EP0785338B1 - Turbine disc cooling device - Google Patents

Turbine disc cooling device Download PDF

Info

Publication number
EP0785338B1
EP0785338B1 EP97400078A EP97400078A EP0785338B1 EP 0785338 B1 EP0785338 B1 EP 0785338B1 EP 97400078 A EP97400078 A EP 97400078A EP 97400078 A EP97400078 A EP 97400078A EP 0785338 B1 EP0785338 B1 EP 0785338B1
Authority
EP
European Patent Office
Prior art keywords
turbine
ducts
circuit
ventilating
plate
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP97400078A
Other languages
German (de)
French (fr)
Other versions
EP0785338A1 (en
Inventor
Christian Largillier
Gérard Jacques Stangalini
Marc Roger Marchi
Laurent Palmisano
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0785338A1 publication Critical patent/EP0785338A1/en
Application granted granted Critical
Publication of EP0785338B1 publication Critical patent/EP0785338B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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 turbine provided with a device for cooling of a turbine disk.
  • the high turbine pressure 1 starts in a disc 2 carrying a first stage of movable blades 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 located itself downstream of a high pressure compressor 7.
  • the gases resulting from the combustion of fuel in chamber 5 very strongly heat the disc 2, that it is therefore a question of cooling vigorously for maintain the material that composes it at a temperature compatible with maintaining its properties of mechanical resistance.
  • 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 line, uses air drawn just upstream of the combustion chamber 5 and which passes through a volume chamber 28 before leaving it by holes 8 for entering injection chambers 9 where air comes out of high pressure injectors 10 that accelerate and propel it at high speed towards the flank 14 of the 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 where it comes out through a labyrinth or brush seal 17 thrown away between these pieces and more specifically composed of wipers 18, i.e. circular ridges erected on rotor 4, which rub on a material abradable 19 fixed to stator 6, i.e. a soft material that they dig at the discretion of the expansions differentials to different machine speeds.
  • wipers 18, i.e. circular ridges erected on rotor 4 which rub on a material abradable 19 fixed to stator 6, i.e. a soft material that they dig at the discretion of the expansions differentials to different machine speeds.
  • Air pressure projects air out of the chamber 16 and in an annular and orientation channel 20 divergent, contiguous to part of the back of the chamber 28 over a large part of its length and from which the air comes out by upper injectors 36 which open out in front a radially outer ring 22 of the disc turbine 2, actually belonging to a flank surface 29 of the flange 13 secured to this disc.
  • the air from the second ventilation circuit exerts significant refrigeration on the outer ring 22 in reaching this area near the combustion gases and therefore more strongly heated.
  • the need to cool the whole disk 2 but especially its periphery justifies the duality of the cooling circuits, whose air can also come from other places of the machine.
  • part of the air from the first ventilation circuit does not pass through the holes 12 but bypasses the flange 13 by outside and goes through a labyrinth seal or brush 23, roughly similar to previous 17 and composed like him of wipers 24 erected on the flange 13 and an abradable layer 25 welded on a surface of the stator 6.
  • the invention consists in adding parts of which the function is to channel the flows so that their mixing is excluded and that the air of circuit II originating from the upper injectors 36 arrives without crowded on the outer ring 22; this air of circuit II is significantly cooler than that of first circuit I, because the labyrinth or brush 17 associated with it, heats the air less than Labyrinth seal 23, of larger diameter, and the air from the first circuit I is centrifuged at the outlet of labyrinth 23, therefore compressed, which heats it up also.
  • the invention therefore consists of a turbine fitted with a device for cooling a turbine disc, comprising first and second air ventilation circuits originating from a stator and opening respectively in front of a crown radially internally and a radially outer crown radially of a flank surface of the disc, characterized in that it comprises a part located in front of said radially outer crown, crossing of first channels substantially perpendicular to the axis of the turbine and 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 crown distributor 30 integral with stator 6 and located in front the outer ring 22 to be cooled, a short distance away from her.
  • the distributor crown 30 is traversed by axial channels 32 which extend the injectors upper 36 to end in front of the outer crown 22, and the channels 32 are separated by channels substantially radial 31 which intersect the previous ones without cutting them, as shown in detail in section in Figure 3.
  • the interior of the distributor crown 30 is arranged to minimize pressure drops; this is how the axial channels 32 can be connected to oblique direction injectors 36, bend 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 channels radial 31; mixing of flows does occur that at the periphery of the disc 2, beyond the crown external 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 of several tens of degrees for the flask 13. Progress is important if we consider the high level of quality already achieved with engines existing; it can be exploited by using less expensive materials to build disc 2 and its flange 13, or by reducing the flow rates of cooling.

Landscapes

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

Description

L'invention concerne une turbine munie d'un dispositif de refroidissement d'un disque de turbine.The invention relates to a turbine provided with a device for cooling of a turbine disk.

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 a machine shown in Figure 1, the high turbine pressure 1 starts in a disc 2 carrying a first stage of movable blades 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 located itself 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 fuel in chamber 5 very strongly heat the disc 2, that it is therefore a question of cooling vigorously for maintain the material that composes it at a temperature compatible with maintaining its properties of mechanical resistance. 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 line, uses air drawn just upstream of the combustion chamber 5 and which passes through a volume chamber 28 before leaving it by holes 8 for entering injection chambers 9 where air comes out of high pressure injectors 10 that accelerate and propel it at high speed towards the flank 14 of the 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 actually reaches an internal crown 11 belonging to the side 14 after having passed through orifices 12 of a flange 13 covering disc 2, after which rotation of disc 2 produces a centrifugal force on the air flow, which directs outward; the air is guided between the flank surface 14 of disc 2 and flange 13 for finally cool the periphery of disc 2 in 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 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 where it comes out through a labyrinth or brush seal 17 thrown away between these pieces and more specifically composed of wipers 18, i.e. circular ridges erected on rotor 4, which rub on a material abradable 19 fixed to stator 6, i.e. a soft material that they dig at the discretion of the expansions differentials to different machine speeds. Air pressure projects air out of the chamber 16 and in an annular and orientation channel 20 divergent, contiguous to part of the back of the chamber 28 over a large part of its length and from which the air comes out by upper injectors 36 which open out in front a radially outer ring 22 of the disc turbine 2, actually belonging to a flank 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 from the second ventilation circuit exerts significant refrigeration on the outer ring 22 in reaching this area near the combustion gases and therefore more strongly heated. The need to cool the whole disk 2 but especially its periphery justifies the duality of the cooling circuits, whose air can also 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 holes 12 but bypasses the flange 13 by outside and goes through a labyrinth seal or brush 23, roughly similar to previous 17 and composed like him of wipers 24 erected on the flange 13 and an abradable layer 25 welded on a surface of the stator 6. The centrifugal forces that the flange 13 exerts on this portion of the first flow straighten it like the previous portion and make it run along the flank surface 29 for finally cross the flow of the second ventilation circuit in front of the outer 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 rests on the finding that this situation was not ideal because the air flow from circuit I is clearly 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 of which the function is to channel the flows so that their mixing is excluded and that the air of circuit II originating from the upper injectors 36 arrives without crowded on the outer ring 22; this air of circuit II is significantly cooler than that of first circuit I, because the labyrinth or brush 17 associated with it, heats the air less than Labyrinth seal 23, of larger diameter, and the air from the first circuit I is centrifuged at the outlet of labyrinth 23, therefore compressed, which heats it up also.

Ce surcroít 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 of the second circuit more than compensates for the loss of refrigeration following the temporary diversion of the air flow of the first flow, whose action is lesser.

Sous sa forme la plus générale, l'invention consiste donc en une turbine munie d'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 radialement interne et une couronne radialement externe radialement d'une surface de flanc du disque, caractérisé en ce qu'il comprend une pièce située devant ladite couronne radialement externe, traversée de premiers canaux sensiblement perpendiculaires à l'axe de la turbine et 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 turbine fitted with a device for cooling a turbine disc, comprising first and second air ventilation circuits originating from a stator and opening respectively in front of a crown radially internally and a radially outer crown radially of a flank surface of the disc, characterized in that it comprises a part located in front of said radially outer crown, crossing of first channels substantially perpendicular to the axis of the turbine and 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 (voir par example GB-A-2 135 394) 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:
  • FIG. 1, already described, illustrates an already known design (see for example GB-A-2 135 394) 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 crown distributor 30 integral with stator 6 and located in front the outer ring 22 to be cooled, a short distance away from her. The distributor crown 30 is traversed by axial channels 32 which extend the injectors upper 36 to end in front of the outer crown 22, and the channels 32 are separated by channels substantially radial 31 which intersect the previous ones without cutting them, as shown in detail in section in 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 drops; this is how the axial channels 32 can be connected to oblique direction injectors 36, bend 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 channels radial 31; mixing of flows does occur that at the periphery of the disc 2, beyond the crown external 22. To further reduce opportunities for mixture, we can build the flange 13 with a wiper 33 on its flank surface 14, that is to say a ridge whose free end 34 is close to the crown dispenser 30 and whose purpose is to guide the air of the flow I running along the flank surface 29 of the flange 13 towards the radial channels 31, without it allow to slide to the outer crown 22. In the illustrated embodiment where the part of the distributor crown 30 carrying channels 31 and 32 extends in front of a radially inner portion of the outer ring 22, it is possible to add to the distributor crown 30 a screen 35 parallel to the outer ring 22 and which extends in front of the rest of this, to forcefully separate the flows from two circuits beyond the outer ring 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.If we now refer to Figure 4, we finds that the effectiveness of the invention is still improved if the cooler air of the second circuit II is still cooled. We take advantage of the air of first circuit, which is temporarily cooler before he crossed the injectors at high pressure 10 and the labyrinth or brush seal 23 and after the air from the second circuit has passed its joint at labyrinth or brush 17. It turns out that the flows are contiguous in part of this state, since they then circulate in the back of the chamber 28 and the divergent channel 20 which are only separated by a fairly thin partition 37 of the stator housing 6. It then it suffices to establish obstacles 38 such as ribs, bosses or ripples on both sides of this partition 37 to promote the exchange of heat 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 of several tens of degrees for the flask 13. Progress is important if we consider the high level of quality already achieved with engines existing; it can be exploited by using less expensive materials to build disc 2 and its flange 13, or by reducing the flow rates of cooling.

Claims (6)

  1. A turbine having means for cooling a turbine disc (2) covered by a plate (13) comprising a first ventilating air circuit (I) and a second ventilating air circuit (II) which start from a stator (6) and terminate respectively in front of a radially inner ring (11) of the disc and a radially outer ring (22) of the plate (13), a part of the first circuit (I) branching off towards a seal (23) disposed between the plate and the stator and then in front of and parallel to the plate (13) towards the radially outer ring (22) thereof, characterised in that it comprises a member (30) which is disposed in front of the outer ring (22) and which is pierced with first ducts (31) substantially perpendicular to the turbine axis and parallel to a flank surface (29) of the plate (13) and extending the first ventilating circuit and with second ducts (32) extending the second ventilating circuit, the second ducts crossing the first ducts without cutting them and terminating in front of the radially outer ring (22).
  2. A turbine having turbine disc cooling means according to claim 1, characterised in that the plate (13) comprises a member (33) for guiding towards the first ducts (31) a portion of an air flow originating from the first ventilating circuit and flowing centrifugally along the plate flank surface (29).
  3. A turbine having turbine disc cooling means according to claim 2, characterised in that the guide member (33) is an edge crest (34) which wipes the member (30), which is secured to the stator (6).
  4. A turbine having turbine disc cooling means according to any of claims 1 to 3, characterised in that the member (30) pierced with the ducts comprises a screen (35) which is disposed parallel to the outer ring (22) and between the latter and the first ducts (31).
  5. A turbine having turbine disc cooling means according to claim 4, characterised in that the first ducts (31) and the screen (35) extend in front of the radially inner and outer parts respectively of the outer ring (22).
  6. A turbine having turbine disc cooling means according to any of claims 1 to 5 wherein the ventilating circuits have contiguous parts downstream of a labyrinth or brush seal (17) across the second ventilating circuit but upstream of another labyrinth or brush seal (23) across the first ventilating circuit, the labyrinth seals being inserted between the stator (6) and a rotor (4) to which the turbine belongs, characterised in that the contiguous parts have obstacles (38) which promote 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
FR9600521A FR2743844B1 (en) 1996-01-18 1996-01-18 DEVICE FOR COOLING A TURBINE DISC
FR9600521 1996-01-18

Publications (2)

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

Family

ID=9488209

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97400078A Expired - Lifetime EP0785338B1 (en) 1996-01-18 1997-01-16 Turbine disc cooling device

Country Status (5)

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

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US6773225B2 (en) 2002-05-30 2004-08-10 Mitsubishi Heavy Industries, Ltd. Gas turbine and method of bleeding gas therefrom
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
GB0513468D0 (en) * 2005-07-01 2005-08-10 Rolls Royce Plc A mounting arrangement for turbine blades
US7445424B1 (en) * 2006-04-22 2008-11-04 Florida Turbine Technologies, Inc. Passive thermostatic bypass flow control for a brush seal application
GB0620430D0 (en) * 2006-10-14 2006-11-22 Rolls Royce Plc A flow cavity arrangement
FR2922263B1 (en) * 2007-10-11 2009-12-11 Snecma TURBINE STATOR FOR AN AIRCRAFT TURBINE ENGINE INCORPORATING A VIBRATION DAMPING DEVICE
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
KR101232609B1 (en) 2010-12-21 2013-02-13 두산중공업 주식회사 Gas turbine engine pre-swirl rotating-disk apparatus
DE102011101729B3 (en) * 2011-05-17 2012-09-27 Adc Gmbh Distribution block and distribution block with at least two distribution strips
EP2942483B2 (en) * 2014-04-01 2022-09-28 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
EP3130750B1 (en) * 2015-08-14 2018-03-28 Ansaldo Energia Switzerland AG Gas turbine cooling system
FR3054606B1 (en) * 2016-07-29 2020-04-17 Safran Aircraft Engines TURBINE INCLUDING 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
WO2019168501A1 (en) * 2018-02-27 2019-09-06 Siemens Aktiengesellschaft Turbine cooling air delivery system

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3989410A (en) * 1974-11-27 1976-11-02 General Electric Company Labyrinth seal system
US4348157A (en) * 1978-10-26 1982-09-07 Rolls-Royce Limited Air cooled turbine for a gas turbine engine
GB2042643B (en) * 1979-01-02 1982-12-08 Rolls Royce Cooled gas turbine engine
US4466239A (en) * 1983-02-22 1984-08-21 General Electric Company Gas turbine engine with improved air cooling circuit
FR2690482B1 (en) * 1992-04-23 1994-06-03 Snecma CIRCUIT FOR VENTILATION OF COMPRESSOR AND TURBINE DISCS.
US5402636A (en) * 1993-12-06 1995-04-04 United Technologies Corporation Anti-contamination thrust balancing system for gas turbine engines

Also Published As

Publication number Publication date
DE69701405D1 (en) 2000-04-20
US5800125A (en) 1998-09-01
FR2743844B1 (en) 1998-02-20
CA2195040A1 (en) 1997-07-19
CA2195040C (en) 2005-11-15
EP0785338A1 (en) 1997-07-23
DE69701405T2 (en) 2000-08-03
FR2743844A1 (en) 1997-07-25

Similar Documents

Publication Publication Date Title
EP0785338B1 (en) Turbine disc cooling device
EP1881181B1 (en) Turbomachine
EP1882826B1 (en) Ventilation system for an downstream cavity of a centrifugal compressor impeller
EP0651137B1 (en) Turbomachine with heating of the rotor discs during engine acceleration
EP0893577B1 (en) Cooling device for a turbomachine shroud
EP1882815B1 (en) Turbomachine comprising a system for cooling the downstream face of a centrifugal compressor impeller
EP1881182B1 (en) Cooling system for a downstream cavity of a centrifugal compressor impeller
EP1840028B1 (en) De-icing system for the inlet cone of an aircraft turboengine
EP1881179B1 (en) System for ventilating the wall of a combustion chamber in a turbomachine
EP2440746B1 (en) Turbine engine including an improved means for adjusting the flow rate of a cooling air flow extracted at the output of a high-pressure compressor
EP1785671A1 (en) Ventilated combustor dome
EP0177408B1 (en) Apparatus for the automatic control of the play of a labyrinth seal of a turbo machine
CA2715209A1 (en) Ventilation for a turbine wheel in a turbomachine
FR2742804A1 (en) LUBRICATION ENCLOSURE ROTOR ROTOR
FR2955145A1 (en) HIGH PRESSURE TURBINE DISPENSER OF A TURBOREACTOR
FR2605060A1 (en) CENTRIFUGAL WHEEL PUMP WITH BANDAGE
FR2630162A1 (en) ENTRY CONE ANTI-ICING SYSTEM FOR GAS TURBOTORS
FR2905435A1 (en) Clutch device i.e. humid functioning disc clutch, for gear box double disc clutch, has channel with annular protrusion which radially deviates towards interior of cooling fluid outflow before its release to radial outflow opening
EP3350417B2 (en) Device for ventilation of a turbomachine turbine casing
EP0552089B1 (en) Device for the spraying of a liquid, particularly of a liquid fuel in a burner
EP4081698B1 (en) Turbine having an internal secondary space equipped with fins for correcting gyration of an airflow
FR2992346A1 (en) Blade for non-ducted propeller for turbo-shaft engine of aircraft, has pipe provided for circulation of cooling air to pass through blade, where pipe comprises inlet opening to blade base part and outlet opening radially relative to inlet
FR2637251A1 (en) Anti-icing device for the intake cowl of an aircraft engine
FR2549535A1 (en) DEVICE FOR SEPARATING FOREIGN PARTICLES OR DROPS FROM TURBOMACHINE LEAKAGE GAS CURRENTS
FR2996588A1 (en) Propeller for e.g. aeronautical turboengines, has pivots with counterweight system that includes pair of inner channels for airflow ventilation discharge to capture and guide airflow directly in contact with blade foot borne by pivots

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19970203

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19981208

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 69701405

Country of ref document: DE

Date of ref document: 20000420

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20000410

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20120517 AND 20120523

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20141219

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20141218

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20160111

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 69701405

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20160116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160802

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160116

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717