EP0828115B1 - Fuel injection system for a combustion chamber - Google Patents

Fuel injection system for a combustion chamber Download PDF

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Publication number
EP0828115B1
EP0828115B1 EP97402058A EP97402058A EP0828115B1 EP 0828115 B1 EP0828115 B1 EP 0828115B1 EP 97402058 A EP97402058 A EP 97402058A EP 97402058 A EP97402058 A EP 97402058A EP 0828115 B1 EP0828115 B1 EP 0828115B1
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EP
European Patent Office
Prior art keywords
sleeve
swirl inducer
fuel
air
upstream
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Expired - Lifetime
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EP97402058A
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German (de)
French (fr)
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EP0828115A1 (en
Inventor
Denis Roger Henri Ansart
Gilles Gérard Claude Lepretre
Denis Jean Maurice Sandelis
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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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

Definitions

  • the invention relates to fuel and air supply primary of a combustion chamber, especially for turbomachinery.
  • a typical example of antagonistic performances is that of flame stability at idle and the need to avoid fumes and the emission of nitrogen oxides at full gas. So the injection system of fuel and air must ensure proper combustion at rpm and under very diverse conditions.
  • FR-A-2 596 102 shows in FIG. 18 a mechanical injector which has a spin having an even number of fins defining an equal number of air intake passages, one passage in two being at radial inlet in order to deliver an air flow around the injection channel of fuel to constitute a first mixture in a chamber delimited by a socket with a converging / diverging internal contour, the other passages being at axial entry and delivering an air flow to the downstream periphery of the sleeve.
  • the present invention proposes to produce a device mechanical injection combined with strong premix tendrils permeability which makes it possible to meet the criteria of pollution and performance, at different speeds, imposed on engine manufacturers.
  • the invention therefore relates to an air injection device and fuel in a combustion chamber, in particular of turbomachine, said device comprising from upstream to downstream, an injector axis A fuel, a venturi sleeve arranged coaxially to axis A and having a converging / diverging internal contour delimiting a premix chamber in which the fuel is injected, a bowl flared downstream and having a sleeve upstream for fixing it around the socket, and means for injecting air from spraying fuel.
  • this device is characterized in that the means for injecting the fuel spray air have a first high-permeability radial spin arranged upstream of the socket and allowing a first air-fuel mixture to be produced in the premix chamber, a second radial spin having a plurality of channels provided in the upstream part of the socket and opening into the converging internal contour, said second spin being intended to ensure homogeneous carburetion in the venturi, and a third axial spin arranged at the periphery of the downstream part of the bush, and by the fact that the axial outlets of the third spin circumferentially alternate with the radial outlets of the second spin.
  • the inputs of the third spin are supplied in air through radial passages in the upstream part of the socket and alternating with the channels of the second spin.
  • the third spin is formed by grooves in the peripheral wall of the sleeve, said grooves being covered by the bowl fixing sleeve.
  • the drawing shows an air and fuel injection device 1, of this mechanical type, in a combustion chamber, not shown, of a turbomachine.
  • This device 1 comprises a fuel injector 2 of axis A which injects fuel downstream into a premix chamber 3 located at the bottom of the combustion chamber upstream of the zone primary 4 combustion.
  • the premix chamber 3 is delimited by the internal contour 5 of a socket 6 coaxial with the axis A.
  • This internal contour 5 is extended downstream by a flared wall 7 of a traditional bowl 8.
  • Bowl 8 comprises upstream of the flared wall 7 a sleeve 9 allowing its attachment to the socket 6.
  • the bowl 8 is mounted in a known manner in a orifice provided in the bottom of the combustion chamber.
  • the internal contour 5 of the socket 6 is convergent / divergent from upstream downstream and constitutes a venturi.
  • the passages 14a, 14b of the first series of passages are radial, pass right through the upstream part 12 of the socket 6 and open upstream of the neck 15 of the venturi.
  • Passages 16a, 16b of the second series of passages extend from the periphery of the part upstream 12 of the socket 6, to a zone located radially at the inside of the sleeve 9 of the bowl 8, where they axially tilt towards downstream.
  • axial grooves 18a, 18b, of rectangular section which extend the passages 16a, 16b of the second series of passages and which lead to the downstream periphery of the socket 6.
  • the passages 14a, 14b constitute a second radial spin intended to inject air into the premix chamber 3, and the grooves 18a, 18b, covered by the sleeve 9 of the bowl 8 constitute a third axial spin.
  • the outputs of the third axial spin are alternated circumferentially with the outputs of the second radial spin.
  • the number of passages 14a, 14b is equal to the number of passages 16a, 16b.
  • the number of the first spin 10 is equal to the total number of passage 14a, 14b; 16a, 16b formed in the upstream part 12 of the sleeve 6.
  • the first spin 10 therefore has a high permeability.
  • the fins 13 are wedged tangentially by an angle ⁇ between 30 and 40 • relative to the axis A of the fuel injector 2.
  • the axes of the outlet orifices of the passages 14a, 14b of the second spin are also inclined at an angle ⁇ relative to the radial at these points. The second spin therefore creates a swirling movement in the venturi.
  • the fins 20 of the first radial spin 10 are also radially wedged, and preferably the first spin 10 and the second spin are contra-rotating.
  • the first radial spin 10 makes it possible to produce a first premix in the bottom of the premix chamber 3. It makes plus purge office.
  • the second radial spin, tangentially wedged and also radially, ensures a uniform carburetion in the venturi.
  • the tangential incidence of the second radial spin must make an angle of 60 • to 90 • with respect to the tangential component of the first mixture.
  • the timing of the third axial spin is determined by the blading axial located at its outlet, that is to say by the angle of the side walls of the grooves 18a, 18b relative to the axis A.
  • the exit from the third axial spin can be corotative or counter-rotating with respect to the tangential component of the vortex in the venturi depending on the desired fuel table.
  • the tangential tilt of the third spin is depending on the bowl technology used, depending on whether it is a bowl with conventional ports, a bowl with swirling ports corotatives or contrarotatives or a bowl without orifices.
  • the ratio of the speeds of the air injected by the third spin and the mixture at the outlet of the venturi must be between 0.8 and 1.6, this report being dependent on the bowl technology used.

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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 (AREA)

Description

L'invention concerne l'alimentation en carburant et en air primaire d'une chambre de combustion, notamment pour turbomachines.The invention relates to fuel and air supply primary of a combustion chamber, especially for turbomachinery.

Dans les turbomachines aéronautiques, la grande plage de fonctionnement et les spécifications de plus en plus sévères concernant les diverses performances de la chambre de combustion conduisent à des compromis de plus en plus délicats à réaliser.In aeronautical turbomachinery, the wide range of increasingly stringent operation and specifications regarding the various performances of the combustion chamber lead to increasingly delicate compromises to be made.

Un exemple typique de performances antagonistes est celui de la stabilité de flamme au ralenti et la nécessité d'éviter les fumées et l'émission d'oxydes d'azote au plein gaz. Ainsi le système d'injection de carburant et d'air doit assurer une combustion correcte à des régimes et dans des conditions très diverses.A typical example of antagonistic performances is that of flame stability at idle and the need to avoid fumes and the emission of nitrogen oxides at full gas. So the injection system of fuel and air must ensure proper combustion at rpm and under very diverse conditions.

Il est donc impératif d'homogénéiser au mieux la carburation tout en respectant le profil radial des températures en sortie de chambre, afin d'éviter des contraintes thermiques inacceptables sur la roue de turbine.It is therefore imperative to homogenize the carburetion as well as possible. respecting the radial profile of the temperatures leaving the chamber, so avoid unacceptable thermal stresses on the turbine wheel.

FR-A-2 596 102 montre en figure 18 un injecteur mécanique qui comporte une vrille possédant un nombre pair d'ailettes délimitant un nombre égal de passages d'entrée d'air, un passage sur deux étant à entrée radiale afin de débiter un flux d'air autour du canal d'injection de carburant pour constituer un premier mélange dans une chambre délimitée par une douille à contour interne convergent/divergent, les autres passages étant à entrée axiale et débitant un flux d'air à la périphérie aval de la douille.FR-A-2 596 102 shows in FIG. 18 a mechanical injector which has a spin having an even number of fins defining an equal number of air intake passages, one passage in two being at radial inlet in order to deliver an air flow around the injection channel of fuel to constitute a first mixture in a chamber delimited by a socket with a converging / diverging internal contour, the other passages being at axial entry and delivering an air flow to the downstream periphery of the sleeve.

Cette alternance des canaux d'alimentation de l'air limite la perméabilité de la vrille de prémélange.This alternation of air supply channels limits the permeability of the premix spin.

La présente invention se propose de réaliser un dispositif d'injection mécanique associé à des vrilles de prémélange à forte perméabilité qui permette de répondre aux critères de pollution et de performances, aux différents régimes, imposés aux motoristes.The present invention proposes to produce a device mechanical injection combined with strong premix tendrils permeability which makes it possible to meet the criteria of pollution and performance, at different speeds, imposed on engine manufacturers.

L'invention concerne donc un dispositif d'injection d'air et de carburant dans une chambre de combustion, notamment de turbomachine, ledit dispositif comportant d'amont en aval, un injecteur de carburant d'axe A, une douille formant venturi disposé coaxialement à l'axe A et présentant un contour interne convergent/divergent délimitant une chambre de prémélange dans laquelle le carburant est injecté, un bol évasé vers l'aval et présentant en amont un manchon pour sa fixation autour de la douille, et des moyens pour injecter l'air de pulvérisation du carburant.The invention therefore relates to an air injection device and fuel in a combustion chamber, in particular of turbomachine, said device comprising from upstream to downstream, an injector axis A fuel, a venturi sleeve arranged coaxially to axis A and having a converging / diverging internal contour delimiting a premix chamber in which the fuel is injected, a bowl flared downstream and having a sleeve upstream for fixing it around the socket, and means for injecting air from spraying fuel.

Selon l'invention, ce dispositif est caractérisé par le fait que les moyens pour injecter l'air de pulvérisation du carburant comportent une première vrille radiale à forte perméabilité disposée en amont de la douille et permettant de réaliser un premier mélange air-carburant dans la chambre de prémélange, une deuxième vrille radiale présentant une pluralité de canaux ménagés dans la partie amont de la douille et débouchant dans le contour interne convergent, ladite deuxième vrille étant destinée à assurer une carburation homogène dans le venturi, et une troisième vrille axiale disposée à la périphérie de la partie aval de la douille, et par le fait que les sorties axiales de la troisième vrille alternent circonférentiellement avec les sorties radiales de la deuxième vrille.According to the invention, this device is characterized in that the means for injecting the fuel spray air have a first high-permeability radial spin arranged upstream of the socket and allowing a first air-fuel mixture to be produced in the premix chamber, a second radial spin having a plurality of channels provided in the upstream part of the socket and opening into the converging internal contour, said second spin being intended to ensure homogeneous carburetion in the venturi, and a third axial spin arranged at the periphery of the downstream part of the bush, and by the fact that the axial outlets of the third spin circumferentially alternate with the radial outlets of the second spin.

De préférence, les entrées de la troisième vrille sont alimentées en air par des passages radiaux ménagés dans la partie amont de la douille et alternant avec les canaux de la deuxième vrille.Preferably, the inputs of the third spin are supplied in air through radial passages in the upstream part of the socket and alternating with the channels of the second spin.

De façon avantageuse la troisième vrille est formé par des rainures ménagées dans la paroi périphérique de la douille, lesdites rainures étant recouvertes par le manchon de fixation du bol.Advantageously, the third spin is formed by grooves in the peripheral wall of the sleeve, said grooves being covered by the bowl fixing sleeve.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue en coupe selon des plans passant par l'axe de l'injecteur de carburant d'un dispositif d'injection selon l'invention, la partie située au-dessus de l'axe A étant une demi-coupe selon un plan passant par un passage de la deuxième vrille, et la partie située sous l'axe étant une demi-coupe selon un plan passant par un passage de la troisième vrille ;
  • la figure 2 montre l'alternance des sorties des deuxième et troisième vrilles ;
  • la figure 3 est un développement circonférentiel du dispositif d'injection qui montre les calages tangentiels des trois vrilles et l'incidence tangentielle des flux délivrés par chaque vrille ;
  • la figure 4 est une variante de réalisation du dispositif montré à la figure 1 ;
  • la figure 5 est une coupe selon la ligne V-V de la ligne 4 ; et
  • la figure 6 montre en perspective la douille formant venturi du dispositif de la figure 4.
    • Other advantages and characteristics of the invention will emerge on reading the following description given by way of example and with reference to the appended drawings in which:
  • Figure 1 is a sectional view along planes passing through the axis of the fuel injector of an injection device according to the invention, the part located above the axis A being a half-section along a plane passing through a passage of the second spin, and the part located under the axis being a half-section along a plane passing through a passage of the third spin;
  • Figure 2 shows the alternation of the outputs of the second and third tendrils;
  • FIG. 3 is a circumferential development of the injection device which shows the tangential settings of the three tendrils and the tangential incidence of the flows delivered by each spin;
  • Figure 4 is an alternative embodiment of the device shown in Figure 1;
  • Figure 5 is a section along line VV of line 4; and
  • FIG. 6 shows in perspective the socket forming a venturi of the device of FIG. 4.

    • Le dessin montre un dispositif d'injection d'air et de carburant 1, de ce type mecanique, dans un chambre de combustion, non représentée, d'une turbomachine.The drawing shows an air and fuel injection device 1, of this mechanical type, in a combustion chamber, not shown, of a turbomachine.

    Ce dispositif 1 comporte un injecteur de carburant 2 d'axe A qui injecte du carburant vers l'aval dans une chambre de prémélange 3 disposée dans le fond de l'enceinte de combustion en amont de la zone primaire 4 de combustion.This device 1 comprises a fuel injector 2 of axis A which injects fuel downstream into a premix chamber 3 located at the bottom of the combustion chamber upstream of the zone primary 4 combustion.

    La chambre de prémélange 3 est délimitée par le contour interne 5 d'une douille 6 coaxiale à l'axe A. Ce contour interne 5 est prolongé vers l'aval par une paroi évasée 7 d'un bol 8 traditionnel. Le bol 8 comporte en amont de la paroi évasée 7 un manchon 9 permettant sa fixation sur la douille 6. Le bol 8 est monté de manière connue dans un orifice prévu dans le fond de la chambre de combustion.The premix chamber 3 is delimited by the internal contour 5 of a socket 6 coaxial with the axis A. This internal contour 5 is extended downstream by a flared wall 7 of a traditional bowl 8. Bowl 8 comprises upstream of the flared wall 7 a sleeve 9 allowing its attachment to the socket 6. The bowl 8 is mounted in a known manner in a orifice provided in the bottom of the combustion chamber.

    Ainsi qu'on le voit sur les figures 1 et 4, entre l'extrémité amont de la douille 6 et l'extrémité aval de l'injecteur de carburant 2 est interposé une première vrille radiale 10 portée par un anneau de centrage 11 de l'injecteur de carburant 2.As seen in Figures 1 and 4, between the upstream end of the sleeve 6 and the downstream end of the fuel injector 2 is interposed a first radial spin 10 carried by a ring of centering 11 of the fuel injector 2.

    Le contour interne 5 de la douille 6 est convergent/divergent de l'amont vers l'aval et constitue un venturi.The internal contour 5 of the socket 6 is convergent / divergent from upstream downstream and constitutes a venturi.

    Dans la partie amont 12 de la douille 6 située au droit de la zone convergente du contour 5 sont ménagés deux séries de passages alternés et délimités par des ailettes 13.In the upstream part 12 of the socket 6 located at the level of the zone converging of contour 5 are formed two series of alternating passages and delimited by fins 13.

    Les passages 14a, 14b de la première série de passages sont radiaux, traversent de part en part la partie amont 12 de la douille 6 et débouchent en amont du col 15 du venturi.The passages 14a, 14b of the first series of passages are radial, pass right through the upstream part 12 of the socket 6 and open upstream of the neck 15 of the venturi.

    Les passages 16a, 16b de la deuxième série de passages, alternant avec les passages 14a, 14b, s'étendent depuis la périphérie de la partie amont 12 de la douille 6, jusqu'à une zone située radialement à l'intérieur du manchon 9 du bol 8, où ils obliquent axialement vers l'aval.Passages 16a, 16b of the second series of passages, alternating with the passages 14a, 14b, extend from the periphery of the part upstream 12 of the socket 6, to a zone located radially at the inside of the sleeve 9 of the bowl 8, where they axially tilt towards downstream.

    A la périphérie de la partie aval 17 de la douille 6, située au droit du contour interne divergent du contour 5, et radialement à l'intérieur du manchon 9 du bol 8 sont ménagées des rainures axiales 18a, 18b, de section rectangulaire qui prolongent les passages 16a, 16b de la deuxième série de passages et qui débouchent à la périphérie aval de la douille 6.At the periphery of the downstream part 17 of the socket 6, located at the right of the internal contour diverge from contour 5, and radially inside of the sleeve 9 of the bowl 8 are formed axial grooves 18a, 18b, of rectangular section which extend the passages 16a, 16b of the second series of passages and which lead to the downstream periphery of the socket 6.

    Les passages 14a, 14b constituent une deuxième vrille radiale destinée à injecter de l'air dans la chambre du prémélange 3, et les rainures 18a, 18b, recouvertes par le manchon 9 du bol 8 constituent une troisième vrille axiale.The passages 14a, 14b constitute a second radial spin intended to inject air into the premix chamber 3, and the grooves 18a, 18b, covered by the sleeve 9 of the bowl 8 constitute a third axial spin.

    Par construction, et ainsi que cela est montré clairement sur la figure 2, les sorties de la troisième vrille axiale sont alternées circonférentiellement avec les sorties de la deuxième vrille radiale.By construction, and as is clearly shown on the Figure 2, the outputs of the third axial spin are alternated circumferentially with the outputs of the second radial spin.

    Le nombre de passages 14a, 14b est égal au nombre de passage 16a, 16b. De préférence, ainsi que cela se voit sur la figure 3, le nombre de passages de la première vrille 10 est égale au nombre total de passage 14a, 14b ; 16a, 16b ménagés dans la partie amont 12 de la douille 6. La première vrille 10 a donc une forte perméabilité.The number of passages 14a, 14b is equal to the number of passages 16a, 16b. Preferably, as seen in Figure 3, the number of the first spin 10 is equal to the total number of passage 14a, 14b; 16a, 16b formed in the upstream part 12 of the sleeve 6. The first spin 10 therefore has a high permeability.

    Les ailettes 13 sont calées tangentiellement d'un angle α compris entre 30 et 40• par rapport à l'axe A de l'injecteur de carburant 2. Les axes des orifices de sortie des passages 14a, 14b de la deuxième vrille sont également inclinés d'un angle β par rapport à la radiale en ces points. La deuxième vrille crée donc un mouvement tourbillonnant dans le venturi.The fins 13 are wedged tangentially by an angle α between 30 and 40 • relative to the axis A of the fuel injector 2. The axes of the outlet orifices of the passages 14a, 14b of the second spin are also inclined at an angle β relative to the radial at these points. The second spin therefore creates a swirling movement in the venturi.

    Les ailettes 20 de la première vrille radiale 10 sont également calées de manière radiale, et de préférence la première vrille 10 et la deuxième vrille sont contrarotatives.The fins 20 of the first radial spin 10 are also radially wedged, and preferably the first spin 10 and the second spin are contra-rotating.

    La première vrille radiale 10 permet de réaliser un premier prémélange dans le fond de la chambre de prémélange 3. Elle fait en plus office de purge.The first radial spin 10 makes it possible to produce a first premix in the bottom of the premix chamber 3. It makes plus purge office.

    La deuxième vrille radiale, calée tangentiellement et également de manière radiale, assure une carburation homogène dans le venturi.The second radial spin, tangentially wedged and also radially, ensures a uniform carburetion in the venturi.

    Pour cela, l'incidence tangentielle de la deuxième vrille radiale doit faire un angle de 60• à 90• par rapport à la composante tangentielle du premier mélange.For this, the tangential incidence of the second radial spin must make an angle of 60 • to 90 • with respect to the tangential component of the first mixture.

    Le calage de la troisième vrille axiale est déterminée par l'aubage axial situé à sa sortie, c'est-à-dire par l'angle des parois latérales des rainures 18a, 18b par rapport à l'axe A. The timing of the third axial spin is determined by the blading axial located at its outlet, that is to say by the angle of the side walls of the grooves 18a, 18b relative to the axis A.

    La sortie de la troisième vrille axiale peut être corotative ou contrarotative par rapport à la composante tangentielle du tourbillon dans le venturi en fonction de la nappe carburée désirée.The exit from the third axial spin can be corotative or counter-rotating with respect to the tangential component of the vortex in the venturi depending on the desired fuel table.

    De plus, l'inclinaison tangentielle de la troisième vrille est fonction de la technologie de bol utilisée, selon qu'il s'agit d'un bol avec des orifices conventionnels, un bol avec des orifices tourbillonnant corotatifs ou contrarotatifs ou d'un bol sans orifices.In addition, the tangential tilt of the third spin is depending on the bowl technology used, depending on whether it is a bowl with conventional ports, a bowl with swirling ports corotatives or contrarotatives or a bowl without orifices.

    Le rapport des vitesses de l'air injecté par la troisième vrille et du mélange à la sortie du venturi doit être compris entre 0,8 et 1,6, ce rapport étant dépendant de la technologie de bol utilisée.The ratio of the speeds of the air injected by the third spin and the mixture at the outlet of the venturi must be between 0.8 and 1.6, this report being dependent on the bowl technology used.

    Claims (6)

    1. Device for injecting air and fuel into a combustion chamber, particularly of a turbomachine, the said device comprising, from the upstream end downstream, a fuel injector (2) of axis A, a sleeve (6) forming a venturi arranged coaxially with respect to the axis A and having a convergent/divergent internal contour (5) delimiting a premixing chamber (3) into which the fuel is injected, a bowl (8) widening in the downstream direction and upstream having a sleeve tube (9) for fixing it around the sleeve (6), and means for injecting the air for atomizing the fuel,
      characterized in that the means for injecting the air for atomizing the fuel comprise a highly permeable radial first swirl inducer (10) arranged upstream of the sleeve (6) and allowing an initial air-fuel mixing in the premixing chamber (3), a radial second swirl inducer having a number of ducts (16a, 16b) formed in the upstream part (12) of the sleeve (6) and opening into the convergent internal contour (5), the said second swirl inducer being intended to ensure homogeneous carburation in the venturi, and an axial third swirl inducer (18a, 18b) arranged at the periphery of the downstream part (17) of the sleeve (6), and in that the axial outlets of the third swirl inducer (18a, 18b) alternate circumferentially with the radial outlets of the second swirl inducer.
    2. Device according to Claim 1, characterized in that the inlets of the third swirl inducer (18a, 18b) are supplied with air via radial passages (16a, 16b) formed in the upstream part (12) of the sleeve (6) and alternating with the ducts (14a, 14b) of the second swirl inducer.
    3. Device according to either one of Claims 1 and 2, characterized in that the third swirl inducer is formed by grooves (18a, 18b) formed in the peripheral wall of the sleeve (6), the said grooves (18a, 18b) being covered by the sleeve tube (9) for attachment of the bowl (8).
    4. Device according to either one of Claims 1 and 2, characterized in that the first swirl inducer (10) and the second swirl inducer (14a, 14b) are contrarotary.
    5. Device according to Claim 4, characterized in that the tangential incidence of the air injected by the second swirl inducer (14a, 14b) into the premixing chamber (3) makes an angle of between 60° and 90° with the tangential component from the first mixing.
    6. Device according to any one of Claims 1 to 4, characterized in that the second swirl inducer (14a, 14b) is set tangentially and radially.
    EP97402058A 1996-09-05 1997-09-04 Fuel injection system for a combustion chamber Expired - Lifetime EP0828115B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR9610823A FR2752917B1 (en) 1996-09-05 1996-09-05 ADVANCED HOMOGENIZATION INJECTION SYSTEM
    FR9610823 1996-09-05

    Publications (2)

    Publication Number Publication Date
    EP0828115A1 EP0828115A1 (en) 1998-03-11
    EP0828115B1 true EP0828115B1 (en) 2003-08-13

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    Family Applications (1)

    Application Number Title Priority Date Filing Date
    EP97402058A Expired - Lifetime EP0828115B1 (en) 1996-09-05 1997-09-04 Fuel injection system for a combustion chamber

    Country Status (6)

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    US (1) US5941075A (en)
    EP (1) EP0828115B1 (en)
    JP (1) JP3954165B2 (en)
    CA (1) CA2207831C (en)
    DE (1) DE69724054T2 (en)
    FR (1) FR2752917B1 (en)

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    FR2836986B1 (en) * 2002-03-07 2004-11-19 Snecma Moteurs MULTI-MODEL INJECTION SYSTEM FOR AN AIR / FUEL MIXTURE IN A COMBUSTION CHAMBER
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    FR2752917A1 (en) 1998-03-06
    CA2207831C (en) 2006-05-30
    DE69724054T2 (en) 2004-04-15
    FR2752917B1 (en) 1998-10-02
    JPH1089688A (en) 1998-04-10
    CA2207831A1 (en) 1998-03-05
    JP3954165B2 (en) 2007-08-08
    DE69724054D1 (en) 2003-09-18
    US5941075A (en) 1999-08-24
    EP0828115A1 (en) 1998-03-11

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