EP1278012B1 - Aeromechanical injection system with non-return primary swirler - Google Patents
Aeromechanical injection system with non-return primary swirler Download PDFInfo
- Publication number
- EP1278012B1 EP1278012B1 EP02291767A EP02291767A EP1278012B1 EP 1278012 B1 EP1278012 B1 EP 1278012B1 EP 02291767 A EP02291767 A EP 02291767A EP 02291767 A EP02291767 A EP 02291767A EP 1278012 B1 EP1278012 B1 EP 1278012B1
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- EP
- European Patent Office
- Prior art keywords
- injection
- fuel
- injection nozzle
- 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.)
- Expired - Lifetime
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Classifications
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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
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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
- F23R3/28—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 more particularly concerned with the problem posed by the injection of fuel into the combustion chamber of a turbomachine.
- the injection of fuel into the combustion chamber 50 is carried out from several injection systems 52 each comprising, on the one hand, a nozzle of fuel injection 54 ensuring the vaporization of the fuel in the combustion chamber and secondly a mixer / deflector assembly 56 which carries the combustion / fuel mixture and the diffuse in this combustion chamber.
- This mixer / baffle assembly comprises a first vortex or swirl device 58 (swirler 58) slidably mounted on the fuel injection nozzle 54 (via a sleeve 60), a venturi device 62, a second vortex device or secondary swirler 64 and a deflector 66 fixed to the bottom of the combustion chamber 68.
- This conventional injection system architecture has the major drawback 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 of the venturi, necessary to obtain a film of fuel whose fragmentation in fine droplets will be ensured by the shears generated by the primary and secondary tendrils, sometimes results in fuel increases in the vanes of the primary swirl. In addition, because the impact zone of the fuel on this inner 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 contribute to bringing this fuel outside the flame tube and thus risk destroying the focus of the combustion chamber of the turbomachine.
- a turbomachine injection system comprising firstly a fuel injection nozzle for vaporizing the fuel in the combustion chamber and secondly a mixer / deflector assembly disposed coaxially to said injection nozzle and which conducts the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly comprising a first vortex device (or primary swirler) and at least a second vortex device (or secondary swirler) ) disposed axially at a determined distance from each other and separated by a venturi device disposed coaxially with said injection nozzle, said first vortex device being fixedly attached to said injection nozzle and separated therefrom constant radial distance, characterized in that the venturi device has an internal surface presenting r an upstream part a discontinuity of slope.
- the second vortex device is slidably mounted relative to said injection nozzle via a ring integral with said second vortex device and which can move perpendicularly to an axis of revolution of said vane nozzle. injection, in an annular housing of said venturi device.
- the upstream portion of the inner surface of the venturi device may comprise a concave step or a convex step.
- capillary fuel injection into the primary swirler can be limited.
- the annular combustion chamber is formed of an outer axial wall 24 and an inner axial wall 26, both coaxial with axis 10, and a transverse wall 28 forming chamber bottom and provided with a plurality of openings 30 for fixing the injection systems.
- the different connections between the upstream ends of the axial walls of the chamber 24, 26, possibly caps 32, 34 extending upstream these wall ends, and folded ends of the chamber bottom 28 is performed by any conventional fastening means (not shown), for example screw bolts with a conical head, preferably of the type with a prison nut.
- Each injection system of the injection assembly comprises firstly a fuel injection nozzle 36 for vaporizing the fuel in the combustion chamber and secondly a mixer / deflector assembly 38 coaxial with this nozzle injection and that achieves the combustion / fuel mixture and the diffuse in this combustion chamber.
- This mixer / baffle assembly comprises at least a first vortex device (swirler 40) and a second vortex device 42 spaced axially from each other by a predetermined distance and separated by a device. Venturi 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 injection nozzle 36, for example by means of a sleeve 48, and from which it is separated by a constant radial distance. This distance is determined so that, irrespective of the operating conditions of the turbomachine (autorotation, idle, full throttle), the fuel vaporized by the injection nozzle can not in any way impact the primary swirler. Thus, it is possible to avoid any possible countercurrent injection of fuel into this primary swirler resulting from the fuel dispersions naturally existing from one injector to the other (because of the injection angles, the circumferential homogeneity, etc.). ) as fuel rebounds on the venturi device.
- the venturi device furthermore has on its inner surface 44A an upstream portion presenting at P a slope discontinuity so as to prevent, or at the very least, to reduce significantly, any risk of capillary rise of the fuel in the primary swirler 40 of the injection system 20.
- This discontinuity of slope made upstream of the outer surface E of the fuel injection cone may for example be constituted by a step concave. In the embodiment of FIG. 3, this discontinuity of slope is instead constituted by a convex step.
- the secondary swirler 42 is slidably mounted relative to to this injection nozzle, perpendicularly to an axis of revolution S of the nozzle, for example by means of a ring 47 fixed to this secondary swirler and movable in an annular housing 49 of the venturi device 44. A this effect, a sufficient clearance is left between the inner periphery of this annular housing and the outer periphery of the ring.
- the injection nozzle is constantly centered with respect to the primary swirler and the venturi device thus avoiding any injection of countercurrent fuel, and the slope discontinuity of this venturi also makes it possible to avoid any rise of fuel by capillarity.
- a good spraying of the fuel is ensured in all flight conditions and in particular in the most severe special conditions of re-ignition in autorotation at low Mach, conditions under which the pressure drops of air supply are too weak to ensure sufficient fragmentation of the fuel and thus access to a large field of re-ignition.
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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)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
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 more particularly concerned with the problem posed by the injection of 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 FIG. 4, the injection of fuel into the
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 drawback 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 of the venturi, necessary to obtain a film of fuel whose fragmentation in fine droplets will be ensured by the shears generated by the primary and secondary tendrils, sometimes results in fuel increases in the vanes of the primary swirl. In addition, because the impact zone of the fuel on this inner 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 contribute to bringing this fuel outside the flame tube and thus risk destroying the focus 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, ledit premier dispositif à tourbillon étant fixé solidairement à ladite buse d'injection et séparé de celle-ci d'une distance radiale constante, caractérisé en ce que le dispositif à venturi comporte une surface interne présentant sur une partie amont une discontinuité de pente.The present invention overcomes these disadvantages by proposing a turbomachine injection system comprising firstly a fuel injection nozzle for vaporizing the fuel in the combustion chamber and secondly a mixer / deflector assembly disposed coaxially to said injection nozzle and which conducts the combustion / fuel mixture and diffuses it into said combustion chamber, said mixer / deflector assembly comprising a first vortex device (or primary swirler) and at least a second vortex device (or secondary swirler) ) disposed axially at a determined distance from each other and separated by a venturi device disposed coaxially with said injection nozzle, said first vortex device being fixedly attached to said injection nozzle and separated therefrom constant radial distance, characterized in that the venturi device has an internal surface presenting r an upstream part a discontinuity of slope.
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 relative to said injection nozzle via a ring integral with said second vortex device and which can move perpendicularly to an axis of revolution of said vane nozzle. injection, 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 connection system at the level of the only secondary swirler, the injection of fuel against the current in the primary swirler is eliminated.
Selon un mode de réalisation avantageux, la partie amont de la surface interne du dispositif à venturi peut comporter une marche concave ou une marche convexe.According to an advantageous embodiment, the upstream portion of the inner 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, capillary fuel injection into 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 diffusion 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 firstly 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. 2, the venturi device furthermore has 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, in order 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 injection of countercurrent fuel, and the slope discontinuity of this venturi also makes it possible to avoid any rise of fuel by capillarity. Thus, with the particular structure of the invention, a good spraying of the fuel is ensured in all flight conditions and in particular in the most severe special conditions of re-ignition in autorotation at low Mach, conditions under which the pressure drops of air supply are too weak to ensure sufficient fragmentation of the fuel and thus access to a large field of re-ignition.
Claims (4)
- An injection system for a turbomachine combustion chamber, the system comprising firstly a fuel injection nozzle (36) for vaporizing fuel in the combustion chamber (22) and secondly a mixer/deflector assembly (38) disposed coaxially with said injection nozzle and serving to mix fuel and oxidizer and to diffuse the mixture in said combustion chamber, said mixer/deflector assembly comprising a first spinner device or "primary swirler" (40) fixed securely to said injection nozzle and is spaced apart therefrom by a constant radial distance, and at least one second spinner device or "secondary swirler" (42) disposed coaxially at a determined distance from each other and separated by a Venturi device (44) disposed coaxially with said injection nozzle, the system being characterised in that said Venturi device has an inside surface (44A) presenting an upstream portion having a slope discontinuity P.
- An injection system according to claim 1, characterised in that said second spinner device is mounted to slide relative to said injection nozzle via a ring (47) secured to said second spinner device and capable of moving perpendicularly to an axis of symmetry S of said injection nozzle in an annular housing (49) of said Venturi device.
- An injection system according to claim 1, characterised in that said upstream portion of the inside surface of the Venturi device has a step that is concave.
- An injection system according to claim 1, characterised in that said upstream portion of the inside surface of the Venturi device has a step that is convex.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0109456 | 2001-07-16 | ||
| FR0109456A FR2827367B1 (en) | 2001-07-16 | 2001-07-16 | AEROMECHANICAL INJECTION SYSTEM WITH ANTI-RETURN PRIMARY LOCK |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1278012A2 EP1278012A2 (en) | 2003-01-22 |
| EP1278012A3 EP1278012A3 (en) | 2003-11-19 |
| EP1278012B1 true 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) |
Families Citing this family (30)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6691515B2 (en) * | 2002-03-12 | 2004-02-17 | Rolls-Royce Corporation | Dry low combustion system with means for eliminating combustion noise |
| JP4414769B2 (en) | 2002-04-26 | 2010-02-10 | ロールス−ロイス・コーポレーション | Fuel premixing module for gas turbine engine combustors. |
| 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 |
| FR2903173B1 (en) | 2006-06-29 | 2008-08-29 | Snecma Sa | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
| FR2903170B1 (en) * | 2006-06-29 | 2011-12-23 | Snecma | DEVICE FOR INJECTING A MIXTURE OF AIR AND FUEL, COMBUSTION CHAMBER AND TURBOMACHINE HAVING SUCH A DEVICE |
| 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 |
| GB2611115B (en) * | 2021-09-23 | 2024-10-09 | Gen Electric | Floating primary vane swirler |
| US12072099B2 (en) * | 2021-12-21 | 2024-08-27 | General Electric Company | Gas turbine fuel nozzle having a lip extending from the vanes of a swirler |
Family Cites Families (14)
| 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 |
| US3853273A (en) * | 1973-10-01 | 1974-12-10 | Gen Electric | Axial swirler central injection carburetor |
| US5117637A (en) * | 1990-08-02 | 1992-06-02 | General Electric Company | Combustor dome assembly |
| 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 | |
| US5966937A (en) * | 1997-10-09 | 1999-10-19 | United Technologies Corporation | Radial inlet swirler with twisted vanes for fuel injector |
| 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 DE DE60215589T patent/DE60215589T2/en not_active Expired - Lifetime
- 2002-07-12 ES ES02291767T patent/ES2272650T3/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
- 2002-07-15 US US10/194,230 patent/US6959551B2/en not_active Expired - Lifetime
- 2002-07-15 UA UA2002075852A patent/UA76709C2/en unknown
- 2002-07-16 CN CN02126114.8A patent/CN1230650C/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| CN1230650C (en) | 2005-12-07 |
| CA2393082C (en) | 2010-10-19 |
| CA2393082A1 (en) | 2003-01-16 |
| DE60215589D1 (en) | 2006-12-07 |
| FR2827367B1 (en) | 2003-10-17 |
| RU2295645C2 (en) | 2007-03-20 |
| JP4066241B2 (en) | 2008-03-26 |
| JP2003042452A (en) | 2003-02-13 |
| FR2827367A1 (en) | 2003-01-17 |
| RU2002118252A (en) | 2004-02-10 |
| US20030010034A1 (en) | 2003-01-16 |
| UA76709C2 (en) | 2006-09-15 |
| CN1407280A (en) | 2003-04-02 |
| DE60215589T2 (en) | 2007-08-30 |
| ES2272650T3 (en) | 2007-05-01 |
| EP1278012A2 (en) | 2003-01-22 |
| EP1278012A3 (en) | 2003-11-19 |
| US6959551B2 (en) | 2005-11-01 |
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