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EP2012061B1 - Chamber dome deflector, combustion chamber comprising the same and gas turbine engine equipped with the same - Google Patents

Chamber dome deflector, combustion chamber comprising the same and gas turbine engine equipped with the same Download PDF

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Publication number
EP2012061B1
EP2012061B1 EP08159737.9A EP08159737A EP2012061B1 EP 2012061 B1 EP2012061 B1 EP 2012061B1 EP 08159737 A EP08159737 A EP 08159737A EP 2012061 B1 EP2012061 B1 EP 2012061B1
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EP
European Patent Office
Prior art keywords
combustion chamber
chamber
edge
baffles
edges
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EP08159737.9A
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German (de)
French (fr)
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EP2012061A1 (en
EP2012061B2 (en
Inventor
Patrice Commaret
Didier Hernandez
Romain Lunel
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • 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
    • 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
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • the present invention relates to the technical field of combustion chambers for gas turbine engine. It is particularly aimed at the bedroom floor. Finally, it relates to a gas turbine engine such as a turbojet engine equipped with such a combustion chamber.
  • a divergent conventional combustion chamber is illustrated on the figure 1 , which is an axial section showing a half of the combustion chamber, the other half of which is deduced by symmetry with respect to the axis of the motor (not shown).
  • the combustion chamber 110 is housed in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, into which is introduced an oxidant, ambient air, compressed coming upstream of a compressor (no represented) via an annular diffusion duct 136.
  • This diverging combustion chamber 110 comprises two concentric walls: one external 112 and the other internal 114, which are coaxial and substantially conical. The walls widen from upstream to downstream. The outer 112 and inner 114 walls of the combustion chamber 110 are connected together, upstream of the combustion chamber by a chamber bottom 116.
  • the chamber bottom 116 is a frustoconical annular piece, which extends between two substantially transverse planes flaring from downstream to upstream.
  • the chamber bottom 116 is connected to each of the two outer wall 112 and inner 114 of the combustion chamber 110.
  • the chamber bottom 116 has a small taper. It is equipped with injection systems 118 through which pass injectors 120 which introduce fuel to the upstream end of the combustion chamber 110 where the combustion reactions take place.
  • deflectors 122 are interposed between the fireplace and the walls of the chamber bottom.
  • These deflectors 122 are substantially flat plates brazed to the chamber bottom 116 with a central opening 122a for the passage of the injection system. They comprise two lateral walls 122b 122c along the radial edges, turned towards the wall of the chamber bottom and two tongues 122e 122f for guiding air along the transverse edges facing the hearth and leaving a space with the walls 114 and 112 , internally respectively external, of the chamber.
  • the baffles are cooled by the impacts of cooling air jets entering the combustion chamber 110 through cooling orifices 124 drilled in the chamber bottom 116.
  • the air forming these jets, flowing from the upstream downstream, is guided by chamber shrouds 126, passes through the chamber bottom 116 through the cooling orifices, and impinges on the upstream face of the deflectors 122.
  • the air is then guided radially inwards and outside the focus to initiate the cooling film of the walls 114 and 112 respectively.
  • This guidance along the baffles is provided by the side walls oriented radially. These walls also have a sealing function. By being in contact or by ensuring a minimum clearance with the chamber bottom, They prevent air from coming in between two adjacent baffles, enter the home and disrupt combustion. These disturbances affect pollution and should be avoided. Indeed, the pollutant discharge performance, CO and CHx are likely to be degraded by the parasitic introduction of this cold air particularly at engine idling speed where the game is more important.
  • convergent combustion chambers In the context of other engine architectures where the flow of gas is generally convergent between the compressor outlet and the inlet of the turbine, there are so-called convergent combustion chambers, the outer and inner walls of the combustion chamber are inclined by widening from downstream to upstream, and not from upstream to downstream as with the first combustion chambers mentioned above, said divergent. These convergent combustion chambers may have a larger cone angle than the cone angle of the diverging combustion chambers.
  • Such a large inclination of the combustion chamber affects the taper of the chamber bottom and the position of the baffles relative to the chamber bottom.
  • a combustion chamber is partially illustrated at the figure 2 , in axial section. In this figure appear an axial direction 100 parallel to the axis of the turbojet, the main direction 200 of the combustion chamber 210, and the angle ⁇ between these two axes 100, 200. Due to the significant inclination of the chamber 200, the chamber bottom 216 has a larger taper angle than for a chamber bottom of convergent combustion. When not only the inclination of the chamber bottom 216 is important, but also the injectors 220 are present in reduced number and / or the combustion chamber 210 has a small diameter, it affects the distance between the chamber bottom and flat deflectors.
  • the geometry of the chamber bottom can also make difficult the necessary adjustments and tolerances between the bottom wall of the chamber and the baffles.
  • the optimal operation of the room is no longer ensured.
  • the variation of the clearance between the baffles on the one hand and the baffles and the bottom chamber on the other hand is large enough so that the solution using side walls along the radial edges of the deflectors is no longer satisfactory.
  • one of the longitudinal edges of two adjacent deflectors comprises a tab forming covers joint.
  • the present invention aims to propose an alternative to this solution.
  • a combustion chamber bottom deflector of a gas turbine engine comprising a wall portion with an opening for the passage of an injection system of the combustion chamber, two edges longitudinal and two transverse edges, characterized in that at least one of the longitudinal edges comprises a joint cover forming a groove forming a housing along said edge for an attached tongue or the edge of an adjacent deflector so as to render sealing the junction between said edge and the edge of an adjacent baffle.
  • the solution of the invention is thus to seal the space between the baffles so as not to be dependent on the geometry of the combustion chamber and the chamber bottom in particular and to be able to absorb the dimensional variations related to the operation of the baffle. the room between idle speed and full throttle.
  • the present invention also relates to a combustion chamber of an annular gas turbine engine comprising an outer wall, an inner wall, a wall connecting the two walls and constituting a chamber bottom, and a plurality of deflectors according to the invention. with a portion of wall parallel to the chamber bottom, reported in the bottom.
  • the deflector 10 comprises a flat portion 10a with a central opening 10b corresponding to the housing of a not shown injection system. On the figure 5 , the opening is bordered by a flange 10b1 with shoulder for fixing in the chamber bottom.
  • the deflector comprises two longitudinal edges which are oriented in a radial direction relative to the axis of the engine, when in position.
  • the longitudinal edge 10c and the edge 10d are rectilinear.
  • the deflector 10 also comprises two transverse edges 10e and 10f both rounded to follow the curvature of the combustion chamber and curved towards the interior of the combustion chamber for guiding the air.
  • the edge 10c left on the figure 4 , is rectilinear and follows the radial profile of the deflector.
  • the edge 10d on the other side comprises a rear recess with respect to the visible face on the figure 4 formed by a tongue 10d1 which extends the rear face of the wall of the baffle. This recess forms a longitudinal housing 10d10 for the edge 10'c of the adjacent deflector 10 '.
  • This deflector 10 ' is identical to the deflector 10. It comprises a flat portion 10'a, two longitudinal edges 10'c and 10'd and two transverse edges curved and curved 10'e and 10'f.
  • the edge 10'd comprises a longitudinal tab 10'd1 providing a housing 10'd10.
  • the baffles are all identical and are mounted on the periphery of the chamber bottom being fixed by the flanges of the openings for the injection systems.
  • the joint cover formed by the tongue 10d1 of each of the baffles covers the edge 10'c adjacent deflector 10 'over a width sufficient to accommodate variations in expansion of the combustion chamber.
  • Each housing 10d10, 10'd10 is arranged to retain the edge 10c, 10'c of the adjacent baffle such that leaks between two adjacent baffles are reduced or completely eliminated whatever the engine speed.
  • FIGS 7, 8 and 9 represent an embodiment according to the invention with a throat seal cover which improves the sealing with respect to the previous solution.
  • the deflectors 20, 20 ' are seen with a planar wall 20a, 20'a, a central opening 20b, 20'b two longitudinal edges 20c, 20'c and 20d, 20'd and two rounded and curved transverse edges 20e, 20'. e and 20f, 20'f.
  • the longitudinal edge 20d comprises a tongue 20d1 parallel to the wall of the baffle and providing a housing 20d10g in the form of a groove. This groove is arranged to cooperate with the edge 20'c of the adjacent deflector.
  • the edge 20'c forms a rear recess to engage in the groove 20d10g.
  • the game is enough to allow the expansion of the combustion chamber during different engine speeds while maintaining a sealing contact between the edge 20'c and the sides of the groove 20d10g.
  • baffles may all be identical or alternate: one with covers joined on both edges and the other with simple edges cooperating with the grooves of the edges with joint covers.
  • the Figures 10 and 11 show an improvement between the baffles and the chamber bottom.
  • the chamber floor 2 comprises a radial groove 2r in the area where the joint cover of the junction of the baffles is placed. This groove 2r allows to provide a sufficient air gap, when the covers joined are of a greater thickness than the clearance between the flat portion 20a of the deflector and the wall of the chamber bottom.
  • baffles 30, 30 ' with a flat wall 30a, 30'a, a central opening 30b, 30'b, two longitudinal edges 30c, 30'c and 30d, 30'd and two transverse edges curved and curved 30e, 30e and 30f, 30'f.
  • the two longitudinal edges 30c, 30d; 30'c, 30'd each comprise a tab 30c1, 30d1; 30'c1, 30'd1 parallel to the wall of the baffle and providing a housing 30c10g and 30d10g, 30'c10g, 304d10g shaped throat.
  • These grooves are arranged to cooperate with a metal insert tab 31.
  • the tongue is housed in the adjacent grooves 30d10g and 30'c10g.
  • the clearance is sufficient to allow the expansion of the combustion chamber during different engine speeds while maintaining a sealing contact between the edge 20'c and the sides of the groove 20d10g.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Supercharger (AREA)

Description

La présente invention se rapporte au domaine technique des chambres de combustion pour moteur à turbine à gaz. Elle vise en particulier le fond de chambre. Elle vise enfin un moteur à turbine à gaz tel qu'un turboréacteur équipé d'une telle chambre de combustion.The present invention relates to the technical field of combustion chambers for gas turbine engine. It is particularly aimed at the bedroom floor. Finally, it relates to a gas turbine engine such as a turbojet engine equipped with such a combustion chamber.

Dans tout ce qui suit, les termes « axial », « radial », « transversal » correspondent respectivement à une direction axiale, à une direction radiale, et à un plan transversal du moteur, et les termes « amont » et « aval » correspondent respectivement au sens de l'écoulement des gaz dans le moteur.In all that follows, the terms "axial", "radial", "transverse" correspond respectively to an axial direction, to a radial direction, and to a transverse plane of the engine, and the terms "upstream" and "downstream" correspond to respectively in the direction of the flow of gases in the engine.

Une chambre de combustion conventionnelle divergente est illustrée sur la figure 1, qui est une coupe axiale montrant une moitié de la chambre de combustion, l'autre moitié de celle-ci se déduisant par symétrie par rapport à l'axe du moteur (non représenté). La chambre de combustion 110 est logée dans une chambre de diffusion 130 qui est un espace annulaire défini entre un carter externe 132 et un carter interne 134, dans lequel est introduit un comburant, air ambiant, comprimé provenant en amont d'un compresseur (non représenté) par l'intermédiaire d'un conduit annulaire de diffusion 136.A divergent conventional combustion chamber is illustrated on the figure 1 , which is an axial section showing a half of the combustion chamber, the other half of which is deduced by symmetry with respect to the axis of the motor (not shown). The combustion chamber 110 is housed in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, into which is introduced an oxidant, ambient air, compressed coming upstream of a compressor (no represented) via an annular diffusion duct 136.

Cette chambre de combustion divergente 110 comporte deux parois concentriques : l'une externe 112 et l'autre interne 114, qui sont coaxiales et sensiblement coniques. Les parois s'évasent de l'amont vers l'aval. Les parois externe 112 et interne 114 de la chambre de combustion 110 sont reliées entre elles, vers l'amont de la chambre de combustion par un fond de chambre 116.This diverging combustion chamber 110 comprises two concentric walls: one external 112 and the other internal 114, which are coaxial and substantially conical. The walls widen from upstream to downstream. The outer 112 and inner 114 walls of the combustion chamber 110 are connected together, upstream of the combustion chamber by a chamber bottom 116.

Le fond de chambre 116 est une pièce annulaire tronconique, qui s'étend entre deux plans sensiblement transversaux en s'évasant de l'aval vers l'amont. Le fond de chambre 116 se raccorde à chacune des deux parois externe 112 et interne 114 de la chambre de combustion 110. Le fond de chambre 116 présente une faible conicité. Il est doté de systèmes d'injection 118 à travers lesquelles passent des injecteurs 120 qui introduisent du carburant à l'extrémité amont de la chambre de combustion 110 où se déroulent les réactions de combustion.The chamber bottom 116 is a frustoconical annular piece, which extends between two substantially transverse planes flaring from downstream to upstream. The chamber bottom 116 is connected to each of the two outer wall 112 and inner 114 of the combustion chamber 110. The chamber bottom 116 has a small taper. It is equipped with injection systems 118 through which pass injectors 120 which introduce fuel to the upstream end of the combustion chamber 110 where the combustion reactions take place.

Ces réactions de combustion ont pour effet de faire rayonner de la chaleur de l'aval vers l'amont en direction du fond de chambre 116. Ainsi en fonctionnement le fond de chambre est-il soumis à de fortes températures. Afin de le protéger, des écrans thermiques sectorisés, encore appelés déflecteurs 122 sont interposés entre le foyer et les parois du fond de chambre. Ces déflecteurs 122, dont un est représenté sur la figure 3 sont des plaques sensiblement planes fixées par brasage sur le fond de chambre 116 avec une ouverture centrale 122a pour le passage du système d'injection. Ils comprennent deux murets latéraux 122b 122c le long des bords radiaux, tournés vers la paroi du fond de chambre et deux languettes 122e 122f de guidage d'air le long des bords transversaux tournés vers le foyer et ménageant un espace avec les parois 114 et 112, interne respectivement externe, de la chambre. Les déflecteurs sont refroidis par les impacts de jets d'air de refroidissement pénétrant dans la chambre de combustion 110 à travers des orifices de refroidissement 124 percés dans le fond de chambre 116. L'air formant ces jets, s'écoulant de l'amont vers l'aval, est guidé par des carénages de chambre 126, traverse le fond de chambre 116 à travers les orifices de refroidissement, et vient impacter la face amont des déflecteurs 122. L'air est ensuite guidé radialement vers l'intérieur et l'extérieur du foyer pour initier le film de refroidissement des parois 114 et 112 respectivement.These combustion reactions have the effect of radiating heat downstream upstream towards the chamber bottom 116. Thus in operation the chamber bottom is subjected to high temperatures. In order to protect it, sectorized heat shields, also called deflectors 122 are interposed between the fireplace and the walls of the chamber bottom. These deflectors 122, one of which is shown on the figure 3 are substantially flat plates brazed to the chamber bottom 116 with a central opening 122a for the passage of the injection system. They comprise two lateral walls 122b 122c along the radial edges, turned towards the wall of the chamber bottom and two tongues 122e 122f for guiding air along the transverse edges facing the hearth and leaving a space with the walls 114 and 112 , internally respectively external, of the chamber. The baffles are cooled by the impacts of cooling air jets entering the combustion chamber 110 through cooling orifices 124 drilled in the chamber bottom 116. The air forming these jets, flowing from the upstream downstream, is guided by chamber shrouds 126, passes through the chamber bottom 116 through the cooling orifices, and impinges on the upstream face of the deflectors 122. The air is then guided radially inwards and outside the focus to initiate the cooling film of the walls 114 and 112 respectively.

Ce guidage le long des déflecteurs est assuré par les murets latéraux orientés radialement. Ces murets ont aussi une fonction d'étanchéité. En étant au contact ou en assurant un jeu minimal avec le fond de chambre, Ils empêchent l'air de venir s'immiscer entre deux déflecteurs adjacents, pénétrer dans le foyer et perturber la combustion. Ces perturbations ont une incidence sur la pollution et sont à éviter. En effet les performances en rejets de polluants, CO et CHx sont susceptibles d'être dégradées par l'introduction parasite de cet air froid particulièrement au régime de ralenti moteur où le jeu est plus important.This guidance along the baffles is provided by the side walls oriented radially. These walls also have a sealing function. By being in contact or by ensuring a minimum clearance with the chamber bottom, They prevent air from coming in between two adjacent baffles, enter the home and disrupt combustion. These disturbances affect pollution and should be avoided. Indeed, the pollutant discharge performance, CO and CHx are likely to be degraded by the parasitic introduction of this cold air particularly at engine idling speed where the game is more important.

Dans le cadre d'autres architectures de moteurs où le flux de gaz est globalement convergent entre la sortie du compresseur et l'entrée de la turbine, on dispose de chambres de combustion dites convergentes, les parois externe et interne de la chambre de combustion sont inclinées en s'évasant de l'aval vers l'amont, et non pas de l'amont vers l'aval comme avec les premières chambres de combustion mentionnées plus haut, dites divergentes. Ces chambres de combustion convergentes peuvent avoir un angle de cône plus important que l'angle de cône des chambres de combustion divergentes.In the context of other engine architectures where the flow of gas is generally convergent between the compressor outlet and the inlet of the turbine, there are so-called convergent combustion chambers, the outer and inner walls of the combustion chamber are inclined by widening from downstream to upstream, and not from upstream to downstream as with the first combustion chambers mentioned above, said divergent. These convergent combustion chambers may have a larger cone angle than the cone angle of the diverging combustion chambers.

Une inclinaison aussi importante de la chambre de combustion a des répercussions sur la conicité du fond de chambre et sur la position des déflecteurs par rapport au fond de chambre. Une telle chambre de combustion est partiellement illustrée à la figure 2, en coupe axiale. Sur cette figure apparaissent une direction axiale 100 parallèle à l'axe du turboréacteur, la direction principale 200 de la chambre de combustion 210, et l'angle α entre ces deux axes 100, 200. Du fait de l'inclinaison importante de la chambre de combustion 210, le fond de chambre 216 présente une conicité d'angle plus grand que pour un fond de chambre de combustion convergent. Lorsque non seulement l'inclinaison du fond de chambre 216 est importante, mais qu'aussi les injecteurs 220 sont présents en nombre réduit et/ou que la chambre de combustion 210 présente un faible diamètre, cela affecte la distance entre le fond de chambre et les déflecteurs plans.Such a large inclination of the combustion chamber affects the taper of the chamber bottom and the position of the baffles relative to the chamber bottom. Such a combustion chamber is partially illustrated at the figure 2 , in axial section. In this figure appear an axial direction 100 parallel to the axis of the turbojet, the main direction 200 of the combustion chamber 210, and the angle α between these two axes 100, 200. Due to the significant inclination of the chamber 200, the chamber bottom 216 has a larger taper angle than for a chamber bottom of convergent combustion. When not only the inclination of the chamber bottom 216 is important, but also the injectors 220 are present in reduced number and / or the combustion chamber 210 has a small diameter, it affects the distance between the chamber bottom and flat deflectors.

Ainsi la géométrie du fond de chambre peut aussi rendre difficile les ajustements et les tolérances nécessaires entre la paroi du fond de chambre et les déflecteurs. Le fonctionnement optimal de la chambre n'est plus assuré. La variation du jeu entre les déflecteurs d'une part et les déflecteurs et le fond de chambre d'autre part est suffisamment importante pour que la solution mettant en oeuvre des murets latéraux le long des bords radiaux des déflecteurs ne soit plus satisfaisante.Thus the geometry of the chamber bottom can also make difficult the necessary adjustments and tolerances between the bottom wall of the chamber and the baffles. The optimal operation of the room is no longer ensured. The variation of the clearance between the baffles on the one hand and the baffles and the bottom chamber on the other hand is large enough so that the solution using side walls along the radial edges of the deflectors is no longer satisfactory.

Pour remédier à ce problème, la demanderesse a proposé dans le document EP-A1-2012062 que l'un des bords longitudinaux de deux déflecteurs adjacents comporte une languette formant couvre joint.To remedy this problem, the plaintiff has proposed in the document EP-A1-2012062 that one of the longitudinal edges of two adjacent deflectors comprises a tab forming covers joint.

La présente invention a pour objectif de proposer une alternative à cette solution.The present invention aims to propose an alternative to this solution.

Conformément à l'invention on réalise un déflecteur de fond de chambre de combustion d'un moteur à turbine à gaz, comprenant une portion de paroi avec une ouverture pour le passage d'un système d'injection de la chambre de combustion, deux bords longitudinaux et deux bords transversaux, caractérisé par le fait qu'au moins l'un des bords longitudinaux comporte un couvre joint ménageant une gorge formant un logement le long dudit bord pour une languette rapportée ou le bord d'un déflecteur adjacent de façon à rendre étanche la jonction entre ledit bord et le bord d'un déflecteur adjacent.According to the invention there is provided a combustion chamber bottom deflector of a gas turbine engine, comprising a wall portion with an opening for the passage of an injection system of the combustion chamber, two edges longitudinal and two transverse edges, characterized in that at least one of the longitudinal edges comprises a joint cover forming a groove forming a housing along said edge for an attached tongue or the edge of an adjacent deflector so as to render sealing the junction between said edge and the edge of an adjacent baffle.

La solution de l'invention consiste donc à rendre étanche l'espace entre les déflecteurs de manière à ne pas être tributaire de la géométrie de la chambre de combustion et du fond de chambre en particulier et à pouvoir absorber les variations dimensionnelles liées au fonctionnement de la chambre entre le régime de ralenti et les pleins gaz.The solution of the invention is thus to seal the space between the baffles so as not to be dependent on the geometry of the combustion chamber and the chamber bottom in particular and to be able to absorb the dimensional variations related to the operation of the baffle. the room between idle speed and full throttle.

Différentes solutions sont proposées :

  • Les bords transversaux comprenant une portion de paroi incurvée, les logements sont ménagés également le long des bords longitudinaux de ladite portion incurvée.
  • Le déflecteur comprend un couvre joint le long d'un bord longitudinal et un bord sans couvre joint le long de l'autre bord longitudinal les deux bords étant complémentaires pour venir s'adapter à un bord d'un autre même déflecteur disposé bord à bord.
  • Le déflecteur comprend un couvre joint le long des deux bords longitudinaux.
  • Le déflecteur comprend deux bords longitudinaux complémentaires des couvre joints.
Different solutions are proposed:
  • The transverse edges comprising a curved wall portion, the housings are also formed along the longitudinal edges of said curved portion.
  • The deflector comprises a joint cover along a longitudinal edge and an edge without joint cover along the other longitudinal edge, the two edges being complementary to fit an edge of another same deflector disposed edge to edge .
  • The deflector comprises a joint cover along the two longitudinal edges.
  • The deflector comprises two longitudinal edges complementary to the joint covers.

La présente invention concerne également une chambre de combustion d'un moteur à turbine à gaz, annulaire comprenant une paroi externe, une paroi interne, une paroi reliant les deux parois et constituant un fond de chambre, et une pluralité de déflecteurs selon l'invention avec une portion de paroi parallèle au fond de chambre, rapportée dans le fond.The present invention also relates to a combustion chamber of an annular gas turbine engine comprising an outer wall, an inner wall, a wall connecting the two walls and constituting a chamber bottom, and a plurality of deflectors according to the invention. with a portion of wall parallel to the chamber bottom, reported in the bottom.

Selon les modes de réalisation :

  • Tous les déflecteurs sont identiques ou bien
  • les déflecteurs avec couvre joints alternent avec les déflecteurs sans couvre joint.
  • Le fond de chambre comprend des rainures radiales ménageant des entrefers entre le fond de chambre et les couvre joints.
  • La chambre de combustion est de type convergent.
According to the embodiments:
  • All baffles are identical or
  • the baffles with joint covers alternate with the baffles without joint covers.
  • The bottom chamber includes radial grooves leaving air gaps between the bottom chamber and the covers joint.
  • The combustion chamber is of convergent type.

D'autres caractéristiques et avantages ressortiront de la description qui suit de modes de réalisation de l'invention en référence aux dessins annexés sur lesquels :

  • La figure 1 représente en coupe axiale une moitié de chambre de combustion de type divergent en soi connue ;
  • La figure 2 représente en coupe axiale une moitié de chambre de combustion de type convergent en soi connue ;
  • La figure 3 montre un déflecteur de l'art antérieur utilisé pour la protection thermique de la paroi du fond de chambre de combustion ;
  • La figure 4 montre, vus depuis l'intérieur de la chambre de combustion, deux déflecteurs de protection thermique du fond de chambre de l'art antérieur;
  • La figure 5 montre l'autre face des déflecteurs de la figure 4;
  • La figure 6 montre le détail du couvre joint des déflecteurs des figures 4 et 5 ;
  • La figure 7 montre un mode de réalisation de l'étanchéité entre deux déflecteurs adjacents selon l'invention;
  • La figure 8 montre l'autre face des déflecteurs de la figure 7;
  • La figure 9 montre le détail du couvre joint des déflecteurs des figures 7 et 8 ;
  • La figure 10 est une vue montrant une rainure radiale ménagée dans la paroi du fond de chambre pour permettre la réalisation d'un entrefer entre la paroi du fond de chambre et le couvre joint des déflecteurs
  • La figure 11 montre, vu de dessus en direction radiale, l'entrefer entre la paroi du fond de chambre et le couvre joint à la liaison entre deux déflecteurs adjacents.
  • La figure 12 montre une variante de réalisation du couvre joint vue depuis l'intérieur de la chambre de combustion ;
  • La figure 13 montre le bord d'un déflecteur de la figure 12 avec une languette
  • La figure 14 montre le détail du couvre joint des figures 12 et 13.
Other features and advantages will emerge from the following description of embodiments of the invention with reference to the accompanying drawings, in which:
  • The figure 1 represents in axial section a divergent type of combustion chamber of known per se;
  • The figure 2 represents in axial section a combustion chamber of convergent type known per se;
  • The figure 3 shows a deflector of the prior art used for thermal protection of the wall of the combustion chamber bottom;
  • The figure 4 shows, seen from inside the combustion chamber, two thermal protection baffles of the chamber bottom of the prior art;
  • The figure 5 shows the other side of the deflectors of the figure 4 ;
  • The figure 6 shows the detail of the joint cover of the wind deflectors Figures 4 and 5 ;
  • The figure 7 shows an embodiment of the seal between two adjacent deflectors according to the invention;
  • The figure 8 shows the other side of the deflectors of the figure 7 ;
  • The figure 9 shows the detail of the joint cover of the wind deflectors Figures 7 and 8 ;
  • The figure 10 is a view showing a radial groove formed in the wall of the chamber bottom to allow the realization of an air gap between the wall of the chamber bottom and the joint cover of the baffles
  • The figure 11 shows, seen from above in the radial direction, the gap between the wall of the chamber bottom and the cover joined to the connection between two adjacent deflectors.
  • The figure 12 shows an alternative embodiment of the joint cover seen from inside the combustion chamber;
  • The figure 13 shows the edge of a deflector of the figure 12 with a tongue
  • The figure 14 shows the detail of the joint cover Figures 12 and 13 .

On se reporte maintenant aux figures 4 à 6 représentant un premier mode de réalisation de l'étanchéité entre deux déflecteurs 10 et 10' en matériau réfractaire disposés côte à côte sur le fond de chambre selon l'art antérieur. Le déflecteur 10 comprend une partie plane 10a avec une ouverture centrale 10b correspondant au logement d'un système d'injection non représenté. Sur la figure 5, l'ouverture est bordée d'une collerette 10b1 avec épaulement pour la fixation dans le fond de chambre. Le déflecteur comprend deux bords longitudinaux qui sont orientés selon une direction radiale par rapport à l'axe du moteur, lorsqu'il est en position. Le bord longitudinal 10c et le bord 10d sont rectilignes. Le déflecteur 10 comprend aussi deux bords transversaux 10e et 10f à la fois arrondis pour suivre la courbure de la chambre de combustion et incurvés en direction de l'intérieur de la chambre de combustion pour le guidage de l'air. Le bord 10c, à gauche sur la figure 4, est rectiligne et suit le profil radial du déflecteur. Le bord 10d de l'autre côté comprend un décrochement arrière par rapport à la face visible sur la figure 4, formé par une languette 10d1 qui prolonge la face arrière de la paroi du déflecteur. Ce décrochement forme un logement longitudinal 10d10 pour le bord 10'c du déflecteur adjacent 10'. Ce déflecteur 10' est identique au déflecteur 10. Il comprend une partie plane 10'a, deux bords longitudinaux 10'c et 10'd et deux bords transversaux arrondis et incurvés 10'e et 10'f. Le bord 10'd comprend une languette longitudinale 10'd1 ménageant un logement 10'd10.We now turn to Figures 4 to 6 representing a first embodiment of the seal between two baffles 10 and 10 'of refractory material arranged side by side on the chamber bottom according to the prior art. The deflector 10 comprises a flat portion 10a with a central opening 10b corresponding to the housing of a not shown injection system. On the figure 5 , the opening is bordered by a flange 10b1 with shoulder for fixing in the chamber bottom. The deflector comprises two longitudinal edges which are oriented in a radial direction relative to the axis of the engine, when in position. The longitudinal edge 10c and the edge 10d are rectilinear. The deflector 10 also comprises two transverse edges 10e and 10f both rounded to follow the curvature of the combustion chamber and curved towards the interior of the combustion chamber for guiding the air. The edge 10c, left on the figure 4 , is rectilinear and follows the radial profile of the deflector. The edge 10d on the other side comprises a rear recess with respect to the visible face on the figure 4 formed by a tongue 10d1 which extends the rear face of the wall of the baffle. This recess forms a longitudinal housing 10d10 for the edge 10'c of the adjacent deflector 10 '. This deflector 10 'is identical to the deflector 10. It comprises a flat portion 10'a, two longitudinal edges 10'c and 10'd and two transverse edges curved and curved 10'e and 10'f. The edge 10'd comprises a longitudinal tab 10'd1 providing a housing 10'd10.

Sur l'exemple des figures 4 à 6 les déflecteurs sont tous identiques et sont montés sur le pourtour du fond de chambre en étant fixé par les collerettes des ouvertures pour les systèmes d'injection. Il y a un système d'injection par déflecteur. Le couvre joint formé par la languette 10d1 de chacun des déflecteurs, recouvre le bord 10'c du déflecteur adjacent 10' sur une largeur suffisante pour s'accommoder des variations de dilatation de la chambre de combustion. Chaque logement 10d10, 10'd10 est agencé pour retenir le bord 10c, 10'c du déflecteur adjacent de telle manière que les fuites entre deux déflecteurs adjacents soient réduites sinon totalement éliminées quel que soit le régime moteur.On the example of Figures 4 to 6 the baffles are all identical and are mounted on the periphery of the chamber bottom being fixed by the flanges of the openings for the injection systems. There is a deflector injection system. The joint cover formed by the tongue 10d1 of each of the baffles, covers the edge 10'c adjacent deflector 10 'over a width sufficient to accommodate variations in expansion of the combustion chamber. Each housing 10d10, 10'd10 is arranged to retain the edge 10c, 10'c of the adjacent baffle such that leaks between two adjacent baffles are reduced or completely eliminated whatever the engine speed.

Dans la réalisation des figures 4 à 6 les déflecteurs sont identiques mais la solution comprend aussi le cas où un premier déflecteur comprend un couvre joint le long des deux bords longitudinaux coopérant avec les bords simples d'un second déflecteur sans couvre joint. L'efficacité est la même. Le montage est cependant différent et nécessite la fabrication de deux références de pièces.In the realization of Figures 4 to 6 the baffles are identical but the solution also includes the case where a first deflector comprises a joint cover along the two longitudinal edges cooperating with the single edges of a second deflector without joint cover. The effectiveness is the same. However, the assembly is different and requires the manufacture of two parts references.

Les figures 7, 8 et 9 représentent un mode de réalisation selon l'invention avec un couvre joint à gorge qui améliore l'étanchéité par rapport à la solution précédente.The Figures 7, 8 and 9 represent an embodiment according to the invention with a throat seal cover which improves the sealing with respect to the previous solution.

On voit les déflecteurs 20, 20' avec une paroi plane 20a, 20'a, une ouverture centrale 20b, 20'b deux bords longitudinaux 20c, 20'c et 20d, 20'd et deux bords transversaux arrondis et incurvés 20e, 20'e et 20f, 20'f. Le bord longitudinal 20d comprend une languette 20d1 parallèle à la paroi du déflecteur et ménageant un logement 20d10g en forme de gorge. Cette gorge est agencée de manière à coopérer avec le bord 20'c du déflecteur adjacent. Ici le bord 20'c forme un décrochement arrière pour venir s'engager dans la gorge 20d10g. Le jeu est suffisant pour permettre la dilation de la chambre de combustion pendant les différents régimes du moteur tout en conservant un contact d'étanchéité entre le bord 20'c et les flancs de la gorge 20d10g.The deflectors 20, 20 'are seen with a planar wall 20a, 20'a, a central opening 20b, 20'b two longitudinal edges 20c, 20'c and 20d, 20'd and two rounded and curved transverse edges 20e, 20'. e and 20f, 20'f. The longitudinal edge 20d comprises a tongue 20d1 parallel to the wall of the baffle and providing a housing 20d10g in the form of a groove. This groove is arranged to cooperate with the edge 20'c of the adjacent deflector. Here the edge 20'c forms a rear recess to engage in the groove 20d10g. The game is enough to allow the expansion of the combustion chamber during different engine speeds while maintaining a sealing contact between the edge 20'c and the sides of the groove 20d10g.

Comme dans la solution précédente les déflecteurs peuvent être tous identiques ou bien alterner : l'un avec des couvre joints sur les deux bords et l'autre avec des bords simples coopérant avec les gorges des bords à couvre joints.As in the previous solution the baffles may all be identical or alternate: one with covers joined on both edges and the other with simple edges cooperating with the grooves of the edges with joint covers.

Les figures 10 et 11 montrent une amélioration entre les déflecteurs et le fond de chambre. Le fond de chambre 2 comprend une rainure 2r radiale dans la zone où vient se placer le couvre joint de la jonction des déflecteurs. Cette rainure 2r permet de ménager un entrefer suffisant, lorsque les couvre joints sont d'une épaisseur plus importante que le jeu entre la partie plane 20a du déflecteur et la paroi du fond de chambre.The Figures 10 and 11 show an improvement between the baffles and the chamber bottom. The chamber floor 2 comprises a radial groove 2r in the area where the joint cover of the junction of the baffles is placed. This groove 2r allows to provide a sufficient air gap, when the covers joined are of a greater thickness than the clearance between the flat portion 20a of the deflector and the wall of the chamber bottom.

On a représenté une autre variante sur les figures 12, 13 et 14.Another variant on the Figures 12, 13 and 14 .

On voit les déflecteurs 30, 30' avec une paroi plane 30a, 30'a, une ouverture centrale 30b, 30'b, deux bords longitudinaux 30c, 30'c et 30d, 30'd et deux bords transversaux arrondis et incurvés 30e, 30'e et 30f, 30'f. Les deux bords longitudinaux 30c, 30d ; 30'c, 30'd comprennent chacun une languette 30c1, 30d1 ; 30'c1, 30'd1 parallèle à la paroi du déflecteur et ménageant un logement 30c10g et 30d10g, 30'c10g, 304d10g en forme de gorge. Ces gorges sont agencées de manière à coopérer avec une languette rapportée métallique 31. Ainsi la languette est logée dans les gorges adjacentes 30d10g et 30'c10g. Le jeu est suffisant pour permettre la dilation de la chambre de combustion pendant les différents régimes du moteur tout en conservant un contact d'étanchéité entre le bord 20'c et les flancs de la gorge 20d10g.We see the baffles 30, 30 'with a flat wall 30a, 30'a, a central opening 30b, 30'b, two longitudinal edges 30c, 30'c and 30d, 30'd and two transverse edges curved and curved 30e, 30e and 30f, 30'f. The two longitudinal edges 30c, 30d; 30'c, 30'd each comprise a tab 30c1, 30d1; 30'c1, 30'd1 parallel to the wall of the baffle and providing a housing 30c10g and 30d10g, 30'c10g, 304d10g shaped throat. These grooves are arranged to cooperate with a metal insert tab 31. Thus the tongue is housed in the adjacent grooves 30d10g and 30'c10g. The clearance is sufficient to allow the expansion of the combustion chamber during different engine speeds while maintaining a sealing contact between the edge 20'c and the sides of the groove 20d10g.

Claims (11)

  1. A baffle (10, 20, 30) for the bottom of a combustion chamber of a gas turbine engine, comprising a portion of wall (20a, 30) with an opening for an injector of the combustion chamber to pass through, two longitudinal edges (20c, 20d; 30c, 30d) and two transverse edges (20e, 20f; 30e, 30f), and wherein at least one of the longitudinal edges comprises a joint cover (10d1; 20d1; 30d1, 30'c1) characterized in that the joint cover arranges a groove (20d10g; 30d10g, 30'c10g) forming an housing along said edge for an insert tongue (31) or the edge (20'c) of an adjacent baffle (10'; 20'; 30') so as to seal the junction between the two edges while allowing them to slide relative to one another when the wall of the chamber bottom expands.
  2. The baffle as claimed in the preceding claims, wherein the transverse edges (20e, 20f; 30e, 30f) comprise a curved portion of wall, the groove being arranged equally along the longitudinal edges of said curved portion.
  3. The baffle ad claimed in one of the preceding claims, comprising a joint cover (10d1; 20d1) along a longitudinal edge and an edge (20c) without a joint cover along the other longitudinal edge, the two edges being matched in order to adapt to an edge of another same baffle placed edge-to-edge.
  4. The baffle as claimed in claim 1 or 2, comprising a joint cover along the two longitudinal edges.
  5. A combustion chamber of a gas turbine engine, being annular comprising an outer wall, an inner wall, a wall connecting the two walls and forming a chamber bottom, baffles (20; 30) as claimed in at least one of the preceding claims and comprising a portion of wall parallel to the chamber bottom, being fitted in the bottom.
  6. The combustion chamber as claimed in the preceding claim, with baffles as claimed in claim 3, all being identical.
  7. The combustion chamber as claimed in claim 5, with baffles as claimed in claim 4, all the baffles being identical, a metal tongue being housed in the grooves of the joint covers.
  8. The combustion chamber as claimed in claim 5 with baffles as claimed in claim 4 and baffles with simple edges comprising two longitudinal edges matching the joint covers of the baffle of claim 4.
  9. The combustion chamber as claimed in one of claims 5 to 8, wherein the chamber bottom comprises a channel arranging an air gap between the chamber bottom and the joint covers.
  10. A chamber of the convergent type as claimed in one of claims 5 to 9.
  11. A gas turbine engine comprising a combustion chamber (10) as claimed in any one of claims 5 to 10.
EP08159737.9A 2007-07-05 2008-07-04 Combustion chamber of a gas turbine engine Active EP2012061B2 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0704869A FR2918444B1 (en) 2007-07-05 2007-07-05 CHAMBER BOTTOM DEFLECTOR, COMBUSTION CHAMBER COMPRISING SAME, AND GAS TURBINE ENGINE WHERE IT IS EQUIPPED

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EP2012061A1 EP2012061A1 (en) 2009-01-07
EP2012061B1 true EP2012061B1 (en) 2016-12-07
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EP (1) EP2012061B2 (en)
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Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2943403B1 (en) 2009-03-17 2014-11-14 Snecma TURBOMACHINE COMBUSTION CHAMBER COMPRISING IMPROVED AIR SUPPLY MEANS
CH704185A1 (en) * 2010-12-06 2012-06-15 Alstom Technology Ltd GAS TURBINE AND METHOD FOR recondition SUCH GAS TURBINE.
EP2954261B1 (en) * 2013-02-08 2020-03-04 United Technologies Corporation Gas turbine engine combustor
US9534784B2 (en) * 2013-08-23 2017-01-03 Pratt & Whitney Canada Corp. Asymmetric combustor heat shield panels
US8984896B2 (en) * 2013-08-23 2015-03-24 Pratt & Whitney Canada Corp. Interlocking combustor heat shield panels
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment
US10041679B2 (en) * 2015-06-24 2018-08-07 Delavan Inc Combustion systems
US10739001B2 (en) 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
FR3064050B1 (en) 2017-03-14 2021-02-19 Safran Aircraft Engines TURBOMACHINE COMBUSTION CHAMBER
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
FR3078384B1 (en) * 2018-02-28 2021-05-28 Safran Aircraft Engines DOUBLE BOTTOM COMBUSTION CHAMBER
FR3081974B1 (en) 2018-06-04 2020-06-19 Safran Aircraft Engines COMBUSTION CHAMBER OF A TURBOMACHINE
US11408609B2 (en) * 2018-10-26 2022-08-09 Collins Engine Nozzles, Inc. Combustor dome tiles
US11143108B2 (en) 2019-03-07 2021-10-12 Pratt & Whitney Canada Corp. Annular heat shield assembly for combustor
US11226099B2 (en) * 2019-10-11 2022-01-18 Rolls-Royce Corporation Combustor liner for a gas turbine engine with ceramic matrix composite components
US12209750B2 (en) * 2023-02-14 2025-01-28 Collins Engine Nozzles, Inc. Line replaceable fuel injector panels with single hatch installation

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2012062A1 (en) * 2007-07-04 2009-01-07 Snecma Combustion chamber comprising deflectors for thermal protection of the chamber dome and gas turbine engine equipped with same

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US4180974A (en) * 1977-10-31 1980-01-01 General Electric Company Combustor dome sleeve
JPS5915728A (en) * 1982-07-19 1984-01-26 Central Res Inst Of Electric Power Ind Heat shield construction of wall surface exposed to high heating temperature
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
SU1753783A1 (en) * 1990-02-27 1996-06-10 Моторостроительное конструкторское бюро Combustion chamber of gas turbine engine
GB2247522B (en) * 1990-09-01 1993-11-10 Rolls Royce Plc Gas turbine engine combustor
CA2070518C (en) * 1991-07-01 2001-10-02 Adrian Mark Ablett Combustor dome assembly
DE59205187D1 (en) * 1992-10-05 1996-03-07 Asea Brown Boveri Guide blade attachment for axially flow-through turbomachine
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
GB2298267B (en) * 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
EP1118806A1 (en) * 2000-01-20 2001-07-25 Siemens Aktiengesellschaft Thermally charged wall structure and method to seal gaps in such a structure
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
US7121095B2 (en) * 2003-08-11 2006-10-17 General Electric Company Combustor dome assembly of a gas turbine engine having improved deflector plates
EP1528343A1 (en) * 2003-10-27 2005-05-04 Siemens Aktiengesellschaft Refractory tile with reinforcing members embedded therein, as liner for gas turbine combustion chamber
JP4476152B2 (en) * 2005-04-01 2010-06-09 三菱重工業株式会社 Gas turbine combustor
FR2897417A1 (en) * 2006-02-10 2007-08-17 Snecma Sa ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE
FR2914399B1 (en) * 2007-03-27 2009-10-02 Snecma Sa FURNITURE FOR BOTTOM OF COMBUSTION CHAMBER.

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2012062A1 (en) * 2007-07-04 2009-01-07 Snecma Combustion chamber comprising deflectors for thermal protection of the chamber dome and gas turbine engine equipped with same

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CA2636659A1 (en) 2009-01-05
FR2918444A1 (en) 2009-01-09
EP2012061A1 (en) 2009-01-07
US20130312420A1 (en) 2013-11-28
US20090019856A1 (en) 2009-01-22
EP2012061B2 (en) 2020-06-17
CA2636659C (en) 2015-10-27
FR2918444B1 (en) 2013-06-28
RU2498162C2 (en) 2013-11-10
US8683806B2 (en) 2014-04-01
RU2008127426A (en) 2010-01-10

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