EP2748443B1 - Verfahren zur mischung von verbrennungsreaktanten für die verbrennung in einem gasturbinenmotor - Google Patents

Verfahren zur mischung von verbrennungsreaktanten für die verbrennung in einem gasturbinenmotor 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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Prior art keywords
nozzles
liner
volume
fuel
air
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EP11871108.4A
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English (en)
French (fr)
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EP2748443A1 (de
EP2748443A4 (de
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Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao Yamane
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    • 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. Verfahren zum Mischen von Verbrennungsreaktanden zur Verbrennung in einem Gasturbinenmotor, umfassend die Schritte:
    Bereitstellen einer Ringbrennkammer, wobei die Ringbrennkammer eine Vielzahl von in Umfangsrichtung beabstandeten Kammern (1) umfasst, die zwischen zwei zylindrischen Auskleidungen (2, 3) eingeschlossen sind, die Kammern (1) separate Verbrennungszonen definieren und jede Kammer als eine Kammerauskleidung ausgebildet ist,
    die Kammerauskleidung ein stromaufwärtiges Ende einschließlich einer Vorderwand (13) und ein stromabwärtiges Ende aufweist, wobei die Verbrennungszone ein Kammervolumen der Kammerauskleidung ist, sich das Kammervolumen in einer Längsrichtung von der Vorderwand (13) des stromaufwärtigen Endes der Kammerauskleidung zu dem stromabwärtigen Ende der Kammerauskleidung erstreckt,
    eine Vielzahl von die Vorderwand (13) durchdringenden Verdünnungslöchern (14),
    erste die Kammerauskleidung durchdringende Düsen, und
    zweite die Kammerauskleidung durchdringende Düsen, wobei die ersten Düsen voneinander beabstandet und in Umfangsrichtung um die Verbrennungszone zwischen der Vorderwand (13) und dem stromabwärtigen Ende der Kammerauskleidung angeordnet sind, die zweiten Düsen voneinander beabstandet sind und in Umfangsrichtung um die Verbrennungszone zwischen der Vorderwand (13) und den ersten Düsen angeordnet sind, die ersten Düsen stromabwärts der zweiten Düsen zum stromabwärtigen Ende der Kammerauskleidung angeordnet sind und in einer ersten Ebene (B) liegen, die senkrecht zur Längsrichtung des Kammervolumens liegt, und die zweiten Düsen stromaufwärts der ersten Düsen in Richtung des stromaufwärtigen Endes der Kammerauskleidung angeordnet sind und in einer zweiten Ebene (A) liegen, die senkrecht zur Längsrichtung des Kammervolumens verläuft; und für jede der Kammern (1) gleichzeitig folgende Schritte durchgeführt werden:
    a) Einspritzen eines ersten vorgemischten Kraftstoff-Luft-Gemisches in das Kammervolumen durch alle ersten Düsen, wobei die ersten Düsen jeweils das erste vorgemischte Kraftstoff-Luft-Gemisch in eine von einer Tangentenlinie versetzt angeordnete Richtung relativ zu der Kammerauskleidung in das Ringvolumen einspritzen;
    b) Einspritzen eines zweiten vorgemischten Brennstoff-Luft-Gemisches in das Kammervolumen durch alle zweiten Düsen, wobei die zweiten Düsen jeweils das zweite vorgemischte Brennstoff-Luft-Gemisch in eine Richtung auf das Kammervolumen einspritzen, die von der Tangentenlinie bezogen auf die Kammerauskleidung winkelversetzt ist,
    das erste vorgemischte Kraftstoff-Luft-Gemisch ein erstes Kraftstoff-Luft-Verhältnis aufweist,
    das zweite vorgemischte Kraftstoff-Luft-Gemisch ein zweites Kraftstoff-Luft-Verhältnis aufweist und
    das zweite Kraftstoff-Luft-Verhältnis größer ist als das erste Kraftstoff-Luft-Verhältnis; und
    c) Einspritzen der Kompressorauslassluft durch die Vielzahl von die Vorderwand durchdringenden Verdünnungslöchern (14) in das Kammervolumen in Längsrichtung des Kammervolumens;
    wobei die gleichzeitigen Schritte des Einspritzens des ersten vorgemischten Kraftstoff-Luft-Gemisches in das Kammervolumen durch alle ersten Düsen, das Einspritzen des zweiten vorgemischten Kraftstoff-Luft-Gemisches in das Kammervolumen durch alle zweiten Düsen und das Einspritzen von Kompressorauslassluft durch eine Vielzahl von Verdünnungslöchern (14) durch die Vorderwand (13) in das Kammervolumen eine Brennstoff-Luft-Stufung zur Verbesserung der Verbrennung und zur Verringerung der NOx- und CO-Emissionen schaffen.
  2. Verfahren nach Anspruch 1, ferner umfassend die Schritte des Bereitstellens von in Umfangsrichtung beabstandeten und die Kammerauskleidung durchdringenden Kühlluftlöchern (12) zwischen dem stromabwärtigen Ende der Kammerauskleidung und den ersten Düsen, und des umfänglichen Aufbringens von Kühlluft durch die in Umfangsrichtung beabstandete Kühlluftlöcher (12) in das Kammervolumen zwischen dem stromabwärtigen Ende des Kammervolumens und den ersten Düsen für jede der Kammern (1).
  3. Verfahren nach Anspruch 1, wobei jede der ersten Düsen eine Flamme zu einer benachbarten ersten Düse zum Verstärken der Verbrennung richtet, und jede der zweiten Düsen eine Flamme zu einer benachbarten zweiten Düse zum Verstärken der Verbrennung richtet.
  4. Verfahren nach Anspruch 1, wobei die ersten Düsen in Umfangsrichtung relativ zu den zweiten Düsen versetzt sind.
EP11871108.4A 2011-08-22 2011-08-22 Verfahren zur mischung von verbrennungsreaktanten für die verbrennung in einem gasturbinenmotor Active EP2748443B1 (de)

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 (en) 2011-08-22 2011-08-22 Can-annular combustor with premixed tangential fuel-air nozzles for use on gas turbine engines

Publications (3)

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

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

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

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