EP1112462B1 - Verfahren zum betrieb einer gasturbine und gasturbine - Google Patents
Verfahren zum betrieb einer gasturbine und gasturbine Download PDFInfo
- Publication number
- EP1112462B1 EP1112462B1 EP99952383A EP99952383A EP1112462B1 EP 1112462 B1 EP1112462 B1 EP 1112462B1 EP 99952383 A EP99952383 A EP 99952383A EP 99952383 A EP99952383 A EP 99952383A EP 1112462 B1 EP1112462 B1 EP 1112462B1
- 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.)
- Expired - Lifetime
Links
Images
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 one Combustion chamber.
- the invention also relates to a gas turbine with a plurality of hybrid burners in one combustion chamber, such as described in document US-A-5 450 725.
- DE 196 37 725 A1 describes a method and a device for burning fuel with air in a combustion chamber described.
- the combustion chamber will be through at least an air inlet and the air through several burners Fuel supplied.
- Each burner has a characteristic Phase response, e.g. an associated delay time, accordingly a period of time after which an acoustic pulse in the combustion chamber a thermal pulse during combustion of the fuel supplied through this burner.
- the supply of the fuel via the burner becomes like this controlled that the delay times of the burners differ significantly are with each other.
- the delay time of a burner corresponds to a phase difference at the burner location between an acoustic vibration in the combustion chamber and one thermal vibration on the burner.
- Such combustion vibrations are caused by the interaction between the Acoustics of the combustion chamber and a thermal power release caused by the combustion. These combustion vibrations can lead to high noise pollution or even mechanical damage.
- the delay time of a Brenners in a combustion chamber is composed of different ones Summands, each on individual components of the system consisting of burner, combustion chamber and flame traceable are. Those related to the burner and the combustion chamber Summands are mainly determined by the geometry of burner and combustion chamber; a traceable to the flame itself Summand is essential due to its properties the combustion itself.
- the summand itself can be further decompose into a convective delay time, the one Transport time for the transport of the reactants to Flame front, where the combustion begins, characterizes, a heating time, which is the time for heating the Reaction partner to the temperature required for ignition indicates, as well as a reaction kinetic delay, which is determined by the course of the combustion itself.
- a convective delay time usually outweighs the other two Summands clearly. Different delay times for the Different burners cause that the individual Burning vibrations not emanating from burners reinforce each other more.
- the object of the invention is to provide a method of operation a burner arrangement in which combustion vibrations be largely suppressed.
- Another object of the invention is the specification of a gas turbine, particularly with regard to a slight tendency to form combustion vibrations has favorable properties.
- the object is directed to a method solved by a method for operating a burner arrangement with a plurality of hybrid burners in one combustion chamber, each hybrid burner having a pilot burner and a main burner and each pilot burner has a pilot fuel amount is fed, with at least two of the Pilot burners with a different amount of pilot fuel operated, and being the difference in the pilot fuel amount depending on the output of the burner arrangement is set.
- a hybrid burner has a pilot burner and a main burner on.
- the pilot burner preferably works as one Diffusion burner, d. H. Fuel and combustion air mixed and burned in the combustion chamber by diffusion.
- the main burner is a premix burner, i.e. H. Fuel and combustion air are removed before entering the Combustion chamber mixed and then burned. Ignited usually the fuel mixture of the main burner on the flame of the pilot burner.
- the burner assembly delivers power.
- This power output can e.g. B. a power for a boiler or a Power to drive a turbine.
- High output are achieved by operating the main burners, the pilot burner primarily used to stabilize the Combustion of the main burner are responsible. At low The pilot burner can also only supply power work as a diffusion burner.
- Such a burner arrangement can come to the formation of a combustion vibration.
- the Invention is based on the knowledge that a static Supply of a different amount of fuel to the Burners to suppress combustion vibrations not over the entire range of possible output, also called load, the burner arrangement can be carried out.
- the pilot burner must have a lower output to be supplied with a high amount of fuel to ignite the lean fuel mixture of the main burner stably.
- pilot fuel quantities supplied depend on the output the burner arrangement can be adjusted a detuning of the burners to each other, adapted to the respective operating status.
- the supply of different pilot fuel quantities is designed for stabilization the minimum amount of pilot fuel required for combustion.
- the burner arrangement is thus stable on the one hand at low temperatures Loads can be operated and, on the other hand, combustion vibrations by supplying different amounts of pilot fuel to at least two of the pilot burners by means of this caused different delay times of the pilot burner effectively suppressable.
- the difference in the pilot fuel quantity preferably increases with increasing output. This increases the output power a bigger difference in the amount of pilot fuel adjustable without affecting the stability of the combustion. Since it is just at higher output rates too disturbing combustion vibrations, here is an operation the pilot burner with different pilot fuel quantities regarding the suppression of combustion vibrations particularly advantageous.
- a large part is preferred at maximum load of the gas turbine the hybrid burner with one to two percent of a maximum Pilot fuel amount and the rest of the hybrid burners at five operated up to 15 percent of the maximum pilot fuel quantity.
- a gas turbine with an annular combustion chamber This can be a stationary gas turbine or an aircraft engine.
- the object is directed to a gas turbine solved by a gas turbine with a plurality of hybrid burners in a combustion chamber, each hybrid burner has a pilot burner and a main burner and wherein a pilot fuel quantity can be supplied to each pilot burner, a control unit for load-dependent control of the feed at least different amounts of pilot fuel two of the pilot burners are provided.
- FIG. 1 shows a gas turbine directed along an axis 3 1.
- axis 3 are arranged one behind the other Compressor 5, an annular combustion chamber 7 and a turbine 9.
- annular combustion chamber 7 Along a circumference of the annular combustion chamber 7 are a large number arranged by hybrid burners 11.
- hybrid burners 11 For each hybrid burner 11 leads a fuel supply line 13 for pilot fuel.
- a control unit is part of the fuel supply lines 13 15 switched.
- the control unit 15 could also be used in all of the Fuel supply lines 13 may be switched.
- To the control unit 15 also carries a signal line 17.
- the gas turbine 1 can with different output powers or loads are operated.
- Via the signal line 17 a signal is fed to the control unit 15, which is the size of a current output power of the Gas turbine 1 reproduces.
- the control unit 15 does not necessarily need to go directly to the fuel supply lines 13 to be connected. You could also use valves control which is arranged in the fuel supply lines 13 are.
- the control unit 15 makes at least two the hybrid burner 11 a different amount of pilot fuel delivered. Because of this different amount of pilot fuel 11 different results for these hybrid burners Delays.
- the delay times indicate a phase difference between an acoustic Vibration in the combustion chamber 7 and a vibration one thermal power release on the respective hybrid burner 11. Due to the different delay times these phases are changed so that combustion vibrations, which emanate from the individual hybrid burners 11, weaken each other, or at least not each other strengthen. This will suppress training a combustion vibration reached.
- a hybrid burner is shown schematically in a longitudinal section in FIG 11 shown.
- the hybrid burner 11 has a central one Pilot burner 21 on.
- the pilot burner 21 is about a fuel supply line 13 a pilot fuel amount 23 and combustion air 24 is supplied via an air duct 22.
- the pilot burner 21 is concentric of an annular channel Main burner 25 surround. In this is a premixed Fuel air flow 27 performed, which is on a Pilot flame 29 of the pilot burner 21 ignites.
- a control unit 15 is connected in the fuel supply line 13, . This controls depending on a signal from a signal line 17 the amount of pilot fuel supplied in the fuel supply line 13 23. This regulation depends on the output of a service not shown here Gas turbine in which the hybrid burner 11 is installed.
- a small part of the hybrid burners is compared with one the remaining hybrid burners 11 increased amount of pilot fuel operated. This causes efficient suppression of 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)
Description
Claims (6)
- Verfahren zum Betrieb einer Gasturbine (1) mit einer Mehrzahl von Hybridbrennern (11) in einer Brennkammer, wobei jeder Hybridbrenner (11) einen Pilotbrenner (21) und einen Hauptbrenner (25) aufweist und wobei jedem Pilotbrenner (21) eine Pilotbrennstoffmenge (23) zugeleitet wird,
dadurch gekennzeichnet, daß mindestens zwei der Pilotbrenner (21) mit einer unterschiedlichen Pilotbrennstoffmenge (23) betrieben werden, wobei der Unterschied in der Pilotbrennstoffmenge (23) abhängig von der Last der Gasturbine (1) eingestellt wird. - Verfahren nach Anspruch 1,
dadurch gekennzeichnet, daß der Unterschied in der Pilotbrennstoffmenge (23) mit steigender Last ansteigt. - Verfahren nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß bei Maximallast der Gasturbine (1) ein Großteil der Hybridbrenner (11) mit ein bis zwei Prozent einer maximalen Pilotbrennstoffmenge (23) und der Rest der Hybridbrenner (11) mit fünf bis 15 Prozent der maximalen Pilotbrennstoffmenge (23) betrieben werden. - Verfahren nach einem der vorhergehenden Ansprüche,
dadurch gekennzeichnet, daß bei Lasten oberhalb von XX% der Maximallast der Gasturbine (1) eine erste Anzahl der Hybridbrenner (11) mit einer ersten Pilotbrennstoffmenge (23) und eine zweite Anzahl der Hybridbrenner (11) mit einer zweiten Pilotbrennstoffmenge (23) betrieben werden, wobei die erste Anzahl mehr als XX-mal so groß wie die zweite Anzahl und die zweite Pilotbrennstoffmenge (23) mehr als XX-mal so groß wie die erste Pilotbrennstoffmenge (23) ist. - Verfahren nach einem der vorhergehenden Ansprüche, bei dem die Gasturbine (1) eine Ringbrennkammer (7) aufweist.
- Gasturbine (1) mit einer Mehrzahl von Hybridbrennern (11) in einer Brennkammer (7), wobei jeder Hybridbrenner (11) einen Pilotbrenner (21) und einen Hauptbrenner (25) aufweist und wobei jedem Pilotbrenner (21) eine Pilotbrennstoffmenge (23) zuleitbar ist,
dadurch gekennzeichnet, daß eine Steuereinheit (15) zur lastabhängigen Steuerung der Zufuhr unterschiedlich großer Pilotbrennstoffmengen (23) zu mindestens zwei der Pilotbrenner (21) vorgesehen ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19839626 | 1998-08-31 | ||
DE19839626 | 1998-08-31 | ||
PCT/DE1999/002531 WO2000012940A1 (de) | 1998-08-31 | 1999-08-13 | Verfahren zum betrieb einer gasturbine und gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1112462A1 EP1112462A1 (de) | 2001-07-04 |
EP1112462B1 true EP1112462B1 (de) | 2003-06-18 |
Family
ID=7879310
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99952383A Expired - Lifetime EP1112462B1 (de) | 1998-08-31 | 1999-08-13 | Verfahren zum betrieb einer gasturbine und gasturbine |
Country Status (5)
Country | Link |
---|---|
US (1) | US6425239B2 (de) |
EP (1) | EP1112462B1 (de) |
JP (1) | JP4339519B2 (de) |
DE (1) | DE59906025D1 (de) |
WO (1) | WO2000012940A1 (de) |
Families Citing this family (14)
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 |
WO1999056060A1 (de) * | 1998-04-23 | 1999-11-04 | Siemens Aktiengesellschaft | Brennkammeranordnung |
SE521293C2 (sv) * | 2001-02-06 | 2003-10-21 | Volvo Aero Corp | Förfarande och anordning för tillförsel av bränsle till en brännkammare |
DE60217768T2 (de) * | 2001-07-18 | 2007-11-15 | Rolls-Royce Plc | Kraftstofffördervorrichtung |
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 (de) * | 2010-08-27 | 2012-02-29 | Siemens Aktiengesellschaft | Brenneranordnung |
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 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
-
1999
- 1999-08-13 EP EP99952383A patent/EP1112462B1/de not_active Expired - Lifetime
- 1999-08-13 WO PCT/DE1999/002531 patent/WO2000012940A1/de active IP Right Grant
- 1999-08-13 JP JP2000567887A patent/JP4339519B2/ja not_active Expired - Fee Related
- 1999-08-13 DE DE59906025T patent/DE59906025D1/de not_active Expired - Lifetime
-
2001
- 2001-02-28 US US09/795,097 patent/US6425239B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US20010020358A1 (en) | 2001-09-13 |
WO2000012940A1 (de) | 2000-03-09 |
US6425239B2 (en) | 2002-07-30 |
JP4339519B2 (ja) | 2009-10-07 |
JP2002523685A (ja) | 2002-07-30 |
EP1112462A1 (de) | 2001-07-04 |
DE59906025D1 (de) | 2003-07-24 |
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