EP3250857A1 - Burner arrangement - Google Patents

Burner arrangement

Info

Publication number
EP3250857A1
EP3250857A1 EP16713412.1A EP16713412A EP3250857A1 EP 3250857 A1 EP3250857 A1 EP 3250857A1 EP 16713412 A EP16713412 A EP 16713412A EP 3250857 A1 EP3250857 A1 EP 3250857A1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
annular air
tube
nozzles
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.)
Granted
Application number
EP16713412.1A
Other languages
German (de)
French (fr)
Other versions
EP3250857B1 (en
Inventor
Andreas Böttcher
Tobias Krieger
Patrick Lapp
Andreas Mann
Simon Purschke
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
Publication of EP3250857A1 publication Critical patent/EP3250857A1/en
Application granted granted Critical
Publication of EP3250857B1 publication Critical patent/EP3250857B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/70—Baffles or like flow-disturbing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D3/00—Burners using capillary action
    • F23D3/02—Wick burners
    • F23D3/18—Details of wick burners
    • F23D3/28—Wick-adjusting devices
    • F23D3/34—Wick stop devices; Wick-fixing devices
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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
    • 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
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
    • 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

Definitions

  • the invention relates to a burner arrangement for a combustion chamber, in particular a gas turbine combustion chamber, for firing fluid fuels.
  • pilot premix burner In a burner with, for example, main premix burner and pilot premix burner, these are primarily the fuel mass flows of the main premix burner and the pilot premix burner. Depending on the setting, about 90% -95% of the fuel mass flow passes through the main premix burner, the remainder through the pilot premix burner. It is known that a change (even in the percentage range) of the pilot gas mass flow has a significant influence on emissions and buoyancy. However, such a rule by a single fuel level in Pilotvormischbrenner is be ⁇ borders.
  • both stages can be controlled independently.
  • both pilot fuel ⁇ levels can be integrated in pilot burner blades to allow for both stages, a good mixing of fuel and air.
  • Bohrungsmus ⁇ ters so the radial fuel distribution can be actively influenced during operation and thus influence on emissions and combustion stability are taken. This makes it possible to extend the corridors, through which must be maneuvered when starting and stopping the machine, and the emissi ⁇ ons- and stability behavior, especially in the partial load range, can be improved.
  • WO 2014/114533 A1 discloses a burner arrangement with a diffusion gas passage lying on the axis of the burner arrangement.
  • This passage could be ⁇ example be used by a tube-in-tube design for the fuel supply of a second stage in the pilot burner.
  • the tube-in-tube construction would then have to be relieved by a complex and therefore comparatively expensive compensator.
  • the object of the invention is therefore to provide a burner assembly of the type mentioned, which allows a beträchtli ⁇ che improvement in terms of emissions and stability and at the same time as simple and inexpensive to manufacture and assemble.
  • the invention solves this task by at a Derar ⁇ term burner assembly for a combustion chamber, in particular a gas turbine combustion chamber for firing fluidic fuels, comprising a main burner and a reasonable centrally therein arranged pilot burner, which serves to ignite and / or stabilize the combustion of the main burner, the main ⁇ burner comprising a first annular air duct for supplying combustion air and first fuel nozzles for injecting a fuel in the first annular air duct, the Pilotbren ⁇ ner comprising a second annular air duct Supply of combustion air and a burner head with second fuel ⁇ fuel nozzles for injecting a fuel in the second annular air passage, wherein the second fuel nozzles are provided as separately controllable first and second fuel stages, for supplying fuel to the first and second fuel stages,
  • the emission and stability behavior of the torch assembly is improved, and it can be dispensed with the comparatively complicated and expensive as ⁇ pipe-in-pipe construction with com- expansion joint.
  • the first and second deep hole bores are arranged at different radii relative to the longitudinal axis of the burner support tube in the pipe wall, so that
  • Fuel can be supplied directly via straight bores of a respective fuel stage.
  • the preparation of sol ⁇ cher bores is comparatively cost effective.
  • the at least one first and one second deep hole bore open into a respective fuel distributor channel of a fuel stage.
  • the number of deep hole bores can be smaller than the number of fuel nozzles per fuel stage.
  • the burner support tube has on its axis a diffusion gas passage, the also flows into the burner head, so that a Diffu ⁇ sion operation is possible.
  • the burner carrier tube is connected in the flow direction of a fuel upstream of the burner head to a carrier plate, wherein the carrier plate has fuel ring distributor, of which the at least one first and one second deep hole bore abzwei ⁇ conditions.
  • the carrier plate has fuel connections which open into the fuel ring manifolds.
  • FIG. 2 shows a known pilot burner
  • FIG. 3 shows a downstream detail of the pilot burner
  • FIG. 2 is a diagrammatic representation of FIG. 1
  • FIG. 4 shows an upstream detail of the pilot burner
  • FIG. 2 is a diagrammatic representation of FIG. 1
  • FIG. 5 shows a sectional view of the burner arrangement according to the invention, showing the inner channel
  • FIG. 6 is a sectional view of the burner assembly according to the invention showing the outer channel
  • Figure 7 is a side view of the downstream end of the
  • Burner support tube of the burner assembly Figure 8 shows a section through the support plate and outer channel of
  • FIG. 9 shows a section through carrier plate and connection for the outer channel and through the inner channel of the burner carrier tube, FIG.
  • Figure 11 is a Einschraubverbinder with through hole and radial openings in the external thread in the
  • FIG. 12 is a sectional view of a screw-in connector with a through bore and radial openings in the external thread
  • FIG. 13 shows a detailed view of the burner head with transition to the burner support tube and Figure 14 is an oblique view of the upstream side of the burner head.
  • FIG. 1 shows schematically and by way of example a section through part of a burner arrangement 1 according to the invention.
  • the burner arrangement 1 is essentially radially symmetrical about the longitudinal axis 13 and comprises a main burner 2 and a pilot burner 3 arranged centrally therein, which serves to ignite and / or stabilize the combustion of the main burner 2.
  • the main burner 2 comprises a first annular air passage 4 for supplying combustion air and first fuel nozzles 5 for injecting a fuel into the first annular air passage 4.
  • the pilot burner 3 comprises a second annular air passage 6 for supplying combustion air and second fuel nozzles 8 for injecting a fuel into the second annular air passage 6th
  • the second fuel nozzles 8 are first and second
  • Fuel stages 9, 10 are provided, each fuel stage 9, 10 has its own fuel supply.
  • the first annular air channel 4 has first swirl vanes 30, in which the first fuel nozzles 5 are arranged.
  • the second annular air channel 6 has second swirl blades 31.
  • the second fuel nozzles 8 are arranged, which, as already stated, in a first and a second fuel stage 9, 10 split.
  • Figure 2 shows a known pilot burner 32 with a central diffusion gas passage 20, in which a tube 33 is arranged, wherein between an inner wall 34 of the Diffusionsgaspas ⁇ sage 20 and a tube outer wall 35, an annular channel 36 for the Fuel supply to the second fuel stage 10 is formed.
  • This tube-in-tube construction is relieved by a compensator 37.
  • FIG. 3 shows a downstream detail of the pilot burner 3 from FIG. 2, in particular the pilot burner head 7 with the fuel supply for the first and second fuel stages 9, 10.
  • FIG. 4 shows an upstream detail of the pilot burner 3 from FIG. 2, in particular the compensator 37 of the tube in-pipe construction.
  • FIGS. 5 and 6 the pilot burner 3 according to the invention is shown in different sectional planes.
  • FIG. 5 shows the section through second deep hole bores 15, which represent the inner channel 38
  • FIG. 6 shows the corresponding view with first deep hole bores 14 for the outer channel 39.
  • the first and second deep hole bores 14, 15 are at different radii 16, 17 are arranged with respect to the longitudinal axis 13 of the burner support tube 11 in the tube wall 12.
  • FIGS. 5 and 6 show that the at least one first and one second deep hole bores 14, 15 open into a respective fuel distributor channel 18, 19 of a fuel stage 9, 10.
  • Figure 7 shows a side view of the downstream end of the burner support tube 11 of the burner assembly 1. It can be seen the ends of the first and second deep holes 14, 15 of the inner and outer channel 38, 39th
  • Figures 8, 9 and 10 show sectional detail views in the region of the support plate 21 of the pilot burner 3.
  • Figure 8 shows a section through the Trä ⁇ carrier plate 21 ler with the first and second Brennstoffringvertei- 22, 23 and the outer channel formed by deep-hole bores 14 39 in the tube wall 12 of the burner support tube eleventh
  • FIG. 9 shows a section through the carrier plate 21 with the first and second fuel ring distributors 22, 23 and the inner channel 38 formed by deep-hole bores 15 in the tube wall 12 of the burner carrier tube 11.
  • FIG. 9 shows a section through the serious fuel port 24 to the first fuel ring distributor 22 for the outer channel 39.
  • Figure 10 finally shows a section through the Trä- carrier plate 21 with the second fuel port 25 for two ⁇ th annular fuel manifold 23 for the inner channel 38. It can be seen in Figure 10 that the second fuel ⁇ ring distributor 23 relatively close to the inner channel 38 lies below the surface of the carrier plate 21.
  • the fuel connection 25 is realized via a screw-in connector 26 with a through-hole 27 and essentially radial openings 28 in the external thread 29.
  • Figures 11 and 12 show such a Einschraubverbinder 26 in plan view and in section.
  • FIG. 13 shows a detailed view of the burner head 7 with transition to the burner support tube 11.
  • the burner head 7, which is shown in the oblique view in FIG. 14, is the same as in FIG. 3. According to the invention, only the burner support tube 11 is changed.

Landscapes

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

Abstract

The invention relates to a burner arrangement (1) for a combustion chamber, in particular a gas turbine combustion chamber, for burning fluid fuels, having a main burner (2) and a pilot burner (3) which is arranged centrally therein and serves to ignite and/or stabilize the combustion of the main burner (2), the main burner (2) comprising a first annular air duct (4) for supplying combustion air and first fuel nozzles (5) for injecting a fuel into the first annular air duct (4), the pilot burner (3) comprising a second annular air duct (6) for supplying combustion air and a burner head (7) with second fuel nozzles (8) for injecting a fuel into the second annular air duct (6), wherein the second fuel nozzles (8) are provided as separately controllable first and second fuel stages (9, 10), wherein for the purpose of supplying fuel to the first and second fuel stages (9, 10) there is provided a burner support pipe (11) that connects to the burner head (7) and has a pipe wall (12), and that the pipe wall (12) has, parallel to the longitudinal axis (13) of the burner support pipe (11), at least one first and one second deep-hole bore (14, 15) for supplying fuel to the first and second fuel stages (9, 10).

Description

Beschreibung description
Brenneranordnung Die Erfindung betrifft eine Brenneranordnung für eine Brennkammer, insbesondere eine Gasturbinenbrennkammer, zum Verfeuern fluidischer Brennstoffe. The invention relates to a burner arrangement for a combustion chamber, in particular a gas turbine combustion chamber, for firing fluid fuels.
Gasturbinen sind in Ihrer Verfügbarkeit hauptsächlich durch Problemstellungen im Verbrennungssystem limitiert. DieseGas turbines are limited in their availability mainly by problems in the combustion system. These
Probleme sind im speziellen das Überschreiten von Emissionsgrenzwerten (NOx und CO) sowie das Brummverhalten, verursacht durch thermoakustische Schwingungen im Bereich der Brennkammer. Um die Emissionen unter Grenzwertbereichen zu halten und das Brummverhalten der Maschine zu unterdrücken, bedarf es einer sehr guten Einstellung (Tuning) der veränderbaren Verbrennungsparameter . In particular, problems are the exceeding of emission limit values (NOx and CO) as well as the buzzing behavior caused by thermoacoustic oscillations in the area of the combustion chamber. In order to keep the emissions below the limits and to suppress the buzzing behavior of the engine, it requires a very good tuning of the variable combustion parameters.
Bei einem Brenner mit beispielsweise Hauptvormischbrenner und Pilotvormischbrenner sind dies in erster Linie die Brennstoffmassenströme des Hauptvormischbrenners sowie des Pilot- vormischbrenners . Dabei gehen je nach Einstellung ca. 90%-95% des Brennstoffmassenstroms durch den Hauptvormischbrenner, der Rest durch den Pilotvormischbrenner. Es ist bekannt dass eine Änderung (schon im Prozentbereich) des Pilotgasmassen- stroms einen nennenswerten Einfluss auf Emissionen und auf das Brummverhalten hat. Jedoch ist eine solche Regelung durch eine einzige Brennstoffstufe im Pilotvormischbrenner be¬ grenzt . In a burner with, for example, main premix burner and pilot premix burner, these are primarily the fuel mass flows of the main premix burner and the pilot premix burner. Depending on the setting, about 90% -95% of the fuel mass flow passes through the main premix burner, the remainder through the pilot premix burner. It is known that a change (even in the percentage range) of the pilot gas mass flow has a significant influence on emissions and buoyancy. However, such a rule by a single fuel level in Pilotvormischbrenner is be ¬ borders.
Bisher muss daher vor dem reibungslosen Betrieb der Gasturbine in der Inbetriebnahmephase aufwändig getuned werden. Durch die wenigen Einstellmöglichkeiten an Haupt- und Pilotbrenner müssen so aufwändig enge Korridore durchfahren werden, die durch Emissionen und Stabilität begrenzt sind. Oft müssen hier Kompromisse zwischen stabiler Fahrweise und geringen Emissionen eingegangen werden. Um hier Abhilfe zu schaffen, kann eine zweite vorgemischte Brennstoffstufe in den Pilotbrenner integriert werden. Diese Stufe muss dann auch über eine eigene Brennstoffzufuhr und einen eigenen Brennstoffkanal versorgt werden. So far, therefore, must be tuned consuming before the smooth operation of the gas turbine in the commissioning phase. Due to the few adjustment options on the main and pilot burners, it is necessary to pass through elaborately narrow corridors that are limited by emissions and stability. Often compromises between stable driving style and low emissions have to be made here. To remedy this situation, a second premixed fuel stage can be integrated into the pilot burner. This stage must then be powered by its own fuel supply and its own fuel channel.
Durch diese Ausführung können beide Stufen unabhängig voneinander gesteuert werden. Beispielsweise können beide Pilot¬ brennstoffstufen in Pilotbrennerschaufeln integriert sein, um für beide Stufen eine gute Durchmischung von Brennstoff und Luft zu ermöglichen. Durch geschickte Wahl des Bohrungsmus¬ ters kann so die radiale Brennstoffverteilung aktiv im Betrieb beeinflusst werden und somit Einfluss auf Emissionen und Verbrennungsstabilität genommen werden. Hierdurch ist es möglich, die Korridore, durch die beim An- und Abfahren der Maschine manövriert werden muss, zu erweitern und das Emissi¬ ons- und Stabilitätsverhalten, vor allem im Teillastbereich, kann verbessert werden. Through this design, both stages can be controlled independently. For example, both pilot fuel ¬ levels can be integrated in pilot burner blades to allow for both stages, a good mixing of fuel and air. By skillful choice of Bohrungsmus ¬ ters so the radial fuel distribution can be actively influenced during operation and thus influence on emissions and combustion stability are taken. This makes it possible to extend the corridors, through which must be maneuvered when starting and stopping the machine, and the emissi ¬ ons- and stability behavior, especially in the partial load range, can be improved.
Die WO 2014/114533 AI offenbart beispielsweise eine Brenner- anordnung mit einer auf der Achse der Brenneranordnung liegenden Diffusionsgaspassage. Diese Passage könnte beispiels¬ weise durch eine Rohr-in-Rohr-Konstruktion für die Brennstoffzufuhr einer zweiten Stufe im Pilotbrenner genutzt werden. Allerdings müsste dann aufgrund der zu erwartenden un- terschiedlichen thermischen Dehnungen der Bauteile die Rohr- in-Rohr-Konstruktion durch einen aufwändigen und daher auch vergleichsweise teuren Kompensator entlastet werden. For example, WO 2014/114533 A1 discloses a burner arrangement with a diffusion gas passage lying on the axis of the burner arrangement. This passage could be ¬ example be used by a tube-in-tube design for the fuel supply of a second stage in the pilot burner. However, due to the expected different thermal expansions of the components, the tube-in-tube construction would then have to be relieved by a complex and therefore comparatively expensive compensator.
Aufgabe der Erfindung ist es daher, eine Brenneranordnung der eingangs genannten Art bereitzustellen, die eine beträchtli¬ che Verbesserung hinsichtlich Emissionen und Stabilität ermöglicht und die zugleich möglichst einfach und kostengünstig herzustellen und zu montieren ist. Die Erfindung löst diese Aufgabe, indem sie bei einer derar¬ tigen Brenneranordnung für eine Brennkammer, insbesondere eine Gasturbinenbrennkammer, zum Verfeuern fluidischer Brennstoffe, mit einem Hauptbrenner und einem zentral darin ange- ordneten Pilotbrenner, der zum Zünden und/oder zum Stabilisieren der Verbrennung des Hauptbrenners dient, der Haupt¬ brenner umfassend einen ersten Ringluftkanal zur Zuführung von Verbrennungsluft und erste Brennstoffdüsen zum Eindüsen eines Brennstoffs in den ersten Ringluftkanal, der Pilotbren¬ ner umfassend einen zweiten Ringluftkanal zur Zuführung von Verbrennungsluft und einem Brennerkopf mit zweiten Brenn¬ stoffdüsen zum Eindüsen eines Brennstoffs in den zweiten Ringluftkanal, wobei die zweiten Brennstoffdüsen als getrennt ansteuerbare erste und zweite Brennstoffstufen vorgesehen sind, zum Zuführen von Brennstoff zu den ersten und zweiten Brennstoffstufen ein an den Brennerkopf anschließendes Brennerträgerrohr mit einer Rohrwand vorsieht, wobei die Rohrwand mindestens eine erste und eine zweite parallel zur Längsachse des Brennerträgerrohres verlaufende Tieflochbohrung für dieThe object of the invention is therefore to provide a burner assembly of the type mentioned, which allows a beträchtli ¬ che improvement in terms of emissions and stability and at the same time as simple and inexpensive to manufacture and assemble. The invention solves this task by at a Derar ¬ term burner assembly for a combustion chamber, in particular a gas turbine combustion chamber for firing fluidic fuels, comprising a main burner and a reasonable centrally therein arranged pilot burner, which serves to ignite and / or stabilize the combustion of the main burner, the main ¬ burner comprising a first annular air duct for supplying combustion air and first fuel nozzles for injecting a fuel in the first annular air duct, the Pilotbren ¬ ner comprising a second annular air duct Supply of combustion air and a burner head with second fuel ¬ fuel nozzles for injecting a fuel in the second annular air passage, wherein the second fuel nozzles are provided as separately controllable first and second fuel stages, for supplying fuel to the first and second fuel stages, a subsequent to the burner head burner support tube with a tube wall, wherein the tube wall at least a first and a second parallel to the longitudinal axis of the burner tube extending deep hole for the
Versorgung der ersten und zweiten Brennstoffstufen mit Brennstoff aufweist. Supplying the first and second fuel stages with fuel.
Hierdurch wird das Emissions- und Stabilitätsverhalten der Brenneranordnung verbessert und es kann auf die vergleichs¬ weise aufwändige und teure Rohr-in-Rohr-Konstruktion mit Kom- pensator verzichtet werden. Thereby, the emission and stability behavior of the torch assembly is improved, and it can be dispensed with the comparatively complicated and expensive as ¬ pipe-in-pipe construction with com- expansion joint.
Zweckmäßigerweise sind die erste und zweite Tieflochbohrung auf unterschiedlichen Radien bezogen auf die Längsachse des Brennerträgerrohres in der Rohrwand angeordnet, so dass Expediently, the first and second deep hole bores are arranged at different radii relative to the longitudinal axis of the burner support tube in the pipe wall, so that
Brennstoff direkt über gerade Bohrungen einer jeweiligen Brennstoffstufe zugeführt werden kann. Die Herstellung sol¬ cher Bohrungen ist vergleichsweise kostengünstig. Fuel can be supplied directly via straight bores of a respective fuel stage. The preparation of sol ¬ cher bores is comparatively cost effective.
In einer vorteilhaften Ausführungsform münden die mindestens eine erste und eine zweite Tieflochbohrung in je einen BrennstoffVerteilerkanal einer Brennstoffstufe . So kann die Anzahl der Tieflochbohrungen kleiner sein, als die Anzahl der Brenn- stoffdüsen je Brennstoffstufe . In an advantageous embodiment, the at least one first and one second deep hole bore open into a respective fuel distributor channel of a fuel stage. Thus, the number of deep hole bores can be smaller than the number of fuel nozzles per fuel stage.
Weiterhin kann es vorteilhaft sein, wenn das Brennerträgerrohr auf seiner Achse eine Diffusionsgaspassage aufweist, die ebenfalls in den Brennerkopf mündet, so dass auch ein Diffu¬ sionsbetrieb möglich ist. Furthermore, it may be advantageous if the burner support tube has on its axis a diffusion gas passage, the also flows into the burner head, so that a Diffu ¬ sion operation is possible.
In einer weiteren vorteilhaften Ausführungsform ist das Bren- nerträgerrohr in Strömungsrichtung eines Brennstoffs stromauf des Brennerkopfes mit einer Trägerplatte verbunden, wobei die Trägerplatte Brennstoffringverteiler aufweist, von denen die mindestens eine erste und eine zweite Tieflochbohrung abzwei¬ gen . In a further advantageous embodiment, the burner carrier tube is connected in the flow direction of a fuel upstream of the burner head to a carrier plate, wherein the carrier plate has fuel ring distributor, of which the at least one first and one second deep hole bore abzwei ¬ conditions.
Dabei ist es zweckmäßig, wenn die Trägerplatte Brennstoffan- schlüsse aufweist, die in die Brennstoffringverteiler münden. It is expedient if the carrier plate has fuel connections which open into the fuel ring manifolds.
Im Hinblick auf eingeschränkte Platzverhältnisse ist es vor- teilhaft, wenn ein Brennstoffanschluss über einen Einschraub¬ verbinder mit durchgehender Bohrung und im Wesentlichen radialen Öffnungen im Außengewinde erfolgt, wobei im einge¬ schraubten Zustand die radialen Öffnungen auf Höhe eines Brennstoffringverteilers zu liegen kommen. Dadurch wird auch bei vergleichsweise dicht unter der Oberfläche der Träger¬ platte liegenden Brennstoffringverteilern sichergestellt, dass der Einschraubverbinder ausreichend tief in die Trägerplatte eingeschraubt werden kann, um eine sichere Verbindung herzustellen . In view of limited space, it is advantageous if a fuel connection via a screw ¬ connector with a continuous bore and substantially radial openings in the external thread takes place, in the screwed ¬ come the radial openings come to rest at the height of a fuel ring manifold. As a result, it is ensured even with comparatively close below the surface of the support ¬ plate lying fuel ring manifolds that the Einschraubverbinder can be sufficiently deep screwed into the support plate to make a secure connection.
Weiterhin ist es im Hinblick auf eine gute Durchmischung von Brennstoff und Luft vorteilhaft, wenn der erste Ringluftkanal erste Drallschaufeln aufweist und die ersten Brennstoffdüsen in den ersten Drallschaufeln angeordnet sind. Furthermore, it is advantageous in view of a good mixing of fuel and air when the first annular air channel has first swirl blades and the first fuel nozzles are arranged in the first swirl blades.
Ebenso gilt dies für den zweiten Ringluftkanal, der vorteil¬ hafterweise zweite Drallschaufeln aufweist, wobei die zweiten Brennstoffdüsen in den zweiten Drallschaufeln angeordnet sind . This also applies to the second annular air channel which has advantageous adhesive ¬ legally second swirl blades, the second fuel nozzles are arranged in the second swirl blades.
Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen schematisch und nicht maßstäblich: Figur 1 Brenneranordnung, The invention will be explained in more detail by way of example with reference to the drawings. Shown schematically and not to scale: FIG. 1 burner arrangement,
Figur 2 einen bekannten Pilotbrenner, Figur 3 ein stromabwärtiges Detail des Pilotbrenners aus FIG. 2 shows a known pilot burner, FIG. 3 shows a downstream detail of the pilot burner
Figur 2,  FIG. 2,
Figur 4 ein stromaufwärtiges Detail des Pilotbrenners aus FIG. 4 shows an upstream detail of the pilot burner
Figur 2,  FIG. 2,
Figur 5 eine Schnittdarstellung der erfindungsgemäßen Brenneranordnung den Innenkanal zeigend, FIG. 5 shows a sectional view of the burner arrangement according to the invention, showing the inner channel,
Figur 6 eine Schnittdarstellung der erfindungsgemäßen Bren- neranordnung den Außenkanal zeigend, FIG. 6 is a sectional view of the burner assembly according to the invention showing the outer channel;
Figur 7 eine Seitenansicht auf das stromabwärtige Ende des Figure 7 is a side view of the downstream end of the
Brennerträgerrohrs der Brenneranordnung, Figur 8 einen Schnitt durch Trägerplatte und Außenkanal des  Burner support tube of the burner assembly, Figure 8 shows a section through the support plate and outer channel of
Brennerträgerrohrs ,  Burner carrier pipe,
Figur 9 einen Schnitt durch Trägerplatte und Anschluss für den Außenkanal sowie durch den Innenkanal des Bren- nerträgerrohrs , 9 shows a section through carrier plate and connection for the outer channel and through the inner channel of the burner carrier tube, FIG.
Figur 10 eine Seitenansicht auf einen Schnitt durch die Trä¬ gerplatte mit Anschluss für den Innenkanal, Figur 11 einen Einschraubverbinder mit durchgehender Bohrung und radialen Öffnungen im Außengewinde in der 10 is a side view of a section through the Trä ¬ gerplatte with connection for the inner channel, Figure 11 is a Einschraubverbinder with through hole and radial openings in the external thread in the
Draufsicht,  Top view,
Figur 12 einen Einschraubverbinder mit durchgehender Bohrung und radialen Öffnungen im Außengewinde im Schnitt, FIG. 12 is a sectional view of a screw-in connector with a through bore and radial openings in the external thread;
Figur 13 eine Detailsicht auf den Brennerkopf mit Übergang zum Brennerträgerrohr und Figur 14 eine Schrägansicht der stromaufwärtigen Seite des Brennerkopfes . Die Figur 1 zeigt schematisch und beispielhaft einen Schnitt durch einen Teil einer Brenneranordnung 1 nach der Erfindung. Die Brenneranordnung 1 ist im Wesentlichen radialsymmetrisch um die Längsachse 13 und umfasst einen Hauptbrenner 2 sowie einen zentral darin angeordneten Pilotbrenner 3, der zum Zün- den und/oder Stabilisieren der Verbrennung des Hauptbrenners 2 dient. 13 shows a detailed view of the burner head with transition to the burner support tube and Figure 14 is an oblique view of the upstream side of the burner head. FIG. 1 shows schematically and by way of example a section through part of a burner arrangement 1 according to the invention. The burner arrangement 1 is essentially radially symmetrical about the longitudinal axis 13 and comprises a main burner 2 and a pilot burner 3 arranged centrally therein, which serves to ignite and / or stabilize the combustion of the main burner 2.
Der Hauptbrenner 2 umfasst einen ersten Ringluftkanal 4 zur Zuführung von Verbrennungsluft und erste Brennstoffdüsen 5 zum Eindüsen eines Brennstoffs in den ersten Ringluftkanal 4. Der Pilotbrenner 3 umfasst einen zweiten Ringluftkanal 6 zur Zuführung von Verbrennungsluft und zweite Brennstoffdüsen 8 zum Eindüsen eines Brennstoffs in den zweiten Ringluftkanal 6. The main burner 2 comprises a first annular air passage 4 for supplying combustion air and first fuel nozzles 5 for injecting a fuel into the first annular air passage 4. The pilot burner 3 comprises a second annular air passage 6 for supplying combustion air and second fuel nozzles 8 for injecting a fuel into the second annular air passage 6th
Die zweiten Brennstoffdüsen 8 sind als erste und zweite The second fuel nozzles 8 are first and second
Brennstoffstufen 9, 10 vorgesehen, wobei jede Brennstoffstufe 9, 10 eine eigene Brennstoffzufuhr aufweist. In der Brenneranordnung 1 der Figur 1 weist der erste Ringluftkanal 4 erste Drallschaufeln 30 auf, in denen die ersten Brennstoffdüsen 5 angeordnet sind. Fuel stages 9, 10 are provided, each fuel stage 9, 10 has its own fuel supply. In the burner arrangement 1 of FIG. 1, the first annular air channel 4 has first swirl vanes 30, in which the first fuel nozzles 5 are arranged.
Weiterhin weist in der Brenneranordnung 1 der Figur 1 der zweite Ringluftkanal 6 zweite Drallschaufeln 31 auf. In den zweiten Drallschaufeln 31 sind die zweiten Brennstoffdüsen 8 angeordnet, die sich, wie bereits ausgeführt, in eine erste und eine zweite Brennstoffstufe 9, 10 aufteilen. Figur 2 zeigt einen bekannten Pilotbrenner 32 mit einer zentralen Diffusionsgaspassage 20, in der ein Rohr 33 angeordnet ist, wobei zwischen einer Innenwand 34 der Diffusionsgaspas¬ sage 20 und einer Rohraußenwand 35 ein Ringkanal 36 für die Brennstoffzufuhr zur zweiten Brennstoffstufe 10 gebildet ist. Diese Rohr-in-Rohr-Konstruktion wird durch einen Kompensator 37 entlastet. Figur 3 zeigt ein stromabwärtiges Detail des Pilotbrenners 3 aus Figur 2, insbesondere den Pilotbrennerkopf 7 mit der Brennstoffzufuhr für die erste und zweite Brennstoffstufe 9, 10. Figur 4 zeigt ein stromaufwärtiges Detail des Pilotbrenners 3 aus Figur 2, insbesondere den Kompensator 37 der Rohr-inRohr-Konstruktion . Furthermore, in the burner arrangement 1 of FIG. 1, the second annular air channel 6 has second swirl blades 31. In the second swirl blades 31, the second fuel nozzles 8 are arranged, which, as already stated, in a first and a second fuel stage 9, 10 split. Figure 2 shows a known pilot burner 32 with a central diffusion gas passage 20, in which a tube 33 is arranged, wherein between an inner wall 34 of the Diffusionsgaspas ¬ sage 20 and a tube outer wall 35, an annular channel 36 for the Fuel supply to the second fuel stage 10 is formed. This tube-in-tube construction is relieved by a compensator 37. FIG. 3 shows a downstream detail of the pilot burner 3 from FIG. 2, in particular the pilot burner head 7 with the fuel supply for the first and second fuel stages 9, 10. FIG. 4 shows an upstream detail of the pilot burner 3 from FIG. 2, in particular the compensator 37 of the tube in-pipe construction.
In den Figuren 5 und 6 ist der erfindungsgemäße Pilotbrenner 3 in unterschiedlichen Schnittebenen gezeigt. In Figur 5 verläuft der Schnitt durch zweite Tieflochbohrungen 15, die den Innenkanal 38 darstellen, in Figur 6 ist die entsprechende Ansicht mit ersten Tieflochbohrungen 14 für den Außenkanal 39. Man erkennt, dass die erste und zweite Tieflochbohrung 14, 15 auf unterschiedlichen Radien 16, 17 bezogen auf die Längsachse 13 des Brennerträgerrohres 11 in der Rohrwand 12 angeordnet sind. Ferner zeigen die Figuren 5 und 6, dass die mindestens eine erste und eine zweite Tieflochbohrung 14, 15 in je einen Brennstoff erteilerkanal 18, 19 einer Brennstoff- stufe 9, 10 münden. In FIGS. 5 and 6, the pilot burner 3 according to the invention is shown in different sectional planes. FIG. 5 shows the section through second deep hole bores 15, which represent the inner channel 38, FIG. 6 shows the corresponding view with first deep hole bores 14 for the outer channel 39. It can be seen that the first and second deep hole bores 14, 15 are at different radii 16, 17 are arranged with respect to the longitudinal axis 13 of the burner support tube 11 in the tube wall 12. Furthermore, FIGS. 5 and 6 show that the at least one first and one second deep hole bores 14, 15 open into a respective fuel distributor channel 18, 19 of a fuel stage 9, 10.
Figur 7 zeigt eine Seitenansicht auf das stromabwärtige Ende des Brennerträgerrohrs 11 der Brenneranordnung 1. Man erkennt die Enden der ersten und zweiten Tieflochbohrungen 14, 15 von Innen- und Außenkanal 38, 39. Figure 7 shows a side view of the downstream end of the burner support tube 11 of the burner assembly 1. It can be seen the ends of the first and second deep holes 14, 15 of the inner and outer channel 38, 39th
Die Figuren 8, 9 und 10 zeigen geschnittene Detailansichten im Bereich der Trägerplatte 21 des Pilotbrenners 3. Insbesondere zeigt die Figur 8 einen Schnitt durch die Trä¬ gerplatte 21 mit dem ersten und zweiten Brennstoffringvertei- ler 22, 23 sowie den durch Tieflochbohrungen 14 gebildeten Außenkanal 39 in der Rohrwand 12 des Brennerträgerrohrs 11. Die Figur 9 zeigt einen Schnitt durch die Trägerplatte 21 mit dem ersten und zweiten Brennstoffringverteiler 22, 23 sowie den durch Tieflochbohrungen 15 gebildeten Innenkanal 38 in der Rohrwand 12 des Brennerträgerrohrs 11. Ferner zeigt Figur 9 einen Schnitt durch den ernsten Brennstoffanschluss 24 zum ersten Brennstoffringverteiler 22 für den Außenkanal 39. Figures 8, 9 and 10 show sectional detail views in the region of the support plate 21 of the pilot burner 3. In particular, Figure 8 shows a section through the Trä ¬ carrier plate 21 ler with the first and second Brennstoffringvertei- 22, 23 and the outer channel formed by deep-hole bores 14 39 in the tube wall 12 of the burner support tube eleventh FIG. 9 shows a section through the carrier plate 21 with the first and second fuel ring distributors 22, 23 and the inner channel 38 formed by deep-hole bores 15 in the tube wall 12 of the burner carrier tube 11. Further, FIG. 9 shows a section through the serious fuel port 24 to the first fuel ring distributor 22 for the outer channel 39.
Die Figur 10 zeigt schließlich einen Schnitt durch die Trä- gerplatte 21 mit dem zweiten Brennstoffanschluss 25 zum zwei¬ ten Brennstoffringverteiler 23 für den Innenkanal 38. Dabei ist in der Figur 10 erkennbar, dass der zweite Brennstoff¬ ringverteiler 23 für den Innenkanal 38 vergleichsweise dicht unter der Oberfläche der Trägerplatte 21 liegt. Um eine me- chanisch zuverlässige Brennstoffzufuhr sicherzustellen, ist der Brennstoffanschluss 25 über einen Einschraubverbinder 26 mit durchgehender Bohrung 27 und im Wesentlichen radialen Öffnungen 28 im Außengewinde 29 realisiert. Die Figuren 11 und 12 zeigen einen solchen Einschraubverbinder 26 in der Draufsicht und im Schnitt. Figure 10 finally shows a section through the Trä- carrier plate 21 with the second fuel port 25 for two ¬ th annular fuel manifold 23 for the inner channel 38. It can be seen in Figure 10 that the second fuel ¬ ring distributor 23 relatively close to the inner channel 38 lies below the surface of the carrier plate 21. In order to ensure a mechanically reliable fuel supply, the fuel connection 25 is realized via a screw-in connector 26 with a through-hole 27 and essentially radial openings 28 in the external thread 29. Figures 11 and 12 show such a Einschraubverbinder 26 in plan view and in section.
Figur 13 zeigt eine Detailsicht auf den Brennerkopf 7 mit Übergang zum Brennerträgerrohr 11. Der Brennerkopf 7, der in der Figur 14 in der Schrägansicht gezeigt ist, ist derselbe wie in Figur 3. Nach der Erfindung ist lediglich das Brennerträgerrohr 11 verändert. 13 shows a detailed view of the burner head 7 with transition to the burner support tube 11. The burner head 7, which is shown in the oblique view in FIG. 14, is the same as in FIG. 3. According to the invention, only the burner support tube 11 is changed.

Claims

Patentansprüche claims
1. Brenneranordnung (1) für eine Brennkammer, insbesondere eine Gasturbinenbrennkammer, zum Verfeuern fluidischer Brennstoffe, mit einem Hauptbrenner (2) und einem zentral darin angeordneten Pilotbrenner (3) , der zum Zünden und/oder zum Stabilisieren der Verbrennung des Hauptbrenners (2) dient, der Hauptbrenner (2) umfassend einen ersten Ringluftkanal (4) zur Zuführung von Verbrennungsluft und erste Brennstoffdüsen (5) zum Eindüsen eines Brennstoffs in den ersten Ringluftkanal (4), der Pilotbrenner (3) umfassend einen zweiten Ringluftkanal (6) zur Zufüh¬ rung von Verbrennungsluft und einem Brennerkopf (7) mit zweiten Brennstoffdüsen (8) zum Eindüsen eines Brenn- Stoffs in den zweiten Ringluftkanal (6), wobei die zwei¬ ten Brennstoffdüsen (8) als getrennt ansteuerbare erste und zweite Brennstoffstufen (9, 10) vorgesehen sind, dadurch gekennzeichnet, dass zum Zuführen von Brennstoff zu den ersten und zweiten Brennstoffstufen (9, 10) ein an den Brennerkopf (7) anschließendes Brennerträgerrohr (11) mit einer Rohrwand (12) vorgesehen ist, und dass die Rohrwand (12) parallel zur Längsachse (13) des Brenner¬ trägerrohres (11) mindestens eine erste und eine zweite Tieflochbohrung (14, 15) für die Versorgung der ersten und zweiten Brennstoffstufen (9, 10) mit Brennstoff auf¬ weist. A burner assembly (1) for a combustion chamber, in particular a gas turbine combustor, for firing fluid fuels, comprising a main burner (2) and a pilot burner (3) arranged centrally therein for igniting and / or stabilizing combustion of the main burner (2) the main burner (2) comprises a first annular air channel (4) for supplying combustion air and first fuel nozzles (5) for injecting a fuel into the first annular air channel (4), the pilot burner (3) comprising a second annular air channel (6) for Zufüh ¬ tion of combustion air and a burner head (7) with second fuel nozzles (8) for injecting a fuel in the second annular air duct (6), wherein the two ¬ th fuel nozzles (8) as separately controllable first and second fuel stages (9, 10 ) are provided, characterized in that for supplying fuel to the first and second fuel stages (9, 10) one to the burner head (7) subsequently it is provided burner plate tube (11) with a tube wall (12), and that the tube wall (12) parallel to the longitudinal axis (13) of the burner ¬ carrier tube (11) at least a first and a second deep hole bore (14, 15) for the supply of first and second fuel stages (9, 10) with fuel on ¬ has.
2. Brenneranordnung (1) nach Anspruch 1, wobei die erste und zweite Tieflochbohrung (14, 15) auf unterschiedlichen Ra- dien (16, 17) bezogen auf die Längsachse (13) des Bren¬ nerträgerrohres (11) in der Rohrwand (12) angeordnet sind . 2. burner assembly (1) according to claim 1, wherein the first and second deep hole bore (14, 15) on different Ria dia (16, 17) relative to the longitudinal axis (13) of the Bren ¬ nerträgerrohres (11) in the pipe wall (12 ) are arranged.
3. Brenneranordnung (1) nach einem der vorhergehenden An- sprüche, wobei die mindestens eine erste und eine zweite3. burner assembly (1) according to any one of the preceding claims, wherein the at least one first and a second
Tieflochbohrung (14, 15) in je einen Brennstoffverteiler- kanal (18, 19) einer Brennstoffstufe (9, 10) münden. Brenneranordnung (1) nach einem der vorhergehenden Ansprüche, wobei das Brennerträgerrohr (11) auf seiner Ach¬ se (13) eine Diffusionsgaspassage (20) aufweist, die ebenfalls in den Brennerkopf (7) mündet. Deep hole (14, 15) each in a fuel distributor channel (18, 19) of a fuel stage (9, 10) open. Burner assembly (1) according to any one of the preceding claims, wherein the burner support tube (11) on its Ach ¬ se (13) has a diffusion gas passage (20), which also opens into the burner head (7).
Brenneranordnung (1) nach einem der vorhergehenden Ansprüche, wobei das Brennerträgerrohr (11) in Strömungs¬ richtung eines Brennstoffs stromauf des Brennerkopfes (7) mit einer Trägerplatte (21) verbunden ist, wobei die Trä¬ gerplatte (21) Brennstoffringverteiler (22, 23) aufweist, von denen die mindestens eine erste und eine zweite Tief¬ lochbohrung (14, 15) abzweigen. Burner arrangement (1) according to one of the preceding claims, wherein the burner support tube (11) in the flow ¬ direction of a fuel upstream of the burner head (7) with a support plate (21) is connected, wherein the Trä ¬ gerplatte (21) fuel ring manifold (22, 23 ), of which the at least one first and a second deep ¬ hole bore (14, 15) branch off.
Brenneranordnung (1) nach Anspruch 5, wobei die Trägerplatte (21) Brennstoffanschlüsse (24, 25) aufweist, die in die Brennstoffringverteiler (22, 23) münden. A burner assembly (1) according to claim 5, wherein the support plate (21) has fuel ports (24, 25) opening into the fuel ring manifolds (22, 23).
Brenneranordnung (1) nach Anspruch 6, wobei ein Brennstoffanschluss (25) über einen Einschraubverbinder (26) mit durchgehender Bohrung (27) und im Wesentlichen radialen Öffnungen (28) im Außengewinde (29) erfolgt, wobei im eingeschraubten Zustand die radialen Öffnungen (28) auf Höhe eines Brennstoffringverteilers (23) zu liegen kom¬ men . Burner assembly (1) according to claim 6, wherein a fuel connection (25) via a Einschraubverbinder (26) with a through bore (27) and substantially radial openings (28) in the external thread (29), wherein in the screwed state, the radial openings (28 ) at the level of a fuel ring distributor (23) lie com ¬ men.
Brenneranordnung (1) nach einem der vorhergehenden Ansprüche, wobei der erste Ringluftkanal (4) erste Burner arrangement (1) according to one of the preceding claims, wherein the first annular air channel (4) first
Drallschaufeln (30) aufweist und die ersten Brennstoffdü- sen (5) in den ersten Drallschaufeln (30) angeordnet sind . Having swirl blades (30) and the first fuel nozzles (5) are arranged in the first swirl blades (30).
Brenneranordnung (1) nach einem der vorhergehenden Ansprüche, wobei der zweite Ringluftkanal (6) zweite Burner assembly (1) according to one of the preceding claims, wherein the second annular air channel (6) second
Drallschaufeln (31) aufweist und die zweiten Brennstoff¬ düsen (8) in den zweiten Drallschaufeln (31) angeordnet sind . Swirl vanes (31) and the second fuel ¬ nozzles (8) are arranged in the second swirl blades (31).
EP16713412.1A 2015-04-08 2016-03-30 Burner arrangement Active EP3250857B1 (en)

Applications Claiming Priority (2)

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DE102015206227.9A DE102015206227A1 (en) 2015-04-08 2015-04-08 burner arrangement
PCT/EP2016/056892 WO2016162248A1 (en) 2015-04-08 2016-03-30 Burner arrangement

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DE (1) DE102015206227A1 (en)
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CN111720732B (en) * 2020-05-28 2022-05-13 克莱普（浙江）气体设备有限公司 Full-automatic fuel heating integral gasifier
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EP0580683B1 (en) * 1991-04-25 1995-11-08 Siemens Aktiengesellschaft Burner arrangement, especially for gas turbines, for the low-pollutant combustion of coal gas and other fuels
US6698207B1 (en) * 2002-09-11 2004-03-02 Siemens Westinghouse Power Corporation Flame-holding, single-mode nozzle assembly with tip cooling
EP1659339A1 (en) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Method of starting up a burner
FR2881813B1 (en) * 2005-02-09 2011-04-08 Snecma Moteurs TURBOMACHINE COMBUSTION CHAMBER FAIRING
US8448441B2 (en) * 2007-07-26 2013-05-28 General Electric Company Fuel nozzle assembly for a gas turbine engine
DE102009038848A1 (en) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Burner, in particular for gas turbines
DE102009038845A1 (en) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Swirl vane, burner and gas turbine
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EP2503240A1 (en) * 2011-03-22 2012-09-26 Siemens Aktiengesellschaft Gas turbine burner
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EP2860453A1 (en) * 2013-10-10 2015-04-15 Siemens Aktiengesellschaft Premix burner for a gas turbine having a burner tip with internal impingement cooling
EP3008390A1 (en) * 2013-10-31 2016-04-20 Siemens Aktiengesellschaft Gas turbine burner hub with pilot burner
WO2015067482A1 (en) * 2013-11-08 2015-05-14 Siemens Aktiengesellschaft Gas turbine burner having separately controllable fuel stages in pilot burner swirl vanes

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RU2669439C1 (en) 2018-10-11
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WO2016162248A1 (en) 2016-10-13
CN107429918B (en) 2019-09-06
CN107429918A (en) 2017-12-01

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