EP2732214A1 - Chambre de combustion pour une installation de turbine à gaz - Google Patents

Chambre de combustion pour une installation de turbine à gaz

Info

Publication number
EP2732214A1
EP2732214A1 EP12748203.2A EP12748203A EP2732214A1 EP 2732214 A1 EP2732214 A1 EP 2732214A1 EP 12748203 A EP12748203 A EP 12748203A EP 2732214 A1 EP2732214 A1 EP 2732214A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
resonator
wall
combustion
air
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.)
Ceased
Application number
EP12748203.2A
Other languages
German (de)
English (en)
Inventor
Bernd Prade
Jaap Van Kampen
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP2732214A1 publication Critical patent/EP2732214A1/fr
Ceased 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
    • F23R3/02—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
    • 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
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • Combustion chamber for a gas turbine system The invention relates to a combustor for a gas turbine plant according to the preamble of claim 1 and an ent ⁇ speaking formed gas turbine plant according to claim. 7
  • Gas turbine plants essentially consist of a compressor, a combustion chamber with burner and an expansion turbine. Intake air is compressed in the compressor before it is mixed with fuel in the combustion chamber, which is arranged downstream of the burner and arranged in the compressor plenum, and this mixture is burned.
  • the expansion turbine connected downstream of the combustion chamber then extracts thermal energy from the combustion exhaust gases produced in the burner and converts them into mechanical energy.
  • a with for drinks ⁇ cycle turbine couplable generator may convert this mechanical power to generate electricity in electrical energy.
  • thermoacoustically induced oscillations leading to an increased risk that thermoacoustically induced oscillations begin.
  • thermoacoustic oscillations in the combustion chamber pose a problem in the design and especially in the operation of gas turbine plants.
  • Helmholtz resonators consisting of at least one resonator tube and one resonator volume are used today for damping purposes.
  • Helmholtz resonators attenuate the amplitude of oscillations with the Helmholtz frequency as a function of the cross-sectional area and length of the resonator tube and of the resonator volume in certain frequency ranges.
  • Helmholtz resonators as damping devices for limiting thermoacoustic oscillations in combustion chambers are known, for example, from EP 1 605 209 A1 or US Pat
  • FIG 1 shows, for example, from US 2007/0125089 AI ⁇ be known array of Helmholtz resonators 20 on a ring of the combustion chamber 10 transverse to the flow direction.
  • the combustion chamber wall 10 is tubular and separates the combustion chamber 1 from the surrounding compressor plenum 2.
  • the openings 22 in the combustion chamber wall 10 between the resonator volume 21 and the combustion chamber 1 form the resonator tubes of the Helmholtz resonators.
  • Each Helmholtz resonator can - as shown in FIG 1 - have a plurality of resonator tubes or even a single Resonatorröhe.
  • ⁇ comes with it at any entry of the hot combustion gases from the combustion chamber 1 into the Helmholtz resonators 20, additional openings for the supply of barrier air are provided.
  • these are arranged to ⁇ -openings 23 on the resonator tubes 22 opposite wall of the resonator 21st
  • These openings 23 make it possible for compressed air S to flow from the compressor plenum 2 surrounding the combustion chamber into the resonator volume 21 and from there via the resonator tubes 22 into the combustion chamber 1, thereby blocking the penetration of hot combustion gases into the resonator tubes 22.
  • Helmholtz resonators with Sperr KunststoffZu exiten over the solid have the disadvantage that this, the Helmholtz resonator flowing through blocking air can reduce its damping properties so that it can lead to instability in the operation of the burner.
  • the Helmholtz resonator flowing through blocking air can reduce its damping properties so that it can lead to instability in the operation of the burner.
  • a certain sealing air velocity in the resonator tubes is not ⁇ agile to effect a secure barrier to the entering from the combustion chamber into the resonator combustion gases.
  • this type of sealing air supply requires an introduction of a large proportion of air from the Verêtrplenum, which then but not the actual
  • the object of the invention is to provide a combustion chamber embostel ⁇ len, which overcomes the disadvantages described above.
  • Blocking air flows over the resonator can be dispensed with the known from the prior art injection of sealing air through the Helmholtz resonator. Its damping Properties are thus no longer influenced by the air flowing through the sealing air, whereby a reliable damping thermoacoustic vibrations is achieved, which ultimately ⁇ Lich increases the life of the burner chamber and thus the entire gas turbine plant. In addition, less air is required from the Verêtrplenum in the invention designed according to the blocking air supply compared to the known embodiments, so that overall the NOx and CO emissions of the gas turbine plant will turn out lower.
  • FIG. 2 shows schematically a first embodiment according to the invention of a damping device
  • FIG. 3 shows schematically a second embodiment according to the invention of a damping device
  • FIG. 5 shows schematically a fourth embodiment of a damping device according to the invention.
  • the sealing air S is not performed by the damping device 20 according to the invention, but supply openings 23 'and / or 23''provided and aligned in the Brennschdung 10 that through the feed openings 23', 23 ''flowing sealing air S the resonator tube mouth M in the region of the combustion chamber inner wall almost like a film cooling flows over.
  • FIG. 2 shows a first embodiment in which the resonator tube openings M in the combustion chamber wall 10 are recessed away from the combustion chamber interior in a defined area 10 "in relation to the combustion chamber inner wall 10 ', and the feed opening 23' is aligned such that the blocking air S is almost parallel to the combustion air Flow direction of the combustion gases G is injected into the space between the surface 10 '' and the combustion chamber inner wall 10 'so that they completely overflows the recessed Resona ⁇ torröhrenmünditch M of the resonator tubes 22.
  • a barrier air film is formed which very effectively makes the penetration of hot air even with a small mass flow of blocking air
  • the axial effective range is limited by film cooling holes may as shown in FIG 3 indicates a second, the first Zuzhouöff ⁇ voltage 23 'opposite feed opening 23''be provided, which is oriented so that the sealing air S virtually In parallel to and opposite to the Flow direction of the combustion gases G is injected, so that even resonators with a larger extent in the flow direction can still be effectively blocked.
  • the combustion chamber wall 10 at the recessed surface 10 '' at the level of the internal comb ⁇ channel wall 10 'an overlap L with the recessed faces 10''on may also the extent of the resonators ⁇ factors are increased, without an additional gegenü ⁇ berridgede row barrier air holes is required.
  • the supply port is 23 'or other supply ports such as the feed shown in FIG 3 23''in the combustion chamber wall 10 are arranged as in FIG 5 that its axis A is inclined toward the Resonatorröh ⁇ renmündung M.
  • an additional impingement cooling of the resonator wall is achieved in addition to the blocking, which may be useful in particular in areas of the combustion chamber with a particularly high heat input into the combustion chamber wall.
  • FIG 2 to FIG 5 show various advantageous from ⁇ embossing, loosen the inventions to the invention idea and in combination, namely without the passage of sealing air through the damper an efficient and safe barrier against the ingress of hot gases from the combustion chamber individually or in to ensure the damping devices.
  • embodiments encompassed by the invention also include embodiments in which, unlike the embodiments shown, the purging air feeds are located so close to the resonator tube openings that they form a direct component of each of the resonator tube openings and are thus virtually integrated into each resonator tube mouth.

Abstract

L'invention concerne une chambre de combustion (1) pour une installation de turbine à gaz, dotée d'une paroi (10) traversée par des gaz de combustion en direction d'une turbine à cycle d'expansion montée en aval. La paroi (10) de la chambre de combustion comporte un dispositif d'amortissement (20) destiné à amortir des vibrations thermoacoustiques provoquées par les gaz de combustion. Le dispositif d'amortissement (20) comprend au moins un résonateur de Helmholtz, réalisé de sorte que son volume (21) vienne se placer sur la face, de la paroi de chambre de combustion (10), opposée à une paroi intérieure de chambre de combustion (10') et comporte au moins un tube de résonateur (22) coopérant avec le volume de résonateur (21) et débouchant par son embouchure de tube de résonateur (M) opposée au volume de résonateur (21) dans la paroi intérieure de chambre de combustion (10') dans la chambre de combustion (1). Au moins une ouverture d'alimentation (23, 23', 23'') permet d'introduire dans la chambre de combustion (1) l'air de blocage destiné à bloquer l'embouchure de tube de résonateur (M) partant d'un plénum de compresseur (2) entourant la chambre de combustion, d'un compresseur pouvant être monté en aval. La ou les premières ouvertures d'alimentation (23', 23'') sont disposées dans une zone de la paroi de chambre de combustion (10) à proximité de l'embouchure de tube de résonateur (M) du ou des tubes de résonateurs (22) et sont orientées de sorte que l'air de blocage (S) circulant à travers l'ouverture d'alimentation (23', 23'') s'écoule dans l'embouchure de résonateur (M).
EP12748203.2A 2011-09-01 2012-08-14 Chambre de combustion pour une installation de turbine à gaz Ceased EP2732214A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011081962A DE102011081962A1 (de) 2011-09-01 2011-09-01 Brennkammer für eine Gasturbinenanlage
PCT/EP2012/065849 WO2013029981A1 (fr) 2011-09-01 2012-08-14 Chambre de combustion pour une installation de turbine à gaz

Publications (1)

Publication Number Publication Date
EP2732214A1 true EP2732214A1 (fr) 2014-05-21

Family

ID=46690501

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12748203.2A Ceased EP2732214A1 (fr) 2011-09-01 2012-08-14 Chambre de combustion pour une installation de turbine à gaz

Country Status (6)

Country Link
US (1) US20140345283A1 (fr)
EP (1) EP2732214A1 (fr)
CN (1) CN103765105A (fr)
DE (1) DE102011081962A1 (fr)
RU (1) RU2014112332A (fr)
WO (1) WO2013029981A1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105008805A (zh) * 2013-02-28 2015-10-28 西门子公司 用于燃气轮机的减振设备、燃气轮机和用于衰减热声振动的方法
EP2913589B1 (fr) * 2014-02-28 2020-01-22 Ansaldo Energia Switzerland AG Dispositif d'amortissement acoustique pour chambres à écoulement rasant
CN104566477B (zh) * 2014-12-31 2019-02-01 北京华清燃气轮机与煤气化联合循环工程技术有限公司 用于燃气轮机火焰筒的调频装置及燃气轮机火焰筒
CN104595928B (zh) * 2015-01-23 2020-02-14 北京华清燃气轮机与煤气化联合循环工程技术有限公司 扩散燃烧室声学火焰筒
CN104676649A (zh) * 2015-02-05 2015-06-03 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种阻尼热声振荡声学火焰筒
WO2016135833A1 (fr) * 2015-02-23 2016-09-01 三菱重工業株式会社 Dispositif d'amortissement, chambre de combustion, et turbine à gaz
US10513984B2 (en) 2015-08-25 2019-12-24 General Electric Company System for suppressing acoustic noise within a gas turbine combustor
US10197275B2 (en) 2016-05-03 2019-02-05 General Electric Company High frequency acoustic damper for combustor liners
JP7289752B2 (ja) * 2019-08-01 2023-06-12 三菱重工業株式会社 音響減衰器、筒アッセンブリ、燃焼器、ガスタービン及び筒アッセンブリの製造方法

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4135603A (en) * 1976-08-19 1979-01-23 United Technologies Corporation Sound suppressor liners
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
US7832211B2 (en) * 2002-12-02 2010-11-16 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor and a gas turbine equipped therewith
JP2005076982A (ja) * 2003-08-29 2005-03-24 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
DE502004011481D1 (de) 2004-06-07 2010-09-16 Siemens Ag Brennkammer mit einer Dämpfungseinrichtung zur Dämpfung von thermoakustischen Schwingungen
DE102006026969A1 (de) * 2006-06-09 2007-12-13 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammerwand für eine mager-brennende Gasturbinenbrennkammer

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2013029981A1 *

Also Published As

Publication number Publication date
CN103765105A (zh) 2014-04-30
US20140345283A1 (en) 2014-11-27
RU2014112332A (ru) 2015-10-10
DE102011081962A1 (de) 2013-03-07
WO2013029981A1 (fr) 2013-03-07

Similar Documents

Publication Publication Date Title
WO2013029981A1 (fr) Chambre de combustion pour une installation de turbine à gaz
DE4316475C2 (de) Gasturbinen-Brennkammer
EP2732215A2 (fr) Chambre de combustion pour une installation de turbine à gaz
CH701454A2 (de) Brennerrohr-Strömungskonditionierer.
EP0985882B1 (fr) Amortissement des vibrations dans des combusteurs
DE102007042059A1 (de) Einspritzanordnung für eine Brennkammer
DE102014117621A1 (de) Brennstoffinjektor mit Vormisch-Pilotdüse
CH702172A2 (de) Brennkammer für eine Gasturbine ,mit verbesserter Kühlung.
DE102011018937A1 (de) Verbrennungsvorrichtung für eine Gasturbine
DE10058688A1 (de) Dämpferanordnung zur Reduktion von Brennkammerpulsationen
DE112008001448T5 (de) Kraftstoffinjektor mit Helmholtz-Resonatoren für einen Turbinenmotor
DE102011000879A1 (de) Angewinkelte Leitschaufeln in eriner Brennkammerströmungshülse
WO2003074936A1 (fr) Turbine a gaz
DE10254825A1 (de) Wassersprühvorrichtung für Gasturbinen
EP1429001A2 (fr) Silencieux d'admission pour turbines à gaz
DE102005062079A1 (de) Magervormischbrenner mit einer Zerstäuberlippe
EP1481195A1 (fr) Bruleur, procede de fonctionnement d'un bruleur et turbine a gaz
EP2500648B1 (fr) Chambre de combustion de turbines à gaz
WO2009109454A1 (fr) Procédé et ensemble brûleur servant à produire du gaz chaud et utilisation dudit procédé
EP1605209B1 (fr) Chambre de combustion avec dispositif d'amortissement des vibrations thermo-acoustiques
EP3132202A1 (fr) Élément de protection thermique par déviation
EP1934523B1 (fr) Chambre de combustion et turbine à gaz
EP2187125A1 (fr) Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
CH701138A2 (de) Drallkörper für einen Turbinenbrenner.
DE102004010620A1 (de) Verfahren zur wirksamen Nutzung von Kühlung zur akustischen Dämpfung von Brennkammerpulsationen sowie Brennkammer

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140213

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20150424

REG Reference to a national code

Ref country code: DE

Ref legal event code: R003

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN REFUSED

18R Application refused

Effective date: 20150907