EP2583033B1 - Brûleur de turbines - Google Patents

Brûleur de turbines Download PDF

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Publication number
EP2583033B1
EP2583033B1 EP11711862.0A EP11711862A EP2583033B1 EP 2583033 B1 EP2583033 B1 EP 2583033B1 EP 11711862 A EP11711862 A EP 11711862A EP 2583033 B1 EP2583033 B1 EP 2583033B1
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EP
European Patent Office
Prior art keywords
fuel nozzle
fuel
turbine burner
burner according
feed unit
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.)
Active
Application number
EP11711862.0A
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German (de)
English (en)
Other versions
EP2583033A1 (fr
Inventor
Boris Ferdinand Kock
Berthold Köstlin
Bernd Prade
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP11711862.0A priority Critical patent/EP2583033B1/fr
Publication of EP2583033A1 publication Critical patent/EP2583033A1/fr
Application granted granted Critical
Publication of EP2583033B1 publication Critical patent/EP2583033B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/36—Supply of different fuels
    • 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
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • 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
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits

Definitions

  • the invention relates to a turbine burner according to the preamble of claim 1.
  • the combustible components of the synthesis gases are essentially CO and H2.
  • the calorific value of the synthesis gas is about 5 to 10 times smaller compared to the calorific value of natural gas.
  • Main constituents in addition to CO and H2 are inert fractions such as nitrogen and / or water vapor and possibly also carbon dioxide. Due to the low calorific value consequently high volume flows of fuel gas must be supplied through the burner of the combustion chamber. As a result, for the combustion of low calorific fuels - e.g. Synthesis gas one or more separate fuel passages must be made available.
  • the synthesis gas is in the burner of the prior art - as in the US 2009/025394 A1 or in the EP 1 649 219 B1 described over a arranged around the burner axis Ringraumpassage the combustion chamber.
  • the US 2009/025394 A1 describes a turbine combustor having a secondary supply unit for supplying a secondary fuel and for discharging the fuel from an opening into a combustion zone, and a primary supply unit having a primary (upstream) and a fuel (downstream) with a fuel nozzle exit for supplying a primary fuel into the combustion zone wherein the fuel nozzle and the primary tube are disposed concentrically about the secondary supply unit, the primary tube and the fuel nozzle having a fluid flow connection, the fuel nozzle having an annular wall radially spaced axially from the secondary supply unit such that through the annular wall and Secondary feed unit is formed a gap height, wherein the annular wall of the fuel nozzle has a directed to the secondary feed unit inner wall, and wherein between sec undärzu melt Switzerland and the annular wall, a fluid passage is formed.
  • swirl vanes are arranged in the above fluid channel in the region of the fuel nozzle outlet. These swirl vanes have a leading edge on their upstream side and the fuel nozzle has a nozzle inlet (not shown, upstream) with the swirl vanes at an axial distance from the nozzle inlet.
  • the gas is carried out upstream of the burner nozzle through an existing in the burner nozzle nozzle ring with salaried holes, wherein the gas is acted upon by a peripheral speed component.
  • the synthesis gas directly on the nozzle a relatively low Mach number is impressed.
  • there is also only a relatively small intensity with regard to the mixing with the combustion air which encloses the annular fuel flow both from inside and outside.
  • aggravating for a quick mixing of the fuel with the combustion air is the geometric design of the annular gap with a relatively large gap width and a correspondingly large mixing path.
  • the nozzle ring of EP 1 649 219 B1 Anchored holes have been chosen, in particular, for synthesis gases having a relatively high calorific value in order to achieve a sufficiently high pressure loss at the nozzle for acoustic stability, without substantially changing the main dimensions.
  • this embodiment has aerodynamic disadvantages. Thus, discrete jets are generated which can not be sufficiently evened out on the path available up to the burner exit, which leads to increased NO x emissions. In addition, due to the flow separations inside and in front of the nozzle, a considerable total pressure loss occurs, so that this pulse loss is not available as mixing energy.
  • the invention causes a lower pressure drop to occur with the same swirl intensity compared to the nozzle ring of the prior art nozzle.
  • the vanes cause a greater portion of the pressure loss to be applied to the fuel nozzle outlet for the same total pressure loss, resulting in higher acoustic stability in the combustion zone than in the prior art nozzle.
  • FIG. 1 shows such a turbine burner according to the invention.
  • FIG. 2 shows a fuel nozzle according to the invention.
  • the turbine burner after Fig.1 has a secondary supply unit for supplying a secondary fuel or air and for discharging the fuel or air from an opening 6 into a combustion zone 10.
  • the secondary fuel may include natural gas and air.
  • the secondary feed unit has a radius Ri.
  • the secondary supply unit may also include a pilot burner 2, which is designed for a further fuel such as oil.
  • a further, arranged around the pilot burner 2 annular natural gas duct 35 may be provided for supplying natural gas Gn.
  • the natural gas can be diluted with steam or water to control the NOx levels.
  • the secondary supply unit can provide a further annular air duct 30, into which compressor air L 'flows.
  • the secondary supply unit comprises at the downstream end at least one swirl generator, a so-called axial grid 22 for generating a swirl.
  • the axial grid 22 can be arranged in the downstream end of the air duct 30 of the secondary supply unit be.
  • the natural gas Gn of the channel 35 is flowed into the air channel 30 in front of the axial grid 22.
  • the resulting air-natural gas mixture is then introduced by the axial grid 22 twisted into the combustion zone 10.
  • the burner further comprises a primary supply unit having a primary mixing tube 11 and a fuel nozzle 1 with an opening facing the combustion zone, the fuel nozzle outlet 4 for supplying a primary fuel, wherein the fuel nozzle 1 and the primary mixing tube 11 is arranged concentrically around the secondary supply unit.
  • the primary mixing tube 11 and the fuel nozzle 1 have a fluid flow connection. Through the primary mixer tube 11 and the fuel nozzle 1 of the combustion zone 10 synthesis gas is supplied.
  • annular channel 40 Arranged at least partially around the primary supply unit is an annular channel 40 which has a plurality of circumferentially arranged swirlers 45 with or without fuel nozzles. Compressor air L ", into which fuel can be injected by means of the swirlers 45, is flowed through this annular channel 40. The resulting compressor air L" fuel mixture or the air L "is likewise introduced into the combustion zone 10 in a twisted manner.
  • the fuel nozzle 1 has an annular wall 9, which is radially spaced from the Sekundärzu GmbH in the axial direction, so that a gap height h is formed by the annular wall 9 and secondary feed.
  • the fuel nozzle 1 has an inner wall 50 directed toward the secondary feed unit, wherein the inner wall 50 has annularly arranged blades 12 (FIG. Fig.2 ).
  • the blades 12 may be disposed on the outer wall of the secondary feed unit (not shown).
  • the external wall of the secondary feed unit is understood to mean the outer wall of the secondary feed unit directed toward the fuel nozzle.
  • the fuel nozzle 1 also has a fuel nozzle inlet 20 and a fuel nozzle outlet 4. Through the blades 12, the pressure loss is applied to the fuel nozzle outlet 4.
  • the pressure loss can also be adjusted in this embodiment on the speed of the synthesis gas or the cross section of the fuel nozzle outlet.
  • the fuel nozzle 1 is formed downstream at least partially conical.
  • the blades 12 have a blade leading edge 51 on the upstream side and a blade trailing edge 60 opposite thereto.
  • the blade leading edge 51 has an axial distance s from the fuel nozzle inlet 20.
  • the ratio of distance s and gap height h is greater than 1 and less than 4.
  • the fuel nozzle inlet 20 is designed with a larger gap height h.
  • the maximum utilization of the acceptable pressure loss and the avoidance of parasitic pressure losses takes place at the fuel nozzle outlet 4. This results in stable combustion.
  • the fuel nozzle inlet 20 is also rounded, the rounding having a fuel nozzle inlet radius Re.
  • the rounding points away from a fuel nozzle interior.
  • the ratio of the fuel nozzle inlet radius Re and the gap height h is greater than 0.2 and less than 0.8. This results in a uniform flow acceleration up to the blade inflow edge 51, which causes a minimization of the inlet pressure losses and on the blades 12 a uniform flow profile.
  • this can also be done by a straight nozzle 1 with a straight fuel nozzle inlet 20 are caused by an angle ⁇ 75 ° (not shown).
  • the blade inflow edge 51 has the above-mentioned upstream relative axial distance of about 1 ⁇ s (distance) / h (gap height) ⁇ 4 to the fuel nozzle inlet 20.
  • the nozzle 1 is thus designed such that by reducing the gap height h at the fuel nozzle inlet 20, the axial velocity is increased before the blades 12 and a uniform acceleration of the gas takes place until it leaves the nozzle 1.
  • the gap height h at the fuel nozzle outlet 4 is between 0.1 ⁇ h (gap height) / Ra ⁇ 0.2, where Ra represents the outer fuel nozzle radius Ra, so that a Mach number in the range 0.4 ⁇ Ma ⁇ 0.8 is maintained, resulting in a better acoustic decoupling of the fuel system caused by combustion chamber pressure oscillations.
  • an increase in the mixing energy is associated with the higher Mach number. Due to the smaller gap height h than in the nozzles of the prior art at the nozzle outlet 4 also mixing paths are minimized.
  • the blades 12 additionally have a blade angle of attack ( Fig. 2 ).
  • the blade angle of attack is to be selected, in which the highest possible swirl number S is set, but without causing a flow separation at the blade trailing edge 60 and the hub 70, wherein the swirl number S sets the angular momentum current to the axial momentum ratio.
  • the hub 70 that part of the secondary feed unit is referred to, which is located on the axial grid 22 and which represents the inner boundary of the fuel nozzle 1 at the nozzle outlet 4.
  • the swirl number S is in a range of greater than 1.2 and less than 1.7.
  • the ratio of the radius Ri of the secondary feed unit to the outer fuel nozzle radius Ra of the fuel nozzle 1 must be greater than 0.6 and less than 0.8 at the fuel nozzle outlet 4. Since the swirl number S depends on the ratio Ri / Ra, compliance with the ratio, that the synthesis gas flow still follows the contour of the fuel nozzle 1, without detaching itself on the hub side.
  • the fuel-air mixture which flows through the axial grid 22, also has a tangential flow direction 100 (swirl). Also in the fuel nozzle 1, a tangential flow direction 110 is impressed on the synthesis gas stream by an angle of attack of the blades 12. The blade angle can now be arranged so that the tangential flow directions 100 and 110 now have an opposite direction of rotation. For this purpose, the blades 12 and the axial grid 22 must have an opposing arrangement. This causes a significant increase in the mixing intensity due to the increased shear rates in the contact zones of the flows 100 and 110.
  • the relative velocities between the air-fuel mixture and synthesis gas is well above the relative velocities of a co-directional arrangement, which in turn significantly higher mixing of the two streams entails. This in turn has a positive effect on NOx emissions.
  • the air flowing through the annular passage 40 has a twist 120. This is preferably rectified to the swirl flow 100.
  • the fuel nozzle 1, seen in the flow direction after the blades 12 still have holes 130.
  • the air of the annular channel 40 can occur when the burner is not in the synthesis gas operation.
  • an operation of the burner without synthesis gas is possible when fuel is supplied via the pilot burner or fuel via the Ergaspassage 35.
  • no hot gas, which is present in the combustion zone 10 can flow back through the nozzle 1 during operation without synthesis gas.
  • the holes 130 may be formed in the flow direction with an inlet shell (7), which projects into the channel 40.
  • the air L "can be more selectively flowed through the holes 130 into the nozzle 1, thus the hot gas even more targeted to prevent hot gas from the combustion zone 10 flows back into the nozzle 1.
  • FIG. 2 shows a fuel nozzle 1 according to the invention in detail.
  • This nozzle 1 has an inner wall 50.
  • the blades 12 are arranged annularly over the circumference of the inner wall 50.
  • the nozzle 1 is conical over the entire area of the hub 70 (FIG. Fig. 1 ), resulting in a lower gap height h at the fuel nozzle outlet 4 ( Fig. 1 ) than is the case with the nozzles of the prior art.
  • the volume flow of the synthesis gas which must be supplied through the burner according to the invention of the combustion zone 10, can be reduced with the same NOx emissions.
  • the better acoustic stability allows for an extended operating range of the burner according to the invention in terms of load and fuel quality.

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

Claims (13)

  1. Brûleur de turbines qui a une unité d'apport secondaire, pour l'apport d'un combustible secondaire ou d'air et pour l'évacuation du combustible ou de l'air par une ouverture ( 6 ), d'une zone ( 10 ) de combustion et une unité d'apport primaire, qui a une tube ( 11 ) de mélange primaire et une tuyère ( 1 ) de combustible ayant, pour l'apport d'un combustible primaire, une sortie ( 4 ) de tuyère, tournée vers la zone de combustion, la tuyère ( 1 ) de combustible ainsi que le tube ( 11 ) de mélange primaire étant disposés concentriquement autour de l'unité d'apport secondaire, le tube ( 11 ) de mélange primaire et la tuyère ( 1 ) de combustible ayant une liaison fluidique, la tuyère ( 1 ) de combustible ayant une paroi ( 9 ) annulaire, qui est à distance, dans la direction axiale, radialement de l'unité d'apport secondaire, de manière à former une hauteur ( h ) de fente, par la paroi ( 9 ) annulaire et par l'unité d'apport secondaire, la paroi ( 9 ) annulaire de la tuyère ( 1 ) de combustible ayant une paroi ( 50 ) intérieure dirigée vers l'unité d'apport secondaire, un canal pour du fluide étant formé entre l'unité d'apport secondaire et la paroi ( 9 ) annulaire et des aubes ( 12 ) étant disposées dans le canal pour du fluide,
    caractérisé en ce que les aubes ( 12 ) ont, sur le côté en amont dans le sens du courant, un bord ( 51 ) d'afflux et la tuyère ( 1 ) de combustible a une entrée ( 20 ) de combustible et les aubes ( 12 ) sont à une distance ( s ) axiale de cette entrée ( 20 ) de tuyère, le rapport de la distance ( s ) et de la hauteur ( h ) de fente étant plus grand que 1 et plus petit que 4, et l'entrée ( 20 ) de la tuyère étant réalisée en ayant une hauteur de fente assez grande, de sorte que l'entrée du combustible soit élargie.
  2. Brûleur de turbines suivant la revendication 1,
    caractérisé en ce que les aubes ( 12 ) sont disposées annulairement sur le pourtour de la paroi ( 50 ) intérieure.
  3. Brûleur de turbines suivant la revendication 1,
    caractérisé en ce que l'unité d'apport secondaire a une paroi extérieure dirigée vers la tuyère ( 1 ), les aubes ( 12 ) étant disposées annulairement sur tout le pourtour de la paroi extérieure.
  4. Brûleur de turbines suivant l'une des revendications précédentes,
    caractérisé en ce que la tuyère ( 1 ) est, dans la direction d'écoulement, au moins en partie conique.
  5. Brûleur de turbines suivant la revendication 4,
    caractérisé en ce que la tuyère ( 1 ) a, dans la direction d'écoulement, considérée après les aubes ( 12 ), une réduction continue de la hauteur ( h ) de fente.
  6. Brûleur de turbines suivant l'une des revendications précédentes,
    caractérisé en ce que l'entrée ( 20 ) de la tuyère est arrondie, l'arrondi ayant un rayon ( Re ) d'entrée de tuyère, l'arrondi s'éloignant de l'intérieur de la tuyère.
  7. Brûleur de turbines suivant la revendication 6,
    caractérisé en ce que le rapport du rayon ( Re ) d'entrée de la tuyère et de la hauteur ( h ) de fente est plus grand que 0.2 et plus petit que 0.8.
  8. Brûleur de turbines suivant l'une des revendications précédentes,
    caractérisé en ce que la tuyère ( 1 ) a un rayon ( Ra ) extérieur.
  9. Brûleur de turbines suivant la revendication 8,
    caractérisé en ce qu'à l'entrée ( 20 ) de la tuyère, le rapport de la hauteur ( h ) de fente et du rayon ( Ra ) de la tuyère est plus grand que 0.2 et plus petit que 0.3.
  10. Brûleur de turbines suivant la revendication 8 ou 9,
    caractérisé en ce que l'unité d'apport secondaire a un rayon ( Ri ) et, à la sortie ( 4 ) de la tuyère, le rapport du rayon ( Ri ) au rayon ( Ra ) extérieur de la tuyère ( 1 ) est plus grand que 0.6 et plus petit que 0.8.
  11. Brûleur de turbines suivant l'une des revendications précédentes,
    caractérisé en ce que la tuyère ( 1 ) a des trous ( 130 ), qui, considérés dans la direction du courant, sont en aval des aubes ( 12 ) et qui sont disposés sur tout le pourtour de la paroi ( 9 ) de la tuyère ( 1 ).
  12. Brûleur de turbines suivant la revendication 11,
    caractérisé en ce que les trous ( 130 ) ont une cuvette ( 7 ) d'entrée.
  13. Brûleur de turbines suivant l'une des revendications précédentes,
    caractérisé en ce qu'au moins en partie autour de l'unité d'apport primaire est disposé un canal ( 40 ) annulaire, qui a plusieurs dispositifs ( 45 ) de tourbillonnement ayant des tuyères à combustible et disposés sur le pourtour.
EP11711862.0A 2010-06-18 2011-03-29 Brûleur de turbines Active EP2583033B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11711862.0A EP2583033B1 (fr) 2010-06-18 2011-03-29 Brûleur de turbines

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10166431A EP2397764A1 (fr) 2010-06-18 2010-06-18 Brûleur de turbines
EP11711862.0A EP2583033B1 (fr) 2010-06-18 2011-03-29 Brûleur de turbines
PCT/EP2011/054777 WO2011157458A1 (fr) 2010-06-18 2011-03-29 Brûleur de turbine

Publications (2)

Publication Number Publication Date
EP2583033A1 EP2583033A1 (fr) 2013-04-24
EP2583033B1 true EP2583033B1 (fr) 2014-06-25

Family

ID=43086876

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Application Number Title Priority Date Filing Date
EP10166431A Withdrawn EP2397764A1 (fr) 2010-06-18 2010-06-18 Brûleur de turbines
EP11711862.0A Active EP2583033B1 (fr) 2010-06-18 2011-03-29 Brûleur de turbines

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10166431A Withdrawn EP2397764A1 (fr) 2010-06-18 2010-06-18 Brûleur de turbines

Country Status (4)

Country Link
US (1) US8869535B2 (fr)
EP (2) EP2397764A1 (fr)
CN (1) CN102947650B (fr)
WO (1) WO2011157458A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2312215A1 (fr) * 2008-10-01 2011-04-20 Siemens Aktiengesellschaft Brûleur et procédé de fonctionnement d'un brûleur
US20160195271A1 (en) * 2013-09-23 2016-07-07 Siemens Aktiengesellschaft Burner for a gas turbine and method for reducing thermoacoustic oscillations in a gas turbine
US10731861B2 (en) * 2013-11-18 2020-08-04 Raytheon Technologies Corporation Dual fuel nozzle with concentric fuel passages for a gas turbine engine
EP2993406A1 (fr) 2014-09-03 2016-03-09 Siemens Aktiengesellschaft Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz
DE102021002508A1 (de) 2021-05-12 2022-11-17 Martin GmbH für Umwelt- und Energietechnik Düse zum Einblasen von Gas in eine Verbrennungsanlage mit einem Rohr und einem Drallerzeuger, Rauchgaszug mit einer derartigen Düse und Verfahren zur Verwendung einer derartigen Düse

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2079049C1 (ru) * 1991-04-25 1997-05-10 Сименс А.Г. Устройство горелки
DE19549143A1 (de) * 1995-12-29 1997-07-03 Abb Research Ltd Gasturbinenringbrennkammer
WO1999004196A1 (fr) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz
DE19757617A1 (de) * 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
ATE394637T1 (de) 2003-07-25 2008-05-15 Ansaldo Energia Spa Gasturbinenbrenner
EP1659339A1 (fr) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Procédé de démarrage d'un brûleur
US8104285B2 (en) * 2005-09-30 2012-01-31 Ansaldo Energia S.P.A. Gas turbine equipped with a gas burner and axial swirler for the burner
US7685823B2 (en) * 2005-10-28 2010-03-30 Power Systems Mfg., Llc Airflow distribution to a low emissions combustor
US8393891B2 (en) * 2006-09-18 2013-03-12 General Electric Company Distributed-jet combustion nozzle

Also Published As

Publication number Publication date
EP2397764A1 (fr) 2011-12-21
EP2583033A1 (fr) 2013-04-24
CN102947650B (zh) 2014-12-17
WO2011157458A1 (fr) 2011-12-22
US20130074506A1 (en) 2013-03-28
US8869535B2 (en) 2014-10-28
CN102947650A (zh) 2013-02-27

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