EP2026002A1 - Mehrpunkt-Einspritzer für Turbotriebwerk - Google Patents

Mehrpunkt-Einspritzer für Turbotriebwerk Download PDF

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Publication number
EP2026002A1
EP2026002A1 EP08161242A EP08161242A EP2026002A1 EP 2026002 A1 EP2026002 A1 EP 2026002A1 EP 08161242 A EP08161242 A EP 08161242A EP 08161242 A EP08161242 A EP 08161242A EP 2026002 A1 EP2026002 A1 EP 2026002A1
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EP
European Patent Office
Prior art keywords
injector
fuel
multipoint
ferrule
channels
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
EP08161242A
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English (en)
French (fr)
Other versions
EP2026002B1 (de
Inventor
Didier Hippolyte Hernandez
Thomas Olivier Marie Noel
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2026002A1 publication Critical patent/EP2026002A1/de
Application granted granted Critical
Publication of EP2026002B1 publication Critical patent/EP2026002B1/de
Active 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
    • F23R3/283—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
    • 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
    • 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
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49405—Valve or choke making
    • Y10T29/49412—Valve or choke making with assembly, disassembly or composite article making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49405—Valve or choke making
    • Y10T29/49412—Valve or choke making with assembly, disassembly or composite article making
    • Y10T29/49416—Valve or choke making with assembly, disassembly or composite article making with material shaping or cutting
    • Y10T29/49419—Valve or choke making with assembly, disassembly or composite article making with material shaping or cutting including machining or drilling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49428—Gas and water specific plumbing component making
    • Y10T29/49446—Ferrule making or reforming

Definitions

  • the invention relates to a multipoint injector intended to be mounted in an injection system fixed to a combustion chamber casing of a turbomachine, such as an aircraft engine.
  • It relates more particularly to the structure of such an injector, and in particular the part of the structure dedicated to supplying the pilot and multipoint circuits and cooling the latter.
  • Fuel injectors called “multipoint” are new generation injectors that allow adaptation to different speeds of the turbomachine. Each injector is equipped with two fuel circuits: the so-called “pilot” which has a steady flow optimized for low speeds and the one called “multipoint” which has an intermittent flow optimized for high speeds.
  • the multipoint circuit is used when there is a need for additional engine thrust, especially in the cruising and take-off phases of aircraft.
  • the intermittent operation of the multipoint circuit has the major disadvantage of inducing, under the effect of high temperatures, a decomposition otherwise known as coking of the stagnant fuel inside the multipoint circuit when the flow of the latter is greatly reduced. even cut.
  • a decomposition otherwise known as coking of the stagnant fuel inside the multipoint circuit when the flow of the latter is greatly reduced. even cut.
  • the object of the invention is then to propose a new multipoint injector structure making it possible to obtain homogeneous cooling of the stagnant fuel inside the multipoint circuit.
  • the intake chamber is arranged on a sector angular diametrically opposed to the angular sector into which the flow channels in the baffles.
  • the intake chamber is arranged at least partly according to the diameter of the ferrule passing through the multi-point traffic channel.
  • the multipoint fuel flow is homogeneous.
  • the first and second ferrules each comprise a one-piece piece machined with at least one in the form of a first hollow cylindrical crown, the baffles being constituted by said first hollow cylindrical crown and a second cylindrical crown housed at the inside and soldered to the first and whose base is pierced with channels opposite the multipoint channels, in order to control the cooling / supply flow rate in the pilot injection channels.
  • the baffles were made by machining essentially electroerosion directly and partially in one two monobloc ferrules. However, this direct machining in a one-piece part does not allow for grooves of low height, that is to say, baffles of low height.
  • the sections of the baffles and therefore directly machined circuits monobloc can not be adapted to the desired flow rates and speeds.
  • Machine two cylindrical hollow crowns of different section and then lodge one in the other and finally braze together to obtain sections of very precise dimensions.
  • they can be easily adapted to the desired flow rates and / or fuel speeds. It is also possible to use conventional machining techniques without using EDM machining.
  • the inlet chamber is formed in the first ferrule and communicates with the nozzle through a pipe not passing through the tendrils or any space separating them.
  • the pilot circuit is connected to the nozzle by the outside of the injection head. This eliminates the drilling of additional channels in the tendrils as currently performed. This also makes it possible to obtain new configurations of multi-point injector with fine tendrils and / or of multi-twist type, that is to say with several stages of tendrils. Indeed, in these injector configurations, the drilling of the tendrils or the crossing of several floors is impossible to achieve.
  • the pipe is connected on the one hand to the portion of the inlet chamber facing the opening portion of the peripheral baffles and on the other hand to the part of the hub of the stage of tendrils facing and communication with the jet housing.
  • the pipe is a U-shaped bent tube, one of whose branches connected to the hub of the stage of tendrils extends along the axis of the nozzle and the other of the branches connected parallel to the chamber intake extending parallel to the axis of the nozzle.
  • This provides a space-saving connection that does not interfere with the entry of air on the tendrils.
  • the implementation of a bent and brazed tube is also easy to perform and inexpensive.
  • the body of the distributor is pierced with four distinct channels, two of which each communicate with a pilot circulation channel of the first ferrule itself opening on the outer peripheral baffle and the other two each communicate with a pilot circulation channel of the first ferrule itself leading to the internal peripheral baffle.
  • the tendrils of each stage are tendrils arranged helically with respect to the axis of the injector and of constant thickness over the width of the stage.
  • two stages of tendrils nested one inside the other with the device itself encased in the inner opening of the second ferrule.
  • the invention also relates to a combustion chamber for a turbomachine comprising at least one multipoint injector as described above.
  • the invention also relates to a turbomachine comprising a combustion chamber to which is fixed an injector as described above, mounted in an injection system itself attached to the combustion chamber.
  • FIG. figure 1 A combustion chamber portion 1 of a turbomachine is shown in FIG. figure 1 .
  • the combustion chamber 1 usually comprises an outer wall 10, an inner wall 11, hooking flanges 10 and outer inner walls 11 (not shown) with the chamber casing C in a junction zone 12, a chamber fund 13 bolted or welded to the walls 10, 11, a deflector 14 to protect the chamber 13 of the radiation of the flames from combustion, various fairings monoblock or separate and finally a plurality of injection systems 2 in each of which is mounted an injector 3.
  • a revolution combustion chamber usually comprises a large number of injectors 3, generally 10 to 50, depending on the number of engine power to be supplied.
  • Each system injection 2 comprises a bowl 20 diverging towards the interior of the chamber for bursting the outgoing air and fuel mixture jet, a floating ring 21 for sliding the bowl 20 into the anchor sleeve 22, a or several tendrils 23 for introducing air with a gyration movement, an air-cooled collar 24 for thermally protecting the fastening system.
  • Each multipoint injector 3 essentially comprises a fuel supply arm 30, one or more stages of vortex 31 allowing, like the tendrils 23 of the injection system, to introduce air with a gyration movement, a nozzle of fuel 32 placed on the axis II 'of the injector 3 and a network 33 of n fuel injection orifices 330 pierced at the periphery of the injector 3 ( figure 1 ).
  • Each injector 3 is fixed to the chamber housing 10 and is mounted in an injection system 2 described above. More exactly, the supply arm 30 is fixed to the housing 10 in such a way that the network 33 of injection orifices 330 is mounted in the upstream part of the body of tendrils 23 ( figure 1 ).
  • a multipoint injector 3 comprises one or more bleed holes t for introducing air axially into the injection system 2.
  • a multipoint injector 3 is designed to have on the one hand a fuel nozzle 32 disposed along its axis which injects fuel at a steady flow, generally optimized for low speeds of the engine, and on the other hand multipoint ports 330 pierced at the periphery of the injector and injecting fuel at an intermittent flow for the high engine speeds, for example those required during takeoff of an aircraft equipped with the engine.
  • the fuel circuit provided to supply the nozzle 32 and called “pilot circuit” is also used to cool the fuel circuit provided to feed the multipoint ports 330 and called “multipoint circuit”. Indeed, since this multipoint circuit is intended to supply fuel intermittently, fuel stagnates inside it and a risk of coking or scrubbing of this stagnant fuel remains. Constantly cooling the multipoint circuit by the pilot circuit therefore aims to avoid any risk of coking fuel.
  • a multipoint injector 3 firstly comprises a fuel supply arm 30. It also comprises a first ferrule 34 comprising a connection portion 340 for housing an end of the arm 30 and a body portion 341 internally open O1, having an outer diameter D1, and pierced internally with fuel circulation channels 342 communicating with the supply arm 30. At least one stage of tendrils 31 is engaged in the opening of the body of the first ferrule. A jet fuel 32 is housed in a hub portion 310 of the vane stage 31, for injecting fuel from the interior of the circulation channels 342 of the first ferrule towards the axis I of the injection system.
  • the injector 3 finally comprises a second shell 35 which comprises a body portion 350 open internally 02, having an outer diameter D2 and whose periphery is pierced with multipoint channels 351 for injecting fuel to the periphery of the injection system.
  • the output ports 330 of the multipoint channels 351 constitute the multipoint network 33 of the injector.
  • the bodies 341, 350 of the first 34 and second ferrules are nested one inside the other so that their inner openings O1, 02 and outer diameters D1, D2 overlap each other at least partially. Their overlap delimits a hollow volume comprising at least three concentric baffles 36, of which the central 360 opens on the multipoint channels 351 and the other peripherals 361, 362 are adapted to circulate fuel around the central baffle 360 to cool the fuel supplying fuel. the multipoint channels 351 and then to supply the nozzle 32 ( Figure 2C ).
  • the baffles 361, 362 of the fuel pilot circuit are arranged concentrically with the central one 360 of the multipoint circuit in order to cool it as well as possible, and thus to avoid any risk of coking.
  • the central baffle 360 is discontinuous, the peripheral baffles 361, 362 communicate with each other by the discontinuity 3600 made in the central baffle 360, and the internal peripheral baffle 362 does not communicate with the circulation channels 342 pierced in the body of the first ferrule 34.
  • the outer peripheral baffle 361 communicates with a circulation channel 342 ( Figure 2A ) or two circulation channels 342 ( Figure 2B ).
  • the pilot fuel circulates within the inner peripheral baffle 362 from the circulation channel (s) 342 firstly into the outer peripheral baffle 361 and then through the discontinuity 3600.
  • the arrows, represented in Figures 2A and 2B , inside two peripheral cavities 361, 362 thus indicate the route of the pilot fuel before its circulation in the intake channel 310 drilled inside the stage of tendrils 31.
  • the pilot fuel circulating in the duct admission 310 arrives in the nozzle 32 ( Figure 2C ).
  • the three concentric baffles 360, 361, 362 are continuous over their entire circumference ( figures 3 and 3A ) and they each communicate with at least one separate circulation channel 342 ( figure 3C , 3D figures and 3E ).
  • the peripheral baffles 361, 362 open into a fuel intake chamber 37 diametrically opposed to the circulation channels 342 and which communicates with the nozzle 32 (FIG. figure 3B ).
  • the baffles 360, 361, 362 of both the pilot fuel circuit and the multipoint fuel system are concentric complete rings from which homogeneous cooling.
  • the baffles 360, 361, 362 do not communicate with each other, which simplifies their geometry. They can thus be produced by conventional machining.
  • the first 34 and second 35 rings are each constituted by a one-piece piece machined with the second 35 in the form of a first cylindrical ring hollow 350: the baffles 360, 361, 362 are thus constituted by the hollow cylindrical crown 350 and another hollow cylindrical crown 380 housed inside the ring 350 by being brazed therein.
  • the base 380a of this other hollow cylindrical crown 380 is pierced with channels 3800 facing the multipoint channels 351.
  • the ferrule 35 is a one-piece piece machined to form the hollow cylindrical ring 350
  • the other ring 380 is also a single piece 38 of suitable dimensions to be housed inside the large cylindrical ring hollow and machined.
  • the two bases 380a, 350 are soldered tightly together and then drilled simultaneously to obtain the multipoint injection channels 351, 3800.
  • a one-piece piece is produced comprising a large full cylindrical crown 343 and a small full cylindrical ring 344 projecting axially with respect to the large ring 343, the pilot circulation channels 342p and multipoint 342m are drilled in the solid cylindrical rings 343, 344 and then machined the diameters of the solid cylindrical rings 343, 344 drilled.
  • the first ferrule 34 is then engaged in the second ferrule 35 so as to overlap both between the large full and hollow crowns 343, 350 and between the small solid and hollow crowns 344, 380 and then brazing is carried out. sealing rings 343, 350, 344, 380 between them.
  • the inlet chamber 37 is formed in the first ferrule 34 and communicates with the nozzle 32 via a pipe 39 which does not pass through the stages of tendrils 31 or any space between the tendrils.
  • the peripheral pilot fuel circuit is connected to the axis II 'of the injector 3 by the outside of the injection head. Such a connection is advantageous because it can be obtained whatever the configuration of the tendrils 311, 311a (inclination, length, thickness, number of stages of tendrils ).
  • the pipe 39 is preferably connected on the one hand to the portion of the inlet chamber 37 facing the opening portion of the peripheral baffles 361, 362 ( figure 3B ) and on the other hand to the part of the hub of the stage 31 of tendrils opposite and in communication with the housing of the nozzle 32 ( figure 3A ).
  • the pipe 39 is a U-shaped bent tube, one of the branches 390 connected to the hub 310 of the stage 31 of tendrils extends along the axis II 'of the nozzle 32 and the other of the branches 391 connected parallel to the inlet chamber 37 extending parallel to the axis II 'of the nozzle 32.
  • the swirlers of each stage 31, 31a can thus be spirals 31 arranged helically with respect to the axis II 'of the injector and of constant thickness over the width of the stage and advantageously reduced to a minimum.
  • the injector 3 may comprise two stages 31, 31a of tendrils nested one inside the other with the peripheral device itself encased in the inner opening of the ferrule 35 ( figure 3 ).
  • a one-piece piece 4 forming a fuel distributor whose body 40 is brazed inside the connection 340 of the shell 34 and pierced with at least two separate channels 400, 401, 402, 403 each communicating with each other. a part with the inside of the arm 30 connected to the pilot supply circuit and secondly with at least one pilot circulation channel 342p pierced in the shell 34.
  • the distributor 4 also comprises a duct 41 which extends to the the interior of the arm 30 and which is connected on the one hand to the multipoint supply circuit and on the other hand with a multipoint circulation channel 342m pierced in the first ferrule 34.
  • the body 40 of the distributor 4 is pierced four separate channels 400, 401, 402, 403, two of which 400, 401 each communicate with a pilot circulation channel 342p of the first ferrule itself opening on the outer peripheral baffle 361 and both of which other 402, 403 each communicate with a pilot circulation channel 342p of the shell 34 itself opening on the internal peripheral baffle 362.
  • completely separate pilot supply channels 400, 401, 402, 403 are obtained for feeding the baffle external device 361 and partially joined to supply the inner peripheral baffle 362 by means of drilling a hole shaped "bean". This provides a set of duct 41 and supply channels 400, 401, 402, 403 made with minimal space.
  • a second shell 35 in the form of a single piece ( figure 3A ) in which are integrally formed venturis 500 and 501. This avoids so-called “aero” steps which are obstacles at the junction between two parts located in the air flow.
  • a ferrule without venturi is, of course, within the scope of 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)
  • Fuel-Injection Apparatus (AREA)
EP08161242.6A 2007-08-10 2008-07-28 Mehrpunkt-Einspritzer für Turbotriebwerk Active EP2026002B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0757025A FR2919898B1 (fr) 2007-08-10 2007-08-10 Injecteur multipoint pour turbomachine

Publications (2)

Publication Number Publication Date
EP2026002A1 true EP2026002A1 (de) 2009-02-18
EP2026002B1 EP2026002B1 (de) 2016-07-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08161242.6A Active EP2026002B1 (de) 2007-08-10 2008-07-28 Mehrpunkt-Einspritzer für Turbotriebwerk

Country Status (6)

Country Link
US (2) US8186163B2 (de)
EP (1) EP2026002B1 (de)
JP (1) JP5165495B2 (de)
CA (1) CA2638814C (de)
FR (1) FR2919898B1 (de)
RU (1) RU2477808C2 (de)

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EP2230458A1 (de) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Brenneranordnung für fluidische Brennstoffe und Verfahren zum Herstellen der Brenneranordnung
FR2951245A1 (fr) * 2009-10-13 2011-04-15 Snecma Dispositif d'injection multi-point pour une chambre de combustion de turbomachine
FR2951246A1 (fr) * 2009-10-13 2011-04-15 Snecma Injecteur multi-point pour une chambre de combustion de turbomachine
FR2952699A1 (fr) * 2009-11-18 2011-05-20 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection et de melange de deux carburants distincts
FR2958015A1 (fr) * 2010-03-24 2011-09-30 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant entre deux flux d'air coaxiaux
FR2971038A1 (fr) * 2011-01-31 2012-08-03 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
EP2489939A1 (de) * 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Brennkammer mit einem Wandabschnitt und einem Randelement
WO2015025109A1 (fr) 2013-08-20 2015-02-26 Snecma Procédé et système d'injection de carburant dans une chambre de combustion d'un moteur
FR3010139A1 (fr) * 2013-09-04 2015-03-06 Snecma Dispositif et procede d'estimation de colmatage dans un systeme d'injection de carburant dans une chambre de combustion d'un moteur
FR3017416A1 (fr) * 2014-02-12 2015-08-14 Snecma Refroidissement d'une canalisation principale dans un systeme carburant a injection multipoints
WO2018060590A1 (fr) 2016-09-29 2018-04-05 Safran Helicopter Engines Dispositif d'alimentation en carburant d'une chambre de combustion de turbomachine améliorant l'homogénéité de l'alimentation des dispositifs d'injection du carburant
FR3118791A1 (fr) * 2021-01-14 2022-07-15 Safran Aircraft Engines Système et procédé d’alimentation en carburant d’une chambre de combustion dans un turbomoteur d’aéronef

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US9151227B2 (en) 2010-11-10 2015-10-06 Solar Turbines Incorporated End-fed liquid fuel gallery for a gas turbine fuel injector
US9188063B2 (en) 2011-11-03 2015-11-17 Delavan Inc. Injectors for multipoint injection
US9316154B2 (en) * 2013-03-07 2016-04-19 Solar Turbines Incorporated Gas turbine fuel injector with metering cavity
US9920693B2 (en) 2013-03-14 2018-03-20 United Technologies Corporation Hollow-wall heat shield for fuel injector component
FR3003632B1 (fr) 2013-03-19 2016-10-14 Snecma Systeme d'injection pour chambre de combustion de turbomachine comportant une paroi annulaire a profil interne convergent
US9366190B2 (en) * 2013-05-13 2016-06-14 Solar Turbines Incorporated Tapered gas turbine engine liquid gallery
US9556795B2 (en) * 2013-09-06 2017-01-31 Delavan Inc Integrated heat shield
US9447976B2 (en) * 2014-01-10 2016-09-20 Solar Turbines Incorporated Fuel injector with a diffusing main gas passage
JP6535442B2 (ja) 2014-08-18 2019-06-26 川崎重工業株式会社 燃料噴射装置
US9897321B2 (en) 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles
US10876477B2 (en) 2016-09-16 2020-12-29 Delavan Inc Nozzles with internal manifolding
US11466620B2 (en) * 2017-10-20 2022-10-11 Siemens Energy, Inc. Hybrid manufacturing of a support housing
FR3091574B1 (fr) * 2019-01-08 2020-12-11 Safran Aircraft Engines Systeme d’injection pour turbomachine, comprenant une vrille et des trous tourbillonnaires de bol melangeur
CN112082174B (zh) * 2019-06-12 2022-02-25 中国航发商用航空发动机有限责任公司 燃油喷嘴、燃烧室、燃气轮机以及防止燃油喷嘴内燃油结焦的方法
GB201910284D0 (en) 2019-07-18 2019-09-04 Rolls Royce Plc Fuel injector
CN112590222B (zh) * 2020-11-27 2022-12-02 江苏神力医用制品有限公司 一种注射器的自动化制造设备
CN114754378B (zh) * 2022-06-13 2022-08-19 成都中科翼能科技有限公司 一种燃气轮机燃烧器结构

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FR2896031B1 (fr) * 2006-01-09 2008-04-18 Snecma Sa Dispositif d'injection multimode pour chambre de combustion, notamment d'un turboreacteur
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EP1806536A1 (de) * 2006-01-09 2007-07-11 Snecma Kühlung einer multimodalen Einspritzvorrichtung für eine Brennkammer, insbesondere für eine Gasturbine

Cited By (34)

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CN102159890A (zh) * 2009-03-17 2011-08-17 西门子公司 流体燃料燃烧器装置和制造燃烧器装置的方法
WO2010105956A1 (de) * 2009-03-17 2010-09-23 Siemens Aktiengesellschaft Brenneranordnung für fluidische brennstoffe und verfahren zum herstellen der brenneranordnung
EP2230458A1 (de) * 2009-03-17 2010-09-22 Siemens Aktiengesellschaft Brenneranordnung für fluidische Brennstoffe und Verfahren zum Herstellen der Brenneranordnung
RU2523517C2 (ru) * 2009-03-17 2014-07-20 Сименс Акциенгезелльшафт Устройство горелки для текучего топлива и способ изготовления устройства горелки
CN102159890B (zh) * 2009-03-17 2013-02-13 西门子公司 流体燃料燃烧器装置和制造燃烧器装置的方法
US9046271B2 (en) 2009-10-13 2015-06-02 Snecma Multipoint injector for a turbine engine combustion chamber
CN102575844B (zh) * 2009-10-13 2014-12-31 斯奈克玛 用于涡轮发动机的燃烧室的多点喷射器
WO2011045503A1 (fr) 2009-10-13 2011-04-21 Snecma Dispositif d'injection multi-point pour une chambre de combustion de turbomachine
FR2951245A1 (fr) * 2009-10-13 2011-04-15 Snecma Dispositif d'injection multi-point pour une chambre de combustion de turbomachine
CN102575843A (zh) * 2009-10-13 2012-07-11 斯奈克玛 用于涡轮发动机燃烧室的多点喷油装置
CN102575844A (zh) * 2009-10-13 2012-07-11 斯奈克玛 用于涡轮发动机的燃烧室的多点喷射器
RU2543097C2 (ru) * 2009-10-13 2015-02-27 Снекма Многоточечный инжектор для камеры сгорания турбомашины
RU2539223C2 (ru) * 2009-10-13 2015-01-20 Снекма Устройство многоточечного впрыска для камеры сгорания турбомашины
US9003802B2 (en) 2009-10-13 2015-04-14 Snecma Multipoint injection device for a combustion chamber of a turbine engine
FR2951246A1 (fr) * 2009-10-13 2011-04-15 Snecma Injecteur multi-point pour une chambre de combustion de turbomachine
WO2011045486A1 (fr) 2009-10-13 2011-04-21 Snecma Injecteur multi-point pour une chambre de combustion de turbomachine
FR2952699A1 (fr) * 2009-11-18 2011-05-20 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection et de melange de deux carburants distincts
FR2958015A1 (fr) * 2010-03-24 2011-09-30 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant entre deux flux d'air coaxiaux
WO2012104523A3 (fr) * 2011-01-31 2013-01-03 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
RU2583486C2 (ru) * 2011-01-31 2016-05-10 Снекма Устройство впрыска для камеры сгорания турбомашины
US9605594B2 (en) 2011-01-31 2017-03-28 Snecma Injection device for a turbine engine combustion chamber
WO2012104523A2 (fr) 2011-01-31 2012-08-09 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
FR2971038A1 (fr) * 2011-01-31 2012-08-03 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
US9316398B2 (en) 2011-02-18 2016-04-19 Siemens Aktiengesellschaft Combustion chamber with a wall section and a brim element
WO2012110315A1 (en) * 2011-02-18 2012-08-23 Siemens Aktiengesellschaft Combustion chamber with a wall section and a brim element
EP2489939A1 (de) * 2011-02-18 2012-08-22 Siemens Aktiengesellschaft Brennkammer mit einem Wandabschnitt und einem Randelement
WO2015025109A1 (fr) 2013-08-20 2015-02-26 Snecma Procédé et système d'injection de carburant dans une chambre de combustion d'un moteur
US10072578B2 (en) 2013-08-20 2018-09-11 Safran Aircraft Engines Method and system for injecting fuel into an engine combustion chamber
FR3010139A1 (fr) * 2013-09-04 2015-03-06 Snecma Dispositif et procede d'estimation de colmatage dans un systeme d'injection de carburant dans une chambre de combustion d'un moteur
FR3017416A1 (fr) * 2014-02-12 2015-08-14 Snecma Refroidissement d'une canalisation principale dans un systeme carburant a injection multipoints
WO2015121580A1 (fr) * 2014-02-12 2015-08-20 Snecma Refroidissement d'une canalisation principale dans un système carburant à injection multipoints
WO2018060590A1 (fr) 2016-09-29 2018-04-05 Safran Helicopter Engines Dispositif d'alimentation en carburant d'une chambre de combustion de turbomachine améliorant l'homogénéité de l'alimentation des dispositifs d'injection du carburant
FR3118791A1 (fr) * 2021-01-14 2022-07-15 Safran Aircraft Engines Système et procédé d’alimentation en carburant d’une chambre de combustion dans un turbomoteur d’aéronef
WO2022152621A1 (fr) * 2021-01-14 2022-07-21 Safran Aircraft Engines Système et procédé d'alimentation en carburant d'une chambre de combustion dans un turbomoteur d'aéronef

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FR2919898B1 (fr) 2014-08-22
RU2008132887A (ru) 2010-02-20
CA2638814A1 (fr) 2009-02-10
US8959772B2 (en) 2015-02-24
FR2919898A1 (fr) 2009-02-13
US20120186083A1 (en) 2012-07-26
CA2638814C (fr) 2015-11-03
US20090038312A1 (en) 2009-02-12
RU2477808C2 (ru) 2013-03-20
US8186163B2 (en) 2012-05-29
JP5165495B2 (ja) 2013-03-21
JP2009041903A (ja) 2009-02-26
EP2026002B1 (de) 2016-07-20

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