EP1255074A1 - Diminution des oscillations dans une chambre de combustion - Google Patents

Diminution des oscillations dans une chambre de combustion Download PDF

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Publication number
EP1255074A1
EP1255074A1 EP01810429A EP01810429A EP1255074A1 EP 1255074 A1 EP1255074 A1 EP 1255074A1 EP 01810429 A EP01810429 A EP 01810429A EP 01810429 A EP01810429 A EP 01810429A EP 1255074 A1 EP1255074 A1 EP 1255074A1
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EP
European Patent Office
Prior art keywords
burners
kgv
combustion chamber
modulatable
modulated
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
EP01810429A
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German (de)
English (en)
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EP1255074B1 (fr
Inventor
Wolfgang Weisenstein
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General Electric Technology GmbH
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ABB Schweiz AG
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Publication date
Application filed by ABB Schweiz AG filed Critical ABB Schweiz AG
Priority to DE50108163T priority Critical patent/DE50108163D1/de
Priority to EP01810429A priority patent/EP1255074B1/fr
Priority to US10/132,152 priority patent/US6595002B2/en
Publication of EP1255074A1 publication Critical patent/EP1255074A1/fr
Application granted granted Critical
Publication of EP1255074B1 publication Critical patent/EP1255074B1/fr
Anticipated expiration legal-status Critical
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the invention relates to the field of thermal turbomachinery. It relates to a combustion chamber and a method for reduction thermoacoustic vibrations in a combustion chamber according to the generic term of claims 1 and 9.
  • thermoacoustic vibrations A well-known method for suppressing thermoacoustic vibrations is an installation of so-called Helmholtz resonators, as in “Technical Akustik ", Ivar Veit, Vogel Buchverlag, 1996, page 84
  • Helmholtz resonators have the disadvantage that they are only for one predetermined frequency are designed, and that with the emergence of further Pulsations with other frequencies further, for these frequencies designed resonators must be installed.
  • the combustion chamber according to the invention therefore has a number b0 of annular arranged burners, of which a number k of modulatable Burners have means for modulating a fuel mass flow, where k ⁇ b0 and the modulatable burners are arranged in such a way that between two modulatable burners each a1, a2, ... ak not modulable Burner are arranged, and that the values a1 + 1, a2 + 1, ..., ak + 1 are not integer divisors of b0.
  • the number k of modulatable burners is at least three.
  • the a1, a2, ... ak are different from each other.
  • distances between modulatable burners are also taken into account, between which exactly one modulatable burner is arranged:
  • the modulatable burners are thus arranged such that a greatest value of kgV (b0, a1 + 1), kgV (b0, a2 + 1), ... kgV (b0, ak + 1), kgV (b0, a1 + a2 + 2), kgV (b0, a2 + a3 + 2), ... kgV (b0, ak + a1 + 2) is maximum.
  • thermoacoustic vibrations in an annular combustion chamber with several annularly arranged Burners of which several are modular burners means of modulation have a fuel mass flow, the number of burners b0, the number of modulable burners is k Fuel mass flow modulated, this modulated burner in such a way are arranged so that between two modulated burners each a1, a2, ... ak non-modulated burners are arranged, and the distances between the burners a1 + 1, a2 + 1, ..., ak + 1 are not integer divisors of b0.
  • the method according to the invention allows in a combustion chamber which with is equipped with several modulatable burners, a damping of combustion pulsations to effect. In a preferred variant of the invention this is done by using constant modulation frequencies, so that in the operation of the combustion chamber no measurement of pulsations and one complex regulations are required.
  • Figure 1 shows schematically an annular arrangement of burners Ring combustion chamber with 24 burners. Burners are schematically represented by circles shown, modulatable burner 1,2,3 are by circles with a cross shown.
  • the combustion chamber is part of a thermal turbo machine or Turbomachine, in particular an industrial gas turbine.
  • the combustion chamber is preferably an annular or an annular tube combustion chamber this means that your combustion chamber encloses a rotor of the gas turbine.
  • a burner or single burner is a system for Fuel supply, for introducing the fuel into a working medium, for mixing the fuel with the working medium and if necessary understood to stabilize a flame.
  • Functions include a burner, for example a flame tube, an arrangement for swirl stabilization of the flame or a fuel lance.
  • a modulatable burner 1,2,3 becomes a means of modulating the fuel mass flow also considered part of the burner.
  • a modulatable burner 1, 2, 3 has, for example, a main valve and as Modulation means on a modulation valve connected in parallel, which feed the fuel mass flow to the burner. It will Main valve set to a mass flow that is below a nominal mass flow of the burner. With the modulation valve, an additional, periodically modulated with an excitation frequency of 0.1 to 1000 Hz, Mass flow added, so that the total mass flow of the burner periodically around an average value of the nominal mass flow fluctuates. As a result, the combustion process in the combustion chamber becomes too a periodic fluctuation which is harmless itself, however the periodic caused by disturbing combustion fluctuations Pressure fluctuations withdraw energy so that they are damped. With small fuel mass flows, fuel modulation can also through a single suitable fuel valve per modulated burner happen.
  • the nominal mass flow of the fuel is determined by a superimposed control the gas turbine specified, for example, power, speed and / or regulates and monitors the temperatures of the gas turbine.
  • burners have common main valve, and have individual modular burners 1,2,3 each an associated modulation valve for adding a modulated Mass flow.
  • only a part of the burners can be modulated, and the modulatable burners are arranged such that a1, a2,... Ak non-modulable between each pair of adjacent modulatable burners Burner are arranged, and that the values a1 + 1, a2 + 1, ..., ak + 1 are not integer divisors of b0.
  • a largest value is kgV (b0, a1 + 1), kgV (b0, a2 + 1), ... kgV (b0, ak + 1) maximum, where kgV is the smallest common multiple.
  • the sum a1 + a2 + ... + ak + k is always b0.
  • the smallest common multiples of ⁇ b0, a1 + 1 ⁇ , ⁇ b0, a2 + 1 ⁇ , ⁇ b0, a3 + 1 ⁇ are here 120, 72 and 120. The largest of these values is therefore 120.
  • Azimuthal acoustic Vibrations always propagate in such combustion modes in ring combustion chambers from the fact that one or more pressure knots appear on such burners, the due to uncontrollable flow processes over a for this have a suitable flow field. The fashion that emerges will due to the mostly symmetrical for mechanical engineering reasons Arrangement of the burner determined.
  • the possible instability frequencies result resulting from the combustion chamber azimuth, which is the length of a solid wave corresponds, or their integer divisors and multiples. Usually turns out a mode whose vibration processes are completely on 360 ° of the combustion chamber azimuth run.
  • an azimuthal thermoacoustic oscillation can occur in an annular combustion chamber also spread in a fashion that the pressure vibration runs around more than 360 ° around the azimuth of the combustion chamber, until a pressure knot has to be established again.
  • the sense of the invention represents the smallest common multiple here a minimal run length, measured in a number of burner diameters, an adjusting one Pressure oscillation, after which there is again a pressure node can adjust. Because long wavelengths naturally require less energy, have a lower pressure amplitude here, the sense of the invention, the sustainable reduction of pressure fluctuation amplitudes, and so on can be achieved better, the larger the smallest common multiple.
  • the invention works as follows: The first modular burner excited with a frequency that of a natural frequency of an azimuthal Vibration of the combustion chamber is different. This creates a vibration damped with this natural frequency and damage is avoided, that would be caused by this vibration. Is only a first modulatable Burner 1 is present, so this presence means one Asymmetry of the combustion chamber with otherwise unmodulated burners. This asymmetry usually leads to an azimuthal pulsation with a spatial wavelength, which is equal to the circumference of the combustion chamber and which modulated an oscillation node at the location of the first Has burner 1. This vibration is also called the (basic) mode of the called oscillatory system. Higher frequency modes have additional ones Vibration node, and its wavelength is an integer divisor the combustion chamber azimuths.
  • the pulsation caused by the first modulatable burner 1 to dampen, the second modulatable burner 2 is placed according to the invention. As a result, it is not in a node of the basic mode or one the first higher frequency modes.
  • the wavelength of the next mode, the can be influenced by the position of the first and second modular burner 1, 2 is twice the distance between the two modulatable Burners.
  • This next mode is achieved by placing the third modulable burner 3 damped. Depending on the exact geometric and physical conditions in the combustion chamber are remaining modes through the combustion chamber itself and without active Dampened.
  • Values of the parameters k, a1, a2, ... ak which meet one or more of the required conditions are determined heuristically or using non-linear or stochastic optimization methods.
  • the conditions are preferably checked by first checking the first condition according to the list above. If several combinations of values meet the first condition, those combinations of values are selected that also meet the second condition. If several combinations of values also meet the second condition, those combinations of values are selected that also meet the third condition. The procedure is continued analogously until only one optimal combination of values remains and / or all conditions are taken into account. In a variant of the invention, the fulfillment of the third condition is checked before the second condition is met.
  • Excitation frequencies for the modulable burners 1, 2, 3 are preferred different and chosen so that they are none of the present Stimulate vibration modes.
  • the excitation frequencies are therefore of natural frequencies of modes due to the arrangement of the modulated burner arise, different.
  • Typical frequencies of azimuthal thermoacoustic Combustion instabilities are in current annular combustion chambers at around 50 - 80 Hz.
  • the modulation frequency can be significantly lower should be selected and should be around 20 - 30 Hz for the example mentioned. Practical experience shows that about 5% of the fuel mass flow must be modulated to effectively suppress instability.
  • the excitation frequencies are based, for example, on calculations or measurements of natural frequencies during commissioning the turbine determines. These excitation frequencies once determined are the modulatable in a preferred embodiment of the invention Assigned to burners 1,2,3. In a gas turbine operation everyone will the modular burner 1,2,3 in an "open-loop" or uncontrolled Operation excited with the respective excitation frequency. It is not a measurement of pulsations and / or a special regulation for controlling the Modular burner 1,2,3 required due to measurements.
  • Figure 3 shows schematically an annular arrangement of burners Annular combustion chamber, with burners offset in the radial direction are. As long as this radial offset is relatively small, the arrangement will be treated like an arrangement without offset and become modular Burner 1,2,3 arranged as described above. If the radial Offset is larger, the arrangement can be two concentric annular Arrangements of burners are considered, as shown in Figure 4. In this embodiment of the invention, distances between modulatable Burners 1,2,34,5 for each of the two concentric arrangements determined individually. In a preferred embodiment of the invention the two concentric arrangements are at least approximately the same Distances between modulable burners 1,2,34,5, the arrangements are twisted against each other.
  • thermoacoustic Vibrations are arranged in a combustion chamber with several rings Burners, of which several are modular burners means of modulation have a fuel mass flow. Of the multiple, modular burners become individual, but not necessarily all modulated according to the invention. A distinction is therefore made between modulatable burners and actually modulated according to the invention Burners. According to the invention, a number k of the modulable Burner the fuel mass flow periodically modulated, this modulated burners are arranged such that between two modulated Burners are arranged per a1, a2, ... ak non-modulated burners, and a smallest common multiple of ⁇ b0, a1 + 1a2 + 1, ... ak + 1 ⁇ each is maximum.
  • the method according to the invention has the advantage that, for example, in a Gas turbine with modular burners to combat axial and / or helical combustion instabilities or for temperature control are equipped, in a simple manner also azimuthal vibrations can be dampened.
  • the modulation frequencies to combat the different instabilities are in similar frequency ranges different in individual cases. It is advantageous if by the choice of frequencies as different as possible the system Fuel / air supply combustion combustion chamber sustainably acoustic is out of tune.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP01810429A 2001-05-01 2001-05-01 Diminution des oscillations dans une chambre de combustion Expired - Lifetime EP1255074B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE50108163T DE50108163D1 (de) 2001-05-01 2001-05-01 Schwingungsreduktion in einer Brennkammer
EP01810429A EP1255074B1 (fr) 2001-05-01 2001-05-01 Diminution des oscillations dans une chambre de combustion
US10/132,152 US6595002B2 (en) 2001-05-01 2002-04-26 Vibration reduction in a combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01810429A EP1255074B1 (fr) 2001-05-01 2001-05-01 Diminution des oscillations dans une chambre de combustion

Publications (2)

Publication Number Publication Date
EP1255074A1 true EP1255074A1 (fr) 2002-11-06
EP1255074B1 EP1255074B1 (fr) 2005-11-23

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EP01810429A Expired - Lifetime EP1255074B1 (fr) 2001-05-01 2001-05-01 Diminution des oscillations dans une chambre de combustion

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US (1) US6595002B2 (fr)
EP (1) EP1255074B1 (fr)
DE (1) DE50108163D1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10325455A1 (de) * 2003-06-05 2004-12-30 Alstom Technology Ltd Verfahren zum Betrieb einer ringförmigen Brenneranordnung in einer Zwischenerhitzungsstufe einer mehrstufigen Verbrennungseinrichtung einer Gasturbine
WO2005093326A2 (fr) * 2004-03-29 2005-10-06 Alstom Technology Ltd Chambre a combustion de turbine a gaz et procede pour la faire fonctionner
DE102017201771A1 (de) 2017-02-03 2018-08-09 Siemens Aktiengesellschaft Umfangsstufungskonzept für eine Brenneranordnung

Families Citing this family (15)

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Publication number Priority date Publication date Assignee Title
US6986254B2 (en) * 2003-05-14 2006-01-17 Power Systems Mfg, Llc Method of operating a flamesheet combustor
US7568349B2 (en) * 2005-09-30 2009-08-04 General Electric Company Method for controlling combustion device dynamics
DE102006051286A1 (de) * 2006-10-26 2008-04-30 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennervorrichtung
EP1930569A1 (fr) * 2006-11-01 2008-06-11 ALSTOM Technology Ltd Système de contrôle d'une procédé de combustion pour une turbine à gaz
US8028512B2 (en) 2007-11-28 2011-10-04 Solar Turbines Inc. Active combustion control for a turbine engine
US8631656B2 (en) * 2008-03-31 2014-01-21 General Electric Company Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
US20100192578A1 (en) * 2009-01-30 2010-08-05 General Electric Company System and method for suppressing combustion instability in a turbomachine
US8650880B1 (en) 2009-02-13 2014-02-18 Jansen's Aircraft Systems Controls, Inc. Active combustion control for turbine engine
US8408004B2 (en) * 2009-06-16 2013-04-02 General Electric Company Resonator assembly for mitigating dynamics in gas turbines
US20110067377A1 (en) * 2009-09-18 2011-03-24 General Electric Company Gas turbine combustion dynamics control system
US9719685B2 (en) * 2011-12-20 2017-08-01 General Electric Company System and method for flame stabilization
US20150167980A1 (en) * 2013-12-18 2015-06-18 Jared M. Pent Axial stage injection dual frequency resonator for a combustor of a gas turbine engine
US9709279B2 (en) 2014-02-27 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9845956B2 (en) * 2014-04-09 2017-12-19 General Electric Company System and method for control of combustion dynamics in combustion system
CN106796032B (zh) * 2014-10-06 2019-07-09 西门子公司 用于阻抑高频燃烧动力状态下的振动模式的燃烧室和方法

Citations (3)

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EP0962704A2 (fr) * 1998-05-29 1999-12-08 United Technologies Corporation Procédé et dispositif pour fonctionner un brûleur à gaz
DE19849300A1 (de) * 1998-10-16 2000-04-20 Siemens Ag Verfahren und Anordnung zur Reduzierung der akustischen Energie benachbarter Brennquellen in Verbrennungsanlagen
US6202401B1 (en) * 1996-09-05 2001-03-20 Siemens Aktiengesellschaft Method and device for acoustic modulation of a flame produced by a hybrid burner

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WO1993010401A1 (fr) * 1991-11-15 1993-05-27 Siemens Aktiengesellschaft Dispositif permettant de supprimer les vibrations dues a la combustion dans une chambre de combustion d'une installation a turbine a gaz
DE19615910B4 (de) * 1996-04-22 2006-09-14 Alstom Brenneranordnung
DE19704540C1 (de) * 1997-02-06 1998-07-23 Siemens Ag Verfahren zur aktiven Dämpfung einer Verbrennungsschwingung und Verbrennungsvorrichtung
SE9802707L (sv) * 1998-08-11 2000-02-12 Abb Ab Brännkammaranordning och förfarande för att reducera inverkan av akustiska trycksvängningar i en brännkammaranordning
US20020157400A1 (en) * 2001-04-27 2002-10-31 Siemens Aktiengesellschaft Gas turbine with combined can-type and annular combustor and method of operating a gas turbine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6202401B1 (en) * 1996-09-05 2001-03-20 Siemens Aktiengesellschaft Method and device for acoustic modulation of a flame produced by a hybrid burner
EP0962704A2 (fr) * 1998-05-29 1999-12-08 United Technologies Corporation Procédé et dispositif pour fonctionner un brûleur à gaz
DE19849300A1 (de) * 1998-10-16 2000-04-20 Siemens Ag Verfahren und Anordnung zur Reduzierung der akustischen Energie benachbarter Brennquellen in Verbrennungsanlagen

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10325455A1 (de) * 2003-06-05 2004-12-30 Alstom Technology Ltd Verfahren zum Betrieb einer ringförmigen Brenneranordnung in einer Zwischenerhitzungsstufe einer mehrstufigen Verbrennungseinrichtung einer Gasturbine
WO2005093326A2 (fr) * 2004-03-29 2005-10-06 Alstom Technology Ltd Chambre a combustion de turbine a gaz et procede pour la faire fonctionner
WO2005093326A3 (fr) * 2004-03-29 2006-02-09 Alstom Technology Ltd Chambre a combustion de turbine a gaz et procede pour la faire fonctionner
DE102017201771A1 (de) 2017-02-03 2018-08-09 Siemens Aktiengesellschaft Umfangsstufungskonzept für eine Brenneranordnung
US11703218B2 (en) 2017-02-03 2023-07-18 Siemens Energy Global GmbH & Co. KG Burner arrangement having a peripheral staging concept

Also Published As

Publication number Publication date
US6595002B2 (en) 2003-07-22
EP1255074B1 (fr) 2005-11-23
US20020162336A1 (en) 2002-11-07
DE50108163D1 (de) 2005-12-29

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