EP2515042A2 - Buse à combustible aérodynamique - Google Patents

Buse à combustible aérodynamique Download PDF

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Publication number
EP2515042A2
EP2515042A2 EP12164848A EP12164848A EP2515042A2 EP 2515042 A2 EP2515042 A2 EP 2515042A2 EP 12164848 A EP12164848 A EP 12164848A EP 12164848 A EP12164848 A EP 12164848A EP 2515042 A2 EP2515042 A2 EP 2515042A2
Authority
EP
European Patent Office
Prior art keywords
combustor
fuel
flow
stages
blocks
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.)
Withdrawn
Application number
EP12164848A
Other languages
German (de)
English (en)
Other versions
EP2515042A3 (fr
Inventor
Joel Meier Haynes
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2515042A2 publication Critical patent/EP2515042A2/fr
Publication of EP2515042A3 publication Critical patent/EP2515042A3/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/02—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

Definitions

  • the present application relates generally to gas turbine engines and more particularly relates to an aerodynamic fuel nozzle with a triple stage swirler for late lean injection and turndown.
  • Dry Low NO x technology may be applied for emissions control with gaseous fuel combustion in industrial gas turbines using annular can combustion systems and the like.
  • These known Dry Low NO x combustion systems provide premixing of the fuel and the air for a generally uniform rate of combustion with relatively constant reaction zone temperatures.
  • reaction zone temperatures may be optimized for very low production of nitrogen oxides ("NO x "), carbon monoxide (“CO”), unburned hydrocarbons (“UHC”), and other types of undesirable emissions.
  • NO x nitrogen oxides
  • CO carbon monoxide
  • UHC unburned hydrocarbons
  • the modulation of a center premix fuel nozzle may expand the range of operation by allowing the fuel-air ratio and the corresponding reaction rates of the outer nozzles to remain relatively constant while varying the fuel input into the turbine.
  • Fuel staging allows for higher turbine inlet temperatures with a uniform heat release.
  • Axially staged systems generally employ multiple planes of fuel injection along the combustor flow path. Even with advances in materials and heat transfer methods, however, current combustor designs are challenged to produce low nitrogen oxide emissions at full load conditions. Likewise, carbon monoxide emissions at part load conditions pose a challenge in reducing combustion firing temperatures. By firing only selected nozzles, the adjacent unfired nozzles may quench the reaction and produce carbon monoxide. The fired nozzle also may cause significant thermal stresses in the combustor liner so as to reduce component life time.
  • the present invention resides in a combustor for a turbine engine including a number of fuel nozzles with one or more of the fuel nozzles including a swirler assembly.
  • the swirler assembly includes a number of stages with a number of fueled structures and a number of unfueled structures.
  • the present invention further resides in a method of operating a combustor for late lean injection including the steps of providing a flow of air to a fuel nozzle, providing a flow of fuel through one or more fueled structures of a swirler assembly, swirling the flow of air and the flow of fuel through multiple stages of the swirler assembly, establishing a primary recirculation zone about the fuel nozzle for low emissions, and establishing a secondary recirculation zone downstream of the fuel nozzle for high temperatures.
  • Fig. 1 shows a schematic view of a turbo-machine such as a gas turbine engine 10 as may be described herein.
  • the gas turbine engine 10 may include a compressor 15.
  • the compressor 15 compresses an incoming flow of air 20.
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
  • the combustor 25 mixes the compressed flow of air 20 with a compressed flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
  • the gas turbine engine 10 may include any number of combustors 25.
  • the flow of combustion gases 35 is delivered in turn to a turbine 40.
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines such as those offered by General Electric Company of Schenectady, New York and the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • Figs. 2 and 3 show an example of a known combustor 25.
  • the combustor includes an outer casing 55.
  • the outer casing 55 may be bolted to the turbine 40 or otherwise attached.
  • One end of the outer casing 55 may be enclosed by an end cover 60.
  • the end cover 60 receives supply tubes, manifolds, and associated valves for feeding gaseous fuel, liquid fuel, air, and water.
  • the end cover 60 supports a number of outer fuel nozzles 65 that surround a center nozzle 70.
  • Other components and other configurations may be used herein.
  • a combustion zone 75 may be positioned within the outer casing 55 downstream of the end cover 60 and the fuel nozzles 65, 70.
  • the combustion zone 75 may be enclosed via a combustion liner 80.
  • a flow sleeve 85 may surround the combustion liner 80 and define a flow path 90 therebetween.
  • the flow of air 20 from the compressor 15 flows through the flow path 90, reverses direction about the end cover 60, and flows into the fuel nozzle 65, 70.
  • a transition piece 95 may extend about the downstream end of the outer casing 55. The transition piece 95 may be in communication with the turbine 10 for directing the flow of combustion gases 35 thereto.
  • Other components and other configurations may be used herein.
  • the combustor 25 may be late lean injection compatible.
  • a late lean injection compatible combustor may be any combustor with either an exit temperatures that exceeds about 2,500 degrees Fahrenheit (about 1,371 degrees Celsius) or handles fuels with components that are more reactive than, for example, methane with a hot side residence time greater than about 10 milliseconds.
  • Examples of late lean injection compatible combustors include a DLN-1 ("Dry-Low NO x ”) combustor, a DLN-2 combustor, and a DLN-2.6 combustor offered by General Electric Company of Schenectady, New York. Other types of late lean injection compatible combustors may be used herein.
  • Such late lean injection compatible combustors may have a number of fuel injectors (not shown) positioned about the transition piece 95 or otherwise for fuel staging and the like. These downstream fuel injectors, however, may increase the overall complexity of the combustor 25. Other components and other configurations may be used herein.
  • Fig. 4 shows an example of a portion of a combustor 100 as may be described herein.
  • the combustor 100 includes a number of fuel nozzles 110. Any number of the fuel nozzles 110 may be used.
  • at least a center nozzle 120 may include a swirler assembly 130.
  • the swirler assembly 130 may be a swirler with three stages 140.
  • the three stages 140 thus include a first stage 150, a second stage 160, and a third stage 170. Any number of stages 140 may be used herein.
  • the stages 140 may be positioned in an axial direction 180 as is shown in Fig. 4 , in a circumferential direction 190 as shown in Fig. 5 , or in combinations thereof.
  • the outer swirler may have a swirl number S3 > 0.6 and the inner swirlers may have a swirl number S2 > S3 and a swirl number S 1 > S3.
  • the swirl number characterizes combustor recirculation with a swirl number greater than 0.6 indicating good recirculation.
  • Other components and other configurations may be used herein.
  • the stages 140 of the swirler assembly 130 may take many different forms.
  • the swirlers 130 may include a number of radial vanes 200 as is shown in Fig. 6 , a number of blocks 210 as shown in Fig. 7 , and/or combinations thereof. Other shapes also may be used herein.
  • a number of fixed blocks 220 and a number of movable blocks 230 may be used so as to provide a variable swirler.
  • a number of injection ports 240 may be used as are shown in Fig. 8 for a fueled structure 245.
  • the injection ports 240 may be positioned in radial, axial, and/or circumferential directions. For example, three (3) different directions may be used in the vane 200 of Fig. 7 .
  • the vanes 200 and blocks 210 also may be unfueled structures 250. Other configurations and other components may be used herein.
  • vanes 200 and blocks 210 being fueled or unfueled may be used herein.
  • the fuel nozzle 110 thus creates a primary recirculation zone 260 near the nozzle 120 and a secondary recirculation zone 270 downstream.
  • the primary recirculation zone 260 operates near the flammability limits (about Phi - 2.5 or about Phi - 0.4) and the combustion products travel downstream without forming significant nitrogen oxides or other emissions.
  • the secondary recirculation zone 270 the core and tertiary air mix at overall lean conditions and raise the overall temperature of the hot combustion gases so as to reduce fuel staging by aerodynamic means.
  • the primary recirculation zone 260 may be fired at moderately lean temperatures (about Phi - 0.5 to 0.6). This may accomplish good fuel burnout and maintain low emissions. Further downstream, the inner products mix with the tertiary stream in the secondary recirculation zone 270 so as to bring the mixture to overall lean conditions.
  • the fuel nozzle 110 thus is able to form turndown while maintaining low carbon monoxide in the presence of unfired nozzles.
  • the nozzle 110 thus enables increased combustion firing temperatures without increasing nitrogen oxides by effectively implementing late lean injection performance without significant hardware changes.
  • the nozzle 110 also enables high combustion turndown without producing significant levels of carbon monoxide.
  • the nozzle 110 may be used in conjunction with existing nozzles that may remain unfired without impacting on the low carbon monoxide performance.
  • the use of the swirler assembly 130 with a center nozzle 120 thus provides fuel staging so as to create a downstream aero-staged flame. Fuel staging herein thus may be maximized. Moreover, such fuel staging may dampen combustion dynamics.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12164848.9A 2011-04-22 2012-04-19 Buse à combustible aérodynamique Withdrawn EP2515042A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/092,345 US20120266602A1 (en) 2011-04-22 2011-04-22 Aerodynamic Fuel Nozzle

Publications (2)

Publication Number Publication Date
EP2515042A2 true EP2515042A2 (fr) 2012-10-24
EP2515042A3 EP2515042A3 (fr) 2014-01-08

Family

ID=46084805

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12164848.9A Withdrawn EP2515042A3 (fr) 2011-04-22 2012-04-19 Buse à combustible aérodynamique

Country Status (3)

Country Link
US (1) US20120266602A1 (fr)
EP (1) EP2515042A3 (fr)
CN (1) CN102809176A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104406197A (zh) * 2014-11-24 2015-03-11 中国科学院工程热物理研究所 一种采用径向旋流进气燃油分级方案的低排放回流燃烧室
WO2023180315A3 (fr) * 2022-03-24 2023-11-16 Rolls-Royce Deutschland Ltd & Co Kg Ensemble injecteur comportant une alimentation centrale en carburant et au moins un canal d'air

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9347378B2 (en) 2013-05-13 2016-05-24 Solar Turbines Incorporated Outer premix barrel vent air sweep
US11181274B2 (en) 2017-08-21 2021-11-23 General Electric Company Combustion system and method for attenuation of combustion dynamics in a gas turbine engine
CN109812341A (zh) * 2018-12-31 2019-05-28 华电电力科学研究院有限公司 一种采用lve运行方式的dln-2.6+燃烧系统燃烧调整方法
CN110345513B (zh) * 2019-07-12 2021-04-16 中国航发沈阳发动机研究所 一种分级燃烧的旋流雾化装置
US12072099B2 (en) * 2021-12-21 2024-08-27 General Electric Company Gas turbine fuel nozzle having a lip extending from the vanes of a swirler
EP4202304A1 (fr) * 2021-12-21 2023-06-28 General Electric Company Buse de carburant et tourbillonneur
US20230212984A1 (en) * 2021-12-30 2023-07-06 General Electric Company Engine fuel nozzle and swirler
CN114526497B (zh) * 2022-01-07 2023-02-07 清华大学 双缩口组合旋流式中心分级高温升燃烧室

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US5365865A (en) * 1991-10-31 1994-11-22 Monro Richard J Flame stabilizer for solid fuel burner
US6374615B1 (en) * 2000-01-28 2002-04-23 Alliedsignal, Inc Low cost, low emissions natural gas combustor
US6389815B1 (en) * 2000-09-08 2002-05-21 General Electric Company Fuel nozzle assembly for reduced exhaust emissions
US7134287B2 (en) * 2003-07-10 2006-11-14 General Electric Company Turbine combustor endcover assembly
EP1821035A1 (fr) * 2006-02-15 2007-08-22 Siemens Aktiengesellschaft Brûleur de turbine à gaz et procédé pour mélanger le carburant et l'air dans une zone de tourbillonage d'un brûleur de turbine à gaz
US7631500B2 (en) * 2006-09-29 2009-12-15 General Electric Company Methods and apparatus to facilitate decreasing combustor acoustics
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
EP2192347B1 (fr) * 2008-11-26 2014-01-01 Siemens Aktiengesellschaft Chambre tubulaire de tourbillonnement
EP2233836B1 (fr) * 2009-03-23 2015-07-29 Siemens Aktiengesellschaft Générateur de torsion, procédé destiné à empêcher des retours de flammes dans un brûleur, doté d'au moins un générateur de torsion et d'un brûleur

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104406197A (zh) * 2014-11-24 2015-03-11 中国科学院工程热物理研究所 一种采用径向旋流进气燃油分级方案的低排放回流燃烧室
WO2023180315A3 (fr) * 2022-03-24 2023-11-16 Rolls-Royce Deutschland Ltd & Co Kg Ensemble injecteur comportant une alimentation centrale en carburant et au moins un canal d'air

Also Published As

Publication number Publication date
EP2515042A3 (fr) 2014-01-08
US20120266602A1 (en) 2012-10-25
CN102809176A (zh) 2012-12-05

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