EP4148327A1 - Gasturbinenmotor mit akustischer modenstabilisierung, verfahren zur steuerung und verfahren zum nachrüsten eines gasturbinenmotors - Google Patents

Gasturbinenmotor mit akustischer modenstabilisierung, verfahren zur steuerung und verfahren zum nachrüsten eines gasturbinenmotors Download PDF

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Publication number
EP4148327A1
EP4148327A1 EP21195837.6A EP21195837A EP4148327A1 EP 4148327 A1 EP4148327 A1 EP 4148327A1 EP 21195837 A EP21195837 A EP 21195837A EP 4148327 A1 EP4148327 A1 EP 4148327A1
Authority
EP
European Patent Office
Prior art keywords
burners
time delay
gas turbine
turbine engine
flame
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
EP21195837.6A
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English (en)
French (fr)
Inventor
Alessandro Scarpato
Mirko Ruben Bothien
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
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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 EP21195837.6A priority Critical patent/EP4148327A1/de
Priority to CN202211099646.0A priority patent/CN115773183A/zh
Publication of EP4148327A1 publication Critical patent/EP4148327A1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/964—Preventing, counteracting or reducing vibration or noise counteracting thermoacoustic noise
    • 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
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution

Definitions

  • the present invention relates to a gas turbine engine with acoustic mode stabilization, method for controlling and method for retrofitting a gas turbine engine.
  • combustion instabilities may arise in certain operating conditions. Such conditions may depend on the response of the complex structure and dynamics of fluids in the gas turbine engines and may widely vary according to the kind and the size of gas turbines.
  • Critical acoustic vibrating modes are known, because normally they become apparent during the steps of design and test. It is therefore possible to implement protective measures that avoid or reduce effects of critical acoustic vibrating modes.
  • Known measures that include acoustic dampers and controlling fuel supply to change operating conditions, are not completely satisfactory, however.
  • Acoustic dampers such as Helmholtz dampers, occupy relatively large space and require mechanical and fluidic coupling to the flow path of the gas turbine engine. Moreover, damping action of the acoustic dampers may depend on the specific location where the dampers are connected and optimal positioning may not be achieved because of geometrical or mechanical constraints.
  • a gas turbine engine according to claim 1 a method for operating a gas turbine engine according to claim 9 and a method for retrofitting a gas turbine engine according to claim 13.
  • a combustor has first burners that generate first flames with a first time delay ⁇ 1 and second burners that generate second flames with a second time delay ⁇ 2 .
  • the acoustic vibration modes i.e. pulsations
  • the natural vibration frequency f 0 i.e. at the critical frequency where acoustic vibration modes may amplify and cause damage of the gas turbine engine.
  • the attenuation is achieved without use of additional components, such as acoustic dampers, which are bulky and need fluid coupling to the hot gas path from outside. Moreover, the overall fuel supply is not altered by throttling to either the first burners or to the second burners.
  • Figure 1 shows a simplified view of a gas turbine engine, designated as whole with numeral 1.
  • the gas turbine engine 1 comprises a compressor 2, a first combustor 3, optionally a high-pressure turbine 5, a second combustor 7 (also referred to as sequential combustor) and a low-pressure turbine 8.
  • the example of figure 1 is not limitative, as the invention may be advantageously exploited also in gas turbine engines having different structure, such as with a single combustor or with two combustors and no high-pressure turbine between the first combustor and the second combustor.
  • a diluter to introduce diluting air in the hot gas passing through the combustors, may also be provided between the first and the second combustors, in addition to or as an alternative to the high pressure turbine.
  • the two combustors may also be directly coupled, i.e. without any components in-between.
  • the gas turbine engine further comprises a fuel supply system 9 and a controller 10.
  • the fuel supply system 9 delivers fuel flowrates for operation of the first combustor 3 and second combustor 7 and comprises a first supply system 11, coupled to the first combustor 3, and a second supply system 12, coupled to the second combustor 7. Both the first supply system 11 and the second supply system 12 are controlled by the controller 10.
  • the controller 10 receives state signals from system sensors 13 and operates the gas turbine through actuators to provide a controlled power output.
  • the actuators include orientable inlet guide vanes 14 of the compressor 2 and valves of the first supply system 11 and second supply system 12.
  • a flow of compressed air supplied by the compressor 2 is added with fuel and the air/fuel mixture thus obtained is burnt in the first combustor 3.
  • the exhaust gas of the first combustor 3 is partly expanded in the high-pressure turbine 5; then additional fuel is mixed and burnt in the second combustor 7.
  • the exhaust gas is finally expanded in the low-pressure turbine 8 and discharged either to the outside or e.g. to a heat recovery steam generator.
  • the amount of fuel delivered by the first supply system 11 and second supply system 12 is controlled by the controller 10.
  • the first combustor 3 is schematically shown in figure 2 and comprises an annular combustion chamber 15, extending about a longitudinal combustor axis A of the gas turbine engine 1, a plurality of first burners 17 and a plurality of second burners 18, circumferentially distributed around the combustor axis A at a common radial distance therefrom.
  • the first burners 17 and the second burners 18 may define a first asymmetric group of burners and a second asymmetric group of burners, respectively.
  • first burners 17 and the second burners 18 can be symmetrically distributed as a whole, the sole first burners 17 and the sole second burners 18 may be not.
  • Such a configuration helps promoting cancellation of the vibrating modes that propagate in the combustion chamber and counteracting their amplification.
  • the first combustor 3 has a natural vibration frequency f 0 .
  • the natural vibration frequency is the resonance frequency of the first combustor, such that acoustic vibration modes (i.e. pulsations) having that frequency do not attenuate when propagating through the first combustor, but are amplified. Therefore, pulsations having the natural vibration frequency need to be dampened to avoid structural damages and loss of efficiency.
  • the first burners 17 and the second burners 18 may be all operated with a same fuel flowrate by the controller 10.
  • the first burners 17 are configured to produce first flames with a first time delay ⁇ 1 and the second burners 18 are configured to produce second flames with a second time delay ⁇ 2 , where the second time delay ⁇ 2 is different from the first time delay ⁇ 1 .
  • the time delay is a characteristic time required for the fuel to be conveyed from a fuel injection point to the flame front.
  • the first burners 17 and the second burners 18 may comprise respective first stages 20, 21 and respective second stages 22, 23.
  • the first stages 20, 21 may be pilot stages (e.g. arranged for generating a diffusion flame) that extend along a burner axis B and the second stages 22, 23 may be main premix stages that extend around the respective first stages 20, 21.
  • the time delay of the first burner preferably refers to the time delay of the second (main) stage 22 and likewise the time delay of the second burner preferably refers to the time delay of the second (main) stage 23.
  • the time delay of the first burner 17 refers to an average of the time delay of the first and second stages 20, 22 and likewise the time delay of the second burner 18 refers to an average of the time delay of the first and second stages 21, 23; such a solution may be preferred in case a substantial amount of fuel, e.g. 10% or more, is fed via the first (pilot) stages 20, 21.
  • the first burners 17 have first air passages 25 and the second burners 18 have second air passages 27.
  • the second air passages 27 are different from the first air passages 25. Differences in air passages determine different air supply, that in turn results in different time delays.
  • the first burners 17 may have first air passages 25 with respective air inlets and first inlet grids 26 at the air inlets.
  • the second burners 18 may likewise have second air passages 27 with respective air inlets and second inlet grids 28 at the air inlets.
  • the first inlet grids 26 and the second inlet grids 28 are different from one another and e.g. they are configured to differently affect inlet airflows and cause different first time delay ⁇ 1 and second time delay ⁇ 2 .
  • Use of different inlet grids is a simple and cheap, yet effective solution to differentiate air supply and obtain different time delays.
  • the first burners 17 may have swirlers 30, 31; the second burners 18 may have swirlers 32, 33, which are different from the swirlers 30, 31.
  • air splitters may be arranged to differently divide airflows in the first air passages 25 of the first burners 17 and in the second air passages 27 of the second burners 18.
  • the first burners 17 have a first fuel split ratio between the respective first stage 20 and second stage 22 and the second burners 18 have a second fuel split ratio between the respective first stage 21 and second stage 23, whereby the second fuel split ratio is different from the first fuel split ratio.
  • the first supply system 11 may comprise independent fuel valves 33, 35 for the first stage 20 and for the second stage 22 of the first burners 17, and further independent fuel valves 34, 36 for the first stage 21 and for the second stage 23 of the second burners 18.
  • the fuel valves 33-36 are controlled by the controller 10 to supply fuel flowrates F 1 , F 2 to the first stage 20 and to second stage 22 respectively of the first burners 17 and fuel flowrates F 1 ', F 2 ' to the first stage 21 and to second stage 23 respectively of the second burners 18.
  • the fuel flowrates F 1 , F 2 and the fuel flowrates F 1 ', F 2 ' are selected such that a first fuel split ratio F 1 /F 2 of the first burners 17 is different from a second fuel split ratio F 1 '/F 2 ' of the second burners 18: F 1 / F 2 ⁇ F 1 ⁇ / F 2 ⁇ .
  • the fuel split ratio between the first and second burners may be used to control flame characteristic (shape, location) and thus the time delay, without any structural modification of the first and second burners, as damping of the target frequencies may be obtained through gas turbine engine control.
  • the first burners 17 and the second burners 18 have respective different outlets.
  • burner outlets may be exploited to differentiate the behavior of the first burners 17 and second burners 18. Differences may reside e.g. in shape, length and width of the outlets.
  • the first burners 17 are provided with respective first outlets 40, which project in an axial direction and are defined by conical or generally convergent or cylindrical sections having a first length L 1 and a first width W 1 .
  • the second burners 18 are provided with respective second outlets 41, which project in an axial direction and are defined by conical or generally convergent or cylindrical sections having a second length L 2 , different from the first length L 1 , and/or a second width W 2 , different from the first width W 1 .
  • only the first burners 17 or the second burners 18 are provided with projecting outlets.
  • the first burners 17 may also be configured to cause respective first flame anchorage locations and the second burners 18 may be configured to cause respective second flame anchorage locations, the second flame anchorage locations being axially different from the first flame anchorage locations.
  • the effect may be achieved in a simple and cost effective manner e.g. by using lance injectors of different length at the first burners 17 and second burners 18.
  • the first burners 17 include respective first lance injectors 43 having a first length L 1 ' and the second burners 18 include respective first lance injectors 44 having a second length L 2 ', where the second length L 2 ' is different from the first length L 1 ' ( figures 9 and 10 ).
  • the burners have a first flame stabilizer 45, configured to trigger a first flame configuration and make the burners to operate as the first burners 17, and a second flame stabilizer 46, configured to trigger a second flame configuration and make the burners to operate as the second burners 18.
  • the first flame stabilizers 45 and the second flame stabilizers 46 may be e.g. spark plugs or plasma generators.
  • the first flame stabilizers 45 and the second flame stabilizers 46 are controlled by the controller 10.
  • the present invention also refers to method for operating a gas turbine engine.
  • first burners 17 of a gas turbine engine combustor are operated to produce first flames with a first time delay ⁇ 1 and second burners 18 of the gas turbine combustor are operated to produce second flames with a second time delay ⁇ 2 .
  • the first flames have a first flame shape and the second flames have a second flame shape, different from the first flame shape.
  • first flames are set at a first distance D 1 from the respective first burner assemblies 17 and the second flames are set at a second distance D 2 from the respective second burner assemblies 18, the second distance D 2 being different from the first distance D 1 .
  • the first burners 17 have a first fuel split ratio F 1 /F 2 between a first stage 20 and second stage 22 thereof and the second burners 18 have a second fuel split ratio F 1 '/F 2 ' between a first stage 21 and second stage 23 thereof, the second fuel split ratio F 1 '/F 2 ' being different from the first fuel split ratio F 1 /F 2 .
  • a gas turbine engine may also be retrofitted to achieve suppression of natural vibration frequency as described above.
  • the gas turbine engine comprises a combustor having a natural vibration frequency f 0 .
  • the combustor 3, 7 comprises a plurality of first burners 17.
  • the first burners are configured to produce flames with a first time delay ⁇ 1 .
  • the retrofitting method comprises replacing one or more components of at least one of the first burners 17 with a modified component to obtain a second burner 18.
  • the second burners 18 are configured to generate flames with a second time delay ⁇ 2 .
  • the second time delay ⁇ 2 is different from the first time delay ⁇ 1 .
  • the difference between the first (native) time delay ⁇ 1 and the second (modified) time delay ⁇ 2 is equal to the reciprocal of the natural vibration frequency f 0 , as explained above.
  • the replacement component may be at least one of inlet grids (26, 28); swirlers (30, 31, 32, 33); air splitters; outlets (40, 41); lance injectors (43, 44); stabilizing actuators (45, 46); etc.
  • the controller 10 contains a computer program configured to control operation of the gas turbine engine 1.
  • component replacement to achieve suppression of natural vibration frequency may also include replacing the controller 10 or replacing the computer program loaded in the controller 10 with a modified computer program or replacing or adding code portions to the computer program.
  • the native computer program that controls the fuel split ratio F 1 /F 2 of the first stage 20 and second stage 22 of one or more of the first burners 17 may be replaced with a modified computer program that controls the fuel split ratio F 1 '/F 2 '.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
EP21195837.6A 2021-09-09 2021-09-09 Gasturbinenmotor mit akustischer modenstabilisierung, verfahren zur steuerung und verfahren zum nachrüsten eines gasturbinenmotors Pending EP4148327A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP21195837.6A EP4148327A1 (de) 2021-09-09 2021-09-09 Gasturbinenmotor mit akustischer modenstabilisierung, verfahren zur steuerung und verfahren zum nachrüsten eines gasturbinenmotors
CN202211099646.0A CN115773183A (zh) 2021-09-09 2022-09-09 具有声模稳定的燃气涡轮发动机、控制方法和改装的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP21195837.6A EP4148327A1 (de) 2021-09-09 2021-09-09 Gasturbinenmotor mit akustischer modenstabilisierung, verfahren zur steuerung und verfahren zum nachrüsten eines gasturbinenmotors

Publications (1)

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EP4148327A1 true EP4148327A1 (de) 2023-03-15

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EP21195837.6A Pending EP4148327A1 (de) 2021-09-09 2021-09-09 Gasturbinenmotor mit akustischer modenstabilisierung, verfahren zur steuerung und verfahren zum nachrüsten eines gasturbinenmotors

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EP (1) EP4148327A1 (de)
CN (1) CN115773183A (de)

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20010018172A1 (en) * 1998-01-28 2001-08-30 Lovett Jeffery Allan Combustors with improved dynamics
US20030041588A1 (en) * 1999-08-18 2003-03-06 Franz Joos Method for generating hot gases in a combustion device and combustion device for carrying out the method
US20040093851A1 (en) * 2002-11-19 2004-05-20 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
DE102004015186A1 (de) * 2004-03-29 2005-10-20 Alstom Technology Ltd Baden Gasturbinen-Brennkammer und zugehöriges Betriebsverfahren
US20080053097A1 (en) * 2006-09-05 2008-03-06 Fei Han Injection assembly for a combustor
EP2848865A1 (de) * 2013-09-12 2015-03-18 Alstom Technology Ltd Thermoakustisches Stabilisierungsverfahren
US20150219337A1 (en) * 2014-02-03 2015-08-06 General Electric Company System and method for reducing modal coupling of combustion dynamics

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20010018172A1 (en) * 1998-01-28 2001-08-30 Lovett Jeffery Allan Combustors with improved dynamics
US20030041588A1 (en) * 1999-08-18 2003-03-06 Franz Joos Method for generating hot gases in a combustion device and combustion device for carrying out the method
US20040093851A1 (en) * 2002-11-19 2004-05-20 Siemens Westinghouse Power Corporation Gas turbine combustor having staged burners with dissimilar mixing passage geometries
DE102004015186A1 (de) * 2004-03-29 2005-10-20 Alstom Technology Ltd Baden Gasturbinen-Brennkammer und zugehöriges Betriebsverfahren
US20080053097A1 (en) * 2006-09-05 2008-03-06 Fei Han Injection assembly for a combustor
EP2848865A1 (de) * 2013-09-12 2015-03-18 Alstom Technology Ltd Thermoakustisches Stabilisierungsverfahren
US20150219337A1 (en) * 2014-02-03 2015-08-06 General Electric Company System and method for reducing modal coupling of combustion dynamics

Also Published As

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