EP0909921B1 - Brenner für den Betrieb eines Wärmeerzeugers - Google Patents
Brenner für den Betrieb eines Wärmeerzeugers Download PDFInfo
- Publication number
- EP0909921B1 EP0909921B1 EP97810773A EP97810773A EP0909921B1 EP 0909921 B1 EP0909921 B1 EP 0909921B1 EP 97810773 A EP97810773 A EP 97810773A EP 97810773 A EP97810773 A EP 97810773A EP 0909921 B1 EP0909921 B1 EP 0909921B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- burner according
- downstream
- fuel
- swirl generator
- 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
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Classifications
-
- 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
- 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
- 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
- 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
- F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
- F23D14/78—Cooling burner parts
-
- 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
- F23D—BURNERS
- F23D23/00—Assemblies of two or more burners
-
- 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
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
Definitions
- a large number of mixing elements are concentric with the mixing section provided which the formation of a mixture of combustion air and Serve fuel. This mixture forms from the respective mixing element then a pilot stage of the combustion chamber.
- This burner guarantees compared to those from the previous state the technology a significant improvement in terms of strengthening flame stability, lower pollutant emissions, lower pulsations, complete Burnout, large operating area, good cross-ignition between the different Brennem, compact design, improved mixing, etc.
- This burner has autonomous arrangements to drive the gas turbine safely, especially in its transient load ranges to be able to. The integration of such precautions in the burner lead to no additional pollutant emissions, which the operational and emissions advantages of the underlying burner could question.
- the invention seeks to remedy this.
- the invention the task is based on a burner at the beginning to propose precautions which strengthen the flame stability for stable operation, especially in the transient load ranges, ensure under the further task that the Pollutant emissions remain low.
- the burner is expanded in such a way that in the area of its transition a ring-shaped system to provide for the downstream combustion chamber a fuel / air mixture is generally provided as Pilot stage acts.
- Pilot stage acts Through a number of circumferential exit bores Appropriate pilot burners are created in the combustion chamber, which are operated in diffusion mode for stability reasons and directly in the combustion chamber.
- the object according to the invention also ensures that the minimized Cooling amount can also be fed to the burning process.
- Fig. 1 shows the overall structure of a burner.
- a swirl generator 100 is effective, the design of which is shown and described in more detail in the following FIGS. 3-6.
- This swirl generator 100 is a conical structure which is acted upon tangentially several times by a tangentially flowing combustion air flow 115.
- the flow formed here is seamlessly transferred to a transition piece 200 using a transition geometry provided downstream of the swirl generator 100, in such a way that no separation areas can occur there.
- the configuration of this transition geometry is described in more detail in FIG. 6.
- This transition piece 200 is extended on the outflow side of the transition geometry by a mixing tube 20, both parts forming the actual mixing section 220.
- these bores 21 run at an acute angle with respect to the burner axis 60.
- the outlet of the transition channels 201 corresponds to the narrowest flow cross-section of the mixing tube 20.
- the transition channels 201 mentioned therefore bridge the respective cross-sectional difference without adversely affecting the flow formed. If the selected precaution triggers an intolerable pressure loss when guiding the pipe flow 40 along the mixing pipe 20, this can be remedied by providing a diffuser (not shown in the figure) at the end of this mixing pipe.
- a combustion chamber 30 combustion chamber then adjoins the end of the mixing tube 20, a cross-sectional jump formed by a burner front 70 being present between the two flow cross sections.
- the transfer of the gaseous fuel 303 from the annular chamber 301 into the downstream annular chamber 308 is accomplished by a number of openings 309 arranged in the circumferential direction.
- the passage geometry of these openings 309 is designed such that the gaseous fuel 303 flows into the downstream annular chamber 308 with a large mixing potential.
- the other annular chamber 302 closes with a perforated plate 305, the bores 310 provided here being designed in such a way that the air volume 304 flowing through there impacts cooling on the base plate 307 of the downstream annular chamber 308.
- This base plate has the function of a heat protection plate against the calorific load from the combustion chamber 30, so that this impingement cooling must be extremely efficient here.
- this air mixes within this annular chamber 308 with the inflowing gaseous fuel 303 from the openings 309 of the upstream annular chamber 301 before this mixture through a number of bores 306 arranged on the combustion chamber side into the combustion chamber 30 flows out.
- the mixture flowing out burns as a premixed diffusion flame with minimized pollutant emissions and therefore forms Bore 306 a pilot burner acting in the combustion chamber 30, which one guaranteed stable operation.
- Fig. 2 shows a schematic view of the burner according to Fig. 1, here in particular the flushing of a centrally arranged fuel nozzle 103 and the effect of fuel injectors 170 is pointed out.
- the mode of action the remaining main components of the burner, namely swirl generator 100 and transition piece 200 are closer under the following figures described.
- the fuel nozzle 103 is spaced with a ring 190 encased in which a number of circumferentially bored holes 161 are placed, through which an amount of air 160 into an annular chamber 180 flows and removes the flow around the fuel lance.
- These holes 161 are slanted forward so that it is appropriate axial component arises on the burner axis 60.
- FIG. 4 is used at the same time as FIG. 3.
- 3 is referred to the other figures as necessary in the description of FIG.
- the first part of the burner according to FIG. 1 forms the swirl generator shown in FIG. 3 100.
- This consists of two hollow conical partial bodies 101, 102, which are nested in a staggered manner.
- the number of conical Partial body can of course be larger than two, like the figures 5 and 6 show; this depends in each case, as will be explained in more detail below will depend on the operating mode of the entire burner. It is with certain Operating constellations are not excluded, one from a single spiral to provide existing swirl generator.
- the offset of the respective central axis or longitudinal symmetry axes 101b, 102b (cf. FIG. 4) of the conical partial bodies 101, 102 creates each other in the adjacent wall, in mirror image Arrangement, each a tangential channel, i.e.
- the conical sub-bodies 101, 102 each have a fuel line 108, 109 which run along the tangential air inlet slots 119, 120 arranged and provided with injection openings 117, through which preferably a gaseous fuel 113 in the combustion air flowing through there 115 is injected, as the arrows 116 want to symbolize.
- Fuel nozzle 103 brought fuel 112 is, as mentioned, normally a liquid fuel, whereby a mixture formation with a other medium, for example with a recirculated flue gas, without further is possible.
- This fuel 112 is preferably very low acute angle injected into the cone cavity 114. From the fuel nozzle 103 A conical fuel spray 105 is thus formed, which flows in from the tangential one rotating combustion air 115 is enclosed and degraded.
- the concentration of the injected fuel is then in the axial direction 112 continuously through the incoming combustion air 115 for mixing Degraded towards evaporation. If a gaseous fuel 113 Introduced via the opening nozzles 117, the fuel / air mixture is formed directly at the end of the air inlet slots 119, 120. Is the combustion air 115 additionally preheated, or for example with a recirculated Flue gas or exhaust gas enriched, so this sustainably supports the Evaporation of the liquid fuel 112 before this mixture in the downstream Stage flows, here in the transition piece 200 (see FIGS. 1 and 7). The same considerations also apply if liquid lines 108, 109 Fuels should be supplied.
- the construction of the swirl generator 100 is furthermore particularly suitable, change the size of the tangential air inlet slots 119, 120, which is a relatively large one without changing the overall length of the swirl generator 100 operational bandwidth can be captured.
- the partial bodies 101, 102 can also be moved relative to one another in another plane, which even an overlap of the same can be provided.
- the sub-bodies 101, 102 by a counter-rotating movement spiral to nest into each other. So it is possible, the shape, the size and the configuration of the tangential air inlet slots 119, 120 arbitrarily vary, with which the swirl generator 100 is universal without changing its overall length can be used.
- Baffles 121a, 121b have a flow initiation function which, according to their length, the respective end of the tapered Partial bodies 101, 102 in the flow direction with respect to the combustion air 115 extend.
- Channeling the combustion air 115 into the cone cavity 114 can be opened or closed by one of the baffles 121a, 121b Area of entry of this channel into the cone cavity 114 placed fulcrum 123 can be optimized, especially if the original Gap size of the tangential air inlet slots 119, 120 changed dynamically should be, for example, to change the speed of the combustion air 115 to achieve.
- these can be dynamic Precautions can also be provided statically by using baffles as needed form a fixed component with the tapered partial bodies 101, 102.
- FIG. 6 differs from FIG. 5 in that the partial bodies 140 here 141, 142, 143 have a blade profile shape which is used to provide a certain Flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same.
- the admixture of fuel 116 in the combustion air flow 115 happens from inside the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
- the swirl angle of the transition channels 201 in the flow direction is selected so that that the pipe flow then up to the cross-sectional jump on Combustion chamber entry still has a sufficient distance to be perfect Premix with the injected fuel. Further increases the axial speed due to the above-mentioned measures on the mixing tube wall downstream of the swirl generator.
- the transition geometry and the measures in the area of the mixing tube cause a significant increase the axial velocity profile towards the center of the mixing tube, see above that the danger of early ignition is decisively counteracted.
- the flow cross section of the tube 20 receives one in this area Transition radius R, the size of which basically depends on the flow within of the tube 20 depends.
- This radius R is chosen so that the Applies flow to the wall and so the swirl number increases sharply.
- the size of the radius R can be defined so that it is> 10% of the inside diameter d of the tube is 20.
- the backflow bladder 50 increases enormously.
- This radius R runs to the exit plane of the tube 20, the angle ⁇ between the beginning and end of curvature is ⁇ 90 °.
- the tear-off edge A runs inside the tube 20 and thus forms a tear-off step S opposite the front point of the tear-off edge A, whose depth> 3 mm is.
- this can be parallel to the exit plane of the tube 20 running edge based on a curved course back to the exit level to be brought.
- the angle ⁇ ' which is between the tangent of the tear-off edge A and perpendicular to the exit plane of the tube 20 is the same size like angle ⁇ .
- Another Design of the tear-off edge for the same purpose can be done with the combustion chamber achieve toroidal notches. This publication is inclusive the scope of protection there regarding the tear-off edge is an integrating one Part of this description.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Description
- Fig. 1
- einen als Vormischbrenner ausgelegten Brenner mit einer Mischstrecke stromab eines Drallerzeugers sowie mit Pilotbrennern,
- Fig. 2
- eine schematische Darstellung des Brenners gemäss Fig. 1 mit Disposition der zusätzlichen Brennstoff-Injektoren.
- Fig. 3
- einen aus mehreren Schalen bestehenden Drallerzeuger in perspektivischer Darstellung, entsprechend aufgeschnitten,
- Fig. 4
- einen Querschnitt durch einen zweischaligen Drallerzeuger,
- Fig. 5
- einen Querschnitt durch einen vierschaligen Drallerzeuger,
- Fig. 6
- eine Ansicht durch einen Drallerzeuger, dessen Schalen schaufelförmig profiliert sind,
- Fig. 7
- eine Ausgestaltung der Uebergangsgeometrie zwischen Drallerzeuger und Mischstrecke und
- Fig. 8
- eine Abrisskante zur räumlichen Stabilisierung der Rückströmzone.
Konzentrisch zum Mischrohr 20, im Bereich seines Auslaufes, wird ein Pilotbrennersystem 300 vorgesehen. Dieses besteht aus einer inneren Ringkammer 301, in welche ein Brennstoff, vorzugsweise ein gasförmiger Brennstoff 303 einströmt. Nebengeordnet zu dieser inneren Ringkammer 301 ist eine zweite Ringkammer 302 disponiert, in welche eine Luftmenge 304 einströmt. Beide Ringkammern 301, 302 weisen individuell gestaltete Durchgangsöffnungen auf, dergestalt, dass die einzelnen Medien 303, 304 funktionsbedingt in eine gemeinsame nachgeschaltete Ringkammer 308 strömen. Die Ueberleitung des gasförmigen Brennstoffes 303 von der Ringkammer 301 in die nachgeschaltete Ringkammer 308 wird durch eine Anzahl in Umfangsrichtung angeordneter Oeffnungen 309 bewerkstelligt. Die Durchgangsgeometrie dieser Oeffnungen 309 ist so gestaltet, dass der gasförmige Brennstoff 303 mit einem grossen Vermischungspotential in die nachgeschaltete Ringkammer 308 einströmt. Die andere Ringkammer 302 schliesst mit einer gelochten Platte 305 ab, wobei die hier vorgesehenen Bohrungen 310 so gestaltet sind, dass die dort durchströmende Luftmenge 304 eine Prallkühlung auf die Bodenplatte 307 der nachgeschalteten Ringkammer 308. Diese Bodenplatte hat die Funktion eines Hitzeschutzbleches gegenüber der kalorischen Belastung aus dem Brennraum 30, so dass diese Prallkühlung hier äusserst effizient ausfallen muss.
- 10
- Buchsenring
- 20
- Mischrohr, Teil der Mischstrecke 220
- 21
- Bohrungen, Oeffnungen
- 30
- Brennkammer, Brennraum
- 40
- Strömung, Rohrströmung im Mischrohr, Hauptströmung
- 50
- Rückströmzone, Rückströmblase
- 60
- Brennerachse
- 100
- Drallerzeuger
- 101, 102
- Kegelförmige Teilkörper
- 101a
- Ringförmiger Anfangsteil
- 101b, 102b
- Längssymmetrieachsen
- 103
- Brennstoffdüse
- 104
- Brennstoffeindüsung
- 105
- Brennstoffspray (Brennstoffeindüsungsprofil)
- 108, 109
- Brennstoffleitungen
- 112
- Flüssiger Brennstoff
- 113
- Gasförmiger Brennstoff
- 114
- Kegelhohlraum
- 115
- Verbrennungsluft (Verbrennungsluftstrom)
- 116
- Brennstoff-Eindüsung aus den Leitungen 108, 109
- 117
- Brennstoffdüsen
- 119, 120
- Tangentiale Lufteintrittsschlitze
- 121a, 121b
- Leitbleche
- 123
- Drehpunkt der Leitbleche
- 130, 131, 132, 133
- Teilkörper
- 131a, 131a, 132a, 133a
- Längssymmetrieachsen
- 140, 141, 142, 143
- Schaufelprofilförmige Teilkörper
- 140a, 141a, 142a, 143a
- Längssymmetrieachsen
- 150
- Brennstoffkonzentration
- 160
- Luftmenge, Mischluft
- 161
- Bohrungen, Oeffnungen
- 170
- Brennstoff-Injektoren
- 180
- Ringförmige Luftkammer
- 190
- Ring
- 200
- Uebergangsstück, Teil der Mischstrecke 220
- 201
- Uebergangskanäle
- 220
- Mischstrecke
- 300
- Pilotbrennersystem
- 301
- Innere Ringkammer
- 302
- Nebengeordnete Ringkammer
- 303
- Gasförmiger Brennstoff
- 304
- Luftmenge
- 305
- Gelochte Platte
- 306
- Bohrungen in den Brennraum, Pilotbrenner
- 307
- Hitzeschutzblech
- 308
- Nachgeschaltete Ringkammer
- 309
- Oeffnungen der inneren Ringkammer
- 310
- Löcher für Prallkühlung des Hitzeschutzbleches
Claims (18)
- Brenner zum Betrieb eines Wärmeerzeugers, wobei der Brenner im wesentlichen aus einem Drallerzeuger (100) für einen Verbrennungsluftstrom, aus Mitteln zur Eindüsung mindestens eines Brennstoffes in den Verbrennungsluftstrom besteht, wobei stromab des Drallerzeugers eine Mischstrecke (220) angeordnet ist, welche innerhalb eines ersten Streckenteils in Strömungsrichtung eine Anzahl Uebergangskanäle (201) zur Ueberführung einer im Drallerzeuger gebildeten Strömung in ein stromab dieser Uebergangskanäle nachgeschaltetes Mischrohr (20) aufweist, wobei im unteren Bereich des Mischrohres (20) mit Wirkung in einen dem Mischrohr (20) nachgeschalteten Brennraum (30) ein Pilotbrennersystem (300) angeordnet ist, welches aus mindestens zwei medienführenden Kammern (301, 302) und aus einer weiteren gemeinsamen nachgeschalteten Kammer (308) besteht, wobei in dieser nachgeschalteten Kammer (308) die Medien (303, 304) aus den beiden anderen Kammern (301, 302) mischbar sind, und wobei die nachgeschaltete Kammer (308) Mittel zur Bildung von in den Brennraum (30) wirkenden vom Gemisch der beiden Medien (303, 304) betreibbaren Pilotbrennern (306) aufweist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass durch die medienführenden Kammern (301, 303) ringförmig und nebengeordnet ausgebildet sind, dass durch die erste Ringkammer (301) ein gasförmiger Brennstoff (303) und durch die zweite Ringkammer (302) eine Luftmenge (304) strömen, dass in der zweiten Ringkammer (302) Mittel (305) eingebaut sind, durch welche die dort strömende Luft (304) eine Prallkühlung auf ein endseitig des Pilotbrennersystems (300) angeordnetes Hitzeschutzblech (307) bewerkstelligt.
- Brenner nach Anspruch 2, dadurch gekennzeichnet, dass das Mittel zur Bildung der Prallkühlung eine in der nebengeordneten Ringkammer (302) bodenbildende gelochte Platte (305) ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass die Mittel aus einem kopfseitig des Drallerzeugers (100) und in Wirkverbindung mit einer Brennstoffdüse (103) angeordneten Ring (190) besteht, dass dier Ring (190) eine Anzahl in Umfangsrichtung angeordneter Bohrungen (161) aufweist, und dass in eine durch die Bohrungen (161) strömende Luftmenge (160) ein Brennstoff (170) eindüsbar ist.
- Brenner nach Anspruch 4, dadurch gekennzeichnet, dass die Bohrungen (161) schräg nach vorne gerichtet sind.
- Brenner nach Anspruch 4, dadurch gekennzeichnet, dass die Brennstoffdüse (103) von einer rinförmiger Luftkammer (180) umgeben ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass die Brennerfront des Mischrohres (20) zur nachgeschalteten Brennraum (30) mit einer Abrisskante (A) ausgebildet ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass die Anzahl der Uebergangskanäle (201) in der Mischstrecke (220) der Anzahl der vom Drallerzeuger (100) gebildeten Teilströme entspricht.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass das den Uebergangskanälen (201) nachgeschaltete Mischrohr (20) in Strömungs- und Umfangsrichtung mit Oeffnungen (21) zur Eindüsung eines Luftstromes ins Innere des Mischrohres (20) versehen ist.
- Brenner nach Anspruch 9, dadurch gekennzeichnet, dass die Oeffnungen (21) unter einem spitzen Winkel gegenüber der Brennerachse (60) des Mischrohres (20) verlaufen.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass der Durchflussquerschnitt des Mischrohres (20) stromab der Uebergangskanäle (201) kleiner, gleich gross oder grösser als der Querschnitt der im Drallerzeuger (100, 100a) gebildeten Strömung (40) ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass stromab der Mischstrecke (220) eine Brennkammer (30) angeordnet ist, dass zwischen der Mischstrecke (220) und der Brennkammer (30) ein Querschnittssprung vorhanden ist, der den anfänglichen Strömungsquerschnitt der Brennkammer (30) induziert, und dass im Bereich dieses Querschnittssprunges eine Rückströmzone (50) wirkbar ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass stromauf der Brennerfront (70) ein Diffusor und/oder eine Venturistrecke vorhanden ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass der Drallerzeuger (100) aus mindestens zwei hohlen, kegelförmigen, in Strömungsrichtung ineinandergeschachtelten Teilkörpern (101, 102; 130, 131, 132, 133; 140, 141, 142, 143) besteht, dass die jeweiligen Längssymmetrieachsen (101b, 102b; 130a, 131a, 132a, 133a; 140a, 141a, 142a, 143a) dieser Teilkörper gegeneinander versetzt verlaufen, dergestalt, dass die benachbarten Wandungen der Teilkörper in deren Längserstreckung tangentiale Kanäle (119, 120) für einen Verbrennungsluftstromes (115) bilden, und dass im von den Teilkörpern gebildeten Innenraum (114) mindestens eine Brennstoffdüse (103 wirkbar ist.
- Brenner nach Anspruch 14, dadurch gekennzeichnet, dass im Bereich der tangentialen Kanäle (119, 120) in deren Längserstreckung weitere Brennstoffdüsen (117) angeordnet sind.
- Brenner nach Anspruch 14, dadurch gekennzeichnet, dass die Teilkörper (140, 141, 142, 143) im Querschnitt eine schaufelförmige Profilierung aufweisen.
- Brenner nach Anspruch 14, dadurch gekennzeichnet, dass die Teilkörper in Strömungsrichtung einen festen Kegelwinkel, oder eine zunehmende Kegelneigung, oder eine abnehmende Kegelneigung aufweisen.
- Brenner nach Anspruch 14, dadurch gekennzeichnet, dass die Teilkörper spiralförmig ineinandergeschachtelt sind.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP97810773A EP0909921B1 (de) | 1997-10-14 | 1997-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
DE59709061T DE59709061D1 (de) | 1997-10-14 | 1997-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
US09/169,140 US5954495A (en) | 1997-10-14 | 1998-10-09 | Burner for operating a heat generator |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP97810773A EP0909921B1 (de) | 1997-10-14 | 1997-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0909921A1 EP0909921A1 (de) | 1999-04-21 |
EP0909921B1 true EP0909921B1 (de) | 2003-01-02 |
Family
ID=8230430
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97810773A Expired - Lifetime EP0909921B1 (de) | 1997-10-14 | 1997-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
Country Status (3)
Country | Link |
---|---|
US (1) | US5954495A (de) |
EP (1) | EP0909921B1 (de) |
DE (1) | DE59709061D1 (de) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ATE237101T1 (de) * | 1998-01-23 | 2003-04-15 | Alstom Switzerland Ltd | Brenner für den betrieb eines wärmeerzeugers |
EP0987493B1 (de) * | 1998-09-16 | 2003-08-06 | Abb Research Ltd. | Brenner für einen Wärmeerzeuger |
DE59810284D1 (de) * | 1998-10-14 | 2004-01-08 | Alstom Switzerland Ltd | Brenner für den Betrieb eines Wärmeerzeugers |
DE10061526A1 (de) | 2000-12-11 | 2002-06-20 | Alstom Switzerland Ltd | Vormischbrenneranordnung zum Betrieb einer Brennkammer |
US20030229559A1 (en) * | 2002-04-09 | 2003-12-11 | Panttaja James T. | Asset management platform |
EP1389713A1 (de) * | 2002-08-12 | 2004-02-18 | ALSTOM (Switzerland) Ltd | Stromabwärtiger Pilotringbrenner für Vormischbrenner |
US6623267B1 (en) | 2002-12-31 | 2003-09-23 | Tibbs M. Golladay, Jr. | Industrial burner |
US20040202977A1 (en) * | 2003-04-08 | 2004-10-14 | Ken Walkup | Low NOx burner |
US7303388B2 (en) * | 2004-07-01 | 2007-12-04 | Air Products And Chemicals, Inc. | Staged combustion system with ignition-assisted fuel lances |
CN101243287B (zh) * | 2004-12-23 | 2013-03-27 | 阿尔斯托姆科技有限公司 | 具有混合段的预混燃烧器 |
DE102008000050A1 (de) * | 2007-08-07 | 2009-02-12 | Alstom Technology Ltd. | Brenner für eine Brennkammer einer Turbogruppe |
EP2110601A1 (de) * | 2008-04-15 | 2009-10-21 | Siemens Aktiengesellschaft | Brenner |
EP2650612A1 (de) * | 2012-04-10 | 2013-10-16 | Siemens Aktiengesellschaft | Brenner |
US9400104B2 (en) | 2012-09-28 | 2016-07-26 | United Technologies Corporation | Flow modifier for combustor fuel nozzle tip |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3033988C2 (de) * | 1980-09-10 | 1986-04-17 | Karl-Friedrich Dipl.-Ing. Dipl.-Wirtsch.-Ing. 4100 Duisburg Schmid | Gasbrenner mit integrierter Brennerkopf-Luftkühlung |
CN1017744B (zh) * | 1988-12-26 | 1992-08-05 | 株式会社日立制作所 | 低氮氧化物锅炉 |
JPH0682084A (ja) * | 1992-09-02 | 1994-03-22 | Daikin Ind Ltd | 空気調和装置の運転制御装置 |
IT1273369B (it) * | 1994-03-04 | 1997-07-08 | Nuovo Pignone Spa | Sistema perfezionato combustione a basse emissioni inquinanti per turbine a gas |
DE4411623A1 (de) * | 1994-04-02 | 1995-10-05 | Abb Management Ag | Vormischbrenner |
DE4416650A1 (de) * | 1994-05-11 | 1995-11-16 | Abb Management Ag | Verbrennungsverfahren für atmosphärische Feuerungsanlagen |
JPH0882419A (ja) * | 1994-09-14 | 1996-03-26 | Hitachi Ltd | ガスタービン用燃焼器 |
DE19547913A1 (de) | 1995-12-21 | 1997-06-26 | Abb Research Ltd | Brenner für einen Wärmeerzeuger |
DE19547912A1 (de) * | 1995-12-21 | 1997-06-26 | Abb Research Ltd | Brenner für einen Wärmeerzeuger |
DE19610930A1 (de) * | 1996-03-20 | 1997-09-25 | Abb Research Ltd | Brenner für einen Wärmeerzeuger |
-
1997
- 1997-10-14 DE DE59709061T patent/DE59709061D1/de not_active Expired - Lifetime
- 1997-10-14 EP EP97810773A patent/EP0909921B1/de not_active Expired - Lifetime
-
1998
- 1998-10-09 US US09/169,140 patent/US5954495A/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DE59709061D1 (de) | 2003-02-06 |
EP0909921A1 (de) | 1999-04-21 |
US5954495A (en) | 1999-09-21 |
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