EP2144000B1 - Dipositif de brûleur - Google Patents

Dipositif de brûleur Download PDF

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Publication number
EP2144000B1
EP2144000B1 EP09163782.7A EP09163782A EP2144000B1 EP 2144000 B1 EP2144000 B1 EP 2144000B1 EP 09163782 A EP09163782 A EP 09163782A EP 2144000 B1 EP2144000 B1 EP 2144000B1
Authority
EP
European Patent Office
Prior art keywords
fuel
burner
intake
lances
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.)
Not-in-force
Application number
EP09163782.7A
Other languages
German (de)
English (en)
Other versions
EP2144000A3 (fr
EP2144000A2 (fr
Inventor
Harald Schütz
Guido Schmitz
Oliver Lammel
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
WS Warmeprozesstechnik GmbH
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
WS Warmeprozesstechnik GmbH
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 Deutsches Zentrum fuer Luft und Raumfahrt eV, WS Warmeprozesstechnik GmbH filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP2144000A2 publication Critical patent/EP2144000A2/fr
Publication of EP2144000A3 publication Critical patent/EP2144000A3/fr
Application granted granted Critical
Publication of EP2144000B1 publication Critical patent/EP2144000B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors

Definitions

  • the invention relates to a combustion device having at least one burner, which has a substantially rectangular inlet and a substantially circular mixing tube.
  • a combustion device is off US 4,383,820 A known.
  • a burner which has an inlet with coaxial inlets for fuel and air.
  • the burner inlet is followed by a mixing section in which fuel and air mix before the mixture enters a combustion chamber.
  • Fuel and air have such a flow impulse that combustion takes place only in the combustion chamber.
  • a gas turbine fuel air premixer having a dual cylinder structure of an inner cylinder and an outer cylinder. Between the two cylinders are flow paths, are introduced into the fuel and air, whereby in the flow paths, a fuel-air mixture is formed. Nozzles for injecting the fuel into the flow paths are arranged eccentrically to a longitudinal center plane of the flow path. These nozzles can be controlled independently.
  • the invention has for its object to provide a combustion device with improved mixing of fuel and air, in which the composition of the mixture of fuel and air, ie the air ratio, is variable, on the one hand to keep the NO emission low and on the other a extinction to avoid the flame.
  • the combustion device according to the invention is defined by the patent claim 1. It is generally designed in the same way as in US 4,383,820 A However, it differs from this by the characterizing features of claim 1.
  • the degree of mixing in the outlet of the burner nozzle has a significant influence on the subsequent combustion processes in the combustion chamber.
  • the goal of the best possible reduction of nitrogen oxide emissions can be achieved by keeping the combustion temperature as low as possible by appropriate control of the mixing and combustion processes.
  • the combustion temperature is regulated by an excess of combustion air through the burner.
  • the problem of power modulation is now addressed over the widest possible ⁇ range by fuel variation at a constant air mass flow.
  • the lower ⁇ limit is determined by the maximum tolerable NO emission and thus by the maximum flame temperature.
  • the NO emission is about 10 ppm (based on 15% O 2 in the combustion chamber outlet).
  • the associated adiabatic flame temperature of the global mixture is approximately 2000 K.
  • One aspect of the present invention is to combine the respective advantages of centric and eccentric positioning of the fuel input by adding a second fuel lance. Both lances can be supplied with fuel independently of each other via separate supply systems.
  • the distance of the lances from each other and also their radial position with respect to the combustion chamber axis can be varied within a certain range and can each be adapted to specific design requirements.
  • Numerical simulations show that for each operating point, that is to say for each ⁇ , a specific value of the fuel split exists on both lances, which causes a minimum of pollutant emissions during combustion. Another important aspect is that due to suitable fuel staging possibly occurring flame instabilities can be almost completely prevented.
  • transverse flows are initiated at the transition stages, by which the mixing process is greatly improved by increasing the turbulent transport and the induction of a convective secondary transport.
  • This is achieved by the combustion air is transferred from a rectangular channel into a channel with a round cross-section. Rectangular channel and round channel are "inline", ie arranged on the same burner axis and form on their transition surface two mutually parallel stages (transition stages).
  • the result is a convective-diffusive transport of the fuel-air mixture and a strong and uniform spread of the fuel in the radial direction.
  • the maximum fuel concentration at the outlet of the mixing section is thus low and the distribution of the fuel over the cross section of the mixing channel is improved.
  • the result is a reduction of thermal nitrogen oxide formation.
  • transition stages between square and round cross-section cause the induction of four Secondary vortices, each rotating about a parallel to the burner axis, but radially offset, extending vortex axis.
  • the rotations of adjacent secondary vortices have opposite directions of rotation.
  • the invention is particularly suitable for a combustion device for gas turbines, in which a plurality of burners are arranged in a ring and open into a common combustion chamber.
  • FIG. 1 a burner 10 is shown, which has a rectangular inlet 11 and subsequently a round mixing tube 12. Between inlet 11 and mixing tube 12 there is a transition 13.
  • the inlet 11 is rectangular Cross-section. It has two parallel longitudinal walls 14,15, between which the center longitudinal plane 16 is defined. The two longitudinal walls are connected by transverse walls 17,18.
  • the diameter of the mixing tube 12 is greater than the transverse extent of the inlet 11, but smaller than the longitudinal extent.
  • each of the fuel lances consists of a tube through which fuel can be supplied.
  • the fuel lances L1, L2 each have an inlet 20 and an outlet 21, which opens into the mixing tube 12.
  • Around the fuel lances is an air passage 22 having an inlet 27.
  • FIG. 1 are the two lances L1, L2 arranged at a distance from the longitudinal center plane 16, that is "eccentric".
  • the two fuel lances are provided symmetrically to the longitudinal central axis.
  • the fuel lance L1 arranged centrally, ie with its axis in the longitudinal center plane 16.
  • the fuel lance L2 is arranged eccentrically, ie at a distance from the longitudinal center plane 16th
  • FIG. 3 shows an annular burner system as used in stationary gas turbines.
  • Numerous burners 10 of the type described are arranged in a ring shape and open into a common combustion chamber 23.
  • the combustion chamber is round here and has a combustion chamber axis 24.
  • the enemas 11 of the burner 10 are not exactly rectangular here. Instead, they form a ring and are therefore bent about the axis 24.
  • FIG. 3 are also the mixing tubes 12 shown, which open into the combustion chamber 23. The flames arise in the flow direction behind the mixing tubes 12 in the combustion chamber 23.
  • Each inlet 11 contains two fuel lances L1, L2 arranged in the same way as in FIG. 1 ,
  • FIG. 4 shows different operating conditions of a burner 10, the two fuel lances according to FIG. 1 Is provided.
  • the supply of fuel to the fuel lances L1, L2 is each separately controllable.
  • the arrows F1 and F2 denote the fuel supply to the fuel lances and the arrow S indicates the air supply.
  • the distribution of the gaseous fuel is plotted on a longitudinal section plane through the burner axis and the combustion chamber axis 24.
  • proportionally different loading of the two fuel lances can be continuously change the formation and position of the flame front 25.
  • the resulting in the combustion chamber 23 recirculation flow 26 is heated by heat release in the flame front 25 to the extent that the entering into the combustion chamber fuel / air mixture undergoes sufficient preheating. This reduces the ignition delay time and prevents the flame from extinguishing.
  • FIG. 4 Figure 11 shows the diagram a) the condition that the outer fuel lance L1 is charged with 100% of the fuel quantity while the inner fuel lance L2 is blocked.
  • the representation b) shows a ratio of 50:50 and the representation c) a ratio of 0: 100.
  • CH 4 is used as the fuel.
  • the flame front 25 can be changed by changing the fuel components. This reduces the ignition delay time and prevents the flame from extinguishing. In this way, the flame temperature for each ⁇ can be adjusted so that the flame is not extinguished and at the same time the lowest possible NO production takes place.
  • Particular attention should be paid to the fact that when approaching the extinction limit an extremely strong increase in CO production, in contrast to NO production, sets in and the burnout is no longer complete.

Landscapes

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

Claims (4)

  1. Dispositif de combustion comprenant au moins un brûleur (10) qui comporte une arrivée (11) sensiblement rectangulaire et présentant deux parois longitudinales parallèles (14, 15) et deux parois transversales parallèles (17, 18), ainsi que des admissions (20, 27) pour le combustible et pour l'air, et au moins une lance à combustible (L1, L2) qui traverse l'arrivée (11), dans lequel un élément de liaison (13) se raccorde au niveau de l'arrivée (11) à un tube de mélange rond (12) dont l'axe se trouve dans le plan médian longitudinal de l'arrivée (11), caractérisé en ce que la lance à combustible (L1, L2), au moins au nombre de une, est disposée excentriquement par rapport au plan médian longitudinal (16) de l'arrivée (11) et en ce que le diamètre du tube de mélange (12) est plus grand que l'écartement des parois longitudinales (14, 15) de l'arrivée et plus petit que l'écartement des parois transversales (17, 18).
  2. Dispositif de combustion selon la revendication 1, caractérisé en ce qu'il est prévu au moins deux lances à combustible (L1, L2), dont au moins une est disposée excentriquement.
  3. Dispositif de combustion selon la revendication 2, caractérisé en ce que les lances à combustible (L1,L2) peuvent être alimentées en combustible dans un mode commandé indépendamment l'une de l'autre.
  4. Dispositif de combustion selon l'une des revendications 1 à 3, caractérisé en ce que plusieurs brûleurs (10) sont disposés en une couronne et débouchent dans une chambre de combustion commune (23), et en ce que dans chaque brûleur (10) est disposée une lance à combustible décalée par rapport à l'axe médian longitudinal de l'arrivée correspondante (11) en direction de l'axe longitudinal (24) de la chambre de combustion (23).
EP09163782.7A 2008-07-09 2009-06-25 Dipositif de brûleur Not-in-force EP2144000B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE200810032265 DE102008032265B4 (de) 2008-07-09 2008-07-09 Verbrennungsvorrichtung

Publications (3)

Publication Number Publication Date
EP2144000A2 EP2144000A2 (fr) 2010-01-13
EP2144000A3 EP2144000A3 (fr) 2010-09-15
EP2144000B1 true EP2144000B1 (fr) 2015-02-18

Family

ID=40845695

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09163782.7A Not-in-force EP2144000B1 (fr) 2008-07-09 2009-06-25 Dipositif de brûleur

Country Status (2)

Country Link
EP (1) EP2144000B1 (fr)
DE (1) DE102008032265B4 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2902809C (fr) 2013-03-13 2018-01-23 Industrial Turbine Company (Uk) Limited Bruleur a flamme azimutale inclinee
DE102015205069B4 (de) 2015-03-20 2020-04-23 Deutsches Zentrum für Luft- und Raumfahrt e.V. Verbrennungsvorrichtung

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4383820A (en) * 1980-10-10 1983-05-17 Technology Application Services Corporation Fuel gas burner and method of producing a short flame
JP2528894B2 (ja) * 1987-09-04 1996-08-28 株式会社日立製作所 ガスタ―ビン燃焼器
DE68923413T2 (de) * 1988-09-07 1996-04-04 Hitachi Ltd Kraftstoff-Luftvormischvorrichtung für eine Gasturbine.
ES2064538T3 (es) 1990-06-29 1995-02-01 Wuenning Joachim Procedimiento y dispositivo para la combustion de combustible en un recinto de combustion.
FR2756593B1 (fr) * 1996-12-03 1999-01-22 Aerospatiale Mat d'injection de combustible pour un statoreacteur fonctionnant sur une large plage de nombre de mach
DE19724861C1 (de) * 1997-06-12 1998-10-15 Stiebel Eltron Gmbh & Co Kg Gasbrenner für einen Heizkessel
DE102007036953B3 (de) * 2007-08-04 2009-04-02 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brenner

Also Published As

Publication number Publication date
EP2144000A3 (fr) 2010-09-15
EP2144000A2 (fr) 2010-01-13
DE102008032265B4 (de) 2010-06-10
DE102008032265A1 (de) 2010-03-18

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