einem Hauptbrenner und einem Pilotbrenner und ein Verfahren zum Betrieb eines Hybridbrenners.The invention relates to a hybrid burner with a main burner and a pilot burner and a method for operating a hybrid burner.

Das Prinzip eines Hybridbrenners ist beschrieben m dem Arti- kel „Progress in Noy and CO Emission Reduction of Gas Turbines" , H. Maghon, P. Behrenbnnk, W. Termuehlen und G. Gärtner, ASME/IEEE Power Generation Conference, Boston, October 1990. Es beruht darauf, daß insbesondere zur Reduktion von Stickoxid-Emissionen vergleichsweise wenig Brennstoff in viel Verbrennungsluft verbrannt wird, wobei diese magere Verbrennung durch eine Pilotflamme eines Pilotbrenners stabilisiert wird. Die magere Verbrennung wird über einen Vormischbrenner erzeugt, d.h. Brennstoff und Verbrennungsluft werden zunächst innig vermischt, bevor sie der Verbrennung zugeführt werden. Der Pilotbrenner arbeitet demgegenüber als Diffusionsbrenner, d.h. Brennstoff und Verbrennungsluft werden am Ort der Verbrennung vereinigt. Der Vormisch- oder Hauptbrenner kann z.B. als ein Ringkanal ausgebildet sein, der einen zentral angeordneten Pilotbrenner umgibt.The principle of a hybrid burner is described in the article "Progress in No y and CO Emission Reduction of Gas Turbines", H. Maghon, P. Behrenbnnk, W. Termuehlen and G. Gärtner, ASME / IEEE Power Generation Conference, Boston, October 1990. It is based on the fact that comparatively little fuel is burned in a lot of combustion air, in particular to reduce nitrogen oxide emissions, this lean combustion being stabilized by a pilot flame of a pilot burner The pilot burner, on the other hand, works as a diffusion burner, ie fuel and combustion air are combined at the location of the combustion. The premix or main burner can be designed, for example, as an annular channel which surrounds a centrally arranged pilot burner.

In dem Artikel "Options for Low Emissions", von Richard J. Antos, Low NOx Gas Turbmes, Mai 1996, Seite 43, ist eine Gasturbine mit einer zweistufigen Verbrennung beschrieben. In einer Pπmarzone erfolgt eine erste Stufe der Verbrennung mit Hilfe eines Vormischbrenners, der durch einen Diffusionsbren- ner stabilisiert ist. An den Verbrennungsraum für die Primar- zone schließt sich ein größerer Verbrennungsraum für eine Se- kundarzone an, m der eine zweite Stufe der Verbrennung ablauft. Dazu wird über eine Anzahl von Offnungen in der Brenn- kammerwand am Eintritt der Sekundarzone ein vorgemischtes Brennstoff-Luft-Gemisch zugeführt. Das Brennstoff-Luft-Gem sch zündet im heißen Abgas, welches von der Primarzone in die Sekundarzone eintritt. Damit ergibt sich die zweite Stufe der Verbrennung.In the article "Options for Low Emissions" by Richard J. Antos, Low NO x Gas Turbmes, May 1996, page 43, a gas turbine with a two-stage combustion is described. In a PM zone, a first stage of combustion takes place with the aid of a premix burner, which is stabilized by a diffusion burner. The combustion chamber for the primary zone is adjoined by a larger combustion chamber for a second zone, in which a second stage of combustion takes place. For this purpose, a premixed fuel-air mixture is supplied through a number of openings in the combustion chamber wall at the entrance to the secondary zone. The fuel-air mixture ignites in the hot exhaust gas, which flows in from the primary zone the secondary zone enters. This results in the second stage of combustion.

Die EP 0 573 300 Bl zeigt ein Verfahren für eine Verbrennung mit niedriger Stickoxidproduktion und eine entsprechendeEP 0 573 300 B1 shows a method for a combustion with low nitrogen oxide production and a corresponding one

Brenneranordnung. Einem zentralen Verbrennungsluftstrom wird an seiner Oberflache Brennstoff zugeführt und in einer ringförmigen, den Verbrennungsluftstrom umgebenden ersten Verbrennungszone verbrannt. In eine durch diese ringförmige Ver- brennungszone ausgebildete sauerstoffarme Zone wird ein sekundärer Brennstoff eingespritzt. Der sekundäre Brennstoff verbrennt teilweise m der sauerstoffarmen Zone der ringförmigen ersten Verbrennungszone, wodurch eine Stickoxidbildung vermindert wird.Burner arrangement. A central combustion air stream is supplied with fuel at its surface and burned in an annular first combustion zone surrounding the combustion air stream. A secondary fuel is injected into a low-oxygen zone formed by this annular combustion zone. The secondary fuel partially burns in the low oxygen zone of the annular first combustion zone, thereby reducing nitrogen oxide formation.

Aufgabe der Erfindung ist die Angabe eines Hybridbrenners mit niedriger Stickoxidemission . Weitere Aufgabe der Erfindung ist die Angabe eines Verfahrens zum Betrieb eines Hybridbrenners, bei dem nur geringe Mengen an Stickoxiden gebildet wer- den.The object of the invention is to provide a hybrid burner with low nitrogen oxide emissions. Another object of the invention is to provide a method for operating a hybrid burner in which only small amounts of nitrogen oxides are formed.

Erfmdungsgemaß wird die auf einen Hybridbrenner gerichtete Aufgabe gelost durch einen entlang einer Brennerachse gerichteten Hybridbrenner, umfassend einen als Vormischbrenner aus- geführten Hauptbrenner für einen Hauptbrenngasstrom und einen als Diffusionsbrenner ausgeführten Pilotbrenner für einen Pilotbrenngasstrom, wobei der Pilotbrenngasstrom zumindest teilweise getrennt vom Hauptbrenngasstrom verbrennbar ist.According to the invention, the object directed to a hybrid burner is achieved by a hybrid burner directed along a burner axis, comprising a main burner designed as a premix burner for a main fuel gas stream and a pilot burner designed as a diffusion burner for a pilot fuel gas stream, the pilot fuel gas stream being combustible at least partially separately from the main fuel gas stream.

Mit der Erfindung wird erstmals eine gestufte Verbrennung intern in einem Hybridbrenner verwirklicht. Zunächst wird der Pilotbrenngasstrom aus dem Pilotbrenner zumindest teilweise verbrannt. Der Pilotbrenner funktioniert dabei als Diffusi- onsbrenner, daß heißt, es findet keine intensive Vormischung von Brennstoff und Verbrennungsluft statt, sondern der Brennstoff wird mit der Verbrennungsluft am Ort der Verbrennung vereinigt. Der heiße Pilotbrenngasstrom zündet anschließend den Hauptbrenngasstrom, wodurch eine zweite Stufe der Verbrennung entsteht. Die Verbrennungsprodukte der ersten Verbrennungsstufe stabilisieren damit einerseits die Reaktion im Hauptbrenngasstrom. Andererseits wird die Flammentemperatur der zweiten Verbrennungsstufe, d.h. die Verbrennung desWith the invention, a staged combustion is realized internally in a hybrid burner for the first time. First, the pilot fuel gas stream from the pilot burner is at least partially burned. The pilot burner functions as a diffusion burner, which means that there is no intensive premixing of fuel and combustion air, but the fuel is combined with the combustion air at the point of combustion. The hot pilot fuel gas stream then ignites the main fuel gas stream, creating a second stage of combustion. The combustion products of the first combustion stage thus stabilize the reaction in the main fuel gas flow. On the other hand, the flame temperature of the second combustion stage, ie the combustion of the

Hauptbrenngasstromes heruntergekühlt, da die Verbrennungsprodukte der ersten Verbrennungsstufe nicht mehr an der Reaktion teilnehmen. Der Bereich unmittelbar hinter dem Pilotbrenner wird zu einer Art Vorbrennkammer. Dadurch wird erreicht, daß geringere Spitzenwerte bei der Flammentemperatur der Verbrennung auftreten. Solche Spitzenwerte bestimmen maßgeblich die Produktion von Stickoxid, da die Stickoxidbildung exponenti- ell mit der Flammentemperatur steigt. Durch die gestufte Verbrennung im Hybridbrenner wird also eine Verbrennung mit ge- ringer Stickoxidemission erreicht.Main fuel gas stream cooled down, since the combustion products of the first combustion stage no longer participate in the reaction. The area immediately behind the pilot burner becomes a kind of pre-combustion chamber. It is thereby achieved that lower peak values occur at the flame temperature of the combustion. Such peak values largely determine the production of nitrogen oxide, since nitrogen oxide formation increases exponentially with the flame temperature. As a result of the staged combustion in the hybrid burner, combustion with low nitrogen oxide emissions is achieved.

Durch die zweistufige Verbrennung wird weiterhin erreicht, daß die Verbrennung m einem größeren Reaktionsvolumen stattfindet. Dadurch wird das Auftreten von Verbrennungsschwmgun- gen gedampft, weil lokale, spontane Verbrennungen, welcheThe two-stage combustion also ensures that the combustion takes place in a larger reaction volume. This dampens the occurrence of burns, because local, spontaneous burns, which

Ausgangspunkte von Verbrennungsschwingungen sein können, über einen größeren Bereich verteilt sind.Starting points of combustion vibrations can be distributed over a larger area.

Vorzugsweise ist der Hauptbrenngasstrom an einer Hauptver- brennungsposition entzündbar und der Pilotbrenngasstrom so verbrennbar, daß er an einer Pilotverbrennungsposition zu mehr als die Hälfte verbrannt ist, wobei die Pilotverbrennungsposition entlang der Brennerachse stromungstechnisch vor der Hauptverbrennungsposition liegt. In dieser Ausfuhrung wird der Pilotbrenngasstrom mindestens zur Hälfte verbrannt, bevor er den Hauptbrenngasstrom zündet.The main combustible gas stream is preferably ignitable at a main combustion position and the pilot combustible gas stream is combustible in such a way that more than half of it is burned at a pilot combustion position, the pilot combustion position along the burner axis being upstream of the main combustion position in terms of flow technology. In this embodiment, the pilot fuel gas stream is burned at least half before it ignites the main fuel gas stream.

Vorzugsweise ist dem Hauptbrenner in einem Hauptluftkanal und dem Pilotbrenner m einem Pilotluftkanal jeweils Verbren- nungsluft zufuhrbar, wobei im Hauptluftkanal ein Hauptdrallgitter und im Pilotluftkanal ein Pilotdrallgitter angeordnet sind und wobei das Pilotdrallgitter entlang der Brennerachse stromungstechnisch vor dem Hauptdrallgitter liegt. Durch ein Drallgitter wird der Verbrennungsluft sowohl für den Hauptbrenner als auch für den Pilotbrenner jeweils ein Drall erteilt. Ein solcher Drall fuhrt zu einer Stabilisierung der Verbrennung. Vorzugsweise ist das Drallgitter des Pilotbrenners entlang der Brennerachse stromungstechnisch vor dem Drallgitter des Hauptbrenners angeordnet. Mit anderen Worten: Ein jeweiliger, für beide Drallgitter äquivalenter Bezugspunkt, z.B. der jeweilige Schwerpunkt der Drallgitter weist eine axiale Position entlang der Brennerachse auf. Dabei liegt die axiale Position für das Pilotdrallgitter stromungstechnisch vor der axialen Position des Hauptdrallgitters.Combustion air can preferably be fed to the main burner in a main air duct and the pilot burner in a pilot air duct, a main swirl grille being arranged in the main air duct and a pilot swirl grille being arranged in the pilot air duct, and the pilot swirl grille along the burner axis in terms of flow technology lies in front of the main swirl grille. A swirl grille gives the combustion air a swirl for both the main burner and the pilot burner. Such a swirl stabilizes the combustion. The swirl grille of the pilot burner is preferably arranged in terms of flow technology in front of the swirl grille of the main burner along the burner axis. In other words: a respective reference point, which is equivalent for both swirl grids, for example the respective center of gravity of the swirl grids has an axial position along the burner axis. In terms of flow technology, the axial position for the pilot swirl grille lies before the axial position of the main swirl grille.

Bevorzugtermaßen umgibt der Hauptbrenner den Pilotbrenner und zwar vorzugsweise ringkanalformig . Weiter bevorzugt ist durch den Hauptbrenner für den Pilotbrenner eine Vorbrennkammer mit einer Vorbrennkammerwand gebildet, wobei die Vorbrennkammer- wand durch den Hauptbrenngasstrom kuhlbar ist. Der Hauptbrenner umgibt mit seinem Verbrennungsluftkanal den Pilotbrenner und zwar z.B. im Form eines Ringspaltes. Die innere Wand dieses Rmgspaltkanales stellt dabei eine Vorbrennkammerwand für die m der ersten Stufe der Verbrennung ablaufende Verbrennung des Pilotbrenngasstromes dar. Der Hauptbrenngasstrom kühlt diese Vorbrennkammerwand konvektiv.The main burner preferably surrounds the pilot burner, preferably in the form of an annular channel. The main burner for the pilot burner further preferably forms a pre-combustion chamber with a pre-combustion chamber wall, the pre-combustion chamber wall being able to be cooled by the main combustion gas flow. The main burner surrounds the pilot burner with its combustion air duct, e.g. in the form of an annular gap. The inner wall of this gap duct represents a pre-combustion chamber wall for the combustion of the pilot combustion gas stream which takes place in the first stage of the combustion. The main combustion gas stream convectively cools this pre-combustion chamber wall.

Bevorzugt laßt sich der Hybridbrenner wahlweise mit Erdgas oder Erdöl betreiben. Bevorzugtermaßen ist der Hybridbrenner für eine Gasturbine, z.B. für ein Flugtriebwerk, ausgelegt, vorzugsweise aber für eine stationäre Gasturbine.The hybrid burner can preferably be operated with natural gas or petroleum. The hybrid burner is preferably for a gas turbine, e.g. for an aircraft engine, designed, but preferably for a stationary gas turbine.

Erfindungsgemaß wird die auf einen Hybridbrenner gerichtete Aufgabe weiterhin gelost durch ein entlang einer Brennerachse gerichteten Hybridbrenner, umfassend einen als Vormischbren- ner ausgebildeten Hauptbrenner für einen Hauptbrenngasstrom und einen als Diffusionsbrenner ausgebildeten Pilotbrenner für einen Pilotbrenngasstrom, wobei der Pilotbrenner in eine Vorbrennkammer mundet, welche einen Austritt mit einem Aus- trittsdurchmesser zu einer Hauptbrennkammer und eine Höhe aufweist, die durch den Abstand des Pilotbrenners zum Austritt definiert ist, wobei die Höhe mindestens xx % vom Austrittsdurchmesser beträgt.According to the invention, the object directed to a hybrid burner is further achieved by a hybrid burner directed along a burner axis, comprising a main burner designed as a premix burner for a main combustion gas flow and a pilot burner designed as a diffusion burner for a pilot combustion gas flow, the pilot burner opening into a pre-combustion chamber which exits with an off diameter to a main combustion chamber and a height which is defined by the distance of the pilot burner to the outlet, the height being at least xx% of the outlet diameter.

Durch eine Vorbrennkammer für den Pilotbrenner, die die oben angegebene Mindesthöhe im Vergleich zu ihrem Austrittsdurchmesser aufweist, wird der Pilotbrenngasstrom zumindest teilweise unabhängig und getrennt vom Hauptbrenngasstrom ver- brannt, bevor er den Hauptbrenngasstrom zündet. Dadurch wird eine gestufte Verbrennung erreicht, welche die oben genannten Vorteile aufweist.A pilot combustion chamber for the pilot burner, which has the above-mentioned minimum height in comparison to its outlet diameter, burns the pilot combustion gas stream at least partially independently and separately from the main combustion gas stream before it ignites the main combustion gas stream. This achieves a staged combustion, which has the advantages mentioned above.

Erfindungsgemäß wird die auf ein Verfahren gerichtete Aufgabe gelöst durch ein Verfahren zum Betrieb eines Hybridbrenners, bei dem ein Hauptbrenngasstrom durch Vormischung von Brennstoff und Luft erzeugt und durch Zündung an einem brennenden Pilotbrenngasstrom verbrannt wird, wobei der Pilotbrenngasstrom, bevor er den Hauptbrenngasstrom zündet, zu mehr als der Hälfte verbrannt wird.According to the invention, the object directed to a method is achieved by a method for operating a hybrid burner, in which a main fuel gas stream is generated by premixing fuel and air and is burned by ignition on a burning pilot fuel gas stream, the pilot fuel gas stream becoming more before it ignites the main fuel gas stream than half is burned.

Die Vorteile eines solchen Verfahrens entsprechen den obigen Ausführungen zu den Vorteilen eines Hybridbrenners.The advantages of such a method correspond to the above explanations regarding the advantages of a hybrid burner.

Vorzugsweise wird der Hauptbrenngasstrom dem Pilotbrenngasstrom umgebend geführt.The main fuel gas stream is preferably guided to surround the pilot fuel gas stream.

Die Erfindung wird in einem Ausführungsbeispiel näher erläutert. Die einzige Figur zeigt teilweise schematisch einen Längsschnitt durch einen Hybridbrenner 1 einer nicht näher dargestellten Gasturbine.The invention is explained in more detail in an exemplary embodiment. The single figure shows a schematic section of a longitudinal section through a hybrid burner 1 of a gas turbine, not shown.

Der Hybridbrenner 1 wird gebildet aus einem Pilotbrenner 3 und einem Hauptbrenner 5. Der Pilotbrenner 3 weist eine zen- trale Lanze 7 zur Erzeugung einer Pilotflamme auf. Die Lanze 7 ist von einem Pilotluftkanal 9 umgeben. In den Pilotluftka- nal 9 münden BrennstoffZuleitungen 11. Vorzugsweise wird zur im Pilotluftkanal 9 stromende Verbrennungsluft über die BrennstoffZuleitungen 11 Erdöl oder Erdgas gefuhrt. Aus dem Pilotbrenner 3 tritt als Brennstoff-Luftgemisch der Pilotbrenngasstrom 13 aus. Der Hauptbrenner 5 umgibt mit einem ringspaltformigen Luftkanal, im folgenden als Hauptluftkanal 6 bezeichnet, den Pilotbrenner 3. Im Hauptluftkanal 6 wird der Hauptbrenngasstrom 15 gefuhrt. Der Hauptbrenngasstrom 15 besteht aus einer Mischung aus Luft mit Brennstoff, wobei der Brennstoff, z.B. Erdgas oder 01, über nicht naher darge- stellte Mittel zugeführt ist. Der Hauptluftkanal 6 weist eine Kanalwand 17 auf, bestehend aus einer inneren Wand 17A und einer äußeren Wand 17B. Im Mundungsbereich 18 des Hauptluft- kanales 6 weist die innere Wand 17A einen Endbereich auf, welcher eine Vorbrennkammerwand 19 darstellt. Diese Vorbrenn- kammerwand 19 umschließt die Mundung 20 des Pilotbrenners 3 und definiert eine Vorbrennkammer 21 mit einem Austritt 23 zur nicht naher dargestellten Brennkammer 40. Der Austritt 23 weist einen Austrittsdurchmesser 25 auf. Die Mundung 20 des Pilotbrenners 3 weist einen Abstand zum Austritt 23 auf, der die Hohe A der Vorbrennkammer 21 definiert. Vorzugsweise ist das Verhältnis der Hohe A zum Austrittsdurchmesser 25 großer als 50%, insbesondere großer als 100%.The hybrid burner 1 is formed from a pilot burner 3 and a main burner 5. The pilot burner 3 has a central lance 7 for generating a pilot flame. The lance 7 is surrounded by a pilot air duct 9. Fuel feed lines 11 open into the pilot air channel 9 Combustion air flowing in the pilot air duct 9 is led via the fuel supply lines 11 crude oil or natural gas. The pilot fuel gas stream 13 emerges from the pilot burner 3 as a fuel-air mixture. The main burner 5 surrounds the pilot burner 3 with an air duct in the form of an annular gap, hereinafter referred to as the main air duct 6. The main combustion gas stream 15 is guided in the main air duct 6. The main fuel gas stream 15 consists of a mixture of air and fuel, the fuel, for example natural gas or oil, being supplied by means not shown in detail. The main air duct 6 has a duct wall 17 consisting of an inner wall 17A and an outer wall 17B. In the mouth area 18 of the main air duct 6, the inner wall 17A has an end area which represents a pre-combustion chamber wall 19. This pre-combustion chamber wall 19 surrounds the mouth 20 of the pilot burner 3 and defines a pre-combustion chamber 21 with an outlet 23 to the combustion chamber 40 (not shown in more detail). The outlet 23 has an outlet diameter 25. The mouth 20 of the pilot burner 3 is at a distance from the outlet 23, which defines the height A of the pre-combustion chamber 21. The ratio of the height A to the outlet diameter 25 is preferably greater than 50%, in particular greater than 100%.

Der Hauptbrenngasstrom 15 tritt über den Querschnitt des Hauptluftkanales 6 am Austritt 23, im Längsschnitt durch einen Punkt H gekennzeichnet, mit dem Pilotbrenngasstrom 13 in Kontakt. Dabei entzündet sich der Hauptbrenngasstrom 15. Auf der Brennerachse 2 des Hybridbrenners 1 ergibt sich für den Punkt H eine Hauptverbrennungsposition HB. Der Pilotbrenn- gasstrom 13 ist entlang der Brennerachse 2 an einer Pilotverbrennungsposition P zu mehr als der Hälfte verbrannt. Die Pilotverbrennungsposition P liegt entlang der Brennerachse 2 stromungstechnisch vor der Hauptverbrennungsposition HB.The main fuel gas stream 15 comes into contact with the pilot fuel gas stream 13 via the cross section of the main air duct 6 at the outlet 23, identified in longitudinal section by a point H. The main combustion gas stream 15 is ignited in the process. A main combustion position HB results for the point H on the burner axis 2 of the hybrid burner 1. The pilot combustible gas stream 13 has been burned by more than half along the burner axis 2 at a pilot combustion position P. The pilot combustion position P lies along the burner axis 2 in terms of flow technology before the main combustion position HB.

In der Vorbrennkammer 21 findet eine erste Stufe einer Verbrennung des Pilotbrenngasstromes 13 statt. Der Pilotbrenngasstrom 13 wird also getrennt und unabhängig vom Hauptbrenn- gasstrom 15 zumindest teilweise verbrannt. Der Pilotbrenngasstrom 13 bzw. dessen heiße Verbrennungsprodukte entzünden anschließend den Hauptbrenngasstrom 15, wodurch eine zweite Stufe der Verbrennung entsteht. Durch diese zweistufige Ver- brennung werden die maximal auftretenden Flammentemperaturen der Verbrennung reduziert. Dadurch ergibt sich eine verringerte Stickoxidemission, da die Stickoxidbildung exponentiell mit der Flammentemperatur anwachst.A first stage of a combustion of the pilot fuel gas stream 13 takes place in the pre-combustion chamber 21. The pilot fuel gas stream 13 is thus separated and independent of the main fuel gas stream 15 at least partially burned. The pilot fuel gas stream 13 or its hot combustion products then ignite the main fuel gas stream 15, which results in a second stage of combustion. This two-stage combustion reduces the maximum flame temperatures that occur during combustion. This results in a reduced nitrogen oxide emission, since the nitrogen oxide formation increases exponentially with the flame temperature.

Weiterhin erhalt man durch die zweistufige Verbrennung ein größeres Reaktionsvolumen, wodurch es zur Dampfung von Verbrennungsschwingungen kommt. Verbrennungsschwingungen haben unter anderem ihren Ausgangspunkt in spontanen, lokalen Leistungsfreiset ungen der Verbrennung. Durch eine größere Ver- teilung solcher Leistungsfreisetzungen kommt es zu einer wechselseitigen Störung und damit Unterdrückung von Verbrennungsschwingungen .Furthermore, the two-stage combustion gives a larger reaction volume, which leads to the damping of combustion vibrations. Combustion vibrations have their starting point, among other things, in spontaneous, local performance releases of the combustion. A greater distribution of such power releases leads to mutual interference and thus suppression of combustion vibrations.

Vorzugsweise wird dem Hauptbrenngasstrom 15 durch ein Drall- gitter 27 ein Drall erteilt. Das Drallgitter 27 weist im Längsschnitt einen Mittelpunkt 29 auf. Der Mittelpunkt 29 weist eine axiale Position D2 auf der Brennerachse 2 auf. Dem Pilotbrenngasstrom wird durch ein Drallgitter 31 ebenfalls ein Drall erteilt. Das Drallgitter 31 weist im Längsschnitt einen Mittelpunkt 33 auf. Der Mittelpunkt 33 weist eine axiale Position Dl auf der Brennerachse 2 auf. Die axiale Position D2 liegt stromungstechnisch hinter der axialen Position Dl.The main fuel gas stream 15 is preferably given a swirl by a swirl grille 27. The swirl grille 27 has a center point 29 in longitudinal section. The center point 29 has an axial position D2 on the burner axis 2. The pilot fuel gas stream is also given a swirl by a swirl grille 31. The swirl grid 31 has a center point 33 in longitudinal section. The center 33 has an axial position D1 on the burner axis 2. In terms of flow technology, the axial position D2 lies behind the axial position D1.

Die Vorbrennkammerwand 19 wird durch den Hauptbrenngasstrom 15 gekühlt. Für eine verbesserte konvektive Kühlung kann dabei die Vorbrennkammerwand 19 an ihrer Außenseite, d.h. im Hauptluftkanal 6, verrippt sein. The pre-combustion chamber wall 19 is cooled by the main combustion gas stream 15. For improved convective cooling, the pre-combustion chamber wall 19 can be on the outside, i.e. be ribbed in the main air duct 6.

Claims

Patentansprüche claims 1. Entlang einer Brennerachse (2) gerichteter Hybridbrenner (1) , umfassend einen als Vormischbrenner ausgeführten Hauptbrenner (5) f r einen Hauptbrenngasstrom (15) und einen als Diffusionsbrenner ausgeführten Pilotbrenner (3) für einen Pilotbrenngasstrom (13), d a d u r c h g e k e n n z e i c h n e t, daß der Pilot- brenngasstrom (13) zumindest teilweise getrennt vom Hauptbrenngasstrom (15) verbrennbar ist.1. Along a burner axis (2) directed hybrid burner (1), comprising a main burner (5) for a main fuel gas stream (15) and a pilot burner (3) for a pilot fuel gas stream (13), characterized in that the pilot - Fuel gas stream (13) is at least partially combustible separately from the main fuel gas stream (15). 2. Hybridbrenner (1) nach Anspruch 1, d a d u r c h g e k e n n z e i c h n e t, daß der Hauptbrenngasstrom (15) an einer Hauptverbrennungsposition (HB) entzündbar und der Pilotbrenngasstrom (13) so verbrennbar ist, daß er an einer Pilotverbrennungsposition (P) zu mehr als der Hälfte verbrannt ist, wobei die Pilotverbrennungsposition (P) entlang der Brennerachse (2) stromungstech- nisch vor der Hauptverbrennungsposition (HB) liegt.2. Hybrid burner (1) according to claim 1, characterized in that the main fuel gas stream (15) at a main combustion position (HB) is flammable and the pilot fuel gas stream (13) is combustible so that it is burned to more than half at a pilot combustion position (P) , where the pilot combustion position (P) lies in terms of flow technology in front of the main combustion position (HB) along the burner axis (2). 3. Hybridbrenner (1) nach Anspruch 1 oder 2, d a d u r c h g e k e n n z e i c h n e t, daß dem Hauptbrenner (5) in einem Hauptluftkanal (6) und dem Pilotbrenner (3) in einem Pilotluftkanal (9) jeweils Verbrennungsluft zufuhrbar ist, wobei im Hauptluftkanal (6) ein Hauptdrallgitter (27) und im Pilotluftkanal (9) ein Pilotdrallgitter (31) angeordnet sind und wobei das Pilotdrallgitter (31) gemessen entlang der Brennerachse (2) stromungstechnisch vor dem Haupt- drallgitter (27) liegt.3. Hybrid burner (1) according to claim 1 or 2, characterized in that the main burner (5) in a main air duct (6) and the pilot burner (3) in a pilot air duct (9) each combustion air can be supplied, wherein in the main air duct (6) Main swirl grille (27) and a pilot swirl grille (31) are arranged in the pilot air duct (9), and the pilot swirl grille (31), measured along the burner axis (2), lies in terms of flow technology in front of the main swirl grille (27). 4. Hybridbrenner (1) nach Anspruch 1, 2 oder 3, d a d u r c h g e k e n n z e i c h n e t, daß der Hauptbrenner (5) den Pilotbrenner (3) insbesondere ringkanalformig umgibt. 4. Hybrid burner (1) according to claim 1, 2 or 3, characterized in that the main burner (5) surrounds the pilot burner (3) in particular in the form of an annular channel. 5. Hybridbrenner (1) nach Anspruch 4, d a d u r c h g e k e n n z e i c h n e t, daß durch den Hauptbrenner (5) für den Pilotbrenner (3) eine Vorbrennkammer5. hybrid burner (1) according to claim 4, d a d u r c h g e k e n n z e i c h n e t that by the main burner (5) for the pilot burner (3) a pre-combustion chamber (21) mit einer Vorbrennkammerwand (19) gebildet ist, wobei die Vorbrennkammerwand (19) durch Verbrennungsluft, welche dem Hauptbrenner (5) zufuhrbar ist, kuhlbar ist.(21) is formed with a pre-combustion chamber wall (19), the pre-combustion chamber wall (19) being able to be cooled by combustion air which can be supplied to the main burner (5). 6. Hybridbrenner (1) nach einem der vorhergehenden Ansprüche für einen wahlweisen Betrieb mit Erdgas oder Erdöl.6. Hybrid burner (1) according to one of the preceding claims for optional operation with natural gas or petroleum. 7. Hybridbrenner (1) nach einem der vorhergehenden Ansprüche für eine, insbesondere stationäre, Gasturbine.7. Hybrid burner (1) according to one of the preceding claims for a, in particular stationary, gas turbine. 8. Entlang einer Brennerachse (2) gerichteter Hybridbrenner ( 1) , umfassend einen als Vormischbrenner ausgeführten Hauptbrenner (5) für einen Hauptbrenngasstrom (15) und einen als Diffusionsbrenner ausgeführten Pilotbrenner (3) für einen Pilotbrenngasstrom (13), d a d u r c h g e k e n n z e i c h n e t, daß der Pilotbrenner (3) in eine Vorbrennkammer (20) mundet, welche einen Austritt (23) mit einem Austrittsdurchmesser (25) zu einer Brennkammer (40) und eine Hohe (A) aufweist, die durch den Abstand des Pilotbrenners (3) zum Austritt (23) definiert ist, wobei die Hohe (A) mindestens 50%, insbesondere mehr als 100% vom Austrittsdurchmesser (25) betragt.8. Along a burner axis (2) directed hybrid burner (1), comprising a main burner (5) designed as a premix burner for a main fuel gas stream (15) and a pilot burner (3) designed for a pilot fuel gas stream (13), characterized in that the pilot burner (3) flows into a pre-combustion chamber (20), which has an outlet (23) with an outlet diameter (25) to a combustion chamber (40) and a height (A), which is due to the distance of the pilot burner (3) to the outlet (23 ) is defined, the height (A) being at least 50%, in particular more than 100% of the outlet diameter (25). 9. Verfahren zum Betrieb eines Hybridbrenners (1), bei dem ein Hauptbrenngasstrom (15) durch Vormischung von Brennstoff und Luft gebildet und durch Zündung an einem brennenden Pilotbrenngasstrom (13) verbrannt wird, d a d u r c h g e k e n n z e i c h n e t, daß der Pilotbrenngasstrom (13), bevor er den Hauptbrenngasstrom (15) zündet, zu mehr als der Hälfte verbrannt wird.9. A method of operating a hybrid burner (1), in which a main fuel gas stream (15) is formed by premixing fuel and air and burned by ignition on a burning pilot fuel gas stream (13), characterized in that the pilot fuel gas stream (13) before it Main fuel gas stream (15) ignites, more than half is burned. 10. Verfahren nach Anspruch 9, d a d u r c h g e k e n n z e i c h n e t, daß der Haupt- brenngasstrom (15) den Pilotbrenngasstrom (13) umgebend geführt wird. 10. The method according to claim 9, characterized in that the main Fuel gas stream (15) is guided surrounding the pilot fuel gas stream (13).
PCT/DE1999/002532 1998-08-26 1999-08-13 Hybrid burner and method for operating a hybrid burner Ceased WO2000012933A1 (en)

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EP1333228A2 (en) 2002-02-01 2003-08-06 General Electric Company Method and apparatus to decrease combustor emissions
EP1712837A1 (en) * 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Burner assembly and method of operating it
EP1710502A3 (en) * 2005-03-30 2007-03-14 Ansaldo Energia S.P.A. Gas burner assembly for a gas turbine
EP1764553A1 (en) * 2005-09-14 2007-03-21 Enel Produzione S.p.A. High-stability premix burner for gas turbines
EP2244015A1 (en) 2009-04-23 2010-10-27 Siemens Aktiengesellschaft Pre-mix burner

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Cited By (6)

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Publication number Priority date Publication date Assignee Title
EP1333228A2 (en) 2002-02-01 2003-08-06 General Electric Company Method and apparatus to decrease combustor emissions
EP1333228A3 (en) * 2002-02-01 2007-03-28 General Electric Company Method and apparatus to decrease combustor emissions
EP1710502A3 (en) * 2005-03-30 2007-03-14 Ansaldo Energia S.P.A. Gas burner assembly for a gas turbine
EP1712837A1 (en) * 2005-04-14 2006-10-18 Siemens Aktiengesellschaft Burner assembly and method of operating it
EP1764553A1 (en) * 2005-09-14 2007-03-21 Enel Produzione S.p.A. High-stability premix burner for gas turbines
EP2244015A1 (en) 2009-04-23 2010-10-27 Siemens Aktiengesellschaft Pre-mix burner

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