EP0751351B1 - Brennkammer - Google Patents
Brennkammer Download PDFInfo
- Publication number
- EP0751351B1 EP0751351B1 EP96810353A EP96810353A EP0751351B1 EP 0751351 B1 EP0751351 B1 EP 0751351B1 EP 96810353 A EP96810353 A EP 96810353A EP 96810353 A EP96810353 A EP 96810353A EP 0751351 B1 EP0751351 B1 EP 0751351B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- combustion chamber
- flow
- chamber according
- combustion
- air
- 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
- 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
- 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
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
-
- 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 present invention relates to a combustion chamber according to Preamble of claim 1.
- the invention seeks to remedy this.
- the invention how it is characterized in the claims, the task lies based on a combustion chamber of the type mentioned the introduction of the cooling air into the combustion air flow minimized pressure losses with optimal mixing of the two To shape air flows.
- the pressure drops when implementing the cooling air in the Combustion airflow is minimized by at least an injector system at the transition to the plenum itself disembodied diffuser is formed.
- the main advantage of the invention is that that this is a compact configuration, which is the inflow of cooling air into the other airflow within the same framework as when using a relatively long, flow-optimized transition diffuser guaranteed.
- the combustion chamber is more compact can be interpreted and that the admixture of the cooling air fluidic runs optimally, in such a way that on the Flame temperature can be applied in the sense that minimizing pollutant emissions, in particular as far as NOx emissions are concerned.
- the invention develops in particular in gas turbines Annular combustion chambers have great advantages because of the proposed addition the cooling air does not require an extension of the plenum, with an obvious consequence of a shorter rotor shaft of the system this results.
- Annular combustion chamber 1 acts, which is essentially the shape of a coherent annular or quasi-annular cylinder occupies.
- a combustion chamber also from a number of axially, quasi-axially or helically arranged and individually closed combustion chambers consist.
- this combustion chamber can also consist of one single pipe exist.
- this combustion chamber the only combustion stage of a gas turbine or a combustion stage a sequentially fired plant.
- the annular combustion chamber 1 consists of a plenum 7 on the head side, that ends up in the flow direction with a configuration of burners 100. About the distribution and organization burner 100 is shown in the following figures discussed in more detail.
- the combustion chamber 122 Downstream of this burner 100 closes the actual combustion chamber 122 of the combustion chamber 1. In the hot gases generated in this room then act in the Usually a downstream turbine.
- the combustion chamber 122 is included a double annular channel 2, 3 encased, through which a cooling air 4 flows in the counterflow direction.
- this cooling air 4 in operative connection with an air quantity coming from outside 5 higher potential, hereinafter called accelerating air, the interaction of these two air flows 4, 5 over Injector systems 8, 9 takes place, which in the circumferential direction arranged opposite the inner and outer wall of the annular combustion chamber 1 are. On the design of these injector systems is discussed in more detail in Fig. 2.
- FIG. 2 shows the structure of the individual injector systems 8, 9 seen. Furthermore, the arrangement goes from this FIG. 2 the burner 100 within the front wall 110 for subsequent connection Combustion chamber. This arrangement may apply case to be different, including the number of burners can vary. It also takes place within the burner network preferably a division into pilot burner and main burner instead, with this provision the transient load ranges can be approached optimally.
- the cooling air 4 becomes on both sides of the burner 100 through individual self-contained injector systems 8, 9 directed, which have the shape of rectangular channels. In the circumferential direction the acceleration air of each channel 5 through holes 5a there at regular intervals introduced and causes the cooling air 4 within the very short length of the channels an optimal speed profile received before it flows into the plenary.
- the geometric cross-sectional shape is Channels are not limited to the rectangular shape shown. Also the flow cross section and finally the number of these channels in the circumferential direction depends on the case Determine case, with the goal of optimizing each design the speed profile of the cooling air 4 within must be the shortest route.
- FIG. 3 Cuts according to Figures 4-6 are those shown schematically in FIGS. 4-6.
- Baffles 121a, 121b have only been hinted at. The following is the description of FIG. 3 as needed referred to the remaining figures 4-6.
- the burner 100 of FIG. 3 is a premix burner and exists of two hollow conical part-bodies 101, 102 which are nested staggered.
- the dislocation the respective central axis or longitudinal symmetry axes 101b, 102b of the tapered partial bodies 101, 102 to one another creates on both sides, in a mirror image arrangement, each have a tangential air inlet slot or duct 119, 120 free (see Fig. 4-6), through which the combustion air 115 inside the burner 100, i.e. in the cone cavity 114 flows.
- the cone shape of the partial body shown 101, 102 in the flow direction has a certain fixed Angle on.
- the two tapered partial bodies 101, 102 each have a cylindrical Initial part 101a, 102a, which also, analogous to the tapered Partial bodies 101, 102, offset from one another, see above that the tangential air inlet slots 119, 120 over the entire length of the burner 100 are present.
- a nozzle 103 In the area of cylindrical initial part, a nozzle 103 is accommodated, whose fuel injection 104 is approximately the narrowest cross section that formed by the tapered body 101, 102 Cone cavity 114 coincides.
- the injection capacity and the type of this nozzle 103 depends on the given Parameters of the respective burner 100.
- the burner can be purely conical, i.e. without a cylindrical one
- Initial parts 101a, 102a with a single part body a single tangential air inlet slot, or out be executed more than two partial bodies.
- the conical Sub-bodies 101, 102 also each have a fuel line 108, 109 on which along the tangential air inlet slots 119, 120 arranged and with injection openings 117 are provided, through which preferably a gaseous Fuel 113 in the combustion air flowing through there 115 is injected, as shown by the arrows 116 want.
- These fuel lines 108, 109 are preferably at the latest at the end of the tangential inflow, before entering the cone cavity 114, placed, this to get an optimal air / fuel mixture.
- the exit opening of the burner 100 is on the combustion chamber side 122 into a front wall 110 in which a number of holes 110a are present.
- the latter bores 110a occur in function when needed, and ensure that dilution air or cooling air 110b the front part of the combustion chamber 122 is fed.
- this air supply ensures flame stabilization at the output of burner 100.
- This Flame stabilization becomes important when it comes to the compactness of the flame due to a radial flattening to support.
- the fuel supplied through the nozzle 103 it is a liquid or gaseous Fuel 112, which at most with a recirculated exhaust gas can be enriched.
- This fuel 112 will, in particular if it is a liquid, under a acute angle injected into the cone cavity 114. From the Nozzle 103 thus forms a conical fuel profile 105, the rotating combustion air flowing in tangentially 115 is enclosed.
- the concentration of fuel 112 continuously through the incoming combustion air 115 for optimal mixing reduced. If the burner 100 with a gaseous Operated fuel 113, this is preferably done via Opening nozzles 117, the formation of this fuel / air mixture directly at the crossing of air inlet slots 119, 120 to the cone cavity 114 occurs.
- the injection of fuel 112 through nozzle 103 performs the function a head stage; it usually comes at commissioning and for part-load operation. Of course, is about this head stage also a base load operation with a liquid Fuel possible.
- the cross section On the one hand, at the end of the burner 100 the optimal, homogeneous fuel concentration the cross section, on the other hand the critical swirl number; the latter then leads in cooperation with the one scheduled there Cross-sectional expansion to a vortex run, at the same time for the formation of a backflow zone there 106. Ignition occurs at the top of this backflow zone 106. Only at this point can a stable flame front 107 arise. A flashback of the flame inside the burner 100, as is latently the case with known premixing sections is a remedy there with complicated flame holders is not to be feared here.
- the once-fixed backflow zone 106 is on is stable in position because the swirl number increases in the direction of flow in the area of the cone shape of the burner 100.
- the axial speed within the burner 100 leaves by a corresponding supply, not shown change the axial combustion air flow.
- the construction of the burner 100 is furthermore particularly suitable for the Size of the tangential air inlet slots 119, 120 to change, without changing the length of the burner 100 a relatively large operational bandwidth can be recorded can. It is also easily possible to use the tapered Partial bodies 101, 102 to be nested in a spiral shape.
- the geometric configuration of the Baffles 121a, 121b have a flow initiation function these, according to their length, the respective End of the tapered partial body 101, 102 in the direction of flow extend towards the combustion air 115.
- the Channeling the combustion air 115 into the cone cavity 114 can by opening or closing the guide plates 121a, 121b by one in the area of the entry of this channel into the Cone cavity 114 placed pivot point 123 can be optimized, this is particularly necessary if the original gap size the tangential air inlet slots 119, 120 changed becomes.
- these can be dynamic arrangements can also be provided statically, as required Baffles are an integral part with the tapered partial bodies 101, 102 form.
- the burner 100 can also can be operated without baffles, or others can Aids for this are provided.
- FIG. 7 shows the overall structure of a further burner 300.
- a swirl generator 100a is effective, the design of which largely that of the burner 100 according to FIG. 3 equivalent.
- This swirl generator 100a also around a conical structure that is tangentially multiple from the tangentially flowing combustion air flow 115 is applied.
- the current that forms here becomes based on a transition geometry provided downstream of the swirl generator 100a transitioned seamlessly into a transition piece 200, in such a way that no detachment areas occur there can.
- the configuration of this transition geometry is described in more detail in FIG. 12.
- This transition piece 200 is the outflow side of the transition geometry through a pipe 20 extended, both parts of the actual mixing tube 220 of the burner 300 form.
- Transition piece 200 and tube 20 into one contiguous structures are fused, the characteristics of each part are preserved.
- Transition piece 200 and tube 20 created from two parts are connected by a sleeve ring 50, the same socket ring 50 on the head side as anchoring surface for serves the swirl generator 100a.
- a sleeve ring 50 has furthermore the advantage that different mixing tubes are used can be. Downstream of the tube 20 is located the actual combustion chamber 122, which is essentially corresponds to that of Fig. 1 and here only by a flame tube 30 is symbolized.
- the mixing tube 220 met the condition that downstream of the swirl generator 100a a defined mixing section is provided, in which a perfect premix of different types of fuel is achieved.
- This mixing section ie the mixing tube 220, enables furthermore a lossless flow guidance, so that is also in operative connection with the transition geometry cannot initially form a backflow zone, with which the Length of the mixing tube 220 to the mix quality for everyone Fuel types influence can be exerted.
- This mixing tube 220 has yet another property, which is that in the mixing tube 220 itself the axial speed profile a pronounced maximum on the axis possesses, so that the flame reignites from the combustion chamber not possible. However, it is true that at such a configuration this axial speed Wall falls down.
- the swirl generator 100a according to FIG. 8 corresponds to the physical one Design forth, as already mentioned, largely the burner 100 according to FIG. 3, this swirl generator 100a no longer has a front wall. Regarding the Differences that can be identified here are explained below Fig. 7 referenced.
- FIGS. 4-6 relate to the explanations under FIGS. 4-6 directed.
- FIG. 10 shows that the swirl generator 100a now made up of four partial bodies 130, 131, 132, 133 is.
- the associated longitudinal symmetry axes for each partial body are marked with the letter a.
- This configuration can be said that because of the generated lower twist strength and in cooperation with one suitably suitably enlarged slot width, the bursting of the vortex flow on the downstream side of the To prevent swirl generator 110a in the mixing tube 220, which the Mixing tube can best fulfill the role intended for it.
- Fig. 11 differs from Fig. 10 in that here the partial body 140, 141, 142, 143 a blade profile shape have which to provide a certain flow is provided. Otherwise, the mode of operation of the swirl generator stayed the same.
- the admixture of fuel 116 occurs in the combustion air flow 115 the inside of the blade profiles, i.e. the fuel line 108 is now integrated in the individual blades.
- the transition geometry is for a swirl generator 100a with four partial bodies, corresponding to FIG. 10 or 11, built up. Accordingly, the transition geometry points as natural extension of the upstream parts four transition channels 201, creating the conical quarter surfaces the partial body mentioned is extended until it Wall of the tube 20 respectively. of the mixing tube 220 cut.
- the same considerations also apply when the swirl generator from a different principle than that described under Fig. 8, is constructed.
- the one running downward in the direction of flow The area of the individual transition channels 201 has a in the direction of flow in a spiral shape, which describes a crescent shape, corresponding to the The fact that the flow cross section of the Transition piece 200 flared in the direction of flow.
- the swirl angle of the transition channels 201 in the flow direction is selected so that the pipe flow 40 to enough for the cross-sectional jump at the combustion chamber inlet large distance remains to make a 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 220 cause a significant increase in Axial velocity profile to the center of this mixing tube down, so the risk of early ignition is crucial is counteracted.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air Supply (AREA)
- Gas Burners (AREA)
Description
- Fig. 1
- eine Ringbrennkammer im Bereich der Implementierung der Kühlluft in den Verbrennungsluftstrom,
- Fig. 2
- eine Ansicht der Ringbrennkammer entlang der Schnittebene II.-II. aus Fig. 1,
- Fig. 3
- einen Vormischbrenner in perspektivischer Darstellung, entsprechend aufgeschnitten,
- Fig. 4-6
- Ansichten durch verschiedene Schnittebenen des Brenners gemäss Fig. 3,
- Fig. 7
- einen weiteren Brenner,
- Fig. 8
- einen Drallerzeuger als Bestandteil des Brenners gemäss Fig. 7, in perspektivischer Darstellung, entsprechend aufgeschnitten,
- Fig. 9
- eine Schnittebene durch den als zweischalig ausgebildeten Drallerzeuger gemäss Fig. 8,
- Fig. 10
- eine Schnittebene durch einen vierschaligen Drallerzeuger,
- Fig. 11
- eine Schnittebene durch einen Drallerzeuger, dessen Schalen schaufelförmig profiliert sind und
- Fig. 12
- eine Darstellung der Form der Uebergangsgeometrie zwischen Drallerzeuger und nachgeschaltetem Mischrohr.
- 1
- Ringbrennkammer
- 2, 3
- Ringförmiger Kühlluftkanal
- 4
- Kühlluft
- 5
- Beschleunigungsluft
- 5a
- Bohrungen
- 6
- Luftstrom aus Kühlluft und Beschleunigungsluft
- 7
- Plenum
- 8
- Injektorsystem, Kanal
- 9
- Injektorsystem, Kanal
- 10
- Wellenachse
- 11
- Heissgase
- 20
- Rohr
- 21
- Bohrungen, Luftdurchlassöffnungen
- 30
- Flammrohr
- 40
- Strömung, Rohrströmung im Mischrohr
- 50
- Buchsenring
- 100
- Vormischbrenner
- 100a
- Drallerzeuger
- 101, 102
- Teilkörper von Brenner 100 und Brenner 300
- 101a, 102a
- Zylindrische Angangsteile
- 101b, 102b
- Längssymmetrieachsen
- 103
- Brennstoffdüse
- 104
- Brennstoffeindüsung
- 105
- Brennstoffeindüsungsprofil
- 106
- Rückströmzone (Vortex Breakdown)
- 107
- Flammenfront
- 108, 109
- Brennstoffleitungen
- 110
- Frontwand
- 110a
- Luftbohrungen
- 110b
- Kühlluft
- 112
- Flüssiger Brennstoff
- 113
- Gasförmiger Brennstoff
- 114
- Kegelhohlraum
- 115
- Verbrennungsluft
- 116
- Brennstoff-Eindüsung
- 117
- Brennstoffdüsen
- 119, 120
- Tangentiale Lufteintrittsschlitze
- 121a, 121b
- Leitbleche
- 122
- Brennraum
- 123
- Drehpunkt der Leitbleche
- 130, 131, 132, 133
- Teilkörper
- 130a, 131a, 132a, 133a
- Längssymmetrieachsen
- 140, 141, 142, 143
- Schaufelprofilförmige Teilkörper
- 140a, 141a, 142a, 143a
- Längssymmetrieachsen
- 200
- Uebergangssstück
- 201
- Uebergangskanäle
- 220
- Mischrohr
- 300
- Brenner
Claims (19)
- Brennkammer (1), im wesentlichen bestehend aus einem Plenum (7) zur Aufnahme mindestens eines Verdichterluftstromes, aus mindestens einem innerhalb des Plenums (7) plazierten Brenner (100), einem dem Plenum nachgeschalteten Brennraum (122) und einem dem Brennraum ummantelnden, in das Plenum einmündenden, kühlluftführenden Kanal (2, 3), dadurch gekennzeichnet, dass im Bereich der Einmündung des kühlluftführenden Kanals (2, 3) in das Plenum (7) Injektorsysteme (8, 9) angeordnet sind, welche jeweils aus einem Durchflusskanal als Fortsetzung des kühlluftführenden Kanals (2, 3) und aus einer Anzahl von in Umfangsrichtung des Durchflusskanals angeordneten Oeffnungen (5a) bestehen, und dass die Oeffnungen (5a) mit einer Beschleunigungsluft (5) beaufschlagbar sind.
- Brennkammer nach Anspruch 1, dadurch gekennzeicnet, dass die Brennkammer (1) eine Ringbrennkammer ist.
- Brennkammer nach den Ansprüchen 1 und 2, dadurch gekennzeichnet, dass die Injektorsysteme (8, 9) ringförmig um die Wände des Brennraumes (122) angeordnet sind.
- Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Injektorsysteme (8, 9) in das Plenum (7) hineinragen.
- Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass der Brenner (100) aus mindestens zwei hohlen, kegelförmigen, in Strömungsrichtung ineinandergeschachtelten Teilkörpern (101, 102) besteht, deren jeweilige Längssymmetrieachsen (101b, 102b) zueinander versetzt verlaufen, dass die benachbarten Wandungen der Teilkörper (101, 102) in deren Längserstreckung tangentiale Kanäle (119, 120) für einen Verbrennungsluftstrom (115) bilden, dass im von den Teilkörpern (101, 102) gebildeten Kegelhohlraum (114) mindestens eine Brennstoffdüse (103) vorhanden ist.
- Brennkammer nach Anspruch 5, dadurch gekennzeichnet, dass im Bereich der tangentialen Kanäle (119, 120) in deren Längserstreckung weitere Brennstoffdüsen (117) angeordnet sind.
- Brennkammer nach Anspruch 5, dadurch gekennzeichnet, dass sich die Teilkörper (101, 102) in Strömungsrichtung unter einem festen Winkel kegelig erweitern, oder eine zunehmende Kegelneigung, oder eine abnehmende kegelneigung aufweisen.
- Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass der Brenner (300) aus einem Drallerzeugers (100a) und einer stromab des Drallerzeugers angeordneten Mischstrecke (220) besteht, und dass die Mischstrecke (220) stromab des Drallerzeugers (100a) innerhalb eines ersten Streckenteils (200) in Strömungsrichtung verlaufende Uebergangskanäle (201) zur Ueberführung einer im Drallerzeuger (100a) gebildeten Strömung (40) in den stromab der Uebergangskanäle (201) nachgeschalteten Durchflussquerschnitt (20) der Mischstrecke (220) aufweist.
- Brennkammer nach Anspruch 8, dadurch gekennzeichnet, dass der Drallerzeuger (100a) 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; 131a, 132a, 133a, 134a; 140a, 141a, 142a, 143a) der Teilkörper zueinander 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 Kegelhohlraum (114) mindestens eine Brennstoffdüse (103) angeordnet ist.
- Brennkammer nach Anspruch 9, dadurch gekennzeichnet, dass im Bereich der tangentialen Kanäle (119, 120) in deren Längserstreckung weitere Brennstoffdüsen (117) angeordnet sind.
- Brennkammer nach Anspruch 9, dadurch gekennzeichnet, dass die Teilkörper (140, 141, 142, 143) im Querschnitt eine schaufelförmige Profilierung aufweisen.
- Brennkammer nach Anspruch 8, dadurch gekennzeichnet, dass die Mischstrecke (220) als rohrförmiges Mischelement ausgebildet ist.
- Brennkammer nach den Ansprüchen 8 und 9, dadurch gekennzeichnet, dass die Anzahl der Uebergangskanäle (201) in der Mischstrecke (220) der Anzahl der Teilkörper (101, 102; 131, 132, 133, 134; 140, 141, 142, 143) des Drallerzeugers (100a) entspricht.
- Brennkammer nach Anspruch 8, dadurch gekennzeichnet, dass die Mischstrecke (220) stromab der Uebergangskanäle (201) in Strömungsrichtung und in Umfangsrichtung mit Oeffnungen als Filmlegungsbohrungen (21) zur Eindüsung eines Luftstromes versehen ist.
- Brennkammer nach Anspruch 8, dass die Mischstrecke (220) stromab der Uebergangskanäle (201) mit tangentialen Oeffnungen zur Eindüsung eines Luftstromes versehen ist.
- Brennkammer nach Anspruch 8, dadurch gekennzeichnet, dass der Durchflussquerschnitt (20) der Mischstrecke (220) stromab der Uebergangskanäle (201) kleiner, gleich gross oder grösser als der Querschnitt der im Drallerzeuger (100a) gebildeten Strömung (40) ist.
- Brennkammer nach Anspruch 8, dadurch gekennzeichnet, dass die Uebergangskanäle (201) sektoriell die Stirnfläche der Mischstrecke (220) erfassen und in Strömungsrichtung drallförmig verlaufen.
- Brennkammer nach Anspruch 8, dadurch gekennzeichnet, dass am Ende der Mischstrecke (220) ein Diffusor vorhanden ist.
- Brennkammer nach einem der Anspruche 5 oder 8, dadurch gekennzeichnet, dass stromab des Brenners (100, 300) ein Brennraum (122) angeordnet ist, dass zwischen dem Brenner (100, 300) und dem Brennraum (122) ein Querschnittssprung vorhanden ist, und dass im Bereich dieses Querschnittssprunges eine Rückströmzone (106) vorhanden ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19523094A DE19523094A1 (de) | 1995-06-26 | 1995-06-26 | Brennkammer |
DE19523094 | 1995-06-26 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0751351A1 EP0751351A1 (de) | 1997-01-02 |
EP0751351B1 true EP0751351B1 (de) | 2002-10-16 |
Family
ID=7765231
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP96810353A Expired - Lifetime EP0751351B1 (de) | 1995-06-26 | 1996-05-31 | Brennkammer |
Country Status (4)
Country | Link |
---|---|
US (1) | US5832732A (de) |
EP (1) | EP0751351B1 (de) |
JP (1) | JP4001952B2 (de) |
DE (2) | DE19523094A1 (de) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19720786A1 (de) * | 1997-05-17 | 1998-11-19 | Abb Research Ltd | Brennkammer |
WO1999006767A1 (de) * | 1997-07-31 | 1999-02-11 | Siemens Aktiengesellschaft | Brenner |
DE19737997A1 (de) * | 1997-08-30 | 1999-03-04 | Asea Brown Boveri | Plenum |
EP0918190A1 (de) * | 1997-11-21 | 1999-05-26 | Abb Research Ltd. | Brenner für den Betrieb eines Wärmeerzeugers |
AUPP895999A0 (en) * | 1999-03-01 | 1999-03-25 | Bowin Technology Pty Limited | Gas fired burner apparatus |
GB9929601D0 (en) * | 1999-12-16 | 2000-02-09 | Rolls Royce Plc | A combustion chamber |
DE10049205A1 (de) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Verfahren und Vorrichtung zur Brennstoffversorgung eines Vormischbrenners |
US6360776B1 (en) | 2000-11-01 | 2002-03-26 | Rolls-Royce Corporation | Apparatus for premixing in a gas turbine engine |
US7624722B2 (en) * | 2007-12-31 | 2009-12-01 | Cummins, Inc | Apparatus and system for efficiently recirculating an exhaust gas in a combustion engine |
EP2252831B1 (de) * | 2008-03-07 | 2013-05-08 | Alstom Technology Ltd | Brenneranordnung sowie anwendung einer solchen brenner-anordnung |
WO2009109454A1 (de) * | 2008-03-07 | 2009-09-11 | Alstom Technology Ltd | Verfahren und brenneranordnung zum erzeugen von heissgas sowie anwendung des verfahrens |
DE102010014037A1 (de) | 2009-04-02 | 2010-11-04 | Cummins Filtration IP, Inc., Minneapolis | Reduktionsmittelzersetzungssystem |
FR2945854B1 (fr) * | 2009-05-19 | 2015-08-07 | Snecma | Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant |
EP2685163B1 (de) * | 2012-07-10 | 2020-03-25 | Ansaldo Energia Switzerland AG | Multikonus-Vormischungsbrenner für eine Gasturbine |
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US2621477A (en) * | 1948-06-03 | 1952-12-16 | Power Jets Res & Dev Ltd | Combustion apparatus having valve controlled passages for preheating the fuel-air mixture |
US3691762A (en) * | 1970-12-04 | 1972-09-19 | Caterpillar Tractor Co | Carbureted reactor combustion system for gas turbine engine |
US3751991A (en) * | 1971-05-21 | 1973-08-14 | Technovator Inc | Particulate solid material inspection system |
US3859786A (en) * | 1972-05-25 | 1975-01-14 | Ford Motor Co | Combustor |
US4098075A (en) * | 1976-06-01 | 1978-07-04 | United Technologies Corporation | Radial inflow combustor |
GB1571213A (en) * | 1977-01-28 | 1980-07-09 | Kainov G | Combustion chamber for gas turbine engine |
US4561841A (en) * | 1980-11-21 | 1985-12-31 | Donald Korenyi | Combustion apparatus |
US4651534A (en) * | 1984-11-13 | 1987-03-24 | Kongsberg Vapenfabrikk | Gas turbine engine combustor |
USH1008H (en) * | 1985-05-28 | 1992-01-07 | The United States Of America As Represented By The Secretary Of The Navy | Dump combustor with noncoherent flow |
JPH0816531B2 (ja) * | 1987-04-03 | 1996-02-21 | 株式会社日立製作所 | ガスタ−ビン燃焼器 |
AU1688488A (en) * | 1987-04-30 | 1988-12-02 | Michael G. May | Process and device for combustion of fuel |
US4875339A (en) * | 1987-11-27 | 1989-10-24 | General Electric Company | Combustion chamber liner insert |
US4887432A (en) * | 1988-10-07 | 1989-12-19 | Westinghouse Electric Corp. | Gas turbine combustion chamber with air scoops |
CH678100A5 (de) * | 1989-03-10 | 1991-07-31 | Oertli Waermetechnik Ag | |
CH680816A5 (de) * | 1989-04-27 | 1992-11-13 | Asea Brown Boveri | |
CH680084A5 (de) * | 1989-06-06 | 1992-06-15 | Asea Brown Boveri | |
DE4232442A1 (de) * | 1992-09-28 | 1994-03-31 | Asea Brown Boveri | Gasturbinenbrennkammer |
US5490388A (en) * | 1992-09-28 | 1996-02-13 | Asea Brown Boveri Ltd. | Gas turbine combustion chamber having a diffuser |
DE59208715D1 (de) * | 1992-11-09 | 1997-08-21 | Asea Brown Boveri | Gasturbinen-Brennkammer |
DE4320212A1 (de) * | 1993-06-18 | 1994-12-22 | Abb Research Ltd | Feuerungsanlage |
DE4411624A1 (de) * | 1994-04-02 | 1995-10-05 | Abb Management Ag | Brennkammer mit Vormischbrennern |
DE4415315A1 (de) * | 1994-05-02 | 1995-11-09 | Abb Management Ag | Kraftwerksanlage |
DE4435266A1 (de) * | 1994-10-01 | 1996-04-04 | Abb Management Ag | Brenner |
DE4439619A1 (de) * | 1994-11-05 | 1996-05-09 | Abb Research Ltd | Verfahren und Vorrichtung zum Betrieb eines Vormischbrenners |
-
1995
- 1995-06-26 DE DE19523094A patent/DE19523094A1/de not_active Withdrawn
-
1996
- 1996-05-31 DE DE59609792T patent/DE59609792D1/de not_active Expired - Lifetime
- 1996-05-31 EP EP96810353A patent/EP0751351B1/de not_active Expired - Lifetime
- 1996-06-12 US US08/662,798 patent/US5832732A/en not_active Expired - Lifetime
- 1996-06-20 JP JP15988096A patent/JP4001952B2/ja not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPH0914635A (ja) | 1997-01-17 |
DE59609792D1 (de) | 2002-11-21 |
EP0751351A1 (de) | 1997-01-02 |
US5832732A (en) | 1998-11-10 |
JP4001952B2 (ja) | 2007-10-31 |
DE19523094A1 (de) | 1997-01-02 |
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