EP2416070A1 - Gas turbine combustion chamber - Google Patents
Gas turbine combustion chamber Download PDFInfo
- Publication number
- EP2416070A1 EP2416070A1 EP10171601A EP10171601A EP2416070A1 EP 2416070 A1 EP2416070 A1 EP 2416070A1 EP 10171601 A EP10171601 A EP 10171601A EP 10171601 A EP10171601 A EP 10171601A EP 2416070 A1 EP2416070 A1 EP 2416070A1
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- EP
- European Patent Office
- Prior art keywords
- pilot
- gas turbine
- opening
- pilot cone
- fuel nozzle
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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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
- F23R3/28—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
Definitions
- the present invention relates to a gas turbine combustor according to the preamble of claim 1.
- a gas turbine combustor wherein premix combustion takes place is provided with a pilot burner for combustion in addition to the main burners for premix combustion.
- the pilot burner serves to stabilize the combustion.
- the pilot-generated diffusion flame or premix flame is used as a pilot flame for the main burner to produce a more fuel-rich flame, thereby stabilizing combustion.
- a pilot burner may optionally have a cone at the outlet, thereby facilitating the stabilization of the pilot flame.
- the main burners are arranged at regular intervals around the pilot burner. High outputs of such a gas turbine combustor require high turbine inlet temperatures, which result from a high flame temperature. With regard to the formation of CO and NOx values, it is necessary to keep the flame temperature and the residence time of the gas in the combustion chamber in an allowable range.
- the high temperatures in the gas turbine require a high flame temperature, which also affect the NOx values and increase them.
- the average flame temperature in the combustion chamber should be minimized to an allowable value adjusted for efficiency with respect to the resulting NOx levels.
- it would be necessary to increase the residence time of the gas in the combustion chamber e.g. reduced by a shortened combustion chamber.
- the object of the present invention is therefore to specify a gas turbine combustion chamber which can be operated with an increased flame temperature and thus improved efficiency and without the disadvantages described above.
- Fig. 1 and Fig. 2 show a gas turbine combustor according to the prior art.
- the gas turbine combustor in this case has a pilot fuel nozzle, which is arranged in the middle section of a cylinder 2.
- the cylinder 2 opens at its end to a combustion chamber (not shown).
- the pilot fuel nozzle comprises a fuel nozzle 1, as well as a cylindrical outer lining 9 radially spaced around the outer circumference of the fuel nozzle 1.
- a pilot swirler 5 is arranged between the fuel nozzle 1 and the outer lining 9, a pilot swirler 5 is arranged.
- a pilot cone 4 with inside 11 and outside 12 is arranged on the combustion chamber side of the pilot fuel nozzle.
- the pilot cone 4 has an opening 6 within the front region of the cylinder 2.
- Each main burner has a main nozzle 7 and an outer cylinder 20 arranged with a gap around the outer circumference of the main nozzle 7 in question.
- main swirling elements 21 are arranged in the intermediate space. Such a main burner, by mixing fuel with air, produces a main mixture which is expelled from the main burner towards the combustion chamber (not shown).
- pilot cone 4 a mixed pilot flame (pilot mixture) is formed by mixing air and pilot fuel so that the fuel present in the mixture from the main burners is ignited and thus burns the mixture (main mixture) coming from the main burner.
- FIG. 3 and FIG. 4 Now show a first embodiment of the invention.
- turbulence generators in the form of projections are mounted on the inside 11 of the pilot cone ( Fig. 3 and Fig.4 ). These are mounted above all in the region of the opening 6 of the pilot cone 4.
- the bosses 30 may also be attached to the outside 12 of the pilot cone 4 (not shown).
- the humps 30 are preferably mounted at uniform intervals over the entire circumference of the opening 6 of the pilot cone 4 ( Fig. 4 ). Instead of the humps 30, dimples or dimples may also be attached (not shown).
- the turbulence generators cause better mixing and thus improved CO values. Thereby, even with a short residence time and a short mixing path of the combustion gas in the combustion chamber (not shown) with high flame temperatures, good NO x values are obtained. Other measures for reducing the NOx values can thus be dispensed with. Thus, no impairment of the operation, for example in base load longer exists.
- Fig. 5 now shows a second embodiment of the invention.
- a single strip ring 33 is provided as a turbulence generator, which is arranged over the entire circumference of the outer side 12 in the region of the opening 6 of the pilot cone 4.
- Altnernativ may also be provided strips which are arranged spaced apart from each other over the circumference of the outer side 12 in the region of the opening 6 of the pilot cone 4.
- the strip ring 33 is arranged at an angle of 30 ° to 60 ° to the outer side 12 of the pilot cone 4.
- the strips (not shown) in such Be arranged angle This results in a particularly good mixing of pilot mixture and main mixture and thus a particularly good combustion.
- Fig. 6 and Fig. 7 Now show a third embodiment of the invention.
- the turbulence generators are designed as trapezoidal strips 35, which are arranged on the opening 6 over the entire circumference of the opening 6, wherein the trapezoidal strips 35 are arranged alternately at an angle of - / + 30 ° to the pilot cone 4. Even so, the mixing of the pilot mixture and the main mixture can be significantly increased.
- Turbulence generators may, for example, also be sharp, straight edge vanes, corners or prisms placed at a predetermined angle over the entire circumference of the opening 6 on the pilot cone 4 (not shown).
- the sharp edge points towards the combustion chamber (not shown).
- such wings with different angles alternately (not shown), in particular at an angle of +/- 30 ° to the pilot cone 4, be arranged.
- Fig. 8 shows a further embodiment of a gas turbine combustor according to the invention.
- the gas turbine combustor has an axial direction A.
- Each of the main burners also has main nozzles 7 and an outer cylinder 20 arranged with a clearance around the outer periphery of the main nozzle 7 in question.
- extension tubes 230 are formed to elongate the openings of the outer cylinders 20 such that the extension tubes 230 radially constrict and expand circumferentially such that each extension tube 230 merges with the adjacent extension tube 230.
- the annular main nozzle opening 240 extends in the axial direction A to the opening 6 of the pilot cone 4.
- turbulence generators for example bosses 30, are arranged on the inside 111 of the annular main nozzle opening 240.
- turbulence generators for example bosses 30, are arranged on the inside 11 and / or the outer side 12 of the pilot cone mounted 4 turbulence generators. This results in better mixing and thus improved CO values than in such a configuration of the gas turbine without turbulence generators.
- Fig. 9 shows a fifth example of a gas turbine combustor according to the invention.
- This has an axial direction A.
- Each of the main burners has main nozzles 7 and an outer cylinder 20 (with a clearance around the outer circumference of the main nozzle 7 around).
- Fig. 8 on.
- 250 turbulence generators, such as hump 30 are arranged on an inner side 260 of the extension tubes 250 in the region of the outlet opening of the extension tubes.
- 4 turbulence generators are mounted on the inside 11 and / or the outer side 12 of the pilot cone. This results in better mixing and thus improved CO values than in such a configuration of the gas turbine without turbulence generators.
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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)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
Description
Die vorliegende Erfindung betrifft eine Gasturbinenbrennkammer nach dem Oberbegriff des Anspruchs 1.The present invention relates to a gas turbine combustor according to the preamble of claim 1.
Eine Gasturbinenbrennkammer bei der eine Vormischverbrennung stattfindet, ist mit einem Pilotbrenner für eine Verbrennung zusätzlich zu den Hauptbrennern für eine Vormischverbrennung versehen. Der Pilotbrenner dient dazu, die Verbrennung zu stabilisieren. Die vom Piloten erzeugte Diffusionsflamme oder Vormischflamme wird als Pilotflamme für den Hauptbrenner verwendet, um eine brennstoffreichere Flamme zu erzeugen, wodurch die Verbrennung stabilisiert wird. Ein Pilotbrenner kann gegebenenfalls am Austritt einen Konus aufweisen, wodurch die Stabilisierung der Pilotflamme erleichtert wird. Bei solch einer Gasturbinebrennkammer sind die Hauptbrenner in regelmäßigen Abständen um den Pilotbrenner angeordnet. Hohe Leistungen einer solchen Gasturbinenbrennkammer erfordern hohe Turbineneinlasstemperaturen, welche durch eine hohe Flammentemperatur entstehen. Im Hinblick auf die Entstehung von CO- und NOx-Werten ist es notwendig, die Flammentemperatur und die Verweildauer des Gases in der Brennkammer in einem zulässigen Bereich zu halten.A gas turbine combustor wherein premix combustion takes place is provided with a pilot burner for combustion in addition to the main burners for premix combustion. The pilot burner serves to stabilize the combustion. The pilot-generated diffusion flame or premix flame is used as a pilot flame for the main burner to produce a more fuel-rich flame, thereby stabilizing combustion. A pilot burner may optionally have a cone at the outlet, thereby facilitating the stabilization of the pilot flame. In such a gas turbine combustor, the main burners are arranged at regular intervals around the pilot burner. High outputs of such a gas turbine combustor require high turbine inlet temperatures, which result from a high flame temperature. With regard to the formation of CO and NOx values, it is necessary to keep the flame temperature and the residence time of the gas in the combustion chamber in an allowable range.
Die hohen Temperaturen in der Gasturbine erfordern eine hohe Flammentemperatur, die sich auch auf die NOx-Werte auswirken und diese erhöhen. Um die NOx-Werte jedoch im zulässigen Bereich zu halten, ist die mittlere Flammentemperatur in der Brennkammer in Bezug auf die entstehenden NOx-Werte auf einen dem Wirkungsgrad angepassten, zulässigen Wert zu minimieren. Zudem wäre es notwendig, die Verweildauer des Gases in der Brennkammer, z.B. durch eine verkürzte Brennkammer herabzusetzen.The high temperatures in the gas turbine require a high flame temperature, which also affect the NOx values and increase them. However, in order to keep the NOx levels within the permissible range, the average flame temperature in the combustion chamber should be minimized to an allowable value adjusted for efficiency with respect to the resulting NOx levels. In addition, it would be necessary to increase the residence time of the gas in the combustion chamber, e.g. reduced by a shortened combustion chamber.
Zu den niedrigen NOx-Werten ist es jedoch notwendig, ebenfalls niedrige CO-Werte zu erzielen. Bei einer Flammentemperatur von unter 1300°C erhöhen sich jedoch die CO-Werte. Auch lokal begrenzte Volumen in der Brennkammer, in denen diese untere Temperaturgrenze unterschritten wird, können einen dominierenden Einfluss auf erhöhte Emissionen von CO haben. Um CO auf einen niedrigen Wert zu halten, ist eine gute Durchmischung erforderlich. Hierfür ist es jedoch notwendig, die Verweildauer oder den Mischungsweg des Gases in der Brennkammer, z.B. durch eine verlängerte Brennkammer, zu erhöhen. Dies steht jedoch im Widerspruch zu einer Verkürzung der Verweildauer zur Reduktion der NOx-Werte.However, at the low NOx levels it is necessary to also obtain low CO values. At a flame temperature however, below 1300 ° C, CO values increase. Also, locally limited volumes in the combustion chamber, in which this lower temperature limit is exceeded, can have a dominant influence on increased emissions of CO. Keeping CO at a low level requires good mixing. For this purpose, however, it is necessary to increase the residence time or the mixing path of the gas in the combustion chamber, for example by an extended combustion chamber. However, this is in contradiction to a shortening of the residence time for the reduction of the NOx values.
Um die NOx-Werte jedoch weiterhin im zulässigen Bereich zu halten, könnten daher Maßnahmen vorgenommen werden, wie beispielsweise die Verdichterluft, welche der Brennkammer zugeführt wird, vorzuwärmen oder aber zu reduzieren oder aber, durch Änderung des Zufuhrsystems, zumindest teilweise um die Brennkammer herumzulenken. Dies würde jedoch den Betrieb der Turbine in Grundlast nachteilig beeinträchtigen. Zudem würden dadurch die Fertigungskosten erhöht. Auch könnte die Verfügbarkeit der Maschine beeinträchtigen werden, was ebenfalls einen großen Nachteil darstellen würde.However, in order to keep the NOx levels within the permissible range, measures could be taken, such as preheating or reducing the compressor air supplied to the combustion chamber, or at least partially divert it around the combustion chamber by changing the supply system. However, this would adversely affect the operation of the turbine in base load. In addition, this would increase the production costs. Also, the availability of the machine could be compromised, which would also be a major drawback.
Die Aufgabe der vorliegenden Erfindung ist daher die Angabe einer Gasturbinenbrennkammer, welche mit einer erhöhten Flammentemperatur und damit verbesserten Wirkungsgrad und ohne die oben beschrieben Nachteile betrieben werden kann.The object of the present invention is therefore to specify a gas turbine combustion chamber which can be operated with an increased flame temperature and thus improved efficiency and without the disadvantages described above.
Die Aufgabe wird gelöst durch einen Brenner nach Anspruch 1. Die weiteren Unteransprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The object is achieved by a burner according to claim 1. The other subclaims contain advantageous embodiments of the invention.
Durch die Turbulenzgeneratoren an der Innenseite und/oder Außenseite des Pilotkonus wird stromab des Pilotkonus eine bessere Durchmischung zwischen den Pilotgemisch, welches im Pilotkonus entsteht, und dem Hauptgemisch, welches durch die Hauptbrenner entsteht, erzielt. Stromab des Pilotkonus entsteht somit eine verbesserte Verbrennung des entstehenden Pilot-Hauptgemisches. Dadurch ist eine Verringerung der Verweildauer und eine Verkürzung des Mischungsweges des Gases in der Brennkammer möglich, ohne dass die CO-Werte erhöht werden. Dadurch werden selbst bei hohen Flammentemperaturen niedrige NOx-Werte erzielt. Dadurch kann auf NOx-Werte reduzierende Maßnahmen verzichtet werden. Zudem kann durch die Vermeidung von kalten lokal begrenzten Volumen in der Brennkammer somit der stabile Betriebsbereich mit geringen CO-Emissionen zu geringerer Mitteltemperatur ausgedehnt werden.Due to the turbulence generators on the inside and / or outside of the pilot cone, a better mixing is achieved downstream of the pilot cone between the pilot mixture which arises in the pilot cone and the main mixture which is produced by the main burners. Downstream of the pilot cone thus results in improved combustion of the resulting pilot main mix. This reduces the length of stay and a shortening of the mixing path of the gas in the combustion chamber possible without the CO values are increased. As a result, low NOx levels are achieved even at high flame temperatures. As a result, NOx reduction measures can be dispensed with. In addition, by avoiding cold localized volumes in the combustion chamber, the stable operating range with low CO emissions can be extended to lower mean temperatures.
Weitere Vorteile, Merkmale und Eigenschaften der vorliegenden Erfindung werden im Folgenden anhand von Ausführungsbeispielen unter Bezugnahme auf die beigefügten Figuren näher beschrieben. Die Merkmale der Ausführungsbeispiele können hierbei einzeln oder in Kombination miteinander vorteilhaft sein.
- Fig. 1
- zeigt schematisch einen Längsschnitt durch eine Gasturbinenbrennkammer nach dem Stand der Technik.
- Fig. 2
- zeigt schematisch einen Querschnitt, welcher senkrecht zum Längsschnitt ist, durch eine Gasturbinenbrennkammer nach dem Stand der Technik.
- FIG. 3
- zeigt schematisch eine Seitenansicht des erfindungsgemäßen Pilotkonus in einem ersten Ausführungsbeispiel.
- Fig. 4
- zeigt schematisch einen Querschnitt, welcher senkrecht zum Längsschnitt ist, durch die erfindungsgemäße Gasturbinenbrennkammer des ersten Ausführungsbeispiels.
- Fig. 5
- zeigt schematisch eine Seitenansicht eines erfindungsgemäßen Pilotkonus in einem zweiten Ausführungsbeispiel.
- FIG. 6
- zeigt schematisch eine Seitenansicht eines erfindungsgemäßen Pilotkonus in einem dritten Ausführungsbeispiel.
- Fig. 7
- zeigt schematisch einen Querschnitt, welcher senkrecht zum Längsschnitt ist, durch die erfindungsgemäße Gasturbinenbrennkammer des dritten Ausführungsbeispiels.
- Fig. 8
- zeigt schematisch einen Längsschnitt durch eine erfindungsgemäße Gasturbinenbrennkammer in einem vierten Ausführungsbeispiel.
- Fig. 9
- zeigt schematisch einen Querschnitt, welcher senkrecht zum Längsschnitt ist, durch eine erfindungsgemäße Gasturbinenbrennkammer in einem fünften Ausführungsbeispiel.
- Fig. 1
- schematically shows a longitudinal section through a gas turbine combustor according to the prior art.
- Fig. 2
- shows schematically a cross section, which is perpendicular to the longitudinal section, through a gas turbine combustor according to the prior art.
- FIG. 3
- schematically shows a side view of the pilot cone according to the invention in a first embodiment.
- Fig. 4
- schematically shows a cross section, which is perpendicular to the longitudinal section, through the gas turbine combustor of the first embodiment of the invention.
- Fig. 5
- schematically shows a side view of a pilot cone according to the invention in a second embodiment.
- FIG. 6
- schematically shows a side view of a pilot cone according to the invention in a third embodiment.
- Fig. 7
- schematically shows a cross section, which is perpendicular to the longitudinal section, through the gas turbine combustor of the third embodiment according to the invention.
- Fig. 8
- schematically shows a longitudinal section through a gas turbine combustor according to the invention in a fourth embodiment.
- Fig. 9
- schematically shows a cross section, which is perpendicular to the longitudinal section, through a gas turbine combustor according to the invention in a fifth embodiment.
Im Pilotkonus 4 wird durch Mischen von Luft und Pilotbrennstoff eine gemischte Pilotflamme (Pilotgemisch) gebildet, so dass der von den Hauptbrennern kommende, im Gemisch vorhandene Brennstoff gezündet wird, und somit das vom Hauptbrenner kommende Gemisch (Hauptgemisch) verbrennt.In the
Turbulenzgeneratoren können beispielsweise auch Flügel, Ecken oder Prismen mit scharfer, gerader Kante sein, die in einem vorbestimmten Winkel über den gesamten Umfang der Öffnung 6 am Pilotkonus 4 angeordnet sind (nicht gezeigt). Dabei weist die scharfe Kante zur Brennkammer hin (nicht gezeigt). Ebenso können solche Flügel mit unterschiedlichen Winkeln alternierend (nicht gezeigt), insbesondere im Winkel von +/- 30° am Pilotkonus 4, angeordnet sein.Turbulence generators may, for example, also be sharp, straight edge vanes, corners or prisms placed at a predetermined angle over the entire circumference of the
Claims (10)
dadurch gekennzeichnet, dass die Turbulenzgeneratoren im Bereich der Öffnung (6) des Pilotkonus (4) angeordnet sind.Gas turbine combustor according to claim 1,
characterized in that the turbulence generators in the region of the opening (6) of the pilot cone (4) are arranged.
dadurch gekennzeichnet, dass die Turbulenzgeneratoren über den Umfang des Pilotkonus (4) verteilt sind.Gas turbine combustor according to one of the preceding claims,
characterized in that the turbulence generators are distributed over the circumference of the pilot cone (4).
dadurch gekennzeichnet, dass die Turbulenzgeneratoren Streifen sind, welche über den Umfang des Pilotkonus (4) voneinander beabstandet angeordnet sind.Gas turbine combustor according to one of the preceding claims,
characterized in that the turbulence generators are strips which are arranged spaced apart from each other over the circumference of the pilot cone (4).
dadurch gekennzeichnet, dass ein oder mehrere Streifenringe (33) als Turbulenzgeneratoren vorgesehen sind, welche über den Umfang des Pilotkonus (4) angeordnet sind.Gas turbine combustor according to one of the preceding claims 1-3,
characterized in that one or more strip rings (33) are provided as turbulence generators, which are arranged over the circumference of the pilot cone (4).
dadurch gekennzeichnet, dass die Streifen oder die ein oder mehreren Streifenringe (33) über den Umfang der Außenseite (12) des Pilotkonus (4) im Winkel von 30° bis 60° zur Außenseite (12) des Pilotkonus (4) angeordnet sind.Gas turbine combustor according to claim 4 or 5,
characterized in that the strips or the one or more strip rings (33) over the circumference of the outer side (12) of the pilot cone (4) at an angle of 30 ° to 60 ° to the outer side (12) of the pilot cone (4) are arranged.
dadurch gekennzeichnet, dass die Turbulenzgeneratoren trapezförmige Streifen (35) sind, welche an der Öffnung (6) des Pilotkonus (4) über den gesamten Umfang der Öffnung (6) angeordnet sind.Gas turbine combustor according to claims 1-3,
characterized in that the turbulence generators are trapezoidal strips (35) which are arranged on the opening (6) of the pilot cone (4) over the entire circumference of the opening (6).
dadurch gekennzeichnet, dass die trapezförmige Streifen (35) alternierend im Winkel von +/-30° am Pilotkonus (4) angeordnet sind.Gas turbine combustor according to claim 7,
characterized in that the trapezoidal strips (35) are arranged alternately at an angle of +/- 30 ° to the pilot cone (4).
dadurch gekennzeichnet, dass die Gasturbinenbrennkammer eine axiale Richtung (A) aufweist und jeder Hauptbrenner Hauptdüsen (7) sowie einen mit einem Zwischenraum um den Außenumfang der betreffenden Hauptdüse (7) herum angeordneten Außenzylinder (20) aufweist, und wobei Verlängerungsrohre (230) so ausgebildet sind, dass sie die Öffnungen der Außenzylinder (20) verlängern, und zwar so, dass die Verlängerungsrohre (230) sich radial verengen und in Umfangsrichtung erweitern, so dass jedes Verlängerungsrohr (230) mit dem angrenzenden Verlängerungsrohr (230) ineinander übergeht, so dass eine ringförmige Hauptdüsenöffnung (240) entsteht, welche sich in axialer Richtung (A) bis zur Öffnung (6) des Pilotkonus (4) verlängert und wobei auf der Innenseite (111) der ringförmige Hauptdüsenöffnung (240) Turbulenzgeneratoren angeordnet sind.Gas turbine according to one of the preceding claims,
characterized in that the gas turbine combustor has an axial direction (A), and each main burner has main nozzles (7) and an outer cylinder (20) having a clearance around the outer periphery of the main nozzle (7) around, and wherein extension tubes (230) are formed are that they extend the openings of the outer cylinder (20), in such a way that the extension tubes (230) radially narrow and in Extend the circumferential direction so that each extension tube (230) with the adjacent extension tube (230) into each other, so that an annular main nozzle opening (240) is formed, which extends in the axial direction (A) to the opening (6) of the pilot cone (4) and wherein on the inside (111) of the annular main nozzle opening (240) turbulence generators are arranged.
dadurch gekennzeichnet, dass die Gasturbinenbrennkammer eine axiale Richtung (A) aufweist, und jeder Hauptbrenner Hauptdüsen (7), sowie mit einem Zwischenraum um den Außenumfang der betreffenden Hauptdüse (7) herum angeordneten Außenzylinder (20), aufweist, und wobei Verlängerungsrohre (250) mit einer brennkammerseitigen Austrittsöffnung so ausgebildet sind, dass sie die Öffnungen der Außenzylinder (20) in axialer Richtung (A) bis zur Öffnung (6) des Pilotkonus (4) verlängern, und wobei auf einer Innenseite (260) der Verlängerungsrohre (250) im Bereich der Austrittsöffnung Turbulenzgeneratoren angeordnet sind.Gas turbine combustor according to any one of claims 1-8,
characterized in that the gas turbine combustor has an axial direction (A), and each main burner has main nozzles (7) and outer cylinders (20) arranged around the outer circumference of the main nozzle (7) around, and wherein extension tubes (250) are formed with a combustion chamber side outlet opening so that they extend the openings of the outer cylinder (20) in the axial direction (A) to the opening (6) of the pilot cone (4), and wherein on an inner side (260) of the extension tubes (250) in Region of the outlet opening turbulence generators are arranged.
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10171601A EP2416070A1 (en) | 2010-08-02 | 2010-08-02 | Gas turbine combustion chamber |
EP11725735.2A EP2601447A2 (en) | 2010-08-02 | 2011-06-15 | Gas turbine combustion chamber |
JP2013522155A JP5657794B2 (en) | 2010-08-02 | 2011-06-15 | Gas turbine combustion chamber |
CN201180037995.3A CN103119369B (en) | 2010-08-02 | 2011-06-15 | gas turbine combustion chamber |
US13/813,494 US9194587B2 (en) | 2010-08-02 | 2011-06-15 | Gas turbine combustion chamber |
PCT/EP2011/059901 WO2012016748A2 (en) | 2010-08-02 | 2011-06-15 | Gas turbine combustion chamber |
RU2013109306/06A RU2566866C2 (en) | 2010-08-02 | 2011-06-15 | Combustion chamber of gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10171601A EP2416070A1 (en) | 2010-08-02 | 2010-08-02 | Gas turbine combustion chamber |
Publications (1)
Publication Number | Publication Date |
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EP2416070A1 true EP2416070A1 (en) | 2012-02-08 |
Family
ID=43479914
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP10171601A Withdrawn EP2416070A1 (en) | 2010-08-02 | 2010-08-02 | Gas turbine combustion chamber |
EP11725735.2A Withdrawn EP2601447A2 (en) | 2010-08-02 | 2011-06-15 | Gas turbine combustion chamber |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP11725735.2A Withdrawn EP2601447A2 (en) | 2010-08-02 | 2011-06-15 | Gas turbine combustion chamber |
Country Status (6)
Country | Link |
---|---|
US (1) | US9194587B2 (en) |
EP (2) | EP2416070A1 (en) |
JP (1) | JP5657794B2 (en) |
CN (1) | CN103119369B (en) |
RU (1) | RU2566866C2 (en) |
WO (1) | WO2012016748A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US11175043B2 (en) | 2016-03-07 | 2021-11-16 | Mitsubishi Power, Ltd. | Burner assembly, combustor, and gas turbine |
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JP6037736B2 (en) * | 2012-09-11 | 2016-12-07 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor and gas turbine engine equipped with the same |
US9528702B2 (en) | 2014-02-21 | 2016-12-27 | General Electric Company | System having a combustor cap |
US9528704B2 (en) * | 2014-02-21 | 2016-12-27 | General Electric Company | Combustor cap having non-round outlets for mixing tubes |
JP6692847B2 (en) * | 2018-03-26 | 2020-05-13 | 三菱重工業株式会社 | Gas turbine combustor and gas turbine engine including the same |
JP7096182B2 (en) * | 2019-02-27 | 2022-07-05 | 三菱重工業株式会社 | Gas turbine combustor and gas turbine |
KR102583224B1 (en) * | 2022-01-26 | 2023-09-25 | 두산에너빌리티 주식회사 | Combustor with cluster and gas turbine including same |
CN115030837B (en) * | 2022-08-10 | 2022-11-08 | 中国空气动力研究与发展中心低速空气动力研究所 | Spout noise reduction device |
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- 2011-06-15 EP EP11725735.2A patent/EP2601447A2/en not_active Withdrawn
- 2011-06-15 WO PCT/EP2011/059901 patent/WO2012016748A2/en active Application Filing
- 2011-06-15 RU RU2013109306/06A patent/RU2566866C2/en not_active IP Right Cessation
- 2011-06-15 CN CN201180037995.3A patent/CN103119369B/en not_active Expired - Fee Related
- 2011-06-15 JP JP2013522155A patent/JP5657794B2/en not_active Expired - Fee Related
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US6122916A (en) * | 1998-01-02 | 2000-09-26 | Siemens Westinghouse Power Corporation | Pilot cones for dry low-NOx combustors |
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US11175043B2 (en) | 2016-03-07 | 2021-11-16 | Mitsubishi Power, Ltd. | Burner assembly, combustor, and gas turbine |
DE112017001173B4 (en) | 2016-03-07 | 2022-12-08 | Mitsubishi Power, Ltd. | BURNER ARRANGEMENT, COMBUSTION CHAMBER AND GAS TURBINE |
Also Published As
Publication number | Publication date |
---|---|
EP2601447A2 (en) | 2013-06-12 |
WO2012016748A2 (en) | 2012-02-09 |
JP2013535651A (en) | 2013-09-12 |
JP5657794B2 (en) | 2015-01-21 |
RU2566866C2 (en) | 2015-10-27 |
RU2013109306A (en) | 2014-09-10 |
US20130125550A1 (en) | 2013-05-23 |
WO2012016748A3 (en) | 2013-03-21 |
CN103119369A (en) | 2013-05-22 |
US9194587B2 (en) | 2015-11-24 |
CN103119369B (en) | 2016-03-09 |
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