EP1512913A1 - Eindüsungsvorrichtung für Luft und Brennstoff mit Mitteln zur Erzeugung von Kaltplasma - Google Patents

Eindüsungsvorrichtung für Luft und Brennstoff mit Mitteln zur Erzeugung von Kaltplasma Download PDF

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Publication number
EP1512913A1
EP1512913A1 EP04292036A EP04292036A EP1512913A1 EP 1512913 A1 EP1512913 A1 EP 1512913A1 EP 04292036 A EP04292036 A EP 04292036A EP 04292036 A EP04292036 A EP 04292036A EP 1512913 A1 EP1512913 A1 EP 1512913A1
Authority
EP
European Patent Office
Prior art keywords
air
fuel
fuel injector
downstream
bowl
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP04292036A
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English (en)
French (fr)
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EP1512913B1 (de
Inventor
Michel Cazalens
Frédéric Beule
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 Moteurs SA
SNECMA SAS
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Publication of EP1512913A1 publication Critical patent/EP1512913A1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/99005—Combustion techniques using plasma gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K2300/00—Pretreatment and supply of liquid fuel
    • F23K2300/10—Pretreatment
    • F23K2300/101—Application of magnetism or electricity

Definitions

  • the present invention relates to the general field of systems for injecting an air / fuel mixture into a chamber of turbomachine combustion. It aims more particularly at a system Injection equipped with a cold plasma generator capable of controlling the reactivity of the air / fuel mixture during injection into the chamber of combustion.
  • the main purpose of the combustion chamber of a turbomachine is to reconcile the implementation of the operational performance of the chamber (combustion efficiency, stability domain, domain ignition and re-ignition, lifetime of the combustion chamber, etc.) in according to the mission envisaged for the airplane on which the turbomachine while minimizing polluting emissions (nitrogen oxides, carbon monoxide, unburnt hydrocarbons, etc.).
  • polluting emissions nitrogen oxides, carbon monoxide, unburnt hydrocarbons, etc.
  • the combustion chamber of a turbomachine is composed typically of several systems: a system for injecting a mixture air / fuel in a flame tube, a cooling system and a dilution system.
  • the combustion is organized mainly within of a first part of the flame tube (primary zone) in which it is stabilized by means of recirculation zones of the mixture air / fuel induced by the flow of air from the injection system.
  • primary zone In this primary zone of the mixing tube, different phenomena are implemented: injection and atomization into fines fuel droplets, evaporation of droplets, mixture of fuel vapors with air and chemical oxidation reactions of the fuel by the oxygen of the air.
  • the chemical activity used is more low and the flow is diluted by means of dilution holes.
  • staged combustion which can be presented under two forms: double-headed combustion chambers and so-called “multipoint” injection systems.
  • Staged double-head combustion chambers are rooms whose fuel injectors are distributed over a so-called head "Pilot” and on a so-called “take-off” head.
  • the pilot head works in permanence and thus prevents the combustion chamber from goes off, while the take-off head is designed to reduce NOx emissions.
  • this solution appears satisfactory, a room with double stepped head remains difficult to fly and expensive given the doubling of the number of fuel injectors per compared to a conventional single head combustion chamber.
  • the injection systems of the air / fuel mixture “Multipoint” are systems in which the injection of air and fuel is carried by several independent ducts and is regulated in function of the operating speed of the turbomachine. Disadvantage The main feature of such multipoint injection systems lies in the complexity different fuel systems and the control system.
  • the main object of the present invention is therefore to overcome such disadvantages by proposing a system for injecting a mixture air / fuel in a combustion chamber that can increase the resistance of the combustion chamber to extinction while maintaining a simple architecture and limiting polluting emissions.
  • a system for injecting a mixture air / fuel in a turbomachine combustion chamber having a hollow tubular structure for the flow of the mixture air / fuel to the combustion chamber, means for injecting fuel disposed at an upstream end of the tubular structure hollow, and air injection means arranged downstream of the means fuel injection system, characterized in that it further comprises means for generating cold plasmas arranged downstream of the means injection of air to generate active species in the flow of air / fuel mixture and to pre-break the molecules of the air / fuel mixture, and means for controlling the means of generation of cold plasmas according to the operating regime of the turbomachine.
  • the cold plasma generator makes it possible to adapt the times characteristics of the chemical reactions according to the operation of the turbomachine. Time control characteristics of the chemical reactions is ensured by the production and the injection of active species (radical species and excited species) in the flow of the air / fuel mixture and by pre-breaking the molecules of air and fuel.
  • the means for generating cold plasmas can as well adapt to aeromechanical injection systems as aerodynamic type injection systems.
  • the means for generating cold plasmas may comprise at least one pair of electrodes connected to a current generator alternative which is controlled by the control means.
  • these means of generation of cold plasmas may include a winding solenoidal connected to an alternating current generator which is also driven by the control means.
  • the present invention makes it easy to adapt to known systems for injecting an air / fuel mixture without causing important transformations of these injection systems.
  • the means for generating cold plasmas can be associated with one or all injection systems of the same chamber of combustion, which improves the operation of the chambers existing combustion.
  • the injection system according to the present invention can also work for operating points of the turbomachine where the combustion is stabilized so that the output of combustion is increased for these points. For example, if we considers a re-ignition point at altitude in auto-rotation, the volume of the focus must be sufficient to ensure combustion efficiency allowing the turbomachine to accelerate. In these circumstances, this invention reduces the volume of combustion fires and therefore to reduce the mass of the turbomachine.
  • the present invention makes it possible to simplify the systems ignition of the combustion chamber by integrating this function into injection system.
  • the ignition is in fact carried out by the means of generation of cold plasmas powered with energy and frequency adapted. It is thus possible to delete conventional devices spark plugs and avoid the problems associated with them (cooling of the body and nose of the candle, disturbance of the fireplace cooling, spark plug life, etc.).
  • FIG. 1 represents, in longitudinal section, a system injection according to one embodiment of the invention.
  • the injection system is of the aeromechanical type.
  • the X-X longitudinal axis injection system 10 consists of essentially a tubular structure for the flow of a mixture air / fuel to the firebox of a combustion chamber 12 of a turbine engine. This air / fuel mixture is intended to be burned in the combustion chamber 12.
  • the combustion chamber 12 is for example of the type annular. It is delimited by two annular walls (not shown in Figure 1) spaced radially from the axis of the turbomachine and connected upstream by a chamber bottom 14.
  • the bottom of chamber 14 has a plurality of openings 16 regularly spaced circumferentially around the axis of the turbomachine. In each of these openings 16 is mounted an injection system 10 according to the invention.
  • the gases resulting from the combustion of the air / fuel mixture flow downstream into the combustion chamber 12 to supply a high-pressure turbine (not shown) disposed at the outlet of the combustion chamber.
  • An annular deflector 18 is mounted in the opening 16 by through a sleeve 20. This deflector is mounted parallel to the chamber bottom 14 and plays a role of heat shield against the radiation from the combustion flame.
  • a bowl 22 is mounted inside the sleeve 20.
  • This bowl 22 has a wall 22a flared downstream in the extension of a substantially cylindrical wall 22b arranged coaxially with the axis longitudinal X-X injection system 10. Through its angle opening, the bowl 22 distributes the air / fuel mixture in the primary zone of the combustion chamber.
  • the flared wall 22a of bowl has a plurality of holes 24 for introducing air into the hearth of combustion. These holes 24 make it possible to refocus the flow of the air / fuel mixture around the X-X longitudinal axis at the bowl outlet.
  • the bowl 22 has an annular flange 25 which extends parallel to the chamber bottom 14. As for the deflector 18, this flange 25 forms a heat shield between the radiation of the combustion flame and bowl 22.
  • the collar is cooled by impact of air passing through holes 25a through the flared wall 22a of the bowl.
  • the cylindrical wall 22b of the bowl 22 surrounds a venturi 26 having an inner contour of convergent divergent form.
  • the venturi 26 allows to delimit the air flows coming from an internal swirler 28 and of an external swirler 30.
  • the venturi 26 comprises a radial flange 26a separating the internal swirler 28 and the external swirler 30.
  • the internal swirler 28 is of radial type. She is willing to upstream of the venturi 26 and delivers an internal radial air flow inside the venturi.
  • the external swirler 30 is also of the radial type. She is willing upstream of the cylindrical wall 22b of the bowl 22 and delivers a flow of air external radial between the venturi 26 and the cylindrical wall 22b of the bowl 22.
  • the internal 28 and outer 30 tendrils rotate the flow of the air / fuel mixture and thus increase turbulence and shear to promote the atomization of the fuel and its mixing with the air.
  • the internal swirler 28 is secured to a piece of retainer 32 having an annular groove 34 open on the axis side X-X longitudinal injection system.
  • a support ring 36 is mounted in the annular groove 34. This support ring 36 allows the fixation of the downstream end of a fuel injector 38 centered on the longitudinal axis X-X injection system.
  • the support ring 36 can move radially in the annular groove 34 to allow a catching up gambling that can cause the thermal stresses that are subjected the various elements of the injection system 10.
  • the support ring 36 In its part in contact with the fuel injector 38, the support ring 36 is pierced with a plurality of orifices 40 regularly Circularly spaced around the X-X longitudinal axis of the system injection. These orifices 40 act as a purge by ventilating the jet of fuel 38 and avoiding the formation of coke at the downstream end of this one.
  • the support ring 36, the internal 28 and external 30 tendrils, the venturi 26 and the bowl 22 thus form the hollow tubular structure 41 of injection system 10 in which flows the air / fuel mixture.
  • the fuel injector 38 is secured upstream of an arm injector (not shown). After flowing in the arm injector, the fuel is sprayed by the injector 38 in the form of a fuel cone that comes in part to hit the venturi 26. Once sprayed, the fuel is mixed with the air from the internal tendrils 28 and external 30 and holes 24 of the bowl 22.
  • the fuel is sprayed in the form of fine droplets under the effect of aerodynamic shear differences between the velocities of the liquid flow and of the gas flow.
  • the air / fuel mixture thus formed is then introduced into the combustion chamber 12 to be burned.
  • the injection system 10 further comprises means for generating cold plasmas in order to generate species active in the flow of the air / fuel mixture and to achieve a pre-breaking molecules of the air / fuel mixture.
  • Means of command are also provided in order to control these means of generation of cold plasmas according to the operating regime of the turbomachine.
  • these means for generating cold plasmas can be arranged around the downstream end of the venturi 26 (implantation A), either around the upstream end of the bowl 22 (implantation B), or around the downstream end of the venturi 26 and around the upstream end of the bowl 22 (implantation C).
  • FIG. 2A illustrates the implantation A of generation means of cold plasmas around the downstream end of the venturi 26. This figure schematically represents, in front view, the circular downstream end of the venturi.
  • the means for generating plasmas are made by at least one pair of electrodes 42 arranged on the circumference of the downstream end of the venturi 26. These electrodes 42 are connected by means of electrical wires 44 to a current generator 46. The generator is controlled by a control system steering 48 described later.
  • the electrodes 42 are arranged on the same diameter of the venturi 26, ie they are aligned radially one with respect to the other. However, as illustrated in dashed lines by couple of electrodes 42 ', the latter can be radially offset relative to each other by being arranged on different radii of the venturi 26.
  • the number of electrode pairs may be more important. These electrodes are then angularly distributed around the circumference of the venturi, for example uniform way. Moreover, in the case of several couples electrodes, these couples can be powered by the generator of alternating current 46 simultaneously or sequentially.
  • the means of generating cold plasmas can also be made in the form of a solenoidal winding connected to the AC generator.
  • the outer surface of the venturi has a solenoidal winding.
  • implantation B The implantation of the means for generating cold plasmas around the upstream end of the bowl 22 (implantation B) corresponds to implementation A described above and will not be repeated.
  • FIG. 2B illustrates the implantation C of the generation means of cold plasmas around the downstream end of the venturi 26 and around the upstream end of the bowl 22.
  • the venturi 26 and the bowl 22 each have a substantially circular cross-section and are arranged concentrically with respect to each other.
  • the means for generating plasmas are made by at least one pair of electrodes 42, one of which electrodes is disposed on the circumference of the downstream end of the venturi 26 and the other electrode is disposed on the circumference of the end upstream of the bowl 22.
  • These electrodes 42 are also connected by via electrical wires 44 to an alternating current generator 46 controlled by a steering system 48.
  • the electrodes 42 are arranged on the same radius of the ring defined by the downstream end of the venturi 26 and the upstream end of the bowl 22, that is to say that they are aligned radially one with respect to the other. However, as illustrated in dashed lines by couple of electrodes 42 ', the latter can be radially offset relative to each other by being arranged on different radii of the crowned.
  • the number of electrode pairs may be more important depending on the nature and the need of the application.
  • the arrangement of these pairs of electrodes may vary on the circumference of the venturi and the bowl. Couples electrodes can also be powered simultaneously or sequentially.
  • the pairs of electrodes allow to create, via the generator of alternating current 46 connected to the control system 48, a discharge in the air / fuel mixture flowing between the electrodes (or inside the solenoidal winding).
  • the parameters of the AC generator 46 are controlled by the pilotage system 48 in accordance with the operation of the turbomachine, compared to the active species (radical species, excited species) that one wishes to produce, by the desired degree of pre-breakage of the air molecules and fuel and in relation to the intended function (ignition, re-ignition altitude, extension of the stability domain, active control of the combustion, etc.).
  • cold plasmas are characterized by an electric discharge of type "streamer", ie by a propagation of an ionization front.
  • Cold plasmas are characterized also by a thermodynamic imbalance in which the temperature of the electrons emitted during the electric discharge is very high compared to the air / fuel mixture passing through the discharge electric. This feature has the main advantage of allowing the production of active radical species in the flow of the mixture air / fuel with less energy expenditure than with plasmas hot.
  • Such an alternating current generator 46 making it possible to generate cold plasmas is reflected in particular by a duration electrical pulses between 2 and 50 nanoseconds, and preferably between 2 and 30 nanoseconds.
  • a generator of electric current for the production of hot plasmas delivers electrical pulses typically having a duration of the order of the hundred microsecond.
  • the 48 steering system can use information captured in real time within the home of combustion.
  • the control system 48 it may be planned to connect to the control system 48 an instability detector placed in the combustion chamber.
  • Such instability detector measures the pressure (or any other parameter) at inside the combustion chamber and transmits it in real time to the steering system.
  • Such an optical detector thus makes it possible to inform in time real the driving system in case of extinction of the flame of combustion.
  • the injection system is also of type aeromechanical so that only the differences with the injection system illustrated in Figure 1.
  • this injection system is of the type LLP (for "Lean Premixed Prevaporized").
  • the Injection system 50 of longitudinal axis Y-Y is essentially composed of a hollow tubular structure 51 for the flow of a mixture air / fuel to the firebox hearth 12 of a turbine engine.
  • An annular baffle 52 is mounted in the opening 16 practiced in the chamber bottom 14 via a sleeve 54.
  • a bowl 56 forming a vaporization and premix tube is mounted inside the sleeve 54.
  • This bowl 56 has a downstream wall 56a divergent which is formed in the extension of an intermediate wall 56b convergent, itself formed in the extension of a wall substantially cylindrical upstream 56c arranged coaxially with the axis longitudinal Y-Y injection system.
  • this bowl 56 can feed the combustion chamber by a homogeneous air / fuel mixture poor to avoid settlement in the focus of generating stoichiometric combustion conditions NOx emissions.
  • the bowl 56 surrounds a first venturi 58.
  • This first venturi 58 has the function of guiding air through holes 60 formed in through the cylindrical wall 56c of the bowl 56, at its end upstream. This air is intended to cool the bowl 56 while circulating along the internal face of it.
  • the first venturi 58 surrounds a second venturi 62 having a internal contour of convergent divergent form.
  • the second venturi 62 delimits the air flows coming from a radial internal swirler 64 and a radial external swirler 66.
  • the internal swirler 64 delivers a radial air flow to the inside of the second venturi 62 and the external swirler 66 delivers a flow of air radial between the first venturi 58 and the second venturi 62.
  • a fuel injector 68 centered on the Y-Y longitudinal axis of the injection system is arranged upstream of the internal swirler 64. fuel injector is attached to the injection system via a support ring 70.
  • the generation means of cold plasmas to generate active species in the flow of the air / fuel mixture and to pre-break the air / fuel mixture molecules are arranged around the end downstream of the bowl 56 (implantation D in FIG. 3).
  • the implantation D of cold plasma generation means around the downstream end of the bowl 56 corresponds to the illustrated implantation in Figure 2A.
  • the generation means cold plasmas can thus be realized in the form of at least one pair of electrodes disposed on the circumference of the downstream end of the bowl or in the form of a solenoidal winding.
  • the implantation D of the means of generation of cold plasmas allows, on the one hand to increase the area of stability of the combustion chamber by pushing the extinction limits a poor mixture of air / fuel and, on the other hand, to control the in order to reduce its vulnerability to instabilities of combustion.
  • the injection system is of the aerodynamic type.
  • the system injection device 72 with a longitudinal axis Z-Z essentially consists of a hollow tubular structure 73 for the flow of a mixture air / fuel to the firebox hearth 12 of a turbine engine.
  • a deflector 74 is mounted in the opening 16 made in the chamber bottom 14 via a sleeve 76.
  • a bowl 78 is mounted inside the sleeve 76. This bowl has a divergent wall downstream.
  • the bowl 78 is extended by a ring retaining ring 80 which surrounds and maintains an injector fuel 82 centered on the Z-Z longitudinal axis of the injection system.
  • the fuel injector 82 has a first part tubular 84 disposed coaxially with the longitudinal axis Z-Z of the system 72.
  • This first tubular portion 84 defines a first axial internal volume 86 which opens at its downstream end for mixing air / fuel.
  • the inner surface of the first tubular portion 84 of the nozzle of fuel 82 surrounds a second tubular portion 90 which is also arranged coaxially with the longitudinal axis Z-Z of the system injection.
  • the first tubular portion 84 and the second tubular portion 90 define between them a second annular passage 92.
  • This second tubular part 90 further defines a second axial internal volume 94 which opens in the axial internal volume 86 of the first tubular portion 84.
  • the fuel injector 82 also has a plurality air supply channels 96 opening out of the injector and opening into the second axial internal volume 94, at one end upstream of the second tubular portion 90. These air supply channels 96 thus making it possible to inject air at an upstream end of the second tubular portion 90 in a substantially axial direction.
  • the fuel injector 82 comprises at minus a fuel input 98 in the form of a cylindrical recess. This cylindrical recess is fed with fuel by an injector arm (not shown).
  • Fuel supply channels 100 open in this cylindrical recess 98 and open into the second annular passage 92. These fuel supply channels therefore make it possible to inject fuel fuel between the first tubular portion 84 and the second portion tubular 90.
  • the fuel injector 82, the retaining ring 80 and the bowl 78 thus form the hollow tubular structure 73 of the injection system 72.
  • the injected fuel is atomized by the shear effect of the air. Indeed, a film of fuel is formed at the second annular passage 92. At the exit of the second tubular part 90, this film of fuel is subjected to the action of the air coming from air supply channels 96 before being subjected, at the exit of the first tubular portion 84, to the action of the air from the first passage ring 88.
  • the generation means of Cold plasmas can be implanted in three different zones: around the downstream end of the second tubular portion 90 (implantation E), around the downstream end of the first tubular portion 84 (implantation F) or around the downstream end of the annular retaining ring 80 and around the downstream end of the first tubular portion 84 (implantation G).
  • the means for generating cold plasmas can be made under the at least one pair of electrodes or in the form of a solenoidal winding.
  • the implantation G around the downstream end of the ring annular holding 80 and around the downstream end of the first tubular portion 84 corresponds to the implantation illustrated in FIG. 2B and so will not be detailed either.
  • the means of generation of cold plasmas can be realized in the form of at less a pair of electrodes.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
EP04292036A 2003-09-02 2004-08-11 Eindüsungsvorrichtung für Luft und Brennstoff mit Mitteln zur Erzeugung von Kaltplasma Active EP1512913B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0310379A FR2859272B1 (fr) 2003-09-02 2003-09-02 Systeme d'injection air/carburant, dans une chambre de combustion de turbomachine, ayant des moyens de generation de plasmas froids
FR0310379 2003-09-02

Publications (2)

Publication Number Publication Date
EP1512913A1 true EP1512913A1 (de) 2005-03-09
EP1512913B1 EP1512913B1 (de) 2008-10-22

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EP04292036A Active EP1512913B1 (de) 2003-09-02 2004-08-11 Eindüsungsvorrichtung für Luft und Brennstoff mit Mitteln zur Erzeugung von Kaltplasma

Country Status (9)

Country Link
US (1) US7114337B2 (de)
EP (1) EP1512913B1 (de)
JP (1) JP4252513B2 (de)
CA (1) CA2478876C (de)
DE (1) DE602004017263D1 (de)
ES (1) ES2316942T3 (de)
FR (1) FR2859272B1 (de)
RU (1) RU2287742C2 (de)
UA (1) UA82991C2 (de)

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DE102007025551A1 (de) 2007-05-31 2008-12-11 Siemens Ag Verfahren und Vorrichtung zur Verbrennung von kohlenwasserstoffhaltigen Brennstoffen
FR2919672A1 (fr) * 2007-07-30 2009-02-06 Snecma Sa Injecteur de carburant dans une chambre de combustion de turbomachine
FR3135114A1 (fr) * 2022-05-02 2023-11-03 Safran Procede d’injection de melange hydrogene-air pour bruleur de turbomachine

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US10184664B2 (en) * 2014-08-01 2019-01-22 Capstone Turbine Corporation Fuel injector for high flame speed fuel combustion
KR101730446B1 (ko) 2015-10-12 2017-05-11 한국기계연구원 농후연소와 희박연소 및 마일드 연소가 가능한 연소기
KR101777320B1 (ko) * 2015-10-26 2017-09-26 한국기계연구원 다단연소를 이용한 초저 NOx 연소기
FR3043173B1 (fr) * 2015-10-29 2017-12-22 Snecma Systeme d'injection aerodynamique pour turbomachine d'aeronef, a melange air/carburant ameliore
US20200224877A1 (en) * 2016-10-21 2020-07-16 Fgc Plasma Solutions Apparatus and method for using plasma to assist with the combustion of fuel
US10794331B2 (en) * 2017-07-31 2020-10-06 The Boeing Company Scramjets and associated aircraft and methods
RU2761262C2 (ru) * 2017-12-26 2021-12-06 Ансальдо Энергия Свитзерленд Аг Трубчатая камера сгорания для газовой турбины и газовая турбина, содержащая такую трубчатую камеру сгорания
FR3091574B1 (fr) * 2019-01-08 2020-12-11 Safran Aircraft Engines Systeme d’injection pour turbomachine, comprenant une vrille et des trous tourbillonnaires de bol melangeur
US11346557B2 (en) * 2019-08-12 2022-05-31 Raytheon Technologies Corporation Aerodynamic guide plate collar for swirler assembly
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FR3103540B1 (fr) * 2019-11-26 2022-01-28 Safran Aircraft Engines Système d'injection de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée
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EP2026007A1 (de) * 2007-07-30 2009-02-18 Snecma Kraftstoffeinspritzer in eine Brennkammer einer Strömungsmaschine
US8015813B2 (en) 2007-07-30 2011-09-13 Snecma Fuel injector for injecting fuel into a turbomachine combustion chamber
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WO2023214129A1 (fr) * 2022-05-02 2023-11-09 Safran Procede d'injection de melange hydrogene-air pour bruleur de turbomachine

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JP4252513B2 (ja) 2009-04-08
ES2316942T3 (es) 2009-04-16
RU2004126198A (ru) 2006-02-10
CA2478876C (fr) 2012-04-24
FR2859272A1 (fr) 2005-03-04
US20050044854A1 (en) 2005-03-03
RU2287742C2 (ru) 2006-11-20
US7114337B2 (en) 2006-10-03
DE602004017263D1 (de) 2008-12-04
JP2005077087A (ja) 2005-03-24
CA2478876A1 (fr) 2005-03-02
EP1512913B1 (de) 2008-10-22
UA82991C2 (uk) 2008-06-10
FR2859272B1 (fr) 2005-10-14

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