EP2860451A1 - Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré - Google Patents

Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré Download PDF

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Publication number
EP2860451A1
EP2860451A1 EP13188229.2A EP13188229A EP2860451A1 EP 2860451 A1 EP2860451 A1 EP 2860451A1 EP 13188229 A EP13188229 A EP 13188229A EP 2860451 A1 EP2860451 A1 EP 2860451A1
Authority
EP
European Patent Office
Prior art keywords
chamber
dampers
acoustic
gas turbine
section
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.)
Withdrawn
Application number
EP13188229.2A
Other languages
German (de)
English (en)
Inventor
Mirko Ruben Bothien
Bruno Schuermans
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 Technology GmbH
Original Assignee
Alstom Technology 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 filed Critical Alstom Technology AG
Priority to EP13188229.2A priority Critical patent/EP2860451A1/fr
Priority to US14/510,501 priority patent/US20150101332A1/en
Priority to CN201410856317.5A priority patent/CN104676645A/zh
Publication of EP2860451A1 publication Critical patent/EP2860451A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • 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
    • 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 is related to the acoustic damping of combustions dynamics.
  • Combustion dynamics in the meaning of this application comprises pulsations, acoustic oscillations, pressure and velocity fluctuations and what is called in the everyday language noise.
  • the terms “combustions dynamics” and “noise” are sometimes used synonymously.
  • Combustion dynamics occur for example in gas turbines at different places or chambers, where combustion dynamics occur.
  • places or chambers are the combustor chamber, a mixing chamber, a plenum and air channels.
  • the term "chamber" is used and comprises all locations where combustion dynamics occur.
  • a gas for example a mixture of fuel and air or exhaust gas
  • Burning air and fuel in the combustion chamber causes further combustion dynamics.
  • acoustic damping devices like a Helmholtz resonator, a half-wave tube, a quarter-wave tube or other types of damping devices with or without flow through of gas.
  • acoustic damping devices have one or more resonance frequencies. If under operation of the gas turbine the combustions dynamics stimulate the resonance frequencies of the acoustic damping devices, the combustion dynamics are reduced or damped.
  • a chamber of a gas turbine with combustion dynamics comprising several acoustic dampers circumferentially being arranged around an opening of the chamber by arranging at least two acoustic dampers of the same type in one section of the chamber covering an angle of 60°.
  • the acoustic dampers are arranged in an annular ring around the opening.
  • dampers that are tuned to the same damping frequency, for example 90 Hz +- 2%, are of the same type.
  • Helmholtz dampers and quarter-wave dampers may be of the same type in the meaning of the claimed invention.
  • a further advantageous embodiment is characterized in that an angle between two adjacent acoustic dampers is equal to or greater than 10°.
  • Another advantageous embodiment is characterized in that in one section of the chamber at least six burners and uppermost ten burners are arranged.
  • these burners are selected from the group of dual fuel burners for gas turbines.
  • the applicable acoustic dampers are not restricted to Helmholtz dampers with one or more damping volumes but may be half-wave length dampers, quarter-wave length dampers and other acoustic dampers with one or more damping volumes.
  • the claimed invention may be applied to combustion chambers, mixing chambers, a plenum and/or air channels of a gas turbine.
  • Both figures illustrate a front view of a combustor chamber 10 of a gas turbine.
  • the combustor chamber 10 comprises an opening 12 covering a center angle of 360°. This center angle is divided in six sections 1, 2, 3, 4, 5, and 6 each covering an angle ⁇ of 60.
  • T1 for example may be tuned to a damping frequency of 90 Hz
  • T2 for example may be tuned to a damping frequency of 100 Hz and so on.
  • dual fuel burners B1 for gas turbines are arranged in each section 1, 2, 3, 4, 5, 6 in the annular ring 14 besides the several types of acoustic dampers T1, T2, T3, T4, T5 and T6.
  • acoustic dampers T1, T2, T3, T4, T5 and T6 are arranged in each section.
  • eight burners B1 are arranged in section 4 of figure 1 and figure 2 for example.
  • only one burner B1 is marked with an own reference numeral.
  • the sections 4, 5 and 6, each comprise in clockwise direction one T4-, T5-, T1- and T3-type damper.
  • each comprise in clockwise direction a T3, a T1-, a T3- and a T5-type damper.
  • each comprise in clockwise direction a T6, a T1-, a T6- and a T5-type damper.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Soundproofing, Sound Blocking, And Sound Damping (AREA)
  • Gas Burners (AREA)
EP13188229.2A 2013-10-11 2013-10-11 Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré Withdrawn EP2860451A1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13188229.2A EP2860451A1 (fr) 2013-10-11 2013-10-11 Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré
US14/510,501 US20150101332A1 (en) 2013-10-11 2014-10-09 Combustion chamber of a gas turbine with improved acoustic damping
CN201410856317.5A CN104676645A (zh) 2013-10-11 2014-10-10 具有改善的声阻尼的燃气涡轮燃烧室

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13188229.2A EP2860451A1 (fr) 2013-10-11 2013-10-11 Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré

Publications (1)

Publication Number Publication Date
EP2860451A1 true EP2860451A1 (fr) 2015-04-15

Family

ID=49354497

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13188229.2A Withdrawn EP2860451A1 (fr) 2013-10-11 2013-10-11 Chambre de combustion d'une turbine à gaz avec amortissement acoustique amélioré

Country Status (3)

Country Link
US (1) US20150101332A1 (fr)
EP (1) EP2860451A1 (fr)
CN (1) CN104676645A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10941939B2 (en) 2017-09-25 2021-03-09 General Electric Company Gas turbine assemblies and methods

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2016057009A1 (fr) * 2014-10-06 2016-04-14 Siemens Aktiengesellschaft Chambre de combustion et procédé d'amortissement de modes vibratoires sous une dynamique de combustion à haute fréquence
EP3760925A1 (fr) * 2019-07-01 2021-01-06 Ansaldo Energia Switzerland AG Amortisseur pour ensemble de chambre de combustion d'un ensemble de turbine à gaz, ensemble de chambre de combustion comportant ledit amortisseur et procédé de fabrication d'un amortisseur pour un ensemble de chambre de combustion

Citations (4)

* Cited by examiner, † Cited by third party
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US20070214796A1 (en) * 2006-03-17 2007-09-20 Siemens Power Generation, Inc. Monitoring health of a combustion dynamics sensing system
US20090241548A1 (en) * 2008-03-31 2009-10-01 Allen Michael Danis Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
US20100313568A1 (en) * 2009-06-16 2010-12-16 General Electric Company Resonator assembly for mitigating dynamics in gas turbines
US20110138812A1 (en) * 2009-12-15 2011-06-16 Johnson Clifford E Resonator System for Turbine Engines

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US6464489B1 (en) * 1997-11-24 2002-10-15 Alstom Method and apparatus for controlling thermoacoustic vibrations in a combustion system
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
JP2002317650A (ja) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
US7080514B2 (en) * 2003-08-15 2006-07-25 Siemens Power Generation,Inc. High frequency dynamics resonator assembly
US7413053B2 (en) * 2006-01-25 2008-08-19 Siemens Power Generation, Inc. Acoustic resonator with impingement cooling tubes
GB0610800D0 (en) * 2006-06-01 2006-07-12 Rolls Royce Plc Combustion chamber for a gas turbine engine
DE102006026969A1 (de) * 2006-06-09 2007-12-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer
US7788926B2 (en) * 2006-08-18 2010-09-07 Siemens Energy, Inc. Resonator device at junction of combustor and combustion chamber
US8146364B2 (en) * 2007-09-14 2012-04-03 Siemens Energy, Inc. Non-rectangular resonator devices providing enhanced liner cooling for combustion chamber
EP2119964B1 (fr) * 2008-05-15 2018-10-31 Ansaldo Energia IP UK Limited Procédé pour réduire les émissions d'une chambre à combustion
US9810081B2 (en) * 2010-06-11 2017-11-07 Siemens Energy, Inc. Cooled conduit for conveying combustion gases
US9546558B2 (en) * 2010-07-08 2017-01-17 Siemens Energy, Inc. Damping resonator with impingement cooling
US8973365B2 (en) * 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators
US8720204B2 (en) * 2011-02-09 2014-05-13 Siemens Energy, Inc. Resonator system with enhanced combustor liner cooling
US20130074471A1 (en) * 2011-09-22 2013-03-28 General Electric Company Turbine combustor and method for temperature control and damping a portion of a combustor
US9395082B2 (en) * 2011-09-23 2016-07-19 Siemens Aktiengesellschaft Combustor resonator section with an internal thermal barrier coating and method of fabricating the same
US9410484B2 (en) * 2013-07-19 2016-08-09 Siemens Aktiengesellschaft Cooling chamber for upstream weld of damping resonator on turbine component

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070214796A1 (en) * 2006-03-17 2007-09-20 Siemens Power Generation, Inc. Monitoring health of a combustion dynamics sensing system
US20090241548A1 (en) * 2008-03-31 2009-10-01 Allen Michael Danis Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
US20100313568A1 (en) * 2009-06-16 2010-12-16 General Electric Company Resonator assembly for mitigating dynamics in gas turbines
US20110138812A1 (en) * 2009-12-15 2011-06-16 Johnson Clifford E Resonator System for Turbine Engines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10941939B2 (en) 2017-09-25 2021-03-09 General Electric Company Gas turbine assemblies and methods
US11536457B2 (en) 2017-09-25 2022-12-27 General Electric Company Gas turbine assemblies and methods

Also Published As

Publication number Publication date
US20150101332A1 (en) 2015-04-16
CN104676645A (zh) 2015-06-03

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