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EP1205713B1 - Procédé d'injection de combustible dans un brûleur - Google Patents

Procédé d'injection de combustible dans un brûleur Download PDF

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Publication number
EP1205713B1
EP1205713B1 EP01125598A EP01125598A EP1205713B1 EP 1205713 B1 EP1205713 B1 EP 1205713B1 EP 01125598 A EP01125598 A EP 01125598A EP 01125598 A EP01125598 A EP 01125598A EP 1205713 B1 EP1205713 B1 EP 1205713B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
max
nozzles
cone
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
EP01125598A
Other languages
German (de)
English (en)
Other versions
EP1205713A1 (fr
Inventor
Christian Oliver Dr. Paschereit
Peter Dr. Flohr
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 EP1205713A1 publication Critical patent/EP1205713A1/fr
Application granted granted Critical
Publication of EP1205713B1 publication Critical patent/EP1205713B1/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2210/00—Noise abatement

Definitions

  • the present invention relates to a method of injecting fuel into a burner, which is designed as a double-cone burner, and to a burner for carrying out this method.
  • thermoacoustic fluctuations In burners, which supply liquid or gaseous fuel to a combustion chamber where the fuel burns at a flame front, so-called thermoacoustic fluctuations often occur. So also, for example, but not exclusively, in the very successfully used so-called double-cone burner, as in the EP 0 321 809 is described.
  • mixture rupture fluctuations are a major reason for the occurrence of such thermoacoustic instabilities.
  • Fluid-mechanical instability waves which arise at the burner, lead to the formation of vortices (coherent structures), which influence the combustion and can lead to periodic heat release with the associated pressure fluctuations.
  • the fluctuating air column in the burner leads to fluctuations in the mixing fraction with the associated fluctuations in the heat release.
  • thermoacoustic vibrations pose a danger to any type of combustion application. They lead to high amplitude pressure oscillations, a limitation of the operating range and can increase pollutant emissions. This is especially true for low acoustic attenuation combustion systems.
  • active control of the combustion vibrations may be necessary.
  • Coherent structures play a crucial role in mixing processes between air and fuel. The dynamics of these structures consequently influence the combustion and thus the heat release. By influencing the shear layer between the fresh gas mixture and the recirculated exhaust gas, a control of the combustion instabilities is possible (eg.
  • the flame position can be influenced and thus the influence of flow instabilities as well as time delay effects reduced.
  • thermoacoustic oscillations Another mechanism that can lead to thermoacoustic oscillations are fluctuations in the mixture break between fuel and air
  • DE 44 46 945 A1 discloses a double-cone burner, in which the delay time from the injection to the combustion of all fuel streams is the same size, so that disadvantageous thermoacoustic oscillations occur.
  • the fuel concentration at the outlet of the burner in the region of the burner axis is greater than the average fuel concentration in the exit plane of the burner.
  • the combustion chamber can be operated near the lean extinction limit.
  • a burner is known in which via axially distributed fuel nozzles fuel is injected to improve the burner stability by damping the amplitude change. The burner is operated so that there is a decoupling of the fuel from the combustion and the dynamic pressure instability is reduced in the combustion chamber.
  • the invention is therefore an object of the invention to provide a method and a Brenne the Doppelkegelbauart for performing such a method in which the occurrence of such thermoacoustic vibrations is reduced or even avoided.
  • thermoacoustic oscillations are reduced or even completely avoided by injecting the fuel via fuel nozzles distributed over the entire burner length and arranged on the cone surfaces of the partial cone bodies (8, 9) on a specific area of the flame front in that the delay time ⁇ between injection of the fuel and its combustion at the flame front for the different fuel nozzles corresponds to a distribution which varies systematically over the burner length and avoids combustion-induced vibrations.
  • the fuel is injected in such a way that the time delay distribution over the burner length towards the burner end is designed to be substantially linearly decreasing from the maximum value ⁇ max by a maximum delay difference ⁇ to a minimum value at the burner end of ⁇ max - ⁇ .
  • This simple distribution can be realized with relatively little effort and shows an efficient effect. It can be seen that preferably the delay difference ⁇ is set in the range of 10-90% of the maximum value ⁇ max , in particular in the range of more than 50% of the maximum value ⁇ max
  • the method is a double-cone burner in which the burner of at least two successive hollow cone bodies, which have an increasing conical inclination in the flow direction, and which part cone bodies are arranged offset to each other, so that the combustion air through a gap between the part cone bodies in the Interior flows, is formed.
  • premix-type double-cone burner the method can be applied particularly favorable.
  • the invention relates to a double-cone burner for carrying out the above method, wherein the fuel nozzles are arranged on the cone surfaces of the Teikegel Orchestra on lines for a region of the flame front wherein the fuel nozzles are divided into groups, and wherein each of a group of Fuel nozzles is arranged in a line such that all the fuel nozzles of a group are responsible for the supply of the same area in the flame front.
  • the fuel nozzles are distributed such that the number of lines is greater than the average number of fuel nozzles of a group. It turns out that a division of the total of 32 nozzles of a double-cone burner in 8 groups on 8 lines with 4 nozzles is advantageous.
  • Premixed gas is constant at certain operating points. For example, in a double-cone burner according to the prior art as shown in Fig. 1a).
  • the fuel / air mixture then passes into the combustion chamber 2, where it ignites at a flame front 3.
  • the delay time ⁇ which elapses between the injection at the fuel nozzles 6 to the ignition at the flame front 3, almost constant for all positions of the fuel nozzles, as shown schematically in Fig. 1b) (the coordinate x extends from the outlet 10 of the burner 1 to its rear end, ie in the figure 1a) from right to left).
  • the delay times ⁇ as a function of the fuel nozzle position along the burner 1 can be observed (eg shorter delay times for nozzles 6 near the burner exit 10), but rather a more or less random distribution which fluctuates only a little as a function of injection location x.
  • the distribution is set in a first choice so that the delay times ⁇ linearly varies by a delay time difference ⁇ , linearly increasing from a minimum ⁇ max - ⁇ to the maximum in the rear burner region of ⁇ max .
  • FIG. 3 the burner stability as a function of the parameters ⁇ (x-axis) and ⁇ max (y-axis) for a delay time distribution is indicated as in FIG. 2.
  • ⁇ x-axis
  • ⁇ max y-axis
  • three values for the behavior at different flow velocities in the burner are given as individual measured values: for low flow velocity 17, for average flow velocity 18 and for high flow velocity 19.
  • two basically unstable, here hatched areas form.
  • an unstable region 16 short delay times.
  • Such a distribution can be implemented technically on a double-cone burner serving as an exemplary embodiment, as already illustrated in FIG. 1, by way of a simple modification of the fuel injection into the combustion air stream 23.
  • the fuel nozzles 6 become no longer arranged directly on the column 7 between the two shells 8 and 9 here, but are resp. embedded in the cone surfaces of the elements 8 and 9, and thereby systematically set the delay times.
  • the fuel nozzles 6 can be divided into groups, and in each case the fuel nozzles of a group are arranged on lines 20 which follow the flow lines along the burner contour. Nozzles of a group feed a certain area of the flame front, but with a different delay time ⁇ between moment of injection and arrival at the flame front 3.
  • thermoacoustic oscillations prevent it is advantageous to form as many groups as possible to form a uniformly submerged flame for additional scattering of the time delay.

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

Claims (9)

  1. Procédé d'injection de combustible dans un brûleur (1), lequel brûleur (1) comprend un espace interne (22) entouré par au moins une coque (8, 9), du combustible étant injecté par des buses à combustible (6) dans un courant d'air comburant (23) affluant dans l'espace interne (22), le mélange air/combustible ainsi formé s'écoulant, en l'espace d'un temps de retard (τ), jusqu'à un front de flamme (3) dans une chambre de combustion (2) et s'y enflammant, le brûleur (1) étant un brûleur à double cône, le brûleur (1) se composant d'au moins deux corps coniques partiels creux positionnés l'un sur l'autre (8, 9) qui présentent, dans la direction de l'écoulement, une pente conique croissante, et qui sont disposés de manière décalée l'un par rapport à l'autre, de sorte que l'air comburant (23) s'écoule dans l'espace interne (22) par une fente (7) entre les corps coniques partiels (8, 9),
    le combustible étant injecté au moyen de buses à combustible (6) réparties sur toute la longueur du brûleur et disposées sur les surfaces coniques des corps coniques partiels (8, 9) sur une plage définie de lignes (20) alimentant le front de flamme, de telle sorte que le temps de retard (τ) entre l'injection du combustible et sa combustion au front de flamme (3) corresponde, pour les différentes buses à combustible, à une répartition (12) variant systématiquement sur la longueur du brûleur, qui évite des oscillations provoquées par la combustion.
  2. Procédé selon la revendication 1, caractérisé en ce que le retard maximal (τmax) entre le lieu d'injection (6) et le front de flamme (3) est compris dans la plage de τmax = 5-50 ms.
  3. Procédé selon la revendication 2, caractérisé en ce que pour une vitesse d'écoulement du mélange air/combustible dans l'espace interne dans la plage de 20-50 m/s, le retard maximal (τmax) est compris dans la plage de τmax = 5-15 ms.
  4. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que le combustible est injecté de telle sorte que la répartition retardée dans le temps (12) est configurée sur la longueur du brûleur jusqu'à l'extrémité du brûleur (10) depuis la valeur maximale τmax avec une différence de retard maximale (Δτ) essentiellement en décroissance linéaire jusqu'à une valeur minimale à l'extrémité du brûleur (10) de τmax - Δτ.
  5. Procédé selon la revendication 4, caractérisé en ce que la différence de retard (Δτ) est comprise dans la plage de 10-90% de la valeur maximale (τmax), notamment dans la plage de plus de 50% de la valeur maximale (τmax).
  6. Brûleur (1) pour la mise en oeuvre d'un procédé selon l'une quelconque des revendications 1 à 5, le brûleur (1) comprenant un espace interne (22) entouré par au moins une coque (8, 9), du combustible étant injecté au moyen de buses à combustible (6) disposées le long de toute la longueur du brûleur dans un courant d'air comburant (23) affluant dans l'espace interne (22), le mélange air/combustible ainsi formé s'écoulant, en l'espace d'un temps de retard (τ), jusqu'à un front de flamme (3) dans une chambre de combustion (2) et s'y enflammant, le brûleur (1) étant un brûleur à double cône, le brûleur (1) se composant d'au moins deux corps coniques partiels creux positionnés l'un sur l'autre (8, 9) qui sont disposés de manière décalée l'un par rapport à l'autre, de sorte que l'air comburant (23) afflue dans l'espace interne (22) par une fente (7) entre les corps coniques partiels (8, 9), les buses à combustible étant disposées sur les surfaces coniques des corps coniques partiels (8, 9) sur une plage définie des lignes (20) alimentant le front de flamme, caractérisé en ce que les corps coniques partiels (8, 9) présentent, dans la direction de l'écoulement, une pente conique croissante.
  7. Brûleur (1) selon la revendication 6, caractérisé en ce que les buses à combustible (6) sont divisées en groupes, un groupe de buses à combustible (6) étant à chaque fois disposé sur une ligne de telle sorte que toutes les buses (6) du groupe alimentent une région définie du front de flamme (3) avec un retard différent (τ).
  8. Brûleur (8) selon la revendication 7, caractérisé en ce que le nombre de lignes (20) est supérieur au nombre moyen des buses à combustible (6) d'un groupe.
  9. Brûleur (1) selon la revendication 8, caractérisé en ce que le brûleur présente au total 32 buses qui sont réparties en 8 groupes sur 8 lignes (20) comprenant chacune 4 buses.
EP01125598A 2000-11-09 2001-10-26 Procédé d'injection de combustible dans un brûleur Expired - Lifetime EP1205713B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10055408 2000-11-09
DE10055408A DE10055408A1 (de) 2000-11-09 2000-11-09 Verfahren zur Brenstoffeinspritzung in einen Brenner

Publications (2)

Publication Number Publication Date
EP1205713A1 EP1205713A1 (fr) 2002-05-15
EP1205713B1 true EP1205713B1 (fr) 2007-07-11

Family

ID=7662615

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01125598A Expired - Lifetime EP1205713B1 (fr) 2000-11-09 2001-10-26 Procédé d'injection de combustible dans un brûleur

Country Status (3)

Country Link
US (1) US6705857B2 (fr)
EP (1) EP1205713B1 (fr)
DE (2) DE10055408A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
US7089746B2 (en) * 2002-06-26 2006-08-15 Georgia Tech Reasearch Corporation Systems and methods for detection of blowout precursors in combustors
US7454892B2 (en) * 2002-10-30 2008-11-25 Georgia Tech Research Corporation Systems and methods for detection and control of blowout precursors in combustors using acoustical and optical sensing
WO2005095863A1 (fr) * 2004-03-31 2005-10-13 Alstom Technology Ltd Brûleur
US7303388B2 (en) * 2004-07-01 2007-12-04 Air Products And Chemicals, Inc. Staged combustion system with ignition-assisted fuel lances
WO2006058843A1 (fr) * 2004-11-30 2006-06-08 Alstom Technology Ltd Procede et dispositif de combustion d'hydrogene dans un bruleur a premelange
EP2423598A1 (fr) 2010-08-25 2012-02-29 Alstom Technology Ltd Dispositif de combustion
CN113719861B (zh) * 2021-09-10 2022-12-06 中国联合重型燃气轮机技术有限公司 燃烧室和具有该燃烧室的燃气轮机

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH674561A5 (fr) 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
EP0592717B1 (fr) * 1992-10-16 1998-02-25 Asea Brown Boveri Ag Brûleur opérant au gaz du type à prémélange
DE4336096B4 (de) * 1992-11-13 2004-07-08 Alstom Vorrichtung zur Reduktion von Schwingungen in Brennkammern
DE4304213A1 (de) * 1993-02-12 1994-08-18 Abb Research Ltd Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
DE4440558A1 (de) * 1994-11-12 1996-05-15 Abb Research Ltd Vormischbrenner
DE4441235A1 (de) * 1994-11-19 1996-05-23 Abb Management Ag Brennkammer mit Mehrstufenverbrennung
DE4441641A1 (de) * 1994-11-23 1996-05-30 Abb Management Ag Brennkammer mit Vormischbrennern
DE4446945B4 (de) * 1994-12-28 2005-03-17 Alstom Gasbetriebener Vormischbrenner
EP0918152A1 (fr) 1997-11-24 1999-05-26 Abb Research Ltd. Procédé et dispositif pour contrÔler les vibrations thermoacoustiques dans les chambres de combustion
DE59810032D1 (de) * 1998-09-10 2003-12-04 Alstom Switzerland Ltd Verfahren zum Minimieren thermoakustischer Schwingungen in Gasturbinenbrennkammern
DE59811961D1 (de) * 1998-11-09 2004-10-21 Alstom Technology Ltd Baden Brenner
DE19948674B4 (de) * 1999-10-08 2012-04-12 Alstom Verbrennungseinrichtung, insbesondere für den Antrieb von Gasturbinen
DE19948673B4 (de) * 1999-10-08 2009-02-26 Alstom Verfahren zum Erzeugen von heissen Gasen in einer Verbrennungseinrichtung sowie Verbrennungseinrichtung zur Durchführung des Verfahrens
US6360776B1 (en) * 2000-11-01 2002-03-26 Rolls-Royce Corporation Apparatus for premixing in a gas turbine engine
DE10064893A1 (de) 2000-12-23 2002-11-14 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeindüsung

Also Published As

Publication number Publication date
EP1205713A1 (fr) 2002-05-15
DE50112704D1 (de) 2007-08-23
US20020177093A1 (en) 2002-11-28
US6705857B2 (en) 2004-03-16
DE10055408A1 (de) 2002-05-23

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