EP2409087A2 - Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz - Google Patents

Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz

Info

Publication number
EP2409087A2
EP2409087A2 EP10711184A EP10711184A EP2409087A2 EP 2409087 A2 EP2409087 A2 EP 2409087A2 EP 10711184 A EP10711184 A EP 10711184A EP 10711184 A EP10711184 A EP 10711184A EP 2409087 A2 EP2409087 A2 EP 2409087A2
Authority
EP
European Patent Office
Prior art keywords
burner
jet nozzle
central axis
axis
air
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP10711184A
Other languages
German (de)
English (en)
Inventor
Matthias Hase
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 EP10711184A priority Critical patent/EP2409087A2/fr
Publication of EP2409087A2 publication Critical patent/EP2409087A2/fr
Withdrawn legal-status Critical Current

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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/34—Feeding into different combustion zones

Definitions

  • the present invention relates to methods of operating a burner, a burner and a gas turbine.
  • the jet flames are stabilized by mixing in hot recirculating gases.
  • the fuel distribution in the premix passage is an important parameter. Since the fuel distribution in the premix passage depends not only on the fuel distributor used, but also on the air flow to the jet nozzle, which may also be load-dependent, additional measures must be taken to reliably set the desired fuel profile.
  • a first object of the present invention to provide an advantageous method for operating a burner.
  • a second object is to provide an advantageous burner.
  • a third object of the present invention is to provide an advantageous gas turbine.
  • the first object is achieved by a method according to claim 1, which is the second object by a burner according to claim 8 and the third object by a gas turbine according to claim 16.
  • the dependent claims contain further advantageous embodiments of the invention.
  • the method according to the invention for operating a burner relates to a burner which comprises a burner axis and at least one jet nozzle. Typically, however, a number will be arranged around the torch axis
  • Jet nozzles may be present.
  • the at least one jet nozzle comprises a central axis, a steel nozzle outlet and a wall which, starting from the central axis, faces the burner axis in the radial direction.
  • a fluid mass flow comprising a fuel flows through the at least one jet nozzle towards the jet nozzle outlet.
  • the method according to the invention is characterized in that an air or inert gas film is formed at the jet nozzle outlet between the fluid mass flow comprising the fuel and the wall facing the burner axis by passing air or inert gas along the wall
  • Burner axis facing wall is injected into the at least one jet nozzle.
  • At least the region of the steel nozzle wall which is located between the central axis of the jet nozzle and the burner axis is referred to as the burner axis facing wall.
  • the delayed ignition allows for a longer mixing length, which leads to a lower nitrogen oxide value.
  • the delayed allows Ignition a distributed heat release, which is favorable from a thermoacoustic point of view.
  • the fuel profile is changed such that, for example, the part of the professional facing the burner axis contains no or only very little fuel.
  • the aim should be to use as little air or inert gas as possible to adjust the profile.
  • the at least one jet nozzle may have a circumferential direction running around the central axis.
  • the air or the inert gas can be injected into the jet nozzle in the circumferential direction in an angular range of at least ⁇ 15 ° with respect to a radial connecting line between the burner axis and the central axis. In this way, it is achieved that the part of the fuel profile facing the burner axis contains no or only very little fuel.
  • the air or the inert gas in the circumferential direction in an angular range of at most ⁇ 135 °, in particular in an angular range of at most between ⁇ 90 ° and more particularly of at most ⁇ 45 °, relative to a radial
  • Connecting line between the burner axis and the central axis are injected into the jet nozzle.
  • air or inert gas can also be injected in the presence of adjacent jet nozzles on the sides facing the adjacent jets. This air or this inert gas prevents coalescence of the jet flames and thus enables an advantageous heat release zone, as it is desired for jet flame based burner systems.
  • the air or Inertgaseindüsung on the nachbar bar rays facing sides can be performed on two sides or only on one side.
  • the air can be injected in the circumferential direction about the central axis in an asymmetric angle range of at most -135 ° to + 45 ° or at most -45 ° to + 135 °, based on a radial connecting line between the burner axis and the central axis, in the jet nozzle , As a result, in each case a one-sided air or inert gas introduction is achieved on the sides facing the neighboring beams.
  • the at least one jet nozzle can comprise a central axis.
  • the air or the inert gas can advantageously be injected at an angle between 0 ° and 60 ° to the central axis in the jet nozzle.
  • the burner according to the invention comprises a burner axis and at least one jet nozzle. However, it may also comprise a number of nozzles arranged around the burner axis.
  • the at least one jet nozzle comprises a central axis and a wall region extending therearound in an angular range of at most -135 ° to + 135 ° and at least -15 ° to + 15 ° relative to a radial connecting line between the burner axis and the central axis (hereinafter also referred to as the burner axis facing wall).
  • the burner according to the invention is characterized in that only the wall region extending around the central axis in the angular range of at most -135 ° to + 135 ° and at least -15 ° to + 15 ° at least one flow channel leading into the jet nozzle to the air or inert gas supply.
  • the burner according to the invention is suitable for carrying out the method according to the invention described above.
  • the flow channel may be connected to an air reservoir or an inert gas source.
  • the wall region comprising the at least one flow channel which opens into the jet nozzle can in particular also be around the central axis in the angular range of at most ⁇ 90, in particular at most ⁇ 45 or at most -45 ° to + 135 ° or at most -135 ° to +45 ° extend.
  • one-sided air or Inertgaseindüsung reached on the neighboring beams facing sides.
  • the flow channel may advantageously be configured as a bore or partial annular gap.
  • the bore may comprise a central axis which encloses an angle between 0 ° and 60 °, in particular between 20 ° and 40 °, with the central axis of the jet nozzle.
  • the injected air or the injected inert gas which or which is entrained by the main flow in the jet nozzle, then forms a particularly advantageous film.
  • the bore may, for example, have a round, an elliptical or any other cross-section.
  • the bore may have a profiled exit cross-section, which corresponds to that of film cooling openings. Similar to the film cooling air is the requirement for the injected air or the injected inert gas that they or it mixes as little as possible with the core flow.
  • the partial annular gap can form an imaginary partial cone jacket, which can form an angle between 0 ° and 60 °, in particular between 20 ° and 40 °, with the central axis of the jet nozzle.
  • the partial annular gap may comprise a plurality of partial annular gap segments. This causes a better controllability of the gap size.
  • the partial annular gap can be designed so that it closes or opens depending on the operating conditions. It may, for example, be designed so that it closes or opens by thermal expansion of a component, in particular by thermal expansion of the adjacent components.
  • the burner may include a pilot fuel nozzle and the sub-annulus may be configured to close or open the sub-annulus depending on the temperature of the pilot fuel nozzle.
  • a hot pilot fuel nozzle in part-load cause the gap to close while the gap reaches a maximum size near the base load with very little pilot gas, ie, a pilot fuel nozzle cooler than the part-load range.
  • the burner according to the invention allows the use of air films or inert gas films to model the mixing profile for a jet burner, as it is optimal for operation.
  • the gas turbine according to the invention comprised at least one burner according to the invention described above. Their properties and advantages result from those of the burner according to the invention already described. Overall, the present invention allows by the use of air films or
  • Inert gas films to model the mixing profile for a jet burner, as it is optimal for the operation of the gas turbine.
  • FIG. 1 shows schematically a gas turbine.
  • FIG. 2 schematically shows a section through a jet burner transversely to its longitudinal direction.
  • FIG. 3 schematically shows a section through another jet burner transversely to its longitudinal direction.
  • FIG. 4 shows schematically a section through a part of a jet burner in the longitudinal direction.
  • 5 schematically shows an unfavorable fuel profile at the jet nozzle outlet.
  • 6 schematically shows an advantageous fuel profile at the jet nozzle outlet.
  • FIG. 7 shows schematically a further advantageous fuel profile at the jet nozzle outlet.
  • FIG. 8 schematically shows a further advantageous fuel profile at the jet nozzle outlet.
  • FIG. 9 shows schematically a further advantageous fuel profile at the jet nozzle outlet.
  • 10 shows schematically another advantageous fuel profile at the jet nozzle outlet.
  • FIG. 11 schematically shows a further advantageous fuel profile at the jet nozzle outlet.
  • FIG. 12 schematically shows a section through part of a jet nozzle in the longitudinal direction.
  • FIG. 13 schematically shows a section through the jet nozzle shown in FIG. 12 along XIII-XIII.
  • FIGS. 1 to 13 show schematically a gas turbine.
  • a gas turbine has inside a rotor rotatably mounted about a rotation axis with a shaft 107, which is also referred to as a turbine runner.
  • a turbine runner Along the rotor follow one another an intake housing 109, a compressor 101, a combustion system 151 with a number of jet burners 1, a turbine 105 and the exhaust housing 190.
  • the combustion system 151 communicates with an annular hot gas passage.
  • turbine stages connected in series form the turbine 105.
  • Each turbine stage is formed by blade rings.
  • a guide vane ring 117 is followed by a rotor blade ring formed by rotor blades 115.
  • the guide vanes 117 are fastened to an inner housing of a stator, whereas the moving blades 115 of a running blade ring row are attached to the rotor, for example by means of a turbine disk.
  • Coupled to the rotor is a generator or a work machine.
  • the combustion system 151 comprises at least one burner according to the invention and may in principle comprise an annular combustion chamber or a plurality of tube combustion chambers.
  • the burner 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 substantially circular cross-section. Within the housing 6, a certain number of jet nozzles 2 are arranged substantially annularly. Each jet nozzle 2 has a circular cross section.
  • the burner 1 may comprise a pilot burner.
  • FIG. 3 schematically shows a section through an alternative jet burner Ia, wherein the section is perpendicular to the central axis of the burner Ia.
  • the burner 1a 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.
  • Figures 2 and 3 show only examples of the arrangement of jet nozzles 2, 3 within a jet burner 1, Ia. Of course, alternative arrangements, as well as the use of a different number of jet nozzles 2, 3 are possible
  • FIG. 4 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 is indicated by the reference numeral 5.
  • the jet nozzle 2 comprises a jet nozzle inlet 8 and a jet nozzle outlet 9.
  • the jet nozzle outlet 9 is adjoined by the combustion chamber 18.
  • the jet nozzle 2 is arranged in the housing 6 such that the jet nozzle inlet 8 faces the rear wall 24 of the burner 1.
  • the housing 6 further comprises a radially outer housing part 127 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 jet nozzle inlet 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 jet nozzle inlet 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 center axis 5 of the jet nozzle 2.
  • the in the direction of Arrow 15 flowing air is then deflected at the rear wall 24 of the burner 1 by 180 ° and then flows through the jet nozzle inlet 8 in the jet nozzle 2.
  • the flow direction of the air within the jet nozzle 2 is marked by an arrow 10.
  • the jet nozzle inlet 8 there is also a fuel nozzle 19, through which a fuel 12 is injected into the jet nozzle 2.
  • the direction of flow of the fuel is indicated by the reference numeral 17.
  • the fuel nozzle 19 may have at its circumference fuel outlet openings 119, via which fuel can be introduced in the direction of the arrow 117 shown in dashed lines in FIG.
  • the jet nozzle 2 further comprises a wall 7 facing the burner axis 4.
  • the wall 7 facing the burner axis at least the region of the steel nozzle wall which is located between the center axis 5 of the jet nozzle 1 and the burner axis 4 is designated.
  • the burner axis facing the wall 7 may in particular around the central axis 5 around in an angular range of at most -135 ° to + 135 ° and at least - 15 ° to + 15 °, based on the radial connecting line 26 between the burner axis 4 and the central axis. 5 , extending.
  • an air supply line 13 communicating with the compressor is located in the interior of the housing 6.
  • air inlet openings 14 lead into the interior of the jet nozzle 2.
  • the air inlet openings 14 are in the present embodiment as bores designed with a circular cross-section. They each include a central axis 27, which encloses an angle ⁇ with the central axis 5 of the jet nozzle 2, which may be, for example, between 0 ° and 60 °, in particular between 20 ° and 40 °.
  • an inert gas can also be supplied via the supply line.
  • the line 13 is not in communication with the compressor, but with an inert gas reservoir or an inert gas source.
  • Air is injected into the jet nozzle 2 through the air feed line 13 and the air inlet openings 14 in such a way that it is entrained by the main stream indicated by the arrow 10 and therefore an air film is formed along the wall 7 facing the burner axis 4.
  • the direction of flow of the injected air is designated by the reference numeral 20.
  • the burner 1 according to the invention can in principle also be designed without the outer housing part 127 or without the outer housing 127. In this case, the compressed air can flow directly into the "plenum", ie the area between the rear wall 24 and the jet nozzle inlet 8.
  • the burner 1 according to the invention can furthermore be designed without the rear wall 24.
  • FIG. 5 shows schematically a fuel profile, as it is generated without the inventive air film production on the burner axis facing the wall at the jet nozzle outlet.
  • the radial connecting line between the central axis 5 of the jet nozzle 2 and the central axis of the burner 4 is indicated by the reference numeral 26 for orientation.
  • the burner profile shown schematically in FIG. 5 is characterized in that a fuel-enriched region 25 is formed in the outer region of the jet nozzle 2, that is to say on the jet nozzle wall. Two further enriched with fuel areas 25 are located near the central axis of the jet nozzle 5. Furthermore, located near the central axis of the jet nozzle 5 is a fuel-free or fuel-poor area 21, and a region 22 in which the desired air-fuel Mixture 22 prevails.
  • the fuel profile shown schematically in FIG. 5 is unfavorable, since at the wall facing the burner axis 7 combustion Fabric 25 prevails. This fuel enriched area 25 is caused by air flow to the jet nozzle 2.
  • the fuel profile shown schematically in FIG. 6 can be produced.
  • This profile is characterized in that a fuel-free region 21 prevails on the wall 7 facing the burner axis.
  • the area 21 is ideally fuel-free, but can also be low in fuel.
  • the fuel profile shown in FIG. 6 is advantageous because the air film 21 on the wall 7 facing the burner axis prevents an early ignition of the jet flames and makes possible a distributed heat release zone.
  • FIGS. 7 to 12 show schematically different fuel profiles at the jet nozzle exit 9, as can be produced with the aid of the method according to the invention, in particular using a burner according to the invention.
  • the fuel profile shown in FIG 7 is characterized in that a fuel-free or fuel-poor area along the burner axis facing wall 7 at an angle about the central axis 5 of the jet nozzle 2, starting from a radial connecting line 26 between the central axis 5 of the jet nozzle 2 and the burner axis 4 from - ⁇ to + ⁇ forms.
  • the angle ⁇ is approximately 45 ° in FIG.
  • the fuel-free or fuel-poor region 21 is generated by injecting air at an angle of - ⁇ to + ⁇ about the central axis 5 of the jet nozzle 2, starting from the connecting line 26.
  • the angle ⁇ is 90 °, in FIG 9 it is 15 ° and in FIG 10 it is 135 °.
  • the fuel profile shown in FIG. 10, in contrast to the profiles shown in FIG. 7 and FIG. 9, is distinguished by the fact that, in addition to a shielding of the fuel, an air film is directed in the direction of the burner axis. se 4 a shield to the respective adjacent jet nozzles is achieved and thereby coalescence of the flames is prevented.
  • the fuel profile shown in FIG. 11 is distinguished by a fuel-free or fuel-lean region 21, which extends in an asymmetrical angular range from -135 ° to + 45 ° about the center axis 5 of the jet nozzle, starting from the connection line 26.
  • a one-sided shielding to an adjacent jet nozzle and in the direction of the central axis 4 of the burner is achieved. This configuration is advantageous in order to keep the amount of inserted air or inert gas used as small as possible.
  • FIG. 12 schematically shows a section through part of a jet nozzle in the longitudinal direction.
  • FIG. 13 shows a section through the jet nozzle shown in FIG. 12 transversely to the central axis 5.
  • the jet nozzle 2 shown in FIGS. 12 and 13 comprises a partial annular gap 28. Air is injected into the interior of the jet nozzle 2 along the flow direction 20 through the partial annular gap 28. As a result of the flow 22 of the jet nozzle 2 flowing through the air-fuel mixture forms along the burner axis facing wall 7, an air film.
  • the partial annular gap 28 forms an imaginary partial cone sheath, which is characterized by the reference numeral 29 and with the central axis 5 of the jet nozzle 2 an angle ß between 0 ° and 60 °, in particular between 20 ° and 40 °, includes.
  • FIG. 13 schematically shows a section along XIII-XIII of the jet nozzle shown in FIG.
  • the partial annular gap 28 shown in FIG. 13 comprises a plurality of partial annular gap segments, in the present embodiment three partial annular gap segments. Segments 30.
  • the configuration of the partial annular gap 28 from a plurality of partial annular gap segments 30 allows better controllability of the gap size, in particular a controllability and adjustability of the angular range ⁇ for the air film to be produced.
  • the embodiment with the aid of partial ring gap segments 30 results in increased stability of the jet nozzle 2 in the region of the partial annular gap 28.
  • the partial annular gap 28 may be designed such that it closes or opens depending on the operating conditions, for example as a result of thermal expansion of a component.
  • the burner 1 may comprise at least one pilot fuel nozzle and the partial annular gap 28 may be configured to be in thermal contact with the pilot fuel nozzle so as to close or open depending on the temperature of the pilot fuel nozzle.
  • a hot pilot fuel nozzle may cause part-ring gap 28 to close during part-load operation, while partial-ring gap 28 will reach a maximum size with very little pilot gas near the base load, ie, a cooler pilot fuel nozzle.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

L'invention concerne un procédé pour faire fonctionner un brûleur (1). Le brûleur selon l'invention présente un axe de brûleur (4) et au moins une buse de pulvérisation (2), au moins une buse de pulvérisation (2) présentant un axe médian (5), une sortie de buse (9), une paroi (7) orientée dans la direction radiale de l'axe du brûleur (4) et qui s'étend à partir de l'axe médian (5), et un écoulement massique de fluide, contenant un combustible, qui traverse au moins une buse de pulvérisation (2) jusqu'à sa sortie (9). A la sortie de buse (9), il se forme un film d'air (20) entre l'écoulement massique de fluide contenant un combustible et la paroi (7) orientée vers l'axe du brûleur (4), du fait que de l'air est injecté dans la buse de pulvérisation (2), le long de la paroi (7) orientée vers l'axe du brûleur (4).
EP10711184A 2009-03-17 2010-03-16 Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz Withdrawn EP2409087A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10711184A EP2409087A2 (fr) 2009-03-17 2010-03-16 Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09155341A EP2236932A1 (fr) 2009-03-17 2009-03-17 Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz
PCT/EP2010/053325 WO2010106034A2 (fr) 2009-03-17 2010-03-16 Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz
EP10711184A EP2409087A2 (fr) 2009-03-17 2010-03-16 Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2409087A2 true EP2409087A2 (fr) 2012-01-25

Family

ID=41021051

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09155341A Withdrawn EP2236932A1 (fr) 2009-03-17 2009-03-17 Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz
EP10711184A Withdrawn EP2409087A2 (fr) 2009-03-17 2010-03-16 Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09155341A Withdrawn EP2236932A1 (fr) 2009-03-17 2009-03-17 Procédé de fonctionnement d'un brûleur et brûleur, notamment pour une turbine à gaz

Country Status (6)

Country Link
US (1) US9032736B2 (fr)
EP (2) EP2236932A1 (fr)
JP (1) JP5460850B2 (fr)
CN (1) CN102356279B (fr)
RU (1) RU2523519C2 (fr)
WO (1) WO2010106034A2 (fr)

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EP2587158A1 (fr) * 2011-10-31 2013-05-01 Siemens Aktiengesellschaft Chambre de combustion pour une turbine à gaz et agencement de brûleur
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JP2022049136A (ja) * 2020-09-16 2022-03-29 三菱重工業株式会社 燃料ノズルおよびガスタービン燃焼器

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Also Published As

Publication number Publication date
EP2236932A1 (fr) 2010-10-06
CN102356279A (zh) 2012-02-15
WO2010106034A2 (fr) 2010-09-23
WO2010106034A3 (fr) 2011-05-26
JP5460850B2 (ja) 2014-04-02
RU2523519C2 (ru) 2014-07-20
JP2012520984A (ja) 2012-09-10
US9032736B2 (en) 2015-05-19
CN102356279B (zh) 2014-03-12
US20120000203A1 (en) 2012-01-05
RU2011141846A (ru) 2013-04-27

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