EP3406974A1 - Mischer und verfahren zum betrieb davon - Google Patents

Mischer und verfahren zum betrieb davon Download PDF

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Publication number
EP3406974A1
EP3406974A1 EP17172854.6A EP17172854A EP3406974A1 EP 3406974 A1 EP3406974 A1 EP 3406974A1 EP 17172854 A EP17172854 A EP 17172854A EP 3406974 A1 EP3406974 A1 EP 3406974A1
Authority
EP
European Patent Office
Prior art keywords
injector
mixer
fluid
mass flow
inlet
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.)
Granted
Application number
EP17172854.6A
Other languages
English (en)
French (fr)
Other versions
EP3406974B1 (de
Inventor
Alessandro Scarpato
Bruno Schuermans
Mirko Bothien
Franklin Genin
Luis TAY WO CHONG HILARES
Naresh Kumar Aluri
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
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Publication date
Application filed by Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP17172854.6A priority Critical patent/EP3406974B1/de
Priority to CN201810507686.1A priority patent/CN108954386B/zh
Publication of EP3406974A1 publication Critical patent/EP3406974A1/de
Application granted granted Critical
Publication of EP3406974B1 publication Critical patent/EP3406974B1/de
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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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00013—Reducing thermo-acoustic vibrations by active means

Definitions

  • the present invention relates to a mixer and a method for operating the same.
  • the mixer is part of a gas turbine, e.g. a gas turbine of a power plant.
  • Figure 1 schematically shows an example of a gas turbine; the gas turbine 1 has a compressor 2, a first combustion chamber 3, a second combustion chamber 4 and a turbine 5. Possibly between the first combustion chamber 3 and the second combustion chamber 4 a high pressure turbine is provided. During operation air is compressed at the compressor 2 and is used to combust a fuel in the first combustion chamber 3; the hot gas (possibly partly expanded in the high pressure turbine) is then sent into the second combustion chamber 4 where further fuel is injected and combusted; the hot gas generated at the second combustion chamber 4 is then expanded in the turbine 5.
  • a mixer 7 can be provided between the first combustion chamber 3 and the second combustion chamber 4 in order to dilute with air (or other gas) the hot gas coming from the first combustion chamber 3 and directed into the second combustion chamber 4. This allows a correct fuel injection and mixing with the hot gas at the second combustion chamber.
  • Figure 2 schematically shows the section of the gas turbine including the first and the second combustion chambers 3, 4.
  • Figure 2 shows a first burner 3a of the first combustion chamber 3 where the compressed air coming from the compressor 2 is mixed with the fuel and a combustor 3b where the mixture is combusted generating hot gas (reference 20a indicates the flame).
  • the hot gas is directed via a transition piece 3c into the mixer 7, where air is supplied into the hot gas to dilute it.
  • the diluted (and cooled) hot gas is thus supplied into the burner 4a of the second combustion chamber 4 where further fuel is injected into the hot gas via a lance 8 and mixed to it.
  • This mixture combusts in the combustor 4b by auto combustion (reference 20b indicates the flame), after a "delay time" from the injection into the second burner 4a.
  • the temperature at the inlet of the second burner 4a can fluctuate, typically because of mass flow fluctuation of the air coming from the mixer 7 and directed into the second burner 4a.
  • the delay time depends on, inter alia, the temperature within the second burner 4a, such that temperature fluctuations in the second burner 4a cause increase/decrease of the delay time and thus axial upstream/downstream oscillations of the flame in the combustor 4b.
  • the temperature in the second burner 4a has to be maintained constant and thus the temperature of the flow emerging from the mixer 7 has to be maintained constant.
  • the flow temperature at the exit of mixer 7 can vary because within the mixer 7 pressure fluctuations exist (e.g. due to the combustion in the combustor 3b and/or 4b); these pressure fluctuations cause diluting air fluctuating mass flow injection into the mixer.
  • multiple injectors can be provided at different axial locations of the mixer 7, in such a way that fluctuating air mass flow supplied through upstream injectors compensate for fluctuating air mass flow supplied trough downstream injectors.
  • air is injected in such a way that the dilution air mass flow injected from upstream injectors reaches the downstream injectors in phase opposition with respect to the dilution air injected through them (and vice versa); this way the upstream/downstream mass flows compensate for one another and air mass flow fluctuations are counteracted.
  • the acoustic mode is the maximum fluctuation amplitude of the acoustic pressure over the axial axis of the mixer.
  • figure 3A shows an example of an acoustic mode in connection with the axial position x along the mixer; references 17a and 17b indicate the injectors, which respectively inject the mass flow Ma and mass flow Mb.
  • Aa and Ab identify the maximum amplitude of the acoustic pressure fluctuations at the injector axial locations 17a and 17b.
  • Figures 3B and 3C respectively show the mass flow Ma and Mb and their fluctuations; the mass flows Ma and Mb propagate along the mixer towards the mixer exit; the fluctuation course is defined with respect to the mean flow (which is in general different but could also be the same) and is shown as a wave that moves from the inlet to the outlet of the mixer.
  • Figure 3D shows the total mass flow Mtot and the fluctuations thereof, resulting from the overlapping of the mass flows Ma and Mb; as shown, since the fluctuation amplitude of the mass flow Mb is larger than the fluctuation amplitude of the mass flow Ma, the overlapping of the mass flows Ma and Mb does not result in fluctuation cancellation, but only in attenuated fluctuations.
  • An aspect of the invention includes providing a mixer and a method by which the mass flow fluctuation cancellation for the fluid injected into the mixer can be improved.
  • the fluctuations amplitude can be made comparable, such that overlapping of the mass flows injected through the different injectors can result in a large reduction or also cancellation of the mass flow fluctuations.
  • the mixer 7 comprises a housing 15, a duct 16 within the housing 15, a first injector 17a and a second injector 17b for injecting a fluid (such as compressed air from the compressor, possibly cooled) into the duct 16; the fluid is injected by the first and second injector 17a, 17b with a fluctuating mass flow.
  • a fluid such as compressed air from the compressor, possibly cooled
  • the first injectors 17a and 17b can be provided around the periphery of the duct 16 and can open in one or more points into the duct, as explained in the following.
  • the first injector 17a and the second injector 17b are at a distance D such that the fluid mass flow injected through the first injector 17a reaches the second injector 17b in phase opposition with the fluid mass flow injected through the second injector 17b.
  • the large fluid mass flow axially travels through the duct 16 and reaches the second injector 17b when the second injector 17b is injecting fluid with a small fluid mass flow.
  • the first and the second injectors 17a, 17b are configured and arranged for injecting a mass flow (e.g. instantaneous mass flow) having substantially the same fluctuation amplitude.
  • a mass flow e.g. instantaneous mass flow
  • This allows a large reduction or also cancellation of the mass flow fluctuation for the mass flow resulting from the sum of the mass flow Ma from the first injector 17a and the mass flow Mb from the second injector 17b.
  • the first injector 17a can comprise a plenum 19a with at least an inlet 20a and at least a nozzle 21a for injecting the fluid into the duct 16.
  • the plenum 19a can be annular in shape and can embrace and be connected to the duct 16
  • the inlet 20a can be provided on any surface of the plenum 19a and the inlet 21a can protrude into the duct 16 or not.
  • the second injector 17b can comprise a plenum 19b with at least an inlet 20b and at least a nozzle 21b for injecting the fluid into the duct 16.
  • the plenum 19b can be annular in shape and can embrace and be connected to the duct 16, the inlet 20b can be provided on any surface of the plenum 19b and the inlet 21b can protrude into the duct 16 or not.
  • the injector can also be defined by a plurality of nozzles without the need of a plenum connected to it, as e.g. shown in figure 5 .
  • the first and/or the second injector can have any of the described structures.
  • the following reference to an embodiment with a plenum at both the first and the second injector 17a, 17b is made.
  • the inlet 20a of the first injector 17a and the inlet 20b of the second injector have different features in order to cause a different pressure drop for the fluid moving from the housing 15 into the plena 19a, 19b.
  • these features of the inlets 20a, 20b include the inlet cross section and/or the inlet surface rugosity; other means are possible.
  • the nozzle 21a of the first injector 17a and the nozzle 21b of the second injector 17b can have different features in order to cause a different pressure drop for the fluid moving from the plena 19a, 19b into the duct 16.
  • the nozzle 21a or 21b causes a pressure drop in the fluid moving from the housing 15 into the duct 16.
  • These features can include the nozzle cross section and/or the nozzle surface rugosity; other means are possible.
  • Hot gas G coming from the first combustion chamber 3 enters the duct 16 and passes through it, to be then discharged into the second combustion chamber 4.
  • the first injector 17a injects a fluid (compressed air e.g. from the compressor 2 possibly cooled) into the duct 16 to dilute and cool the hot gas; the fluid is injected into the duct 16 with a fluctuating mass flow Ma. After injection the mass flow (while mixing with the hot gas) travels through the duct 16 and reaches (completely or partly mixed to the hot gas) the second injector 17b ( figure 6B ).
  • a fluid compressed air e.g. from the compressor 2 possibly cooled
  • the second injector 17b injects a fluid (compressed air) into the duct 16 to dilute and cool the hot gas; the fluid is injected into the duct 16 with a fluctuating mass flow Mb ( figure 6C ).
  • the mass flow Ma reaches the second injector 17b in phase opposition with the mass flow Mb.
  • the fluid passes from the inside of the housing 15 into the plenum 19a of the first injector and 19b of the second injector. While passing through the inlets 20a and 20b the fluid undergoes a different pressure drop, such that the pressure inside the plena 19a and 19b is different and the flow injected through the injectors 17a and 17b and in particular the flow fluctuation amplitude thereof is different.
  • the nozzles 21a and 21b can cause pressure drop for the fluid passing through them, to cause or contribute to cause injection of a different mass flow and thus different flow fluctuation amplitudes through the first and second injectors 17a, 17b.
  • the flow fluctuation amplitude for the mass flow Ma and Mb is made substantially equal; in addition, since the flow fluctuations are in phase opposition, their overlapping causes fluctuation cancellation.
  • the present invention also refers to a method for operating a mixer 7.
  • the method comprises injecting through the first and the second injectors 17a, 17b a mass flow (e.g. instantaneous mass flow) having substantially the same fluctuation amplitude.
  • a mass flow e.g. instantaneous mass flow
  • the different pressure drop within the plena 19a, 19b and/or through the nozzles 21a, 21b causes injection of fluid with different fluctuation amplitude with respect to what would be imposed by the acoustic mode; therefore the fluctuations being in phase opposition and with substantially the same amplitude are cancelled following their overlapping.
  • the mixer can have more than two axially spaced injectors, which are at distances such as to reduce or cancel different frequencies.
  • a mixer could have a first, a second and a third injectors, the first and the third injectors cooperating to cancel a fluctuation at a frequency and the second and third injectors cooperating to cancel fluctuations at another frequency.
  • the mixer can have four injectors, with a first and a second injectors that cancel a frequency and a third and a fourth injectors that cancel another frequency.
  • any number of injectors are possible.
EP17172854.6A 2017-05-24 2017-05-24 Gasturbine und verfahren zum betrieb davon Active EP3406974B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17172854.6A EP3406974B1 (de) 2017-05-24 2017-05-24 Gasturbine und verfahren zum betrieb davon
CN201810507686.1A CN108954386B (zh) 2017-05-24 2018-05-24 混合器及用于操作该混合器的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17172854.6A EP3406974B1 (de) 2017-05-24 2017-05-24 Gasturbine und verfahren zum betrieb davon

Publications (2)

Publication Number Publication Date
EP3406974A1 true EP3406974A1 (de) 2018-11-28
EP3406974B1 EP3406974B1 (de) 2020-11-11

Family

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EP17172854.6A Active EP3406974B1 (de) 2017-05-24 2017-05-24 Gasturbine und verfahren zum betrieb davon

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EP (1) EP3406974B1 (de)
CN (1) CN108954386B (de)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
US20070074518A1 (en) * 2005-09-30 2007-04-05 Solar Turbines Incorporated Turbine engine having acoustically tuned fuel nozzle
US20150226434A1 (en) * 2012-01-05 2015-08-13 Mitsubishi Heavy Industries, Ltd. Combustor
US20160177832A1 (en) * 2014-12-22 2016-06-23 General Electric Technology Gmbh Mixer for admixing a dilution air to the hot gas flow

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5010453A (en) * 1990-08-28 1991-04-23 General Motors Corporation Vehicle lamp ventilation system
US5590529A (en) * 1994-09-26 1997-01-07 General Electric Company Air fuel mixer for gas turbine combustor
JPH08145361A (ja) * 1994-11-16 1996-06-07 Ishikawajima Harima Heavy Ind Co Ltd ガスタービン用燃料噴射弁
US5622054A (en) * 1995-12-22 1997-04-22 General Electric Company Low NOx lobed mixer fuel injector
US6735949B1 (en) * 2002-06-11 2004-05-18 General Electric Company Gas turbine engine combustor can with trapped vortex cavity
US7127899B2 (en) * 2004-02-26 2006-10-31 United Technologies Corporation Non-swirl dry low NOx (DLN) combustor
US7013649B2 (en) * 2004-05-25 2006-03-21 General Electric Company Gas turbine engine combustor mixer
US9347669B2 (en) * 2012-10-01 2016-05-24 Alstom Technology Ltd. Variable length combustor dome extension for improved operability
CN102937300B (zh) * 2012-11-28 2014-09-17 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用的稀释剂分级注入系统
EP2837888A1 (de) * 2013-08-15 2015-02-18 Alstom Technology Ltd Sequentielle Verbrennung mit Verdünnungsgasmischer
EP3037728B1 (de) * 2014-12-22 2020-04-29 Ansaldo Energia Switzerland AG Axial gestufte Mischer mit Verdünnungslufteinspritzung

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
US20070074518A1 (en) * 2005-09-30 2007-04-05 Solar Turbines Incorporated Turbine engine having acoustically tuned fuel nozzle
US20150226434A1 (en) * 2012-01-05 2015-08-13 Mitsubishi Heavy Industries, Ltd. Combustor
US20160177832A1 (en) * 2014-12-22 2016-06-23 General Electric Technology Gmbh Mixer for admixing a dilution air to the hot gas flow

Also Published As

Publication number Publication date
CN108954386B (zh) 2022-03-08
CN108954386A (zh) 2018-12-07
EP3406974B1 (de) 2020-11-11

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