EP3320269B1 - Bent combustion chamber of a turbine engine - Google Patents

Bent combustion chamber of a turbine engine Download PDF

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Publication number
EP3320269B1
EP3320269B1 EP16748329.6A EP16748329A EP3320269B1 EP 3320269 B1 EP3320269 B1 EP 3320269B1 EP 16748329 A EP16748329 A EP 16748329A EP 3320269 B1 EP3320269 B1 EP 3320269B1
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EP
European Patent Office
Prior art keywords
flame tube
combustion chamber
injection system
axis
injector
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EP16748329.6A
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German (de)
French (fr)
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EP3320269A1 (en
Inventor
Guillaume Aurélien GODEL
Alain René CAYRE
Romain Nicolas Lunel
Haris MUSAEFENDIC
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
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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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/425—Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Definitions

  • the invention relates to the field of combustion chambers for turbomachines and more particularly the structure and the fixing of a flame tube in a combustion chamber of a turbomachine.
  • a turbomachine downstream of a high-pressure compressor (not shown), a turbomachine comprises a combustion chamber delimited by inner revolution casings 1b and external la which are concentric.
  • the combustion chamber comprises a flame tube 2 disposed in the space defined by the inner casings 1b and external 1a.
  • the flame tube 2 is delimited by internal walls 2b and external 2a called internal and external ferrules and a bottom plate of chamber 3 which serves as a support for injectors 4.
  • the combustion chamber also comprises a shroud 5 arranged in front of the chamber floor to partially cover the injectors 4 in order to protect them from possible shocks (that can occur when ingestion of a bird or an ice block in engines) and reduce aerodynamic energy losses to improve engine consumption.
  • the combustion chamber comprises an air diffuser 6 opening on the injector 4 which allows to cool the injectors 4.
  • the bottom plate 3, the inner walls 2b and outer 2a of the flame tube 2 and the fairing 5 are assembled by bolts (not shown).
  • the combustion chamber of the figure 1 is said to be annular axial direct in that it extends in the preferred direction of the motor axis without reversal cylindrical shells flame tube.
  • This architecture is the reference for modern turbomachines, especially on high power. In the field of small powers, it coexists with the return chamber architecture which is very compact axially. However, it has the main disadvantage a large area-to-volume ratio which makes it difficult to cool the walls of the flame tube and handicaps their lifetimes.
  • the invention proposes to overcome at least one of these disadvantages.
  • the invention proposes, according to a first aspect, a combustion chamber of a turbomachine according to claim 1.
  • the invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination.
  • the mouth comprises a straight portion extending tangentially to the circular portion and a diverging portion extending from the circular portion.
  • the circular portion has a constant radius around the injector axis.
  • the circular portion has a growing radius around the injector axis.
  • the mouth has a general shape: circular, rectangular, profiled.
  • the flame tube is connected to the outer casing via said injection system in connection with the chamber bottom.
  • the invention also relates to a turbomachine comprising a combustion chamber according to the invention.
  • the invention makes it possible to bring air from the diffuser more efficiently.
  • the invention makes it possible to lower the pressure drop between the diffuser and the inlet of the collector.
  • the outlet flow of the compressor partially feeds the injector (between 10% and 30% of the total flow compressor output).
  • the remaining percentage is both reintroduced along the flame tube via the various holes (primary holes, dilution holes and multi-perforation) and is also used to cool a set of parts of the turbine unit.
  • the diffuser compressor outlet
  • the invention solves this problem by placing between the diffuser outlet and the inlet of the injection system a manifold whose role is to capture a portion of the air flow and achieve aerodynamic continuity.
  • This device makes it possible to optimize the compressor / injection system connection, to channel the flow towards the injection system and to reduce the passage of orifices or the circumvention of parts by the flow.
  • the particular shape of the manifold allows to direct the flow of air before admission into the injection system to improve the supply of the injection system.
  • the injection system is composed of several tendrils whose role is to generate a rotating flow output of the injection system. These tendrils have a wedging angle (between 10 ° and 80 ° with respect to the injector axis).
  • the feed of the tendrils is not optimal in the case of a conventional injection system whose main axis is inclined relative to the mean direction of the flow at the outlet of the diffuser.
  • the flow can be made to make significant changes of direction to feed a spin which has a singular transition, detrimental to the performance of the combustion chamber module.
  • the invention that solves this problem is to use one of the two side walls of the manifold to guide the flow before admission into the injection system without applying to the flow other significant change of direction other than expected by its rotation.
  • This technical solution makes it possible to generate an overall rotation movement around the axis around which the tendrils are arranged, which is beneficial for feeding the tendrils.
  • the figures 2 and 3 illustrate views of a combustion chamber according to one embodiment.
  • the combustion chamber comprises an outer casing 10a to which is connected a flame tube 20.
  • the flame tube 20 comprises an inner annular wall 20b and an outer annular wall 20a.
  • the inner and outer annular walls define on the one hand a first radial portion 201 around a radial axis Y of the combustion chamber and which extends radially with respect to a longitudinal axis XX of rotation of the turbomachine.
  • the inner and outer annular walls define a second axial portion 202 about a longitudinal axis X perpendicular to the radial axis Y and parallel to the longitudinal axis XX of rotation of the turbomachine.
  • the first portion 201 extends to the second portion 202 forming a bend between the inlet and the outlet of the flame tube.
  • Such a bend allows an effective aerodynamic connection with a high pressure stage downstream of the gas flow (dashed arrow on the figure 2 ).
  • this bent shape makes it possible to reduce the axial size of the flame tube 20.
  • the combustion chamber also comprises a chamber bottom 30 which has the shape of a plate located at the inlet of the flame tube 20.
  • combustion chamber may optionally include a heat shield 50 in the form of a plate attached to the chamber bottom 30 located in the flame tube 20.
  • This heat shield 50 is located at the entrance of the flame tube 20 and protects the injection system 40 from high temperatures above 2200 K that can prevail in the flame tube 20.
  • Primary holes 202a, 202b are drilled in the inner and outer annular walls at the first portion 201 at the inlet of the flame tube.
  • dilution holes 203a, 203b are drilled in the inner and outer annular walls at the bent portion of the flame tube 20 (see FIG. figure 3 ).
  • the number of holes, their respective diameters and positions may vary depending on the intended application.
  • a diffuser 60 can bring air to the injection system 40 to cool it.
  • the injection system 40 comprises an injector body 40a surrounding an injection pipe 40b through which the fuel is introduced as such into the flame tube 20.
  • the injector body 40a is fixed to the outer casing 10a by means of bolts 70 and fixing plates 80 (see FIG. figure 3 ).
  • the inner and outer annular walls are fixed to the outer casing 10a via the injector body 40a thus making it possible to simplify the bowl-chamber connection and thus to avoid the use of a play-catching system.
  • a connecting disk 40c surmounted by a cylinder 40d in which is inserted the body 40a of the injector is connected to the chamber bottom 30 in which a recess 30a to the size of the connecting disk has been formed.
  • the body 40a of the injector is connected to the injection pipe 40b and the body 40a of the injection system 40 is inserted into the cylinder 40d surmounting the connecting disk 40c so that the injector body 40a ( and therefore the injection pipe 40b) is movable relative to the cylinder 40d. This allows a compensation of the movements to which the flame tube 20 is subjected. There is therefore no need for complex compensation systems.
  • the injector body 40a comprises an air inlet 40e through which air from the diffuser 60 is introduced. This air makes it possible to supply air to the injection system 40.
  • the air inlet 40e has, in a nonlimiting manner, the shape of an oval recess formed in the injector body 40a. It will therefore be understood that other forms can be envisaged.
  • the combustion chamber according to a second embodiment differs from the first embodiment by the structure of an injection system 40 'of a second type.
  • the flame tube 20 involved in this second embodiment is identical to that previously described.
  • the injection system 40 ' is attached to the chamber bottom 30, the flame tube 20 being connected to the outer casing 10a of the turbomachine via the injection system 40'.
  • the injection system 40 'in this second embodiment comprises an injector body 40'a surmounting a circular connecting structure 40'c comprising at least one connecting disc.
  • the connecting structure 40'c is inserted into the chamber bottom 30 in which a recess of the size of the circular connecting structure has been formed.
  • the collector 40'd is integral with the injector body 40'a.
  • the inner and outer annular walls are fixed to the outer casing 10a via the injector body 40'a thus making it possible to simplify the connection between the bowl and the chamber bottom and thus to avoid the use of a system of catching up games.
  • the injector body 40 ' surrounds an injection pipe 40' (along the injector axis AA ') through which the fuel is fed as such into the flame tube 20.
  • the injector axis AA' is coincides with the radial axis Y, so as to be parallel to the first radial portion 201 of the flame tube 20.
  • an air collector 40'd overcomes the injection pipe 40'b.
  • the tendrils are formed by vanes arranged around a parallel implantation axis with the injector axis AA '.
  • This collector is arranged near the diffuser 60 without being connected to the latter (in which case the vibrations could damage the structure). In addition, the collector is physically separated from the diffuser because of the expansion rates that are different.
  • the air collector 40'd may be in the axis AA 'of the injection system and comprises a circular portion 41 surrounding the injection pipe 40'b according to a constant radius.
  • This circular portion 41 has identical dimensions to the injector body 40'a. From this circular portion 41 extends a mouth 42 through which air from the diffuser 60 is introduced.
  • the mouth 42 has a straight portion 43 tangent to the circular portion 41 and a diverging portion 44 from the circular portion 41 (or converging from the air inlet).
  • the collector can of course take other forms.
  • the circular shape of this circular part 41 makes it possible to facilitate the rotation of the air flow around the axis of implantation of the tendrils which coincides with the injector axis AA 'on the exemplary embodiment illustrated in FIGS. Figures 6 and 7 .
  • the air collector 40'd can be offset relative to the axis AA 'of the injector. In these figures, it is deported to the left but can of course be deported to the right of the axis AA 'of the injector.
  • the collector comprises a circular portion 41 'having a radius increasing around the injection pipe (non-constant radius around the injection pipe).
  • the circular portion 41 ' first extends in a constant radius on a first portion, and a radius increasing beyond (volute type). And from this circular portion 41 'extends the mouth 42 having a straight portion 43 tangential to the circular portion and a diverging portion 44 from the circular portion.
  • the mouth 42 can take several forms: rectangular, circular or profiled.
  • the latter can prevent water entering the engine in the case of ingestion of water or hail from entering the collector and then injected into the flame tube, especially in the primary combustion zone.
  • the outer radius of the mouth 42 may be judiciously adapted to not capture the water (liquid or vapor) which is preferably on the outer radii of the centrifugal wheel and the axial diffuser.

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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)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Description

DOMAINE TECHNIQUE GENERALGENERAL TECHNICAL FIELD

L'invention concerne le domaine des chambres de combustion pour des turbomachines et plus particulièrement la structure et la fixation d'un tube à flamme dans une chambre de combustion d'une turbomachine.The invention relates to the field of combustion chambers for turbomachines and more particularly the structure and the fixing of a flame tube in a combustion chamber of a turbomachine.

ETAT DE LA TECHNIQUESTATE OF THE ART

De manière connue et en relation avec la figure 1 , en aval d'un compresseur à haute pression (non représenté), une turbomachine comprend une chambre de combustion délimitée par des carters de révolution interne 1b et externe la qui sont concentriques.In a known manner and in relation to the figure 1 , downstream of a high-pressure compressor (not shown), a turbomachine comprises a combustion chamber delimited by inner revolution casings 1b and external la which are concentric.

La chambre à combustion comprend un tube à flamme 2 disposé dans l'espace défini par les carters interne 1b et externe 1a.The combustion chamber comprises a flame tube 2 disposed in the space defined by the inner casings 1b and external 1a.

Le tube à flamme 2 est délimité par des parois interne 2b et externe 2a appelées viroles interne et externe et une plaque de fond de chambre 3 qui sert de support à des injecteurs 4.The flame tube 2 is delimited by internal walls 2b and external 2a called internal and external ferrules and a bottom plate of chamber 3 which serves as a support for injectors 4.

Par ailleurs, la chambre de combustion comprend également un carénage 5 disposé devant le fond de chambre pour couvrir partiellement les injecteurs 4 afin de les protéger des chocs éventuels (que peut produire l'ingestion d'un oiseau ou d'un bloc de glace dans des moteurs) et de réduire les pertes énergétiques aérodynamiques pour améliorer la consommation moteur. Et la chambre de combustion comprend un diffuseur 6 d'air débouchant sur l'injecteur 4 qui permet de refroidir les injecteurs 4.Furthermore, the combustion chamber also comprises a shroud 5 arranged in front of the chamber floor to partially cover the injectors 4 in order to protect them from possible shocks (that can occur when ingestion of a bird or an ice block in engines) and reduce aerodynamic energy losses to improve engine consumption. And the combustion chamber comprises an air diffuser 6 opening on the injector 4 which allows to cool the injectors 4.

La plaque de fond 3, les parois interne 2b et externe 2a du tube à flamme 2 et le carénage 5 sont assemblées par des boulons (non représentés).The bottom plate 3, the inner walls 2b and outer 2a of the flame tube 2 and the fairing 5 are assembled by bolts (not shown).

La chambre de combustion de la figure 1 est dite annulaire axiale directe en ce sens qu'elle s'étend selon la direction privilégiée de l'axe moteur sans retournement des viroles cylindriques du tube à flamme. Cette architecture est la référence pour les turbomachines modernes, notamment sur les fortes puissances. Sur le domaine des petites puissances, elle cohabite avec l'architecture de chambre à retour qui est très compacte axialement. Cependant elle possède pour principal inconvénient un important rapport surface sur volume qui rend difficile le refroidissement des parois du tube à flamme et handicape leurs durées de vie.The combustion chamber of the figure 1 is said to be annular axial direct in that it extends in the preferred direction of the motor axis without reversal cylindrical shells flame tube. This architecture is the reference for modern turbomachines, especially on high power. In the field of small powers, it coexists with the return chamber architecture which is very compact axially. However, it has the main disadvantage a large area-to-volume ratio which makes it difficult to cool the walls of the flame tube and handicaps their lifetimes.

A l'opposé, un problème avec le type de chambre axiale directe est que l'encombrement axial du tube à flamme est conséquent.In contrast, a problem with the direct axial chamber type is that the axial size of the flame tube is substantial.

Un autre problème est que les fixations du carénage, des parois interne 2b et externe 2a et de la plaque de fond sont soumises à des vibrations de la turbomachine ainsi qu'à des dilatations thermiques des sous-composants du module chambre qui peuvent dégrader son fonctionnement de sorte que des systèmes de compensations vibratoires et thermiques généralement complexes sont prévus.Another problem is that the fastenings of the fairing, the inner 2b and outer walls 2a and the bottom plate are subjected to vibrations of the turbomachine as well as thermal expansions of the sub-components of the chamber module which can degrade its operation. so that generally complex vibratory and thermal compensation systems are provided.

Le document US 4 081 957 décrit une chambre de combustion d'une turbomachine selon le préambule de la revendication 1.The document US 4,081,957 discloses a combustion chamber of a turbomachine according to the preamble of claim 1.

PRESENTATION DE L'INVENTIONPRESENTATION OF THE INVENTION

L'invention propose de pallier au moins un de ces inconvénients.The invention proposes to overcome at least one of these disadvantages.

A cet effet, l'invention propose, selon un premier aspect, une chambre de combustion d'une turbomachine selon la revendication 1.For this purpose, the invention proposes, according to a first aspect, a combustion chamber of a turbomachine according to claim 1.

L'invention est avantageusement complétée par les caractéristiques suivantes, prises seules ou en une quelconque de leur combinaison techniquement possible.The invention is advantageously completed by the following characteristics, taken alone or in any of their technically possible combination.

L'embouchure comprend une partie droite qui s'étend tangentiellement à la partie circulaire et une partie divergente s'étendant à partir de la partie circulaire.The mouth comprises a straight portion extending tangentially to the circular portion and a diverging portion extending from the circular portion.

La partie circulaire présente un rayon constant autour de l'axe injecteur.The circular portion has a constant radius around the injector axis.

La partie circulaire présente un rayon croissant autour de l'axe injecteur.The circular portion has a growing radius around the injector axis.

L'embouchure présente une forme générale : circulaire, rectangulaire, profilée.The mouth has a general shape: circular, rectangular, profiled.

Le tube à flamme est connecté au carter externe par l'intermédiaire dudit système d'injection en liaison avec le fond de chambre.The flame tube is connected to the outer casing via said injection system in connection with the chamber bottom.

L'invention concerne également une turbomachine comprenant une chambre de combustion selon l'invention.The invention also relates to a turbomachine comprising a combustion chamber according to the invention.

L'invention permet d'amener l'air issu du diffuseur de manière plus efficace. En d'autres termes, l'invention permet d'abaisser la perte de charge entre le diffuseur et l'entrée du collecteur.The invention makes it possible to bring air from the diffuser more efficiently. In other words, the invention makes it possible to lower the pressure drop between the diffuser and the inlet of the collector.

En effet, dans le cas d'une architecture conventionnelle et selon l'état de l'art actuel, l'écoulement en sortie de compresseur alimente partiellement l'injecteur (entre 10% et 30% du débit total sortie compresseur). Le pourcentage restant est à la fois réintroduit le long du tube à flamme via les différents perçages (trous primaires, trous de dilution et multi perforation) et est aussi utilisé pour refroidir un ensemble de pièces du module turbine. Le diffuseur (sortie compresseur) permet de ralentir l'écoulement qui est ensuite éclaté avant d'alimenter le système d'injection et les contournements interne/externe ceci dans le but de réduire les pertes de charge au contournement. Cette transition singulière entre la sortie compresseur et le système d'injection n'est pas optimale car elle est la source de perte énergétique : L'écoulement est d'abord ralenti à la sortie du compresseur, emprunte plusieurs passages (traversée du carénage et contournement du système d'injection) puis est ré-accéléré à l'entrée du système d'injection.Indeed, in the case of a conventional architecture and according to the current state of the art, the outlet flow of the compressor partially feeds the injector (between 10% and 30% of the total flow compressor output). The remaining percentage is both reintroduced along the flame tube via the various holes (primary holes, dilution holes and multi-perforation) and is also used to cool a set of parts of the turbine unit. The diffuser (compressor outlet) slows the flow which is then exploded before feeding the injection system and the internal / external bypasses this in order to reduce pressure losses around the bypass. This singular transition between the compressor output and the injection system is not optimal because it is the source of energy loss: The flow is first slowed at the compressor outlet, borrows several passages (through the fairing and bypassing injection system) and is re-accelerated at the inlet of the injection system.

Ainsi, l'invention résout cette problématique en disposant entre la sortie diffuseur et l'entrée du système d'injection un collecteur dont le rôle est de capter une partie de l'écoulement d'air et de réaliser une continuité aérodynamique. Ce dispositif permet d'optimiser la liaison sortie compresseur / système d'injection, de canaliser l'écoulement en direction du système d'injection et de réduire la traversée d'orifices ou le contournement de pièces par l'écoulement.Thus, the invention solves this problem by placing between the diffuser outlet and the inlet of the injection system a manifold whose role is to capture a portion of the air flow and achieve aerodynamic continuity. This device makes it possible to optimize the compressor / injection system connection, to channel the flow towards the injection system and to reduce the passage of orifices or the circumvention of parts by the flow.

En outre, la forme particulière du collecteur permet d'orienter l'écoulement d'air avant son admission dans le système d'injection afin d'améliorer l'alimentation du système d'injection.In addition, the particular shape of the manifold allows to direct the flow of air before admission into the injection system to improve the supply of the injection system.

En effet, dans le cas d'une architecture conventionnelle et selon l'état de l'art actuel, le système d'injection est composé de plusieurs vrilles dont le rôle est de générer un écoulement tournant en sortie de système d'injection. Ces vrilles présentent un angle de calage (entre 10° et 80° par rapport à l'axe injecteur).Indeed, in the case of a conventional architecture and according to the state of the art, the injection system is composed of several tendrils whose role is to generate a rotating flow output of the injection system. These tendrils have a wedging angle (between 10 ° and 80 ° with respect to the injector axis).

L'alimentation des vrilles n'est pas optimale dans le cas d'un système d'injection conventionnel dont l'axe principal est incliné par rapport à la direction moyenne de l'écoulement à la sortie du diffuseur. L'écoulement peut être amené à réaliser des changements de direction important pour alimenter une vrille ce qui présente une transition singulière, néfaste à la performance du module chambre de combustion.The feed of the tendrils is not optimal in the case of a conventional injection system whose main axis is inclined relative to the mean direction of the flow at the outlet of the diffuser. The flow can be made to make significant changes of direction to feed a spin which has a singular transition, detrimental to the performance of the combustion chamber module.

Ainsi, l'invention qui résout cette problématique consiste à utiliser une des deux parois latérales du collecteur pour orienter l'écoulement avant son admission dans le système d'injection sans appliquer à l'écoulement d'autre changement de direction important autre que celui attendu par sa mise en rotation. Cette solution technique permet de générer un mouvement d'ensemble de rotation autour de l'axe autour duquel sont disposées les vrilles, bénéfique à l'alimentation des vrilles.Thus, the invention that solves this problem is to use one of the two side walls of the manifold to guide the flow before admission into the injection system without applying to the flow other significant change of direction other than expected by its rotation. This technical solution makes it possible to generate an overall rotation movement around the axis around which the tendrils are arranged, which is beneficial for feeding the tendrils.

PRESENTATION DES FIGURESPRESENTATION OF FIGURES

D'autres caractéristiques, buts et avantages de l'invention ressortiront de la description qui suit, qui est purement illustrative et non limitative, et qui doit être lue en regard des dessins annexés sur lesquels outre la figure 1 déjà discutée,

  • La figure 2 illustre une vue en coupe d'un chambre de combustion ;
  • La figure 3 illustre une vue en perspective d'une chambre de combustion ;
  • La figure 4 illustre une vue détaillée de la liaison de la chambre de combustion selon un premier mode de réalisation ;
  • La figure 5 illustre une vue détaillée de la chambre de combustion selon un second mode de réalisation ;
  • Les figures 6 et 7 illustrent un collecteur d'un premier type de la chambre de combustion selon un second mode de réalisation ;
  • Les figures 8 et 9 illustrent un collecteur d'un second type de la chambre de combustion selon le second mode de réalisation.
Other characteristics, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended drawings in which, in addition to the figure 1 already discussed,
  • The figure 2 illustrates a sectional view of a combustion chamber;
  • The figure 3 illustrates a perspective view of a combustion chamber;
  • The figure 4 illustrates a detailed view of the connection of the combustion chamber according to a first embodiment;
  • The figure 5 illustrates a detailed view of the combustion chamber according to a second embodiment;
  • The Figures 6 and 7 illustrate a manifold of a first type of the combustion chamber according to a second embodiment;
  • The Figures 8 and 9 illustrate a collector of a second type of the combustion chamber according to the second embodiment.

Sur l'ensemble des figures les éléments similaires portent des références identiques.In the set of figures, similar elements bear identical references.

DESCRIPTION DETAILLEE DE L'INVENTIONDETAILED DESCRIPTION OF THE INVENTION

Les figures 2 et 3 illustrent des vues d'une chambre de combustion selon un mode de réalisation.The figures 2 and 3 illustrate views of a combustion chamber according to one embodiment.

La chambre de combustion comprend un carter externe 10a auquel est connecté un tube à flamme 20.The combustion chamber comprises an outer casing 10a to which is connected a flame tube 20.

Le tube à flamme 20 comprend une paroi annulaire interne 20b et une paroi annulaire externe 20a.The flame tube 20 comprises an inner annular wall 20b and an outer annular wall 20a.

Les parois annulaire interne et externe définissent d'une part une première portion 201 radiale autour d'un axe radial Y de la chambre de combustion et qui s'étend radialement par rapport à un axe longitudinal XX de rotation de la turbomachine.The inner and outer annular walls define on the one hand a first radial portion 201 around a radial axis Y of the combustion chamber and which extends radially with respect to a longitudinal axis XX of rotation of the turbomachine.

D'autre part, les parois annulaire interne et externe définissent une seconde portion 202 axiale autour d'un axe longitudinal X perpendiculaire à l'axe radial Y et parallèle à l'axe longitudinal XX de rotation de la turbomachine.On the other hand, the inner and outer annular walls define a second axial portion 202 about a longitudinal axis X perpendicular to the radial axis Y and parallel to the longitudinal axis XX of rotation of the turbomachine.

Comme on peut le voir sur les figures 2 et 3 la première portion 201 s'étend vers la seconde portion 202 en formant un coude entre l'entrée et la sortie du tube à flamme.As can be seen on the figures 2 and 3 the first portion 201 extends to the second portion 202 forming a bend between the inlet and the outlet of the flame tube.

Un tel coude permet une liaison aérodynamique efficace avec un étage haute pression en aval de l'écoulement des gaz (flèche en pointillés sur la figure 2).Such a bend allows an effective aerodynamic connection with a high pressure stage downstream of the gas flow (dashed arrow on the figure 2 ).

En outre, cette forme coudée permet de réduire l'encombrement axial du tube à flamme 20.In addition, this bent shape makes it possible to reduce the axial size of the flame tube 20.

Ceci présente les avantages suivants.

  • la masse du moteur est réduite :
    • ∘ la forme du tube à flamme permet de réduire la longueur du carter externe, qui est souvent commun avec la turbine haute pression en aval de la chambre de combustion;
    • ∘ la réduction de longueur pour les équipements - canalisations - nacelle et l'ensemble des constituants « hors-veine » ;
    • ∘ la structure de la chambre est simplifiée notamment par le fait que le tube à flamme est connecté au carter externe par l'intermédiaire de l'injecteur ce qui permet de supprimer le capotage et les boulons associés. Ces pièces sont généralement utilisées sur des chambres de type axial direct ;
  • la situation dynamique du rotor haute pression, située sous la chambre de combustion, est améliorée :
    ∘ cette pièce est en effet un élément complexe de la turbomachine et doit respecter de nombreux critères de dimensionnement. Pour des turbomachines de petite dimension et avec des impératifs de performances élevées (en consommation et émissions), on est tenté de positionner un régime de rotation élevé : la difficulté étant alors d'assurer une raideur et une dynamique d'arbre acceptable. Ainsi, la forme coudée donnée au tube à flamme permet de diminuer la longueur d'arbre haute pression (constitué d'un compresseur haute pression en amont de la chambre de combustion et de la turbine haute pression en aval de la chambre de combustion) ;
  • l'interface avec la turbine haute pression est améliorée :
    ∘ en effet, la sortie du tube à flamme est colinéaire au dessin des plateformes du DHP : cela permet de limiter le nombre de lignes de courant d'écoulement chaud qui impacteraient la paroi (notamment sur la virole interne) et pourraient potentiellement interférer avec le refroidissement de ces pièces dont la durée de vie est critique
  • la bougie d'allumage peut être positionnée à différentes positions : en fond de chambre et/ou en coin de chambre et/ou sur la paroi externe.
This has the following advantages.
  • the mass of the engine is reduced:
    • The shape of the flame tube makes it possible to reduce the length of the outer casing, which is often common with the high pressure turbine downstream of the combustion chamber;
    • ∘ length reduction for equipment - pipelines - nacelle and all "off-vein"components;
    • ∘ the structure of the chamber is simplified in particular by the fact that the flame tube is connected to the outer casing via the injector which allows to remove the cowling and associated bolts. These parts are generally used on direct axial type chambers;
  • the dynamic situation of the high-pressure rotor, located under the combustion chamber, is improved:
    ∘ this part is indeed a complex element of the turbomachine and must meet many design criteria. For turbomachines of small size and with high performance requirements (consumption and emissions), it is tempting to position a high rotation speed: the difficulty then being to ensure stiffness and acceptable shaft dynamics. Thus, the bent shape given to the flame tube makes it possible to reduce the high pressure shaft length (consisting of a high pressure compressor upstream of the combustion chamber and the high pressure turbine downstream of the combustion chamber);
  • the interface with the high pressure turbine is improved:
    ∘ indeed, the exit of the flame tube is collinear with the design of the platforms of the DHP: this makes it possible to limit the number of lines of flow of hot flow which would impact the wall (in particular on the inner shell) and could potentially interfere with the cooling of these parts whose life is critical
  • the spark plug can be positioned at different positions: at the bottom of the chamber and / or in the corner of the chamber and / or on the outer wall.

La chambre de combustion comprend également un fond de chambre 30 qui a la forme d'une plaque situé en entrée du tube à flamme 20.The combustion chamber also comprises a chamber bottom 30 which has the shape of a plate located at the inlet of the flame tube 20.

A ce fond de chambre 30 est attaché un système d'injection 40 d'un premier type par lequel est connecté le tube à flamme 20 au carter externe 10a de la turbomachine.At this bottom chamber 30 is attached an injection system 40 of a first type by which the flame tube 20 is connected to the outer casing 10a of the turbomachine.

En outre, la chambre de combustion peut éventuellement comprendre un bouclier thermique 50 sous la forme d'une plaque attachée au fond de chambre 30 situé dans le tube à flamme 20. Ce bouclier thermique 50 est situé à l'entrée du tube à flamme 20 et protège le système d'injection 40 des fortes températures supérieures à 2200 K pouvant régner dans le tube à flamme 20.In addition, the combustion chamber may optionally include a heat shield 50 in the form of a plate attached to the chamber bottom 30 located in the flame tube 20. This heat shield 50 is located at the entrance of the flame tube 20 and protects the injection system 40 from high temperatures above 2200 K that can prevail in the flame tube 20.

Des trous primaires 202a, 202b sont percés dans les parois annulaires interne et externe au niveau de la première portion 201 en entrée du tube à flamme.Primary holes 202a, 202b are drilled in the inner and outer annular walls at the first portion 201 at the inlet of the flame tube.

En outre, des trous de dilution 203a, 203b sont percés dans les parois annulaires interne et externe au niveau de la partie coudée du tube à flamme 20 (voir la figure 3). Le nombre de trous, leurs diamètres et positions respectifs pouvant varier selon l'application visée.In addition, dilution holes 203a, 203b are drilled in the inner and outer annular walls at the bent portion of the flame tube 20 (see FIG. figure 3 ). The number of holes, their respective diameters and positions may vary depending on the intended application.

De plus, un diffuseur 60 permet d'amener de l'air vers le système d'injection 40 afin de le refroidir.In addition, a diffuser 60 can bring air to the injection system 40 to cool it.

Comme cela est visible sur la figure 4 , le système d'injection 40 selon un premier mode de réalisation comprend un corps 40a d'injecteur entourant un tuyau 40b d'injection par lequel est amené le combustible en tant que tel dans le tube à flamme 20. Le corps 40a d'injecteur est fixé au carter externe 10a par l'intermédiaire de boulons 70 et de plaques 80 de fixation (voir la figure 3 ).As is visible on the figure 4 , the injection system 40 according to a first embodiment comprises an injector body 40a surrounding an injection pipe 40b through which the fuel is introduced as such into the flame tube 20. The injector body 40a is fixed to the outer casing 10a by means of bolts 70 and fixing plates 80 (see FIG. figure 3 ).

Les parois annulaires interne et externe sont fixées au carter externe 10a par l'intermédiaire du corps 40a d'injecteur permettant ainsi de simplifier la liaison bol - fond de chambre et ainsi éviter l'utilisation d'un système de rattrapage des jeux.The inner and outer annular walls are fixed to the outer casing 10a via the injector body 40a thus making it possible to simplify the bowl-chamber connection and thus to avoid the use of a play-catching system.

Un disque de liaison 40c surmonté d'un cylindre 40d dans lequel est inséré le corps 40a de l'injecteur est connecté au fond de chambre 30 dans lequel un évidement 30a à la taille du disque de liaison a été ménagé.A connecting disk 40c surmounted by a cylinder 40d in which is inserted the body 40a of the injector is connected to the chamber bottom 30 in which a recess 30a to the size of the connecting disk has been formed.

Le corps 40a de l'injecteur est en liaison avec le tuyau 40b d'injection et le corps 40a du système d'injection 40 est inséré dans le cylindre 40d surmontant le disque de liaison 40c de telle sorte que le corps 40a d'injecteur (et donc le tuyau 40b d'injection) est mobile par rapport au cylindre 40d. Ceci permet une compensation des mouvements auxquels est soumis le tube à flamme 20. Il n'y a donc pas besoin de systèmes de compensation complexes.The body 40a of the injector is connected to the injection pipe 40b and the body 40a of the injection system 40 is inserted into the cylinder 40d surmounting the connecting disk 40c so that the injector body 40a ( and therefore the injection pipe 40b) is movable relative to the cylinder 40d. This allows a compensation of the movements to which the flame tube 20 is subjected. There is therefore no need for complex compensation systems.

Le corps 40a d'injecteur comprend une entrée d'air 40e par laquelle de l'air issu du diffuseur 60 est introduit. Cet air permet d'alimenter en air le système d'injection 40. L'entrée d'air 40e a, de manière non limitative, la forme d'un évidement ovale pratiqué dans le corps 40a d'injecteur. On comprendra donc que d'autres formes peuvent être envisagées.The injector body 40a comprises an air inlet 40e through which air from the diffuser 60 is introduced. This air makes it possible to supply air to the injection system 40. The air inlet 40e has, in a nonlimiting manner, the shape of an oval recess formed in the injector body 40a. It will therefore be understood that other forms can be envisaged.

De manière alternative, comme cela est visible sur la figure 5 , la chambre de combustion selon un second mode de réalisation diffère du premier mode de réalisation par la structure d'un système d'injection 40' d'un second type.Alternatively, as is visible on the figure 5 , the combustion chamber according to a second embodiment differs from the first embodiment by the structure of an injection system 40 'of a second type.

Le tube à flamme 20 impliqué dans ce second mode de réalisation est identique à celui précédemment décrit. De plus, le système d'injection 40' est attaché au fond de chambre 30, le tube à flamme 20 étant connecté au carter externe 10a de la turbomachine par l'intermédiaire du système d'injection 40'.The flame tube 20 involved in this second embodiment is identical to that previously described. In addition, the injection system 40 'is attached to the chamber bottom 30, the flame tube 20 being connected to the outer casing 10a of the turbomachine via the injection system 40'.

Le système d'injection 40' dans ce second mode de réalisation comprend un corps d'injecteur 40'a surmontant une structure circulaire de liaison 40'c comprenant au moins un disque de liaison. La structure de liaison 40'c est insérée dans le fond de chambre 30 dans laquelle un évidement de la taille de la structure circulaire de liaison a été ménagé. Le collecteur 40'd est solidaire du corps d'injecteur 40'a.The injection system 40 'in this second embodiment comprises an injector body 40'a surmounting a circular connecting structure 40'c comprising at least one connecting disc. The connecting structure 40'c is inserted into the chamber bottom 30 in which a recess of the size of the circular connecting structure has been formed. The collector 40'd is integral with the injector body 40'a.

Comme dans le premier mode de réalisation, les parois annulaires interne et externe sont fixées au carter externe 10a par l'intermédiaire du corps 40'a d'injecteur permettant ainsi de simplifier la liaison bol - fond de chambre et ainsi éviter l'utilisation d'un système de rattrapage des jeux.As in the first embodiment, the inner and outer annular walls are fixed to the outer casing 10a via the injector body 40'a thus making it possible to simplify the connection between the bowl and the chamber bottom and thus to avoid the use of a system of catching up games.

Le corps d'injecteur 40'a entoure un tuyau 40'b d'injection (selon l'axe injecteur AA') par lequel est amené le combustible en tant que tel dans le tube à flamme 20. L'axe injecteur AA' est confondu avec l'axe radial Y, de sorte à être parallèle à la première portion 201 radiale du tube à flamme 20.The injector body 40 'surrounds an injection pipe 40' (along the injector axis AA ') through which the fuel is fed as such into the flame tube 20. The injector axis AA' is coincides with the radial axis Y, so as to be parallel to the first radial portion 201 of the flame tube 20.

Afin d'améliorer l'efficacité de l'alimentation en air du système d'injection par l'intermédiaire de vrilles rapportées au tuyau 40'b, un collecteur d'air 40'd surmonte le tuyau d'injection 40'b. Les vrilles sont formées par des aubages disposés autour d'un axe d'implantation parallèle avec l'axe injecteur AA'. L'axe d'implantation autour duquel les vrilles sont situées et l'axe injecteur AA' peuvent être confondus.In order to improve the efficiency of the air supply of the injection system via twists connected to the pipe 40'b, an air collector 40'd overcomes the injection pipe 40'b. The tendrils are formed by vanes arranged around a parallel implantation axis with the injector axis AA '. The axis of implantation around which the tendrils are located and the injector axis AA 'can be confused.

Ce collecteur est agencé à proximité du diffuseur 60 sans être connecté à ce dernier (auquel cas les vibrations pourraient endommager la structure). En outre, le collecteur est séparé physiquement du diffuseur à cause des vitesses de dilatation qui sont différentes.This collector is arranged near the diffuser 60 without being connected to the latter (in which case the vibrations could damage the structure). In addition, the collector is physically separated from the diffuser because of the expansion rates that are different.

Comme illustré sur les figures 6 et 7 , le collecteur d'air 40'd peut être dans l'axe AA' du système d'injection et comprend une partie circulaire 41 entourant le tuyau 40'b d'injection selon un rayon constant.As illustrated on Figures 6 and 7 , the air collector 40'd may be in the axis AA 'of the injection system and comprises a circular portion 41 surrounding the injection pipe 40'b according to a constant radius.

Cette partie circulaire 41 présente des dimensions identiques au corps d'injecteur 40'a. A partir de cette partie circulaire 41 s'étend une embouchure 42 par laquelle de l'air issu du diffuser 60 est introduit. L'embouchure 42 présente une partie droite 43 tangente à la partie circulaire 41 et une partie divergente 44 à partir de la partie circulaire 41 (ou bien convergente depuis l'entrée d'air). Le collecteur peut bien entendu prendre d'autres formes. La forme circulaire de cette partie circulaire 41 permet de faciliter la rotation de l'écoulement d'air autour de l'axe d'implantation des vrilles qui est confondu avec l'axe injecteur AA' sur l'exemple de réalisation illustré sur les figures 6 et 7 .This circular portion 41 has identical dimensions to the injector body 40'a. From this circular portion 41 extends a mouth 42 through which air from the diffuser 60 is introduced. The mouth 42 has a straight portion 43 tangent to the circular portion 41 and a diverging portion 44 from the circular portion 41 (or converging from the air inlet). The collector can of course take other forms. The circular shape of this circular part 41 makes it possible to facilitate the rotation of the air flow around the axis of implantation of the tendrils which coincides with the injector axis AA 'on the exemplary embodiment illustrated in FIGS. Figures 6 and 7 .

Alternativement, comme illustré sur les figures 8 et 9 , le collecteur d'air 40'd peut être déporté par rapport à l'axe AA' de l'injecteur. Sur ces figures, il est déporté vers la gauche mais peut bien entendu être déporté vers la droite de l'axe AA' de l'injecteur.Alternatively, as illustrated on the Figures 8 and 9 , the air collector 40'd can be offset relative to the axis AA 'of the injector. In these figures, it is deported to the left but can of course be deported to the right of the axis AA 'of the injector.

A ce titre, le collecteur comprend une partie circulaire 41' présentant un rayon croissant autour du tuyau d'injection (rayon non constant autour du tuyau d'injection). De manière avantageuse, la partie circulaire 41' s'étend d'abord selon un rayon constant sur une première portion, et un rayon croissant au-delà (forme de type volute). Et à partir de cette partie circulaire 41', s'étend l'embouchure 42 présentant une partie droite 43 tangent à la partie circulaire et une partie divergente 44 à partir de la partie circulaire.As such, the collector comprises a circular portion 41 'having a radius increasing around the injection pipe (non-constant radius around the injection pipe). Advantageously, the circular portion 41 'first extends in a constant radius on a first portion, and a radius increasing beyond (volute type). And from this circular portion 41 'extends the mouth 42 having a straight portion 43 tangential to the circular portion and a diverging portion 44 from the circular portion.

L'embouchure 42 peut prendre plusieurs formes : rectangulaire, circulaire ou bien profilée.The mouth 42 can take several forms: rectangular, circular or profiled.

En conséquence, de l'air issu du diffuseur entre dans le système d'injection par l'intermédiaire de l'embouchure 42, qui grâce à sa forme permet d'imposer un mouvement d'ensemble de rotation à l'écoulement d'air afin de faciliter l'alimentation des vrilles 40'e.As a result, air from the diffuser enters the injection system via the mouthpiece 42, which by its shape makes it possible to impose a rotational assembly movement to the air flow. to facilitate the feeding of 40'e tendrils.

En outre, selon la forme et les dimensions données à l'embouchure 42, cette dernière peut éviter que de l'eau entrant dans le moteur dans les cas d'ingestion d'eau ou de grêle n'entre dans le collecteur et soit alors injectée dans le tube à flamme, notamment dans la zone primaire de combustion. A ce titre, le rayon externe de l'embouchure 42 peut être judicieusement adapté afin de ne pas capter l'eau (liquide ou vapeur) qui se situe de manière préférentielle sur les rayons extérieurs du rouet centrifuge et du diffuseur axial.In addition, depending on the shape and dimensions given to the mouth 42, the latter can prevent water entering the engine in the case of ingestion of water or hail from entering the collector and then injected into the flame tube, especially in the primary combustion zone. As such, the outer radius of the mouth 42 may be judiciously adapted to not capture the water (liquid or vapor) which is preferably on the outer radii of the centrifugal wheel and the axial diffuser.

Claims (7)

  1. A combustion chamber of a turbomachine, comprising:
    - an annular external casing (10a);
    - a flame tube (20) connected to the external casing (10a), said flame tube (20) comprising an annular internal wall (20b) and an annular external wall (20a) defining on the one hand a first radial portion (201) at the inlet of the flame tube and on the other hand a second axial portion (202) at the outlet of the flame tube, the first portion (201) of the flame tube (20) extending toward the second portion (202) while forming a bend between the inlet and the outlet of the flame tube (20), the flame tube further comprising a chamber bottom (30) located at the inlet of the flame tube (20);
    - a fuel injection system (40') configured to inject fuel into the flame tube via the inlet of the flame tube, the injection system comprising an injector axis (AA') and having a main direction coaxial with a longitudinal axis Y along which the first portion (201) extends, said injection system (40') comprising an air manifold, comprising a circular portion (41) around the injector axis, the circular portion from which extends an orifice (42) forming an air inlet of the manifold, the orifice (42) being configured to rotate the entering flow of air around the implantation axis so that it feeds spirals, the combustion chamber being characterized in that the injector axis (AA') of the injection system is parallel to the first portion (201), in that the injection system (40') includes spirals (40'e) disposed around an implantation axis which is parallel to the injector axis (AA'), and in that the air manifold (40'd) is further configured to bring air to said spirals (40'e) of said injection system (40').
  2. The combustion chamber according to claim 1, wherein the orifice (42) comprises a straight portion (43) which extends tangentially to the circular portion (41) and a divergent portion (44) extending from the circular portion (41).
  3. The combustion chamber according to one of claims 1 to 2, wherein the circular portion (41) has a constant radius around the injector axis (AA').
  4. The combustion chamber according to one of claims 1 to 2, wherein the circular portion (41) has a radius that increases around the injector axis (AA').
  5. The combustion chamber according to one of claims 1 to 4, wherein the orifice (42) has a circular, rectangular or profiled shape.
  6. The combustion chamber according to one of claims 1 to 5, wherein the flame tube is connected to an external casing (10a) by means of said injection system (40) in connection with the chamber bottom (30).
  7. Turbomachine comprising a combustion chamber according to one of the preceding claims.
EP16748329.6A 2015-07-08 2016-07-07 Bent combustion chamber of a turbine engine Active EP3320269B1 (en)

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FR1556482A FR3038699B1 (en) 2015-07-08 2015-07-08 BENT COMBUSTION CHAMBER OF A TURBOMACHINE
PCT/FR2016/051735 WO2017006063A1 (en) 2015-07-08 2016-07-07 Bent combustion chamber from a turbine engine

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FR3090747B1 (en) * 2018-12-21 2021-01-22 Turbotech Combustion chamber of a turbomachine
US20220252268A1 (en) * 2019-06-07 2022-08-11 Safran Helicopter Engines Method for manufacturing a flame tube for a turbomachine

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE535905A (en) * 1954-02-23
US3605405A (en) * 1970-04-09 1971-09-20 Gen Electric Carbon elimination and cooling improvement to scroll type combustors
US3648457A (en) * 1970-04-30 1972-03-14 Gen Electric Combustion apparatus
JPS548890B1 (en) * 1971-04-01 1979-04-19
US4081957A (en) * 1976-05-03 1978-04-04 United Technologies Corporation Premixed combustor
US4458481A (en) * 1982-03-15 1984-07-10 Brown Boveri Turbomachinery, Inc. Combustor for regenerative open cycle gas turbine system
FR2827367B1 (en) * 2001-07-16 2003-10-17 Snecma Moteurs AEROMECHANICAL INJECTION SYSTEM WITH ANTI-RETURN PRIMARY LOCK
US6834505B2 (en) * 2002-10-07 2004-12-28 General Electric Company Hybrid swirler
US7310952B2 (en) * 2003-10-17 2007-12-25 General Electric Company Methods and apparatus for attaching swirlers to gas turbine engine combustors
US7437876B2 (en) * 2005-03-25 2008-10-21 General Electric Company Augmenter swirler pilot
FR2886714B1 (en) * 2005-06-07 2007-09-07 Snecma Moteurs Sa ANTI-ROTARY INJECTION SYSTEM FOR TURBO-REACTOR
EP1924762B1 (en) * 2005-09-13 2013-01-02 Rolls-Royce Corporation, Ltd. Gas turbine engine combustion systems
US7716931B2 (en) * 2006-03-01 2010-05-18 General Electric Company Method and apparatus for assembling gas turbine engine
EP1994260B1 (en) * 2006-03-15 2017-09-20 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with a positioning system
CN201991616U (en) * 2011-01-25 2011-09-28 苏艾今 Scramjet double-working substance steam turbine
EP2710298B1 (en) * 2011-05-17 2020-09-23 Safran Aircraft Engines Annular combustion chamber for a turbine engine
FR3035707B1 (en) 2015-04-29 2019-11-01 Safran Aircraft Engines COMBUSTION CHAMBER WITH TURBOMACHINE

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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US20180209649A1 (en) 2018-07-26
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FR3038699B1 (en) 2022-06-24
CN107735619A (en) 2018-02-23
US11125435B2 (en) 2021-09-21
CN107735619B (en) 2019-07-05
EP3320269A1 (en) 2018-05-16
FR3038699A1 (en) 2017-01-13

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