EP1476699A1 - Chambre de combustion et dispositif d'amortissement destine a reduire des pulsations de chambre de combustion dans un systeme de turbines a gaz - Google Patents

Chambre de combustion et dispositif d'amortissement destine a reduire des pulsations de chambre de combustion dans un systeme de turbines a gaz

Info

Publication number
EP1476699A1
EP1476699A1 EP02782607A EP02782607A EP1476699A1 EP 1476699 A1 EP1476699 A1 EP 1476699A1 EP 02782607 A EP02782607 A EP 02782607A EP 02782607 A EP02782607 A EP 02782607A EP 1476699 A1 EP1476699 A1 EP 1476699A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
damping
helmholtz
damping volume
volume
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
EP02782607A
Other languages
German (de)
English (en)
Other versions
EP1476699B1 (fr
Inventor
Peter Graf
Stefan Tschirren
Helmar Wunderle
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
Publication of EP1476699A1 publication Critical patent/EP1476699A1/fr
Application granted granted Critical
Publication of EP1476699B1 publication Critical patent/EP1476699B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

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
    • F23R3/002—Wall structures
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement
    • 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

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a combustion chamber for a gas turbine according to the preamble of claim 1.
  • Such a combustion chamber is e.g. B. from EP-A1-0 597 138 or US-A-5,373,695 known.
  • thermoacoustic vibrations occurring in a combustion chamber are influenced in frequency and amplitude by the most varied geometrical and operating parameters of the combustion chamber, the vibrations to be expected in a new combustion chamber can only be predicted very inadequately. It may therefore be the case that the Helmholtz steamers used on the combustion chamber are not optimally matched to the vibrations actually occurring in the combustion chamber.
  • the object is achieved by the entirety of the features of claim 1.
  • the essence of the invention is that the Helmholtz steamer is designed such that its damping frequency is adjustable, in particular continuously adjustable. As a result, the damping can be easily adapted to the thermoacoustic behavior of the combustion chamber and optimized accordingly. An exchange of parts or entire dampers is not necessary, so that correspondingly large access options can be dispensed with.
  • the adjustability of the Helmholtz steamer eliminates the need to manufacture and keep differently configured dampers or damper parts for different resonance frequencies.
  • a preferred embodiment of the invention is characterized in that the damping volume of the Helmholtz damper can be changed continuously. This type of adjustability of the damping frequency can be implemented particularly simply and effectively.
  • Damping volume and a variable damping volume is divided and the damping volume is changed by changing the variable damping volume.
  • variable damping volume is preferably achieved in that the variable damping volume is limited on one side by a displaceable piston.
  • This configuration can be implemented very easily from the mechanical point of view and is reliable in operation and easy to operate.
  • a proven type of actuation is characterized in that an adjusting element, in particular in the form of a threaded rod, is arranged on the Helmholtz steamer, by means of which the piston can be displaced. Since the combustion chamber is arranged within a turbine housing, it is particularly advantageous for the actuation of the Helmholtz damper if the adjusting element can be operated through a closable access opening in the turbine housing.
  • the adjusting element can easily be designed so that only a small opening is required for its actuation, which does not require any significant changes on the turbine housing.
  • the damping effect of the Helmholtz damper is particularly high if, in the case of a combustion chamber which has a plurality of burners on its inlet side and which open into the combustion chamber, the at least one Helmholtz steamer is arranged on the inlet side in the immediate vicinity of the burners. If the combustion chamber is annular and the burners are arranged in concentric rings, the at least one Helmholtz steamer is preferably arranged between the rings.
  • FIG. 1 shows a detail in cross section of the inlet side of a gas turbine combustion chamber with two rings of double-cone burners and an adjustable Helmholtz steamer arranged between them according to a preferred exemplary embodiment of the invention
  • FIG. 2 shows an enlarged sectional view of the Helmholtz steamer from FIG. 1.
  • FIG. 1 shows a section in cross section of the inlet side of the combustion chamber of a gas turbine with two rings of double-cone burners and an adjustable Helmholtz steamer arranged between them, in accordance with a preferred exemplary embodiment of the invention.
  • the gas turbine 10 is enclosed by a gas turbine housing 11, within which there is a plenum 12 filled with compressed air.
  • the plenum 12 surrounds the combustion chamber 16, which is separated from the plenum 12 by a combustion chamber housing 13.
  • the arrangement of the combustion chamber 16 within the gas turbine 10 is essentially the same as that described in the document EP-A1-0 597 138 mentioned at the beginning.
  • the combustion chamber 16 is delimited on the inlet side by a front cover 26.
  • the combustion chamber 16 is of annular design and is equipped with burners 14, 15, which are designed in a known manner as double-cone burners and are arranged in rings around the axis of the gas turbine, as is disclosed in EP-A1-0 597 138.
  • the burners 14, 15 are arranged in corresponding openings in the front cover 26 and open into the combustion chamber 16.
  • Helmholtz steamers 17 are provided between the rings with the burners 14, 15.
  • the Helmholtz steamers 17 each have a damping volume 20, 21 that is composed of a fixed cylindrical damping volume 20 and a variable cylindrical damping volume 21.
  • the damping volume 20, 21 is connected to the combustion chamber 16 via a comparatively narrow connecting channel 18.
  • the arrangement of the connecting channel 18 and the damping volume 20, 21 forms a damping resonator, the resonance frequency of which is determined, among other things, by the size of the damping volume 20, 21.
  • the fixed damping volume 20 is selected such that the damping frequency which can be achieved thereby is close to the frequency of one of those in the combustion chamber 16. waiting thermoacoustic vibrations, and that with the addition of the variable damping volume 21, the possible range of variation of this frequency is covered. In this way, it is possible to tune the Helmholtz steamers 17 in a gas turbine which is to be put into operation exactly to the occurring, previously not exactly known vibration frequencies and thus to obtain optimal damping with the least possible means. It goes without saying that differently dimensioned Helmholtz steamers 17 can also be used in combination for damping different vibration frequencies.
  • variable damping volume 21 can in principle be achieved in different ways.
  • the configuration shown in FIGS. 1 and 2 in which the variable damping volume can be changed continuously by means of a piston 22 which is displaceable in volume, is particularly favorable for the adjustability.
  • the piston 22 is displaced in a particularly simple and safe manner via an adjusting element 23 in the form of a threaded rod which is rotatably mounted in a threaded hole 25 in the cover 24 and which closes off the variable volume 21 from the outside.
  • the piston 22 can also be fixedly connected to the adjusting element 23.
  • the setting is made by a thread in the cover 24, in which the adjusting element 23 is guided.
  • a slot can be provided on the outer end face of the adjusting element 23, in which the blade of a screwdriver can engage.
  • a comparatively small access opening 19 is provided for operating the adjusting element 23 on the turbine housing 11, aligned with the axis of rotation, which comprises a screwed-in, closable connecting piece.
  • adjusting element e.g. threaded rod

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Air Supply (AREA)
  • Fluid-Damping Devices (AREA)

Abstract

Selon l'invention, une chambre de combustion (16) d'une turbine à gaz (10) comporte au moins un amortisseur de Helmholtz (17) destiné à amortir des oscillations thermoacoustiques, dont le volume d'amortissement (20, 21) est connecté à la chambre de combustion (16) par l'intermédiaire d'un canal de connexion (18). Un amortissement optimal est obtenu simplement par mise en oeuvre d'un amortisseur de Helmholtz (17) dont la fréquence d'amortissement est réglable. Par ailleurs, le volume d'amortissement (20, 21) est divisé en un volume d'amortissement fixe (20) et un volume d'amortissement variable (21), le volume d'amortissement étant modifié par variation du volume d'amortissement variable (21).
EP02782607.2A 2002-01-16 2002-12-16 Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz Expired - Fee Related EP1476699B1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH672002 2002-01-16
CH67022002 2002-01-16
PCT/CH2002/000696 WO2003060381A1 (fr) 2002-01-16 2002-12-16 Chambre de combustion et dispositif d'amortissement destine a reduire des pulsations de chambre de combustion dans un systeme de turbines a gaz

Publications (2)

Publication Number Publication Date
EP1476699A1 true EP1476699A1 (fr) 2004-11-17
EP1476699B1 EP1476699B1 (fr) 2013-11-13

Family

ID=4313973

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02782607.2A Expired - Fee Related EP1476699B1 (fr) 2002-01-16 2002-12-16 Chambre de combustion et dispositif d'amortissement destiné a reduire des pulsations de chambre de combustion dans un système de turbines a gaz

Country Status (5)

Country Link
US (1) US7331182B2 (fr)
EP (1) EP1476699B1 (fr)
CN (1) CN100523615C (fr)
AU (1) AU2002347185A1 (fr)
WO (1) WO2003060381A1 (fr)

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EP1596130B1 (fr) 2004-05-14 2014-12-31 Siemens Aktiengesellschaft Appareil pour absorber les oscillations thermo-acoustiques dans une chambre de combustion, présentant une fréquence de résonance variable
DE102005035085B4 (de) * 2005-07-20 2014-01-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verfahren zur Einstellung der akustischen Eigenschaften einer Brennkammer
FR2901578B1 (fr) * 2006-05-23 2008-07-25 Snecma Sa Corps central pour canal d'echappement d'un turboreacteur, turboreacteur
GB0610800D0 (en) * 2006-06-01 2006-07-12 Rolls Royce Plc Combustion chamber for a gas turbine engine
GB2443838B (en) * 2006-11-16 2009-01-28 Rolls Royce Plc Combustion control for a gas turbine
GB0708459D0 (en) * 2007-05-02 2007-06-06 Rolls Royce Plc A temperature controlling arrangement
US8127546B2 (en) * 2007-05-31 2012-03-06 Solar Turbines Inc. Turbine engine fuel injector with helmholtz resonators
JP4981615B2 (ja) * 2007-10-19 2012-07-25 三菱重工業株式会社 ガスタービン
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US8789372B2 (en) * 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator
RU2508506C2 (ru) * 2009-09-01 2014-02-27 Дженерал Электрик Компани Способ и установка для ввода текучей среды в камеру сгорания газотурбинного двигателя
CH702594A1 (de) 2010-01-28 2011-07-29 Alstom Technology Ltd Helmholtzdämpfer für den Einbau in die Brennkammer einer Gasturbine sowie Verfahren zum Einbau eines solchen Helmholtzdämpfers.
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EP2397760B1 (fr) 2010-06-16 2020-11-18 Ansaldo Energia IP UK Limited Agencement d'amortisseur et procédé pour le concevoir
US8973365B2 (en) 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators
US20140311156A1 (en) * 2011-09-22 2014-10-23 General Electric Company Combustor cap for damping low frequency dynamics
US9188340B2 (en) * 2011-11-18 2015-11-17 General Electric Company Gas turbine combustor endcover with adjustable flow restrictor and related method
EP2642204A1 (fr) * 2012-03-21 2013-09-25 Alstom Technology Ltd Amortissement à large bande simultanée à de multiples emplacements dans une chambre de combustion
RU2561956C2 (ru) * 2012-07-09 2015-09-10 Альстом Текнолоджи Лтд Газотурбинная система сгорания
ITMI20122265A1 (it) * 2012-12-28 2014-06-29 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas provvisto di risonatore di helmholtz
US20140216038A1 (en) * 2013-02-06 2014-08-07 General Electric Company Variable Volume Combustor with Cantilevered Support Structure
EP2962039A1 (fr) * 2013-02-28 2016-01-06 Siemens Aktiengesellschaft Dispositif d'amortissement pour une turbine à gaz, turbine à gaz et procédé permettant d'amortir des vibrations thermoacoustiques
US9400108B2 (en) 2013-05-14 2016-07-26 Siemens Aktiengesellschaft Acoustic damping system for a combustor of a gas turbine engine
EP2816289B1 (fr) 2013-05-24 2020-10-07 Ansaldo Energia IP UK Limited Amortisseur pour turbines à gaz
US9709279B2 (en) 2014-02-27 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9709278B2 (en) 2014-03-12 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9644846B2 (en) * 2014-04-08 2017-05-09 General Electric Company Systems and methods for control of combustion dynamics and modal coupling in gas turbine engine
US9845956B2 (en) 2014-04-09 2017-12-19 General Electric Company System and method for control of combustion dynamics in combustion system
US9845732B2 (en) 2014-05-28 2017-12-19 General Electric Company Systems and methods for variation of injectors for coherence reduction in combustion system
US10113747B2 (en) 2015-04-15 2018-10-30 General Electric Company Systems and methods for control of combustion dynamics in combustion system
US10221769B2 (en) * 2016-12-02 2019-03-05 General Electric Company System and apparatus for gas turbine combustor inner cap and extended resonating tubes
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Also Published As

Publication number Publication date
CN100523615C (zh) 2009-08-05
WO2003060381A1 (fr) 2003-07-24
AU2002347185A1 (en) 2003-07-30
EP1476699B1 (fr) 2013-11-13
US20050103018A1 (en) 2005-05-19
US7331182B2 (en) 2008-02-19
CN1615416A (zh) 2005-05-11

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