EP1001214B1 - Brûleur - Google Patents

Brûleur Download PDF

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Publication number
EP1001214B1
EP1001214B1 EP98811115A EP98811115A EP1001214B1 EP 1001214 B1 EP1001214 B1 EP 1001214B1 EP 98811115 A EP98811115 A EP 98811115A EP 98811115 A EP98811115 A EP 98811115A EP 1001214 B1 EP1001214 B1 EP 1001214B1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
cones
combustion
flow
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
EP98811115A
Other languages
German (de)
English (en)
Other versions
EP1001214A1 (fr
Inventor
Jakob Prof.Dr. Keller
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
Priority to DE59811961T priority Critical patent/DE59811961D1/de
Priority to EP98811115A priority patent/EP1001214B1/fr
Priority to US09/431,176 priority patent/US20010019815A1/en
Publication of EP1001214A1 publication Critical patent/EP1001214A1/fr
Application granted granted Critical
Publication of EP1001214B1 publication Critical patent/EP1001214B1/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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • 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
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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 the field of burners, in particular the burner for use in gas turbines, according to the generic term of the independent claim.
  • EP-B1-0 321 809 describes a burner for liquid and gaseous fuels become known with premixing section, in which supplied from the outside Combustion air tangentially displaced between at least two inlet slots arranged, hollow semi-cones occurs and there in the direction of the combustion chamber flows, and in which either on the side facing away from the combustion chamber, tapered side of the half cones of liquid fuel centrally, or in the region of the entry slots is injected.
  • the fuel becomes more certain masses captured by the combustion air and "enveloped", so that between the cones form a conical liquid fuel profile, which is in Expands towards the combustion chamber and burns there.
  • gaseous Fuel is obtained from fuel supply pipes that run along the air inlet slots run, injected transversely into the incoming air through rows of holes.
  • EP-A2-0 851 172 discloses a burner for operating a combustion chamber with a liquid and / or gaseous fuel.
  • a burner for operating a combustion chamber with a liquid and / or gaseous fuel the combustion air required for this through tangential air inlet ducts into an interior of the burner.
  • This flow guidance creates a swirl flow in the interior, which at the exit of the Brenner induced a backflow zone.
  • at least one zone is provided for each partial body forming the burner, within which inlet openings for the injection of additional air into the swirl flow are provided.
  • a part is formed on the inner wall of the partial body Film, which prevents the flame along the inner wall of the partial body into the interior of the burner can strike back.
  • US-A-5,375,995 discloses a double cone burner in which near the burner outlet at a distance of at least 30% from the burner diameter Nozzles for a medium-sized gaseous fuel containing highly reactive components Calorific value is attached to the circumference of the partial cone body. There is also a fuel line and a distribution channel placed in the area of the nozzles for the highly reactive Fuel presence.
  • the fuel containing gaseous, highly reactive components is at high speed through the nozzles, which have a diameter of less than 1% of the nominal diameter of the burner have been injected into the zones of high air velocity and the depth of penetration and the depth of the fuel jets are coordinated so that the ignition only takes place behind the burner after mixing.
  • the combustion air is formed behind the front edge in the direction of flow the half-cones immediately a shear layer.
  • This shear layer lies between the essentially stationary ones in the combustion chamber and hot combustion gases, and the emerging, flowing mixture of fuel and combustion air. It is in the nature of such shear layers, that, regardless of the Reynolds number, this will eventually roll up and turbulence result. This rolling up can be such that initially so-called Kelvin-Helmholtz waves appear on the shear layers form, whose wave crests are transverse to the direction of flow, and which then create vortices.
  • thermoacoustic oscillations This largely coherent waves lead to a burner of the type mentioned above under typical operating conditions to vibrations with frequencies of about 100 Hz. Since this frequency with typical fundamental eigenmodes of many ring burners of gas turbines coincide, make the thermoacoustic Oscillations are a problem.
  • the invention is therefore based on the object To provide burners which is the rocking interaction of coherent flow instabilities and acoustic field reduced.
  • This task is characterized by the features of the independent claim the formation of the first periodic, coherent is solved Flow instabilities in a boundary layer between the fuel-air mixture and the formwork elements disturbed and a coupling acoustic field in the combustion chamber is at such first flow instabilities reduced.
  • the essence of the invention is that targeted prevention of coherent flow instabilities the resonant rocking of Prevents thermoacoustic oscillations when they are caused.
  • the first flow instabilities are Tolmien-Schlichting waves in the boundary layer between combustion air flow and formwork elements, which are capable of second flow instabilities, which change when the fuel-air mixture enters the Form combustion chamber on the shear layers that occur and which, for example Kelvin-Helmholtz waves can be clocked.
  • FIG. 1 shows schematically the flow conditions in a double-cone burner 19.
  • the combustion air 10 passes laterally through the inlet slots 17 with light arranged displaced axes, hollow half-cones 13 and 16, flows to the front end of the burner 19, describing a slight curve, and enters the burner 19 after passing the front edges 18 of the half cones the combustion chamber 21 is located at the tapered end of the half-cones 13 and 16 a cylindrical part 15, in which a fuel nozzle 14 is arranged, which is the liquid fuel in this case centrally between the two half cones 13 and 16 injected.
  • a gaseous fuel is preferred along the Entry slots 17 injected through a plurality of holes.
  • the combustion air flow 10 envelops the injected fuel and a fuel cone is formed, which widens towards the front, and which after leaving the Combustion chamber 21 at the burner mouth 20 in one, schematically in the figure illustrated flame 12 burns. Rolling up is also indicated in FIG. 1 of the fuel-combustion air mixture behind the front edge 18 when entering the combustion chamber 21. Because for the thermoacoustic feedback Properties of the boundary layer between flowing mixture 11 and half cones 13 and 16 is crucial, the behavior of this boundary layer should first be more precise to be examined.
  • the displacement thickness is given by:
  • the combustion in the eddies 24 of the Kelvin-Helmholtz waves 22 also pulsates at the same frequency and drives the acoustic field in the combustion chamber 21. Since the acoustic field is able to transmit the Tolmien-Schlichting waves (TS) in the to clock the first boundary layer, the following feedback circuit forms: ⁇ TS ⁇ KH ⁇ pulsating combustion ⁇ acoustic field ⁇ TS ⁇ KH ⁇ ....
  • vertically extending TS waves can be attached of shark tooth-like, essentially the central axis of the torch Prevent 19 facing projections on the front edges 18.
  • the coherent Cross waviness in the boundary layer is thus overlaid by a longitudinal disturbance and destroyed by this. Problems with such "shark teeth” can be that they can burn down due to the heat and radiation.
  • a ring of through bores 25 in the formwork elements acts in an analogous manner 13 and / or 16, as shown in Figure 2.
  • the Bores 25 are in the region of the leading edge 18 and in their sequence arranged substantially parallel to the front edge. Is the pressure drop comparable to the pressure drop across the entire burner 19 via the bores 25, such bores are able to cross the boundary layer in the area of the leading edge 18 and thus disturb the TS waves in this region to destroy.
  • the diameter of the bores 25 should at least match that The thickness of the boundary layer may be comparable. For an applicant's EV17 burner is therefore a diameter of a few millimeters, in particular 3 mm prefer.
  • the distance between the holes 25 should be roughly in the range the wavelength of the highest occurring thermoacoustic frequency lie. To prevent the suction effects of neighboring holes 25 do not cancel each other out, you should also make sure that the distance between the bores 25 is not significantly smaller than the distance of holes 25 from the leading edge.

Landscapes

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

Claims (1)

  1. Brûleur (19)
    comprenant deux demi-cônes (13, 16) dont les axes sont décalés l'un par rapport à l'autre et forment ainsi des fentes d'entrées (17) pour l'entrée tangentielle d'un courant d'air de combustion (10),
    dans lequel le long des fentes d'entrée (17) est disposée une pluralité de trous pour l'injection d'un combustible gazeux,
    dans lequel, au niveau de l'extrémité rétrécie des demi-cônes (13, 16), se trouve une partie cylindrique (15), dans laquelle est disposée une buse de combustible centrale (14) et
    dans lequel le mélange air-combustible (11) formé dans le brûleur (19) peut être introduit dans une chambre de combustion (21) suivant le brûleur (19),
    caractérisé en ce qu'
    une pluralité de saillies en forme de dents est disposée au niveau des bords avant (18) des demi-cônes (13, 16), tournée vers l'axe central du brûleur (19), afin de perturber des instabilités d'écoulement cohérentes dans la couche limite entre le mélange air-combustible (11) et les demi-cônes (13, 16) et d'éviter un couplage d'un champ acoustique dans la chambre de combustion (21) suivant le brûleur (19) aux instabilités d'écoulement cohérentes.
EP98811115A 1998-11-09 1998-11-09 Brûleur Expired - Lifetime EP1001214B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE59811961T DE59811961D1 (de) 1998-11-09 1998-11-09 Brenner
EP98811115A EP1001214B1 (fr) 1998-11-09 1998-11-09 Brûleur
US09/431,176 US20010019815A1 (en) 1998-11-09 1999-11-01 Method for preventing flow instabilities in a burner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811115A EP1001214B1 (fr) 1998-11-09 1998-11-09 Brûleur

Publications (2)

Publication Number Publication Date
EP1001214A1 EP1001214A1 (fr) 2000-05-17
EP1001214B1 true EP1001214B1 (fr) 2004-09-15

Family

ID=8236431

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98811115A Expired - Lifetime EP1001214B1 (fr) 1998-11-09 1998-11-09 Brûleur

Country Status (3)

Country Link
US (1) US20010019815A1 (fr)
EP (1) EP1001214B1 (fr)
DE (1) DE59811961D1 (fr)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10000415A1 (de) * 2000-01-07 2001-09-06 Alstom Power Schweiz Ag Baden Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine
FI108810B (fi) * 2000-07-06 2002-03-28 Nirania Ky Laitteisto ja menetelmä polttotapahtuman ja lämmönsiirron tehostamiseksi
DE10055408A1 (de) 2000-11-09 2002-05-23 Alstom Switzerland Ltd Verfahren zur Brenstoffeinspritzung in einen Brenner
DE10064893A1 (de) * 2000-12-23 2002-11-14 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeindüsung
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE102008012794B3 (de) * 2008-03-05 2009-08-20 Auerhahn Bestecke Gmbh Feuerungseinrichtung
US20100119984A1 (en) * 2008-11-10 2010-05-13 Fox Allen G Abatement system
US10197291B2 (en) 2015-06-04 2019-02-05 Tropitone Furniture Co., Inc. Fire burner
USD791930S1 (en) 2015-06-04 2017-07-11 Tropitone Furniture Co., Inc. Fire burner

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5375995A (en) * 1993-02-12 1994-12-27 Abb Research Ltd. Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation
EP0851172A2 (fr) * 1996-12-23 1998-07-01 Abb Research Ltd. Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1134996A (en) * 1967-04-21 1968-11-27 Lev Iosifovich Sorkin Jet noise suppressor in jet engine
US4244441A (en) * 1979-07-31 1981-01-13 The Garrett Corporation Broad band acoustic attenuator
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
US5676538A (en) * 1993-06-28 1997-10-14 General Electric Company Fuel nozzle for low-NOx combustor burners
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
ATE170968T1 (de) * 1995-07-20 1998-09-15 Dvgw Ev Verfahren und vorrichtung zur unterdrückung von flammen-/druckschwingungen bei einer feuerung

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5375995A (en) * 1993-02-12 1994-12-27 Abb Research Ltd. Burner for operating an internal combustion engine, a combustion chamber of a gas turbine group or firing installation
EP0851172A2 (fr) * 1996-12-23 1998-07-01 Abb Research Ltd. Brûleur pour la mise en oeuvre d'une chambre de combustion avec un combustible liquide ou gazeux

Also Published As

Publication number Publication date
DE59811961D1 (de) 2004-10-21
EP1001214A1 (fr) 2000-05-17
US20010019815A1 (en) 2001-09-06

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