EP2078898A1 - Brûleur et procédé pour réduire des oscillations de flammes autoinduites - Google Patents

Brûleur et procédé pour réduire des oscillations de flammes autoinduites Download PDF

Info

Publication number
EP2078898A1
EP2078898A1 EP08000497A EP08000497A EP2078898A1 EP 2078898 A1 EP2078898 A1 EP 2078898A1 EP 08000497 A EP08000497 A EP 08000497A EP 08000497 A EP08000497 A EP 08000497A EP 2078898 A1 EP2078898 A1 EP 2078898A1
Authority
EP
European Patent Office
Prior art keywords
fluid
burner
mass flow
fuel
jet nozzle
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.)
Withdrawn
Application number
EP08000497A
Other languages
German (de)
English (en)
Inventor
David Barkowski
Matthias Dr. Hase
Werner Dr. Krebs
Berthold Köstlin
Martin Lenze
Martin Stapper
Jaap Dr. Van Kampen
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP08000497A priority Critical patent/EP2078898A1/fr
Priority to PCT/EP2008/054969 priority patent/WO2009086943A1/fr
Priority to EP08749689.9A priority patent/EP2232147B1/fr
Priority to US12/812,301 priority patent/US20100323309A1/en
Publication of EP2078898A1 publication Critical patent/EP2078898A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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 vibrations and a burner with which this method can be carried out.
  • Self-induced flame vibrations often occur in combustion chambers and are referred to in this context as Brennschbrummen.
  • a feedback between pressure changes in the combustion chamber and mass flow fluctuations of fuel and air are responsible.
  • the combustion chamber vibrations are an undesirable side effect of the combustion process, since they cause an increased mechanical and thermal loading of the burner components and the combustion chamber components.
  • the combustion chamber hum caused an increased noise in the environment of the respective combustion chamber.
  • a reduction in the combustion chamber humming or a minimization of self-induced flame vibrations has been achieved in part by using Helmholtz resonators.
  • Another possibility is to supply the burner used an increased pilot gas quantity. Pilot gas or pilot fuel is usually used to stabilize the flame. However, an increased supply of pilot gas also leads to increased NO x emissions.
  • the first object is achieved by a method according to claim 1.
  • the second object is achieved by a burner according to claim 9 solved.
  • the dependent claims contain further, advantageous embodiments of the invention.
  • a second fluid mass flow is injected into a first fluid mass flow which flows through a jet nozzle from a fluid inlet opening to a fluid outlet opening at at least one axial flow position of the jet nozzle downstream of the fluid inlet opening.
  • one of the two fluid mass flows comprises air.
  • the other fluid mass flow includes a fuel.
  • the second fluid mass flow can be injected into the first fluid mass flow at a plurality of positions of the circumference of the jet nozzle.
  • the second fluid mass flow can be injected into a plurality of axially offset positions of the circumference of the jet nozzle in the first fluid mass flow. This causes the flow in the jet nozzle is not always weakened at the same circumferential position.
  • the fluid mass flow comprising a fuel can be, for example, an air-fuel mixture.
  • the fuel used may in particular be gaseous fuel, for example natural gas or a synthesis gas.
  • natural gas the fuel mass flows are significantly lower than the air mass flows, is Even in the case of an injection perpendicular to the flow direction of the air not to expect a significant increase in pressure loss.
  • the method can also be applied to liquid fuels.
  • a third fluid mass flow can be injected into the first fluid mass flow.
  • the second fluid mass flow may comprise a fuel and the first fluid mass flow may comprise air.
  • the third fluid mass flow may also comprise air, steam or another gas, for example an inert gas.
  • the second and / or the third fluid mass flow can be injected into the first fluid mass flow at an angle between 0 ° and 90 °.
  • the second fluid mass flow may be injected into the first fluid mass flow at an angle of 90 ° and the third fluid mass flow may be injected into the first fluid mass flow at an angle of 45 °.
  • the first and the third fluid mass flow may be an air mass flow and the second fluid mass flow may be a fuel mass flow.
  • the burner according to the invention comprises at least one jet nozzle with a main fluid inlet opening and a fluid outlet opening, wherein the main fluid inlet opening is connected to a fluid supply line.
  • the burner according to the invention is characterized in that at least one fluid secondary inlet opening, which is connected to a fluid supply line, is arranged on at least one axial axial position of the jet nozzle downstream of the main fluid inlet opening.
  • the fluid supply line connected to the fluid main inlet opening can be used, for example, as a fuel feed line, as an air feed line or be designed as a fuel-air mixture supply line.
  • the main fluid inlet port is connected to an air supply line.
  • the fluid supply line connected to at least one secondary fluid inlet opening can preferably be designed as a fuel supply line. However, it can also be configured as an air supply line, as a steam supply line, as a nitrogen supply line or as a fuel-air mixture supply line.
  • the secondary fluid inlet openings are arranged at a plurality of axial positions of the jet nozzle.
  • the secondary fluid inlet openings which may be arranged at different axial positions, may in particular be air inlet openings.
  • fluid sub-inlet openings may be disposed at a plurality of positions along the circumference of the jet nozzle.
  • secondary fluid inlet openings are arranged at a plurality of positions offset in the axial direction from each other along the circumference of the jet nozzle. This causes the flow in the jet nozzle is not always weakened at the same circumferential position.
  • the main fluid inlet port may be connected to an air supply line and a part of the fluid sub-inlet ports may be connected to a fuel supply line.
  • a first part of the fluid sub-inlet openings can be connected to a fuel feed line and a second part of the fluid sub-inlet openings can be connected to an air feed line.
  • the fluid sub-inlet openings and the main fluid inlet opening can each have a central axis.
  • the center axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to the central axis of the main fluid inlet opening and / or to the center axis of the jet nozzle.
  • the center axes of a first part of the fluid sub-inlet ports may be at an angle of 90 ° to the central axis of the main fluid inlet port and / or to the central axis of the jet nozzle and the center axes of a second part of the fluid secondary inlet openings are at an angle of 45 ° to the central axis of the main fluid inlet opening and / or to the central axis of the jet nozzle.
  • the fluid sub-inlet openings and the main fluid inlet opening may each have a central axis, and the center axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to a radial direction with respect to the center axis of the main fluid inlet opening.
  • This can be injected tangentially along the circumference of the jet nozzle and in this way a wall film can be produced on the inner surface of the jet nozzle.
  • An injection along the circumference of the jet nozzle can also be used to generate vortices in the jet nozzle.
  • a plurality of fluid supply lines connected to fluid side inlet openings may be connected to one another via a ring distributor arranged along the circumference of the jet nozzle.
  • a fuel nozzle can be arranged in the main fluid inlet opening or directly in front of the main fluid inlet opening.
  • the fuel nozzle may include a fuel distributor disposed in or immediately in front of the main fluid inlet port.
  • At least one secondary fluid inlet opening may be designed as an annular gap extending along the circumference of the jet nozzle.
  • the burner according to the invention may comprise a plurality of jet nozzles, wherein the annular gaps of the various jet nozzles are arranged at respectively different axial positions. By varying the axial positions of the annular gaps, an additional design parameter against thermoacoustic flame oscillations is obtained.
  • the burner according to the invention may comprise a plurality of, for example, annularly arranged with respect to the central axis of the burner, jet nozzles. It may further include one or more pilot burners.
  • FIG. 1 schematically shows a section through a jet burner 1 perpendicular to a central axis 4 of the burner 1.
  • the burner 1 comprises a housing 6 which has a circular cross-section. Within the housing 6 a certain number of jet nozzles 2 is arranged substantially annular. Each jet nozzle 2 has a circular cross section.
  • the burner 1 may comprise a pilot burner.
  • FIG. 2 schematically shows a section through a jet burner 101, wherein the section is perpendicular to the central axis of the burner 101.
  • the burner 101 also has a housing 6, which has a circular cross section and in which a number of inner and outer jet nozzles 2, 3 is arranged.
  • the jet nozzles 2, 3 each have a circular cross-section, wherein the outer jet nozzles 2 have an equal or larger cross-sectional area than the inner jet nozzles 3.
  • the outer jet nozzles 2 are arranged substantially annularly within the housing 6 and form an outer ring.
  • the inner jet nozzles 3 are also arranged annularly within the housing 6.
  • the inner jet nozzles 3 form an inner ring, which is arranged concentrically to the outer jet nozzle ring.
  • FIGS. 1 and 2 merely show examples of the arrangement of jet nozzles 2, 3 within a jet burner 1, 101. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 2, 3 are possible.
  • FIG. 3 schematically shows a section through a portion of a jet burner 1 according to the invention in the longitudinal direction, ie along the central axis 4 of the burner 1.
  • the burner 1 has at least one arranged in a housing 6 jet nozzle 2 on.
  • the central axis of the jet nozzle 2 is indicated by the reference numeral 5.
  • the jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9.
  • the combustion chamber 18 adjoins the fluid outlet opening 9.
  • the jet nozzle 2 is arranged in the housing 6 such that the main fluid inlet opening 8 faces the rear wall 24 of the burner 1.
  • the housing 6 further comprises a radially outer housing part 27 with respect to the central axis 4 of the burner 1.
  • the jet nozzle 2 is fluidically connected to a compressor.
  • the compressed air coming from the compressor is conducted via an annular gap 22 to the main fluid inlet opening 8 and / or directed via an air inlet opening 23 radially with respect to the central axis 5 of the jet nozzle 2 to the main fluid inlet opening 8.
  • the compressed air flows through the annular gap 22 in the direction of the arrow indicated by the reference numeral 15, ie parallel to the central axis 5 of the jet nozzle 2.
  • the in the direction of arrow 15th flowing air is then deflected at the rear wall 24 of the burner 1 by 180 ° and then flows through the main fluid inlet 8 into the jet nozzle 2.
  • the flow direction of the air within the jet nozzle 2 is indicated by an arrow 10.
  • the compressed air coming from the compressor can also be supplied through an opening 23 which is arranged in the housing 6 of the burner 1 radially 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 by 90 ° and then flows through the main fluid inlet 8 into the jet nozzle. 2
  • the burner 1 according to the invention can in principle also without the outer housing part 27 or without an outer housing 27 be configured.
  • the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the main fluid inlet opening 8.
  • the burner 1 according to the invention can furthermore be designed without the rear wall 24.
  • the jet nozzle 2 is surrounded radially by a ring distributor 7, which is supplied with fuel 12 via a fuel feed line 13.
  • the annular distributor 7 has a number of fluid secondary inlet openings 14, through which fuel can be injected into the air mass flow flowing through the jet nozzle 2.
  • the direction of flow of the fuel 12 injected into the jet nozzle 2 through the fluid sub-inlet openings 14 is indicated by arrows 17.
  • the flow direction 17 of the injected fuel 12 extends perpendicular to the central axis 5 of the jet nozzle 2 and thus also perpendicular to the main flow direction 10 of the compressed air 11 flowing through the jet nozzle 2.
  • Fluid side inlet openings 14 are arranged at three different axial positions, wherein at each axial position in each case two fluid side inlet openings 14 are arranged opposite to each other.
  • a number of fluid sub-inlet openings 14 are arranged along the circumference of the jet nozzle 2. These can in particular also be arranged axially offset from one another.
  • secondary fluid inlet openings 14 may be arranged at only one or at further axial positions along the circumference of the jet nozzle 2.
  • FIG. 4 schematically shows a section through a burner 201, a further development of in the FIG. 3 shown Burner 1 represents.
  • the compressed air 11 coming from a compressor can in turn be supplied to the jet nozzle 2 either via an annular gap 22 or, as in FIG FIG. 3 is shown, are injected via an air inlet opening perpendicular to the central axis 5 of the jet nozzle.
  • the compressed air 11 is supplied via an annular gap 22 of the jet nozzle 2.
  • the injection perpendicular to the central axis 5 is therefore indicated only by a dashed arrow 26.
  • burner 201 in addition to the fluid sub-inlet openings 14, is injected through the fuel in the jet nozzle 2, further fluid side inlet openings 25, is injected through the additional compressed air in the flow direction indicated by arrows 16 in the jet nozzle 2.
  • additional fluid sub-inlet openings 25 are connected to the annular gap 22. This means that part of the compressed air coming from the compressor 11 is passed through the annular gap 22 to the rear wall 24 of the burner, where it is deflected by 180 ° and then passes through the main fluid inlet opening 8 into the jet nozzle 2. This air mass flow flows through the jet nozzle 2 in the direction indicated by an arrow 10 direction.
  • the fluid sub-inlet openings 25 can be arranged at different axial positions of the jet nozzle 2.
  • the fluid secondary inlet openings 25, through which compressed air is injected into the jet nozzle 2 are arranged such that a fluid secondary inlet opening 25 is arranged downstream of a fluid secondary inlet opening 14 through which fuel 12 is injected into the jet nozzle 2 in the flow direction 10 downstream.
  • the fluid secondary inlet openings 25 along the circumference of the Blasting nozzle 2 are arranged offset radially. In this way, the flow is not always weakened at the same circumferential position.
  • the fluid side inlet openings 14 and 25 are arranged such that the fuel 12 is injected through the fluid secondary inlet openings 14 perpendicular 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 through the fluid sub-inlet openings 25 at an angle of about 45 ° to the main flow direction 10 in the jet nozzle 2. Both the fuel 12 and the additional compressed air can be injected at any other angle between 0 ° and 90 ° to the main flow direction 10 at different axial positions in the jet nozzle 2. Since, for example, for natural gas, the fuel mass flows are significantly lower than the air mass flows, no significant increase in the pressure loss is to be expected even in the case of a vertical fuel injection. The fuel 12 can also be injected counter to the air flow direction 10.
  • the fuel can be supplied via one or more fuel supply lines 13 and transported via a ring distributor 7 to the individual jet nozzles 2.
  • these can advantageously be arranged along the circumference of the burner. It is also advantageous if the injection of the fuel into the air jet at more than one axial position of the jet pipe 2 is completed. In addition, for a better mixing at several circumferential positions of the jet pipe 2 can be injected.
  • FIGS. 5 to 7 each show sections through a portion of a burner 301 along the central axis 4 of the burner 301.
  • the burner 301 has at least one, but advantageously a plurality, substantially annularly arranged around the central axis 4 jet nozzles 2. With respect to possible arrangements of the jet nozzles 2, 3 is on the Figures 1 and 2 and the remarks made in this connection.
  • a fuel nozzle 19 is arranged.
  • fuel 12 is injected into the jet nozzle 2.
  • the fuel 12 is preferably injected at an angle of approximately 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 injected fuel nozzle 19 through the fuel 12 is indicated by arrows 17.
  • the fuel 12 can also be injected at a different angle between 0 ° and 90 ° to the flow direction 10 of the compressed air 11 in the jet nozzle 2.
  • the compressed air coming from a compressor is injected through an air inlet opening 23 perpendicular to the central axis 5 of the jet nozzle 2 in the burner 301.
  • the flow direction of the opening 23 passing compressed air 11 is indicated by an arrow 26.
  • the compressed air 11 now flows through the annular gap 22 to the fluid sub-inlet openings 25 and passes through them into the jet nozzle 2.
  • the majority of the compressed air 11 is introduced into the jet nozzle 2 through the main fluid inlet opening 8 in the flow direction 10.
  • FIG. 7 shows an alternative embodiment of the in the FIG. 5 shown burner 301.
  • the fluid sub-inlet openings 25 are arranged so that the compressed air injected through the fluid sub-inlet openings 25 into the blasting nozzle 2 is injected into the blasting tube 2 at an angle of approximately 45 ° to the central axis 5 of the latter.
  • another Eindüswinkel between 0 ° and 90 ° is possible and useful.
  • the air used for the axially stepped Heileindüsung of the present embodiment can be removed either from the annular gap 22 or directly from a surrounding the burner 301 plenum and are injected into the fuel-air mixture in the jet nozzle.
  • the air can be introduced as a jet in the cross flow or as a wall film.
  • the advantage of jet-in-cross-flow injection is a contribution to increased mixing of the fuel-air mixture, while wall-film formation is primarily a measure against potential flashback.
  • the air can be injected tangentially with respect to the circumference of the jet nozzle 2 in this. In this case, a wall film can be produced on the entire inner surface of the jet nozzle 2. Tangential injection can also be used to generate turbulence in the jet nozzle 2.
  • jet-in-cross-flow injection with a wall-film injection by arranging the nozzles very shortly one behind the other.
  • the jet-in-cross flow injection provides for improved mixing, especially in the core region of the jet, and the film of the second jet strengthens the flow boundary layer and thus prevents a flashback.
  • This embodiment is particularly advantageous for a central co-flow injection in the Hauptbrennscherindüsung, for example for synthesis gas. With a high proportion of air in the axial staging, it is possible to adjust the nozzle diameter of the jet nozzle so that the flow velocity in the nozzle remains substantially the same.
  • FIGS. 8 and 9 schematically show various variants of a burner 401 longitudinally along the central axis 4 of the burner 401.
  • the burner 401 has a number of jet nozzles 2, which are arranged substantially annularly around the central axis 4 of the burner 401.
  • jet nozzles 2, 3 is on the Figures 1 and 2 and the remarks made in this connection.
  • Each jet nozzle 2 comprises a main fluid inlet opening 8 and a fluid outlet opening 9.
  • the fluid outlet opening 9 opens into the combustion chamber 18.
  • a fuel nozzle 19 is arranged in the main fluid inlet opening 8.
  • the fuel nozzle 19 comprises a fuel distributor 20 with the aid of which fuel 12 can 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.
  • annular gap 21 is arranged at a further downstream with respect to the flow directions 10 and 17 located axial position of the jet nozzle 2. Air is injected into the jet nozzle 2 through the annular gap 21. The flow direction the injected air is indicated by arrows 16. The air is injected almost parallel to the central axis 5 of the jet nozzle 2 in this. Unlike the one in the FIG. 8 shown variant is in the FIG. 9 the annular gap 21 is disposed at a position further downstream of the main fluid inlet port 8. In both in the FIGS. 8 and 9 The compressed air used can be passed from a compressor either 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 perpendicular to the central axis 5 in the flow direction 26.
  • FIGS. 8 and 9 embodiments shown include the possibility of the downstream with respect to the flow direction 15 of the compressed air coming from the compressor nozzle part, which also depends on the fuel distribution, stuck from the rear wall 24 of the burner in the burner 401 and this through the front, combustion chamber side part to position, for example by spacers in the annulus. In extreme cases, the downstream nozzle part sits directly in the bottom of the flame tube.
  • the burner 1, 101, 201, 301, 401 according to the invention can be configured in all exemplary embodiments and variants without the outer housing part 27 or without the outer housing 27.
  • the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the main fluid inlet opening 8.
  • the burner 1, 101, 201, 301, 401 according to the invention can furthermore be designed without the rear wall 24.
  • annular gaps 21 By varying the axial positions of the annular gaps 21, an additional design parameter against thermoacoustic flame oscillations is obtained. It is also possible to provide the different jet nozzles 2 of a burner 401 with annular gaps 21 at different axial positions.

Landscapes

  • 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)
EP08000497A 2008-01-11 2008-01-11 Brûleur et procédé pour réduire des oscillations de flammes autoinduites Withdrawn EP2078898A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP08000497A EP2078898A1 (fr) 2008-01-11 2008-01-11 Brûleur et procédé pour réduire des oscillations de flammes autoinduites
PCT/EP2008/054969 WO2009086943A1 (fr) 2008-01-11 2008-04-24 Brûleurs et procédés pour réduire les oscillations de flammes auto-induites
EP08749689.9A EP2232147B1 (fr) 2008-01-11 2008-04-24 Brûleur et procédé pour réduire des oscillations de flammes autoinduites
US12/812,301 US20100323309A1 (en) 2008-01-11 2008-04-24 Burner and Method for Reducing Self-Induced Flame Oscillations

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08000497A EP2078898A1 (fr) 2008-01-11 2008-01-11 Brûleur et procédé pour réduire des oscillations de flammes autoinduites

Publications (1)

Publication Number Publication Date
EP2078898A1 true EP2078898A1 (fr) 2009-07-15

Family

ID=39420374

Family Applications (2)

Application Number Title Priority Date Filing Date
EP08000497A Withdrawn EP2078898A1 (fr) 2008-01-11 2008-01-11 Brûleur et procédé pour réduire des oscillations de flammes autoinduites
EP08749689.9A Active EP2232147B1 (fr) 2008-01-11 2008-04-24 Brûleur et procédé pour réduire des oscillations de flammes autoinduites

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08749689.9A Active EP2232147B1 (fr) 2008-01-11 2008-04-24 Brûleur et procédé pour réduire des oscillations de flammes autoinduites

Country Status (3)

Country Link
US (1) US20100323309A1 (fr)
EP (2) EP2078898A1 (fr)
WO (1) WO2009086943A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2216599A2 (fr) * 2009-02-04 2010-08-11 General Electric Company Buse de prémélange pour injection directe
EP2236932A1 (fr) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz
EP2282122A1 (fr) * 2009-08-03 2011-02-09 Siemens Aktiengesellschaft Stabilisation de la flamme d'un brûleur à prémélange
EP2587158A1 (fr) * 2011-10-31 2013-05-01 Siemens Aktiengesellschaft Chambre de combustion pour une turbine à gaz et agencement de brûleur
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9534781B2 (en) * 2012-05-10 2017-01-03 General Electric Company System and method having multi-tube fuel nozzle with differential flow
US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube
DE102015003920A1 (de) * 2014-09-25 2016-03-31 Dürr Systems GmbH Brennerkopf eines Brenners und Gasturbine mit einem solchen Brenner
JP7379265B2 (ja) * 2020-04-22 2023-11-14 三菱重工業株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2350227A1 (de) * 1973-10-05 1975-04-17 Handschack & Co Heinz Mischduese zur mischung brennbarer gase, insbesondere fuer geblaesebrenner
DE2856399A1 (de) * 1978-01-04 1979-07-12 Secr Defence Brit Brennstoff-luft-mischeinrichtung
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
EP1172610A1 (fr) * 2000-07-13 2002-01-16 Mitsubishi Heavy Industries, Ltd. Buse d'alimentation en combustible pour une chambre de combustion de turbine à prémélange
US20040231586A1 (en) * 2001-09-19 2004-11-25 Jacques Dugue Method and device for mixing two reactant gases
WO2006069861A1 (fr) * 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123285A (en) * 1964-03-03 Diffuser with boundary layer control
US1826776A (en) * 1928-07-20 1931-10-13 Charles O Gunther Liquid fuel burner and method of atomizing liquids
US2424654A (en) * 1944-06-03 1947-07-29 Lindberg Eng Co Fluid mixing device
US3070317A (en) * 1958-05-21 1962-12-25 Hunter Variable rate multiple fuel nozzle
US2974090A (en) * 1959-11-24 1961-03-07 Allied Chem High velocity combustion-jet motivater coke oven battery
NL154819B (nl) * 1967-05-10 1977-10-17 Shell Int Research Inrichting voor het aanbrengen van een laag vloeistof met lage viscositeit tussen een stroom vloeistof met hoge viscositeit en de wand van een pijpleiding.
US3705492A (en) * 1971-01-11 1972-12-12 Gen Motors Corp Regenerative gas turbine system
US3986347A (en) * 1973-12-06 1976-10-19 Phillips Petroleum Company Combustor process for low-level NOx and CO emissions
US4255927A (en) * 1978-06-29 1981-03-17 General Electric Company Combustion control system
US4474477A (en) * 1983-06-24 1984-10-02 Barrett, Haentjens & Co. Mixing apparatus
JPH0660640B2 (ja) * 1985-09-09 1994-08-10 清之 堀井 管路に螺旋流体流を生成させる装置
DE3545524C2 (de) * 1985-12-20 1996-02-29 Siemens Ag Mehrstufenbrennkammer für die Verbrennung von stickstoffhaltigem Gas mit verringerter NO¶x¶-Emission und Verfahren zu ihrem Betrieb
US5004484A (en) * 1988-08-31 1991-04-02 Barrett, Haentjens & Co. Air stripping of liquids using high intensity turbulent mixer
US5338113A (en) * 1990-09-06 1994-08-16 Transsonic Uberschall-Anlagen Gmbh Method and device for pressure jumps in two-phase mixtures
US5492404A (en) * 1991-08-01 1996-02-20 Smith; William H. Mixing apparatus
US5240409A (en) * 1992-04-10 1993-08-31 Institute Of Gas Technology Premixed fuel/air burners
US5893641A (en) * 1998-05-26 1999-04-13 Garcia; Paul Differential injector
DE19905572A1 (de) * 1999-02-11 2000-08-31 Bayer Ag Vorrichtung zum Mischen und Reagieren mehrphasiger gasförmiger und flüssiger Gemische und Verwendung dieser Vorrichtung
US6623154B1 (en) * 2000-04-12 2003-09-23 Premier Wastewater International, Inc. Differential injector
US6427435B1 (en) * 2000-05-20 2002-08-06 General Electric Company Retainer segment for swirler assembly
US6623267B1 (en) * 2002-12-31 2003-09-23 Tibbs M. Golladay, Jr. Industrial burner
JP4728176B2 (ja) * 2005-06-24 2011-07-20 株式会社日立製作所 バーナ、ガスタービン燃焼器及びバーナの冷却方法
EP1950494A1 (fr) * 2007-01-29 2008-07-30 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz
EP2006606A1 (fr) * 2007-06-21 2008-12-24 Siemens Aktiengesellschaft Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
EP2236932A1 (fr) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2350227A1 (de) * 1973-10-05 1975-04-17 Handschack & Co Heinz Mischduese zur mischung brennbarer gase, insbesondere fuer geblaesebrenner
DE2856399A1 (de) * 1978-01-04 1979-07-12 Secr Defence Brit Brennstoff-luft-mischeinrichtung
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
EP1172610A1 (fr) * 2000-07-13 2002-01-16 Mitsubishi Heavy Industries, Ltd. Buse d'alimentation en combustible pour une chambre de combustion de turbine à prémélange
US20040231586A1 (en) * 2001-09-19 2004-11-25 Jacques Dugue Method and device for mixing two reactant gases
WO2006069861A1 (fr) * 2004-12-23 2006-07-06 Alstom Technology Ltd Bruleur de premelange dote d'un parcours de melange

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2216599A2 (fr) * 2009-02-04 2010-08-11 General Electric Company Buse de prémélange pour injection directe
EP2216599A3 (fr) * 2009-02-04 2014-05-21 General Electric Company Buse de prémélange pour injection directe
EP2236932A1 (fr) * 2009-03-17 2010-10-06 Siemens Aktiengesellschaft Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz
WO2010106034A3 (fr) * 2009-03-17 2011-05-26 Siemens Aktiengesellschaft Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz
US9032736B2 (en) 2009-03-17 2015-05-19 Siemens Aktiengesellschaft Method for operating a burner and burner, in particular for a gas turbine
EP2282122A1 (fr) * 2009-08-03 2011-02-09 Siemens Aktiengesellschaft Stabilisation de la flamme d'un brûleur à prémélange
EP2587158A1 (fr) * 2011-10-31 2013-05-01 Siemens Aktiengesellschaft Chambre de combustion pour une turbine à gaz et agencement de brûleur
WO2013064383A1 (fr) * 2011-10-31 2013-05-10 Siemens Aktiengesellschaft Chambre de combustion pour turbine à gaz et système de brûleurs
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system

Also Published As

Publication number Publication date
WO2009086943A1 (fr) 2009-07-16
EP2232147B1 (fr) 2015-10-28
EP2232147A1 (fr) 2010-09-29
US20100323309A1 (en) 2010-12-23

Similar Documents

Publication Publication Date Title
EP2232147B1 (fr) Brûleur et procédé pour réduire des oscillations de flammes autoinduites
DE2143012C3 (de) Brenneranordnung bei einer Gasturbinen-Brennkammer
EP1802915B1 (fr) Bruleur pour turbine a gaz
DE112005002065B4 (de) Gasturbinen-Brennkammer
EP0769655B1 (fr) Buse de pulvérisation par air comprimé
DE3029095C2 (de) Doppelbrennstoffinjektor für ein Gasturbinentriebwerk
DE3889539T2 (de) Gasturbinenbrennkammer mit tangentialer brennstoffeinspritzung und zusätzlichen treibstrahlen.
DE69922347T2 (de) Brennstoff-luft mischvorrichtung für radialdom einer gasturbine
DE102006011326C5 (de) Rundbrenner
EP1336800A1 (fr) Procédé de réduction des oscillations induites par la combustion dans les dispositifs de combustion ainsi que brûleur à prémélange pour la mise en oeuvre du procédé
EP0433790A1 (fr) BrÀ»leur
EP2423597B1 (fr) Brûleur à prémélange pour une turbine à gaz
EP2470834B1 (fr) Brûleur notamment destiné à des turbines à gaz
WO2005078348A1 (fr) Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion
EP3087323A1 (fr) Brûleur, turbine à gaz munie dudit brûleur et injecteur de combustible
DE19905995A1 (de) Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer sowie Verfahren zum Betrieb einer solchen Brennstofflanze
DE102004041272B4 (de) Hybridbrennerlanze
DE102011052594A1 (de) Mehrzweckflansch für eine sekundäre Brennstoffdüse einer Gasturbinenbrennkammer
DE2641605C2 (de) Vorrichtung zur Zufuhr von Luft und Brennstoff
DE19654008A1 (de) Brenner
DE4424597B4 (de) Verbrennungsvorrichtung
DE112019006023T5 (de) Brennkammer für eine Gasturbine und Gasturbine mit einer solchen Brennkammer
DE2552864A1 (de) Verfahren und brenner zum verbrennen von fluessigen brennstoffen
DE19507088B4 (de) Vormischbrenner
DE19542373B4 (de) Brennerkopf für Gasbrenner

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

AKX Designation fees paid
REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20100116