EP3143335B1 - Brûleur pour un moteur à combustion et moteur à combustion - Google Patents

Brûleur pour un moteur à combustion et moteur à combustion Download PDF

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Publication number
EP3143335B1
EP3143335B1 EP15744537.0A EP15744537A EP3143335B1 EP 3143335 B1 EP3143335 B1 EP 3143335B1 EP 15744537 A EP15744537 A EP 15744537A EP 3143335 B1 EP3143335 B1 EP 3143335B1
Authority
EP
European Patent Office
Prior art keywords
burner
adapter
cover plate
air
pilot burner
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.)
Not-in-force
Application number
EP15744537.0A
Other languages
German (de)
English (en)
Other versions
EP3143335A1 (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
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
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

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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
    • F23R3/34—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, e.g. burner cooling means, noise reduction means
    • 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, e.g. noise reduction means
    • 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 an internal combustion engine 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 with a power of several hundred megawatts.
  • 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 combustion regions is part of a combustion chamber which substantially corresponds to the interior of the combustion chamber.
  • This combustion chamber is, 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 each other and in which the fuel / air mixture is respectively formed before it is injected into the combustion chamber, that is, in particular the combustion region.
  • the nozzles are often arranged annularly, sometimes along several concentric rings.
  • the nozzles each have a nozzle outlet which opens into the combustion chamber.
  • the nozzles near the nozzle outlets are connected to a nozzle carrier, which at the same time constitutes the upstream end of the combustion chamber, and in particular the combustion chamber from one on the other side of the combustion chamber Düsentheses lying nozzle chamber separates.
  • the nozzle carrier thus also serves as a cover plate.
  • a burner having the features of the preamble of claim 1 is known from US 2010/300104 A1 known.
  • a burner having the features of the preamble of claim 1 is known from US 2010/300104 A1 known.
  • auxiliary systems used for operating the internal combustion engine for example cooling systems and on the other an enlargement of the system, in particular of the nozzle carrier.
  • assembly is made more difficult by the typically massive design of the same or, in the case of certain internal combustion engines, due to their design, is completely prevented.
  • cooling of the nozzle carrier in its function as a cover plate with greater power is increasingly difficult.
  • the burner is designed for use in an internal combustion engine, in particular a gas turbine in the megawatt power range, and comprises a pilot burner which extends in the axial direction, a nozzle chamber and a combustion region. 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 arranged for guiding air from the nozzle chamber along a predetermined flow path in the direction of the combustion region.
  • an embodiment of the burner is made possible in lightweight construction, as 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 to assemble 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 cover plate advantageously prevents smoke and / or exhaust gases from reaching the combustion chamber into 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 towards 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 in 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.
  • 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. In the case of several stages, the rings are preferably arranged concentrically.
  • Upstream of the nozzles are formed in particular for receiving air from the nozzle chamber, that is, have a suitable nozzle inlet into which in particular in each case a burner lance for supplying fuel protrudes.
  • the air provided in the nozzle chamber is, in particular, compressed air, which is conducted into the nozzle chamber from a compressor of the internal combustion engine arranged upstream of the burner.
  • 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 serves in particular for suitable guidance of the air, that is to say in particular of an air flow along a suitable flow path.
  • the air in this case has a flow direction, which is generally oriented from the nozzle chamber in the direction of the focal 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 flow channel with the cover plate.
  • the radial section of the flow channel is also referred to as a radial section.
  • the annular portion 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 portion.
  • each of the nozzles extending in the axial direction in the flow channel forms an interruption.
  • the nozzles each have an end portion which is arranged in the flow space, that is to say in the radial section and is thereby advantageously surrounded by the air flowing there. 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 shaped 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, which in turn is followed by the radial portion.
  • the three sections are formed either in one piece or the radial section and the bell are separate, interconnected 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 general flow direction in the internal combustion engine.
  • the air flows into the head area and gets there deflected such that the flow direction of the air substantially corresponds to the general flow direction.
  • the air is guided along the downstream end of the pilot 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.
  • the air is thereby introduced particularly uniformly.
  • the pilot burner or at least its end in particular has a circular border; Likewise, the inlet opening is circular.
  • part of the cover plate is designed as an axial cone, at the upstream end of which the inlet opening is arranged.
  • 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 forms in particular a cone-shaped extension of the combustion chamber in the direction of the burner.
  • the axial cone is in this case also referred to as axial lattice cone and serves accordingly for improved guidance or introduction of the fuel / air mixture in the direction of 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 portion of the flow channel.
  • the cone-shaped portion is also referred to as a diagonal section. Due to this development, it is in particular possible to use the air from the nozzle chamber advantageously for cooling the axial cone.
  • an axial swirler is arranged between the inlet opening of the axial cone and the outlet opening of the pilot burner, for improved mixing of air supplied by means of the annular channel and fuel supplied by means of the pilot burner.
  • the axial swirler extends at least partially past the end of the pilot burner and into the annular channel.
  • the Axialverwirbler is expediently surrounded or surrounded by a collar which is formed in particular on the axial cone. In this case, 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 designed as an annular space.
  • annular space is understood in particular to mean that the flow channel is a space enclosed by suitable side walls, 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.
  • the flow channel formed as an annular space can be made particularly cost-saving and is also lighter in terms of its weight.
  • the cover plate advantageously increases.
  • the latter preferably has an air inlet lying in the radial direction.
  • an air flow is formed from outside to inside and a particularly large part of the cover plate is cooled 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 can be achieved. Thus, a corresponding amount of air is available for cooling and then for introduction into the combustion area.
  • annular gap is formed in the radial direction between the pilot burner and the adapter, into which a sealing ring is inserted. This serves, in particular, to prevent or at least reduce an inflow of air out of the nozzle chamber through the gap, that is to say past the pilot burner into the head interior enclosed by the head region of the adapter.
  • the sealing ring is attached to one of the two parts, namely the pilot burner or the adapter and 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 thermal load of the various parts of the burner, which is usually present in operation, a thermal expansion results, which may also be different for different parts or directed in different directions.
  • 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 abuts 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 spacer, which abuts on the cover plate.
  • the spacer is attached to the diagonal portion of the adapter and abuts the axial cone, whereby in particular at the same time a suitable spacing in the radial and in the axial direction takes place.
  • the mounting of the burner is simplified by the spacer so that when assembling automatically a suitable spacing and alignment, in particular centering of the cover plate, the adapter and the pilot burner takes place.
  • the spacer is formed as a deformation of the adapter.
  • a suitable spacer can be produced in a particularly simple manner.
  • the spacer is designed as a dimple, nub or cam and constitutes an elevation or depression along the surface of the adapter.
  • a plurality of spacers are provided, in particular for improving the spacing during assembly and for improved centering with respect to the longitudinal axis of the burner. In the case of several spacers, these are in particular distributed uniformly 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, whereby the burner can be produced 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 schematically a burner 2 is shown, in a sectional view taken along a longitudinal axis L of the burner 2.
  • a pilot burner 4 for conveying a fuel in a combustion region 6, which is arranged downstream of the pilot burner 4 is.
  • the fuel is injected into the combustion region 6 via an outlet opening 8 of the pilot burner 4.
  • the combustion region 6 corresponds to the interior of a burner downstream of the burner 2, not shown here combustion chamber.
  • a fuel lance 14 is arranged in each case for each nozzle 12 in such a way that it protrudes into the nozzle 12 at least partially at the rear, that is to say at the upstream nozzle end 16.
  • an annular nozzle inlet in particular is formed, by means of which air from the nozzle chamber 10 can be flowed into or sucked into the nozzle 12 in order to be mixed there with the fuel spouted out of the respective fuel lance 14.
  • the air present in the nozzle chamber 10 is here provided, in particular, by a compressor which is connected upstream of the burner 2 and is not shown here, and thus compressed air.
  • the fuel is provided upstream of the fuel lances 14 via a number of, here two fuel ring channels 18. Accordingly, the nozzles 12 are arranged along a number of, here two rings and form in FIG. 1 an inside and an outside step.
  • 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 substantially in the radial direction R and has a number of recesses, which are each associated with a nozzle outlet 22 of a nozzle 12, for admitting the fuel / air mixture formed in the nozzles 12 in the focal region 6.
  • the cover plate 20 has an axial cone 24 which is widened in the flow direction S. At the upstream end of the axial cone 24 has an inlet opening 26, which is arranged in the embodiment shown here downstream of the outlet opening 8 of the pilot burner 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 portion 22 extends from a radial portion 34 in the radial direction R.
  • the diagonal and the radial portion 32, 34 are each arranged at a suitable distance A1, A2 with respect to the axial cone 24 and the cover plate 20, for example about 2-5mm.
  • the adapter 28 is made in one piece, but alternatively, a multi-part design is possible, as in FIG. 2 shown.
  • 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 into the combustion region 6 while cooling the cover plate 20.
  • the flow channel 36 for this purpose comprises a plurality of sections 38, 40, 42, namely: a radial section 38 along the cover plate 20, also referred to as radial section 38, a diagonal section 40 along the axial cone 24 along, also referred to as diagonal section 40, and an annular channel 42nd 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 circumscribes the radial portion 34 of the adapter 28, as particularly FIG. 2 clearly shows.
  • FIG. 2 in combination with FIG. 1 It can be seen that the nozzles 12 each project into the radial section 38 with their nozzle ends 16 and in this way form cylindrical recesses 48 in the radial section 38.
  • FIG. 1 the flow path P of the air is indicated by a number of arrows.
  • the air is first admitted via the air inlet 44 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.
  • an axial swirler 50 into which the air is introduced from the pilot burner 4 before being mixed with the fuel, is additionally arranged between the inlet and outlet openings 26, 8.
  • the Axialverwirbler 50 is surrounded by a collar 52 which is attached as an extension on the axial cone 24.
  • FIG. 1 and in an enlargement FIG. 3 show, between the pilot burner 4 and the upstream end of the adapter 28, a gap 54 is formed, in which a sealing ring 56 is inserted.
  • a sealing ring 56 is inserted. This is fixed in the embodiment shown here 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 a sealing surface 60 outwardly, which rests against a mating surface 62 of the adapter 28.
  • FIG. 4 shows further that the adapter 28 has a number of spacers 64 to suitably space the adapter 28 from the cover plate 20 and to achieve proper alignment of the cover plate 20, the adapter 28 and the pilot burner 4 during assembly of the burner 2.
  • the Indian FIG. 4 shown adapter 28 is also in FIG. 5 shown in a perspective view. Clearly visible are formed as depressions with respect to the outside of the adapter 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 are seated on the outside of the axial cone 24.

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

Claims (13)

  1. Brûleur (2) pour une machine à combustion, comprenant un brûleur (4) pilote, qui s'étend dans une direction (A) axiale, comprenant une chambre (10) de buses, comprenant une région (6) de combustion et comprenant une plaque (20) de recouvrement, disposée entre la chambre (10) de buses et la région (6) de combustion et ayant une ouverture (26) d'entrée, ainsi que des buses (12) disposées tout autour du brûleur (4) pilote dans la chambre (10) de buses, s'étendant chacune dans une direction (A) axiale et ayant chacune une sortie (22) de buse, qui correspond à un évidement ménagé dans la plaque (20) de recouvrement, un adaptateur (28) étant disposé pour guider de l'air de la chambre (10) de buse, suivant un trajet (P) d'écoulement donné à l'avance, en direction de la région (6) de combustion, dans lequel un conduit (36) d'écoulement est formé entre l'adaptateur (28) et la plaque (20) de recouvrement, en tant que partie du trajet (P) d'écoulement, et en ce que l'adaptateur (28) a une partie (34) annulaire s'étendant radialement, qui constitue, avec la plaque (20) de recouvrement, un tronçon (38) radial du conduit (36) d'écoulement, pour le refroidissement de la plaque (20) de recouvrement au moyen de l'air, caractérisé en ce que les buses (12) ont chacune un tronçon d'extrémité, qui est disposé dans le tronçon (38) radial.
  2. Brûleur (2) suivant la revendication 1,
    caractérisé en ce que l'adaptateur (28) a une partie (30) de tête, qui pénètre dans le brûleur (4) pilote.
  3. Brûleur (2) suivant la revendication précédente,
    caractérisé en ce qu'entre le brûleur (4) pilote et la partie (30) de tête, un canal (42) annulaire est formé en tant que partie du trajet (P) d'écoulement.
  4. Brûleur (2) suivant l'une des revendications précédentes,
    caractérisé en ce qu'une partie de la plaque (20) de recouvrement est constituée en cône (24) axial, à l'extrémité amont duquel est disposée l'ouverture (26) d'entrée.
  5. Brûleur (2) suivant la revendication précédente,
    caractérisé en ce que l'adaptateur (28) a un tronçon (32), qui s'étend en diagonal, qui s'étend à distance du cône (24) axial et qui constitue ainsi un tronçon (40) en diagonal en forme de surface latérale de cône du conduit (36) d'écoulement.
  6. Brûleur (2) suivant l'une des revendications précédentes,
    caractérisé en ce que le conduit (36) d'écoulement est constitué sous la forme d'un espace annulaire.
  7. Brûleur (2) suivant l'une des revendications précédentes,
    caractérisé en ce que le conduit (36) d'écoulement a une entrée (44) d'air se trouvant à l'extérieur dans la direction (R) radiale.
  8. Brûleur (2) suivant l'une des revendications précédentes,
    caractérisé en ce que, dans la direction (R) radiale, entre le brûleur (4) pilote et l'adaptateur (28), est constitué un intervalle (54) annulaire, dans lequel est inséré un joint (56).
  9. Brûleur (2) suivant la revendication précédente,
    caractérisé en ce que le joint (56) est fixé à l'une des deux parties, à savoir au brûleur (4) pilote ou à l'adaptateur (28) et peut se déplacer par rapport à l'autre de ces deux parties.
  10. Brûleur (2) suivant l'une des deux revendications précédentes,
    caractérisé en ce que le joint (56) a au moins une barrette (58), qui s'étend dans la direction (A) axiale et qui entoure le joint (56), la barrette (58) formant une surface (60) d'étanchéité, qui est mise sur l'adaptateur (28).
  11. Brûleur (2) suivant l'une des revendications précédentes,
    caractérisé en ce que l'adaptateur (28) a au moins une entretoise (64), qui est mise sur la plaque (20) de recouvrement.
  12. Brûleur (2) suivant la revendication précédente,
    caractérisé en ce que l'entretoise 64) est constituée sous la forme d'une déformation de l'adaptateur (28).
  13. Machine de combustion, notamment turbine à gaz, comprenant un brûleur (2) suivant l'une des revendications précédentes.
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 EP3143335A1 (fr) 2017-03-22
EP3143335B1 true EP3143335B1 (fr) 2018-02-28

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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)

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EP14179137.6A Withdrawn EP2980482A1 (fr) 2014-07-30 2014-07-30 Brûleur pour un moteur à combustion interne et moteur à combustion interne

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

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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

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* 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

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WO2016016116A1 (fr) 2016-02-04
EP2980482A1 (fr) 2016-02-03
US20170227227A1 (en) 2017-08-10
EP3143335A1 (fr) 2017-03-22
CA2956526A1 (fr) 2016-02-04
CA2956526C (fr) 2018-08-21

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