EP2748444B1 - Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz - Google Patents

Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz Download PDF

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Publication number
EP2748444B1
EP2748444B1 EP11871243.9A EP11871243A EP2748444B1 EP 2748444 B1 EP2748444 B1 EP 2748444B1 EP 11871243 A EP11871243 A EP 11871243A EP 2748444 B1 EP2748444 B1 EP 2748444B1
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European Patent Office
Prior art keywords
nozzles
volume
liner
air
fuel
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EP11871243.9A
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German (de)
English (en)
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EP2748444A4 (fr
EP2748444A2 (fr
Inventor
Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao Yamane
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Publication of EP2748444A4 publication Critical patent/EP2748444A4/fr
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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
    • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • This invention relates to devices in gas turbine engines that aid in containing and producing the combustion of a fuel and air mixture.
  • Such devices include but are not limited to fuel-air nozzles, combustor liners and casings and flow transition pieces that are used in military and commercial aircraft, power generation, and other gas turbine related applications.
  • Gas turbine engines include machinery that extracts work from combustion gases flowing at very high temperatures, pressures and velocity. The extracted work can be used to drive a generator for power generation or for providing the required thrust for an aircraft.
  • a typical gas turbine engine consists of a multistage compressor where the atmospheric air is compressed to high pressures. The compressed air is then mixed at a specified fuel/air ratio in a combustor wherein its temperature is increased. 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.
  • the combustor portion of a gas turbine engine can be of several different types: can/tubular, annular, and a combination of the two forming a can-annular combustor. It is in this component that the compressed fuel-air mixture passes through fuel-air swirlers or nozzles and a combustion reaction of the mixture takes place, creating a hot gas flow causing it to drop in density and accelerate downstream.
  • the can type combustor typically comprises of individual, circumferentially spaced cans that contain the flame of each nozzle separately. Flow from each can is then directed through a duct and combined in an annular transition piece before it enters the first stage vane.
  • a fuel air nozzle can take on different configurations such as single to multiple annular inlets with swirling vanes on each one.
  • a typical method for cooling the combustor is effusion cooling, implemented by surrounding the combustion liner with an additional, offset liner, which between the two, compressor discharge air passes through and enters the hot gas flow path through dilution holes and cooling passages. This technique removes heat from the component as well as forms a thin boundary layer film of cool air between the liner and the combusting gases, preventing heat transfer to the liner.
  • the dilution holes serve two purposes depending on its axial position on the liner: a dilution hole closer to the fuel-air nozzles will aid in the mixing of the gases to enhance combustion as well as provide unburned air for combustion, second, a hole that is placed closer to the turbine will cool the hot gas flow and can be designed to manipulate the combustor outlet temperature profile.
  • 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.
  • EP1882885 describes a combustor assembly having a support assembly between a metal support assembly and a ceramic combustor can section that accommodates a thermal expansion difference therebetween.
  • An air fuel mixer and an igniter are mounted to the support assembly secured to the ceramic combustion can which receives the ignition products of the ignited fuel and air mixture.
  • a novel and improved combustor design that is capable of operating in a typical fashion while minimizing the pollutant emissions that are a result of combustion of a fuel and air mixture and address other issues faced by such devices.
  • a can-annular combustor comprising the features of independent claim 1.
  • the invention consists of a typical can-annular combustor with fuel and air nozzles and/or dilution holes that introduce the compressor discharge air and pressurized fuel into the combustor at various locations in the longitudinal and circumferential directions.
  • the original feature of the invention is that the fuel and air nozzles are placed in such a way as to create an environment with enhanced mixing of combustion reactants and products.
  • the combustor will improve gas turbine emission levels, thus reducing the need for emission control devices as well as minimize the environmental impact of such devices.
  • the tangentially firing fuel and fuel-air nozzles directs any initial flame fronts to the adjacent burner nozzles in each can, greatly enhancing the ignition process of the combustor.
  • FIG. 1 shows an example of the general arrangement of a can-annular combustor with the can 1 spaced circumferentially on a common radius, all cans of which are enclosed between a cylindrical outer liner 2 and a cylindrical inner liner 3.
  • the FIG. also shows the tangential nozzle arrangement of the cans.
  • FIG. 2 shows the can in more detail.
  • a can liner 4 forms the can volume, with fuel/air nozzles 5 injecting either fuel or air.
  • the nozzles form an angle 8 between the nozzle centerline 6 and a line tangent to the can liner 4 that intersections with the nozzle centerline 6. This angle defines the circumferential direction of the nozzles.
  • FIG. 2 also shows the general operation of the can in the example can-annular combustor configuration, where the fuel or air 9 is injected into the cans 1 at an angle 8.
  • These tangentially directed nozzles result in flow from each nozzle interacting with the downstream and adjacent nozzle. This key feature enhances ignition and reduces the issue of piloting multiple burner nozzles by allowing the flame to be directed from one nozzle to ignite the fuel at the adjacent and downstream nozzle.
  • FIG. 3 shows the beginning or upstream portion of an example can with the downstream portion excluded.
  • the said invention will have a plurality of nozzle rows that are spaced along the longitudinal direction of the can.
  • Each row of nozzles 12, 13 may have at least one nozzle and can be offset by a circumferential angle from adjacent nozzle rows.
  • the nozzles 12 in the row close to the front wall 15 inject pure/mostly fuel into the can in a manner previously described, whereas nozzles 13 downstream of these inject pure compressor discharge air or a fuel-air mixture into the can in a similar manner.
  • the can may also have several rows of circumferentially spaced holes 14 or passages for cooling air to enter the can at any location.
  • FIGS. 5 and 6 show how nozzles 12, 13 from each set of nozzles may be offset by a circumferential angle.
  • the different rows of nozzles allows for the separate injection of the fuel and air creating a zone of combusting reactants near the front wall that does not see a high oxygen concentration, which in effect will reduce peak flame temperatures. Flue gases that travel upstream towards the front wall will be diluted from combustion products, making it possible for the combusting reactants to see a lower oxygen concentration. This combustion environment created by the staged fuel and air nozzles makes the reduced emissions possible.

Claims (5)

  1. Chambre de combustion turbo annulaire destinée à une turbine à gaz utilisée pour la génération de puissance terrestre, des véhicules terrestres ou marins ou des applications dans des moteurs d'avions comprenant une série de caissons (1) situés à distance périphérique compris entre deux chemises cylindriques (2, 3), les caissons (1) définissant des zones de combustion séparées, chaque caisson ayant une chemise de caisson (4) comprenant une extrémité amont, ayant une paroi frontale (15) et une extrémité aval et la zone de combustion étant le volume de la chemise du caisson (4), le volume du caisson s'étendant en direction longitudinale de la paroi frontale (15) de l'extrémité amont de la chemise du caisson (4) à l'extrémité aval de la chemise du caisson (4), caractérisée en ce que
    la chambre de combustion comporte en outre une série de perçages de dilution (16) au travers de la paroi frontale (15) réalisés pour permettre d'appliquer de l'air d'évacuation de la chambre de combustion dans le volume du caisson, dans la direction longitudinale de ce volume, un premier ensemble de premières buses (13) dirigées tangentiellement et situées à distance périphérique entre l'extrémité amont et l'extrémité aval de la chemise du caisson (4) susceptibles d'injecter de l'air ou un mélange carburant-air sur la périphérique du volume du caisson dans des directions tangentielles par rapport à la direction longitudinale du volume du caisson, et un second ensemble de secondes buses (12) dirigées tangentiellement et situées à distance périphérique entre les premières buses (13) et l'extrémité amont de la chemise du caisson (4) pour permettre d'injecter du carburant sur la périphérie du volume du caisson dans des directions tangentielles par rapport à la direction longitudinale du volume du caisson entre les perçages de dilution de l'ensemble de perçages de dilution (16) situés sur la paroi frontale de l'extrémité amont de la chemise de caisson (4) et les premières buses (13).
  2. Chambre de combustion turbo annulaire conforme à la revendication 1,
    comprenant en outre des perçages d'air de refroidissement (14) situés à distance périphérique au travers de la chemise du caisson (4) et positionnés entre l'extrémité aval de la chemise du caisson et les premières buses (13) de façon à permettre d'appliquer périphériquement de l'air de refroidissement dans le volume du caisson entre l'extrémité aval de ce volume et les premières buses (13).
  3. Chambre de combustion turbo annulaire conforme à la revendication 1,
    dans laquelle les premières buses (13) et les secondes buses (12) ne s'étendent pas dans le volume du caisson.
  4. Chambre de combustion turbo annulaire conforme à la revendication 1,
    dans laquelle les premières buses (13) sont susceptibles de diriger toute flamme vers la première buse adjacente suivante (13) pour faciliter leur allumage mutuel et les secondes buses (12) sont susceptibles de diriger toute flamme vers la seconde buse adjacente (12) suivante pour faciliter leur allumage mutuel.
  5. Chambre de combustion turbo annulaire conforme à la revendication 1,
    dans laquelle les premières buses (13) sont décalées sur la périphérie par rapport aux secondes buses (12).
EP11871243.9A 2011-08-22 2011-08-22 Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz Active EP2748444B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL11871243T PL2748444T3 (pl) 2011-08-22 2011-08-22 Komora spalania cylindryczno-pierścieniowa z rozstawionymi, stycznymi dyszami paliwowo-powietrznymi do zastosowania w silnikach turbinowych

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2011/048612 WO2013028167A2 (fr) 2011-08-22 2011-08-22 Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz

Publications (3)

Publication Number Publication Date
EP2748444A2 EP2748444A2 (fr) 2014-07-02
EP2748444A4 EP2748444A4 (fr) 2015-05-27
EP2748444B1 true EP2748444B1 (fr) 2019-02-13

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EP11871243.9A Active EP2748444B1 (fr) 2011-08-22 2011-08-22 Chambre de combustion annulaire en forme de boîte présentant des buses de carburant-air étagées et tangentielles, en vue d'une utilisation sur des moteurs à turbine à gaz

Country Status (7)

Country Link
EP (1) EP2748444B1 (fr)
JP (1) JP6086391B2 (fr)
KR (1) KR101774093B1 (fr)
CN (1) CN103998745B (fr)
PL (1) PL2748444T3 (fr)
RU (1) RU2611217C2 (fr)
WO (1) WO2013028167A2 (fr)

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US10139111B2 (en) * 2014-03-28 2018-11-27 Siemens Energy, Inc. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine
FR3032781B1 (fr) * 2015-02-17 2018-07-06 Safran Helicopter Engines Systeme de combustion a volume constant pour turbomachine de moteur d'aeronef
WO2018090383A1 (fr) * 2016-11-21 2018-05-24 深圳智慧能源技术有限公司 Chambre de combustion d'un moteur à turbine à gaz, et buse associée
WO2018090384A1 (fr) * 2016-11-21 2018-05-24 深圳智慧能源技术有限公司 Chambre de combustion de turbine à gaz
CN106439914A (zh) * 2016-11-21 2017-02-22 深圳智慧能源技术有限公司 燃气轮机燃烧室
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
KR102265626B1 (ko) * 2020-09-25 2021-06-16 박재현 샌드 스프레이 시험 장치
CN114135901A (zh) * 2021-11-08 2022-03-04 中国航发四川燃气涡轮研究院 一种防烧蚀的火焰筒大孔射流套筒
CN114857617B (zh) * 2022-05-20 2023-07-14 南昌航空大学 一种带锯齿型凹槽涡流发生器的支板火焰稳定器

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Also Published As

Publication number Publication date
WO2013028167A2 (fr) 2013-02-28
KR20140082658A (ko) 2014-07-02
PL2748444T3 (pl) 2019-11-29
KR101774093B1 (ko) 2017-09-12
EP2748444A4 (fr) 2015-05-27
EP2748444A2 (fr) 2014-07-02
RU2014110628A (ru) 2015-09-27
JP6086391B2 (ja) 2017-03-01
CN103998745A (zh) 2014-08-20
CN103998745B (zh) 2017-02-15
JP2014526029A (ja) 2014-10-02
WO2013028167A3 (fr) 2014-03-20
RU2611217C2 (ru) 2017-02-21

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