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EP2161502A1 - Brûleur à prémélange pour un combustible pauvre et riche - Google Patents

Brûleur à prémélange pour un combustible pauvre et riche Download PDF

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Publication number
EP2161502A1
EP2161502A1 EP08015728A EP08015728A EP2161502A1 EP 2161502 A1 EP2161502 A1 EP 2161502A1 EP 08015728 A EP08015728 A EP 08015728A EP 08015728 A EP08015728 A EP 08015728A EP 2161502 A1 EP2161502 A1 EP 2161502A1
Authority
EP
European Patent Office
Prior art keywords
premix burner
inlet
distributor
fuel
opening
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Withdrawn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
EP08015728A
Other languages
German (de)
English (en)
Inventor
Matthias Dr. Hase
Berthold Köstlin
Martin Lenze
Udo Schmitz
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP08015728A priority Critical patent/EP2161502A1/fr
Publication of EP2161502A1 publication Critical patent/EP2161502A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a premix burner for combustion of a low calorific fuel, in particular a synthesis gas and a high calorie fuel.
  • burners and operating methods for burners have been developed in recent years, which have particularly low emissions of nitrogen oxides (NO X ). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil, natural gas and / or low calorific fuel, which is also referred to as syngas, either or even in combination operable to to increase security of supply and flexibility of operation.
  • fuels such as oil, natural gas and / or low calorific fuel, which is also referred to as syngas, either or even in combination operable to to increase security of supply and flexibility of operation.
  • Synthesis gas burners are characterized by the fact that synthesis gases are used as fuel in them. Compared with the traditional gas turbine fuels natural gas and petroleum, which consist essentially of hydrocarbon compounds, the combustible constituents of synthesis gas are essentially carbon monoxide and hydrogen.
  • the burner in the gas turbine associated combustion chamber must then be designed as a two- or multi-fuel burner, both with the synthesis gas and with the second fuel, such as natural gas or fuel oil can be applied as needed.
  • the respective fuel is supplied via a fuel passage in the burner of the combustion zone.
  • the calorific value of the synthesis gas is about five to ten times smaller compared to the calorific value of natural gas.
  • Main constituent in addition to CO and H 2 are inert components such as nitrogen and / or water vapor and possibly also carbon dioxide. Due to the low calorific value consequently high volume flows of fuel, that is, for example, larger Eindüsequeritese must be supplied through the burner of the combustion chamber. As a result, one or more separate fuel passages must be made available for the combustion of low calorific fuels, such as synthesis gas.
  • diffusion burners designed as synthesis gas burners can not meet the increasing demands on the exhaust gas emissions of gas turbines, even in synthesis gas operation.
  • One requirement, for example, is to get along with as little dilution as possible for the fuel in the synthesis gas operation.
  • premix combustion is becoming increasingly important also in the combustion of low calorific gases.
  • Premix burners typically include a premix zone in which air and fuel are mixed before passing the mixture into a combustion chamber.
  • the introduced into the combustion chamber air mass flow is typically twisted by means of a swirl device.
  • this twisted air mass flow of high-calorie fuel is injected via one or more juxtaposed or successively arranged circular rows of holes in the twisting device.
  • premix burners In connection with the operation of premix burners, it is particularly important to keep the nitrogen oxide emissions low and to avoid a flashback. In the case of premix combustion can the formation of follow-up areas or H disclosegurström whichen within the burner, for example, reduced by suitable shaping of Eindüsbohrungen, but not avoided in principle.
  • Such as premix burner designed synthesis gas burners are for example in the EP 1 645 807 A1 and in the EP 1 723 369 B1 disclosed.
  • inert mass streams as dilution medium into the air mass flow or the fuel mass flow.
  • inert mass streams as dilution medium into the air mass flow or the fuel mass flow.
  • lean premix technology enables the reduction in the amount of diluent used, increasing plant economics. Due to the then missing inertization but then there is a highly reactive fuel.
  • the object of the present invention is to provide an advantageous premix burner which enables safe operation of high-calorie and low-calorie fuel.
  • SG low calorific
  • NG high calorific fuel
  • the swirl device is referred to below as a swirl blade. But it can also be understood as other spin-producing means.
  • a targeted radial fuel distribution into an axial or diagonal flow channel becomes possible with the premix burner of the invention. It is thus possible to keep the fuel away from the channel walls of the premix channel, which can serve as potential ignition ranges. This avoids the risk of flashback in boundary layers. Additional air-side pressure loss through separation areas behind the fuel jets is largely prevented in the premix burner according to the invention.
  • a distributor opening in particular distributor bore, is present.
  • the low-calorie fuel in particular the synthesis gas, flows to the inlet openings and is thus injected into the premixing channel.
  • the distribution opening has a substantially trapezoidal base.
  • the base further has rounded portions on both sides.
  • the base may have semicircles, in particular etched semicircles.
  • the fillets are preferably radii or semicircles.
  • the trapezoidal base surface is particularly advantageous, since the approximately parallelism of the wall of the distributor opening hereinafter referred to as distributor hole, and the surface of the swirl device so the swirl blade, resulting in approximately equal opening lengths for the inlet openings.
  • the resistance coefficient of the openings is approximate same, and this results in a very uniform fuel distribution. This is especially the case when all inlet opening diameters have the same diameter.
  • the distributor opening in particular therefore the distributor bore, has a slot shape or an oval shape. This is particularly advantageous in order to achieve the largest possible area for the distributor bore, without falling below the minimum required wall thickness.
  • the at least one inlet opening is a bore. This is manufacturing technology particularly easy to implement.
  • At least two inlet openings are present, wherein the at least two inlet openings form an axial (that is to say in blade height) inlet opening row (RW1).
  • at least two rows of inlet openings (RW1, RW2) are present, which are arranged offset to one another.
  • the inlet opening rows can also be arranged in parallel. This may depend on the configuration of the swirl device, in particular swirl blade.
  • multiple rows of intake ports (RW1, ..., RWn) may be present. For an odd number of rows, about three rows (RW1, RW2, RW3), e.g.
  • the second row RW2 to the first row RW1 and the third row RW3 be offset, while the first row RW1 and the third row RW3 are arranged in parallel or in a row.
  • all three rows RW1, RW2, RW3 can also be arranged offset from one another / parallel to one another.
  • the distance between the individual rows should preferably comprise at least one bore diameter.
  • the inlet opening rows can each have a different number of inlet openings.
  • the at least two rows of inlet openings have the same inlet opening diameters ( ⁇ RW1, ⁇ RW2) of the inlet ports. If the inlet opening lengths of the inlet openings are also approximately the same, this results in an approximately equal coefficient of resistance of the inlet openings, and thus also a very uniform fuel distribution.
  • the at least two rows of inlet openings are preferably designed with different inlet opening diameters ( ⁇ RW1, ⁇ RW2) of the inlet openings.
  • Fuel jets with a larger diameter have a greater penetration depth. This can preferably be provided for a uniform distribution on the circumference, since thus a different penetration depth of the fuel jets is achieved.
  • the ratio of the area of the inlet openings to the area of the distributor opening, in particular the distributor bore is 1: 4. This is particularly advantageous because of the large mass flows required for the low calorific fuel, in particular synthesis gas.
  • the lower limit here is a ratio of the area of the inlet openings to the area of the distributor opening, in particular the distributor hole 1: 1.
  • the distributor opening in particular the distributor bore, preferably has an inlet mouth. This has the advantage that the flow is evened over a longer distance and especially separation zones, which can form at the inlet, do not extend to the inlet openings.
  • the inlet mouth into the distributor opening in particular the distributor bore into it. This means that the remindström capablee that start at the inlet mouth, away from the first inlet openings.
  • the entry plane for the fuel into the distribution well is thus artificially shifted further away from the inlet ports, into the distribution well.
  • the area of the distributor opening, in particular of the distributor bore is reduced in the flow direction.
  • the flow rate is changed, in particular kept the same, so that a better uniform distribution of the fuel is achieved. Furthermore, thus secondary flows can be suppressed.
  • FIG. 1a shows a premix burner 1a according to the prior art, which is approximately rotationally symmetrical with respect to a burner axis 12.
  • a directed along the burner axis 12 pilot burner 9 with a fuel supply channel 8 and a concentrically enclosing this air supply annular channel 7 is concentrically surrounded by a fuel ring channel 3.
  • This fuel ring channel 3 is partially concentrically enclosed by a premixed air channel 2.
  • Der premix air duct 2 is designed as an annular channel 14, which has an outer channel wall 15.
  • the central axis 12 facing side of the premixing channel 2 is hereinafter referred to as the hub-side channel wall 16.
  • this premix air duct 2 a - shown schematically - ring of swirl vanes 5 is installed, which forms a swirl device.
  • at least one of these swirl blades 5 is formed as a hollow blade 5a. It has an inlet formed by a plurality of small openings 6 for a fuel supply ( FIG. 1a ) on.
  • the inlet openings 6 is connected to the fuel channel 3.
  • the hollow blade 5a is designed for the supply of high-calorie fuel 11, for example natural gas or fuel oil.
  • the fuel ring channel 3 opens into this hollow blade 5a.
  • the premix burner 1a can be operated via the pilot burner 9 as a diffusion burner. Usually, however, it is used as a premix burner, that is, fuel and air are first mixed and then sent to combustion.
  • the pilot burner 9 serves to maintain a pilot flame, which stabilizes the combustion during premix burner operation with a possibly changing fuel-air ratio.
  • combustion air 10 and the high-calorie fuel 11 are mixed in the premixed air channel 2 and then fed to the combustion.
  • the high-calorie fuel 11 is conducted from the fuel ring channel 3 into a hollow blade 5a of the swirl vane ring 5 and from there via which the inlet opening 6 is introduced into the combustion air 10 in the premix air channel 2.
  • a further injection stage comprising at least one, but preferably a plurality of inlet openings 40, designed here as a bore 40, is provided in the swirl blade 5, 5 a.
  • the injection via further inlet openings 40 on the swirl blade 5, 5 a enables a radial fuel distribution in an axial or diagonal flow channel. This makes it possible to keep the fuel from the endangered channel walls, which can serve as a potential Zündungs Surrey.
  • the inlet openings 40 are connected to a gas distribution ring 17 via a distributor opening, hereinafter referred to as a distributor bore 27, which surrounds the premixed air channel 2 at least partially radially outwardly.
  • the distribution bore 27 for synthesis gas has a substantially trapezoidal base ( fig2 and fig3 ).
  • a trapezoidal base with rounding, for example radii or semicircles, on both sides is particularly advantageous.
  • the trapezoidal base is particularly advantageous because approximately equal bore lengths for the fuel bores 40 are provided by the approximate parallelism of the wall of the manifold bores 27 and the blade surface.
  • the resistance coefficient of the holes 40 is approximately equal and thus the fuel distribution is very uniform. This is especially true when the fuel holes 40 are made with the same bore diameter.
  • the distributor bore 27 has a slot shape 42 (FIG. fig2 and fig3 ), through which the synthesis gas is supplied to the inlet ports 40 at the swirl vanes 5, 5a. This has the advantage of achieving the largest possible area for the distributor bore 27, without falling below the minimum wall thickness required.
  • the injection stage of the swirl blade 5 for high-calorie and low-calorie fuel consists of several inlet openings 6 and 40.
  • the inlet openings 6 are shown below for the injection of high-calorie fuel, in particular natural gas.
  • the inlet openings 6 are-as described above-supplied with fuel from the fuel channel 3.
  • a bore 50 which in particular has a round cross-sectional area ( FIG. 2 and FIG. 4 ) and which is separate from the distribution bore 27 made.
  • certain features will be described only for the synthesis gas inlet port 40 and the manifold bore 27. However, they may nevertheless be applied to the corresponding high calorific fuel inlet port 6 and bore 50 as well.
  • These inlet openings 40 can thereby different patterns for the injection (see. FIG.
  • the inlet openings 40 for low calorific fuel are arranged in an axial row RW1.
  • a plurality of axial rows RW1 and RW2 are present.
  • the axial rows RW1 and RW2 can be arranged either offset from each other or parallel or in a row.
  • the second row RW2 may also be offset from the first row RW1 and third row RW3 while the first row RW1 and the third row RW3 are arranged in parallel or in a row.
  • all three rows RW1, RW2, RW3 can also be arranged offset from each other.
  • Such patterns are for example in FIG6 in Examples 1 (Var1) to 6 (Var 6).
  • the distance between the individual rows should preferably comprise at least one bore diameter.
  • the bore diameter ( ⁇ RW1, ⁇ RW2) of the inlet openings 40 of, for example, two rows (RW1, RW2) is the same, this is particularly advantageous if the holes 40 have the same bore length.
  • the resistance value of the holes 40 is approximately equal and the fuel distribution is very uniform.
  • the bore diameter ( ⁇ RW1, ⁇ RW2) of the inlet openings 40 of, for example, two rows (RW1, RW2) may also be different, since fuel jets having a larger hydraulic diameter have a greater penetration depth. Thus, this can be used to achieve an even distribution at the periphery by means of different penetration depth of the fuel jets.
  • the bore diameter ( ⁇ RW1) of the inlet ports 40 of a single row can also be adjusted to the characteristics / physical characteristics of the individual premix burner 1b.
  • a ratio of 1: 4 is desirable due to the mass flows for the synthesis gas.
  • a ratio of 1: 1 is to be achieved.
  • the surface of the distributor bore 27 may decrease with increasing distance from entry of the low calorie fuel, that is to say in the flow direction. Thus, a better uniform distribution of the fuel is achieved. Furthermore, it is thus possible in particular to suppress secondary flows.
  • the distributor bore 27 can be subdivided into two sub-channels from about half of the distributor height (not shown). This can be done for example by means of a separating plate.
  • the introduction of an inlet mouth 45 to the distributor bore 27 has proved to be advantageous ( FIG. 5 ).
  • the inlet opening 45 causes the flow to be evened out over a longer distance, and in particular to detachment zones, which can form at an inlet, does not extend to the holes 40.
  • the inlet plane that is to say the plane at which the fuel enters the distributor bore 27, is thus artificially displaced away from the inlet openings 40.
  • premix burner for synthesis gas and natural gas low and high calorific fuel
  • synthesis gas and natural gas low and high calorific fuel
  • the premix burner according to the invention Due to the configuration of the fuel holes and the distributor bore a uniform fuel distribution is largely ensured.
  • the inlet openings for low-calorie combustible gas are farther from the outer channel wall and the hub-side channel wall than the inlet openings for high-calorie fuel gas. This also reduces, for example, the flashback or the inflammation of areas near the channel walls.
  • Different patterns for inlet openings are also provided according to the invention.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP08015728A 2008-09-05 2008-09-05 Brûleur à prémélange pour un combustible pauvre et riche Withdrawn EP2161502A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08015728A EP2161502A1 (fr) 2008-09-05 2008-09-05 Brûleur à prémélange pour un combustible pauvre et riche

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08015728A EP2161502A1 (fr) 2008-09-05 2008-09-05 Brûleur à prémélange pour un combustible pauvre et riche

Publications (1)

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EP2161502A1 true EP2161502A1 (fr) 2010-03-10

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Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2251604A1 (fr) * 2009-05-05 2010-11-17 General Electric Company Étouffement de carburant par gaz inerte ou couche de carburant moins réactif pour empêcher le retour de flamme dans les dispositifs de prémélange
WO2011023669A1 (fr) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brûleur notamment destiné à des turbines à gaz
WO2011128179A1 (fr) * 2010-04-15 2011-10-20 Siemens Aktiengesellschaft Générateur de turbulence pour un brûleur
EP2461101A1 (fr) * 2010-12-03 2012-06-06 Siemens Aktiengesellschaft Dispositif de brûleur pour une installation de turbine à gaz et procédé de fonctionnement d'un tel dispositif de brûleur
EP2472179A1 (fr) 2010-12-30 2012-07-04 Ansaldo Energia S.p.A. Ensemble de brûleur, centrale à turbine à gaz comportant cet ensemble de brûleur et procédé de fonctionnement de cet ensemble de brûleur
CN104807011A (zh) * 2014-01-27 2015-07-29 西门子公司 作为用于固态的及液态的燃料的压力气化的燃烧器装置的组成部分的辅助燃烧器
DE102015204594A1 (de) * 2015-03-13 2016-09-15 Siemens Aktiengesellschaft Monolithische Brennerdüse
EP3301368A1 (fr) * 2016-09-28 2018-04-04 Siemens Aktiengesellschaft Générateur de turbulence, ensemble chambre de combustion et turbine à gaz avec mélange d'air/carburant amélioré
EP3425281A1 (fr) * 2017-07-04 2019-01-09 General Electric Company Buse pilote dotée de prémélange en ligne
EP4299984A1 (fr) * 2022-06-29 2024-01-03 Doosan Enerbility Co., Ltd. Buse creuse, chambre de combustion comprenant une buse creuse, et turbine à gaz comprenant une chambre de combustion

Citations (7)

* Cited by examiner, † Cited by third party
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DE4212810A1 (de) * 1991-04-25 1992-10-29 Siemens Ag Brenner mit zusaetzlicher zufuehrungsmoeglichkeit fuer fluidische stoffe, insbesondere fuer gasturbinen, und verfahren zu seinem betrieb
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5351477A (en) * 1993-12-21 1994-10-04 General Electric Company Dual fuel mixer for gas turbine combustor
EP1614967A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP1645807A1 (fr) 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
EP1723369B1 (fr) 2004-02-24 2007-07-18 Siemens Aktiengesellschaft Bruleur a premelange et procede pour bruler un gaz pauvre
DE102007046623A1 (de) * 2006-10-03 2008-04-30 General Electric Co. Flüssigbrennstoffverbesserung für drallstabilisierte Erdgasdüse und Verfahren

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4212810A1 (de) * 1991-04-25 1992-10-29 Siemens Ag Brenner mit zusaetzlicher zufuehrungsmoeglichkeit fuer fluidische stoffe, insbesondere fuer gasturbinen, und verfahren zu seinem betrieb
US5251447A (en) * 1992-10-01 1993-10-12 General Electric Company Air fuel mixer for gas turbine combustor
US5351477A (en) * 1993-12-21 1994-10-04 General Electric Company Dual fuel mixer for gas turbine combustor
EP1723369B1 (fr) 2004-02-24 2007-07-18 Siemens Aktiengesellschaft Bruleur a premelange et procede pour bruler un gaz pauvre
EP1614967A1 (fr) * 2004-07-09 2006-01-11 Siemens Aktiengesellschaft Procédé et système de combustion à prémélange
EP1645807A1 (fr) 2004-10-11 2006-04-12 Siemens Aktiengesellschaft Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
DE102007046623A1 (de) * 2006-10-03 2008-04-30 General Electric Co. Flüssigbrennstoffverbesserung für drallstabilisierte Erdgasdüse und Verfahren

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2251604A1 (fr) * 2009-05-05 2010-11-17 General Electric Company Étouffement de carburant par gaz inerte ou couche de carburant moins réactif pour empêcher le retour de flamme dans les dispositifs de prémélange
WO2011023669A1 (fr) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Brûleur notamment destiné à des turbines à gaz
CN102597631A (zh) * 2009-08-26 2012-07-18 西门子公司 尤其用于燃气轮机的燃烧器
CN102597631B (zh) * 2009-08-26 2014-08-13 西门子公司 尤其用于燃气轮机的燃烧器
WO2011128179A1 (fr) * 2010-04-15 2011-10-20 Siemens Aktiengesellschaft Générateur de turbulence pour un brûleur
EP2461101A1 (fr) * 2010-12-03 2012-06-06 Siemens Aktiengesellschaft Dispositif de brûleur pour une installation de turbine à gaz et procédé de fonctionnement d'un tel dispositif de brûleur
EP2472179A1 (fr) 2010-12-30 2012-07-04 Ansaldo Energia S.p.A. Ensemble de brûleur, centrale à turbine à gaz comportant cet ensemble de brûleur et procédé de fonctionnement de cet ensemble de brûleur
CN104807011A (zh) * 2014-01-27 2015-07-29 西门子公司 作为用于固态的及液态的燃料的压力气化的燃烧器装置的组成部分的辅助燃烧器
CN104807011B (zh) * 2014-01-27 2019-11-05 西门子公司 用于给具有主燃烧器的气化反应器点火的辅助燃烧器
DE102015204594A1 (de) * 2015-03-13 2016-09-15 Siemens Aktiengesellschaft Monolithische Brennerdüse
WO2018060044A1 (fr) 2016-09-28 2018-04-05 Siemens Aktiengesellschaft Coupelle de turbulence, ensemble chambre de combustion et turbine à gaz dotée d'un mélange carburant/air amélioré
CN109804200A (zh) * 2016-09-28 2019-05-24 西门子股份公司 旋流器、燃烧装置组件以及具有改善燃料/空气混合的燃气涡轮
EP3301368A1 (fr) * 2016-09-28 2018-04-04 Siemens Aktiengesellschaft Générateur de turbulence, ensemble chambre de combustion et turbine à gaz avec mélange d'air/carburant amélioré
JP2019536976A (ja) * 2016-09-28 2019-12-19 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ 燃料／空気の混合が改良されたスワーラ、燃焼器アセンブリおよびガスタービン
CN109804200B (zh) * 2016-09-28 2021-06-04 西门子股份公司 旋流器、燃烧装置组件以及具有改善燃料/空气混合的燃气涡轮
US11421882B2 (en) 2016-09-28 2022-08-23 Siemens Energy Global GmbH & Co. KG Swirler, combustor assembly, and gas turbine with improved fuel/air mixing
EP3425281A1 (fr) * 2017-07-04 2019-01-09 General Electric Company Buse pilote dotée de prémélange en ligne
US10823420B2 (en) 2017-07-04 2020-11-03 General Electric Technology Gmbh Pilot nozzle with inline premixing
EP4299984A1 (fr) * 2022-06-29 2024-01-03 Doosan Enerbility Co., Ltd. Buse creuse, chambre de combustion comprenant une buse creuse, et turbine à gaz comprenant une chambre de combustion
US20240003538A1 (en) * 2022-06-29 2024-01-04 Doosan Enerbility Co., Ltd Hollow nozzle, combustor including hollow nozzle, and gas turbine including combustor
US12078346B2 (en) * 2022-06-29 2024-09-03 Doosan Enerbility Co., Ltd. Hollow nozzle, combustor including hollow nozzle, and gas turbine including combustor

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