EP1483536B1 - Turbine a gaz - Google Patents

Turbine a gaz Download PDF

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Publication number
EP1483536B1
EP1483536B1 EP03706564A EP03706564A EP1483536B1 EP 1483536 B1 EP1483536 B1 EP 1483536B1 EP 03706564 A EP03706564 A EP 03706564A EP 03706564 A EP03706564 A EP 03706564A EP 1483536 B1 EP1483536 B1 EP 1483536B1
Authority
EP
European Patent Office
Prior art keywords
resonator
combustion chamber
gas turbine
combustion
combustor
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.)
Expired - Lifetime
Application number
EP03706564A
Other languages
German (de)
English (en)
Other versions
EP1483536A1 (fr
Inventor
Patrick Flohr
Werner Krebs
Bernd Prade
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
Priority to ES03706564T priority Critical patent/ES2303892T3/es
Priority to EP03706564A priority patent/EP1483536B1/fr
Publication of EP1483536A1 publication Critical patent/EP1483536A1/fr
Application granted granted Critical
Publication of EP1483536B1 publication Critical patent/EP1483536B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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 gas turbine with a burner, which opens into a combustion chamber.
  • the combustion chamber is designed as an annular combustion chamber.
  • thermoacoustically induced combustion oscillations can occur. These arise through an interaction of the combustion flame and the associated heat release with acoustic pressure fluctuations.
  • acoustic excitation By means of an acoustic excitation, the position of the flame, the flame front surface or the mixture composition can fluctuate, which in turn leads to fluctuations of the heat release. With a constructive phase position, positive feedback and amplification can occur. Such an increased combustion vibration can lead to considerable noise and vibration damage.
  • thermoacoustically induced instabilities are significantly influenced by the acoustic properties of the combustion chamber and the boundary conditions present at the combustion chamber inlet and the combustion chamber outlet as well as at the combustion chamber walls.
  • the acoustic properties can be changed by installing Helmholtz resonators.
  • the WO 93/10401 A1 shows a device for suppressing combustion oscillations in a combustion chamber of a gas turbine plant.
  • a Helmholtz resonator is fluidly connected to a fuel supply line.
  • the acoustic properties of the supply line or the overall acoustic system are thereby changed so that combustion oscillations are suppressed.
  • this measure is not sufficient in all operating conditions, as it is also at a suppression of vibrations In the fuel line to combustion vibrations can come.
  • the US-A-6 058 709 proposes to avoid combustion oscillations to introduce fuel at axially different positions in the combustion channel of a burner.
  • constructive phase positions in the mixture composition are superimposed by destructive, so that overall there are lower fluctuations and thus a reduced tendency to form combustion oscillations.
  • this measure is comparatively expensive in comparison to the purely passive measure of the use of Helmholtz resonators.
  • a gas turbine combustor which has air-purged Helmholtz resonators in the burner.
  • the resonators are arranged alternately on the end face of the combustion chamber between the burners. By these resonators, vibration energy is absorbed by combustion vibrations occurring in the combustion chamber and the combustion vibrations are thereby damped.
  • a combustion chamber is disclosed with a resonator formed in the form of a cylindrical double sleeve, which is arranged concentrically between a combustion chamber housing and a combustion chamber liner.
  • the double sleeve is formed inter alia by an annular flange and the inner surface of the combustion chamber housing.
  • the object of the invention is to specify a gas turbine with a particularly low tendency to form combustion oscillations, wherein structural measures should be avoided on a combustion chamber wall.
  • This object is achieved by specifying a gas turbine having a combustion chamber and a burner opening into the combustion chamber at a burner mouth, wherein the burner mouth is annularly surrounded by a Helmholtz resonator and according to the invention the characterizing features of claim 1 are provided.
  • the Helmholtz resonator is placed around the mouth of a burner.
  • the attenuation of combustion oscillations by a resonator can lead to local temperature differences if the resonator acts unevenly on the combustion area. This is avoided by the symmetrical, annular arrangement around the burner flame.
  • the consequent temperature uniformity increases the damping effect and at the same time leads to a reduction of the formation of nitrogen oxides.
  • by the arrangement of the resonator immediately around the flame around can be acted intensively directly on the place of the highest heat release. Also, this improved contact with the main source of combustion vibrations increases the effect of the resonator.
  • the Helmholtz resonator preferably has a resonator volume and opens at a resonator opening into the combustion chamber, the resonator mouth having a small tube continuing into the resonator volume. More preferably, the resonator mouth is formed by a plurality of openings which are each continued via a tube into the resonator volume. The tubes thus protrude into the resonator volume.
  • a resonator consists of a volume V and holes of a certain length I and cross section A.
  • the outer dimensions of the resonator and thus the burner insert and the open total cross-sectional area need not be changed.
  • the tube or tubes are curved or twisted so that the tube length is increased without falling below a minimum distance to the resonator wall.
  • the resonator volume is adjustable, for example by a piston-like displacement of a resonator wall.
  • the acoustic properties, in particular the impedance can be adjusted and adjusted.
  • the combustion chamber is designed as an annular combustion chamber. Especially in annular combustion chambers combustion oscillations can lead to very disturbing and damaging combustion oscillations by a comparatively large combustion chamber volume and burners coupled together. In addition, the acoustic properties of such a combustion chamber are difficult to calculate.
  • the Helmholtz resonator is integrated in a burner insert, wherein the burner is connected to the burner via the burner insert.
  • the burner insert can be a separate component, which is bolted to the combustion chamber wall, for example, and in the then the actual burner is used. But it can also be connected to the burner, so that, for example, the burner insert forms a flange on the burner, with which the burner is connected to the combustion chamber wall.
  • the Helmholtz resonator is formed through air.
  • the impedance of the resonator can be changed and adjusted in a simple manner.
  • a cooling of the resonator and in the case of integration of the resonator in the burner insert a cooling of the entire burner insert is achieved.
  • FIG. 1 a gas turbine 51 is shown.
  • the gas turbine 51 has a compressor 53, an annular combustion chamber 55 and a turbine part 57. Air 58 from the environment is fed to the compressor 53 where it is compressed to combustion air 9 high. Subsequently, the combustion air 9 of the annular combustion chamber 55 is supplied. About gas turbine burner 1 is burned there with fuel 11 to a hot gas 59. The hot gas 59 drives the turbine part 57.
  • annular combustion chamber 55 may, for reasons described above, for the formation of combustion vibrations come that can significantly affect the operation of the gas turbine 51.
  • Helmholtz resonators may be used to dampen such combustion oscillations, with a particularly effective design being described below:
  • FIG. 2 a gas turbine combustor 1 is shown, which is connected via a burner insert 2 with a combustion chamber wall 56 of a combustion chamber 55 and opens at a burner port 4 into the combustion chamber 55.
  • a burner channel 3 of the gas turbine burner 1 surrounds a central channel 41 as an annular channel 30.
  • the annular channel 30 is designed as a premixing channel in which fuel 11 and combustion air 9 are intensively mixed prior to combustion. This is called pre-mixed combustion.
  • the fuel 11 is introduced via hollow swirl blades 13 in the annular channel 30.
  • the central channel 41 opens into the combustion zone 27 together with a central fuel lance 45, the fuel, in particular oil, via a swirl nozzle 47 supplies.
  • fuel 11 and combustion air 9 are first mixed in the combustion zone 27 and it is called a diffusion combustion.
  • fuel 11, in particular natural gas can also be added via a fuel inlet 43 into the central channel 41 upstream of the combustion zone 27.
  • the Helmholtz resonator 19 surrounds the burner mouth 4 annular.
  • the annular enclosure of the burner opening 4 through the resonator 19 leads to a uniform action on the combustion zone 27. This does not lead to temperature irregularities through the resonator 19.
  • the Resonator 19 is very effective immediately on the zone of maximum heat release.
  • the tubes 61 allow a comparatively small size for the resonator 19 so that it can be integrated into the burner insert 2. Air is introduced into the resonator 19 via air inlets 63, so that this can be adapted on the one hand in terms of its impedance, and on the other hand can also be cooled.

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)

Claims (9)

  1. Turbine (51) à gaz comprenant une chambre de combustion (55) et un brûleur (1) débouchant dans la chambre de combustion (55) sur une embouchure (4) de brûleur, dans laquelle l'embouchure (4) de brûleur est entourée annulairement d'un résonateur (19) de Helmholtz,
    caractérisée en ce que le résonateur (19) de Helmholtz est intégré dans un insert (2) de brûleur, le brûleur (1) étant relié à la chambre de combustion (55) par l'insert (2) de brûleur.
  2. Turbine à gaz suivant la revendication 1, dans laquelle le résonateur (19) de Helmholtz a un volume (23) de résonateur et débouche dans la chambre de combustion (55) sur une embouchure (21) de résonateur, l'embouchure (21) de résonateur se poursuivant par un petit tube (61) dans le volume (23) de résonateur.
  3. Turbine (51) à gaz suivant la revendication 2, dans laquelle le petit tube (61) est courbé ou tordu.
  4. Turbine (51) à gaz suivant la revendication 2 ou 3, dans laquelle le volume (23) de résonateur est réglable.
  5. Turbine (51) à gaz suivant l'une des revendications précédentes, dans laquelle la chambre de combustion (55) est constituée sous la forme d'une chambre de combustion annulaire.
  6. Turbine (51) suivant l'une des revendications 1 à 5, dans laquelle l'insert (2) de brûleur est un élément constitutif propre dans lequel le brûleur (1) est inséré.
  7. Turbine (51) suivant la revendication 6, dans laquelle l'insert (2) de brûleur est vissé à une paroi (56) de la chambre de combustion.
  8. Turbine (51) suivant les revendications 1 à 5, dans laquelle l'insert (2) de brûleur forme un flasque sur le brûleur (1).
  9. Turbine (51) suivant l'une des revendications précédentes, dans laquelle le résonateur (19) de Helmholtz est constitué de manière à ce que de l'air puisse y passer.
EP03706564A 2002-03-07 2003-02-24 Turbine a gaz Expired - Lifetime EP1483536B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
ES03706564T ES2303892T3 (es) 2002-03-07 2003-02-24 Turbina de gas.
EP03706564A EP1483536B1 (fr) 2002-03-07 2003-02-24 Turbine a gaz

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP02005137 2002-03-07
EP02005137A EP1342953A1 (fr) 2002-03-07 2002-03-07 Turbine à gaz
PCT/EP2003/001862 WO2003074936A1 (fr) 2002-03-07 2003-02-24 Turbine a gaz
EP03706564A EP1483536B1 (fr) 2002-03-07 2003-02-24 Turbine a gaz

Publications (2)

Publication Number Publication Date
EP1483536A1 EP1483536A1 (fr) 2004-12-08
EP1483536B1 true EP1483536B1 (fr) 2008-04-23

Family

ID=27741145

Family Applications (2)

Application Number Title Priority Date Filing Date
EP02005137A Withdrawn EP1342953A1 (fr) 2002-03-07 2002-03-07 Turbine à gaz
EP03706564A Expired - Lifetime EP1483536B1 (fr) 2002-03-07 2003-02-24 Turbine a gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP02005137A Withdrawn EP1342953A1 (fr) 2002-03-07 2002-03-07 Turbine à gaz

Country Status (7)

Country Link
US (1) US7246493B2 (fr)
EP (2) EP1342953A1 (fr)
JP (1) JP4429730B2 (fr)
CN (1) CN1320314C (fr)
DE (1) DE50309686D1 (fr)
ES (1) ES2303892T3 (fr)
WO (1) WO2003074936A1 (fr)

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EP1493972A1 (fr) * 2003-07-04 2005-01-05 Siemens Aktiengesellschaft Ensemble de brûleur pour une turbine à gaz et turbine à gaz
US7272931B2 (en) * 2003-09-16 2007-09-25 General Electric Company Method and apparatus to decrease combustor acoustics
EP1645805A1 (fr) * 2004-10-11 2006-04-12 Siemens Aktiengesellschaft brûleur pour combustible fluide et procédé pour uriliser un tel brûleur
DE602005001611T2 (de) * 2005-02-04 2008-03-13 Enel Produzione S.P.A. Dämpfung von thermoakustischen Schwingungen in einer Gasturbinenbrennkammer mit ringförmiger Kammer
DE102005062284B4 (de) * 2005-12-24 2019-02-28 Ansaldo Energia Ip Uk Limited Brennkammer für eine Gasturbine
US7788926B2 (en) * 2006-08-18 2010-09-07 Siemens Energy, Inc. Resonator device at junction of combustor and combustion chamber
US9291104B2 (en) * 2007-11-21 2016-03-22 Mitsubishi Hitachi Power Systems, Ltd. Damping device and gas turbine combustor
US8516819B2 (en) 2008-07-16 2013-08-27 Siemens Energy, Inc. Forward-section resonator for high frequency dynamic damping
CH699322A1 (de) * 2008-08-14 2010-02-15 Alstom Technology Ltd Verfahren zum einstellen eines helmholtz-resonators sowie helmholtz-resonator zur durchführung des verfahrens.
EP2187125A1 (fr) * 2008-09-24 2010-05-19 Siemens Aktiengesellschaft Dispositif et procédé destinés à l'amortissement d'oscillations de combustion
US8336312B2 (en) * 2009-06-17 2012-12-25 Siemens Energy, Inc. Attenuation of combustion dynamics using a Herschel-Quincke filter
US8789372B2 (en) * 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator
US8474265B2 (en) * 2009-07-29 2013-07-02 General Electric Company Fuel nozzle for a turbine combustor, and methods of forming same
US20110209481A1 (en) * 2010-02-26 2011-09-01 General Electric Company Turbine Combustor End Cover
EP2383514A1 (fr) 2010-04-28 2011-11-02 Siemens Aktiengesellschaft Système de brûleur et procédé d'amortissement d'un tel système de brûleur
EP2383515B1 (fr) 2010-04-28 2013-06-19 Siemens Aktiengesellschaft Système de brûleur pour l'amortissement d'un tel système de brûleur
US9810081B2 (en) 2010-06-11 2017-11-07 Siemens Energy, Inc. Cooled conduit for conveying combustion gases
US8720204B2 (en) 2011-02-09 2014-05-13 Siemens Energy, Inc. Resonator system with enhanced combustor liner cooling
EP2642203A1 (fr) * 2012-03-20 2013-09-25 Alstom Technology Ltd Amortisseur de helmholtz annulaire
US9188342B2 (en) * 2012-03-21 2015-11-17 General Electric Company Systems and methods for dampening combustor dynamics in a micromixer
ITMI20122265A1 (it) * 2012-12-28 2014-06-29 Ansaldo Energia Spa Gruppo bruciatore per una turbina a gas provvisto di risonatore di helmholtz
US20150362189A1 (en) * 2014-06-13 2015-12-17 Siemens Aktiengesellschaft Burner system with resonator
WO2016032434A1 (fr) 2014-08-26 2016-03-03 Siemens Energy, Inc. Agencement de trous de refroidissement de film pour résonateurs acoustiques dans des moteurs à turbine à gaz
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
JP2020056542A (ja) * 2018-10-02 2020-04-09 川崎重工業株式会社 航空機用のアニュラ型ガスタービン燃焼器

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Also Published As

Publication number Publication date
CN1320314C (zh) 2007-06-06
US20050144950A1 (en) 2005-07-07
EP1483536A1 (fr) 2004-12-08
JP4429730B2 (ja) 2010-03-10
CN1639512A (zh) 2005-07-13
ES2303892T3 (es) 2008-09-01
EP1342953A1 (fr) 2003-09-10
JP2005527763A (ja) 2005-09-15
US7246493B2 (en) 2007-07-24
DE50309686D1 (de) 2008-06-05
WO2003074936A1 (fr) 2003-09-12

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