EP2671028B1 - Injector for the combustion chamber of a gas turbine having a dual fuel circuit, and combustion chamber provided with at least one such injector - Google Patents

Injector for the combustion chamber of a gas turbine having a dual fuel circuit, and combustion chamber provided with at least one such injector Download PDF

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Publication number
EP2671028B1
EP2671028B1 EP12706638.9A EP12706638A EP2671028B1 EP 2671028 B1 EP2671028 B1 EP 2671028B1 EP 12706638 A EP12706638 A EP 12706638A EP 2671028 B1 EP2671028 B1 EP 2671028B1
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EP
European Patent Office
Prior art keywords
circuit
injector
combustion chamber
injectors
fuel
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EP12706638.9A
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German (de)
French (fr)
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EP2671028A1 (en
Inventor
Bernard Joseph Jean-Pierre Carrere
Jean-Luc DABAT
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Safran Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Priority to PL12706638T priority Critical patent/PL2671028T3/en
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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
    • 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
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • 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
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
    • 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
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
    • 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

Definitions

  • the invention relates to a gas turbine combustion chamber injector, in particular a gas turbine engine, comprising a double fuel injection circuit.
  • the invention also relates to a combustion chamber equipped with at least one such dual circuit injector and single circuit injectors.
  • a mixture of compressed air and suitable fuel is generally injected into the combustion chamber using a plurality of injectors.
  • the injectors are mounted in the wall of a flame tube arranged, preferably at the bottom of the chamber. This makes it possible to homogeneously distribute the mixtures originating from the various injectors.
  • a nozzle introduces fuel at the end of a tubing.
  • the fuel is adjusted in a centering guide.
  • the air comes from the last stage of a compressor of the gas machine and is introduced into the injector annularly.
  • Air and fuel are typically introduced into contra-rotated channel swirlers or tendrils, and the fuel particles are sprayed into the air via a mixer.
  • the mixture ignited with a candle located at a certain distance, is burned in the chamber.
  • the generated gases then have a high kinetic energy, which is exploited to generate propulsion or mechanical energy.
  • the ignition of the chamber is provided by two injectors dedicated to start, each starter injector being associated with a candle.
  • the other injectors are dedicated to the post-start systems: transient acceleration or deceleration regimes and stabilized flight regimes.
  • This architecture requires the availability of specific starter injectors, and therefore an additional mass, specific mounting holes for these injectors on the flame tube that supports all the injectors, as well as the introduction of additional controls which result.
  • combustion chambers equipped with injectors having a dual fuel supply circuit, an auxiliary circuit and a main circuit.
  • the auxiliary circuit is dedicated to idle operation, that is to say at low load, while the main circuit or both circuits are solicited at intermediate speeds and stabilized. At full throttle, the ratio of flows between the two circuits is reversed and the main circuit becomes dominant or the sole supplier of fuel.
  • FR 2 906 868 or FR 2,896,030 filed in the name of the plaintiff.
  • Another double circuit injector is known from the patent US 7,513,116 .
  • the invention aims to remedy this problem, by proposing a starter injector that can also be used in all flight regimes without cost or additional mass. To do this, this starter injector has a particular configuration of dual fuel circuit and air circuit.
  • the present invention relates to a gas turbine combustion chamber injector, having a dual fuel injection circuit and an air circuit.
  • the fuel injection circuits consist of a starter fuel circuit, capable of triggering the ignition of the chamber and then operating in all flight regimes, and a main fuel circuit, able to operate in the engine. all the flight regimes after the start.
  • the fuel systems have parallel conduits formed in a common tube of longitudinal axis.
  • the conduit of the starting circuit opens, at one end, substantially in the center of a spherical injector body extending the common tube.
  • the duct houses an injection ramp capable of driving the fuel in rotation before projecting it inside the chamber by a central channel passing through a central swirling wall.
  • the conduit of the main circuit opens into an annular channel formed in the body facing nozzle channels arranged radially in the main wall around the central channel.
  • the air circuit is guided between two portions of concentric spheres constituted by the injector body and a sheath surrounding the injector body and having an opening through which the whirlpool opens.
  • the injector according to the invention has a greatly reduced size thanks to its doubly spherical architecture.
  • the central starting circuit is thermally protected from coking by the circulation of fuel in the annular channel of the main circuit.
  • the main circuit is itself thermally protected by the flow of peripheral air flowing in the inter-spherical space.
  • the swirler is in an inclined position with respect to the longitudinal axis of the injector. This inclination makes it possible to position the end of the starting circuit at the center of the latter and to orient the air and fuel jets in the direction of the candle arranged at the bottom of the chamber.
  • the invention also relates to a combustion chamber equipped with at least one double circuit injector presented above and single circuit injectors. All the injectors are mounted in alignment on the casing surrounding the combustion chamber and pass through a flame tube through orifices formed along at least one line parallel to the longitudinal axis of the flame tube.
  • the dual circuit injectors are directed towards the spark plug so that these injectors are able to project an air / fuel cone at the outlet of the whirlpool directed towards the bottom of the combustion chamber.
  • the combustion chamber is equipped with two non-adjacent dual circuit injectors on the injector line.
  • an injector 1 comprises a fastening flange 10 on a casing 2 of the annular combustion chamber 3, a common shaft tube 11 X'X longitudinal reference of the injector, and a circular swirl 4 central wall 14 and axis of symmetry Y'Y inclined relative to the axis X'X.
  • This central wall 14 allows to project, through the opening 15 of a sleeve 5, an air / fuel mixture in a flame tube 6 which bears on the sleeve 5.
  • the swirl 4 is dimensioned so that the fins 40 of this whirlpool, regularly distributed around the periphery of the central wall 14, support in a self-adjusting and self-centering manner on the edge of the opening 15.
  • the dual fuel injection circuit consists of a starting fuel circuit C1, able to trigger the ignition of the chamber 3 and to operate in all flight regimes, and a main fuel circuit C2, able to work in all flight regimes after starting.
  • the circuits C1 and C2 are coupled to fuel supply pipes (not shown). These circuits consist of access bores 2a, 2b formed in the fastening flange 10, in connection with parallel longitudinal conduits, respectively 12a and 12b, extending in the tube 11 bearing on sealing sleeves 13a and 13b housed in this tube. These ducts extend in the tube 11 parallel to the longitudinal axis X'X and open into the combustion chamber 3 through the central wall 14.
  • the conduit 12a opens - at one end 12e - substantially in the center of a hemispherical injector body 11s in extension of the tube 11.
  • the conduit 12a houses - in a recess cylindrical 21 inclined axis coincides with the Y'Y axis of the whirlpool 4 - a helical fuel rail 7.
  • the recess 21 has a conical end 21c coupled through the central wall 14 of the whirlpool 4, to a central channel 41 of axis coincides with the Y'Y axis of the whirlpool 4 or the recess 21. This central channel 41 opens into the combustion chamber 3.
  • a nozzle 8 is advantageously mounted in the access bore 2b of the flange 10. This nozzle makes it possible to calibrate the fuel flow which varies according to the flight phases.
  • the longitudinal duct 12b is oriented in a final portion 12f parallel to the axis Y'Y and opens into an annular channel 16 formed in the spherical body 11s.
  • This annular channel 16 advantageously has two ends 16e. In other words, this channel is not looped on itself. Thus, no "dead" zone where fuel could stagnate is formed.
  • the annular channel 16 is brazed to the central wall by means of a suitable solder 20 which reveals the non-looped shape of the annular channel 16.
  • This annular channel 16 communicates with nozzle channels 42 arranged radially and distributed equidistantly around of the central channel 41.
  • these nozzle channels have the same diameter.
  • the radial channels 42 advantageously have an orientation along axes K'K symmetrically inclined with respect to the axis Y'Y of the central channel 41 (see in particular the figure 1b ), and contra-rotation relative to the inclination of the vanes 40 of the swirler 4.
  • the number of radial channels 42 is equal to a multiple of the number of vanes 40 of the swirler 4.
  • the inlet air flow F E - from the last compression stage - passes through openings 170 formed in a flared lid 17 extending the tube 11, and is then guided in an air circuit C3 circulating in a space inter-spherical "E".
  • This space "E” is formed between two portions of concentric spheres formed by the injector body 11s and partially by the sleeve 5 in a spherical portion 5s enveloping the injector body 11s.
  • the sheath also has a cylindrical portion with a circular section 5c, which makes it possible to provide support for the flame tube 6 and the flared lid 17 of the tube 11.
  • the injector according to the invention has a minimum space requirement thanks to this interpass. -spherical.
  • the central starting circuit C1 is thermally protected from coking by the circulation of the fuel in the annular channel 16 of the main circuit C2, this main circuit being itself thermally protected by the flow of peripheral air F flowing in the inter-spherical space "E" of the air circuit C3.
  • the air flow F S advantageously forms, passing between the fins 40, an air cone Ca enclosing the fuel outlet cone Cs of the main circuit C2.
  • the tube 11 'does not have a flared lid 17 to form the openings 170 for access to the air flow F E in the circuit C3.
  • the tube 11 ' is extended directly by the spherical body 11s.
  • the conical end portion 21c of the recess 21 passes through the central wall 14 of the swirler 4 and acts as a central channel 41.
  • the partial perspective view illustrates the combustion chamber 3 equipped with injectors mounted on the wall of the flame tube 6: two double circuit injectors 1 shown above and seven single circuit injectors 100.
  • the chamber is partially cut to to show some injectors in full and the candle 101 on the side of the bottom 3f of the chamber.
  • All the injectors 1, 100 are regularly mounted on the annular periphery of the chamber 3. Orifices 60 were made in the tube 6 to enclose the sleeves 5 of the injectors 1, 100.
  • the dual circuit injectors 1 are oriented towards the spark plug 101. Thanks to the inclined orientation of the nozzle channels 42 and the central channels 41, the dual circuit injectors 1 are able to project air / fuel cones Ca / Cs at the outlet of the swirlers to the bottom 3f of the combustion chamber 3. After ignition, the flame goes to the bottom 3f, turns and emerges through the opposite outlet 3s.
  • the two dual circuit injectors 1 are separated by a single circuit injector 100 so as to facilitate the orientation of the dual circuit injectors 1 towards the candle 101.
  • the body of the injector may form a more or less complete sphere part depending on the opening size or the diameter of the common tube. It is also possible to form several lines of injectors in the flame tube.

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention concerne un injecteur de chambre de combustion de turbine à gaz, en particulier de turbomoteur, comportant un double circuit d'injection de carburant. L'invention concerne également une chambre de combustion équipée d'au moins un tel injecteur à double circuit et d'injecteurs à simple circuit.The invention relates to a gas turbine combustion chamber injector, in particular a gas turbine engine, comprising a double fuel injection circuit. The invention also relates to a combustion chamber equipped with at least one such dual circuit injector and single circuit injectors.

Un mélange d'air comprimé et de carburant approprié est en général injecté dans la chambre de combustion à l'aide d'une pluralité d'injecteurs. Les injecteurs sont montés dans la paroi d'un tube à flamme agencé, de préférence, en fond de chambre. Ceci permet de répartir de manière homogène les mélanges provenant des différents injecteurs.A mixture of compressed air and suitable fuel is generally injected into the combustion chamber using a plurality of injectors. The injectors are mounted in the wall of a flame tube arranged, preferably at the bottom of the chamber. This makes it possible to homogeneously distribute the mixtures originating from the various injectors.

Dans chaque injecteur, un gicleur introduit du carburant à l'extrémité d'une tubulure. Le carburant est ajusté dans un guide de centrage. L'air provient du dernier étage d'un compresseur de la machine à gaz et est introduit dans l'injecteur de manière annulaire. L'air et le carburant sont en général introduits dans des tourbillonneurs à canaux orientés en contra-rotation ou des vrilles, puis les particules de carburant sont pulvérisées dans l'air via un mélangeur. Le mélange, enflammé à l'aide d'une bougie située à une distance déterminée, est brûlé dans la chambre. Les gaz générés possèdent alors une haute énergie cinétique, qui est exploitée pour générer de la propulsion ou de l'énergie mécanique.In each injector, a nozzle introduces fuel at the end of a tubing. The fuel is adjusted in a centering guide. The air comes from the last stage of a compressor of the gas machine and is introduced into the injector annularly. Air and fuel are typically introduced into contra-rotated channel swirlers or tendrils, and the fuel particles are sprayed into the air via a mixer. The mixture, ignited with a candle located at a certain distance, is burned in the chamber. The generated gases then have a high kinetic energy, which is exploited to generate propulsion or mechanical energy.

ETAT DE LA TECHNIQUESTATE OF THE ART

De nos jours, l'allumage de la chambre est assuré par deux injecteurs dédiés au démarrage, chaque injecteur de démarrage étant associé à une bougie. Les autres injecteurs sont dédiés aux régimes post démarrage : régimes transitoires d'accélération ou décélération et régimes stabilisés en vol. Cette architecture nécessite de disposer d'injecteurs de démarrage spécifiques, et donc une masse supplémentaire, des orifices de montage spécifiques pour ces injecteurs sur le tube à flamme qui supporte l'ensemble des injecteurs, ainsi que la mise en place de contrôles supplémentaires qui en résultent.Nowadays, the ignition of the chamber is provided by two injectors dedicated to start, each starter injector being associated with a candle. The other injectors are dedicated to the post-start systems: transient acceleration or deceleration regimes and stabilized flight regimes. This architecture requires the availability of specific starter injectors, and therefore an additional mass, specific mounting holes for these injectors on the flame tube that supports all the injectors, as well as the introduction of additional controls which result.

Il existe par ailleurs des chambres de combustion équipées d'injecteurs ayant un double circuit d'alimentation en carburant, un circuit auxiliaire et un circuit principale. Le circuit auxiliaire est dédié au fonctionnement au ralenti, c'est-à-dire à faible charge, alors que le circuit principal ou les deux circuits sont sollicités aux régimes intermédiaires et stabilisés. Au régime plein gaz, le rapport des débits entre les deux circuits s'inversent et le circuit principal devient prépondérant ou l'unique fournisseur de carburant. Une telle répartition est décrite par exemple dans le document de brevet FR 2 906 868 ou FR 2 896 030 , déposés au nom de la demanderesse. Un autre injecteur à double circuit est connu du brevet US 7 513 116 .There are also combustion chambers equipped with injectors having a dual fuel supply circuit, an auxiliary circuit and a main circuit. The auxiliary circuit is dedicated to idle operation, that is to say at low load, while the main circuit or both circuits are solicited at intermediate speeds and stabilized. At full throttle, the ratio of flows between the two circuits is reversed and the main circuit becomes dominant or the sole supplier of fuel. Such a distribution is described for example in the patent document FR 2 906 868 or FR 2,896,030 , filed in the name of the plaintiff. Another double circuit injector is known from the patent US 7,513,116 .

Cependant ces injecteurs à double circuit ne sont pas adaptés pour être utilisés en phase de démarrage car leur structure ne permet pas d'éjection de mélange à vitesse élevée au démarrage. C'est pourquoi la présence d'injecteurs spécifiques perdure avec les inconvénients cités plus haut.However these dual circuit injectors are not suitable for use in the start-up phase because their structure does not allow high speed mixing ejection at startup. This is why the presence of specific injectors continues with the disadvantages mentioned above.

EXPOSE DE L'INVENTIONSUMMARY OF THE INVENTION

L'invention vise à remédier à ce problème, en proposant un injecteur de démarrage qui puisse également être utilisé dans tous les régimes de vol sans coût ni masse supplémentaire. Pour ce faire, cet injecteur de démarrage possède une configuration particulière de double circuit de carburant et de circuit d'air.The invention aims to remedy this problem, by proposing a starter injector that can also be used in all flight regimes without cost or additional mass. To do this, this starter injector has a particular configuration of dual fuel circuit and air circuit.

Plus précisément, la présente invention a pour objet un injecteur de chambre de combustion de turbine à gaz, comportant un double circuit d'injection de carburant et un circuit d'air. Les circuits d'injection de carburant se composent d'un circuit de carburant de démarrage, apte à déclencher l'allumage de la chambre puis à fonctionner dans tous les régimes de vol, et d'un circuit de carburant principal, apte à fonctionner dans tous les régimes de vol suite au démarrage. Les circuits de carburant ont des conduits parallèles formés dans un tube commun d'axe longitudinal. Le conduit du circuit de démarrage débouche, en une extrémité, sensiblement au centre d'un corps d'injecteur sphérique prolongeant le tube commun. En cette extrémité, le conduit loge une rampe d'injection apte à entraîner le carburant en rotation avant de le projeter à l'intérieur de la chambre par un canal central traversant une paroi centrale de tourbillonneur. Le conduit du circuit principal débouche dans un canal annulaire formé dans le corps en regard de canaux gicleurs agencés radialement dans la paroi principale autour du canal central. Le circuit d'air est guidé entre deux portions de sphères concentriques constituées par le corps d'injecteur et un fourreau enveloppant le corps d'injecteur et présentant une ouverture par laquelle débouche le tourbillonneur.More specifically, the present invention relates to a gas turbine combustion chamber injector, having a dual fuel injection circuit and an air circuit. The fuel injection circuits consist of a starter fuel circuit, capable of triggering the ignition of the chamber and then operating in all flight regimes, and a main fuel circuit, able to operate in the engine. all the flight regimes after the start. The fuel systems have parallel conduits formed in a common tube of longitudinal axis. The conduit of the starting circuit opens, at one end, substantially in the center of a spherical injector body extending the common tube. At this end, the duct houses an injection ramp capable of driving the fuel in rotation before projecting it inside the chamber by a central channel passing through a central swirling wall. The conduit of the main circuit opens into an annular channel formed in the body facing nozzle channels arranged radially in the main wall around the central channel. The air circuit is guided between two portions of concentric spheres constituted by the injector body and a sheath surrounding the injector body and having an opening through which the whirlpool opens.

Ainsi l'injecteur selon l'invention présente un encombrement fortement réduit grâce à son architecture doublement sphérique.Thus the injector according to the invention has a greatly reduced size thanks to its doubly spherical architecture.

De plus, le circuit de démarrage central est thermiquement protégé de la cokéfaction par la circulation du carburant dans le canal annulaire du circuit principal. Le circuit principal est lui-même thermiquement protégé par le flux d'air périphérique circulant dans l'espace inter-sphérique.In addition, the central starting circuit is thermally protected from coking by the circulation of fuel in the annular channel of the main circuit. The main circuit is itself thermally protected by the flow of peripheral air flowing in the inter-spherical space.

Avantageusement, le tourbillonneur est en position inclinée par rapport à l'axe longitudinal de l'injecteur. Cette inclinaison permet de positionner l'extrémité du circuit de démarrage au centre de celui-ci et d'orienter les jets d'air et de carburant en direction de la bougie agencée en fond de chambre.Advantageously, the swirler is in an inclined position with respect to the longitudinal axis of the injector. This inclination makes it possible to position the end of the starting circuit at the center of the latter and to orient the air and fuel jets in the direction of the candle arranged at the bottom of the chamber.

Selon des formes de réalisation particulières :

  • le conduit de carburant du circuit de démarrage présente en son extrémité un évidement cylindrique pour loger la rampe ;
  • le canal central est de forme conique se rétrécissant vers l'intérieur de la chambre de combustion dans laquelle il débouche ;
  • les canaux radiaux présentent une orientation inclinée par rapport à l'axe du canal central et en contra-rotation par rapport à l'inclinaison des ailettes du tourbillonneur ; le flux d'air en sortie d'injecteur forme alors un cône d'air enveloppant le cône de carburant du circuit principal ;
  • la rampe d'injection du circuit de démarrage est hélicoïdale ;
  • le canal annulaire du circuit de carburant principal n'est pas bouclé sur lui-même et présente des extrémités afin de ne pas former de zone « morte » où le carburant pourrait stagner ;
  • le nombre de canaux radiaux est égal à un multiple du nombre d'ailettes du tourbillonneur.
According to particular embodiments:
  • the fuel line of the starting circuit has at its end a cylindrical recess for accommodating the ramp;
  • the central channel is conical in shape narrowing towards the inside of the combustion chamber in which it opens;
  • the radial channels have an inclined orientation relative to the axis of the central channel and contra-rotation relative to the inclination of the vanes of the whirlpool; the air flow at the injector outlet then forms an air cone enveloping the fuel cone of the main circuit;
  • the injection circuit of the starting circuit is helical;
  • the annular channel of the main fuel circuit is not looped on itself and has ends so as not to form a "dead" zone where the fuel could stagnate;
  • the number of radial channels is equal to a multiple of the number of vanes of the whirlpool.

L'invention se rapport également à une chambre de combustion équipée d'au moins un injecteur à double circuit présenté ci-dessus et d'injecteurs à simple circuit. Tous les injecteurs sont montés en alignement sur le carter enveloppant la chambre de combustion et traversent un tube à flamme par des orifices formés le long d'au moins une ligne parallèle à l'axe longitudinal du tube à flamme.The invention also relates to a combustion chamber equipped with at least one double circuit injector presented above and single circuit injectors. All the injectors are mounted in alignment on the casing surrounding the combustion chamber and pass through a flame tube through orifices formed along at least one line parallel to the longitudinal axis of the flame tube.

Les injecteurs à double circuit sont orientés vers la bougie d'allumage de sorte que ces injecteurs sont aptes à projeter un cône air/carburant en sortie du tourbillonneur dirigé vers le fond de la chambre de combustion.The dual circuit injectors are directed towards the spark plug so that these injectors are able to project an air / fuel cone at the outlet of the whirlpool directed towards the bottom of the combustion chamber.

Dans un mode de réalisation préféré, la chambre de combustion est équipée de deux injecteurs à double circuit non adjacents sur la lignée d'injecteurs.In a preferred embodiment, the combustion chamber is equipped with two non-adjacent dual circuit injectors on the injector line.

BRÈVE DESCRIPTION DES FIGURESBRIEF DESCRIPTION OF THE FIGURES

D'autres caractéristiques et avantages de la présente invention apparaîtront à la lecture de l'exemple détaillé de réalisation qui suit, en référence aux figures annexées qui représentent, respectivement :

  • les figures 1a et 1b, une vue éclatée et une vue en coupe d'un exemple d'injecteur à double circuit selon l'invention,
  • les figures 2a et 2b, une vue en perspective et une vue en coupe d'une variante de l'exemple précédent ; et
  • la figure 3, une vue en perspective partielle d'une chambre de combustion équipée d'injecteurs à double circuit présentés ci-dessus et d'injecteurs à simple circuit.
Other characteristics and advantages of the present invention will become apparent on reading the detailed embodiment example which follows, with reference to the appended figures which represent, respectively:
  • the Figures 1a and 1b an exploded view and a sectional view of an exemplary dual circuit injector according to the invention,
  • the Figures 2a and 2b , a perspective view and a sectional view of a variant of the previous example; and
  • the figure 3 , a partial perspective view of a combustion chamber equipped with dual circuit injectors presented above and single circuit injectors.

DESCRIPTION DÉTAILLÉEDETAILED DESCRIPTION

En référence à la vue éclatée et à la vue en coupe des figures respectives 1a et 1b, un injecteur 1 selon l'invention comporte une bride de fixation 10 sur un carter 2 de chambre de combustion annulaire 3, un tube commun 11 d'axe longitudinal X'X de référence de l'injecteur, et un tourbillonneur circulaire 4 de paroi centrale 14 et d'axe de symétrie Y'Y incliné par rapport à l'axe X'X. Cette paroi centrale 14 permet de projeter, à travers l'ouverture 15 d'un fourreau 5, un mélange air/carburant dans un tube à flamme 6 qui prend appui sur le fourreau 5. Le tourbillonneur 4 est dimensionné de sorte que les ailettes 40 de ce tourbillonneur, régulièrement réparties en périphérie de la paroi centrale 14, prennent appui de manière auto-ajustée et autocentrée sur le bord de l'ouverture 15.Referring to the exploded view and the sectional view of the respective figures 1a and 1b, an injector 1 according to the invention comprises a fastening flange 10 on a casing 2 of the annular combustion chamber 3, a common shaft tube 11 X'X longitudinal reference of the injector, and a circular swirl 4 central wall 14 and axis of symmetry Y'Y inclined relative to the axis X'X. This central wall 14 allows to project, through the opening 15 of a sleeve 5, an air / fuel mixture in a flame tube 6 which bears on the sleeve 5. The swirl 4 is dimensioned so that the fins 40 of this whirlpool, regularly distributed around the periphery of the central wall 14, support in a self-adjusting and self-centering manner on the edge of the opening 15.

Le double circuit d'injection de carburant se compose d'un circuit de carburant de démarrage C1, apte à déclencher l'allumage de la chambre 3 et à fonctionner dans tous les régimes de vol, et d'un circuit de carburant principal C2, apte à fonctionner dans tous les régimes de vol suite au démarrage.The dual fuel injection circuit consists of a starting fuel circuit C1, able to trigger the ignition of the chamber 3 and to operate in all flight regimes, and a main fuel circuit C2, able to work in all flight regimes after starting.

Les circuits C1 et C2 sont couplés à des tubulures d'alimentation en carburant (non représentés). Ces circuits sont constitués d'alésages d'accès 2a, 2b formés dans la bride de fixation 10, en liaison avec des conduits longitudinaux parallèles, respectivement 12a et 12b, s'étendant dans le tube 11 en appui sur des douilles d'étanchéité 13a et 13b logées dans ce tube. Ces conduits s'étendent dans le tube 11 parallèlement à l'axe longitudinal X'X et débouchent dans la chambre de combustion 3 par la paroi centrale 14.The circuits C1 and C2 are coupled to fuel supply pipes (not shown). These circuits consist of access bores 2a, 2b formed in the fastening flange 10, in connection with parallel longitudinal conduits, respectively 12a and 12b, extending in the tube 11 bearing on sealing sleeves 13a and 13b housed in this tube. These ducts extend in the tube 11 parallel to the longitudinal axis X'X and open into the combustion chamber 3 through the central wall 14.

Concernant le circuit de démarrage C1, le conduit 12a débouche - en une extrémité 12e - sensiblement au centre d'un corps d'injecteur hémisphérique 11s en prolongement du tube 11. De plus, à cette extrémité, le conduit 12a loge - dans un évidement cylindrique 21 d'axe incliné confondu avec l'axe Y'Y du tourbillonneur 4 - une rampe hélicoïdale de carburant 7. Avantageusement, l'évidement 21 présente une extrémité conique 21c couplée, à travers la paroi centrale 14 du tourbillonneur 4, à un canal central 41 d'axe confondu avec l'axe Y'Y du tourbillonneur 4 ou de l'évidement 21. Ce canal central 41 débouche dans la chambre de combustion 3.Regarding the starting circuit C1, the conduit 12a opens - at one end 12e - substantially in the center of a hemispherical injector body 11s in extension of the tube 11. In addition, at this end, the conduit 12a houses - in a recess cylindrical 21 inclined axis coincides with the Y'Y axis of the whirlpool 4 - a helical fuel rail 7. Advantageously, the recess 21 has a conical end 21c coupled through the central wall 14 of the whirlpool 4, to a central channel 41 of axis coincides with the Y'Y axis of the whirlpool 4 or the recess 21. This central channel 41 opens into the combustion chamber 3.

Concernant le circuit principal C2, un gicleur 8 est avantageusement monté dans l'alésage d'accès 2b de la bride 10. Ce gicleur permet de calibrer le débit de carburant qui varie suivant les phases de vol. Après un coude 12c, le conduit longitudinal 12b est orienté dans une portion finale 12f parallèlement à l'axe Y'Y et débouche dans un canal annulaire 16 réalisé dans le corps sphérique 11s. Ce canal annulaire 16 présente avantageusement deux extrémités 16e. En d'autres termes, ce canal n'est pas bouclé sur lui-même. Ainsi, aucune zone « morte » où le carburant pourrait stagner ne se forme.Concerning the main circuit C2, a nozzle 8 is advantageously mounted in the access bore 2b of the flange 10. This nozzle makes it possible to calibrate the fuel flow which varies according to the flight phases. After a bend 12c, the longitudinal duct 12b is oriented in a final portion 12f parallel to the axis Y'Y and opens into an annular channel 16 formed in the spherical body 11s. This annular channel 16 advantageously has two ends 16e. In other words, this channel is not looped on itself. Thus, no "dead" zone where fuel could stagnate is formed.

Le canal annulaire 16 est brasé sur la paroi centrale à l'aide d'une brasure appropriée 20 qui laisse apparaître la forme non bouclée du canal annulaire 16. Ce canal annulaire 16 communique avec des canaux gicleurs 42 agencés radialement et répartis de manière équidistante autour du canal central 41. Avantageusement, ces canaux gicleurs ont le même diamètre. Les canaux radiaux 42 présentent avantageusement une orientation selon des axes K'K symétriquement inclinés par rapport à l'axe Y'Y du canal central 41 (voir en particulier la figure 1b), et en contra-rotation par rapport à l'inclinaison des ailettes 40 du tourbillonneur 4. Avantageusement, le nombre de canaux radiaux 42 est égal à un multiple du nombre d'ailettes 40 du tourbillonneur 4.The annular channel 16 is brazed to the central wall by means of a suitable solder 20 which reveals the non-looped shape of the annular channel 16. This annular channel 16 communicates with nozzle channels 42 arranged radially and distributed equidistantly around of the central channel 41. Advantageously, these nozzle channels have the same diameter. The radial channels 42 advantageously have an orientation along axes K'K symmetrically inclined with respect to the axis Y'Y of the central channel 41 (see in particular the figure 1b ), and contra-rotation relative to the inclination of the vanes 40 of the swirler 4. Advantageously, the number of radial channels 42 is equal to a multiple of the number of vanes 40 of the swirler 4.

Par ailleurs, le flux d'air en entrée FE - provenant du dernier étage de compression - traverse des ouvertures 170 formées dans un couvercle évasé 17 prolongeant le tube 11, et est ensuite guidé dans un circuit d'air C3 circulant dans un espace inter-sphérique « E ». Cet espace « E » est formé entre deux portions de sphères concentriques formées par le corps d'injecteur 11s et partiellement par le fourreau 5 dans une partie sphérique 5s enveloppant le corps d'injecteur 11s. Le fourreau présente également une partie cylindrique à section circulaire 5c, qui permet d'assurer un appui au tube à flamme 6 et au couvercle évasé 17 du tube 11. Ainsi l'injecteur selon l'invention présente un encombrement minimal grâce à ce passage inter-sphérique.Furthermore, the inlet air flow F E - from the last compression stage - passes through openings 170 formed in a flared lid 17 extending the tube 11, and is then guided in an air circuit C3 circulating in a space inter-spherical "E". This space "E" is formed between two portions of concentric spheres formed by the injector body 11s and partially by the sleeve 5 in a spherical portion 5s enveloping the injector body 11s. The sheath also has a cylindrical portion with a circular section 5c, which makes it possible to provide support for the flame tube 6 and the flared lid 17 of the tube 11. Thus, the injector according to the invention has a minimum space requirement thanks to this interpass. -spherical.

De plus, le circuit de démarrage central C1 est thermiquement protégé de la cokéfaction par la circulation du carburant dans le canal annulaire 16 du circuit principal C2, ce circuit principal étant lui-même thermiquement protégé par le flux d'air périphérique F circulant dans l'espace inter-sphérique « E » du circuit d'air C3.In addition, the central starting circuit C1 is thermally protected from coking by the circulation of the fuel in the annular channel 16 of the main circuit C2, this main circuit being itself thermally protected by the flow of peripheral air F flowing in the inter-spherical space "E" of the air circuit C3.

En sortie d'injecteur 1, le flux d'air FS forme avantageusement, en passant entre les ailettes 40, un cône d'air Ca enveloppant le cône de sortie de carburant Cs du circuit principal C2.At the outlet of the injector 1, the air flow F S advantageously forms, passing between the fins 40, an air cone Ca enclosing the fuel outlet cone Cs of the main circuit C2.

Selon une variante de réalisation en référence aux vues en perspective et en coupe des figures 2a et 2b, l'injecteur illustré 1' reprend des éléments de l'exemple précédent. Ces élément identiques sont donc représentés avec les mêmes signes de référence : la description précédente de ces éléments est applicable directement aux figures 2a et 2b dans leur structure et leur fonction.According to an alternative embodiment with reference to perspective and sectional views of Figures 2a and 2b , the illustrated injector 1 'takes elements from the previous example. These identical elements are therefore represented with the same reference signs: the foregoing description of these elements is directly applicable to Figures 2a and 2b in their structure and function.

Les modifications proviennent essentiellement de la configuration de la liaison entre le tube longitudinal 11 et le fourreau 5. Dans l'exemple illustré aux figure 2a et 2b, le tube 11' ne présente pas de couvercle évasé 17 pour former les ouvertures 170 d'accès du flux d'air FE dans le circuit C3. Ici, le tube 11' est prolongé directement par le corps sphérique 11s. Et le fourreau 5' se prolonge dans sa partie cylindrique jusqu'à venir se fixer sur la bride 10. Les ouvertures 170' de passage du flux d'air FE dans le circuit C3' sont alors pratiquées dans la partie cylindrique du fourreau 5', du côté de la bride 10. La partie d'extrémité conique 21c de l'évidement 21 traverse la paroi centrale 14 du tourbillonneur 4 et fait fonction de canal central 41.The modifications come essentially from the configuration of the connection between the longitudinal tube 11 and the sleeve 5. In the example illustrated in FIGS. Figure 2a and 2b the tube 11 'does not have a flared lid 17 to form the openings 170 for access to the air flow F E in the circuit C3. Here, the tube 11 'is extended directly by the spherical body 11s. And the sheath 5 'extends in its cylindrical portion until it is fixed on the flange 10. The openings 170' for passage of the air flow F E in the circuit C3 'are then formed in the cylindrical part of the sheath 5 on the side of the flange 10. The conical end portion 21c of the recess 21 passes through the central wall 14 of the swirler 4 and acts as a central channel 41.

En référence à la figure 3, la vue en perspective partielle illustre la chambre de combustion 3 équipée d'injecteurs montés sur la paroi du tube à flamme 6 : deux injecteurs à double circuit 1 présentés ci-dessus et sept injecteurs à simple circuit 100. La chambre est partiellement écorchée afin de faire apparaître certains injecteurs en entier et la bougie 101 du côté du fond 3f de la chambre.With reference to the figure 3 , the partial perspective view illustrates the combustion chamber 3 equipped with injectors mounted on the wall of the flame tube 6: two double circuit injectors 1 shown above and seven single circuit injectors 100. The chamber is partially cut to to show some injectors in full and the candle 101 on the side of the bottom 3f of the chamber.

Tous les injecteurs 1, 100 sont montés régulièrement sur le pourtour annulaire de la chambre 3. Des orifices 60 ont été pratiqués dans le tube 6 pour enserrer les fourreaux 5 des injecteurs 1, 100.All the injectors 1, 100 are regularly mounted on the annular periphery of the chamber 3. Orifices 60 were made in the tube 6 to enclose the sleeves 5 of the injectors 1, 100.

Les injecteurs à double circuit 1 sont orientés vers la bougie d'allumage 101. Grâce à l'orientation inclinée des canaux gicleurs 42 et des canaux centraux 41, les injecteurs à double circuit 1 sont aptes à projeter des cônes air/carburant Ca/Cs en sortie des tourbillonneurs vers le fond 3f de la chambre de combustion 3. Après allumage, la flamme se dirige vers le fond 3f, se retourne et ressort par la sortie opposée 3s.The dual circuit injectors 1 are oriented towards the spark plug 101. Thanks to the inclined orientation of the nozzle channels 42 and the central channels 41, the dual circuit injectors 1 are able to project air / fuel cones Ca / Cs at the outlet of the swirlers to the bottom 3f of the combustion chamber 3. After ignition, the flame goes to the bottom 3f, turns and emerges through the opposite outlet 3s.

Dans l'exemple illustré, les deux injecteurs à double circuit 1 sont séparés par un injecteur simple circuit 100 de sorte à faciliter l'orientation des injecteurs à double circuit 1 vers la bougie 101.In the illustrated example, the two dual circuit injectors 1 are separated by a single circuit injector 100 so as to facilitate the orientation of the dual circuit injectors 1 towards the candle 101.

L'invention n'est pas limitée à l'exemple de réalisation décrit et représenté. Par exemple, le corps de l'injecteur peut former une partie de sphère plus ou moins complète suivant la dimension d'ouverture ou le diamètre du tube commun. Il est par ailleurs possible de former plusieurs lignes d'injecteurs dans le tube à flamme.The invention is not limited to the embodiment described and shown. For example, the body of the injector may form a more or less complete sphere part depending on the opening size or the diameter of the common tube. It is also possible to form several lines of injectors in the flame tube.

Claims (11)

  1. An injector (1, 1') for a gas turbine combustion chamber (3), comprising a dual fuel supply circuit (C1, C2) and an air circuit (C3), in which the fuel injection circuits (C1, C2) consist in a starting fuel supply circuit (C1) being able to trigger the chamber (3) ignition, and then to operate in any flight mode, and a main fuel supply circuit (C2) being able to operate in any flight mode further to starting, in which the fuel supply circuits (C1, C2) have parallel conducts (12a, 12b) made into a common tube (11, 11') with a longitudinal axis (X'X), in which the conduct of the starting circuit (12a) opens, on one end (12e), substantially into the center of a spherical injector body (11s) extending the common tube (11, 11'), in which, on such end (12e), the conduct houses an injection ramp (7) being able to drive fuel into rotation before projecting it inside the chamber (3) through a central channel (41) passing through a central wall (14) of a swirling device (4), in which the conduct (12b) of the main circuit (C2) opens into an annular channel (16) made in the body (11s) facing jet channels (42) radially arranged in the main wall (14) around the central channel (41), and in which the air circuit (C3) is guided between two concentric sphere portions consisting of the injector body (11s) and a sheath (5, 5') surrounding the injector body (11s) and presenting an opening (15) through which the swirling device (4) opens into.
  2. The injector according to claim 1, wherein the swirling device (4) is located in a slanting position (Y'Y) with respect to the longitudinal axis of the injector (X'X) so as to position the end (12e) of the starting circuit (12a) in the center of the latter and to orient the air and fuel jets (Ca, Cs) on the injector output in the direction of a plug (101) arranged in the bottom (3f) of the chamber.
  3. The injector according to any of claims 1 or 2, wherein the conduct (12a) of the starting circuit (C1) shows on its end (12e) a cylindrical recess (21) to house the ramp (7).
  4. The injector according to any of preceding claims, wherein the central channel (41) is made with a conical shape tapering towards the inside part of the combustion chamber (3) into which it opens.
  5. The injector according to any of preceding claims, wherein, the swirling device (4) comprising slanting fins (40), the radial channels (42) show a slanting orientation (K'K) with respect to the axis (Y'Y) of the central channel (41) and in contra-rotation with respect to the slanting of the fins (40) of the swirling device (4).
  6. The injector according to any of preceding claims, wherein the injection ramp (7) of the starting circuit (C1) is helical.
  7. The injector according to any of preceding claims, wherein the annular channel (16) of the main fuel supply circuit (C2) is not looped on itself and shows ends (16e) so as not to form any "dead" zone where the fuel might stagnate.
  8. The injector according to any of claims 5 to 7, wherein the number of radial channels (42) is equal to a multiple of the number of fins (42) of the swirling device (4).
  9. A combustion chamber provided of at least one dual circuit injector (1, 1') according to any of preceding claims, and single circuit injectors 100), in which all the injectors (1, 1'; 100) are mounted in alignment on the casing (2) surrounding the combustion chamber (3) and cross a flame tube (6) through ports (60) arranged along at least one line parallel to the longitudinal axis of the flame tube (6).
  10. The combustion chamber according to preceding claim, wherein the dual circuit injectors (1, 1') are oriented towards the ignition plug (101) so that such injectors are able to project an air/fuel cone (Ca, Cs) on the output of the swirling device (4) oriented towards the bottom (3f) of the combustion chamber (3).
  11. The combustion chamber according to any of claims 9 or 10,which is provided with two dual circuit injectors (1, 1') being not adjacent on the line of injectors.
EP12706638.9A 2011-02-02 2012-01-27 Injector for the combustion chamber of a gas turbine having a dual fuel circuit, and combustion chamber provided with at least one such injector Active EP2671028B1 (en)

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PL12706638T PL2671028T3 (en) 2011-02-02 2012-01-27 Injector for the combustion chamber of a gas turbine having a dual fuel circuit, and combustion chamber provided with at least one such injector

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FR1150807A FR2971039B1 (en) 2011-02-02 2011-02-02 GAS TURBINE FUEL COMBUSTION CHAMBER INJECTOR WITH DOUBLE FUEL CIRCUIT AND COMBUSTION CHAMBER EQUIPPED WITH AT LEAST ONE SUCH INJECTOR
PCT/FR2012/050177 WO2012104525A1 (en) 2011-02-02 2012-01-27 Injector for the combustion chamber of a gas turbine having a dual fuel circuit, and combustion chamber provided with at least one such injector

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JP (1) JP5985514B2 (en)
KR (1) KR101877591B1 (en)
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Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2996288B1 (en) * 2012-10-01 2014-09-12 Turbomeca DUAL TURBOMACHINE COMBUSTION CHAMBER INJECTOR.
FR2996289B1 (en) * 2012-10-01 2018-10-12 Turbomeca COMBUSTION CHAMBER COMPRISING A FIXED FLAME TUBE USING THREE CENTERING ELEMENTS.
FR3001497B1 (en) * 2013-01-29 2016-05-13 Turbomeca TURBOMACHINE COMBUSTION ASSEMBLY COMPRISING AN IMPROVED FUEL SUPPLY CIRCUIT
FR3001525B1 (en) * 2013-01-29 2016-12-09 Turbomeca METHOD FOR MANAGING FUEL CONSUMPTION OF A BIMOTOR ASSEMBLY AND ASSOCIATED ASSEMBLY
EP2951505A4 (en) * 2013-02-01 2016-01-06 Hamilton Sundstrand Corp Fuel injector for high altitude starting and operation of a gas turbine engine
US9404422B2 (en) * 2013-05-23 2016-08-02 Honeywell International Inc. Gas turbine fuel injector having flow guide for receiving air flow
EP3022492A4 (en) * 2013-07-15 2017-02-22 Hamilton Sundstrand Corporation Combustion system, apparatus and method
US9625156B2 (en) * 2013-10-30 2017-04-18 Honeywell International Inc. Gas turbine engines having fuel injector shrouds with interior ribs
FR3017693B1 (en) * 2014-02-19 2019-07-26 Safran Helicopter Engines TURBOMACHINE COMBUSTION CHAMBER
CN104019475A (en) * 2014-06-23 2014-09-03 叶祖湘 Big/small cooking stove with combustion engine system
FR3050255B1 (en) * 2016-04-13 2019-10-25 Safran Helicopter Engines IMPROVED INJECTORS FOR GAS TURBINE COMBUSTION CHAMBER
FR3059047B1 (en) * 2016-11-21 2020-08-28 Safran Helicopter Engines COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS
FR3067444B1 (en) * 2017-06-12 2019-12-27 Safran Helicopter Engines TURBOMACHINE FUEL COMBUSTION ARCHITECTURE COMPRISING DEFLECTION MEANS
FR3068113B1 (en) 2017-06-27 2019-08-23 Safran Helicopter Engines FLAT JET FUEL INJECTOR FOR AN AIRCRAFT TURBOMACHINE
US10816211B2 (en) * 2017-08-25 2020-10-27 Honeywell International Inc. Axially staged rich quench lean combustion system
FR3081211B1 (en) * 2018-05-16 2021-02-26 Safran Aircraft Engines TURBOMACHINE COMBUSTION CHAMBER SET
CN109185923B (en) * 2018-08-03 2023-09-12 新奥能源动力科技（上海）有限公司 Combustion chamber head device, combustion chamber and gas turbine
CN109185924B (en) * 2018-08-03 2023-09-12 新奥能源动力科技（上海）有限公司 Combustion chamber head device, combustion chamber and gas turbine
FR3087250B1 (en) 2018-10-11 2020-09-25 Safran Helicopter Engines MONOBLOC FLAT JET FUEL INJECTOR FOR AN AIRCRAFT TURBOMACHINE AND ITS MANUFACTURING PROCESS
RU187491U1 (en) * 2018-11-15 2019-03-11 Публичное Акционерное Общество "Одк-Сатурн" VAPOR COMBUSTION CAMERA FOR GAS-TURBINE ENGINE
FR3099231B1 (en) 2019-07-24 2022-08-12 Safran Helicopter Engines PURGE CIRCUIT FUEL INJECTOR FOR AN AIRCRAFT TURBOMACHINE
US20230175696A1 (en) * 2021-12-03 2023-06-08 Honeywell International Inc. Gas turbine engine injector module with thermally coupled fuel lines having respective outlets

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4817389A (en) * 1987-09-24 1989-04-04 United Technologies Corporation Fuel injection system
SU1560923A1 (en) * 1988-06-29 1990-04-30 Войсковая часть 27177 Combustion chamber of gas-turbine engine
US7513116B2 (en) * 2004-11-09 2009-04-07 Woodward Fst, Inc. Gas turbine engine fuel injector having a fuel swirler
JP3958767B2 (en) * 2005-03-18 2007-08-15 川崎重工業株式会社 Gas turbine combustor and ignition method thereof
US7624576B2 (en) * 2005-07-18 2009-12-01 Pratt & Whitney Canada Corporation Low smoke and emissions fuel nozzle
FR2896030B1 (en) * 2006-01-09 2008-04-18 Snecma Sa COOLING A MULTIMODE INJECTION DEVICE FOR A COMBUSTION CHAMBER, IN PARTICULAR A TURBOREACTOR
US20070193272A1 (en) * 2006-02-21 2007-08-23 Woodward Fst, Inc. Gas turbine engine fuel injector
FR2906868B1 (en) 2006-10-06 2011-11-18 Snecma FUEL INJECTOR FOR GAS TURBINE ENGINE COMBUSTION CHAMBER
US7908864B2 (en) * 2006-10-06 2011-03-22 General Electric Company Combustor nozzle for a fuel-flexible combustion system
FR2911667B1 (en) 2007-01-23 2009-10-02 Snecma Sa FUEL INJECTION SYSTEM WITH DOUBLE INJECTOR.
US9513009B2 (en) * 2009-02-18 2016-12-06 Rolls-Royce Plc Fuel nozzle having aerodynamically shaped helical turning vanes

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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US9347667B2 (en) 2016-05-24
CN103354890A (en) 2013-10-16
JP5985514B2 (en) 2016-09-06
KR101877591B1 (en) 2018-07-12
KR20140008350A (en) 2014-01-21
FR2971039A1 (en) 2012-08-03
FR2971039B1 (en) 2013-01-11
WO2012104525A1 (en) 2012-08-09
ES2686560T3 (en) 2018-10-18
CA2825864C (en) 2019-05-21
CA2825864A1 (en) 2012-09-09
US20130305726A1 (en) 2013-11-21
RU2013139354A (en) 2015-03-10
CN103354890B (en) 2016-06-29
PL2671028T3 (en) 2018-11-30
JP2014504696A (en) 2014-02-24
RU2584741C2 (en) 2016-05-20
EP2671028A1 (en) 2013-12-11

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