EP2232147A1 - Brûleurs et procédés pour réduire les oscillations de flammes auto-induites - Google Patents

Brûleurs et procédés pour réduire les oscillations de flammes auto-induites

Info

Publication number
EP2232147A1
EP2232147A1 EP08749689A EP08749689A EP2232147A1 EP 2232147 A1 EP2232147 A1 EP 2232147A1 EP 08749689 A EP08749689 A EP 08749689A EP 08749689 A EP08749689 A EP 08749689A EP 2232147 A1 EP2232147 A1 EP 2232147A1
Authority
EP
European Patent Office
Prior art keywords
fluid
burner
mass flow
jet nozzle
fuel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08749689A
Other languages
German (de)
English (en)
Other versions
EP2232147B1 (fr
Inventor
Matthias Hase
David Barkowski
Werner Krebs
Berthold Köstlin
Martin Lenze
Martin Stapper
Jaap 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 EP08749689.9A priority Critical patent/EP2232147B1/fr
Publication of EP2232147A1 publication Critical patent/EP2232147A1/fr
Application granted granted Critical
Publication of EP2232147B1 publication Critical patent/EP2232147B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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.
  • 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 and claim 2.
  • the second task is by a Burner according to claim 11 and 12 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 is injected at at least one radial position of the jet nozzle with respect to the circumference of the jet nozzle. This achieves, as already described above, also the smearing of the delay time between injection and combustion.
  • 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. Since the fuel mass flows for natural gas are significantly lower than the air mass flows, no significant increase in the pressure loss is to be expected even in the case of injection perpendicular to the flow direction of the air. Furthermore, 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 include air.
  • the third fluid mass flow may also be air,
  • 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, 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 fluid secondary inlet opening, which is connected to a fluid supply line, is arranged on at least one axial secondary position of the jet nozzle with respect to the main fluid inlet opening.
  • the Fluidzulei- connected to the Fluidhaupteinlassö réelle can be configured for example as fuel supply, as an air supply line or 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 fluid inlet 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 opening can be connected to an air feed line and a part of the fluid sub-inlet openings can be connected to a fuel feed 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 central main 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 90 ° to the central axis of the main fluid inlet port and / or the central axis of the jet nozzle and the central axes of a second portion of the fluid sub-inlet ports may be at 45 ° to the central axis of the main fluid inlet port and / or having 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 central axes of the fluid sub-inlet openings may have an angle between 0 ° and 90 ° to a radial direction with respect to the central axis of the fluid main 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 can 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 fluid main 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 different 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.
  • the burner according to the invention is preferably used in a gas turbine.
  • Fig. 1 shows schematically a section through a jet burner transversely to its longitudinal direction.
  • Fig. 2 shows schematically a section through another jet burner transversely to its longitudinal direction.
  • Fig. 3 shows schematically a section through a part of a jet burner in the longitudinal direction.
  • Fig. 4 shows schematically a section through a part of another jet burner in the longitudinal direction.
  • Fig. 5 shows schematically a section through a part of an alternative jet burner in the longitudinal direction.
  • Fig. 6 shows schematically a longitudinal section through another jet burner.
  • Fig. 7 shows schematically a section through a part of a jet burner in the longitudinal direction.
  • Fig. 8 shows schematically a jet burner in the longitudinal direction, which has an annular gap.
  • FIG. 9 schematically shows an alternative arrangement of the annular gap of the jet burner shown in FIG.
  • FIG. 10 shows the cross section of a steel burner and of the annular distributor with a plurality of radial secondary fluid inlet openings.
  • 1 shows schematically 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, the section being perpendicular to the middle axis of the burner 101 runs.
  • 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 show only 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 part of a jet burner 1 according to the invention in the longitudinal direction, that is to say along the central axis 4 of the burner 1.
  • the burner 1 has at least one jet nozzle 2 arranged in a housing 6.
  • the central axis of the jet nozzle 2 is through the
  • 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. Coming from the compressor compressed air is passed through an annular gap 22 to the main fluid inlet 8 and / or radially via an air inlet opening 23 in relation directed to the central axis 5 of the jet nozzle 2 to the fluid main 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 direction of flow 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 be designed 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 according to the invention can also 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 inlet inlet openings 14, through which fuel can be injected into the air mass flow flowing through the jet nozzle 2.
  • the fluid sub-inlet openings 14 may be designed as a slot or oval nozzle. This is particularly advantageous for synthesis gas injection because it allows the air Flow is offered a smaller inflow area. This also results in a lower tendency for recirculation behind the fuel injection.
  • 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 sub-inlet openings 14 are arranged at three different axial positions, wherein two fluid sub-inlet openings 14 are arranged opposite one another at each axial position.
  • 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, which represents a further development of the burner 1 shown in FIG.
  • 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 shown in FIG. 3, 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.
  • Compressed air 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 in the jet nozzle 2.
  • This air mass flow flows through the jet nozzle 2 in the direction indicated by an arrow 10 direction.
  • Another part of the compressed air coming from the compressor is injected from the annular gap 22 through the fluid sub-inlet openings 25 in the direction of the flow direction indicated by the arrows 16 in the jet nozzle 2.
  • the fluid secondary inlet openings 25 can be arranged at different axial positions of the jet nozzle 2. In FIG. 4, the fluid sub-inlet openings 25, through which compressed air is injected into the jet nozzle 2, are arranged so that in each case downstream of a fluid sub-inlet opening 14, through the fuel 12 into the flow direction 10 downstream
  • a fluid secondary inlet opening 25 is arranged. Any other arrangements are of course possible. However, it is advantageous if the fluid sub-inlet openings 25 are arranged offset radially along the circumference of the jet nozzle 2. In this way, the flow is not always weakened at the same circumferential position.
  • the fluid sub-inlet openings 14 and 25 are arranged such that the fuel 12 is injected through the fluid sub-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 into the jet nozzle 2 through the fluid sub-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 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, a significant increase in the pressure loss is not to be expected even in the case of 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 feed 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 peripheral positions of the jet pipe 2 can be injected.
  • a second exemplary embodiment will be described in more detail below with reference to FIGS. 5 to 7. Elements corresponding to elements already described in the first embodiment are given the same reference numerals and will not be described again in detail.
  • FIGS. 5 to 7 each show sections through a part of a burner 301 along the center axis 4 of the burner 301.
  • the burner 301 has at least one, but advantageously a plurality of jet nozzles 2 arranged essentially annularly around the central axis 4.
  • a fuel nozzle 19 is arranged in FIGS. 5 to 7.
  • 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 direction of flow of the fuel 12 injected through the fuel nozzle 19 is indicated by arrows 17e.
  • 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 into 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 burner 301 shown in FIG. 5.
  • the fluid secondary inlet openings 25 are shown as such. arranged that the compressed air injected by the secondary fluid inlet openings 25 in the jet nozzle 2 at an angle of about 45 ° to the central axis 5 of the jet pipe 2 in this is injected.
  • 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-crossflow injection ensures 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 show schematically different 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 With regard to possible arrangements of the jet nozzles 2, 3, reference is made to FIGS. 1 and 2 and the statements 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 help of which at different radial positions and different circumferential positions of the main fluid inlet opening 8 fuel 12 into the
  • Blasting nozzle 2 can be injected.
  • 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 direction of flow of 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.
  • the annular gap 21 is arranged at a position further away from the fluid main inlet opening 8.
  • the compressed air used can be directed by 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 lowered. be injected to the central axis 5 in the flow direction 26.
  • FIGS. 8 and 9 include the possibility of inserting into the burner 401 from the rear wall 24 of the burner, downstream of the jet section downstream of the compressed air coming from the compressor, to which the fuel distribution also depends To position this by the front, brennhuntsei- term part, for example by spacers in the annulus. In extreme cases, the downstream nozzle part sits directly in the bottom of the flame tube.
  • FIG. 10 shows a cross-section of a steel burner 1 and of the annular distributor 7 with a plurality of radial fluid inlet openings 14.
  • the annular distributor 7 comprises a complete ring of jet nozzles 2. From the annular distributor 7 there are fluid secondary inlet openings 14 which guide the jet nozzles 2 at different circumferential positions to meet. In this case, long fluid secondary inlet openings 14 can be made. Also, secondary fluid inlet ports 14 may be at an angle to the jet nozzle 2.
  • the jet nozzles 2 can be arranged arbitrarily. It is also conceivable that only an external ring distributor 7 is present with fuel and the jet nozzles are arbitrarily arranged in the interior (central jet burner 1).
  • 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.

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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)

Abstract

L'invention concerne un procédé pour réduire les oscillations de flammes auto-induites selon lequel on injecte un deuxième flux massique de fluide dans un premier flux massique de fluide qui s'écoule à travers une buse en acier (2, 3) depuis une ouverture d'admission de fluide (8) jusqu'à une ouverture d'évacuation de fluide (9), cette injection s'effectuant en au moins une position axiale de la buse en acier (2, 3) située en aval par rapport à l'ouverture d'admission de fluide (8) ; sachant qu'un des deux flux massiques de fluide comprend de l'air (11) et que l'autre flux massique de fluide comprend un combustible (12). L'invention concerne en outre un procédé pour réduire les oscillations de flammes auto-induites selon lequel on injecte un deuxième flux massique de fluide dans un premier flux massique de fluide qui s'écoule à travers une buse en acier (2, 3) depuis une ouverture d'admission de fluide (8) jusqu'à une ouverture d'évacuation de fluide (9), cette injection s'effectuant en au moins une position radiale de la buse en acier (2, 3) relativement à la circonférence de la buse en acier (2) ; sachant qu'un des deux flux massiques de fluide comprend de l'air (11) et que l'autre flux massique de fluide comprend un combustible (12). L'invention concerne en outre des brûleurs garantissant la mise en oevre des procédés.
EP08749689.9A 2008-01-11 2008-04-24 Brûleur et procédé pour réduire des oscillations de flammes autoinduites Active EP2232147B1 (fr)

Priority Applications (1)

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

Applications Claiming Priority (3)

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
EP08749689.9A EP2232147B1 (fr) 2008-01-11 2008-04-24 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

Publications (2)

Publication Number Publication Date
EP2232147A1 true EP2232147A1 (fr) 2010-09-29
EP2232147B1 EP2232147B1 (fr) 2015-10-28

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Family Applications (2)

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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

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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

Country Status (3)

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

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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
US9534781B2 (en) * 2012-05-10 2017-01-03 General Electric Company System and method having multi-tube fuel nozzle with differential flow
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube
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EP2232147B1 (fr) 2015-10-28
US20100323309A1 (en) 2010-12-23
EP2078898A1 (fr) 2009-07-15
WO2009086943A1 (fr) 2009-07-16

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