EP2487419A2 - System und Verfahren zum Betrieb einer Brennkammer - Google Patents

System und Verfahren zum Betrieb einer Brennkammer Download PDF

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Publication number
EP2487419A2
EP2487419A2 EP12154941A EP12154941A EP2487419A2 EP 2487419 A2 EP2487419 A2 EP 2487419A2 EP 12154941 A EP12154941 A EP 12154941A EP 12154941 A EP12154941 A EP 12154941A EP 2487419 A2 EP2487419 A2 EP 2487419A2
Authority
EP
European Patent Office
Prior art keywords
fuel
diluent
air
inlet
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.)
Withdrawn
Application number
EP12154941A
Other languages
English (en)
French (fr)
Inventor
Joseph Kirzhner
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 EP2487419A2 publication Critical patent/EP2487419A2/de
Withdrawn legal-status Critical Current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
    • F23R3/28—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
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2221/00—Pretreatment or prehandling
    • F23N2221/10—Analysing fuel properties, e.g. density, calorific
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/003—Systems for controlling combustion using detectors sensitive to combustion gas properties

Definitions

  • the present invention generally involves a system and method for operating a combustor.
  • the systems and methods of the present invention may be used for operating a combustor in a gas turbine.
  • Combustors are commonly used to ignite fuel to produce combustion gases having a high temperature and pressure.
  • gas turbines typically include one or more combustors to generate power or thrust.
  • a typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear.
  • Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state.
  • the compressed working fluid exits the compressor and flows through one or more nozzles in each combustor where the compressed working fluid mixes with fuel and ignites to generate combustion gases having a high temperature, pressure, and velocity.
  • the combustion gases expand in the turbine to produce work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
  • the fuel rich regions may increase the chance for the flame in the combustor to flash back into the nozzles and/or become attached inside the nozzles which may damage the nozzles.
  • flame flash back and flame holding may occur with any fuel, they occur more readily with high reactive fuels, such as hydrogen, that have a higher burning rate, flame velocity, and wider flammability range.
  • the present invention also resides in a method for operating a combustor that includes flowing a fuel through a fuel inlet in a nozzle and flowing air through an air inlet in the nozzle.
  • the method further includes sensing an operating parameter of the combustor, generating a signal reflective of the operating parameter, and controlling a flow of at least one of air or diluent to the fuel inlet based on the signal reflective of the operating parameter.
  • Various embodiments of the present invention include a system and method for operating a combustor.
  • liquid and/or gas fuels may flow through a nozzle in the combustor, and a controller may adjust the fuel flow and/or the injection of a diluent and/or air into the fuel flow to enhance the efficiency of the combustor, reduce undesirable emissions, and/or prevent or reduce the occurrence or damaging effects of flash back and flame holding.
  • a controller may adjust the fuel flow and/or the injection of a diluent and/or air into the fuel flow to enhance the efficiency of the combustor, reduce undesirable emissions, and/or prevent or reduce the occurrence or damaging effects of flash back and flame holding.
  • the compressed working fluid may pass through the flow holes 26 in the flow sleeve 24 to flow along the outside of the liner 20 to provide film or convective cooling to the liner 20.
  • the compressed working fluid reaches the end cover 18, the compressed working fluid reverses direction to flow through the one or more nozzles 14 where it mixes with fuel before igniting in the combustion chamber 22 to produce combustion gases having a high temperature and pressure.
  • the liquid fuel passage 32 and liquid fuel outlet 40 may be generally aligned with or along an axial centerline 54 of the nozzle 14, with the gaseous fuel passage 30 and gaseous fuel outlet 36 generally located radially outward from the liquid fuel passage 32.
  • the diluent and air passages 42, 44 may be generally aligned with the one or more fuel passages 30, 32 so that the diluent and air outlets 48, 52 are proximate to one or more of the fuel outlets 36, 40.
  • the various fuel, diluent, and air passages may extend through the nozzle at various angles, depending on the relative location of the various inlets and outlets, and the particular orientation or location of the various passages is not a limitation of the present invention unless specifically recited in the claims.
  • the fuel supply 62, 64 is in fluid communication with the nozzle through the one or more fuel inlets (e.g., the gaseous and/or liquid fuel inlets 34, 38) and/or the diluent inlet 46.
  • the system 60 may support various fuel operating modes for the combustor 10 by supplying liquid fuel to the combustion chamber 22 through the liquid fuel inlet 38 and/or diluent inlet 46 and gaseous fuel to the combustion chamber 22 through the gaseous fuel inlet 34, the liquid fuel inlet 38, and/or the diluent inlet 46.
  • the combustor 10 may operate using only liquid fuel supplied through valve 70 to the liquid fuel passage 32 and/or through valves 72 and 74 to the diluent passage 42.
  • the combustor 10 may operate using only gaseous fuel supplied through valve 78 to the gaseous fuel passage 30, through valve 80 to the liquid fuel passage 32, and/or through valve 82 to the diluent passage 44.
  • the combustor 10 may operate with a staged supply of liquid and/or gaseous fuel simultaneously supplied through the liquid fuel passage 32, the diluent passage 42, and the gaseous fuel passage 30.
  • the diluent may also be supplied through valve 92 to the gaseous fuel inlet 34 and/or through valves 94 and 96 to the liquid fuel inlet 38, and the air may also be supplied through valve 98 to the gaseous fuel inlet 34 and/or through valve 100 to the liquid fuel inlet 38 to flow diluent and/or air through the respective fuel passages 30, 32 for a number of purposes.
  • the diluent and/or air may be supplied to one or more fuel inlets 34, 38 to disperse or atomize the fuel flowing through the fuel passages 34, 38 to disburse the fuel and enhance mixing between the fuel and the compressed working fluid prior to combustion.
  • the diluent may be supplied through the homogenizer 76 to emulsify the liquid fuel prior to injection into the combustion chamber 22.
  • the emulsified liquid fuel may cool the downstream surface of the nozzle 14 and/or reduce the peak flame temperature of the combustion flame. Cooling the downstream surface of the nozzle 14 protects the nozzle 14 from excessive wear, premature failure, and/or carbon deposition (coking) on the surface of the nozzle 14. Reducing the peak flame temperature of the combustion flame reduces the production of undesirable emissions.
  • the diluent may be supplied through the valves 94, 96, and/or homogenizer 76 to increase the volume of the combustible fluid in the desired delivery passage prior to injection into the combustion chamber 22.
  • the pressure increases, improving the shape of the exit jet and reducing deposits/coking on the surface of the nozzle 14.
  • An additional combustible fluid pressure increase and improvement of atomization may be achieved by delivering air through valves 90, 98, 100 and mixing air with the combustible fluid. Air will create an effervescent (bubbling) effect, which will further promote better atomization and a more uniform combustion flame.
  • the diluent and/or air may be supplied to one or more fuel inlets 34, 38 in response to a flame holding event to cool the surface of the nozzle 14 proximate to the flame holding and/or extinguish the flame holding.
  • Embodiments of the systems and methods set forth herein may be implemented by one or more general-purpose or customized controllers adapted in any suitable manner to provide the desired functionality.
  • the controller 110 may be adapted to provide additional functionality, either complementary or unrelated to the present subject matter.
  • any suitable programming, scripting, or other type of language or combinations of languages may be used to implement the teachings contained herein.
  • some systems and methods set forth and disclosed herein may also be implemented by hard-wired logic or other circuitry, including, but not limited to, application-specific circuits. Of course, various combinations of computer-executed software and hard-wired logic or other circuitry may be suitable as well.
  • the controller 110 may be operably connected to one or more sensors that generate one or more parameter signals reflective of operating parameters of the combustor 10.
  • the sensors may be broadly organized as combustor/gas turbine performance sensors 114, fluid sensors 116, and stability sensors 118.
  • the combustion/gas turbine sensors 114 may be located throughout the combustor 10 or gas turbine to provide real time or near real-time parameter signals 120 reflective of the operating parameters of the combustor 10 or gas turbine.
  • the combustion/gas turbine sensors 114 may monitor and provide parameter signals 120 reflective of the pressure of the compressed working fluid (compressor discharge pressure), temperature of the compressed working fluid, various temperatures inside the combustor 10, gas turbine exhaust temperature, power level, or any number of other operating parameters of the combustor 10 or gas turbine.
  • the fluid sensors 116 may be positioned in various fluid supplies to the combustor 10 to provide parameter signals 122 reflective of the physical characteristics of the various fluids.
  • the fluid sensors 116 may monitor and provide parameter signals 122 reflective of the ambient air temperature and/or humidity, diluent temperature and/or pressure, or pressure, temperature, and/or calorie content of the fuel.
  • the stability sensors 118 may similarly be positioned throughout the combustor 10 and/or gas turbine to provide parameter signals 124 reflective of abnormal conditions in the combustor 10 and/or gas turbine.
  • the stability sensors 118 may monitor and provide parameter signals 124 reflective of temperatures inside or proximate to each nozzle 14 to indicate a flashback or flame holding event, pressure amplitudes and/or frequencies inside the combustor 10 to indicate combustor flame stability, or emissions content to indicate excessive undesirable emissions.
  • Fig. 4 provides a block diagram of a method for operating the combustor 10 shown in Fig. 1 according to one embodiment of the present invention.
  • the method may include generating an operating mode signal 126 reflective of the desired operating mode for the combustor 10.
  • the operating mode signal 126 may be generated manually, for example by an operator as indicated by block 128, or automatically, for example in response to a sensed operating level of the combustor 10.
  • the method may further include monitoring one or more operating parameters of the combustor 10 and generating one or more parameter signals reflective of the operating parameters.
  • combustor/gas turbine performance sensors 114 may generate parameter signals 120 reflective of the pressure of the compressed working fluid (compressor discharge pressure), temperature of the compressed working fluid, various temperatures inside the combustor 10, gas turbine exhaust temperature, power level, or any number of other operating parameters of the combustor 10 or gas turbine.
  • the fluid sensors 116 may generate parameter signals 122 reflective of the ambient air temperature and/or humidity, diluent temperature and/or pressure, or pressure, temperature, and/or calorie content of the fuel.
  • the stability sensors 118 may generate parameter signals 124 reflective of temperatures inside or proximate to each nozzle 114, pressure amplitudes and/or frequencies inside the combustor 10, or emissions content to indicate excessive undesirable emissions.
  • the controller 110 receives the one or more parameter signals 120, 122, 124 and/or the operating mode signal 126 and generates the control signal 112.
  • the control signal 112 adjusts the flow of at least one of the fuel, diluent, or air through the nozzle 14 to the combustor 10.
  • the controller 110 may simply adjust the flow rate of one or more of the fuel, diluent, or air through the respective fuel, diluent, or air passages in response to a change in power demand, ambient temperature, fuel quality, or various other operating parameters of the combustor 10 or gas turbine.
  • control signal 112 from the controller 110 may adjust the flow rate of one or more of the fuel, diluent, or air through one or more of the cross connected fuel, diluent, or air passages in response to a change in the operating mode signal 126.
  • control signal 112 from the controller 110 may adjust the diluent and/or air flow through the liquid fuel passage 32 to purge the liquid fuel from the liquid fuel passage 32 in anticipation of operating in a gaseous fuel only mode.
  • control signal 112 from the controller 110 may adjust the flow rate of one or more of the fuel, diluent, or air through one or more of the cross connected fuel or diluent passages in response to the stability sensor 118 parameter signal 124.
  • control signal 112 and the controller 110 may adjust the diluent and/or air flow through one or more of the fuel passages 30, 32 in response to a detected flame holding event and/or excessive amount of undesirable emissions.
  • Fig. 5 provides an exemplary graph of nitrous oxide emissions associated with various diluent to fuel ratios for non-emulsified fuel (dashed curve) compared to emulsified fuel (solid curve).
  • the system 60 may adjust the amount of diluent flow through the mixing piping and/or homogenizer 76 to adjust the combustible fluid pressure and diluent to fuel ratio in the emulsified fuel injected through the liquid fuel passage 32, thereby reducing the nitrous oxide emissions for the same diluent to fuel ratio.
  • Fig. 6 provides an exemplary graph of pressure oscillations associated with various diluent to fuel ratios for non-emulsified fuel (dashed curve) compared to emulsified fuel (solid curve).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP12154941A 2011-02-11 2012-02-10 System und Verfahren zum Betrieb einer Brennkammer Withdrawn EP2487419A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/025,426 US20120208136A1 (en) 2011-02-11 2011-02-11 System and method for operating a combustor

Publications (1)

Publication Number Publication Date
EP2487419A2 true EP2487419A2 (de) 2012-08-15

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EP12154941A Withdrawn EP2487419A2 (de) 2011-02-11 2012-02-10 System und Verfahren zum Betrieb einer Brennkammer

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US (1) US20120208136A1 (de)
EP (1) EP2487419A2 (de)
CN (1) CN102679359A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016063222A1 (en) * 2014-10-20 2016-04-28 A.S.EN. ANSALDO SVILUPPO ENERGIA S.r.l. Gas turbine unit with multifluid fuel supply and method of supplying a burner of a gas turbine unit

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US20130189632A1 (en) * 2012-01-23 2013-07-25 General Electric Company Fuel nozzel
CN103982911B (zh) * 2014-04-25 2017-01-25 广东工业大学 分段式陶瓷窑燃气与空气联动控制系统

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US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US6047550A (en) * 1996-05-02 2000-04-11 General Electric Co. Premixing dry low NOx emissions combustor with lean direct injection of gas fuel
US5857320A (en) * 1996-11-12 1999-01-12 Westinghouse Electric Corporation Combustor with flashback arresting system
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
US6092363A (en) * 1998-06-19 2000-07-25 Siemens Westinghouse Power Corporation Low Nox combustor having dual fuel injection system
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016063222A1 (en) * 2014-10-20 2016-04-28 A.S.EN. ANSALDO SVILUPPO ENERGIA S.r.l. Gas turbine unit with multifluid fuel supply and method of supplying a burner of a gas turbine unit

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Publication number Publication date
CN102679359A (zh) 2012-09-19
US20120208136A1 (en) 2012-08-16

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