EP2071242B1 - Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer eines Turbotriebwerks - Google Patents

Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer eines Turbotriebwerks Download PDF

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Publication number
EP2071242B1
EP2071242B1 EP08169015.8A EP08169015A EP2071242B1 EP 2071242 B1 EP2071242 B1 EP 2071242B1 EP 08169015 A EP08169015 A EP 08169015A EP 2071242 B1 EP2071242 B1 EP 2071242B1
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Prior art keywords
venturi
air
annular
injection system
injector
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EP08169015.8A
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English (en)
French (fr)
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EP2071242A1 (de
Inventor
Christophe Pieussergues
Denis Jean Maurice Sandelis
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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
    • F23R3/02—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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the present invention relates to a system for injecting a mixture of air and fuel into a combustion chamber of a turbomachine, such as an airplane turbojet or turboprop engine.
  • An injection system of this type generally comprises a fuel injector and primary and secondary tendrils which are arranged downstream of the injector, coaxially with it, and which each delimit a radial air flow downstream of the injector.
  • the air flows from the two tendrils are delimited by a venturi inserted between the two tendrils and a frustoconical bowl which is mounted downstream of the tendrils and which accelerate the flow of the air / fuel mixture to the combustion chamber.
  • the venturi has an inner surface having a constriction or narrowing and delimiting a premix chamber in which are mixed a portion of the fuel ejected by the injector and the air flow delivered by the primary swirler
  • a system for injecting a mixture of air and fuel into a turbomachine combustion chamber comprises a fuel injector and a venturi disposed downstream of the injector, coaxially thereto, the venturi having a surface interior delimiting a premix chamber wherein fuel is mixed with a flow of air from an outer enclosure and passing through a primary swirler upstream of the venturi, which has an inner annular airflow cavity.
  • the present invention is intended in particular to provide a simple, effective and economical solution to these problems of the prior art.
  • a flow of air coming from an external enclosure will circulate in the internal cavity of the venturi and then will be injected into the premixing chamber, through air outlet ducts opening on the inner surface of the venturi, to form a air film near this surface opposing the deposition of soot and the formation of coke on this surface.
  • the air flow injected into the premixing chamber will be sufficient to prevent the air / fuel mixture coming into contact with the inner surface of the venturi, but will also be small enough not to impede the flow of air and the air. injection of fuel inside the venturi and not to cause flow detachment at the outlet of the venturi.
  • the air flow circulating in the internal cavity of the venturi represents approximately 0.5 to 1% of the air flow supplying the injection system.
  • the venturi comprises at its upstream end an annular flange extending radially outwards and separating the primary swirler from a secondary swirl of passage of a second air flow, the cavity annular extending into the venturi rim.
  • the annular cavity has a substantially L-shaped section.
  • the venturi is formed of two annular pieces of substantially L-shaped section which are coaxially engaged one inside the other and which are fixed to each other by brazing or welding, the first and the second piece parts delimiting between them the annular cavity of air circulation.
  • the first part extends upstream and inside the second part and has a substantially radial upstream annular wall which is connected at its inner periphery to a substantially cylindrical downstream wall in which the air outlet ducts are formed.
  • the second part comprises a substantially radial upstream annular wall which is connected at its inner periphery to a substantially cylindrical downstream wall, the radial wall being fixed at its outer periphery to the outer periphery of the radial wall of the first part, and its cylindrical wall. being attached at its downstream end to the downstream end of the cylindrical wall of the first piece.
  • At least a portion of the air inlet ducts may extend substantially radially relative to the axis of the injector and be formed at the outer periphery of the radial wall of one or each part.
  • the air coming from the external enclosure then passes radially from outside to inside directly inside the internal cavity of the venturi.
  • At least a portion of the air inlet ducts extend substantially parallel to the axis of the injector and are formed through blades of the secondary swirler and the radial wall of the second room.
  • air from the outer enclosure flows axially downstream upstream in the ducts formed in the vanes of the secondary auger and in the radial wall of the second part into the internal cavity of the venturi.
  • the air outlet ducts are inclined axially and circumferentially with respect to the axis of the injector, in the same direction as the vanes of the primary swirler, so that that the air leaving these ducts does not disturb the flow of air delivered by the primary swirler and does not impact the head of the injector.
  • the invention thus makes it possible to prevent the formation of coke on the venturi without modifying the flow of air and fuel injection inside the venturi.
  • each outlet duct formed between the axis of this duct and the axis of the injector is for example between 10 and 40 °, this angle being measured in a plane passing through the axis of the injector.
  • each outlet duct formed between the axis of this duct and a plane passing through the axis of the injector is, for example, between approximately 50 and 75 °, this angle being measured in a plane perpendicular to the axis of the injector.
  • the outlets of the air outlet ducts are regularly arranged around the axis of the injector and are distributed in one, two, three or four annular rows spaced axially from each other.
  • the inclinations in the axial and circumferential direction of the air ducts may vary from row to row.
  • the injection system comprises for example between 10 and 30 air inlet ducts and between 10 and 30 air outlet ducts.
  • the invention also relates to a turbomachine, such as an airplane turbojet or turboprop, comprising an injection system as described above.
  • the invention also relates to a venturi for an injection system as described above, comprising an inner surface having a neck.
  • the venturi is formed of two annular pieces of substantially L-shaped section which are coaxially fixed one inside the other and which delimit between them an internal cavity of air circulation, the inner annular piece having a cylindrical wall having air outlet ducts connected at one of their ends to the internal cavity and opening at the other end of their ends on the inner surface, and the outer annular wall having a radial annular wall having at its outer periphery ducts of air inlet connected at one of their ends to the internal cavity.
  • the figure 1 represents an annular combustion chamber 10 of a turbomachine such as a turbojet engine or an airplane turboprop, this chamber being arranged at the outlet of a diffuser 12, itself located at the outlet of a compressor (not shown).
  • the chamber 10 comprises a wall of internal revolution 14 and a wall of external revolution 16, connected upstream to an annular wall 18 of the chamber bottom and attached downstream by internal and external 20 frustoconical ferrules 22 respectively on an internal frustoconical web 24 of the diffuser, and on an outer casing 26 of the chamber, the upstream end of this housing 26 being connected to an outer frustoconical web 28 of the diffuser.
  • An annular fairing 29 is attached to the upstream ends of the walls 14, 16 and 18 of the chamber and includes air passage holes aligned with openings 30 of the wall 18 of the chamber floor in which are mounted systems 32 for injecting a mixture of air and fuel into the chamber, the air coming from the diffuser 12 and the fuel being supplied by injectors (not shown) fixed on the outer casing 26 and regularly distributed around the axis of the room.
  • Each injector comprises a fuel injection head 36 aligned with the axis 38 of the corresponding opening 30.
  • the other part of the air flow enters the annular enclosure 46 defined by the shroud 29, passes into the injection system 32 (arrows 48 and 50), and is then mixed with the fuel supplied by the injector and sprayed in the combustion chamber.
  • the injection system 32 comprises two coaxial upstream turbulence swirlers 52 and downstream 54 which are separated from each other by a venturi 56 and which are connected upstream to means 58 for centering and guiding the injector head 36 and downstream to a mixing bowl 60 which is mounted axially in the opening 30 of the wall 18 of the chamber bottom.
  • the swirlers 52, 54 each comprise a plurality of vanes extending radially around the axis of the swirler and regularly distributed around this axis to deliver a flow of air 48, 50 swirling downstream of the injection head 36.
  • the means 58 for guiding the injection head 36 of the injector comprise a ring 62 traversed axially by the injection head 36 and mounted radially sliding in a socket 64 fixed on the vanes of the primary swirler 52.
  • the mixing bowl 60 has a substantially frustoconical wall flared downstream and connected at its downstream end to a cylindrical flange 66, extending upstream and axially mounted in the opening 30 of the wall 18 of the chamber bottom with a deflector ring 68.
  • the upstream end of the wall frustoconical 60 of the bowl is connected to an intermediate annular piece 70 fixed on the vanes of the secondary swirler 54.
  • the venturi 56 has a substantially L-shaped cross section and comprises at its upstream end a substantially radial annular flange 71 which is interposed axially between the two tendrils 52, 54 and which axially delimits with the bushing 64 located upstream the annular passing channel.
  • the venturi 56 extends axially downstream to the interior of the secondary swirler 54 and separates the air flows coming from upstream tendrils 52 and downstream 54.
  • the venturi 56 comprises an inner cylindrical surface 72 having a neck and delimiting a premix chamber 74 in which a portion of the ejected fuel mixes with the air flow 48 delivered by the primary swirler 52. This air / fuel premix then mixes with downstream of the venturi to the air stream 50 from the secondary swirler 54 to form a sprayed fuel cone within the chamber.
  • the air / fuel premix formed in the chamber 74 can come into contact with the inner surface 72 of the venturi and cause the deposition of soot and the formation of coke on this surface, which can reduce the life of the venturi 56.
  • the invention overcomes this problem through the formation of an air film on the inner surface 72 of the venturi which opposes the deposit of coke and soot on this surface.
  • This result is obtained by means of a hollow venturi comprising an internal annular cavity for circulating air, this cavity being supplied with air coming from the outer enclosure 46 and being connected to air outlet ducts opening on the inner surface 72 of the venturi.
  • the venturi 56 is formed of two annular pieces 80, 82 with section substantially L-shaped which are fixed coaxially one inside the other and which delimit between them the annular cavity 84 of air flow.
  • This cavity 84 also has a substantially L-shaped section and comprises a cylindrical portion which extends axially inside the venturi, over substantially its entire axial dimension, and which is connected at its upstream end to a radial portion which is extends inside the flange of the venturi, over substantially its entire radial dimension.
  • Each piece 80, 82 comprises a substantially radial upstream annular wall 86 which is connected at its inner periphery to a substantially cylindrical downstream wall 88.
  • the radial walls 86 of the parts 80, 82 form the annular flange 71 of the venturi.
  • the downstream and outboard part 82 further comprises a cylindrical flange 90 which extends upstream from the outer periphery of the radial wall 86 and which is attached by brazing or welding to the outer periphery of the wall. radial 86 of the other room 80.
  • This cylindrical flange 88 comprises orifices or ducts 92 of substantially radial air inlet which provide fluid communication between the enclosure 46 and the internal cavity 84 of the venturi.
  • the injection system 32 comprises for example between 10 and 30 conduits 92 which are regularly distributed around the axis of the venturi.
  • the downstream end of the cylindrical wall 88 of the part 82 is fixed by brazing or welding at the downstream end of the cylindrical wall of the other part.
  • the cylindrical wall 88 of the piece 80 located upstream and inside comprises orifices or air outlet ducts 94 which open at one of their ends on the inner surface 72 of the venturi and at the other of their ends. in the internal cavity 84, to ensure fluid communication between this cavity 84 and the premix chamber 74.
  • the injection system 32 comprises for example between 10 and 30 ducts 94 which are distributed in annular rows, for example three in number in the example shown, which are spaced axially each other.
  • the air ducts 94 of each row are regularly spaced from each other about the axis of the injection head.
  • the angle formed between the axis of each outlet duct 94 and the axis of the injection head 36 is between approximately 10 and 40 °, this angle being measured in a plane passing through the axis of the injection head.
  • the angle formed between the axis of each outlet duct 94 and a plane passing through the axis of the injection head is between approximately 50 and 75 °, this angle being measured in a plane perpendicular to the axis of the injection head.
  • the ducts 94 of the same annular row of ducts have identical inclinations in axial and circumferential directions but which may be different from the inclinations of the ducts of the or each other row.
  • the inclination in the axial direction of the ducts 94 of the first row located upstream may for example be lower than that of the pipes of the third row located downstream ( figure 4 ).
  • FIGS 5 to 7 represent an alternative embodiment of the invention which comprises, in addition to the characteristics described with reference to the Figures 3 and 4 , additional ducts 96 of air inlet into the internal cavity 84 of the venturi. These ducts 96 extend substantially parallel to the axis of the venturi and also connect the internal cavity 84 of the venturi to the outer enclosure 46.
  • these ducts 96 extend through the radial wall of the piece 82 located downstream and outward, through at least a portion of the vanes of the secondary swirler 54, and through the element.
  • the ducts 96 open at their upstream ends into the internal cavity 84 and at their downstream ends into an annular space delimited by the element 70 and the bowl 60, this annular space communicating with the external enclosure 46.
  • injection comprises for example between 10 and 30 ducts 96.
  • the ducts 96 may have a section of circular or oblong shape.
  • the ducts 92 and 94 described above may also have in section a circular or oblong shape.
  • the dimensions of these ducts 92, 94, 96 are in particular determined as a function of the flow rate of air inside the cavity. They typically have a diameter of about 1 to 2 mm.
  • the flow rate of air circulating inside the cavity 84 represents approximately 0.5 to 1% of the flow rate of air supplying the injection system 32.
  • the inner cavity 84 is connected to the outer enclosure 46 only by the axial ducts 96 of air inlet.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Fuel-Injection Apparatus (AREA)

Claims (15)

  1. Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer (10) eines Turbotriebwerks, enthaltend eine Brennstoffeinspritzdüse (36) und eine der Einspritzdüse koaxial zu dieser nachgelagerte Venturi-Einrichtung (56), wobei die Venturi-Einrichtung eine Innenfläche (72) aufweist, die eine Vormischkammer (74) abgrenzt, in welcher der Brennstoff und ein Luftstrom vermischt werden, der von einem Außenbehälter (46) kommt und eine der Venturi-Einrichtung vorgelagerte Primärschleife (52) durchströmt, wobei die Venturi-Einrichtung einen ringförmigen Innenhohlraum (84) zur Luftzirkulation aufweist, dadurch gekennzeichnet, dass der ringförmige Innenhohlraum (84) zur Luftzirkulation über Lufteinlassleitungen (92, 96) mit dem Außenbehälter und über Luftauslassleitungen (94) mit der Vormischkammer verbunden ist, wobei die Luftauslassleitungen an der Innenfläche der Venturi-Einrichtung ausmünden.
  2. Einspritzvorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Venturi-Einrichtung (56) an ihrem vorderen Ende ein ringförmiger Flansch aufweist, die sich radial nach außen erstreckt und die Primärschleife (52) von einer Sekundärschleife (54) zum Durchtritt eines zweiten Luftstroms trennt, wobei der ringförmige Hohlraum (84) sich bis zum Flansch der Venturi-Einrichtung erstreckt.
  3. Einspritzvorrichtung nach Anspruch 2, dadurch gekennzeichnet, dass der ringförmige Hohlraum (84) der Venturi-Einrichtung im Schnitt im Wesentlichen eine L-Form hat.
  4. Einspritzvorrichtung nach Anspruch 2 oder 3, dadurch gekennzeichnet, dass die Venturi-Einrichtung (56) aus zwei ringförmigen Teilen (80, 82) mit im Wesentlichen L-förmigem Schnitt ausgebildet ist, die koaxial ineinandergreifen und durch Verlöten bzw. Verschweißen aneinander befestigt sind, wobei das erste und das zweite Teil den ringförmigen Hohlraum (84) zur Luftzirkulation zwischen sich eingrenzen.
  5. Einspritzvorrichtung nach Anspruch 4, dadurch gekennzeichnet, dass das erste Teil (80) sich vor dem zweiten Teil und innerhalb desselben erstreckt, wobei dieses erste Teil eine im Wesentlichen radial verlaufende vordere Ringwand (86) aufweist, die an ihrem Innenumfang mit einer im Wesentlichen zylindrischen hinteren Wand (88) verbunden ist, in welcher die Luftauslassleitungen (94) ausgebildet sind.
  6. Einspritzvorrichtung nach Anspruch 5, dadurch gekennzeichnet, dass das zweite Teil (82) eine im Wesentlichen radial verlaufende, vordere Ringwand (84) aufweist, die an ihrem Innenumfang mit einer im Wesentlichen zylindrischen hinteren Wand (86) verbunden ist, wobei die radial verlaufende Wand an ihrem Außenumfang mit dem Außenumfang der radial verlaufenden Wand des ersten Teils (80) verbunden ist und seine zylindrische Wand an ihrem hinteren Ende an das hintere Ende der zylindrischen Wand des ersten Teils befestigt ist.
  7. Einspritzvorrichtung nach Anspruch 6, dadurch gekennzeichnet, dass zumindest ein Teil der Lufteinlassleitungen (92) sich im Wesentlichen radial zur Achse der Einspritzdüse erstreckt und am Außenumfang der radial verlaufenden Wand eines bzw. jedes Teils (80, 82) ausgebildet ist.
  8. Einspritzvorrichtung nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass zumindest ein Teil der Lufteinlassleitungen (96) sich im Wesentlichen parallel zur Achse der Einspritzdüse erstreckt und durch Schaufeln der Sekundärschleife (54) und durch die radial verlaufende Wand des zweiten Teils (82) hindurch ausgebildet ist.
  9. Einspritzvorrichtung nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Luftauslassleitungen (94) in axialer und umfänglicher Richtung bezüglich der Achse der Einspritzdüse geneigt in der gleichen Richtung wie die Schaufeln der Primärschleife (52) verlaufen.
  10. Einspritzvorrichtung nach Anspruch 9, dadurch gekennzeichnet, dass der axiale Neigungswinkel einer jeden Auslassleitung (94), der zwischen der Achse dieser Leitung und der Achse der Einspritzdüse gebildet ist, zwischen etwa 10 und 40° beträgt, wobei dieser Winkel in einer Ebene gemessen wird, die durch die Achse der Einspritzdüse tritt.
  11. Einspritzvorrichtung nach Anspruch 9 oder 10, dadurch gekennzeichnet, dass der umfängliche Neigungswinkel einer jeden Auslassleitung (94), der zwischen der Achse dieser Leitung und einer durch die Achse der Einspritzdüse tretenden Ebene gebildet wird, zwischen etwa 50 und 75° beträgt, wobei dieser Winkel in einer Ebene senkrecht zur Achse der Einspritzdüse gemessen wird.
  12. Einspritzvorrichtung nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Ausmündungen der Luftauslassleitungen (94) gleichmäßig um die Achse der Einspritzdüse herum angeordnet und auf eine, zwei, drei oder vier Ringreihen verteilt sind, die axial voneinander beabstandet sind.
  13. Einspritzvorrichtung nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass sie zwischen 10 und 30 Lufteinlassleitungen (92, 96) und zwischen 10 und 30 Luftauslassleitungen (94) aufweist.
  14. Turbotriebwerk, wie etwa Turbostrahltriebwerk oder Turboprop-Triebwerk für Flugzeige, dadurch gekennzeichnet, dass es eine Einspritzvorrichtung (32) nach einem der vorangehenden Ansprüche enthält.
  15. Venturi-Einrichtung für eine Einspritzvorrichtung nach einem der Ansprüche 1 bis 13, enthaltend eine Innenfläche (72) mit einem Kragen, wobei die Venturi-Einrichtung aus zwei ringförmigen Teilen (80, 82) mit im Wesentlichen L-förmigem Schnitt gebildet sind, die koaxial ineinander befestigt sind und zwischen sich einen Innenhohlraum (84) zur Luftzirkulation eingrenzen, dadurch gekennzeichnet, dass das ringförmige Innenteil (80) eine zylindrische Wand mit Luftauslassleitungen (94) enthält, die an einem ihrer Enden mit dem Innenhohlraum verbunden sind und am anderen ihrer Enden an der Innenfläche (72) ausmünden, und dass das ringförmige Außenteil (82) eine radial verlaufende Ringwand enthält, die an ihrem Außenumfang Lufteinlassleitungen (92, 96) aufweist, die an einem ihrer Enden mit dem Innenhohlraum (84) verbunden sind.
EP08169015.8A 2007-12-14 2008-11-13 Vorrichtung zum Einspritzen eines Gemisches aus Luft und Brennstoff in eine Brennkammer eines Turbotriebwerks Active EP2071242B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708703A FR2925146B1 (fr) 2007-12-14 2007-12-14 Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine

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EP2071242A1 EP2071242A1 (de) 2009-06-17
EP2071242B1 true EP2071242B1 (de) 2017-08-02

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US (1) US8312723B2 (de)
EP (1) EP2071242B1 (de)
JP (1) JP5260245B2 (de)
CA (1) CA2646959C (de)
FR (1) FR2925146B1 (de)
RU (1) RU2478878C2 (de)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2903169B1 (fr) * 2006-06-29 2011-11-11 Snecma Dispositif d'injection d'un melange d'air et de carburant, chambre de combustion et turbomachine munies d'un tel dispositif
FR2941288B1 (fr) 2009-01-16 2011-02-18 Snecma Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine
FR2952166B1 (fr) * 2009-11-05 2012-01-06 Snecma Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
US9951955B2 (en) 2011-05-17 2018-04-24 Snecma Annular combustion chamber for a turbine engine
FR2980554B1 (fr) * 2011-09-27 2013-09-27 Snecma Chambre annulaire de combustion d'une turbomachine
FR2986856B1 (fr) * 2012-02-15 2018-05-04 Safran Aircraft Engines Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine
US9441543B2 (en) * 2012-11-20 2016-09-13 Niigata Power Systems Co., Ltd. Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion
FR3033030B1 (fr) * 2015-02-20 2018-04-13 Safran Aircraft Engines Systeme d'injection d'un melange air-carburant dans une chambre de combustion de turbomachine d'aeronef, comprenant un venturi perfore de trous d'injection d'air
FR3080437B1 (fr) 2018-04-24 2020-04-17 Safran Aircraft Engines Systeme d'injection pour une chambre annulaire de combustion de turbomachine
CN111006243B (zh) * 2019-12-03 2021-03-30 哈尔滨工程大学 一种防回火燃油闪蒸旋流一体化喷嘴
US11378275B2 (en) * 2019-12-06 2022-07-05 Raytheon Technologies Corporation High shear swirler with recessed fuel filmer for a gas turbine engine
FR3106374B1 (fr) 2020-01-21 2022-01-21 Safran Aircraft Engines Circuit d’alimentation en carburant pour une chambre de combustion d’une turbomachine
FR3108162B1 (fr) 2020-03-10 2023-01-13 Safran Aircraft Engines Système d’injection pour une chambre annulaire de combustion de turbomachine
CN112983652B (zh) * 2021-03-12 2022-09-02 广州大学城华电新能源有限公司 一种燃气轮机进气控制系统
US11802693B2 (en) 2021-04-16 2023-10-31 General Electric Company Combustor swirl vane apparatus
US11598526B2 (en) 2021-04-16 2023-03-07 General Electric Company Combustor swirl vane apparatus
US11846423B2 (en) 2021-04-16 2023-12-19 General Electric Company Mixer assembly for gas turbine engine combustor
US11428411B1 (en) * 2021-05-18 2022-08-30 General Electric Company Swirler with rifled venturi for dynamics mitigation

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3570242A (en) 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
US3811278A (en) 1973-02-01 1974-05-21 Gen Electric Fuel injection apparatus
US4809512A (en) 1986-07-30 1989-03-07 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Air-fuel injection system for a turbojet engine
US5603211A (en) 1993-07-30 1997-02-18 United Technologies Corporation Outer shear layer swirl mixer for a combustor

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3121996A (en) * 1961-10-02 1964-02-25 Lucas Industries Ltd Liquid fuel combustion apparatus
FR2572463B1 (fr) * 1984-10-30 1989-01-20 Snecma Systeme d'injection a geometrie variable.
FR2585770B1 (fr) * 1985-08-02 1989-07-13 Snecma Dispositif d'injection a bol elargi pour chambre de combustion de turbomachine
FR2596102B1 (fr) * 1986-03-20 1988-05-27 Snecma Dispositif d'injection a vrille axialo-centripete
FR2717250B1 (fr) * 1994-03-10 1996-04-12 Snecma Système d'injection à prémélange.
RU2157954C2 (ru) * 1995-09-05 2000-10-20 Открытое акционерное общество "Самарский научно-технический комплекс им. Н.Д.Кузнецова" Топливовоздушная горелка
FR2752917B1 (fr) * 1996-09-05 1998-10-02 Snecma Systeme d'injection a degre d'homogeneisation avancee
US6412272B1 (en) * 1998-12-29 2002-07-02 United Technologies Corporation Fuel nozzle guide for gas turbine engine and method of assembly/disassembly
US6474071B1 (en) * 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
US20050229600A1 (en) * 2004-04-16 2005-10-20 Kastrup David A Methods and apparatus for fabricating gas turbine engine combustors
US7389643B2 (en) * 2005-01-31 2008-06-24 General Electric Company Inboard radial dump venturi for combustion chamber of a gas turbine
US20070119052A1 (en) * 2005-11-28 2007-05-31 General Electric Company Combustor dome repair method
FR2901349B1 (fr) * 2006-05-19 2008-09-05 Snecma Sa Chambre de combustion d'une turbomachine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3570242A (en) 1970-04-20 1971-03-16 United Aircraft Corp Fuel premixing for smokeless jet engine main burner
US3811278A (en) 1973-02-01 1974-05-21 Gen Electric Fuel injection apparatus
US4809512A (en) 1986-07-30 1989-03-07 Societe Nationale D'etude Et De Construction De Moteurs D-Aviation (Snecma) Air-fuel injection system for a turbojet engine
US5603211A (en) 1993-07-30 1997-02-18 United Technologies Corporation Outer shear layer swirl mixer for a combustor

Also Published As

Publication number Publication date
CA2646959C (fr) 2016-10-18
US20090151357A1 (en) 2009-06-18
FR2925146B1 (fr) 2009-12-25
RU2478878C2 (ru) 2013-04-10
FR2925146A1 (fr) 2009-06-19
US8312723B2 (en) 2012-11-20
JP5260245B2 (ja) 2013-08-14
RU2008149163A (ru) 2010-06-20
JP2009145039A (ja) 2009-07-02
EP2071242A1 (de) 2009-06-17
CA2646959A1 (fr) 2009-06-14

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