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WO2003067055A1 - Procédé pour faire fonctionner une turbine à gaz comportant plusieurs brûleurs - Google Patents

Procédé pour faire fonctionner une turbine à gaz comportant plusieurs brûleurs Download PDF

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Publication number
WO2003067055A1
WO2003067055A1 PCT/CH2003/000067 CH0300067W WO03067055A1 WO 2003067055 A1 WO2003067055 A1 WO 2003067055A1 CH 0300067 W CH0300067 W CH 0300067W WO 03067055 A1 WO03067055 A1 WO 03067055A1
Authority
WO
WIPO (PCT)
Prior art keywords
gas turbine
combustion chamber
burners
operating
temperature
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/CH2003/000067
Other languages
German (de)
English (en)
Inventor
Peter Keller-Sornig
Ilja Tuschy
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.)
General Electric Switzerland GmbH
GE Vernova GmbH
Original Assignee
Alstom Technology AG
Alstom Schweiz 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 Alstom Technology AG, Alstom Schweiz AG filed Critical Alstom Technology AG
Publication of WO2003067055A1 publication Critical patent/WO2003067055A1/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
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/14—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
    • F02C6/16—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads for storing compressed air
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/26—Control of fuel supply
    • 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
    • F02C9/32—Control of fuel supply characterised by throttling of fuel
    • F02C9/34—Joint control of separate flows to main and auxiliary burners
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/16—Mechanical energy storage, e.g. flywheels or pressurised fluids

Definitions

  • the present invention relates to a method for operating gas turbines, such as in conventional gas turbine power plants or a compressed air energy storage system (CAES system), and in particular to a method for operating gas turbines with multiple burners.
  • CAES system compressed air energy storage system
  • FIG. 1 the layout of an example of a compressed air energy storage system (CAES system) is shown schematically. It contains a cavern 1 for storing compressed air, which is used to generate electricity particularly in times of high demand.
  • the control of a valve arrangement 9 supplies the compressed air to a waste heat processor 2, where it is heated by heat transfer from the gas turbine exhaust gas.
  • Another valve arrangement 8 regulates the compressed air supply to an air turbine 3.
  • a combustion chamber 4 and a gas turbine 5 are arranged behind the air turbine 3.
  • An auxiliary burner 6 is arranged behind the gas turbine 5 and in front of the waste heat processor 2.
  • the gas turbine combustion chamber 4 has several burners.
  • the gas turbine 5 is operated with different combustion chamber heat loads, the number of active burners changes.
  • Automatic activation or deactivation of individual burners or burner groups by means of gas turbine control requires one or more criteria for determining the switching point for the burners.
  • This criterion can be the gas turbine load, for example.
  • the combustion process can be characterized by the equivalence ratio ⁇ , which is given by the ratio of the fuel mass flow to the oxidizing agent - mass flow, the oxidizing agent generally being air. This is expressed by Equation 1:
  • Lant Lant ⁇ fuel m oxide.
  • the factor Lant (abbreviation for air fraction, since the oxidant is usually air) is the ratio of oxidant mass flow to fuel mass flow for stoichiometric combustion, i.e. H. for a complete chemical reaction in which there are no oxidant or fuel residues in the exhaust gas.
  • the equivalence ratio ⁇ can have any value between zero and infinity.
  • the area is limited by the
  • the combustion emissions, especially NOx, are strongly related to the flame temperature.
  • the value ⁇ B ⁇ together with the combustion chamber air inlet temperature and the fuel temperature determine the ignition temperature of the combustion chamber.
  • the gas turbine air mass flow, the combustion chamber air mass flow and the air supply to a single burner are determined in part by the design geometry of the gas turbine.
  • the gas turbine fuel mass flow is equal to the combustor fuel flow.
  • the ratio of the fuel flow of a single burner to the combustion chamber fuel mass flow is of the number n and
  • Burner technology is preferably one
  • the burners of the combustion chamber are individually switched on and off or are arranged in separately switchable burner groups. To achieve a stable combustion process and low emissions, the number of single burners or burner groups in operation is varied over the operating range.
  • the combustion chamber heat load increases (given by the product of the combustion chamber air mass flow and the temperature difference between the combustion chamber air inlet temperature and the combustion chamber exhaust gas outlet temperature).
  • the total fuel mass flow into the combustion chamber increases with the heat load.
  • combustion chamber equivalence ratio ⁇ B ⁇ increases with the temperature difference between the combustion chamber air inlet temperature and the combustion chamber exhaust gas outlet temperature. In combustion chamber operation can be increased
  • Heat load can basically be responded to in three ways. More fuel is supplied during the
  • Number of active burners is either reduced, remains the same, or is increased.
  • Combustion chamber equivalence ratio ⁇ BK leads to a constant or even reduced number of burners leading to a higher burner equivalence ratio ⁇ EB . Therefore, if there is no increase in the number of burners to compensate for the increased ⁇ B ⁇ , there is an increase in emissions and the individual burner heat load. However, even if the ⁇ BK remains unchanged, the higher heat load can lead to burner operation being closer to the lean fire extinguishing limit. Thus, when the gas turbine load increases, the connection of further individual burners can be advantageous in order to reduce the emissions and the thermal load of the individual burners. A reduced individual burner heat load in turn causes a reduction in the thermal load on the individual burners.
  • FIG. 2 shows various gas turbine temperatures which are of interest for the operation of a gas turbine and its combustion chamber.
  • This contains the temperature of the premixed flame at position 1.
  • the combustion gases are cooled by air that flows past the main reaction zone and re-enters the combustion chamber at position 2.
  • the so-called "ignition temperature” is defined as the temperature immediately before the first row of guide vanes of the turbine at position 3.
  • This temperature and the temperature before the first row of rotor blades at position 4 are limited with regard to the guide and rotor blade material.
  • both the vanes also be cooled as the rotor blades usually with air 'or steam.
  • the temperature that changes when mixed of all cooling media with the combustion chamber exhaust gases is defined as the gas turbine inlet mixture temperature T G ⁇ TET . This temperature cannot be measured, but can be determined by calculation.
  • the equivalence ratio is a suitable criterion for determining the burner switching processes.
  • the equivalence ratio according to equation 1 is a normalized ratio of fuel and oxidant mass flow. To be able to use this ratio as a switching criterion, however, the fuel and oxidant mass flows of the burners must be known.
  • the mass flow and the temperature at the compressor outlet vary depending on the ambient conditions, whereby the ambient temperature and the ambient pressure are the most important factors; the mass flow and the temperature at the compressor outlet can change over time due to aging and contamination of the compressor.
  • the invention has for its object to provide a method for operating a gas turbine, in which the burner switching points are determined by a criterion that avoids the disadvantages described in connection with the prior art.
  • the invention relates to a method for operating a gas turbine which is arranged in a power generation system and has a compressed air source, a gasification burner with a combustion chamber and a plurality of burners.
  • a gas turbine control controls the activation and deactivation of the burners according to a switching point criterion that is proportional to the difference between the compressed air temperature upstream of the combustion chamber and the exhaust gas temperature downstream of the combustion chamber.
  • the compressed air temperature in front of the combustion chamber is preferably immediately before entering the Combustion chamber detected. If the power generation system is a compressed air energy storage system, this temperature can also be the temperature at a point in front of the air turbine or even before the waste heat processor.
  • the exhaust gas temperature behind the combustion chamber is the exhaust gas temperature at some point past the point where the chemical reaction has ended.
  • the temperature behind the combustion chamber is the gas turbine inlet mixture temperature, which is a virtual temperature calculated from a mixture of exhaust gases and cooling media. These cooling media are supplied to one or more of the following: burner, combustion chamber and gas turbine.
  • the temperature difference for the switching criterion can then be designated K s and means the difference between the gas turbine inlet mixture temperature and the combustion chamber inlet temperature of the compressed air, expressed by the following equation 7:
  • This temperature difference K s is physically related to various equivalence ratios of the combustion process. For example, it is proportional to the equivalence ratio ⁇ BK in the combustion chamber, that is to say to the ratio of the fuel mass flow to the air mass flow through the combustion chamber according to equation 8:
  • Air mass flow can be measured with high accuracy, the switching criterion according to the invention is advantageous.
  • the criterion is therefore fully applicable to CAES power plants, as shown in FIG. 1, to which air is fed from cavern 1 and where an exact measurement of the air mass flow to the combustion chamber is possible.
  • CAES power plant as outlined in Figure 1, changes in temperature at the compressor outlet is equivalent to changes in the air turbine exit temperature. These can possibly occur if the air turbine inlet temperature has changed due to fluctuations in the shaft burner output.
  • the switching criterion according to the invention can be applied to the activation and deactivation of individual burners and groups of individual burners.
  • the burners are activated and deactivated in order to modify and regulate the heat load of the burners. This enables, for example, a limitation of the thermal load in relation to the lean fire extinguishing limit or the permissible emission values.
  • Figure 1 shows a typical CAES power plant design
  • FIG. 3 shows a graph of a single burner equivalence ratio for a CAES gas turbine, in which the number of activated burners is determined according to the relative load criterion;
  • FIG. 4 shows a graph similar to that in FIG. 3, but in which the number of activated burners is determined according to the switching criterion according to the invention
  • Figure 5 is a graph of a single burner equivalence ratio for a CAES gas turbine, in which the number of activated burners is determined according to the relative load criterion, and for the special case that the combustion chamber air inlet temperature fluctuates over a range of + 50 ° C;
  • FIG. 6 shows a graph similar to that in FIG. 5, but in which the burners are activated using the switching criterion according to the invention.
  • FIGS. 3 and 4 The improved method for operating a CAES gas turbine is illustrated in FIGS. 3 and 4, in which the fluctuations in the single burner equivalence ratio ⁇ EB or Phi are shown, the number of activated burners being determined by a switching criterion corresponding to the relative load or by switching criterion according to the invention is determined.
  • FIGS. 3 and 4 show that by using the switching criterion according to the invention, the spread of the burner equivalence ratio ⁇ EB or Phi is significantly smaller over the entire load range. Reducing the ratio spread has the following advantages:
  • FIG. 6 shows the fluctuations in the single burner equivalence ratio for the same large fluctuations in the combustion chamber air inlet temperature by ⁇ 50 ° C., but for a CAES gas turbine which is operated with the switching criterion according to the invention. Since the switching criterion according to the invention takes full account of temperature fluctuations, even large fluctuations, these temperature deviations only cause relatively small changes in the individual burner equivalence ratio Phi. As a result, the combustion chamber imposes fewer restrictions on power plant operation, so that overall there is greater operational flexibility for the power plant. drawing Legend

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un procédé pour faire fonctionner une turbine à gaz, disposée dans un système de génération de d'électricité et dotée d'une source d'air comprimé et d'un brûleur à gazéification avec chambre de combustion et plusieurs brûleurs. Une régulation de la turbine à gaz active et désactive chaque brûleur individuel et/ou des groupes de brûleurs selon un critère de commutation proportionnel à la différence existant entre la température de l'air à l'aspiration de la chambre de combustion et la température derrière la chambre de combustion. Le critère de commutation selon l'invention tient systématiquement compte de grandes variations de températures de l'air d'aspiration de la chambre de combustion, lesquelles ne provoquent que des modifications relativement faibles du rapport d'équivalence des brûleurs. La présente invention est particulièrement adaptée à une utilisation dans des centrales électriques à air comprimé à accumulation d'énergie.
PCT/CH2003/000067 2002-02-04 2003-01-28 Procédé pour faire fonctionner une turbine à gaz comportant plusieurs brûleurs Ceased WO2003067055A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US35319602P 2002-02-04 2002-02-04
US60/353,196 2002-02-04
CH15932002 2002-09-20
CH1593/02 2002-09-20

Publications (1)

Publication Number Publication Date
WO2003067055A1 true WO2003067055A1 (fr) 2003-08-14

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH2003/000067 Ceased WO2003067055A1 (fr) 2002-02-04 2003-01-28 Procédé pour faire fonctionner une turbine à gaz comportant plusieurs brûleurs

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Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE888335C (de) * 1941-05-16 1953-08-31 Aeg Einrichtung zur Leistungsregelung von Gleichdruckgasturbinenanlagen
DE2136184A1 (de) * 1971-07-20 1973-01-25 Kraftwerk Union Ag Gasturbinenanlage
GB1388404A (en) * 1971-06-18 1975-03-26 Rolls Royce Fuel control system for a gas turbine engine
US4058975A (en) * 1975-12-08 1977-11-22 General Electric Company Gas turbine temperature sensor validation apparatus and method
US4455820A (en) * 1976-09-09 1984-06-26 General Electric Company Control system and method for controlling a gas turbine in accordance with the temperature conditions thereof
US4735052A (en) * 1985-09-30 1988-04-05 Kabushiki Kaisha Toshiba Gas turbine apparatus
US5319931A (en) * 1992-12-30 1994-06-14 General Electric Company Fuel trim method for a multiple chamber gas turbine combustion system
US5533329A (en) * 1993-05-17 1996-07-09 Hitachi, Ltd. Control apparatus for and control method of gas turbine
GB2323428A (en) * 1997-03-18 1998-09-23 Vosper Thornycroft Controls Li Valve arrangement to control flow to burners
DE19825335A1 (de) * 1998-06-05 1999-12-09 Abb Patent Gmbh Verfahren zum Betrieb einer Gasturbine
EP1077349A1 (fr) * 1999-08-19 2001-02-21 General Electric Company Appareil à injection étagée de carburant et procédé pour injecteurs de turbines à gaz
US6247300B1 (en) * 1999-02-26 2001-06-19 Honda Giken Kogyo Kabushiki Kaisha Gas turbine engine
US20010047650A1 (en) * 1998-07-27 2001-12-06 Gerhard Muller Method of operating a gas-turbine chamber with gaseous fuel
US6338240B1 (en) * 1999-01-08 2002-01-15 Hitachi, Ltd. Control method for gas turbine load

Patent Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE888335C (de) * 1941-05-16 1953-08-31 Aeg Einrichtung zur Leistungsregelung von Gleichdruckgasturbinenanlagen
GB1388404A (en) * 1971-06-18 1975-03-26 Rolls Royce Fuel control system for a gas turbine engine
DE2136184A1 (de) * 1971-07-20 1973-01-25 Kraftwerk Union Ag Gasturbinenanlage
US4058975A (en) * 1975-12-08 1977-11-22 General Electric Company Gas turbine temperature sensor validation apparatus and method
US4455820A (en) * 1976-09-09 1984-06-26 General Electric Company Control system and method for controlling a gas turbine in accordance with the temperature conditions thereof
US4735052A (en) * 1985-09-30 1988-04-05 Kabushiki Kaisha Toshiba Gas turbine apparatus
US5319931A (en) * 1992-12-30 1994-06-14 General Electric Company Fuel trim method for a multiple chamber gas turbine combustion system
US5533329A (en) * 1993-05-17 1996-07-09 Hitachi, Ltd. Control apparatus for and control method of gas turbine
GB2323428A (en) * 1997-03-18 1998-09-23 Vosper Thornycroft Controls Li Valve arrangement to control flow to burners
DE19825335A1 (de) * 1998-06-05 1999-12-09 Abb Patent Gmbh Verfahren zum Betrieb einer Gasturbine
US20010047650A1 (en) * 1998-07-27 2001-12-06 Gerhard Muller Method of operating a gas-turbine chamber with gaseous fuel
US6338240B1 (en) * 1999-01-08 2002-01-15 Hitachi, Ltd. Control method for gas turbine load
US6247300B1 (en) * 1999-02-26 2001-06-19 Honda Giken Kogyo Kabushiki Kaisha Gas turbine engine
EP1077349A1 (fr) * 1999-08-19 2001-02-21 General Electric Company Appareil à injection étagée de carburant et procédé pour injecteurs de turbines à gaz

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