[go: up one dir, main page]

EP2609368A1 - Burner arrangement - Google Patents

Burner arrangement

Info

Publication number
EP2609368A1
EP2609368A1 EP11745767.1A EP11745767A EP2609368A1 EP 2609368 A1 EP2609368 A1 EP 2609368A1 EP 11745767 A EP11745767 A EP 11745767A EP 2609368 A1 EP2609368 A1 EP 2609368A1
Authority
EP
European Patent Office
Prior art keywords
burner
burners
fuel
arrangement according
burner arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
EP11745767.1A
Other languages
German (de)
French (fr)
Inventor
Matthias Hase
Jürgen MEISL
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP11745767.1A priority Critical patent/EP2609368A1/en
Publication of EP2609368A1 publication Critical patent/EP2609368A1/en
Ceased legal-status Critical Current

Links

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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C5/00—Disposition of burners with respect to the combustion chamber or to one another; Mounting of burners in combustion apparatus
    • F23C5/08—Disposition of burners
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/12—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour characterised by the shape or arrangement of the outlets from the nozzle
    • 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
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • 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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/06042—Annular arrangement of burners in a furnace, e.g. in a gas turbine, operated in alternate lean-rich mode
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11002—Liquid fuel burners with more than one nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the present invention relates to a burner assembly according to the preamble of claim 1.
  • the combustion chamber is supplied with compressed air from the compressor.
  • the compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber.
  • the hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.
  • a burner assembly has a carrier with at least two burners, which are mounted in the flow direction on the carrier.
  • Each burner comprises a cylindrical housin ⁇ se with a centrally disposed therein, a fuel channel having lance which is supported via helical blades on the housing.
  • an attachment is arranged on the leading to a combustion chamber side, wherein at least one fuel nozzle in the attachment preferably downstream of the swirl ⁇ blades arranged and connected to the fuel channel.
  • the oil nozzles can not be arranged so that the Ver ⁇ mixture of the fuel with the air leads to an optimal result in terms of pressure pulsations.
  • the object of the present invention is therefore to provide a burner assembly which solves the above problem.
  • such a burner arrangement comprising at least two fuel nozzles of the at least two burners on a different operating characteristics and / or spray ⁇ form.
  • Such smearing is understood to mean effects such as widening the flame zone, avoiding symmetrical structures and creating zones with different temperatures. This leads to an improved thermoacoustic behavior.
  • Fig. 1 shows schematically a section through a single burner of a burner assembly according to the invention.
  • Fig. 2 shows a fuel distribution of a first burner assembly according to the invention with eight burners.
  • Fig. 3 shows a fuel distribution of a second burner assembly according to the invention with eight burners.
  • Fig. 4 shows a fuel distribution of a third burner assembly according to the invention with eight burners.
  • Fig. 1 shows a single burner 2 such a burner assembly according to the invention.
  • twist scoops ⁇ feln 4 are arranged around a lance around.
  • the swirl vanes 4 are arranged in the housing 12 along the circumference of the lance.
  • a compressor air flow 7 in the leading to a combustion chamber (not shown) leading part of the burner 2 is passed.
  • the air is displaced by the swirl blades 4 in a swirling motion.
  • the lance also comprises a fuel channel 3.
  • the burner 2 further comprises an attachment 10 on the side leading to the combustion chamber.
  • the attachment 10 can be welded, screwed or directly cast with the lance, for example.
  • the mostly several Brennstoffdü- sen 1 are described in the article 10 preferably downstream from the helical ⁇ blades 4 arranged and are in the process illustrated in flow communication with the fuel passageway 3 to herein as oil passage verbun ⁇ .
  • eight such burners 2 are arranged circularly on a support (not shown).
  • the burners 2 are arranged around a pilot burner (not shown) with pilot cone.
  • the swirl blades 4 and additional fuel nozzles which are not shown here, however, have.
  • the at least two burners 2 have internal invention ⁇ nozzles 1 onto each having a different family of functions file ⁇ rintegrating and / or spray form.
  • three or more burners 2 may have fuel nozzles 1 according to the invention with a respectively different functional characteristic and / or spray shape.
  • the number of burners 2 and the number of fuel nozzles 1, each with different functional characteristics and / or spray shape is therefore not fixed.
  • the functional characteristic of a fuel nozzle 1 is characterized at least by the nozzle size, the jet angle, the liq ⁇ stechniksver notorious and the Zerstäubungs characterizing.
  • the nozzle size essentially defines the
  • the atomization encompasses at least the Tröpf ⁇ size distribution. For example, simple ones
  • Pressure atomizers, swirl nozzles, or air-protected atomizers can be used. It is also possible to distinguish between the spray form, so that the fuel nozzles 1 can, for example, form a full jet, hollow cone jet, a full cone jet or a flat jet. Other spray forms are possible. Due to the different functional characteristics and / or spray shape, the fuel nozzles 1 of the respective burners 2 have a different distribution and penetration behavior of the fuel into the compressor air flow 7. For example, a significantly wider penetration of the fuel into the airflow 7 may result in a narrower distribution of the fuel around the periphery of the attachment 10. The different distribution and penetration behavior leads to a different stabilization of the flame zone of the respective burners 2. This results in a smearing of the combustion zones in the entire combustion system. The amount of energy available for feedback at a given frequency is thus reduced and falls below a critical limit. This leads to an improved thermoacoustic behavior.
  • FIG. 2 shows a fuel distribution of a first burner assembly according to the invention with eight burners 2a, 2b from the front.
  • the invention is not limited to eight burners 2a, 2b and a different number of burners is possible.
  • the burner 2a fuel nozzles 1 (Fig.l) with a functional characteristic and spray shape, which cause a mean radial penetration depth and a wide fuel ⁇ fuel distribution around the top 10 around.
  • the burner 2a therefore has a wide fuel distribution ring 19a the essay 10 around.
  • the fuel distribution ring 19a has a large radial distance from the attachment 10.
  • the burner 2b on the other hand have fuel nozzles 1 (Fig. 1) having a function characteristic and spray form on which cause a very small radial depth of penetration and a narrow fuel ⁇ distribution around the attachment 10 around.
  • the burner 2b therefore has a narrow fuel distribution ring 19b around the attachment 10 around.
  • the fuel distribution ring 19b also has a small radial distance from the attachment 10.
  • Fig. 2 shows a symmetrical arrangement of burners 2a, 2b.
  • the four burners 2a are arranged opposite each other with the same functional characteristics and spray form. This also applies to the burner 2b.
  • other arrangements may be possible Kings ⁇ nen.
  • Fig. 3 shows a fuel distribution of a second burner assembly according to the invention with eight burners 2a, 2b from the front.
  • the burners 2a, 2b are arranged alternately
  • FIG. 2 and FIG. 3 show burner arrangements which each have two burners 2a, 2b with a different functional characteristic and / or spray form in the fuel nozzles 1 (FIG. 1). However, several burners 2 with different functional characteristics and / or spray form may be present in the fuel nozzles 1 (FIG. 1) in such a burner arrangement.
  • Fig. 4 shows a fuel distribution of a third burner assembly according to the invention with eight burners 2a, 2b from the front.
  • six burners 2a have fuel nozzles 1 (FIG. 1) with the same functional characteristic and spray shape
  • the two other burners 2b have fuel nozzles (FIG. 1) with a different functional characteristic and / or spray shape.
  • Thejanscharak is terumbling and spray shape of the fuel nozzles 1 of the burner 2b, however, equal to each other. This corresponds to an asymmetrical arrangement of burners 2a, 2b. Under thermoacoustic point of view, such a non-symmetrical arrangement in particular ⁇ sondere advantageous to prevent circumferential modes in the entire Brennersys ⁇ tem.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

The invention relates to a burner arrangement having a carrier, at least two burners (2, 2a, 2b) mounted on the carrier in the direction of flow, wherein each burner (2, 2a, 2b) comprises a cylindrical housing (12) having a lance centrally disposed therein and comprising a fuel channel (3) and supported on the housing (12) by means of swirl blades (4), and wherein a cap (10) is disposed on the side leading to a combustion chamber, wherein at least one fuel nozzle (1) is disposed in the cap (10) preferably downstream of the swirl blades (4) and is connected to the fuel channel (3), wherein the at least two fuel nozzles (1) of the at least two burners (2, 2a, 2b) comprise different functional characteristics and/or spray shapes.

Description

Beschreibung Brenneranordnung Description Burner arrangement

Die vorliegende Erfindung betrifft eine Brenneranordnung nach dem Oberbegriff des Anspruchs 1. The present invention relates to a burner assembly according to the preamble of claim 1.

Im Betrieb der Gasturbine wird der Brennkammer verdichtete Luft aus dem Verdichter zugeführt. Die verdichtete Luft wird mit einem Brennstoff, beispielsweise Öl oder Gas, vermischt und das Gemisch in der Brennkammer verbrannt. Die heißen Verbrennungsabgase werden schließlich als Arbeitsmedium über einen Brennkammerausgang der Turbine zugeführt, wo sie unter Entspannung und Abkühlung Impuls auf die Laufschaufeln übertragen und so Arbeit leisten. During operation of the gas turbine, the combustion chamber is supplied with compressed air from the compressor. The compressed air is mixed with a fuel, such as oil or gas, and the mixture burned in the combustion chamber. The hot combustion exhaust gases are finally supplied as a working medium via a combustion chamber outlet of the turbine, where they transmit momentum to the blades under relaxation and cooling and thus do work.

Eine Brenneranordnung weist einen Träger mit mindestens zwei Brennern auf, welche in Strömungsrichtung an dem Träger montiert sind. Jeder Brenner umfasst ein zylinderförmiges Gehäu¬ se mit einer darin zentral angeordneten, einen Brennstoffkanal aufweisende Lanze, welche über Drallschaufeln am Gehäuse abgestützt ist. Dabei ist an der zu einer Brennkammer hinführenden Seite ein Aufsatz angeordnet, wobei mindestens eine Brennstoffdüse in dem Aufsatz vorzugsweise stromab der Drall¬ schaufeln angeordnet und mit dem Brennstoffkanal verbunden ist. Bei Gasturbinen, insbesondere solchen, die mit zwei ver¬ schiedenen Brennstoffen betrieben werden, erfolgt beispielsweise eine Eindüsung des Brennstoffes Öl im Bereich von A burner assembly has a carrier with at least two burners, which are mounted in the flow direction on the carrier. Each burner comprises a cylindrical housin ¬ se with a centrally disposed therein, a fuel channel having lance which is supported via helical blades on the housing. In this case, an attachment is arranged on the leading to a combustion chamber side, wherein at least one fuel nozzle in the attachment preferably downstream of the swirl ¬ blades arranged and connected to the fuel channel. In gas turbines, which are operated with two different fuels ver ¬ especially those which takes place for example, a injection of the fuel oil in the range of

Drallerzeugern, in denen das Öl mit Luft vermischt wird. Zur besseren Vermischung von Öl und Luft wird das Öl innerhalb der zur Eindüsung verwendeten Düsen in eine Drallbewegung versetzt. Diese Öldüse wird auch als Druck-Drall-Düse be¬ zeichnet . Swirl generators in which the oil is mixed with air. For better mixing of oil and air, the oil within the nozzles used for the injection into a swirling motion is added. This oil nozzle is also called pressure-swirl nozzle be ¬ draws.

Gerade bei Gasturbinen mit zwei verschiedenen Brennstoffen können die Öldüsen nicht so angeordnet werden, dass die Ver¬ mischung des Brennstoffs mit der Luft zu einem optimalen Ergebnis hinsichtlich der Druckpulsationen führt. Die Aufgabe der vorliegenden Erfindung ist daher die Angabe einer Brenneranordnung, welche das obige Problem löst. Especially in gas turbines with two different fuels, the oil nozzles can not be arranged so that the Ver ¬ mixture of the fuel with the air leads to an optimal result in terms of pressure pulsations. The object of the present invention is therefore to provide a burner assembly which solves the above problem.

Die Aufgabe wird gelöst durch eine Brenneranordnung nach Anspruch 1. Die weiteren Unteransprüche enthalten vorteilhafte Ausgestaltungen der Erfindung. The object is achieved by a burner assembly according to claim 1. The other subclaims contain advantageous embodiments of the invention.

Erfindungsgemäß weisen bei solch einer Brenneranordnung die mindestens zwei Brennstoffdüsen der mindestens zwei Brenner eine unterschiedliche Funktionscharakteristik und/oder Sprüh¬ form auf. Dadurch ergibt sich, in Bezug auf den jeweiligen Brenner, ein unterschiedliches Eindringverhalten des durch die Brennstoffdüsen eingedüsten Brennstoffs in z.B. die Verdichterluft. Dies hat zur Folge, dass die Flammenzone der je¬ weiligen Brenner einen unterschiedlichen Stabilisierungspunkt aufweist und somit auch unterschiedlich stabilisiert wird. Bezogen auf das gesamte Verbrennungssystem ergibt sich damit eine Verschmierung der Verbrennungszonen. Dabei versteht man unter einer solchen Verschmierung Effekte, wie z.B. Verbreiterung der Flammenzone, Vermeiden von symmetrischen Strukturen und Erzeugung von Zonen mit unterschiedlicher Temperatur. Dies führt zu einem verbesserten thermoakustischen Verhalten. According to the invention in such a burner arrangement comprising at least two fuel nozzles of the at least two burners on a different operating characteristics and / or spray ¬ form. This results, with respect to the respective burner, a different penetration behavior of the fuel injected by the fuel nozzles in, for example, the compressor air. This has the consequence that the flame zone of the burner depending ¬ weiligen having a different stabilization point and is thus stabilized also different. Based on the entire combustion system, this results in a smearing of the combustion zones. Such smearing is understood to mean effects such as widening the flame zone, avoiding symmetrical structures and creating zones with different temperatures. This leads to an improved thermoacoustic behavior.

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 hier¬ bei einzeln oder in Kombination miteinander vorteilhaft sein. Further advantages, features and characteristics of the present invention will be described in more detail below on the basis of exemplary embodiments with reference to the attached figures. The features of the exemplary embodiments can be advantageous here individually or in combination with one another.

Fig. 1 zeigt schematisch einen Schnitt durch einen einzelnen Brenner einer erfindungsgemäßen Brenneranordnung . Fig. 1 shows schematically a section through a single burner of a burner assembly according to the invention.

Fig. 2 zeigt eine Brennstoffverteilung einer ersten erfindungsgemäßen Brenneranordnung mit acht Brennern. Fig. 2 shows a fuel distribution of a first burner assembly according to the invention with eight burners.

Fig. 3 zeigt eine Brennstoffverteilung einer zweiten erfindungsgemäßen Brenneranordnung mit acht Brennern. Fig. 4 zeigt eine Brennstoffverteilung einer dritten erfindungsgemäßen Brenneranordnung mit acht Brennern. Fig. 3 shows a fuel distribution of a second burner assembly according to the invention with eight burners. Fig. 4 shows a fuel distribution of a third burner assembly according to the invention with eight burners.

Fig. 1 zeigt einen einzelnen Brenner 2 solch einer erfindungsgemäßen Brenneranordnung. In dem Gehäuse 12 des erfindungsgemäßen Brenners 2 sind um eine Lanze herum Drallschau¬ feln 4 angeordnet. Die Drallschaufeln 4 sind entlang des Um- fanges der Lanze in dem Gehäuse 12 angeordnet. Durch die Drallschaufeln 4 wird ein Verdichterluftstrom 7 in den zu einer Brennkammer (nicht gezeigt) führenden Teil des Brenners 2 geleitet. Die Luft wird durch die Drallschaufeln 4 in eine Drallbewegung versetzt. Die Lanze umfasst zudem einen Brennstoffkanal 3. Der Brenner 2 umfasst weiterhin einen an der zu der Brennkammer hinführenden Seite einen Aufsatz 10. Der Aufsatz 10 kann z.B. mit der Lanze verschweißt, verschraubt oder direkt mitangegossen sein. Die zumeist mehreren Brennstoffdü- sen 1 sind in dem Aufsatz 10 vorzugsweise stromab der Drall¬ schaufeln 4 angeordnet und sind dabei strömungstechnisch mit dem Brennstoffkanal 3, hier als Ölkanal dargestellt, verbun¬ den. Bevorzugt sind acht solcher Brenner 2 kreisrund an einem Träger angeordnet (nicht gezeigt) . Dabei werden die Brenner 2 um einen (nicht gezeigten) Pilotbrenner mit Pilotkonus angeordnet. Zudem können die Drallschaufeln 4 auch zusätzliche Brennstoffdüsen, welche hier jedoch nicht dargestellt sind, aufweisen . Fig. 1 shows a single burner 2 such a burner assembly according to the invention. In the housing 12 of the burner 2 according to the invention twist scoops ¬ feln 4 are arranged around a lance around. The swirl vanes 4 are arranged in the housing 12 along the circumference of the lance. Through the swirl vanes 4, a compressor air flow 7 in the leading to a combustion chamber (not shown) leading part of the burner 2 is passed. The air is displaced by the swirl blades 4 in a swirling motion. The lance also comprises a fuel channel 3. The burner 2 further comprises an attachment 10 on the side leading to the combustion chamber. The attachment 10 can be welded, screwed or directly cast with the lance, for example. The mostly several Brennstoffdü- sen 1 are described in the article 10 preferably downstream from the helical ¬ blades 4 arranged and are in the process illustrated in flow communication with the fuel passageway 3 to herein as oil passage verbun ¬. Preferably, eight such burners 2 are arranged circularly on a support (not shown). The burners 2 are arranged around a pilot burner (not shown) with pilot cone. In addition, the swirl blades 4 and additional fuel nozzles, which are not shown here, however, have.

Die zumindest zwei Brenner 2 weisen erfindungsgemäße Brenn¬ stoffdüsen 1 mit jeweils unterschiedlicher Funktionscharakte¬ ristik und/oder Sprühform auf. Dies bedeutet, dass die Brennstoffdüsen 1 des einen Brenners 2 sich hinsichtlich ihrer Funktionscharakteristik und/oder ihrer Sprühform von den Brennstoffdüsen 1 des anderen Brenners 2 unterscheiden. Alternativ können auch drei oder mehrere Brenner 2 erfindungsgemäße Brennstoffdüsen 1 mit einer jeweils unterschiedlichen Funktionscharakteristik und/oder Sprühform aufweisen. Die Anzahl der Brenner 2 sowie die Anzahl der Brennstoffdüsen 1 mit jeweils unterschiedlicher Funktionscharakteristik und/oder Sprühform ist daher nicht festgelegt. Die Funktionscharakteristik einer Brennstoffdüse 1 ist dabei zumindest durch die Düsengröße, den Strahlwinkel, die Flüs¬ sigkeitsverteilung und die Zerstäubungscharakteristik gekennzeichnet. Dabei legt die Düsengröße im Wesentlichen den The at least two burners 2 have internal invention ¬ nozzles 1 onto each having a different family of functions file ¬ ristik and / or spray form. This means that the fuel nozzles 1 of the one burner 2 differ from the fuel nozzles 1 of the other burner 2 with regard to their functional characteristics and / or their spray form. Alternatively, three or more burners 2 may have fuel nozzles 1 according to the invention with a respectively different functional characteristic and / or spray shape. The number of burners 2 and the number of fuel nozzles 1, each with different functional characteristics and / or spray shape is therefore not fixed. The functional characteristic of a fuel nozzle 1 is characterized at least by the nozzle size, the jet angle, the liq ¬ sigkeitsverteilung and the Zerstäubungscharakteristik. The nozzle size essentially defines the

Brennstoffmassenstrom bei gegebener Druckdifferenz fest. Die Zerstäubungscharakteristik umfasst dabei zumindest die Tröpf¬ chengrößenverteilung. So können beispielsweise einfache Fuel mass flow at a given pressure difference fixed. The atomization encompasses at least the Tröpf ¬ size distribution. For example, simple ones

Druckzerstäuber, Dralldüsen, oder luftgeschützte Zerstäuber verwendet werden. Auch bei der Sprühform kann unterschieden werden, so können die Brennstoffdüsen 1 beispielsweise einen Vollstrahl, Hohlkegelstrahl, einen Vollkegelstrahl oder einen Flachstrahl ausbilden. Auch andere Sprühformen sind möglich. Die Brennstoffdüsen 1 der jeweiligen Brenner 2 weisen durch die unterschiedliche Funktionscharakteristik und/oder Sprüh- form ein unterschiedliches Verteilungs- und Eindringverhalten des Brennstoffs in den Verdichterluftstrom 7 auf. So kann zum Beispiel eine deutlich weitere Eindringtiefe des Brennstoffs in die Luftströmung 7 eine engere Verteilung des Brennstoffs um den Umfang des Aufsatzes 10 zur Folge haben. Das unter- schiedliche Verteilungs- und Eindringverhalten führt zu einer unterschiedlichen Stabilisierung der Flammenzone der jeweiligen Brenner 2. Dadurch ergibt sich eine Verschmierung der Verbrennungszonen im gesamten Verbrennungssystem. Die jeweils für eine Rückkopplung bei einer bestimmten Frequenz zur Ver- fügung stehende Energiemenge wird somit verringert und sinkt unter eine kritische Grenze. Dies führt zu einem verbesserten thermoakustischen Verhalten. Pressure atomizers, swirl nozzles, or air-protected atomizers can be used. It is also possible to distinguish between the spray form, so that the fuel nozzles 1 can, for example, form a full jet, hollow cone jet, a full cone jet or a flat jet. Other spray forms are possible. Due to the different functional characteristics and / or spray shape, the fuel nozzles 1 of the respective burners 2 have a different distribution and penetration behavior of the fuel into the compressor air flow 7. For example, a significantly wider penetration of the fuel into the airflow 7 may result in a narrower distribution of the fuel around the periphery of the attachment 10. The different distribution and penetration behavior leads to a different stabilization of the flame zone of the respective burners 2. This results in a smearing of the combustion zones in the entire combustion system. The amount of energy available for feedback at a given frequency is thus reduced and falls below a critical limit. This leads to an improved thermoacoustic behavior.

Fig. 2 zeigt eine Brennstoffverteilung einer ersten erfin- dungsgemäßen Brenneranordnung mit acht Brennern 2a, 2b von vorne. Die Erfindung ist jedoch nicht eingeschränkt auf acht Brenner 2a, 2b auch eine andere Anzahl von Brennern ist möglich. So weisen hier die Brenner 2a Brennstoffdüsen 1 (Fig.l) mit einer Funktionscharakteristik und Sprühform auf, welche eine mittlere radiale Eindringtiefe und eine breite Brenn¬ stoffverteilung um den Aufsatz 10 herum bewirken. Der Brenner 2a weist daher einen breiten Brennstoffverteilungsring 19a um den Aufsatz 10 herum auf. Der Brennstoffverteilungsring 19a weist von dem Aufsatz 10 einen großen radialen Abstand auf. FIG. 2 shows a fuel distribution of a first burner assembly according to the invention with eight burners 2a, 2b from the front. However, the invention is not limited to eight burners 2a, 2b and a different number of burners is possible. Thus, here have the burner 2a fuel nozzles 1 (Fig.l) with a functional characteristic and spray shape, which cause a mean radial penetration depth and a wide fuel ¬ fuel distribution around the top 10 around. The burner 2a therefore has a wide fuel distribution ring 19a the essay 10 around. The fuel distribution ring 19a has a large radial distance from the attachment 10.

Die Brenner 2b hingegen weisen Brennstoffdüsen 1 (Fig. 1) mit einer Funktionscharakteristik und Sprühform auf, welche eine sehr geringe radiale Eindringtiefe und eine enge Brennstoff¬ verteilung um den Aufsatz 10 herum bewirken. Der Brenner 2b weist daher einen schmalen Brennstoffverteilungsring 19b um den Aufsatz 10 herum auf. Der Brennstoffverteilungsring 19b weist zudem von dem Aufsatz 10 einen geringen radialen Abstand auf. Fig. 2 zeigt dabei eine symmetrische Anordnung von Brennern 2a, 2b. Dabei sind die jeweils vier Brenner 2a mit gleicher Funktionscharakteristik und Sprühform gegenüberliegend angeordnet. Ebenso gilt dies für die Brenner 2b. Es kön¬ nen jedoch auch andere Anordnungen möglich sein. The burner 2b on the other hand have fuel nozzles 1 (Fig. 1) having a function characteristic and spray form on which cause a very small radial depth of penetration and a narrow fuel ¬ distribution around the attachment 10 around. The burner 2b therefore has a narrow fuel distribution ring 19b around the attachment 10 around. The fuel distribution ring 19b also has a small radial distance from the attachment 10. Fig. 2 shows a symmetrical arrangement of burners 2a, 2b. The four burners 2a are arranged opposite each other with the same functional characteristics and spray form. This also applies to the burner 2b. However, other arrangements may be possible Kings ¬ nen.

Fig. 3 zeigt eine Brennstoffverteilung einer zweiten erfindungsgemäßen Brenneranordnung mit acht Brennern 2a, 2b von vorne. Dabei sind die Brenner 2a, 2b alternierend angeordnet Fig. 3 shows a fuel distribution of a second burner assembly according to the invention with eight burners 2a, 2b from the front. The burners 2a, 2b are arranged alternately

Fig. 2 und Fig. 3 sind Brenneranordnungen gezeigt, die jeweils zwei Brenner 2a, 2b mit einer unterschiedlichen Funktionscharakteristik und/oder Sprühform bei den Brennstoffdüsen 1 (Fig. 1) aufweisen. Es können jedoch noch mehrere Brenner 2 mit unterschiedlicher Funktionscharakteristik und/oder Sprühform bei den Brennstoffdüsen 1 (Fig. 1) in einer solchen Brenneranordnung vorhanden sein. FIG. 2 and FIG. 3 show burner arrangements which each have two burners 2a, 2b with a different functional characteristic and / or spray form in the fuel nozzles 1 (FIG. 1). However, several burners 2 with different functional characteristics and / or spray form may be present in the fuel nozzles 1 (FIG. 1) in such a burner arrangement.

Fig. 4 zeigt eine Brennstoffverteilung einer dritten erfindungsgemäßen Brenneranordnung mit acht Brennern 2a, 2b von vorne. Dabei weisen sechs Brenner 2a Brennstoffdüsen 1 (Fig. 1) mit gleicher Funktionscharakteristik und Sprühform auf, die zwei anderen Brenner 2b hingegen weisen Brennstoffdüsen (Fig. 1) mit einer dazu unterschiedlichen Funktionscharakteristik und/oder Sprühform auf. Dabei ist die Funktionscharak teristik und Sprühform der Brennstoffdüsen 1 der Brenner 2b jedoch untereinander gleich. Dies entspricht einer unsymmetrischen Anordnung von Brennern 2a, 2b. Unter thermoakusti- scher Sicht ist eine solche unsymmetrische Anordnung insbe¬ sondere vorteilhaft, um Umfangsmoden im gesamten Brennersys¬ tem zu unterbinden. Fig. 4 shows a fuel distribution of a third burner assembly according to the invention with eight burners 2a, 2b from the front. In this case, six burners 2a have fuel nozzles 1 (FIG. 1) with the same functional characteristic and spray shape, while the two other burners 2b have fuel nozzles (FIG. 1) with a different functional characteristic and / or spray shape. The Funktionscharak is teristik and spray shape of the fuel nozzles 1 of the burner 2b, however, equal to each other. This corresponds to an asymmetrical arrangement of burners 2a, 2b. Under thermoacoustic point of view, such a non-symmetrical arrangement in particular ¬ sondere advantageous to prevent circumferential modes in the entire Brennersys ¬ tem.

Claims

Patentansprüche claims 1. Brenneranordnung mit 1. Burner arrangement with - einem Träger , a carrier, - mindestens zwei Brennern (2, 2a, 2b) welche in Strömungs¬ richtung an dem Träger montiert sind, - at least two burners (2, 2a, 2b) which are mounted in flow ¬ direction to the support, wobei jeder Brenner (2, 2a, 2b) ein zylinderförmiges Gehäuse (12) mit einer darin zentral angeordneten, einen Brennstoffkanal (3) aufweisende Lanze umfasst, welche über Drallschau- fein (4) am Gehäuse (12) abgestützt ist und wobei an der zu einer Brennkammer hinführenden Seite ein Aufsatz (10) angeordnet ist, wobei mindestens eine Brennstoffdüse (1) in dem Aufsatz (10) vorzugsweise stromab der Drallschaufeln (4) angeordnet und mit dem Brennstoffkanal (3) verbunden ist, d a d u r c h g e k e n n z e i c h n e t, d a s s die min¬ destens zwei Brennstoffdüsen (1) der mindestens zwei Brenner (2, 2a, 2b) eine unterschiedliche Funktionscharakteristik und/oder Sprühform aufweisen. wherein each burner (2, 2a, 2b) comprises a cylindrical housing (12) with a centrally disposed therein, a fuel channel (3) having lance, which is supported on spin view (4) on the housing (12) and wherein at the an attachment (10) is arranged to a combustion chamber side, wherein at least one fuel nozzle (1) in the attachment (10) preferably downstream of the swirl vanes (4) and connected to the fuel channel (3), characterized in that the min ¬ at least two fuel nozzles (1) of the at least two burners (2, 2a, 2b) have a different functional characteristic and / or spray shape. 2. Brenneranordnung nach Anspruch 1, 2. Burner arrangement according to claim 1, d a d u r c h g e k e n n z e i c h n e t, d a s s die Brennstoffdüsen (1) mit unterschiedlicher Funktionscharakteristik sich zumindest durch eine Düsengröße oder einen The fuel nozzles (1) with different functional characteristics are at least one nozzle size or one another Strahlwinkel oder eine Flüssigkeitsverteilung oder eine Zer- stäubungscharakteristik voneinander unterscheiden. Beam angle or a liquid distribution or a Zerustäubungscharakteristik differ from each other. 3. Brenneranordnung nach einem der vorhergehenden Ansprüche 1 oder 2, 3. Burner arrangement according to one of the preceding claims 1 or 2, d a d u r c h g e k e n n z e i c h n e t, d a s s bei un- terschiedlicher Zerstäubungscharakteristik der Brennstoffdüsen sich zumindest die Tröpfchengrößenverteilung voneinander unterscheidet . In the case of different atomization characteristics of the fuel nozzles, at least the droplet size distribution differs from one another. 4. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , d a s s die4. burner arrangement according to one of the preceding claims, d a d u c h e c e n e c i n e t, d a s s the Brennstoffdüsen mit unterschiedlicher Sprühform einen Vollstrahl, Hohlkegelstrahl, einen Vollkegelstrahl oder einen Flachstrahl ausbilden. Form fuel nozzles with different spray shape a full jet, hollow cone jet, a full cone jet or a flat jet. 5. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , d a s s die mindestens zwei Brennstoffdüsen (1) der mindestens zwei Bren¬ ner (2, 2a, 2b) mit unterschiedlicher Funktionscharakteristik und/oder Sprühform mindestens eine Vollstrahldüse und mindes¬ tens eine Druck-Drall-Düse umfassen. 5. Burner arrangement according to one of the preceding claims, characterized in that the at least two fuel nozzles (1) of the at least two Bren ¬ ner (2, 2a, 2b) with different functional characteristic and / or spray form at least one full jet and Minim ¬ least a pressure-swirl Include nozzle. 6. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, d a s s die 6. Burner arrangement according to one of the preceding claims, d a d u c h e c e n c i n e s, d a s s Brennstoffdüsen (1) Öldüsen sind. Fuel nozzles (1) are oil nozzles. 7. Brenneranordnung nach einem der vorhergehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t, d a s s eine ge¬ rade Anzahl von Brennern (2a, 2b) vorgesehen ist, welche ringförmig auf dem Träger angebracht sind. 7. Burner arrangement according to one of the preceding claims, characterized in that a ge ¬ rade number of burners (2 a, 2 b) is provided, which are annularly mounted on the carrier. 8. Brenneranordnung nach Anspruch 7, 8. burner assembly according to claim 7, d a d u r c h g e k e n n z e i c h n e t, d a s s acht, zehn oder zwölf Brenner (2a, 2b) vorgesehen sind. There are eight, ten, or twelve burners (2a, 2b). 9. Brenneranordnung nach Anspruch 7 oder 8, 9. Burner arrangement according to claim 7 or 8, d a d u r c h g e k e n n z e i c h n e t, d a s s mindes¬ tens vier Brenner (2a, 2b) vorgesehen sind, wobei alle sich gegenüberliegende Brenner (2a, 2b) Brennstoffdüsen (1) mit gleicher Funktionscharakteristik und Sprühform aufweisen. characterized in that Minim ¬ least four burners (2a, 2b) are provided, wherein all the opposing burner (2a, 2b) fuel nozzle (1) having the same function characteristic and spray form. 10. Brenneranordnung nach Anspruch 7 oder 8, 10. Burner arrangement according to claim 7 or 8, d a d u r c h g e k e n n z e i c h n e t, d a s s mindes¬ tens vier Brenner (2a, 2b) vorgesehen sind, wobei zumindest zwei sich gegenüberliegende Brenner (2a, 2b) Brennstoffdüsen (1) aufweisen, welche unterschiedliche Funktionscharakteris¬ tik und/oder Sprühform aufweisen. characterized in that Minim ¬ least four burners (2a, 2b) are provided, wherein at least two opposite burner (2a, 2b) fuel nozzles (1) which have different Funktionscharakteris ¬ tik and / or spray form. 11. Brenneranordnung nach einem der Ansprüche 1 bis 6, d a d u r c h g e k e n n z e i c h n e t, d a s s eine un¬ gerade Anzahl von Brennern (2a, 2b) vorgesehen ist. 11. Burner arrangement according to one of claims 1 to 6, characterized in that an un ¬ even number of burners (2a, 2b) is provided.
EP11745767.1A 2010-08-27 2011-08-16 Burner arrangement Ceased EP2609368A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11745767.1A EP2609368A1 (en) 2010-08-27 2011-08-16 Burner arrangement

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10174338A EP2423589A1 (en) 2010-08-27 2010-08-27 Burner assembly
PCT/EP2011/064072 WO2012025427A1 (en) 2010-08-27 2011-08-16 Burner arrangement
EP11745767.1A EP2609368A1 (en) 2010-08-27 2011-08-16 Burner arrangement

Publications (1)

Publication Number Publication Date
EP2609368A1 true EP2609368A1 (en) 2013-07-03

Family

ID=43479478

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10174338A Withdrawn EP2423589A1 (en) 2010-08-27 2010-08-27 Burner assembly
EP11745767.1A Ceased EP2609368A1 (en) 2010-08-27 2011-08-16 Burner arrangement

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10174338A Withdrawn EP2423589A1 (en) 2010-08-27 2010-08-27 Burner assembly

Country Status (4)

Country Link
US (1) US20130180251A1 (en)
EP (2) EP2423589A1 (en)
JP (1) JP5606628B2 (en)
WO (1) WO2012025427A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5458121B2 (en) * 2012-01-27 2014-04-02 株式会社日立製作所 Gas turbine combustor and method of operating gas turbine combustor
JP6021705B2 (en) * 2013-03-22 2016-11-09 三菱重工業株式会社 Combustor and gas turbine
JP5984770B2 (en) * 2013-09-27 2016-09-06 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
DE112015001975A5 (en) * 2014-09-12 2017-02-09 Siemens Aktiengesellschaft Burner for a gas turbine and gas turbine
US10775043B2 (en) 2014-10-06 2020-09-15 Siemens Aktiengesellschaft Combustor and method for damping vibrational modes under high-frequency combustion dynamics
US20190056108A1 (en) * 2017-08-21 2019-02-21 General Electric Company Non-uniform mixer for combustion dynamics attenuation
CN110056863B (en) * 2019-04-30 2024-08-23 恩平市景业陶瓷有限公司 Combustion device for coal tar

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999063268A1 (en) * 1998-06-04 1999-12-09 Siemens Aktiengesellschaft Fuel injector
JP2003090535A (en) * 2001-09-17 2003-03-28 Ishikawajima Harima Heavy Ind Co Ltd Gas turbine combustor

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
JPH05203148A (en) * 1992-01-13 1993-08-10 Hitachi Ltd Gas turbine combustion apparatus and its control method
US5309710A (en) * 1992-11-20 1994-05-10 General Electric Company Gas turbine combustor having poppet valves for air distribution control
DE19615910B4 (en) * 1996-04-22 2006-09-14 Alstom burner arrangement
WO1998012478A1 (en) * 1996-09-16 1998-03-26 Siemens Aktiengesellschaft Method and device for fuel combustion with air
JP4127858B2 (en) * 1996-12-20 2008-07-30 シーメンス アクチエンゲゼルシヤフト Burner for liquid fuel
EP0911583B1 (en) * 1997-10-27 2003-03-12 ALSTOM (Switzerland) Ltd Method of operating a premix burner
US6269646B1 (en) * 1998-01-28 2001-08-07 General Electric Company Combustors with improved dynamics
WO2000012940A1 (en) * 1998-08-31 2000-03-09 Siemens Aktiengesellschaft Method for operating a gas turbine and corresponding gas turbine
DE19939235B4 (en) * 1999-08-18 2012-03-29 Alstom Method for producing hot gases in a combustion device and combustion device for carrying out the method
JP2001280641A (en) * 2000-03-31 2001-10-10 Mitsubishi Heavy Ind Ltd Gas turbine combustor, and method for mixing fuel and air in gas turbine combustor
DE10108560A1 (en) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Method for operating an annular combustion chamber and an associated annular combustion chamber
US6539724B2 (en) * 2001-03-30 2003-04-01 Delavan Inc Airblast fuel atomization system
JP3498142B2 (en) * 2001-08-01 2004-02-16 独立行政法人航空宇宙技術研究所 Wall collision type liquid atomization nozzle
US6931853B2 (en) * 2002-11-19 2005-08-23 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
JP2005288390A (en) * 2004-04-02 2005-10-20 Kyoritsu Gokin Co Ltd Two-fluid nozzle and spraying method
US7827797B2 (en) * 2006-09-05 2010-11-09 General Electric Company Injection assembly for a combustor
GB2454247A (en) * 2007-11-02 2009-05-06 Siemens Ag A Combustor for a Gas-Turbine Engine Has a Burner Head with Fuel Delivered at a Compound Angle

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999063268A1 (en) * 1998-06-04 1999-12-09 Siemens Aktiengesellschaft Fuel injector
JP2003090535A (en) * 2001-09-17 2003-03-28 Ishikawajima Harima Heavy Ind Co Ltd Gas turbine combustor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2012025427A1 *

Also Published As

Publication number Publication date
EP2423589A1 (en) 2012-02-29
JP2013536397A (en) 2013-09-19
JP5606628B2 (en) 2014-10-15
WO2012025427A1 (en) 2012-03-01
US20130180251A1 (en) 2013-07-18

Similar Documents

Publication Publication Date Title
EP2588805B1 (en) Burner
DE69632111T2 (en) Premix burner for a gas turbine combustion chamber with low pollutant emission
DE102018126462B4 (en) Fuel nozzle and combustion chamber and gas turbine containing them
DE69414107T2 (en) RADIAL AIR COMPRESSOR INJECTOR FOR FUEL
EP2609368A1 (en) Burner arrangement
EP3087323B1 (en) Fuel nozzle, burner having such a fuel nozzle, and gas turbine having such a burner
CH701539A2 (en) Apparatus for fuel injection in a turbine.
DE3029095A1 (en) DOUBLE FUEL INJECTOR FOR GAS TURBINE ENGINES
DE102010060281A1 (en) Premixing device for fuel injection in a gas turbine
EP2601447A2 (en) Gas turbine combustion chamber
DE112014004695T5 (en) Fuel injection device for a gas turbine
EP0924470A2 (en) Premix combustor for a gas turbine
EP2161502A1 (en) Pre-mix burner for a low calorie and high calorie fuel
EP1754002B1 (en) Staged premix burner with an injector for liquid fuel
EP2507557B1 (en) Burner assembly
EP1855054B1 (en) Method for supplying fuel to a premix burner
EP1781988B1 (en) Hybrid burner lance
CH708058A2 (en) Swirl control structure for a turbine system.
EP2864706B1 (en) Local improvement of the mixture of air and fuel in burners comprising swirl generators having blade ends that are crossed in the outer region
WO2015062962A1 (en) Gas turbine burner hub with pilot burner
EP1734306A1 (en) Burner for premix-type combustion
EP3143335A1 (en) Burner for a combustion machine and combustion machine
DE102010027808A1 (en) Swirl generator for a burner
DE3132352A1 (en) "TWO WAY FUEL NOZZLE"
EP2151630B1 (en) Swirler

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20130107

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20150327

REG Reference to a national code

Ref country code: DE

Ref legal event code: R003

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20160703