EP2627883A1 - Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante - Google Patents

Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante

Info

Publication number
EP2627883A1
EP2627883A1 EP11781771.8A EP11781771A EP2627883A1 EP 2627883 A1 EP2627883 A1 EP 2627883A1 EP 11781771 A EP11781771 A EP 11781771A EP 2627883 A1 EP2627883 A1 EP 2627883A1
Authority
EP
European Patent Office
Prior art keywords
gas turbine
gas
combustion chamber
air
fuel
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Withdrawn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
EP11781771.8A
Other languages
German (de)
English (en)
Inventor
Holger Hesse
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
Priority to EP11781771.8A priority Critical patent/EP2627883A1/fr
Publication of EP2627883A1 publication Critical patent/EP2627883A1/fr
Withdrawn legal-status Critical Current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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • 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
    • 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
    • F02C9/46—Emergency fuel control
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F05D2270/021—Purpose of the control system to control rotational speed (n) to prevent overspeed
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/091—Purpose of the control system to cope with emergencies in particular sudden load loss
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/092—Purpose of the control system to cope with emergencies in particular blow-out and relight

Definitions

  • the invention relates to a method for operating a gas turbine during load shedding and / or during quick closing with the steps: operating the gas turbine by burning fuel in at least one combustion chamber of the gas turbine with the addition of combustion air.
  • the inven ⁇ tion relates to a device for controlling the operation of a gas turbine, with which a method for operating a gas turbine during load shedding and / or quick closure is feasible and a power plant comprising a gas turbine with at least ⁇ at least one combustion chamber and a compressor wherein the combustion chamber from the compressor provided combustion air and fuel can be fed.
  • the stationary gas turbines usually drive an electric generator, which feeds the electrical energy generated by it into a power distribution network.
  • the shaft train of the power plant which includes the genera ⁇ torrotor and the gas turbine rotor rotates duringdes ⁇ sen with the grid frequency of the electrical power distribution network: at 50 Hz mains frequency with a speed of 3000 min -1 and 60 Hz mains frequency with a speed of 3600 min - 1 .
  • the speed is imposed on the shaft train from the mains frequency due to the mostly synchronous generators.
  • the load decelerating the gas turbine rotor falls away.
  • the speed of the Wel ⁇ lenstrangs is no longer specified by the grid frequency.
  • Admission of the aforementioned case which is also known as load shedding, so far the fuel valves have been closed to an extent necessary for idling operation. If a multi-stage burner system is present, all burner stages, with the exception of those necessary for idling operation, switched off and their fuel valves are closed.
  • Due to the self-adjusting in the gas turbine Druckgeponent ⁇ les concluded between the Brennstoffventi ⁇ len and the fuel nozzles escapes into the fuel line verblie ⁇ bene proportion of fuel into the combustion chamber. In the combustion chamber, this fuel fraction supports the combustion that is still taking place, as a result of which the rotor is still driven in the turbine unit. This accelerates the rotor of the gas turbine or the shaft train, so that the speed increases sharply and rises to a so-called overspeed. Since ⁇ falls after the speed again and the gas turbine is operated at idle.
  • a similar method is known in the case of the quick closure.
  • a quick-closing is usually triggered in the case of a Be ⁇ dysfunction of the gas turbine or power plant. Again, the generator is disconnected from the power distribution network. In addition, however, all fuel valves are closed and the combustion stopped as quickly as possible. In this case too, the fuel which relaxes from the lines between fuel valves and burner nozzles still ensures a short speed acceleration of the gas turbine. Thereafter, however, the rotor runs out and is held only at ge ⁇ ringer speed of a few hundred revolutions per minute in the so-called turn-operation to ab ⁇ cool the gas turbine.
  • US Pat. No. 5,680,753 proposes to temporarily set the fuel quantity of premix burners during load shedding by means of a control valve and a bypass valve connected in parallel thereto .
  • US 5,896,736 proposes to change the ratio of the fuel-air mixture in the short term.
  • a correction signal for the position of the Ver Whyreinlassleitschaufein is generated during the load shedding, by which they continue to turn for a predetermined period of time.
  • a small amount of compressor air flows into the burner, whereby the fuel-air mixture is enriched.
  • WO 99/54610 Al discloses the purging of fuel lines and burner stages of a gas turbine with air after a load shedding. Accordingly, the still present in the lines of fuel with increased pressure in the combustion ⁇ chamber is fed. This leads to an undesirable Extend the previous combustion process with a correspondingly increased overspeed.
  • gas turbines also see polykalori- fuels, such as syngas fired who can ⁇ .
  • Such gas turbines have - compared to gas turbines with identical rated power, which are operated with high calorific fuel, much larger wire cross-sections for the fuel lines in order to provide the appropriate amount of energy as well.
  • the object of the invention is therefore to provide a method for operating a gas turbine during load shedding and / or quick closing, with which the smallest possible over ⁇ speed and / or a low speed acceleration can be realized Siert.
  • Another object of the invention is the Be ⁇ provision of a device for controlling the operation of a gas turbine, with which the overspeed of the gas turbine can be reduced in load shedding and quick closure.
  • Another object of the invention is to provide a power station, in which also the disadvantages mentioned safely ver ⁇ avoided.
  • the object relating to the method object is achieved with a ⁇ Ver drive for operating a gas turbine during load disconnection and quick-dissolved, which according to the features of the
  • Patent claim 1 is configured.
  • the solution of the object directed to the device comprising the features of at ⁇ entitlement 7.
  • the object relating to a power plant object is achieved with such according to the features of claim 9.
  • the invention is based on the finding that the acceleration of the rotor speed and the overspeed also depend on the Pressure level in the combustion chamber and its time course are dependent.
  • additional refers to the amount of fuel and the amount of combustion air, which would otherwise be fed into the combustion chamber of the gas turbine after load shedding or rapid closure - without appropriate action.
  • the maximum overspeed is limited at load shedding or quick closing, with the result that the rotating components undergo a lower mechanical load and also a low centrifugal load.
  • This extends the life of the rotating components and protects the compo ⁇ nents from damage.
  • gas volume Compressed air used.
  • other media such as nitrogen or the like to maintain a higher pressure in the combustion chamber after the load shedding or rapid closure are fed.
  • the gas volume can be removed from a correspondingly dimensioned gas storage tank or gas tank.
  • gas turbines which are designed for operation with low calorific fuel and having a so-called Heilentsleyleitun
  • the gas volume of this air extraction line can be removed.
  • Such gas turbines usually have an air extraction line when compressed air is needed for the production of low calorific fuel.
  • the amount of air taken represents a significant proportion of the total compressor mass flow.
  • the compressed air is supplied to an air separation plant. Part of the decomposed air is then used to produce the low calorific fuel. Since the usual way such air extraction lines are relatively long - usually 100m and longer - they have a corre sponding volume.
  • the air bleed pipe in operation continuously fed Ver compressor air input side and the output side is ent ⁇ taken, it can be considered also as a reservoir for a volume of gas and used.
  • a comparatively large amount of air ⁇ stored in the air extraction line which is then not supplied to the Luftzerlegungsstrom in the case of load shedding or fast conclusion. Rather, then present therein air entgege their previous flow direction back to gas turbine compressor and then on to the combustion chamber In order to supply these as additional gas volume of the combustion chamber this is only necessary that the existing in the air extraction line existing valve remains open at load shedding and quick closing.
  • the method may preferably be performed at power plants where a gas turbine in operation drives an electrical generator connected to a power distribution network and wherein the load shedding is by a sudden reduction of the electric power to be supplied by the generator or by disconnecting the generator from the power distribution network he follows.
  • inventive method can advantageously be used even when the Lastab ⁇ litter or quick-closing occurs unexpectedly or is only simulated.
  • the latter is required, for example in the commissioning ⁇ drive reduction newly created gas turbine systems where the intended operation of the gas turbine must be demonstrated to the operator.
  • the device according to the invention comprises an input with which a signal representing the load state of the gas turbine or a signal representing the coupling state of the generator and the power distribution network can be fed.
  • the device comprises an output whose signal controls an actuator by means of which a combustion chamber of the gas turbine in the normal operation of the gas turbine is not provided for supplying into the combustion chamber gas volume can be supplied, wherein a unit is provided which theönsig ⁇ nal depending on Input signal controls, preferably according to the methods described above.
  • the power plant according to the invention comprises a gas turbine with at least one combustion chamber and a compressor, wherein the combustion chamber provided by the compressor combustion air and fuel can be fed.
  • Power plant also has a space filled with a gas volume, and means are provided with which in load shedding and / or quick closing the gas volume in addition to
  • FIG 1 Shown schematically are a power plant with some components of a gas turbine and a generator coupled thereto; a time-pressure diagram of the pressure in a Brennkam mer the gas turbine; a time-rotation diagram of the gas turbine rotor; an alternative to FIG 1 embodiment of the inventions ⁇ to the invention power plant in a schematic representation
  • a power plant 10 is shown in a schematic representation.
  • the power plant 10 comprises a gas turbine 12 and a generator 14 coupled thereto. In operation, the latter feeds the electrical energy generated by it into a power distribution network 15 during operation.
  • the power plant 10 may further include a steam turbine.
  • the coupling of the generator 14 with the gas turbine 12 or the steam turbine ⁇ he is known to follow the connection of the gas turbine rotor 16 and possibly the steam turbine rotor with the rotor 18 of the generator 14 to a shaft train.
  • components of the gas turbine 12 shown here are the compressor 20, the combustion chamber 22 and the turbine unit 24.
  • the Brennkam- mer 22 may be configured on the one hand as an annular combustion chamber.
  • the combustion chamber 22 may also include a plurality of combustion chambers, which are known as tube combustion chambers.
  • the gas turbine 12 shown in FIG. 1 is equipped for operation with a low-calorie fuel F, for example synthesis gas or the like, which can be fed to the combustion chamber 22 via a corresponding fuel line 26 and main burner connected thereto.
  • a fuel valve 27 is arranged, which shuts off the supply of fuel F in the combustion chamber 22 via the main burner at load shedding. If the gas turbine 12 is also equipped with pilot burners, they will continue to be supplied with fuel even during load shedding.
  • the compressor 20 is designed and dimensioned such that it draws in during operation much more ambient air U and compresses than the amount required for the combustion of the supplied fuel F ⁇ .
  • the gas turbine 12 includes a Lucasent ⁇ acquisition line 28, taken out through the compressor end and a larger amount of, for example, to a non Darge ⁇ introduced air separation plant can be forwarded.
  • the removal of Verêtrend Kunststoff for Heilzerlegungsstrom can be controlled via a valve 30, which übli ⁇ cher way in the immediate vicinity of the compressor housing is seen before ⁇ .
  • the valve 30 is arranged in the air extraction line 28 on the input side.
  • Air passages introduced into the combustion chamber 22 The addition of fuel into the combustion chamber 22 via
  • Power distribution network 15 feeds.
  • FIG. 3 the rotational speed of the gas turbine rotor 16 and the generator rotor 18 rigidly coupled thereto are shown, wherein the rotational speed n0 is predetermined by the grid frequency of the power distribution network 15 until the time t0.
  • a load rejection a for example, by an unplanned separation of the generator 14 from the power ⁇ distribution network 15. Because of the loss of contact of the genes ⁇ rators 14 to the power distribution network 15, the speed of the rotors 16, 18 are no longer on the mains frequency of the power distribution network 15 predetermined. Likewise, the braking effect that produced the electrically interrogated power so far falls away.
  • the pressure in the combustion chamber dropped relatively quickly after load shedding.
  • the previous course of the combustion chamber pressure p is shown schematically in FIG. 2 with a dashed line type as a characteristic curve 42. As a result, set a speed curve, as shown in FIG 3 in the dashed line shown characteristic 40.
  • the speed of the rotors increased with a large gradient - that is comparatively fast - up to a maximum overspeed nl and then decreased with a comparably large, but signed gradient after a short undershoot on the target speed nO again.
  • Combustion chamber 22 flows.
  • the air extraction line 28 thus serves as a gas storage. Due to the provision of the additional volume of gas from the air extraction conduit 28 and the delivery of the volume of gas stored therein into the combustion chamber 22, the pressure drop in the combustion chamber 22 can be retarded compared to the prior art. This is shown in FIG.
  • the solid line curve 44 shown therein shows that in its drop
  • combustion chamber 22 shown schematically in FIGS. 1 and 4 is now equipped as an annular combustion chamber or as a so-called tube combustion chamber, of which the gas turbine can have, for example, two or substantially more.
  • the solution shown in FIG. 4 is also particularly suitable for stationary gas turbines which are to be operated for operation with high or higher calorific fuel since, as a rule, such gas turbines 12 have no significant removal of compressor air, apart from that in the turbine unit and in the combustion chamber used cooling and
  • the compressor 20 illustrated in FIG. 4 is suitably dimensioned for the thermal power output provided in the turbine unit 24.
  • Both embodiments each comprise a device 34 for regulating the operation of the gas turbine 12.
  • the device 34 comprises at least one input E, which represents a signal representing the load state of the gas turbine 12 or the coupling state of generator 14 and power distribution network 15 representing signal can be fed. Further, the device 34 comprises an output 38 whose signal controls an actuator, that is, the valve 30, with the help of the
  • Combustion chamber 22 of the gas turbine 12 a in the operation of Gastur- bine 12 not provided for supplying into the combustion chamber 22 gas volume can be fed.
  • FIGS. 1 and 4 merely serve to explain the invention and are not restrictive of it. So can in particular several
  • Combustion chambers 22 may be provided, each comprising a pilot burner and a main burner, each having one or more stages.
  • the description of the invention is given by way of example with gaseous fuel. However, the use of gaseous fuel is not mandatory.
  • the invention relates to a method for limiting an overspeed of a gas turbine 12 during load shedding comprising the steps of: operating the gas turbine 12 by combusting fuel F in a combustion chamber 22 of the gas turbine 12 and adding combustion air. Furthermore, the invention relates to a device 34 for controlling such an operation and a power plant 10 with a gas turbine 12 and a generator 14. In order to further reduce the maximum overspeed of the gas turbine rotor 16 during load shedding, it is proposed that with or immediately after the load shedding of the combustion chamber 22 additionally a gas volume is supplied, in addition to the otherwise supplied combustion air of the otherwise supplied fuel stream.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Control Of Eletrric Generators (AREA)

Abstract

L'invention concerne un procédé pour limiter la survitesse d'une turbine à gaz (12) en cas de délestage brusque, ledit procédé comprenant les étapes suivantes: faire fonctionner la turbine à gaz (12) par combustion de combustible (F) dans une chambre de combustion (22) de la turbine à gaz (12) et apport d'air de combustion. L'invention concerne en outre un dispositif (34) pour réguler un tel mode de fonctionnement, ainsi qu'une centrale (10) équipée d'une turbine à gaz (12) et d'un générateur (14). L'invention vise à réduire davantage encore la survitesse maximale du rotor (16) de turbine à gaz, en cas de délestage brusque ou d'arrêt d'urgence. A cet effet, un volume de gaz est acheminé jusqu'à la chambre de combustion (22), simultanément au délestage brusque ou immédiatement après, en complément de l'air de combustion du flux de combustible, acheminés l'un et l'autre par ailleurs.
EP11781771.8A 2010-11-30 2011-10-31 Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante Withdrawn EP2627883A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11781771.8A EP2627883A1 (fr) 2010-11-30 2011-10-31 Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10193132A EP2458180A1 (fr) 2010-11-30 2010-11-30 Procédé de fonctionnement d'une turbine à gaz lors de la régulation de la charge, dispositif de réglage du fonctionnement d'une turbine à gaz et centrale
PCT/EP2011/069099 WO2012072352A1 (fr) 2010-11-30 2011-10-31 Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante
EP11781771.8A EP2627883A1 (fr) 2010-11-30 2011-10-31 Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante

Publications (1)

Publication Number Publication Date
EP2627883A1 true EP2627883A1 (fr) 2013-08-21

Family

ID=43920990

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10193132A Withdrawn EP2458180A1 (fr) 2010-11-30 2010-11-30 Procédé de fonctionnement d'une turbine à gaz lors de la régulation de la charge, dispositif de réglage du fonctionnement d'une turbine à gaz et centrale
EP11781771.8A Withdrawn EP2627883A1 (fr) 2010-11-30 2011-10-31 Procédé de fonctionnement d'une turbine à gaz en cas de délestage brusque, dispositif de régulation du fonctionnement d'une turbine à gaz et centrale correspondante

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10193132A Withdrawn EP2458180A1 (fr) 2010-11-30 2010-11-30 Procédé de fonctionnement d'une turbine à gaz lors de la régulation de la charge, dispositif de réglage du fonctionnement d'une turbine à gaz et centrale

Country Status (6)

Country Link
US (1) US20140060066A1 (fr)
EP (2) EP2458180A1 (fr)
JP (1) JP5746361B2 (fr)
CN (1) CN103339359B (fr)
RU (1) RU2013129764A (fr)
WO (1) WO2012072352A1 (fr)

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CN103339359A (zh) 2013-10-02
JP2013544336A (ja) 2013-12-12
CN103339359B (zh) 2016-02-03
US20140060066A1 (en) 2014-03-06
WO2012072352A1 (fr) 2012-06-07
EP2458180A1 (fr) 2012-05-30
JP5746361B2 (ja) 2015-07-08
RU2013129764A (ru) 2015-01-10

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