EP1319895B1 - Lean-burn premix burner for gas turbine and its method of operation - Google Patents

Lean-burn premix burner for gas turbine and its method of operation Download PDF

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Publication number
EP1319895B1
EP1319895B1 EP02023428A EP02023428A EP1319895B1 EP 1319895 B1 EP1319895 B1 EP 1319895B1 EP 02023428 A EP02023428 A EP 02023428A EP 02023428 A EP02023428 A EP 02023428A EP 1319895 B1 EP1319895 B1 EP 1319895B1
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EP
European Patent Office
Prior art keywords
fuel
nozzles
lean
burn
accordance
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EP02023428A
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German (de)
French (fr)
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EP1319895A3 (en
EP1319895A2 (en
Inventor
Ralf Sebastian Von Der Bank
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34Feeding into different combustion zones
    • F23R3/346Feeding into different combustion zones for staged combustion
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2201/00Staged combustion
    • F23C2201/20Burner staging

Definitions

  • the invention relates to a lean burn burner for a gas turbine with the features of the preamble of the main claim and to a method for operating a lean burn burner.
  • the invention relates to a lean burn burner with at least one fuel feed ring provided with primary fuel nozzles.
  • Such a lean burn burner can be designed either as an LPP module or as a swirl cup.
  • Magervormischbrenner are known from the prior art in a variety of Ausgestaltunsformen.
  • lean burn burners have been developed to prevent the formation of nitrogen oxides.
  • the air-fuel ratio is set high due to the process, resulting in a very lean mixture. This produces relatively low combustion temperatures in the main burnup zone.
  • a further disadvantage is that a combustion guide is achieved by the very lean mixture, which under normal circumstances can not be carried much further without creating instabilities. Another transformation finally leads to the extinction of the flame. It follows that additional so-called pilot burners must be available for safe, aviation-efficient operation. These pilot burners ensure a high local combustion temperature. This in turn leads to a high flame stability. A disadvantage of the operation of the pilot burner, it turns out that relatively high NO x emissions arise.
  • the US Pat. No. 6,109,038 A discloses a burner having two concentric independent fuel supply rings. These are each provided with fuel outlet openings, which serve to introduce fuel into different air flow paths
  • the US 5,351,477 A. discloses a separate fuel conduit disposed in a gas-fuel conduit and serving to deliver additional fuel. It is thus provided fuel supply ring, which is equipped with additional fuel nozzles.
  • the US 4 222 243 A shows fuel ports, which are arranged on two axially staggered rings and can be controlled separately.
  • the invention is based on the object to provide a lean burn burner and a method for operating a lean burn burner, which lead in a simple structure while avoiding the prior art to a low thermal load and burn safely even under very lean conditions.
  • the object is achieved with regard to the lean burn burner by the combination of features of the main claim, with regard to the method, the solution of the problem by the feature combination of the independent claim.
  • the respective subclaims show further advantageous embodiments of the invention.
  • the lean burn burner according to the invention is characterized by a number of significant advantages.
  • the additional fuel secondary nozzles it is possible to locally enrich the fuel-air mixture. It is thus not necessary to provide additional pilot burners or the like. Rather, according to the invention, there are areas on the fuel injection ring at which a richer fuel-air mixture is present. This leads to combustion at higher temperatures and thus to a more stable flame guidance. This results in a more stable operation of the lean burn burner, the risk of extinction is thereby avoided in a reliable manner.
  • the fuel primary nozzles are evenly distributed on the circumference of the fuel supply ring, while the fuel secondary nozzles are distributed unevenly around the circumference. It is particularly advantageous if the fuel secondary nozzles are arranged only in some sectors of the fuel injection system. This ensures that individual areas of the fuel injection system can be supplied with a richer mixture.
  • the fuel supply is switched according to the invention so that selectively at low or low load in the vicinity of at least two primary fuel nozzles additional, adjacent fuel secondary nozzles for enrichment of the fuel-air mixture are put into operation.
  • the primary fuel nozzles are switched on again in order to achieve a continuous increase in the fuel mass flow. The then no longer required fuel secondary nozzles are blown out accordingly.
  • fuel mini nozzles are formed on the fuel injection ring. These fuel mini nozzles can be arranged in groups (clusters).
  • a richer air-fuel mixture is locally adjusted at the fuel supply ring, while no fuel is injected at other locations of the fuel supply ring.
  • the total amount of fuel supplied to the lean premix burner remains substantially the same.
  • Another significant advantage of the invention is that a continuous transition from full load to low or low load can be made.
  • discontinuous fuel shift between pilot burners and Magervormischbrennern and the systems required for this purpose can be completely dispensed with according to the invention. This in turn results in a better thrust curve when switching the gas turbine to different load ranges.
  • the reference numeral 1 shows a schematic side view of an inventive lean premix module in a gas turbine combustor.
  • the reference numeral 1 denotes a flame tube, which is preceded by a lean premix burner. This comprises an outer housing 2 and an inner housing 3. On the inner housing, a fuel-injection ring 4 is formed.
  • the reference numeral 5 describes an inner body of the lean premix burner, with the reference numeral 6 are generally fuel nozzles shown.
  • FIG. 2 shows a sectional view along the line A-B of FIG. 1.
  • a plurality of fuel nozzles 6 are shown schematically on the fuel supply ring 4.
  • FIG. 2 explains that individual ones of the fuel nozzles 6, namely the fuel nozzles 6a are in operation while the illustrated fuel nozzles 6b are out of operation.
  • Fig. 3 is again enlarged a section through an embodiment of the fuel supply ring according to the invention 4.
  • This comprises two fuel supply ducts 7, which each have a plurality of fuel primary nozzles 8 and fuel secondary nozzles 9 are assigned at the periphery. From the representation of FIG. 3 it follows that the fuel primary nozzles 8 and the fuel primary nozzles 9 are each provided with their own fuel supply channels 7, so that a different supply of fuel can take place.
  • FIGS. 4 and 5 each show in an end view (greatly simplified) the arrangement of the fuel nozzles on the circumference of the fuel supply ring 4.
  • the individual fuel primary nozzles 8 are evenly distributed around the circumference and are accordingly in Business.
  • Fig. 5 shows a total of four fuel nozzle sectors in which different, unevenly distributed over the circumference arrangements of fuel secondary nozzles 9 are shown. Since the fuel primary nozzles 8 and the fuel primary nozzles 9 are located in different planes (see FIG. 3), the arrangement of the fuel secondary nozzles 9 shown in FIG. 5 results.
  • FIG. 6 shows a symmetrical peripheral circuit in which lean premix modules 14 which are in operation alternate with lean premix modules 15 which are out of operation.
  • FIG. 7 a diagram is selected in which an asymmetrical circumferential step (grouping peripheral circuit) is selected.
  • Each of a plurality of lean premix modules 14 are operating side-by-side, while adjacent several bulk premix modules 15 are taken out of service.
  • FIG. 8 shows a sectional view, similar to FIG. 2, in which fuel mini-nozzles 13 are additionally provided in a clustered arrangement on the fuel supply ring 4. These fuel mini-nozzles 13 have a higher injection speed of the fuel and thereby lead to a locally richer fuel-air mixture. Adjacent to the fuel mini-nozzles 13 schematically fuel-primary nozzles 8 are shown.
  • Fig. 9 is a diagram is shown, in which the fuel mass flow is shown against the thermal load of the engine / the gas turbine. The resulting straight line leads from the zero point through a full load point.
  • the burners are switched to the three different operating stages shown below.
  • a switching point is provided.
  • the burner modules or lean burn burners are switched off in such a way that the lean burn burners or modules remaining in operation reach a thermal load of approximately 100% at the switching point I.
  • the circuit is via valves, with switches or controllable valves can be used.
  • a middle switching point II which may be about half the thermal load of the first point I, groups of injectors of the previously left in operation lean burn burner or lean modules are turned off. This achieves a continued operation of the existing fuel injectors at 100% (at the switching point) of the individual fuel mass flow rate.
  • an asymmetrical arrangement of the fuel nozzles remaining in operation can be provided (asymmetric group circuit).
  • At the third switching point III is a further load reduction switching from the normal nozzles (fuel primary nozzles and fuel secondary nozzles) on clusters of mini nozzles or secondary Eindadorering before.
  • These mini nozzles have, as described, a significantly smaller diameter than the normal nozzles.
  • the mini nozzles / secondary nozzles lead to an acceptable fuel Zersteubungs at low load with comparatively better droplet evaporation behavior and yet locally produce a relatively rich air-fuel mixture.
  • the improved fuel atomization and better droplet evaporation behavior are also advantageous and important because in the low load range of the gas turbine, the delivery temperature of the compressor is low. According to the invention, a flameproof mixture is thus produced.
  • a grouping or interconnection of individual modules of lean premix burners takes place in an annular combustion chamber in order to combine the lean burn burners in operation into groups at low load.
  • By switching off other lean burn burner or modules results in the remaining modules or lean burn burner with a constant fuel quantity of the combustion chamber a richer or richer mixture.
  • additional secondary nozzles or mini-nozzles in order to select individual areas within a lean burn burner in which (seen in the circumferential direction) a single sector richer or richer fuel-air mixture is present.

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

Description

Die Erfindung bezieht sich auf einen Magervormischbrenner für eine Gasturbine mit den Merkmalen des Oberbegriffs des Hauptanspruchs sowie auf ein Verfahren zum Betrieb eines Magervormischbrenners.The invention relates to a lean burn burner for a gas turbine with the features of the preamble of the main claim and to a method for operating a lean burn burner.

Im Einzelnen bezieht sich die Erfindung auf einen Magervormischbrenner mit zumindest einem mit Brennstoff-Primärdüsen versehenen Brennstoff-Versorgungsring.In particular, the invention relates to a lean burn burner with at least one fuel feed ring provided with primary fuel nozzles.

Ein derartiger Magervormischbrenner kann entweder als LPP-Modul oder als Swirlcup ausgebildet sein.Such a lean burn burner can be designed either as an LPP module or as a swirl cup.

Magervormischbrenner sind aus dem Stand der Technik in unterschiedlichsten Ausgestaltunsformen bekannt.Magervormischbrenner are known from the prior art in a variety of Ausgestaltunsformen.

Magervormischbrenner wurden unter anderem entwickelt, um die Bildung von Stickoxiden zu vermeiden. Hierfür wird das Luft-Brennstoff-Verhältnis verfahrensbedingt hoch eingestellt, sodass ein sehr mageres Gemisch entsteht. Dieses erzeugt in der Hauptabbrandzone relativ niedrige Verbrennungstemperaturen.For example, lean burn burners have been developed to prevent the formation of nitrogen oxides. For this purpose, the air-fuel ratio is set high due to the process, resulting in a very lean mixture. This produces relatively low combustion temperatures in the main burnup zone.

Als nachteilig kann sich erweisen, dass durch die relativ niedrigen Verbrennungstemperaturen die Verbrennung selbst nicht so vollständig ist, wie sie bei höheren Temperaturen wäre. Somit entstehen unverbrannte Kohlenwasserstoff- und Kohlenmonoxid-Emissionen.It may be disadvantageous that due to the relatively low combustion temperatures, the combustion itself is not as complete as it would be at higher temperatures. This produces unburned hydrocarbon and carbon monoxide emissions.

Ein weiterer Nachteil besteht darin, dass durch das sehr magere Gemisch eine Verbrennungsführung erzielt wird, welche unter normalen Umständen nicht sehr viel weiter zu vermagern ist, ohne Instabilitäten zu erzeugen. Eine weitere Vermagerung führt schließlich zum Verlöschen der Flamme. Hieraus ergibt sich, dass zum sicheren, luftfahrttüchtigen Betrieb zusätzliche sogenannte Pilotbrenner vorhanden sein müssen. Diese Pilotbrenner gewährleisten eine hohe lokale Verbrennungstemperatur. Dies wiederum führt zu einer hohen Flammenstabilität. Nachteilig beim Betrieb der Pilotbrenner erweist es sich, dass relativ hohe NOx-Emissionen entstehen.A further disadvantage is that a combustion guide is achieved by the very lean mixture, which under normal circumstances can not be carried much further without creating instabilities. Another transformation finally leads to the extinction of the flame. It follows that additional so-called pilot burners must be available for safe, aviation-efficient operation. These pilot burners ensure a high local combustion temperature. This in turn leads to a high flame stability. A disadvantage of the operation of the pilot burner, it turns out that relatively high NO x emissions arise.

Der Stand der Technik zeigt die Verwendung dieser Pilotbrenner in axial gestuften Brennkammern, welche zusammen mit Magervormischbrennern eingesetzt werden. Derartige Brennkammern sind relativ groß, sie weisen eine komplexe Geometrie auf und haben eine große zu kühlende Oberfläche.The prior art shows the use of these pilot burners in axially stepped combustors used with lean burn burners. Such combustion chambers are relatively large, they have a complex geometry and have a large surface to be cooled.

Die US 6 109 038 A offenbart einen Brenner mit zwei zueinander konzentrischen, unabhängigen Brennstoffversorgungsringen. Diese sind jeweils mit Brennstoff-Austrittsöffnungen versehen, welche dazu dienen, Brennstoff in unterschiedliche Luft-Strömungswege einzubringenThe US Pat. No. 6,109,038 A discloses a burner having two concentric independent fuel supply rings. These are each provided with fuel outlet openings, which serve to introduce fuel into different air flow paths

Die US 5 351 477 A offenbart eine separate Brennstoffleitung, die in einer Gas-Brennstoff-Leitung angeordnet ist und dazu dient, zusätzlichen Brennstoff auszubringen. Es ist somit Brennstoff-Versorgungsring vorgesehen, welcher mit zusätzlichen Brennstoff-Düsen ausgerüstet ist.The US 5,351,477 A. discloses a separate fuel conduit disposed in a gas-fuel conduit and serving to deliver additional fuel. It is thus provided fuel supply ring, which is equipped with additional fuel nozzles.

Die US 4 222 243 A zeigt Brennstofföffnungen, die auf zwei axial zueinander versetzten Ringen angeordnet und separat ansteuerbar sind.The US 4 222 243 A shows fuel ports, which are arranged on two axially staggered rings and can be controlled separately.

Der Erfindung liegt die Aufgabe zu Grunde, einen Magervormischbrenner sowie ein Verfahren zum Betrieb eines Magervormischbrenners zu schaffen, welche bei einfachem Aufbau unter Vermeidung des Standes der Technik zu einer niedrigen thermischen Belastung führen und auch bei sehr mageren Bedingungen sicher brennen.The invention is based on the object to provide a lean burn burner and a method for operating a lean burn burner, which lead in a simple structure while avoiding the prior art to a low thermal load and burn safely even under very lean conditions.

Erfindungsgemäß wird die Aufgabe hinsichtlich des Magervormischbrenners durch die Merkmalskombination des Hauptanspruchs gelöst, hinsichtlich des Verfahrens erfolgt die Lösung der Aufgabe durch die Merkmalskombination des nebengeordneten Anspruchs. Die jeweiligen Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention, the object is achieved with regard to the lean burn burner by the combination of features of the main claim, with regard to the method, the solution of the problem by the feature combination of the independent claim. The respective subclaims show further advantageous embodiments of the invention.

Der erfindungsgemäße Magervormischbrenner zeichnet sich durch eine Reihe erheblicher Vorteile aus.The lean burn burner according to the invention is characterized by a number of significant advantages.

Durch die zusätzlichen Brennstoff-Sekundärdüsen ist es möglich, lokal das Brennstoff-Luft-Gemisch anzureichern. Es ist somit nicht erforderlich, zusätzliche Pilotbrenner oder Ähnliches vorzusehen. Vielmehr ergeben sich erfindungsgemäß Bereiche an dem Brennstoff-Eindüsering, an denen ein reicheres Brennstoff-Luftgemisch vorliegt. Dieses führt zu einer Verbrennung bei höheren Temperaturen und damit zu einer stabileren Flammenführung. Hierdurch ergibt sich ein stabilerer Betrieb des Magervormischbrenners, die Gefahr eines Verlöschens wird dabei in zuverlässiger Weise vermieden. In der Erfindung ist vorgesehen, dass die Brennstoff-Primärdüsen gleichmäßig am Umfang des Brennstoff-Versorgungsrings verteilt sind, während die Brennstoff-Sekundärdüsen ungleichmäßig am Umfang verteilt sind. Dabei ist es besonders günstig, wenn die Brennstoff-Sekundärdüsen nur in einigen Sektoren des Brennstoff-Eindüserings angeordnet sind. Hierdurch wird erreicht, dass einzelne Bereiche des Brennstoff-Eindüserings mit einem reicheren Gemisch versorgt werden können.The additional fuel secondary nozzles, it is possible to locally enrich the fuel-air mixture. It is thus not necessary to provide additional pilot burners or the like. Rather, according to the invention, there are areas on the fuel injection ring at which a richer fuel-air mixture is present. This leads to combustion at higher temperatures and thus to a more stable flame guidance. This results in a more stable operation of the lean burn burner, the risk of extinction is thereby avoided in a reliable manner. In the invention it is provided that the fuel primary nozzles are evenly distributed on the circumference of the fuel supply ring, while the fuel secondary nozzles are distributed unevenly around the circumference. It is particularly advantageous if the fuel secondary nozzles are arranged only in some sectors of the fuel injection system. This ensures that individual areas of the fuel injection system can be supplied with a richer mixture.

Erfindungsgemäß ergibt sich somit eine interne Stufung der Brennstoffzufuhr über den Brennstoff-Versorgungsring. Die Brennstoffzufuhr wird erfindungsgemäß derart geschaltet, dass punktuell bei Minder- bzw. Niedriglast in der Nähe von mindestens zwei Brennstoff-Primärdüsen zusätzliche, benachbarte Brennstoff-Sekundärdüsen zur Anreicherung des Brennstoff-Luft-Gemisches in Betrieb genommen werden.According to the invention thus results in an internal gradation of the fuel supply via the fuel supply ring. The fuel supply is switched according to the invention so that selectively at low or low load in the vicinity of at least two primary fuel nozzles additional, adjacent fuel secondary nozzles for enrichment of the fuel-air mixture are put into operation.

Um in dem jeweiligen Lastbereich der Gasturbine die Gesamt-Brennstoffmenge konstant zu halten, werden erfindungsgemäß andere, nicht benötigte Brennstoff-Primärdüsen abgeschaltet.In order to keep constant in the respective load range of the gas turbine, the total amount of fuel, according to the invention other, unnecessary fuel primary nozzles are turned off.

Sofern von dem Minder- bzw. Niedriglastbetrieb wieder auf einen Vollastbetrieb übergegangen wird, werden zur Erzielung eines kontinuierlichen Anstiegs des Brennstoff-Massenstroms die Brennstoff-Primärdüsen jeweils wieder zugeschaltet. Die dann nicht mehr benötigten Brennstoff-Sekundärdüsen werden entsprechend ausgeblasen.If a change is made from the low-load or low-load mode to a full-load mode, the primary fuel nozzles are switched on again in order to achieve a continuous increase in the fuel mass flow. The then no longer required fuel secondary nozzles are blown out accordingly.

Um einen sicheren Betrieb auch in einem niedrigen Lastbereich zu gewährleisten, kann es günstig sein, wenn an dem Brennstoff-Eindüsering zusätzliche Brennstoff-Minidüsen ausgebildet sind. Diese Brennstoff-Minidüsen können in Gruppen angeordnet sein (Cluster).In order to ensure safe operation even in a low load range, it may be favorable if additional fuel mini nozzles are formed on the fuel injection ring. These fuel mini nozzles can be arranged in groups (clusters).

Hinsichtlich des erfindungsgemäßen Verfahrens ist somit vorgesehen, dass lokal an dem Brennstoff-Versorgungsring ein reicheres Luft-Brennstoff-Gemisch eingestellt wird, während an anderen Stellen des Brennstoff-Versorgungsrings kein Brennstoff eingespritzt wird. Wie erwähnt, bleibt dabei die Gesamt-Brennstoffmenge, die dem Magervormischbrenner zugeführt wird, im Wesentlichen gleich.With regard to the method according to the invention, it is thus provided that a richer air-fuel mixture is locally adjusted at the fuel supply ring, while no fuel is injected at other locations of the fuel supply ring. As mentioned, the total amount of fuel supplied to the lean premix burner remains substantially the same.

Erfindungsgemäß ergibt sich somit eine hohe Flammensicherheit (Stabilität) des Magervormischbrenners, sodass auf zusätzliche Pilotbrenner gänzlich verzichtet werden kann. Hierdurch wird das Brennkammervolumen kleiner. Auch die Oberfläche der Brennkammer verringert sich, wodurch wiederum der Kühlluftbedarf sinkt. Hierdurch ergibt sich eine Steigerung des Wirkungsgrades der Gasturbine.According to the invention thus results in a high flame resistance (stability) of the lean burn burner, so that can be completely dispensed with additional pilot burner. As a result, the combustion chamber volume is smaller. The surface of the combustion chamber is also reduced, which in turn reduces the cooling air requirement. This results in an increase in the efficiency of the gas turbine.

Ein weiterer, wesentlicher Vorteil der Erfindung besteht darin, dass ein kontinuierlicher Übergang von einem Vollastbetrieb auf einen Minder- oder Niedriglastbetrieb erfolgen kann. Auf die aus dem Stand der Technik bekannte diskontinuierliche Brennstoffverschiebung zwischen Pilotbrennern und Magervormischbrennern und die hierfür benötigten Systeme kann erfindungsgemäß gänzlich verzichtet werden. Hieraus wiederum ergibt sich ein besserer Schubverlauf beim Umschalten der Gasturbine auf unterschiedliche Lastbereiche.Another significant advantage of the invention is that a continuous transition from full load to low or low load can be made. On the known from the prior art discontinuous fuel shift between pilot burners and Magervormischbrennern and the systems required for this purpose can be completely dispensed with according to the invention. This in turn results in a better thrust curve when switching the gas turbine to different load ranges.

Im Folgenden wird die Erfindung anhand von Ausführungsbeispielen in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Fig. 1
eine vereinfachte Darstellung eines Magervormischbrenners in einer Gasturbinenbrennkammer,
Fig. 2
eine Prinzipansicht entlang der Linie A-B von Fig. 1, die die Anordnung von Primärdüsen am Umfang zeigt,
Fig. 3
eine vergrößerte Teil-Schnittansicht eines erfindungsgemäßen Brennstoff-Eindüserings,
Fig. 4
eine stark vereinfachte schematische stirnseitige Ansicht eines Brennstoff-Versorgungsrings mit gleichmäßiger Verteilung der Brennstoff-Primärdüsen,
Fig. 5
eine Ansicht analog Fig. 4, eines Teillast- oder Niedriglastbetriebs,
Fig. 6
eine Darstellung, ähnlich den Fig. 4 und 5, mit Darstellung unterschiedlich geschalteten Magervormischbrennern,
Fig. 7
eine abgewandelte Darstellung der Fig. 6,
Fig. 8
eine Schnittansicht, ähnlich Fig. 2, zur Darstellung von Brennstoff-Minidüsen, und
Fig. 9
ein Betriebsdiagramm unterschiedlicher Laststufen.
In the following the invention will be described by means of embodiments in conjunction with the drawing. Showing:
Fig. 1
a simplified representation of a lean burn burner in a gas turbine combustor,
Fig. 2
1 is a schematic view along the line AB of FIG. 1, showing the arrangement of primary nozzles on the circumference;
Fig. 3
an enlarged partial sectional view of a fuel Eindüsserings invention,
Fig. 4
a greatly simplified schematic frontal view of a fuel supply ring with uniform distribution of the fuel primary nozzles,
Fig. 5
a view analogous to FIG. 4, a partial load or low load operation,
Fig. 6
a representation, similar to FIGS. 4 and 5, showing differently connected lean burn burners,
Fig. 7
a modified representation of FIG. 6,
Fig. 8
a sectional view, similar to Figure 2, showing fuel mini-nozzles, and
Fig. 9
an operating diagram of different load levels.

In den Ausführungsbeispielen sind gleiche Teile jeweils mit gleichen Bezugsziffern versehen.In the embodiments, the same parts are each provided with the same reference numerals.

Die Fig. 1 zeigt in schematischer Seitenansicht ein erfindungsgemäßes Magervormischmodul in einer Gasturbinenbrennkammer. Mit dem Bezugszeichen 1 ist ein Flammrohr bezeichnet, welchem ein Magervormischbrenner vorgeschaltet ist. Dieser umfasst ein äußeres Gehäuse 2 sowie ein inneres Gehäuse 3. An dem inneren Gehäuse ist ein Brennstoff-Eindüsering 4 ausgebildet. Das Bezugszeichen 5 beschreibt einen inneren Körper des Magervormischbrenners, mit dem Bezugszeichen 6 sind ganz allgemein Brennstoffdüsen dargestellt.1 shows a schematic side view of an inventive lean premix module in a gas turbine combustor. The reference numeral 1 denotes a flame tube, which is preceded by a lean premix burner. This comprises an outer housing 2 and an inner housing 3. On the inner housing, a fuel-injection ring 4 is formed. The reference numeral 5 describes an inner body of the lean premix burner, with the reference numeral 6 are generally fuel nozzles shown.

Derartige Magervormischbrenner sind in ihrer Grundkonstruktion aus dem Stand der Technik bekannt, sodass auf weitere Ausführungen an dieser Stelle verzichtet werden kann.Such lean burn burners are known in their basic construction from the prior art, so that it is possible to dispense with further embodiments at this point.

Die Fig. 2 zeigt eine Schnittansicht längs der Linie A-B von Fig. 1. Hierbei sind schematisch an dem Brennstoff-Versorgungsring 4 mehrere Brennstoffdüsen 6 dargestellt. Auf die Brennstoffversorgung selbst und ähnliche Details wurde hierbei verzichtet. Die Fig. 2 erläutert, dass einzelne der Brennstoffdüsen 6, nämlich die Brennstoffdüsen 6a in Betrieb sind, während die dargestellten Brennstoffdüsen 6b außer Betrieb sind.FIG. 2 shows a sectional view along the line A-B of FIG. 1. Here, a plurality of fuel nozzles 6 are shown schematically on the fuel supply ring 4. On the fuel supply itself and similar details was omitted here. FIG. 2 explains that individual ones of the fuel nozzles 6, namely the fuel nozzles 6a are in operation while the illustrated fuel nozzles 6b are out of operation.

In Fig. 3 ist nochmals vergrößert ein Schnitt durch ein Ausführungsbeispiel des erfindungsgemäßen Brennstoff-Versorgungsrings 4 gezeigt. Dieser umfasst zwei Brennstoff-Zuführungskanäle 7, denen jeweils am Umfang mehrere Brennstoff-Primärdüsen 8 sowie Brennstoff-Sekundärdüsen 9 zugeordnet sind. Aus der Darstellung der Fig. 3 ergibt sich, dass die Brennstoff-Primärdüsen 8 und die Brennstoff-Primärdüsen 9 jeweils mit eigenen Brennstoff-Zuführungskanälen 7 versehen sind, sodass eine unterschiedliche Versorgung mit Brennstoff stattfinden kann.In Fig. 3 is again enlarged a section through an embodiment of the fuel supply ring according to the invention 4. This comprises two fuel supply ducts 7, which each have a plurality of fuel primary nozzles 8 and fuel secondary nozzles 9 are assigned at the periphery. From the representation of FIG. 3 it follows that the fuel primary nozzles 8 and the fuel primary nozzles 9 are each provided with their own fuel supply channels 7, so that a different supply of fuel can take place.

Die Fig. 4 und 5 zeigen jeweils in stirnseitiger Ansicht (stark vereinfacht) die Anordnung der Brennstoffdüsen am Umfang des Brennstoff-Versorgungsrings 4. Bei der Darstellung der Fig. 4 sind die einzelnen Brennstoff-Primärdüsen 8 gleichmäßig am Umfang verteilt und befinden sich dementsprechend in Betrieb. Demgegenüber zeigt die Fig. 5 insgesamt vier Brennstoff-Düsensektoren, in denen unterschiedliche, ungleichmäßig über den Umfang verteilte Anordnungen von Brennstoff-Sekundärdüsen 9 dargestellt sind. Da sich die Brennstoff-Primärdüsen 8 und die Brennstoff-Primärdüsen 9 in unterschiedlichen Ebenen befinden (siehe Fig. 3), ergibt sich die in Fig. 5 gezeigte Anordnung der Brennstoff-Sekundärdüsen 9.FIGS. 4 and 5 each show in an end view (greatly simplified) the arrangement of the fuel nozzles on the circumference of the fuel supply ring 4. In the illustration of Fig. 4, the individual fuel primary nozzles 8 are evenly distributed around the circumference and are accordingly in Business. In contrast, Fig. 5 shows a total of four fuel nozzle sectors in which different, unevenly distributed over the circumference arrangements of fuel secondary nozzles 9 are shown. Since the fuel primary nozzles 8 and the fuel primary nozzles 9 are located in different planes (see FIG. 3), the arrangement of the fuel secondary nozzles 9 shown in FIG. 5 results.

Die Fig. 6 und 7 zeigen in vereinfachter, schematischer Darstellung die Anordnung von umfangsgestuften Magervormischbrennern. Die Fig. 6 zeigt dabei eine symmetrische Umfangsschaltung, bei der sich Magervormischmodule 14, die in Betrieb sind, mit Magervormischmodulen 15, die außer Betrieb sind, abwechseln. Demgegenüber ist in Fig. 7 eine Darstellung gewählt, bei der eine asymmetrische Umfangsstufung (gruppierende Umfangsschaltung) gewählt ist. Es sind jeweils mehrere Magervormischmodule 14 nebeneinander in Betrieb, während angrenzend mehrere Magervormischmodule 15 außer Betrieb genommen sind.Figures 6 and 7 show, in a simplified schematic representation, the arrangement of circumferentially graded lean burn burners. FIG. 6 shows a symmetrical peripheral circuit in which lean premix modules 14 which are in operation alternate with lean premix modules 15 which are out of operation. On the other hand, in Fig. 7, a diagram is selected in which an asymmetrical circumferential step (grouping peripheral circuit) is selected. Each of a plurality of lean premix modules 14 are operating side-by-side, while adjacent several bulk premix modules 15 are taken out of service.

Die Fig. 8 zeigt eine Schnittansicht, ähnlich Fig. 2, in welcher zusätzlich Brennstoff-Minidüsen 13 in einer gruppierten Anordnung (Cluster) an dem Brennstoff-Versorgungsring 4 vorgesehen sind. Diese Brennstoff-Minidüsen 13 weisen eine höhere Einspritzgeschwindigkeit des Brennstoffs auf und führen dabei zu einem lokal reicheren Brennstoff-Luft-Gemisch. Angrenzend an die Brennstoff-Minidüsen 13 sind schematisch Brennstoff-Primärdüsen 8 gezeigt.FIG. 8 shows a sectional view, similar to FIG. 2, in which fuel mini-nozzles 13 are additionally provided in a clustered arrangement on the fuel supply ring 4. These fuel mini-nozzles 13 have a higher injection speed of the fuel and thereby lead to a locally richer fuel-air mixture. Adjacent to the fuel mini-nozzles 13 schematically fuel-primary nozzles 8 are shown.

In Fig. 9 ist ein Diagramm dargestellt, in welchem der Brennstoff-Massenstrom gegen die thermische Last des Triebwerks / der Gasturbine dargestellt ist. Die sich ergebende Gerade führt vom Nullpunkt durch einen Vollastpunkt. Um einen Betrieb der Magervormischbrenner oder Magervormischmodule in einer annularen Brennkammer flammensicher zu gewährleisten, werden die Brenner auf die nachfolgend dargestellten drei unterschiedlichen Betriebsstufen geschaltet.In Fig. 9 is a diagram is shown, in which the fuel mass flow is shown against the thermal load of the engine / the gas turbine. The resulting straight line leads from the zero point through a full load point. In order to ensure flameproof operation of the lean burn burner or lean premixing modules in an annular combustion chamber, the burners are switched to the three different operating stages shown below.

Die nachfolgende Beschreibung bezieht sich auf eine Reduzierung der Triebwerksleistung, analoges gilt jedoch auch für eine entsprechende Laststeigerung.The following description refers to a reduction in engine power, but analogous applies to a corresponding load increase.

An dem Betriebspunkt I ist ein Schaltpunkt vorgesehen. Dort erfolgt eine Umfangsstufung von ganzen Brennermodulen in bekannter symmetrischer oder asymmetrischer Weise. Die Brennermodule oder Magervormischbrenner werden dabei derart ausgeschaltet, dass die in Betrieb bleibenden Magervormischbrenner oder Module eine thermische Last von ungefähr 100 % am Schaltpunkt I erreichen. Die Schaltung erfolgt über Ventile, wobei Schalter oder regelbare Ventile eingesetzt werden können.At the operating point I, a switching point is provided. There is a circumferential gradation of whole burner modules in a known symmetrical or asymmetric manner. The burner modules or lean burn burners are switched off in such a way that the lean burn burners or modules remaining in operation reach a thermal load of approximately 100% at the switching point I. The circuit is via valves, with switches or controllable valves can be used.

Bei einem mittleren Schaltpunkt II, der bei ungefähr der Hälfte der thermischen Last des ersten Punktes I liegen kann, werden Gruppen von Einspritzdüsen der bisher in Betrieb verbliebenen Magervormischbrenner oder Magermodule abgeschaltet. Man erreicht hierdurch einen Weiterbetrieb der vorhandenen Brennstoff-Einspritzdüsen bei 100 % (am Schaltpunkt) des individuellen Brennstoff-Massendurchsatzes. Besonders vorteilhaft kann in diesem Niedriglastbereich eine asymmetrische Anordnung der in Betrieb verbleibenden Brennstoffdüsen vorgesehen werden (asymmetrische Gruppenschaltung).At a middle switching point II, which may be about half the thermal load of the first point I, groups of injectors of the previously left in operation lean burn burner or lean modules are turned off. This achieves a continued operation of the existing fuel injectors at 100% (at the switching point) of the individual fuel mass flow rate. Particularly advantageously, in this low-load range, an asymmetrical arrangement of the fuel nozzles remaining in operation can be provided (asymmetric group circuit).

Bei dem dritten Schaltpunkt III liegt bei weiterer Lastreduzierung ein Umschalten von den Normaldüsen (Brennstoff-Primärdüsen und Brennstoff-Sekundärdüsen) auf Cluster von Minidüsen oder Sekundär-Eindüsering vor. Diese Minidüsen haben, wie beschrieben, einen deutlich geringeren Durchmesser als die Normaldüsen. Die Minidüsen / Sekundärdüsen führen auch bei Niedriglast zu einem akzeptablen Brennstoff-Zersteubungsverhalten bei vergleichweise besserem Tropfenverdampfungsverhalten und erzeugen dennoch lokal ein relativ fettes Luft-Brennstoff-Gemisch. Die verbesserte Brennstoff-Zersteubung und das bessere Tropfenverdampfungsverhalten sind auch deshalb vorteilhaft und wichtig, weil im Niedriglastbereich der Gasturbine die Liefertemperatur des Kompressors gering ist. Erfindungsgemäß wird somit ein flammensicheres Gemisch erzeugt.At the third switching point III is a further load reduction switching from the normal nozzles (fuel primary nozzles and fuel secondary nozzles) on clusters of mini nozzles or secondary Eindüssering before. These mini nozzles have, as described, a significantly smaller diameter than the normal nozzles. The mini nozzles / secondary nozzles lead to an acceptable fuel Zersteubungsverhalten at low load with comparatively better droplet evaporation behavior and yet locally produce a relatively rich air-fuel mixture. The improved fuel atomization and better droplet evaporation behavior are also advantageous and important because in the low load range of the gas turbine, the delivery temperature of the compressor is low. According to the invention, a flameproof mixture is thus produced.

Es ist somit festzustellen, dass erfindungsgemäß eine Gruppierung oder Zusammenschaltung von einzelnen Modulen von Magervormischbrennern in einer annularen Brennkammer erfolgt, um die im Betrieb befindlichen Magervormischbrenner bei Niedriglast in Gruppen zusammenzulegen. Durch das Abschalten anderer Magervormischbrenner oder Module ergibt sich bei den verbleibenden Modulen oder Magervormischbrenner bei gleich bleibender Brennstoffmenge der Brennkammer ein reicheres oder fetteres Gemisch. Bei einer nochmaligen Erniedrigung der Last ist es dann, oder in Verbindung mit der eben beschriebenen Maßnahme, möglich, zusätzliche Sekundärdüsen oder Minidüsen in Betrieb zu setzen, um innerhalb eines Magervormischbrenners einzelne Bereiche auszuwählen, in denen (über den Umfang gesehen) in einzelnen Sektoren ein reicheres oder fetteres Brennstoff-Luft-Gemisch vorliegt. Hierdurch wird die Flammensicherheit etc., wie oben beschrieben, des einzelnen Moduls oder Magervormischbrenners sichergestellt.It is thus to be noted that, according to the invention, a grouping or interconnection of individual modules of lean premix burners takes place in an annular combustion chamber in order to combine the lean burn burners in operation into groups at low load. By switching off other lean burn burner or modules results in the remaining modules or lean burn burner with a constant fuel quantity of the combustion chamber a richer or richer mixture. With a further reduction of the load, it is then possible, or in conjunction with the measure just described, to set in operation additional secondary nozzles or mini-nozzles in order to select individual areas within a lean burn burner in which (seen in the circumferential direction) a single sector richer or richer fuel-air mixture is present. As a result, the flame safety, etc., as described above, of the single module or lean burn burner is ensured.

Die Erfindung ist nicht auf die gezeigten Ausführungsbeispiele beschränkt, vielmehr ergeben sich im Rahmen der Erfindung vielfältige Abwandlungs- und Modifikationsmöglichkeiten.The invention is not limited to the embodiments shown, but rather arise within the scope of the invention varied modification and modification options.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Flammrohrflame tube
22
äußeres Gehäuse des Magervormischbrennersouter casing of the lean premix burner
33
inneres Gehäuse des Magervormischbrennersinner casing of the lean premix burner
44
Brennstoff-Versorgungsring des MagervormischbrennersFuel supply ring of the lean premix burner
55
innerer Körper des Magervormischbrennersinner body of the lean premix burner
66
allgemeine Brennstoffdüsengeneral fuel nozzles
77
allgemeiner Brennstoff-Zuführungskanalgeneral fuel supply duct
88th
Brennstoff-PrimärdüseFuel primary nozzle
99
Brennstoff-SekundärdüseFuel secondary nozzle
1212
Brennstoff-DüsensektorFuel nozzle sector
1313
Brennstoff-MinidüseFuel Minidüse
1414
Magervormischmodul in BetriebMagervormischmodul in operation
1515
Magervormischmodul außer BetriebMagervormischmodul out of service

Claims (10)

  1. Lean-burn premix burner for a gas turbine with at least one fuel supply ring (4) provided with primary fuel nozzles (8), at which additional secondary fuel nozzles (9) are arranged, with the fuel supply to the secondary fuel nozzles (9) being independent of the fuel supply to the primary fuel nozzles (8), characterized in that the primary fuel nozzles (8) are evenly distributed on the circumference of the fuel supply ring (4), while the secondary fuel nozzles (9) are unevenly distributed on the circumference.
  2. Lean-burn premix burner in accordance with Claim 1, characterized in that the secondary fuel nozzles (9) are arranged only in some sectors of the fuel supply ring (4).
  3. Lean-burn premix burner in accordance with Claim 1, characterized in that fuel mini-nozzles (13) are provided on the fuel supply ring (4).
  4. Lean-burn premix burner in accordance with Claim 3, characterized in that fuel mini-nozzles (13) are arranged in groups.
  5. Lean-burn premix burner in accordance with one of the Claims 1 to 4, characterized in that the secondary fuel nozzles (9) and/or the fuel mini-nozzles (13) supply a richer air-fuel mixture.
  6. Method for the operation of a lean-burn premix burner for a gas turbine with at least one fuel supply ring (4) provided with primary fuel nozzles (8), at which additional secondary fuel nozzles (9) are arranged, characterized in that at low or reduced load conditions of the gas turbine a richer air-fuel mixture is set locally on the fuel supply ring (4) via the secondary fuel nozzles (9), while at other locations of the fuel supply ring (4) no fuel is injected via the primary fuel nozzles (8), with the total fuel quantity supplied to the lean-burn premix burner essentially remaining constant.
  7. Method in accordance with Claim 6, characterized in that at low or reduced load conditions of the gas turbine secondary fuel nozzles (9) are activated in the vicinity of at least two primary fuel nozzles (8), to locally enrich the fuel-air mixture.
  8. Method in accordance with Claim 6 or 7, characterized in that the primary fuel nozzles (8) not arranged in the vicinity of the secondary fuel nozzles (9) are shut-off.
  9. Method in accordance with one of the Claims 6 to 8, characterized in that with further decreasing load of the gas turbine, local supply of richer fuel-air mixture is accomplished via additional fuel mini-nozzles (13).
  10. Method in accordance with Claim 9, characterized in that the respective primary fuel nozzles (8), secondary fuel nozzles (9) and fuel mini-nozzles (13), which are in operation, are combined to form local groups on the circumference of the fuel supply ring (4).
EP02023428A 2001-12-12 2002-10-19 Lean-burn premix burner for gas turbine and its method of operation Expired - Lifetime EP1319895B1 (en)

Applications Claiming Priority (2)

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DE10160997 2001-12-12
DE10160997A DE10160997A1 (en) 2001-12-12 2001-12-12 Lean premix burner for a gas turbine and method for operating a lean premix burner

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EP1319895A3 EP1319895A3 (en) 2004-01-07
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DE10160997A1 (en) 2003-07-03
DE50211162D1 (en) 2007-12-20
US20030106321A1 (en) 2003-06-12
US6945053B2 (en) 2005-09-20
EP1319895A2 (en) 2003-06-18

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