EP3143335A1 - Brûleur destiné à un moteur à combustion interne et moteur à combustion interne - Google Patents

Brûleur destiné à un moteur à combustion interne et moteur à combustion interne

Info

Publication number
EP3143335A1
EP3143335A1 EP15744537.0A EP15744537A EP3143335A1 EP 3143335 A1 EP3143335 A1 EP 3143335A1 EP 15744537 A EP15744537 A EP 15744537A EP 3143335 A1 EP3143335 A1 EP 3143335A1
Authority
EP
European Patent Office
Prior art keywords
burner
adapter
cover plate
air
flow channel
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
EP15744537.0A
Other languages
German (de)
English (en)
Other versions
EP3143335B1 (fr
Inventor
Jens Kleinfeld
Christian Beck
Andreas Böttcher
Christopher Grandt
Thomas Hauser
Tobias Krieger
Stefan Reich
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
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
Publication of EP3143335A1 publication Critical patent/EP3143335A1/fr
Application granted granted Critical
Publication of EP3143335B1 publication Critical patent/EP3143335B1/fr
Not-in-force 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78—Cooling burner parts
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners

Definitions

  • the invention relates to a burner for a Verbrennungsma ⁇ machine and an internal combustion engine.
  • the internal combustion engine is in particular a gas turbine in the megawatt power range, preferably for a power plant for
  • the internal combustion engine typically comprises a plurality of burners, for example, in a ring arrangement and a compressor upstream of the burners and a turbine connected downstream of the burners.
  • each of the burners comprises a combustion region which is arranged in the interior of a combustion chamber of the internal combustion engine.
  • Each of the internal spaces is a part of a combustion chamber corresponding to the interior of the combustion chamber in Wesent ⁇ union.
  • This combustion chamber is designed, for example, annular, that is, as an annular combustion chamber, along which the burners are arranged.
  • a suitable fuel / air mixture is first injected and then burned.
  • the fuel is, for example, natural gas.
  • nozzles are typically provided which run parallel to one another and in which the fuel / air mixture is respectively formed before it is injected into the combustion chamber, that is to say in particular the combustion region.
  • the nozzles are often annular angeord ⁇ net, sometimes along several concentric rings.
  • the nozzles each have a nozzle outlet which opens into the combustion chamber.
  • the nozzles close to the nozzle outlet ⁇ lässen are connected to a nozzle carrier, which also constitutes the upstream end of the combustor and in particular ⁇ sondere the combustion chamber from another on the side of Düsenarris lying nozzle chamber separates.
  • the nozzle carrier thus also serves as a cover plate.
  • the burner is designed for use in an internal combustion engine, in particular gas turbine in the megawatt power range ⁇ forms and includes a pilot burner, which extends in the axial direction, a nozzle chamber and a combustion area. Furthermore, the burner comprises a cover plate, which is arranged between the nozzle chamber and the focal region and which has an inlet opening. In addition, an adapter is required. arranges, for guiding air from the nozzle chamber along a predetermined flow path in the direction of the combustion region.
  • an embodiment of the burner in lightweight ⁇ example allows, since is dispensed through the adapter to a massive nozzle carrier, whereby the burner is also inexpensive to manufacture.
  • the burner is particularly easy to assemble, in particular it is advantageously possible borrowed to mount the components of the burner through the combustion chamber of the internal combustion engine.
  • Another advantage is in particular that by means of the adapter at least a portion of the air is particularly efficient fed to the pilot burner as combustion air.
  • the deck plate advantageously prevented that smoke and / or fumes from Brennbe get ⁇ rich in the nozzle chamber. This is achieved in particular by the air flowing along the flow path into the combustion region. In other words, although a fluidic connection exists between the nozzle chamber and the combustion region, the penetration of exhaust gases into the nozzle chamber is prevented, in particular, by the fact that air flows from the nozzle chamber into the combustion region.
  • the internal combustion engine has a general flow direction which points from the compressor in the direction of the burner in the direction of the turbine.
  • the terms used in the following upstream and downstream are to be understood in particular with respect to this general flow direction.
  • the pilot burner extends along a longitudinal axis and is in particular arranged centrally in the burner.
  • the pilot ⁇ burner is used to supply a fuel, in particular oil into the combustion area.
  • a number of nozzles are arranged, each extending parallel to the longitudinal axis, that is to say also in the axial direction.
  • the nozzles are arranged in the nozzle chamber and each have downstream of a nozzle outlet, which corresponds to a respectively introduced into the cover plate recess. With others Words: the nozzles each lead into the focal area.
  • the nozzles are arranged in particular on a number of rings, the center of each of which lies on the longitudinal axis.
  • Each ring of nozzles is also called a stage.
  • the rings preferably concentrically angeord ⁇ net are.
  • the nozzles are designed in particular for receiving air from the nozzle chamber, that is to say they have a suitable nozzle inlet into which, in particular, in each case a burner lance for supplying fuel protrudes.
  • the provided in SI ⁇ senraum air is in particular compressed air, which is led from an upstream compressor to the burner of the combustion engine into the nozzle chamber.
  • the nozzle chamber thus serves in particular as a reservoir for compressed air.
  • the nozzle chamber is fluidically connected to the combustion region, whereby a supply of the pilot burner with air as combustion air is made possible.
  • the adapter is used in particular for appropriate guidance of the air, that is the special ⁇ an air flow along a suitable Strö ⁇ tion path.
  • the air has a flow direction, which is oriented generally from the nozzle chamber in the direction of the combustion region.
  • the flow direction does not generally correspond to the axial direction, but may change along the flow path.
  • the adapter allows a deflection of the air in a particularly suitable manner.
  • a flow channel is formed between the adapter and the cover plate, whereby a suitable flow path is realized in a particularly simple manner.
  • the flow channel is therefore limited by the adapter and the cover plate, that is, the adapter and the cover plate each form a boundary of the flow channel.
  • the flow channel is a flow space that extends around the inlet opening in such a way that the Air at a predetermined position in the flow space in each case flows substantially in the direction of the inlet opening.
  • the adapter For cooling the cover plate by means of the air, the adapter has a radially extending, annular portion, which forms a radial portion of the Strö ⁇ mungskanals with the cover plate.
  • the radial portion of the Strömungska ⁇ nals is also referred to as a radial section.
  • the annular Ab ⁇ cut of the adapter and the cover plate include an annular flow space through which the air flows substantially in the radial direction and in the direction of the diagonal section.
  • the running in the axial direction due-sen form in the flow channel in particular in each case a interrup ⁇ monitoring.
  • the nozzles each have an end portion which is disposed in the flow chamber, that is, in radial section and is advantageous ⁇ bathed by the flowing air therein. This makes it possible in particular, in addition to the cover plate and the nozzle ends, that is to cool the end portions of the nozzle by means of the air.
  • the adapter is formed in particular in the manner of a bell ⁇ , wherein the head portion forms an upper bell portion and the diagonal portion forms a lower part of the bell, to which in turn connects the radial portion.
  • the three sections are either formed in one piece or the radial section and the bell are separate, miteinan ⁇ the connected parts.
  • the air flowing out of the nozzle chamber is then drawn in via the outer edge of the radial section and flows along the nozzle-chamber-side wall of the cover plate into the lower part of the bell.
  • the cover plate is cooled by means of the air. In the lower part of the bell, the air flows along the axial cone and, in particular, also cools it.
  • the flow direction on the diagonal section is substantially opposite to the gen ⁇ rellen flow direction in the internal combustion engine. Then the air flows into the head area and gets there diverted in such a way that the flow direction of the air in ⁇ We sentlichen the general direction of flow corresponds.
  • the air is guided along the downstream end of the Pi ⁇ lot burner and finally provided in the combustion area as combustion air for the pilot burner. The air thus flows generally from outside to inside along the inner wall of the adapter.
  • the adapter in a preferred embodiment, a head portion into which projects the pilot burner.
  • the head area encloses the downstream end of the pilot burner and in particular also the outlet opening.
  • annular channel is expediently formed between the pilot burner and the head region.
  • this air is particularly even ⁇ introduced .
  • the inlet opening is circular.
  • a portion of the cover plate is formed as axial cone, the inlet opening is disposed at the upstream-lying end.
  • the axial cone is arranged in the center of the cover plate and widens in the opposite direction to the pilot burner, that is, downstream. The axial cone thus insbeson ⁇ particular forming a cone-shaped extension of the combustion chamber in the direction of the burner.
  • the axial cone is referred to here insbeson ⁇ particular as Axialgitterkegel and is used correspondingly for improved guiding or introduction of the fuel / air mixture towards the combustion chamber.
  • the adapter has a diagonally extending portion which extends at a distance from the axial cone and thereby forms a cone-shaped Ab ⁇ section of the flow channel.
  • the cone-shaped portion is also referred to as a diagonal section.
  • Axialverwirbler arranged for improved mixing of supplied by means of the annular channel air and fuel supplied by the Pi ⁇ lot burner.
  • the Axialverwirbler extends at least partially at the end of Pi ⁇ lotbrenners and into the annular channel into it.
  • Axialverwirbler is expediently surrounded or surrounded by a collar, which is in particular formed on the axial cone.
  • the Axialverwirbler is disposed within the collar and the outer side of the collar forms in combination with the adapter an advantageous extension of the diagonal portion of the flow channel.
  • the flow channel is expediently designed as an annular space.
  • annular space is understood in particular to mean that the flow channel is a space enclosed by suitable sidewalls, which has an extension in at least one direction transverse to the flow direction which is comparable to the length of the flow channel in the flow direction of the air.
  • flow channels which are introduced into a solid part by means of bores, can be as
  • Ring space formed flow channel make particularly material Spa ⁇ rend and is also lighter in terms of its weight.
  • the contact Surface between air and elements to be cooled, here in particular the cover plate advantageously increases.
  • the latter preferably has an air inlet lying in the radial direction.
  • Characterized in particular an air flow from the outside ⁇ SEN is formed inwardly and cooled a particularly large portion of the cover plate by means of the air flowing past it.
  • the air inlet is in particular annular and is then also referred to as a ring inlet. This has a radius which is in particular greater than the radial distances of the nozzles to the longitudinal axis of the burner. The air is thus sucked in from the outside of the nozzle area with respect to the nozzles. Due to the outer layer of the air inlet also a particularly large flow cross-section is achieved ⁇ bar.
  • an annular gap is formed in the radial direction between the pilot burner and the adapter, into which a sealing ring is inserted.
  • the ⁇ ser serves, in particular, an inflow of air from the nozzle chamber through the gap, i.e., the pilot burner over to avoid, in the area enclosed by the head portion of the adapter head interior or at least reduce.
  • the sealing ring is fastened to one of the two parts, namely to the pilot burner or to the adapter, and is displaceable relative to the other of these two parts.
  • the sealing ring is thus either attached to the pilot burner and displaceable relative to the adapter or attached to the adapter and displaceable relative to the pilot burner. Due to the typically present in the operating thermal see loading of the different parts of the burner results in a thermal expansion, which may also differ in size for different parts or is directed in different directions ⁇ Liche.
  • the displaceability of the Sealing piston then allows in particular an avoidance of tension of the pilot burner against the adapter and possibly resulting damage.
  • the sealing ring has at least one web which extends in the axial direction and rotates the sealing ring, wherein the web forms a sealing ⁇ surface which ana on the adapter.
  • the sealing ring thus has an approximately H-shaped cross-section and is therefore particularly economical to produce, at the same time suitable sealing effect.
  • the adapter has at least one from ⁇ spacers on the anabut on the cover plate.
  • the spacer is attached to the diagonal portion of the adapter and abuts the axial cone, whereby in ⁇ special at the same time a suitable spacing in radia ⁇ ler and in the axial direction takes place.
  • the mounting of the burner is simplified by the spacer in such a way that during assembly automatically takes place a suitable spacing and alignment, in particular centering of the cover plate, the adapter and the pilot burner.
  • the spacer is formed as a deformation of the adapter.
  • a suitable spacer can be produced in a particularly simple manner.
  • the spacer as dimples, nub or cam is formed and represents an elevation or depression along the surface of the adapter.
  • insbesonde ⁇ re to improve the spacing in the assembly and for improved centering with respect to the longitudinal axis of the burner ners.
  • these are insbesonde re evenly distributed in the direction of rotation of the adapter.
  • the adapter and the cover plate are each made of sheets, that is, with a low material thickness, where can be produced by the burner in an advantageous lightweight construction.
  • the material thickness is in particular about 1-4 mm in the case of both the adapter and the cover plate.
  • FIG. 1 shows a burner in a longitudinal sectional view, with a nozzle chamber and with an adapter
  • FIG. 2 shows a detail of the nozzle chamber according to FIG. 1 and an alternative adapter
  • FIG. 3 shows a detail of the arrangement according to FIG. 1,
  • FIG. 4 shows a detail of the arrangement according to FIG. 1 with an alternative sealing ring
  • FIG 5 shows the adapter according to FIG 2 in a perspective view.
  • a burner 2 is shown schematically, in a sectional view taken along a longitudinal axis L of the burner 2.
  • a longitudinal axis L that is, in the axial direction A he stretches a pilot burner 4, to promote a fuel in a combustion region 6, the downstream of the pilot burner 4 is arranged.
  • the fuel is via an outlet opening 8 of the pilot burner 4 in the combustion region.
  • the combustion region 6 corresponds to the réelleraun a burner 2 downstream, not illustrated here Darge combustion chamber.
  • a burner chamber 10 Around the pilot burner 4 around a number of nozzles 12 is arranged in a nozzle chamber 10, which also each extend in the axial direction A and parallel to each other.
  • the nozzles 12 are used to provide a combustible fuel / air mixture in the combustion region 6.
  • each SI ⁇ se 12 each have a fuel lance 14 such that it at least partly at the back, that is, at the upstream end of the nozzle 16 in the nozzle 12 protrudes.
  • an annular nozzle inlet is formed exclusively in particular in each case, by means of which air from the nozzle chamber 10 is sucked into the einströmbar or SI ⁇ se 12 in order to be mixed there with the jetted from the respective fuel lance 14 fuel.
  • the existing in the nozzle chamber 10, air is here in particular a burner 2 upstream, not shown here compressor provided and thus ver ⁇ composed air.
  • the fuel is provided upstream of the fuel lances 14 via a number of, here two fuel ring channels 18.
  • the nozzles 12 are arranged along a number of, here two rings and form an inner and an outer stage in FIG.
  • the nozzle chamber 10 is separated from the combustion region 6, that is to say from the combustion chamber by means of a cover plate 20.
  • This extends essentially in the radial direction R and has a number of recesses, which are each assigned to a nozzle outlet 22 of a nozzle 12, for admitting the fuel / air mixture formed in the nozzles 12 into the combustion area 6.
  • the cover plate 20 has an axial cone 24 which is widened in the flow direction S.
  • the axial cone ⁇ an inlet opening 26 which is in the here ge Service ⁇ th embodiment arranged downstream of the outlet opening 8 of the Pi ⁇ lotbrenners. 4
  • an adapter 28 is arranged, the one surrounding the end of the pilot burner 4 head portion 30, extending from this downstream and widening diagonal section 32 has.
  • the adapter 28 is formed in the manner of a bell, wherein the head portion 30 is an upper part of the bell and the diagonal portion 32 is a frusto-conical, lower part.
  • From the downstream end of the diagonal section 22 from a ra ⁇ dialer portion 34 extends in the radial direction R.
  • the diagonal and the radial portion 32, 34 are each in a ge ⁇ suitable distance AI, A2 relative to the Axialkegels 24 Bezie ⁇ hung as the cover plate 20 is arranged, for example about 2-5mm.
  • the adapter 28 is made in one piece, but alternatively a multi-part design is possible, as shown in FIG.
  • the cover plate 20 and the adapter 28 form a gap which serves as a flow channel 36 to flow air from the nozzle ⁇ chamber 10 in the combustion region 6 and thereby cool the cover plate 20.
  • the flow channel 36 thereto comprises a plurality of sections 38, 40, 42, namely a radial From ⁇ cut 38 to the top plate 20 along, as Radialab ⁇ cut 38 denotes a diagonal portion 40 on Axi ⁇ alkegel 24 along, as a diagonal section 40 and an annular channel 42, in the head region 30 between the adapter 28 and the pilot burner 4.
  • the air inlet 44 is an annular inlet, which is also referred to as a ring inlet. This revolves around the radial portion 34 of the adapter 28, as shown particularly clearly in FIG.
  • Air inlet 44 is inserted into the flow channel 36 and then follows the radial section 38 from the outside inwards to the diagonal section 40. This is followed by a deflection along of the axial cone 24 in the interior of the head portion 30. There, the air is again deflected in the direction of the inlet opening 26. Between inlet and outlet opening 26, 8 is in the embodiment shown here in addition to a
  • Axialverwirbler 50 arranged, in which the air is introduced before mixing with the fuel from the pilot burner 4.
  • the Axialverwirbler 50 is surrounded by a collar 52 which is attached as an extension on the axial cone 24.
  • a gap 54 is formed between the pilot burner 4 and the upstream end of the adapter 28, in which a sealing ring 56 is inserted. This is fixed in the embodiment shown here ⁇ example on the pilot burner 4 and relative to the adapter 28 slidably.
  • FIG 4 a variant of the sealing ring 56 is shown, with this radially outwardly encircling, axially extending web 58 which forms outwardly a sealing surface 60 which is located on a mating surface 62 of the adapter 28 ⁇ .
  • the adapter 28 has a number of spacers 64 to suitably space the adapter 28 from the cover plate 20 and, when mounting the burner 2, a suitable orientation of the cover plate 20, the adapter 28 and the pilot burner 4 to each other achieve.
  • the adapter 28 shown in FIG 4 is also shown in FIG 5 in a perspective view. Clearly visible are formed as depressions with respect to the outside of the Adap ⁇ age 28 spacers 64, which are each formed in the manner of a dimple, a knob or a cam. The spacers 64 protrude into the flow channel 36 and sit against the cover plate 20. In the embodiment shown here, the spacers 64 are arranged on the diagonal section 32 of the adapter 28 and seat on the outside on the axial cone 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

L'invention concerne un brûleur (2) destiné à un moteur à combustion interne. Ledit brûleur comprend un brûleur pilote (4), qui s'étend dans une direction axiale (A), une chambre d'injection (10), une zone de combustion (6) et une plaque de recouvrement (20), qui est disposée entre la chambre d'injection (10) et la zone de combustion (6) et qui comporte une ouverture d'entrée (26). L'invention prévoit un adaptateur (28) servant à acheminer de l'air en provenance de la chambre d'injection (10), le long d'un trajet d'écoulement (P) prédéfini, en direction de la zone de combustion (6). Un canal d'écoulement (36) faisant partie intégrante du trajet d'écoulement (P) est formé entre l'adaptateur (28) et la plaque de recouvrement (20). L'adaptateur (28) comporte une section (34) de forme annulaire s'étendant radialement, qui réalise avec la plaque de recouvrement (20) une section radiale (38) du canal d'écoulement (36) afin de refroidir la plaque de recouvrement (20) au moyen de l'air. L'invention concerne en outre un moteur à combustion interne équipé d'un brûleur (2) de ce type.
EP15744537.0A 2014-07-30 2015-07-24 Brûleur pour un moteur à combustion et moteur à combustion Not-in-force EP3143335B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14179137.6A EP2980482A1 (fr) 2014-07-30 2014-07-30 Brûleur pour un moteur à combustion interne et moteur à combustion interne
PCT/EP2015/066984 WO2016016116A1 (fr) 2014-07-30 2015-07-24 Brûleur destiné à un moteur à combustion interne et moteur à combustion interne

Publications (2)

Publication Number Publication Date
EP3143335A1 true EP3143335A1 (fr) 2017-03-22
EP3143335B1 EP3143335B1 (fr) 2018-02-28

Family

ID=51260658

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14179137.6A Withdrawn EP2980482A1 (fr) 2014-07-30 2014-07-30 Brûleur pour un moteur à combustion interne et moteur à combustion interne
EP15744537.0A Not-in-force EP3143335B1 (fr) 2014-07-30 2015-07-24 Brûleur pour un moteur à combustion et moteur à combustion

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP14179137.6A Withdrawn EP2980482A1 (fr) 2014-07-30 2014-07-30 Brûleur pour un moteur à combustion interne et moteur à combustion interne

Country Status (4)

Country Link
US (1) US20170227227A1 (fr)
EP (2) EP2980482A1 (fr)
CA (1) CA2956526C (fr)
WO (1) WO2016016116A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016118633B4 (de) 2016-09-30 2021-03-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennerkopf, Brennersystem und Verwendung des Brennersystems
CN107238106B (zh) * 2017-06-10 2020-01-24 北京航空航天大学 一种用于多点喷射燃烧室的多层环形油轨
US10837643B2 (en) 2018-08-06 2020-11-17 General Electric Company Mixer assembly for a combustor
CN113028449B (zh) * 2021-02-26 2023-03-17 中国空气动力研究与发展中心设备设计与测试技术研究所 一种燃气发生器流线型燃料分流盘

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5235814A (en) * 1991-08-01 1993-08-17 General Electric Company Flashback resistant fuel staged premixed combustor
US8020385B2 (en) * 2008-07-28 2011-09-20 General Electric Company Centerbody cap for a turbomachine combustor and method
US8205452B2 (en) * 2009-02-02 2012-06-26 General Electric Company Apparatus for fuel injection in a turbine engine
EP2261563A1 (fr) * 2009-05-27 2010-12-15 Siemens Aktiengesellschaft Brûleur, procédé de fonctionnement et procédé de montage
US9127842B2 (en) * 2009-05-27 2015-09-08 Siemens Aktiengesellschaft Burner, operating method and assembly method
US8707672B2 (en) * 2010-09-10 2014-04-29 General Electric Company Apparatus and method for cooling a combustor cap
US20120192566A1 (en) * 2011-01-28 2012-08-02 Jong Ho Uhm Fuel injection assembly for use in turbine engines and method of assembling same
JP5438727B2 (ja) * 2011-07-27 2014-03-12 株式会社日立製作所 燃焼器、バーナ及びガスタービン
DE102012216080A1 (de) * 2012-08-17 2014-02-20 Dürr Systems GmbH Brenner
US9285121B2 (en) * 2012-08-23 2016-03-15 General Electric Company Gas turbine cooling circuit including a seal for a perforated plate
DE102013204307A1 (de) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Strahlbrenner mit Kühlkanal in der Grundplatte
US9835333B2 (en) * 2014-12-23 2017-12-05 General Electric Company System and method for utilizing cooling air within a combustor
US10458655B2 (en) * 2015-06-30 2019-10-29 General Electric Company Fuel nozzle assembly

Also Published As

Publication number Publication date
EP2980482A1 (fr) 2016-02-03
CA2956526C (fr) 2018-08-21
EP3143335B1 (fr) 2018-02-28
CA2956526A1 (fr) 2016-02-04
US20170227227A1 (en) 2017-08-10
WO2016016116A1 (fr) 2016-02-04

Similar Documents

Publication Publication Date Title
DE102005024062B4 (de) Brennerrohr und Verfahren zum Mischen von Luft und Gas in einem Gasturbinentriebwerk
DE102007004864B4 (de) Brennkammer einer Gasturbine und Verbrennungssteuerverfahren für eine Gasturbine
DE112011103736B4 (de) Gasturbinenbrennkammer mit ultraniedrigen Emissionen
EP2156095B1 (fr) Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
DE69205576T2 (de) Gasturbinenbrennkammer.
DE102012100368B4 (de) Brennkammerdüse
DE102015112767A1 (de) Brennstoffinjektoranordnungen in Verbrennungsturbinen
EP2340397B1 (fr) Pièce du brûleur pour une chambre de combustion d'une turbine à gaz et turbine à gaz
EP2162681B1 (fr) Brûleur de turbine à gaz
DE102010060281A1 (de) Vormischvorrichtung zur Brennstoffeinspritzung in eine Gasturbine
EP2808611B1 (fr) Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
DE112013007579B4 (de) Flüssigbrennstoffpatrone für eine Brennstoffdüse und Brennstoffdüse
DE102010017623A1 (de) Monolithischer Brennstoffinjektor und zugehöriges Herstellungsverfahren
DE102015113146A1 (de) Systeme und Vorrichtungen im Zusammenhang mit Gasturbinenbrennkammern
DE112021000904T5 (de) Brenneranordnung, gasturbinen-brennkammer und gasturbine
DE102008002934A1 (de) Brennstoffdüse für ein Gasturbinentriebwerk und Verfahren zur Herstellung desselben
WO2023180315A2 (fr) Ensemble injecteur comportant une alimentation centrale en carburant et au moins un canal d'air
EP3143335A1 (fr) Brûleur destiné à un moteur à combustion interne et moteur à combustion interne
WO2019020350A1 (fr) Brûleur de turbine à gaz à jets de flamme prémélangés
EP2583033B1 (fr) Brûleur de turbines
EP2462379B1 (fr) Stabilisation de la flamme d'un brûleur
EP2409087A2 (fr) Procédé pour faire fonctionner un brûleur et brûleur correspondant, en particulier brûleur destiné à une turbine à gaz
EP2409086B1 (fr) Arrangement de brûleur pour une turbine à gaz
EP2864706A1 (fr) Amélioration locale du mélange d'air et de combustible dans des brûleurs pourvus de générateurs de tourbillon comprenant des extrémités à aube entrecroisées dans la zone extérieure
EP2151630B1 (fr) Dispositif de tourbillonnement

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

17P Request for examination filed

Effective date: 20161216

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: BA ME

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
INTG Intention to grant announced

Effective date: 20171004

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 974570

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180315

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015003259

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180228

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 4

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180528

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180528

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180529

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20180726

Year of fee payment: 4

Ref country code: DE

Payment date: 20180920

Year of fee payment: 4

Ref country code: IT

Payment date: 20180731

Year of fee payment: 4

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015003259

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20181129

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20181005

Year of fee payment: 4

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180724

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20180731

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180724

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180731

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502015003259

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20190724

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190724

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200201

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190731

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190731

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190731

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20150724

Ref country code: MK

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20180628

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190724

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 974570

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200724

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200724