EP1278012A2 - Aeromechanical injection system with non-return primary swirler - Google Patents
Aeromechanical injection system with non-return primary swirler Download PDFInfo
- Publication number
- EP1278012A2 EP1278012A2 EP02291767A EP02291767A EP1278012A2 EP 1278012 A2 EP1278012 A2 EP 1278012A2 EP 02291767 A EP02291767 A EP 02291767A EP 02291767 A EP02291767 A EP 02291767A EP 1278012 A2 EP1278012 A2 EP 1278012A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- injection nozzle
- injection
- combustion chamber
- injection system
- 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
Links
Images
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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- 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
Definitions
- the present invention relates to the specific field of turbomachines and is particularly interested in the problem posed by injecting fuel into the combustion chamber of a turbomachine.
- fuel injection into the chamber of combustion 50 is carried out from several injection systems 52 each comprising, on the one hand, a fuel injection nozzle 54 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 56 which produces the combustion / fuel mixture and diffuses it into this combustion chamber.
- This mixer / baffle assembly includes a first swirl device or primary swirler (swirler 58) mounted sliding on the fuel injection nozzle 54 (via a sleeve 60), a venturi device 62, a second vortex or secondary spin device 64 and a deflector 66 fixed on the bottom of the combustion chamber 68.
- This conventional injection system architecture however has the major disadvantage of presenting, under certain particular conditions of use, a risk of self-ignition likely to cause destruction of the combustion chamber. Indeed, the impact of fuel on the internal surface venturi, necessary to obtain a film of fuel whose fragmentation into fine droplets will be ensured by the shears generated by the primary tendrils and secondary, sometimes results in fuel lift in the bladders of the primary spin. Moreover, because the impact zone of the fuel on this internal surface is not precisely localized, a fuel injection to countercurrent in this primary swirl may also possibly occur. However, such a return of fuel in the primary swirler can help to bring this fuel on the outside of the flame tube and thus risk destroying the fire of the combustion chamber of the turbomachine.
- the present invention overcomes these disadvantages by proposing a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand a mixer / deflector assembly disposed coaxially with said nozzle of injection and which carries out the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly having a first vortex device (or primary swirler) and at least one second device with a vortex (or secondary swirl) arranged axially at a determined distance from each other and separated by a venturi device arranged coaxially with said injection nozzle, characterized in that said first vortex device is attached integrally with said injection nozzle and separated therefrom by a radial distance constant, determined so that the fuel vaporized by said nozzle injection device can not in any way impact on said first device whirlwind.
- a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand
- the second vortex device is slidably mounted by relative to said injection nozzle via a fixed crown of said second vortex device and which can move, perpendicular to a axis of revolution of said injection nozzle, in an annular housing of said Venturi device.
- this venturi device comprises an inner surface having on an upstream portion a slope discontinuity.
- This upstream part of the internal surface of the venturi device may comprise a concave step or a convex step.
- the annular combustion chamber is formed of an outer axial wall 24 and an inner axial wall 26, both coaxial axis 10, and a wall transverse 28 forming chamber bottom and provided with a plurality of openings 30 for fixing the injection systems.
- the different links between upstream ends of the axial walls of the chamber 24, 26, optionally caps 32, 34 extending upstream these ends of walls, and ends folded from the bottom chamber 28 is performed by any means of attachment conventional (not shown), for example screw bolts with conical head, preferably of prison nut type.
- Each injection system of the injection assembly comprises on the one hand a fuel injection nozzle 36 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 38 coaxial with this injection nozzle and which produces the fuel / fuel mixture and the diffuses into this combustion chamber.
- This mixer / baffle assembly has at least one first vortex or swirl device (swirler 40) and a second secondary vortex or swirl device 42 spaced axially from each other by a determined distance and separated by a venturi device 44.
- the secondary swirler is extended by a deflector 46 fixed to the chamber bottom 28 and which extends through the opening 30 in the combustion chamber 22.
- the primary swirler 40 is fixed integrally to the nozzle injection device 36, for example by means of a sleeve 48, and of which it is therefore separated by a constant radial distance. This distance is determined from such that, irrespective of the operating conditions of the turbomachine (autorotation, idle, full throttle), the fuel vaporized by the injection nozzle can in no way impact the primary swirler.
- the turbomachine autorotation, idle, full throttle
- the fuel vaporized by the injection nozzle can in no way impact the primary swirler.
- venturi device further comprises on its inner surface 44A an upstream portion P with a slope discontinuity so as to prevent, or at the very least, significantly reduce any risk of fuel rising by capillarity in the primary swirl 40 of the injection system 20.
- This discontinuity of slope carried out upstream of the outer surface E of the fuel injection cone may example be constituted by a concave step.
- this discontinuity of slope is instead constituted by a step convex.
- the secondary spin 42 is slidably mounted relative to this injection nozzle, perpendicular to a axis of revolution S of the nozzle, for example by means of a ring 47 fixed on this secondary swirler and able to move in an annular housing 49 of the venturi device 44.
- sufficient clearance is left between the inner periphery of this annular housing and the outer periphery of the crowned.
- the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any fuel injection against the current, and the discontinuity of slope of this venturi also makes it possible to avoid any fuel capillarity.
- the particular structure of the invention ensures a good spraying fuel in all flight conditions and in particular in the most severe conditions for re-ignition in low autorotation Mach, conditions under which the air supply pressure drops are too small to guarantee sufficient fragmentation of the fuel and thus access a vast re-ignition domain.
Landscapes
- 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)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
Système d'injection d'une chambre de combustion de turbomachine comportant une buse d'injection de carburant assurant la vaporisation du carburant dans la chambre de combustion et un ensemble mélangeur/déflecteur coaxial à cette buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans la chambre de combustion, cet ensemble mélangeur/déflecteur comportant une vrille primaire (40) et une vrille secondaire (42) disposés axialement à une distance déterminée l'un de l'autre et séparés par un dispositif à venturi (44) disposé coaxialement à la buse d'injection, la vrille primaire étant fixée solidairement à la buse d'injection et séparée de celle-ci d'une distance radiale constante, déterminée de telle sorte que le carburant vaporisé par la buse d'injection ne peut en aucune façon impacter sur la vrille primaire. De préférence, le dispositif à venturi comporte une surface interne (44A) présentant sur une partie amont une discontinuité de pente P. <IMAGE>Injection system of a turbomachine combustion chamber comprising a fuel injection nozzle for vaporizing the fuel in the combustion chamber and a mixer / deflector assembly coaxial with this injection nozzle and which carries out the combustion / fuel and diffuses it into the combustion chamber, this mixing / deflecting assembly comprising a primary swirler (40) and a secondary swirler (42) arranged axially at a determined distance from one another and separated by a venturi device ( 44) disposed coaxially with the injection nozzle, the primary swirler being integrally fixed to the injection nozzle and separated therefrom by a constant radial distance, determined so that the fuel vaporized by the injection nozzle can not in any way impact on the primary spin. Preferably, the venturi device comprises an inner surface (44A) presenting on an upstream part a slope discontinuity P. <IMAGE>
Description
La présente invention se rapporte au domaine spécifique des turbomachines et elle s'intéresse plus particulièrement au problème posé par l'injection de carburant dans la chambre de combustion d'une turbomachine.The present invention relates to the specific field of turbomachines and is particularly interested in the problem posed by injecting fuel into the combustion chamber of a turbomachine.
Classiquement, dans un turboréacteur ou un turbopropulseur,
comme l'illustre la figure 4, l'injection de carburant dans la chambre de
combustion 50 est effectuée à partir de plusieurs systèmes d'injection 52
comportant chacun, d'une part une buse d'injection de carburant 54 assurant la
vaporisation du carburant dans la chambre de combustion et d'autre part un
ensemble mélangeur/déflecteur 56 qui réalise le mélange comburant/carburant et
le diffuse dans cette chambre de combustion. Cet ensemble mélangeur/déflecteur
comporte un premier dispositif à tourbillon ou vrille primaire (swirler 58) monté
coulissant sur la buse d'injection de carburant 54 (via un manchon 60), un
dispositif à venturi 62, un second dispositif à tourbillon ou vrille secondaire 64 et
un déflecteur 66 fixé sur le fond de la chambre de combustion 68. La demande de
brevet française N° 2 728 330 et le brevet américain N° 5 490 378 sont deux
exemples parfaits de cet art antérieur. On notera que dans les tous systèmes
d'injection divulgués à ce jour, comme l'illustre la figure 5, la surface interne du
venturi 62A sur laquelle va impacter le carburant vaporisé par la buse d'injection
54 présente toujours une surface continue (sans discontinuité de pente) jusqu'à la
sortie d'air de la vrille primaire.Conventionally, in a turbojet engine or a turboprop engine,
as illustrated in Figure 4, fuel injection into the chamber of
Cette architecture conventionnelle de système d'injection a toutefois l'inconvénient majeur de présenter, dans certaines conditions particulières d'utilisation, un risque d'auto-inflammation de nature à provoquer une destruction de la chambre de combustion. En effet, l'impact du carburant sur la surface interne du venturi, nécessaire pour obtenir un film de carburant dont la fragmentation en fines gouttelettes sera assurée par les cisaillements générés par les vrilles primaire et secondaire, se traduit parfois par des remontées de carburant dans les aubages de la vrille primaire. De plus, du fait que la zone d'impact du carburant sur cette surface interne n'est pas précisément localisée, une injection de carburant à contre-courant dans cette vrille primaire peut aussi éventuellement se produire. Or, un tel retour de carburant dans la vrille primaire peut contribuer à amener ce carburant à l'extérieur du tube à flamme et donc risquer une destruction du foyer de la chambre de combustion de la turbomachine.This conventional injection system architecture however has the major disadvantage of presenting, under certain particular conditions of use, a risk of self-ignition likely to cause destruction of the combustion chamber. Indeed, the impact of fuel on the internal surface venturi, necessary to obtain a film of fuel whose fragmentation into fine droplets will be ensured by the shears generated by the primary tendrils and secondary, sometimes results in fuel lift in the bladders of the primary spin. Moreover, because the impact zone of the fuel on this internal surface is not precisely localized, a fuel injection to countercurrent in this primary swirl may also possibly occur. However, such a return of fuel in the primary swirler can help to bring this fuel on the outside of the flame tube and thus risk destroying the fire of the combustion chamber of the turbomachine.
La présente invention pallie ces inconvénients en proposant un système d'injection de turbomachine comportant d'une part une buse d'injection de carburant assurant la vaporisation du carburant dans la chambre de combustion et d'autre part un ensemble mélangeur/déflecteur disposé coaxialement à ladite buse d'injection et qui réalise le mélange comburant/carburant et le diffuse dans ladite chambre de combustion, ledit ensemble mélangeur/déflecteur comportant un premier dispositif à tourbillon (ou vrille primaire) et au moins un second dispositif à tourbillon (ou vrille secondaire) disposés axialement à une distance déterminée l'un de l'autre et séparés par un dispositif à venturi disposé coaxialement à ladite buse d'injection, caractérisé en ce que ledit premier dispositif à tourbillon est fixé solidairement à ladite buse d'injection et séparé de celle-ci d'une distance radiale constante, déterminée de telle sorte que le carburant vaporisé par ladite buse d'injection ne peut en aucune façon impacter sur ledit premier dispositif à tourbillon.The present invention overcomes these disadvantages by proposing a system turbomachine injection system comprising on the one hand an injection nozzle of fuel to vaporize the fuel in the combustion chamber and on the other hand a mixer / deflector assembly disposed coaxially with said nozzle of injection and which carries out the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly having a first vortex device (or primary swirler) and at least one second device with a vortex (or secondary swirl) arranged axially at a determined distance from each other and separated by a venturi device arranged coaxially with said injection nozzle, characterized in that said first vortex device is attached integrally with said injection nozzle and separated therefrom by a radial distance constant, determined so that the fuel vaporized by said nozzle injection device can not in any way impact on said first device whirlwind.
De préférence, le second dispositif à tourbillon est monté coulissant par rapport à ladite buse d'injection par l'intermédiaire d'une couronne solidaire dudit second dispositif à tourbillon et qui peut se déplacer, perpendiculairement à un axe de révolution de ladite buse d'injection, dans un logement annulaire dudit dispositif à venturi.Preferably, the second vortex device is slidably mounted by relative to said injection nozzle via a fixed crown of said second vortex device and which can move, perpendicular to a axis of revolution of said injection nozzle, in an annular housing of said Venturi device.
Avec ce système de liaison coulissante au niveau de la seule vrille secondaire, l'injection de carburant à contre-courant dans la vrille primaire est éliminée.With this sliding link system at the level of the single twist secondary, fuel injection against the current in the primary spin is eliminated.
Selon un mode de réalisation avantageux, ce dispositif à venturi comporte une surface interne présentant sur une partie amont une discontinuité de pente. Cette partie amont de la surface interne du dispositif à venturi peut comporter une marche concave ou une marche convexe. According to an advantageous embodiment, this venturi device comprises an inner surface having on an upstream portion a slope discontinuity. This upstream part of the internal surface of the venturi device may comprise a concave step or a convex step.
Avec cette architecture spécifique de venturi, l'injection de carburant par capillarité dans la vrille primaire peut être limitée.With this specific Venturi architecture, fuel injection by capillarity in the primary swirler can be limited.
Les caractéristiques et avantages de la présente invention ressortiront mieux de la description suivante, faite à titre indicatif et non limitatif, en regard des dessins annexés sur lesquels :
- la figure 1 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine conforme à l'invention,
- la figure 2 est une vue agrandie d'une partie de la figure 1 dans un premier exemple de réalisation de l'invention,
- la figure 3 est une vue agrandie d'une partie de la figure 1 dans un second exemple de réalisation de l'invention,
- la figure 4 est une vue schématique en demi-coupe axiale d'une partie d'injection d'une turbomachine incorporant un système d'injection de l'art antérieur, et
- la figure 5 est une vue agrandie d'une partie de la figure 4.
- FIG. 1 is a diagrammatic axial half-section view of an injection part of a turbomachine according to the invention,
- FIG. 2 is an enlarged view of a portion of FIG. 1 in a first embodiment of the invention;
- FIG. 3 is an enlarged view of part of FIG. 1 in a second embodiment of the invention;
- FIG. 4 is a diagrammatic axial half-section view of an injection part of a turbomachine incorporating an injection system of the prior art, and
- Figure 5 is an enlarged view of a portion of Figure 4.
La figure 1 montre en demi-coupe axiale une partie d'injection d'une turbomachine comprenant :
- une enveloppe annulaire externe (ou carter externe) 12, d'axe longitudinal 10,
- une enveloppe annulaire interne (ou carter interne) coaxiale 14,
- un espace annulaire 16 compris entre les deux
enveloppes 12 et 14 recevant le comburant comprimé, généralement de l'air, provenant en amont d'un compresseur (non représenté) de la turbomachine, au travers d'un conduit annulaire de diffusion 18 (on notera la présence de la grille dediffusion 18a) définissant un flux général F d'écoulement des gaz, cetespace 16 comportant, dans le sens d'écoulement de ces gaz, tout d'abord un ensemble d'injection comportant une pluralité de systèmes d'injection 20 fixés sur l'enveloppe annulaire externe 12 et régulièrement répartis autour duconduit 18, ensuite une chambre de combustion annulaire 22, et enfin un distributeur annulaire (non représenté) formant un étage d'entrée d'une turbine haute pression.
- an outer annular casing (or outer casing) 12, of
longitudinal axis 10, - an inner annular envelope (or inner casing) coaxial 14,
- an
annular space 16 between the twoenvelopes 12 and 14 receiving the compressed oxidant, generally air, coming upstream of a compressor (not shown) of the turbomachine, through an annular diffusion duct 18 (on note the presence of thediffusion gate 18a) defining a general flow F of gas flow, thisspace 16 having, in the direction of flow of these gases, first of all an injection assembly comprising a plurality ofsystems injection 20 fixed on the outerannular envelope 12 and regularly distributed around theconduit 18, then anannular combustion chamber 22, and finally an annular distributor (not shown) forming an inlet stage of a high pressure turbine.
La chambre de combustion annulaire est formée d'une paroi axiale externe
24 et d'une paroi axiale interne 26, toutes deux coaxiales d'axe 10, et d'une paroi
transversale 28 formant fond de chambre et pourvue d'une pluralité d'ouvertures
30 pour la fixation des systèmes d'injection. Les différentes liaisons entre les
extrémités amont des parois axiales de la chambre 24, 26, éventuellement des
casquettes 32, 34 prolongeant en amont ces extrémités de parois, et des extrémités
rabattues du fond de chambre 28 est effectuée par tout moyen de fixation
conventionnel (non représenté), par exemple des boulons à vis à tête conique, de
préférence de type à écrou prisonnier.The annular combustion chamber is formed of an outer
Chaque système d'injection de l'ensemble d'injection comporte d'une part
une buse d'injection de carburant 36 assurant la vaporisation du carburant dans la
chambre de combustion et d'autre part un ensemble mélangeur/déflecteur 38
coaxial à cette buse d'injection et qui réalise le mélange comburant/carburant et le
diffuse dans cette chambre de combustion. Cet ensemble mélangeur/déflecteur
comporte au moins un premier dispositif à tourbillon ou vrille primaire (swirler
40) et un second dispositif à tourbillon ou vrille secondaire 42 espacés axialement
l'un de l'autre d'une distance déterminée et séparés par un dispositif à venturi 44.
La vrille secondaire est prolongée par un déflecteur 46 fixé au fond de chambre 28
et qui s'étend au travers de l'ouverture 30 dans la chambre de combustion 22.Each injection system of the injection assembly comprises on the one hand
a
Selon l'invention, la vrille primaire 40 est fixée solidairement à la buse
d'injection 36, par exemple par l'intermédiaire d'un manchon 48, et dont elle est
donc séparée par une distance radiale constante. Cette distance est déterminée de
telle sorte que, quels que soient les régimes de fonctionnement de la turbomachine
(autorotation, ralenti, plein gaz), le carburant vaporisé par la buse d'injection ne
peut en aucune façon impacter sur la vrille primaire. Ainsi, on peut éviter toute
éventuelle injection à contre-courant de carburant dans cette vrille primaire
résultant des dispersions de carburant existant naturellement d'un injecteur à
l'autre (du fait des angles d'injection, de l'homogénéité circonférentielle, etc.)
comme des rebonds de carburant sur le dispositif à venturi.According to the invention, the
Selon un premier mode de réalisation de l'invention illustré à la figure 2, le
dispositif à venturi comporte en outre sur sa surface interne 44A une partie amont
présentant en P une discontinuité de pente de façon à empêcher, ou à tout le moins
réduire notablement, tout risque de remontée du carburant par capillarité dans la
vrille primaire 40 du système d'injection 20. Cette discontinuité de pente effectuée
en amont de la surface externe E du cône d'injection de carburant peut par
exemple être constituée par une marche concave. Sur l'exemple de réalisation de
la figure 3, cette discontinuité de pente est au contraire constituée par une marche
convexe.According to a first embodiment of the invention illustrated in FIG.
venturi device further comprises on its
En outre, afin de laisser un débattement suffisant entre la buse d'injection
36 solidaire de l'enveloppe externe 12 et l'ensemble mélangeur/déflecteur 38
(notamment pour la gestion des dilatations thermiques), la vrille secondaire 42 est
montée coulissante par rapport à cette buse d'injection, perpendiculairement à un
axe de révolution S de la buse, par exemple par l'intermédiaire d'une couronne 47
fixée sur cette vrille secondaire et pouvant se déplacer dans un logement annulaire
49 du dispositif à venturi 44. A cet effet, un jeu suffisant est laissé entre la
périphérie interne de ce logement annulaire et la périphérie externe de la
couronne.In addition, to allow sufficient clearance between the
Avec la configuration de liaison coulissante proposée, la buse d'injection est constamment centrée par rapport à la vrille primaire et le dispositif à venturi évitant ainsi toute injection de carburant à contre-courant, et la discontinuité de pente de ce venturi permet en outre d'éviter toute remontée de carburant par capillarité. Ainsi, avec la structure particulière de l'invention, on assure une bonne pulvérisation du carburant dans toutes les conditions de vol et notamment dans les conditions particulières les plus sévères de rallumage en autorotation à faible Mach, conditions dans lesquelles les pertes de charge d'alimentation en air sont trop faibles pour garantir une fragmentation suffisante du carburant et ainsi accéder à un vaste domaine de rallumage.With the proposed sliding link configuration, the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any fuel injection against the current, and the discontinuity of slope of this venturi also makes it possible to avoid any fuel capillarity. Thus, with the particular structure of the invention, it ensures a good spraying fuel in all flight conditions and in particular in the most severe conditions for re-ignition in low autorotation Mach, conditions under which the air supply pressure drops are too small to guarantee sufficient fragmentation of the fuel and thus access a vast re-ignition domain.
Claims (5)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0109456A FR2827367B1 (en) | 2001-07-16 | 2001-07-16 | AEROMECHANICAL INJECTION SYSTEM WITH ANTI-RETURN PRIMARY LOCK |
FR0109456 | 2001-07-16 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1278012A2 true EP1278012A2 (en) | 2003-01-22 |
EP1278012A3 EP1278012A3 (en) | 2003-11-19 |
EP1278012B1 EP1278012B1 (en) | 2006-10-25 |
Family
ID=8865551
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02291767A Expired - Lifetime EP1278012B1 (en) | 2001-07-16 | 2002-07-12 | Aeromechanical injection system with non-return primary swirler |
Country Status (10)
Country | Link |
---|---|
US (1) | US6959551B2 (en) |
EP (1) | EP1278012B1 (en) |
JP (1) | JP4066241B2 (en) |
CN (1) | CN1230650C (en) |
CA (1) | CA2393082C (en) |
DE (1) | DE60215589T2 (en) |
ES (1) | ES2272650T3 (en) |
FR (1) | FR2827367B1 (en) |
RU (1) | RU2295645C2 (en) |
UA (1) | UA76709C2 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1488086A1 (en) * | 2002-03-12 | 2004-12-22 | Rolls-Royce Corporation | Dry low combustion system with means for eliminating combustion noise |
EP1873457A1 (en) * | 2006-06-29 | 2008-01-02 | Snecma | Device for injecting a mix of air and fuel, combustion chamber and turbomachine equipped with such a device |
EP1873456A1 (en) * | 2006-06-29 | 2008-01-02 | Snecma | Device for injecting a mix of air and fuel, combustion chamber and turbomachine equipped with such a device |
Families Citing this family (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6968692B2 (en) | 2002-04-26 | 2005-11-29 | Rolls-Royce Corporation | Fuel premixing module for gas turbine engine combustor |
US20050229600A1 (en) * | 2004-04-16 | 2005-10-20 | Kastrup David A | Methods and apparatus for fabricating gas turbine engine combustors |
US7966832B1 (en) * | 2004-12-29 | 2011-06-28 | Solar Turbines Inc | Combustor |
US7316117B2 (en) * | 2005-02-04 | 2008-01-08 | Siemens Power Generation, Inc. | Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations |
US7628019B2 (en) * | 2005-03-21 | 2009-12-08 | United Technologies Corporation | Fuel injector bearing plate assembly and swirler assembly |
JP2006300448A (en) * | 2005-04-22 | 2006-11-02 | Mitsubishi Heavy Ind Ltd | Combustor for gas turbine |
CN100390397C (en) * | 2005-04-30 | 2008-05-28 | 张鸿元 | Air compression aeroengine |
US7513098B2 (en) | 2005-06-29 | 2009-04-07 | Siemens Energy, Inc. | Swirler assembly and combinations of same in gas turbine engine combustors |
US7617689B2 (en) * | 2006-03-02 | 2009-11-17 | Honeywell International Inc. | Combustor dome assembly including retaining ring |
FR2901574B1 (en) * | 2006-05-29 | 2008-07-04 | Snecma Sa | DEVICE FOR GUIDING AN AIR FLOW AT THE ENTRANCE OF A COMBUSTION CHAMBER IN A TURBOMACHINE |
FR2908867B1 (en) * | 2006-11-16 | 2012-06-15 | Snecma | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
FR2920032B1 (en) * | 2007-08-13 | 2014-08-22 | Snecma | DIFFUSER OF A TURBOMACHINE |
US9027350B2 (en) * | 2009-12-30 | 2015-05-12 | Rolls-Royce Corporation | Gas turbine engine having dome panel assembly with bifurcated swirler flow |
US10317081B2 (en) * | 2011-01-26 | 2019-06-11 | United Technologies Corporation | Fuel injector assembly |
FR2986856B1 (en) * | 2012-02-15 | 2018-05-04 | Safran Aircraft Engines | DEVICE FOR INJECTING AIR AND FUEL FOR A COMBUSTION CHAMBER OF A TURBOMACHINE |
CN103836647B (en) * | 2014-02-27 | 2015-07-29 | 中国科学院工程热物理研究所 | A kind of Venturi tube runner wall structure |
FR3029608B1 (en) * | 2014-12-03 | 2017-01-13 | Snecma | AIR INTAKE CROWN FOR TURBOMACHINE COMBUSTION CHAMBER INJECTION SYSTEM AND FUEL ATOMIZATION METHOD IN INJECTION SYSTEM COMPRISING SAID AIR INTAKE CROWN |
CN104676647A (en) * | 2014-12-15 | 2015-06-03 | 西北工业大学 | Venturi apparatus for strengthening liquid-membrane crushing effect |
CN104566467B (en) * | 2014-12-31 | 2018-02-23 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of anti-backfire type nozzle |
FR3038699B1 (en) * | 2015-07-08 | 2022-06-24 | Snecma | BENT COMBUSTION CHAMBER OF A TURBOMACHINE |
US10801726B2 (en) | 2017-09-21 | 2020-10-13 | General Electric Company | Combustor mixer purge cooling structure |
FR3080437B1 (en) * | 2018-04-24 | 2020-04-17 | Safran Aircraft Engines | INJECTION SYSTEM FOR A TURBOMACHINE ANNULAR COMBUSTION CHAMBER |
US11378275B2 (en) * | 2019-12-06 | 2022-07-05 | Raytheon Technologies Corporation | High shear swirler with recessed fuel filmer for a gas turbine engine |
US11428411B1 (en) * | 2021-05-18 | 2022-08-30 | General Electric Company | Swirler with rifled venturi for dynamics mitigation |
CN115711176A (en) | 2021-08-23 | 2023-02-24 | 通用电气公司 | Dome with integrated trumpet swirler |
GB2611115A (en) * | 2021-09-23 | 2023-03-29 | Gen Electric | Floating primary vane swirler |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2246734A1 (en) * | 1973-10-01 | 1975-05-02 | Gen Electric | |
EP0469899A1 (en) * | 1990-08-02 | 1992-02-05 | General Electric Company | Combustor dome assembly |
US5966937A (en) * | 1997-10-09 | 1999-10-19 | United Technologies Corporation | Radial inlet swirler with twisted vanes for fuel injector |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3703259A (en) * | 1971-05-03 | 1972-11-21 | Gen Electric | Air blast fuel atomizer |
US3946552A (en) * | 1973-09-10 | 1976-03-30 | General Electric Company | Fuel injection apparatus |
GB9023004D0 (en) * | 1990-10-23 | 1990-12-05 | Rolls Royce Plc | A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber |
DE4110507C2 (en) | 1991-03-30 | 1994-04-07 | Mtu Muenchen Gmbh | Burner for gas turbine engines with at least one swirl device which can be regulated in a load-dependent manner for the supply of combustion air |
GB2272756B (en) * | 1992-11-24 | 1995-05-31 | Rolls Royce Plc | Fuel injection apparatus |
DE4444961A1 (en) | 1994-12-16 | 1996-06-20 | Mtu Muenchen Gmbh | Device for cooling in particular the rear wall of the flame tube of a combustion chamber for gas turbine engines |
FR2753779B1 (en) * | 1996-09-26 | 1998-10-16 | AERODYNAMIC INJECTION SYSTEM FOR A FUEL AIR MIXTURE | |
US6571559B1 (en) * | 1998-04-03 | 2003-06-03 | General Electric Company | Anti-carboning fuel-air mixer for a gas turbine engine combustor |
US6314739B1 (en) * | 2000-01-13 | 2001-11-13 | General Electric Company | Brazeless combustor dome assembly |
US6735950B1 (en) * | 2000-03-31 | 2004-05-18 | General Electric Company | Combustor dome plate and method of making the same |
US6427435B1 (en) * | 2000-05-20 | 2002-08-06 | General Electric Company | Retainer segment for swirler assembly |
-
2001
- 2001-07-16 FR FR0109456A patent/FR2827367B1/en not_active Expired - Fee Related
-
2002
- 2002-07-10 RU RU2002118252/06A patent/RU2295645C2/en active
- 2002-07-10 CA CA2393082A patent/CA2393082C/en not_active Expired - Lifetime
- 2002-07-12 EP EP02291767A patent/EP1278012B1/en not_active Expired - Lifetime
- 2002-07-12 JP JP2002203572A patent/JP4066241B2/en not_active Expired - Lifetime
- 2002-07-12 DE DE60215589T patent/DE60215589T2/en not_active Expired - Lifetime
- 2002-07-12 ES ES02291767T patent/ES2272650T3/en not_active Expired - Lifetime
- 2002-07-15 UA UA2002075852A patent/UA76709C2/en unknown
- 2002-07-15 US US10/194,230 patent/US6959551B2/en not_active Expired - Lifetime
- 2002-07-16 CN CN02126114.8A patent/CN1230650C/en not_active Expired - Lifetime
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2246734A1 (en) * | 1973-10-01 | 1975-05-02 | Gen Electric | |
EP0469899A1 (en) * | 1990-08-02 | 1992-02-05 | General Electric Company | Combustor dome assembly |
US5966937A (en) * | 1997-10-09 | 1999-10-19 | United Technologies Corporation | Radial inlet swirler with twisted vanes for fuel injector |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1488086A1 (en) * | 2002-03-12 | 2004-12-22 | Rolls-Royce Corporation | Dry low combustion system with means for eliminating combustion noise |
EP1488086A4 (en) * | 2002-03-12 | 2007-07-04 | Rolls Royce Corp | Dry low combustion system with means for eliminating combustion noise |
EP1873457A1 (en) * | 2006-06-29 | 2008-01-02 | Snecma | Device for injecting a mix of air and fuel, combustion chamber and turbomachine equipped with such a device |
EP1873456A1 (en) * | 2006-06-29 | 2008-01-02 | Snecma | Device for injecting a mix of air and fuel, combustion chamber and turbomachine equipped with such a device |
FR2903173A1 (en) * | 2006-06-29 | 2008-01-04 | Snecma Sa | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
FR2903170A1 (en) * | 2006-06-29 | 2008-01-04 | Snecma Sa | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
US7861529B2 (en) | 2006-06-29 | 2011-01-04 | Snecma | Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine both equipped with such a device |
US7908865B2 (en) | 2006-06-29 | 2011-03-22 | Snecma | Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device |
Also Published As
Publication number | Publication date |
---|---|
RU2295645C2 (en) | 2007-03-20 |
CN1407280A (en) | 2003-04-02 |
CA2393082A1 (en) | 2003-01-16 |
RU2002118252A (en) | 2004-02-10 |
US6959551B2 (en) | 2005-11-01 |
CN1230650C (en) | 2005-12-07 |
UA76709C2 (en) | 2006-09-15 |
FR2827367A1 (en) | 2003-01-17 |
JP2003042452A (en) | 2003-02-13 |
EP1278012B1 (en) | 2006-10-25 |
US20030010034A1 (en) | 2003-01-16 |
JP4066241B2 (en) | 2008-03-26 |
DE60215589T2 (en) | 2007-08-30 |
DE60215589D1 (en) | 2006-12-07 |
ES2272650T3 (en) | 2007-05-01 |
FR2827367B1 (en) | 2003-10-17 |
EP1278012A3 (en) | 2003-11-19 |
CA2393082C (en) | 2010-10-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1278012B1 (en) | Aeromechanical injection system with non-return primary swirler | |
EP0833107B1 (en) | Aerodynamic fuel-air mixture injection device | |
CA2207831C (en) | Injection system with very high degree of homogenization | |
CA2593186C (en) | Device for the injection of an air-fuel mixture, combustion chamber and turbine engine equipped with such a device | |
EP1640661B1 (en) | Aerodynamic effervescent fuel/air injection system for a gas turbine combustion chamber | |
EP1431658B1 (en) | Compact gas burner with internal flame | |
CA2646959C (en) | Injection system of a fuel and air mixture in a turbine engine combustion system | |
FR2825784A1 (en) | HANGING THE CMC COMBUSTION TURBOMACHINE USING THE DILUTION HOLES | |
EP1640662A1 (en) | Effervescent injector for an aeromechanical air/fuel injection system integrated into a gas turbine combustor | |
FR2967479A1 (en) | DEVICE AND METHOD FOR IGNITING A COMBUSTION SYSTEM | |
EP3530908B1 (en) | Combustion chamber comprising two types of injectors in which the sealing members have a different opening threshold | |
CA2610516A1 (en) | Device for injecting a fuel-air mixture, combustion chamber and turbomachine equipped with such device | |
CA2033366C (en) | Industrial oil burner with low nitrogen oxides emission generating multiple elementary flames and use thereof | |
EP1621817B1 (en) | Afterburner with assured ignition | |
FR3082284A1 (en) | COMBUSTION CHAMBER FOR A TURBOMACHINE | |
EP1939528B1 (en) | Deflector for the bottom of a combustion chamber, combustion chamber equipped with same and jet engine comprising them | |
EP3784958B1 (en) | Injection system for an annular combustion chamber of a gas turbine | |
FR2931929A1 (en) | ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE | |
FR2706020A1 (en) | Combustion chamber assembly, in particular for a gas turbine; comprising separate combustion and vaporization zones. | |
EP4004443B1 (en) | Combustion chamber comprising secondary injection systems, and fuel supply method | |
EP4042070B1 (en) | Pre-vaporisation tube for a turbine engine combustion chamber | |
EP4179256B1 (en) | Annular combustion chamber for an aircraft turbomachine | |
FR3113302A1 (en) | Combustion chamber for a turbomachine | |
WO2022223914A1 (en) | Diffusion cone for the rear part of a jet engine, incorporating a flame-holder ring at the trailing edge | |
FR2619891A1 (en) | Gas-burner head |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20020718 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL LT LV MK RO SI |
|
AKX | Designation fees paid |
Designated state(s): DE ES FR GB IT SE |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SNECMA |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE ES FR GB IT SE |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REF | Corresponds to: |
Ref document number: 60215589 Country of ref document: DE Date of ref document: 20061207 Kind code of ref document: P |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20070131 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2272650 Country of ref document: ES Kind code of ref document: T3 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20070726 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20120716 Year of fee payment: 11 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20140807 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20130713 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 15 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN AIRCRAFT ENGINES Effective date: 20170717 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 17 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20210623 Year of fee payment: 20 Ref country code: IT Payment date: 20210622 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20210623 Year of fee payment: 20 Ref country code: GB Payment date: 20210623 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20210622 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 60215589 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20220711 |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20220711 |