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WO2013028167A2 - 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
WO2013028167A2
WO2013028167A2 PCT/US2011/048612 US2011048612W WO2013028167A2 WO 2013028167 A2 WO2013028167 A2 WO 2013028167A2 US 2011048612 W US2011048612 W US 2011048612W WO 2013028167 A2 WO2013028167 A2 WO 2013028167A2
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
air
nozzles
annular combustor
combustor
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.)
Ceased
Application number
PCT/US2011/048612
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English (en)
Other versions
WO2013028167A3 (fr
Inventor
Majed Toqan
Brent Allan Gregory
Jonathan David Regele
Ryan Sadao Yamane
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to PL11871243T priority Critical patent/PL2748444T3/pl
Priority to PCT/US2011/048612 priority patent/WO2013028167A2/fr
Priority to RU2014110628A priority patent/RU2611217C2/ru
Priority to KR1020147007518A priority patent/KR101774093B1/ko
Priority to JP2014527126A priority patent/JP6086391B2/ja
Priority to EP11871243.9A priority patent/EP2748444B1/fr
Priority to CN201180073013.6A priority patent/CN103998745B/zh
Publication of WO2013028167A2 publication Critical patent/WO2013028167A2/fr
Anticipated expiration legal-status Critical
Publication of WO2013028167A3 publication Critical patent/WO2013028167A3/fr
Ceased legal-status Critical Current

Links

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
    • F23R3/44—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.
  • annular combustor In the annular combustor type, fuel-air nozzles are typically distributed circumferentially and introduce the mixture into a single annular chamber where combustion takes place. Flow simply exits the downstream end of the annulus into the first stage turbine, without the need for a transition piece.
  • a can- annular combustor The key difference of the last type, a can- annular combustor, is that it has individual cans encompassed by an annular casing that contains the air being fed into each can. Each variation has its benefits and disadvantages, depending on the application.
  • 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 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 is a two-dimensional sketch showing the can-annular arrangement with the nozzles that attach to the outer can liner injecting fuel and air into a common plane;
  • FIG. 2 is a two-dimensional sketch showing the general idea of the tangential nozzles applied to the can in a can-annular combustor;
  • FIG. 3 is an isometric side view of the upstream portion of an example configuration of the said invention;
  • FIG. 4A is an isometric cutaway view of the invention.
  • FIG. 4B is a close up view of the image from FIG. 4A;
  • FIG. 5 is a section view showing section A- A as defined in FIG. 3 ;
  • FIG. 6 is a section view showing section B-B as defined in FIG. 3.
  • 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, where as 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.

Landscapes

  • 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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur un dispositif de combustion utilisé dans des moteurs à turbine à gaz pour produire une propulsion ou pour faire tourner un arbre pour la production d'énergie, qui comprend une chambre de combustion de forme annulaire munie d'un système de passages d'entrée de carburant et d'air et de buses qui a pour effet un environnement de combustion optimal du carburant et de l'air. Le carburant, l'air et/ou les entrées de carburant et d'air sont placés en différents points de la longueur et répartis sur la circonférence et dirigent le flux tangentiellement ou à peu près tangentiellement au revêtement de la boîte. Le dispositif de combustion produit un mélange optimal du carburant et de l'air, il crée un environnement de combustion qui réduit les émissions de polluants, il réduit la nécessité de dispositifs de commande de la pollution qui sont coûteux, améliore l'allumage et la stabilité de la flamme, réduit les difficultés de pilotage et améliore la réduction des vibrations.
PCT/US2011/048612 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 Ceased WO2013028167A2 (fr)

Priority Applications (7)

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
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
RU2014110628A RU2611217C2 (ru) 2011-08-22 2011-08-22 Трубчато-кольцевая камера сгорания со ступенчатыми и тангенциальными топливовоздушными форсунками для использования в газотурбинных двигателях
KR1020147007518A KR101774093B1 (ko) 2011-08-22 2011-08-22 가스 터빈 엔진에서 사용되는 스테이지가 형성되고 접선방향으로 형성된 연료-공기 노즐을 가진 캔-애뉼러형 연소실
JP2014527126A JP6086391B2 (ja) 2011-08-22 2011-08-22 ガス・タービン・エンジンで使用するための段階的で接線方向の燃料空気ノズルを備えた環状筒型燃焼器
EP11871243.9A 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
CN201180073013.6A CN103998745B (zh) 2011-08-22 2011-08-22 在燃气轮机上使用的具有分级切向燃料‑空气喷嘴的筒状环形燃烧室

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 (2)

Publication Number Publication Date
WO2013028167A2 true WO2013028167A2 (fr) 2013-02-28
WO2013028167A3 WO2013028167A3 (fr) 2014-03-20

Family

ID=47747020

Family Applications (1)

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PCT/US2011/048612 Ceased 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

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)

Cited By (4)

* Cited by examiner, † Cited by third party
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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
CN114427689A (zh) * 2022-01-20 2022-05-03 中国空气动力研究与发展中心空天技术研究所 一种可实现超声速流场观测的圆盘形旋转爆震燃烧室
CN114857617A (zh) * 2022-05-20 2022-08-05 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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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
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
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
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

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN114427689A (zh) * 2022-01-20 2022-05-03 中国空气动力研究与发展中心空天技术研究所 一种可实现超声速流场观测的圆盘形旋转爆震燃烧室
CN114857617A (zh) * 2022-05-20 2022-08-05 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
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

Also Published As

Publication number Publication date
EP2748444A2 (fr) 2014-07-02
PL2748444T3 (pl) 2019-11-29
EP2748444A4 (fr) 2015-05-27
RU2611217C2 (ru) 2017-02-21
CN103998745B (zh) 2017-02-15
EP2748444B1 (fr) 2019-02-13
KR20140082658A (ko) 2014-07-02
CN103998745A (zh) 2014-08-20
JP6086391B2 (ja) 2017-03-01
RU2014110628A (ru) 2015-09-27
KR101774093B1 (ko) 2017-09-12
JP2014526029A (ja) 2014-10-02
WO2013028167A3 (fr) 2014-03-20

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