EP1806536B1 - Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboréacteur - Google Patents

Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboréacteur Download PDF

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Publication number
EP1806536B1
EP1806536B1 EP07100253.9A EP07100253A EP1806536B1 EP 1806536 B1 EP1806536 B1 EP 1806536B1 EP 07100253 A EP07100253 A EP 07100253A EP 1806536 B1 EP1806536 B1 EP 1806536B1
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EP
European Patent Office
Prior art keywords
fuel
annular
distribution chamber
fuel injector
primary circuit
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP07100253.9A
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German (de)
English (en)
French (fr)
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EP1806536A1 (fr
Inventor
Didier Hernandez
Thomas Noel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1806536A1 publication Critical patent/EP1806536A1/fr
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Classifications

    • 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
    • F23R3/283—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
    • 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 invention relates to a multimode injection device for a combustion chamber, in particular the combustion chamber of a turbojet engine. It relates more particularly to the cooling of the annular distribution chamber supplied by the secondary circuit and which communicates with a plurality of fuel ejection holes for the peripheral spraying of the fuel delivered by the secondary circuit.
  • the combustion chamber is provided with a plurality of injection devices regularly distributed circumferentially at the bottom thereof.
  • Each injection device comprises an arm in which coaxial ducts belonging respectively to a so-called primary fuel circuit and a so-called secondary fuel circuit are defined.
  • Each of the coaxial conduits defined inside the arm feeds two coaxial fuel spraying systems defined in the same spray head.
  • the primary circuit or idle circuit is designed to obtain a particularly fine spray of fuel. Its flow is limited but permanent.
  • the secondary circuit or full gas circuit is designed to supplement the fuel flow to the full throttle point, allowing, in particular, to achieve all the power required for takeoff. On the other hand, this secondary circuit is not used continuously and its flow is sometimes very low at certain speeds.
  • the patent EP 1 369 644 discloses a multimode injection device of this type.
  • the patent application EP 1 798 475 belonging to the state of the art according to Article 54 (3) EPC, describes an injection device for a turbomachine.
  • Compressed air from a high pressure compressor circulates in the crankcase where the combustion chamber is located. Part of the air passes through the injection devices, mixes with the fuel delivered by the primary and secondary circuits in the bottom of the combustion chamber, before igniting in it.
  • the injection device can be subjected to high temperatures (300 ° K to 950 ° K for full throttle) since it is installed in a hot air stream from the last stage of the high pressure compressor.
  • high temperatures 300 ° K to 950 ° K for full throttle
  • the secondary circuit may not be used or have a very low flow rate.
  • the invention proposes a new design of the spray head to eliminate the risk of coking by cooling the fuel delivered by the secondary circuit by the permanent circulation of the fuel delivered by the primary circuit.
  • the invention relates to a multimode injection device for a combustion chamber, of the type comprising two coaxial fuel spraying systems fed respectively by two circuits, a primary circuit with a permanent flow rate and an intermittent secondary circuit characterized by it comprises a spray head in which said secondary circuit is connected to an annular distribution chamber pierced with a plurality of regularly circumferentially distributed fuel ejection holes and wherein said primary circuit comprises at least a portion of the duct adjacent said distribution chamber, for its cooling.
  • Said duct portion comprises an outer annular section arranged radially outwardly with respect to said distribution chamber and an inner annular section formed radially inwardly with respect to the same distribution chamber.
  • the two annular sections can be connected in series.
  • the distribution chamber comprises two symmetrical parts fed separately while the two inner and outer annular sections each comprise two branches respectively adjacent said two symmetrical parts.
  • the spray head is constituted by the assembly of several parts.
  • an annular body connected to the arm has grooves cut on its downstream face and defining the distribution chamber and said duct portion of said primary circuit responsible for cooling.
  • An annular collar covers these grooves, said fuel ejection holes being made in this collar.
  • said grooves are the result of an electro-erosion treatment carried out at one time on a massive blank of this annular body.
  • FIG. 1 is schematically shown in section one of the multimode injection devices 11 mounted on the bottom wall 13 of an annular combustion chamber 15 of a turbo reactor.
  • two injection modes are combined and the device described comprises two fuel spraying systems, coaxial, fed respectively by two fuel distribution circuits, a primary circuit 17, here at constant flow and a secondary circuit 19 , here at intermittent flow.
  • the two circuits share an arm 21 in which are arranged two coaxial conduits 17a, 19a respectively belonging to the primary and secondary circuits connected to a spraying head 18.
  • the primary permanent flow circuit has a relatively low flow rate. It is more particularly adapted to the engine idling speed.
  • the intermittent secondary circuit 19 is designed to complete the fuel flow to the full-throttle point, in particular to achieve all the power required for take-off. Its flow, which is essentially variable, can be zero or very low in certain plans.
  • Compressed air from a high pressure compressor (not shown) circulates in a housing 23 surrounding the combustion chamber 15. The air flows from upstream to downstream, in the direction of the arrow F.
  • upstream or downstream are used to designate the position of one element relative to another by considering the flow direction of the gases.
  • the fuel is mixed with air in the chamber bottom before igniting in said combustion chamber.
  • the primary circuit 17 leads to an axial fuel ejection nozzle 27 (here we consider the X axis of the spray head itself) while the secondary circuit is connected to a distributor. 29 having an annular distribution chamber 30 communicating with a plurality of fuel ejection holes 31 regularly distributed circumferentially at the downstream end of the dispenser.
  • the spray head comprises an annular body 39 attached to the arm 21, in which holes are formed belonging to said primary and secondary circuits and connecting the conduits 17a 19a to the nozzle 27 and the distribution chamber 30, respectively.
  • annular body 39 attached to the arm 21, in which holes are formed belonging to said primary and secondary circuits and connecting the conduits 17a 19a to the nozzle 27 and the distribution chamber 30, respectively.
  • the spraying head 18 also comprises an annular air deflector 33, commonly called a “swirler”, installed radially outwardly relative to said plurality of ejection holes.
  • This deflector comprises fins 35 defining between them air ejection channels 36 regularly spaced circumferentially and directing the air to the fuel jets.
  • the distributor 29 consists of two annular parts engaged one inside the other (and brazed together) and defining between them said distribution chamber 30.
  • One of the parts is the body 39 mentioned above.
  • the other part is an annular flange 41 forming a kind of cover; it is engaged at the downstream end of the body.
  • the holes 31 are pierced in this collar 41.
  • the body 39 and the flange 41 comprise cylindrical spans of corresponding diameters, ensuring a good centering of one with respect to the other.
  • the two pieces are assembled by soldering.
  • grooves are cut on the downstream face of the body 39.
  • the groove 45 generally annular, defines the essential of the distribution chamber 30, this groove being closed by the collar 41 to form said chamber 30.
  • the other grooves 47, 48 define a conduit portion of the primary circuit 17 (they are also closed by the flange 41) and will be described in detail later.
  • the grooves 45, 47, 48 may be the result of an electro-erosion treatment carried out at one time on a solid blank of the annular body 39.
  • the electroerosion tool has a shape corresponding to the configuration of the visible imprints. on the figure 3 and which define these grooves 45, 47, 48.
  • the annular gyratory deflector 33 is formed of two annular pieces 51, 53 joined by brazing. It is visible in perspective on the figure 4 .
  • the two pieces form a kind of squirrel cage with the fins 35 of decreasing thickness towards the inside, as shown in FIG. figure 2 .
  • the upstream annular part 51 engages in the downstream annular part 53 comprising the fins 35.
  • the part 51 that is to say the upstream wall of the deflector, has an internal cylindrical surface 55 of diameter equal to the outer diameter of a spherical bearing 57 of the collar 41. This spherical bearing 57 of the distributor engages in the cylindrical bearing surface 55 of the deflector.
  • the downstream annular piece 53 is extended downstream by a divergent conical element 61, conventionally called a bowl, pierced with two series of holes 63, 65 regularly distributed circumferentially.
  • the holes 63 are made on the conical part of the element 61.
  • the holes 65 are made on a collar radial outer 67. They open opposite a radial deflector 69 ( Fig. 1 ).
  • the annular baffle 33 composed of two parts 51, 53 comprises two internally frustoconical walls 51a, 53a, coaxial, respectively upstream and downstream.
  • the wall 51a is defined in the part 51.
  • the wall 53a is defined in the part 53.
  • the conicity of these walls is directed downstream, that is to say that their diameter decreases from upstream to downstream .
  • the distribution chamber 30 also has a frustoconical downstream wall. This is the wall of the collar 41 in which the holes 31 are formed.
  • the outer face of this wall has a parallel generatrix or (as is the case here) coincides with the inner face of the upstream wall 51a of the annular deflector. .
  • the taper angle of these faces is between 45 ° and 80 °.
  • the axis of each hole 31 is perpendicular to the generatrix of the surface 51a at this point.
  • a median M for each air ejection channel 36 is defined as being a line equidistant from the parallel surfaces of its radially innermost part, at least.
  • the surface a of one of the fins 35 is flat while the surface b of the other fin, adjacent, has at least a short inner portion c, parallel to the surface a.
  • the median M is equidistant from the surfaces a and c.
  • the portion between a and c constitutes the calibration zone of the air ejection channel considered.
  • the surface b could be confused with the portion c.
  • each fuel ejection axis defined by an ejection hole 31 there is an air ejection channel 36 (between two fins 35), of which at least the radially innermost part (c). that is, the calibrating zone) has a median M substantially intersecting this fuel ejection axis.
  • the number of fuel ejection holes is equal to the number of air ejection channels.
  • the number of air ejection channels may be a multiple of the number of fuel ejection holes.
  • indexing means (notches and tenons) are provided so as to obtain the configuration of the figure 2 , assembly.
  • the distributor 29 is part of the injection device 11, the deflector 33 is mounted on the chamber bottom 13 (the injection device 11 and the chamber bottom 13 being oriented by the housing 23).
  • the distributor 29 slides in the deflector 33 at the surfaces 55 and 57.
  • This particular configuration which locates the air channels of the auger relative to the fuel ejection holes, makes it possible to optimize the spraying of this fuel.
  • the homogeneity of the air-fuel mixture improves combustion and reduces pollution.
  • the inclination of the walls 51a, 53a has the effect of less disturbing the flow of air through the gyratory baffle.
  • the overall axial size of the device is also reduced overall.
  • the spray head 18 also comprises a central piece 75 (forming a gyratory air deflector) mounted axially inside the annular body 39.
  • This part is represented in perspective on the figure 5 . It comprises fins 77 regularly spaced circumferentially. Grooves 78 are thus defined between these fins. The shape of these is such that the grooves are inclined relative to the axis X.
  • the grooves 78 are closed radially outwardly and define air ejection channels d another gyratory deflector or "spin" arranged around the nozzle 27.
  • the part 75 comprises a tapered conical downstream portion directed downstream, which engages in a corresponding conical portion defined in the body 39, at its upstream end.
  • the fins 77 are defined in this conical part, which further reduces the axial size (along X) of the spray head 18.
  • the part 75 upstream, has a cylindrical bearing surface 85 which fits into the a corresponding cylindrical bearing surface defined upstream of the body 39, for a good centering of the workpiece 75 in said body 39.
  • Indexing means provide positioning in the circumferential direction between the workpiece 75 and the body 39.
  • a closed cavity 79 is defined in the center of the piece 75. the nozzle 27 is mounted in this cavity.
  • a conduit 80 is provided in a fin 77 and opens into said cavity 79. It constitutes the terminal part of the primary circuit.
  • This duct 80 communicates with another bore 81 of the body 39 which opens at one end of the groove 48 ( figure 3 ).
  • a bore 82 formed in the body 39 connects an end of the groove 47 to the end of the conduit 17a which belongs to the primary circuit defined above.
  • said primary circuit comprises at least a portion of duct 86 adjoining said distribution chamber 30, for its cooling.
  • this duct portion 86 is constituted by the channels defined by the grooves 47, 48 covered by the flange 41.
  • said duct portion comprises an outer annular section (corresponding to the groove 47) formed radially outwardly. relative to said distribution chamber and an inner annular section (corresponding to the groove 48) formed radially inwardly with respect to said distribution chamber.
  • the configuration obtained by electroerosion defines a radial passage 84 passing through the groove 45 and establishing the communication between the grooves 47 and 48.
  • a radial wall 87 is also defined in the vicinity of the orifice of the bore 81, forcing the fuel to flow. practically 360 ° in the inner annular section.
  • the two aforementioned annular sections constituting said duct portion 86 of the primary circuit are connected in series.
  • the fuel of the primary circuit enters this labyrinth through the bore 82, circularly circulates around the distribution chamber 30 radially externally and then radially inwardly relative thereto before reaching the cavity 79 via the bore 81 and the conduit 80.
  • the figure 6 illustrates a variant of the configuration of the distribution chamber 30 and said conduit portion 86a ensuring its cooling.
  • the distribution chamber comprises two symmetrical parts (defined by two grooves 45a, 45b symmetrical) separately supplied by two holes 19b1, 19b2, both connected to the conduit 19a.
  • the outer annular section comprises two such symmetrical branches (grooves 47a, 47b) which separately feed the two holes 82a, 82b communicating with the cavity 79 through the ducts 80a and 80b. They meet at a radial passage 87 formed between the two symmetrical parts of the distribution chamber and joining the inner annular section which also comprises two symmetrical branches (grooves 48a, 48b) which meet at a point diametrically opposed to the passage 87, to join the piercing 81 fed by the conduit 17a.
  • the air rotating deflector arranged around the nozzle 27 has been modified. It consists of two axially assembled annular guides 90, 91 defining two contra-rotating "tendrils" .
  • annular guides 90, 91 defining two contra-rotating "tendrils” .
  • Another annular guide 91 extends downstream to the bowl to avoid interactions with the "spin" associated with the distribution chamber 30. This arrangement produces an increase in "shear" in the air flows, which participate the atomization of the fuel from the nozzle.

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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)
  • Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
EP07100253.9A 2006-01-09 2007-01-08 Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboréacteur Active EP1806536B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650069A FR2896030B1 (fr) 2006-01-09 2006-01-09 Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboreacteur

Publications (2)

Publication Number Publication Date
EP1806536A1 EP1806536A1 (fr) 2007-07-11
EP1806536B1 true EP1806536B1 (fr) 2017-08-16

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EP07100253.9A Active EP1806536B1 (fr) 2006-01-09 2007-01-08 Refroidissement d'un dispositif d'injection multimode pour chambre de combustion, notamment d'un turboréacteur

Country Status (7)

Country Link
US (1) US7891193B2 (ru)
EP (1) EP1806536B1 (ru)
JP (1) JP5008401B2 (ru)
CN (1) CN101000136B (ru)
CA (1) CA2572857C (ru)
FR (1) FR2896030B1 (ru)
RU (1) RU2431082C2 (ru)

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7513116B2 (en) * 2004-11-09 2009-04-07 Woodward Fst, Inc. Gas turbine engine fuel injector having a fuel swirler
GB2439097B (en) * 2006-06-15 2008-10-29 Rolls Royce Plc Fuel injector
FR2911667B1 (fr) * 2007-01-23 2009-10-02 Snecma Sa Systeme d'injection de carburant a double injecteur.
FR2919898B1 (fr) * 2007-08-10 2014-08-22 Snecma Injecteur multipoint pour turbomachine
GB2455729B (en) * 2007-12-19 2012-06-13 Rolls Royce Plc A fuel distribution apparatus
US8549859B2 (en) * 2008-07-28 2013-10-08 Siemens Energy, Inc. Combustor apparatus in a gas turbine engine
US8528340B2 (en) * 2008-07-28 2013-09-10 Siemens Energy, Inc. Turbine engine flow sleeve
US20100071377A1 (en) * 2008-09-19 2010-03-25 Fox Timothy A Combustor Apparatus for Use in a Gas Turbine Engine
JP4733195B2 (ja) 2009-04-27 2011-07-27 川崎重工業株式会社 ガスタービンエンジンの燃料噴霧装置
FR2951245B1 (fr) * 2009-10-13 2013-05-17 Snecma Dispositif d'injection multi-point pour une chambre de combustion de turbomachine
FR2951246B1 (fr) * 2009-10-13 2011-11-11 Snecma Injecteur multi-point pour une chambre de combustion de turbomachine
US9151227B2 (en) * 2010-11-10 2015-10-06 Solar Turbines Incorporated End-fed liquid fuel gallery for a gas turbine fuel injector
FR2971039B1 (fr) 2011-02-02 2013-01-11 Turbomeca Injecteur de chambre de combustion de turbine a gaz a double circuit de carburant et chambre de combustion equipee d'au moins un tel injecteur
US9188063B2 (en) 2011-11-03 2015-11-17 Delavan Inc. Injectors for multipoint injection
US11015808B2 (en) * 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
FR2996286B1 (fr) * 2012-09-28 2014-09-12 Snecma Dispositif d'injection pour une chambre de combustion de turbomachine
GB2516445A (en) * 2013-07-22 2015-01-28 Rolls Royce Plc A fuel spray nozzle
FR3013421B1 (fr) * 2013-11-20 2018-12-07 Safran Aircraft Engines Dispositif d'injection multipoint pour moteur d'aeronef
JP6240327B2 (ja) 2013-11-27 2017-11-29 ゼネラル・エレクトリック・カンパニイ 流体ロックとパージ装置とを有する燃料ノズル
CN104713128B (zh) * 2013-12-12 2018-09-11 中国航发商用航空发动机有限责任公司 喷嘴杆部、燃油喷嘴及航空发动机燃气轮机
US9995220B2 (en) 2013-12-20 2018-06-12 Pratt & Whitney Canada Corp. Fluid manifold for gas turbine engine and method for delivering fuel to a combustor using same
CN105829800B (zh) 2013-12-23 2019-04-26 通用电气公司 用于空气协助的燃料喷射的燃料喷嘴结构
JP6695801B2 (ja) 2013-12-23 2020-05-20 ゼネラル・エレクトリック・カンパニイ 可撓性支持構造体を備えた燃料ノズル
JP6535442B2 (ja) 2014-08-18 2019-06-26 川崎重工業株式会社 燃料噴射装置
US10385809B2 (en) 2015-03-31 2019-08-20 Delavan Inc. Fuel nozzles
US9897321B2 (en) * 2015-03-31 2018-02-20 Delavan Inc. Fuel nozzles
US10364751B2 (en) * 2015-08-03 2019-07-30 Delavan Inc Fuel staging
US9889418B2 (en) * 2015-09-29 2018-02-13 Dow Global Technologies Llc Fluidized fuel gas combustor system for a catalytic dehydrogenation process
US10876477B2 (en) 2016-09-16 2020-12-29 Delavan Inc Nozzles with internal manifolding
US11181269B2 (en) * 2018-11-15 2021-11-23 General Electric Company Involute trapped vortex combustor assembly
CN111981512B (zh) * 2020-07-31 2022-09-02 中国航发贵阳发动机设计研究所 一种燃油空气雾化装置
KR102498060B1 (ko) * 2021-04-12 2023-02-10 동우에이치에스티 주식회사 가스 공급유닛
CN114810424B (zh) * 2022-04-29 2024-02-02 西北工业大学 一种基于喷雾冷却的发动机主动冷却凹腔结构

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1798475A2 (en) * 2005-12-13 2007-06-20 Kawasaki Jukogyo Kabushiki Kaisha Fuel spraying apparatus of gas turbine engine

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2172383A (en) * 1936-03-23 1939-09-12 Honn Harlan Verne Fuel injection device
GB1114728A (en) * 1967-03-20 1968-05-22 Rolls Royce Burner e.g. for a gas turbine engine combustion chamber
US3684186A (en) * 1970-06-26 1972-08-15 Ex Cell O Corp Aerating fuel nozzle
US4139157A (en) * 1976-09-02 1979-02-13 Parker-Hannifin Corporation Dual air-blast fuel nozzle
US4111369A (en) * 1977-07-05 1978-09-05 General Motors Corporation Fuel nozzle
US4798330A (en) * 1986-02-14 1989-01-17 Fuel Systems Textron Inc. Reduced coking of fuel nozzles
US4865542A (en) * 1988-02-17 1989-09-12 Shell Oil Company Partial combustion burner with spiral-flow cooled face
US5423178A (en) * 1992-09-28 1995-06-13 Parker-Hannifin Corporation Multiple passage cooling circuit method and device for gas turbine engine fuel nozzle
FR2721694B1 (fr) * 1994-06-22 1996-07-19 Snecma Refroidissement de l'injecteur de décollage d'une chambre de combustion à deux têtes.
US6161387A (en) * 1998-10-30 2000-12-19 United Technologies Corporation Multishear fuel injector
US6321541B1 (en) * 1999-04-01 2001-11-27 Parker-Hannifin Corporation Multi-circuit multi-injection point atomizer
US6755024B1 (en) * 2001-08-23 2004-06-29 Delavan Inc. Multiplex injector
US6802178B2 (en) * 2002-09-12 2004-10-12 The Boeing Company Fluid injection and injection method
US6898926B2 (en) * 2003-01-31 2005-05-31 General Electric Company Cooled purging fuel injectors

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1798475A2 (en) * 2005-12-13 2007-06-20 Kawasaki Jukogyo Kabushiki Kaisha Fuel spraying apparatus of gas turbine engine

Also Published As

Publication number Publication date
FR2896030B1 (fr) 2008-04-18
EP1806536A1 (fr) 2007-07-11
JP2007183094A (ja) 2007-07-19
RU2007100426A (ru) 2008-07-20
CA2572857C (fr) 2014-10-21
CN101000136A (zh) 2007-07-18
FR2896030A1 (fr) 2007-07-13
JP5008401B2 (ja) 2012-08-22
CN101000136B (zh) 2010-12-08
CA2572857A1 (fr) 2007-07-09
RU2431082C2 (ru) 2011-10-10
US20070157616A1 (en) 2007-07-12
US7891193B2 (en) 2011-02-22

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