EP1939528B1 - Deflector for the bottom of a combustion chamber, combustion chamber equipped with same and jet engine comprising them - Google Patents

Deflector for the bottom of a combustion chamber, combustion chamber equipped with same and jet engine comprising them Download PDF

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Publication number
EP1939528B1
EP1939528B1 EP07122639.3A EP07122639A EP1939528B1 EP 1939528 B1 EP1939528 B1 EP 1939528B1 EP 07122639 A EP07122639 A EP 07122639A EP 1939528 B1 EP1939528 B1 EP 1939528B1
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EP
European Patent Office
Prior art keywords
deflector
combustion chamber
sides
chamber
central region
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EP07122639.3A
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German (de)
French (fr)
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EP1939528A1 (en
Inventor
Patrice Commaret
Didier Hernandez
David Locatelli
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Safran Aircraft Engines SAS
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SNECMA Services SA
SNECMA SAS
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Publication of EP1939528A1 publication Critical patent/EP1939528A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures

Definitions

  • the present invention relates to the technical field of combustion chambers for turbojet engines.
  • it relates to a thermal protection screen, or baffle, for a combustion chamber bottom. It also aims a combustion chamber with at least one such deflector.
  • a turbojet engine equipped with such a combustion chamber and / or at least one such deflector.
  • a conventional combustion chamber, called divergent, is illustrated on the figure 11 , 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 (not shown) of the turbojet engine.
  • the combustion chamber 110 is comprised in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, into which a compressed oxidant originating upstream of a compressor (not shown) by the compressor is introduced. intermediate of an annular diffusion duct 136.
  • said divergent 110 has an outer wall 112 and an inner wall 114, which are coaxial and substantially conical, and which flare from upstream to downstream with a cone angle ⁇ .
  • the outer 112 and inner 114 walls of the combustion chamber 110 are interconnected upstream of the combustion chamber by a chamber bottom 116.
  • the chamber bottom 116 is a substantially frustoconical 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 112 and inner 114 walls of the combustion chamber 110. Due to the small inclination of the combustion chamber 110, the chamber bottom 116 has a small taper. It has 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.
  • thermal protection screens also called deflectors 122.
  • deflectors 122 are substantially flat plates arranged and brazed on an inner face of the chamber bottom 116. They are cooled by means of cooling air jets entering the chamber of combustion 110 through cooling orifices 124 drilled in the chamber bottom 116. These air jets, flowing from upstream to downstream, are guided by chamber fairings 126, through the chamber bottom 116 through the cooling orifices 124, and impact an upstream face of the deflectors 122.
  • so-called convergent combustion chambers the outer and inner walls of the combustion chamber are inclined flaring from downstream to upstream, and not from upstream to downstream as with the conventional combustion chambers, said divergent, previously described.
  • These so-called convergent combustion chambers may have a cone angle ⁇ greater than the cone angle ⁇ of the so-called 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 12 , 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 110, and the angle ⁇ between these two axes 100, 200. Due to the significant inclination of the chamber 110, the chamber bottom 116 has a larger conicity than a traditional combustion chamber bottom. When not only the inclination of the chamber bottom 116 is important, but also the injectors 120 are present in reduced number and / or the combustion chamber 110 has a small diameter, it affects the distance D between the chamber bottom and the flat deflectors.
  • the object of the invention is to remedy these drawbacks, and proposes a thermal protection screen for chamber bottom, or deflector, which is configured in such a way that the distance D between the chamber bottom and this deflector remains constant.
  • the invention relates to a deflector for a chamber bottom of a combustion chamber of a turbojet, in the form of a plate with a hole.
  • said plate is a portion of a conical surface of revolution about a cone axis, said plate having a substantially concave face and a substantially convex face, and said plate having a contour that has four sides, among which two first sides are concentric circle arcs and centered on said cone axis, and two second sides are generator segments of said cone which connect said first sides.
  • Said deflector further comprises a central zone which surrounds said hole and a peripheral zone which surrounds said central zone, said central zone having a plane face on the side of said concave face.
  • said central zone is substantially circular.
  • said deflector has a connection zone between said peripheral zone and said central zone.
  • said central zone is a plane portion delimited by two edges which are segments of generatrices of said cone parallel to said second sides.
  • said first sides of the plate forming the baffle are each provided with a flange extending on the side of the concave face of the baffle.
  • said deflector is furthermore provided with angular positioning means.
  • said angular positioning means comprise a locking groove for receiving a locking key.
  • they also comprise a locking key intended to cooperate with a locking groove formed on said deflector.
  • the invention relates to a combustion chamber which has at least one deflector according to the first aspect.
  • said deflector is soldered to the chamber bottom.
  • Said combustion chamber further comprises angular positioning means.
  • Said angular positioning means comprise a first locking groove for receiving a locking key. They comprise, in addition, a second locking groove for cooperating with a stop finger.
  • said combustion chamber is a so-called convergent combustion chamber, having a coaxial and substantially frustoconical outer wall and inner wall which are inclined flaring from downstream to upstream.
  • the invention relates to a turbojet, which comprises a combustion chamber according to the first aspect and / or at least one deflector according to the second aspect.
  • FIG. 1 there is shown a portion of a turbojet engine 2 extending in an axial direction 100 and equipped with a combustion chamber 10.
  • This combustion chamber 10 said convergent, comprises an outer wall 12 and an inner wall 14, which are coaxial and substantially frustoconical.
  • the combustion chamber 10 is comprised in a diffusion chamber 30 which is an annular space defined between an outer casing 32 and an inner casing 34, into which a compressed oxidant originating upstream of a compressor (not shown) by the compressor is introduced. intermediate of an annular diffusion duct 36.
  • the outer 12 and inner 14 walls of the combustion chamber 10 are connected to each other upstream of the combustion chamber by a chamber bottom 16, which is a substantially frustoconical piece extending between two substantially transverse planes in s'. flaring from upstream to downstream.
  • the chamber bottom 16 is connected to each of the two outer walls 12 and inner 14 of the combustion chamber 10. It is provided with injection systems 18 through which pass injectors 20 which pass through the outer casing 32 and which introduce fuel at the upstream end of the combustion chamber 10 where the combustion reactions take place.
  • a deflector 22 is shown diagrammatically and in perspective at the figure 2 .
  • This deflector 22 is in the form of a plate which is a portion of a conical surface of a cone, this cone having a cone axis 300 and a cone angle ⁇ .
  • said cone axis 300 is substantially coincident with the axis 100 of the turbojet engine.
  • the deflector 22 has a concave face 62 and a convex face 64, and a contour having four sides 72, 74, 76, 78. Two 72, 76 of these four sides are concentric parallel circular arcs of the same axis 300.
  • the other two 74, 78 of these four sides are segments of generators of the cone, which connect the two sides 72, 76 in arcs.
  • the deflector 22 according to the embodiment comprises an injection hole 40, substantially central, intended to be opposite an injection system 18 of the chamber bottom 16 when the deflector 22 is installed on the chamber floor 16 Said injection hole 40 is a hole with a fallen edge, that is to say it has an edge 402 rising on the side of the upstream face of the deflector 22.
  • FIG 3 illustrates a portion of the chamber bottom 16 in the vicinity of an injection system 18 in which is disposed an injection bowl 206.
  • the chamber bottom 16 has a large conicity (see figure 1 ).
  • the deflector 22 is arranged parallel to the chamber bottom 16, on the inside of the combustion chamber 10. Due to the conical curvature of the deflector 22, which is similar to the conical curvature of the chamber bottom 16, said deflector 22 is parallel to said chamber bottom 16.
  • An advantage of such a deflector 22 lies in the fact that the distance D between said deflector 22 and the chamber bottom 16 is substantially constant for the entire surface of said deflector 22. As a result, such a deflector 22 can be cooled satisfactorily by air streams which impact after passing through cooling orifices 24 formed in the chamber bottom 16.
  • the figure 3 also shows the relative position of the deflector 22 with respect to the injection bowl 206.
  • the injection bowl 206 is oriented around an axis 200. It comprises a flange 208 which itself comprises a fastening flange 210 which is retained axially between a first ring 50 and the injection hole 40 of the deflector 22 and the edge 402 of the injection hole 40 of the deflector 22.
  • the chamber bottom 16 is locked between an outer shoulder 226 of the edge 402 of the injection hole 40 of the deflector 22 and a second ring 52 which is itself fixed by brazing in an outer peripheral groove 404 of the edge 402 of the injection hole 40 of the deflector 22.
  • the second ring 52 also has an inner shoulder in which fits the first ring 50, the two rings 50, 52 being fixed together by a weld bead 54.
  • This assembly is such that the flange 208 is allowed to move slightly in a plane perpendicular to the axis 200.
  • the injection bowl 206 is allowed to a slight clearance transverse to the axis 200, which allows the entry of air threads through the injection hole 40 even when the injection bowl 206 is in place.
  • These air streams represented by the arrows 60 in the figures, have the function of cooling the edge 402 of the injection hole 40 of the deflector 22, this edge 402 constituting a relatively thick zone of the deflector 22 which can not be reached by the cooling air passing through the cooling orifices 24 of the chamber bottom 16.
  • the injection bowl 206 also has a flange 220 located inside the combustion chamber 10 which is separated from the flange 208 by a groove 222, and which extends parallel to the fastening flange 210 substantially until aplomb of the inner face of the edge 402 of the injection hole 40 of the deflector 22.
  • the figure 4 shows an enlarged detail of the figure 3 . More specifically, it shows the edge 402 of the injection hole 40 of the deflector 22 and the flange 208, the flange 220 and the groove 222 of the injection bowl 206. It appears that, due to the shape conical, and not planar, deflector 22, the inner face of the deflector 22 is offset from the inner face of the flange 208. This shift, or walk, is designated by the letter M to the figure 4 . The existence of this step M is likely to create a disturbance of the flow of the cooling jets represented by the arrow 60, for example in the form of vortices, which is likely to affect the cooling of the falling edge 402 of the hole d injection 40 of the deflector 22.
  • FIGS 7-8 and 9-10 represent respectively a first variant and a second variant of an embodiment of the deflector 22, which constitutes an improvement of the first embodiment described above.
  • the characteristics of the embodiment of the deflector 22 already described are also characteristics of the two variants of the embodiment illustrated in these embodiments.
  • Figures 7 to 10 are also characteristics of the two variants of the embodiment illustrated in these embodiments.
  • the deflector 22 has a central zone 90 which surrounds the injection hole 40, and a peripheral zone 92 which surrounds the central zone 90 to the edges 72, 74, 76, 78 of the deflector 22.
  • the peripheral zone 92 has a concave conical surface.
  • said central zone 90 is circular and has a flat surface, while the peripheral zone 92 has a concave conical surface.
  • a connection zone 94 connects said central zone 90 and said peripheral zone 92.
  • said central zone 90 is between two edges 96, 98 substantially parallel to the straight sides 74, 78 of the contour of said deflector 22, and extends to the arcuate sides 72, 76 of the contour of said deflector 22. It has a flat surface.
  • the two edges 96, 98 materialize the intersection between the flat surface of said central zone 90 and the concave conical surface of the peripheral zone 92.
  • the central zone 90 has a planar surface on the concavity side of the deflector 22.
  • the distance D between said deflector 22 and the chamber bottom 16 is substantially constant for the entire surface of said deflector 22.
  • the deflector 22 can be cooled satisfactorily by air streams which come to impact after passing through cooling orifices 24 arranged in the chamber bottom 16.
  • the cooling air streams 60 may flow from outside the bowl 206 through the injection opening 40 without being disturbed by turbulence. It follows that the cooling of the dropped edge 402 of the injection hole 40 of the deflector 22 can be satisfactorily performed.
  • the flat surface of the central zone 90 and the inner face of the flange 208 of the bowl 206 are substantially in the same plane.
  • the two arcuate sides 72, 76 of the plate forming the deflector 22 are each provided with a flange 80 extending on the side of the concave face 62 of the baffle. This characteristic is common to the embodiments.
  • the flanges 80 of the deflector 22 have the function of creating a cooling film by guiding the cooling air of the deflectors 22 which is coming from the cooling orifices 24, in order to cool the outer 12 and inner 14 walls of the combustion chamber 10 .
  • the deflector 22 is provided with angular positioning means consisting of first angular positioning means and second angular positioning means. This characteristic is common embodiments.
  • the figure 6 illustrates the first angular positioning means 82, 84 which comprise a first locking groove 82 having three sections formed respectively in the chamber bottom 16, the deflector 22 and the second ring 52 and a key 84.
  • the insertion of the key 84 in said first locking groove 82 prevents relative rotation of the second ring 52 and the deflector 22 with respect to the chamber bottom 16.
  • the figure 5 illustrates the second angular positioning means 86, 88 which comprise a second locking groove 86 formed in the second ring 52 and a stop pin 88 integral with the injection bowl 206, the insertion of the finger stop 88 in said second locking groove 86 prevents relative rotation of the injection bowl 206 relative to the second ring 52.
  • the invention also relates to a combustion chamber 10 which comprises a chamber bottom 16 and at least one deflector 22 as previously described.
  • said deflector 22 is brazed to said chamber bottom 16.

Description

La présente invention se rapporte au domaine technique des chambres de combustion pour turboréacteurs. Elle vise en particulier un écran de protection thermique, ou déflecteur, pour un fond de chambre de combustion. Elle vise aussi une chambre de combustion dotée d'au moins un tel déflecteur. Elle vise enfin un turboréacteur équipé d'une telle chambre de combustion et/ou d'au moins un tel déflecteur.The present invention relates to the technical field of combustion chambers for turbojet engines. In particular, it relates to a thermal protection screen, or baffle, for a combustion chamber bottom. It also aims a combustion chamber with at least one such deflector. Finally, it relates to a turbojet engine equipped with such a combustion chamber and / or at least one such deflector.

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 turboréacteur, et les termes « amont » et « aval » correspondent respectivement au sens de l'écoulement des gaz dans le turboréacteur.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 turbojet, and the terms "upstream" and "downstream" correspond to respectively in the direction of the flow of gas in the turbojet engine.

Une chambre de combustion conventionnelle, dite divergente, est illustrée sur la figure 11, 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 (non représenté) du turboréacteur. La chambre de combustion 110 est comprise 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 comprimé provenant en amont d'un compresseur (non représenté) par l'intermédiaire d'un conduit annulaire de diffusion 136.A conventional combustion chamber, called divergent, is illustrated on the figure 11 , 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 (not shown) of the turbojet engine. The combustion chamber 110 is comprised in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, into which a compressed oxidant originating upstream of a compressor (not shown) by the compressor is introduced. intermediate of an annular diffusion duct 136.

Cette chambre de combustion conventionnelle, dite divergente 110 comporte une paroi externe 112 et une paroi interne 114, qui sont coaxiales et sensiblement coniques, et qui s'évasent de l'amont vers l'aval avec un angle de cône α. 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 conventional combustion chamber, said divergent 110 has an outer wall 112 and an inner wall 114, which are coaxial and substantially conical, and which flare from upstream to downstream with a cone angle α. The outer 112 and inner 114 walls of the combustion chamber 110 are interconnected upstream of the combustion chamber by a chamber bottom 116.

Le fond de chambre 116 est une pièce sensiblement 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. Du fait de la faible inclinaison 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 substantially frustoconical 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 112 and inner 114 walls of the combustion chamber 110. Due to the small inclination of the combustion chamber 110, the chamber bottom 116 has a small taper. It has 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. Afin d'éviter un endommagement de ce fond de chambre 116, dû à la chaleur, il est prévu des écrans de protection thermique encore appelés déflecteurs 122. Ces déflecteurs 122 sont des plaques sensiblement planes disposées et fixées par brasage sur une face intérieure du fond de chambre 116. Ils sont refroidis au moyen 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. Ces jets d'air, s'écoulant de l'amont vers l'aval, sont guidés par des carénages de chambre 126, traversent le fond de chambre 116 à travers les orifices de refroidissement 124, et viennent impacter une face amont des déflecteurs 122.These combustion reactions have the effect of radiating heat downstream upstream towards the chamber bottom 116. In order to avoid damage to the chamber bottom 116, due to the heat, it is provided thermal protection screens also called deflectors 122. These deflectors 122 are substantially flat plates arranged and brazed on an inner face of the chamber bottom 116. They are cooled by means of cooling air jets entering the chamber of combustion 110 through cooling orifices 124 drilled in the chamber bottom 116. These air jets, flowing from upstream to downstream, are guided by chamber fairings 126, through the chamber bottom 116 through the cooling orifices 124, and impact an upstream face of the deflectors 122.

Dans des conceptions plus récentes 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 chambres de combustion conventionnelles, dites divergentes, précédemment décrites. Ces chambres de combustion dites convergentes peuvent avoir un angle de cône α plus important que l'angle de cône α des chambres de combustion dites divergentes.In more recent designs of so-called convergent combustion chambers, the outer and inner walls of the combustion chamber are inclined flaring from downstream to upstream, and not from upstream to downstream as with the conventional combustion chambers, said divergent, previously described. These so-called convergent combustion chambers may have a cone angle α greater than the cone angle α of the so-called 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 12, 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 110, et l'angle α entre ces deux axes 100, 200. Du fait de l'inclinaison importante de la chambre de combustion 110, le fond de chambre 116 présente une conicité plus importante qu'un fond de chambre de combustion traditionnelle. Lorsque non seulement l'inclinaison du fond de chambre 116 est importante, mais qu'aussi les injecteurs 120 sont présents en nombre réduit et/ou que la chambre de combustion 110 présente un faible diamètre, cela affecte la distance D entre le fond de chambre et les déflecteurs plans. Dans le plan de la coupe axiale de la figure 12, la distance D entre le fond de chambre 116 et les déflecteurs 122 apparaît comme étant constante. En revanche, comme illustré sur la figure 13, qui est une coupe suivant le plan XIII-XIII de la figure 12, cette distance D s'amenuise en parcourant une génératrice circonférentielle du fond de chambre 116, à un point tel que le fond de chambre 116 et les déflecteurs 122 peuvent entrer en contact. Un tel contact entre ces pièces est préjudiciable à un montage correct des déflecteurs dans la chambre de combustion. Le fait que la distance D entre le fond de chambre 116 et le déflecteur 122 n'est pas constante est préjudiciable à un bon refroidissement dudit déflecteur 122.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 12 , 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 110, and the angle α between these two axes 100, 200. Due to the significant inclination of the chamber 110, the chamber bottom 116 has a larger conicity than a traditional combustion chamber bottom. When not only the inclination of the chamber bottom 116 is important, but also the injectors 120 are present in reduced number and / or the combustion chamber 110 has a small diameter, it affects the distance D between the chamber bottom and the flat deflectors. In the plane of the axial section of the figure 12 the distance D between the chamber bottom 116 and the deflectors 122 appears to be constant. On the other hand, as illustrated on the figure 13 , which is a section along the XIII-XIII plane of the figure 12 this distance D diminishes by traversing a circumferential generatrix of the chamber bottom 116, to such a point that the chamber bottom 116 and the deflectors 122 can come into contact. Such contact between these parts is detrimental to a correct mounting of the baffles in the combustion chamber. The fact that the distance D between the chamber bottom 116 and the deflector 122 is not constant is detrimental to a good cooling of said deflector 122.

Le document EP 1 584 871 décrit des déflecteurs pour chambre de combustion de turbine à gaz.The document EP 1,584,871 discloses deflectors for gas turbine combustion chamber.

L'invention a pour but de remédier à ces inconvénients, et propose un écran de protection thermique pour fond de chambre, ou déflecteur, qui soit configuré de telle manière que la distance D entre le fond de chambre et ce déflecteur reste constante.The object of the invention is to remedy these drawbacks, and proposes a thermal protection screen for chamber bottom, or deflector, which is configured in such a way that the distance D between the chamber bottom and this deflector remains constant.

Selon un premier aspect, l'invention se rapporte à un déflecteur pour un fond de chambre d'une chambre de combustion d'un turboréacteur, se présentant sous la forme d'une plaque dotée d'un trou.According to a first aspect, the invention relates to a deflector for a chamber bottom of a combustion chamber of a turbojet, in the form of a plate with a hole.

Selon un mode de réalisation, ladite plaque est une portion d'une surface conique de révolution autour d'un axe de cône, ladite plaque ayant une face sensiblement concave et une face sensiblement convexe, et ladite plaque ayant un contour qui possède quatre côtés, parmi lesquels deux premiers côtés sont des arcs de cercles concentriques et centrés sur ledit axe de cône, et deux deuxièmes côtés sont des segments de génératrices dudit cône qui relient lesdits premiers côtés. Ledit déflecteur comporte en outre, une zone centrale qui entoure ledit trou et une zone périphérique qui entoure ladite zone centrale, ladite zone centrale ayant une face plane du côté de ladite face concave.According to one embodiment, said plate is a portion of a conical surface of revolution about a cone axis, said plate having a substantially concave face and a substantially convex face, and said plate having a contour that has four sides, among which two first sides are concentric circle arcs and centered on said cone axis, and two second sides are generator segments of said cone which connect said first sides. Said deflector further comprises a central zone which surrounds said hole and a peripheral zone which surrounds said central zone, said central zone having a plane face on the side of said concave face.

Selon une première variante de réalisation, ladite zone centrale est sensiblement circulaire. Selon cette première variante ledit déflecteur présente une zone de raccordement entre ladite zone périphérique et ladite zone centrale.According to a first embodiment, said central zone is substantially circular. According to this first variant, said deflector has a connection zone between said peripheral zone and said central zone.

Selon une deuxième variante du mode de réalisation, ladite zone centrale est une portion de plan délimitée par deux arêtes qui sont des segments de génératrices dudit cône parallèles auxdits deuxièmes côtés.According to a second variant of the embodiment, said central zone is a plane portion delimited by two edges which are segments of generatrices of said cone parallel to said second sides.

De manière commune au premier mode de réalisation et aux deux variantes du mode de réalisation, lesdits premiers côtés de la plaque formant le déflecteur sont dotés chacun d'un rebord s'étendant du côté de la face concave du déflecteur.In a common manner to the first embodiment and to both variants of the embodiment, said first sides of the plate forming the baffle are each provided with a flange extending on the side of the concave face of the baffle.

De manière commune au premier mode de réalisation et aux deux variantes du mode de réalisation, ledit déflecteur est, en outre, doté de moyens de positionnement angulaire. Selon une forme de réalisation, lesdits moyens de positionnement angulaire comportent une rainure de blocage destinée à recevoir une clavette de blocage. Selon cette même forme de réalisation, ils comportent également une clavette de blocage destinée à coopérer avec une rainure de blocage ménagée sur ledit déflecteur.In common with the first embodiment and the two variants of the embodiment, said deflector is furthermore provided with angular positioning means. According to one embodiment, said angular positioning means comprise a locking groove for receiving a locking key. According to this same embodiment, they also comprise a locking key intended to cooperate with a locking groove formed on said deflector.

Selon un deuxième aspect, l'invention se rapporte à une chambre de combustion qui possède au moins un déflecteur selon le premier aspect.According to a second aspect, the invention relates to a combustion chamber which has at least one deflector according to the first aspect.

De préférence, ledit déflecteur est fixé par brasage sur le fond de chambre.Preferably, said deflector is soldered to the chamber bottom.

Ladite chambre de combustion comporte, en outre, des moyens de positionnement angulaire. Lesdits moyens de positionnement angulaire comportent une première rainure de blocage destinée à recevoir une clavette de blocage. Ils comportent, en outre, une deuxième rainure de blocage destinée à coopérer avec un doigt d'arrêt.Said combustion chamber further comprises angular positioning means. Said angular positioning means comprise a first locking groove for receiving a locking key. They comprise, in addition, a second locking groove for cooperating with a stop finger.

De préférence, ladite chambre de combustion est une chambre de combustion dite convergente, ayant une paroi externe et une paroi interne coaxiales et sensiblement tronconiques qui sont inclinées en s'évasant de l'aval vers l'amont.Preferably, said combustion chamber is a so-called convergent combustion chamber, having a coaxial and substantially frustoconical outer wall and inner wall which are inclined flaring from downstream to upstream.

Selon un troisième aspect, l'invention se rapporte à un turboréacteur, qui comporte une chambre de combustion selon le premier aspect et/ou au moins un déflecteur selon le deuxième aspect.According to a third aspect, the invention relates to a turbojet, which comprises a combustion chamber according to the first aspect and / or at least one deflector according to the second aspect.

L'invention sera mieux comprise à la lecture de la description détaillée qui va suivre, d'un mode de réalisation particulier de l'invention, fourni à titre indicatif et nullement limitatif, et illustré au moyen des dessins annexés, dans lesquels :

  • la figure 1 est une vue en coupe axiale d'une partie de turboréacteur dont la chambre de combustion dite convergente, montrant une moitié de la chambre de combustion, l'autre moitié se déduisant par symétrie axiale ;
  • la figure 2 représente en perspective et de façon schématique un déflecteur selon l'invention ;
  • la figure 3 représente, en coupe axiale, une partie de chambre de combustion dite convergente ainsi qu'un déflecteur selon un mode de réalisation de l'invention, vus en coupe axiale ;
  • la figure 4 est une vue agrandie d'un détail de la figure 3 ;
  • la figure 5 est analogue à la figure 3, pour un autre mode de réalisation de l'invention, vus en coupe axiale, et montre des premiers moyens de positionnement angulaire ;
  • la figure 6 représente, en coupe axiale, d'autres moyens de positionnement angulaire ;
  • la figure 7 est une vue en perspective d'une première variante du mode de réalisation ;
  • la figure 8 est une vue en coupe selon le plan VIII-VIII de la figure 7 ;
  • la figure 9 est une vue en perspective d'une deuxième variante du mode de réalisation ;
  • la figure 10 est une vue en coupe selon le plan X-X de la figure 9 ;
  • la figure 11, déjà décrite, est une vue en coupe axiale d'une chambre de combustion de la technique antérieure dite divergente ;
  • la figure 12, déjà décrite, représente à plus grande échelle, une partie de chambre de combustion dite convergente, ainsi qu'un déflecteur plan de la technique antérieure, vus en coupe axiale ; et
  • la figure 13, déjà décrite, représente à plus grande échelle, une partie de chambre de combustion dite convergente, ainsi qu'un déflecteur plan de la technique antérieure, vus en coupe suivant les flèches XIII-XIII de la figure 12.
The invention will be better understood on reading the following detailed description of a particular embodiment of the invention, provided for information and in no way limiting, and illustrated by means of the appended drawings, in which:
  • the figure 1 is an axial sectional view of a turbojet portion of which the so-called convergent combustion chamber, showing a half of the combustion chamber, the other half being deduced by axial symmetry;
  • the figure 2 represents in perspective and schematically a deflector according to the invention;
  • the figure 3 represents, in axial section, a so-called convergent combustion chamber part and a deflector according to one embodiment of the invention, seen in axial section;
  • the figure 4 is an enlarged view of a detail of the figure 3 ;
  • the figure 5 is analogous to the figure 3 , for another embodiment of the invention, seen in axial section, and shows first angular positioning means;
  • the figure 6 represents, in axial section, other angular positioning means;
  • the figure 7 is a perspective view of a first variant of the embodiment;
  • the figure 8 is a sectional view according to plan VIII-VIII of the figure 7 ;
  • the figure 9 is a perspective view of a second variant of the embodiment;
  • the figure 10 is a sectional view along plane XX of the figure 9 ;
  • the figure 11 , already described, is an axial sectional view of a combustion chamber of the so-called divergent prior art;
  • the figure 12 , already described, represents on a larger scale, a so-called convergent combustion chamber part, as well as a plane deflector of the prior art, seen in axial section; and
  • the figure 13 , already described, represents on a larger scale, a so-called convergent combustion chamber part, as well as a plane deflector of the prior art, seen in section along the arrows XIII-XIII of the figure 12 .

En se référant tout d'abord à la figure 1, il est représenté une portion d'un turboréacteur 2 s'étendant suivant une direction axiale 100 et équipé d'une chambre de combustion 10. Cette chambre de combustion 10, dite convergente, comporte une paroi externe 12 et une paroi interne 14, qui sont coaxiales et sensiblement tronconiques.Referring first to the figure 1 , there is shown a portion of a turbojet engine 2 extending in an axial direction 100 and equipped with a combustion chamber 10. This combustion chamber 10, said convergent, comprises an outer wall 12 and an inner wall 14, which are coaxial and substantially frustoconical.

La chambre de combustion 10 est comprise dans une chambre de diffusion 30 qui est un espace annulaire défini entre un carter externe 32 et un carter interne 34, dans lequel est introduit un comburant comprimé provenant en amont d'un compresseur (non représenté) par l'intermédiaire d'un conduit annulaire de diffusion 36.The combustion chamber 10 is comprised in a diffusion chamber 30 which is an annular space defined between an outer casing 32 and an inner casing 34, into which a compressed oxidant originating upstream of a compressor (not shown) by the compressor is introduced. intermediate of an annular diffusion duct 36.

Les parois externe 12 et interne 14 de la chambre de combustion 10 sont reliées entre elles vers l'amont de la chambre de combustion par un fond de chambre 16, qui est une pièce sensiblement tronconique s'étendant entre deux plans sensiblement transversaux en s'évasant de l'amont vers l'aval. Le fond de chambre 16 se raccorde à chacune des deux parois externe 12 et interne 14 de la chambre de combustion 10. Il est doté de systèmes d'injection 18 à travers lesquelles passent des injecteurs 20 qui traversent le carter extérieur 32 et qui introduisent du carburant à l'extrémité amont de la chambre de combustion 10 où se déroulent les réactions de combustion.The outer 12 and inner 14 walls of the combustion chamber 10 are connected to each other upstream of the combustion chamber by a chamber bottom 16, which is a substantially frustoconical piece extending between two substantially transverse planes in s'. flaring from upstream to downstream. The chamber bottom 16 is connected to each of the two outer walls 12 and inner 14 of the combustion chamber 10. It is provided with injection systems 18 through which pass injectors 20 which pass through the outer casing 32 and which introduce fuel at the upstream end of the combustion chamber 10 where the combustion reactions take place.

Un mode de réalisation d'un déflecteur 22 selon l'invention est représenté de manière schématique et en perspective à la figure 2. Ce déflecteur 22 se présente sous la forme d'une plaque qui est une portion d'une surface conique d'un cône, ce cône ayant un axe de cône 300 et un angle de cône α. En service, lorsque ledit déflecteur 22 est installé sur le fond de chambre 16, ledit axe de cône 300 est sensiblement confondu avec l'axe 100 du turboréacteur. Le déflecteur 22 possède une face concave 62 et une face convexe 64, ainsi qu'un contour ayant quatre côtés 72, 74, 76, 78. Deux 72, 76 de ces quatre côtés sont des arcs de cercle parallèles concentriques de même axe 300. Les deux autres 74, 78 de ces quatre côtés sont des segments de génératrices du cône, qui relient les deux côtés 72, 76 en arcs de cercle. Le déflecteur 22 selon le mode de réalisation comporte un trou d'injection 40, sensiblement central, destiné à se trouver en regard d'un système d'injection 18 du fond de chambre 16 lorsque le déflecteur 22 est installé sur le fond de chambre 16. Ledit trou d'injection 40 est un trou à bord tombé, c'est-à-dire qu'il comporte un bord 402 s'élevant du côté de la face amont du déflecteur 22.One embodiment of a deflector 22 according to the invention is shown diagrammatically and in perspective at the figure 2 . This deflector 22 is in the form of a plate which is a portion of a conical surface of a cone, this cone having a cone axis 300 and a cone angle α. In use, when said deflector 22 is installed on the chamber bottom 16, said cone axis 300 is substantially coincident with the axis 100 of the turbojet engine. The deflector 22 has a concave face 62 and a convex face 64, and a contour having four sides 72, 74, 76, 78. Two 72, 76 of these four sides are concentric parallel circular arcs of the same axis 300. The other two 74, 78 of these four sides are segments of generators of the cone, which connect the two sides 72, 76 in arcs. The deflector 22 according to the embodiment comprises an injection hole 40, substantially central, intended to be opposite an injection system 18 of the chamber bottom 16 when the deflector 22 is installed on the chamber floor 16 Said injection hole 40 is a hole with a fallen edge, that is to say it has an edge 402 rising on the side of the upstream face of the deflector 22.

Ce mode de réalisation du déflecteur 22 selon l'invention est illustré sur la figure 3, qui illustre une partie du fond de chambre 16 aux environs d'un système d'injection 18 dans laquelle est disposé un bol d'injection 206. Le fond de chambre 16 présente une conicité importante (voir figure 1). Le déflecteur 22 est disposé parallèlement au fond de chambre 16, du côté de l'intérieur de la chambre de combustion 10. Du fait de la courbure conique du déflecteur 22, qui est analogue à la courbure conique du fond de chambre 16, ledit déflecteur 22 est parallèle audit fond de chambre 16.This embodiment of the deflector 22 according to the invention is illustrated on the figure 3 , which illustrates a portion of the chamber bottom 16 in the vicinity of an injection system 18 in which is disposed an injection bowl 206. The chamber bottom 16 has a large conicity (see figure 1 ). The deflector 22 is arranged parallel to the chamber bottom 16, on the inside of the combustion chamber 10. Due to the conical curvature of the deflector 22, which is similar to the conical curvature of the chamber bottom 16, said deflector 22 is parallel to said chamber bottom 16.

Un avantage d'un tel déflecteur 22 réside dans le fait que la distance D entre ledit déflecteur 22 et le fond de chambre 16 est sensiblement constante pour toute la surface dudit déflecteur 22. Par suite, un tel déflecteur 22 peut être refroidi de façon satisfaisante par des filets d'air qui viennent l'impacter après avoir traversé des orifices de refroidissement 24 ménagés dans le fond de chambre 16.An advantage of such a deflector 22 lies in the fact that the distance D between said deflector 22 and the chamber bottom 16 is substantially constant for the entire surface of said deflector 22. As a result, such a deflector 22 can be cooled satisfactorily by air streams which impact after passing through cooling orifices 24 formed in the chamber bottom 16.

La figure 3 montre également la position relative du déflecteur 22 par rapport au bol d'injection 206.The figure 3 also shows the relative position of the deflector 22 with respect to the injection bowl 206.

Le bol d'injection 206 est orienté autour d'un axe 200. Il comporte un flasque 208 qui comporte lui-même une bride de fixation 210 qui est retenue axialement entre une première bague 50 et le trou d'injection 40 du déflecteur 22 et le bord 402 du trou d'injection 40 du déflecteur 22. Autour de son système d'injection 18, le fond de chambre 16 est bloqué entre un épaulement extérieur 226 du bord 402 du trou d'injection 40 du déflecteur 22 et une deuxième bague 52 qui est elle-même fixée par brasage dans une rainure périphérique extérieure 404 du bord 402 du trou d'injection 40 du déflecteur 22. La deuxième bague 52 présente également un épaulement intérieur dans lequel s'adapte la première bague 50, les deux bagues 50, 52 étant fixées entre elles par un cordon de soudure 54.The injection bowl 206 is oriented around an axis 200. It comprises a flange 208 which itself comprises a fastening flange 210 which is retained axially between a first ring 50 and the injection hole 40 of the deflector 22 and the edge 402 of the injection hole 40 of the deflector 22. Around its injection system 18, the chamber bottom 16 is locked between an outer shoulder 226 of the edge 402 of the injection hole 40 of the deflector 22 and a second ring 52 which is itself fixed by brazing in an outer peripheral groove 404 of the edge 402 of the injection hole 40 of the deflector 22. The second ring 52 also has an inner shoulder in which fits the first ring 50, the two rings 50, 52 being fixed together by a weld bead 54.

Ce montage est tel que le flasque 208 est autorisé à se déplacer légèrement dans un plan perpendiculaire à l'axe 200. Par suite, le bol d'injection 206 est autorisé à un léger jeu transversal par rapport à l'axe 200, ce qui autorise l'entrée de filets d'air à travers le trou d'injection 40 même lorsque le bol d'injection 206 est en place. Ces filets d'air, matérialisés par les flèches 60 aux figures, ont pour fonction de refroidir le bord 402 du trou d'injection 40 du déflecteur 22, ce bord 402 constituant une zone relativement épaisse du déflecteur 22 qui ne peut pas être atteinte par l'air de refroidissement traversant les orifices de refroidissement 24 du fond de chambre 16.This assembly is such that the flange 208 is allowed to move slightly in a plane perpendicular to the axis 200. As a result, the injection bowl 206 is allowed to a slight clearance transverse to the axis 200, which allows the entry of air threads through the injection hole 40 even when the injection bowl 206 is in place. These air streams, represented by the arrows 60 in the figures, have the function of cooling the edge 402 of the injection hole 40 of the deflector 22, this edge 402 constituting a relatively thick zone of the deflector 22 which can not be reached by the cooling air passing through the cooling orifices 24 of the chamber bottom 16.

Le bol d'injection 206 comporte également une collerette 220 située à l'intérieur de la chambre de combustion 10 qui est séparée du flasque 208 par une gorge 222, et qui s'étend parallèlement à la bride de fixation 210 sensiblement jusqu'à l'aplomb de la face intérieure du bord 402 du trou d'injection 40 du déflecteur 22.The injection bowl 206 also has a flange 220 located inside the combustion chamber 10 which is separated from the flange 208 by a groove 222, and which extends parallel to the fastening flange 210 substantially until aplomb of the inner face of the edge 402 of the injection hole 40 of the deflector 22.

La figure 4 montre un détail agrandi de la figure 3. Plus précisément, elle montre le bord 402 du trou d'injection 40 du déflecteur 22 ainsi que le flasque 208, la collerette 220 et la gorge 222 du bol d'injection 206. Il apparaît que, du fait de la forme conique, et non plus plane, du déflecteur 22, la face intérieure du déflecteur 22 est décalée par rapport à la face intérieure de la flasque 208. Ce décalage, ou marche, est désigné par la lettre M à la figure 4. L'existence de cette marche M est susceptible de créer une perturbation de l'écoulement des jets de refroidissement représentés par la flèche 60, par exemple sous forme de tourbillons, ce qui est susceptible d'affecter le refroidissement du bord tombé 402 du trou d'injection 40 du déflecteur 22.The figure 4 shows an enlarged detail of the figure 3 . More specifically, it shows the edge 402 of the injection hole 40 of the deflector 22 and the flange 208, the flange 220 and the groove 222 of the injection bowl 206. It appears that, due to the shape conical, and not planar, deflector 22, the inner face of the deflector 22 is offset from the inner face of the flange 208. This shift, or walk, is designated by the letter M to the figure 4 . The existence of this step M is likely to create a disturbance of the flow of the cooling jets represented by the arrow 60, for example in the form of vortices, which is likely to affect the cooling of the falling edge 402 of the hole d injection 40 of the deflector 22.

Les figures 7-8 et 9-10 représentent respectivement une première variante et une deuxième variante d'un mode de réalisation du déflecteur 22, qui constitue un perfectionnement du premier mode de réalisation précédemment décrit. Les caractéristiques du mode de réalisation du déflecteur 22 déjà décrit sont aussi des caractéristiques des deux variantes du mode de réalisation illustrées sur ces figures 7 à 10.The Figures 7-8 and 9-10 represent respectively a first variant and a second variant of an embodiment of the deflector 22, which constitutes an improvement of the first embodiment described above. The characteristics of the embodiment of the deflector 22 already described are also characteristics of the two variants of the embodiment illustrated in these embodiments. Figures 7 to 10 .

Le déflecteur 22 selon l'une ou l'autre du mode de réalisation présente une zone centrale 90 qui entoure le trou d'injection 40, et une zone périphérique 92 qui entoure la zone centrale 90 jusqu'aux bords 72, 74, 76, 78 du déflecteur 22. La zone périphérique 92 présente une surface conique concave.The deflector 22 according to either embodiment has a central zone 90 which surrounds the injection hole 40, and a peripheral zone 92 which surrounds the central zone 90 to the edges 72, 74, 76, 78 of the deflector 22. The peripheral zone 92 has a concave conical surface.

Selon la première variante du mode de réalisation illustrée aux figures 7 et 8, ladite zone centrale 90 est circulaire et présente une surface plane, tandis que la zone périphérique 92 présente une surface conique concave. Une zone de raccordement 94 relie ladite zone centrale 90 et ladite zone périphérique 92.According to the first variant of the embodiment illustrated in FIGS. Figures 7 and 8 , said central zone 90 is circular and has a flat surface, while the peripheral zone 92 has a concave conical surface. A connection zone 94 connects said central zone 90 and said peripheral zone 92.

Selon la deuxième variante du mode de réalisation illustrée aux figures 9 et 10, ladite zone centrale 90 est comprise entre deux arêtes 96, 98 sensiblement parallèles aux côtés rectilignes 74, 78 du contour dudit déflecteur 22, et elle s'étend jusqu'aux côtés en arc de cercle 72, 76 du contour dudit déflecteur 22. Elle présente une surface plane. En d'autre termes, les deux arêtes 96, 98 matérialisent l'intersection entre la surface plane de ladite zone centrale 90 et la surface conique concave de la zone périphérique 92.According to the second variant of the embodiment illustrated in Figures 9 and 10 , said central zone 90 is between two edges 96, 98 substantially parallel to the straight sides 74, 78 of the contour of said deflector 22, and extends to the arcuate sides 72, 76 of the contour of said deflector 22. It has a flat surface. In other words, the two edges 96, 98 materialize the intersection between the flat surface of said central zone 90 and the concave conical surface of the peripheral zone 92.

De manière commune aux modes de réalisation, la zone centrale 90 présente une surface plane du côté de la concavité du déflecteur 22.In common with the embodiments, the central zone 90 has a planar surface on the concavity side of the deflector 22.

Comme illustré sur la figure 5, et aux figures 3 et 4, la distance D entre ledit déflecteur 22 et le fond de chambre 16 est sensiblement constante pour toute la surface dudit déflecteur 22. Par suite, le déflecteur 22 peut être refroidi de façon satisfaisante par des filets d'air qui viennent l'impacter après avoir traversé des orifices de refroidissement 24 ménagés dans le fond de chambre 16. En outre, du fait de la planéité de la zone centrale 90, les filets d'air de refroidissement 60 peuvent s'écouler depuis l'extérieur du bol 206 à travers l'ouverture d'injection 40 sans être perturbés par des turbulences. Il s'ensuit que le refroidissement du bord tombé 402 du trou d'injection 40 du déflecteur 22 peut s'effectuer de façon satisfaisante. En effet, la surface plane de la zone centrale 90 et la face intérieure du flasque 208 du bol 206 se trouvent sensiblement dans un même plan.As illustrated on the figure 5 , and Figures 3 and 4 , the distance D between said deflector 22 and the chamber bottom 16 is substantially constant for the entire surface of said deflector 22. As a result, the deflector 22 can be cooled satisfactorily by air streams which come to impact after passing through cooling orifices 24 arranged in the chamber bottom 16. In addition, due to the flatness of the central zone 90, the cooling air streams 60 may flow from outside the bowl 206 through the injection opening 40 without being disturbed by turbulence. It follows that the cooling of the dropped edge 402 of the injection hole 40 of the deflector 22 can be satisfactorily performed. Indeed, the flat surface of the central zone 90 and the inner face of the flange 208 of the bowl 206 are substantially in the same plane.

En outre, et comme illustré aux figures 7 et 9, les deux côtés en arcs de cercle 72, 76 de la plaque formant le déflecteur 22 sont dotés chacun d'un rebord 80 s'étendant du côté de la face concave 62 du déflecteur. Cette caractéristique est commune aux modes de réalisation. Les rebords 80 du déflecteur 22 ont pour fonction de créer un film de refroidissement en guidant l'air de refroidissement des déflecteurs 22 qui est issu des orifices de refroidissement 24, afin de refroidir les parois externe 12 et interne 14 de la chambre de combustion 10.In addition, and as illustrated in Figures 7 and 9 , the two arcuate sides 72, 76 of the plate forming the deflector 22 are each provided with a flange 80 extending on the side of the concave face 62 of the baffle. This characteristic is common to the embodiments. The flanges 80 of the deflector 22 have the function of creating a cooling film by guiding the cooling air of the deflectors 22 which is coming from the cooling orifices 24, in order to cool the outer 12 and inner 14 walls of the combustion chamber 10 .

En outre, le déflecteur 22 est doté de moyens de positionnement angulaire constitués de premiers moyens de positionnement angulaire et de deuxièmes moyens de positionnement angulaire. Cette caractéristique est commune modes de réalisation.In addition, the deflector 22 is provided with angular positioning means consisting of first angular positioning means and second angular positioning means. This characteristic is common embodiments.

La figure 6 illustre les premiers moyens de positionnement angulaire 82, 84 qui comportent une première rainure de blocage 82 comportant trois sections ménagées respectivement dans le fond de chambre 16, le déflecteur 22 et la deuxième bague 52 et une clavette 84. L'insertion de la clavette 84 dans ladite première rainure de blocage 82 empêche une rotation relative de la deuxième bague 52 et du déflecteur 22 par rapport au fond de chambre 16.The figure 6 illustrates the first angular positioning means 82, 84 which comprise a first locking groove 82 having three sections formed respectively in the chamber bottom 16, the deflector 22 and the second ring 52 and a key 84. The insertion of the key 84 in said first locking groove 82 prevents relative rotation of the second ring 52 and the deflector 22 with respect to the chamber bottom 16.

La figure 5 illustre les deuxièmes moyens de positionnement angulaire 86, 88 qui comportent une deuxième rainure de blocage 86 ménagée dans la deuxième bague 52 et un doigt d'arrêt 88 solidaire du bol d'injection 206, L'insertion du doigt d'arrêt 88 dans ladite deuxième rainure de blocage 86 empêche une rotation relative du bol d'injection 206 par rapport à la deuxième bague 52.The figure 5 illustrates the second angular positioning means 86, 88 which comprise a second locking groove 86 formed in the second ring 52 and a stop pin 88 integral with the injection bowl 206, the insertion of the finger stop 88 in said second locking groove 86 prevents relative rotation of the injection bowl 206 relative to the second ring 52.

La coopération de ces quatre moyens de positionnement angulaire 82, 84, 86, 88 permet donc d'empêcher une rotation relative du déflecteur 22 par rapport au fond de chambre 16. Par suite, le déflecteur 22 et le fond de chambre 16 restent correctement positionnés l'un par rapport à l'autre, leur parallélisme est maintenu, et la distance D reste constante.The cooperation of these four angular positioning means 82, 84, 86, 88 therefore makes it possible to prevent relative rotation of the deflector 22 with respect to the chamber floor 16. As a result, the deflector 22 and the chamber floor 16 remain correctly positioned. relative to each other, their parallelism is maintained, and the distance D remains constant.

L'invention se rapporte également à une chambre de combustion 10 qui comporte un fond de chambre 16 et au moins un déflecteur 22 comme précédemment décrit. De préférence, ledit déflecteur 22 est fixé par brasage sur ledit fond de chambre 16.The invention also relates to a combustion chamber 10 which comprises a chamber bottom 16 and at least one deflector 22 as previously described. Preferably, said deflector 22 is brazed to said chamber bottom 16.

Claims (12)

  1. A deflector (22) for a chamber endwall (16) of a combustion chamber (10) of a turbine engine (2), taking the form of a plate provided with a hole (40) said plate being a portion of a conical surface of revolution about a cone axis (300), said plate having a substantially concave face (62) and a substantially convex face (64), and said plate having a contour which possesses four sides (72, 74, 76, 78), of which two first sides (72, 76) are concentric circular arcs centered on said cone axis (300), and two second sides (74, 78) are segments of generatrices of said cone which connect said first sides (72, 76), wherein the deflector (22) comprises a central region (90) which surrounds said hole (40) and a peripheral region (92) which surrounds said central region (90), said central region (90) having a planar face on the same side as said substantially concave face (62).
  2. The deflector (22) as claimed in claim 1, wherein said central region (90) is substantially circular.
  3. The deflector (22) as claimed in claim 2, which has a connection region (94) between said peripheral region (92) and said central region (90).
  4. The deflector (22) as claimed in claim 1, wherein said central region (90) is a plane portion bounded by two edges (96, 98) which are segments of generatrices of said cone which are substantially parallel to said second sides (74, 78).
  5. The deflector (22) as claimed in any one of claims 1 to 4, wherein said first sides (72, 76) of the plate forming the deflector (22) are each provided with a lip (80) extending on the same side as the concave face (62) of the deflector (22).
  6. A combustion chamber (10) which possesses at least one deflector (22) as claimed in any one of claims 1 to 5.
  7. The combustion chamber (10) as claimed in claim 6, wherein said deflector (22) is fastened by brazing to the chamber endwall (16).
  8. The combustion chamber (10) as claimed in claim 6 or 7, which additionally comprises angular positioning means (82, 84, 86, 88).
  9. The combustion chamber (10) as claimed in claim 8, wherein said angular positioning means (82, 84 86, 88) comprise a first locking keyway (84) intended to receive a locking key (84).
  10. The combustion chamber (10) as claimed in claim 8 or 9, wherein said angular positioning means (82, 84, 86, 88) comprise a second locking keyway (86) intended to cooperate with a stop finger (88).
  11. The combustion chamber (10) as claimed in any one of claims 6 to 10, which is a "convergent" combustion chamber having an external wall (12) and an internal wall (14) which are coaxial and substantially frustoconical and are inclined by widening out from downstream to upstream.
  12. A turbine engine (2) which comprises a combustion chamber (10) as claimed in any one of claims 6 to 11.
EP07122639.3A 2006-12-19 2007-12-07 Deflector for the bottom of a combustion chamber, combustion chamber equipped with same and jet engine comprising them Active EP1939528B1 (en)

Applications Claiming Priority (1)

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FR0655657A FR2910115B1 (en) 2006-12-19 2006-12-19 DEFLECTOR FOR BOTTOM OF COMBUSTION CHAMBER, COMBUSTION CHAMBER WHERE IT IS EQUIPPED AND TURBOREACTOR COMPRISING THEM

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EP1939528A1 EP1939528A1 (en) 2008-07-02
EP1939528B1 true EP1939528B1 (en) 2016-06-22

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Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2920032B1 (en) * 2007-08-13 2014-08-22 Snecma DIFFUSER OF A TURBOMACHINE
FR2927951B1 (en) * 2008-02-27 2011-08-19 Snecma DIFFUSER-RECTIFIER ASSEMBLY FOR A TURBOMACHINE
MY174142A (en) 2011-04-07 2020-03-10 Excel Dryer Inc Sanitizing hand dryer
US9421291B2 (en) 2011-05-12 2016-08-23 Fifth Third Bank Hand dryer with sanitizing ionization assembly
US8839627B2 (en) * 2012-01-31 2014-09-23 United Technologies Corporation Annular combustor
FR2998038B1 (en) * 2012-11-09 2017-12-08 Snecma COMBUSTION CHAMBER FOR A TURBOMACHINE
US9284963B2 (en) 2013-01-28 2016-03-15 American Dryer, Inc. Blower assembly for hand dryer, with helmholtz motor mount

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4454711A (en) * 1981-10-29 1984-06-19 Avco Corporation Self-aligning fuel nozzle assembly
US4567730A (en) * 1983-10-03 1986-02-04 General Electric Company Shielded combustor
EP0153842B1 (en) * 1984-02-29 1988-07-27 LUCAS INDUSTRIES public limited company Combustion equipment
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
GB9018014D0 (en) * 1990-08-16 1990-10-03 Rolls Royce Plc Gas turbine engine combustor
FR2673454B1 (en) * 1991-02-28 1995-01-13 Snecma COMBUSTION CHAMBER COMPRISING A BOTTOM WALL COMPRISING A PLURALITY OF PARTIAL CONE TRUNKS.
CA2070518C (en) * 1991-07-01 2001-10-02 Adrian Mark Ablett Combustor dome assembly
US5154060A (en) * 1991-08-12 1992-10-13 General Electric Company Stiffened double dome combustor
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
DE4427222A1 (en) * 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Heat shield for a gas turbine combustor
US5682747A (en) * 1996-04-10 1997-11-04 General Electric Company Gas turbine combustor heat shield of casted super alloy
US6260359B1 (en) * 1999-11-01 2001-07-17 General Electric Company Offset dilution combustor liner
US6973419B1 (en) * 2000-03-02 2005-12-06 United Technologies Corporation Method and system for designing an impingement film floatwall panel system
US6557349B1 (en) * 2000-04-17 2003-05-06 General Electric Company Method and apparatus for increasing heat transfer from combustors
US6530227B1 (en) * 2001-04-27 2003-03-11 General Electric Co. Methods and apparatus for cooling gas turbine engine combustors
US6952927B2 (en) * 2003-05-29 2005-10-11 General Electric Company Multiport dome baffle
US7062920B2 (en) * 2003-08-11 2006-06-20 General Electric Company Combustor dome assembly of a gas turbine engine having a free floating swirler
US7121095B2 (en) * 2003-08-11 2006-10-17 General Electric Company Combustor dome assembly of a gas turbine engine having improved deflector plates
US7310952B2 (en) * 2003-10-17 2007-12-25 General Electric Company Methods and apparatus for attaching swirlers to gas turbine engine combustors
US6983599B2 (en) * 2004-02-12 2006-01-10 General Electric Company Combustor member and method for making a combustor assembly
US20050227106A1 (en) * 2004-04-08 2005-10-13 Schlichting Kevin W Single crystal combustor panels having controlled crystallographic orientation
US7628019B2 (en) * 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base
FR2897145B1 (en) * 2006-02-08 2013-01-18 Snecma ANNULAR COMBUSTION CHAMBER FOR TURBOMACHINE WITH ALTERNATE FIXINGS.
FR2897107B1 (en) * 2006-02-09 2013-01-18 Snecma CROSS-SECTIONAL COMBUSTION CHAMBER WALL HAVING MULTIPERFORATION HOLES
FR2897417A1 (en) * 2006-02-10 2007-08-17 Snecma Sa ANNULAR COMBUSTION CHAMBER OF A TURBOMACHINE
FR2897922B1 (en) * 2006-02-27 2008-10-10 Snecma Sa ARRANGEMENT FOR A TURBOREACTOR COMBUSTION CHAMBER
US8596071B2 (en) * 2006-05-05 2013-12-03 General Electric Company Method and apparatus for assembling a gas turbine engine
FR2903171B1 (en) * 2006-06-29 2008-10-17 Snecma Sa CRABOT LINK ARRANGEMENT FOR TURBOMACHINE COMBUSTION CHAMBER
US7730725B2 (en) * 2006-09-14 2010-06-08 Solar Turbines Inc. Splash plate dome assembly for a turbine engine
US7770397B2 (en) * 2006-11-03 2010-08-10 Pratt & Whitney Canada Corp. Combustor dome panel heat shield cooling
US7681398B2 (en) * 2006-11-17 2010-03-23 Pratt & Whitney Canada Corp. Combustor liner and heat shield assembly
US7665306B2 (en) * 2007-06-22 2010-02-23 Honeywell International Inc. Heat shields for use in combustors
FR2918443B1 (en) * 2007-07-04 2009-10-30 Snecma Sa COMBUSTION CHAMBER COMPRISING THERMAL PROTECTION DEFLECTORS OF BOTTOM BOTTOM AND GAS TURBINE ENGINE BEING EQUIPPED

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RU2433347C2 (en) 2011-11-10
JP2008151498A (en) 2008-07-03
RU2007147326A (en) 2009-06-27
FR2910115A1 (en) 2008-06-20
FR2910115B1 (en) 2012-11-16
US8037691B2 (en) 2011-10-18
CA2615029A1 (en) 2008-06-19
JP5175081B2 (en) 2013-04-03
CA2615029C (en) 2014-12-02
EP1939528A1 (en) 2008-07-02
US20080141674A1 (en) 2008-06-19

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