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WO2010097427A1 - Dispositif et procédé de commande d'une turbine équipée de plusieurs brûleurs pour des combustibles liquides ou gazeux - Google Patents

Dispositif et procédé de commande d'une turbine équipée de plusieurs brûleurs pour des combustibles liquides ou gazeux Download PDF

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Publication number
WO2010097427A1
WO2010097427A1 PCT/EP2010/052388 EP2010052388W WO2010097427A1 WO 2010097427 A1 WO2010097427 A1 WO 2010097427A1 EP 2010052388 W EP2010052388 W EP 2010052388W WO 2010097427 A1 WO2010097427 A1 WO 2010097427A1
Authority
WO
WIPO (PCT)
Prior art keywords
burner
burners
turbine
fuel
control
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/EP2010/052388
Other languages
German (de)
English (en)
Inventor
Georg Bachmaier
Oliver Hennig
Gerit Ebelsberger
Randolf Mock
Thomas Vontz
Wolfgang Zöls
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
Original Assignee
Siemens AG
Siemens Corp
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 filed Critical Siemens AG
Publication of WO2010097427A1 publication Critical patent/WO2010097427A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/228—Dividing fuel between various burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed

Definitions

  • the invention relates to the control of turbines whose fuel supply is divided by a plurality of burners.
  • the fuel quantities are set for all burners together in a main line.
  • the combustion air is often supplied via a fan, the amount can be controlled differently within certain limits.
  • more burners or burner baskets in a turbine usually who to, applies first ⁇ that each burner is provided with a fuel feed ⁇ .
  • the control of the amount of fuel is done in a relatively far away from the burner main ⁇ line, only then a division of the fuel quantity is done to the individual burners.
  • the burners are provided, for example, a turbine by a calibration approximately equal, that is, ⁇ represents voreinge in their function to the same level during operation.
  • the adjustment or calibration of the individual burners happens statically and in particular in a single operating point. Flow changes due to fuel composition, aging of materials or different pressures in the system can result in uneven functions.
  • the above-mentioned Cal ⁇ turing is repeated at every major service at the turbine.
  • the calorific value of the fuel used can fluctuate.
  • the individual burners must be adapted as quickly as possible to a new fuel composition. It can not be relied upon as a rule that sämtli ⁇ che burner show the same behavior in a fuel switch in all operating areas.
  • Instabilities of individual burners can for example also lead to vibrations in the turbine. This can cause damage to the turbine. An active system to suppress these vibrations and vibrations is currently not available.
  • the invention has for its object to improve the controls or controls of burners on a fuel turbine such that the above-mentioned disadvantages do not occur as in the prior art.
  • the invention is based on the finding that a Integ ⁇ ration of at least one highly dynamic and precisely adjustable FestMechaktorventils or solenoid controlled Ven ⁇ TILs at each performs at least one fuel supply line for each burner to a personalization related to each individual burner control or regulation, which at any time can be and driven to each operating status of each individual burner on the fuel side individually and optimally or Ge ⁇ controls.
  • each burner can always be entered on a specific, de ⁇ finêts by predetermined parameter level.
  • vibrations can be avoided by the exact settings of individual burners. This is especially true when setting the lean mode, with each burner has different characteristics in the control of this operating state.
  • a piezoelectric valve is used as a solid-state actuator valve. This has ben ne ⁇ a sufficient fuel flow rate, gas or liquid, a highly dynamic function and is gleichzei ⁇ tig precisely adjustable.
  • a highly dynamic control valve is located in each fuel feed line.
  • this can be designed differently, preferably piezoelectrically operated valves are used, but depending on the requirements, too
  • Solenoid controlled valves are eligible. Solenoid gesteu ⁇ erte valves are inexpensive and robust, but have a larger volume. A piezoelectric valve can control we ⁇ sentlich detail.
  • a burner control can be significantly supported by databases with operating parameters of individual burners or the respective turbine are available and are accessible to the burner control.
  • a further possibility for a total of trouble-free operation of a turbine consists ⁇ A set of physical or mathematical models. For this purpose, the combination with a regulation of individual burners or the entire turbine is generally advantageous.
  • Vibrations or vibrations on a gas turbine can be actively eliminated by so-called noise suppression or vibration monitoring systems. Furthermore, it is advantageous to control individual burners individually due to under ⁇ different handy design features or to fix and at the same time to consider the higher-level parameters for the operation of the turbine, in particular the gas turbine, at the individual burners.
  • the figure shows a gas turbine 7, shown schematically in section, with combustion air supply from the right side and individual burners 9, 10, and fuel gas supply lines with corresponding Festangeaktorventilen 5, 6.
  • a fuel control valve for example 20% can be useful.
  • the entire amount of from 0% to 100% is not varied, but only for example the SET ⁇ lung or gas volume or amount of liquid fuel from 100% to 80%.
  • a main flow or a pilot flow of fuel through the highly dynamic valve can be set in the shortest possible time, but no overshoots are generated during such load changes of the turbine.
  • a fluctuating fuel composition can affect the desired equality of all burners on a fuel turbine during operation. State-of-the-art calibration, which takes place in the static state, takes significant uptime.
  • each burner can be individually adapted by its valves 5, 6 present in its fuel supply line.
  • each burner can be individually adjusted or adjusted to new fuel compositions, liquid or gaseous fuel. This is done by appropriate control or by using at least one control loop.
  • a turbine is supplied, for example, with a line for a main gas stream 1 and additionally with a line for a pilot gas stream 2 with fuel gas or liquid fuel, then according to the invention a division by a distributor or manifold is made.
  • the highly dynamic piezoelectrically controlled valves are in
  • burners 9, 10 are generally arranged in a circle around the circumference of the turbine, wherein in the figure, only 2 burners are shown in section.
  • the control or regulating devices in the form of the valves 5, 6 are present on each burner.
  • a high dynamic piezoelectric valve or a solenoid controlled valve can be used. Vibrations can be eliminated as much as possible over a ge ⁇ suitable sensor technology in combination with active noise cancellation.
  • a burner By controlling or regulating a pilot flame of each burner basket / burner, a burner is correspondingly driven by a piezo valve in a fuel supply line. By modulating, for example, the pilot gas stream 2, the position of the flame front in the combustion chamber of the corresponding gas turbine can be varied.
  • An admixture of air in the fuel gas supply lines corresponds to a change in the calorific value of the fuel gas used.
  • a setting of a burner at a load change of the turbine when using the invention can be realized within milliseconds.
  • a control of burners on a gas turbine is made in accordance with the invention in fuel gas supply lines behind a distributor, ie in individual, burner individually supplying lines through a corresponding valve.

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)

Abstract

L'invention concerne un dispositif de commande d'une turbine à gaz (7) équipée de plusieurs brûleurs. Pour un fonctionnement uniforme de tous les brûleurs, la commande du gaz combustible et des quantités d'air pour tous les brûleurs est réalisée conjointement en amont d'un distributeur pour l'acheminement vers chaque brûleur individuel. Dans la conduite d'alimentation en gaz combustible vers les brûleurs de la turbine à gaz (7), chaque brûleur est relié séparément à au moins une conduite d'acheminement de gaz combustible, et au moins une soupape d'actionnement intégrée (5, 6) est présente pour la commande de gaz combustible. L'invention concerne également un procédé pour faire fonctionner un dispositif selon une des revendications 1 à 5, permettant de moduler un flux de gaz combustible dans une conduite d'alimentation de brûleur dans une plage de 20 % max. de la plage de fonctionnement d'une soupape intégrée (5, 6).
PCT/EP2010/052388 2009-02-25 2010-02-25 Dispositif et procédé de commande d'une turbine équipée de plusieurs brûleurs pour des combustibles liquides ou gazeux Ceased WO2010097427A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009010611.1 2009-02-25
DE200910010611 DE102009010611A1 (de) 2009-02-25 2009-02-25 Vorrichtung und Verfahren zur Steuerung einer mit mehreren Brennern ausgestatteten Turbine für flüssige oder gasförmige Brennstoffe

Publications (1)

Publication Number Publication Date
WO2010097427A1 true WO2010097427A1 (fr) 2010-09-02

Family

ID=42154825

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/052388 Ceased WO2010097427A1 (fr) 2009-02-25 2010-02-25 Dispositif et procédé de commande d'une turbine équipée de plusieurs brûleurs pour des combustibles liquides ou gazeux

Country Status (2)

Country Link
DE (1) DE102009010611A1 (fr)
WO (1) WO2010097427A1 (fr)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4716719A (en) * 1985-04-17 1988-01-05 Hitachi, Ltd. Method of and apparatus for controlling fuel of gas turbine
WO1998034067A1 (fr) * 1997-02-04 1998-08-06 Siemens Aktiengesellschaft Dispositif de combustion et procede d'attenuation active des vibrations dues a la combustion
WO2000014451A1 (fr) * 1998-09-10 2000-03-16 Siemens Aktiengesellschaft Procede pour faire fonctionner un bruleur, et ensemble bruleur correspondant
EP1396681A1 (fr) * 2002-09-04 2004-03-10 Siemens Building Technologies AG Regulateur de brûleur et procédé pour ajuster un regulateur de brûleur
EP1662116A1 (fr) * 2004-11-24 2006-05-31 General Electric Company Système de combustion à chambres multiples d'une turbine à gaz
US20070119147A1 (en) * 2004-05-07 2007-05-31 Cornwell Michael D Active combustion control system for gas turbine engines
WO2009003729A1 (fr) * 2007-07-02 2009-01-08 Siemens Aktiengesellschaft Brûleur et procédé de gestion du fonctionnement d'un brûleur
GB2451144A (en) * 2007-07-26 2009-01-21 Gen Electric Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN1480466A (zh) * 2002-09-03 2004-03-10 �й������ž�����ҽѧ��ѧԺ����ҽ 一类溶栓抗凝双功能融合蛋白及应用

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4716719A (en) * 1985-04-17 1988-01-05 Hitachi, Ltd. Method of and apparatus for controlling fuel of gas turbine
WO1998034067A1 (fr) * 1997-02-04 1998-08-06 Siemens Aktiengesellschaft Dispositif de combustion et procede d'attenuation active des vibrations dues a la combustion
WO2000014451A1 (fr) * 1998-09-10 2000-03-16 Siemens Aktiengesellschaft Procede pour faire fonctionner un bruleur, et ensemble bruleur correspondant
EP1396681A1 (fr) * 2002-09-04 2004-03-10 Siemens Building Technologies AG Regulateur de brûleur et procédé pour ajuster un regulateur de brûleur
US20070119147A1 (en) * 2004-05-07 2007-05-31 Cornwell Michael D Active combustion control system for gas turbine engines
EP1662116A1 (fr) * 2004-11-24 2006-05-31 General Electric Company Système de combustion à chambres multiples d'une turbine à gaz
WO2009003729A1 (fr) * 2007-07-02 2009-01-08 Siemens Aktiengesellschaft Brûleur et procédé de gestion du fonctionnement d'un brûleur
GB2451144A (en) * 2007-07-26 2009-01-21 Gen Electric Method and apparatus for actively controlling fuel flow to a mixer assembly of a gas turbine engine combustor

Also Published As

Publication number Publication date
DE102009010611A1 (de) 2010-08-26

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