EP2031304B1 - Separator for the cooling air supply of a turbine - Google Patents

Separator for the cooling air supply of a turbine Download PDF

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Publication number
EP2031304B1
EP2031304B1 EP08163040.2A EP08163040A EP2031304B1 EP 2031304 B1 EP2031304 B1 EP 2031304B1 EP 08163040 A EP08163040 A EP 08163040A EP 2031304 B1 EP2031304 B1 EP 2031304B1
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EP
European Patent Office
Prior art keywords
combustion chamber
separator
tubular portion
upstream
chamber
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EP08163040.2A
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German (de)
French (fr)
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EP2031304A1 (en
Inventor
Christophe Pieussergues
Denis Sandelis
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the present invention relates to the field of annular combustion chambers.
  • upstream and downstream are defined with respect to the direction of normal circulation of the air along the outside of the annular wall of the combustion chamber.
  • inner and outer / “outer” characterize a position more or less remote from the main axis of the combustion chamber, unless otherwise specified.
  • This combustion chamber is typically delimited by a bottom wall 12 comprising the fuel injectors 13 and the combustion air inlets, and by an annular wall 15 extending in the longitudinal direction of the chamber 10 (which therefore corresponds to the upstream-downstream direction), substantially parallel to the main axis A of the turbomachine (not shown).
  • the chamber 10 is closed at its upstream end by the bottom wall 12, and is open at its downstream end 17, in its longitudinal direction, to allow the evacuation of the burnt gases.
  • This annular wall 15 is typically constituted by an annular inner ring (radially inner wall) 151 and an annular outer ring (radially outer wall) 152.
  • the inner ferrule 151 and the outer ferrule 152 are coaxial with respect to the main axis A of the turbomachine, the inner ferrule 151 being closer to the main axis of the turbomachine than the outer ferrule 152, that is to say say having a radius less than the radius of the outer shell 152.
  • an upstream annular inner wall 11 of chamber 10 extends upstream the inner ring 151.
  • the annular wall 15 is pierced over its entire surface area (or a major part of it) with several orifices, larger or smaller, which are intended to allow air to enter the combustion chamber 10.
  • the air which runs along the inner ferrule 151 outside the chamber 10, and which then enters this chamber through these orifices flows between the inner ferrule 151 and a wall called internal chamber flange 21.
  • the internal flange 21 is pierced with orifices, some of which (upstream orifices 215) are located on its upstream part, substantially facing the central part of the inner ferrule 21 of the chamber 10 (that is, say halfway between the bottom wall 12 of the chamber 10 and the downstream end 217 of the inner flange 21).
  • upstream orifices 215 are located on its upstream part, substantially facing the central part of the inner ferrule 21 of the chamber 10 (that is, say halfway between the bottom wall 12 of the chamber 10 and the downstream end 217 of the inner flange 21).
  • the air flow intended to pass through the orifices of the inner flange to cool the HP turbine wheel is influenced by the combustion chamber. Indeed, this air is, before passing through these orifices, in contact with the inner wall which is hot and which is further pierced with air inlet orifices, and this air is thus subjected to heating by convection. This air also undergoes radiation heating through these openings of the chamber, this radiation from the flames of combustion. In addition, the instabilities of this combustion generate in this flow of air, through the orifices of the chamber, turbulence may contribute to disrupt the supply of cooling air to the wheel HP.
  • annular combustion chamber having the features according to the preamble of claim 1 is known from the document US 2002/108 374 .
  • the invention aims to provide a device that reduces the heating of the air for cooling the HP turbine wheel, and to reduce the disturbance of this air caused by the combustion instabilities from the combustion chamber.
  • the combustion chamber is equipped with a separator disposed between the radially inner wall of the chamber and the internal flange of the chamber, this separator comprising a tubular portion centered on the main axis of the chamber. of combustion and whose upstream end is located upstream of the orifices of the radially inner wall of the chamber, and a fastening portion integral with the combustion chamber, so that the tubular portion divides the air flow along this radially inner wall in an interior air flow passing between this tubular portion and the internal flange of the chamber, and in an outside air flow passing between the radially inner wall and this tubular portion.
  • the internal air flow which is intended to cool the HP turbine wheel, is no longer heated by convection and radiation by the chamber wall and by the flame radiation, and is no longer disturbed. by the instabilities of combustion resulting from the orifices of the internal wall of the cooling chamber.
  • the undesirable interaction between the combustion chamber and the air flow intended to cool the HP turbine wheel is greatly reduced or even eliminated.
  • the fixing portion is a radial portion extending from the tubular portion to the main axis, and is pierced with main holes for passing air from upstream to downstream.
  • the separator is not attached directly to the wall (hot) of the chamber, and is not heated by it by solid conduction. This arrangement is advantageous since the separator must be as warm as possible so as not to heat the interior air flow.
  • the figure 1 represents a combustion chamber 10 of a turbomachine and the structures associated therewith.
  • This room excluding the elements according to the invention, is identical to the chamber according to the art previous ( figure 5 ) described above. Common areas figures 1 and 5 therefore have the same numbering, and are not described again.
  • the downstream end of the outer shell 152 is extended radially outwardly by an annular outer flange 22, and the downstream end of the inner shell 151 is extended radially inwardly by an annular inner flange 21.
  • These flanges are therefore integral with the chamber 10.
  • the outer flange 22 and the inner flange 21 are attached to a housing wall 30 which surrounds the chamber 10, and thus serve to fix this chamber on the housing which is integral with the turbomachine.
  • the inner flange 21 extends the downstream end of the inner ferrule 151 inwards and then upstream, so that the inner flange 21, which is coaxial with the inner ferrule 151, has a radius smaller than that of this inner ferrule 151.
  • the inner flange 21 thus delimits with the inner ferrule 151 a downstream annular vein 40.
  • the upstream end 211 of the inner flange 21 is radial and is fixed (for example by several bolts / nuts distributed circumferentially along this upstream end 211), on a downstream end 301 radial wall of the casing 30.
  • the wall of casing 30 extends the inner flange 21 upstream, thus delimiting with the upstream annular inner wall 11 of the chamber 10 an upstream annular vein 49 (which extends downstream by the downstream annular vein 40).
  • the upstream end 211 of the inner flange 21 is in the longitudinal direction substantially at the upstream portion of the inner shell 151 (which terminates upstream approximately at the bottom wall 12 chamber). In the example shown in the figures, this upstream end 211 is located substantially at the first quarter upstream of the length between the bottom wall 12 and the downstream end 217 of the internal flange 21 (this downstream end 217 being located at the downstream end 17 of the chamber 10).
  • downstream annular groove 40 tapers from upstream to downstream, so that the radial dimension of the downstream annular groove 40 at the upstream end 211 of the inner flange 21 is greater than the radial dimension of the annular vein 40 at the downstream end 217 of the internal flange 21.
  • the inner flange 21 is pierced with orifices, including upstream orifices 215.
  • the portion of the air coming from the upstream annular duct 49 which passes through these upstream orifices 215 of the internal flange 21 is intended to go cool the HP turbine wheel (not shown). On the figure 1 this air passes, after having passed through the upstream orifices 215, through a structure 60 before going to cool this turbine.
  • a separator 70 is placed in the downstream annular groove 40, that is to say between the inner shroud 151 and the assembly formed by the internal flange 21 and the housing wall 30.
  • this separator 70 comprises a tubular portion 76 centered on the main axis A of the combustion chamber 10, and a radial portion 71 extending radially from the tubular portion 76 towards the main axis A, and pierced with main holes 72 oriented along the main axis A.
  • the radial portion 71 of the separator 70 is connected to the tubular portion 76 of the separator 70 in the upstream half of this tubular portion 76.
  • the radial portion 71 is connected to the tubular portion 76 at the first upstream quarter or the first third upstream of the tubular portion 76.
  • the tubular portion 76 of the separator 70 divides, from its upstream end 79, the downstream annular groove 40 in two in the upstream-downstream direction, firstly into an outer annular vein 81 located between the inner ferrule 151 of the chamber 10 and this tubular portion 76, and secondly an inner annular vein 82 located between this tubular portion 76 and the assembly constituted by the inner flange 21 and the housing wall 30. More specifically, the portion 78 of the tubular portion 76 located upstream of the radial portion 71 of the separator 70 is located between the housing wall 30 and the inner shell 151. The portion of the tubular portion 76 located downstream of the radial portion 71 is between the inner flange 21 and the inner ferrule 151.
  • the radial portion 71 of the separator 70 is thus located at the interface between the housing wall 30 and the internal flange 21.
  • the separator 70 is fixed to the internal flange 21 by the radially inner end of its radial portion 71.
  • the radially inner end of the radial portion 71 is pierced with fixing holes 711 adapted to receive a device for attaching said radial portion (71) to said inner flange (21).
  • this fixing is done by bolting.
  • the radially inner end of the radial portion 71 is sandwiched between the upstream radial end 211 of the inner flange 21 and the downstream radial end 301 of the casing wall 30.
  • the bolts that hold this upstream end 211 and this downstream end 301 integral pass through the fixing holes 711, the assembly consisting of the upstream end 211, the inner end of the radial portion 71, and the downstream end 301 being tightened by screwed nuts on these bolts.
  • the separator 70 is thus firmly held in position in the downstream annular groove 40.
  • the tubular portion 76 of the separator 70 divides the downstream annular vein 40 in the upstream-downstream direction into an outer annular vein 81 located between the inner ferrule 151 of the chamber 10 and this tubular portion 76, and in one Inner annular groove 82.
  • the tubular portion 76 does not have any holes, since its function is to separate the air circulating in the outer annular vein 81 (and which is heated by the chamber 10) of the air circulating in the annular vein Inner 82.
  • the tubular portion 76 screens between the air flowing in the inner annular vein 82 and the chamber 10.
  • the air coming from the upstream annular vein 49 thus divides into the downstream annular groove 40, at the upstream end 79 of the tubular portion 76 of the separator 70, into an outside air flow F e passing through the vein outer annulus 81, and an internal air flow F i passing into the inner annular vein 82 (these flows are represented by arrows on the figure 2 ).
  • the cross section (radial) of the outer annular vein 81 is smaller than the cross section of the downstream annular groove 40 in the absence of separator 70. Furthermore, the tubular portion 76 of the separator 70, and in particular its portion 78 located upstream of the radial portion 71 of the separator, is substantially parallel to the inner ring 151 of the combustion chamber 10.
  • the outer annular vein 81 is therefore of substantially constant cross section, which was not the case in the absence of separator 70, the inner flange 21 approaching the inner ferrule 151 from upstream to downstream.
  • This characteristic of the outer annular vein 81 leads to a better air flow, and thus to an increase in the Mach number in the outer annular vein 81.
  • This increase in the Mach number allows better cooling by convection of the inner ring 151 of the chamber 10.
  • the tests carried out by the inventors show that the increase in the Mach number is of the order of 10 to 20%.
  • the interior air flow F i flows between the casing wall 30 and the inner casing 151. Then it passes through the main holes 72 of the radial part 71 of the separator 70 and opens into the part of the inner vein 82 delimited by the inner flange 21 and the inner ferrule 151.
  • the separator 70 is in contact with the internal flange 21, so that the downstream end of the Inner annular vein 82 is closed.
  • the downstream end 77 is in contact with a portion 27 of the inner flange 21 which is an annular protrusion as shown in FIG. figure 2 .
  • the internal flange 21 has in its upstream portion upstream orifices 215. These upstream orifices 215 are located between the portion 27 and the upstream end 211 of the inner flange 21.
  • the interior air flow F i must therefore go through the upstream ports 215 of the inner flange 21 to exit the inner annular vein 82. This indoor air flow F i then flows in the direction of the HP turbine wheel that it is intended to go cool.
  • the downstream end 77 of the separator 70 can simply be slid over the portion 27 of the inner flange 21, which helps centering the separator 70 on the internal flange 21.
  • the downstream end 77 of the separator 70 may be attached to the portion 27 of the inner flange 21, for example by brazing.
  • the fixing is not done by bolting, which allows an easier assembly of the separator 70 on the inner flange 21.
  • the separator 70 is thus fixed to the inner flange 21 at the same time by the radially inner end of its part. radial 71, and the downstream end 77 of its tubular portion 76. This double attachment of the separator 70 allows a better attachment thereof on the inner flange 21.
  • the separator 70 is fixed to the inner flange 21 by its upstream and downstream, which improves the stability of the positioning of the separator 70, and stiffens the structure.
  • the separator 70 may comprise, instead of the radial portion 71, a fixing portion which is integral with the combustion chamber 10.
  • the separator 70 can be fixed rigidly (for example by welding) by the downstream end 77 of its tubular portion 76 on the inner flange 21 (for example on the portion 27 of the inner flange 21).
  • the separator 70 comprises only the tubular portion 76 and does not have a radial portion 71, and the downstream end 77 is the fixing portion.
  • the fixing portion can be connected to the tubular portion 76 in the upstream half of this tubular portion 76.
  • the upstream end 79 of the tubular portion 76 of the separator 70 is located upstream of the orifices of the inner ferrule 151 of the chamber 10. This situation is represented on the figure 2 , where the upstream end 79 is at a distance d upstream of the orifice 51 of the inner ferrule 151 situated furthest upstream. This distance d is for example between 15 and 20 mm.
  • the internal air flow F i is completely separated from the inner ferrule 151 of the chamber 10 by the tubular portion 76 of the separator 70.
  • the interior air flow F i is therefore not heated by convection at contact of the inner ring 151, or by the flame radiation passing through the orifices of the inner ring 151, and is also not disturbed by the instabilities of combustion from these orifices.
  • the indoor air flow F i can therefore cool more efficiently the HP turbine.
  • leading edge of the upstream end 79 of the tubular portion 76 of the separator 70 may be rounded, which allows a better flow of the outside air flow F e intended to follow the chamber 10 and the flow of the indoor air F i for cooling the HP turbine wheel.
  • the radial portion 71 of the separator has main holes 72 for passing the interior air flow F i .
  • These main holes 72 are located near the tubular portion 76, between this tubular portion 76 and the location where the radial portion 71 joins the inner flange 21.
  • main holes 72 are for example distributed over the entire circumference of the radial portion 71. They are for example circular, as shown in FIG. Figure 4A , or triangular arranged in staggered rows (i.e. any two adjacent triangles form a rhombus), as shown in FIG. Figure 4B .
  • the cross section of the radial portion 71 is defined as the region of this radial portion which is subjected to the interior air flow F i .
  • This effective section is therefore the annular region between the place where the radial portion 71 is connected to the tubular portion 76 (this location is substantially a circle in the example shown in the figures), and the location where the radial portion 71 comes into contact with the inner flange 21 (this location is substantially a circle in the example shown in the figures).
  • the area of the main holes 72 occupies between 60% and 80% of the effective cross section of the radial portion 71.
  • the separator material is capable of holding temperatures up to 550 ° C.
  • this material may be a nickel / chromium steel.
  • the combustion chamber described above is a turbomachine chamber. This chamber can also be any combustion chamber.

Description

La présente invention concerne le domaine des chambres de combustion annulaires.The present invention relates to the field of annular combustion chambers.

Dans la description qui suit les termes "amont" et "aval" sont définis par rapport au sens de circulation normal de l'air le long de l'extérieur de la paroi annulaire de la chambre de combustion. Les termes "intérieur"/"interne" et "extérieur"/"externe" caractérisent une position plus ou moins éloignée de l'axe principal de la chambre de combustion, sauf s'il en est précisé autrement.In the description which follows, the terms "upstream" and "downstream" are defined with respect to the direction of normal circulation of the air along the outside of the annular wall of the combustion chamber. The terms "inner" / "internal" and "outer" / "outer" characterize a position more or less remote from the main axis of the combustion chamber, unless otherwise specified.

Les turbomachines actuelles sont munies d'une chambre de combustion annulaire dont l'axe de symétrie est l'axe principal de la turbomachine. Une telle chambre est représentée sur la figure 5. Cette chambre de combustion est typiquement délimitée par une paroi de fond 12 comportant les injecteurs de carburant 13 et les entrées d'air comburant, et par une paroi annulaire 15 s'étendant dans la direction longitudinale de la chambre 10 (qui correspond donc à la direction amont-aval), sensiblement parallèle à l'axe principal A de la turbomachine (non-représenté). La chambre 10 est fermée à son extrémité amont par la paroi de fond 12, et est ouverte à son extrémité aval 17, selon sa direction longitudinale, pour permettre l'évacuation des gaz brulés. Cette paroi annulaire 15 est typiquement constituée d'une virole interne (paroi radialement interne) 151 annulaire et d'une virole externe (paroi radialement externe) 152 annulaire. La virole interne 151 et la virole externe 152 sont coaxiales par rapport à l'axe principal A de la turbomachine, la virole interne 151 étant plus proche de l'axe principal de la turbomachine que la virole externe 152, c'est-à-dire ayant un rayon inférieur au rayon de la virole externe 152.Current turbomachines are provided with an annular combustion chamber whose axis of symmetry is the main axis of the turbomachine. Such a room is represented on the figure 5 . This combustion chamber is typically delimited by a bottom wall 12 comprising the fuel injectors 13 and the combustion air inlets, and by an annular wall 15 extending in the longitudinal direction of the chamber 10 (which therefore corresponds to the upstream-downstream direction), substantially parallel to the main axis A of the turbomachine (not shown). The chamber 10 is closed at its upstream end by the bottom wall 12, and is open at its downstream end 17, in its longitudinal direction, to allow the evacuation of the burnt gases. This annular wall 15 is typically constituted by an annular inner ring (radially inner wall) 151 and an annular outer ring (radially outer wall) 152. The inner ferrule 151 and the outer ferrule 152 are coaxial with respect to the main axis A of the turbomachine, the inner ferrule 151 being closer to the main axis of the turbomachine than the outer ferrule 152, that is to say say having a radius less than the radius of the outer shell 152.

En amont de la paroi de fond 12, une paroi interne annulaire amont 11 de chambre 10 prolonge vers l'amont la virole interne 151.Upstream of the bottom wall 12, an upstream annular inner wall 11 of chamber 10 extends upstream the inner ring 151.

La paroi annulaire 15 est percée sur toute sa superficie (ou une majeure partie de celle-ci) de plusieurs orifices, plus ou moins grands, qui sont destinés à permettre à l'air de pénétrer dans la chambre de combustion 10. L'air qui longe la virole interne 151 à l'extérieur de la chambre 10, et qui pénètre ensuite dans cette chambre par ces orifices s'écoule entre cette virole interne 151 et une paroi appelée bride interne 21 de chambre. Cette bride interne 21, annulaire et coaxiale avec la virole interne 151 de la chambre, a donc un rayon inférieur à celui de cette virole interne 151. La bride interne 21 est percée d'orifices, dont certains (orifices amont 215) se situent sur sa partie amont, sensiblement en regard de la partie centrale de la virole interne 21 de la chambre 10 (c'est-à-dire à mi-chemin entre la paroi de fond 12 de la chambre 10 et l'extrémité aval 217 de la bride interne 21). Ainsi, l'air qui longe la virole interne 151 passe en partie par ces orifices amont 215. Une fois passé par ces orifices amont, cet air va refroidir la roue de turbine HP (Haute Pression) située en aval.The annular wall 15 is pierced over its entire surface area (or a major part of it) with several orifices, larger or smaller, which are intended to allow air to enter the combustion chamber 10. The air which runs along the inner ferrule 151 outside the chamber 10, and which then enters this chamber through these orifices flows between the inner ferrule 151 and a wall called internal chamber flange 21. This inner flange 21, annular and coaxial with the inner ferrule 151 of the chamber, therefore has a radius less than that of this inner ferrule 151. The internal flange 21 is pierced with orifices, some of which (upstream orifices 215) are located on its upstream part, substantially facing the central part of the inner ferrule 21 of the chamber 10 (that is, say halfway between the bottom wall 12 of the chamber 10 and the downstream end 217 of the inner flange 21). Thus, the air that runs along the inner ferrule 151 passes in part through these upstream orifices 215. Once passed through these upstream orifices, this air will cool the turbine wheel HP (High Pressure) located downstream.

De par cette disposition de la paroi interne de la chambre de combustion et des orifices de la bride interne, le flux d'air destiné à passer par les orifices de la bride interne pour aller refroidir la roue de turbine HP subit l'influence de la chambre de combustion. En effet, cet air est, avant de passer par ces orifices, en contact avec la paroi interne qui est chaude et qui est de plus percée d'orifices d'entrée d'air, et cet air subit ainsi un échauffement par convection. Cet air subit également un échauffement par rayonnement au travers de ces orifices de la chambre, ce rayonnement provenant des flammes de la combustion. De plus, les instabilités de cette combustion génèrent dans ce flux d'air, au travers des orifices de la chambre, des turbulences susceptibles de contribuer à perturber l'alimentation de l'air de refroidissement de la roue HP.By this arrangement of the internal wall of the combustion chamber and the orifices of the inner flange, the air flow intended to pass through the orifices of the inner flange to cool the HP turbine wheel is influenced by the combustion chamber. Indeed, this air is, before passing through these orifices, in contact with the inner wall which is hot and which is further pierced with air inlet orifices, and this air is thus subjected to heating by convection. This air also undergoes radiation heating through these openings of the chamber, this radiation from the flames of combustion. In addition, the instabilities of this combustion generate in this flow of air, through the orifices of the chamber, turbulence may contribute to disrupt the supply of cooling air to the wheel HP.

Une chambre de combustion annulaire ayant les caractéristiques selon le préambule de la revendication 1 est connue du document US 2002/108 374 .An annular combustion chamber having the features according to the preamble of claim 1 is known from the document US 2002/108 374 .

Globalement, cet air subit donc un réchauffement qui est préjudiciable puisque la fonction de cet air est d'aller refroidir la roue de turbine HP.Overall, this air undergoes a warming which is detrimental since the function of this air is to go cool the HP turbine wheel.

L'invention vise à proposer un dispositif qui permette de diminuer le réchauffement de l'air destiné à refroidir la roue de turbine HP, et de diminuer la perturbation de cet air causé par les instabilités de combustion provenant de la chambre de combustion.The invention aims to provide a device that reduces the heating of the air for cooling the HP turbine wheel, and to reduce the disturbance of this air caused by the combustion instabilities from the combustion chamber.

Ce but est atteint grâce au fait que la chambre de combustion est équipée d'un séparateur disposé entre la paroi radialement interne de la chambre et la bride interne de la chambre, ce séparateur comprenant une partie tubulaire centrée sur l'axe principal de la chambre de combustion et dont l'extrémité amont se situe en amont des orifices de la paroi radialement interne de la chambre, et une partie de fixation solidaire de la chambre de combustion, de telle sorte que la partie tubulaire divise le flux d'air longeant cette paroi radialement interne en un flux d'air intérieur passant entre cette partie tubulaire et la bride interne de la chambre, et en un flux d'air extérieur passant entre la paroi radialement interne et cette partie tubulaire.This object is achieved thanks to the fact that the combustion chamber is equipped with a separator disposed between the radially inner wall of the chamber and the internal flange of the chamber, this separator comprising a tubular portion centered on the main axis of the chamber. of combustion and whose upstream end is located upstream of the orifices of the radially inner wall of the chamber, and a fastening portion integral with the combustion chamber, so that the tubular portion divides the air flow along this radially inner wall in an interior air flow passing between this tubular portion and the internal flange of the chamber, and in an outside air flow passing between the radially inner wall and this tubular portion.

Grâce à ces dispositions, le flux d'air intérieur, qui est destiné à refroidir la roue de turbine HP n'est plus réchauffé par convection et rayonnement par la paroi de la chambre et par le rayonnement de flamme, et n'est plus perturbé par les instabilités de combustion issues des orifices de la paroi interne de la chambre de refroidissement. L'interaction indésirable entre la chambre de combustion et le flux d'air destiné à refroidir la roue de turbine HP est donc fortement diminuée, voire supprimée.Thanks to these arrangements, the internal air flow, which is intended to cool the HP turbine wheel, is no longer heated by convection and radiation by the chamber wall and by the flame radiation, and is no longer disturbed. by the instabilities of combustion resulting from the orifices of the internal wall of the cooling chamber. The undesirable interaction between the combustion chamber and the air flow intended to cool the HP turbine wheel is greatly reduced or even eliminated.

Avantageusement, la partie de fixation est une partie radiale qui s'étend depuis la partie tubulaire vers l'axe principal, et est percée de trous principaux destinés à laisser passer l'air de l'amont vers l'aval.Advantageously, the fixing portion is a radial portion extending from the tubular portion to the main axis, and is pierced with main holes for passing air from upstream to downstream.

Le séparateur n'est donc pas fixé directement sur la paroi (chaude) de la chambre, et n'est donc pas réchauffé par celle-ci par conduction solide. Cette disposition est avantageuse puisque le séparateur doit être le moins chaud possible pour ne pas réchauffer le flux d'air intérieur.The separator is not attached directly to the wall (hot) of the chamber, and is not heated by it by solid conduction. This arrangement is advantageous since the separator must be as warm as possible so as not to heat the interior air flow.

L'invention sera bien comprise et ses avantages apparaîtront mieux, à la lecture de la description détaillée qui suit, d'un mode de réalisation représenté à titre d'exemple non limitatif. La description se réfère aux dessins annexés sur lesquels :

  • la figure 1 est une vue longitudinale d'une chambre de combustion de turbomachine montrant un séparateur selon l'invention,
  • la figure 2 est une vue en coupe longitudinale d'un séparateur selon l'invention illustrant sa fixation sur la turbomachine,
  • la figure 3 est une vue en coupe et en perspective d'un séparateur selon l'invention,
  • la figure 4A est une vue en coupe transversale selon la ligne IV-IV de la figure 3 d'un séparateur selon l'invention,
  • la figure 4B est une vue en coupe transversale d'un autre mode de réalisation d'un séparateur selon l'invention,
  • La figure 5 est une vue longitudinale d'une chambre de combustion de turbomachine selon l'art antérieur.
The invention will be better understood and its advantages will appear better on reading the detailed description which follows, of an embodiment shown by way of non-limiting example. The description refers to the accompanying drawings in which:
  • the figure 1 is a longitudinal view of a turbomachine combustion chamber showing a separator according to the invention,
  • the figure 2 is a longitudinal sectional view of a separator according to the invention illustrating its attachment to the turbomachine,
  • the figure 3 is a sectional and perspective view of a separator according to the invention,
  • the Figure 4A is a cross-sectional view along line IV-IV of the figure 3 of a separator according to the invention,
  • the Figure 4B is a cross-sectional view of another embodiment of a separator according to the invention,
  • The figure 5 is a longitudinal view of a turbomachine combustion chamber according to the prior art.

La figure 1 représente une chambre de combustion 10 d'une turbomachine et les structures connexes à celle-ci. Cette chambre, hors les éléments selon l'invention, est identique à la chambre selon l'art antérieur (figure 5) décrit plus haut. Les parties communes aux figures 1 et 5 ont par conséquent la même numérotation, et ne sont pas décrits à nouveau. L'extrémité aval de la virole externe 152 se prolonge radialement vers l'extérieur par une bride externe 22 annulaire, et l'extrémité aval de la virole interne 151 se prolonge radialement vers l'intérieur par une bride interne 21 annulaire. Ces brides sont donc solidaires de la chambre 10. La bride externe 22 et la bride interne 21 sont attachées sur une paroi de carter 30 qui entoure la chambre 10, et servent ainsi à fixer cette chambre sur ce carter qui est solidaire de la turbomachine.The figure 1 represents a combustion chamber 10 of a turbomachine and the structures associated therewith. This room, excluding the elements according to the invention, is identical to the chamber according to the art previous ( figure 5 ) described above. Common areas figures 1 and 5 therefore have the same numbering, and are not described again. The downstream end of the outer shell 152 is extended radially outwardly by an annular outer flange 22, and the downstream end of the inner shell 151 is extended radially inwardly by an annular inner flange 21. These flanges are therefore integral with the chamber 10. The outer flange 22 and the inner flange 21 are attached to a housing wall 30 which surrounds the chamber 10, and thus serve to fix this chamber on the housing which is integral with the turbomachine.

La bride interne 21 prolonge l'extrémité aval de la virole interne 151 vers l'intérieur puis vers l'amont, de telle sorte que la bride interne 21, qui est coaxiale avec la virole interne 151, a un rayon inférieur à celui de cette virole interne 151. La bride interne 21 délimite ainsi avec la virole interne 151 une veine annulaire aval 40.The inner flange 21 extends the downstream end of the inner ferrule 151 inwards and then upstream, so that the inner flange 21, which is coaxial with the inner ferrule 151, has a radius smaller than that of this inner ferrule 151. The inner flange 21 thus delimits with the inner ferrule 151 a downstream annular vein 40.

L'extrémité amont 211 de la bride interne 21 est radiale et est fixée (par exemple par plusieurs boulons/écrous répartis circonférentiellement le long de cette extrémité amont 211), sur une extrémité aval 301 radiale de la paroi de carter 30. La paroi de carter 30 prolonge la bride interne 21 vers l'amont, délimitant ainsi avec la paroi interne annulaire amont 11 de la chambre 10 une veine annulaire amont 49 (qui se prolonge vers l'aval par la veine annulaire aval 40).The upstream end 211 of the inner flange 21 is radial and is fixed (for example by several bolts / nuts distributed circumferentially along this upstream end 211), on a downstream end 301 radial wall of the casing 30. The wall of casing 30 extends the inner flange 21 upstream, thus delimiting with the upstream annular inner wall 11 of the chamber 10 an upstream annular vein 49 (which extends downstream by the downstream annular vein 40).

L'extrémité amont 211 de la bride interne 21 se situe en direction longitudinale sensiblement au niveau de la partie amont de la virole interne 151 (qui se termine en amont environ au niveau de la paroi de fond 12 de chambre). Dans l'exemple représenté sur les figures, cette extrémité amont 211 se situe sensiblement au premier quart amont de la longueur entre la paroi de fond 12 et l'extrémité aval 217 de la bride interne 21 (cette extrémité aval 217 étant située à l'extrémité aval 17 de la chambre 10).The upstream end 211 of the inner flange 21 is in the longitudinal direction substantially at the upstream portion of the inner shell 151 (which terminates upstream approximately at the bottom wall 12 chamber). In the example shown in the figures, this upstream end 211 is located substantially at the first quarter upstream of the length between the bottom wall 12 and the downstream end 217 of the internal flange 21 (this downstream end 217 being located at the downstream end 17 of the chamber 10).

Typiquement, la veine annulaire aval 40 va en se rétrécissant de l'amont vers l'aval, de telle sorte que la dimension radiale de la veine annulaire aval 40 au niveau de l'extrémité amont 211 de la bride interne 21 est supérieure à la dimension radiale de la veine annulaire 40 au niveau de l'extrémité aval 217 de la bride interne 21.Typically, the downstream annular groove 40 tapers from upstream to downstream, so that the radial dimension of the downstream annular groove 40 at the upstream end 211 of the inner flange 21 is greater than the radial dimension of the annular vein 40 at the downstream end 217 of the internal flange 21.

Comme expliqué plus haut, la bride interne 21 est percée d'orifices, dont des orifices amont 215. La partie de l'air provenant de la veine annulaire amont 49 qui passe par ces orifices amont 215 de la bride interne 21 est destinée à aller refroidir la roue de turbine HP (non-représentée). Sur la figure 1, cet air passe, après avoir traversé les orifices amont 215, au travers d'une structure 60 avant d'aller refroidir cette turbine.As explained above, the inner flange 21 is pierced with orifices, including upstream orifices 215. The portion of the air coming from the upstream annular duct 49 which passes through these upstream orifices 215 of the internal flange 21 is intended to go cool the HP turbine wheel (not shown). On the figure 1 this air passes, after having passed through the upstream orifices 215, through a structure 60 before going to cool this turbine.

Selon l'invention, on place dans la veine annulaire aval 40, c'est-à-dire entre la virole interne 151 et l'ensemble constitué par la bride interne 21 et la paroi de carter 30, un séparateur 70. Comme représenté sur les figures 2 et 3, ce séparateur 70 comprend une partie tubulaire 76 centrée sur l'axe principal A de la chambre de combustion 10, et une partie radiale 71 s'étendant radialement depuis la partie tubulaire 76 vers l'axe principal A, et percée de trous principaux 72 orientés selon l'axe principal A.According to the invention, a separator 70 is placed in the downstream annular groove 40, that is to say between the inner shroud 151 and the assembly formed by the internal flange 21 and the housing wall 30. the figures 2 and 3 this separator 70 comprises a tubular portion 76 centered on the main axis A of the combustion chamber 10, and a radial portion 71 extending radially from the tubular portion 76 towards the main axis A, and pierced with main holes 72 oriented along the main axis A.

Par exemple, la partie radiale 71 du séparateur 70 se raccorde à la partie tubulaire 76 du séparateur 70 dans la moitié amont de cette partie tubulaire 76. Par exemple, la partie radiale 71 se raccorde à la partie tubulaire 76 au niveau du premier quart amont ou du premier tiers amont de la partie tubulaire 76.For example, the radial portion 71 of the separator 70 is connected to the tubular portion 76 of the separator 70 in the upstream half of this tubular portion 76. For example, the radial portion 71 is connected to the tubular portion 76 at the first upstream quarter or the first third upstream of the tubular portion 76.

Ainsi, comme représenté sur la figure 2, la partie tubulaire 76 du séparateur 70 divise, depuis son extrémité amont 79, la veine annulaire aval 40 en deux dans le sens amont-aval, d'une part en une veine annulaire extérieure 81 située entre la virole interne 151 de la chambre 10 et cette partie tubulaire 76, et d'autre part en une veine annulaire intérieure 82 située entre cette partie tubulaire 76 et l'ensemble constitué par la bride interne 21 et la paroi de carter 30. Plus précisément, la portion 78 de la partie tubulaire 76 située en amont de la partie radiale 71 du séparateur 70 se situe entre la paroi de carter 30 et la virole interne 151. La portion de la partie tubulaire 76 située en aval de la partie radiale 71 se situe entre la bride interne 21 et la virole interne 151.So, as represented on the figure 2 , the tubular portion 76 of the separator 70 divides, from its upstream end 79, the downstream annular groove 40 in two in the upstream-downstream direction, firstly into an outer annular vein 81 located between the inner ferrule 151 of the chamber 10 and this tubular portion 76, and secondly an inner annular vein 82 located between this tubular portion 76 and the assembly constituted by the inner flange 21 and the housing wall 30. More specifically, the portion 78 of the tubular portion 76 located upstream of the radial portion 71 of the separator 70 is located between the housing wall 30 and the inner shell 151. The portion of the tubular portion 76 located downstream of the radial portion 71 is between the inner flange 21 and the inner ferrule 151.

La partie radiale 71 du séparateur 70 se situe donc à l'interface entre la paroi de carter 30 et la bride interne 21. Le séparateur 70 est fixé à la bride interne 21 par l'extrémité radialement intérieure de sa partie radiale 71.The radial portion 71 of the separator 70 is thus located at the interface between the housing wall 30 and the internal flange 21. The separator 70 is fixed to the internal flange 21 by the radially inner end of its radial portion 71.

Par exemple, l'extrémité radialement intérieure de la partie radiale 71 est percée de trous de fixation 711 aptes à recevoir un dispositif de fixation de ladite partie radiale (71) sur ladite bride interne (21). Par exemple, cette fixation s'effectue par boulonnage. Ainsi, l'extrémité radialement intérieure de la partie radiale 71 est insérée en sandwich entre l'extrémité amont 211 radiale de la bride interne 21 et l'extrémité aval 301 radiale de la paroi de carter 30. Les boulons qui maintiennent cette extrémité amont 211 et cette extrémité aval 301 solidaires passent au travers des trous de fixation 711, l'ensemble constitué de l'extrémité amont 211, de l'extrémité intérieure de la partie radiale 71, et de l'extrémité aval 301 étant serré par des écrous vissés sur ces boulons. Le séparateur 70 est ainsi fermement maintenu en position dans la veine annulaire aval 40.For example, the radially inner end of the radial portion 71 is pierced with fixing holes 711 adapted to receive a device for attaching said radial portion (71) to said inner flange (21). For example, this fixing is done by bolting. Thus, the radially inner end of the radial portion 71 is sandwiched between the upstream radial end 211 of the inner flange 21 and the downstream radial end 301 of the casing wall 30. The bolts that hold this upstream end 211 and this downstream end 301 integral pass through the fixing holes 711, the assembly consisting of the upstream end 211, the inner end of the radial portion 71, and the downstream end 301 being tightened by screwed nuts on these bolts. The separator 70 is thus firmly held in position in the downstream annular groove 40.

Comme décrit ci-dessus, la partie tubulaire 76 du séparateur 70 divise la veine annulaire aval 40 dans le sens amont-aval en une veine annulaire extérieure 81 située entre la virole interne 151 de la chambre 10 et cette partie tubulaire 76, et en une veine annulaire intérieure 82. La partie tubulaire 76 ne comporte pas de trous, puisque sa fonction est de séparer l'air circulant dans la veine annulaire extérieure 81 (et qui est réchauffé par la chambre 10) de l'air circulant dans la veine annulaire intérieure 82. Ainsi la partie tubulaire 76 fait écran entre l'air circulant dans la veine annulaire intérieure 82 et la chambre 10.As described above, the tubular portion 76 of the separator 70 divides the downstream annular vein 40 in the upstream-downstream direction into an outer annular vein 81 located between the inner ferrule 151 of the chamber 10 and this tubular portion 76, and in one Inner annular groove 82. The tubular portion 76 does not have any holes, since its function is to separate the air circulating in the outer annular vein 81 (and which is heated by the chamber 10) of the air circulating in the annular vein Inner 82. Thus the tubular portion 76 screens between the air flowing in the inner annular vein 82 and the chamber 10.

L'air provenant de la veine annulaire amont 49 se divise donc dans la veine annulaire aval 40, au niveau de l'extrémité amont 79 de la partie tubulaire 76 du séparateur 70, en un flux d'air extérieur Fe passant dans la veine annulaire extérieure 81, et en un flux d'air intérieur Fi passant dans la veine annulaire intérieure 82 (ces flux sont représentés par des flèches sur la figure 2).The air coming from the upstream annular vein 49 thus divides into the downstream annular groove 40, at the upstream end 79 of the tubular portion 76 of the separator 70, into an outside air flow F e passing through the vein outer annulus 81, and an internal air flow F i passing into the inner annular vein 82 (these flows are represented by arrows on the figure 2 ).

Ainsi, la section transversale (radiale) de la veine annulaire extérieure 81 est plus faible que la section transversale de la veine annulaire aval 40 en absence de séparateur 70. Par ailleurs, la partie tubulaire 76 du séparateur 70, et en particulier sa portion 78 située en amont de la partie radiale 71 du séparateur, est sensiblement parallèle à la virole interne 151 de la chambre de combustion 10. La veine annulaire extérieure 81 est donc de section transversale sensiblement constante, ce qui n'était pas le cas en absence de séparateur 70, la bride interne 21 se rapprochant vers la virole interne 151 de l'amont vers l'aval.Thus, the cross section (radial) of the outer annular vein 81 is smaller than the cross section of the downstream annular groove 40 in the absence of separator 70. Furthermore, the tubular portion 76 of the separator 70, and in particular its portion 78 located upstream of the radial portion 71 of the separator, is substantially parallel to the inner ring 151 of the combustion chamber 10. The outer annular vein 81 is therefore of substantially constant cross section, which was not the case in the absence of separator 70, the inner flange 21 approaching the inner ferrule 151 from upstream to downstream.

Cette caractéristique de la veine annulaire extérieure 81 (section transversale sensiblement constante) conduit à un meilleur écoulement d'air, et donc à une augmentation du nombre de Mach dans la veine annulaire extérieure 81. Cette augmentation du nombre de Mach permet un meilleur refroidissement par convection de la virole interne 151 de la chambre 10. Les essais effectués par les inventeurs montrent que l'augmentation du nombre de Mach est de l'ordre de 10 à 20%.This characteristic of the outer annular vein 81 (substantially constant cross-section) leads to a better air flow, and thus to an increase in the Mach number in the outer annular vein 81. This increase in the Mach number allows better cooling by convection of the inner ring 151 of the chamber 10. The tests carried out by the inventors show that the increase in the Mach number is of the order of 10 to 20%.

En pénétrant dans la veine intérieure 82, le flux d'air intérieur Fi circule entre la paroi de carter 30 et la virole interne 151. Puis il traverse les trous principaux 72 de la partie radiale 71 du séparateur 70 et débouche dans la partie de la veine intérieure 82 délimitée par la bride interne 21 et la virole interne 151. A l'extrémité aval 77 de sa partie tubulaire 76, le séparateur 70 est en contact avec la bride interne 21, de telle sorte que l'extrémité aval de la veine annulaire intérieure 82 est fermée. Par exemple, l'extrémité aval 77 est en contact avec une portion 27 de la bride interne 21 qui est une excroissance annulaire comme représenté sur la figure 2.By entering the inner duct 82, the interior air flow F i flows between the casing wall 30 and the inner casing 151. Then it passes through the main holes 72 of the radial part 71 of the separator 70 and opens into the part of the inner vein 82 delimited by the inner flange 21 and the inner ferrule 151. At the downstream end 77 of its tubular portion 76, the separator 70 is in contact with the internal flange 21, so that the downstream end of the Inner annular vein 82 is closed. For example, the downstream end 77 is in contact with a portion 27 of the inner flange 21 which is an annular protrusion as shown in FIG. figure 2 .

Comme indiqué plus haut, la bride interne 21 présente dans sa partie amont des orifices amont 215. Ces orifices amont 215 sont situés entre la portion 27 et l'extrémité amont 211 de la bride interne 21. Le flux d'air intérieur Fi doit donc passer par les orifices amont 215 de la bride interne 21 pour sortir de la veine annulaire intérieure 82. Ce flux d'air intérieur Fi circule ensuite en direction de la roue de turbine HP qu'il est destiné à aller refroidir.As indicated above, the internal flange 21 has in its upstream portion upstream orifices 215. These upstream orifices 215 are located between the portion 27 and the upstream end 211 of the inner flange 21. The interior air flow F i must therefore go through the upstream ports 215 of the inner flange 21 to exit the inner annular vein 82. This indoor air flow F i then flows in the direction of the HP turbine wheel that it is intended to go cool.

L'extrémité aval 77 du séparateur 70 peut être simplement coulissée sur la portion 27 de la bride interne 21, ce qui aide au centrage du séparateur 70 sur la bride interne 21.The downstream end 77 of the separator 70 can simply be slid over the portion 27 of the inner flange 21, which helps centering the separator 70 on the internal flange 21.

Alternativement, l'extrémité aval 77 du séparateur 70 peut être fixée à la portion 27 de la bride interne 21, par exemple par brasage. De préférence la fixation ne se fait pas par boulonnage, ce qui permet un assemblage plus aisé du séparateur 70 sur la bride interne 21. Le séparateur 70 est donc fixé à la bride interne 21 à la fois par l'extrémité radialement intérieure de sa partie radiale 71, et par l'extrémité aval 77 de sa partie tubulaire 76. Cette double fixation du séparateur 70 permet une meilleure fixation de celui-ci sur la bride interne 21. De plus, la partie radiale 71 du séparateur 70 se raccordant à la partie tubulaire 76 du séparateur 70 dans la moitié amont de cette partie tubulaire 76, le séparateur 70 est fixé à la bride interne 21 par son amont et son aval, ce qui améliore la stabilité du positionnement du séparateur 70, et rigidifie la structure.Alternatively, the downstream end 77 of the separator 70 may be attached to the portion 27 of the inner flange 21, for example by brazing. Preferably the fixing is not done by bolting, which allows an easier assembly of the separator 70 on the inner flange 21. The separator 70 is thus fixed to the inner flange 21 at the same time by the radially inner end of its part. radial 71, and the downstream end 77 of its tubular portion 76. This double attachment of the separator 70 allows a better attachment thereof on the inner flange 21. In addition, the radial portion 71 of the separator 70 connecting to the tubular portion 76 of the separator 70 in the upstream half of this tubular portion 76, the separator 70 is fixed to the inner flange 21 by its upstream and downstream, which improves the stability of the positioning of the separator 70, and stiffens the structure.

Plus généralement, le séparateur 70 peut comporter, au lieu de la partie radiale 71, une partie de fixation qui est solidaire de la chambre de combustion 10.More generally, the separator 70 may comprise, instead of the radial portion 71, a fixing portion which is integral with the combustion chamber 10.

Par exemple, le séparateur 70 peut être fixé rigidement (par exemple par soudage) par l'extrémité aval 77 de sa partie tubulaire 76 sur la bride interne 21 (par exemple sur la portion 27 de la bride interne 21). Dans ce cas, le séparateur 70 comporte uniquement la partie tubulaire 76 et ne comporte pas de partie radiale 71, et l'extrémité aval 77 est la partie de fixation. Cette solution présente l'avantage que le flux d'air intérieur Fi circule dans la veine annulaire intérieure 82 sans obstacle (puisqu'il n'a plus de partie radiale à traverser).For example, the separator 70 can be fixed rigidly (for example by welding) by the downstream end 77 of its tubular portion 76 on the inner flange 21 (for example on the portion 27 of the inner flange 21). In this case, the separator 70 comprises only the tubular portion 76 and does not have a radial portion 71, and the downstream end 77 is the fixing portion. This solution has the advantage that the flow of indoor air F i flows in the inner annular vein 82 without obstacles (since it no longer has a radial portion to cross).

Alternativement, la partie de fixation peut se raccorder à la partie tubulaire 76 dans la moitié amont de cette partie tubulaire 76.Alternatively, the fixing portion can be connected to the tubular portion 76 in the upstream half of this tubular portion 76.

L'extrémité amont 79 de la partie tubulaire 76 du séparateur 70 se situe en amont des orifices de la virole interne 151 de la chambre 10. Cette situation est représentée sur la figure 2, où l'extrémité amont 79 est à une distance d en amont de l'orifice 51 de la virole interne 151 situé le plus en amont. Cette distance d est par exemple comprise entre 15 et 20 mm.The upstream end 79 of the tubular portion 76 of the separator 70 is located upstream of the orifices of the inner ferrule 151 of the chamber 10. This situation is represented on the figure 2 , where the upstream end 79 is at a distance d upstream of the orifice 51 of the inner ferrule 151 situated furthest upstream. This distance d is for example between 15 and 20 mm.

On comprend donc que le flux d'air intérieur Fi est complètement séparé de la virole interne 151 de la chambre 10 par la partie tubulaire 76 du séparateur 70. Le flux d'air intérieur Fi n'est donc pas réchauffé par convection au contact de la virole interne 151, ou par le rayonnement de flamme passant par les orifices de la virole interne 151, et n'est pas non plus perturbé par les instabilités de combustion issues de ces orifices. Le flux d'air intérieur Fi peut donc aller refroidir plus efficacement la turbine HP.It is therefore understood that the internal air flow F i is completely separated from the inner ferrule 151 of the chamber 10 by the tubular portion 76 of the separator 70. The interior air flow F i is therefore not heated by convection at contact of the inner ring 151, or by the flame radiation passing through the orifices of the inner ring 151, and is also not disturbed by the instabilities of combustion from these orifices. The indoor air flow F i can therefore cool more efficiently the HP turbine.

De plus, le bord d'attaque de l'extrémité amont 79 de la partie tubulaire 76 du séparateur 70 peut être arrondi, ce qui permet un meilleur écoulement du flux d'air extérieur Fe destiné à longer la chambre 10 et du flux d'air intérieur Fi destiné à refroidir la roue de turbine HP.In addition, the leading edge of the upstream end 79 of the tubular portion 76 of the separator 70 may be rounded, which allows a better flow of the outside air flow F e intended to follow the chamber 10 and the flow of the indoor air F i for cooling the HP turbine wheel.

Comme mentionné plus haut, la partie radiale 71 du séparateur présente des trous principaux 72 destinés à laisser passer le flux d'air intérieur Fi. Ces trous principaux 72 sont situés à proximité de la partie tubulaire 76, entre cette partie tubulaire 76 et l'endroit où la partie radiale 71 rejoint la bride interne 21.As mentioned above, the radial portion 71 of the separator has main holes 72 for passing the interior air flow F i . These main holes 72 are located near the tubular portion 76, between this tubular portion 76 and the location where the radial portion 71 joins the inner flange 21.

Ces trous principaux 72 sont par exemple répartis sur toute la circonférence de la partie radiale 71. Ils sont par exemple circulaires, comme représenté sur la figure 4A, ou triangulaires disposés en quinconce (c'est-à-dire que deux triangles adjacents quelconques forment un losange), comme représenté sur la figure 4B.These main holes 72 are for example distributed over the entire circumference of the radial portion 71. They are for example circular, as shown in FIG. Figure 4A , or triangular arranged in staggered rows (i.e. any two adjacent triangles form a rhombus), as shown in FIG. Figure 4B .

Ces trous principaux 72 occupent la plus grande superficie possible de la superficie de la section efficace de la partie radiale 71, afin de diminuer la perte de charge lors du passage de l'air au travers de ces trous principaux 72, tout en permettant au séparateur 70 de conserver des propriétés de résistance mécanique suffisantes. La section efficace de la partie radiale 71 est définie comme étant la région de cette partie radiale qui est soumise au flux d'air intérieur Fi. Cette section efficace est donc la région annulaire comprise entre l'endroit où la partie radiale 71 se raccorde à la partie tubulaire 76 (cet endroit est sensiblement un cercle dans l'exemple représenté sur les figures), et l'endroit où la partie radiale 71 entre en contact avec la bride interne 21 (cet endroit est sensiblement un cercle dans l'exemple représenté sur les figures). Par exemple, la superficie des trous principaux 72 occupe entre 60% et 80% de la section efficace de la partie radiale 71.These main holes 72 occupy the largest possible area of the cross-sectional area of the radial portion 71, in order to reduce the pressure drop during the passage of air through these main holes 72, while allowing the separator 70 to retain sufficient strength properties. The cross section of the radial portion 71 is defined as the region of this radial portion which is subjected to the interior air flow F i . This effective section is therefore the annular region between the place where the radial portion 71 is connected to the tubular portion 76 (this location is substantially a circle in the example shown in the figures), and the location where the radial portion 71 comes into contact with the inner flange 21 (this location is substantially a circle in the example shown in the figures). For example, the area of the main holes 72 occupies between 60% and 80% of the effective cross section of the radial portion 71.

Le matériau du séparateur est apte à tenir des températures allant jusqu'à 550°C. Par exemple, ce matériau peut être un acier à base nickel/chrome.The separator material is capable of holding temperatures up to 550 ° C. For example, this material may be a nickel / chromium steel.

La chambre de combustion décrite ci-dessus est une chambre de turbomachine. Cette chambre peut également constituer une chambre de combustion quelconque.The combustion chamber described above is a turbomachine chamber. This chamber can also be any combustion chamber.

Claims (12)

  1. An annular combustion chamber (10) that is fitted with a separator (70) disposed between the radially inner wall (151) of said chamber and the inner flange (21) of said chamber, said separator (70) comprising both a tubular portion (76) and a fastener portion, the tubular portion (76) being centered on the main axis of said combustion chamber and having an upstream end (79) that is situated upstream from orifices (51) in said radially inner wall (151) of the chamber, and the fastener portion being secured to said combustion chamber (10), said tubular portion (76) acting at its upstream end (79) to split the flowsection (40) situated between said radially inner wall (151) of the chamber and said inner flange (21) into an inner annular flowsection (82) and an outer annular flowsection (81) such that the flow of air passing along with the radially inner wall (151) is split into an inner air flow (Fi) passing between said tubular portion (76) and the inner flange (21) of said chamber, and an outer air flow (Fe) passing between said a radially inner wall (151) and said tubular portion (76), characterized in that the outer annular flowsection (81) is of substantially constant cross-section.
  2. A combustion chamber (10) according to claim 1, characterized in that said fastener portion is the downstream end (77) of the tubular portion (76), said downstream end (77) being rigidly fastened to said inner flange (21).
  3. A combustion chamber (10) according to claim 1, characterized in that said fastener portion is a radial portion (71) that extends from said tubular portion (76) towards said main axis, and in that said fastener portion is pierced by main holes (72) for passing the air of an inner air flow (Fi) from upstream to downstream.
  4. A combustion chamber (10) according to claim 3, characterized in that said separator (70) is fastened to said inner flange (21) by the radially inner end of its radial portion (71).
  5. A combustion chamber (10) according to claim 4, characterized in that the radially inner end of said radial portion (71) is pierced by holes (711) suitable for receiving a fastener device for fastening said radial portion (71) on said inner flange (21).
  6. A combustion chamber (10) according to any one of claims 3 to 5, characterized in that said separator (70) is in contact with said inner flange (21) via the downstream end (77) of its tubular portion (76).
  7. A combustion chamber (10) according to any one of claims 3 to 6, characterized in that the area of said main holes (72) occupies 60% to 80% of the area of the effective cross-section of said radial portion (71).
  8. A combustion chamber (10) according to any one of claims 3 to 7, characterized in that said main holes (72) are distributed over the entire circumference of said radial portion (71).
  9. A combustion chamber (10) according to any one of claims 1 and 3 to 8, characterized in that said fastener portion of the separator (70) is connected to said tubular portion (76) in the upstream half of said tubular portion (76).
  10. A combustion chamber (10) according to any one of claims 1 to 9, characterized in that the leading edge of said upstream end (79) of the tubular portion (76) is rounded.
  11. A combustion chamber (10) according to any one of claims 1 to 10, characterized in that said tubular portion (76) of the separator (70) is substantially parallel to said radially inner wall (151) of said combustion chamber (10).
  12. A turbomachine provided with a combustion chamber (10) according to any one of claims 1 to 11.
EP08163040.2A 2007-08-31 2008-08-27 Separator for the cooling air supply of a turbine Active EP2031304B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0757283A FR2920525B1 (en) 2007-08-31 2007-08-31 SEPARATOR FOR SUPPLYING THE COOLING AIR OF A TURBINE

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EP2031304A1 EP2031304A1 (en) 2009-03-04
EP2031304B1 true EP2031304B1 (en) 2015-11-18

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US (1) US8069669B2 (en)
EP (1) EP2031304B1 (en)
JP (1) JP5384052B2 (en)
CA (1) CA2639178C (en)
FR (1) FR2920525B1 (en)
RU (1) RU2477822C2 (en)

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EP2031304A1 (en) 2009-03-04
JP5384052B2 (en) 2014-01-08
US20090060723A1 (en) 2009-03-05
FR2920525A1 (en) 2009-03-06
RU2477822C2 (en) 2013-03-20
CA2639178A1 (en) 2009-02-28
FR2920525B1 (en) 2014-06-13
RU2008135300A (en) 2010-03-10
JP2009057970A (en) 2009-03-19
US8069669B2 (en) 2011-12-06

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