EP1314933B1 - Mehrstufiges Einspritzsystem eines Luft/Brennstoff-Gemisches in einer Gasturbinenbrennkammer - Google Patents

Mehrstufiges Einspritzsystem eines Luft/Brennstoff-Gemisches in einer Gasturbinenbrennkammer Download PDF

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Publication number
EP1314933B1
EP1314933B1 EP02292866A EP02292866A EP1314933B1 EP 1314933 B1 EP1314933 B1 EP 1314933B1 EP 02292866 A EP02292866 A EP 02292866A EP 02292866 A EP02292866 A EP 02292866A EP 1314933 B1 EP1314933 B1 EP 1314933B1
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EP
European Patent Office
Prior art keywords
injector
fuel
air
fuel feed
orifices
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.)
Expired - Lifetime
Application number
EP02292866A
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English (en)
French (fr)
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EP1314933A1 (de
Inventor
Etienne David
Marion Michau
José Rodrigues
Denis Sandelis
Alain Tiepel
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Safran Transmission Systems SAS
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Hispano Suiza SA
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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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • 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 present invention relates to the general field of fuel injection systems in a combustion chamber of a gas turbine engine. It is more particularly an injection system comprising in particular an aerodynamic fuel injector multi-point feed fuel.
  • injection systems include fuel injectors and air intake means downstream of the injectors.
  • fuel injectors There are two main categories of fuel injectors: the so-called “aeromechanical” injectors designed to deliver two fuel flows according to the engine speeds, and the so-called “aerodynamic” injectors which comprise only one fuel circuit, whatever the engine speed.
  • some so-called “aerodynamic” injectors have, at their end or nose, air supply channels to directly deliver an air / fuel mixture.
  • the present invention relates more particularly to injection systems comprising so-called "aerodynamic" injectors belonging to the latter category.
  • the air intake means known from the prior art (as for example that disclosed in U.S. 4,425,755 ) generally comprise primary and secondary tendrils which deliver a swirling air flow at the outlet of the fuel injector.
  • a venturi separating these two tendrils accelerates the flow of air from the primary swirler and a bowl mounted downstream of the secondary swirler allows the mounting of the injector on the bottom of the combustion chamber while aiming to prevent a rise in the combustion flame of the air / fuel mixture to the injector.
  • This type of injection system has disadvantages.
  • the air / fuel mixture delivered at the injector outlet is generally not homogeneous, thus increasing the pollutant emissions of the engine.
  • the fuel flow rate at the injector outlet is also insufficient, especially for low flow rates, which leads to risks of coking at the nose of the injector and causes heterogeneity of the air / fuel mixture.
  • a low fuel flow rate also has the disadvantage of increasing the risk of a rise in the combustion flame of the air / fuel mixture to the end of the injector which is detrimental to the proper functioning of the fuel. gas turbine.
  • traces of coking appear between the body of the injector and the bowl.
  • the present invention therefore aims to overcome such drawbacks by proposing an injection system whose fuel injector makes it possible to obtain a better homogenization of the air / fuel mixture and a greater speed of flow of the fuel at its outlet.
  • a system for injecting an air / fuel mixture into a turbomachine combustion chamber comprising an injector comprising an axial internal volume which opens at one end via an axial outlet for the air mixture. /fuel ; a first fuel supply stage with a plurality of first fuel supply ports which open into the internal volume, are distributed around an axis of the injector and are connected by fuel supply channels at a fuel inlet in the injector; and at least one air supply channel which opens into the internal volume and is connected to an air inlet in the injector, characterized in that the injector further comprises at least a second supply stage in fuel with a plurality of second fuel supply ports which open into the internal volume, are distributed around the axis of the injector, and are connected to the fuel inlet in the injector through channels which are at least partly confused with the fuel supply channels of the first stage.
  • the second fuel supply stage makes it possible to multiply the number of fuel supply points in the internal volume of the injector around the axis of the latter. Homogenization of the air / fuel mixture is thus improved.
  • the passage in which the fuel supply openings open has a decrease in section in the direction of flow of the fuel. This feature makes it possible to increase the flow rate of the fuel to improve the resistance of the injector to coking, and to make the fuel ply more homogeneous, especially for low fuel flow rates.
  • the second fuel supply orifices are axially offset with respect to the first fuel supply orifices.
  • the second fuel supply ports preferably have angular positions about the axis of the injector offset from those of the first fuel supply ports.
  • the fuel supply channels are oriented, in their terminal parts adjacent to the first and second fuel supply ports, substantially tangentially with respect to the wall of the internal volume. This characteristic makes it possible to obtain a rotation of the fuel in the internal volume and thus improves the flow rate and the homogeneity of the air / fuel mixture.
  • the injector comprises a rear part in which the air supply channel or channels are formed, at least one ring in which the first and second fuel supply stages are formed and which is introduced into a formed housing. at the downstream end of the rear portion, and a front portion which connects to the rear portion, the ring being immobilized axially between the rear portion and the front portion of the injector.
  • each fuel supply stage comprises four fuel supply orifices distributed regularly around the axis of the injector.
  • the system according to the invention further comprises a bushing surrounding at least a part of the injector, a divergent forming bowl for mounting the injection system on a bottom of the combustion chamber, at least one air swirl interposed between the sleeve and the bowl, and a venturi formed between the part of the injector surrounded by the sleeve and the bowl.
  • a passage for air is provided between the socket and the portion of the injector surrounded by the socket to prevent coke from forming at the nose of the injector, and through holes. of air are formed in the wall of the diverging bowl.
  • the figure 1 illustrates an injection system 2 according to the invention mounted in a combustion chamber 4 of a gas turbine engine used in a turbojet for example.
  • the combustion chamber 4 for example of the annular type, is delimited by internal and external walls (not shown in the drawing) joined by a chamber bottom 6.
  • the latter comprises a plurality of openings 6a of axis 8 regularly spaced around the axis of the motor.
  • an injection system 2 according to the invention for injecting an air / fuel mixture into the combustion chamber 4.
  • the gases resulting from the combustion of this air / fuel mixture flow towards the downstream in the combustion chamber 4 and are then discharged to a high-pressure turbine (not shown).
  • annular baffle 10 is mounted in each of the openings 6a.
  • This deflector is disposed in the combustion chamber 4 parallel to the chamber bottom 6.
  • a divergent bowl 20 is also mounted inside the opening 6a. It comprises a wall 21 flared downstream in the extension of a cylindrical wall 22 disposed coaxially with the axis 8 of the opening 6a. At its downstream end, the wall 21 of the bowl has a flange 23 which, with a facing wall 24, defines an annular recess or U-shaped bowl flange.
  • the cylindrical wall 22 of the bowl 20 surrounds a venturi 30 of axis 8.
  • the venturi 30 delimits the air flows coming from a primary swirler 32 and a secondary swirler 34.
  • the primary swirler 32 is arranged upstream of the venturi 30 and delivers a flow of air inside the venturi.
  • the secondary swirler 34 is disposed upstream of the cylindrical wall 22 of the bowl 20 and delivers a flow of air between the venturi 30 and the cylindrical wall 22.
  • the primary swirler 32 is secured upstream of a retaining piece 40 which has an annular groove 42 open on the side of the axis 8 of the opening 6a and in which is mounted a sleeve 44 surrounding at least a portion of the end or nose of a fuel injector 50.
  • the injection system may further be provided with a fairing typically formed of a cap 46. This fairing minimizes the losses of fuel. load of air bypassing the injector and to ensure a good supply of the chamber bottom.
  • the fuel injector 50 of axis XX coincides with the axis 8 of the opening 6a, is aerodynamic type, that is to say it delivers only one fuel flow whatever the regime engine operation.
  • the injector is typically formed of a tubular portion 52 supplying fuel to an injector nose 54, at which the fuel mixes with air before receiving the air from the primary and secondary tendrils and being injected. in the combustion chamber 4.
  • FIGS 2 to 6 which more particularly illustrate an embodiment of the fuel injector nose of the injection system according to the invention.
  • the nozzle nose 54 has an axial internal volume 56 which opens at one end via an axial outlet 58 for the air / fuel mixture.
  • At the end of the nose opposite that having the axial outlet 58 is provided at least one fuel inlet 60 in the form of a cylindrical recess, for example.
  • This inlet 60 is supplied with fuel by the tubular part of the fuel injector.
  • Fuel supply channels 62 open into the fuel inlet 60 and are connected to a plurality of first fuel supply ports 64 forming a first fuel supply stage. These first orifices are distributed around the axis XX of the injector and open into the internal volume 56.
  • At least one air supply channel 66 connected to an air inlet 68 in the injector opens also in the internal volume 56.
  • the fuel injector 50 comprises, at its nose 54, at least a second fuel supply stage with a plurality of second fuel supply ports 70 which open in the volume internal 56. These second orifices are distributed around the axis XX of the injector and are connected to the fuel inlet 60 in the injector by fuel supply channels 72 which are at least partially merged with the fuel supply channels 62 of the first fuel supply stage.
  • each fuel supply stage advantageously comprises four feed orifices, fuel 64, 70 connected to the fuel supply channels 62, 72 and distributed regularly around the axis XX of the injector.
  • the feed channels 62, 72 are preferably arranged alternately with four air supply channels 66.
  • first 64 and second 70 fuel supply ports on the one hand, and the air supply duct or channels 66, on the other hand, open in two coaxial passages 74 and 76, respectively. formed in the inner volume 56.
  • the air supply channels 66 open into a central passage 76
  • the first and second fuel supply ports open into an annular passage 74 surrounding the passage. central 76.
  • the annular passage 74 into which the fuel supply openings open has a reduction of section 74a in the direction of flow of the fuel in order to form a convergent allowing the acceleration of the fuel. at its exit from this annular passage.
  • the second fuel supply stage can be axially offset from the first stage, so that the second fuel supply ports 70 are axially offset from the first fuel supply ports 64.
  • This shift of the stages fuel supply can be provided when, for reasons of space, it is not possible to have all the supply ports 64, 70 in the same axial plane.
  • the second fuel supply ports 70 preferably have angular positions about the axis XX of the injector offset from those of the first fuel supply ports 64. In this way, the distribution fuel around the axis of the injector and thus the homogeneity of the air / fuel mixture are improved.
  • the fuel supply channels 62, 72 each comprise a first part, respectively 62a and 72a, extending parallel to the axis XX of the injector and connected to the fuel inlet 60 in the injector, and a second portion, respectively 62b and 72b, which connects the first portion to a fuel supply port 64, 70.
  • first parts 62a, 72a of the fuel supply channels 62, 72 are at least partially merged.
  • these fuel supply channels are oriented substantially tangentially with respect to the wall of the internal volume 56.
  • the fuel flowing in these channels is rotated before its introduction into the internal volume which allows to increase its flow rate and thus to promote the homogeneity of the air / fuel mixture.
  • the arrangement of the air supply channel (s) 66 is particularly illustrated by the Figures 3 and 6 . These channels open into the internal volume 56 in a direction which is substantially tangential to the wall of the internal volume and which is inclined downstream relative to a plane normal to the axis XX of the injector. This particular arrangement also improves the homogeneity and flow velocity of the air / fuel mixture.
  • the injector nose is essentially formed of three parts: a rear part 78 in which the air supply duct or ducts 66 are formed, at least one ring 80 in which the first and second fuel supply stage and which is introduced into a housing 82 formed at the downstream end of the rear portion, and a front portion 84 which connects to the rear portion, the ring being immobilized axially between the rear portion and the front part.
  • the nose of the injector comprises, at the ring 80, two fuel supply stages.
  • the nose of the injector, and more particularly the ring 80 has more than two stages of fuel supply so as to further multiply the number of fuel supply points in the internal volume of the fuel. the injector.
  • the additional floors can be shifted axially relative to each other to increase the number of fuel supply points in the internal volume of the injector.
  • FIG. 1 Another advantageous features of the injection system according to the invention are represented on the figure 1 .
  • at least one passage for air is arranged between the sleeve 44 and the nose portion surrounded by it.
  • This passage makes it possible to carry out an anti-coking purge, that is to say that it prevents fuel from coking at the nose of the injector, especially at low fuel flow rates.
  • This passage for the air can for example be made in the form of a plurality of orifices 48 regularly distributed around the nose and opening in the vicinity of the axial outlet 58 thereof in a direction substantially parallel to the axis XX of the injector 50. In order to accelerate the flow of the air passing through these orifices 48, a reduction in section of this passage in the direction of flow of the air may be provided.
  • air passage holes 25 are formed in the wall 21 of the bowl 20 to effect an anti-coking purge at the bowl. These holes open into the combustion chamber in a direction which may be tilted with respect to the X-X axis and be tangential to the flared wall 21 of the bowl to avoid any risk of coking.
  • air passage holes 26 are formed in the facing wall 24 of the bowl flange to feed it, and more particularly the annular baffle 10, with air. These holes 26 open for example substantially parallel to the X-X axis of the injector so that the air passing through them hits the flange 23 of the wall 21 of the bowl and flows along the annular baffle 10.
  • the holes 25, 26 and air passage holes 48 of the various elements of the injection system, as well as air slots 36, 38 respectively for the primary 32 and secondary 34 tendrils may be distributed along N 360 angular sectors. / N ° each. More specifically, for each angular sector, the bowl 20 may for example comprise n air passage holes 25 of identical shapes to each other (for example circular, elliptical, ...) and opening out parallel to each other. This same principle can be adopted for other holes and air passage slots.
  • the figure 7 schematically illustrates, in a plane P perpendicular to the axis XX, an example of distribution of these different air passages.
  • the air passages of an angular sector of 60 ° are represented; they comprise: three orifices 48 arranged between the bush 44 and the nose part surrounded by the latter, two air slots 36 for the primary swirler, three air slots 38 for the secondary swirler, four holes 25 for passing through air formed in the wall 21 of the bowl, and eight air passage holes 26 formed in the facing wall 24 of the bowl collar.
  • the distribution of these different air passages is regular around the axis XX. They can be made directly in the foundry.

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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)

Claims (18)

  1. Einspritzsystem (2) zum Einspritzen eines Luft-Brennstoff-Gemisches in eine Gasturbinenbrennkammer (4), umfassend einen Injektor (50), weicher aufweist:
    ein axiales Innenvolumen (56), welches sich an einem Ende über einen axialen Ausgang (58) für das Luft-Brennstoff-Gemisch öffnet,
    eine erste Brennstoffversorgungsstufe mit mehreren ersten Brennstoffversorgungsöffnungen (64), welche sich in das Innenvolumen öffnen, um eine Achse (X-X) des Injektors herum verteilt sind und über Brennstoffversorgungskanäle (62) mit einem Brennstoffeingang (60) in dem Injektor verbunden sind, und
    mindestens einen Luftversorgungskanal (66), welcher sich in das Innenvolumen öffnet und mit einem Lufteingang (68) in dem Injektor verbunden ist,
    dadurch gekennzeichnet, daß der Injektor außerdem mindestens eine zweite Brennstoffversorgungsstufe mit mehreren zweiten Brennstoffversorgungsöffnungen (70) aufweist, welche sich in das Innenvolumen öffnen, um die Achse des Injektors herum verteilt sind und mit dem Brennstoffeingang in dem Injektor über Brennstoffversorgungskanäie (72) verbunden sind, welche wenigstens teilweise mit den Brennstoffversorgungskanälen (62) der ersten Stufe zusammenfalten.
  2. System nach Anspruch 1, dadurch gekennzeichnet, daß die ersten und zweiten Brennstoffversorgungsöffnungen (64, 70) einerseits und der oder die Luftversorgungskanäle (66) andererseits sich in zwei koaxiale Durchgänge (74, 76) öffnen, die in dem Innenvolumen ausgebildet sind. 4
  3. System nach Anspruch 2, dadurch gekennzeichnet, daß der Durchgang (74), in welchen sich die Brennstoffversorgungsöffnungen (64, 70) öffnens eine Querschnittsverminderung in der Strömungsrichtung des Brennstoffes aufweist, um das Strömen des Brennstoffes in dem Innenvolumen zu beschleunigen.
  4. System nach einem der Ansprüche 2 oder 3, dadurch gekennzeichnet, daß der oder die Luftversorgungskanäle (66) sich in einen mittleren Durchgang (76) öffnen und die Brennstoffversorgungsöffnungen (64, 70) sich in einen ringförmigen Durchgang (74) öffnen, der den mittleren Durchgang umgibt.
  5. System nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß die zweiten Brennstoffversorgungsöffnungen (70) bezüglich der ersten Brennstoffversorgungsöffnungen (64) axial versetzt sind.
  6. System nach Anspruch 5, dadurch gekennzeichnet, daß die zweiten Brennstoffversorgungsöffnungen (70) Winkelpositionen um die Achse des Injektors herum aufweisen, die bezüglich derjenigen der ersten Brennstoffversorgungsöffnungen (64) versetzt sind.
  7. System nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die Brennstoffversorgungskanäle (62, 72) in ihren Endabschnittes, die den ersten (64) und zweiten (70) Brennstoffversorgungsöffnungen benachbart sind, im Wesentlichen tangential bezüglich der Wand des Innenvolumens (56) ausgerichtet sind.
  8. System nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß die Brennstoffversorgungskanäle (62, 72) einen ersten Abschnitt (62a, 72a) aufweisen, der sich parallel zur Achse des Injektors erstreckt und an den Brennstoffeingang in dem Injektor abgeschlossen ist, und einen zweiten Abschnitt (62b, 72b), welcher den ersten Abschnitt an eine Brennstoffversorgungsöffnung (64, 70) abschließt.
  9. System nach Anspruch 8, dadurch gekennzeichnet, daß der erste Abschnitt (62a) der Brennstoffversorgungskanäle (62), die mit den ersten Brennstoffversorgungsöffnungen (64) verbunden sind, und der erste Abschnitt (72a) der Brennstoffversorgungskanäle (72), die mit den zweiten Brennstoffversorgungsöffnungen (70) verbunden sind, wenigstens teilweise zusammenfallen.
  10. System nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, daß der oder die Luftversorgungskanäle (66) in das Innenvolumen (56) in einer Richtung einmünden, welche im Wesentlichen tangential bezüglich der Wand des Innenvolumens ist und welche bezüglich einer zur Achse (X-X) des Injektors senkrechten Ebene stromabwärts geneigt ist.
  11. System nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, daß der Injektor aufweist:
    einen hinteren Abschnitt (78), in welchem der oder die Luftversorgungskanäle (66) ausgebildet sind,
    mindestens einen Ring (80), in welchem die erste und die zweite Brennstoffversorgungsstufe ausgebildet sind und welcher in eine Aufnahme (82) eingesetzt ist, die am stromabwärts befindlichen Ende des hinteren Abschnitts ausgebildet ist, und
    einen vorderen Abschnitt (84), welcher sich an den hinteren Abschnitt anschließt, wobei der Ring zwischen dem hinteren Abschnitt und dem vorderen Abschnitt des Injektors axial festgelegt ist.
  12. System nach einem der Ansprüche 1 bis 11, dadurch gekennzeichnet, daß jede Brennstoffversorgungsstufe vier Brennstoffversorgungsöffnungen (64, 70) umfaßt, die gleichmäßig um die Achse (X-X) des Injektors herum verteilt sind.
  13. System nach einem der Ansprüche 1 bis 12, dadurch gekennzeichnet, daß es außerdem eine Hülse (44), die wenigstens einen Abschnitt des Injektors (50) umgibt, eine ein divergentes Teil bildende Schale (20) für die Montage des Einspritzsystems auf einem Brennkammerboden (6) und mindestens eine Luftspirale (32, 34), die zwischen der Hülse und der Schale angeordnet ist, aufweist.
  14. System nach Anspruch 13, dadurch gekennzeichnet, daß mindestens ein Durchgang (48) für Luft zwischen der Hülse (44) und dem Abschnitt des Injektors, der von der Hülse umgeben ist, eingerichtet ist.
  15. System nach einem der Ansprüche 13 oder 14, dadurch gekennzeichnet, daß zwischen dem von der Hülse umgebenen Abschnitt des Injektors und der Schale (20) ein Lufttrichter (30) ausgebildet ist.
  16. System nach einem der Ansprüche 13 bis 15, dadurch gekennzeichnet, daß es zwei Luftspiralen umfaßt, eine primäre (32) und eine sekundäre (34).
  17. System nach einem der Ansprüche 13 bis 16, dadurch gekennzeichnet, daß in der Wand (21) der ein divergentes Teil bildende Schale Luftdurchgangslöcher (25) ausgebildet sind.
  18. System nach einem der Ansprüche 13 bis 17, dadurch gekennzeichnet, daß die Schale (20) an ihrem stromabwärts befindlichen Ende eine Umrandung (23) aufweist, welche mit einer gegenüberliegenden Wand (24) eine ringförmige Vertiefung mit U-förmigem Querschnitt begrenzt, und in der gegenüberliegenden Wand Luftdurchgangslöcher (26) ausgebildet sind, um die Vertiefung mit Luft zu versorgen.
EP02292866A 2001-11-21 2002-11-19 Mehrstufiges Einspritzsystem eines Luft/Brennstoff-Gemisches in einer Gasturbinenbrennkammer Expired - Lifetime EP1314933B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0115042A FR2832493B1 (fr) 2001-11-21 2001-11-21 Systeme d'injection multi-etages d'un melange air/carburant dans une chambre de combustion de turbomachine
FR0115042 2001-11-21

Publications (2)

Publication Number Publication Date
EP1314933A1 EP1314933A1 (de) 2003-05-28
EP1314933B1 true EP1314933B1 (de) 2008-09-17

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US (1) US6820425B2 (de)
EP (1) EP1314933B1 (de)
DE (1) DE60228924D1 (de)
ES (1) ES2314022T3 (de)
FR (1) FR2832493B1 (de)
RU (1) RU2293862C2 (de)

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FR2893390B1 (fr) * 2005-11-15 2011-04-01 Snecma Fond de chambre de combustion avec ventilation
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RU2293862C2 (ru) 2007-02-20
DE60228924D1 (de) 2008-10-30
FR2832493B1 (fr) 2004-07-09
US6820425B2 (en) 2004-11-23
EP1314933A1 (de) 2003-05-28
ES2314022T3 (es) 2009-03-16
US20030131600A1 (en) 2003-07-17
FR2832493A1 (fr) 2003-05-23

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