EP0987491B1 - Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner - Google Patents
Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner Download PDFInfo
- Publication number
- EP0987491B1 EP0987491B1 EP98810924A EP98810924A EP0987491B1 EP 0987491 B1 EP0987491 B1 EP 0987491B1 EP 98810924 A EP98810924 A EP 98810924A EP 98810924 A EP98810924 A EP 98810924A EP 0987491 B1 EP0987491 B1 EP 0987491B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- air
- fuel
- combustion
- disturbance
- burner
- 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
Links
Images
Classifications
-
- 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
- F23C7/02—Disposition of air supply not passing through burner
-
- 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
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
-
- 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
- F23D2206/00—Burners for specific applications
- F23D2206/10—Turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2210/00—Noise abatement
Definitions
- the present invention relates to Method for operating a burner, according to the preamble of claim 1.
- the invention relates also to a burner according to the preamble of claim 2.
- EP-B1-0 321 809 is a burner for liquid and gaseous fuels known with premix, in which externally supplied combustion air moved tangentially between at least two entry slots arranged, hollow half-cones enters and there in the direction of the combustion chamber flows, and in which on the side facing away from the combustion chamber, the tapered side the half-cones of the liquid fuel is injected centrally.
- the fuel will so to speak, captured and "enveloped" by the combustion air, so that forms a conical liquid fuel profile between the half-cones, which expands in the direction of the combustion chamber and burns there.
- gaseous Fuel is taken from fuel supply pipes that run along the air intake slots run, injected through rows of holes across the incoming air.
- thermoacoustic oscillations are primarily responsible for an important class 1 of reaction rate variations induced thermoacoustic oscillations.
- These largely coherent waves result in a burner of the above Type under typical operating conditions to vibrations with frequencies of about 100 Hz. Since this frequency has typical fundamental eigenmodes of Of many torches of gas turbines coincide, represent the thermoacoustic Oscillations are a problem.
- 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 required combustion air passed through tangential air inlet channels in an interior of the burner.
- This flow is created in the interior of a swirl flow, which at the output of Burner induces a backflow zone.
- At least one zone is provided in each part body forming the burner, within which inlet openings for the injection of additional air into the swirl flow are provided.
- this injection forms on the inner wall of the body part Film, which prevents the flame along the inner wall of the part body in the interior of the burner can strike back.
- the invention is therefore based on the object a procedure and to provide a burner for carrying out the method, which provides for the formation of coherent flow instabilities of the combustion air flow after exiting into the Combustion chamber prevented.
- Another embodiment of the invention is characterized in that it the burner is a double - cone burner, that the injection of the Disturbance air through interference nozzles, and that the disturbance air directly at the leading edges of the half-cones takes place where the shear layers form. Furthermore, it is preferred that the disturbance nozzles be uniform in certain Distributes intervals on the sizes of leading edges of half-cones, becomes so the periodicity of the waves on the shear layers disrupted what the prevention the thermoacoustic oscillations targeted causes in the nucleus of their formation.
- FIG. 1 shows a section through an idealized shear layer 10, as assumed for the subsequent calculations.
- the shear layer 10 is of a thickness h, and the coordinate system is laid so that the axes x and z are in the shear layer, the axis y is perpendicular thereto, and the main flow direction (longitudinal) is along x.
- the origin of the coordinate system is such that the thickness of the shear layers 10 extends along y from -h / 2 to + h / 2, and that the layer at the top in the figure moves along x at a velocity U o Moves to the right, while the layer shown in Figure 1 below moves at a speed -U o along x to the left.
- a is the growth exponent of the perturbation in 1 / s
- U 0 is the edge velocity at the shear layer 10
- k z is the Component of the wave vector along z, ie in the transverse direction.
- FIG. 5 shows various views of a double-cone burner 26, based on which the technical realization of the above-described principle is to be shown.
- figure 5a shows a perspective view of a double-cone burner 26.
- the combustion air 14 enters laterally through the entry slots 23 of the slightly shifted Axes arranged, hollow half-cones 18 and 21, flows to the front end the burner 26 with description of a slight arc, and occurs after passing the leading edge 24 of the half-cones 18, 21 from the burner 26 into the combustion chamber 28.
- Am tapered end of the half-cones 18, 21 is a cylindrical part 20, in which a fuel nozzle 19 is arranged, which in this case liquid Insert fuel centrally between the two half-cones 18 and 21.
- the combustion air 14 envelops the injected fuel, and it forms a fuel cone, which expands towards the front, and which as a mixture 15 of combustion air 14 and fuel and Greunstaff after exiting into the Combustion chamber 28 burns at the burner mouth 27 in a flame 17.
- FIG. 5c) shows a view from above onto the double-cone burner 26.
- the spacing of the stub nozzles 16 can be easily traced.
- the transversal perturbation must be such that the perturbation nozzles 16 generate perturbation air streams which are 5 cm apart in the x-direction, ie in the flow direction of the mixture.
- FIG. 5d) shows a schematic front view of a double-cone burner 26. Again, the orthogonal intermingling of the mixture 15 and the interfering air 22 is recognizable.
- the injected air flow 22 has no strong, inwardly directed components, so that the mixture 15 is not disturbed .
- the total pressure of the injection of the disturbance air 22 must be at least as great as the total pressure of the mixture flowing past 15, so that significant transversal disturbances can form at all.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Description
- Fig. 1
- zeigt eine schematische Darstellung einer Scherschicht und die in der Beschreibung verwendeten Grössen inkl. Koordinatensystem;
- Fig. 2
- zeigt den dimensionslosen Wachstumskoeffizienten als Funktion der dimensionslosen Wellenlänge;
- Fig. 3
- zeigt die dimensionslose Wellenzahl mit maximalem Wachstum als Funktion der dimensionslosen transversalen Komponente des Wellenvektors;
- Fig. 4
- zeigt den dimensionslosen Wachstumsfaktor als Funktion der dimensionslosen transversalen Komponente des Wellenvektors; und in
- Fig. 5
- sind schematische Darstellungen eines Doppelkegelbrenners mit Störungsdüsen abgebildet. a) perspektivische Ansicht, b) Schnitt senkrecht zur Hauptströmungsrichtung durch Störungsdüse, c) Ansicht von oben, d) Ansicht von vorn.
- 10
- Scherschicht
- 11
- Maximum des dimensionslosen Wachstumskoeffizienten
- 12
- Bereich ohne Wachstum
- 13
- Bereich mit Wachstum
- 14
- Verbrennungsluft
- 15
- Gemisch von Verbrennungsluft 14 und Brennstoff
- 16
- Störungsdüsen
- 17
- Flamme
- 18
- erster Halbkonus
- 19
- Brennstoffdüse
- 20
- zylindrischer Teil des Brenners 26
- 21
- zweiter Halbkonus
- 22
- Störungsluft
- 23
- Eintrittsschlitz
- 24
- Vorderkante des Halbkonus 18, 21
- 25
- Leitung zu Störungsdüse 16
- 26
- Brenner, Doppelkegelbrenner
- 27
- Brennermündung
- 28
- Brennkammer
Claims (5)
- Verfahren zum Betrieb eines aus versetzt angeordneten, hohlen Halbkonussen (18,21) bestehenden Vormischbrenners (26), bei welchemein Verbrennungsluftstrom (14) über wenigstens zwei durch die Halbkonusse gebildeten Eintrittsschlitze (23) tangential eingedüst wird,ein Brennstoff zentral eingedüst wird und/oder ein gasförmiger Brennstoff in die quer eintretende Verbrennungsluftströmung eingedüst wird,der Verbrennungsluftstrom (14) mit Brennstoff innerhalb des Brenners (26) vorgemischt wird, und das sich bildende Brennstoff-/Luft-Gemisch (15) in eine dem Brenner (26) nachfolgende Brennkammer (28) transportiert wird,in welcher das Brennstoff-/Luft-Gemisch (15) unter Bildung von Heissgasen verbrannt wird,wobei sich kohärente Strömungsinstabilitäten nach Austritt des Brennstoff-/Luft-Gemisches (15) in die Brennkammer (28) infolge einer Scherschicht (10) zwischen dem austreten den Gemisch (15) und den Heissgasen in der Brennkammer (28) bilden, undwobei eine Störungsluft (22) in das Brennstoff-/Luft-Gemisch (15) eingedüst wird,
unmittelbar an den Vorderkanten (24) der Halbkonusse die Störungsluft (22) im wesentlichen senkrecht zu der Hauptströmungsrichtung des Brennstoff-/Luft-Gemisches (15) und im wesentlichen parallel zur Scherschicht (10) in den Strom des Brennstoff-/Luft-Gemisches (15) eingedüst wird. - Vormischbrenner zur Durchführung des Verfahrens, wobeider Vormischbrenner (26) aus versetzt angeordneten, hohlen Halbkonussen (18, 21) besteht, die wenigstens zwei Eintrittsschlitze (23) für eine Verbrennungsluft (14) bilden,die Halbkonusse (18, 21) brennkammerseitig von Vorderkanten (24) begrenzt sind,am verjüngten Ende der Halbkonusse (18, 21) ein zylindrischer Teil (20) mit einer Brennstoffdüse angeordnet ist,die Halbkonusse (18, 21) Störungsdüsen (16) zur Eindüsung von Strörungsluft aufweisen,die Störungsdüsen (16) unmittelbar vor den Vorderkanten (24) der Halbkonusse (18,21) derart eingelassen sind, dass sie eine Störungsluft (22) senkrecht zur Hauptströmungsrichtung eines austretenden Brennstoff-/Luft-Gemisches (15) in die Brennkammer (28) in die stromab der Vorderkanten (24) sich bildende Scherschicht (10) und im wesentlichen parallel zu dieser Scherschicht eindüsen.
- Vormischbrenner nach Anspruch 2,
dadurch gekennzeichnet, dass
eine Vielzahl von Störungsdüsen (16) angeordnet ist, und dass die Störungsdüsen (16) gleichmässig auf den Umfängen der Halbkonusse (18,21) verteilt sind. - Vormischbrenner nach Anspruch 3,
dadurch gekennzeichnet, dassdie gleichmässige Beabstandung der Störungsdüsen (16) derart gewählt ist, dass sie gleich oder kleiner ist als ein kritischer Wert, undsich dieser kritische Wert aus der Strömungsgeschwindigkeit der Verbrennungsluft und der beim Brenner ohne Störungsdüsen (16) auftretenden Frequenz der kohärenten Strömungsinstabilitäten des Brennstoff-/Luft-Gemisches (15) ergibt,dergestalt, dass sich der kritische Wert als mit 0.312 multiplizierter Quotient der Strömungsgeschwindigkeit der Verbrennungsluft (15) und der beim Brenner ohne Störungsdüsen (16) auftretenden Frequenz der kohärenten Strömungsinstabilitäten des Verbrennungsluftstroms (15) ergibt. - Vormischbrenner nach Anspruch 4,
dadurch gekennzeichnet, dass
bei einer beim Vormischbrenner (26) ohne Störungsdüsen (16) auftretenden Frequenz der kohärenten Strömungsinstabilitäten des Verbrennungsluftstroms (15) im Bereich von 100 bis 125 Hz und einer Strömungsgeschwindigkeit der Verbrennungsluft (15) im Bereich von 20 bis 30 m/s die Störungsdüsen (16) auf den Halbkonussen (18, 21) eine Beabstandung im Bereich von 3 bis 5 cm, insbesondere im Bereich von 4.5 bis 5cm aufweisen.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98810924A EP0987491B1 (de) | 1998-09-16 | 1998-09-16 | Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner |
DE59812944T DE59812944D1 (de) | 1998-09-16 | 1998-09-16 | Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner |
US09/382,628 US6390805B1 (en) | 1998-09-16 | 1999-08-25 | Method of preventing flow instabilities in a burner |
JP11254540A JP2000104923A (ja) | 1998-09-16 | 1999-09-08 | バ―ナにおける流動不安定性を回避するための方法 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98810924A EP0987491B1 (de) | 1998-09-16 | 1998-09-16 | Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0987491A1 EP0987491A1 (de) | 2000-03-22 |
EP0987491B1 true EP0987491B1 (de) | 2005-07-20 |
Family
ID=8236326
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98810924A Expired - Lifetime EP0987491B1 (de) | 1998-09-16 | 1998-09-16 | Verfahren zur Verhinderung von Strömungsinstabilitäten in einem Brenner |
Country Status (4)
Country | Link |
---|---|
US (1) | US6390805B1 (de) |
EP (1) | EP0987491B1 (de) |
JP (1) | JP2000104923A (de) |
DE (1) | DE59812944D1 (de) |
Families Citing this family (4)
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 |
DE50212753D1 (de) | 2001-07-26 | 2008-10-23 | Alstom Technology Ltd | Vormischbrenner mit hoher Flammenstabilität |
BR112015031702B1 (pt) * | 2013-06-17 | 2021-07-06 | Schlumberger Technology B.V. | conjuntos de queimadores para queima de gás de baixo valor calorífico e método de queima de gás de baixo valor calorífico |
CN115751378A (zh) * | 2022-11-10 | 2023-03-07 | 南昌航空大学 | 一种带梯形筋条和三角凸块的支板火焰稳定器 |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0851172A2 (de) * | 1996-12-23 | 1998-07-01 | Abb Research Ltd. | Brenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff |
Family Cites Families (11)
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 |
US3788065A (en) * | 1970-10-26 | 1974-01-29 | United Aircraft Corp | Annular combustion chamber for dissimilar fluids in swirling flow relationship |
US3879939A (en) * | 1973-04-18 | 1975-04-29 | United Aircraft Corp | Combustion inlet diffuser employing boundary layer flow straightening vanes |
JPS5632961A (en) | 1979-08-25 | 1981-04-02 | Minamoto:Kk | Oshizushi (pressed vinegared fish and rice) of yellowtail and its preparation |
JPS5632962A (en) | 1979-08-27 | 1981-04-02 | Hiroji Shimizu | Forming device for maki (rolled)sushi (vinegared rice with fish and vegetables) |
JPS57108507A (en) * | 1980-12-25 | 1982-07-06 | Matsushita Electric Ind Co Ltd | Gun type burner |
JPS57108508A (en) * | 1980-12-25 | 1982-07-06 | Matsushita Electric Ind Co Ltd | Gun type burner |
CH674561A5 (de) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
CH680467A5 (de) * | 1989-12-22 | 1992-08-31 | Asea Brown Boveri | |
US5345768A (en) * | 1993-04-07 | 1994-09-13 | General Electric Company | Dual-fuel pre-mixing burner assembly |
ATE170968T1 (de) * | 1995-07-20 | 1998-09-15 | Dvgw Ev | Verfahren und vorrichtung zur unterdrückung von flammen-/druckschwingungen bei einer feuerung |
-
1998
- 1998-09-16 EP EP98810924A patent/EP0987491B1/de not_active Expired - Lifetime
- 1998-09-16 DE DE59812944T patent/DE59812944D1/de not_active Expired - Fee Related
-
1999
- 1999-08-25 US US09/382,628 patent/US6390805B1/en not_active Expired - Fee Related
- 1999-09-08 JP JP11254540A patent/JP2000104923A/ja active Pending
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0851172A2 (de) * | 1996-12-23 | 1998-07-01 | Abb Research Ltd. | Brenner zum Betrieb einer Brennkammer mit einem flüssigen und/oder gasförmigen Brennstoff |
Also Published As
Publication number | Publication date |
---|---|
US6390805B1 (en) | 2002-05-21 |
EP0987491A1 (de) | 2000-03-22 |
DE59812944D1 (de) | 2005-08-25 |
JP2000104923A (ja) | 2000-04-11 |
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