US20100323309A1 - Burner and Method for Reducing Self-Induced Flame Oscillations - Google Patents

Burner and Method for Reducing Self-Induced Flame Oscillations Download PDF

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Publication number
US20100323309A1
US20100323309A1 US12/812,301 US81230108A US2010323309A1 US 20100323309 A1 US20100323309 A1 US 20100323309A1 US 81230108 A US81230108 A US 81230108A US 2010323309 A1 US2010323309 A1 US 2010323309A1
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United States
Prior art keywords
fluid
fluid inlet
jet nozzle
mass flow
burner
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Abandoned
Application number
US12/812,301
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English (en)
Inventor
David Barkowski
Matthias Hase
Werner Krebs
Berthold Köstlin
Martin Lenze
Martin Stapper
Jaap Van Kampen
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Siemens AG
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Siemens AG
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Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BARKOWSKI, DAVID, KOESTLIN, BERTHOLD, KREBS, WERNER, LENZE, MARTIN, STAPPER, MARTIN, VAN KAMPEN, JAAP, HASE, MATTHIAS
Publication of US20100323309A1 publication Critical patent/US20100323309A1/en
Abandoned legal-status Critical Current

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    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the present invention relates to a method for reducing self-induced flame oscillations and to a burner with which this method can be carried out.
  • combustion hum Self-induced flame oscillations frequently occur in combustion chambers and in this context are also known as combustion hum.
  • Combustion chamber oscillations are caused by feedback between pressure changes in the combustion chamber and fluctuations in the mass flow of fuel and air.
  • the combustion chamber oscillations constitute an undesirable side-effect of the combustion process, as they place increased mechanical and thermal stress on the burner components and the combustion chamber components.
  • combustion hum produces increased levels of noise pollution in the vicinity of the combustion chamber in question.
  • pilot gas i.e. pilot fuel
  • NO X emissions Reducing combustion hum, i.e. minimizing self-induced flame oscillations, has hitherto been achieved in some cases with the aid of Helmholtz resonators.
  • Another possibility is to supply an increased amount of pilot gas to the burner used. Pilot gas, i.e. pilot fuel, is normally used to stabilize the flame. However, increasing the pilot gas supply results in higher NO X emissions.
  • the object of the present invention is therefore to provide an advantageous method for reducing self-induced flame oscillations.
  • Another object of the present invention is to provide an advantageous burner.
  • the first object is achieved by a method as claimed in the claims.
  • the second object is achieved by a burner as claimed in the claims.
  • the dependent claims contain further advantageous embodiments of the invention.
  • a second mass flow of fluid at least one axial position on the jet nozzle downstream of the fluid inlet opening, one of the two mass flows of fluid being air.
  • the other mass flow of fluid comprises a fuel.
  • the second mass flow of fluid can be injected at at least one radial position on the jet nozzle with respect to the circumference of the jet nozzle.
  • Different radial fuel distributions are preferably implemented.
  • the second mass flow of fluid can preferably be injected into the first mass flow of fluid at a plurality of positions around the circumference of the jet nozzle.
  • the second mass flow of fluid can be injected into the first mass flow of fluid at a plurality of positions disposed mutually offset in the axial direction around the circumference of the jet nozzle.
  • the mass flow of fluid comprising a fuel can be, for example, an air/fuel mixture.
  • the fuel used can, in particular, be gaseous fuel, such as natural gas or a synthesis gas.
  • gaseous fuel such as natural gas or a synthesis gas.
  • natural gas as the mass flows of fuel are much smaller than the air mass flows, there is unlikely to be a significant increase in pressure loss even in the case of injection perpendicular to the flow direction of the air.
  • the method can also be applied to liquid fuels.
  • a third mass flow of fluid can be injected into the first mass flow of fluid.
  • the second mass flow of fluid can comprise a fuel and the first mass flow of fluid can comprise air.
  • the third mass flow of fluid can likewise comprise air, steam or another gas, e.g. an inert gas.
  • the second and/or the third mass flow of fluid can be injected into the first mass flow of fluid at an angle of between 0° and 90°.
  • the second mass flow of fluid can be injected into the first mass flow of fluid at an angle of 90° and the third mass flow of fluid can be injected into the first mass flow of fluid at an angle of 45°.
  • Said first and third mass flow of fluid can be, for example, a mass flow of air, and the second mass flow of fluid can be a mass flow of fuel.
  • the advantage of jet-in-crossflow injection is that it helps to increase the mixing of the air/fuel mixture, while wall film formation is primarily a measure to counteract flashback.
  • the burner according to the invention comprises at least one jet nozzle with a main fluid inlet opening and a fluid outlet opening, the main fluid inlet opening being connected to a fluid supply line.
  • the burner according to the invention is characterized in that at least one secondary fluid inlet opening connected to a fluid supply line is disposed at least one axial position on the jet nozzle downstream of the main fluid inlet opening.
  • the fluid supply line connected to the main fluid inlet opening can be implemented, for example, as a fuel supply line, as an air supply line or as a fuel/air mixture supply line.
  • the main fluid inlet opening is preferably connected to an air supply line.
  • the fluid supply line connected to at least one secondary fluid inlet opening can preferably be implemented as a fuel supply line, it can also be implemented as an air supply line, as a steam supply line, as a nitrogen supply line or as an air/fuel mixture supply line.
  • the secondary fluid inlet openings are disposed at a plurality of axial positions on the jet nozzle.
  • the secondary fluid inlet openings which can be disposed at different axial positions, can be, in particular, air inlet openings.
  • secondary fluid inlet openings can be disposed at a plurality of positions along the circumference of the jet nozzle.
  • secondary fluid inlet openings are disposed at a plurality of positions disposed mutually offset in the axial direction along the circumference of the jet nozzle. This means that the flow in the jet nozzle is not always attenuated at the same circumferential position.
  • the main fluid inlet opening can preferably be connected to an air supply line and a portion of the secondary fluid inlet openings can be connected to a fuel supply line.
  • a first portion of the secondary fluid inlet openings can be connected to a fuel supply line and a second portion of the secondary fluid inlet openings can be connected to an air supply line.
  • the secondary fluid inlet openings and the main fluid inlet opening can have a central axis in each case.
  • Said central axes of the secondary fluid inlet openings can be at an angle of between 0° and 90° to the central axis of the main fluid inlet opening and/or to the central axis of the jet nozzle.
  • the central axes of a first portion of the secondary fluid inlet openings can be at 90° to the central axis of the main fluid inlet opening and/or to the central axis of the jet nozzle
  • the central axes of a second portion of the secondary fluid inlet openings can be at 45° to the central axis of the main fluid inlet opening and/or to the central axis of the jet nozzle.
  • the secondary fluid inlet openings and the main fluid inlet opening may have a central axis in each case and the central axes of the secondary fluid inlet openings can be at an angle of between 0° and 90° to a radial direction with respect to the central axis of the main fluid inlet opening. This enables injection to take place tangentially along the circumference of the jet nozzle, thereby producing a wall film on the inner surface of the jet nozzle. Injection along the circumference of the jet nozzle can also be used to produce swirl in the jet nozzle.
  • a plurality of fluid supply lines connected to secondary fluid inlet openings can be interconnected via an annular distributor disposed along the circumference of the jet nozzle.
  • a fuel nozzle can be disposed in the main fluid inlet opening or immediately preceding the main fluid inlet opening.
  • the fuel nozzle can comprise a fuel distributor which is disposed in or immediately preceding the main fluid inlet opening.
  • At least one secondary fluid inlet opening can be implemented as an annular gap running along the circumference of the jet nozzle.
  • the burner according to the invention can comprise a plurality of jet nozzles, the annular gaps of the different jet nozzles being disposed at different axial positions in each case. Varying the axial positions of the annular gaps provides an additional design parameter for counteracting thermoacoustic flame oscillations.
  • the burner according to the invention can comprise a plurality of jet nozzles disposed e.g. annularly with respect to the central axis of the burner. It can also incorporate one or more pilot burners.
  • the burner according to the invention is preferably used in a gas turbine.
  • FIG. 1 schematically illustrates a section through a jet burner at right angles to its longitudinal direction.
  • FIG. 2 schematically illustrates a section through another jet burner at right angles to its longitudinal direction.
  • FIG. 3 schematically illustrates a section through part of a jet burner in the longitudinal direction.
  • FIG. 4 schematically illustrates a section through part of another jet burner in the longitudinal direction.
  • FIG. 5 schematically illustrates a section through part of an alternative jet burner in the longitudinal direction.
  • FIG. 6 schematically illustrates a section in the longitudinal direction through another jet burner.
  • FIG. 7 schematically illustrates a section through part of a jet burner in the longitudinal direction.
  • FIG. 8 schematically illustrates a jet burner having an annular gap, in the longitudinal direction
  • FIG. 9 schematically illustrates an alternative arrangement of the annular gap of the jet burner shown in FIG. 8 .
  • FIG. 10 shows a cross-section of a jet burner and of the annular distributor with a plurality of radial secondary fluid inlet openings.
  • FIG. 1 schematically illustrates a section through a jet burner 1 perpendicular to a central axis 4 of the burner 1 .
  • the burner 1 comprises a housing 6 having a circular cross-section. Inside the housing 6 , a particular number of jet nozzles 2 are disposed in an essentially annular manner. Each of said jet nozzles 2 has a circular cross-section.
  • the burner 1 can also incorporate a pilot burner.
  • FIG. 2 schematically illustrates a section through a jet burner 101 , said section running perpendicular to the central axis of the burner 101 .
  • the burner 101 likewise has a housing 6 of circular cross-section in which are disposed a number of inner and outer jet nozzles 2 , 3 .
  • the jet nozzles 2 , 3 each have a circular cross-section, said outer jet nozzles 2 having a cross-sectional area that is the same size as, or larger than, that of the inner jet nozzles 3 .
  • the outer jet nozzles 2 are disposed in an essentially annular manner inside the housing 6 and form an outer ring.
  • the inner jet nozzles 3 are likewise disposed in an essentially annular manner inside the housing 6 .
  • the inner jet nozzles 3 fond an inner ring which is disposed concentrically to the outer jet nozzle ring.
  • FIGS. 1 and 2 merely show examples of the arrangement of jet nozzles 2 , 3 inside a jet burner 1 , 101 .
  • FIG. 3 schematically illustrates a section through part of a jet burner 1 according to the invention in the longitudinal direction, i.e. along the central axis 4 of the burner 1 .
  • the burner 1 has at least one jet nozzle 2 disposed in a housing 6 .
  • the central axis of the jet nozzle 2 is identified by the reference character 5 .
  • the jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9 .
  • the combustion chamber 18 is connected to the fluid outlet opening 9 .
  • the jet nozzle 2 is disposed in the housing 6 such that the main fluid inlet opening 8 faces the back wall 24 of the burner 1 .
  • the housing 6 also comprises an outer housing section 27 disposed radially with respect to the central axis 4 of the burner 1 .
  • the jet nozzle 2 is fluidically connected to a compressor.
  • the compressed air from the compressor is conveyed via an annular gap 22 to the main fluid inlet opening 8 and/or is conveyed radially with respect to the central axis 5 of the jet nozzle 2 via an air inlet opening 23 to the main fluid inlet opening 8 .
  • said compressed air flows through the annular gap 22 in the direction of the arrow identified by the reference character 15 , i.e. parallel to the central axis 5 of the jet nozzle 2 .
  • the air flowing in the direction of the arrow 15 is then deflected through 180° at the back wall 24 of the burner 1 and then flows through the main fluid inlet opening 8 into the jet nozzle 2 .
  • the flow direction of the air inside the jet nozzle 2 is indicated by an arrow 10 .
  • the compressed air from the compressor can also be supplied through an opening 23 disposed radially in the housing 6 of the burner 1 with respect to the central axis 5 of the jet nozzle 2 .
  • the flow direction of the compressed air flowing through the opening 23 is indicated by an arrow 26 .
  • the compressed air is then deflected through 90° and then flows into the jet nozzle 2 through the main fluid inlet opening 8 .
  • the burner according to the invention 1 can basically also be implemented without the outer housing section 27 , i.e. without an external casing 27 .
  • the compressed air can flow directly into the “plenum”, i.e. the area between the back wall 24 and the main fluid inlet opening 8 .
  • the burner according to the invention 1 can also be implemented even without the back wall 24 .
  • the jet nozzle 2 is encircled radially by an annular distributor 7 which is supplied with fuel 12 via a fuel supply line 13 .
  • the annular distributor 7 has a number of secondary fluid inlet openings 14 through which fuel can be injected into the mass flow of air flowing through the jet nozzle 2 .
  • the secondary fluid inlet openings 14 can be implemented as a slit or an oval nozzle. This is particularly advantageous for synthesis gas injection, as it means that a smaller inflow surface is offered to the flow of air. This also results in a lesser tendency to recirculation downstream of fuel injection.
  • the flow direction of the fuel 12 injected into the jet nozzle 2 through the secondary fluid inlet openings 14 is indicated by arrows 17 . Said flow direction 17 of the injected fuel 12 runs perpendicular to the central axis 5 of the jet nozzle 2 and therefore also perpendicular to the main flow direction 10 of the compressed air 11 flowing through the jet nozzle 2 .
  • secondary fluid inlet openings 14 are disposed at three different axial positions, two secondary fluid inlet openings 14 being disposed opposite one another at each axial position.
  • a number of secondary fluid inlet openings 14 are advantageously disposed along the circumference of the jet nozzle 2 . These can in particular also be disposed in an axially offset manner with respect to one another. Secondary fluid inlet openings 14 can basically be disposed at only one or at additional axial positions along the circumference of the jet nozzle 2 .
  • FIG. 4 schematically illustrates a section through a burner 201 which constitutes a development of the burner 1 shown in FIG. 3 .
  • the compressed air 11 from a compressor can again either be supplied to the jet nozzle 2 via an annular gap 22 or, as shown in FIG. 3 , injected via an air inlet opening perpendicularly to the central axis 5 of the jet nozzle.
  • the compressed air 11 is preferably supplied to the jet nozzle 2 via an annular gap 22 . Injection perpendicular to the central axis 5 is therefore only denoted by a dashed arrow 26 .
  • the burner 201 shown in FIG. 4 not only has the secondary fluid inlet openings 14 through which fuel is injected into the jet nozzle 2 , but also secondary fluid inlet openings 25 through which the additional compressed air is injected into the jet nozzle 2 in the flow direction indicated by the arrows 16 .
  • Said additional secondary fluid inlet openings 25 are connected to the annular gap 22 . This means that a portion of the compressed air 11 coming from the compressor is conveyed through the annular gap 22 to the back wall 24 of the burner where it is deflected through 180° and is then fed through the main fluid inlet opening 8 into the jet nozzle 2 . This mass flow of air flows through the jet nozzle 2 in the direction indicated by the arrow 10 .
  • Another portion of the compressed air from the compressor is injected from the annular gap 22 into the jet nozzle 2 through the secondary fluid inlet openings 25 in the flow direction indicated by the arrows 16 .
  • Said secondary fluid inlet openings 25 can be disposed at different axial positions around the jet nozzle 2 .
  • the secondary fluid inlet openings 25 through which compressed air is injected into the jet nozzle 2 are disposed such that a secondary fluid inlet opening 25 is disposed in each case in the flow direction 10 downstream of a secondary fluid inlet opening 14 through which fuel 12 is injected into the jet nozzle 2 .
  • Any other arrangements are self-evidently also possible.
  • the secondary fluid inlet openings 25 are disposed in a radial offset manner along the circumference of the jet nozzle 2 . This means that the flow is not always attenuated at the same circumferential position.
  • the secondary fluid inlet openings 14 and 25 are disposed such that the fuel 12 is injected through the secondary fluid inlet openings 14 perpendicularly to the flow direction 10 of the compressed air 11 flowing through the main fluid inlet opening 8 into the jet nozzle 2 . Further compressed air is injected into the jet nozzle 2 through the secondary fluid inlet openings 25 at an angle of about 45° to the main flow direction 10 . Both the fuel 12 and the additional compressed air can be injected into the jet nozzle 2 at any other angle of between 0° and 90° to the main flow direction 10 at different axial positions. As e.g. for natural gas, the mass flows of fuel are much smaller than the mass flows of air, a significant increase in the pressure loss is unlikely to occur even in the case of perpendicular fuel injection. The fuel 12 can also be injected against the air flow direction 10 .
  • the fuel can basically be supplied via one or more fuel supply lines 13 and transported to the individual jet nozzles 2 via an annular distributor 7 . If a plurality of fuel supply lines 13 are present, these can be advantageously disposed along the circumference of the burner. It is further advantageous if the injection of the fuel into the air jet is carried out at more than one axial position of the jet pipe 2 . In addition, to ensure better mixing, injection can take place at a plurality of circumferential positions on the jet pipe 2 .
  • a second exemplary embodiment will now be described in greater detail with reference to FIGS. 5 to 7 .
  • Elements corresponding to elements already described in the first exemplary embodiment are provided with the same reference characters and will not be described again in detail.
  • FIGS. 5 to 7 each show sections through part of a burner 301 along the central axis 4 of the burner 301 .
  • the burner 301 has at least one, but advantageously a plurality of jet nozzles 2 disposed in an essentially annular manner about the central axis 4 .
  • the jet nozzles 2 , 3 please refer to FIGS. 1 and 2 and the statements made in that context.
  • a fuel nozzle 19 is disposed in the region of the main fluid inlet opening 8 of the jet nozzle 2 .
  • fuel 12 is injected into the jet nozzle 2 .
  • the fuel 12 is preferably injected at an angle of about 45° to the flow direction 10 of the compressed air 11 flowing into the jet nozzle through the main fluid inlet opening 8 .
  • the flow direction of the fuel 12 injected through the fuel nozzle 19 is indicated by arrows 17 .
  • the fuel 12 can also be injected into the jet nozzle 2 at an angle of between 0° and 90° with respect to the flow direction 10 of the compressed air 11 .
  • Disposed at different axial positions on the jet nozzle 2 are further secondary fluid inlet openings 25 through which compressed air can be injected into the jet nozzle 2 .
  • Said compressed air is fed to the secondary fluid inlet openings 25 via an annular gap 22 .
  • the compressed air is injected through the secondary fluid inlet openings 25 into the jet nozzle 2 perpendicularly to the central axis 5 of the jet nozzle.
  • said compressed air from a compressor flows through the annular gap 22 in the direction of the arrow 15 .
  • the compressed air coming from a compressor is injected into the burner 301 perpendicularly to the central axis 5 of the jet nozzle 2 through an air inlet opening 23 .
  • the flow direction of the compressed air 11 passing through the opening 23 is indicated by an arrow 26 .
  • the compressed air 11 now flows through the annular gap 22 to the secondary fluid inlet openings 25 and is fed via the latter into the jet nozzle 2 .
  • the main portion of the compressed air 11 is introduced into the jet nozzle 2 though the main fluid inlet opening 8 in the flow direction 10 .
  • FIG. 7 shows an alternative embodiment of the burner 301 shown in FIG. 5 .
  • the secondary fluid inlet openings 25 are disposed such that the compressed air injected into the jet nozzle 2 through the secondary fluid inlet openings 25 is injected into said jet nozzle at an angle of approximately 45° to the central axis 5 of the jet pipe 2 .
  • Another injection angle between 0° and 90° is basically possible and practical.
  • the air used for the axially stepped air injection in this exemplary embodiment can either be extracted from the annular gap 22 or directly from a plenum surrounding the burner 301 and injected into the fuel/air mixture in the jet nozzle.
  • Said air can be introduced as a jet into the crossflow or as a wall film.
  • the advantage of jet-in-crossflow injection is that it helps to increase the mixing of the fuel/air mixture, while wall film formation is primarily a measure to counteract possible flashback.
  • the air can be injected into the jet nozzle 2 tangentially to the circumference thereof. Said wall film can be produced over the entire inner surface of the jet nozzle 2 . Tangential injection can also be used to generate swirl in the jet nozzle 2 .
  • jet-in-crossflow injection it is also conceivable for jet-in-crossflow injection to be combined with wall film injection by disposing the nozzles in very close succession. Jet-in-crossflow injection ensures improved mixing, particularly also in the core region of the jet, and the film of the second nozzle strengthens the flow boundary layer, thereby preventing flashback.
  • This design is particularly advantageous for central co-flow injection into the main fuel injection, e.g. for synthesis gas. If there is a high proportion of air in the axial stepping, it is possible to adjust the nozzle diameter of the jet nozzle such that the flow rate in the nozzle remains essentially the same.
  • a third exemplary embodiment will now be explained in greater detail with reference to FIGS. 8 and 9 .
  • Elements corresponding to elements already described in the first exemplary embodiment are provided with the same reference characters and will not be described again in detail.
  • FIGS. 8 and 9 schematically illustrate different variants of a burner 401 in the longitudinal direction along the central axis 4 of the burner 401 .
  • the burner 401 has a number of jet nozzles 2 which are disposed in an essentially annular manner about the central axis 4 of the burner 401 .
  • the jet nozzles 2 , 3 please refer to FIGS. 1 and 2 and the statements made in that context.
  • Each jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9 .
  • the fluid outlet opening 9 leads into the combustion chamber 18 .
  • a fuel nozzle 19 is disposed in the main fluid inlet opening 8 .
  • the fuel nozzle 19 comprises a fuel distributor 20 which enables fuel 12 to be injected into the jet nozzle 2 at different radial positions and different circumferential positions of the main fluid inlet opening 8 .
  • the flow direction of the injected fuel 12 is indicated by arrows 17 .
  • An annular gap 21 is disposed at another axial position on the jet nozzle 2 downstream in respect of the flow directions 10 and 17 . Air is injected into the jet nozzle 2 through the annular gap 21 . The flow direction of the injected air is indicated by arrows 16 . Said air is injected into the jet nozzle 2 virtually parallel to the central axis 5 thereof. In contrast to the variant shown in FIG. 8 , in FIG. 9 the annular gap 21 is disposed at a position further downstream of the main fluid inlet opening 8 . In the two variants shown in FIGS.
  • the compressed air used from a compressor can be either passed through an annular gap 22 in the flow direction 15 to the main fluid inlet opening 8 of the jet nozzle 2 and/or injected perpendicularly to the central axis 5 in the flow direction 26 .
  • the variants shown in FIGS. 8 and 9 include the possibility of inserting into the burner 401 , from the back wall 24 of the burner, the nozzle section located downstream in terms of the flow direction 15 of the compressed air coming from the compressor and on which the fuel distribution also depends, and positioning it by means of the front combustion-chamber-side section, e.g. by means of spacers in the annular space. In the extreme case, the downstream nozzle section sits directly in the bottom of the fire tube.
  • FIG. 10 shows a cross-section of a jet burner 1 and of the annular distributor 7 with a plurality of radial secondary fluid inlet openings 14 .
  • Said annular distributor 7 comprises a complete annulus of jet nozzles 2 . Radiating from the annular distributor 7 are secondary fluid inlet openings 14 which meet the jet nozzles 2 at different circumferential positions. Long secondary fluid inlet openings 14 can be used. Secondary fluid inlet openings 14 can also be at an angle to the jet nozzle 2 .
  • the jet nozzles 2 can be disposed in any manner. It is also conceivable merely for an annular distributor 7 with fuel to be present and the jet nozzles to be disposed in any manner within it (central jet burner 1 ).
  • the inventive burner 1 , 101 , 201 , 301 , 401 can also be implemented without the outer housing section 27 or rather without an outer casing 27 .
  • the compressed air can flow directly into the “plenum”, i.e. the area between the back wall 24 and the main fluid inlet opening 8 .
  • the inventive burner 1 , 101 , 201 , 301 , 401 can also be implemented without the back wall 24 .
  • Varying the axial positions of the annular gaps 21 provides an additional design parameter to guard against thermoacoustic flame oscillations. It is also possible to provide different jet nozzles 2 of a burner 401 with annular gaps 21 at different axial positions.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)
US12/812,301 2008-01-11 2008-04-24 Burner and Method for Reducing Self-Induced Flame Oscillations Abandoned US20100323309A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08000497A EP2078898A1 (de) 2008-01-11 2008-01-11 Brenner und Verfahren zur Verringerung von selbstinduzierten Flammenschwingungen
EP08000497.1 2008-01-11
PCT/EP2008/054969 WO2009086943A1 (de) 2008-01-11 2008-04-24 Brenner und verfahren zur verringerung von selbstinduzierten flammenschwingungen

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EP (2) EP2078898A1 (de)
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CN104024737A (zh) * 2011-10-31 2014-09-03 西门子公司 用于燃气轮机的燃烧室和燃烧器装置
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US20150308349A1 (en) * 2014-04-23 2015-10-29 General Electric Company Fuel delivery system
US20170198914A1 (en) * 2014-09-25 2017-07-13 Duerr Systems Ag Burner head of a burner and gas turbine having a burner of this type
CN115176114A (zh) * 2020-04-22 2022-10-11 三菱重工业株式会社 烧嘴集合体、燃气轮机燃烧器以及燃气轮机

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US8539773B2 (en) * 2009-02-04 2013-09-24 General Electric Company Premixed direct injection nozzle for highly reactive fuels
EP2236932A1 (de) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Verfahren zum Betrieb eines Brenners und Brenner, insbesondere für eine Gasturbine
EP2282122A1 (de) * 2009-08-03 2011-02-09 Siemens Aktiengesellschaft Stabilisierung der Flamme eines Vormischbrenners

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EP2078898A1 (de) 2009-07-15
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WO2009086943A1 (de) 2009-07-16

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