EP0790466A2 - Méthode pour le changement rapide entre combustion de prémélange et de diffusion pour chambre de combustion de turbine à gaz alimentée à gaz - Google Patents

Méthode pour le changement rapide entre combustion de prémélange et de diffusion pour chambre de combustion de turbine à gaz alimentée à gaz Download PDF

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Publication number
EP0790466A2
EP0790466A2 EP96118560A EP96118560A EP0790466A2 EP 0790466 A2 EP0790466 A2 EP 0790466A2 EP 96118560 A EP96118560 A EP 96118560A EP 96118560 A EP96118560 A EP 96118560A EP 0790466 A2 EP0790466 A2 EP 0790466A2
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EP
European Patent Office
Prior art keywords
premix
switching
diffusion
criterion
fuel gas
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.)
Granted
Application number
EP96118560A
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German (de)
English (en)
Other versions
EP0790466A3 (fr
EP0790466B1 (fr
Inventor
Kurt Dr.-Ing. Bauermeister
Michael Dr.-Ing. Brodmann
Peter Dipl.-Ing. Küper
Jürgen Dipl.-Ing. Moroni
Hans Dipl.-Ing. Weibel
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.)
Everllence SE
Original Assignee
MAN Gutehoffnungshutte GmbH
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Publication date
Application filed by MAN Gutehoffnungshutte GmbH filed Critical MAN Gutehoffnungshutte GmbH
Publication of EP0790466A2 publication Critical patent/EP0790466A2/fr
Publication of EP0790466A3 publication Critical patent/EP0790466A3/fr
Application granted granted Critical
Publication of EP0790466B1 publication Critical patent/EP0790466B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2237/00—Controlling
    • F23N2237/02—Controlling two or more burners

Definitions

  • the invention relates to a method and a device for rapid switching from premixing mode to diffusion mode in gas turbines with at least one combustion chamber with simultaneous control of the diffusion and premixing control valves in the fuel gas supply lines, i. H. Opening of the diffusion gas path and simultaneous closing of the premix gas path of a burner with rapid load reduction and extinguishing of the premix flame.
  • Such a burner can be operated both in the so-called diffusion and in the premix mode.
  • diffusion mode there are also zones with stoichiometric combustion and thus high temperature in the flame, which lead to NO x formation.
  • the gas turbine starts, the burner works as a diffusion burner and, as soon as the gas turbine has reached a certain output, is switched over to operation as a premix burner.
  • the premix flame is stabilized by a small pilot flame.
  • Gas turbines are used, for example, to drive pipeline compressors and generators.
  • the fuel gas control valve closes very quickly to prevent the turbine speed from increasing.
  • the reignition occurs either through the pilot gas flame still burning or through hot parts in the combustion chamber or in the hot gas area of the gas turbine. This reignition takes place in an uncontrolled manner and takes the form of a deflagration or detonation.
  • a premix burner with an integrated diffusion burner having a premixing chamber delimited at the downstream end by a flame holder, into which a main fuel nozzle opens and wherein the diffusion burner has a pilot fuel nozzle.
  • the entire supply of the combustion air takes place via a feed device which opens into the premixing chamber.
  • a fuel control device regulates the fuel supply in such a way that a pure diffusion burner operation occurs after starting, then a diffusion burner and premix burner operation and a premix burner operation in the upper load range.
  • the fuel control device to which a load signal is applied, regulates the flow through the fuel control valve via corresponding control lines.
  • So-called two-way valves are used as fuel control valves, which limit the fuel supply between a min. and max. Control the flow rate. Control devices that enable a quick switchover in unstable operation are not arranged here.
  • a method is also known in which the combustion chamber and burner in the event of load jumps or load shedding, the gas turbine working as a generator drive, switches from premixing to diffusion operation.
  • the speed gradient of the gas turbine is used to identify these transient operating processes. If this criterion detects a load jump, the diffusion control valves are opened and the premixing control valves are closed at the same time.
  • the valve operating time is 5 seconds.
  • the pilot gas quantity is increased via a 2/2 way valve with a positioning time of approx. 150 ms and a so-called quick changeover is carried out.
  • the object of the invention is to provide a control method for a rapid switchover from premixing to diffusion operation in order to prevent fuel deflagrations and detonations in the combustion chamber or in the hot gas area during premixing operation, combined with an uncontrolled reignition of the premixing flame.
  • rapid changeover valves are installed in the premixing gas line with a connection to the diffusion gas burner, which upon detection of such a process - extinguishing of the premixing flame or upon occurrence of a fault which can lead to extinguishing of the premixing flame - switches from premixing mode to diffusion mode within approx. 100 ms so that an uncontrolled re-ignition of the premixing flame is excluded.
  • the amount of fuel gas to be burned can be passed from the premix gas supply line to the diffusion gas line and thus to the diffusion burner within approx. 100 ms.
  • FIG. 1 shows the control method according to the invention, including the associated devices for operating a gas turbine with two burners (11, 12) on the combustion chambers (9, 10).
  • the combustion chambers (9, 10) are designed in the upper part as a flame tube (17) and in the lower part as a mixing tube (18) with the inlet manifold (19) for the supply of compressor or combustion air.
  • Fuel gas is fed to the burners (11, 12) via a fuel gas supply line (13).
  • a pilot gas line (14) branches off in front of the fuel gas control valve (1) with the displacement sensor (Z) (4), in which the fuel supply is regulated by a pilot gas control valve (2).
  • the fuel gas supply line (13) branches after the fuel gas control valve (1, 4) into fuel supply lines for both combustion chambers (9, 10).
  • a quick changeover valve (3) with servo valves V 1 , V 2 (7) in the branching fuel supply lines (13) the fuel supply to the diffusion gas line (15) and the premix gas line (16) is controlled.
  • the combustion chambers (9, 10) are monitored in the area of the flame tube (17) by pressure measuring devices P 1 , P 2 (5) and by an optical flame monitor B 1 , B 2 (6).
  • Quick changeover valves (3) are wired with control logic for quick changeover (8).
  • Fig. 2 shows the structure of the control logic of a rapid changeover (8) which contains a total of three changeover criteria from premixing to diffusion operation in the case of two burners. Additional switching criteria can be added if required.
  • Switching criterion 20 is the path measurement (Z) (4) of the fuel gas valve (1)
  • switchover criterion 21 is the pressure measurement P 1 , P 2 (5) in the flame tube (17)
  • switchover criterion 22 is the optical flame monitoring B 1 , B 2 (6) in the flame tube (17) of the combustion chamber (9, 10).
  • the control logic of the quick changeover (8) immediately after evaluating the entered measurement results for the changeover criteria 20 and 21 or for all three changeover criteria 20, 21 and 22 causes a parallel Control of the servo valves V 1 , V 2 (7) for the quick changeover valves (3), which divert the fuel gas quantity from the premix gas line (16) into the diffusion gas line (15) within approx. 100 ms.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Feeding And Controlling Fuel (AREA)
EP96118560A 1996-02-16 1996-11-20 Méthode et appareil pour le changement rapide entre combustion de prémélange et de diffusion pour chambre de combustion de turbine à gaz alimentée à gaz Expired - Lifetime EP0790466B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19605736 1996-02-16
DE19605736A DE19605736A1 (de) 1996-02-16 1996-02-16 Verfahren zur Schnellumschaltung vom Vormischbetrieb in den Diffusionsbetrieb in einer Brennkammer einer mit Brenngas betriebenen Gasturbine

Publications (3)

Publication Number Publication Date
EP0790466A2 true EP0790466A2 (fr) 1997-08-20
EP0790466A3 EP0790466A3 (fr) 1998-12-16
EP0790466B1 EP0790466B1 (fr) 2003-05-07

Family

ID=7785563

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96118560A Expired - Lifetime EP0790466B1 (fr) 1996-02-16 1996-11-20 Méthode et appareil pour le changement rapide entre combustion de prémélange et de diffusion pour chambre de combustion de turbine à gaz alimentée à gaz

Country Status (3)

Country Link
US (1) US5806299A (fr)
EP (1) EP0790466B1 (fr)
DE (2) DE19605736A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107228382A (zh) * 2016-03-25 2017-10-03 安萨尔多能源公司 带有光学探头的燃气轮机燃烧器组件

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6092362A (en) * 1996-11-27 2000-07-25 Hitachi, Ltd. Gas-turbine combustor with load-responsive premix burners
DE59710054D1 (de) * 1997-11-10 2003-06-12 Alstom Switzerland Ltd Verfahren zur Überwachung des Versorgungssystems einer Gasturbine mit Mehrbrennersystem sowie Vorrichtung zur Durchführung des Verfahrens
EP1199442A3 (fr) * 1998-05-08 2003-01-22 Mitsubishi Heavy Industries, Ltd. Système de purge de carburant liquide d'une turbine à gaz
US6169334B1 (en) 1998-10-27 2001-01-02 Capstone Turbine Corporation Command and control system and method for multiple turbogenerators
JP2000248964A (ja) * 1999-02-26 2000-09-12 Honda Motor Co Ltd ガスタービンエンジン
US6385960B1 (en) * 1999-10-14 2002-05-14 General Electric Company Methods and apparatus for operation of gas turbines
US6405522B1 (en) * 1999-12-01 2002-06-18 Capstone Turbine Corporation System and method for modular control of a multi-fuel low emissions turbogenerator
DE10049205A1 (de) * 2000-10-05 2002-05-23 Alstom Switzerland Ltd Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners
EP1270902B1 (fr) * 2001-06-22 2009-10-21 ALSTOM Technology Ltd Procédé de démarrage d'un système de turbine à gaz
JP3975232B2 (ja) * 2002-10-22 2007-09-12 川崎重工業株式会社 ガスタービンエンジンの制御方法および制御システム
US7640725B2 (en) * 2006-01-12 2010-01-05 Siemens Energy, Inc. Pilot fuel flow tuning for gas turbine combustors
EP1944547A1 (fr) * 2007-01-15 2008-07-16 Siemens Aktiengesellschaft Procédé de contrôle d'une fuite de carburant
US7950215B2 (en) * 2007-11-20 2011-05-31 Siemens Energy, Inc. Sequential combustion firing system for a fuel system of a gas turbine engine
JP5185757B2 (ja) 2008-10-01 2013-04-17 三菱重工業株式会社 ガスタービンの燃料制御方法および燃料制御装置ならびにガスタービン
ITCO20120008A1 (it) 2012-03-01 2013-09-02 Nuovo Pignone Srl Metodo e sistema per monitorare la condizione di un gruppo di impianti
US10215412B2 (en) * 2012-11-02 2019-02-26 General Electric Company System and method for load control with diffusion combustion in a stoichiometric exhaust gas recirculation gas turbine system
US20150075170A1 (en) * 2013-09-17 2015-03-19 General Electric Company Method and system for augmenting the detection reliability of secondary flame detectors in a gas turbine
CN109416181B (zh) 2016-05-12 2021-05-28 西门子公司 用于减少排放的选择性燃烧器控制方法
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

Citations (1)

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Publication number Priority date Publication date Assignee Title
DE3241162A1 (de) 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner

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US3747340A (en) * 1971-08-12 1973-07-24 Ford Motor Co Flame sensing system for a turbine engine
JP2618448B2 (ja) * 1988-08-09 1997-06-11 株式会社日立製作所 ガスタービン燃焼器状態監視装置及び監視方法及び制御方法
JP2894861B2 (ja) * 1991-04-18 1999-05-24 株式会社日立製作所 ガスタービン燃焼器の制御装置
JP2954401B2 (ja) * 1991-08-23 1999-09-27 株式会社日立製作所 ガスタービン設備およびその運転方法
GB9122965D0 (en) * 1991-10-29 1991-12-18 Rolls Royce Plc Turbine engine control system
JP2758301B2 (ja) * 1991-11-29 1998-05-28 株式会社東芝 ガスタービン燃焼器
JPH06323165A (ja) * 1993-05-17 1994-11-22 Hitachi Ltd ガスタービン用制御装置及び制御方法
CA2124069A1 (fr) * 1993-05-24 1994-11-25 Boris M. Kramnik Chambre de combustion de turbine a gaz a geometrie invariable, a faible niveau de pollution
US5465570A (en) * 1993-12-22 1995-11-14 United Technologies Corporation Fuel control system for a staged combustor

Patent Citations (1)

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Publication number Priority date Publication date Assignee Title
DE3241162A1 (de) 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107228382A (zh) * 2016-03-25 2017-10-03 安萨尔多能源公司 带有光学探头的燃气轮机燃烧器组件

Also Published As

Publication number Publication date
US5806299A (en) 1998-09-15
DE19605736A1 (de) 1997-08-21
EP0790466A3 (fr) 1998-12-16
EP0790466B1 (fr) 2003-05-07
DE59610422D1 (de) 2003-06-12

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