EP2488791B1 - Mehrpunkt-einspritzvorrichtung für eine brennkammer eines turbinenmotors - Google Patents

Mehrpunkt-einspritzvorrichtung für eine brennkammer eines turbinenmotors Download PDF

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Publication number
EP2488791B1
EP2488791B1 EP10778699.8A EP10778699A EP2488791B1 EP 2488791 B1 EP2488791 B1 EP 2488791B1 EP 10778699 A EP10778699 A EP 10778699A EP 2488791 B1 EP2488791 B1 EP 2488791B1
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EP
European Patent Office
Prior art keywords
annular
ring
chamber
front face
injection
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EP10778699.8A
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English (en)
French (fr)
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EP2488791A1 (de
Inventor
Didier Hippolyte Hernandez
Emilie Lachaud
Thomas Olivier Marie Noel
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • 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

Definitions

  • the present invention relates to a "multipoint" fuel injection device for an annular turbomachine combustion chamber such as an airplane turbojet or turboprop engine.
  • a turbomachine comprises an annular combustion chamber arranged at the outlet of a high pressure compressor and provided with a plurality of fuel injection devices regularly distributed circumferentially at the inlet of the combustion chamber.
  • a multipoint injection device comprises a first venturi inside which is mounted a pilot injector centered on the axis of the first venturi and continuously supplied by a pilot circuit and a second venturi coaxial with the first venturi and surrounding it.
  • This second venturi comprises an annular chamber at its upstream end in which is mounted an annular ring supplied with fuel by a multipoint circuit.
  • the ring has fuel injection orifices formed in a front face and aligned with orifices of a front face of the annular chamber to eject the fuel downstream and outward of the second venturi.
  • the pilot circuit continuously provides optimized fuel flow for low revs and the multi-point circuit provides optimized intermittent fuel flow for high revs.
  • the intermittent use of the multipoint circuit has the major disadvantage of inducing, under the effect of the high temperatures due to the radiation of the flame in the combustion chamber, scrubbing or coking of the fuel stagnant inside the circuit multipoint when it is cut off. These phenomena can lead to the formation of coke in the ring and at the fuel injection ports of the multipoint circuit impacting the spraying of the fuel. fuel by the multipoint circuit and thus the operation of the combustion chamber.
  • the document EP 1806536 discloses a fuel injection device for an annular turbomachine combustion chamber, comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit intermittently supplying injection orifices formed in the front face of an upstream annular chamber of a second venturi coaxial with and surrounding the first venturi, an annular ring mounted in the annular chamber, the device also comprising thermal insulation means of the lateral portion of the annular ring.
  • Such a configuration does not, however, sufficiently reduce the risk of coking the fuel at the front face of the annular chamber which remains highly exposed to the heat radiation generated by the combustion of the fuel downstream.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a fuel injection device for an annular turbomachine combustion chamber comprising a pilot circuit continuously supplying an injector opening into a first venturi and a multipoint circuit intermittently supplying the injection orifices and a annular chamber formed upstream of a second venturi coaxial with and surrounding the first venturi, characterized in that the injection orifices are formed in a front face of an annular ring mounted in the annular chamber and in that that the device comprises means for thermal insulation of the end face of the annular ring comprising an annular cavity formed around the injection orifices between the end face of the annular ring and a front wall of the annular chamber and intended to be filled in operation of air or coked fuel.
  • thermal insulation means formed by an insulating annular cavity interposed between the front face of the ring and a downstream wall the annular chamber protects the injection ports of the crown to prevent coking, and thus ensures a optimal operation of the multipoint circuit.
  • the annular cavity may be filled with air or coked fuel which forms a good thermal insulator of the multipoint annular ring and its fuel injection ports relative to the thermal radiation of the fuel combustion.
  • the device also comprises a cooling circuit of the annular ring by circulation of the fuel of the pilot circuit in an internal annular channel formed between inner cylindrical walls of the ring and the annular chamber and an outer annular channel formed between cylindrical walls. external of the crown and the annular chamber.
  • one of the internal or external channels communicates with the aforementioned annular cavity, the other of the inner or outer channels being isolated from this cavity, which makes it possible to fill the front annular fuel cavity which will coke under the effect of thermal radiation from fuel combustion.
  • the radially inner or outer periphery of the front face of the annular ring comprises an annular flange whose downstream end defines with the front wall of the chamber an annular communication passage between the aforementioned annular cavity. and one of the internal or external channels of the cooling circuit.
  • This annular passage allows a fuel supply inside the front cavity and its coking under the effect of thermal radiation for the isolation of the injection ports of the crown.
  • the radially outer periphery of the front face of the ring is in radial abutment on the outer cylindrical wall of the chamber for centering the ring in the chamber.
  • each injection orifice of the ring is formed in a protruding lug on the front face of the ring, these pins being inserted in abutment in a cavity of a corresponding boss formed on the front wall of the annular chamber.
  • the positioning in abutment ensures a correct axial mounting of the ring in the annular chamber.
  • Each cavity of a boss opens out of the annular chamber by a bore aligned with the injection port of the corresponding stud, this bore having a diameter greater than that of the injection orifice, which allows moving the coking zone of the drops of fuel out of the nipple injection holes and towards the holes of the annular chamber.
  • the injection orifices are formed in cylindrical pins fixed in holes in the end face of the annular ring, these pegs protruding projecting on this front face and forming positioning means and centering in the annular chamber.
  • This configuration is particularly interesting when the space inside the chamber is reduced and does not allow the realization of nipples and bosses as in the previous embodiment.
  • the injection port of each pin comprises a downstream end of larger diameter to prevent coking of the injection ports during the stopping of the multipoint circuit.
  • the axial positioning of the ring in the annular chamber is formed by an annular flange formed at the radially inner end of the downstream wall of the ring, this flange abutting on the front wall of the annular chamber.
  • the invention also relates to an annular turbomachine combustion chamber, comprising at least one fuel injection device of the type described above.
  • FIG 1 illustrating an injection device 10 according to the prior art and comprising two fuel injection systems, one of which is a pilot system operating continuously and the other a multipoint system operating intermittently.
  • This device is intended to be mounted in an opening of a bottom wall of an annular combustion chamber of a turbomachine which is fed with air by an upstream high-pressure compressor and whose combustion gases feed a turbine mounted downstream.
  • This device comprises a first venturi 12 and a second venturi 14 coaxial, the first venturi 12 being mounted inside the second venturi 14.
  • a pilot injector 16 is mounted inside a first stage of tendrils 18 inserted axially to the interior of the first venturi 12.
  • a second stage of tendrils 20 is formed at the upstream end and radially outside the first venturi 12 and separates the first and second venturi, 12, 14.
  • the second venturi 14 comprises an annular chamber 22 formed by two radially inner cylindrical walls 24 and outer 26 connected to each other by a frustoconical downstream wall 28 converging downstream.
  • An annular ring 30 also comprising two radially inner cylindrical walls 32 and external wall 34 connected to each other by a downstream convergent downstream conical downstream wall 36 is mounted inside the annular chamber 22 so that the downstream walls 28, 36 of the annular chamber 22 and the annular ring 30 are in contact.
  • the annular ring 30 and the annular chamber 22 each comprise an annular opening at their upstream end.
  • the cylindrical walls 24, 26 of the annular chamber 22 extend projecting upstream with respect to the upstream ends of the cylindrical walls 32, 34 of the annular ring 30.
  • the downstream wall 36 of the annular ring 30 comprises injection orifices 40 uniformly distributed circumferentially and opening into corresponding orifices 42 in the downstream wall 28 of the annular chamber 22.
  • the orifices 40, 42 of the annular chamber 22 and the annular ring 30 have identical diameters.
  • An internal annular channel 44 for passing fuel is defined between the inner cylindrical walls 24, 34 of the annular ring 30 and the annular chamber 22.
  • an annular channel external fuel passage 46 is defined between the outer cylindrical walls 26, 34 of the annular ring 30 and the annular chamber 22.
  • the injection device comprises a fuel feed body 48 whose downstream portion is annular and comprises a cylindrical duct 50 axially engaged with sealing between the inner cylindrical walls 24 and outer 26 of the annular chamber 22 and opening sealing between internal cylindrical walls 32 and outer 34 of the annular ring 30.
  • the duct 50 has a radial shoulder 54 abutting on the upstream ends of the inner cylindrical walls 32 and outer 34 of the annular ring 30.
  • This sealing assembly of the body 48 makes it possible to guarantee that the inner and outer annular channels 44 and 44 are sealed with respect to the annular space formed inside the annular ring 30.
  • a fuel supply arm 56 is connected to the body 48 and comprises two coaxial ducts of which one central 58 feeds a channel 60 of the body 48 opening downstream inside the annular ring 30 and the other formed outer 62 around the central duct 58 supplies at the output of separate channels (not shown) opening into the inner annular channels 44 and outer 46, respectively.
  • the body 48 comprises a fuel collection cavity 64 formed diametrically opposite the fuel supply arm 56 and at the upstream ends of the cylindrical walls 32, 34 of the annular ring 30 so that the annular channels internal 44 and outer 46 communicate with the collection cavity 64.
  • a duct 66 is connected at one end to the pilot injector 16 and at the other end opens into the collection cavity 64.
  • the central duct 58 of the arm 56 supplies fuel to the channel 60 of the body 48, the fuel then circulating in the annular ring 30 and being injected into the combustion chamber downstream through the orifices 40, 42 of the ring gear 30 and from bedroom 22.
  • the external duct 62 of the arm 56 feeds the channels of the body 48 opening into the inner and outer annular channels 44 and 46, the fuel then passing into the collection cavity 64 to supply the pilot injector 16 via the duct 66.
  • the pilot circuit operates continuously while the multipoint circuit operates intermittently during specific flight phases such as takeoff requiring additional power.
  • the hot air (at about 600 ° C.) coming from the high-pressure compressor flows inside the first venturi 12, in the first radial swirler 18, and from the air also flows inside the second radial swirler 20, between the first 12 and second 14 venturis.
  • downstream face 28 of the annular ring 22 is subjected directly to the thermal radiation of the combustion, which can lead to a coking of the fuel in the injection orifices 40, 42 of the ring 30 and the annular chamber 22 during flight phases where the multipoint circuit is not used.
  • the invention provides a solution to this problem by integrating in the injection device 68 thermal insulation means of the front wall of the annular ring multipoint.
  • thermal insulation means comprise an insulating annular cavity 70 formed between the end face 72 of the annular ring 74 and the downstream wall 76 of the annular chamber 78.
  • This cavity 70 extends between the injection orifices 80 so as to achieve thermal insulation closer to them. This reduces the risk of coking fuel at the fuel injection ports 80 to ensure optimum operation of the multipoint circuit.
  • the end face 72 of the annular ring 74 comprises a plurality of pins 82 projecting regularly distributed around the ring 74 and each comprising an injection port 80. These pins 82 are inserted into boss cavities 84 of the upstream face. of the downstream wall 76 of the annular chamber 78. The pins 82 are engaged inside the cavities of the bosses so as to abut on the downstream wall 76 of the annular chamber 78 to ensure correct axial positioning of the ring 74 in the annular chamber 78.
  • the downstream wall 76 of the annular chamber 78 comprises ( figure 3 ) bores 86 each opening upstream in the cavity of a boss 84 and downstream to the outside of the second venturi, each bore 86 being aligned with an injection port 80 of the ring 74 and having a diameter greater than that of an injection orifice 80, in order to move the coking zone of the drops of fuel towards the bores 86 of the annular chamber 78.
  • the pins 82 have a substantially cylindrical shape and are brazed inside the cavities of the bosses 84 to seal between the driver circuit and the multipoint circuit. It is possible to check the good performance of the stirring by visual inspection through the holes 86 of the downstream wall 76 of the annular chamber 78 because these holes 86 have a diameter greater than that of the injection orifices 80.
  • the radially outer periphery of the end face 72 of the ring 74 extends radially outside its outer cylindrical wall 90 and bears radially on the outer cylindrical wall 92 of the annular chamber 78 so as to center the ring 74 in the annular chamber 78.
  • the radially inner periphery of the end face 72 comprises an annular flange 94 extending downstream of the end face 72 and in the extension of the internal cylindrical wall 96. The downstream end this annular flange 94 forms an annular fuel passage between the inner annular channel 44 and the front annular cavity 70.
  • the device according to the invention also comprises a cooling circuit formed by an internal annular channel 44 delimited by the internal cylindrical walls 96, 97 of the ring 74 and the annular chamber 78 and an external annular channel 46 delimited by the outer cylindrical walls 90, 92 of the crown 74 and the annular chamber 78.
  • the outer annular channel 46 is isolated from the front cavity by the radially outer periphery of the end face 72 of the ring 74 which can be brazed or not on the outer cylindrical wall 92 of the annular chamber 78 so as to achieve or not a tight connection.
  • the device comprises a plurality of pins 96 for centering the ring gear 100 in the annular chamber 102, these pins 98 being regularly distributed around the ring gear 100 and mounted axially in holes 101 in the front wall 104 of the ring gear 100 and in corresponding holes 103 in the annular chamber 102.
  • the upstream and downstream faces of the pins are substantially parallel to the frustoconical walls 104, 106 of the ring gear 100 and of the annular chamber 102.
  • the axial dimension of each pin is such that its upstream faces and downstream are aligned with the upstream face of the front wall 104 of the ring 100 and with the downstream face of the downstream wall 106 of the annular chamber 102, respectively.
  • Each pin 98 comprises an injection orifice 108 formed of a first bore 110 opening upstream inside the annular ring 100 and downstream in a second hole 112 of larger diameter which opens outwards from the second venturi 14.
  • the holes 110, 112 are aligned along a straight line perpendicular to the walls frustoconical downstream 104, 106 of the crown 100 and the annular chamber 102.
  • the larger diameter of the holes 112 of the annular chamber with respect to the diameters of the injection orifices 110 makes it possible to limit the coking of the injection orifices 110.
  • the radially inner and outer peripheries of the front wall 104 of the ring gear 100 each comprise an inner and outer annular rim 114, extending downstream of the end wall 104 and in the extension of the inner cylindrical 118 and outer 120, respectively .
  • the inner annular flange 114 is in contact with the downstream wall 106 of the chamber 102 to provide an axial positioning stop of the ring gear 100 in the annular chamber 102 while the outer annular flange 116 defines with the front wall 106 of the chamber 102 an annular passage of communication between the outer annular cavity 46 of the pilot circuit and the front cavity 70 of thermal insulation.
  • the assembly of the ring gear 100, the chamber 102 and the pins 98 is made in the following manner: the annular ring 100 is mounted in axial abutment inside the annular chamber 102 by virtue of the internal annular flange 114 of the ring 100 and oriented angularly so that the holes 101 of the ring 100 are aligned with the holes 103 of the annular chamber 102.
  • the centering pins 98 are then mounted in the holes 101, 103 of the ring 100 and the chamber 102 and a soldering operation of pins 98 in these holes, for sealing between the pilot circuit and the multipoint circuit.
  • the upstream and downstream faces of the pins 98 are machined again.
  • the bores 110, 112 are formed in each of the pins 98, this operation being performed after the soldering and machining operations to avoid a partial closure of the holes 110, 112 of the pins 98.
  • This configuration with centering pins is particularly interesting in multipoint nozzle configurations where the space inside the chamber is reduced and does not allow to make nipples and bosses.
  • the front annular cavity is in communication with one of the internal channels ( figure 4 ) or external ( figure 8 ) of the cooling circuit to supply the front annular cavity 70 with fuel during operation of the turbomachine.
  • the fuel present inside the front cavity will coke under the effect of thermal radiation, thus forming a thermal insulation protecting the multipoint annular ring.

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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)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Claims (11)

  1. Vorrichtung zum Einspritzen von Kraftstoff für eine ringförmige Verbrennungskammer einer Turbomaschine bzw. eines Turbotriebwerks, enthaltend einen Pilotkreis, der einen Injektor (16) dauerhaft speist, welcher in eine erste Venturi-Düse (12) mündet, und einen Mehrpunktkreis, der Einspritzöffnungen (80, 110) intermittierend speist, sowie eine ringförmige Kammer (78, 102), die einer zweiten Venturi-Düse (14) vorgelagert ausgebildet ist, welche koaxial zur ersten Venturi-Düse (12) verläuft und diese umgibt, dadurch gekennzeichnet, dass die Einspritzöffnungen (80, 110) in einer Stirnseite (72, 104) eines ringförmigen Kranzes (74, 100) ausgebildet sind, der in der ringförmigen Kammer (78, 102) gelagert ist, und dass die Vorrichtung Wärmeisoliermittel für die Stirnseite (72, 104) des ringförmigen Kranzes (74, 100) aufweist, enthaltend einen ringförmigen Hohlraum (70), der um die Einspritzöffnungen (80, 100) herum zwischen der Stirnseite (72, 104) des ringförmigen Kranzes und einer Stirnwand (76, 106) der ringförmigen Kammer (78, 102) ausgebildet und dazu bestimmt ist, im Betrieb mit Luft oder verkoktem Kraftstoff gefüllt zu werden.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass sie auch einen Kühlkreis für den ringförmigen Kranz (74, 100) durch Strömen von Kraftstoff des Pilotkreises in eine ringförmige Innenleitung (44) aufweist, die zwischen den zylindrischen Innenwänden (96, 118, 97) des Kranzes (74, 100) und der ringförmigen Kammer (78, 102) ausgebildet ist, und in eine ringförmige Außenleitung (46), die zwischen den zylindrischen Außenwänden (90, 120, 92) des Kranzes (74, 100) und der ringförmigen Kammer (78, 102) ausgebildet ist.
  3. Vorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass eine der Leitungen, die Innenleitung (44) oder die Außenleitung (46), mit dem vorgenannten ringförmigen Hohlraum (70) kommuniziert, wobei die andere Leitung, die Innenleitung (44) oder die Außenleitung (46), von diesem Hohlraum (70) getrennt ist.
  4. Vorrichtung nach Anspruch 3, dadurch gekennzeichnet, dass der radial innere bzw. äußere Umkreis der Stirnseite (72, 104) des ringförmigen Kranzes (74, 100) eine ringförmige Randleiste (94) aufweist, deren stromabwärtiges Ende mit der Stirnwand (76) der Kammer (78, 102) einen ringförmigen Durchgang zur Kommunikation zwischen dem vorgenannten ringförmigen Hohlraum (70) und einer der Leitungen, der Innenleitung (44) oder der Außenleitung (46), des Kühlkreises definiert.
  5. Vorrichtung nach einem der Ansprüche 2 bis 4, dadurch gekennzeichnet, dass der radial äußere Umkreis der Stirnseite (72) des Kranzes (74) radial in Anlage an der zylindrischen Außenwand (92) der Kammer (78) zum Zentrieren des Kranzes (74) in der Kammer (78) ist.
  6. Vorrichtung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass jede Einspritzöffnung (80) des Kranzes (74) in einem Ansatzstück (82) ausgebildet ist, das an der Stirnseite (72) des Kranzes (74) vorspringt, wobei diese Ansatzstücke (82) in Anschlag in einem Hohlraum einer entsprechenden Erhebung (84) einschoben sind, die an der Stirnwand (76) der ringförmigen Kammer (78) ausgebildet ist.
  7. Vorrichtung nach Anspruch 6, dadurch gekennzeichnet, dass jeder Hohlraum einer Erhebung (84) außerhalb der ringförmigen Kammer (78) über eine Bohrung (6) ausmündet, die mit der Einspritzöffnung (80) des entsprechenden Ansatzstücks (82) fluchtet, wobei diese Bohrung (86) im Durchmesser größer als die Einspritzöffnung (80) ist.
  8. Vorrichtung nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass die Einspritzöffnungen (108) in zylindrischen Zapfen (98) ausgebildet sind, die in Löchern der Stirnseite (104) des ringförmigen Kranzes (100) befestigt sind, wobei diese Zapfen (98) an dieser Stirnwand vorspringend abstehen und Mittel zum Positionieren und Zentrieren in der ringförmigen Kammer (102) bilden.
  9. Vorrichtung nach Anspruch 8, dadurch gekennzeichnet, dass die Einspritzöffnung (108) eines jeden Zapfens (98) ein stromabwärtiges Ende mit größerem Durchmesser aufweist.
  10. Vorrichtung nach den Ansprüchen 8 oder 9, dadurch gekennzeichnet, dass das radial innere Ende der Stirnseite (104) des Kranzes (100) eine ringförmige Randleiste (114) zum axialen Positionieren in der ringförmigen Kammer (102) aufweist.
  11. Ringförmige Verbrennungskammer einer Turbomaschine bzw. eines Turbotriebwerks, dadurch gekennzeichnet, dass sie zumindest eine Vorrichtung (68) zum Einspritzen von Kraftstoff nach einem der vorangehenden Ansprüche aufweist.
EP10778699.8A 2009-10-13 2010-10-06 Mehrpunkt-einspritzvorrichtung für eine brennkammer eines turbinenmotors Active EP2488791B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0904906A FR2951245B1 (fr) 2009-10-13 2009-10-13 Dispositif d'injection multi-point pour une chambre de combustion de turbomachine
PCT/FR2010/052101 WO2011045503A1 (fr) 2009-10-13 2010-10-06 Dispositif d'injection multi-point pour une chambre de combustion de turbomachine

Publications (2)

Publication Number Publication Date
EP2488791A1 EP2488791A1 (de) 2012-08-22
EP2488791B1 true EP2488791B1 (de) 2014-08-06

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US (1) US9003802B2 (de)
EP (1) EP2488791B1 (de)
JP (1) JP5616456B2 (de)
CN (1) CN102575843B (de)
BR (1) BR112012008509B1 (de)
CA (1) CA2776848C (de)
FR (1) FR2951245B1 (de)
RU (1) RU2539223C2 (de)
WO (1) WO2011045503A1 (de)

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JP5631223B2 (ja) * 2011-01-14 2014-11-26 三菱重工業株式会社 燃料ノズル、これを備えたガスタービン燃焼器およびこれを備えたガスタービン

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CA2776848A1 (fr) 2011-04-21
CA2776848C (fr) 2017-07-04
RU2012119598A (ru) 2013-11-20
CN102575843A (zh) 2012-07-11
JP2013507600A (ja) 2013-03-04
WO2011045503A1 (fr) 2011-04-21
BR112012008509B1 (pt) 2020-09-29
CN102575843B (zh) 2014-12-24
EP2488791A1 (de) 2012-08-22
US20120198853A1 (en) 2012-08-09
US9003802B2 (en) 2015-04-14
FR2951245A1 (fr) 2011-04-15
JP5616456B2 (ja) 2014-10-29
BR112012008509A2 (pt) 2016-04-05
FR2951245B1 (fr) 2013-05-17
RU2539223C2 (ru) 2015-01-20

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