EP1662202B1 - Brûleur pour une turbine à gaz - Google Patents
Brûleur pour une turbine à gaz Download PDFInfo
- Publication number
- EP1662202B1 EP1662202B1 EP04028334.3A EP04028334A EP1662202B1 EP 1662202 B1 EP1662202 B1 EP 1662202B1 EP 04028334 A EP04028334 A EP 04028334A EP 1662202 B1 EP1662202 B1 EP 1662202B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- stage
- burner
- fuel stage
- burner according
- 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
Links
- 239000000446 fuel Substances 0.000 claims description 163
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 description 28
- 239000007789 gas Substances 0.000 description 26
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 14
- 239000000203 mixture Substances 0.000 description 12
- 239000007788 liquid Substances 0.000 description 7
- 230000010355 oscillation Effects 0.000 description 6
- 238000009792 diffusion process Methods 0.000 description 4
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000001228 spectrum Methods 0.000 description 2
- 230000002123 temporal effect Effects 0.000 description 2
- 241001156002 Anthonomus pomorum Species 0.000 description 1
- NYIWQJCNXCTWOB-UHFFFAOYSA-N [N].[N+][O-] Chemical class [N].[N+][O-] NYIWQJCNXCTWOB-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 238000000638 solvent extraction Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
Images
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
-
- 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
- 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
- F23D2900/14—Special features of gas burners
- F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
-
- 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 with at least one air supply, a primary fuel stage and a secondary fuel stage and a gas turbine plant with such a burner.
- a further reduction in nitrogen oxide formation is achieved by operating the burner in the so-called premix mode, in which the fuel is mixed with the air before it is ignited.
- Low-pollutant gas turbine plants are usually operated close to the lean stability limit, ie with an air-fuel mixture with a very low fuel content, ie very high excess air.
- the gas turbine plants are susceptible to combustion vibrations whose occurrence leads to serious damage to the gas turbine plant being able to lead.
- combustion oscillations arise due to an oscillating interaction between thermal and acoustic disturbances in the combustion process.
- resonators which damp the vibrations are used to reduce combustion oscillations.
- Such a resonator is for example in DE 44 14 232 A1 described.
- Other approaches to reducing combustion oscillations include optimizing the air-fuel mixture, adjusting the pressure losses of fuel nozzles and air passages, and actively modulating fuel flows. Such measures are for example in Geoff Meyers, et al. "Dry, Low Emissions for the 'H' Heavy-Duty Industrial Gas Turbines: Full-Scale Combustion System Ring Test Results, in proceedings of ASME Turbo Expo 2003: Power for Land, Sea and Air, June 16 - 19, 2003 Atlanta, Georgia , USA described.
- This document also includes a concept for staged fueling.
- a burner with a central fuel supply has four further fuel feeds arranged around the central fuel supply, which can be controlled independently of one another. Depending on the operating mode, the central fuel supply and the fuel feeds arranged around it are operated differently.
- a fuel-stacked axial-flow concept is described in Michael A. Davi and Marv Weiss in GE Gas Turbine Fuel Flexibility, GE Power Systems Schenectady, NY. Between a primary fuel supply and the diffusion zone in which the combustion takes place, a secondary fuel supply stage is arranged, which also has a supplementary air supply.
- Another object of the present invention is to provide an advantageous burner design.
- Another object of the present invention is to provide an advantageous gas turbine plant.
- the first object is achieved by a burner according to claim 1 and the second object by a gas turbine plant according to claim 11.
- the dependent claims contain advantageous embodiments of the invention.
- An inventive burner comprises at least one air supply and assigned to an air supply a primary fuel stage, which serves as a main stage for supplying fuel, and a secondary fuel stage, which serves as an auxiliary stage for the fuel supply.
- the secondary fuel stage is arranged in the air flow direction of the air supply upstream of the primary fuel stage.
- the primary fuel stage and the secondary fuel stage are arranged in the air supply such that no backflow regions form between them, i. that there is no flow from the primary fuel stage to the secondary fuel stage.
- the primary fuel stage can be used to bring about a homogeneous spatial mixture of fuel and air in the air supply characteristic of a low-emission combustion.
- the secondary fuel stage arranged upstream as seen in the air flow direction, the temporal air-fuel mixture can be mixed in the burner to reduce combustion oscillations.
- the fuel mass flow supplied by the secondary fuel stage is to be regulated independently of the fuel mass flow supplied by the primary fuel stage.
- the secondary fuel stage may also be designed to supply a fuel mass flow which corresponds to a maximum of 30% of the fuel mass flow supplied by the primary fuel stage.
- the secondary fuel stage By increasing the fuel mass flow supplied via the secondary fuel stage, it is also possible to increase the capacity for introducing fuel into the air supply, which may be expedient, for example, when using fuels with a low calorific value and / or with fuel preheating.
- the secondary fuel stage thus allows an expansion of the fuel spectrum or an increased fuel flexibility of the burner.
- Acoustic tuning of the secondary fuel stage to the primary fuel stage may be accomplished by having the secondary fuel stage impedance at a value that results in a reduction in airspeed variations or heat release variations over a burner without a secondary fuel stage.
- the impedance hereby expresses the acoustic resistance exerted by the fuel stage with respect to a pressure wave.
- An adaptation of the impedance can be achieved, for example, by suitably dimensioning at least one fuel passage in the region of the secondary fuel stage.
- the fuel passage may be formed as an annular fuel distributor passage, wherein the impedance may be varied by varying the volume of the fuel distributor passage.
- the impedance can be adapted by a fuel supply line to the secondary fuel stage is present, which is equipped with at least one acoustic filter, which may be embodied for example as a resonator.
- the secondary fuel stage comprises fuel nozzles configured to reduce the pressure loss of the fuel supplied through these nozzles than the pressure loss of the fuel supplied via the nozzles of the primary fuel stage.
- the burner according to the invention can be designed, in particular, as a so-called premix burner to be operated in a premixing mode or as a hybrid burner, that is to say as a burner which is to be operated in both the diffusion and premix mode.
- it can also be designed as a so-called.
- Mehrbrennstoffbrenner so as a burner, which is designed for the combustion of different fuels.
- it can be designed as a multi-fuel burner both for burning gaseous as well as for burning liquid fuels.
- a gas turbine plant according to the invention is equipped with a burner according to the invention.
- a burner according to the invention In her can be realized the advantages described with reference to the burner according to the invention. In particular, combustion oscillations can be reduced during operation of the system.
- the gas turbine plant 101 has a compressor 102 for combustion air, a combustion chamber or gas turbine combustor 104 and a turbine 106 for driving the compressor 102 and a generator, not shown, or a working machine.
- the turbine 106 and the compressor 102 are arranged on a common turbine shaft 108, also referred to as turbine rotor, to which the generator or the working machine is also connected and which is rotatably mounted about its central axis 109.
- the combustor 104 is equipped with a number of burners 110 for combustion of a liquid or gaseous fuel. It is also provided on its inner wall or Brennschwandung 123 with interior trim elements 125.
- the turbine 106 includes a number of rotatable blades 112 connected to the turbine shaft 108.
- the blades 112 are annularly disposed on the turbine shaft 108 and thus form a number of blade rows.
- the turbine 106 includes a number of fixed vanes 114 which are also annularly attached to an inner shell 116 of the turbine 106 to form vanes.
- the blades 112 serve to drive the turbine shaft 108 by momentum transfer from the turbine 106 flowing through the working medium M.
- the vanes 114 serve to guide the flow of the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
- a successive pair of a ring of vanes 114 or a row of vanes and from a ring of blades 112 or a blade row is also referred to as a turbine stage.
- Each guide blade 114 has a platform 118, also referred to as a blade root 119, which is arranged as a wall element for fixing the respective guide blade 114 to the inner housing 16 of the turbine 106.
- the platform 118 is a thermally comparatively heavily loaded component which forms the outer boundary of a hot gas channel for the turbine 106 flowing through the working medium M.
- Each blade 112 is attached in an analogous manner to the turbine shaft 108 via a blade root 119, also referred to as a platform 118, the blade root 119 each carrying a profiled blade 120 extending along a blade axis.
- each guide ring 121 is arranged on the inner housing 116 of the turbine 106.
- the outer surface of each guide ring 121 is also exposed to the hot, the turbine 106 flowing through the working fluid M and spaced radially from the outer end 122 of the blade 112 opposite it through a gap.
- the guide rings 121 arranged between adjacent guide blade rows serve, in particular, as cover elements which protect the inner wall 116 or other housing installation parts from thermal overload by the hot working medium M flowing through the turbine 106.
- the gas turbine plant 101 is designed for a comparatively high outlet temperature of the working medium M emerging from the combustion chamber 104 from about 1200 ° C. to 1300 ° C.
- the combustion chamber wall 123 is internally cooled.
- the combustion air is heated in a desired manner at the same time.
- the burner according to the invention comprises an internal burner system 1, which is referred to below as a pilot burner system, and a main burner system 3 arranged concentrically around the pilot burner system 1.
- the burner is designed as a multi-fuel burner which is suitable both for burning gaseous fuels and for burning liquid fuels.
- it is designed as a hybrid burner, ie it can be operated both in the diffusion mode and in the premix mode.
- the pilot burner system 1 includes an inner liquid fuel supply passage 5, an inner gas supply passage 7 for gaseous fuels, and an inner air supply passage 9 for supplying combustion air.
- the inner gas supply channel 7 is arranged concentrically around the inner supply channel for liquid fuels around.
- Around the inner gas supply channel 7 around the inner air supply channel 9 is arranged concentrically.
- the inner supply channel for liquid fuels opens via a nozzle 11 into the combustion chamber 13.
- the inner gas supply channel 7, however, opens via outlet openings 15 in the air supply channel 9, where a mixing of the gaseous fuel with the air.
- a suitable ignition system is also arranged, which in FIG. 2 not shown.
- the pilot burner system 1 serves to maintain a pilot flame supporting the stability of the burner flame and, in principle, allows the burner to operate as a diffusion burner or as a burner with a premixed air-fuel mixture.
- the main burner system 3 arranged concentrically around the pilot burner system 1 comprises a primary fuel stage 20, a secondary fuel stage 50 and an air supply channel 17 arranged concentrically around the pilot burner system 1.
- the two fuel stages 20, 50 are arranged axially one behind the other in the air supply direction (arrow A) and serve for supply a gaseous fuel. They each include a number of nozzle tubes 22, 52 with fuel nozzles 24, 54 disposed therein, with the nozzle tubes 54 of the secondary fuel stage 50 being disposed upstream of the nozzle tubes 22 of the primary fuel stage 20 as viewed in the air supply direction.
- the two fuel stages each comprise 20 distributed over the circumference of the main burner system 3 nozzle tubes 22, 52, on which the fuel nozzles 24, 54 are arranged radially.
- the nozzle tubes 22, 52 are each connected to ring manifolds 26 and 56, via which the gaseous fuel is supplied to them.
- the ring manifold 26 of the primary fuel stage 20 and the ring manifold 56 of the secondary fuel stage 50 are each supplied with gas via a number of evenly distributed around the pilot combustion system 1 around gas supply lines 28, 58.
- the main burner system 3 also includes a supply system 19 for supplying liquid fuels, which will not be discussed further.
- the impedance of the secondary fuel stage 50 is matched to the impedance of the primary fuel stage 20 by suitably dimensioning the ring manifold 56 and resonators 60 disposed in the gas supply lines 58.
- Both fuel stages 20,50 are separately controllable, wherein the secondary fuel stage is controlled such that it receives a maximum of 30% of the fuel mass flow of the main burner 3.
- An optimization of the air-fuel mixture in the burner is achieved by suitable arrangement of the nozzles 54 de secondary fuel stage.
- the nozzles 54 are configured such that the pressure loss of the fuel via these nozzles 54 is lower than the pressure loss of the fuel via the nozzles 24 of the primary fuel stage 20.
- the secondary fuel stage 50 fulfills various tasks. It serves, for example, to reduce fluctuations in the number of air-burners in the burner, that is to say temporal variations in the air-fuel mixture ratio. This can be accomplished by properly dividing the fuel mass flow to the primary fuel stage 20 and the secondary fuel stage 50. Proper partitioning also makes it possible to vary the spatial air-fuel mixture field in the burner.
- the use of the secondary fuel stage 50 also increases the capacity for introducing fuel into the air supply passage, which may be useful, for example, when using fuels with a low calorific value and / or with fuel pre-heating.
- the secondary fuel stage 50 thus allows in particular an extension of the fuel spectrum or an increased fuel flexibility of the burner. By separately controlling the primary fuel stage 20 and the secondary fuel stage 50, the aforementioned effects can be achieved or maintained even with changes in the ambient conditions, the combustion gas properties or the performance of the turbine system.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Claims (11)
- Brûleur pour une installation de turbine à gaz, comprenant au moins un apport (17) d'air, un étage (20) de combustible primaire, ainsi qu'un étage (50) de combustible secondaire, qui sont associés à un apport (17) d'air, caractérisé en ce que l'étage (50) de combustible secondaire est monté, dans le sens (A) d'écoulement de l'air de l'apport (17) d'air, en amont de l'étage (20) de combustible primaire, de sorte que les deux étages (20, 50) de combustible sont disposés l'un derrière l'autre axialement dans le sens d'apport de l'air de sorte qu'aucun écoulement n'arrive de l'étage (20) de combustible primaire à l'étage (50) de combustible secondaire et qu'il ne se forme pas ainsi de domaine de reflux entre l'étage (20) de combustible primaire et l'étage (50) de combustible secondaire, et dans lequel le courant massique de combustible apporté par l'étage (50) de combustible secondaire peut être réglé indépendamment du courant massique de combustible apporté par l'étage (20) de combustible primaire.
- Brûleur suivant l'une des revendications précédentes, caractérisé en ce que l'étage (50) de combustible secondaire est conçu pour apporter un courant massique de combustible qui représente au maximum 30% du courant massique de combustible apporté par l'étage (20) de combustible primaire.
- Brûleur suivant l'une des revendications précédentes, caractérisé en ce que l'étage (50) de combustible secondaire comprend des buses (54) à combustible, qui sont disposées de manière à effectuer un mélange optimisé du combustible à l'air.
- Brûleur suivant l'une des revendications précédentes, caractérisé en ce que l'étage (50) de combustible secondaire comprend des buses (54) à combustible, qui sont conformées de manière à ce que la perte de charge du combustible apporté par ces buses soit maintenu plus petite que la perte de charge du combustible apporté par les buses (24) de l'étage (20) de combustible primaire.
- Brûleur suivant la revendication 4, caractérisé en ce que l'impédance de l'étage (50) de combustible secondaire a une valeur qui, par rapport à un brûleur sans étage (50) de combustible secondaire, entraîne une diminution des fluctuations de l'indice d'air ou des fluctuations de dégagements de chaleur.
- Brûleur suivant la revendication 5, caractérisé en ce que l'impédance est donnée par un dimensionnement approprié d'au moins un passage (56) pour du combustible allant à l'étage (50) de combustible secondaire.
- Brûleur suivant la revendication 6, caractérisé en ce qu'il comprend comme passage pour du combustible allant à l'étage (50) de combustible secondaire un conduit (56) formant répartiteur de combustible, dont le dimensionnement est choisi en fonction d'une adaptation d'impédance.
- Brûleur suivant l'une des revendications 5 à 7, caractérisé en ce qu'il comprend un conduit (58) d'apport de combustible allant à l'étage (50) de combustible secondaire et équipé d'au moins un filtre (60) acoustique.
- Brûleur suivant l'une des revendications précédentes, caractérisé par une conformation en brûleur hybride.
- Brûleur suivant l'une des revendications précédentes, caractérisé par sa conformation en brûleur à plusieurs combustibles.
- Installation de turbine ayant un brûleur suivant l'une des revendications précédentes.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04028334.3A EP1662202B1 (fr) | 2004-11-30 | 2004-11-30 | Brûleur pour une turbine à gaz |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04028334.3A EP1662202B1 (fr) | 2004-11-30 | 2004-11-30 | Brûleur pour une turbine à gaz |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1662202A1 EP1662202A1 (fr) | 2006-05-31 |
EP1662202B1 true EP1662202B1 (fr) | 2016-11-16 |
Family
ID=34927580
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04028334.3A Active EP1662202B1 (fr) | 2004-11-30 | 2004-11-30 | Brûleur pour une turbine à gaz |
Country Status (1)
Country | Link |
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EP (1) | EP1662202B1 (fr) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ITTO20070193A1 (it) * | 2007-03-14 | 2008-09-15 | Ansaldo Ricerche S P A | Bruciatore premix di una turbina a gas, in particolare per una microturbina |
DE102009038845A1 (de) * | 2009-08-26 | 2011-03-03 | Siemens Aktiengesellschaft | Drallschaufel, Brenner und Gasturbine |
DE102009038848A1 (de) * | 2009-08-26 | 2011-03-03 | Siemens Aktiengesellschaft | Brenner, insbesondere für Gasturbinen |
US20140123649A1 (en) * | 2012-11-07 | 2014-05-08 | Juan E. Portillo Bilbao | Acoustic damping system for a combustor of a gas turbine engine |
ITMI20122154A1 (it) * | 2012-12-17 | 2014-06-18 | Ansaldo Energia Spa | Gruppo bruciatore, camera di combustione comprendente detto gruppo bruciatore e metodo per alimentare detto gruppo bruciatore |
WO2016037966A1 (fr) * | 2014-09-12 | 2016-03-17 | Siemens Aktiengesellschaft | Brûleur comprenant un oscillateur fluidique pour une turbine à gaz et turbine à gaz comprenant au moins un brûleur de ce type |
DE102017114362A1 (de) * | 2017-06-28 | 2019-01-03 | Man Diesel & Turbo Se | Brennkammer einer Gasturbine, Gasturbine und Verfahren zum Betreiben derselben |
CN109237514B (zh) * | 2018-08-08 | 2024-02-23 | 中国华能集团有限公司 | 一种用于燃气轮机的双管路气体燃料燃烧器 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0611434A1 (fr) * | 1991-11-15 | 1994-08-24 | Siemens Aktiengesellschaft | Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz |
US5813232A (en) * | 1995-06-05 | 1998-09-29 | Allison Engine Company, Inc. | Dry low emission combustor for gas turbine engines |
GB2348484B (en) * | 1997-03-10 | 2001-03-21 | Gen Electric | Dynamically uncoupled low NOx combuster |
EP0936406B1 (fr) * | 1998-02-10 | 2004-05-06 | General Electric Company | Brûleur à prémélange combustible/air uniforme pour une combustion à faibles émissions |
WO2000034715A1 (fr) * | 1998-12-09 | 2000-06-15 | Abb Alstom Power Uk Ltd. | Modification de la dynamique de reaction de combustion |
GB9915770D0 (en) * | 1999-07-07 | 1999-09-08 | Rolls Royce Plc | A combustion chamber |
DE19948674B4 (de) * | 1999-10-08 | 2012-04-12 | Alstom | Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen |
JP2002031343A (ja) * | 2000-07-13 | 2002-01-31 | Mitsubishi Heavy Ind Ltd | 燃料噴出部材、バーナ、燃焼器の予混合ノズル、燃焼器、ガスタービン及びジェットエンジン |
US6820431B2 (en) * | 2002-10-31 | 2004-11-23 | General Electric Company | Acoustic impedance-matched fuel nozzle device and tunable fuel injection resonator assembly |
-
2004
- 2004-11-30 EP EP04028334.3A patent/EP1662202B1/fr active Active
Non-Patent Citations (1)
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Also Published As
Publication number | Publication date |
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EP1662202A1 (fr) | 2006-05-31 |
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