WO2004109188A1 - Procede permettant de faire fonctionner un dispositif bruleur annulaire dans un etage de rechauffement intermediaire d'un dispositif de combustion a plusieurs etages d'une turbine a gaz - Google Patents

Procede permettant de faire fonctionner un dispositif bruleur annulaire dans un etage de rechauffement intermediaire d'un dispositif de combustion a plusieurs etages d'une turbine a gaz Download PDF

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Publication number
WO2004109188A1
WO2004109188A1 PCT/EP2004/051013 EP2004051013W WO2004109188A1 WO 2004109188 A1 WO2004109188 A1 WO 2004109188A1 EP 2004051013 W EP2004051013 W EP 2004051013W WO 2004109188 A1 WO2004109188 A1 WO 2004109188A1
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WO
WIPO (PCT)
Prior art keywords
burners
burner arrangement
burner
unstable
annular
Prior art date
Application number
PCT/EP2004/051013
Other languages
German (de)
English (en)
Inventor
Peter Flohr
Alexander Ni
Christian Oliver Paschereit
Rajeshriben Patel
Majed Toqan
Original Assignee
Alstom Technology Ltd
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 Ltd filed Critical Alstom Technology Ltd
Publication of WO2004109188A1 publication Critical patent/WO2004109188A1/fr

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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
    • 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 burner assemblies for gas turbines. It relates to a method for operating an annular Bre ⁇ ner arrangement according to the preamble of claim 1.
  • a second combustion zone is created by injecting fuel into a high speed flow of contaminated air exiting a first turbine stage.
  • Such high-speed flows into a flue gas Combustion chambers are often susceptible to high-frequency instabilities that can generate high-amplitude pulsations.
  • the suppression of such pressure pulsations is crucial for maintaining the quality of the combustion process and for avoiding deterioration of the burner structure. It has also been found that the excitation of such high-frequency instabilities is sensitive to slight changes in the operating point (such as changes in mass flow or temperature), so that the type of combustion can quickly change from stable to unstable during operation of the machine.
  • DE-A1-199 39235 describes a method for operating a combustion device of a gas turbine, in which a plurality of burners of the same thermal power working in a common combustion chamber are designed so differently to suppress thermo-acoustic combustion instabilities that those of the flames or flame fronts generated by them are positioned distributed along the common axis.
  • the disadvantage here is the different design of the burners, which leads to increased production and maintenance costs.
  • the present invention shows another way of suppressing high-frequency vibrations in the combustion zone of intermediate superheating systems. It is based on an annular burner arrangement with a plurality of similar ones arranged in a ring
  • a changed operating mode means that at least some of the individual burners are operated in a stable operating range. This detunes the entire system in such a way that high-frequency instabilities can no longer occur.
  • a first preferred embodiment of the method according to the invention is characterized in that the heat release in the selected burners is changed compared to the other burners, that the changed heat release in the selected burners is achieved by a change in the fuel supply, and in that for the change a controllable valve or a restriction in the fuel supply is used for the fuel supply.
  • a second preferred embodiment is characterized in that the inlet temperature in the selected burners is changed compared to the other burners, and in that the changed inlet temperature in the selected ones
  • Burners is achieved by a targeted change in the fuel supply in the burner arrangement of the first stage of the combustion device.
  • the burner arrangement can be operated in an operating range with the addition of water, and the changed inlet temperature in the selected burners can be achieved by deliberately changing the water supply.
  • Another preferred embodiment is characterized in that the burners operating in the unstable region are operated in a suitably distributed manner via the annular burner arrangement.
  • FIG. 1 shows an exemplary (schematic) annular burner arrangement with n burners in a reduced coordinate system (x-circumferential coordinate; z-axial coordinate) for the implementation of the invention
  • combustion instabilities can have various causes, e.g. a feedback mechanism between shear layer instabilities and fluctuations in heat release, or a feedback mechanism between local heat release and fluctuations in the equivalence ratio, due to a fluctuating air column within the burner element.
  • a feedback mechanism between shear layer instabilities and fluctuations in heat release or a feedback mechanism between local heat release and fluctuations in the equivalence ratio, due to a fluctuating air column within the burner element.
  • most of these effects can be described by a characteristic time delay, which is essentially based on a convective time scale between the location of the fuel injection (or: the origin of the shear layer instability) and the local position of the flame front. As a result, these mechanisms are sensitive to the central flame location.
  • the frequencies observed in a sequential combustion and high speed flow system are typically in the 1-10 kHz range.
  • L is a characteristic burner length
  • U is a characteristic burner speed
  • Mechanism of sound generation i.e. changes from stable to unstable states.
  • the model assumes that there are, in particular, two parameters or methods for introducing inhomogeneities into the reheat burner arrangement with only minor structural changes to the burners, with their Help you can avoid the occurrence of high frequency vibrations, namely
  • the conventional linear stability approach forms the basis of the investigation. According to this approach, the flow equations are linearized and the development of flow disturbances is checked. The flow disturbances (pressure, speed, etc.) are assumed to have an exponential time dependency
  • FIG. 1 shows a schematic development of an annular burner arrangement 10 with n burners B1, .., Bi, .., Bn, which work in a common combustion chamber 11 with a combustion chamber outlet 12.
  • the coordinate z denotes the circumferential direction and x the axial extent in the flow direction.
  • the flow pattern is periodic with the period L (x), which is determined by the shape of the burner arrangement 10.
  • the flames F1, .., Fi, .., Fn emanating from the burners B1, .., Bi, .., Bn are also shown in FIG. 1.
  • the distance between the outlet of the i-th burner Bi and the associated flame Fi is designated as X f .
  • the burner model described in a previous article (A. Ni, W. Polifke and F. Joos, Ignition delay time as a contribution to thermo-acoustic instability in sequential combustion, ASME Turbo Expo 2000, Paper 2000-GT-0103 ( 2000)) has been proposed, determines the acoustic behavior of the individual burner in the stability analysis.
  • the input variables of the model are: geometry of the burner, pressure drop in the fuel supply line, fuel mass flow, average hydrodynamic and thermodynamic parameters (speed, pressure, density, temperature) of the flow in the burner, location of the flame front and Fuel mixing length.
  • the mechanism of pulsation excitation used is that given by Rayleigh (JWS Rayleigh, The theory of sound, 1945, New York Dover Publications).
  • FIG. 2 shows the behavior of the pulsation
  • FIG. 3 shows the dependence of the growth rate GR at this Strouhal number on the position of the flame front (X f / L).
  • X f / L 0.53
  • the influence of the burners, which have been throttled to stability, has also been investigated in calculations.
  • the throttling has been simulated by reducing the fuel supply to the respective burner.
  • the third column of the table contains the numbers of the burners that have been throttled by 50%.
  • the fourth column shows the calculated growth rate for the respective burner configuration.
  • the stability depends on the number of unstable burners. The more unstable burners there are, the greater the growth rate. 2. The stability depends on the mutual positioning of the unstable burners. Comparing the data in rows 5 and 7, it can be concluded that there are 4 unstable burners in both cases; however, the second case is more stable (the growth rate is smaller). There are three unstable burners in rows 3 and 4; however, they are both more stable than the case in row 7.
  • the stability is also strongly determined by the number and position of the throttled burners.
  • the stability of the overall system depends on the number of unstable burners. The more burners are unstable, the greater the growth rate.
  • the stability of the burner assembly depends on the relative position of the unstable burner within the system. A coherent group of unstable burners makes the entire system unstable. Statistically distributed unstable burners do not necessarily lead to an unstable combustion system.
  • At least a selected part of the burners B1, .., Bi, .., Bn are operated in a stable operating range in a predetermined unstable operating range of the burner arrangement 10.
  • this can be done by changing the heat release in the selected burners compared to the other burners, in particular the changed heat release being achieved in the selected burners by changing the fuel supply.
  • a controllable valve or a restriction in the fuel supply is preferably used to change the fuel supply.
  • the inlet temperature in the selected burners can be changed compared to the other burners, in particular the changed inlet temperature in the selected burners being achieved by a targeted change in the fuel supply in the burner arrangement of the first stage of the combustion device.
  • the changed inlet temperature in the selected burners can also be achieved by a targeted change in the water supply.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)

Abstract

L'invention concerne un procédé permettant de faire fonctionner un dispositif brûleur (10) annulaire dans un étage de réchauffement intermédiaire d'un dispositif de combustion à plusieurs étages d'une turbine à gaz, ce dispositif brûleur comprenant une pluralité de brûleurs identiques (B1,..,Bi,..,Bn) disposés en cercle. L'invention vise à améliorer le fonctionnement du dispositif brûleur. Pour supprimer les instabilités hautes fréquences apparaissant lors de la combustion, dans une plage de fonctionnement instable prédéterminée du dispositif brûleur (10) au moins une partie sélectionnée du brûleur (B1,..,Bi,..,Bn) fonctionne dans une plage de fonctionnement stable.
PCT/EP2004/051013 2003-06-05 2004-06-03 Procede permettant de faire fonctionner un dispositif bruleur annulaire dans un etage de rechauffement intermediaire d'un dispositif de combustion a plusieurs etages d'une turbine a gaz WO2004109188A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE2003125455 DE10325455A1 (de) 2003-06-05 2003-06-05 Verfahren zum Betrieb einer ringförmigen Brenneranordnung in einer Zwischenerhitzungsstufe einer mehrstufigen Verbrennungseinrichtung einer Gasturbine
DE10325455.2 2003-06-05

Publications (1)

Publication Number Publication Date
WO2004109188A1 true WO2004109188A1 (fr) 2004-12-16

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Country Status (2)

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DE (1) DE10325455A1 (fr)
WO (1) WO2004109188A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20081514A1 (it) * 2008-08-08 2010-02-09 Ansaldo Energia Spa Metodo per determinare la collocazione di bruciatori in una camera di combustione anulare di una turbina a gas
US8631656B2 (en) 2008-03-31 2014-01-21 General Electric Company Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20060218933A1 (en) * 2005-02-10 2006-10-05 Bruno Schuermans Method for producing a model-based control device
US20160273449A1 (en) * 2015-03-16 2016-09-22 General Electric Company Systems and methods for control of combustion dynamics in combustion system

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4339094A1 (de) * 1993-11-16 1995-05-18 Abb Management Ag Verfahren zur Dämpfung von thermoakustischen Schwingungen sowie Vorrichtung zur Durchführung des Verfahrens
WO1998034067A1 (fr) * 1997-02-04 1998-08-06 Siemens Aktiengesellschaft Dispositif de combustion et procede d'attenuation active des vibrations dues a la combustion
DE19849300A1 (de) * 1998-10-16 2000-04-20 Siemens Ag Verfahren und Anordnung zur Reduzierung der akustischen Energie benachbarter Brennquellen in Verbrennungsanlagen
US6205765B1 (en) * 1999-10-06 2001-03-27 General Electric Co. Apparatus and method for active control of oscillations in gas turbine combustors
US20020134086A1 (en) * 2001-02-22 2002-09-26 Klaus Doebbeling Process for the operation of an annular combustion chamber, and annular combustion chamber
US20020162336A1 (en) * 2001-05-01 2002-11-07 Wolfgang Weisenstein Vibration reduction in a combustion chamber
US20020178733A1 (en) * 2000-12-16 2002-12-05 Jaan Hellat Method for operating a premix burner

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19545311B4 (de) * 1995-12-05 2006-09-14 Alstom Verfahren zur Betrieb einer mit Vormischbrennern bestückten Brennkammer
DE59710046D1 (de) * 1997-03-20 2003-06-12 Alstom Switzerland Ltd Gasturbine mit toroidaler Brennkammer
DE19726975A1 (de) * 1997-06-26 1999-01-07 Asea Brown Boveri Strahltriebwerk
DE59810344D1 (de) * 1998-07-27 2004-01-15 Alstom Switzerland Ltd Verfahren zum Betrieb einer Gasturbinenbrennkammer mit gasförmigem Brennstoff

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4339094A1 (de) * 1993-11-16 1995-05-18 Abb Management Ag Verfahren zur Dämpfung von thermoakustischen Schwingungen sowie Vorrichtung zur Durchführung des Verfahrens
WO1998034067A1 (fr) * 1997-02-04 1998-08-06 Siemens Aktiengesellschaft Dispositif de combustion et procede d'attenuation active des vibrations dues a la combustion
DE19849300A1 (de) * 1998-10-16 2000-04-20 Siemens Ag Verfahren und Anordnung zur Reduzierung der akustischen Energie benachbarter Brennquellen in Verbrennungsanlagen
US6205765B1 (en) * 1999-10-06 2001-03-27 General Electric Co. Apparatus and method for active control of oscillations in gas turbine combustors
US20020178733A1 (en) * 2000-12-16 2002-12-05 Jaan Hellat Method for operating a premix burner
US20020134086A1 (en) * 2001-02-22 2002-09-26 Klaus Doebbeling Process for the operation of an annular combustion chamber, and annular combustion chamber
US20020162336A1 (en) * 2001-05-01 2002-11-07 Wolfgang Weisenstein Vibration reduction in a combustion chamber

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8631656B2 (en) 2008-03-31 2014-01-21 General Electric Company Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities
ITMI20081514A1 (it) * 2008-08-08 2010-02-09 Ansaldo Energia Spa Metodo per determinare la collocazione di bruciatori in una camera di combustione anulare di una turbina a gas
EP2151629A2 (fr) * 2008-08-08 2010-02-10 Ansaldo Energia S.p.A. Procédé pour déterminer la position de brûleurs dans une chambre de combustion annulaire d'une turbine à gaz
EP2151629A3 (fr) * 2008-08-08 2013-06-26 Ansaldo Energia S.p.A. Procédé pour déterminer la position de brûleurs dans une chambre de combustion annulaire d'une turbine à gaz

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