EP2409085B1 - Turbine engine combustion chamber comprising improved primary air supply means - Google Patents

Turbine engine combustion chamber comprising improved primary air supply means Download PDF

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Publication number
EP2409085B1
EP2409085B1 EP10708769.4A EP10708769A EP2409085B1 EP 2409085 B1 EP2409085 B1 EP 2409085B1 EP 10708769 A EP10708769 A EP 10708769A EP 2409085 B1 EP2409085 B1 EP 2409085B1
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EP
European Patent Office
Prior art keywords
combustion chamber
air
annular
injection system
upstream
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EP10708769.4A
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German (de)
French (fr)
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EP2409085A1 (en
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Sébastien Alain Christophe BOURGOIS
Romain Nicolas Lunel
Thomas Olivier Marie Noel
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04Air inlet arrangements
    • F23R3/10Air inlet arrangements for primary air

Definitions

  • the present invention relates to an annular combustion chamber of a turbomachine, such as for example an airplane turbojet or turboprop.
  • Turbomachines generally comprise an annular combustion chamber mounted downstream of a compressor.
  • the combustion chamber is delimited upstream by an annular bottom equipped with injection systems regularly distributed around the axis of the turbomachine and for injecting a mixture of air and fuel into the combustion chamber.
  • the output of the compressor opens into an enclosure in which is housed the combustion chamber.
  • the compressor may be of axial type and have an output substantially aligned with the injection systems of the combustion chamber, or be of the centrifugal type, and comprise at the output an annular rectifier opening in a radially outer region of the enclosure of the combustion chamber.
  • Injection systems of the combustion chamber have peripheral bores through which air from the compressor can enter, and means for centering and guiding fuel injector heads.
  • the injection systems are designed to optimize the performance of the combustion chamber and thus reduce fuel consumption and pollutant emissions at the outlet of this combustion chamber.
  • the performance of the injection systems is, in general, even higher than the pressure drop is important inside these injection systems, and that the air supply of these systems is uniform. around their respective axes. To limit the overall pressure drop experienced by the air flow supplying the combustion chamber while allowing a high pressure drop inside the injection systems, it is therefore desirable to reduce the pressure drop as much as possible. upstream of these injection systems.
  • the document EP0153842 A1 shows a turbomachine combustion chamber having combustion air collectors associated with each injection system in an annular fairing.
  • the collectors have a shape of the circular holes formed in and by the fairing.
  • Said fairing intended to cover the annular chamber bottom of a turbomachine combustion chamber is described in the document FR2910597 .
  • Said fairing comprises openings to allow the passage of fuel injectors supported by the chamber bottom. Said openings extend to the free end of an outer fixing edge, so that the outer fixing edge is split between some of its attachment points.
  • the invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the aforementioned drawbacks.
  • it aims to reduce the pressure drop of the air flow coming from a compressor in a turbomachine, between the output of this compressor and the inlet of injection systems of a combustion chamber of the turbomachine , in particular to allow an increase in the pressure drop inside these injection systems without considerably increasing the overall pressure drop of the air flow supplying the combustion chamber.
  • the invention also aims to improve the uniformity of the air supply combustion chamber injection systems.
  • the invention proposes an annular combustion chamber intended to equip a turbomachine, comprising a chamber bottom arranged at the upstream end of the combustion chamber, as well as a plurality of air injection and air injection systems. fuel distributed circumferentially around an axis of the combustion chamber and mounted on the chamber bottom.
  • the annular combustion chamber further comprises, associated with each injection system, an air manifold comprising two walls mounted on the chamber bottom and projecting upstream to form an obstacle to a circumferential flow of air around the chamber. the axis of the combustion chamber, and an air inlet opening formed at the upstream end of the aforementioned air collector.
  • the air intake opening of each air collector is open radially outwards with respect to an axis of the corresponding injection system.
  • the air collectors according to the invention can optimally channel a flow of air from a radially outer region relative to the respective axes of the injection systems and feeding these injection systems, around each of these systems.
  • Air collectors thus make it possible to reduce the pressure drop experienced by this flow of air upstream of these injection systems, and to make the air supply of these systems more uniform.
  • the portion of said opening which is located radially outwardly with respect to the aforesaid tangential plane has an opening area greater than that of the part of said opening which is located radially inward with respect to this tangential plane.
  • This configuration further optimizes the intake of air from a radially outer region relative to the respective axes of the injection systems of the combustion chamber.
  • Each air manifold comprises two walls which are mounted on the chamber bottom, project upstream, and are arranged on either side of the corresponding injection system, these walls forming an obstacle to a circumferential flow of air around the axis of the combustion chamber.
  • each air collector has a concavity turned towards said air collector and are connected to one another by two opposite ends of each of these walls, so that each air manifold has a generally tubular shape and has an upstream end forming said air inlet opening.
  • each air manifold is shaped so that a radially inner portion of the upstream end is offset upstream relative to a radially outer portion of said upstream end of the air collector.
  • the combustion chamber comprises an annular fairing of chamber bottom arranged upstream of the chamber bottom and to which the walls of each air manifold are connected substantially sealingly on either side of an orifice corresponding formed in the shroud and forming said air intake opening of the air collector.
  • the aforementioned walls allow to delimit compartments forming air collectors between the chamber bottom and the fairing, around each injection system.
  • each air collector extends radially and each of these walls is part of two consecutive air collectors around the axis of the combustion chamber.
  • This configuration has the particular advantage of minimizing the total number of air collector walls.
  • each air manifold preferably has a flared shape radially outwardly.
  • the annular fairing may comprise a radially inner annular portion and a radially outer annular portion between which said air intake openings are formed, the radially inner annular portion being offset upstream relative to at the radially outer annular portion.
  • the shape of the fairing makes it possible to orient the air intake opening radially outwards.
  • each injection system comprising an injector head centering and guiding sleeve
  • each air collector preferably comprises at least one part extending upstream beyond an upstream end of said bushing of the corresponding injection system.
  • the air collectors and have optimal abilities to channel air admitted into the injection systems that equip the combustion chamber.
  • the invention also relates to a turbomachine comprising a combustion chamber of the type described above.
  • the Figures 1 to 2 represent a combustion chamber 10 of a turbomachine according to a demonstrative example as well as the immediate environment of this combustion chamber.
  • the combustion chamber 10 is housed in an enclosure 12 which is arranged downstream of a compressor of the turbomachine, of the centrifugal type, the output of which is connected to a radial diffuser 14, itself connected at the output to a flow rectifier 16 which opens into a radially outer region of the enclosure 12.
  • the combustion chamber 10 is delimited by two substantially cylindrical coaxial walls 18 and 20, respectively internal and external, and by an annular chamber bottom 22 which extends substantially radially at the upstream end of the chamber 10 and which is connected by its radial ends to both walls 18 and 20.
  • the inner 18 and outer 20 walls of the combustion chamber 10 are attached downstream by two inner and outer ferrules 24 and 26 respectively on a substantially cylindrical inner wall 28 connected to the diffuser 14, and on an outer casing 30, so as to delimit the enclosure 12.
  • Injection systems 32 which are regularly distributed around the axis 34 of the combustion chamber, are mounted in the chamber bottom 22.
  • Each injection system 32 comprises in particular a centering and guiding bushing 36.
  • a head 38 of a fuel injector 40, and air inlet ports 42 arranged around an axis 44 of the injection system.
  • each injection system 32 aligns the corresponding injector head 38 on the axis 44 of the injection system.
  • the injection systems 32 are configured to allow a certain radial and axial displacement of the injector heads 38, to take account of any differential expansions likely to cause relative displacements between the injectors 40 and the combustion chamber 10.
  • the air flow 46 which arrives in a radially outer region of the enclosure 12, separates into three parts in this chamber 12.
  • a first portion 48 of the air flow flows downstream along the outer wall 20 of the combustion chamber 10, and partially enters the combustion chamber 10 through orifices 50 formed in its outer wall 20.
  • a second portion 52 of the air flow flows downstream along the internal wall 18 of the combustion chamber 10, and partially enters the combustion chamber 10 through orifices 54 formed in its inner wall 18.
  • a third portion 56 of the air flow feeds the injection systems 32 of the combustion chamber 10.
  • the combustion chamber 10 is equipped with a plurality of air collectors 58 (one of which is visible on the Figures 1 to 2 ).
  • Each air manifold 58 comprises two similar walls 60 and 62 ( figure 1 ) which are curved around the injection system 32 corresponding by having a concavity facing the injection system 32, and which are mounted on the chamber bottom 22 at their respective downstream ends.
  • each air collector 58 each comprise two opposite end edges, respectively 60a, 60b and 62a, 62b, through which these two walls 60 and 62 are connected to each other. the other, so that each air manifold 58 has a generally tubular shape.
  • the air manifolds 58 each have an upstream end edge defining an air inlet opening 64, through which air 56 from the rectifier 16 can penetrate to reach the air inlet ports 42 of the injection systems 32.
  • each air collector 58 The two walls 60, 62 of each air collector 58 are truncated upstream along a plane inclined relative to the axis 44 of the corresponding injection system so that the air intake opening 64 of each collector air 58 is open towards the outlet of the rectifier 16, that is to say open radially outwardly relative to the axis 44 of the aforementioned injection system, to facilitate the entry of air from this rectifier 16 in the air collectors 58.
  • each air manifold 58 thus has a radially inner portion 66 which is offset upstream with respect to a radially outer portion 68 of the upstream edge.
  • each air manifold 58 extends upstream beyond the upstream end of the bushing 36 for centering and guiding the corresponding injector head 38.
  • This radially inner portion 66 thus forms a scoop which is particularly effective for guiding the flow of air 56 coming from the rectifier 16.
  • the inclination of the air intake opening 64 of each air manifold 58 with respect to the axis 44 of the corresponding injection system is notably defined so as not to hinder axial and radial displacements of the injector head 38 corresponding in operation and also during assembly and disassembly of the injector 40.
  • the air intake opening 64 forms with the axis 44 an angle ⁇ ( figure 2 ) which is typically between about 40 degrees and 80 degrees.
  • each air manifold 58 is fixed at their downstream end to an annular piece 70, sometimes called a cup stopper, which is integral with the chamber bottom 22, and which comprises an annular flange 72 extending radially about the axis 44 of the corresponding injection system 32, and an annular flange 74 which extends parallel to the 44 axis from the inner periphery of the annular flange 72 of the stop cup 70.
  • annular piece 70 sometimes called a cup stopper
  • Fixing the walls 60 and 62 on the stop cup 70 is for example made by welding and so that the walls 60 and 62 extend in the extension of the annular rim 74 of the stop cup 70.
  • the stop cup 70 makes it possible to axially block the injection system 32 by cooperation of the annular flange 72 of the stop cup with an annular flange 76 secured to the injection system 32 and mounted sliding radially in an annular groove formed between the chamber bottom 22 and the flange 72 of the stop cup 70.
  • the air collectors 58 make it possible to channel the air coming from the straightener 16 around each injection system 32, which makes it possible to reduce the pressure losses upstream of these injection systems improve the uniformity of the air supply of these injection systems.
  • the air collectors 58 have a remarkable property in that they each form an obstacle to the flow of air circumferentially between two neighboring injection systems, along the chamber bottom 22.
  • the figure 3 represents an embodiment of the invention in which the bottom 22 of the combustion chamber 10 is equipped with an annular protective fairing 78 arranged upstream of the chamber bottom 22.
  • the shroud 78 has a radially inner continuous annular portion 80 which has an edge 82 fastened together on an inner rim 84 of the chamber bottom 22 and on an upstream edge 86 of the inner wall 18 of the combustion chamber 10.
  • the fairing 78 further comprises air intake openings 88 which are arranged opposite each injection system 32 and which extend outwards as far as the radially outer end of the fairing 78 so that the latter has a radially outer edge 90 split at each of these openings 88.
  • This outer edge 90 of the shroud is fixed jointly on an outer rim 92 of the chamber bottom 22 and on an upstream edge 94 of the outer wall 20 of the combustion chamber 10.
  • the air intake openings 88 are thus open radially outwardly relative to the axis 44 of each injection system 32, which facilitates the flow of the air stream 56 from the rectifier 16 and feeding injection systems 32.
  • each air inlet opening 88 may have a shape centered on an axis 95 contained in a plane passing through the axis 44 of the corresponding injection system and by the axis 34 of the combustion chamber, and which is offset radially outwardly with respect to said axis 44 of the injection system or inclined with respect to this axis 44.
  • figure 4 illustrates an opening 88 of this type seen in projection in the aforementioned transverse plane P1.
  • each air intake opening 88 extends between a radially outer portion 102 of the fairing and the radially inner annular portion 80 of said fairing 78, which radially inner portion 80 is shifted towards the outside. upstream relative to the radially outer portion 102 above.
  • the bottom 22 of the combustion chamber 10 is equipped with pairs of collector walls 96 and 98 arranged on either side of each injection system 32 and on the other side. corresponding aperture 88, as shown in FIG. figure 3 .
  • These collector walls 96, 98 are flat and project upstream from the chamber bottom 22 extending in respective substantially radial planes with respect to the axis 34 of the combustion chamber.
  • Only one wall 96, 98 of the air collector 100 is provided between two adjacent injection systems 32, so that each wall 96, 98 of the air collector 100 participates in the formation of two collectors. 100 neighbors.

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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)

Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention concerne une chambre annulaire de combustion d'une turbomachine, telle par exemple qu'un turboréacteur ou un turbopropulseur d'avion.The present invention relates to an annular combustion chamber of a turbomachine, such as for example an airplane turbojet or turboprop.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

Les turbomachines comprennent en général une chambre annulaire de combustion montée en aval d'un compresseur.Turbomachines generally comprise an annular combustion chamber mounted downstream of a compressor.

La chambre de combustion est délimitée en amont par un fond annulaire équipé de systèmes d'injection régulièrement répartis autour de l'axe de la turbomachine et destinés à l'injection d'un mélange d'air et de carburant dans la chambre de combustion.The combustion chamber is delimited upstream by an annular bottom equipped with injection systems regularly distributed around the axis of the turbomachine and for injecting a mixture of air and fuel into the combustion chamber.

La sortie du compresseur débouche dans une enceinte dans laquelle est logée la chambre de combustion. Le compresseur peut être du type axial et comporter une sortie sensiblement alignée avec les systèmes d'injection de la chambre de combustion, ou être du type centrifuge, et comprendre en sortie un redresseur annulaire débouchant dans une région radialement externe de l'enceinte de la chambre de combustion.The output of the compressor opens into an enclosure in which is housed the combustion chamber. The compressor may be of axial type and have an output substantially aligned with the injection systems of the combustion chamber, or be of the centrifugal type, and comprise at the output an annular rectifier opening in a radially outer region of the enclosure of the combustion chamber.

Les systèmes d'injection de la chambre de combustion comportent des perçages périphériques par lesquels de l'air provenant du compresseur peut entrer, et des moyens de centrage et de guidage de têtes d'injecteurs de carburant.Injection systems of the combustion chamber have peripheral bores through which air from the compressor can enter, and means for centering and guiding fuel injector heads.

Les systèmes d'injection sont conçus pour optimiser les performances de la chambre de combustion et réduire ainsi sa consommation de carburant et les émissions de polluants en sortie de cette chambre de combustion.The injection systems are designed to optimize the performance of the combustion chamber and thus reduce fuel consumption and pollutant emissions at the outlet of this combustion chamber.

Les performances des systèmes d'injection sont, d'une manière générale, d'autant plus élevées que la perte de charge est importante à l'intérieur de ces systèmes d'injection, et que l'alimentation en air de ces systèmes est uniforme autour de leurs axes respectifs. Pour limiter la perte de charge globale subie par le flux d'air alimentant la chambre de combustion tout en autorisant une perte de charge élevée à l'intérieur des systèmes d'injection, il est donc souhaitable de réduire au mieux la perte de charge en amont de ces systèmes d'injection.The performance of the injection systems is, in general, even higher than the pressure drop is important inside these injection systems, and that the air supply of these systems is uniform. around their respective axes. To limit the overall pressure drop experienced by the air flow supplying the combustion chamber while allowing a high pressure drop inside the injection systems, it is therefore desirable to reduce the pressure drop as much as possible. upstream of these injection systems.

Or, la sortie du compresseur étant distante axialement des systèmes d'injection, le flux d'air provenant du compresseur arrive en général au niveau des systèmes d'injection en ayant subi une perte de charge considérable et en étant réparti d'une façon non uniforme autour de chaque système d'injection.However, since the compressor outlet is axially distant from the injection systems, the air flow from the compressor generally arrives at the level of the injection systems having undergone a considerable loss of load and being distributed in a non-controlled manner. uniform around each injection system.

Ces problèmes sont particulièrement sensibles dans le cas des compresseurs centrifuges dont la sortie n'est pas alignée avec les systèmes d'injection des chambres de combustion mais est disposée radialement vers l'extérieur par rapport à ces systèmes d'injection.These problems are particularly sensitive in the case of centrifugal compressors whose output is not aligned with the injection systems of the combustion chambers but is arranged radially outwardly with respect to these injection systems.

Le document EP0153842 A1 montre une chambre de combustion de turbomachine ayant des collecteurs d'air de combustion associés à chaque système d'injection dans un carénage annulaire. Les collecteurs ont une forme des trous circulaires formés dans et par le carénage.The document EP0153842 A1 shows a turbomachine combustion chamber having combustion air collectors associated with each injection system in an annular fairing. The collectors have a shape of the circular holes formed in and by the fairing.

Un carénage annulaire destiné à recouvrir le fond de chambre annulaire d'une chambre de combustion de turbomachine est décrit dans le document FR2910597 . Ledit carénage comprend des ouvertures pour permettre le passage d'injecteurs de carburant supportés par le fond de chambre. Lesdites ouvertures se prolongent jusqu'à l'extrémité libre d'un bord de fixation extérieur, de sorte que le bord de fixation extérieur est fendu entre certains de ses points de fixation.An annular fairing intended to cover the annular chamber bottom of a turbomachine combustion chamber is described in the document FR2910597 . Said fairing comprises openings to allow the passage of fuel injectors supported by the chamber bottom. Said openings extend to the free end of an outer fixing edge, so that the outer fixing edge is split between some of its attachment points.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

L'invention a notamment pour but d'apporter une solution simple, économique et efficace à ces problèmes, permettant d'éviter les inconvénients précités.The invention aims in particular to provide a simple, economical and effective solution to these problems, to avoid the aforementioned drawbacks.

Elle a en particulier pour but de réduire les pertes de charge du flux d'air provenant d'un compresseur dans une turbomachine, entre la sortie de ce compresseur et l'entrée de systèmes d'injection d'une chambre de combustion de la turbomachine, de manière à permettre notamment une augmentation de la perte de charge à l'intérieur de ces systèmes d'injection sans augmenter considérablement la perte de charge globale du flux d'air alimentant la chambre de combustion.In particular, it aims to reduce the pressure drop of the air flow coming from a compressor in a turbomachine, between the output of this compressor and the inlet of injection systems of a combustion chamber of the turbomachine , in particular to allow an increase in the pressure drop inside these injection systems without considerably increasing the overall pressure drop of the air flow supplying the combustion chamber.

L'invention a également pour but d'améliorer l'uniformité de l'alimentation en air des systèmes d'injection des chambres de combustion.The invention also aims to improve the uniformity of the air supply combustion chamber injection systems.

L'invention propose à cet effet une chambre annulaire de combustion destinée à équiper une turbomachine, comprenant un fond de chambre agencé à l'extrémité amont de la chambre de combustion, ainsi qu'une pluralité de systèmes d'injection d'air et de carburant répartis circonférentiellement autour d'un axe de la chambre de combustion et montés sur le fond de chambre. La chambre annulaire de combustion comprend en outre, associé à chaque système d'injection, un collecteur d'air comprenant deux parois montées sur le fond de chambre et se projetant vers l'amont pour former obstacle à un écoulement circonférentiel d'air autour de l'axe de la chambre de combustion, ainsi qu'une ouverture d'admission d'air formée à l'extrémité amont du collecteur d'air précité. Selon l'invention, l'ouverture d'admission d'air de chaque collecteur d'air est ouverte radialement vers l'extérieur par rapport à un axe du système d'injection correspondant.To this end, the invention proposes an annular combustion chamber intended to equip a turbomachine, comprising a chamber bottom arranged at the upstream end of the combustion chamber, as well as a plurality of air injection and air injection systems. fuel distributed circumferentially around an axis of the combustion chamber and mounted on the chamber bottom. The annular combustion chamber further comprises, associated with each injection system, an air manifold comprising two walls mounted on the chamber bottom and projecting upstream to form an obstacle to a circumferential flow of air around the chamber. the axis of the combustion chamber, and an air inlet opening formed at the upstream end of the aforementioned air collector. According to the invention, the air intake opening of each air collector is open radially outwards with respect to an axis of the corresponding injection system.

Les collecteurs d'air selon l'invention permettent de canaliser de manière optimale un flux d'air provenant d'une région radialement externe par rapport aux axes respectifs des systèmes d'injection et alimentant ces systèmes d'injection, autour de chacun de ces systèmes.The air collectors according to the invention can optimally channel a flow of air from a radially outer region relative to the respective axes of the injection systems and feeding these injection systems, around each of these systems.

Les collecteurs d'air permettent ainsi de réduire la perte de charge subie par ce flux d'air en amont de ces systèmes d'injection, et de rendre l'alimentation en air de ces systèmes plus uniforme.Air collectors thus make it possible to reduce the pressure drop experienced by this flow of air upstream of these injection systems, and to make the air supply of these systems more uniform.

Il en résulte une amélioration des performances générales de la chambre de combustion, et plus particulièrement une augmentation de son rendement et une réduction des émissions de substances polluantes par la chambre de combustion.This results in an improvement in the general performance of the combustion chamber, and more particularly an increase in its efficiency and a reduction of emissions of pollutants by the combustion chamber.

Un flux d'air provenant d'une région radialement externe par rapport aux axes respectifs des systèmes d'injection de la chambre de combustion se rencontre en particulier dans les turbomachines comprenant un compresseur centrifuge. L'invention est donc particulièrement avantageuse lorsqu'elle est appliquée à une turbomachine de ce type.An air flow coming from a region radially external to the respective axes of the injection systems of the combustion chamber is encountered in particular in turbomachines comprising a centrifugal compressor. The invention is therefore particularly advantageous when applied to a turbomachine of this type.

Préférentiellement, lorsque l'ouverture d'admission d'air de chaque collecteur est vue en projection dans un plan transversal perpendiculaire à un plan tangentiel passant par l'axe du système d'injection correspondant, la partie de ladite ouverture qui est située radialement a l'extérieur par rapport au plan tangentiel précité présente une surface d'ouverture plus grande que celle de la partie de ladite ouverture qui est située radialement a l'intérieur par rapport à ce plan tangentiel.Preferably, when the air intake opening of each collector is viewed in projection in a transverse plane perpendicular to a tangential plane passing through the axis of the corresponding injection system, the portion of said opening which is located radially outwardly with respect to the aforesaid tangential plane has an opening area greater than that of the part of said opening which is located radially inward with respect to this tangential plane.

Cette configuration permet d'optimiser davantage l'admission d'air provenant d'une région radialement externe par rapport aux axes respectifs des systèmes d'injection de la chambre de combustion.This configuration further optimizes the intake of air from a radially outer region relative to the respective axes of the injection systems of the combustion chamber.

Chaque collecteur d'air comprend deux parois qui sont montées sur le fond de chambre, se projettent vers l'amont, et sont agencées de part et d'autre du système d'injection correspondant, ces parois formant obstacle à un écoulement circonférentiel d'air autour de l'axe de la chambre de combustion.Each air manifold comprises two walls which are mounted on the chamber bottom, project upstream, and are arranged on either side of the corresponding injection system, these walls forming an obstacle to a circumferential flow of air around the axis of the combustion chamber.

Dans un premier mode de réalisation d'exemple démonstratif , les deux parois de chaque collecteur d'air présentent une concavité tournée vers ledit collecteur d'air et sont raccordées l'une à l'autre par deux extrémités opposées de chacune de ces parois, de sorte que chaque collecteur d'air a une forme globalement tubulaire et comporte une extrémité amont formant ladite ouverture d'admission d'air.In a first embodiment of demonstrative example, the two walls of each air collector have a concavity turned towards said air collector and are connected to one another by two opposite ends of each of these walls, so that each air manifold has a generally tubular shape and has an upstream end forming said air inlet opening.

Cela permet de rendre plus uniforme la répartition de l'air autour de chaque système d'injection.This makes the distribution of air around each injection system more uniform.

Avantageusement, l'extrémité amont de chaque collecteur d'air est conformée de sorte qu'une partie radialement interne de cette extrémité amont soit décalée vers l'amont par rapport à une partie radialement externe de ladite extrémité amont du collecteur d'air.Advantageously, the upstream end of each air manifold is shaped so that a radially inner portion of the upstream end is offset upstream relative to a radially outer portion of said upstream end of the air collector.

Selon l'invention, la chambre de combustion comporte un carénage annulaire de fond de chambre agencé en amont du fond de chambre et auquel les parois de chaque collecteur d'air sont raccordées de manière sensiblement étanche de part et d'autre d'un orifice correspondant formé dans le carénage et formant ladite ouverture d'admission d'air du collecteur d'air.According to the invention, the combustion chamber comprises an annular fairing of chamber bottom arranged upstream of the chamber bottom and to which the walls of each air manifold are connected substantially sealingly on either side of an orifice corresponding formed in the shroud and forming said air intake opening of the air collector.

Les parois précitées permettent de délimiter des compartiments formant collecteurs d'air entre le fond de chambre et le carénage, autour de chaque système d'injection.The aforementioned walls allow to delimit compartments forming air collectors between the chamber bottom and the fairing, around each injection system.

Lesdites parois de chaque collecteur d'air s'étendent radialement et chacune de ces parois fait partie de deux collecteurs d'air consécutifs autour de l'axe de la chambre de combustion.Said walls of each air collector extend radially and each of these walls is part of two consecutive air collectors around the axis of the combustion chamber.

Cette configuration présente notamment l'avantage de minimiser le nombre total de parois de collecteur d'air.This configuration has the particular advantage of minimizing the total number of air collector walls.

L'ouverture d'admission d'air de chaque collecteur d'air a de préférence une forme évasée radialement vers l'extérieur.The air inlet opening of each air manifold preferably has a flared shape radially outwardly.

En variante, ou de manière complémentaire, le carénage annulaire peut comporter une partie annulaire radialement interne et une partie annulaire radialement externe entre lesquelles sont ménagées lesdites ouvertures d'admission d'air, la partie annulaire radialement interne étant décalée vers l'amont par rapport à la partie annulaire radialement externe.Alternatively, or in a complementary manner, the annular fairing may comprise a radially inner annular portion and a radially outer annular portion between which said air intake openings are formed, the radially inner annular portion being offset upstream relative to at the radially outer annular portion.

Dans ce cas, la forme du carénage permet d'orienter l'ouverture d'admission d'air radialement vers l'extérieur.In this case, the shape of the fairing makes it possible to orient the air intake opening radially outwards.

D'une manière générale, chaque système d'injection comprenant une douille de centrage et de guidage de tête d'injecteur, chaque collecteur d'air comprend de préférence au moins une partie qui s'étend vers l'amont au-delà d'une extrémité amont de ladite douille du système d'injection correspondant.In a general manner, each injection system comprising an injector head centering and guiding sleeve, each air collector preferably comprises at least one part extending upstream beyond an upstream end of said bushing of the corresponding injection system.

Les collecteurs d'air présentent ainsi des aptitudes optimales pour canaliser l'air admis dans les systèmes d'injection qui équipent la chambre de combustion.The air collectors and have optimal abilities to channel air admitted into the injection systems that equip the combustion chamber.

L'invention concerne également une turbomachine comprenant une chambre de combustion du type décrit ci-dessus.The invention also relates to a turbomachine comprising a combustion chamber of the type described above.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

L'invention sera mieux comprise, et d'autres détails, avantages et caractéristiques de celle-ci apparaîtront à la lecture de la description suivante faite à titre d'exemple non limitatif et en référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue schématique partielle en perspective d'une turbomachine selon un exemple démonstratif ;
  • la figure la est une vue schématique partielle de la turbomachine de la figure 1 en projection dans le plan P1 de la figure 1 ;
  • la figure 2 est une vue schématique partielle en coupe axiale et à plus grande échelle de la turbomachine de la figure 1 ;
  • la figure 3 est une vue semblable à la figure 1, d'une turbomachine selon l'invention ;
  • la figure 3a est une vue schématique partielle de la turbomachine de la figure 3 en projection dans le plan P1 de la figure 3 ;
  • la figure 4 est une vue semblable à la figure 3a, illustrant une variante de réalisation de la turbomachine de la figure 3.
The invention will be better understood, and other details, advantages and characteristics thereof will appear on reading the description. following example by way of non-limiting example and with reference to the accompanying drawings in which:
  • the figure 1 is a partial schematic perspective view of a turbomachine according to a demonstrative example;
  • FIG. 1a is a partial schematic view of the turbomachine of the figure 1 in projection in the plane P1 of the figure 1 ;
  • the figure 2 is a partial schematic view in axial section and on a larger scale of the turbomachine of the figure 1 ;
  • the figure 3 is a view similar to the figure 1 , a turbomachine according to the invention;
  • the figure 3a is a partial schematic view of the turbomachine of the figure 3 in projection in the plane P1 of the figure 3 ;
  • the figure 4 is a view similar to the figure 3a , illustrating an embodiment variant of the turbomachine of the figure 3 .

EXPOSÉ DÉTAILLÉDETAILED PRESENTATION

Les figures 1 à 2 représentent une chambre de combustion 10 d'une turbomachine selon un exemple démonstratif ainsi que l'environnement immédiat de cette chambre de combustion.The Figures 1 to 2 represent a combustion chamber 10 of a turbomachine according to a demonstrative example as well as the immediate environment of this combustion chamber.

D'une manière connue, la chambre de combustion 10 est logée dans une enceinte 12 qui est agencée en aval d'un compresseur de la turbomachine, du type centrifuge, dont la sortie est raccordée à un diffuseur radial 14, lui-même raccordé en sortie à un redresseur de flux 16 qui débouche dans une région radialement externe de l'enceinte 12.In a known manner, the combustion chamber 10 is housed in an enclosure 12 which is arranged downstream of a compressor of the turbomachine, of the centrifugal type, the output of which is connected to a radial diffuser 14, itself connected at the output to a flow rectifier 16 which opens into a radially outer region of the enclosure 12.

La chambre de combustion 10 est délimitée par deux parois coaxiales sensiblement cylindriques 18 et 20, respectivement interne et externe, et par un fond de chambre annulaire 22 qui s'étend sensiblement radialement à l'extrémité amont de la chambre 10 et qui est raccordé par ses extrémités radiales aux deux parois 18 et 20.The combustion chamber 10 is delimited by two substantially cylindrical coaxial walls 18 and 20, respectively internal and external, and by an annular chamber bottom 22 which extends substantially radially at the upstream end of the chamber 10 and which is connected by its radial ends to both walls 18 and 20.

Les parois interne 18 et externe 20 de la chambre de combustion 10 sont fixées en aval par deux viroles interne 24 et externe 26 respectivement sur une paroi interne 28 sensiblement cylindrique reliée au diffuseur 14, et sur un carter externe 30, de manière à délimiter l'enceinte 12.The inner 18 and outer 20 walls of the combustion chamber 10 are attached downstream by two inner and outer ferrules 24 and 26 respectively on a substantially cylindrical inner wall 28 connected to the diffuser 14, and on an outer casing 30, so as to delimit the enclosure 12.

Des systèmes d'injection 32, qui sont régulièrement répartis autour de l'axe 34 de la chambre de combustion, sont montés dans le fond de chambre 22. Chaque système d'injection 32 comprend notamment une douille 36 de centrage et de guidage d'une tête 38 d'un injecteur de carburant 40, et des orifices d'entrée d'air 42 agencés autour d'un axe 44 du système d'injection.Injection systems 32, which are regularly distributed around the axis 34 of the combustion chamber, are mounted in the chamber bottom 22. Each injection system 32 comprises in particular a centering and guiding bushing 36. a head 38 of a fuel injector 40, and air inlet ports 42 arranged around an axis 44 of the injection system.

La douille 36 de chaque système d'injection 32 permet d'aligner la tête d'injecteur 38 correspondante sur l'axe 44 du système d'injection. De plus, les systèmes d'injection 32 sont configurés pour permettre un certain débattement radial et axial des têtes d'injecteur 38, pour tenir compte d'éventuelles dilatations différentielles de nature à provoquer des déplacements relatifs entre les injecteurs 40 et la chambre de combustion 10.The bushing 36 of each injection system 32 aligns the corresponding injector head 38 on the axis 44 of the injection system. In addition, the injection systems 32 are configured to allow a certain radial and axial displacement of the injector heads 38, to take account of any differential expansions likely to cause relative displacements between the injectors 40 and the combustion chamber 10.

En fonctionnement, un flux d'air 46 provenant du compresseur centrifuge est injecté par le redresseur 16 dans l'enceinte 12.In operation, a stream of air 46 coming from the centrifugal compressor is injected by the rectifier 16 into the enclosure 12.

Le flux d'air 46, qui arrive dans une région radialement externe de l'enceinte 12, se sépare globalement en trois parties dans cette enceinte 12.The air flow 46, which arrives in a radially outer region of the enclosure 12, separates into three parts in this chamber 12.

Une première partie 48 du flux d'air s'écoule vers l'aval le long de la paroi externe 20 de la chambre de combustion 10, et pénètre partiellement dans la chambre de combustion 10 par des orifices 50 pratiqués dans sa paroi externe 20.A first portion 48 of the air flow flows downstream along the outer wall 20 of the combustion chamber 10, and partially enters the combustion chamber 10 through orifices 50 formed in its outer wall 20.

Une deuxième partie 52 du flux d'air s'écoule vers l'aval le long de la paroi interne 18 de la chambre de combustion 10, et pénètre partiellement dans la chambre de combustion 10 par des orifices 54 pratiqués dans sa paroi interne 18.A second portion 52 of the air flow flows downstream along the internal wall 18 of the combustion chamber 10, and partially enters the combustion chamber 10 through orifices 54 formed in its inner wall 18.

Enfin, une troisième partie 56 du flux d'air alimente les systèmes d'injection 32 de la chambre de combustion 10.Finally, a third portion 56 of the air flow feeds the injection systems 32 of the combustion chamber 10.

Conformément à l'exemple démonstratif , la chambre de combustion 10 est équipée d'une pluralité de collecteurs d'air 58 (dont l'un est visible sur les figures 1 à 2).In accordance with the illustrative example, the combustion chamber 10 is equipped with a plurality of air collectors 58 (one of which is visible on the Figures 1 to 2 ).

Chaque collecteur d'air 58 comprend deux parois 60 et 62 semblables (figure 1) qui sont incurvées autour du système d'injection 32 correspondant en présentant une concavité tournée vers ce système d'injection 32, et qui sont montées sur le fond de chambre 22 à leurs extrémités aval respectives.Each air manifold 58 comprises two similar walls 60 and 62 ( figure 1 ) which are curved around the injection system 32 corresponding by having a concavity facing the injection system 32, and which are mounted on the chamber bottom 22 at their respective downstream ends.

Dans l'exemple démonstratif les deux parois 60 et 62 de chaque collecteur d'air 58 comportent chacune deux bords d'extrémité opposés, respectivement 60a, 60b et 62a, 62b, par lesquels ces deux parois 60 et 62 sont raccordées l'une à l'autre, de sorte que chaque collecteur d'air 58 a une forme globalement tubulaire.In the demonstrative example, the two walls 60 and 62 of each air collector 58 each comprise two opposite end edges, respectively 60a, 60b and 62a, 62b, through which these two walls 60 and 62 are connected to each other. the other, so that each air manifold 58 has a generally tubular shape.

Les collecteurs d'air 58 présentent chacun un bord d'extrémité amont délimitant une ouverture d'admission d'air 64, par laquelle de l'air 56 provenant du redresseur 16 peut pénétrer pour atteindre les orifices d'entrée d'air 42 des systèmes d'injection 32.The air manifolds 58 each have an upstream end edge defining an air inlet opening 64, through which air 56 from the rectifier 16 can penetrate to reach the air inlet ports 42 of the injection systems 32.

Les deux parois 60, 62 de chaque collecteur d'air 58 sont tronquées en amont selon un plan incliné par rapport à l'axe 44 du système d'injection correspondant de sorte que l'ouverture d'admission d'air 64 de chaque collecteur d'air 58 soit ouverte vers la sortie du redresseur 16, c'est-à-dire ouverte radialement vers l'extérieur par rapport à l'axe 44 du système d'injection précité, pour faciliter l'entrée d'air provenant de ce redresseur 16 dans les collecteurs d'air 58.The two walls 60, 62 of each air collector 58 are truncated upstream along a plane inclined relative to the axis 44 of the corresponding injection system so that the air intake opening 64 of each collector air 58 is open towards the outlet of the rectifier 16, that is to say open radially outwardly relative to the axis 44 of the aforementioned injection system, to facilitate the entry of air from this rectifier 16 in the air collectors 58.

Le bord d'extrémité amont de chaque collecteur d'air 58 comporte ainsi une partie radialement interne 66 qui est décalée vers l'amont par rapport à une partie radialement externe 68 de ce bord amont.The upstream end edge of each air manifold 58 thus has a radially inner portion 66 which is offset upstream with respect to a radially outer portion 68 of the upstream edge.

Comme le montre la figure 1a, lorsque chaque ouverture d'admission d'air 64 est vue en projection dans le plan transversal P1 de la figure 1, qui est perpendiculaire au plan tangentiel P2 passant par l'axe 44 du système d'injection 32, la partie de l'ouverture 64 qui est située radialement a l'extérieur par rapport au plan tangentiel P2 précité présente une surface d'ouverture S1 plus grande que celle S2 de la partie de ladite ouverture 64 qui est située radialement a l'intérieur par rapport au plan tangentiel P2.As shown in figure 1a when each air inlet opening 64 is viewed in projection in the transverse plane P1 of the figure 1 , which is perpendicular to the tangential plane P2 passing through the axis 44 of the injection system 32, the portion of the opening 64 which is located radially outwardly relative to the aforementioned tangential plane P2 has an opening surface S 1 greater than that S 2 of the portion of said opening 64 which is located radially inward with respect to the tangential plane P2.

Comme le montre la figure 2, la partie radialement interne 66 du bord amont de chaque collecteur d'air 58 s'étend vers l'amont au-delà de l'extrémité amont de la douille 36 de centrage et de guidage de la tête d'injecteur 38 correspondante. Cette partie radialement interne 66 forme ainsi une écope particulièrement efficace pour guider le flux d'air 56 provenant du redresseur 16.As shown in figure 2 , the radially inner portion 66 of the upstream edge of each air manifold 58 extends upstream beyond the upstream end of the bushing 36 for centering and guiding the corresponding injector head 38. This radially inner portion 66 thus forms a scoop which is particularly effective for guiding the flow of air 56 coming from the rectifier 16.

L'inclinaison de l'ouverture d'admission d'air 64 de chaque collecteur d'air 58 par rapport à l'axe 44 du système d'injection correspondant est notamment définie de manière à ne pas gêner des déplacements axiaux et radiaux de la tête d'injecteur 38 correspondante en fonctionnement et aussi lors du montage et du démontage de l'injecteur 40.The inclination of the air intake opening 64 of each air manifold 58 with respect to the axis 44 of the corresponding injection system is notably defined so as not to hinder axial and radial displacements of the injector head 38 corresponding in operation and also during assembly and disassembly of the injector 40.

Ainsi, l'ouverture d'admission d'air 64 forme avec l'axe 44 un angle α (figure 2) qui est typiquement compris entre 40 degrés et 80 degrés environ.Thus, the air intake opening 64 forms with the axis 44 an angle α ( figure 2 ) which is typically between about 40 degrees and 80 degrees.

Dans l'exemple démonstratif représenté sur les figures 1 à 2, les deux parois 60 et 62 de chaque collecteur d'air 58 sont fixées à leur extrémité aval sur une pièce annulaire 70, parfois appelée coupelle d'arrêt, qui est solidaire du fond de chambre 22, et qui comprend un flasque annulaire 72 s'étendant radialement autour de l'axe 44 du système d'injection 32 correspondant, et un rebord annulaire 74 qui s'étend parallèlement à l'axe 44 depuis la périphérie interne du flasque annulaire 72 de la coupelle d'arrêt 70.In the demonstrative example shown on the Figures 1 to 2 , the two walls 60 and 62 of each air manifold 58 are fixed at their downstream end to an annular piece 70, sometimes called a cup stopper, which is integral with the chamber bottom 22, and which comprises an annular flange 72 extending radially about the axis 44 of the corresponding injection system 32, and an annular flange 74 which extends parallel to the 44 axis from the inner periphery of the annular flange 72 of the stop cup 70.

La fixation des parois 60 et 62 sur la coupelle d'arrêt 70 est par exemple réalisée par soudage et de telle sorte que les parois 60 et 62 s'étendent dans le prolongement du rebord annulaire 74 de la coupelle d'arrêt 70.Fixing the walls 60 and 62 on the stop cup 70 is for example made by welding and so that the walls 60 and 62 extend in the extension of the annular rim 74 of the stop cup 70.

D'une manière connue en soi, la coupelle d'arrêt 70 permet de bloquer axialement le système d'injection 32 par coopération du flasque annulaire 72 de la coupelle d'arrêt avec un flasque annulaire 76 solidaire du système d'injection 32 et monté coulissant radialement dans une gorge annulaire ménagée entre le fond de chambre 22 et le flasque 72 de la coupelle d'arrêt 70.In a manner known per se, the stop cup 70 makes it possible to axially block the injection system 32 by cooperation of the annular flange 72 of the stop cup with an annular flange 76 secured to the injection system 32 and mounted sliding radially in an annular groove formed between the chamber bottom 22 and the flange 72 of the stop cup 70.

D'une manière générale, les collecteurs d'air 58 permettent de canaliser l'air provenant du redresseur 16 autour de chaque système d'injection 32, ce qui permet de réduire les pertes de charge en amont de ces systèmes d'injection et d'améliorer l'uniformité de l'alimentation en air de ces systèmes d'injection. A cet effet, les collecteurs d'air 58 présentent une propriété remarquable en ce qu'ils forment chacun un obstacle à l'écoulement de l'air circonférentiellement entre deux systèmes d'injection voisins, le long du fond de chambre 22.In general, the air collectors 58 make it possible to channel the air coming from the straightener 16 around each injection system 32, which makes it possible to reduce the pressure losses upstream of these injection systems improve the uniformity of the air supply of these injection systems. For this purpose, the air collectors 58 have a remarkable property in that they each form an obstacle to the flow of air circumferentially between two neighboring injection systems, along the chamber bottom 22.

La figure 3 représente un mode de réalisation de l'invention dans lequel le fond 22 de la chambre de combustion 10 est équipé d'un carénage annulaire de protection 78 agencé en amont de ce fond de chambre 22.The figure 3 represents an embodiment of the invention in which the bottom 22 of the combustion chamber 10 is equipped with an annular protective fairing 78 arranged upstream of the chamber bottom 22.

Le carénage 78 comporte une partie annulaire continue radialement interne 80 qui présente un bord 82 fixé conjointement sur un rebord interne 84 du fond de chambre 22 et sur un bord amont 86 de la paroi interne 18 de la chambre de combustion 10.The shroud 78 has a radially inner continuous annular portion 80 which has an edge 82 fastened together on an inner rim 84 of the chamber bottom 22 and on an upstream edge 86 of the inner wall 18 of the combustion chamber 10.

Le carénage 78 comporte en outre des ouvertures 88 d'admission d'air qui sont ménagées en regard de chaque système d'injection 32 et qui s'étendent vers l'extérieur jusqu'à l'extrémité radialement externe du carénage 78 de sorte que ce dernier présente un bord radialement externe 90 fendu au niveau de chacune de ces ouvertures 88. Ce bord externe 90 du carénage est fixé conjointement sur un rebord externe 92 du fond de chambre 22 et sur un bord amont 94 de la paroi externe 20 de la chambre de combustion 10.The fairing 78 further comprises air intake openings 88 which are arranged opposite each injection system 32 and which extend outwards as far as the radially outer end of the fairing 78 so that the latter has a radially outer edge 90 split at each of these openings 88. This outer edge 90 of the shroud is fixed jointly on an outer rim 92 of the chamber bottom 22 and on an upstream edge 94 of the outer wall 20 of the combustion chamber 10.

Comme le montre la figure 3a, lorsque chaque ouverture d'admission d'air 88 est vue en projection dans le plan transversal P1 perpendiculaire au plan tangentiel P2 passant par l'axe 44 du système d'injection 32, la partie de l'ouverture 88 qui est située radialement a l'extérieur par rapport au plan tangentiel P2 précité présente une surface d'ouverture S1 plus grande que celle S2 de la partie de l'ouverture 88 qui est située radialement a l'intérieur par rapport au plan tangentiel P2.As shown in figure 3a when each air inlet opening 88 is seen in projection in the transverse plane P1 perpendicular to the tangential plane P2 passing through the axis 44 of the injection system 32, the portion of the opening 88 which is situated radially at the outside relative to the aforementioned tangential plane P2 has an opening surface S 1 greater than that S 2 of the portion of the opening 88 which is located radially inward with respect to the tangential plane P2.

Les ouvertures d'admission d'air 88 sont ainsi ouvertes radialement vers l'extérieur par rapport à l'axe 44 de chaque système d'injection 32, ce qui permet de faciliter l'écoulement du flux d'air 56 provenant du redresseur 16 et alimentant les systèmes d'injection 32.The air intake openings 88 are thus open radially outwardly relative to the axis 44 of each injection system 32, which facilitates the flow of the air stream 56 from the rectifier 16 and feeding injection systems 32.

Dans l'exemple représenté sur la figure 3, les ouvertures d'admission d'air 88 du carénage 78 ont une forme évasée radialement vers l'extérieur.In the example shown on the figure 3 , the air intake openings 88 of the shroud 78 have a flared shape radially outwardly.

En variante, chaque ouverture d'admission d'air 88 peut avoir une forme centrée sur un axe 95 contenu dans un plan passant par l'axe 44 du système d'injection correspondant et par l'axe 34 de la chambre de combustion, et qui est décalé radialement vers l'extérieur par rapport audit axe 44 du système d'injection ou incliné par rapport à cet axe 44. La figure 4 illustre une ouverture 88 de ce type vue en projection dans le plan transversal P1 précité.Alternatively, each air inlet opening 88 may have a shape centered on an axis 95 contained in a plane passing through the axis 44 of the corresponding injection system and by the axis 34 of the combustion chamber, and which is offset radially outwardly with respect to said axis 44 of the injection system or inclined with respect to this axis 44. figure 4 illustrates an opening 88 of this type seen in projection in the aforementioned transverse plane P1.

Dans tous les cas, les ouvertures d'admission d'air 88 vérifient la propriété ci-dessus relative aux surfaces d'ouverture S1 et S2 définies de part et d'autre du plan tangentiel P2.In any case, the air intake openings 88 verify the property above relative to the opening surfaces S 1 and S 2 defined on either side of the tangential plane P2.

De plus, il est à noter que chaque ouverture d'admission d'air 88 s'étend entre une partie radialement externe 102 du carénage et la partie annulaire radialement interne 80 précitée de ce carénage 78, laquelle partie radialement interne 80 est décalée vers l'amont par rapport à la partie radialement externe 102 précitée.In addition, it should be noted that each air intake opening 88 extends between a radially outer portion 102 of the fairing and the radially inner annular portion 80 of said fairing 78, which radially inner portion 80 is shifted towards the outside. upstream relative to the radially outer portion 102 above.

Par ailleurs, dans le mode de réalisation de l'invention, le fond 22 de la chambre de combustion 10 est équipé de paires de parois de collecteur 96 et 98 agencées de part et d'autre de chaque système d'injection 32 et de l'ouverture 88 correspondante, comme le montre la figure 3. Ces parois de collecteur 96, 98 sont planes et se projettent vers l'amont depuis le fond de chambre 22 en s'étendant dans des plans respectifs sensiblement radiaux par rapport à l'axe 34 de la chambre de combustion.Furthermore, in the embodiment of the invention, the bottom 22 of the combustion chamber 10 is equipped with pairs of collector walls 96 and 98 arranged on either side of each injection system 32 and on the other side. corresponding aperture 88, as shown in FIG. figure 3 . These collector walls 96, 98 are flat and project upstream from the chamber bottom 22 extending in respective substantially radial planes with respect to the axis 34 of the combustion chamber.

Chaque paroi de collecteur 96, 98 est raccordée d'une manière sensiblement étanche au fond de chambre 22 ainsi qu'au carénage 78, par exemple par soudage ou par boulonnage.Each collector wall 96, 98 is substantially sealingly connected to the chamber bottom 22 and to the fairing 78, for example by welding or bolting.

De cette manière, chaque paire de parois 96 et 98 délimite un compartiment entre le fond de chambre 22 et le carénage 78. Ce compartiment forme un collecteur d'air 100 qui est fonctionnellement analogue d'air au collecteur d'air 58 tel exemple démonstratif. Ce collecteur d'air 100 permet en particulier de canaliser l'air autour de chaque système d'injection 32 en interdisant tout écoulement circonférentiel de l'air entre deux systèmes d'injection voisins le long du fond de chambre 22.In this way, each pair of walls 96 and 98 delimits a compartment between the chamber bottom 22 and the fairing 78. This compartment forms an air manifold 100 which is functionally similar to air to the air manifold 58 as a demonstrative example. . This air collector 100 allows in particular to channel the air around each injection system 32 by prohibiting any flow circumferential air between two neighboring injection systems along the chamber bottom 22.

Il n'est prévue qu'une seule paroi 96, 98 de collecteur d'air 100 entre deux systèmes d'injection 32 voisins, de sorte que chaque paroi 96, 98 de collecteur d'air 100 participe à la formation de deux collecteurs d'air 100 voisins.Only one wall 96, 98 of the air collector 100 is provided between two adjacent injection systems 32, so that each wall 96, 98 of the air collector 100 participates in the formation of two collectors. 100 neighbors.

Claims (6)

  1. Annular combustion chamber (10) to be fitted on a turbomachine and comprising a chamber end wall (22) arranged at the upstream end of the combustion chamber (10), an annular chamber end wall shielding (78) arranged on the upstream side of the chamber end wall (22), and a plurality of air and fuel injection systems (32) circumferentially distributed around an axis (34) of the combustion chamber (10) and mounted on said chamber end wall (22), said combustion chamber (10) also comprising an air manifold (100) associated with each injection system (32), said air manifold comprising two walls (96, 98) mounted on the chamber end wall (22) and projecting in the upstream direction on each side of the corresponding injection system (32) to form an obstacle to a circumferential airflow around the axis (34) of the combustion chamber (10), said walls (96, 98) being connected in an almost airtight manner to the annular shielding chamber end wall (78) on each side of a corresponding orifice formed in said annular chamber end wall shielding (78), said orifice forming an air inlet opening (88) at the upstream end of said air manifold (100) and said orifice opening radially outwards from an axis (44) of said injection system, said combustion chamber (10) being characterized in that said walls (96, 98) extend radially, and in that each of these walls (96, 98) forms part of two consecutive air manifolds (100).
  2. Annular combustion chamber according to claim 1, characterised in that when said air inlet opening (88) of each air manifold (100) is seen in projection in a transverse plane (P1) perpendicular to a tangential plane (P2) passing through said centre line (44) of the corresponding injection system (32), the part of said opening (88) located radially outwards from said tangential plane (P2) has a larger opening area than the part of said opening (88) that is located radially inwards from said tangential plane (P2).
  3. Annular combustion chamber according to claim 1 or 2, characterised in that said air inlet opening (88) of each air manifold (100) is tapered radially outwards.
  4. Annular combustion chamber according to any one of claims 1 to 3, characterised in that said annular shielding (78) comprises a radially inward annular part (80) and a radially outward annular part (102) between which said air inlet openings (88) are formed, said radially inward annular part (80) being offset from the radially outward annular part (102) in the upstream direction.
  5. Annular combustion chamber according to any one of the previous claims, characterised in that each injection system (32) comprises a centring and guide bushing (36) for the injector head, and each air manifold (100) comprises at least one part that extends in the upstream direction beyond an upstream end of said bushing (36) of the corresponding injection system (32).
  6. Turbomachine, characterised in that it comprises a combustion chamber (10) according to any one of the previous claims.
EP10708769.4A 2009-03-17 2010-03-15 Turbine engine combustion chamber comprising improved primary air supply means Active EP2409085B1 (en)

Applications Claiming Priority (2)

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FR0951673A FR2943403B1 (en) 2009-03-17 2009-03-17 TURBOMACHINE COMBUSTION CHAMBER COMPRISING IMPROVED AIR SUPPLY MEANS
PCT/EP2010/053249 WO2010105999A1 (en) 2009-03-17 2010-03-15 Turbine engine combustion chamber comprising improved air supply means

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EP2409085B1 true EP2409085B1 (en) 2015-02-25

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EP (1) EP2409085B1 (en)
CN (1) CN102362120B (en)
BR (1) BRPI1008982B1 (en)
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FR (1) FR2943403B1 (en)
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FR2964725B1 (en) * 2010-09-14 2012-10-12 Snecma AERODYNAMIC FAIRING FOR BOTTOM OF COMBUSTION CHAMBER
FR3011317B1 (en) * 2013-10-01 2018-02-23 Safran Aircraft Engines COMBUSTION CHAMBER FOR TURBOMACHINE WITH HOMOGENEOUS AIR INTAKE THROUGH INJECTION SYSTEMS
FR3017255B1 (en) 2014-02-03 2017-10-13 Snecma SEMICONDUCTOR IGNITION CANDLE FOR AIRCRAFT TURBOMACHINE, INCLUDING ECOPES FOR THE EVACUATION OF POSSIBLE FUEL RELIQUATES
FR3035481B1 (en) * 2015-04-23 2017-05-05 Snecma TURBOMACHINE COMBUSTION CHAMBER COMPRISING A SPECIFICALLY SHAPED AIR FLOW GUIDING DEVICE
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FR2943403A1 (en) 2010-09-24
EP2409085A1 (en) 2012-01-25
RU2011141837A (en) 2013-04-27
FR2943403B1 (en) 2014-11-14
CA2754419A1 (en) 2010-09-23
BRPI1008982B1 (en) 2021-01-26
WO2010105999A1 (en) 2010-09-23
CN102362120B (en) 2014-07-16
RU2527932C2 (en) 2014-09-10
US9127841B2 (en) 2015-09-08
CN102362120A (en) 2012-02-22
CA2754419C (en) 2017-04-04
BRPI1008982A2 (en) 2016-03-22
US20120055164A1 (en) 2012-03-08

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