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EP2748443B1 - Méthode pour mélanger des réactifs de combustion pour la combustion dans un moteur de turbine à gaz - Google Patents

Méthode pour mélanger des réactifs de combustion pour la combustion dans un moteur de turbine à gaz Download PDF

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Publication number
EP2748443B1
EP2748443B1 EP11871108.4A EP11871108A EP2748443B1 EP 2748443 B1 EP2748443 B1 EP 2748443B1 EP 11871108 A EP11871108 A EP 11871108A EP 2748443 B1 EP2748443 B1 EP 2748443B1
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EP
European Patent Office
Prior art keywords
nozzles
liner
volume
fuel
air
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.)
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Application number
EP11871108.4A
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German (de)
English (en)
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EP2748443A1 (fr
EP2748443A4 (fr
Inventor
Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao Yamane
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Publication of EP2748443A4 publication Critical patent/EP2748443A4/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
    • F23R3/34—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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/58—Cyclone or vortex type combustion chambers
    • 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
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Definitions

  • the high temperature and pressure combustion gases are then expanded through a turbine to extract work so as to provide the required thrust or drive a generator depending on the application.
  • the turbine includes at least a single stage with each stage consisting of a row of blades and a row of vanes.
  • the blades are circumferentially distributed on a rotating hub with the height of each blade covering the hot gas flow path.
  • Each stage of non-rotating vanes is placed circumferentially, which also extends across the hot gas flow path.
  • the included invention involves the combustor of gas turbine engines and components that introduce the fuel and air into the said device.
  • US 2007/0107437 A1 describes a combustor.
  • the combustor includes a combustor liner and a swirl premixer disposed on a head end of the combustor liner and configured to provide a fuel-air mixture to the combustor.
  • the combustor also includes a plurality of tangentially staged injectors disposed downstream of the swirl premixer on the combustor liner, wherein each of the plurality of injectors is configured to introduce the fuel-air mixture in a transverse direction to a longitudinal axis of the combustor and to sequentially ignite the fuel-air mixtures from adjacent tangential injectors.
  • FIG. 2 also shows the general operation of the can in the example can-annular combustor configuration, where a pre-mixed fuel-air mixture 9 is injected into the cans 1 at an angle 8.
  • a flame 10 forms and travels through the can in a path 11 that follows the can liner.
  • These tangentially directed nozzles result in flames from each nozzle interacting with the downstream and adjacent nozzle. This key feature enhances ignition and reduces the need of piloting burner nozzles by allowing the flame from a nozzle to ignite the fuel at the adjacent and downstream nozzle.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)

Claims (4)

  1. Méthode pour mélanger des réactifs de combustion pour la combustion dans un moteur de turbine à gaz comprenant les étapes suivantes :
    le fait de fournir une chambre de combustion annulaire, la chambre de combustion annulaire comprenant une pluralité de chambres (1) espacées de manière circonférentielle et enfermées entre deux revêtements cylindriques (2, 3), les chambres (1) définissant des zones de combustion séparées et chaque chambre étant un revêtement de chambre, le revêtement de chambre ayant une extrémité an amont, comprenant une paroi avant (13), et une extrémité en aval, la zone de combustion étant un volume de chambre du revêtement de chambre, le volume de chambre s'étendant dans une direction longitudinale à partir de la paroi avant (13) de l'extrémité an amont du revêtement de chambre jusqu'à l'extrémité en aval du revêtement de chambre, une pluralité de trous de dilution (14) traversant la paroi avant (13), des premières buses traversant le revêtement de chambre, des secondes buses traversant le revêtement de chambre, les premières buses étant espacées et disposées de manière circonférentielle autour de la zone de combustion entre la paroi avant (13) et l'extrémité en aval du revêtement de chambre, les secondes buses étant espacées et sont disposées de manière circonférentielle autour de la zone de combustion entre la paroi avant (13) et les premières buses, les premières buses étant an aval des secondes buses en direction de l'extrémité en aval du revêtement de chambre et se trouvant dans un premier plan (B) qui est normal à la direction longitudinale du volume de chambre, les secondes buses étant en amont des premières buses en direction de l'extrémité en amont du revêtement de chambre et se trouvant dans un second plan (A) qui est normal à la direction longitudinale du volume de chambre ;
    et pour chacune des chambres (1) simultanément :
    a) l'injection d'un premier mélange carburant-air prémélangé dans le volume de chambre à travers toutes les premières buses, les premières buses apportant chacune le premier mélange carburant-air prémélangé dans le volume annulaire dans une direction qui est décalée angulairement d'une ligne tangente par rapport au revêtement de chambre ;
    b) l'injection d'un second mélange carburant-air prémélangé dans le volume de chambre à travers toutes les secondes buses, les secondes buses apportant chacune le second mélange carburant-air prémélangé dans le volume de chambre dans une direction qui est décalée angulairement de la ligne tangente par rapport au revêtement de chambre ;
    le premier mélange carburant-aire prémélangé ayant un premier rapport carburant-air, le second mélange carburant-aire prémélangé ayant un second rapport carburant-air, et
    le second rapport carburant-air étant supérieur au premier rapport carburant-air ; et
    c) l'injection d'un air de sortie du compresseur à travers la pluralité de trous de dilution (14) traversant la paroi avant (13) dans le volume de chambre dans la direction longitudinale du volume de chambre ;
    dans lequel les étapes simultanées d'injection du premier mélange carburant-air prémélangé dans le volume de chambre à travers toutes les premières buses, d'injection du second mélange carburant-air prémélangé dans le volume de chambre à travers toutes les secondes buses, et d'injection d'un air de sortie du compresseur à travers la pluralité de trous de dilution (14) traversant la paroi avant (13) dans le volume de chambre créent une gradation carburant-air destinée à améliorer la combustion et à réduire les émissions de NOx et de CO.
  2. Méthode selon la revendication 1, comprenant en outre les étapes du fait de fournir des trous d'air de refroidissement (12) espacés de manière circonférentielle à travers le revêtement de chambre entre l'extrémité en aval du revêtement de chambre et les premières buses, et le fait d'apporter de manière circonférentielle de l'air de refroidissement à travers les trous d'air de refroidissement (12) dans le volume de chambre entre l'extrémité en aval du revêtement de chambre et les premières buses, pour chacune des chambres (1).
  3. Méthode selon la revendication 1, dans laquelle chacune des premières buses dirige n'importe quelle flamme vers une première buse adjacente afin d'améliorer la combustion, et chacune des secondes buses dirige n'importe quelle flamme vers une seconde buse adjacente afin d'améliorer la combustion.
  4. Méthode selon la revendication 1, dans laquelle les premières buses sont décalées de manière circonférentielle par rapport aux secondes buses.
EP11871108.4A 2011-08-22 2011-08-22 Méthode pour mélanger des réactifs de combustion pour la combustion dans un moteur de turbine à gaz Active EP2748443B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL11871108T PL2748443T3 (pl) 2011-08-22 2011-08-22 Sposób mieszania reagentów spalania do spalania w turbinie gazowej

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2011/048622 WO2013028169A1 (fr) 2011-08-22 2011-08-22 Chambre de combustion tubo-annulaire dotée de buses d'air et de combustible tangentielles destinées à être utilisées sur des moteurs de turbine à gaz

Publications (3)

Publication Number Publication Date
EP2748443A1 EP2748443A1 (fr) 2014-07-02
EP2748443A4 EP2748443A4 (fr) 2015-05-27
EP2748443B1 true EP2748443B1 (fr) 2019-04-24

Family

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Application Number Title Priority Date Filing Date
EP11871108.4A Active EP2748443B1 (fr) 2011-08-22 2011-08-22 Méthode pour mélanger des réactifs de combustion pour la combustion dans un moteur de turbine à gaz

Country Status (7)

Country Link
EP (1) EP2748443B1 (fr)
JP (1) JP6086371B2 (fr)
KR (1) KR101774094B1 (fr)
CN (1) CN104053883B (fr)
PL (1) PL2748443T3 (fr)
RU (1) RU2619673C2 (fr)
WO (1) WO2013028169A1 (fr)

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KR102010646B1 (ko) 2017-07-04 2019-08-13 두산중공업 주식회사 터닝 가이드, 연료 노즐, 연료 노즐 조립체 및 이를 포함하는 가스 터빈
CN107631323B (zh) * 2017-09-05 2019-12-06 中国联合重型燃气轮机技术有限公司 燃气轮机的喷嘴
CN108487988A (zh) * 2018-03-14 2018-09-04 罗显平 一种燃气螺管转子发动机全环形燃烧室
CN109404965A (zh) * 2018-12-04 2019-03-01 新奥能源动力科技（上海）有限公司 一种燃气轮机的燃烧室及燃气轮机
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
CN112923398B (zh) * 2021-03-04 2022-07-22 西北工业大学 一种加力燃烧室防振隔热屏
CN114646077B (zh) * 2022-03-23 2023-08-11 西北工业大学 一种环腔开孔的空气雾化喷嘴

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Also Published As

Publication number Publication date
KR20140082659A (ko) 2014-07-02
WO2013028169A8 (fr) 2014-04-17
KR101774094B1 (ko) 2017-09-04
WO2013028169A1 (fr) 2013-02-28
RU2014110631A (ru) 2015-09-27
EP2748443A1 (fr) 2014-07-02
PL2748443T3 (pl) 2019-09-30
RU2619673C2 (ru) 2017-05-17
JP6086371B2 (ja) 2017-03-01
CN104053883A (zh) 2014-09-17
CN104053883B (zh) 2017-02-15
EP2748443A4 (fr) 2015-05-27
JP2014526030A (ja) 2014-10-02

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