EP1936276A1 - Gas turbine burner - Google Patents

Gas turbine burner Download PDF

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Publication number
EP1936276A1
EP1936276A1 EP06026685A EP06026685A EP1936276A1 EP 1936276 A1 EP1936276 A1 EP 1936276A1 EP 06026685 A EP06026685 A EP 06026685A EP 06026685 A EP06026685 A EP 06026685A EP 1936276 A1 EP1936276 A1 EP 1936276A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
receptacle
burner
support structure
tip
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.)
Withdrawn
Application number
EP06026685A
Other languages
German (de)
French (fr)
Inventor
Andreas Dr. Böttcher
Jens Kleinfeld
Tobias Krieger
Sabine Tüschen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP06026685A priority Critical patent/EP1936276A1/en
Priority to US12/520,134 priority patent/US8869534B2/en
Priority to PCT/EP2007/064338 priority patent/WO2008077882A1/en
Priority to EP07857958.8A priority patent/EP2092245B1/en
Priority to JP2009542067A priority patent/JP5047309B2/en
Publication of EP1936276A1 publication Critical patent/EP1936276A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means

Definitions

  • the invention relates to a burner for a gas turbine with a main burner and a pilot burner.
  • Gas turbines include, such as from the US 6,038,861 is known, a compressor for compressing air, a combustion chamber for generating hot gas by burning fuel in conjunction with the compressed air and a turbine for expanding the hot gas. It is known that gas turbines eject undesirable nitrogen oxides (NO x ) and carbon monoxide (CO).
  • NO x nitrogen oxides
  • CO carbon monoxide
  • Two-stage combustion systems have been developed that simultaneously produce efficient combustion and reduced NO x emissions. In such a two-stage combustion system, diffusion combustion is performed in the first stage to ignite and stabilize the flame. Premix combustion is performed in the second stage to reduce NO x emissions.
  • the first stage is the so-called pilot stage, which is usually carried out by a diffusion burner and causes significant increases in NO x emissions.
  • the main burner includes several main fuel mixers, each with a swirler that creates turbulence in the airflow.
  • the fuel supply line In the center of the Swirlers is the fuel supply line, which introduces the gas into the airflow.
  • Fig. 1 shows a fuel supply line with a heat shield in a main burner according to the prior art.
  • the fuel supply line 16 is located inside a support structure 6, which is arranged in the center of the Swirlers 4.
  • lines 16 which introduce the fuel from the interior of the support structure 6 in the Swirlerschaufeln 4.
  • the gas mixes with the compressed air.
  • a receptacle 8 which forwards the fuel to the tip 10 of the arrangement.
  • a heat shield 18 which isolates the fuel from the environment.
  • oil injection holes 19 At the end of the heat shield 18 are oil injection holes 19.
  • the heat shield 18 serves to thermally decouple the support structure 6 of the swirler 4 against the oil channels 16 in the interior of the arrangement. It consists of a tube, which was previously soldered or welded into the support structure 6 by the cohesive joints 12, the deformation of the support structure 6 is hindered due to the colder heat shield 18 so that it can cause thermal stress. Due to these possible voltages, the maximum possible starting numbers - and thus also the maximum possible service life - can not be realized.
  • the invention has for its object to provide a burner for a gas turbine available, in which the occurrence of thermal stresses between the support structure and the heat shield can be reduced.
  • the solution of the problem in a burner for a gas turbine with a main burner and a pilot burner comprises a support structure, a heat shield and a receptacle for the heat shield.
  • the receptacle is located at least partially within the support structure, in particular concentrically, within the support structure, and the heat shield is located at least partially within the receptacle, in particular concentrically, within the receptacle.
  • the heat shield is attached by friction to the recording.
  • the receptacle is also secured by frictional engagement on the support structure.
  • a thermal decoupling of the support structure takes place against the recording.
  • the life of the components is increased, which leads to higher starting numbers of the gas turbine.
  • the heat shield is fastened by a clamping fit between the tip and the receptacle.
  • the clamped seat allows free thermal stretching, so that the stresses in the component can be significantly reduced.
  • the required start numbers can be achieved in this way.
  • the solution is cheaper compared to the soldered connection (prior art), which requires high accuracy.
  • the heat shield may further comprise a collar, which serves for better clamping of the heat shield.
  • the tip is screwed to the receptacle.
  • the screw connection is a simple construction that allows the tip to be connected to the receptacle.
  • the tip may be crimped with the receptacle. Crimping provides protection against uncontrolled release during operation of the gas turbine.
  • the heat shield is tubular.
  • the oil channel is thermally insulated inside the heat shield over its entire length.
  • the burner may comprise a Swirler, in the center of which the support structure may be arranged.
  • a main burner 2 with a Swirler 4, a support structure 6, a receptacle 8, a tip 10, an oil passage 16, Swirler channels 17 and a heat shield 18 is shown.
  • the support structure 6 is located in the center of the Swirlers 4. It is tubular and protrudes with its two ends in each case beyond the Swirler.
  • the receptacle 8 is also substantially tubular and is located inside the support structure 6, concentric to the swirler 4. The interior of the receptacle 8 is formed by an oil passage 16 which extends along the longitudinal axis of the receptacle 8.
  • the heat shield 18 is arranged in the downstream part of the receptacle 8.
  • the heat shield 18 connects to the oil passage 16 and protrudes beyond the receptacle 8.
  • the heat shield is also tubular and has at its downstream end bores 19, through which the oil, which is introduced through the oil passage 16 and is passed through the interior of the heat shield 18 and the tip 10, exiting into the combustion chamber 3.
  • the tip 10 has a conical and a cylindrical part.
  • the cylindrical part is screwed to the receptacle 8.
  • this part of the tip is crimped.
  • the tip 10 may also be secured by crimping alone on the receptacle 8.
  • oil outlet holes through which the guided in the heat shield oil can escape into the combustion chamber 3.
  • air is introduced from the compressor (not shown) into the swirler of the main burner 2.
  • the Swirler swirls the air and the oil exiting through the oil channels 17 from the Swirler blades is supplied with the Air mixed.
  • oil is passed through the oil passage 16, passed through the interior of the heat shield and fed through the holes 19 in the heat shield and the passages in the top of the combustion chamber 3 of the main burner 2.
  • Fig. 3 provides a detail X of the heat shield assembly in Fig. 2
  • the heat shield 18 has a collar 22 with two clamping points 20.
  • the clamping points 20 are clamped between a shoulder 24 of the receptacle and a shoulder 26 of the tip.
  • Between the receptacle 8 and the tip 10 is a seal 21.
  • the thread 14 can be clearly seen, with the aid of which the tip 10 is screwed onto the receptacle 8.
  • the nipples 20 between heat shield, receptacle and tip allow during operation a free thermal stretching of the receptacle 8 and the tip 10 around the heat shield 18 around, which hardly expands due to its material (ceramic).
  • the metallic components 8 and 10 have a relatively high thermal expansion during operation.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

The burner comprises at least one main burner (2) and a pilot burner, whereby the main burner is located in a carrier structure (6) together with a heat shield (18) and a receiver (8) for the heat shield. The heat shield is fixed via a friction lock to the receiver.

Description

Hintergrund der ErfindungBackground of the invention

Die Erfindung betrifft einen Brenner für eine Gasturbine mit einem Hauptbrenner und einem Pilotbrenner.The invention relates to a burner for a gas turbine with a main burner and a pilot burner.

Gasturbinen umfassen, wie zum Beispiel aus der US 6,038,861 bekannt ist, einen Verdichter zum Verdichten von Luft, eine Brennkammer zum Erzeugen von Heißgas durch Verbrennen von Brennstoff in Verbindung mit der verdichteten Luft und eine Turbine zum Entspannen des Heißgases. Es ist bekannt, dass Gasturbinen unerwünschte Stickoxide (NOx) und Kohlenmonoxide (CO) ausstoßen. Es wurden zweistufige Verbrennungssysteme entwickelt, die gleichzeitig eine effiziente Verbrennung und verringerte NOx-Emissionen erzeugen. In einem solchen zweistufigen Verbrennungssystem wird eine Diffusionsverbrennung in der ersten Stufe durchgeführt, um die Flamme zu zünden und stabil zu halten. Eine Vormischverbrennung wird in der zweiten Stufe durchgeführt, um die NOx-Ausstöße zu reduzieren.Gas turbines include, such as from the US 6,038,861 is known, a compressor for compressing air, a combustion chamber for generating hot gas by burning fuel in conjunction with the compressed air and a turbine for expanding the hot gas. It is known that gas turbines eject undesirable nitrogen oxides (NO x ) and carbon monoxide (CO). Two-stage combustion systems have been developed that simultaneously produce efficient combustion and reduced NO x emissions. In such a two-stage combustion system, diffusion combustion is performed in the first stage to ignite and stabilize the flame. Premix combustion is performed in the second stage to reduce NO x emissions.

Die erste Stufe ist die sog. Pilotstufe, die normalerweise durch einen Diffusionsbrenner ausgeführt ist und die deutliche Erhöhungen der NOx-Emissionen hervorruft.The first stage is the so-called pilot stage, which is usually carried out by a diffusion burner and causes significant increases in NO x emissions.

Um den Pilotbrenner herum ist der Hauptbrenner angeordnet. Der Hauptbrenner umfasst mehrere Hauptbrennstoffmischer mit jeweils einem Swirler (Drallerzeuger), der eine Turbulenz im Luftstrom erzeugt. Im Zentrum des Swirlers befindet sich die Brennstoffzufuhrleitung, die das Gas in den Luftstrom einführt.Around the pilot burner around the main burner is arranged. The main burner includes several main fuel mixers, each with a swirler that creates turbulence in the airflow. In the center of the Swirlers is the fuel supply line, which introduces the gas into the airflow.

Fig. 1 zeigt eine Brennstoffzufuhrleitung mit einem Hitzeschild in einem Hauptbrenner nach dem Stand der Technik. Die Brennstoffzufuhrleitung 16 befindet sich im Inneren einer Tragstruktur 6, die im Zentrum des Swirlers 4 angeordnet ist. Fig. 1 shows a fuel supply line with a heat shield in a main burner according to the prior art. The fuel supply line 16 is located inside a support structure 6, which is arranged in the center of the Swirlers 4.

In der Tragstruktur 6 befinden sich Leitungen 16, die den Brennstoff aus dem Inneren der Tragstruktur 6 in die Swirlerschaufeln 4 einleiten. Beim Austritt aus den Swirlerschaufeln 4 vermischt sich das Gas mit der verdichteten Luft.In the support structure 6 are lines 16, which introduce the fuel from the interior of the support structure 6 in the Swirlerschaufeln 4. When leaving the Swirlerschaufeln 4, the gas mixes with the compressed air.

Im Inneren der Tragstruktur 6 befindet sich außerdem eine Aufnahme 8 die den Brennstoff zur Spitze 10 der Anordnung weiterleitet. Innerhalb der Aufnahme 8 befindet sich ein Hitzeschild 18, der den Brennstoff gegen die Umgebung isoliert. Am Ende des Hitzeschilds 18 befinden sich Öleinspritzbohrungen 19.In the interior of the support structure 6 is also a receptacle 8 which forwards the fuel to the tip 10 of the arrangement. Within the receptacle 8 is a heat shield 18, which isolates the fuel from the environment. At the end of the heat shield 18 are oil injection holes 19.

Der Hitzeschild 18 dient dazu, die Tragstruktur 6 des Swirlers 4 gegen die Ölkanäle 16 im Innern der Anordnung thermisch zu entkoppeln. Er besteht aus einem Rohr, welches bisher in die Tragstruktur 6 eingelötet bzw. geschweißt wurde 12. Durch die stoffschlüssigen Verbindungsstellen 12 wird die Verformung der Tragstruktur 6 aufgrund des kälteren Hitzeschildes 18 behindert, sodass es zu Thermospannungen kommen kann. Aufgrund dieser möglichen Spannungen können die maximal möglichen Startzahlen - und damit auch die maximal mögliche Lebensdauer - nicht realisiert werden.The heat shield 18 serves to thermally decouple the support structure 6 of the swirler 4 against the oil channels 16 in the interior of the arrangement. It consists of a tube, which was previously soldered or welded into the support structure 6 by the cohesive joints 12, the deformation of the support structure 6 is hindered due to the colder heat shield 18 so that it can cause thermal stress. Due to these possible voltages, the maximum possible starting numbers - and thus also the maximum possible service life - can not be realized.

Zugrundeliegende AufgabeUnderlying task

Der Erfindung liegt die Aufgabe zugrunde, einen Brenner für eine Gasturbine zur Verfügung zu stellen, bei dem das Auftreten von Thermospannungen zwischen der Tragstruktur und dem Hitzeschild verringert werden.The invention has for its object to provide a burner for a gas turbine available, in which the occurrence of thermal stresses between the support structure and the heat shield can be reduced.

Erfindungsgemäße LösungInventive solution

Die Aufgabe wird durch einen Brenner mit den Merkmalen des Anspruchs 1 gelöst. Die abhängigen Ansprüche enthalten vorteilhafte Weiterbildungen der Erfindung.The object is achieved by a burner having the features of claim 1. The dependent claims contain advantageous developments of the invention.

Erfindungsgemäß besteht die Lösung der Aufgabe in einem Brenner für eine Gasturbine mit einem Hauptbrenner und einem Pilotbrenner. Der Hauptbrenner umfasst eine Tragstruktur, einen Hitzeschild und eine Aufnahme für den Hitzeschild. Die Aufnahme befindet sich zumindest teilweise innerhalb der Tragstruktur, insbesondere konzentrisch, innerhalb der Tragstruktur, und der Hitzeschild befindet sich zumindest teilweise innerhalb der Aufnahme, insbesondere konzentrisch, innerhalb der Aufnahme. Der Hitzeschild ist durch Reibschluss an der Aufnahme befestigt.According to the invention, the solution of the problem in a burner for a gas turbine with a main burner and a pilot burner. The main burner comprises a support structure, a heat shield and a receptacle for the heat shield. The receptacle is located at least partially within the support structure, in particular concentrically, within the support structure, and the heat shield is located at least partially within the receptacle, in particular concentrically, within the receptacle. The heat shield is attached by friction to the recording.

Durch die reibschlüssige Verbindung findet eine thermische Entkopplung der Aufnahme gegen die Ölkanäle (TÖl=25°C, Wärmeübergang > 5000 W/M2K) im Inneren des Hitzeschildes statt. Die Thermospannungen zwischen der Aufnahme und dem Hitzeschild sind also geringer als bei der gelöteten oder geschweißten Verbindung nach dem Stand der Technik. Dies erlaubt höhere Startzahlen und ermöglicht dadurch eine höhere Lebensdauer der Komponenten. Außerdem wird ein sicherer Betrieb gewährleistet.Due to the frictional connection, a thermal decoupling of the receptacle against the oil channels (T oil = 25 ° C, heat transfer> 5000 W / M 2 K) takes place inside the heat shield. The thermal stresses between the receptacle and the heat shield are thus lower than in the soldered or welded connection according to the prior art. This allows higher starting numbers and thus enables a longer service life of the components. In addition, safe operation is ensured.

In einer vorteilhaften Weiterbindung der Erfindung ist die Aufnahme ebenfalls durch Reibschluss an der Tragstruktur befestigt. Dadurch findet eine thermische Entkopplung der Tragstruktur gegen die Aufnahme statt. Es entstehen geringere Thermospannungen zwischen der Tragstruktur und der Aufnahme als bei der gelöteten oder geschweißten Verbindung. Außerdem wird die Lebensdauer der Komponenten erhöht, was zur höheren Startzahlen der Gasturbine führt.In an advantageous further connection of the invention, the receptacle is also secured by frictional engagement on the support structure. As a result, a thermal decoupling of the support structure takes place against the recording. There are lower thermal stresses between the support structure and the receptacle than in the soldered or welded connection. In addition, the life of the components is increased, which leads to higher starting numbers of the gas turbine.

In einer weiteren vorteilhaften Weiterbildung der Erfindung wird der Hitzeschild durch einen Klemmsitz zwischen der Spitze und der Aufnahme befestigt. Der Klemmsitz erlaubt ein freies thermisches Dehnen, sodass die Spannungen im Bauteil erheblich gesenkt werden können. Die geforderten Startzahlen können so erreicht werden. Außerdem ist die Lösung kostengünstiger im Vergleich zur gelöteten Verbindung (Stand der Technik), die eine hohe Genauigkeit erfordert.In a further advantageous embodiment of the invention, the heat shield is fastened by a clamping fit between the tip and the receptacle. The clamped seat allows free thermal stretching, so that the stresses in the component can be significantly reduced. The required start numbers can be achieved in this way. In addition, the solution is cheaper compared to the soldered connection (prior art), which requires high accuracy.

Der Hitzeschild kann weiterhin einen Bund aufweisen, der zum besseren Festklemmen des Hitzeschildes dient.The heat shield may further comprise a collar, which serves for better clamping of the heat shield.

Vorzugsweise ist die Spitze mit der Aufnahme verschraubt. Die Verschraubung ist einfache Konstruktion, durch die die Spitze mit der Aufnahme verbunden werden kann.Preferably, the tip is screwed to the receptacle. The screw connection is a simple construction that allows the tip to be connected to the receptacle.

Insbesondere kann die Spitze mit der Aufnahme verkrimpt sein. Das Verkrimpen bietet einen Schutz gegen unkontrolliertes Lösen während des Betriebs der Gasturbine.In particular, the tip may be crimped with the receptacle. Crimping provides protection against uncontrolled release during operation of the gas turbine.

In einer weiteren vorteilhaften Weiterbildung der Erfindung ist der Hitzeschild rohrförmig ausgebildet. Dadurch wird der Ölkanal im Innern des Hitzeschildes über seine gesamte Länge thermisch isoliert.In a further advantageous embodiment of the invention, the heat shield is tubular. As a result, the oil channel is thermally insulated inside the heat shield over its entire length.

Weiterhin kann der Brenners einen Swirler aufweisen, in dessen Zentrum die Tragstruktur angeordnet sein kann.Furthermore, the burner may comprise a Swirler, in the center of which the support structure may be arranged.

Außerdem wird eine Gasturbine mit einem Brenner nach einem der vorangegangenen Ansprüche verwendet.In addition, a gas turbine with a burner according to one of the preceding claims is used.

Kurzbeschreibung der ZeichnungenBrief description of the drawings

Weitere Merkmale, Eigenschaften und Vorteile der Erfindung ergeben sich aus der nachfolgenden Beschreibung von Ausführungsbeispielen unter Bezugnahme auf die beiliegenden Figuren. Es zeigen:

Fig. 1
einen Hauptbrenner mit einem Swirler nach dem Stand der Technik.
Fig. 2
einen Hauptbrenner mit einem Swirler und einem erfindungsgemäßen Hitzeschild.
Fig. 3
eine vergrößerte Detailansicht der Befestigung des Hitzeschilds.
Further features, properties and advantages of the invention will become apparent from the following description of embodiments with reference to the accompanying figures. Show it:
Fig. 1
a main burner with a Swirler according to the prior art.
Fig. 2
a main burner with a Swirler and a heat shield according to the invention.
Fig. 3
an enlarged detail view of the attachment of the heat shield.

Detaillierte Beschreibung des AusführungsbeispielsDetailed description of the embodiment

In Fig. 2 ist ein Hauptbrenner 2 mit einem Swirler 4, einer Tragstruktur 6, einer Aufnahme 8, einer Spitze 10, einem Ölkanal 16, Swirlerkanälen 17 und einem Hitzeschild 18 dargestellt.In Fig. 2 a main burner 2 with a Swirler 4, a support structure 6, a receptacle 8, a tip 10, an oil passage 16, Swirler channels 17 and a heat shield 18 is shown.

Die Tragstruktur 6 befindet sich im Zentrum des Swirlers 4. Sie ist rohrförmig aufgebaut und ragt mit ihren beiden Enden jeweils über den Swirler hinaus. Die Aufnahme 8 ist ebenfalls im Wesentlichen rohrförmig und befindet sich im Innern der Tragstruktur 6, konzentrisch zum Swirler 4. Das Innere der Aufnahme 8 wird von einem Ölkanal 16 gebildet, der entlang der Längsachse der Aufnahme 8 verläuft.The support structure 6 is located in the center of the Swirlers 4. It is tubular and protrudes with its two ends in each case beyond the Swirler. The receptacle 8 is also substantially tubular and is located inside the support structure 6, concentric to the swirler 4. The interior of the receptacle 8 is formed by an oil passage 16 which extends along the longitudinal axis of the receptacle 8.

Im stromabwärts angeordneten Teil der Aufnahme 8 ist der Hitzeschild 18 angeordnet. Der Hitzeschild 18 schließt an den Ölkanal 16 an und ragt über die Aufnahme 8 hinaus. Der Hitzeschild ist ebenfalls rohrförmig und weist an seinem stromabwärts gerichteten Ende Bohrungen 19 auf, durch die das Öl, das durch den Ölkanal 16 eingeführt wird und durch das Innere des Hitzeschildes 18 und durch die Spitze 10 geleitet wird, in den Brennraum 3 austritt.In the downstream part of the receptacle 8, the heat shield 18 is arranged. The heat shield 18 connects to the oil passage 16 and protrudes beyond the receptacle 8. The heat shield is also tubular and has at its downstream end bores 19, through which the oil, which is introduced through the oil passage 16 and is passed through the interior of the heat shield 18 and the tip 10, exiting into the combustion chamber 3.

Die Spitze 10 weist einen konischen und einen zylindrischen Teil auf. Der zylindrische Teil ist mit der Aufnahme 8 verschraubt. Um die Spitze 10 gegen ungewolltes Lösen zu sichern, wird dieser Teil der Spitze verkrimpt. Die Spitze 10 kann auch durch Verkrimpung allein an der Aufnahme 8 befestigt sein. Am Übergang zwischen dem zylindrischen Teil und dem konischen Teil der Spitze befinden sich Ölaustrittsbohrungen, durch die das in dem Hitzeschild geführte Öl in den Brennraum 3 austreten kann.The tip 10 has a conical and a cylindrical part. The cylindrical part is screwed to the receptacle 8. To secure the tip 10 against unwanted loosening, this part of the tip is crimped. The tip 10 may also be secured by crimping alone on the receptacle 8. At the transition between the cylindrical part and the conical part of the tip there are oil outlet holes, through which the guided in the heat shield oil can escape into the combustion chamber 3.

Während des Betriebs wird Luft vom Verdichter (nicht dargestellt) in den Swirler des Hauptbrenners 2 eingeleitet. Der Swirler verwirbelt die Luft und das durch die Ölkanäle 17 aus den Swirlerschaufeln austretende Öl wird mit der zugeführten Luft vermischt. Außerdem wird Öl durch den Ölkanal 16 geführt, durch das Innere des Hitzeschilds geleitet und durch die Bohrungen 19 im Hitzeschild und die Durchgänge in der Spitze dem Brennraum 3 des Hauptbrenners 2 zugeführt.During operation, air is introduced from the compressor (not shown) into the swirler of the main burner 2. The Swirler swirls the air and the oil exiting through the oil channels 17 from the Swirler blades is supplied with the Air mixed. In addition, oil is passed through the oil passage 16, passed through the interior of the heat shield and fed through the holes 19 in the heat shield and the passages in the top of the combustion chamber 3 of the main burner 2.

Fig. 3 stellt eine Detailansicht X der Hitzeschildanordnung in Fig. 2 dar. Der Hitzeschild 18 weist einen Bund 22 mit zwei Klemmstellen 20 auf. Die Klemmstellen 20 sind zwischen einen Absatz 24 der Aufnahme und einen Absatz 26 der Spitze geklemmt. Zwischen der Aufnahme 8 und der Spitze 10 befindet sich eine Dichtung 21. In der Detailansicht ist auch das Gewinde 14 deutlich zu erkennen, mit Hilfe dessen die Spitze 10 auf die Aufnahme 8 geschraubt ist. Fig. 3 provides a detail X of the heat shield assembly in Fig. 2 The heat shield 18 has a collar 22 with two clamping points 20. The clamping points 20 are clamped between a shoulder 24 of the receptacle and a shoulder 26 of the tip. Between the receptacle 8 and the tip 10 is a seal 21. In the detail view, the thread 14 can be clearly seen, with the aid of which the tip 10 is screwed onto the receptacle 8.

Die Klemmstellen 20 zwischen Hitzeschild, Aufnahme und Spitze ermöglichen während des Betriebs ein freies thermisches Dehnen der Aufnahme 8 und der Spitze 10 um den Hitzeschild 18 herum, der sich aufgrund seines Werkstoffes (Keramik) kaum ausdehnt. Die metallischen Bauteile 8 und 10 jedoch weisen eine relativ hohe thermische Dehnung während des Betriebs auf.The nipples 20 between heat shield, receptacle and tip allow during operation a free thermal stretching of the receptacle 8 and the tip 10 around the heat shield 18 around, which hardly expands due to its material (ceramic). However, the metallic components 8 and 10 have a relatively high thermal expansion during operation.

Claims (9)

Brenner für eine Gasturbine mit einem Hauptbrenner (2) und einem Pilotbrenner, wobei der Hauptbrenner (2), eine Tragstruktur (6), einen Hitzeschild (18) und eine Aufnahme (8) für den Hitzeschild (18) aufweist, und wobei sich die Aufnahme (8) zumindest teilweise innerhalb der Tragstruktur (6) und der Hitzeschild (18) zumindest teilweise innerhalb der Aufnahme (8) befinden, dadurch gekennzeichnet, da s s der Hitzeschild (18) durch Reibschluss an der Aufnahme (8) befestigt ist.A burner for a gas turbine with a main burner (2) and a pilot burner, wherein the main burner (2), a support structure (6), a heat shield (18) and a receptacle (8) for the heat shield (18), and wherein the Housing (8) at least partially within the support structure (6) and the heat shield (18) located at least partially within the receptacle (8), characterized in that ss the heat shield (18) by friction on the receptacle (8) is attached. Brenner nach Anspruch 1,
dadurch gekennzeichnet , das s die Aufnahme (8) durch Reibschluss an der Tragstruktur (6) befestigt ist.Burner according to claim 1,
characterized in that s the receptacle (8) is fixed by frictional engagement on the support structure (6). Brenner nach Anspruch 2,
dadurch gekennzeichnet, dass er eine an die Tragstruktur (6), die Aufnahme (8) und den Hitzeschild (18) angrenzende Spitze (10) aufweist und der Hitzeschild (18) durch einen Klemmsitz zwischen der Spitze (10) und der Aufnahme (8) befestigt ist.Burner according to claim 2,
characterized in that it comprises a tip (10) adjacent to the support structure (6), the receptacle (8) and the heat shield (18), and the heat shield (18) is secured by a clamping fit between the tip (10) and the receptacle (8 ) is attached. Brenner nach Anspruch 3,
dadurch gekennzeichnet, dass der Hitzeschild (18) einen Bund (22) aufweist.Burner according to claim 3,
characterized in that the heat shield (18) has a collar (22). Brenner nach Anspruch 3 oder 4,
dadurch gekennzeichnet, dass die Spitze (10) mit der Aufnahme (8) verschraubt ist.Burner according to claim 3 or 4,
characterized in that the tip (10) with the receptacle (8) is screwed. Brenner nach einem der Ansprüche 3 bis 5,
dadurch gekennzeichnet, dass die Spitze (10) mit der Aufnahme (8) verkrimpt ist.Burner according to one of claims 3 to 5,
characterized in that the tip (10) is crimped with the receptacle (8). Brenner nach einem der vorangegangenen Ansprüche,
dadurch gekennzeichnet, dass der Hitzeschild (18) rohrförmig ist.Burner according to one of the preceding claims,
characterized in that the heat shield (18) is tubular. Brenner nach einem der vorangegangenen Ansprüche,
dadurch gekennzeichnet, dass er einen Swirler (4) aufweist und die Tragstruktur (6) im Zentrum des Swirlers (4) angeordnet ist.Burner according to one of the preceding claims,
characterized in that it comprises a Swirler (4) and the support structure (6) in the center of the Swirlers (4) is arranged. Gasturbine mit einem Brenner nach einem der vorangegangenen Ansprüche.Gas turbine with a burner according to one of the preceding claims.
EP06026685A 2006-12-22 2006-12-22 Gas turbine burner Withdrawn EP1936276A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP06026685A EP1936276A1 (en) 2006-12-22 2006-12-22 Gas turbine burner
US12/520,134 US8869534B2 (en) 2006-12-22 2007-12-20 Burner for a gas turbine
PCT/EP2007/064338 WO2008077882A1 (en) 2006-12-22 2007-12-20 Burner for a gas turbine
EP07857958.8A EP2092245B1 (en) 2006-12-22 2007-12-20 Burner for a gas turbine with fuel supply heat shield
JP2009542067A JP5047309B2 (en) 2006-12-22 2007-12-20 Burner in gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06026685A EP1936276A1 (en) 2006-12-22 2006-12-22 Gas turbine burner

Publications (1)

Publication Number Publication Date
EP1936276A1 true EP1936276A1 (en) 2008-06-25

Family

ID=38038921

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06026685A Withdrawn EP1936276A1 (en) 2006-12-22 2006-12-22 Gas turbine burner
EP07857958.8A Active EP2092245B1 (en) 2006-12-22 2007-12-20 Burner for a gas turbine with fuel supply heat shield

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07857958.8A Active EP2092245B1 (en) 2006-12-22 2007-12-20 Burner for a gas turbine with fuel supply heat shield

Country Status (4)

Country Link
US (1) US8869534B2 (en)
EP (2) EP1936276A1 (en)
JP (1) JP5047309B2 (en)
WO (1) WO2008077882A1 (en)

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EP3096082A1 (en) * 2015-05-21 2016-11-23 Doosan Heavy Industries & Construction Co., Ltd. Fuel supply nozzle with detachable cap for minimizing burn damage
EP3247944B1 (en) * 2015-01-22 2020-04-01 Siemens Aktiengesellschaft Combustor inlet mixing system with swirler vanes having slots

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Also Published As

Publication number Publication date
US20100170267A1 (en) 2010-07-08
EP2092245A1 (en) 2009-08-26
JP2010513838A (en) 2010-04-30
US8869534B2 (en) 2014-10-28
JP5047309B2 (en) 2012-10-10
WO2008077882A1 (en) 2008-07-03
EP2092245B1 (en) 2016-11-16

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