EP3376110B1 - Centrale électrique à turbine à gaz et procédé de fonctionnement de ladite centrale électrique à turbine à gaz - Google Patents

Centrale électrique à turbine à gaz et procédé de fonctionnement de ladite centrale électrique à turbine à gaz Download PDF

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Publication number
EP3376110B1
EP3376110B1 EP18161522.0A EP18161522A EP3376110B1 EP 3376110 B1 EP3376110 B1 EP 3376110B1 EP 18161522 A EP18161522 A EP 18161522A EP 3376110 B1 EP3376110 B1 EP 3376110B1
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EP
European Patent Office
Prior art keywords
burner
swirler
internal
fuel
external
Prior art date
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EP18161522.0A
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German (de)
English (en)
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EP3376110A1 (fr
Inventor
Aldo CHIARIONI
Roberto RIO
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Ansaldo Energia SpA
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Ansaldo Energia SpA
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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
    • F23R3/34—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
    • F23R3/38—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising rotary fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the invention relates to a gas turbine electric power plant and to a method for operating said gas turbine plant.
  • combustion technique Due to stricter and stricter rules in terms of polluting emissions, the combustion technique has developed towards the use of combustion chambers structured according to the so-called "lean premix" technology. This technique involves the use of premix burners.
  • Premix burners are supplied with an air-fuel mixture, with a strong excess of air, in order to generate a flame that is such as to ensure a uniform temperature field and avoid possible temperature peaks, which might lead to high NOx emission at the exhaust. By so doing, premix burners ensure a smaller quantity of polluting emissions.
  • the flames generated by premix burners are more likely to be subjected to dynamic instabilities.
  • the periodical fluctuations of the heat release can be associated with pressure fluctuations in the combustor, thus sustaining one another. If these fluctuations are coupled to the resonance frequencies of the mechanical components of the combustor, serious damages can be caused to the mechanical components themselves.
  • Flame instabilities can be thermoacoustic or fluid-dynamic and these two types can interact with one another.
  • Thermoacoustic instability phenomena are usually indicated with the term "humming".
  • Fluid-dynamic instability phenomena mainly occur in burners operating with a vortex flow.
  • An example of fluid-dynamic instability typical of this type of burners is the generation of a precessing vortex core (PVC).
  • the object of the invention is to provide a gas turbine electrical power plant, which is stable and efficient and, at the same time, is capable of keeping polluting emission levels below the limits provided for by law.
  • the invention relates to a gas turbine electrical power plant according to claim 1.
  • a further object of the invention is to provide a method for operating a gas turbine electrical power plant, which is effective and capable of ensuring stability during the combustion as well as, at the same time, low polluting emission levels.
  • the invention relates to a method for operating a gas turbine electrical power plant according to claim 6.
  • number 1 indicates an electrical power plant comprising a gas turbine 2 extending along an axis A, a compressor 3, a combustor 4, a fuel supply unit 6 configured to supply fuel to the combustor 4, and a generator 7, which transforms the mechanical power provided by the gas turbine 2 into emitted electrical power.
  • the combustor 4 preferably is annular and comprises a plurality of seats 8, each designed to be engaged by a burner unit 9 (which is better visible in figures 2-3 ).
  • the seats 8 are arranged along a circular path close to a peripheral edge of the combustor 4. In the non-limiting embodiment described and discussed herein, there are twenty-four seats 8 and burner units 9.
  • each burner unit 9 extends along an axis B and comprises an internal burner 10, an external burner 11, which extends around the internal burner 10, and an intermediate burner 12, which is arranged between the external burner 11 and the internal burner 10 around the internal burner 10.
  • the internal burner 10 extends along the axis B or extends around the axis B so as to create a hollow space that is left free so that it can house possible auxiliary devices.
  • the burner unit 9 further comprises an auxiliary device 14, which is arranged along the axis B, and the internal burner 10 extends around the auxiliary device 14.
  • the auxiliary device 14 is supplied with air coming from the compressor 3.
  • Variants that are not shown herein involve the use of an auxiliary device provided with at least one additional supply for a secondary fuel, such as for example natural gas or Diesel fuel.
  • the internal burner 10, the external burner 11 and the intermediate burner 12 are supplied by the fuel supply unit 6.
  • the fuel supply unit 6 is configured so that the internal burner 10, the external burner 11 and the intermediate burner 12 are supplied with fuel in an independent manner.
  • the quantity of fuel supplied to the internal burner 10 can be regulated independently of the quantity of fuel supplied to the external burner 11 and to the intermediate burner 12, and vice versa.
  • the fuel supply unit 6 comprises at least one first manifold 15, which is configured to supply fuel to the internal burners 10 (schematically shown in figure 3 ) of the burner units 9 of the combustor 4, a second manifold 16, which is configured to supply fuel to the external burners 11 (schematically shown in figure 3 ) of the burner units 9 of the combustor 4, and a third manifold 17, which is configured to supply fuel to the intermediate burners 12 (schematically shown in figure 3 ) of the burner units 9 of the combustor 4.
  • the first manifold 15, the second manifold 16 and the third manifold 17 are connected to the same tank 20 by means of respective supply lines provided with respective regulating valves 21a, 21b, 21c.
  • the quantity of fuel to be supplied to each manifold 15, 16, 17 can be regulated in an independent manner.
  • the regulating valves 21a, 21b, 21c are connected to a control system (which is not shown in the accompanying drawings).
  • the fuel in the tank 20 is natural gas.
  • the internal burner 10, the external burner 11 and the intermediate burner 12 are supplied with air coming from the compressor 3 and with fuel coming from the fuel supply unit 6.
  • the air and the fuel are supplied along a supply direction D1 directed towards the inside of the combustor 4.
  • the internal burner 10 comprises an internal air supply channel 24 and an internal fuel supply channel 25 (which is partially visible in figure 2 ).
  • the internal air supply channel 24 is an annular channel extending around the axis B and around the auxiliary device 14 and is supplied with air coming from the exhaust of the compressor 3.
  • the internal air supply channel 24 is in communication with the inside of a case (not shown), which is supplied with air coming from the compressor 3.
  • the internal air supply channel 24 is sized so as to supply a given air flow rate.
  • an auxiliary regulating device 24a which is optional and is usually used to further regulate the flow rate flowing into the internal burner 10.
  • the auxiliary regulating device 24a is a narrowing of the passageway section of the internal air supply channel 24 and is defined by a ring coupled to the internal surface of the wall which defines the internal air supply channel 24 and is proximal to the axis B.
  • the auxiliary regulating device 24a is defined by a ring coupled to the internal surface of the wall which defines the internal air supply channel 24 and is distal relative to the axis B.
  • an internal swirler 26 which is provided with a plurality of blades 27.
  • the internal swirler 26 is arranged at the outlet of the internal air supply channel 24.
  • the internal swirler 26 is a diagonal swirler.
  • the internal swirler 26 is axial.
  • diagonal swirler we mean a swirler where the blades extend between walls which are shaped so as to define a channel that is substantially transverse to the axis B (annular channel substantially shaped like a truncated cone), whereas by axial swirler we mean a swirler where the blades extend between walls which are substantially shaped so as to define a channel that is parallel to the axis B (substantially cylindrical annular channel).
  • the internal fuel supply channel 25 is connected to the manifold 15 (which is not shown in figure 2 ) and is supplied with a given fuel flow rate QCI.
  • the internal fuel supply channel 25 is an annular channel extending around the axis B and arranged between the auxiliary device 14 and the internal air supply channel 24 and is provided with a plurality of discharge nozzles 28 (only one of them can be seen in figure 2 ).
  • the discharge nozzles 28 are positioned so as to lead between the blades of the internal swirler 26.
  • the intermediate burner 12 comprises an intermediate air supply channel 30 and an intermediate fuel supply channel 31 (which is partially visible in figure 2 ).
  • the intermediate air supply channel 30 is an annular channel extending around the axis B and around the internal burner 10 and is supplied with air coming from the exhaust of the compressor 3.
  • the intermediate air supply channel 30 is in communication with the inside of a case (not shown), which is supplied with air coming from the compressor 3.
  • the intermediate air supply channel 30 is sized so as to supply a given air flow rate QAIn.
  • An intermediate swirler 32 is arranged along the intermediate air supply channel 30.
  • the intermediate swirler 32 is a diagonal swirler provided with a plurality of blades 33.
  • the intermediate swirler 32 is arranged close to the outlet of the intermediate air supply channel 30.
  • the outlet of the intermediate swirler 32 is arranged upstream of the outlet of the internal swirler 26 along the supply direction D1.
  • the outlet of the intermediate swirler 32 is substantially aligned with the outlet of the internal swirler 26 along the supply direction D1.
  • substantially aligned we mean that the outlet of the intermediate swirler 32 and the outlet of the internal swirler 26 are substantially aligned along a direction that is orthogonal to the axis B.
  • outlet of the swirler we mean the outlet portion of the swirler that is axially located at the front along the supply direction D1.
  • the intermediate fuel supply channel 31 is connected to the manifold 17 and is supplied with a given fuel flow rate QCIn.
  • the intermediate fuel supply channel 31 is an annular channel extending around the axis B and arranged between the internal burner 10 and the intermediate air supply channel 30 and has a plurality of discharge nozzles 35 provided along at least some blades 33 of the swirler 32 (only some discharge nozzles 35 can be seen in figure 2 ).
  • the discharge nozzles 35 are obtained along the leading edge of the blades 33.
  • the intermediate swirler 32 is configured so as to help the mixing between the air and the fuel injected into the intermediate air supply channel 30 by the discharge nozzles 35. Indeed, the intermediate swirler 32 is configured so to support the creation of vortexes that facilitate the mixing between air and fuel.
  • the intermediate swirler 32 is an axial swirler.
  • the intermediate swirler 32 and the internal swirler 26 are co-rotating.
  • the intermediate swirler 32 and the internal swirler 26 are configured to cause the inflow to make a rotation in the same direction.
  • the intermediate swirler 32 is counter-rotating relative to the internal swirler 26.
  • the intermediate swirler 32 and the internal swirler 26 are configured to cause the inflow to make a rotation in two opposite directions.
  • the blades 33 of the intermediate swirler 32 are characterized by a blade airfoil that is optimized to as have a uniform profile of the axial velocity of the flow and avoid sudden accelerations or decelerations of the flow itself.
  • the blades 33 of the intermediate swirler 32 are characterized by the following aerodynamic parameters:
  • the external burner 11 comprises an intermediate air supply channel 40 as well as a main external fuel supply channel 41a (which is partially visible in figure 2 ) and a secondary external fuel supply channel 41b.
  • the external air supply channel 40 is an annular channel provided with an axial portion 42, which extends around the axis B, and an inclined portion 43, which extends along a direction that is inclined relative to the axis B.
  • the inclined portion 43 is in communication with the inside of a case (not shown), which is supplied with air coming from the compressor 3.
  • the axial portion 42 leads into the combustor 4 and preferably is coupled to a cylindrical outlet element 44 (generally defined CBO).
  • the external air supply channel 40 is sized so as to supply a given air flow rate QAE.
  • the external air supply channel 40 is provided with an external swirler 45.
  • the external swirler 45 is arranged along the inclined portion 43.
  • the external swirler 45 is a diagonal swirler provided with a plurality of blades 46.
  • outlet of the external swirler 45 is arranged upstream of outlet of the intermediate swirler 32 and of the outlet of the internal swirler 26 along the supply direction D1.
  • outlet of the swirler we mean the outlet portion of the swirler that is axially located at the front along the supply direction D1.
  • the main external fuel supply channel 41a is connected to the manifold 16 and is supplied with a given fuel flow rate QCEp.
  • the main external fuel supply channel 41a is an annular channel extending around the axis B and arranged between the intermediate burner 12 and the external air supply channel 40 and is provided with a plurality of discharge nozzles 47 (only one of them are visible in figure 2 ), which are obtained along at least some blades 46 of the swirler 45.
  • the discharge nozzles 47 are obtained along the leading edge of the blades 46.
  • the secondary external fuel supply channel 41b is optional and is connected to a secondary manifold (also optional), which is not shown in figure 3 .
  • the secondary external fuel supply channel 41b is supplied with a given fuel flow rate QCEs.
  • the secondary external fuel supply channel 41b is an annular channel extending around the axis B and arranged between the intermediate burner 12 and the main external fuel supply channel 41a and has a plurality of discharge nozzles 48 (only some of them are visible in figure 2 ), which are provided along the wall of the external air supply channel 40 substantially at the trailing edge of the blades 46 of the swirler 45.
  • the external swirler 45 is configured so as to help the mixing between the air and the fuel injected into the external air supply channel 40 by the discharge nozzles 47 and by the discharge nozzles 48. Indeed, the external swirler 45 is configured to support the creation of vortexes that facilitate the mixing between air and fuel.
  • the offset position of the external swirler 45, of the intermediate swirler 32 and of the internal swirler 26 supports the generation of one single combustion zone, where the shape of the inner recirculation zone (IRZ) is well defined, so as to reduce the creation of precessing vortex cores (PVC).
  • IRZ inner recirculation zone
  • This configuration permits a regulation of the shape of the flame front and, especially, of the IRZ.
  • the shape of the IRZ can be substantially represented like a parabola having a vertex V arranged along the axis B and a concavity facing the inside of the combustor 4.
  • the intermediate swirler 32 and the internal swirler 26 create two flows, whose vortex component is substantially different and, in addition, can be regulated by means of a controlled and differentiated supply of the internal burner 10 and of the intermediate burner 12.
  • the parabola which schematically defines the shape of the inner recirculation zone - IRZ, is characterized by a widening in a direction that is orthogonal to the axis B, which definitely is already significant in the proximity of the vertex V of the parabola. In this way, a "flattened" shape of the IRZ is obtained, which positively affects the PVC (precessing vortex core) and, as a consequence, determines an improvement of flame stability.
  • the periodic motion of the PVC is prevented from affecting the mixing of the gas in the different areas of interest. This avoids the occurrence of a gas mixing variation phenomenon, which is also periodic and associated with the motion of the PVC itself.
  • the intermediate swirler there is an increase in the degree of air/fuel mixing, which is necessary for the reduction of polluting emissions. Furthermore, thanks to the possibility of independently supplying the internal burner 10, the external burner 11 and the intermediate burner 12, a gradual mixing profile can be created, which helps generate a more stable flame.
  • the degree of mixing can be modulated in the internal swirler 28, in the intermediate swirler 32 and in the external swirler 45, though keeping the power of the burner unit 9, as a whole, constant. By so doing, areas with different values of the air/fuel ratio can be obtained in the combustion zone.
  • the supply of fuel to the internal swirler 28 is regulated so that the air/fuel ratio is smaller than the air/fuel ratios of the intermediate swirler 32 and of the external swirler 45. In this way, a "micro-pilot" flame is obtained in the area of the axis B, which helps increase the stability of the combustion without drastically worsening the quantity of polluting emissions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (7)

  1. Centrale électrique à turbine à gaz comprenant :
    - une chambre de combustion (4) munie d'au moins une unité de brûleur (9) ; dans laquelle l'unité de brûleur (9) s'étend autour d'un axe longitudinal (B) et comprend :
    • un brûleur interne (10) alimenté en air et en carburant, qui s'étend autour de l'axe longitudinal (B) et est muni d'au moins une coupelle rotative interne (28) ;
    • un brûleur externe (11) alimenté en air et en carburant, qui s'étend autour du brûleur interne (10) et est muni d'au moins une coupelle rotative externe (45) ;
    • un brûleur intermédiaire (12) alimenté en air et en carburant, qui est disposé entre le brûleur externe (11) et le brûleur interne (10) autour du brûleur interne (10) et est muni d'une coupelle rotative intermédiaire (32) ;
    • la sortie de la coupelle rotative intermédiaire (32) étant disposée en amont de la sortie de la coupelle rotative interne (26) ou alignée avec la sortie de la coupelle rotative interne (26) dans la direction d'alimentation (D1) de l'air et du carburant dirigés vers l'intérieur de la chambre de combustion (4) ; la sortie de la coupelle rotative externe (45) est disposée en amont de la sortie de la coupelle rotative intermédiaire (32) ;
    - une unité d'alimentation en carburant (6) munie d'au moins un premier collecteur (15) conçu pour alimenter en carburant le brûleur interne (10) de l'au moins une unité de brûleur (9) de la chambre de combustion (4), un deuxième collecteur (16) conçu pour alimenter en carburant le brûleur externe (11) de l'au moins une unité de brûleur (9) de la chambre de combustion (4), et un troisième collecteur (17) conçu pour alimenter en carburant le brûleur intermédiaire (12) de l'au moins une unité de brûleur (9) de la chambre de combustion (4) ; dans laquelle le premier collecteur (15), le deuxième collecteur (16) et le troisième collecteur (17) sont reliés au même réservoir (20) par des conduites d'alimentation respectives munies de vannes de régulation respectives (21a, 21b, 21c) ;
    - dans laquelle les vannes de régulation (21a, 21b, 21c) sont reliées à un système de commande ;
    dans laquelle l'alimentation en carburant de la coupelle rotative interne (28) est régulée de sorte que le rapport air/carburant est inférieur aux rapports air/carburant de la coupelle rotative intermédiaire (32) et de la coupelle rotative externe (45).
  2. Centrale selon la revendication 1, dans laquelle la coupelle rotative intermédiaire (32) est munie d'une pluralité d'aubes (33).
  3. Centrale selon la revendication 2, dans laquelle les aubes (33) ont un angle de fuite compris entre 55° et 70°.
  4. Centrale selon la revendication 2 ou 3, dans laquelle la chute de pression au niveau de la coupelle rotative intermédiaire (32) est inférieure ou égale à 117 kPa.
  5. Centrale selon l'une quelconque des revendications 2 à 4, dans laquelle la coupelle rotative intermédiaire (32) comprend un nombre d'aubes (33) compris entre 6 et 12.
  6. Procédé permettant de faire fonctionner une centrale électrique à turbine à gaz ; la centrale (1) comprenant un compresseur (3), une turbine à gaz (2) et une chambre de combustion (4) munie d'au moins une unité de brûleur (9) ; l'unité de brûleur (9) comprenant :
    • un brûleur interne (10) alimenté en air provenant de l'échappement du compresseur (3) et muni d'au moins une coupelle rotative interne (28) ;
    • un brûleur externe (11) alimenté en air provenant de l'échappement du compresseur (3) et muni d'au moins une coupelle rotative externe (45) ;
    • un brûleur intermédiaire (12) alimenté en air provenant de l'échappement du compresseur (3) et muni d'une coupelle rotative intermédiaire (32) ; dans lequel la sortie de la coupelle rotative intermédiaire (32) est disposée en amont de la sortie de la coupelle rotative interne (26) ou alignée avec la sortie de la coupelle rotative interne (26) dans la direction d'alimentation (D1) de l'air et du carburant dirigés vers l'intérieur de la chambre de combustion (4) et la sortie de la coupelle rotative externe (45) est disposée en amont de la sortie de la coupelle rotative intermédiaire (32) ; le procédé comprenant l'alimentation en carburant du brûleur interne (10), du brûleur externe (11) et du brûleur intermédiaire (12) de manière indépendante ; dans lequel l'étape d'alimentation en carburant du brûleur interne (10), du brûleur externe (11) et du brûleur intermédiaire (12) de manière indépendante comprend la régulation de l'alimentation en carburant du brûleur interne (10) de sorte que le rapport air/carburant est inférieur aux rapports air/carburant du brûleur intermédiaire (12) et du brûleur externe (11) .
  7. Procédé selon la revendication 6, dans lequel l'étape d'alimentation en carburant du brûleur interne (10), du brûleur externe (11) et du brûleur intermédiaire (12) de manière indépendante comprend la régulation de la quantité de carburant fournie à un premier collecteur (15), à un deuxième collecteur (16) et à un troisième collecteur (17), respectivement conçus pour alimenter en carburant au moins un brûleur interne (10), au moins un brûleur externe (11) et au moins un brûleur intermédiaire (12).
EP18161522.0A 2017-03-13 2018-03-13 Centrale électrique à turbine à gaz et procédé de fonctionnement de ladite centrale électrique à turbine à gaz Active EP3376110B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT102017000027637A IT201700027637A1 (it) 2017-03-13 2017-03-13 Gruppo bruciatore per un impianto a turbina a gas per la produzione di energia elettrica, impianto a turbina a gas per la produzione di energia elettrica comprendente detto gruppo bruciatore e metodo per operare detto impianto a turbina a gas

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EP3376110B1 true EP3376110B1 (fr) 2022-07-20

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JP2005283003A (ja) * 2004-03-30 2005-10-13 Osaka Gas Co Ltd 燃焼装置及びガスタービンエンジン
US7350357B2 (en) * 2004-05-11 2008-04-01 United Technologies Corporation Nozzle
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
US20090056336A1 (en) * 2007-08-28 2009-03-05 General Electric Company Gas turbine premixer with radially staged flow passages and method for mixing air and gas in a gas turbine
KR101049359B1 (ko) * 2008-10-31 2011-07-13 한국전력공사 삼중 스월형 가스터빈 연소기
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CN120212538A (zh) 2025-06-27
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