EP1112462A1 - Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante - Google Patents

Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante

Info

Publication number
EP1112462A1
EP1112462A1 EP99952383A EP99952383A EP1112462A1 EP 1112462 A1 EP1112462 A1 EP 1112462A1 EP 99952383 A EP99952383 A EP 99952383A EP 99952383 A EP99952383 A EP 99952383A EP 1112462 A1 EP1112462 A1 EP 1112462A1
Authority
EP
European Patent Office
Prior art keywords
burner
pilot
gas turbine
burners
hybrid
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
EP99952383A
Other languages
German (de)
English (en)
Other versions
EP1112462B1 (fr
Inventor
Stefan Hoffmann
Michael Kessler
Germann Scheer
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
Original Assignee
Siemens AG
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 filed Critical Siemens AG
Publication of EP1112462A1 publication Critical patent/EP1112462A1/fr
Application granted granted Critical
Publication of EP1112462B1 publication Critical patent/EP1112462B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a method for operating a
  • Gas turbine with a plurality of hybrid burners in a combustion chamber also relates to a gas turbine with a plurality of hybrid burners in a combustion chamber.
  • DE 196 37 725 AI describes a method and a device for the combustion of fuel with air in a combustion chamber.
  • the air is supplied to the combustion chamber through at least one air inlet and the fuel is supplied through several burners.
  • Each burner has a characteristic phase response, for example an associated delay time, corresponding to a time period after which an acoustic pulse in the combustion chamber causes a thermal pulse when the fuel supplied via this burner is burned.
  • the supply of the fuel via the burners is controlled in such a way that the delay times of the burners are significantly different from one another.
  • the delay time of a burner corresponds to a phase difference at the location of the burner between an acoustic vibration in the combustion chamber and a thermal vibration at the burner.
  • combustion vibrations are caused by the interaction between the acoustics of the combustion chamber and a thermal power release during combustion. These combustion vibrations can lead to high noise pollution or even mechanical damage.
  • combustion vibrations emanating from the individual burners can counteract reinforce each other. Because different amounts of fuel are supplied to the burners, the delay times for the burners are different. The delay time of a burner in a combustion chamber is made up of different summands, each of which can be traced back to individual components of the system consisting of burner, combustion chamber and flame.
  • the summands related to the burner and the combustion chamber are mainly determined by the geometry of the burner and the combustion chamber; a summand that can be traced back to the flame itself is largely determined by the properties of the combustion itself.
  • the summand itself can be further broken down into a convective delay time, which characterizes a transport time for the transport of the reactants to the flame front where the combustion begins, a heating time which specifies the time for the heating of the reactants to the temperature required for ignition, and a reaction kinetic delay time, which is determined by the course of the combustion itself.
  • the convective delay time clearly outweighs the other two summands. Different delay times for the various burners mean that the combustion vibrations emanating from the individual burners no longer reinforce one another.
  • the object of the invention is to provide a method for operating a burner arrangement in which combustion vibrations are largely suppressed.
  • Another object of the invention is to provide a gas turbine which has favorable properties, in particular with regard to a low tendency to form combustion vibrations.
  • the object directed to a method is achieved by a method for operating a burner arrangement with a plurality of hybrid burners in a combustion chamber, each hybrid burner having a pilot burner and a main burner and wherein a pilot fuel quantity is fed to each pilot burner, at least two of the Pilot burners are operated with a different pilot fuel quantity, and the difference in the pilot fuel quantity is set depending on an output of the burner arrangement.
  • a hybrid burner has a pilot burner and a main burner.
  • the pilot burner preferably works as a diffusion burner, i. H. Fuel and combustion air are mixed and burned in the combustion chamber by diffusion.
  • the main burner is a premix burner, i.e. H.
  • Fuel and combustion air are mixed before entering the combustion chamber and then burned. This usually ignites the fuel from the main burner on the flame of the pilot burner.
  • the burner assembly delivers power.
  • This output can, for. B. a power for a boiler or a power for driving a turbine.
  • High output rates are achieved by operating the main burner, the pilot burners being primarily responsible for stabilizing the combustion of the main burner. If the output is low, only the pilot burner can work as a diffusion burner.
  • the invention is based on the knowledge that a static supply of a different amount of fuel to the burners to suppress combustion vibrations cannot be carried out over the entire range of the possible output power, also called the load, of the burner arrangement.
  • the pilot burners When the output is low, the pilot burners usually have to be supplied with a large amount of fuel in order to stably ignite a lean fuel mixture from the main burner.
  • the supply of different pilot fuel supplies is matched to the minimum pilot fuel supply required to stabilize the combustion.
  • the burner arrangement can thus be operated stably at low loads on the one hand and on the other hand combustion vibrations can be effectively suppressed by supplying different pilot fuel quantities to at least two of the pilot burners by means of the different delay times of the pilot burners caused thereby.
  • the difference in the pilot fuel quantity preferably increases with increasing output. With increased output, a greater difference in the pilot fuel quantity can thus be set without impairing the stability of the combustion. Since disruptive combustion vibrations occur precisely at higher output powers, operating the pilot burners with different amounts of pilot fuel is particularly advantageous with regard to the suppression of combustion vibrations.
  • a majority of the hybrid burners are preferably operated with one to two percent of a maximum pilot fuel quantity and the rest of the hybrid burners with five to 15 percent of the maximum pilot fuel quantity.
  • a first number of hybrid burners are preferably operated with a first pilot fuel quantity and a second number of hybrid burners with a second pilot fuel quantity, the first number being more than 4 times as large as the second Number and the second pilot fuel quantity is more than 2 times as large as the first pilot fuel quantity.
  • the large output of a gas turbine can lead to very strong combustion vibrations.
  • combustion vibrations are practically unpredictable and must be combated by additional measures.
  • the different setting of the pilot fuel quantities depending on the load offers a simple and efficient means of suppressing combustion vibrations.
  • the object directed to a gas turbine is achieved by a gas turbine having a plurality of hybrid burners in a combustion chamber, each hybrid burner having a pilot burner and a main burner and wherein a pilot fuel quantity can be fed to each pilot burner, a control unit for load-dependent control of the supply of differently sized pilot fuel quantities at least two of the pilot burners are provided.
  • 1 shows a gas turbine with an annular combustion chamber and 2 shows a longitudinal section through a hybrid burner.
  • a gas turbine 1 which is directed along an axis 3 Compressor 5, an annular combustion chamber 7 and a turbine 9.
  • a plurality of hybrid burners 11 are arranged along a circumference of the annular combustion chamber 7.
  • a fuel feed line 13 for pilot fuel leads to each hybrid burner 11.
  • a control unit 15 is connected in part of the fuel feed lines 13.
  • the control unit 15 could also be connected to all of the fuel supply lines 13.
  • a signal line 17 also leads to the control unit 15.
  • the gas turbine 1 can be operated at different output powers or loads.
  • the power release from the combustion of fuel and combustion air leads to an output of the gas turbine 1.
  • a signal is fed to the control unit 15 via the signal line 17, which signal reflects the size of an instantaneous output of the gas turbine 1.
  • the control unit 15 regulates the pilot fuel quantity in the connected fuel supply lines 13.
  • the control unit 15 does not necessarily have to be connected directly to the fuel supply lines 13. You could also control valves which are arranged in the fuel supply lines 13.
  • the control unit 15 delivers at least two of the hybrid burners 11 a different amount of pilot fuel. This different pilot fuel quantity results in 11 different delay times for these hybrid burners.
  • a hybrid burner 11 is shown schematically in a longitudinal section in FIG.
  • the hybrid burner 11 has a central pilot burner 21.
  • the pilot burner 21 is supplied with a pilot fuel quantity 23 via a fuel supply line 13 and combustion air 24 via an air duct 22.
  • the pilot burner 21 is surrounded concentrically by a main burner 25 in the form of an annular channel.
  • a premixed fuel-air stream 27 is guided in this and ignites on a pilot flame 29 of the pilot burner 21.
  • a control unit 15 is connected to the fuel supply line 13. Depending on a signal from a signal line 17, this regulates the amount of pilot fuel 23 supplied in the combustion supply line 13. This regulation takes place depending on the output of a gas turbine, not shown here, in which the hybrid burner 11 is installed.
  • the maximum amount of pilot fuel 23 is supplied to the pilot burner 21 in order to stably ignite a relatively lean fuel / air mixture 27 in the main burner 25 by means of an intense pilot flame 29. With a higher output, a richer mixture results for the fuel air flow 27.
  • a somewhat smaller pilot fuel quantity 23 is sufficient to maintain a stable combustion of the fuel / air mixture 27 with the aid of the pilot flame 29.
  • a small part of the hybrid burners is operated with an increased amount of pilot fuel compared to the remaining hybrid burners 11. This effectively suppresses combustion vibrations.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)

Abstract

L'invention concerne une turbine à gaz (1) comportant une pluralité de brûleurs hybrides (11) qui présentent chacun un brûleur à flamme pilote (21) et un brûleur principal (25). Les brûleurs à flamme pilote (21) reçoivent un volume différent de combustible, en fonction de la charge de la turbine à gaz (1). Ce procédé permet de parvenir à un fonctionnement stable de la turbine à gaz (1), aussi bien avec des charges réduites, qu'à une suppression efficace des vibrations de combustion, en cas de charges élevées.
EP99952383A 1998-08-31 1999-08-13 Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante Expired - Lifetime EP1112462B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19839626 1998-08-31
DE19839626 1998-08-31
PCT/DE1999/002531 WO2000012940A1 (fr) 1998-08-31 1999-08-13 Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante

Publications (2)

Publication Number Publication Date
EP1112462A1 true EP1112462A1 (fr) 2001-07-04
EP1112462B1 EP1112462B1 (fr) 2003-06-18

Family

ID=7879310

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99952383A Expired - Lifetime EP1112462B1 (fr) 1998-08-31 1999-08-13 Procede d'exploitation d'une turbine a gaz et turbine a gaz correspondante

Country Status (5)

Country Link
US (1) US6425239B2 (fr)
EP (1) EP1112462B1 (fr)
JP (1) JP4339519B2 (fr)
DE (1) DE59906025D1 (fr)
WO (1) WO2000012940A1 (fr)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20020134740A1 (en) * 2001-03-23 2002-09-26 Pierre Cote Inverted air box aerator and aeration method for immersed membrane
DE59901946D1 (de) * 1998-04-23 2002-08-08 Siemens Ag Brennkammeranordnung
SE521293C2 (sv) * 2001-02-06 2003-10-21 Volvo Aero Corp Förfarande och anordning för tillförsel av bränsle till en brännkammare
EP1278014B1 (fr) * 2001-07-18 2007-01-24 Rolls-Royce PLC Dispositif d'alimentation en carburant
DE102004015187A1 (de) * 2004-03-29 2005-10-20 Alstom Technology Ltd Baden Brennkammer für eine Gasturbine und zugehöriges Betriebsverfahren
US7640725B2 (en) * 2006-01-12 2010-01-05 Siemens Energy, Inc. Pilot fuel flow tuning for gas turbine combustors
US7805922B2 (en) * 2006-02-09 2010-10-05 Siemens Energy, Inc. Fuel flow tuning for a stage of a gas turbine engine
DE102007009922A1 (de) 2007-02-27 2008-08-28 Ulrich Dreizler Hohlflamme
US20110067377A1 (en) * 2009-09-18 2011-03-24 General Electric Company Gas turbine combustion dynamics control system
US20110072826A1 (en) * 2009-09-25 2011-03-31 General Electric Company Can to can modal decoupling using can-level fuel splits
EP2423589A1 (fr) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Agencement de brûleur
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
US20150107255A1 (en) * 2013-10-18 2015-04-23 General Electric Company Turbomachine combustor having an externally fueled late lean injection (lli) system
JP5973096B1 (ja) * 2016-01-14 2016-08-23 三菱日立パワーシステムズ株式会社 プラント分析装置、プラント分析方法、およびプログラム

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DE3361535D1 (en) * 1982-05-28 1986-01-30 Bbc Brown Boveri & Cie Gas turbine combustion chamber and method of operating it
JPS61241425A (ja) * 1985-04-17 1986-10-27 Hitachi Ltd ガスタ−ビンの燃料ガス制御方法及び制御装置
US4735052A (en) * 1985-09-30 1988-04-05 Kabushiki Kaisha Toshiba Gas turbine apparatus
DE4223828A1 (de) * 1992-05-27 1993-12-02 Asea Brown Boveri Verfahren zum Betrieb einer Brennkammer einer Gasturbine
US5289685A (en) * 1992-11-16 1994-03-01 General Electric Company Fuel supply system for a gas turbine engine
JP3335713B2 (ja) * 1993-06-28 2002-10-21 株式会社東芝 ガスタービン燃焼器
US5402634A (en) * 1993-10-22 1995-04-04 United Technologies Corporation Fuel supply system for a staged combustor
US5442922A (en) * 1993-12-09 1995-08-22 United Technologies Corporation Fuel staging system
JP2858104B2 (ja) * 1996-02-05 1999-02-17 三菱重工業株式会社 ガスタービン燃焼器

Non-Patent Citations (1)

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Title
See references of WO0012940A1 *

Also Published As

Publication number Publication date
JP2002523685A (ja) 2002-07-30
US6425239B2 (en) 2002-07-30
DE59906025D1 (de) 2003-07-24
JP4339519B2 (ja) 2009-10-07
EP1112462B1 (fr) 2003-06-18
WO2000012940A1 (fr) 2000-03-09
US20010020358A1 (en) 2001-09-13

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