US20140345282A1 - Combustion chamber for a gas turbine plant - Google Patents

Combustion chamber for a gas turbine plant Download PDF

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Publication number
US20140345282A1
US20140345282A1 US14/240,549 US201214240549A US2014345282A1 US 20140345282 A1 US20140345282 A1 US 20140345282A1 US 201214240549 A US201214240549 A US 201214240549A US 2014345282 A1 US2014345282 A1 US 2014345282A1
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US
United States
Prior art keywords
combustion chamber
resonator
combustion
wall
tube
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.)
Abandoned
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US14/240,549
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English (en)
Inventor
Sebastian Pfadler
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Siemens AG
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Siemens AG
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Filing date
Publication date
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: PFADLER, SEBASTIAN
Publication of US20140345282A1 publication Critical patent/US20140345282A1/en
Abandoned legal-status Critical Current

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    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing 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

Definitions

  • the invention relates to a combustion chamber for a gas turbine plant according to the preamble of claim 1 and to a correspondingly designed gas turbine plant according to claim 6 .
  • Gas turbine plants are composed essentially of a compressor, of a combustion chamber with a burner and of an expansion turbine.
  • a compressor In the compressor, sucked-in air is compressed before it is mixed with fuel in the combustion chamber in the following burner arranged in the compressor plenum, and this mixture is burnt.
  • the expansion turbine following the combustion chamber then extracts thermal energy from the combustion exhaust gases which have occurred in the burner and converts this into mechanical energy.
  • a generator capable of being coupled to the expansion turbine can convert this mechanical energy into electrical energy for current generation.
  • thermoacoustic vibrations of this kind in the combustion chamber present a problem in the design and, in particular, in the operation of gas turbine plants.
  • Helmholtz resonators which are composed of at least one resonator tube and of a resonator volume, are employed nowadays for damping. Helmholtz resonators of this kind damp the amplitude of vibrations at the Helmholtz frequency in specific frequency ranges as a function of the cross-sectional area and the length of the resonator tube and of the resonator volume. Helmholtz resonators as damping devices for limiting thermoacoustic vibrations in combustion chambers are known, for example, from EP 1 605 209 A1 or US 2007/0125089 A1.
  • FIG. 1 shows, for example, the arrangement, known from US 2007/0125089 A1, of Helmholtz resonators 20 on a ring of the combustion chamber wall 10 transverse to the flow direction.
  • the combustion chamber wall 10 is in this case of tubular form and separates the combustion chamber 1 from the surrounding compressor plenum 2 .
  • the perforations 22 in the combustion chamber wall 10 between the resonator volume 21 and combustion chamber 1 form the resonator tubes of the Helmholtz resonators.
  • each Helmholtz resonator may have a plurality of resonator tubes or else only a single resonator tube. So that none of the hot combustion gases from the combustion chamber 1 are introduced into the Helmholtz resonators 20 , additional ports for the delivery of barrier air are provided. In the exemplary embodiment shown in FIG. 1 , these delivery ports 23 are arranged on that wall of the resonator volume 21 which lies opposite the resonator tubes 22 .
  • Helmholtz resonators with deliveries of barrier air via the volume body have the disadvantage that the barrier air flows via the resonator tubes into the combustion chamber and consequently influences the air/fuel mixture prevailing there.
  • the resonator tubes are arranged in the combustion chamber wall such that, on the location where the resonator tubes issue into the combustion chamber, the resonator tube axis comes to lie in the normal to the surface of the combustion chamber inner wall, barrier air is introduced with a maximum depth of penetration into the combustion space of the combustion chamber.
  • this maximum cross current in relation to the internal flow of the combustion chamber may lead, precisely in the low load range of the gas turbine plant, to partial quenching of combustion and consequently to an increase in CO pollutant emission.
  • the object of the invention is to provide a combustion chamber which overcomes the disadvantages described above.
  • a combustion chamber designed according to the preamble of claim 1 , with at least one Helmholtz resonator has at least one resonator tube which is arranged such that, at the location of issue of the resonator tube into the combustion chamber, it lies with its resonator tube axis outside a normal to the surface of the combustion chamber inner wall, the maximum depth of penetration of the barrier air into the combustion space of the combustion chamber is reduced, the more so, the further the resonator tube axis is inclined in relation to the surface normal. Combustion in the combustion chamber is thereby influenced to a lesser extent, so that an increase in pollutant emission, in particular increased CO emission when the gas turbine plant is under part load, can be largely avoided.
  • a significant part of the barrier air flowing in via the resonator tube is entrained by the flow inside the combustion chamber and flows downstream along the combustion chamber inner wall, near the wall, so as to have a cooling effect over a larger region, before the barrier air is mixed more and more with the combustion gases and therefore assumes the same temperature as the combustion gases.
  • the resonator tubes become increasingly longer, with the result that ever better convection cooling of the combustion chamber wall is achieved.
  • a zone for mixing the cooler barrier air with the hot mass flows is configured in the combustion chamber such that, particularly in the low load range, partial quenching of combustion by the cooler barrier air is suppressed, but without the damping properties of the Helmholtz resonators being influenced.
  • Gas turbine plants equipped with such combustion chambers can thus have as low pollutant emissions as possible in all load ranges, while working at maximum efficiency.
  • the invention is in this case not restricted to the inclination of the resonator tubes being solely in the flow direction of the combustion exhaust gases.
  • versions may also be envisaged in which the resonator tubes have in relation to the normal to the surface of the combustion chamber inner wall an inclination which is composed both of an inclination fraction in the flow direction and of an inclination fraction transversely thereto.
  • the resonator tubes can thus be adapted optimally to the local conditions of the internal flow of the combustion chamber.
  • FIG. 1 shows diagrammatically a damping device known from the prior art
  • FIG. 2 shows diagrammatically a first version according to the invention of a damping device
  • FIG. 3 shows diagrammatically a second version according to the invention of a damping device.
  • the concept according to the invention for injecting barrier air S into the combustion space of the combustion chamber 1 of a gas turbine plant is described below, by way of example, by means of a burner which is based on a tubular combustion chamber and in which the damping device 20 is adapted essentially to the outside of the combustion chamber wall 10 .
  • the invention is also just as suitable for use in burners in which the damping device 20 is integrated completely in the combustion chamber wall 10 , or else in any other version in which barrier air S is delivered via the damping device 20 .
  • FIG. 2 illustrates a detail of a combustion chamber 1 along the flow direction of the combustion gases G, with a routing of barrier air in which, in contrast to the prior art, the barrier air S is routed into the combustion space 1 at an angle ⁇ larger than zero degrees (here approximately 45 degrees) in relation to the normal N to the surface of the combustion chamber inner wall of the combustion chamber 10 .
  • ⁇ larger than zero degrees (here approximately 45 degrees) in relation to the normal N to the surface of the combustion chamber inner wall of the combustion chamber 10 .
  • a region B is formed, in which significant mixing between cooler barrier air S and the combustion gases G has not yet taken place, so that, in addition, the film cooling properties of the injected barrier air S can be improved, with the result that the thermal load upon the combustion chamber walls can be reduced.
  • the damping properties of the Helmholtz resonators may, with the resonator volume otherwise being the same and with the number of resonator tubes kept constant, deviate from those of the Helmholtz resonators known from the prior art and having perpendicular injection, it is usually necessary for the damping properties of the resonator parameters to be adapted. This may take place, for example, by a variation in the number of resonator tubes 22 ′ and/or the delivery ports 23 and/or their diameters or by a change in the resonator volume 21 .
  • FIG. 3 illustrates the case where Helmholtz resonators of a different type are arranged in different axial positions of the combustion chamber.
  • the variant illustrated here is aimed at injecting part of the barrier air S as far upstream as possible, that is to say in the direction of the heat release zone (resonator type 1), and at injecting part of the barrier air S as far downstream as possible (resonator type 2).
  • the Helmholtz resonators of type 1 arranged on a first ring around the tubular combustion chamber have resonator tubes 22 ′′, the axes A of which are inclined at an angle ⁇ in the upstream direction to the normal N to the surface of the combustion chamber inner wall
  • the Helmholtz resonators of type 2 arranged in a second ring have resonator tubes 22 ′, the axes A of which are inclined at an angle ⁇ in the downstream direction to the surface normal N.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
US14/240,549 2011-09-01 2012-08-14 Combustion chamber for a gas turbine plant Abandoned US20140345282A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102011081963.0 2011-09-01
DE102011081963 2011-09-01
PCT/EP2012/065856 WO2013029984A2 (de) 2011-09-01 2012-08-14 Brennkammer für eine gasturbinenanlage

Publications (1)

Publication Number Publication Date
US20140345282A1 true US20140345282A1 (en) 2014-11-27

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US14/240,549 Abandoned US20140345282A1 (en) 2011-09-01 2012-08-14 Combustion chamber for a gas turbine plant

Country Status (4)

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US (1) US20140345282A1 (zh)
EP (1) EP2732215A2 (zh)
CN (1) CN103765107B (zh)
WO (1) WO2013029984A2 (zh)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150020498A1 (en) * 2013-07-19 2015-01-22 Reinhard Schilp Cooling cover for gas turbine damping resonator
US20150113992A1 (en) * 2013-10-28 2015-04-30 Alstom Technology Ltd Damper for gas turbine
US20170299182A1 (en) * 2014-09-25 2017-10-19 Mitsubishi Hitachi Power Systems, Ltd. Combustor and gas turbine comprising same
WO2018173659A1 (ja) * 2017-03-24 2018-09-27 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器の共鳴吸音装置並びにこれを備えたガスタービン燃焼器及びガスタービン
US10359194B2 (en) * 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
US10788211B2 (en) 2015-01-23 2020-09-29 Siemens Aktiengesellschaft Combustion chamber for a gas turbine engine
KR20210080625A (ko) * 2016-03-03 2021-06-30 미츠비시 파워 가부시키가이샤 음향 장치, 가스 터빈

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115682033A (zh) * 2021-07-28 2023-02-03 北京航空航天大学 防振燃烧室以及燃烧室防振方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US20060053798A1 (en) * 2004-09-10 2006-03-16 Honeywell International Inc. Waffled impingement effusion method
US20070169992A1 (en) * 2006-01-25 2007-07-26 Siemens Power Generation, Inc. Acoustic resonator with impingement cooling tubes
US20070271925A1 (en) * 2006-05-26 2007-11-29 Pratt & Whitney Canada Corp. Combustor with improved swirl
US20110138812A1 (en) * 2009-12-15 2011-06-16 Johnson Clifford E Resonator System for Turbine Engines

Family Cites Families (5)

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Publication number Priority date Publication date Assignee Title
EP0576717A1 (de) * 1992-07-03 1994-01-05 Abb Research Ltd. Gasturbinen-Brennkammer
US6530221B1 (en) 2000-09-21 2003-03-11 Siemens Westinghouse Power Corporation Modular resonators for suppressing combustion instabilities in gas turbine power plants
JP3962554B2 (ja) * 2001-04-19 2007-08-22 三菱重工業株式会社 ガスタービン燃焼器及びガスタービン
EP1423645B1 (de) * 2001-09-07 2008-10-08 Alstom Technology Ltd Dämpfungsanordnung zur reduzierung von brennkammerpulsationen in einer gasturbinenanlage
EP1605209B1 (de) 2004-06-07 2010-08-04 Siemens Aktiengesellschaft Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US20060053798A1 (en) * 2004-09-10 2006-03-16 Honeywell International Inc. Waffled impingement effusion method
US20070169992A1 (en) * 2006-01-25 2007-07-26 Siemens Power Generation, Inc. Acoustic resonator with impingement cooling tubes
US20070271925A1 (en) * 2006-05-26 2007-11-29 Pratt & Whitney Canada Corp. Combustor with improved swirl
US20110138812A1 (en) * 2009-12-15 2011-06-16 Johnson Clifford E Resonator System for Turbine Engines

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9410484B2 (en) * 2013-07-19 2016-08-09 Siemens Aktiengesellschaft Cooling chamber for upstream weld of damping resonator on turbine component
US20150020498A1 (en) * 2013-07-19 2015-01-22 Reinhard Schilp Cooling cover for gas turbine damping resonator
US20150113992A1 (en) * 2013-10-28 2015-04-30 Alstom Technology Ltd Damper for gas turbine
US10036327B2 (en) * 2013-10-28 2018-07-31 Ansaldo Energia Switzerland AG Damper with bent neck for gas turbine
US10359194B2 (en) * 2014-08-26 2019-07-23 Siemens Energy, Inc. Film cooling hole arrangement for acoustic resonators in gas turbine engines
US20170299182A1 (en) * 2014-09-25 2017-10-19 Mitsubishi Hitachi Power Systems, Ltd. Combustor and gas turbine comprising same
US10788211B2 (en) 2015-01-23 2020-09-29 Siemens Aktiengesellschaft Combustion chamber for a gas turbine engine
KR20210080625A (ko) * 2016-03-03 2021-06-30 미츠비시 파워 가부시키가이샤 음향 장치, 가스 터빈
KR102336086B1 (ko) 2016-03-03 2021-12-06 미츠비시 파워 가부시키가이샤 음향 장치, 가스 터빈
US11261794B2 (en) * 2016-03-03 2022-03-01 Mitsubishi Power, Ltd. Acoustic device and gas turbine
DE112017001100B4 (de) 2016-03-03 2024-05-08 Mitsubishi Heavy Industries, Ltd. Akustische vorrichtung und gasturbine
JP2018159533A (ja) * 2017-03-24 2018-10-11 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器の共鳴吸音装置並びにこれを備えたガスタービン燃焼器及びガスタービン
WO2018173659A1 (ja) * 2017-03-24 2018-09-27 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器の共鳴吸音装置並びにこれを備えたガスタービン燃焼器及びガスタービン
US11326780B2 (en) 2017-03-24 2022-05-10 Mitsubishi Power, Ltd. Resonant sound absorbing device of gas turbine combustor, gas turbine combustor including the same, and gas turbine
DE112018001583B4 (de) 2017-03-24 2022-11-24 Mitsubishi Heavy Industries, Ltd. Gasturbinenbrenner mit resonanzschallabsorptionsvorrichtung, gasturbine und betriebsverfahren einer gasturbine

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CN103765107A (zh) 2014-04-30
WO2013029984A2 (de) 2013-03-07
CN103765107B (zh) 2016-05-04
WO2013029984A3 (de) 2013-12-27
EP2732215A2 (de) 2014-05-21

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