EP4202306A1 - Vormischbrenner für eine gasturbinenanordnung für kraftwerke mit einer durch herkömmliche und hochreaktive brennstoffe gespeisten pilotlanze, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung mit diesem brenner - Google Patents

Vormischbrenner für eine gasturbinenanordnung für kraftwerke mit einer durch herkömmliche und hochreaktive brennstoffe gespeisten pilotlanze, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung mit diesem brenner Download PDF

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Publication number
EP4202306A1
EP4202306A1 EP21217779.4A EP21217779A EP4202306A1 EP 4202306 A1 EP4202306 A1 EP 4202306A1 EP 21217779 A EP21217779 A EP 21217779A EP 4202306 A1 EP4202306 A1 EP 4202306A1
Authority
EP
European Patent Office
Prior art keywords
gas
pilot
nozzles
premix
burner
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.)
Pending
Application number
EP21217779.4A
Other languages
English (en)
French (fr)
Inventor
Michael Thomas Maurer
Luis TAY WO CHONG HILARES
Andrea Ciani
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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 Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP21217779.4A priority Critical patent/EP4202306A1/de
Priority to CN202211681644.2A priority patent/CN116358001A/zh
Publication of EP4202306A1 publication Critical patent/EP4202306A1/de
Pending legal-status Critical Current

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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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • the present invention relates to the technical field of the gas turbine assemblies for power plants (in the following only "gas turbine”).
  • gas turbine gas turbine assemblies
  • an incoming air flow is compressed in a compressor and then mixed with fuel (gas fuel and/or oil fuel) in a combustor before entering in a turbine wherein the hot gas expansion generates a rotating work on a rotor in turn connected to a generator for power production.
  • the present invention relates to all kinds of the above gas turbines (very general definition) wherein the combustor comprises at least a "premix burner”.
  • a premix burner is a burner configured not only for injecting the fuel in the compressed air flow but also for mixing (with a swirl) the compressed air and the fuel before injecting the mixture into the combustion chamber.
  • the present invention refers to the problem of how to improve the premix burner in order to allow a feeding not only with common fuels and also with highly reactive fuel, for instance fuel comprising H2.
  • a gas turbine assembly for power plants comprises a rotor, a compressor, a combustor and a turbine unit.
  • the compressor is configured for compressing air supplied at a compressor inlet.
  • the compressed air leaving the compressor flows into the combustor provided with a plurality of burners configured for injecting fuel in the compressed air.
  • the mixture of fuel and compressed air flows into a combustion chamber where this mixture is combusted for generating a hot gas flow.
  • the expansion of this hot gas flow inside the turbine generates a rotating work on the rotor in turn connected to a generator.
  • the turbine and the compressor comprise a plurality of stages, or rows, of rotor blades that are interposed by a plurality of stages, or rows, of vanes supported by an outer casing surrounding the assembly.
  • a high turbine inlet temperature is required.
  • this high temperature involves an undesired high NOx emission level.
  • a so called “sequential" gas turbine is particularly suitable.
  • a sequential gas turbine comprises two combustors or combustion stages in series wherein each combustor is provided with a plurality of burners and with at least a combustion chamber.
  • the upstream or first combustor comprises a plurality of so-called "premix burners".
  • a premix burner is a burner configured not only for injecting the fuel in the compressed air but also for mixing with a swirl the compressed air and the fuel before injecting the mixture into the combustion chamber.
  • This swirling mixture is obtained by providing a swirling cone configured for generating a swirl in the air flow wherein this cone is provided with a plurality of fuel injecting nozzles (called premix nozzles).
  • premix nozzles This swirling mixture allows to reduce the NOx emission but the generated flame is not enough stable under some conditions.
  • the burner is also provided with a pilot lance configured for injecting fuel in a more concentrate manner into a less turbulent air flow. The diffusion flame generate by the pilot is actually more stable but it generates a high NOx emission.
  • a premix burner is thus widely used because it allows to use a premix flame with low NOx emission during the normal operation and has the option to introduce a more stable diffusion pilot flame, if required for stability reasons.
  • both stages are in operation wherein the majority of the fuel is fed to the premix nozzles for the low NOx and a small portion of the fuel is fed to the pilot for adding stability of the overall burner and to prevent "lean blow out" of the premix stage.
  • the present invention is not limited only to sequential gas turbines but it could be applied in all gas turbine provided with a premix burner as above described.
  • a change in fuel reactivity implies a change in flame location and behavior.
  • higher fuel reactivity like H2 forces the flame to move upstream, increasing NOx emissions, and potentially overheating the nozzles.
  • highly reactive fuels e.g. fuels containing large quantities of either higher hydrocarbons or hydrogen
  • the flame, in particular the premix flame moves upstream compared to the case of natural gas, thus increasing the risk of flashback.
  • a solution for avoiding this flashback of the premix flame could be to lower the flame temperature (by feeding less fuel) to the first stage combustor.
  • the flame temperature cannot be lowered beyond a certain limit, called “lean blow out” temperature, because under this temperature the operation of the combustor is compromised.
  • the solution offered by the prior art practice in case of using highly reacting fuels is to switch a relevant part of the fuel from the premix nozzles to the pilot. For instance, it is diverted up to 10-40% of the total fuel to the pilot lance ( Vs 0-10% in case of natural gas operation).
  • the pilot flame is not premixed and is operating in a diffusion flame mode. The consequence is high NOx emissions which can be only party compensated by the further oxidation along the system.
  • a primary object of the present invention is to provide a premix burner for a gas turbine assembly for power plants and a method for operating this burner for overcoming the drawbacks of the current prior art practice.
  • the scope of the present invention is to provide a premix burner having a pilot lance configured to be selectively fed by common (natural) gas fuels and by highly reactive gas fuel, for instance H2-based fuel having an high % of H2 (in vol. up to 100%) .
  • the scope of the present invention is to provide a pilot lance wherein in case of h2-based gas fuel feeding a relevant part of this fuel can be deviated from the premix nozzles (flashback problem) to the pilot lance without the generation high Nox emission.
  • the main idea at the base of the invention is to create a mixing volume inside the pilot lance wherein the H2-based fuel and air can be mixed prior reaching the pilot nozzles.
  • the scope is to provide a kind of a premix pilot lance.
  • a premix burner structure suitable to be improved by the invention is a premix burner comprising:
  • the above pilot lance comprises:
  • Each main duct have a base end connected to a compressed air source and a tip end provided with at least an pilot nozzles.
  • the feeding of the natural gas to the premix nozzles and/or to pilot gas nozzle are depending of the composition of the gas fuel and on the engine load.
  • the premix burner moreover comprises:
  • the second gas fuel source is a H2-based gas fuel source or a source of highly reactive gas fuel that if fed to the premix nozzles may generate flashback problems.
  • this kind of gas is proportionally fed to the new inner duct whereas compressed air is fed to the main duct so that during H2-based gas fuel operation the volume between the inner nozzle and the pilot nozzles inside each main duct is a mixing volume for mixing the H2-based gas fuel with air before reaching the corresponding pilot nozzle. Due to this mixing before the injection, the corresponding flame generates an acceptable amount of NOx emission.
  • the lance comprises a single main duct provided with a plurality of pilot nozzles and a single inner duct concentric with respect to the main duct.
  • the pilot lance comprises a plurality of parallel main ducts wherein each main duct comprises a single pilot nozzle and each main duct houses an inner duct concentric with respect to the corresponding main duct.
  • the mixing volume is limited bay walls defining a cone portion at the inner nozzle and a tubular portion between the inner nozzle and the tip.
  • premix nozzles may be connected to the H2-based gas fuel source so that a minimal part of this fuel can anyway directed to the swirler.
  • the invention is not limited to a particular kind of gas turbine assembly but it can be applied to a general gas turbine comprising:
  • the gas turbine may involve a single combustion stage or a double/sequential combustion.
  • the following detailed description will refer to two not limiting example of sequential combustion gas turbines.
  • a first feature of the present invention is to provide a first gas fuel source and a second gas fuel source wherein the first source delivers natural gas fuel and the second source delivers H2-based gas fuel.
  • the H2 fuel and natural gas may be mixed before the feeding in order to supply a fuel blend with various H2 content.
  • H2 fuel source we mean a feeding a fuel having a high H2 content.
  • the scope of the present invention is, as foregoing cited, to provide a premix burner configured to be selectively fed by common (natural) gas fuels and by highly reactive gas fuel.
  • the source may be proximal or distal with respect to the burner and each source may comprise more than one feeding lines for feeding with the same fuel a plurality of components of the gas turbine.
  • the swirler can be realized in form of a cone body and a tubular body may be provided downstream the swirler.
  • the invention refers also to a method for operating such a premix burner; the method comprising the steps of:
  • the method may comprise also the step of: d) stopping the feeding of the inner duct and re-starting or increasing with the feeding of the premix nozzles and/or the pilot gas nozzles.
  • steps c) and/or d) may be performed simultaneously or a double feeding may be temporary performed.
  • FIG. 1 is a schematic view of a first example of a gas turbine 1 comprising a sequential combustor that can be operated according to the method of the present invention.
  • figure 1 discloses a gas turbine with a high pressure and a low pressure turbine.
  • the gas turbine 1 of figure 1 comprises a compressor 3, a first combustor 31, a high-pressure turbine 5, a second combustor 32 and a low-pressure turbine 7.
  • the compressor 3 and the two turbines 5, 7 are part of or are connected to a common rotor 8 rotating around an axis 9 and surrounded by a concentric casing 10.
  • the compressor 3 is supplied with air and is provided with rotating blades 18 and stator vanes 19 configured for compressing the air entering the compressor 3.
  • the compressed air flows into a plenum 11 and from there into a plurality of first burners 12 of the first combustor 31 arranged as a ring around the axis 9.
  • Each first burner 12 in configured for injecting fuel (supplied by a first fuel supply 13) in the air flow, in particular this first burner 12 may be defined as a "premix" burner because in configured for mixing the air and the injected fuel before the ignition point.
  • Figures 4 and 5 disclose an example of a premix burner according to the present invention.
  • the fuel/compressed air mixture flows into a first combustion chamber 4 annularly shaped where this mixture are combusted via a forced ignition, for instance by a spark igniter.
  • the resulting hot gas leaves the first combustor chamber 4 and is partially expanded in the high-pressure turbine 5 performing work on the rotor 8.
  • Downstream of the high-pressure turbine 5 the hot gas partially expanded flows into a second burner 33 where fuel supplied by a fuel lance 14 is injected.
  • the partially expanded gas has a high temperature and contains sufficient oxygen for a further combustion that occurred based on a self-ignition in the second combustion chamber 6 arranged downstream the second burner 33.
  • This second burner 33 is also called "reheat" burner.
  • the reheated hot gas leaves the second combustion chamber 6 and flows in the low-pressure turbine 7 where it is expanded performing work on the rotor 8.
  • the low-pressure turbine 7 comprises a plurality of stages, or rows, of rotor blades 15 arranged in series in the main flow direction. Such stages of blades 15 are interposed by stages of stator vanes 16.
  • the rotor blades 15 are connected to the rotor 8 whereas the stator vanes 16 are connected to a vane carrier 17 that is a concentric casing surrounding the low-pressure turbine 7.
  • FIG. 2 is a schematic view of a second example of a gas turbine 20 comprising a sequential combustor that can be operated according to the method of the present invention.
  • figure 2 discloses a gas turbine 20 provided with a compressor 29, one turbine 21 and a sequential combustor 22.
  • the sequential combustor 22 of figure 2 comprises a plurality of so-called can combustors, i.e. a plurality of cylindrical casings wherein each can combustor houses a plurality of first burners 24, for instance four first burners 24, a first combustion chamber 25, a second burner 26, and a second combustion chamber 27.
  • an air mixer (not represented) may be provided configured for adding air in the hot gas leaving the first combustion chamber 25.
  • the sequential combustor arrangement is at least in part housed in an outer casing 28 supporting the plurality of can combustor 22 arranged as a ring around the turbine axis.
  • a first fuel is introduced via a first fuel injector (not shown) into the first burners 24 wherein the fuel is mixed with the compressed gas supplied by the compressor 29.
  • each first burner 24 of this embodiment is a "premix" burner configured for generating a premix flame and a diffusion flame.
  • Each first burner 24 of figure 2 and each first burner 12 of figure 1 is independently operable, i.e.
  • each first burner may be switched off independently on the other first burners and each first burner may be operated independently in terms of ratio between the fuel injected in the diffusion mode and the fuel injected in the premix mode.
  • the hot gas leaving the second combustion chamber 27 expands in the turbine 21 performing work on a rotor 30.
  • the premix burner 34 comprises:
  • Figure 4 discloses in detail a known pilot lance 38. This figures allow to disclose that, in general, a pilot lance 38 comprises:
  • Figure 5 discloses an example of a pilot lance according to the invention, i.e. a pilot lance modified with respect to figure 4 in order to be suitable to be fed by h2-based fuel.
  • the main duct 42 has a base end connected to a compressed air source and a tip with a plurality of pilot nozzles 43.
  • the lance 38 moreover comprises an inner duct 44 extending inside the main duct 42 and having a first end connected to a second or pilot gas fuel source and a second end provided with an inner nozzle 45.
  • This inner nozzle is arranged upstream to the pilot nozzles 43 of the main duct 42 so that between the inner nozzle 45 and the pilot nozzles 43 a volume 46 is present.
  • the feeding of the premix nozzles is stopped or reduced and the feeding of H2-based gas fuel is open to the inner duct.
  • the main duct 42 is also fed by compressed air so that the volume 46 becomes a mixing volume for the H2-based gas fuel and the compresses air before.
  • the gas fuel reaches pilot nozzles 43 already mixed with the air and corresponding less NOx emissions are generated.
  • the pilot nozzles are not parallel with the axis A of the burner but are arranged so that the premixed H2 fuel is injected directly into the shear layer between swirl flow from the premix stage and bluff body recirculation generated by the lance tip (these terms are well known by the skilled person).
  • the mixing volume 46 comprises a cone portion 47 and a tubular portion 48.
  • premix nozzles 36 may be connected to the H2-based gas fuel source for allowing minimal feeding of this fuel also to the swirler.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP21217779.4A 2021-12-27 2021-12-27 Vormischbrenner für eine gasturbinenanordnung für kraftwerke mit einer durch herkömmliche und hochreaktive brennstoffe gespeisten pilotlanze, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung mit diesem brenner Pending EP4202306A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP21217779.4A EP4202306A1 (de) 2021-12-27 2021-12-27 Vormischbrenner für eine gasturbinenanordnung für kraftwerke mit einer durch herkömmliche und hochreaktive brennstoffe gespeisten pilotlanze, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung mit diesem brenner
CN202211681644.2A CN116358001A (zh) 2021-12-27 2022-12-27 适合供给有普通和高反应性燃料的提供有导燃喷枪的针对发电厂的燃气涡轮组件的预混烧嘴

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21217779.4A EP4202306A1 (de) 2021-12-27 2021-12-27 Vormischbrenner für eine gasturbinenanordnung für kraftwerke mit einer durch herkömmliche und hochreaktive brennstoffe gespeisten pilotlanze, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung mit diesem brenner

Publications (1)

Publication Number Publication Date
EP4202306A1 true EP4202306A1 (de) 2023-06-28

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EP21217779.4A Pending EP4202306A1 (de) 2021-12-27 2021-12-27 Vormischbrenner für eine gasturbinenanordnung für kraftwerke mit einer durch herkömmliche und hochreaktive brennstoffe gespeisten pilotlanze, verfahren zum betrieb dieses brenners sowie gasturbinenanordnung mit diesem brenner

Country Status (2)

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EP (1) EP4202306A1 (de)
CN (1) CN116358001A (de)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6070411A (en) * 1996-11-29 2000-06-06 Kabushiki Kaisha Toshiba Gas turbine combustor with premixing and diffusing fuel nozzles
US20040172951A1 (en) * 2001-07-19 2004-09-09 Frank Hannemann Method for operating a burner of a gas turbine and a power plant
US20160215984A1 (en) * 2015-01-28 2016-07-28 General Electric Technology Gmbh Sequential combustor arrangement with a mixer
US20180231254A1 (en) * 2017-02-13 2018-08-16 Ansaldo Energia Switzerland AG Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor
EP3505826A1 (de) * 2017-12-26 2019-07-03 Ansaldo Energia Switzerland AG Brenner für einen gasturbinenkraftwerk, brennkammer eines gasturbinenkraftwerks aufwesend einen solchen brenner und gasturbinenkraftwerk aufweisend eine solche brennerkammer

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6070411A (en) * 1996-11-29 2000-06-06 Kabushiki Kaisha Toshiba Gas turbine combustor with premixing and diffusing fuel nozzles
US20040172951A1 (en) * 2001-07-19 2004-09-09 Frank Hannemann Method for operating a burner of a gas turbine and a power plant
US20160215984A1 (en) * 2015-01-28 2016-07-28 General Electric Technology Gmbh Sequential combustor arrangement with a mixer
US20180231254A1 (en) * 2017-02-13 2018-08-16 Ansaldo Energia Switzerland AG Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor
EP3505826A1 (de) * 2017-12-26 2019-07-03 Ansaldo Energia Switzerland AG Brenner für einen gasturbinenkraftwerk, brennkammer eines gasturbinenkraftwerks aufwesend einen solchen brenner und gasturbinenkraftwerk aufweisend eine solche brennerkammer

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