WO2017018983A1 - Système de chambre de combustion et procédé pour réduire le temps de séjour de combustion et/ou amortir la dynamique de combustion - Google Patents

Système de chambre de combustion et procédé pour réduire le temps de séjour de combustion et/ou amortir la dynamique de combustion Download PDF

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Publication number
WO2017018983A1
WO2017018983A1 PCT/US2015/041952 US2015041952W WO2017018983A1 WO 2017018983 A1 WO2017018983 A1 WO 2017018983A1 US 2015041952 W US2015041952 W US 2015041952W WO 2017018983 A1 WO2017018983 A1 WO 2017018983A1
Authority
WO
WIPO (PCT)
Prior art keywords
flame
combustor system
flow
fuel
fluid
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/US2015/041952
Other languages
English (en)
Inventor
Juan Enrique Portillo Bilbao
Rajesh Rajaram
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.)
Siemens AG
Siemens Corp
Siemens Energy Inc
Original Assignee
Siemens AG
Siemens Corp
Siemens Energy Inc
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 Siemens AG, Siemens Corp, Siemens Energy Inc filed Critical Siemens AG
Priority to PCT/US2015/041952 priority Critical patent/WO2017018983A1/fr
Publication of WO2017018983A1 publication Critical patent/WO2017018983A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F23R3/42—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
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F23N5/247—Preventing development of abnormal or undesired conditions, i.e. safety arrangements using mechanical means
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • Field Disclosed embodiments are generally related to combustion turbine engines, such as gas turbine engines, and, more particularly, to a combustor system and method that may utilize burners effective for reducing combustion residence time and/or damping combustion dynamics.
  • a combustion turbine engine such as a gas turbine engine, comprises for example a compressor section, a combustor section and a turbine section. Intake air is compressed in the compressor section and then mixed with a fuel. The mixture is burned in the combustor section to produce a high-temperature and high-pressure working gas directed to the turbine section, where thermal energy is converted to mechanical energy.
  • FIG. 1 illustrates a schematic representation of non-limiting basic building blocks of disclosed main burners that may be used in a combustor system for a combustion turbine engine, such as a gas turbine engine.
  • FIG. 2 shows a schematic of a disclosed combustor system using respective arrays of main burners, as shown in FIG. 1.
  • FIG. 3 is another no n- limiting embodiment of a main burner embodying further aspects of the present invention.
  • FIG. 4 is a schematic of one non-limiting conceptual embodiment of different temporal and or spatial characteristics that may be imparted to respective flames respectively formed by disclosed main burners.
  • the inventors of the present invention have recognized that in order to achieve substantially lower combustion residence times in a combustion system, the combustion process may have to rely on the formation of relatively compact flames.
  • the present inventors have further recognized that compact flames, can, however, have a substantially larger power density (i.e., increased heat per unit volume) than what is feasible in known combustors.
  • the elevated flame temperatures resulting from such compact flames could drive combustion dynamics instabilities or affect the level of emissions.
  • the present inventors propose a combustor system that can reliably and cost-effectively generate certain non-uniformities (e.g., different temporal and/or spatial non-uniformities) in relatively compact flames effective for a relatively low combustion residence time (such as without limitation in a range from approximately 2 msec to approximately 10 msec), without affecting emissions.
  • certain non-uniformities e.g., different temporal and/or spatial non-uniformities
  • the present inventors propose an improved combustor system and method that may benefit from utilization of burners with fluidic nozzles appropriately tuned for reducing combustion residence time and/or damping combustion dynamics.
  • FIG. 1 illustrates a schematic representation of basic building blocks (e.g., constituent structures) of disclosed main burners that may be used in one non-limiting embodiment of a combustor system 10 for a combustion turbine engine, such as a gas turbine engine.
  • Combustor system 10 may include a first main burner 12 arranged in a combustion chamber 14 of combustor system 10.
  • First main burner 12 includes a first fluidic nozzle 16 (also referred to in the art as a fiuidic oscillator) tuned to convey a first flow of a fluid 18, such as air, that oscillates at a first oscillation frequency.
  • a fluidic nozzle 16 also referred to in the art as a fiuidic oscillator
  • fluidic oscillators are devices that form a self-oscillating flow (e.g., a sweeping jet) with a frequency that depends primarily on the specific fluid dynamics arranged in the device. These devices can provide reliable operation without the need of complicated moving parts, thus ensuring a relatively long operational lifetime in the challenging thermo-mechanical environment of a combustion turbine engine.
  • First flow of fluid 18 is premixed with fuel and ignited to form a first flame 24.
  • fuel may be injected by an injector 20 disposed downstream of first fluidic nozzle 16 into a first flame-forming cup 22 (which in this example functions as a premixing cup) connected to an outlet end of first fluidic nozzle 16.
  • First flame- forming cup 22 comprises a first structural geometry that can impart specific spatial characteristics to first flame 24, e.g., flame size, flame length, flame shaping, etc. It will be appreciated that the injector need not be located downstream of first fluidic nozzle 16.
  • an injector 19 may be located upstream of first fluidic nozzle 16, and in this case first flow of fluid 18 may comprise air already premixed with fuel.
  • combustor system 10 may further include a second main burner 32 arranged in combustion chamber 14.
  • Second main burner 32 includes a second fluidic nozzle 34 tuned to convey a second flow of fluid 36 (e.g., air) that oscillates at a second oscillation frequency.
  • Second flow of fluid 36 is premixed with fuel to form a second flame 38.
  • fuel may be injected by an injector 40 into a second flame-forming cup 42 connected to an outlet end of second fluidic nozzle 34.
  • the injector need not be located downstream of first fluidic nozzle 16.
  • first oscillation frequency and the second oscillation frequency imparted by first and second fluidic nozzles 16, 34 may be respectively tuned to have different values so that respective temporal characteristics (e.g., oscillatory characteristics) of the first and second flames are different relative to one another.
  • Second flame-forming cup 42 may comprise a second structural geometry that can impart specific spatial characteristics to second flame 38.
  • the second structural geometry of second flame-forming cup 42 may be different than the first structural geometry of first flame-forming cup 22 so that the respective spatial characteristics of the first and second flames 24, 38 are different relative to one another.
  • Non-limiting features of the respective structural geometries of the first and second flame-forming cups may include cup axial length, cup shape, cup diameter, and combinations of two or more of such features.
  • the different temporal and/or spatial characteristics of the first and second flames 24, 38 imparted by the first and second fluidic nozzles 16, 34 and/or the first and second flame-forming cups 22, 42 may be effective to reduce combustion instabilities and therefore allow the use of flames with low residence times.
  • the different temporal and or spatial characteristics of the first and second flames 24, 38 may also be effective to dampen predefined vibrational modes of the combustor system.
  • FIG. 2 shows a schematic of a combustor system SO using respective arrays of main burners 52, 54, such as discussed above.
  • the respective arrays of main burners 52, 54 may be annularly disposed about a centrally- disposed pilot burner 56.
  • the annular arrangement of burner mains may comprise at least two concentric annuli of mains. It will be appreciated that aspects of the present invention are not limited to any specific arrangement for the respective arrays of burner mains or any specific number of burner mains.
  • the number of burner mains may be chosen based on the needs of a given application, such as based on a desired mass flow rate of the combustor system and/or flame configuration, flame length, etc.
  • the high-temperature and high-pressure working gases generated in combustion chamber 14 may be conveyed to the turbine section (not shown) by way of a transition duct 58.
  • FIG. 4 shows one non- limiting conceptual embodiment of different temporal and/or spatial characteristics that may be imparted to the respective flames respectively formed by main burners 55, 57, 59, 60. These actions may be performed by appropriately tuning the ftuidic nozzles at different frequencies and/or appropriately configuring the structural geometries of the flame- forming cups.
  • the respective ftuidic nozzles of burners 55 and 59 may be tuned at a frequency fl while the respective fluidic nozzles of burners 57 and 60 may be tuned at a different frequency f2.
  • the respective flame-forming cups of burners 55 and 59 may be configured to have a structural geometry SI while the respective flame-forming cups of burners 57 and 60 may be configured with a different structural geometry S2. It will be appreciated that aspects of the present invention are not limited to burners having two different frequencies, or having two different structural geometries, or to any specific grouping of main burners since such structural and/operational relationships may be tailored based on the needs of a given application.
  • disclosed embodiments are expected to form relatively compact and non-uniform flames (e.g., having different temporal and/or spatial characteristics) effective for reducing combustion residence time with practically no impact on emissions.
  • the respective arrays of burner mains may be appropriately tailored to damp any desired vibrational modes as may be defined by their appropriate eigenvectors, or to reduce vibrational mode interactions (e.g., inter-mode coupling) that could arise under a given combustion dynamics. While embodiments of the present disclosure have been disclosed in exemplary forms, it will be apparent to those skilled in the art that many modifications, additions, and deletions can be made therein without departing from the spirit and scope of the invention and its equivalents, as set forth in the following claims.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

On décrit un système de chambre de combustion et un procédé pour réduire le temps de séjour de combustion et/ou amortir la dynamique de combustion. Le système comprend un premier brûleur principal (12) qui comprend à son tour une première buse fluidique (16) accordée pour transporter un premier écoulement d'un fluide oscillant à une première fréquence d'oscillation pour former une première flamme (24). Le système de chambre de combustion comprend en outre un second brûleur principal (32) qui comprend à son tour une seconde buse fluidique (34) accordée pour transporter un second écoulement dudit fluide oscillant à une seconde fréquence d'oscillation pour former une seconde flamme (38). La première et la seconde fréquence d'oscillation présentent des valeurs différentes de sorte que des caractéristiques temporelles respectives de la première et de la seconde flamme sont différentes les unes des autres. Des coupelles de formation de flammes (22, 42) peuvent être constituées de manière appropriée pour conférer des caractéristiques spatiales différentes aux première et seconde flammes.
PCT/US2015/041952 2015-07-24 2015-07-24 Système de chambre de combustion et procédé pour réduire le temps de séjour de combustion et/ou amortir la dynamique de combustion Ceased WO2017018983A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US2015/041952 WO2017018983A1 (fr) 2015-07-24 2015-07-24 Système de chambre de combustion et procédé pour réduire le temps de séjour de combustion et/ou amortir la dynamique de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2015/041952 WO2017018983A1 (fr) 2015-07-24 2015-07-24 Système de chambre de combustion et procédé pour réduire le temps de séjour de combustion et/ou amortir la dynamique de combustion

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WO2017018983A1 true WO2017018983A1 (fr) 2017-02-02

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6449951B1 (en) * 1999-08-18 2002-09-17 Alstom Combustion device for generating hot gases
EP1426689A1 (fr) * 2002-11-19 2004-06-09 Siemens Westinghouse Power Corporation Chambre de combustion de turbine à gaz comprenant des brûleurs à prémélange ayant des géométries différentes
EP2230459A1 (fr) * 2007-12-27 2010-09-22 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6449951B1 (en) * 1999-08-18 2002-09-17 Alstom Combustion device for generating hot gases
EP1426689A1 (fr) * 2002-11-19 2004-06-09 Siemens Westinghouse Power Corporation Chambre de combustion de turbine à gaz comprenant des brûleurs à prémélange ayant des géométries différentes
EP2230459A1 (fr) * 2007-12-27 2010-09-22 Mitsubishi Heavy Industries, Ltd. Chambre de combustion de turbine à gaz

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