EP1445421A1 - Apparatus for the ventilation of a high pressure turbine rotor - Google Patents

Apparatus for the ventilation of a high pressure turbine rotor Download PDF

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Publication number
EP1445421A1
EP1445421A1 EP04100404A EP04100404A EP1445421A1 EP 1445421 A1 EP1445421 A1 EP 1445421A1 EP 04100404 A EP04100404 A EP 04100404A EP 04100404 A EP04100404 A EP 04100404A EP 1445421 A1 EP1445421 A1 EP 1445421A1
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EP
European Patent Office
Prior art keywords
upstream
downstream
disc
turbine
flange
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Granted
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EP04100404A
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German (de)
French (fr)
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EP1445421B1 (en
Inventor
Patrick Rossi
Jean-Claude Christian Taillant
Maurice Guy Judet
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Safran Aircraft Engines SAS
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SNECMA Moteurs SA
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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
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc

Definitions

  • the present invention relates so general to the field of ventilation of a rotor high pressure turbine of a turbomachine.
  • the invention relates to a device for ventilating a turbine rotor high pressure, including an upstream turbine disc as well as a downstream turbine disk.
  • Figure 1 shows a turbine rotor high pressure 1 conventional of the prior art, disposed downstream of a combustion chamber 2, and comprising an upstream turbine disk 3 fitted with blades 4, as well as a downstream turbine disk 5 equipped vanes 6.
  • the upstream disc 3 is provided on the one hand with a upstream flange 8 ensuring its attachment to a spacer 9 arranged around a rotor shaft 11 of a turbine low pressure, and on the other hand of a downstream flange 10 fixedly assembled to an upstream flange 12 of the downstream disc 5.
  • an inter-disc seal 14 worn by a hollow structure 16 integral with a storey fixed distributor 18 or stator, is located at the assembly between the two flanges 10 and 12.
  • the seal inter-disc 14, of the labyrinth joint type allows well to create a separation between the two floors rotor 20 and 22, arranged on either side of the distributor stage 18.
  • downstream disc 5 has a downstream flange 13, also assembled on the spacer 9 surrounding the shaft 11 of the low pressure turbine.
  • a first air flow of cooling D1 taken from the bottom of the combustion 2 is delivered in a delimited cavity 26 on the one hand using a downstream face of a labyrinth upstream 24 disposed near the upstream disc 3, and on the other hand using an upstream face of this same upstream disc 3.
  • This air flow D1 is effectively taken from the bottom of the combustion chamber 2, then routed into a cavity 30, in particular delimited by an upstream labyrinth seal 32 and a seal downstream labyrinth 34, via a conduit 28 arranged in an enclosure 29 separating the labyrinth upstream 24 from the bottom of the combustion chamber 2, thus that using injectors 36 arranged in the extension of the conduit 28 and opening into the cavity 30.
  • the seals 32 and 34 are arranged so as to be in contact with the upstream labyrinth 24.
  • cooling air located in the cavity 30 is able to penetrate into the cavity 26 by using orifices 38 provided in a upstream part of the upstream labyrinth 24, these orifices 38 being of axes substantially perpendicular to the axis longitudinal 40 of the turbine.
  • cooling D1 circulates in cavity 26 first longitudinally then radially outwards the along the upstream face of the upstream labyrinth 24 in order to cool, then enter cells 4a containing the feet of the blades 4 so as to cool these latest.
  • a second air flow of D2 cooling also taken from the bottom of combustion chamber 2, enters the enclosure 29 and flows through orifices 44 and 42, respectively provided in the upstream part of the upstream labyrinth 24, and in the upstream flange 8 of the disc upstream 3.
  • the second cooling air flow D2 borrows a annular chamber 46 internally bounded by the spacer 9, and externally delimited by successively, from upstream to downstream, the flange 8, a bore inside 48 of the upstream disc 3, the flanges 10 and 12, a inner bore 50 of the downstream disc 5, and the flange 13.
  • a first part D2a of the second air flow of cooling D2 flows through orifices 52 made in the downstream flange 10 of the upstream disc 3, so to join the gap 19 located between the floor fixed distributor 18 and the rotor stage 20, like the schematically represents the arrow referenced D2a.
  • the air flow d shown schematically in Figure 1 corresponds to an air leak at the level of the cells 4a.
  • a second part D2b of the second cooling air flow D2 flows through orifices 54 formed in the downstream flange 13 of the disc downstream 5, to penetrate inside a cavity 56 delimited on the one hand using an upstream face of a downstream labyrinth 58 disposed near the downstream disc 5, and on the other hand using a downstream face of this same downstream disc 5.
  • the rotor ventilation device therefore has two cooling circuits separate, each associated with one of the two discs of turbine, and respectively powered by the first and second cooling air flows D1 and D2.
  • the invention therefore aims to provide a ventilation device of a high turbine rotor pressure of a turbomachine, the turbine being arranged downstream of a combustion chamber and comprising upstream and downstream turbine discs fitted with blades, the device comprising a cooling circuit fitted with injectors arranged upstream of the upstream disc and being supplied by a cooling air flow D taken from the bottom of the combustion chamber, the device at least partially remedying the disadvantages mentioned above relating to the achievements of art prior.
  • the invention relates to a ventilation device of a high turbine rotor pressure of a turbomachine, the turbine being arranged downstream of a combustion chamber and comprising a upstream turbine disk fitted with blades and a downstream turbine disk also fitted with blades, the device comprising a cooling circuit fitted with injectors arranged upstream of the upstream disc, the circuit being supplied by an air flow of cooling D taken from the bottom of the combustion.
  • the circuit cooling is arranged so that the flow cooling air D from the injectors crosses holes made in an upstream flange of the upstream disc allowing its attachment to an upstream flange of the downstream disc, so that this air flow of cooling D flows axially downstream between an inner bore of the upstream disc and an upstream flange of the downstream disc authorizing its attachment to a flange downstream of a high pressure compressor as well as the centering of the upstream disc, the ventilation device further comprising a single labyrinth integral with one of the two turbine disks and being interposed between these two discs, so that the air flow of cooling D separates into a first flow F1 flowing between a downstream face of the upstream disc and a upstream face of the single labyrinth towards the blades of the upstream disc, and in a second flow F2 circulating between an upstream face of the downstream disc and a downstream face of the single labyrinth towards the disc blades downstream.
  • the device ventilation no longer has two labyrinths respectively associated with the upstream turbine disks and downstream, but has a unique inter-disc labyrinth each of the upstream and downstream faces of which is intended for guide a flow of cooling air towards blades. Reducing the number of parts used therefore considerably reduces the mass, size and cost of production of the rotor.
  • the specific positioning of the unique maze leads the latter to be less thermally stressed that a labyrinth arranged in upstream of the upstream disk, mainly due to its location in relation to the combustion chamber, and since the air flow temperature of cooling D drops significantly during passage in the inner bore of the upstream disc. This characteristic thus generates an increase in the lifespan of this labyrinth, compared to the duration of life that an upstream labyrinth could present prior art.
  • the adjacent cavity jointly delimited by an upstream face of the disc downstream and through a downstream face of the single labyrinth is advantageously used to reduce the pressure feeding the blades of the downstream disc.
  • the weak pressure inside this adjacent cavity allows actually not having to provide holes feeding blades that are too small, which are difficult to achieve.
  • the rotor made more compact by reducing the number of elements components of the rotor allows a reconciliation of the bearing under chamber of the upstream and downstream discs, so that it is then possible to obtain a better control of games at the top of blades, and therefore a higher efficiency of the high pressure turbine.
  • FIG 2 it is depicted a high pressure turbine 100 of a turbojet engine, comprising a ventilation device of the turbine rotor according to one embodiment preferred of the present invention. Note that on the Figure 2, the elements bearing the same references digital than those attached to the elements shown in Figure 1 correspond to identical or similar elements.
  • Figure 2 shows a turbine 100 which differs first of all from turbine 1 of prior art by the fact that an air flow of cooling D, taken from the bottom of the combustion 2 and able to pass through the injectors 36, is intended to simultaneously feed the blades 4 and 6 of upstream 3 and downstream 5 discs.
  • the cooling air flow D from the injectors 36 then enters a cavity 64 partially delimited by an upstream flange 66 of the upstream turbine disk 3, this upstream flange 66 main function of which is to secure the this upstream disc 3 on an upstream flange 78 of the downstream disc 5.
  • this cavity 64 is also jointly delimited by the upstream joint 32 and the downstream joint 34, preferably of the joint type labyrinth, arranged near the injectors 36 respectively upstream and downstream of the latter.
  • the upstream seal 32 cooperates with a downstream flange 70 of the high pressure turbine, this downstream flange 70 being formed so as to be locate radially outward relative to the upstream flange 66.
  • the upstream seal 32 closes the cavity 64 by matching the upstream end of the flange upstream 66.
  • the downstream seal 34 cooperates with a secondary upstream flange 72 of the upstream turbine disk 3, arranged so as to lie radially towards the exterior with respect to the upstream flange 66.
  • the cooling air escaping from the cavity 64 by the downstream seal 34 can flow radially towards outside, along the upstream face of the upstream disc 3, towards the blades 4.
  • Ports 74 are provided in the flange upstream 66 of the upstream turbine disk 3, so that the cooling air flow D can be routed towards the two turbine disks 3 and 5.
  • the orifices 74 are preferably arranged so as to be locate radially opposite the injectors 36.
  • the cooling air flow D enters a annular chamber 76 of axis 40, delimited externally via the upstream flange 66 of the disc upstream 3, and using the internal bore 48 of this same disc.
  • the annular chamber 76 is internally bounded by the upstream flange 78 of the downstream disc 5, this upstream flange 78 having for main function of securing this disc downstream 5 on the upstream flange 66 of the upstream disc 3, and center the entire high pressure turbine 100 on a downstream flange 79 of a high pressure compressor.
  • the cooling air flow D can then flow axially downstream between the bore interior 48 and the upstream flange 78, so that the upstream turbine disc 3 can be suitably cooled by contact of cooling air with its internal bore 48.
  • the ventilation device comprises a single labyrinth 80 interposed between the discs of turbine 3 and 5, and is integral with one of these two discs.
  • the labyrinth single 80 also called inter-disc labyrinth, is attached to a secondary upstream flange 82 of the disc downstream turbine 5, the latter being arranged so as to be locate radially outward relative to the upstream flange 78.
  • the labyrinth 80 extends radially up to the fixed distributor stage 18 or stator provided between the two rotor stages 20 and 22, and has an inner bore 83 surrounding the upstream flange 78 of the disc 5, this bore 83 preferably having a diameter substantially identical to the diameter of the inner bore 48 of the disc 3.
  • the first F1 flow therefore flows in a cavity 68 located between the downstream face of the disc upstream turbine 3 and the upstream face of labyrinth 80 so to cool the downstream face of the disc 3, then penetrate in cells 4a containing the feet of the blades 4 in order to cool them too.
  • the second flow F2 flows in a cavity 69 located between the upstream face of the disc downstream turbine 5 and the downstream face of the same labyrinth 80 in order to cool the upstream face of the disc 5, then penetrates into cells 6a containing the feet of vanes 6 in order to cool them as well.
  • a plurality 84 is made in the upstream flange secondary 82 of the downstream disc 5.
  • the ventilation according to the invention is such that the flow cooling air D taken from the chamber bottom 2 and intended to supply simultaneously blades 4 and 6, follows a circuit of one-time cooling to exit the passage between the bore 48 of the upstream disc 3 and the upstream flange 78 of the downstream turbine disk 5.
  • This characteristic specific greatly simplifies the design of turbine 100 relative to that of turbine 1 of the prior art, in which two air flows of cooling were taken from the bottom of the combustion 2, in order to borrow two circuits of totally separate cooling.
  • the upstream flange 78 of the disc downstream turbine 5 has a plurality of orifices 86 capable of being crossed by a third flow F3 of the cooling air flow D.
  • This third flow F3 is therefore routed from the annular chamber 76 to a annular space 88 of the same axis, space 88 being located on the one hand between the upstream flange 78 of the downstream disc 5 and the internal bore 50 of this same downstream disc 5, and on the other hand the spacer 9 arranged around the rotor shaft 11 of the low pressure turbine.
  • the flow of cooling air F3 can flow axially downstream in the annular space 88, in order to cool the downstream disc 5 by contact of the air with its internal bore 50.
  • the third flow F3 is then evacuated downstream of the turbine 100 by the orifices 54 formed on the downstream flange 13 of the disc downstream turbine 5, this downstream flange 13 participating also to the outer delimitation of space annular 88 and being assembled on the spacer 9 axis 40.

Abstract

The device has a coolant circuit allowing cooling air to flow via openings in an upstream support (66) of an upstream disc. The air circulates downstream between an interior boring (48) of the disc and an upstream flange (78) of a downstream disc. A labyrinth (80) placed between the two discs separates the air flow into two (F1, F2), to circulate on both sides of the labyrinth in the direction of paddles (4, 6).

Description

DOMAINE TECHNIQUETECHNICAL AREA

La présente invention se rapporte de façon générale au domaine de la ventilation d'un rotor de turbine à haute pression d'une turbomachine.The present invention relates so general to the field of ventilation of a rotor high pressure turbine of a turbomachine.

Plus précisément, l'invention se rapporte à un dispositif de ventilation d'un rotor de turbine à haute pression, comprenant un disque de turbine amont ainsi qu'un disque de turbine aval.More specifically, the invention relates to a device for ventilating a turbine rotor high pressure, including an upstream turbine disc as well as a downstream turbine disk.

ETAT DE LA TECHNIQUE ANTERIEURESTATE OF THE PRIOR ART

La figure 1 représente un rotor de turbine à haute pression 1 classique de l'art antérieur, disposé en aval d'une chambre de combustion 2, et comportant un disque de turbine amont 3 équipé d'aubes 4, ainsi que d'un disque de turbine aval 5 équipé d'aubes 6.Figure 1 shows a turbine rotor high pressure 1 conventional of the prior art, disposed downstream of a combustion chamber 2, and comprising an upstream turbine disk 3 fitted with blades 4, as well as a downstream turbine disk 5 equipped vanes 6.

Le disque amont 3 est muni d'une part d'une bride amont 8 assurant sa fixation sur une entretoise 9 disposée autour d'un arbre 11 de rotor d'une turbine basse pression, et d'autre part d'une bride aval 10 assemblée fixement à une bride amont 12 du disque aval 5. Il est précisé qu'un joint inter-disque 14, porté par une structure creuse 16 solidaire d'un étage distributeur fixe 18 ou stator, est situé au niveau de l'assemblage entres les deux brides 10 et 12. Le joint inter-disque 14, du type joint à labyrinthe, permet ainsi de créer une séparation entre les deux étages rotoriques 20 et 22, disposés de part et d'autre de l'étage distributeur 18.The upstream disc 3 is provided on the one hand with a upstream flange 8 ensuring its attachment to a spacer 9 arranged around a rotor shaft 11 of a turbine low pressure, and on the other hand of a downstream flange 10 fixedly assembled to an upstream flange 12 of the downstream disc 5. It is specified that an inter-disc seal 14, worn by a hollow structure 16 integral with a storey fixed distributor 18 or stator, is located at the assembly between the two flanges 10 and 12. The seal inter-disc 14, of the labyrinth joint type, allows well to create a separation between the two floors rotor 20 and 22, arranged on either side of the distributor stage 18.

Par ailleurs, le disque aval 5 comporte une bride aval 13, également assemblée sur l'entretoise 9 entourant l'arbre 11 de la turbine basse pression.Furthermore, the downstream disc 5 has a downstream flange 13, also assembled on the spacer 9 surrounding the shaft 11 of the low pressure turbine.

Dans ce type de turbine 1 classique de l'art antérieur, un premier débit d'air de refroidissement D1 prélevé en fond de chambre de combustion 2 est délivré dans une cavité 26 délimitée d'une part à l'aide d'une face aval d'un labyrinthe amont 24 disposé à proximité du disque amont 3, et d'autre part à l'aide d'une face amont de ce même disque amont 3. Ce débit d'air D1 est effectivement prélevé dans le fond de la chambre de combustion 2, puis acheminé dans une cavité 30 notamment délimitée par un joint à labyrinthe amont 32 et un joint à labyrinthe aval 34, par l'intermédiaire d'un conduit 28 disposé dans une enceinte 29 séparant le labyrinthe amont 24 du fond de la chambre de combustion 2, ainsi qu'à l'aide d'injecteurs 36 agencés dans le prolongement du conduit 28 et débouchant dans la cavité 30. Notons que les joints 32 et 34 sont agencés de façon à être en contact avec le labyrinthe amont 24.In this type of turbine 1 conventional prior art, a first air flow of cooling D1 taken from the bottom of the combustion 2 is delivered in a delimited cavity 26 on the one hand using a downstream face of a labyrinth upstream 24 disposed near the upstream disc 3, and on the other hand using an upstream face of this same upstream disc 3. This air flow D1 is effectively taken from the bottom of the combustion chamber 2, then routed into a cavity 30, in particular delimited by an upstream labyrinth seal 32 and a seal downstream labyrinth 34, via a conduit 28 arranged in an enclosure 29 separating the labyrinth upstream 24 from the bottom of the combustion chamber 2, thus that using injectors 36 arranged in the extension of the conduit 28 and opening into the cavity 30. Note that the seals 32 and 34 are arranged so as to be in contact with the upstream labyrinth 24.

De plus, l'air de refroidissement se situant dans la cavité 30 est apte à pénétrer dans la cavité 26 en empruntant des orifices 38 prévus dans une partie amont du labyrinthe amont 24, ces orifices 38 étant d'axes sensiblement perpendiculaires à l'axe longitudinal 40 de la turbine.In addition, the cooling air located in the cavity 30 is able to penetrate into the cavity 26 by using orifices 38 provided in a upstream part of the upstream labyrinth 24, these orifices 38 being of axes substantially perpendicular to the axis longitudinal 40 of the turbine.

De cette façon, le débit d'air de refroidissement D1 circule dans la cavité 26 d'abord longitudinalement puis radialement vers l'extérieur le long de la face amont du labyrinthe amont 24 afin de le refroidir, puis pénètre dans des alvéoles 4a contenant les pieds des aubes 4 afin de refroidir également ces dernières.In this way, the air flow of cooling D1 circulates in cavity 26 first longitudinally then radially outwards the along the upstream face of the upstream labyrinth 24 in order to cool, then enter cells 4a containing the feet of the blades 4 so as to cool these latest.

En outre, un second débit d'air de refroidissement D2, également prélevé en fond de chambre de combustion 2, pénètre dans l'enceinte 29 et s'écoule à travers des orifices 44 et 42, respectivement prévus dans la partie amont du labyrinthe amont 24, et dans la bride amont 8 du disque amont 3. Une fois les orifices 44 et 42 traversés, le second débit d'air de refroidissement D2 emprunte une chambre annulaire 46 intérieurement délimitée par l'entretoise 9, et extérieurement délimitée par successivement, d'amont en aval, la bride 8, un alésage intérieur 48 du disque amont 3, les brides 10 et 12, un alésage intérieur 50 du disque aval 5, et la bride 13.In addition, a second air flow of D2 cooling, also taken from the bottom of combustion chamber 2, enters the enclosure 29 and flows through orifices 44 and 42, respectively provided in the upstream part of the upstream labyrinth 24, and in the upstream flange 8 of the disc upstream 3. Once the orifices 44 and 42 have been crossed, the second cooling air flow D2 borrows a annular chamber 46 internally bounded by the spacer 9, and externally delimited by successively, from upstream to downstream, the flange 8, a bore inside 48 of the upstream disc 3, the flanges 10 and 12, a inner bore 50 of the downstream disc 5, and the flange 13.

A partir de la chambre annulaire 46, une première partie D2a du second débit d'air de refroidissement D2 s'écoule à travers des orifices 52 pratiqués dans la bride aval 10 du disque amont 3, afin de rejoindre l'interstice 19 situé entre l'étage distributeur fixe 18 et l'étage rotorique 20, comme le représente schématiquement la flèche référencée D2a. A titre indicatif, il est noté que le débit d'air d représenté schématiquement sur la figure 1 correspond à une fuite d'air au niveau des alvéoles 4a.From the annular chamber 46, a first part D2a of the second air flow of cooling D2 flows through orifices 52 made in the downstream flange 10 of the upstream disc 3, so to join the gap 19 located between the floor fixed distributor 18 and the rotor stage 20, like the schematically represents the arrow referenced D2a. AT As an indication, it is noted that the air flow d shown schematically in Figure 1 corresponds to an air leak at the level of the cells 4a.

De plus, une seconde partie D2b du second débit d'air de refroidissement D2 s'écoule à travers des orifices 54 ménagés dans la bride aval 13 du disque aval 5, pour pénétrer à l'intérieur d'une cavité 56 délimitée d'une part à l'aide d'une face amont d'un labyrinthe aval 58 disposé à proximité du disque aval 5, et d'autre part à l'aide d'une face aval de ce même disque aval 5.In addition, a second part D2b of the second cooling air flow D2 flows through orifices 54 formed in the downstream flange 13 of the disc downstream 5, to penetrate inside a cavity 56 delimited on the one hand using an upstream face of a downstream labyrinth 58 disposed near the downstream disc 5, and on the other hand using a downstream face of this same downstream disc 5.

Ainsi, le second débit d'air de refroidissement D2b circule sensiblement radialement dans la cavité 56 vers l'extérieur le long de la face aval du labyrinthe aval 58 afin de le refroidir, puis pénètre dans des alvéoles 6a contenant les pieds des aubes 6 afin de refroidir également ces dernières.So the second air flow of D2b cooling circulates substantially radially in the cavity 56 outwards along the face downstream of the downstream labyrinth 58 in order to cool it, then penetrates into cells 6a containing the feet of vanes 6 in order to cool them as well.

Dans ce type de turbine classique de l'art antérieur, le dispositif de ventilation du rotor présente donc deux circuits de refroidissement distincts, chacun associé à l'un des deux disques de turbine, et respectivement alimentés par les premier et second débits d'air de refroidissement D1 et D2.In this type of conventional art turbine front, the rotor ventilation device therefore has two cooling circuits separate, each associated with one of the two discs of turbine, and respectively powered by the first and second cooling air flows D1 and D2.

Néanmoins, cette solution classique de l'art antérieur s'avère contraignante en ce sens que le labyrinthe amont est une pièce de conception extrêmement complexe, de masse importante, et dont le coût de production est grandement élevé, notamment en raison de la nécessité d'utiliser des matériaux spéciaux susceptibles de supporter des sollicitations thermiques de forte intensité. However, this classic solution of the prior art is binding in the sense that the upstream labyrinth is a design piece extremely complex, of large mass, and whose production cost is greatly high, especially in reason for the need to use materials specials likely to withstand stresses high intensity thermal.

En outre, il est précisé que même lorsque les matériaux employés sont de bonne qualité, la durée de vie du labyrinthe amont reste relativement limitée.Furthermore, it is specified that even when the materials used are of good quality, the duration life of the upstream labyrinth remains relatively limited.

EXPOSÉ DE L'INVENTIONSTATEMENT OF THE INVENTION

L'invention a donc pour but de proposer un dispositif de ventilation d'un rotor de turbine à haute pression d'une turbomachine, la turbine étant disposée en aval d'une chambre de combustion et comportant des disques de turbine amont et aval équipés d'aubes, le dispositif comportant un circuit de refroidissement muni d'injecteurs disposés en amont du disque amont et étant alimenté par un débit d'air de refroidissement D prélevé en fond de chambre de combustion, le dispositif remédiant au moins partiellement aux inconvénients mentionnés ci-dessus relatifs aux réalisations de l'art antérieur.The invention therefore aims to provide a ventilation device of a high turbine rotor pressure of a turbomachine, the turbine being arranged downstream of a combustion chamber and comprising upstream and downstream turbine discs fitted with blades, the device comprising a cooling circuit fitted with injectors arranged upstream of the upstream disc and being supplied by a cooling air flow D taken from the bottom of the combustion chamber, the device at least partially remedying the disadvantages mentioned above relating to the achievements of art prior.

Pour ce faire, l'invention a pour objet un dispositif de ventilation d'un rotor de turbine à haute pression d'une turbomachine, la turbine étant disposée en aval d'une chambre de combustion et comportant un disque de turbine amont équipé d'aubes ainsi que d'un disque de turbine aval également équipé d'aubes, le dispositif comportant un circuit de refroidissement muni d'injecteurs disposés en amont du disque amont, le circuit étant alimenté par un débit d'air de refroidissement D prélevé en fond de chambre de combustion. Selon l'invention, le circuit de refroidissement est agencé de manière à ce que le débit d'air de refroidissement D provenant des injecteurs traverse des orifices ménagés dans une bride amont du disque amont autorisant sa fixation sur une bride amont du disque aval, afin que ce débit d'air de refroidissement D circule axialement vers l'aval entre un alésage intérieur du disque amont et une bride amont du disque aval autorisant sa fixation sur une bride aval d'un compresseur haute pression ainsi que le centrage du disque amont, le dispositif de ventilation comportant en outre un labyrinthe unique solidaire de l'un des deux disques de turbine et étant interposé entre ces deux disques, de sorte que le débit d'air de refroidissement D se sépare en un premier flux F1 circulant entre une face aval du disque amont et une face amont du labyrinthe unique en direction des aubes du disque amont, et en un second flux F2 circulant entre une face amont du disque aval et une face aval du labyrinthe unique en direction des aubes du disque aval.To do this, the invention relates to a ventilation device of a high turbine rotor pressure of a turbomachine, the turbine being arranged downstream of a combustion chamber and comprising a upstream turbine disk fitted with blades and a downstream turbine disk also fitted with blades, the device comprising a cooling circuit fitted with injectors arranged upstream of the upstream disc, the circuit being supplied by an air flow of cooling D taken from the bottom of the combustion. According to the invention, the circuit cooling is arranged so that the flow cooling air D from the injectors crosses holes made in an upstream flange of the upstream disc allowing its attachment to an upstream flange of the downstream disc, so that this air flow of cooling D flows axially downstream between an inner bore of the upstream disc and an upstream flange of the downstream disc authorizing its attachment to a flange downstream of a high pressure compressor as well as the centering of the upstream disc, the ventilation device further comprising a single labyrinth integral with one of the two turbine disks and being interposed between these two discs, so that the air flow of cooling D separates into a first flow F1 flowing between a downstream face of the upstream disc and a upstream face of the single labyrinth towards the blades of the upstream disc, and in a second flow F2 circulating between an upstream face of the downstream disc and a downstream face of the single labyrinth towards the disc blades downstream.

Avantageusement et contrairement aux réalisations de l'art antérieur, le dispositif de ventilation ne comporte plus deux labyrinthes respectivement associés aux disques de turbine amont et aval, mais dispose d'un unique labyrinthe inter-disque dont chacune des faces amont et aval est destinée à guider un flux d'air de refroidissement en direction des aubes. La réduction du nombre de pièces utilisées permet par conséquent de réduire considérablement la masse, l'encombrement et le coût de production du rotor. En outre, le positionnement spécifique du labyrinthe unique conduit ce dernier à être moins sollicité thermiquement qu'un labyrinthe agencé en amont du disque amont, principalement en raison de son emplacement par rapport à la chambre de combustion, et dans la mesure où la température du débit d'air de refroidissement D chute sensiblement lors de son passage dans l'alésage intérieur du disque amont. Cette caractéristique engendre ainsi une augmentation de la durée de vie de ce labyrinthe, par rapport à la durée de vie que pouvait présenter un labyrinthe amont de l'art antérieur.Advantageously and unlike achievements of the prior art, the device ventilation no longer has two labyrinths respectively associated with the upstream turbine disks and downstream, but has a unique inter-disc labyrinth each of the upstream and downstream faces of which is intended for guide a flow of cooling air towards blades. Reducing the number of parts used therefore considerably reduces the mass, size and cost of production of the rotor. In addition, the specific positioning of the unique maze leads the latter to be less thermally stressed that a labyrinth arranged in upstream of the upstream disk, mainly due to its location in relation to the combustion chamber, and since the air flow temperature of cooling D drops significantly during passage in the inner bore of the upstream disc. This characteristic thus generates an increase in the lifespan of this labyrinth, compared to the duration of life that an upstream labyrinth could present prior art.

Par ailleurs, il est indiqué que l'injection de l'air de refroidissement à l'amont du disque amont, le contournement de ce disque amont par l'alésage intérieur ainsi que la possibilité de réaliser des éléments constitutifs du rotor de faibles dimensions, permet, par une cavité simple délimitée conjointement par une face aval du disque amont et par une face amont du labyrinthe unique, d'obtenir une pression suffisante au niveau des aubes de ce disque amont.Furthermore, it is stated that the injection of cooling air upstream of the upstream disc, bypassing this upstream disc by the internal bore as well as the possibility of make low rotor components dimensions, allows, by a simple delimited cavity jointly by a downstream face of the upstream disc and by an upstream face of the single labyrinth, to obtain a sufficient pressure at the blades of this disc upstream.

A cette égard, la cavité adjacente délimitée conjointement par une face amont du disque aval et par une face aval du labyrinthe unique est avantageusement utilisée pour diminuer la pression d'alimentation des aubes du disque aval. La faible pression à l'intérieur de cette cavité adjacente permet effectivement de ne pas avoir à prévoir des trous d'alimentation des aubes de dimensions trop petites, qui sont difficilement réalisables.In this regard, the adjacent cavity jointly delimited by an upstream face of the disc downstream and through a downstream face of the single labyrinth is advantageously used to reduce the pressure feeding the blades of the downstream disc. The weak pressure inside this adjacent cavity allows actually not having to provide holes feeding blades that are too small, which are difficult to achieve.

De façon avantageuse, le rotor rendu plus compact par la diminution du nombre d'éléments constitutifs du rotor autorise un rapprochement du palier sous chambre des disques amont et aval, de sorte qu'il est alors possible d'obtenir une meilleure maítrise des jeux en sommet d'aubes, et donc un meilleur rendement de la turbine haute pression.Advantageously, the rotor made more compact by reducing the number of elements components of the rotor allows a reconciliation of the bearing under chamber of the upstream and downstream discs, so that it is then possible to obtain a better control of games at the top of blades, and therefore a higher efficiency of the high pressure turbine.

D'autre part, il est noté que le débit d'air de refroidissement D transitant au niveau de l'alésage intérieur du disque de turbine amont est suffisamment important pour permettre à celui-ci de présenter un temps de réponse relativement faible, et donc de prévoir un jeu en sommet d'aubes peu élevé.On the other hand, it is noted that the flow of cooling air D passing through the inner bore of the upstream turbine disk is large enough to allow it to have a relatively short response time, and therefore to provide a low blade tip clearance.

Enfin, un tel agencement selon l'invention autorise un démontage stator rapide et aisé, dans la mesure où cette tâche ne nécessite qu'un retrait des aubes du disque de turbine aval sans avoir à dissocier les deux disques du rotor, cette dernière opération ayant pourtant toujours été obligatoire avec les réalisations de l'art antérieur.Finally, such an arrangement according to the invention allows quick and easy stator disassembly in the since this task only requires removal of downstream turbine disk vanes without having to dissociate the two rotor discs, this last operation having always been compulsory with achievements of the prior art.

D'autres avantages et caractéristiques de l'invention apparaítront dans la description détaillée non limitative ci-dessous.Other advantages and characteristics of the invention will appear in the detailed description nonlimiting below.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

Cette description sera faite au regard des dessins annexés parmi lesquels ;

  • la figure 1, déjà décrite, représente en demi-coupe une turbine à haute pression d'un turboréacteur selon l'art antérieur, et
  • la figure 2 représente en demi-coupe une turbine à haute pression d'un turboréacteur, comportant un dispositif de ventilation selon un mode de réalisation préféré de la présente invention.
This description will be made with reference to the accompanying drawings, among which;
  • FIG. 1, already described, shows in half-section a high pressure turbine of a turbojet engine according to the prior art, and
  • 2 shows in half-section a high pressure turbine of a turbojet engine, comprising a ventilation device according to a preferred embodiment of the present invention.

EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PRÉFÉRÉSDETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

En référence à la figure 2, il est représenté une turbine 100 à haute pression d'un turboréacteur, comportant un dispositif de ventilation du rotor de la turbine selon un mode de réalisation préféré de la présente invention. Notons que sur la figure 2, les éléments portant les mêmes références numériques que celles attachées aux éléments représentés sur la figure 1 correspondent à des éléments identiques ou similaires.Referring to Figure 2, it is depicted a high pressure turbine 100 of a turbojet engine, comprising a ventilation device of the turbine rotor according to one embodiment preferred of the present invention. Note that on the Figure 2, the elements bearing the same references digital than those attached to the elements shown in Figure 1 correspond to identical or similar elements.

Ainsi, la figure 2 montre une turbine 100 qui se différencie tout d'abord de la turbine 1 de l'art antérieur par le fait qu'un débit d'air de refroidissement D, prélevé en fond de chambre de combustion 2 et apte à traverser les injecteurs 36, est destiné à alimenter simultanément les aubes 4 et 6 des disques amont 3 et aval 5.Thus, Figure 2 shows a turbine 100 which differs first of all from turbine 1 of prior art by the fact that an air flow of cooling D, taken from the bottom of the combustion 2 and able to pass through the injectors 36, is intended to simultaneously feed the blades 4 and 6 of upstream 3 and downstream 5 discs.

En effet, l'air de refroidissement provenant de la chambre de combustion 2 transite par le conduit 28 afin de rejoindre les injecteurs 36, cet ensemble constitué du conduit 28 et des injecteurs 36 étant situé dans une enceinte 62 séparant le disque amont 3 du fond de la chambre de combustion 2.Indeed the cooling air coming from combustion chamber 2 passes through the conduit 28 in order to join the injectors 36, this assembly consisting of conduit 28 and injectors 36 being located in an enclosure 62 separating the disc upstream 3 from the bottom of the combustion chamber 2.

Le débit d'air de refroidissement D provenant des injecteurs 36 pénètre alors dans une cavité 64 partiellement délimitée par une bride amont 66 du disque de turbine amont 3, cette bride amont 66 ayant pour principale fonction d'assurer la fixation de ce disque amont 3 sur une bride amont 78 du disque aval 5. D'autre part, cette cavité 64 est également délimitée conjointement par le joint amont 32 et le joint aval 34, de préférence du type joint à labyrinthe, agencés à proximité des injecteurs 36 respectivement en amont et en aval de ce dernier. A ce titre, il est précisé que le joint amont 32 coopère avec une bride aval 70 de la turbine haute pression, cette bride aval 70 étant ménagée de manière à se situer radialement vers l'extérieur par rapport à la bride amont 66. De plus, le joint amont 32 ferme la cavité 64 en épousant l'extrémité amont de la bride amont 66. En outre, le joint aval 34 coopère avec une bride amont secondaire 72 du disque de turbine amont 3, ménagée de manière à se situer radialement vers l'extérieur par rapport à la bride amont 66. Ainsi, l'air de refroidissement s'échappant de la cavité 64 par le joint aval 34 peut circuler radialement vers l'extérieur, le long de la face amont du disque amont 3, en direction des aubes 4.The cooling air flow D from the injectors 36 then enters a cavity 64 partially delimited by an upstream flange 66 of the upstream turbine disk 3, this upstream flange 66 main function of which is to secure the this upstream disc 3 on an upstream flange 78 of the downstream disc 5. On the other hand, this cavity 64 is also jointly delimited by the upstream joint 32 and the downstream joint 34, preferably of the joint type labyrinth, arranged near the injectors 36 respectively upstream and downstream of the latter. At this title, it is specified that the upstream seal 32 cooperates with a downstream flange 70 of the high pressure turbine, this downstream flange 70 being formed so as to be locate radially outward relative to the upstream flange 66. In addition, the upstream seal 32 closes the cavity 64 by matching the upstream end of the flange upstream 66. In addition, the downstream seal 34 cooperates with a secondary upstream flange 72 of the upstream turbine disk 3, arranged so as to lie radially towards the exterior with respect to the upstream flange 66. Thus, the cooling air escaping from the cavity 64 by the downstream seal 34 can flow radially towards outside, along the upstream face of the upstream disc 3, towards the blades 4.

Des orifices 74 sont prévus dans la bride amont 66 du disque de turbine amont 3, afin que le débit d'air de refroidissement D puisse être acheminé en direction des deux disques de turbine 3 et 5. Les orifices 74 sont de préférence agencés de manière à se situer radialement en regard des injecteurs 36.Ports 74 are provided in the flange upstream 66 of the upstream turbine disk 3, so that the cooling air flow D can be routed towards the two turbine disks 3 and 5. The orifices 74 are preferably arranged so as to be locate radially opposite the injectors 36.

Une fois les orifices 74 traversés, le débit d'air de refroidissement D pénètre dans une chambre annulaire 76 d'axe 40, délimitée extérieurement par l'intermédiaire de la bride amont 66 du disque amont 3, et à l'aide de l'alésage intérieur 48 de ce même disque. En outre, la chambre annulaire 76 est délimitée intérieurement par la bride amont 78 du disque aval 5, cette bride amont 78 ayant pour principale fonction d'assurer la fixation de ce disque aval 5 sur la bride amont 66 du disque amont 3, et de centrer l'ensemble de la turbine haute pression 100 sur une bride aval 79 d'un compresseur haute pression.Once the orifices 74 have been crossed, the cooling air flow D enters a annular chamber 76 of axis 40, delimited externally via the upstream flange 66 of the disc upstream 3, and using the internal bore 48 of this same disc. In addition, the annular chamber 76 is internally bounded by the upstream flange 78 of the downstream disc 5, this upstream flange 78 having for main function of securing this disc downstream 5 on the upstream flange 66 of the upstream disc 3, and center the entire high pressure turbine 100 on a downstream flange 79 of a high pressure compressor.

Le débit d'air de refroidissement D peut alors circuler axialement vers l'aval entre l'alésage intérieur 48 et la bride amont 78, de sorte que le disque de turbine amont 3 peut être convenablement refroidi par contact de l'air de refroidissement avec son alésage intérieur 48.The cooling air flow D can then flow axially downstream between the bore interior 48 and the upstream flange 78, so that the upstream turbine disc 3 can be suitably cooled by contact of cooling air with its internal bore 48.

Comme on peut le voir sur la figure 2, le dispositif de ventilation selon l'invention comporte un labyrinthe unique 80 interposé entre les disques de turbine 3 et 5, et est solidaire de l'un de ces deux disques. A titre d'exemple non limitatif, le labyrinthe unique 80, également appelé labyrinthe inter-disque, est fixé à une bride amont secondaire 82 du disque de turbine aval 5, celle-ci étant agencée de manière à se situer radialement vers l'extérieur par rapport à la bride amont 78. De plus, le labyrinthe 80 s'étend radialement jusqu'à épouser l'étage distributeur fixe 18 ou stator prévu entre les deux étages rotoriques 20 et 22, et dispose d'un alésage intérieur 83 entourant la bride amont 78 du disque 5, cet alésage 83 présentant de préférence un diamètre sensiblement identique au diamètre de l'alésage intérieur 48 du disque 3.As can be seen in Figure 2, the ventilation device according to the invention comprises a single labyrinth 80 interposed between the discs of turbine 3 and 5, and is integral with one of these two discs. By way of nonlimiting example, the labyrinth single 80, also called inter-disc labyrinth, is attached to a secondary upstream flange 82 of the disc downstream turbine 5, the latter being arranged so as to be locate radially outward relative to the upstream flange 78. In addition, the labyrinth 80 extends radially up to the fixed distributor stage 18 or stator provided between the two rotor stages 20 and 22, and has an inner bore 83 surrounding the upstream flange 78 of the disc 5, this bore 83 preferably having a diameter substantially identical to the diameter of the inner bore 48 of the disc 3.

Par conséquent, le débit d'air de refroidissement D transitant dans la chambre annulaire 76 et arrivant au niveau de la face aval du disque amont 3, se sépare en deux flux F1 et F2, respectivement destinés à alimenter les aubes 4 et les aubes 6 des disques 3 et 5.Therefore, the air flow of cooling D passing through the annular chamber 76 and arriving at the level of the downstream face of the disc upstream 3, separates into two flows F1 and F2, respectively intended to supply the blades 4 and the blades 6 of discs 3 and 5.

Le premier flux F1 circule donc dans une cavité 68 située entre la face aval du disque de turbine amont 3 et la face amont du labyrinthe 80 afin de refroidir la face aval du disque 3, puis pénètre dans des alvéoles 4a contenant les pieds des aubes 4 afin de refroidir également ces dernières.The first F1 flow therefore flows in a cavity 68 located between the downstream face of the disc upstream turbine 3 and the upstream face of labyrinth 80 so to cool the downstream face of the disc 3, then penetrate in cells 4a containing the feet of the blades 4 in order to cool them too.

De la même façon, le second flux F2 circule dans une cavité 69 située entre la face amont du disque de turbine aval 5 et la face aval du même labyrinthe 80 afin de refroidir la face amont du disque 5, puis pénètre dans des alvéoles 6a contenant les pieds des aubes 6 afin de refroidir également ces dernières. Notons que pour que le second flux F2 atteigne les aubes 6 du disque de turbine aval 5, une pluralité d'orifices 84 est pratiquée dans la bride amont secondaire 82 du disque aval 5.Similarly, the second flow F2 flows in a cavity 69 located between the upstream face of the disc downstream turbine 5 and the downstream face of the same labyrinth 80 in order to cool the upstream face of the disc 5, then penetrates into cells 6a containing the feet of vanes 6 in order to cool them as well. Note that for the second flow F2 to reach the blades 6 of the downstream turbine disk 5, a plurality 84 is made in the upstream flange secondary 82 of the downstream disc 5.

Par conséquent, le dispositif de ventilation selon l'invention est tel que le débit d'air de refroidissement D prélevé en fond de chambre de combustion 2 et destiné à alimenter simultanément les aubes 4 et 6, emprunte un circuit de refroidissement unique jusqu'à la sortie du passage entre l'alésage 48 du disque amont 3 et la bride amont 78 du disque de turbine aval 5. Cette caractéristique spécifique simplifie considérablement la conception de la turbine 100 par rapport à celle de la turbine 1 de l'art antérieur, dans laquelle deux débits d'air de refroidissement étaient prélevés en fond de chambre de combustion 2, afin d'emprunter deux circuits de refroidissement totalement séparés.Therefore, the ventilation according to the invention is such that the flow cooling air D taken from the chamber bottom 2 and intended to supply simultaneously blades 4 and 6, follows a circuit of one-time cooling to exit the passage between the bore 48 of the upstream disc 3 and the upstream flange 78 of the downstream turbine disk 5. This characteristic specific greatly simplifies the design of turbine 100 relative to that of turbine 1 of the prior art, in which two air flows of cooling were taken from the bottom of the combustion 2, in order to borrow two circuits of totally separate cooling.

D'autre part, la bride amont 78 du disque de turbine aval 5 comporte une pluralité d'orifices 86 aptes à être traversés par un troisième flux F3 du débit d'air de refroidissement D. Ce troisième flux F3 est donc acheminé de la chambre annulaire 76 vers un espace annulaire 88 de même axe, l'espace 88 étant situé entre d'une part la bride amont 78 du disque aval 5 et l'alésage intérieur 50 de ce même disque aval 5, et d'autre part l'entretoise 9 disposée autour de l'arbre 11 de rotor de la turbine basse pression. Ainsi, le flux d'air de refroidissement F3 peut circuler axialement vers l'aval dans l'espace annulaire 88, afin de refroidir le disque aval 5 par contact de l'air avec son alésage intérieur 50. Le troisième flux F3 est ensuite évacué en aval de la turbine 100 par les orifices 54 ménagés sur la bride aval 13 du disque de turbine aval 5, cette bride aval 13 participant également à la délimitation extérieure de l'espace annulaire 88 et étant assemblée sur l'entretoise 9 d'axe 40.On the other hand, the upstream flange 78 of the disc downstream turbine 5 has a plurality of orifices 86 capable of being crossed by a third flow F3 of the cooling air flow D. This third flow F3 is therefore routed from the annular chamber 76 to a annular space 88 of the same axis, space 88 being located on the one hand between the upstream flange 78 of the downstream disc 5 and the internal bore 50 of this same downstream disc 5, and on the other hand the spacer 9 arranged around the rotor shaft 11 of the low pressure turbine. Thus, the flow of cooling air F3 can flow axially downstream in the annular space 88, in order to cool the downstream disc 5 by contact of the air with its internal bore 50. The third flow F3 is then evacuated downstream of the turbine 100 by the orifices 54 formed on the downstream flange 13 of the disc downstream turbine 5, this downstream flange 13 participating also to the outer delimitation of space annular 88 and being assembled on the spacer 9 axis 40.

Bien entendu, diverses modifications peuvent être apportées par l'homme du métier à la turbine 100 et à son dispositif de ventilation qui viennent d'être décrits, uniquement à titre d'exemples non limitatifs.Of course, various modifications can be made by those skilled in the art to the turbine 100 and its ventilation device which have just been described, only as examples not limiting.

Claims (4)

Dispositif de ventilation d'un rotor de turbine (100) à haute pression d'une turbomachine, la turbine (100) étant disposée en aval d'une chambre de combustion (2) et comportant un disque de turbine amont (3) équipé d'aubes (4) ainsi que d'un disque de turbine aval (5) équipé d'aubes (6), ledit dispositif comportant un circuit de refroidissement muni d'injecteurs (36) disposés en amont du disque amont (3) et étant alimenté par un débit d'air de refroidissement D prélevé en fond de chambre de combustion (2), caractérisé en ce que ledit circuit de refroidissement est agencé de manière à ce que le débit d'air de refroidissement D provenant des injecteurs (36) traverse des orifices (74) ménagés dans une bride amont (66) du disque amont (3) autorisant sa fixation sur une bride amont (78) du disque aval (5), afin que ce débit d'air de refroidissement D circule axialement vers l'aval entre un alésage intérieur (48) du disque amont (3) et la bride amont (78) du disque aval (5) autorisant sa fixation sur une bride aval (79) d'un compresseur haute pression ainsi que le centrage du disque amont (3), ledit dispositif de ventilation comportant en outre un labyrinthe unique (80) solidaire de l'un des deux disques de turbine (3,5) et étant interposé entre ces deux disques, de sorte que le débit d'air de refroidissement D se sépare en un premier flux F1 circulant entre une face aval du disque amont (3) et une face amont du labyrinthe unique (80) en direction des aubes (4), et en un second flux F2 circulant entre une face amont du disque aval (5) et une face aval du labyrinthe unique (80) en direction des aubes (6).Device for ventilating a turbine rotor (100) at high pressure of a turbomachine, the turbine (100) being arranged downstream of a combustion chamber (2) and comprising an upstream turbine disc (3) equipped with 'blades (4) as well as a downstream turbine disk (5) equipped with blades (6), said device comprising a cooling circuit provided with injectors (36) arranged upstream of the upstream disk (3) and being supplied with a cooling air flow D taken from the bottom of the combustion chamber (2), characterized in that said cooling circuit is arranged so that the cooling air flow D coming from the injectors (36) passes through orifices (74) formed in an upstream flange (66) of the upstream disc (3) authorizing its attachment to an upstream flange (78) of the downstream disc (5), so that this flow of cooling air D circulates axially towards the downstream between an internal bore (48) of the upstream disc (3) and the upstream flange (78) of the front disc al (5) authorizing its attachment to a downstream flange (79) of a high pressure compressor as well as the centering of the upstream disc (3), said ventilation device further comprising a single labyrinth (80) integral with one of the two turbine discs (3,5) and being interposed between these two discs, so that the cooling air flow D separates into a first flow F1 circulating between a downstream face of the upstream disc (3) and an upstream face of the single labyrinth (80) in the direction of the blades (4), and in a second flow F2 flowing between an upstream face of the downstream disc (5) and a downstream face of the single labyrinth (80) in the direction of the blades (6). Dispositif selon la revendication 1,
caractérisé en ce que les injecteurs (36) débouchent dans une cavité (64) partiellement délimitée par la bride amont (66) du disque de turbine amont (3), ainsi que par un joint amont (32) et un joint aval (34), ce dernier coopérant avec une bride amont secondaire (72) du disque de turbine amont (3).Device according to claim 1,
characterized in that the injectors (36) open into a cavity (64) partially delimited by the upstream flange (66) of the upstream turbine disc (3), as well as by an upstream seal (32) and a downstream seal (34) , the latter cooperating with a secondary upstream flange (72) of the upstream turbine disc (3). Dispositif selon la revendication 1 ou la revendication 2, caractérisé en ce que la bride amont (78) du disque de turbine aval (5) dispose d'une pluralité d'orifices (86) aptes à être traversés par un troisième flux F3 du débit d'air de refroidissement D, ledit troisième flux F3 étant susceptible de circuler axialement vers l'aval dans un espace annulaire (88) situé entre d'une part la bride amont (78) du disque aval (5) et un alésage intérieur (50) de ce disque aval (5), et d'autre part une entretoise (9) disposée autour d'un arbre (11) de rotor d'une turbine basse pression.Device according to claim 1 or claim 2, characterized in that the upstream flange (78) of the downstream turbine disk (5) has a plurality of orifices (86) capable of being traversed by a third flow F3 of the flow of cooling air D, said third flow F3 being capable of circulating axially downstream in an annular space (88) situated on the one hand between the upstream flange (78) of the downstream disc (5) and an internal bore ( 50) of this downstream disc (5), and on the other hand a spacer (9) disposed around a shaft (11) of the rotor of a low pressure turbine. Dispositif selon l'une quelconque des revendications précédentes, caractérisé en ce que le labyrinthe unique (80) est solidaire d'une bride amont secondaire (82) du disque de turbine aval (5), dans laquelle est pratiquée une pluralité d'orifices (84) autorisant la circulation du second flux F2 du débit d'air de refroidissement D, en direction des aubes (6).Device according to any one of the preceding claims, characterized in that the single labyrinth (80) is integral with a secondary upstream flange (82) of the downstream turbine disc (5), in which is formed a plurality of orifices ( 84) authorizing the circulation of the second flow F2 of the cooling air flow D, in the direction of the blades (6).
EP04100404A 2003-02-06 2004-02-04 Apparatus for the ventilation of a high pressure turbine rotor Expired - Lifetime EP1445421B1 (en)

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FR0301391 2003-02-06
FR0301391A FR2851010B1 (en) 2003-02-06 2003-02-06 DEVICE FOR VENTILATION OF A HIGH PRESSURE TURBINE ROTOR OF A TURBOMACHINE

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CA (1) CA2456589C (en)
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FR2960260A1 (en) * 2010-05-21 2011-11-25 Snecma Turbomachine i.e. twin-spool turbine engine, for use in civil aircraft, has supply unit with annular air circulation cavity that traverses high pressure turbine from downstream till upstream radially towards interior with respect to space
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US9920652B2 (en) 2015-02-09 2018-03-20 United Technologies Corporation Gas turbine engine having section with thermally isolated area
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EP3196408A1 (en) * 2015-02-05 2017-07-26 United Technologies Corporation Gas turbine engine having section with thermally isolated area
US9920652B2 (en) 2015-02-09 2018-03-20 United Technologies Corporation Gas turbine engine having section with thermally isolated area
EP3808937A1 (en) * 2019-10-18 2021-04-21 Pratt & Whitney Canada Corp. Tangential on-board injector (tobi) assembly
US11421597B2 (en) 2019-10-18 2022-08-23 Pratt & Whitney Canada Corp. Tangential on-board injector (TOBI) assembly
US11815020B2 (en) 2019-10-18 2023-11-14 Pratt & Whitney Canada Corp. Tangential on-board injector (TOBI) assembly

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FR2851010A1 (en) 2004-08-13
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RU2330976C2 (en) 2008-08-10
ES2255697T3 (en) 2006-07-01
FR2851010B1 (en) 2005-04-15
US6916151B2 (en) 2005-07-12
CA2456589A1 (en) 2004-08-06
JP2004239260A (en) 2004-08-26
EP1445421B1 (en) 2006-01-04
JP4060279B2 (en) 2008-03-12
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RU2004103479A (en) 2005-07-10
DE602004000301D1 (en) 2006-03-30

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