EP0994300A1 - Brenner für den Betrieb eines Wärmeerzeugers - Google Patents
Brenner für den Betrieb eines Wärmeerzeugers Download PDFInfo
- Publication number
- EP0994300A1 EP0994300A1 EP98811023A EP98811023A EP0994300A1 EP 0994300 A1 EP0994300 A1 EP 0994300A1 EP 98811023 A EP98811023 A EP 98811023A EP 98811023 A EP98811023 A EP 98811023A EP 0994300 A1 EP0994300 A1 EP 0994300A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- burner
- flow
- burner according
- mixing tube
- 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
Links
- 238000002156 mixing Methods 0.000 claims abstract description 78
- 239000000446 fuel Substances 0.000 claims abstract description 66
- 238000002485 combustion reaction Methods 0.000 claims abstract description 39
- 230000007704 transition Effects 0.000 claims abstract description 36
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000001154 acute effect Effects 0.000 claims description 2
- 230000003247 decreasing effect Effects 0.000 claims description 2
- 238000002347 injection Methods 0.000 description 13
- 239000007924 injection Substances 0.000 description 13
- 239000000203 mixture Substances 0.000 description 9
- 239000003344 environmental pollutant Substances 0.000 description 6
- 231100000719 pollutant Toxicity 0.000 description 6
- 239000007789 gas Substances 0.000 description 5
- 239000007788 liquid Substances 0.000 description 5
- 230000006641 stabilisation Effects 0.000 description 5
- 238000011105 stabilization Methods 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000010349 pulsation Effects 0.000 description 3
- 241001156002 Anthonomus pomorum Species 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 2
- 230000009172 bursting Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 239000003546 flue gas Substances 0.000 description 2
- 238000011010 flushing procedure Methods 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 241000722921 Tulipa gesneriana Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000004873 anchoring Methods 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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
- F23C7/002—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
Definitions
- the invention relates to a burner for operating a heat generator according to Preamble of claim 1.
- the upstream side consists of a swirl generator, the swirl flow formed therein being seamless is transferred to a mixing section.
- This is done using one at the beginning the mixing section formed for this purpose flow geometry, which Transitional channels exist, which are sectoral, corresponding to the number of tangential acting inflow channels or inflow slots of this swirl generator, form the end face of the mixing section and have a swirling shape in the direction of flow.
- the outflow side of these transition channels has the remaining one Mixing section a number of filming holes through which an amount of air flows into the mixing section, thereby increasing the flow velocity induce along the pipe wall.
- a combustion chamber the transition between the mixing section and the combustion chamber is formed by a cross-sectional jump, in the plane of which there is a backflow zone or backflow bubble forms.
- the swirl strength in the swirl generator is selected so that the bursting of the vortex does not happen within the mixing section, but further downstream takes place, as stated above, in the area of the cross-sectional jump.
- the length of the Mixing section is dimensioned so that a sufficient premix quality for all types of fuel used are guaranteed.
- the invention seeks to remedy this.
- the invention as set out in the claims is characterized, the task is based on a burner at the beginning to propose precautions which strengthen the flame stability to achieve sustainable stable operation, especially in the transient load ranges, always taking into account the Another task, which pursues the goal, the pollutant emissions to minimize from such an operation and therefore the sub-area too special to increase lower partial loads.
- the burner is expanded in such a way that in the area of the transition a system for providing the mixing section to the downstream combustion chamber of a fuel / air mixture is generally provided as Pilot stage acts.
- vortex generators are used in this area provided which on the outside of the main flow of the burner during the company produce so-called swirl braids.
- pilot burners are operated with a low proportion of fuel, and in operative connection with the vortex generators is through a better one Mix the burner fuel with the surrounding hot gas Pre-mix combustion stability reached near the lean extinguishing limit. Becomes the pilot burner fuel into those generated by the vortex generators Vortex braids injected, so the mixing is significantly improved and the pollutant emissions are greatly reduced. Accordingly, by enlarging the Load range with deep pollutants becomes an extension to small loads achieved.
- Fig. 1 shows the overall structure of a burner.
- This burner acts at the top a swirl generator 100, the design of which is shown in the following FIGS. 3-6 is shown and described in more detail.
- It is a conical one trained swirl generator 100, the multiple of a tangential inside incoming combustion air flow 115 is applied.
- the forming flow becomes effective on the basis of a swirl generator 100 downstream
- Transition geometry 200 seamlessly transferred into a mixing section, in such a way that there are no separation areas along this mixing section.
- This mixing section 220 itself consists of the transition piece mentioned 200 and downstream thereof extended from a mixing tube 20.
- Mixing section 220 may consist of a single piece: In such a case, the transition piece 200 and the mixing tube 20 form a single one cohesive structure, the characteristics of each part remain. Become transition piece 200 and mixing tube 20 from two parts created, they are connected by a sleeve ring 10, the same Socket ring 10 on the head side as an on-site anchoring surface for the swirl generator 100 serves. Such a sleeve ring 10 also has the advantage that different mixing tubes can be used. Downstream side of the Mixing tube 20 is the actual combustion chamber 30 of a combustion chamber, which is only symbolized here by a flame tube.
- the mixing section 220 largely fulfills the task that a downstream of the swirl generator 100 defined route is provided, in which a perfect premix with the fuels used can take place.
- a lossless flow forms, so that here no backflow zone or backflow bubble initially arises, with what the entire length of the mixing section 220 to the mixing quality of the injected Fuels influence can be exercised.
- This mixing section 220 unfolds but still another property, which is that in you that Axial velocity profile has a pronounced maximum on the axis, so that the flame reignites from the combustion chamber into the interior of the burner not possible. However, it is correct that with such a configuration the axial velocity drops towards the wall.
- the mixing tube 20 in the flow and circumferential direction with a number of regularly or irregularly distributed bores 21 various cross-sections and directions through which an amount of air flows into the interior of the mixing tube 20, and along the wall in the sense induce an increase in flow rate during filming.
- This Bores 21 can also be designed in such a way that the inner wall of the mixing tube 20 at least additionally an effusion cooling sets.
- Another way of increasing the speed of the Achieving mixture within the mixing tube 20 is that Flow cross-section on the outflow side of those belonging to the transition piece 200 Transition channels 201, which have the transition geometry already mentioned form, undergoes a narrowing, reducing the overall speed level is raised within the mixing tube 20.
- the figures run in the figure bores 21 through which air flows at an acute angle the burner axis 60. Furthermore, the outlet corresponds to the transition channels 201 the narrowest flow cross-section of the mixing tube 20. The transition channels mentioned 201 accordingly bridge the respective cross-sectional difference in the direction of flow without negatively influencing the flow formed. If the selected arrangement for guiding the pipe flow 40 triggers an intolerable pressure loss along the mixing tube 20, so This can be remedied by using this mixing tube at the end 20 a diffuser, not shown in the figure, is provided. At the end of the mixing tube 20 then connects to a combustion chamber 30 (combustion chamber), wherein between the two flow cross-sections, one formed by a burner front 70 Cross-sectional jump is present.
- a combustion chamber 30 combustion chamber
- 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 through which an amount of air 160 is placed in an annular chamber 180 flows and carries out the flushing of the fuel lance there.
- 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 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 displacement 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 neighboring wall, in mirror image Arrangement, each a tangential channel, i.e.
- the cone shape the partial body 101, 102 shown in the flow direction has a certain one fixed angle.
- the partial bodies can 101, 102 an increasing or decreasing cone inclination in the flow direction have, similar to a trumpet. Tulip.
- the latter two Shapes are not recorded in the drawing, as they are without for the specialist are further sensitive.
- the two conical partial bodies 101, 102 have each have a cylindrical annular starting part 101a. In the area of this cylindrical Initially, the fuel nozzle 103 already mentioned under FIG.
- the tapered partial bodies 101, 102 each have a fuel line 108, 109, which along the tangential air inlet slots 119, 120 are 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 lines 108, 109 are preferably at the end of the latest tangential inflow, before entering the cone cavity 114, this to get an optimal air / fuel mixture.
- fuel 112 is, as mentioned, in Normally a liquid fuel, whereby a mixture formation with a other medium, for example with a recirculated flue gas, without further ado is possible.
- This fuel 112 is preferably very pointed under one Angle injected into the cone cavity 114.
- the concentration of the injected fuel 112 then becomes axial continuously through the incoming combustion air 115 for mixing Degraded towards evaporation. If a gaseous fuel 113 over the Introduced 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 Enriched with flue gas or exhaust gas, this sustainably supports evaporation of liquid fuel 112 before this mixture is 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 recorded.
- the partial bodies 101, 102 can also be moved relative to each other in another plane, which even an overlap of the same can be provided. It is further possible, the partial body 101, 102 by a counter-rotating movement spiral to nest into each other. So it is possible, the shape, the size and to vary the configuration of the tangential air inlet slots 119, 120 as desired, which makes the swirl generator 100 universal without changing its overall length can be used.
- FIG. 4 shows, among other things, the geometric configuration of optional ones Baffles 121a, 121b. They 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.
- the channeling of 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 fulcrum 114 placed cone cavity 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 conical partial bodies 101, 102.
- the swirl generator 100 now consists of four partial bodies 130, 131, 132, 133 is constructed.
- the associated longitudinal symmetry axes for each sub-body are marked with the letter a. To this Configuration is to be said that it is due to the lower generated with it Twist strength and in cooperation with a correspondingly enlarged Slot width is best suited, the bursting of the vortex flow on the downstream side to prevent the swirl generator in the mixing tube, thus causing the mixing tube to can fulfill the intended role.
- 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 transition geometry is corresponding for a swirl generator 100 with four partial bodies 5 or 6, built. Accordingly, the transition geometry as a natural extension of the upstream partial bodies, four transition channels 201 on, whereby the conical quarter area of said partial body is extended until it cuts the wall of the mixing tube.
- the same considerations also apply if the swirl generator is based on a principle other than the one below Fig. 3 described, is constructed.
- the down in the direction of flow running surface of the individual transition channels 201 has a flow direction spiral shape, which has a crescent shape Course describes, corresponding to the fact that the flow cross-section is present of the transition piece 200 flared in the flow direction.
- the swirl angle of the transition channels 201 in the flow direction is so chosen that the pipe flow then up to the cross-sectional jump on Combustion chamber entrance still has a sufficient distance to be perfect Premix with the injected fuel. Further increases the axial speed is also affected by 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 bring about a significant increase of 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 a transition radius in this area R, the size of which basically depends on the flow within the Tube 20 depends.
- This radius R is chosen so that the flow turns on puts on the wall and so the swirl number increases sharply.
- This radius R runs up to Exit plane of the tube 20, the angle ⁇ between the beginning and end of the Curvature is ⁇ 90 °.
- FIG. 10 shows an overall picture of the end part of the mixing tube 20, in which the pilot burner system and the vortex generators are housed, whereby this part is designed to be applicable, such as the mounting holes hint.
- End and combustion chamber side of this part are inside the tear-off edge (see FIG. 8) distributed in the circumferential direction a number of Incisions 402 are provided, which in conjunction with the gas flow within of the mixing tube act as vortex generators.
- These cuts are what theirs Size, number in the circumferential direction and their course concerns, in various ways trained, depending on how big, how strong and how directed the resulting Vortex braids (see Fig. 9, item 401) should fail so that the desired Goal can be achieved.
- the mixing becomes significant with qualitatively trained peg braids improved and pollutant emissions greatly reduced.
- the im Area of the vortex generators 402 forming flame front and backflow zone (See Fig. 1) are paired with this injection of the fuel the vortex braids forming there (see Fig. 9, item 401) and in operative connection with the tear-off edge (see FIG. 8), strongly stabilized, this stabilization to close to the lean extinguishing limit.
- the design of the vortex generators is not limited to the version shown here. Instead of cuts the desired turbulence can also be achieved by setting up suitable forms in the Achieve the end area of the mixing tube.
- FIG. 11 and 12 show the incisions 402 acting as vortex generators different views.
- the incisions shown here run along the Behind the tear-off edge with increasing incision depth, and form approximately a truncated cone-shaped path. The course of this path is opposite the center axis of the mixing tube is applied obliquely to obliquely-radial, like this Fig. 12 emerges. The course of these cuts depends on the quality of the pegs to be formed.
- Direction 303 of fuel injection through the nozzles 301 depends on the piloting effect to be achieved; preferably this fuel injection is compared to the main flow in the Mixing tube held tangential, as shown in Fig. 12, the degree the tangential fuel injection is designed on a case-by-case basis.
- the feed of the pilot burner system 300 with fuel can be through an internal feed line achieve through the mixing tube, or fuel from the outside into the chamber 302 promotes.
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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)
Abstract
Description
- Fig. 1
- einen als Vormischbrenner ausgelegten Brenner mit einer Mischstrecke stromab eines Drallerzeugers, mit einer schematisierten Darstellung eines Pilotbrennstoffkanals im Bereich einer Abrisskante,
- Fig. 2
- eine schematisierte Darstellung des Brenners gemäss Fig. 1 mit zusätzlichen kopfseitig angeordneten 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
- einen Querschnitt durch einen Drallerzeuger, dessen Schalen schaufelförmig profiliert sind,
- Fig. 7
- eine Ausgestaltung der Uebergangsgeometrie zwischen Drallerzeuger und Mischstrecke,
- Fig. 8
- eine Abrisskante zur räumlichen Stabilisierung der Rückströmzone,
- Fig. 9
- eine schematisierte Darstellung der endseitigen Ausbildung der Mischstrecke und der dort ausgebildeten Wirbelgeneratoren,
- Fig. 10-12
- Verschiedene Ansichten der Konfiguration der Wirbelgeneratoren.
- 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
- Brennstoffdüse
- 302
- Kammer
- 303
- Brennstoffeindüsung
- 400
- Wirbelgeneratoren
- 401
- Wirbelzöpfe
- 402
- Einschnitte
- A
- Abrisskante
- R
- Radius
- S
- Abrissstufe
- T
- Tangente
- d
- Innendurchmesser des Rohres (Mischrohres 20)
- β, β'
- Winkel
Claims (17)
- Brenner zum Betrieb eines Wärmeerzeugers, wobei der Brenner im wesentlichen aus einem Drallerzeuger für einen Verbrennungsluftstrom, aus Mitteln zur Eindüsung mindestens eines Brennstoffes in den Verbrennungsluftstrom besteht, wobei stromab des Drallerzeugers eine Mischstrecke angeordnet ist, welche innerhalb eines ersten Streckenteils in Strömungsrichtung eine Anzahl Uebergangskanäle zur Ueberführung einer im Drallerzeuger gebildeten Strömung in ein stromab dieser Uebergangskanäle nachgeschaltetes Mischrohr aufweist, dadurch gekennzeichnet, dass im unteren Bereich des Mischrohres (20) ein Pilotbrennersystem (300) angeordnet ist, und dass das Pilotbrennersystem (300) in Wirkverbindung mit endseitig des Mischrohres (20) angeordneten Wirbelgeneratoren (400) steht.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass ein Brennstoff (303) von dem Pilotbrennersystem (300) in die von den Wirbelgeneratoren (400) gebildete Verwirbelung (401) eindüsbar ist.
- Brenner nach Anspruch 2, dadurch gekennzeichnet, dass der Brennstoff (303) tangential gegenüber der Hauptströmung im Mischröhr (20) eindüsbar ist.
- Brenner nach Anspruch 1, dadurch gekennzeichnet, dass die Wirbelgeneratoren (400) aus einer Anzahl endseitig und in Umfangsrichtung des Mischrohres (20) angebrachter Einschnitte (402) bestehen.
- Brenner nach Anspruch 3, dadurch gekennzeichnet, dass die Einschnitte (402) gegenüber dem Strömungsquerschnitt des Mischrohres (20) schräg bis schräg-radial verlaufen.
- 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 10, 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 13, dadurch gekennzeichnet, dass im Bereich der tangentialen Kanäle (119, 120) in deren Längserstreckung weitere Brennstoffdüsen (117) angeordnet sind.
- Brenner nach Anspruch 13, dadurch gekennzeichnet, dass die Teilkörper (140, 141, 142, 143) im Querschnitt eine schaufelförmige Profilierung aufweisen.
- Brenner nach Anspruch 13, dadurch gekennzeichnet, dass die Teilkörper in Strömungsrichtung einen festen Kegelwinkel, oder eine zunehmende Kegelneigung, oder eine abnehmende Kegelneigung aufweisen.
- Brenner nach Anspruch 13, dadurch gekennzeichnet, dass die Teilkörper spiralförmig ineinandergeschachtelt sind.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE59810284T DE59810284D1 (de) | 1998-10-14 | 1998-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
EP98811023A EP0994300B1 (de) | 1998-10-14 | 1998-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
US09/417,846 US6152726A (en) | 1998-10-14 | 1999-10-14 | Burner for operating a heat generator |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP98811023A EP0994300B1 (de) | 1998-10-14 | 1998-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0994300A1 true EP0994300A1 (de) | 2000-04-19 |
EP0994300B1 EP0994300B1 (de) | 2003-11-26 |
Family
ID=8236383
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98811023A Expired - Lifetime EP0994300B1 (de) | 1998-10-14 | 1998-10-14 | Brenner für den Betrieb eines Wärmeerzeugers |
Country Status (3)
Country | Link |
---|---|
US (1) | US6152726A (de) |
EP (1) | EP0994300B1 (de) |
DE (1) | DE59810284D1 (de) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1087178A1 (de) * | 1999-09-23 | 2001-03-28 | Nuovo Pignone Holding S.P.A. | Vormischkammer für Gasturbinen |
EP1389713A1 (de) | 2002-08-12 | 2004-02-18 | ALSTOM (Switzerland) Ltd | Stromabwärtiger Pilotringbrenner für Vormischbrenner |
DE10340826A1 (de) * | 2003-09-04 | 2005-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Homogene Gemischbildung durch verdrallte Einspritzung des Kraftstoffs |
WO2009109452A1 (de) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Brenneranordnung sowie anwendung einer solchen brenner-anordnung |
US7871262B2 (en) * | 2004-11-30 | 2011-01-18 | Alstom Technology Ltd. | Method and device for burning hydrogen in a premix burner |
US7972133B2 (en) | 2006-03-27 | 2011-07-05 | Alstom Technology Ltd. | Burner for the operation of a heat generator and method of use |
US8459985B2 (en) | 2008-03-07 | 2013-06-11 | Alstom Technology Ltd | Method and burner arrangement for the production of hot gas, and use of said method |
US9033263B2 (en) | 2003-10-20 | 2015-05-19 | Rolls-Royce Deutschland Ltd & Co Kg | Fuel injection nozzle with film-type fuel application |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10128063A1 (de) * | 2001-06-09 | 2003-01-23 | Alstom Switzerland Ltd | Brennersystem |
WO2006069861A1 (de) * | 2004-12-23 | 2006-07-06 | Alstom Technology Ltd | Vormischbrenner mit mischstrecke |
NO325990B1 (no) * | 2006-06-23 | 2008-09-01 | Rolf B Rummelhoff | Etterbrenner for gass fra gassifiseringsanlegg for trebrensel |
EP1975506A1 (de) * | 2007-03-30 | 2008-10-01 | Siemens Aktiengesellschaft | Vorverbrennungskammer |
DE102007043626A1 (de) | 2007-09-13 | 2009-03-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenmagerbrenner mit Kraftstoffdüse mit kontrollierter Kraftstoffinhomogenität |
EP2058590B1 (de) * | 2007-11-09 | 2016-03-23 | Alstom Technology Ltd | Verfahren zum Betrieb eines Brenners |
EP2220433B1 (de) * | 2007-11-27 | 2013-09-04 | Alstom Technology Ltd | Verfahren und vorrichtung zur verbrennung von wasserstoff in einem vormischbrenner |
EP2650612A1 (de) | 2012-04-10 | 2013-10-16 | Siemens Aktiengesellschaft | Brenner |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
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US3111979A (en) * | 1960-03-07 | 1963-11-26 | Lennox Ind Inc | Dual fuel burner construction |
FR2319846A1 (fr) * | 1975-07-31 | 1977-02-25 | Exxon Research Engineering Co | Bruleur a alimentation en air etagee |
EP0589520A1 (de) * | 1992-09-24 | 1994-03-30 | NUOVOPIGNONE INDUSTRIE MECCANICHE E FONDERIA S.p.A. | Verbrennungsanlage mit niedriger Schadstoffemission für Gasturbinen |
WO1996000364A1 (en) * | 1994-06-24 | 1996-01-04 | United Technologies Corporation | Pilot injector for gas turbine engines |
EP0780629A2 (de) | 1995-12-21 | 1997-06-25 | ABB Research Ltd. | Brenner für einen Wärmeerzeuger |
EP0797051A2 (de) * | 1996-03-20 | 1997-09-24 | Abb Research Ltd. | Brenner für einen Wärmeerzeuger |
EP0801268A2 (de) * | 1996-04-09 | 1997-10-15 | Abb Research Ltd. | Gasturbinenbrennkammer |
US5794449A (en) * | 1995-06-05 | 1998-08-18 | Allison Engine Company, Inc. | Dry low emission combustor for gas turbine engines |
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Publication number | Priority date | Publication date | Assignee | Title |
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US2365945A (en) * | 1942-03-07 | 1944-12-26 | Nat Airoil Burner Company Inc | Flame retention nozzle |
US2675068A (en) * | 1951-03-16 | 1954-04-13 | Le Roy R Gollus | Gas fueled pilot burner tip or head |
US2647568A (en) * | 1951-03-30 | 1953-08-04 | Peabody Engineering Corp | Burner throat |
US3302596A (en) * | 1966-01-21 | 1967-02-07 | Little Inc A | Combustion device |
US5259755A (en) * | 1992-07-31 | 1993-11-09 | Hauck Manufacturing Company | Combination burner with boost gas injection |
EP0909921B1 (de) * | 1997-10-14 | 2003-01-02 | Alstom | Brenner für den Betrieb eines Wärmeerzeugers |
US6007325A (en) * | 1998-02-09 | 1999-12-28 | Gas Research Institute | Ultra low emissions burner |
-
1998
- 1998-10-14 DE DE59810284T patent/DE59810284D1/de not_active Expired - Lifetime
- 1998-10-14 EP EP98811023A patent/EP0994300B1/de not_active Expired - Lifetime
-
1999
- 1999-10-14 US US09/417,846 patent/US6152726A/en not_active Expired - Lifetime
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3111979A (en) * | 1960-03-07 | 1963-11-26 | Lennox Ind Inc | Dual fuel burner construction |
FR2319846A1 (fr) * | 1975-07-31 | 1977-02-25 | Exxon Research Engineering Co | Bruleur a alimentation en air etagee |
EP0589520A1 (de) * | 1992-09-24 | 1994-03-30 | NUOVOPIGNONE INDUSTRIE MECCANICHE E FONDERIA S.p.A. | Verbrennungsanlage mit niedriger Schadstoffemission für Gasturbinen |
WO1996000364A1 (en) * | 1994-06-24 | 1996-01-04 | United Technologies Corporation | Pilot injector for gas turbine engines |
US5794449A (en) * | 1995-06-05 | 1998-08-18 | Allison Engine Company, Inc. | Dry low emission combustor for gas turbine engines |
EP0780629A2 (de) | 1995-12-21 | 1997-06-25 | ABB Research Ltd. | Brenner für einen Wärmeerzeuger |
EP0797051A2 (de) * | 1996-03-20 | 1997-09-24 | Abb Research Ltd. | Brenner für einen Wärmeerzeuger |
EP0801268A2 (de) * | 1996-04-09 | 1997-10-15 | Abb Research Ltd. | Gasturbinenbrennkammer |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6363725B1 (en) | 1999-09-23 | 2002-04-02 | Nuovo Pignone Holding S.P.A. | Pre-mixing chamber for gas turbines |
EP1087178A1 (de) * | 1999-09-23 | 2001-03-28 | Nuovo Pignone Holding S.P.A. | Vormischkammer für Gasturbinen |
US7140183B2 (en) | 2002-08-12 | 2006-11-28 | Alstom Technology Ltd. | Premixed exit ring pilot burner |
EP1389713A1 (de) | 2002-08-12 | 2004-02-18 | ALSTOM (Switzerland) Ltd | Stromabwärtiger Pilotringbrenner für Vormischbrenner |
WO2004015332A1 (en) * | 2002-08-12 | 2004-02-19 | Alstom Technology Ltd | Premixed exit ring pilot burner |
US7546734B2 (en) | 2003-09-04 | 2009-06-16 | Rolls-Royce Deutschland Ltd & Co Kg | Homogenous mixture formation by swirled fuel injection |
DE10340826A1 (de) * | 2003-09-04 | 2005-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Homogene Gemischbildung durch verdrallte Einspritzung des Kraftstoffs |
US9033263B2 (en) | 2003-10-20 | 2015-05-19 | Rolls-Royce Deutschland Ltd & Co Kg | Fuel injection nozzle with film-type fuel application |
US7871262B2 (en) * | 2004-11-30 | 2011-01-18 | Alstom Technology Ltd. | Method and device for burning hydrogen in a premix burner |
US7972133B2 (en) | 2006-03-27 | 2011-07-05 | Alstom Technology Ltd. | Burner for the operation of a heat generator and method of use |
WO2009109452A1 (de) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Brenneranordnung sowie anwendung einer solchen brenner-anordnung |
US8459985B2 (en) | 2008-03-07 | 2013-06-11 | Alstom Technology Ltd | Method and burner arrangement for the production of hot gas, and use of said method |
US8468833B2 (en) | 2008-03-07 | 2013-06-25 | Alstom Technology Ltd | Burner arrangement, and use of such a burner arrangement |
Also Published As
Publication number | Publication date |
---|---|
US6152726A (en) | 2000-11-28 |
DE59810284D1 (de) | 2004-01-08 |
EP0994300B1 (de) | 2003-11-26 |
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