EP0785338A1 - Turbine disc cooling device - Google Patents

Turbine disc cooling device Download PDF

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Publication number
EP0785338A1
EP0785338A1 EP97400078A EP97400078A EP0785338A1 EP 0785338 A1 EP0785338 A1 EP 0785338A1 EP 97400078 A EP97400078 A EP 97400078A EP 97400078 A EP97400078 A EP 97400078A EP 0785338 A1 EP0785338 A1 EP 0785338A1
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EP
European Patent Office
Prior art keywords
flange
channels
outer ring
circuit
stator
Prior art date
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Granted
Application number
EP97400078A
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German (de)
French (fr)
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EP0785338B1 (en
Inventor
Christian Largillier
Gérard Jacques Stangalini
Marc Roger Marchi
Laurent Palmisano
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Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades

Definitions

  • the invention relates to a device for cooling a turbine disc.
  • the high pressure turbine 1 begins in a disc 2 carrying a first stage of movable vanes 3 and fixed to the rotor 4.
  • This disc 2 is located downstream of a combustion chamber 5 formed in a stator 6 surrounding the rotor 4 and which is itself located downstream of a high pressure compressor 7.
  • the gases resulting from the combustion of the fuel in the chamber 5 very strongly heat the disc 2, which must therefore be cooled vigorously to maintain the material which composes it at a temperature compatible with the maintenance of its mechanical resistance properties.
  • the means used consist of two ventilation circuits I and II of cooler air: the first of them I, illustrated by the arrows in solid lines, uses air drawn just upstream from the combustion chamber 5 and which passes through a chamber bottom volume 28 before leaving it via orifices 8 in order to enter injection chambers 9 from which the air exits by high pressure injectors 10 which accelerate and propel it at great speed speed towards side 14 of disc 2.
  • the second air flow II is taken just after the high pressure compressor 7 and passes through a chamber 16 between the rotor 4 and the stator 6 from which it exits by a labyrinth seal or with a brush 17 thrown between these parts and more precisely composed of wipers 18, that is to say circular ridges erected on the rotor 4, which rub on an abradable material 19 fixed to the stator 6, that is to say to say a soft matter which they dig with the liking of differential expansions with the various modes of the machine.
  • the air pressure projects the air out of the chamber 16 and into an annular channel 20 of divergent orientation, contiguous to a part of the chamber bottom 28 over a large part of its length and from where the air exits via upper injectors 36 which open in front of a radially outer ring 22 of the turbine disc 2, in fact belonging to a side surface 29 of the flange 13 secured to this disc.
  • the air of the second ventilation circuit exerts significant refrigeration on the outer ring 22 by reaching this area close to the combustion gases and therefore more strongly heated.
  • the need to cool the entire disc 2 but especially its periphery justifies the duality of the cooling circuits, the air of which can moreover come from other places of the machine.
  • part of the air from the first ventilation circuit does not pass through the orifices 12 but bypasses the flange 13 from the outside and passes through a labyrinth or brush seal 23, which is roughly similar. to the previous 17 and composed like him of wipers 24 erected on the flange 13 and a layer of abradable 25 welded on a surface of the stator 6.
  • the centrifugal forces that the flange 13 exerts on this portion of the first flow straightens it like the previous portion and makes it run along the flank surface 29 to finally cross the flow of the second ventilation circuit in front of the external crown 22.
  • the origin of the invention is based on the observation that this situation was not ideal because the air stream from circuit I is significantly warmer than that of circuit II (around 50 ° C).
  • the invention consists in adding parts whose function is to channel the flows so that their mixing is excluded and that the air of the circuit II originating from the upper injectors 36 reaches the outer ring 22 without hindrance; this air of circuit II is appreciably cooler than that of the first circuit I, because the labyrinth or brush seal 17 which is associated with it, heats the air less than the labyrinth seal 23, of larger diameter, and the air of the first circuit I is centrifuged at the outlet of the labyrinth 23, therefore compressed, which also heats it up.
  • the invention therefore consists of a device for cooling a turbine disc, comprising first and second air ventilation circuits originating from a stator and opening respectively in front of an internal crown and a outer crown radially of a flank surface of the disc, characterized in that it comprises a part located in front of the outer crown, crossing first channels substantially parallel to the flank surface of the disc and second channels extending the second ventilation circuit, crossing the first channels without cutting them, and ending in front of the outer crown.
  • the fundamental element of the invention is a distributor ring 30 integral with the stator 6 and located in front of the outer ring 22 to be cooled, not far from it.
  • the distributor crown 30 is traversed by axial channels 32 which extend the upper injectors 36 to terminate in front of the external crown 22, and the channels 32 are separated by substantially radial channels 31 which cross the previous ones without cutting them, as shown in detail in section of figure 3.
  • the interior of the distributor crown 30 is arranged to minimize pressure losses; this is how the axial channels 32 can be connected to injectors 36 of oblique direction, bent in the direction of travel of the disc 2.
  • the ventilation air of the second circuit II borrows the axial channels 32 and is therefore not affected by the air of circuit I, which passes through the radial channels 31; the mixing of the flows only occurs at the periphery of the disc 2, beyond the outer ring 22.
  • the flange 13 can be constructed with a wiper 33 on its flank surface 14, that is to say a crest whose free end 34 is close to the distributor crown 30 and whose purpose is to guide the air in the flow I running along the side surface 29 of the flange 13 towards the radial channels 31, without allowing it to slide to the outer ring 22.
  • the turbine disk 2 is brought to a temperature above 650 ° C in the known machine.
  • the use of the invention makes it possible to reduce this temperature by several tens of degrees for the flange 13. Progress is important if we consider the high level of quality already achieved with existing engines; it can be exploited by using less expensive materials to build the disc 2 and its flange 13, or by reducing the cooling rates.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Motor Or Generator Cooling System (AREA)

Abstract

The cooler is for a turbine disc (2) covered by a flange (13). The cooler comprises first and second ventilation circuits (I,II) for air. Both circuits issue from a stator and discharge respectively before an inner crown of the disc and an outer crown (22) of the flange. The first circuit branches towards a seal situated between the flange and the stator, and is parallel to the flange towards the outer crown. The cooler has a component (30) situated in front of the outer crown and having first and second channels (31,32) passing through it. The first channels (31) lie parallel to one surface of the flange, extending the first ventilation circuit. The second channels (32) extend the second circuit, crossing the first channels without intersecting them and ending before the outer crown.

Description

L'invention concerne un dispositif de refroidissement d'un disque de turbine.The invention relates to a device for cooling a turbine disc.

Dans la portion de turbine à gaz d'une machine existante illustrée à la figure 1, la turbine à haute pression 1 commence en un disque 2 porteur d'un premier étage d'aubes mobiles 3 et fixé au rotor 4. Ce disque 2 est situé en aval d'une chambre de combustion 5 formée dans un stator 6 entourant le rotor 4 et qui se situe elle-même en aval d'un compresseur à haute pression 7.In the gas turbine portion of an existing machine illustrated in FIG. 1, the high pressure turbine 1 begins in a disc 2 carrying a first stage of movable vanes 3 and fixed to the rotor 4. This disc 2 is located downstream of a combustion chamber 5 formed in a stator 6 surrounding the rotor 4 and which is itself located downstream of a high pressure compressor 7.

Les gaz résultant de la combustion du carburant dans la chambre 5 chauffent très fortement le disque 2, qu'il s'agit donc de refroidir énergiquement pour maintenir la matière qui le compose à une température compatible avec le maintien de ses propriétés de résistance mécanique. Le moyen utilisé consiste en deux circuits de ventilation I et II d'air plus frais : le premier d'entre eux I, illustré par les flèches en trait plein, utilise de l'air soutiré juste en amont de la chambre de combustion 5 et qui passe par un volume de fond de chambre 28 avant de le quitter par des orifices 8 pour pénétrer dans des chambres d'injection 9 d'où l'air sort par des injecteurs à haute pression 10 qui l'accélèrent et le propulsent à grande vitesse vers le flanc 14 du disque 2.The gases resulting from the combustion of the fuel in the chamber 5 very strongly heat the disc 2, which must therefore be cooled vigorously to maintain the material which composes it at a temperature compatible with the maintenance of its mechanical resistance properties. The means used consist of two ventilation circuits I and II of cooler air: the first of them I, illustrated by the arrows in solid lines, uses air drawn just upstream from the combustion chamber 5 and which passes through a chamber bottom volume 28 before leaving it via orifices 8 in order to enter injection chambers 9 from which the air exits by high pressure injectors 10 which accelerate and propel it at great speed speed towards side 14 of disc 2.

Une partie de cet air parvient effectivement à une couronne interne 11 appartenant au flanc 14 après avoir traversé des orifices 12 d'un flasque 13 couvrant le disque 2, après quoi la rotation du disque 2 produit une force centrifuge sur l'écoulement d'air, qui le dirige vers l'extérieur ; l'air est guidé entre la surface de flanc 14 du disque 2 et le flasque 13 pour refroidir finalement la périphérie du disque 2 en pénétrant dans des cavités 15 creusées dans celle-ci.Part of this air effectively reaches an internal ring 11 belonging to the sidewall 14 after having passed through orifices 12 of a flange 13 covering the disc 2, after which the rotation of the disc 2 produces a centrifugal force on the air flow. , which directs it outwards; the air is guided between the flank surface 14 of the disc 2 and the flange 13 to finally cool the periphery of the disc 2 by penetrating into cavities 15 hollowed out therein.

Le second écoulement d'air II, illustré par les flèches en pointillés, est prélevé juste après le compresseur à haute pression 7 et passe par une chambre 16 comprise entre le rotor 4 et le stator 6 d'où il sort par un joint à labyrinthe ou à brosse 17 jeté entre ces pièces et composé plus précisément de léchettes 18, c'est-à-dire de crêtes circulaires érigées sur le rotor 4, qui frottent sur une matière abradable 19 fixée au stator 6, c'est-à-dire une matière tendre qu'elles creusent au gré des dilatations différentielles aux différents régimes de la machine. La pression de l'air projette l'air hors de la chambre 16 et dans un canal 20 annulaire et d'orientation divergente, contigu à une partie du fond de chambre 28 sur une grande partie de sa longueur et d'où l'air sort par des injecteurs supérieurs 36 qui débouchent devant une couronne radialement externe 22 du disque de turbine 2, appartenant en fait à une surface de flanc 29 du flasque 13 solidaire de ce disque.The second air flow II, illustrated by the dotted arrows, is taken just after the high pressure compressor 7 and passes through a chamber 16 between the rotor 4 and the stator 6 from which it exits by a labyrinth seal or with a brush 17 thrown between these parts and more precisely composed of wipers 18, that is to say circular ridges erected on the rotor 4, which rub on an abradable material 19 fixed to the stator 6, that is to say to say a soft matter which they dig with the liking of differential expansions with the various modes of the machine. The air pressure projects the air out of the chamber 16 and into an annular channel 20 of divergent orientation, contiguous to a part of the chamber bottom 28 over a large part of its length and from where the air exits via upper injectors 36 which open in front of a radially outer ring 22 of the turbine disc 2, in fact belonging to a side surface 29 of the flange 13 secured to this disc.

L'air du second circuit de ventilation exerce une réfrigération notable sur la couronne externe 22 en atteignant cette zone proche des gaz de combustion et donc plus fortement échauffée. La nécessité de refroidir tout le disque 2 mais surtout sa périphérie justifie la dualité des circuits de refroidissement, dont l'air peut d'ailleurs provenir d'autres endroits de la machine. Toutefois, il est prévu qu'une partie de l'air du premier circuit de ventilation ne passe pas par les orifices 12 mais contourne le flasque 13 par l'extérieur et passe par un joint à labyrinthe ou à brosse 23, à peu près semblable au précédent 17 et composé comme lui de léchettes 24 érigées sur le flasque 13 et d'une couche d'abradable 25 soudée sur une surface du stator 6. Les forces centrifuges que le flasque 13 exerce sur cette portion du premier écoulement la redressent comme la portion précédente et la font longer la surface de flanc 29 pour finalement croiser l'écoulement du second circuit de ventilation devant la couronne externe 22.The air of the second ventilation circuit exerts significant refrigeration on the outer ring 22 by reaching this area close to the combustion gases and therefore more strongly heated. The need to cool the entire disc 2 but especially its periphery justifies the duality of the cooling circuits, the air of which can moreover come from other places of the machine. However, it is expected that part of the air from the first ventilation circuit does not pass through the orifices 12 but bypasses the flange 13 from the outside and passes through a labyrinth or brush seal 23, which is roughly similar. to the previous 17 and composed like him of wipers 24 erected on the flange 13 and a layer of abradable 25 welded on a surface of the stator 6. The centrifugal forces that the flange 13 exerts on this portion of the first flow straightens it like the previous portion and makes it run along the flank surface 29 to finally cross the flow of the second ventilation circuit in front of the external crown 22.

L'origine de l'invention repose sur la constatation que cette situation n'était pas idéale car le courant d'air provenant du circuit I est nettement plus chaud que celui du circuit II (d'environ 50°C).The origin of the invention is based on the observation that this situation was not ideal because the air stream from circuit I is significantly warmer than that of circuit II (around 50 ° C).

L'invention consiste à ajouter des pièces dont la fonction est de canaliser les écoulements afin que leur mélange soit exclu et que l'air du circuit II originaire des injecteurs supérieurs 36 parvienne sans encombre sur la couronne extérieure 22 ; cet air du circuit II est sensiblement plus frais que celui du premier circuit I, car le joint à labyrinthe ou à brosse 17 qui lui est associé, échauffe moins l'air que le Joint labyrinthe 23, de plus grand diamètre, et l'air du premier circuit I est centrifugé à la sortie du labyrinthe 23, donc comprimé, ce qui l'échauffe également.The invention consists in adding parts whose function is to channel the flows so that their mixing is excluded and that the air of the circuit II originating from the upper injectors 36 reaches the outer ring 22 without hindrance; this air of circuit II is appreciably cooler than that of the first circuit I, because the labyrinth or brush seal 17 which is associated with it, heats the air less than the labyrinth seal 23, of larger diameter, and the air of the first circuit I is centrifuged at the outlet of the labyrinth 23, therefore compressed, which also heats it up.

Ce surcroît de réfrigération dû à l'air du second circuit compense largement la perte de réfrigération consécutive à la dérivation temporaire du courant d'air du premier écoulement, dont l'action est moindre.This additional refrigeration due to the air from the second circuit more than compensates for the loss of refrigeration following the temporary diversion of the air flow from the first flow, which has less action.

Sous sa forme la plus générale, l'invention consiste donc en un dispositif de refroidissement d'un disque de turbine, comprenant un premier et un second circuits de ventilation d'air originaires d'un stator et débouchant respectivement devant une couronne interne et une couronne externe radialement d'une surface de flanc du disque, caractérisé en ce qu'il comprend une pièce située devant la couronne externe, traversée de premiers canaux sensiblement parallèles à la surface de flanc du disque et de seconds canaux prolongeant le second circuit de ventilation, croisant les premiers canaux sans les couper, et se terminant devant la couronne externe.In its most general form, the invention therefore consists of a device for cooling a turbine disc, comprising first and second air ventilation circuits originating from a stator and opening respectively in front of an internal crown and a outer crown radially of a flank surface of the disc, characterized in that it comprises a part located in front of the outer crown, crossing first channels substantially parallel to the flank surface of the disc and second channels extending the second ventilation circuit, crossing the first channels without cutting them, and ending in front of the outer crown.

D'autres particularités de l'invention seront plus facilement saisies à l'aide de la description détaillée d'une de ses réalisations, qui va maintenant être faite au moyen des figures suivantes :

  • la figure 1, déjà décrite, illustre une conception déjà connue de turbines à gaz à laquelle l'invention peut être appliquée ;
  • les figures 2 et 3 illustrent l'invention, la figure 3 étant une section selon la ligne A-A de la figure 2, et
  • la figure 4 illustre une amélioration possible.
Other particularities of the invention will be more easily understood with the aid of the detailed description of one of its embodiments, which will now be made by means of the following figures:
  • Figure 1, already described, illustrates an already known design of gas turbines to which the invention can be applied;
  • FIGS. 2 and 3 illustrate the invention, FIG. 3 being a section along the line AA in FIG. 2, and
  • Figure 4 illustrates a possible improvement.

L'élément fondamental de l'invention, représenté à la figure 2, est une couronne distributrice 30 solidaire du stator 6 et située devant la couronne externe 22 à refroidir, à peu de distance d'elle. La couronne distributrice 30 est traversée de canaux axiaux 32 qui prolongent les injecteurs supérieurs 36 pour aboutir devant la couronne externe 22, et les canaux 32 sont séparés par des canaux sensiblement radiaux 31 qui croisent les précédents sans les couper, comme le montre le détail en section de la figure 3.The fundamental element of the invention, shown in Figure 2, is a distributor ring 30 integral with the stator 6 and located in front of the outer ring 22 to be cooled, not far from it. The distributor crown 30 is traversed by axial channels 32 which extend the upper injectors 36 to terminate in front of the external crown 22, and the channels 32 are separated by substantially radial channels 31 which cross the previous ones without cutting them, as shown in detail in section of figure 3.

L'intérieur de la couronne distributrice 30 est agencé pour réduire au minimum les pertes de charges ; c'est ainsi que les canaux axiaux 32 peuvent être raccordés à des injecteurs 36 de direction oblique, infléchis dans le sens de défilement du disque 2.The interior of the distributor crown 30 is arranged to minimize pressure losses; this is how the axial channels 32 can be connected to injectors 36 of oblique direction, bent in the direction of travel of the disc 2.

L'air de ventilation du second circuit II emprunte les canaux axiaux 32 et n'est donc pas affecté par l'air du circuit I, qui passe par les canaux radiaux 31; le mélange des écoulements ne se produit qu'à la périphérie du disque 2, au-delà de la couronne externe 22. Pour réduire encore les occasions de mélange, on peut construire le flasque 13 avec une léchette 33 sur sa surface de flanc 14, c'est-à-dire une crête dont l'extrémité libre 34 frôle la couronne distributrice 30 et dont le but est de guider l'air de l'écoulement I longeant la surface de flanc 29 du flasque 13 vers les canaux radiaux 31, sans lui permettre de se glisser jusqu'à la couronne externe 22. Dans la réalisation illustrée où la partie de la couronne distributrice 30 porteuse des canaux 31 et 32 s'étend devant une portion radialement intérieure de la couronne externe 22, il est possible d'adjoindre à la couronne distributrice 30 un écran 35 parallèle à la couronne externe 22 et qui s'étend devant le reste de celle-ci, pour séparer par force les écoulements des deux circuits jusqu'au-delà de la couronne externe 22.The ventilation air of the second circuit II borrows the axial channels 32 and is therefore not affected by the air of circuit I, which passes through the radial channels 31; the mixing of the flows only occurs at the periphery of the disc 2, beyond the outer ring 22. To further reduce the opportunities for mixing, the flange 13 can be constructed with a wiper 33 on its flank surface 14, that is to say a crest whose free end 34 is close to the distributor crown 30 and whose purpose is to guide the air in the flow I running along the side surface 29 of the flange 13 towards the radial channels 31, without allowing it to slide to the outer ring 22. In the illustrated embodiment where the portion of the distributor ring 30 carrying the channels 31 and 32 extends in front of a radially inner portion of the external ring 22, it is possible to 'Add to the distributor crown 30 a screen 35 parallel to the external crown 22 and which extends in front of the rest of the latter, to forcefully separate the flows of the two circuits to beyond the external crown 22.

Si on se reporte maintenant à la figure 4, on constate que l'efficacité de l'invention est encore améliorée si l'air plus frais du second circuit II est encore refroidi. On profite pour cela de l'air du premier circuit, qui est temporairement plus frais avant qu'il n'ait franchi les injecteurs à haute pression 10 et le joint à labyrinthe ou à brosse 23 et après que l'air du second circuit a franchi son joint à labyrinthe ou à brosse 17. Il se trouve que les écoulements sont contigus dans une partie de cet état, puisqu'ils circulent alors dans le fond de chambre 28 et le canal divergent 20 qui ne sont séparés que par une cloison assez mince 37 du carter de stator 6. Il suffit alors d'établir des obstacles 38 tels que des nervures, des bossages ou des ondulations sur les deux faces de cette cloison 37 pour favoriser l'échange de chaleur entre les deux écoulements.Referring now to Figure 4, we see that the efficiency of the invention is further improved if the cooler air of the second circuit II is still cooled. This takes advantage of the air from the first circuit, which is temporarily cooler before it has passed through the high-pressure injectors 10 and the labyrinth or brush seal 23 and after the air from the second circuit has crossed its labyrinth or brush seal 17. It turns out that the flows are contiguous in a part of this state, since they then circulate in the chamber bottom 28 and the divergent channel 20 which are only separated by a fairly partition thin 37 of the stator housing 6. It then suffices to establish obstacles 38 such as ribs, bosses or undulations on the two faces of this partition 37 to promote heat exchange between the two flows.

Le disque de turbine 2 est porté à une température supérieure à 650°C dans la machine connue. L'utilisation de l'invention permet de réduire cette température de plusieurs dizaines de degrés pour le flasque 13. Le progrès est important si on considère le haut niveau de qualité déjà atteint avec les moteurs existants ; il pourra être exploité en recourant à des matières moins coûteuses pour construire le disque 2 et son flasque 13, ou en réduisant les débits de refroidissement.The turbine disk 2 is brought to a temperature above 650 ° C in the known machine. The use of the invention makes it possible to reduce this temperature by several tens of degrees for the flange 13. Progress is important if we consider the high level of quality already achieved with existing engines; it can be exploited by using less expensive materials to build the disc 2 and its flange 13, or by reducing the cooling rates.

Claims (6)

Dispositif de refroidissement d'un disque de turbine (2) couvert par un flasque (13) comprenant un premier (I) et un second (II) circuits de ventilation d'air originaires d'un stator (6) et débouchant respectivement devant une couronne interne (11) du disque et une couronne externe (22) du flasque (13), une portion du premier circuit (I) bifurquant vers un joint d'étanchéité (23) disposé entre le flasque et le stator puis devant le flasque (13) et parallèlement au flasque, vers la couronne externe (22) du flasque, caractérisé en ce qu'il comprend une pièce (30) située devant la couronne externe, traversée de premiers canaux (31) sensiblement parallèles à une surface de flanc (29) du flasque et prolongeant le premier circuit de ventilation et de seconds canaux (32) prolongeant le second circuit de ventilation, croisant les premiers canaux sans les couper, et se terminant devant la couronne externe (22).Device for cooling a turbine disc (2) covered by a flange (13) comprising a first (I) and a second (II) air ventilation circuits originating from a stator (6) and opening respectively in front of a inner ring (11) of the disc and an outer ring (22) of the flange (13), a portion of the first circuit (I) branching off towards a seal (23) disposed between the flange and the stator then in front of the flange ( 13) and parallel to the flange, towards the outer ring (22) of the flange, characterized in that it comprises a part (30) situated in front of the outer ring, crossed by first channels (31) substantially parallel to a flank surface ( 29) of the flange and extending the first ventilation circuit and second channels (32) extending the second ventilation circuit, crossing the first channels without cutting them, and ending in front of the outer ring (22). Dispositif de refroidissement d'un disque de turbine suivant la revendication 1, caractérisé en ce que le flasque (13) comprend une pièce (33) de guidage d'une portion centrifuge et courant le long de la surface de flanc (29) du flasque d'un écoulement d'air originaire du premier circuit de ventilation vers les premiers canaux (31).Turbine disc cooling device according to claim 1, characterized in that the flange (13) comprises a part (33) for guiding a centrifugal portion and running along the flank surface (29) of the flange an air flow originating from the first ventilation circuit towards the first channels (31). Dispositif de refroidissement d'un disque de turbine suivant la revendication 2, caractérisé en ce que la pièce de guidage est une crête à bord (34) frôlant la pièce (30) traversée par les canaux, qui est fixée au stator (6).Turbine disc cooling device according to claim 2, characterized in that the guide piece is a ridge on edge (34) bordering the piece (30) traversed by the channels, which is fixed to the stator (6). Dispositif de refroidissement d'un disque de turbine suivant l'une quelconque des revendications 1 à 3, caractérisé en ce que la pièce (30) traversée par les canaux comprend un écran (35) parallèle à la couronne externe (22) et situé entre celle-ci et les premiers canaux (31).Device for cooling a turbine disk according to any one of Claims 1 to 3, characterized in that the part (30) traversed by the channels comprises a screen (35) parallel to the outer ring (22) and located between the latter and the first channels (31). Dispositif de refroidissement d'un disque de turbine suivant la revendication 4, caractérisé en ce que les premiers canaux (31) et l'écran (35) s'étendent devant respectivement des portions radialement interne et externe de la couronne externe (22).Turbine disc cooling device according to claim 4, characterized in that the first channels (31) and the screen (35) extend in front of respectively radially inner and outer portions of the outer ring (22). Dispositif de refroidissement d'un disque de turbine suivant l'une quelconque des revendications 1 à 5, où les circuits de ventilation possèdent des portions contiguës en aval d'un joint à labyrinthe ou à brosse (17) au travers du second circuit de ventilation mais en amont d'un autre joint à labyrinthe ou à brosse (23) au travers du premier circuit de ventilation, les joints à labyrinthe étant jetés entre le stator (6) et un rotor (4) auquel appartient la turbine, caractérisé en ce que les portions contigues sont munies d'obstacles (38) fournissant un échange de chaleur entre les circuits.Device for cooling a turbine disc according to any one of Claims 1 to 5, in which the ventilation circuits have contiguous portions downstream of a labyrinth or brush seal (17) through the second ventilation circuit but upstream of another labyrinth or brush seal (23) through the first ventilation circuit, the labyrinth seals being thrown between the stator (6) and a rotor (4) to which the turbine belongs, characterized in that that the adjoining portions are provided with obstacles (38) providing a heat exchange between the circuits.
EP97400078A 1996-01-18 1997-01-16 Turbine disc cooling device Expired - Lifetime EP0785338B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9600521 1996-01-18
FR9600521A FR2743844B1 (en) 1996-01-18 1996-01-18 DEVICE FOR COOLING A TURBINE DISC

Publications (2)

Publication Number Publication Date
EP0785338A1 true EP0785338A1 (en) 1997-07-23
EP0785338B1 EP0785338B1 (en) 2000-03-15

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EP97400078A Expired - Lifetime EP0785338B1 (en) 1996-01-18 1997-01-16 Turbine disc cooling device

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US (1) US5800125A (en)
EP (1) EP0785338B1 (en)
CA (1) CA2195040C (en)
DE (1) DE69701405T2 (en)
FR (1) FR2743844B1 (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1367225A2 (en) 2002-05-30 2003-12-03 Mitsubishi Heavy Industries, Ltd. Gas turbine cooling arrangement and method of bleeding gas therefrom
EP1741874A2 (en) * 2005-07-01 2007-01-10 Rolls-Royce plc A mounting arrangement for turbine blades
EP2048324A1 (en) * 2007-10-11 2009-04-15 Snecma Turbine stator for aircraft turbomachine including a vibration damper device
EP1911937A3 (en) * 2006-10-14 2012-09-05 Rolls-Royce plc A flow cavity arrangement for gas turbine engine
KR101232609B1 (en) 2010-12-21 2013-02-13 두산중공업 주식회사 Gas turbine engine pre-swirl rotating-disk apparatus
EP2942483A1 (en) * 2014-04-01 2015-11-11 United Technologies Corporation Vented tangential on-board injector for a gas turbine engine
WO2018020131A1 (en) * 2016-07-29 2018-02-01 Safran Aircraft Engines Turbine comprising a ventilation system between rotor and stator
RU178381U1 (en) * 2017-08-16 2018-04-02 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Shock absorber for damping vibrations of a stator of a turbojet engine
WO2019168590A1 (en) * 2018-02-27 2019-09-06 Siemens Aktiengesellschaft Gas turbine engine with turbine cooling air delivery system

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DE19962244A1 (en) * 1999-12-22 2001-06-28 Rolls Royce Deutschland Cooling air guide system in the high pressure turbine section of a gas turbine engine
FR2881472B1 (en) * 2005-01-28 2011-07-15 Snecma Moteurs VENTILATION CIRCUIT FOR A HIGH PRESSURE TURBINE ROTOR IN A GAS TURBINE ENGINE
GB2426289B (en) * 2005-04-01 2007-07-04 Rolls Royce Plc Cooling system for a gas turbine engine
US7445424B1 (en) * 2006-04-22 2008-11-04 Florida Turbine Technologies, Inc. Passive thermostatic bypass flow control for a brush seal application
JP5134570B2 (en) * 2009-02-23 2013-01-30 三菱重工業株式会社 Turbine cooling structure and gas turbine
US8727703B2 (en) * 2010-09-07 2014-05-20 Siemens Energy, Inc. Gas turbine engine
DE102011101729B3 (en) * 2011-05-17 2012-09-27 Adc Gmbh Distribution block and distribution block with at least two distribution strips
EP3130750B1 (en) * 2015-08-14 2018-03-28 Ansaldo Energia Switzerland AG Gas turbine cooling system

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FR2292868A1 (en) * 1974-11-27 1976-06-25 Gen Electric LABYRINTH SEALING SYSTEM FOR GAS TURBINE
FR2439872A1 (en) * 1978-10-26 1980-05-23 Rolls Royce AIR-COOLED TURBINE FOR A GAS TURBINE ENGINE
GB2042643A (en) * 1979-01-02 1980-09-24 Rolls Royce Cooled Gas Turbine Engine
GB2135394A (en) * 1983-02-22 1984-08-30 Gen Electric Cooling gas turbine engines
GB2266345A (en) * 1992-04-23 1993-10-27 Snecma Ventilation circuit for the compressor and turbine discs of a turbomachine.
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines

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FR2292868A1 (en) * 1974-11-27 1976-06-25 Gen Electric LABYRINTH SEALING SYSTEM FOR GAS TURBINE
FR2439872A1 (en) * 1978-10-26 1980-05-23 Rolls Royce AIR-COOLED TURBINE FOR A GAS TURBINE ENGINE
GB2042643A (en) * 1979-01-02 1980-09-24 Rolls Royce Cooled Gas Turbine Engine
GB2135394A (en) * 1983-02-22 1984-08-30 Gen Electric Cooling gas turbine engines
GB2184167A (en) * 1983-02-22 1987-06-17 Gen Electric Cooling gas turbine engine components
GB2266345A (en) * 1992-04-23 1993-10-27 Snecma Ventilation circuit for the compressor and turbine discs of a turbomachine.
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1367225A3 (en) * 2002-05-30 2010-01-20 Mitsubishi Heavy Industries, Ltd. Gas turbine cooling arrangement and method of bleeding gas therefrom
EP1367225A2 (en) 2002-05-30 2003-12-03 Mitsubishi Heavy Industries, Ltd. Gas turbine cooling arrangement and method of bleeding gas therefrom
EP1741874A3 (en) * 2005-07-01 2014-01-22 Rolls-Royce plc A mounting arrangement for turbine blades
EP1741874A2 (en) * 2005-07-01 2007-01-10 Rolls-Royce plc A mounting arrangement for turbine blades
EP1911937A3 (en) * 2006-10-14 2012-09-05 Rolls-Royce plc A flow cavity arrangement for gas turbine engine
EP2048324A1 (en) * 2007-10-11 2009-04-15 Snecma Turbine stator for aircraft turbomachine including a vibration damper device
FR2922263A1 (en) * 2007-10-11 2009-04-17 Snecma Sa TURBINE STATOR FOR AN AIRCRAFT TURBINE ENGINE INCORPORATING A VIBRATION DAMPING DEVICE
US8133010B2 (en) 2007-10-11 2012-03-13 Snecma Turbine stator for aircraft turbine engine including a vibration damping device
RU2474697C2 (en) * 2007-10-11 2013-02-10 Снекма Aircraft gas turbine engine turbine stator with vibration damper
KR101232609B1 (en) 2010-12-21 2013-02-13 두산중공업 주식회사 Gas turbine engine pre-swirl rotating-disk apparatus
EP2942483A1 (en) * 2014-04-01 2015-11-11 United Technologies Corporation Vented tangential on-board injector for a gas turbine engine
US10697321B2 (en) 2014-04-01 2020-06-30 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
US10920611B2 (en) 2014-04-01 2021-02-16 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
WO2018020131A1 (en) * 2016-07-29 2018-02-01 Safran Aircraft Engines Turbine comprising a ventilation system between rotor and stator
FR3054606A1 (en) * 2016-07-29 2018-02-02 Safran Aircraft Engines TURBINE COMPRISING A VENTILATION SYSTEM BETWEEN ROTOR AND STATOR
US10808537B2 (en) 2016-07-29 2020-10-20 Safran Aircraft Engines Turbine comprising a ventilation system between rotor and stator
RU178381U1 (en) * 2017-08-16 2018-04-02 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Shock absorber for damping vibrations of a stator of a turbojet engine
WO2019168590A1 (en) * 2018-02-27 2019-09-06 Siemens Aktiengesellschaft Gas turbine engine with turbine cooling air delivery system

Also Published As

Publication number Publication date
DE69701405T2 (en) 2000-08-03
US5800125A (en) 1998-09-01
CA2195040C (en) 2005-11-15
FR2743844A1 (en) 1997-07-25
CA2195040A1 (en) 1997-07-19
DE69701405D1 (en) 2000-04-20
EP0785338B1 (en) 2000-03-15
FR2743844B1 (en) 1998-02-20

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