EP1001214A1 - Procédé pour empêcher la formation d'instabilités d'écoulement dans un brûleur - Google Patents

Procédé pour empêcher la formation d'instabilités d'écoulement dans un brûleur Download PDF

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Publication number
EP1001214A1
EP1001214A1 EP98811115A EP98811115A EP1001214A1 EP 1001214 A1 EP1001214 A1 EP 1001214A1 EP 98811115 A EP98811115 A EP 98811115A EP 98811115 A EP98811115 A EP 98811115A EP 1001214 A1 EP1001214 A1 EP 1001214A1
Authority
EP
European Patent Office
Prior art keywords
burner
combustion
flow
flow instabilities
fuel
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
EP98811115A
Other languages
German (de)
English (en)
Other versions
EP1001214B1 (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
ABB Schweiz AG
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Schweiz AG, ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Schweiz 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. It relates to a device and a Method for operating a burner, in which a combustion air flow Fuel is transported to a combustion chamber, where the fuel is burned, and mixed with the fuel during transport of the combustion air stream and is guided by formwork elements.
  • EP-B1-0 321 809 describes a burner for liquid and gaseous fuels became known without a premixing section, in which feed from the outside Combustion air is displaced tangentially through at least two inlet slots arranged, hollow half-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 is so to speak 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 drawn from fuel supply pipes that run along the air inlet slots run, injected transversely into the incoming air through rows of holes.
  • combustion air forms behind the front edge in the direction of flow the half-cones immediately a shear layer.
  • This shear layer lies between the essentially stationary 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 so-called Kelvin-Helmholtz waves first appear on the shear layers form, the wave crests of which run transversely 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 von many ring burners of gas turbines coincide, make the thermoacoustic Oscillations are a problem.
  • the invention is therefore based on the object, a device or a To provide burners and a method for operating such a device, which is the rocking interaction of coherent flow instabilities and acoustic field reduced.
  • This object is achieved in a device or a method of the aforementioned Kind of solved by the formation of first periodic, coherent Flow instabilities in a boundary layer between the combustion air and the formwork elements is disturbed, and by coupling an acoustic Field in the combustion chamber at such first flow instabilities is 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.
  • a first preferred embodiment of the invention is characterized in that that the first flow instabilities are Tolmien-Schlichting waves in the boundary layer between the combustion air flow and formwork elements is that these are more preferably able to handle 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. Also finds the disturbance of the first flow instabilities preferably in the vicinity of the Front edge of the shuttering elements facing the combustion chamber instead.
  • Another embodiment has the feature that the disturbance mediates through holes in the formwork elements. The pressure drop Through these holes, the cross ripple in the boundary layer is broken.
  • FIG. 1 shows schematically the flow conditions in a double-cone burner.
  • the combustion air 10 passes laterally through the inlet slots 17 with light arranged displaced axes, hollow half-cones 13 and 18, flows to the front end of the burner, 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. Gaseous fuels are 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 22 of the fuel / combustion air mixture behind the front edge 18 when entering the combustion chamber.
  • thermoacoustic feedback Properties of the boundary layer between flowing air 11 and half cones 13 and 16 is decisive, 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 also pulsates at the same frequency and thereby drives the acoustic field in the combustion chamber 21. Since the acoustic field is able to transmit the Tolmien-Schlichting waves (TS) in the first To clock the boundary layer, the following feedback circuit forms: ⁇ TS ⁇ KH ⁇ pulsating combustion ⁇ acoustic field ⁇ TS ⁇ KH ⁇ ...
  • Vertical TS waves can be attached, for example of shark tooth-like, essentially the central axis of the torch Prevent 19 facing projections on the front edges 18.
  • the coherent Cross-ripple in the boundary layer is thus overlaid by a longitudinal disturbance 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 acts in the formwork elements 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 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 thermo-acoustic 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)
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 true EP1001214A1 (fr) 2000-05-17
EP1001214B1 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)

Cited By (5)

* 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
EP1205713A1 (fr) * 2000-11-09 2002-05-15 ALSTOM Power N.V. Procédé d'injection de combustible dans un brûleur
WO2002052201A1 (fr) * 2000-12-23 2002-07-04 Alstom (Switzerland) Ltd Bruleur a injection de combustible etagee
WO2003056241A1 (fr) * 2001-12-24 2003-07-10 Alstom Technology Ltd Bruleur presentant une injection de combustible etagee
DE102008012794B3 (de) * 2008-03-05 2009-08-20 Auerhahn Bestecke Gmbh Feuerungseinrichtung

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FI108810B (fi) * 2000-07-06 2002-03-28 Nirania Ky Laitteisto ja menetelmä polttotapahtuman ja lämmönsiirron tehostamiseksi
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 (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
EP0321809A1 (fr) * 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
US5408830A (en) * 1994-02-10 1995-04-25 General Electric Company Multi-stage fuel nozzle for reducing combustion instabilities in low NOX gas turbines
US5676538A (en) * 1993-06-28 1997-10-14 General Electric Company Fuel nozzle for low-NOx combustor burners
US5758587A (en) * 1995-07-20 1998-06-02 Horst Buchner Process and device for suppression of flame and pressure pulsations in a furnace

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4304213A1 (de) * 1993-02-12 1994-08-18 Abb Research Ltd Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage
DE19654116A1 (de) * 1996-12-23 1998-06-25 Abb Research Ltd Brenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff

Patent Citations (7)

* 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
EP0321809A1 (fr) * 1987-12-21 1989-06-28 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
EP0321809B1 (fr) 1987-12-21 1991-05-15 BBC Brown Boveri AG Procédé pour la combustion de combustible liquide dans un brûleur
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
US5758587A (en) * 1995-07-20 1998-06-02 Horst Buchner Process and device for suppression of flame and pressure pulsations in a furnace

Cited By (8)

* 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
US6698209B1 (en) 2000-01-07 2004-03-02 Alstom Technology Ltd Method of and appliance for suppressing flow eddies within a turbomachine
EP1205713A1 (fr) * 2000-11-09 2002-05-15 ALSTOM Power N.V. Procédé d'injection de combustible dans un brûleur
US6705857B2 (en) 2000-11-09 2004-03-16 Alstom Technology Ltd. Method for injecting fuel into a burner
WO2002052201A1 (fr) * 2000-12-23 2002-07-04 Alstom (Switzerland) Ltd Bruleur a injection de combustible etagee
WO2003056241A1 (fr) * 2001-12-24 2003-07-10 Alstom Technology Ltd Bruleur presentant une injection de combustible etagee
US7241138B2 (en) 2001-12-24 2007-07-10 Alstom Technology Ltd. Burner with stepped fuel injection
DE102008012794B3 (de) * 2008-03-05 2009-08-20 Auerhahn Bestecke Gmbh Feuerungseinrichtung

Also Published As

Publication number Publication date
DE59811961D1 (de) 2004-10-21
US20010019815A1 (en) 2001-09-06
EP1001214B1 (fr) 2004-09-15

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