EP1466124B1 - Burner arrangement for the annular combustion chamber of a gas turbine - Google Patents

Burner arrangement for the annular combustion chamber of a gas turbine Download PDF

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Publication number
EP1466124B1
EP1466124B1 EP02782608A EP02782608A EP1466124B1 EP 1466124 B1 EP1466124 B1 EP 1466124B1 EP 02782608 A EP02782608 A EP 02782608A EP 02782608 A EP02782608 A EP 02782608A EP 1466124 B1 EP1466124 B1 EP 1466124B1
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EP
European Patent Office
Prior art keywords
burners
combustion chamber
burner
burner arrangement
combustion
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EP02782608A
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German (de)
French (fr)
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EP1466124A1 (en
Inventor
Peter Graf
Stefan Tschirren
Helmar Wunderle
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General Electric Technology GmbH
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Alstom Technology AG
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    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances

Definitions

  • the present invention relates to the field of gas turbines. It relates to a burner arrangement for the annular combustion chamber of a gas turbine according to the preamble of claim 1.
  • Such a burner arrangement is for example from the document EP-A1-0 597 138 known.
  • annular low-NOx (EV) combustors (EV) for gas turbines with a single row of burners are part of the proven technology (see eg F. Joos et al. "Development of the sequential combustion system for the GT24 / GT26 gas turbine family", ABB review 4, 1998, p. 4-16 (1998 )).
  • the burners are extractable in these gas turbines / combustion chambers through corresponding access openings in the outer turbine housing.
  • the turbine housing must meet certain mechanical requirements and should not deform or crack under pressure and thermal stress. Therefore, a minimum distance between such access openings in the outer turbine housing must be taken into account. This is of great importance especially with double-row burner arrangements.
  • the burners create "hot spots" on the inner linings of the combustion chamber where the hot gas flowing out of the burners hits the walls.
  • US-A-5,829,967 discloses a combustion chamber with two-stage combustion. It has a primary burner of the premixing type, in which fuel injected within a premixing space of the top nozzles is intensively mixed with the combustion air prior to ignition.
  • the primary burners are flame-stabilized, ie without a mechanical flame holder. They are provided with tangential inflow of the combustion air into the premixing chamber. Downstream of a pre-combustion chamber, secondary burners are arranged, which are designed as non-self-contained premix burners.
  • the US-A-3,724,207 discloses a combustion chamber.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention is to align the burner in the two burner rows with their burner axes no longer parallel to each other, but to let run towards each other in the flow direction. This results opposite to the flow direction to the outer turbine housing towards an increasing (lateral) distance between the burner axes, which leads to corresponding access openings for the burner in the outer turbine housing to a greater distance and thus to a significantly reduced mechanical weakening of the housing.
  • the burner axes in the combustion chamber converge, the gases expelled from the burners into the combustion chamber interact more, resulting in improved mixing.
  • the inclination of the burner to each other to a reduced impact of the hot burner gases on the outer combustion chamber walls, so that their thermal load decreases.
  • Center axis of the combustion chamber cross section are arranged, and that the burner axes of the two burners with the central axis each include an angle ( ⁇ ), which is greater than 0 ° and smaller than 90 °.
  • FIGURE shows a section through a gas turbine with an annular combustion chamber and a two-row burner arrangement according to a preferred embodiment of the invention.
  • a section through the combustion chamber of a gas turbine 10 is shown with a burner assembly according to a preferred embodiment of the invention.
  • the gas turbine 10 of which only one section lying above the turbine axis is shown, has an outer turbine housing 13, which encloses a plenum 12 filled with compressed air and a combustion chamber 11 arranged between the compressor part and the turbine part.
  • the combustion chamber 11 is annular with respect to the turbine axis
  • burners 14, 15 are arranged in two rows one above the other, which are formed in a known manner as a double-cone burner, open into the combustion chamber 11 and a primary combustion zone in fire. Between the burner rows extends an intermediate region 26.
  • the burners 14, 15 form coaxial rings, as is similar (but with varying offset) in Fig. 3 of the EP-A1-0 597138 is shown.
  • the head space 27 is closed to the outside (to the plenum 12) by a combustion chamber housing 18.
  • a combustion chamber housing 18 In the combustion chamber housing 18 corresponding openings are provided for the burner 14, 15, through which the burner 14, 15 after outside are pulled out.
  • On the burners 14,15 themselves flanges 19, 20 are arranged, with which the burner 14,15 are bolted to the combustion housing 18, and which at the same time close the openings.
  • In the outer outer turbine housing 13 are also openings 21, 22 are provided, through which the burner 14,15 can be pulled directly and completely outwards.
  • the burners 14, 15, which are arranged one above the other in pairs, are no longer oriented parallel to one another, but are mounted inclined relative to one another in such a way that the burner axis 17 converges towards one another in the flow direction (in the figure to the left).
  • this inclination is formed symmetrically to the central axis 25 of the combustion chamber cross section
  • Each burner 14, 5 is inclined with its burner axis 17 by the same angle ⁇ from the central axis 25 out.
  • the angle ⁇ is about 5 °. Generally it is greater than 0 ° and less than 90 °.

Abstract

The invention relates to a burner arrangement for the annular combustion chamber (11) of a gas turbine (10), according to which a plurality of burners (14, 15) in concentric circles are respectively arranged one above the other, in pairs, in the radial direction. One such burner arrangement increases the mechanical integrity of the turbine housing and optimises the operation of the combustion chamber, the two burners (14, 15) of a pair being oriented such that they deviate from the parallel position in such a way that their axes (17) extend towards each other in the direction of flow.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Die vorliegende Erfindung bezieht sich auf das Gebiet der Technik der Gasturbinen. Sie betrifft eine Brenneranordnung für die ringförmige Brennkammer einer Gasturbine gemäss dem Oberbegriff des Anspruchs 1.The present invention relates to the field of gas turbines. It relates to a burner arrangement for the annular combustion chamber of a gas turbine according to the preamble of claim 1.

Eine solche Brenneranordnung ist z.B. aus der Druckschrift EP-A1-0 597 138 bekannt.Such a burner arrangement is for example from the document EP-A1-0 597 138 known.

STAND DER TECHNIKSTATE OF THE ART

In der heutigen Zeit gehören ringförmige Low-NOx-(EV-)Brennkammem (EV = Environmental) für Gasturbinen mit einer einzigen Reihe von Brennern zur bewährten Technologie (siehe z.B. F. Joos et al. "Development of the sequential combustion system for the GT24/GT26 gas turbine family", ABB review 4, 1998, S. 4-16 (1998 )). Die Brenner sind bei diesen Gasturbinen/Brennkammern durch entsprechende Zugangsöffnungen in dem äusseren Turbinengehäuse herausziehbar.At the present time, annular low-NOx (EV) combustors (EV) for gas turbines with a single row of burners are part of the proven technology (see eg F. Joos et al. "Development of the sequential combustion system for the GT24 / GT26 gas turbine family", ABB review 4, 1998, p. 4-16 (1998 )). The burners are extractable in these gas turbines / combustion chambers through corresponding access openings in the outer turbine housing.

Andere Gasturbinen haben in der ringförmigen Brennkammer eine doppelreihige Anordnung von Brennern, wie dies beispielsweise in den Fig. 1 und 3 der eingangs genannten Druckschrift EP-A1-0 597 138 gezeigt ist. In der dort dargestellten Form (mit parallel orientierten Brennerpaaren) kann eine solche zweireihige Anordnung nur realisiert werden, weil die Brenner nicht nach aussen, sondern in die Brennkammer hinein herausziehbar sind. Die Brennkammer muss dazu gross genug sein und durch eine spezielles Mannloch von aussen zugänglich sein (siehe die Fig. 2 der EP-A1-0 597138 und die zugehörige Beschreibung). Die Öffnungen für die Brennstoffzuleitungen im Turbinengehäuse können in diesem Fall klein ausgebildet werden.Other gas turbines have in the annular combustion chamber a double-row arrangement of burners, as for example in Figs. 1 and 3 of the aforementioned document EP-A1-0 597 138 is shown. In the form shown there (with burner pairs oriented in parallel) such a double-row arrangement can only be realized because the burners can not be pulled outwards, but rather into the combustion chamber. The combustion chamber must be large enough and accessible through a special manhole from the outside (see Fig. 2 of EP-A1-0 597138 and the associated description). The openings for the fuel supply lines in the turbine housing can be made small in this case.

Nachteilig ist bei der bekannten zweireihigen Brenneranordnung der für einen Brennerwechsel notwendige, konstruktiv aufwendige Zugang zur Brennkammer über entsprechende Mannlöcher. Nachteilig ist auch der bei dieser Lösung zeitaufwendige Vorgang des Brennerwechsels. Das Vorsehen von Zugangsöffnungen im Turbinengehäuse, durch weiche die Brenner einfach nach draussen herausgezogen werden können, wirft jedoch hinsichtlich der mechanischen Integrität des Turbinengehäuses Probleme auf. Das Turbinengehäuse muss bestimmten mechanischen Anforderungen genügen und sollte sich unter Druck und thermischer Belastung nicht deformieren oder reissen. Daher muss ein minimaler Abstand zwischen derartigen Zugangsöffnungen im äusseren Turbinengehäuse beachtet werden. Dies ist gerade bei doppelreihigen Brenneranordnungen von grosser Bedeutung.A disadvantage of the known double-row burner assembly necessary for a burner change, structurally complex access to the combustion chamber via corresponding manholes. Another disadvantage is the time-consuming process of burner replacement in this solution. The provision of access openings in the turbine housing, through which the burners can be easily pulled out, however, poses problems in terms of the mechanical integrity of the turbine housing. The turbine housing must meet certain mechanical requirements and should not deform or crack under pressure and thermal stress. Therefore, a minimum distance between such access openings in the outer turbine housing must be taken into account. This is of great importance especially with double-row burner arrangements.

Es ist weiterhin bei jeder Brennkammer wünschenswert, dass sich die Heissgasse in der Primärzone gut vermischen. Gerade bei doppel- oder höherreihigen Brenneranordnungen müssen daher Wege gefunden werden, um eine Vermischung zu erhalten, die selbst bei Teillastbetrieb, bei dem die Brenner abgestuft betrieben werden, ausreichend ist.It is also desirable in any combustor that the hot track in the primary zone mix well. Especially with double or higher-row burner arrangements, therefore, ways must be found to obtain a mixture that is sufficient even at partial load operation, in which the burners are operated graded.

Schliesslich ist zu beachten, dass die Brenner "hot spots" an den inneren Auskleidungen der Brennkammer erzeugen, wo das aus den Brennern ausströmende Heissgas auf die Wände trifft.Finally, it should be noted that the burners create "hot spots" on the inner linings of the combustion chamber where the hot gas flowing out of the burners hits the walls.

US-A-5,829,967 offenbart eine Brennkammer mit zweistufiger Verbrennung. Sie weist einen Primärbrenner der Vormischbauart auf, bei denen innerhalb eines Vormischraumes der Ober Düsen eingespritzte Brennstoff vorgängig der Zündung mit der Brennluft intensiv vermischt wird. Die Primärbrenner sind flammenstabilisierend ausgebildet, d.h. ohne mechanischen Flammenhalter. Sie sind mit tangentialer Einströmung der Brennluft in den Vormischraum versehen. Stromabwärts einer Vorbrennkammer sind Sekundärbrenner angeordnet, die als nicht selbstgängige Vormischbrenner ausgebildet sind. Auch die US-A-3,724,207 offenbart eine Brennkammer. US-A-5,829,967 discloses a combustion chamber with two-stage combustion. It has a primary burner of the premixing type, in which fuel injected within a premixing space of the top nozzles is intensively mixed with the combustion air prior to ignition. The primary burners are flame-stabilized, ie without a mechanical flame holder. They are provided with tangential inflow of the combustion air into the premixing chamber. Downstream of a pre-combustion chamber, secondary burners are arranged, which are designed as non-self-contained premix burners. Also the US-A-3,724,207 discloses a combustion chamber.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist daher Aufgabe der Erfindung, eine doppelreihige Brenneranordnung für ringförmige Brennkammern zu schaffen, welche ohne Beeinträchtigung der mechanischen Integrität des Turbinengehäuses ein direktes Herausziehen der Brenner durch das Turbinengehäuse nach aussen ermöglicht, die Mischung der Heissgase in der Brennkammer verbessert und die thermische Belastung an den Wänden der Brennkammer reduziert.It is therefore an object of the invention to provide a double-row burner assembly for annular combustion chambers, which allows without affecting the mechanical integrity of the turbine housing direct extraction of the burner through the turbine housing to the outside, improves the mixture of hot gases in the combustion chamber and the thermal load on the Walls of the combustion chamber reduced.

Die Aufgabe wird durch die Gesamtheit der Merkmale des Anspruchs 1 gelöst. Der Kern der Erfindung besteht darin, die Brenner in den beiden Brennerreihen mit ihren Brennerachsen nicht länger parallel zueinander auszurichten, sondern in Strömungsrichtung aufeinander zulaufen zu lassen. Hierdurch ergibt sich entgegen der Strömungsrichtung zum äusseren Turbinengehäuse hin ein zunehmender (lateraler) Abstand zwischen den Brennerachsen, der bei entsprechenden Zugangsöffnungen für die Brenner im äusseren Turbinengehäuse zu einem grösseren Abstand und damit zu einer deutlich verringerten mechanischen Schwächung des Gehäuses führt. Da die Brennerachsen in der Brennkammer aufeinander zu laufen, treten auch die von den Brennern in den Brennraum ausgestossenen Gase stärker in Wechselwirkung, was zu einer verbesserten Mischung führt. Gleichzeitig ergibt sich durch die Neigung der Brenner aufeinander zu eine reduzierter Aufprall der heissen Brennergase auf die aussenliegenden Brennkammerwände, so dass deren thermische Belastung sinkt.The object is solved by the entirety of the features of claim 1. The essence of the invention is to align the burner in the two burner rows with their burner axes no longer parallel to each other, but to let run towards each other in the flow direction. This results opposite to the flow direction to the outer turbine housing towards an increasing (lateral) distance between the burner axes, which leads to corresponding access openings for the burner in the outer turbine housing to a greater distance and thus to a significantly reduced mechanical weakening of the housing. As the burner axes in the combustion chamber converge, the gases expelled from the burners into the combustion chamber interact more, resulting in improved mixing. At the same time results from the inclination of the burner to each other to a reduced impact of the hot burner gases on the outer combustion chamber walls, so that their thermal load decreases.

Bevorzugt ist dabei eine "symmetrische" Brenneranordnung, die dadurch gekennzeichnet ist, dass die beiden Brenner eines Brennerpaares auf beiden Seiten derPreference is given to a "symmetrical" burner arrangement, which is characterized in that the two burners of a burner pair on both sides of

Mittelachse des Brennkammerquerschnitts angeordnet sind, und dass die Brennerachsen der beiden Brenner mit der Mittelachse jeweils einen Winkel (α) einschliessen, der grösser als 0° und kleiner als 90° ist.Center axis of the combustion chamber cross section are arranged, and that the burner axes of the two burners with the central axis each include an angle (α), which is greater than 0 ° and smaller than 90 °.

Weitere Ausführungsformen ergeben sich aus den abhängigen Ansprüchen.Further embodiments emerge from the dependent claims.

KURZE ERLÄUTERUNG DER FIGURBRIEF EXPLANATION OF THE FIGURE

Die Erfindung wird nachfolgend anhand von Ausführungsbeispielen im Zusammenhang mit der Zeichnung näher erläutert. Die einzige Figur zeigt in einem Ausschnitt den Schnitt durch eine Gasturbine mit einer ringförmigen Brennkammer und einer zweireihigen Brenneranordnung gemäss einem bevorzugten Ausführungsbeispiel der Erfindung.The invention will be explained in more detail with reference to embodiments in conjunction with the drawings. The single FIGURE shows a section through a gas turbine with an annular combustion chamber and a two-row burner arrangement according to a preferred embodiment of the invention.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS FOR CARRYING OUT THE INVENTION

In der Figur ist ein Schnitt durch die Brennkammer einer Gasturbine 10 mit einer Brenneranordnung gemäss einem bevorzugten Ausführungsbeispiel der Erfindung dargestellt. Die Gasturbine 10, von der nur ein oberhalb der Turbinenachse liegender Ausschnitt gezeigt ist, hat ein äusseres Turbinengehäuse 13, welches ein mit komprimierter Luft gefülltes Plenum 12 und eine zwischen Verdichterteil und Turbinenteil angeordnete Brennkammer 11 umschliesst. Die Brennkammer 11 ist im bezug auf die Turbinenachse ringförmig ausgebildet In ihrem eintrittsseitigen Kopfraum 27 sind in zwei Reihen übereinander Brenner 14, 15 angeordnet, die in bekannter Weise als Doppelkegelbrenner ausgebildet sind, in die Brennkammer 11 münden und eine Primärbrennzone in befeuern. Zwischem den Brennerreihen erstreckt sich ein Zwischen bereich 26. Die Brenner 14, 15 bilden koaxiale Ringe, wie dies ähnlich (allerdings mit wechselndem Versatz) in Fig. 3 der EP-A1-0 597138 dargestellt ist. Der Kopfraum 27 ist nach aussen (zum Plenum 12) durch ein Brennkammergehäuse 18 abgeschlossen. In dem Brennkammergehäuse 18 sind für die Brenner 14, 15 entsprechende Öffnungen vorgesehen, durch welche die Brenner 14, 15 nach aussen herausziehbar sind. An den Brennern 14,15 selbst sind Flansche 19, 20 angeordnet, mit welchen die Brenner 14,15 am Brenngehäuse 18 festgeschraubt sind, und welche gleichzeitig die Öffnungen verschliessen. Im weiter aussen liegenden äusseren Turbinengehäuse 13 sind ebenfalls Öffnungen 21, 22 vorgesehen, durch welche die Brenner 14,15 direkt und ganz nach aussen gezogen werden können.In the figure, a section through the combustion chamber of a gas turbine 10 is shown with a burner assembly according to a preferred embodiment of the invention. The gas turbine 10, of which only one section lying above the turbine axis is shown, has an outer turbine housing 13, which encloses a plenum 12 filled with compressed air and a combustion chamber 11 arranged between the compressor part and the turbine part. The combustion chamber 11 is annular with respect to the turbine axis In its inlet-side head space 27 burners 14, 15 are arranged in two rows one above the other, which are formed in a known manner as a double-cone burner, open into the combustion chamber 11 and a primary combustion zone in fire. Between the burner rows extends an intermediate region 26. The burners 14, 15 form coaxial rings, as is similar (but with varying offset) in Fig. 3 of the EP-A1-0 597138 is shown. The head space 27 is closed to the outside (to the plenum 12) by a combustion chamber housing 18. In the combustion chamber housing 18 corresponding openings are provided for the burner 14, 15, through which the burner 14, 15 after outside are pulled out. On the burners 14,15 themselves flanges 19, 20 are arranged, with which the burner 14,15 are bolted to the combustion housing 18, and which at the same time close the openings. In the outer outer turbine housing 13 are also openings 21, 22 are provided, through which the burner 14,15 can be pulled directly and completely outwards.

Wesentlich ist nun, dass die paarweise übereinander angeordneten Brenner 14, 15 mit ihren Brennerachsen 17 nicht länger parallel zueinander orientiert sind, sondern derart gegeneinander geneigt eingebaut sind, dass die Brennerachse 17 in Strömungsrichtung (in der Figur nach links) aufeinander zu laufen. Bevorzugt ist diese Neigung symmetrisch zur Mittelachse 25 des Brennkammerquerschnitts ausgebildet Jeder Brenner 14, 5 ist mit seiner Brennerachse 17 um denselben Winkel α aus der Mittelachse 25 heraus geneigt. In dem in der Figur dargestellten Ausführungsbeispiel beträgt der Winkel α etwa 5°. Allgemein ist er grösser als 0° und kleiner als 90°.It is essential that the burners 14, 15, which are arranged one above the other in pairs, are no longer oriented parallel to one another, but are mounted inclined relative to one another in such a way that the burner axis 17 converges towards one another in the flow direction (in the figure to the left). Preferably, this inclination is formed symmetrically to the central axis 25 of the combustion chamber cross section Each burner 14, 5 is inclined with its burner axis 17 by the same angle α from the central axis 25 out. In the embodiment shown in the figure, the angle α is about 5 °. Generally it is greater than 0 ° and less than 90 °.

Durch die Neigung der Brenner 14,15 gegeneinander verbreitern sich die Zwischenbereiche 23, 24 zwischen den Öffnungen im Brennkammergehäuse 18 und den Öffnungen 21, 22 im äusseren Turbinengehäuse 13, wodurch Platz für Befestigungsmittel bereitgestellt und die mechanische Stabilität der Gehäuse wesentlich erhöht wird. Durch die Neigung erhöht sich auch die Wechselwirkung zwischen den Flammen 28 der benachbarten Brenner 14,15, was zu einer besseren Vermischung der heissen Gase führt. Schliesslich treffen die Flammen 28 inder Primärbrenn-zone 16 wegen der Neigung der Brenner 14,15 weniger stark auf die inneren und äusseren Auskleidungssegmente 29 und 30 der Brennkammer 11, wodurch die thermische Belastung dieser Segmente deutlich reduziert wird.Due to the inclination of the burner 14,15 against each other widen the intermediate regions 23, 24 between the openings in the combustion chamber housing 18 and the openings 21, 22 in the outer turbine housing 13, whereby space for fastening means provided and the mechanical stability of the housing is substantially increased. The inclination also increases the interaction between the flames 28 of the adjacent burners 14,15, which leads to a better mixing of the hot gases. Finally, due to the inclination of the burners 14, 15, the flames 28 in the primary combustion zone 16 impinge less strongly on the inner and outer lining segments 29 and 30 of the combustion chamber 11, which significantly reduces the thermal load on these segments.

Insgesamt ergeben sich mit der Erfindung die folgenden Effekte und Vorteile:

  • Zwischen den Brennerreihen ist ausreichend Platz vorhanden, um die zugehörigen Flansche mit den Gehäusen bzw. Trägern zu verschrauben.
  • Die geneigte Anordnung der Brenner <14,15> führt zu einem grösseren Abstand der Zugangsöffnungen im äusseren Turbinengehäuse. Hierdurch wird die Konzentration mechanischer Spannungen im Bereich der Öffnungsverteilung abgebaut.
  • Im Vormischbetrieb wird die Mischung zwischen der unteren (inneren) und oberen (äusseren) Brennerreihe intensiviert.
  • Der Abstand zwischen den Flammen und den inneren und äusseren Auskleidungssegmenten wird vergrössert. Dadurch wird die lokale thermische Belastung der Segmente verringert.
Overall, the invention provides the following effects and advantages:
  • There is sufficient space between the rows of burners to bolt the associated flanges to the housings or brackets.
  • The inclined arrangement of the burners <14,15> leads to a greater distance of the access openings in the outer turbine housing. This reduces the concentration of mechanical stresses in the area of the opening distribution.
  • In premix operation, the mixture between the lower (inner) and upper (outer) row of burners is intensified.
  • The distance between the flames and the inner and outer liner segments is increased. This reduces the local thermal load on the segments.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

1010
Gasturbinegas turbine
1111
Brennkammercombustion chamber
1212
Plenumplenum
1313
(äusseres) Turbinengehäuse(outer) turbine housing
14,1514.15
Brenner (Doppelkegelbrenner)Burner (double cone burner)
1616
Primäbrennzone der Brennkammer 11Primary combustion zone of the combustion chamber 11
1717
BrennerachseBrenner
1818
Brennkammergehäusecombustion chamber housing
19,2019.20
Flanschflange
21,2221.22
Öffnungopening
23,24,2623,24,26
Zwischenbereichintermediate area
2525
Mittelachse (Brennkammerquerschnitt)Center axis (combustion chamber cross-section)
2727
Kopfraumheadspace
2828
Flammeflame
2929
Auskleidungssegment (innen)Lining segment (inside)
3030
Auskleidungssegment (aussen)Lining segment (outside)
αα
Winkelangle

Claims (4)

  1. Burner arrangement for the annular combustion chamber (11) of a gas turbine (10), in which burner arrangement a plurality of burners (14, 15) are arranged above one another in a combustion chamber wall, in each case in pairs in the radial direction on concentric rings, it being possible for a primary combustion zone (16) of the combustion chamber (11) to be fired by the burners (14, 15), characterized in that the two burners (14, 15) in a pair of burners are oriented out of the parallel position, in such a manner that their burner axes (17) converge in the direction of flow.
  2. Burner arrangement according to Claim 1, characterized in that the two burners (14, 15) belonging to a pair of burners are arranged on both sides of the center axis (25) of the combustion chamber cross section, and in that the burner axes (17) of the two burners (14, 15) each include an angle (α) of greater than 0° and less than 90° with the center axis (25).
  3. Burner arrangement according to either of Claims 1 and 2, characterized in that the burners (14, 15) are arranged in a head space (27) of the combustion chamber (11), which is surrounded by a combustion-chamber casing (18), and in that there are openings in the combustion-chamber casing (18), through which the burners (14, 15) can be removed outward and which are closed by flanges (19, 20) arranged on the burners (14, 15) when the burners are fitted.
  4. Burner arrangement according to either of Claims 1 and 2, characterized in that the combustion chamber (11) is arranged inside an outer turbine casing (13), and in that in the outer turbine casing (13) there are openings (21, 22) through which the burners (14, 15) can be removed from the turbine casing (13).
EP02782608A 2002-01-14 2002-12-16 Burner arrangement for the annular combustion chamber of a gas turbine Expired - Fee Related EP1466124B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH502002 2002-01-14
CH502002 2002-01-14
PCT/CH2002/000697 WO2003058123A1 (en) 2002-01-14 2002-12-16 Burner arrangement for the annular combustion chamber of a gas turbine

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EP1466124A1 EP1466124A1 (en) 2004-10-13
EP1466124B1 true EP1466124B1 (en) 2008-09-03

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EP02782608A Expired - Fee Related EP1466124B1 (en) 2002-01-14 2002-12-16 Burner arrangement for the annular combustion chamber of a gas turbine

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US (1) US7055331B2 (en)
EP (1) EP1466124B1 (en)
CN (1) CN100529547C (en)
AU (1) AU2002347186A1 (en)
DE (1) DE50212743D1 (en)
WO (1) WO2003058123A1 (en)

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JP4882422B2 (en) * 2006-02-28 2012-02-22 株式会社日立製作所 Gas turbine combustor and combustion method of combustion apparatus
DE102008053755A1 (en) 2008-10-28 2010-04-29 Pfeifer, Uwe, Dr. Arrangement for extension of stability range of pilot flame system and/or pilot burner system in e.g. aircraft, has burner systems with burners distributed radially at periphery of chamber or over cross-section area of chamber
US9243802B2 (en) 2011-12-07 2016-01-26 Pratt & Whitney Canada Corp. Two-stage combustor for gas turbine engine
US9194586B2 (en) 2011-12-07 2015-11-24 Pratt & Whitney Canada Corp. Two-stage combustor for gas turbine engine
US9416972B2 (en) 2011-12-07 2016-08-16 Pratt & Whitney Canada Corp. Two-stage combustor for gas turbine engine
EP2796789B1 (en) * 2013-04-26 2017-03-01 General Electric Technology GmbH Can combustor for a can-annular combustor arrangement in a gas turbine
CN105934632B (en) * 2014-01-31 2018-09-21 阿塞里克股份有限公司 Igniter for gas burner assemblies and the cooking apparatus with igniter

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Also Published As

Publication number Publication date
WO2003058123A1 (en) 2003-07-17
AU2002347186A1 (en) 2003-07-24
CN100529547C (en) 2009-08-19
DE50212743D1 (en) 2008-10-16
EP1466124A1 (en) 2004-10-13
CN1615417A (en) 2005-05-11
US20050039464A1 (en) 2005-02-24
US7055331B2 (en) 2006-06-06

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